Q400_mtm_vol3b_epub.pdf
This document was uploaded by user and they confirmed that they have the permission to share it. If you are author or own the copyright of this book, please report to us by using this DMCA report form. Report DMCA
Overview
Download & View Q400_mtm_vol3b_epub.pdf as PDF for free.
More details
- Words: 84,248
- Pages: 487
Loading documents preview...
DASH 8 Q400 MAINTENANCE TRAINING MANUAL VOLUME 3B ATA 32, 27 REVISION 0.4 FlightSafety International, Inc. Marine Air Terminal, LaGuardia Airport Flushing, New York 11371 (718) 565-4100 www.FlightSafety.com
FOR TRAINING PURPOSES ONLY
NOTICE The material contained in this training manual is based on information obtained from the aircraft manufacturer’s Maintenance Manuals and Pilot Manuals. It is to be used for familiarization and training purposes only. At the time of printing it contained then-current information. In the event of conflict between data provided herein and that in publications issued by the manufacturer or the FAA, that of the manufacturer or the FAA shall take precedence. We at FlightSafety want you to have the best training possible. We welcome any suggestions you might have for improving this manual or any other aspect of our training program.
FOR TRAINING PURPOSES ONLY NOTICE These commodities, t echnology o r softwar e were exported from t he U nited States i n acco rdance w ith t he Expor t Administration Regulations. Diversion contrary to U.S. law is prohibited.
Courses for the Dash 8 Series and other deHavilland aircraft are taught at the following FlightSafety International learning centers:
FlightSafety International Toronto Learning Center 95 Garratt Boulevard Downsview, Ontario M3K 2A5
For course information please contact us:
1-416-638-9313 1-877-FLY-DASH [email protected] www.flightsafety.com
Copyright © 2015 FlightSafety International, Inc. Unauthorized reproduction or distribution is prohibited. All rights reserved.
INSERT LATEST REVISED PAGES, DESTROY SUPERSEDED PAGES LIST OF EFFECTIVE PAGES Dates of issue for original and changed pages are: Second Edition..... 0.............. August 2013 Revision............... 0.1............... April 2014 Revision............... 0.2........... August 2014
Revision............... 0.3............... April 2015 Revision............... 0.4......... October 2015
THIS PUBLICATION CONSISTS OF THE FOLLOWING: Page *Revision No. No.
Page *Revision No. No.
32-i - xi.................................................... 0.4 32-xii - 32-6............................................. 0.3 32-7......................................................... 0.4 32-8 - 32-22............................................ 0.3 32-23....................................................... 0.4 32-24 - 32-42.......................................... 0.3 32-43....................................................... 0.4 32-44 - 32-60.......................................... 0.3 32-61....................................................... 0.4 32-62 - 32-78.......................................... 0.3 32-79....................................................... 0.4 32-80 - 32-86.......................................... 0.3 32-87....................................................... 0.4 32-88 - 32-100........................................ 0.3 32-101..................................................... 0.4 32-102..................................................... 0.3 32-103..................................................... 0.4 32-104..................................................... 0.3 32-105..................................................... 0.4 32-106 - 32-108...................................... 0.3 32-109..................................................... 0.4 32-110..................................................... 0.3 32-111 - 32-112...................................... 0.4 32-113 - 32-120...................................... 0.3 32-121..................................................... 0.4 32-122..................................................... 0.3 32-123..................................................... 0.4 32-124..................................................... 0.3
32-125..................................................... 0.4 32-126 - 32-138...................................... 0.3 32-139..................................................... 0.4 32-140 - 32-142...................................... 0.3 32-143..................................................... 0.4 32-144 - 32-148...................................... 0.3 32-149..................................................... 0.4 32-150..................................................... 0.3 32-151..................................................... 0.4 32-152 - 32-154...................................... 0.3 32-155..................................................... 0.4 32-156 - 32-161...................................... 0.3 32-162 - 32-163..................................... 0.4 32-164 - 32-166...................................... 0.3 32-167..................................................... 0.4 32-168 - 32-169...................................... 0.3 32-170..................................................... 0.4 32-171 - 32-175...................................... 0.3 32-176 - 32-177...................................... 0.4 32-178 - 32-179...................................... 0.3 32-180..................................................... 0.4 32-181 - 32-182...................................... 0.3 32-183 - 32-185...................................... 0.4 32-186 - 32-187...................................... 0.3 32-188 - 190............................................ 0.4 27-i - 27-xii.............................................. 0.4 27-xiii - 27-6............................................ 0.3 27-7......................................................... 0.4
Page *Revision No. No.
Page *Revision No. No.
27-8......................................................... 0.3 27-9......................................................... 0.4 27-10....................................................... 0.3 27-11....................................................... 0.4 27-12 - 27-14.......................................... 0.3 27-15....................................................... 0.4 27-16 - 27-18.......................................... 0.3 27-19....................................................... 0.4 27-20 - 27-22.......................................... 0.3 27-23....................................................... 0.4 27-24 - 27-26.......................................... 0.3 27-27....................................................... 0.4 27-28 - 27-44.......................................... 0.3 27-45....................................................... 0.4 27-46 - 27-50.......................................... 0.3 27-51....................................................... 0.4 27-52 - 27-56.......................................... 0.3 27-57....................................................... 0.4 27-58....................................................... 0.3 27-59....................................................... 0.4 27-60....................................................... 0.3 27-61....................................................... 0.4 27-62 - 27-66.......................................... 0.3 27-67....................................................... 0.4 27-68 - 27-70.......................................... 0.3 27-71....................................................... 0.4 27-72 - 27-74.......................................... 0.3 27-75....................................................... 0.4 27-76 - 27-82.......................................... 0.3 27-83....................................................... 0.4 27-84 - 27-88.......................................... 0.3 27-89....................................................... 0.4 27-90....................................................... 0.3 27-91....................................................... 0.4 27-92 - 27-94.......................................... 0.3 27-95....................................................... 0.4 27-96 - 27-102........................................ 0.3 27-103..................................................... 0.4 27-104 - 27-106...................................... 0.3 27-107..................................................... 0.4
27-108..................................................... 0.4 27-109 - 27-112...................................... 0.3 27-113..................................................... 0.4 27-114 - 27-120...................................... 0.3 27-121 - 27-122...................................... 0.4 27-123 - 27-126...................................... 0.3 27-127..................................................... 0.4 27-128 - 27-144...................................... 0.3 27-145..................................................... 0.4 27-146..................................................... 0.3 27-147..................................................... 0.4 27-148 - 27-152...................................... 0.3 27-153..................................................... 0.4 27-154 - 27-164...................................... 0.3 27-165..................................................... 0.4 27-166 - 27-168...................................... 0.3 27-169..................................................... 0.4 27-170 - 27-172...................................... 0.3 27-173..................................................... 0.4 27-174..................................................... 0.3 27-175..................................................... 0.4 27-176 - 27-184...................................... 0.3 27-185..................................................... 0.4 27-186 - 27-190...................................... 0.3 27-191 - 27-192...................................... 0.4 27-193 - 27-200...................................... 0.3 27-201..................................................... 0.4 27-202..................................................... 0.3 27-203 - 27-204...................................... 0.4 27-205 - 27-211...................................... 0.3 27-212..................................................... 0.4 27-213 - 27-224...................................... 0.3 27-225 - 22-227...................................... 0.4 27-228..................................................... 0.3 27-229..................................................... 0.4 27-230 - 27-244...................................... 0.3 27-245..................................................... 0.4 27-246 - 27-251...................................... 0.3 27-252 - 27-253...................................... 0.4
CONTENTS VOLUME 3B Chapter Title LANDING GEAR FLIGHT CONTROLS
ATA Number 32 27
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
CHAPTER 32 LANDING GEAR CONTENTS
Page
32-00-00 INTRODUCTION........................................................................................ 32-1 General................................................................................................................ 32-1 32-11-00 MAIN LANDING GEAR............................................................................. 32-5 General ............................................................................................................... 32-5 System Description.............................................................................................. 32-5 Component Description........................................................................................ 32-6 Shock Strut................................................................................................... 32-6 Installation of the MLG Electrical Harness................................................... 32-7 Axles............................................................................................................. 32-8 Shock Strut Torque Links.............................................................................. 32-9 Drag Strut .................................................................................................. 32-10 Stabilizer Brace........................................................................................... 32-11 Yoke............................................................................................................ 32-12 Shock Strut Fairings.................................................................................... 32-12 32-12-00 MAIN LANDING GEAR DOORS............................................................. 32-14 Introduction....................................................................................................... 32-14 General.............................................................................................................. 32-14 System Description............................................................................................ 32-15 Component Description...................................................................................... 32-16
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-i
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page Aft MLG Doors........................................................................................... 32-16 Aft MLG Doors Connecting Rods............................................................... 32-16 Aft Door Mechanism................................................................................... 32-17 Forward MLG Doors................................................................................... 32-18 32-12-00 DVI MAIN LANDING GEAR DOOR MECHANISMS............................. 32-19 Controls and Indications.................................................................................... 32-21 Open and Lock the Landing Gear Doors..................................................... 32-23 Installation of the Main Landing Gear Lock Pins........................................ 32-23 32-20-00 NOSE LANDING GEAR AND DOORS.................................................... 32-27 Introduction....................................................................................................... 32-27 General.............................................................................................................. 32-28 Component Description...................................................................................... 32-31 Nose Landing Gear Shock Strut.................................................................. 32-31 Nose Landing Gear Trailing Arm................................................................ 32-32 NLG Drag Strut.......................................................................................... 32-32 NLG Electrical Harness.............................................................................. 32-34 32-22-00 NOSE LANDING GEAR DOORS............................................................. 32-35 Introduction....................................................................................................... 32-35 General.............................................................................................................. 32-35 System Description............................................................................................ 32-35 Component Description...................................................................................... 32-37 Aft NLG Doors........................................................................................... 32-37
32-ii
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Page Aft NLG Doors Connecting Rods................................................................ 32-37 NLG Forward Doors ................................................................................... 32-39 NLG Forward Doors Connecting Rods........................................................ 32-39 32-22-00 DVI NOSE LANDING GEAR DOOR MECHANISMS.............................. 32-39 Controls and Indications.................................................................................... 32-41 32-25-00 NOSE LANDING GEAR GROUND LOCK............................................... 32-42 Introduction....................................................................................................... 32-42 General ............................................................................................................. 32-42 System Description ........................................................................................... 32-42 Component Description...................................................................................... 32-43 Nose Gear Ground-Lock Position Indication System (Optional).................. 32-43 32-30-00 LANDING GEAR EXTENSION AND RETRACTION.............................. 32-45 Introduction....................................................................................................... 32-45 General.............................................................................................................. 32-45 System Description............................................................................................ 32-45 32-31-00 PRIMARY EXTENSION AND RETRACTION.......................................... 32-45 Introduction....................................................................................................... 32-45 General.............................................................................................................. 32-45 Component Description...................................................................................... 32-46 Landing Gear Selector Valve....................................................................... 32-46 MLG Retraction Actuator............................................................................ 32-47 MLG Downlock Actuator............................................................................ 32-48
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-iii
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page MLG Uplock Assembly............................................................................... 32-49 Mechanical Sequence Valve........................................................................ 32-50 Inline Restrictors......................................................................................... 32-50 MLG Solenoid Sequence Valve .................................................................. 32-51 NLG Solenoid Sequence Valve.................................................................... 32-51 NLG Retraction Actuator ........................................................................... 32-52 NLG Lock Actuator..................................................................................... 32-53 NLG Inline Restrictors................................................................................ 32-53 Controls and Indications.................................................................................... 32-55 Fault Isolation............................................................................................. 32-55 Maintenance Practices........................................................................................ 32-56 32-31-00 PRIMARY EXTENSION AND RETRACTION.......................................... 32-59 Operation........................................................................................................... 32-59 Normal System Operation........................................................................... 32-59 MLG Retraction Sequence.......................................................................... 32-59 NLG Retraction Sequence........................................................................... 32-61 Landing Gear Retraction............................................................................. 32-63 Nose Landing Gear Extension..................................................................... 32-69 Landing Gear Normal Extension................................................................. 32-71 32-34-00 ALTERNATE EXTENSION SYSTEM....................................................... 32-75 Introduction....................................................................................................... 32-75 General ............................................................................................................. 32-75
32-iv
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Page System Description ........................................................................................... 32-77 Servicing of the Alternate Landing-Gear Extension Hydraulic Reservoir.................................................................... 32-79 Component Description...................................................................................... 32-80 Main Gear Alternate Release Handle........................................................... 32-80 Nose Gear Alternate Release Handle........................................................... 32-81 Alternate Extension Actuator...................................................................... 32-82 Alternate Extension Downlock Indicators and Switch................................. 32-83 Bypass Valve............................................................................................... 32-85 MLG Alternate Release Control Cables....................................................... 32-87 Operational Check of the Main Landing Gear Alternate Extension Cam Assembly (MRB#323400-204)............................ 32-87 NLG Alternate Release Control Cables....................................................... 32-88 Landing Gear Inhibit Switch....................................................................... 32-89 29-21-01 HYDRAULIC HAND PUMP..................................................................... 32-91 29-21-03 HAND-PUMP LEVER............................................................................... 32-91 29-21-06 SECONDARY MLG SELECTOR VALVE.................................................. 32-93 Operation........................................................................................................... 32-97 Alternate Extension..................................................................................... 32-97 32-41-00 WHEELS................................................................................................... 32-99 General.............................................................................................................. 32-99 System Description............................................................................................ 32-99 Components Description.................................................................................... 32-99
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-v
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page Main Wheels............................................................................................... 32-99 Installation of the Main Wheel and Tire Assembly....................................32-101 MLG Axle Bullet......................................................................................32-101 Nosewheels...............................................................................................32-103 Installation of the Nosewheel and Tire Assembly.......................................32-103 Fill Valve Gauge (Optional).......................................................................32-105 Tire Wear..................................................................................................32-105 32-42-00 MAIN LANDING GEAR BRAKE SYSTEM...........................................32-107 Introduction.....................................................................................................32-107 General............................................................................................................32-107 System Description .........................................................................................32-107 Component Description....................................................................................32-109 Main Wheel Brake Units...........................................................................32-109 Installation of the Main Wheel Brake Units...............................................32-109 Bleed the Brakes with Main Brake System................................................32-111 Brake Bleeding Kit....................................................................................32-112 Brake Control Valve..................................................................................32-113 Fuse/Shuttle Valves...................................................................................32-114 Brake Pedals.............................................................................................32-115 Brake Control Cables................................................................................32-116 Brake Pressure Transducers.......................................................................32-117 32-44-00 PARKING BRAKE SYSTEM..................................................................32-119
32-vi
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Page Introduction.....................................................................................................32-119 General............................................................................................................32-119 System Description..........................................................................................32-119 Component Description....................................................................................32-121 Parking Brake Control Valve.....................................................................32-121 Parking Brake Hand pump.........................................................................32-121 Post SB 84-32-99 Reposition of the Parking Brake Hand Pump Lever to the Nose Compartment...................................32-122 Charge Valve and Gauge...........................................................................32-125 Servicing of the Parking Brake Accumulator with Nitrogen......................32-125 Functional Check of Park Brake Accumulator Pre-Charge Pressure..........32-125 Parking Brake Control Quadrant...............................................................32-126 Parking Brake Control Cable.....................................................................32-127 Controls and Indications .................................................................................32-129 Interfaces..................................................................................................32-129 32-46-00 ANTI-SKID SYSTEM.............................................................................32-133 Introduction.....................................................................................................32-133 General............................................................................................................32-133 System Description .........................................................................................32-133 Components Description..................................................................................32-135 Anti-Skid Control Unit..............................................................................32-135 Skid Control Valves...................................................................................32-136 Wheel Speed Transducer...........................................................................32-137
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-vii
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page Installation of the Wheel-Speed Transducer Electrical Harness.................32-139 Anti-Skid Switch..............................................................................................32-140 Controls and Indications .................................................................................32-141 Functional Test of the Anti-Skid Control System (Built-in Test)................32-143 Touchdown Protection Test........................................................................32-143 Wheel Speed Transducer Test....................................................................32-143 ANTI-SKID SYSTEM............................................................................................32-145 Operation.........................................................................................................32-145 Anti-Skid Operation..................................................................................32-145 Initialization..............................................................................................32-145 Individual Wheel.......................................................................................32-145 Locked Wheel...........................................................................................32-145 Interfaces..................................................................................................32-146 MAINTENANCE PRACTICES IMPORTANT TO THE MLG BRAKING SYSTEM.......................................................................32-149 Fault Isolation..................................................................................................32-149 INBD ANTISKID and OUTBD ANTISKID (Caution lights).....................32-149 PARKING BRAKE, indication discrepancy (Caution Light).....................32-151 32-51-00 NOSEWHEEL STEERING SYSTEM......................................................32-153 Introduction.....................................................................................................32-153 General............................................................................................................32-153 System Description..........................................................................................32-153 Nosewheel Steering Hand Control.............................................................32-153 32-viii
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Page Rudder Pedal Control................................................................................32-153 Shimmy Damping......................................................................................32-153 Component Description....................................................................................32-155 Steering Control Unit (SCU).....................................................................32-155 BITE Test of the Nosewheel Steering System............................................32-155 Nosewheel Steering Hand Control.............................................................32-156 Rudder Pedal Potentiometer......................................................................32-157 Nosewheel Steering Manifold....................................................................32-159 Nosewheel Centering Mechanism..............................................................32-160 Power Steering Unit..................................................................................32-161 Removal of Power Steering Unit................................................................32-163 Steering Feedback Assembly.....................................................................32-165 Steering Switch.........................................................................................32-167 Controls and Indications .................................................................................32-167 Rigging of the RVDT................................................................................32-167 Operation.........................................................................................................32-169 Normal System Operation................................................................................32-169 Operation in the Passive Mode..................................................................32-169 Operational Test of the Nosewheel Steering System..................................32-170 Functional Test of the Nosewheel Steering System....................................32-170 32-61-00 PROXIMITY SENSOR SYSTEM ...........................................................32-173 Introduction.....................................................................................................32-173
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-ix
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page General ...........................................................................................................32-173 System Description .........................................................................................32-173 Component Description....................................................................................32-175 Proximity Sensor Electronic Unit..............................................................32-175 Built-In-Test-Equipment............................................................................32-175 Installation of the Proximity Sensor Electronic-Unit.................................32-176 Retrieval of Data from the Proximity Sensor Electronic Unit (PSEU).......32-176 Erase the Data from the Proximity Sensor Electronic Unit (PSEU)...........32-177 Operational Check of the Proximity Sensor Electronic Unit......................32-177 Proximity Sensors.....................................................................................32-179 Installation of the Proximity Sensors.........................................................32-180 Rigging of the Proximity Sensors..............................................................32-180 Controls and Indications..................................................................................32-181 Landing Gear Control................................................................................32-181 Landing Gear Indications..........................................................................32-181 Alternate Downlock Indications.......................................................................32-181 Operational Check of the Weight On Wheels System ...............................32-183 32-00-00 APPENDIX..............................................................................................32-184 Maintenance Consideration..............................................................................32-184 Safety Precautions.....................................................................................32-184 Main Landing Gear Lower Bearing Seal....................................................32-185 Standard Configuration for an ‘On-Jacks’ Weight-On-Wheels (WOW) Condition.......................................................32-185 32-x
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Page Standard Configuration for an ‘On-Ground’ Weight-Off-Wheels (WOFFW) Condition.................................................32-185 32-00-00 SPECIAL TOOL & TEST EQUIPMENT..................................................32-186 32-00-00 MAINTENANCE PRACTICES................................................................32-188
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-xi
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
ILLUSTRATIONS Figure Title Page 32-1
Landing Gear Functional Block Diagram...................................................32-2
32-2
Main Landing Gears - Details....................................................................32-4
32-4
Main Landing Gear - Shock Strut..............................................................32-6
32-3
Shock Strut................................................................................................32-6
32-5
MLG Axle.................................................................................................32-8
32-6
Shock Strut Torque Links...........................................................................32-9
32-7
MLG Drag Strut .....................................................................................32-10
32-9
MLG Stabilizer Brace..............................................................................32-11
32-8
MLG Ground Lock Pin............................................................................32-11
32-10
MLG Yoke and Actuator..........................................................................32-12
32-11
Shock Strut Fairings................................................................................32-12
32-12
CDL - MLG Shock Strut Fairings............................................................32-13
32-13
Main Gear Doors.....................................................................................32-14
32-14
MLG Doors - Detail................................................................................32-15
32-15
MLG Aft Doors and Connecting Rods.....................................................32-16
32-16
MLG Doors and Connecting Rods...........................................................32-17
32-17
Forward MLG Doors and Connecting Rods.............................................32-18
32-18
Landing Gear Control Panel....................................................................32-20
32-19
Proximity Sensor.....................................................................................32-21
32-20
Landing Gear Doors - Open and Lock/Unlock and Close (1 of 2)............32-22
32-21
Landing Gear Doors - Open and Lock/Unlock and Close (2 of 2)............32-24
FOR TRAINING PURPOSES ONLY
32-xiii
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-22
Nose Landing Gear and Doors.................................................................32-26
32-23
NLG Dressed Shock Strut Assembly (1 of 2)...........................................32-28
32-24
NLG Dressed Shock Strut Assembly (2 of 2)...........................................32-29
32-25
NLG Shock Strut Assembly.....................................................................32-30
32-26
NLG Shock Strut Assembly.....................................................................32-31
32-27
NLG Trailing Arm...................................................................................32-32
32-28
NLG Drag Strut.......................................................................................32-32
32-29
NLG Drag Strut.......................................................................................32-33
32-30
NLG Latest Electrical Harness................................................................32-34
32-31
NLG Aft Doors and Connecting Rods......................................................32-36
32-32
CDL - Nose Landing Gear Aft Doors.......................................................32-37
32-33
NLG Forward Doors and Connecting Rods..............................................32-38
32-34
Main Landing Gear Control Panel...........................................................32-40
32-35
NLG Door Proximity Sensor....................................................................32-41
32-36
NLG Ground-Lock Control Handle..........................................................32-42
32-37
Nose Gear Ground-Lock Position Indication System...............................32-43
32-38
Landing Gear Block Diagram..................................................................32-44
32-39
Landing Gear Selector Valve - Detail.......................................................32-46
32-40
MLG Retraction Actuator - Detail...........................................................32-47
32-41
MLG Downlock Actuator - Detail............................................................32-48
32-43
MLG Uplock Actuator - Detail................................................................32-49
32-42
MLG Uplock Assembly...........................................................................32-49
32-xiv
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-44
MLG Doors Inline Restrictors.................................................................32-50
32-45
Landing Gear Doors Solenoid Sequence Valve........................................32-51
32-46
NLG Doors Sequence Valve.....................................................................32-51
32-48
NLG Retraction and Lock Actuator.........................................................32-52
32-47
NLG Retraction Actuator.........................................................................32-52
32-50
NLG Inline Restrictor..............................................................................32-53
32-49
NLG Lock Actuator.................................................................................32-53
32-51
Landing Gear - Controls and Indications.................................................32-54
32-52
(32-31-00) UP Selection Doors Open......................................................32-58
32-53
(32-31-00) Gear UP and Doors Locked Closed........................................32-60
32-54
(32-31-00) Landing Gear Retraction (Sheet 1 of 3)..................................32-62
32-55
(32-31-00) Landing Gear Retraction (Sheet 2 of 3)..................................32-64
32-56
(32-31-00) Landing Gear Retraction (Sheet 3 of 3)..................................32-66
32-57
Initial DOWN Selection Doors Opening..................................................32-68
32-58
Selection Completed Doors Closed..........................................................32-70
32-59
(32-31-00) Landing Gear Normal Extension............................................32-72
32-60
Alternate Extension System Block Diagram............................................32-74
32-61
Alternate Extension Hydraulic Synoptic..................................................32-76
32-62
Servicing of the Auxiliary System Hydraulic Reservoir...........................32-78
32-63
Main Gear Alternate Release Handle.......................................................32-80
32-64
NLG Alternate Release Handle................................................................32-81
32-65
Alternate Extension Actuator...................................................................32-82
FOR TRAINING PURPOSES ONLY
32-xv
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-66
Landing Gear Downlock Verification Switch...........................................32-83
32-67
Bypass Valve and Alternate Release Cables.............................................32-84
32-68
MLG Alternate Extension System Cam Mechanism Assembly.................32-86
32-69
NLG Alternate Release Cable..................................................................32-88
32-70
Landing Gear Alternate Release - Inhibit Switch.....................................32-89
32-71
Hydraulic Hand Pump and Hand Pump Lever..........................................32-90
32-72
Secondary MLG Selector Valve - Removal and Installation.....................32-92
32-73
LG Downlock Verification Lights - Controls and Indications...................32-94
32-74
Landing Gear Extension and Retraction...................................................32-96
32-75
Main Wheel and Tire Assembly...............................................................32-98
32-76
Main Wheel and Tire Assembly - Removal and Installation.................. 32-100
32-77
MLG Axle Bullet.................................................................................. 32-101
32-78 Nosewheel and Tire Assembly............................................................... 32-102 32-79
Fill Valve Gauge................................................................................... 32-104
32-80
Brakes System Hydraulic Synoptic....................................................... 32-106
32-82
Main Wheel Brake Unit - Removal and Installation.............................. 32-108
32-81
Brake Wear Indicator Pins.................................................................... 32-108
32-83
Main Landing Gear Brake System - Bleed............................................ 32-110
32-84
Brake Bleeding Kit............................................................................... 32-112
32-85
CDL - Brake Assembly Wear Indicator Pin........................................... 32-112
32-86
Brake Control Valve.............................................................................. 32-113
32-88
Fuse - Shuttle Valve.............................................................................. 32-114
32-xvi
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-87
Fuse - Shuttle Valve.............................................................................. 32-114
32-89
Brake Pedals......................................................................................... 32-115
32-90
Brake Control Cables............................................................................ 32-116
32-91
Brake Pressure Transducers.................................................................. 32-117
32-92
Parking Brake Hydraulic System.......................................................... 32-118
32-93
Park Brake Control Valve...................................................................... 32-120
32-94
Park Brake Control Valve...................................................................... 32-120
32-95
Parking Brake Handle Reposition......................................................... 32-122
32-96
CDL - Parking Brake Hand Pump Handle............................................. 32-123
32-97
Parking Brake Accumulator.................................................................. 32-124
32-98
Charge Valve and Gauge....................................................................... 32-125
32-99
Park Brake Control Quadrant................................................................ 32-126
32-100
Parking Brake Control Cable................................................................ 32-127
32-101
Parking Brake Micro-Switch................................................................. 32-128
32-102
Controls and Indications - Parking Brake System................................. 32-130
32-103
CDL - Parking Brake Pressure Indications............................................ 32-131
32-104
Anti-Skid System - Hydraulic Schematic.............................................. 32-132
32-105
Anti-Skid System Control Unit............................................................. 32-134
32-106
Anti-Skid System Control Unit ............................................................ 32-134
32-108
Skid Control Valve ............................................................................... 32-136
32-107
Skid Control Valve................................................................................ 32-136
32-110
Wheel Speed Transducer....................................................................... 32-137
FOR TRAINING PURPOSES ONLY
32-xvii
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-109
Wheel Speed Transducer....................................................................... 32-137
32-111
Wheel Speed Transducer Harness - Removal/Installation...................... 32-138
32-112
Anti-Skid Switch.................................................................................. 32-140
32-113
Anti-Skid Caution Lights...................................................................... 32-141
32-114
Anti-Skid System Functional Test......................................................... 32-142
32-115
Anti-Skid System Electrical Schematic................................................. 32-144
32-116 ARCDU CDS ANTISKID System........................................................ 32-148 32-118
ASC - Current Faults............................................................................ 32-148
32-117
PSEU - Present Faults........................................................................... 32-148
32-119
ASC - No Current Faults....................................................................... 32-150
32-120
Parking Brake Caution Light................................................................ 32-150
32-121
Nosewheel Steering System Schematic................................................. 32-152
32-122
Steering Control Unit............................................................................ 32-154
32-123
Steering Control Unit............................................................................ 32-154
32-124
Nosewheel Steering Hand Control ....................................................... 32-156
32-125
Rudder Forward Assembly (Right Side)................................................ 32-157
32-126
Nosewheel Steering Hydraulic Synoptic............................................... 32-158
32-127 Nosewheel Centering Actuator.............................................................. 32-160 32-128 Nosewheel Centering Mechanism......................................................... 32-160 32-129
Power Steering Unit.............................................................................. 32-161
32-130
Hydraulic Steering Motor..................................................................... 32-164
32-131
Steering Feedback Assembly................................................................. 32-164
32-xviii
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-132
Nosewheel Steering Switch................................................................... 32-166
32-133
Nosewheel Steering System Caution Lights.......................................... 32-166
32-134
Nosewheel Steering - Electrical Schematic........................................... 32-168
32-135
PSEU Input and Output Block Diagram................................................ 32-172
32-136
Proximity Sensor Electronic Unit......................................................... 32-174
32-137 Proximity Sensor Electronic Unit......................................................... 32-175 32-138
Proximity Sensors - Locations.............................................................. 32-178
32-139
Proximity Sensors................................................................................. 32-179
32-140
CAWP with WOW Caution................................................................... 32-182
FOR TRAINING PURPOSES ONLY
32-xix
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CHAPTER 32 LANDING GEAR
32-00-00 INTRODUCTION The landing gear supports the weight of the aircraft on the ground. It is also used to maneuver the aircraft while on the ground.
GENERAL The landing gear is electrically controlled, hydraulically operated and mechanically locked.
if the gear is not extended and the aircraft is in a landing configuration.
The tricycle gear is a retractable dual wheel installation. The main gear retract aft into the nacelles, with the nose gear retracting forward into the nose section. The gear doors completely enclose the landing gear when it is retracted and partially enclose the gear bays when it is extended. Flight compartment advisory lights show position of gear and doors. An aural warning sounds
A Proximity Sensor Electronics Unit (PSEU) monitors and controls the operation of the landing gear components. An alternate landing gear extension system can be used to extend the gear if the primary extension system fails. There is also an alternate down lock verification system.
FOR TRAINING PURPOSES ONLY
32-1
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-2 PILOT HAND CONTROL
RUDDER PEDALS
SELECTOR VALVE
LANDING GEAR CONTROL & INDICATION
NLG SOLENOID SEQUENCE VALVE
PSEU
ANTI-SKID CONTROL UNIT
MLG SOLENOID SEQUENCE VALVES
RIGHT MLG UPLOCK DOWNLOCK 1 DOWNLOCK 2
LEFT MLG UPLOCK DOWNLOCK 1 DOWNLOCK 2
LEFT MLG AFT DOOR
NOSE DOOR
NGDL 1 NGDL 2 NGL 1 NGL 2
Figure 32-1. Landing Gear Functional Block Diagram
RIGHT MLG AFT DOOR
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
STEERING CONTROL UNIT
DASH 8 Q400
ALTERNATE EXTENSION INDICATION
NW CENTER
WOW 1 WOW 2
MAINTENANCE TRAINING MANUAL
Refer to Figure 32-1. Landing Gear Functional Block Diagram.
32 LANDING GEAR
DASH 8 Q400
NOTES
The landing gear system is comprised of the following subsystems: •• Main Landing Gear (MLG) and doors •• Nose Landing Gear (NLG) and doors •• Landing gear extension and retraction •• Wheels and brakes •• Steering system •• Position and warning.
FOR TRAINING PURPOSES ONLY
32-3
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
NOTE Left gear shown. Right gear similar.
6
A
7
5 8 4 9
3
LEGEND 1. Drag Strut 2. Shock Strut 3. Stabilizer Brace 4. Stabilizer Lock 5. Alternate Extension Actuator 6. Yoke 7. Retraction Actuator 8. Uplock Assembly 9. Door Operative Mechanism.
FWD 2
1
A
Figure 32-2. Main Landing Gears - Details
32-4
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-11-00 MAIN LANDING GEAR
An up-lock assembly is attached to the top aft section of the wheel well. It locks the MLG in the retracted position.
GENERAL
The shock strut piston absorbs landing forces.
Refer to Figure 32-2. Main Landing Gears - Details. Each MLG assembly is installed on the airframe structure in the wheel well of the related engine nacelle. Each of the MLG has two wheel and tire assemblies. The main landing gear includes the listed components: •• Drag strut •• Shock strut
A jack pad on the bottom of the shock strut allows for jacking the aircraft from a single point. Proximity sensors send signals to the PSEU of the status of the MLG. A proximity sensor on the uplock assembly signals the gear is up and locked. Two proximity sensors on the stabilizer brace send signals to the PSEU when the MLG is down and locked. Two proximity sensors on the torque links send signals to the PSEU of Weight-OnWheels (WOW) or a Weight-Off-Wheels (WOFW) condition.
•• Stabilizer brace •• Lock actuator •• Alternate extension actuator •• Yoke assembly •• Retraction actuator •• Uplock assembly •• Door operating mechanism.
SYSTEM DESCRIPTION Refer to Figure 32-2. Main Landing Gears - Details. A retraction actuator is attached to the yoke and the shock strut, it is used to extend and retract the MLG. A locking actuator on the stabilizer brace holds the MLG in the down position, it will also unlock the stabilizer brace to allow the main gear to be retracted. An auxiliary extension actuator is attached between aircraft structure in the aft section of the wheel well, and to the forward face of the yoke. The auxiliary extension actuator extends the MLG during an alternate extension sequence.
FOR TRAINING PURPOSES ONLY
32-5
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Shock Strut Refer to: •• Figure 32-3. Shock Strut. •• Figure 32-4. M ain Landing Gear Shock Strut. The shock strut is part of the main gear assembly. The dressed shock strut is attached between the yoke and the drag. The shock strut outer cylinder is a Y-shaped component with a single stage nitrogen and oil filled shock absorbing piston fitted inside a cylinder. The function of the shock strut is to absorb the landing forces of aircraft landings.
Figure 32-3. Shock Strut
1
FWD
10
2
11
3
12
4 5 6 7
13
8
14 9
LEGEND 1. Electrical Harness 2. Drag Strut 3. Hydraulic Brake Line 4. Shock Strut 5. Upper Torque Link 6. Shock Strut Piston 7. Lower Torque Link 8. Axle 9. Jack Pad 10. Fairings 11. Electrical Harness 12. Uplock Roller 13. Proximity Sensors 14. Wheel and Brake Assembly 15. Hydraulic Brake Line.
15
Figure 32-4. Main Landing Gear - Shock Strut
32-6
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Installation of the MLG Electrical Harness
32 LANDING GEAR
DASH 8 Q400
NOTES
The main landing-gear (MLG) electrical harnesses includes the weight-on-wheels and the wheel speed sensors electrical harnesses are installed on the drag strut. You can also find them on the shock strut. The downlock electrical harness is installed on the MLG stabilizer brace assembly.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-7
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Axles
NOTES
Refer to Figure 32-5. MLG Axle. The axle is attached to the shock strut piston with a barrel nut and piston plug. The axle is made of steel with chrome-plated bearing surfaces. The axle is removable and interchangeable.
Figure 32-5. MLG Axle
32-8
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Shock Strut Torque Links
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-6. Shock Strut Torque Links. The lower torque link is attached to two lugs on the rear of the shock strut piston. The upper torque link is attached to two lugs on the bottom of the outer cylinder. The torque links, made of heat-treated steel, are the structural link between the shock strut outer cylinder and the piston. Rotation of the shock strut piston and the axle is prevented by these torque links. The upper torque links are the targets for the WOW sensors.
LEGEND 1. Lower Torque Link 2. Upper Torque Link 3. Axle.
2 1 3
Figure 32-6. Shock Strut Torque Links
FOR TRAINING PURPOSES ONLY
32-9
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Drag Strut Refer to Figure 32-7. MLG Drag Strut. The drag strut is attached at the lower end to the shock strut outer cylinder. It is attached with a lubricated hinge point. The upper end of the drag strut is attached to the airframe structure of the forward section of the wheel well with a lubricated hinge point.
The electrical harnesses for the proximity sensors, wheel speed transducers, and hydraulic pipes for the brakes attach to the drag strut with brackets. A grounding point is fitted to the top of the drag strut. The landing gear pivots at the drag strut upper end hinge during retraction and extension.
The drag strut is a fixed length tubular component. A bracket assembly near the top end provides an attach point for the forward door linkage. 1 2
FWD
A
FWD
3
MAIN LANDING GEAR 4
LEGEND 1. Grounding Point 2. Electrical Harness 3. Drag Strut 4. Hydraulic Brake Line 5. Shock Strut.
5
NOTE Left gear shown. Right gear similar.
Figure 32-7. MLG Drag Strut
32-10
FOR TRAINING PURPOSES ONLY
A
DASH 8 Q400
32 LANDING GEAR
MAINTENANCE TRAINING MANUAL
Stabilizer Brace Refer to: •• Figure 32-9. MLG Stabilizer Brace. •• Figure 32-8. MLG Ground Lock Pin. The stabilizer brace is attached to the airframe structure in the forward section of the wheel well with two lubricated hinge points. The aft section of the stabilizer strut is attached to the yoke with two lubricated hinge points. The stabilizer strut has an overcenter link attached between the two sections of the stabilizer strut. The overcenter link supplies a mechanical lock for the MLG in the down position.
Figure 32-8. MLG Ground Lock Pin
LEGEND 1. Downlock Actuator 2. Overcenter Link 3. Yoke 4. Lock Spring 5. Proximity Sensors 6. Stabilizer Brace.
A 2
FWD 1 3
MAIN LANDING GEAR
6
5
NOTE Left gear shown. Right gear similar.
FWD
4
A
Figure 32-9. MLG Stabilizer Brace
FOR TRAINING PURPOSES ONLY
32-11
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Yoke
Shock Strut Fairings
Refer to Figure 32-10. MLG Yoke and Actuator.
Refer to Figure 32-11. Shock Strut Fairings.
The top of the yoke is attached to the rear spar by two lubricated hinge points. The bottom of the yoke is attached to the top of the shock strut by two lubricated hinge points.
The shock strut fairings are installed on the shock struts of the MLG.
The yoke attaches to the stabilizer brace at the cross beam with two lubricated hinge points. The retraction actuator cylinder attaches to the cross beam of the yoke with two lubricated hinge points.
Mounting lugs on the outer cylinder of the shock strut allow installation of the aluminum fairings to the MLG with standard hardware. The function of the fairings is to reduce the aerodynamic drag induced by the extended MLG in flight.
The rod end of the alternate retraction actuator is attached to lugs at the top of the yoke with lubricated hinge points. The yoke assembly is an H-shaped structural component.
2
1
Aft Fairings
Fwd Fairings
LEGEND 1. Aft Fairings 2. Fwd Fairings.
Figure 32-10. MLG Yoke and Actuator
32-12
Figure 32-11. Shock Strut Fairings
FOR TRAINING PURPOSES ONLY
SYSTEM
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
1.
ATA SUB-SYSTEM
PART DESCRIPTION
32---1
MLG SHOCK STRUT FAIRINGS
32 LANDING GEAR
DASH 8 Q400
NUMBER OF PARTS REQUIRED FOR ALL FLIGHT CONDITIONS EXCEPT AS PROVIDED IN COLUMN 2.
2. REMARKS AND/OR EXCEPTIONS
14
All MLG fairings may be missing provided performance limited weights obtained from the DOT approved Airplane Flight Manual, excluding Sub-Sections 5.7, 5.11 and 5.12, are reduced by 450 kg (1,000 lb). Any or all of the following MLG fairings may be missing provided performance limited weights obtained from the DOT approved Airplane Flight Manual, excluding Sub-Sections 5.7, 5.11 and 5.12, are reduced by 340 kg (750 lb). 46712 46702 46703 or 46730 46711 or 46731
Leading Edge, Center Trailing Edge, Sides Center Aft Lower NOTE 1. MLG fairings 46702, 46703 or 46730, and, 46711 or 46731, must be removed if MLG fairing 46712 is removed. 2. MLG fairing 46711 or 46731 must be removed if MLG fairing 46703 or 46730 is removed.
Any or all of the following MLG fairings may be missing provided performance limited weights obtained from the DOT approved Airplane Flight Manual, excluding Sub-Sections 5.7, 5.11 and 5.12, are reduced by 160 kg (350 lb). 46709 Leading Edge, Upper Center 46710 Trailing Edge, Upper Center
Figure 32-12. CDL - MLG Shock Strut Fairings
FOR TRAINING PURPOSES ONLY
32-13
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-12-00 MAIN LANDING GEAR DOORS
The status of the doors is shown on the LANDING GEAR control panel in the flight compartment. The MLG in Figure 32-13 include the components that are listed below:
INTRODUCTION
1. Forward door
The four doors on each engine nacelle provide an aerodynamic enclosure for the MLG when it is in the retracted position.
2. Aft door 3. Push rods
GENERAL
4. Aft door 5. Door seal
Refer to Figure 32-13. Main Gear Doors.
6. Forward door
Two mechanically operated doors enclose the forward section of the MLG wheel well and open and close with movement of the gear.
7. Door seal 8. Door seal 9. Forward door connecting rods
Two hydraulically operated doors enclose the aft section of the MLG wheel well. The aft doors are closed when the MLG is fully retracted and extended. They will open whenever the gear is in transition.
10. Door seal.
3 2
4
FWD 1
5 6
10
9
8
7
Figure 32-13. Main Gear Doors
32-14
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION
The aft doors are opened and closed by a single hydraulic actuator, with a mechanical sequence valve.
Refer to Figure 32-14. MLG Doors - Detail. The forward doors are operated by mechanical links attached to the drag strut.
Lock links supply an overcenter lock for the doors in the closed position. A proximity sensor sends a signal to the PSEU.
When the MLG is extended the forward doors will open. When the MLG is retracted the doors will close.
4
5
6
3
7 8 9
10 2
1
FWD
NOTE Left gear shown. Right gear similar.
LEGEND 1. Forward Doors Connecting Rods 2. Forward Door 3. Alternate Extension Actuator 4. Yoke 5. Mechanical Sequence Valve 6. Retraction Actuator 7. Uplock Assembly 8. Aft Doors Mechanism 9. Alternate Release Arm 10. Aft Door.
Figure 32-14. MLG Doors - Detail
FOR TRAINING PURPOSES ONLY
32-15
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
Aft MLG Doors Connecting Rods
Aft MLG Doors
Refer to Figure 32-15. MLG Aft Doors and Connecting Rods.
Refer to Figure 32-15. MLG Aft Doors and Connecting Rods. The two aft doors have a hinge on both the forward and aft corners. The doors are symmetrical and meet at the center line when closed.
The connecting rods are installed between the pivot arm assembly and attached to the forward hinges of the aft doors.
The aft doors are opened and closed by a single hydraulic actuator and a linkage mechanism. The mechanism is attached to the forward hinges of the doors. 1 2
3
4 A
8
7
FWD
5
LEGEND 1. Mechanical Sequence Valve 2. Pivot Arm 3. Tension Spring 4. Actuator 5. Lock Link 6. Aft Door 7. Proximity Sensor 8. Connecting Rods.
NOTE Left side shown. Right side similar. 6 fs661a01.cgm
A
Figure 32-15. MLG Aft Doors and Connecting Rods
32-16
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Aft Door Mechanism
During the alternate extension of the MLG, the alternate release arm rotates to move the lock links out from an over center position. A tension spring attached to the pivot arm and to the side of the aft section of the wheel well, provides the force to open the doors in alternate operation.
Refer to Figure 32-16. MLG Doors and Connecting Rods. The pivot arm is attached to a frame assembly on the left side aft section of the wheel well. The pivot arm has hinge points to form a bell crank between the push rods and the lock links.
The system also utilizes a proximity sensor which is installed on 2 brackets below the lock link.
The lock links are attached to the bottom of the pivot arm as well as the side of the aft section of the wheel well.
The function of the aft MLG doors mechanism is to open and close the aft MLG doors.
1
3
2
4
5 6
8 7
LEGEND 1. Mechanical Sequence Valve 2. Pivot Arm 3. Tension Spring 4. Actuator 5. Lock Link 6. Proximity Sensor 7. Connecting Rods 8. Alternate Release Arm.
Figure 32-16. MLG Doors and Connecting Rods
FOR TRAINING PURPOSES ONLY
32-17
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Forward MLG Doors Refer to Figure 32-17. Forward MLG Doors and Connecting Rods. The doors are connected to the bottom of the center section of the engine nacelle by hinges. Each door has a hinge on the forward and aft corner. The doors are symmetrical and meet at the engine nacelle center line when closed. The forward doors are operated by adjustable connecting rods attached between the drag strut and the forward doors.
A
LEGEND 1. Door Fitting 2. Push Rods 3. Forward Door 4. Bracket Assembly 5. Drag Strut.
B
D
FW
A
MLG DOOR
1
2
3
4 5
FWD B
Figure 32-17. Forward MLG Doors and Connecting Rods
32-18
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-12-00 DVI MAIN LANDING GEAR DOOR MECHANISMS
32 LANDING GEAR
DASH 8 Q400
NOTES
Inspect the door mechanisms for: •• Damage •• Corrosion •• Cracks •• Failure •• Defects •• Hydraulic Leaks •• Correct Installation •• Security.
FOR TRAINING PURPOSES ONLY
32-19
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
L. DOOR
N. DOOR R. DOOR
LEFT
NOSE
RIGHT RIGHT
LEFT
NOSE
RIGHT RIGHT
MAIN INSTRUMENT PANEL “Amber” Door Open
LANDING GEAR
LANDING GEA R
DN
LOCK RELEASE
UP
HORN MUTE
TEST
fs507a01.cgm
Figure 32-18. Landing Gear Control Panel
32-20
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Refer to: •• Figure 32-18. Landing Gear Control Panel. •• Figure 32-19. Proximity Sensor.
The proximity sensor sends a signal to the PSEU, which will send a signal to the LANDING GEAR control panel. This will show the status of the aft doors. When the doors are open the amber L DOOR and R DOOR lights come on.
A proximity sensor for the aft doors is installed on a bracket below the aft door mechanism.
1 2
3
4
LEGEND 1. Mechanical Sequence Valve 2. Pivot Arm 3. Tension Spring 4. Actuator 5. Lock Link 6. Aft Door 7. Proximity Sensor 8. Push Rods.
8
7
5
FWD
6 fs661a01.cgm
Figure 32-19. Proximity Sensor
FOR TRAINING PURPOSES ONLY
32-21
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
B 1
2
A
A
3
6 4
5 B
VIEW LOOKING UP DOOR OPEN
B
VIEW LOOKING UP DOOR CLOSED
Figure 32-20. Landing Gear Doors - Open and Lock/Unlock and Close (1 of 2)
32-22
FOR TRAINING PURPOSES ONLY
br842a01.dg, gg, 04/01/99
LEGEND 1. Handle 2. Access Door 3. Access Door 4. Guard 5. Switch 6. Handle.
MAINTENANCE TRAINING MANUAL
Open and Lock the Landing Gear Doors The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to: •• Figure 32-20. Landing Gear Doors - Open and Lock/Unlock and Close (1 of 2). •• Figure 32-21. Landing Gear Doors - Open and Lock/Unlock and Close (2 of 2). WARNING
MAKE SURE THAT THE AREA AROUND THE NOSE LANDING GEAR (NLG) DOORS IS CLEAR OF PERSONNEL AND EQUIPMENT. DO THIS BEFORE YOU OPERATE THE ALTERNATE EXTENSION RELEASE HANDLE OF THE NLG. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. Open the landing gear doors as follows: 1. In the flight compartment ceiling, above the co-pilot position, lift the guard then set the LG DOWN SELECT INHIBIT switch to the INHIBIT position. 2. I n t h e f l i g h t c o m p a r t m e n t c e i l i n g , above the co-pilot position, fully open the LANDING GEAR ALTERNATE RELEASE access door.
5. At the forward end of the LANDING GEAR ALTERNATE EXTENSION access door pull the NOSE L/G RELEASE handle to open the NLG doors. 6. Install the lock pin through the hole in the guard and the door mechanism in the NLG wheel well. 7. Install the lock pins in the hole in the brackets of the MLG doors. Make sure that the lock pins go through the hole in the brackets.
Installation of the Main Landing Gear Lock Pins The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. WARNING
DO NOT USE FORCE WHEN YOU INSTALL OR REMOVE THE LOCKPIN. IF FORCE IS NECESSARY, THE LANDING GEAR MAY NOT BE SAFE AND CAN RETRACT ACCIDENTALLY. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE AIRCRAFT. 1. Install the MLG lockpins in the lockpin holes of the stabilizer down-lock mechanism. 2. If you cannot put the MLG lockpin in its hole easily, the main landing gear is not safe. To ensure the safety of the aircraft and personnel, support the weight of the aircraft with the appropriate nose or main jack BEFORE investigating the cause of the problem.
3. Behind the access door, pull the MAIN L/R RELEASE handle to open the MLG doors. 4. On the flight compartment floor, open the LANDING GEAR ALTERNATE EXTENSION access door.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-23
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Bracket
Lock Pin
Hide
TRONAIR
REMOV E
Lock Pin
REMOVE Figure 32-21. Landing Gear Doors - Open and Lock/Unlock and Close (2 of 2)
32-24
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
32-25
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
2
A
3 1
LEGEND 1. Forward Door 2. Forward Door Operating Mechanism 3. Shock Strut Assembly 4. Aft Door 5. Aft Door Actuating Linkage.
4
FWD
5
A
Figure 32-22. Nose Landing Gear and Doors
32-26
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-20-00 NOSE LANDING GEAR AND DOORS
32 LANDING GEAR
DASH 8 Q400
NOTES
INTRODUCTION Refer to Figure 32-22. Nose Landing Gear and Doors. The NLG absorbs the shock of landing and gives stability and direction control during aircraft taxi. The NLG doors enclose the retracted NLG and add to the aerodynamic efficiency of the aircraft.
FOR TRAINING PURPOSES ONLY
32-27
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-21-00 NOSE LANDING GEAR
The nose landing gear assembly is comprised of the following: •• Shock strut assembly
GENERAL
•• Drag strut assembly and
The NLG is installed in the wheel well in the nose fuselage. It is located forward of the forward pressure bulkhead.
•• Harness electrical.
The NLG retracts forward. When retracted, the aft doors will enclose it in the wheel well.
Electrical Harness Electrical Harness Steering Gearbox
Upper Cable Guide Assembly Trunnion Arm Taxi Light Location Centering Actuator WOW Proximity Switch Cover
Tow-Fitting Assembly
Figure 32-23. NLG Dressed Shock Strut Assembly (1 of 2)
32-28
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
A
Outer Cylinder
Jacking Point
Inner Cylinder
Trailing Arm A
Piston Assembly
Link
DETAIL A-A
Figure 32-24. NLG Dressed Shock Strut Assembly (2 of 2)
FOR TRAINING PURPOSES ONLY
32-29
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND 1. Downlock Actuator. 2. Upper Cable Guide Assembly. 3. Upper Drag Strut. 4. Lower Drag Strut. 5. Steering Hydraulic Lines. 6. Taxi Light. 7. Proximity Sensor Cover. 8. Tow-Fitting Assembly. 9. Trailing Arm. 10. Wheels.
11. Electrical Harness. 12. Retraction Actuator. 13. Steering Gearbox. 14. Trunnion Arms. 15. Outer Cylinder. 16. Centering Spring. 17. Piston Assembly. 18. Link. 19. Axle. 20. Jacking Point.
A
1
FWD 11
2 12 3 13
14
4 5
15 6
16 7 17 8 18
NOTE Left wheel removed for clarity.
9 19 20
10 A
ft273a02.cgm
Figure 32-25. NLG Shock Strut Assembly
32-30
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Nose Landing Gear Shock Strut
A low pressure valve located on the top surface of the inner cylinder, is used to service the piston assembly with hydraulic fluid and dry nitrogen.
Refer to: •• Figure 32-25. N LG Shock Strut Assembly. •• Figure 32-26. N LG Shock Strut Assembly. The NLG shock strut is attached to the NLG wheel well structure, retraction actuator, and the NLG drag strut. The shock strut has an outer cylinder, inner cylinder, piston assembly, a link and a trailing arm. The trailing arm has a jacking point for jacking of the NLG. Two trunnion arms are installed at the upper rear portion of the outer cylinder. The retraction actuator is attached to the mounting lugs on the top of the right trunnion arm. At the top forward side of the outer cylinder, there are two mounting lugs. The lower drag strut is attached to these two mounting lugs. The taxi light is installed on the bottom right side of the outer cylinder.
Figure 32-26. NLG Shock Strut Assembly
The power steering hydraulic motor and gearbox assembly are installed on the top of the shock strut between the trunnion arms. The NLG steering centering actuator assembly, steering sensor, and the centering cam are installed on the aft lower side of the outer cylinder. The outer cylinder has attachment points for the electrical harnesses. The WOW proximity sensors are installed on the inner cylinder above the tow fitting assembly. The piston assembly in the inner cylinder is attached to a link. This link is installed between two lugs on the trailing arm.
FOR TRAINING PURPOSES ONLY
32-31
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Nose Landing Gear Trailing Arm
NLG Drag Strut
Refer to Figure 32-27. NLG Trailing Arm.
Refer to:
•• The NLG Trailing Arm is part of the nose gear shock strut assembly. •• The forward end of the trailing arm is attached to the steerable inner cylinder. •• The midpoint of the trailing arm is attached to the shock strut piston assembly with a link assembly. •• The link assembly is installed between two lugs on the trailing arm. •• The aft end of the trailing arm carries the removable nosewheels and axle. •• The trailing arm has a jacking point for jacking the NLG, for tire change, and servicing. •• The link assembly transmits ground loads from the trailing arm to the piston assembly.
Figure 32-27. NLG Trailing Arm
32-32
•• Figure 32-28. NLG Drag Strut. •• Figure 32-29. NLG Drag Strut. The NLG drag strut is attached to the wheel well structure, retraction actuator, lock actuator, and the shock strut. The drag strut assembly contains the following subcomponents: •• Upper drag strut •• Lower drag strut •• Pivot tube assembly •• Spring assemblies (2) •• Link assembly •• Upper lock link and •• Lower lock link.
Figure 32-28. NLG Drag Strut
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
The two spring and the pivot tube assemblies are installed on the upper drag strut. The pivot tube assembly has six arms: •• Two for the spring assemblies
The lower lock link is installed on the lower drag strut and is connected to the upper lock link. The upper lock link is installed on the upper drag strut and is connected to the lock link assembly. The over centering action of the upper and lower lock links makes a mechanical lock when the gear is in the retracted and the extended positions.
•• One for the downlock actuator •• One for the link assembly •• One for the emergency uplock release mechanism and •• One for the ground lock mechanism.
The function of the drag strut assembly is to stabilize the shock strut in either the retracted or the extended position.
FWD B A
2
1
A
NOSE LANDING GEAR
10 3 9 4
8 5
FWD 7 6
ft149a01.cgm
B
LEGEND 1. Pivot Tube Assembly 2. Pivot Tube Arm Downlock Actuator for Ground Lock Attachment Point 3. Pivot Tube Arm for Emergency Uplock Release 4. Lock Link Assembly 5. NLG Alternate Lock Proximity Sensor 6. Lower Drag Strut 7. NLG Primary-Lock Proximity Sensor 8. Upper Lock Link 9. Upper Drag Strut 10. Spring Assembly.
Figure 32-29. NLG Drag Strut
FOR TRAINING PURPOSES ONLY
32-33
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
NLG Electrical Harness The Nose Landing Gear electrical harnesses are attached to the NLG wheel well structure, shock strut, and the drag strut. Three harnesses on the shock strut give power/ signal input for the listed components: •• WOW1/Taxi light harness •• WOW2/Centering actuator harness and •• Nosewheel steering harness.
Figure 32-30. NLG Latest Electrical Harness
32-34
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-22-00 NOSE LANDING GEAR DOORS
32 LANDING GEAR
DASH 8 Q400
NOTES
INTRODUCTION The NLG doors enclose the retracted NLG in the forward fuselage wheel well. They add to the aerodynamic efficiency of the aircraft.
GENERAL The NLG doors are comprised of the following components: •• NLG forward doors •• NLG forward doors connecting rods •• NLG aft doors and •• NLG aft doors connecting rods.
SYSTEM DESCRIPTION The two NLG forward doors are hydraulically operated and close after the gear is extended or retracted. The two NLG aft doors are connected to the NLG shock strut. They travel with the NLG on extension and retraction.
FOR TRAINING PURPOSES ONLY
32-35
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
LEGEND 1. Aft Doors Connecting Rods 2. Aft Doors.
1
2
FWD A
Figure 32-31. NLG Aft Doors and Connecting Rods
32-36
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
Aft NLG Doors Connecting Rods
Aft NLG Doors
Refer to Figure 32-31. NLG Aft Doors and Connecting Rods.
Refer to Figure 32-31. NLG Aft Doors and Connecting Rods.
The two adjustable connecting rods connect the NLG shock strut to the doors for mechanical operation. This allows the doors be rigged correctly, in the closed position.
The two aft, NLG doors are hinged to the fuselage. Each door is made of an inner and outer skin. The two NLG aft doors are connected to the NLG shock strut by two adjustable connecting rod assemblies. These doors are open when the NLG is extended and closed when the NLG is retracted. Each NLG aft door is hinged to the fuselage at two places. The NLG AFT doors provide an aerodynamic fairing following nose gear retraction.
SYSTEM
1.
32 LANDING
ATA SUB-SYSTEM 32---2
GEAR
PART DESCRIPTION NOSE LANDING GEAR AFT DOORS (714, 715)
NUMBER OF PARTS REQUIRED FOR ALL FLIGHT CONDITIONS EXCEPT AS PROVIDED IN COLUMN 2.
2. REMARKS AND/OR EXCEPTIONS 2
One may be missing provided the airspeed is limited to a maximum of 190 KIAS and operable headsets are made available to each pilot. NOTE LRC cruise data may be used for flight planning. Where LRC speed is greater than 190 KIAS, LRC fuel flow data for a given weight, altitude and temperature condition may be conservatively used when flying at 190 KIAS.
Figure 32-32. CDL - Nose Landing Gear Aft Doors
FOR TRAINING PURPOSES ONLY
32-37
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND 1. Door Attachment Bracket 2. Toggle Link Assembly 3. Forward Door Actuator Assembly 4. Link Assembly 5. Mechanical Sequence Valve 6. Alternate Release Cable 7. Bell Crank 8. Spring Assembly 9. Door Attachment Bracket 10. Forward Door 11. Forward Door 12. Forward Doors Connecting Rods.
4
5
A
7
6
8 9
3
10
13 2
1
12
FWD 11
Figure 32-33. NLG Forward Doors and Connecting Rods
32-38
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
NLG Forward Doors Refer to Figure 32-33. NLG Forward Doors and Connecting Rods. The two NLG forward doors are hinged to the fuselage at two places. The forward hinges form the attachment brackets for the operating mechanism.
32-22-00 DVI NOSE LANDING GEAR DOOR MECHANISMS Inspect the door mechanisms for: •• Damage
Each door is made up of an inner skin and an outer skin. The inner skin is contoured to give clearance for the nosewheels in the retracted position.
•• Corrosion
The operating mechanism is comprised of the following;
•• Defects
•• Two adjustable connecting rods •• Extension spring
•• Cracks •• Failure •• Hydraulic Leaks •• Correct Installation •• Security.
•• Bell crank •• Toggle link assembly •• Link assembly •• Mechanical sequence valve •• Hydraulic actuator. This operating mechanism is attached to the forward wall of the nosewheel bay and is protected by a removable debris guard.
NLG Forward Doors Connecting Rods Refer to Figure 32-33. NLG Forward Doors and Connecting Rods. The two adjustable connecting rods connect the bell crank to the doors. To be rigged correctly the doors must be in the closed position.
FOR TRAINING PURPOSES ONLY
32-39
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
L. DOOR
N. DOOR R. DOOR
LEFT
NOSE
RIGHT RIGHT
LEFT
NOSE
RIGHT RIGHT
MAIN INSTRUMENT PANEL “Amber” Door Open
LANDING GEAR
LANDING GEA R
DN
LOCK RELEASE
UP
HORN MUTE
TEST
fs507a01.cgm
Figure 32-34. Main Landing Gear Control Panel
32-40
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Refer to: •• Figure 32-34. M ain Landing Gear Control Panel.
The PSEU sends a signal to the LANDING GEAR control panel, to show the status of the forward doors. When the doors are open the amber N DOOR light comes on.
•• Figure 32-35. N LG Door Proximity Sensor. A proximity sensor is installed on the forward wall of the nosewheel bay. The target of the proximity sensor is on the toggle link assembly. The toggle link assembly is part of the NLG door mechanism. When the doors operate the toggle link assembly moves. This movement is sensed by the proximity sensor. The proximity sensor sends the signal to the PSEU.
Figure 32-35. NLG Door Proximity Sensor
FOR TRAINING PURPOSES ONLY
32-41
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-25-00 NOSE LANDING GEAR GROUND LOCK INTRODUCTION A remotely operated nose gear ground lock mechanism is controlled from the outside of the aircraft.
GENERAL The ground lock control is on the left side nose fuselage. The ground lock mechanically prevents NLG retraction.
The ground-lock control handle has a momentary action pushbutton. Pushing the pushbutton releases the nose gear control handle from the fuselage. This will cause the control handle to spring partly out. The control handle must be pulled fully out and rotated 90º clockwise to point the chevrons towards the ground. This will lock the nose gear. The nose gear ground-lock is engaged when the downlock arm of the pivot tube assembly is on the drag strut of the NLG. When the control handle is in and flush with the fuselage, the nose gear is unlocked.
SYSTEM DESCRIPTION
CAUTION
Refer to Figure 32-36. NLG Ground-Lock Control Handle. The nose gear ground-lock control handle engages the downlock safety lever.
A
If the nose gear ground-lock cannot be engaged, support the aircraft with the nose fuselage jack before investigation.
PRESS BUTTON TO RELEASE PULL AND TURN TO GROUND LOCK NOSE GEAR
PRESS BUTTON TO RELEASE PULL AND TURN TO GROUND LOCK NOSE GEAR
ENGAGED (FULLY EXTENDED)
DISENGAGED (FULLY RETRACTED)
A
Figure 32-36. NLG Ground-Lock Control Handle
32-42
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
COMPONENT DESCRIPTION Nose Gear Ground-Lock Position Indication System (Optional) Refer to Figure 32-37. Nose Gear Ground-Lock Position Indication System. This system is optional for aircraft with Modsum 4-429586. The switch and, cable assembly are located in the nose landing gear wheel well. The ground-lock position indication system is connected to the ground lock control system. A
When you engage the ground-lock system, an advisory indication shows on the pilot’s side panel. 4
LEGEND 1. Cable Switch Assembly 2. Lever Assembly 3. Striker Plate 4. Advisory Light.
2 NOSE GEAR LOCK
3 B
1 A bram44a01.dg, sw, 17/06/02
Figure 32-37. Nose Gear Ground-Lock Position Indication System
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-43
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
PROXIMITY SENSOR ELECTRONIC UNIT
LDG GEAR INOP
CAUTION & WARNING PANEL CONTROL SEQUENCING
GEAR POSITION AND LOCKED INDICATION
MAIN/NOSE GEAR AND DOOR CONTROL VALVES
MAIN/NOSE GEAR AND DOOR POSITIONS
WEIGHT-ON-WHEELS LOGIC PROCESSING
AIRCRAFT SYSTEMS
Figure 32-38. Landing Gear Block Diagram
32-44
FOR TRAINING PURPOSES ONLY
MAIN GEAR ASSEMBLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
32-30-00 LANDING GEAR EXTENSION AND RETRACTION
32-31-00 PRIMARY EXTENSION AND RETRACTION
INTRODUCTION
INTRODUCTION
The landing gear Retraction Control System (RCS) controls the hydraulic retraction and extension of the landing gear. The RCS shows the landing gear and landing gear door status in the flight compartment.
The Primary RCS controls the extension and retraction of the landing gear and the landing gear doors.
GENERAL
There are three conditions required for the PSEU to activate the selector valve. These conditions are as follows:
The main gear retracts aft. The nose gear retracts forward. There is an alternate method for extending the landing gear. Advisory lights give extension/retraction and fail/safe information.
GENERAL
•• Landing gear selector lever is moved to the UP position
SYSTEM DESCRIPTION
•• PSEU receives the signal that the aircraft is WOFW
Refer to Figure 32-38. Landing Gear Block Diagram.
•• NLG is centered.
The LANDING GEAR selector lever and the PSEU control the operation of the landing gear. The No.2 hydraulic system supplies the power to move the landing gear. Hydraulic retraction and extension starts when the landing gear selector lever is unlocked and moved to the desired position. The PSEU checks the landing gear and landing gear door status, comparing the status of both to the position selected. The PSEU then controls the hydraulic sequences to either fully extend or fully retract the landing gear. The indicator lights installed on the landing gear control panel assembly show the landing gear and the landing gear door status. A LDG GEAR INOP caution light is shown on the flight compartment caution and warning panel in the event of a system malfunction.
FOR TRAINING PURPOSES ONLY
32-45
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Landing Gear Selector Valve Refer to Figure 32-39. Landing Gear Selector Valve - Detail. The landing gear selector valve is installed in the right wing to fuselage area. The valve is a self contained assembly which has two solenoid valves. The valve controls the supply of hydraulic pressure to either the extend or retract hydraulic circuits of the landing gear system.
3
2 A
1
LEGEND 1. Electrical Connector 2. Hydraulic Line 3. Selector Valve.
FWD
2
Figure 32-39. Landing Gear Selector Valve - Detail
32-46
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
MLG Retraction Actuator Refer to Figure 32-40. MLG Retraction Actuator - Detail. The MLG retraction actuator cylinder is attached to the lower front of the MLG yoke cross beam. The rod end is attached to the center top of the MLG shock strut. The actuator is a hydraulic device that has two ports. There are restrictors in both ports. The rod end of the actuator piston has a ball and race with a lubrication fitting.
A
FWD
1
MAIN LANDING GEAR (MLG)
2 4
3
A
FWD
LEGEND 1. Retraction Actuator 2. Hydraulic Line Extension 3. Hydraulic Line Retraction 4. Yoke Assembly.
Figure 32-40. MLG Retraction Actuator - Detail
FOR TRAINING PURPOSES ONLY
32-47
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
MLG Downlock Actuator Refer to Figure 32-41. MLG Downlock Actuator - Detail. The MLG downlock actuator is attached to the MLG stabilizer brace assembly. The MLG downlock actuator has two ports. The rod end of the actuator has a ball and race with a lubrication fitting. Hydraulic lines are attached to the two ports and are sealed with O-rings. The MLG downlock actuator locks the landing gear in the down position. A A
FWD
MAIN LANDING GEAR
A
A
Figure 32-41. MLG Downlock Actuator - Detail
32-48
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
MLG Uplock Assembly Refer to: •• Figure 32-42. MLG Uplock Assembly. •• Figure 32-43. M LG Uplock Actuator - Detail. The uplock assembly is attached to a frame at the top of the wheel well. The uplock roller of the MLG engages the inner face of the latch assembly. The latch assembly pivots into the locked position assisted by the two extension springs of the uplock assembly. A lock link prevents the latch assembly from rotating to the UNLOCK position until the piston of the uplock actuator extends during a MLG extension.
Figure 32-42. MLG Uplock Assembly
A
1
FWD
FWD 2
MLG UPLOCK ACTUATOR
LEGEND 1. MLG Uplock Assembly 2. External Spring 3. MLG Uplock Actuator. 3
Figure 32-43. MLG Uplock Actuator - Detail
FOR TRAINING PURPOSES ONLY
32-49
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Mechanical Sequence Valve
Inline Restrictors
The mechanical sequence valve is installed at the forward end of the MLG aft doors. The MLG mechanical sequence valve is a bolt-on assembly.
Refer to Figure 32-44. MLG Doors Inline Restrictors.
The function of the mechanical sequence valve is to correctly sequence the operation of the MLG uplock release and the MLG retraction actuators.
1
Two inline restrictors are installed in the hydraulic lines. Between the mechanical sequence valves and the retraction actuators. The MLG door inline restrictors reduce the flow of hydraulic pressure to the retraction actuators until the gear doors are almost fully open.
A
MLG DOORS
LEGEND 1. Inline Restrictors 2. Mechanical Sequence.
FWD
2
A
Figure 32-44. MLG Doors Inline Restrictors
32-50
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
MLG Solenoid Sequence Valve Refer to Figure 32-45. Landing Gear Doors Solenoid Sequence Valve. The MLG solenoid sequence valves are located in the wheel-well on the left side, they are forward of the aft doors actuator.
The NLG sequence valve is a bolt-on assembly with four ports. The valve is operated by a single coil solenoid. The NLG solenoid sequence valve controls the opening and closing of the doors by porting hydraulic fluid to the door actuator.
The valve is a self contained, bolt-on assembly. It is directly operated by a single coil solenoid. The valve controls opening and closing of aft doors. This is done by porting hydraulic fluid to the door actuators.
NLG Solenoid Sequence Valve Refer to: •• Figure 32-45. L a n d i n g G e a r D o o r s Solenoid Sequence Valve. •• Figure 32-46. N LG Doors Sequence Valve.
Figure 32-46. NLG Doors Sequence Valve
The NLG solenoid sequence valve is located in the lower right section of the NLG bay, on the outer wall.
FWD
A A
fs133a01.cgm
Figure 32-45. Landing Gear Doors Solenoid Sequence Valve
FOR TRAINING PURPOSES ONLY
32-51
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
NLG Retraction Actuator Refer to: •• Figure 32-47. NLG Retraction Actuator. •• Figure 32-48. NLG Retraction and Lock Actuator. The NLG retraction actuator piston is attached to the top right side of the NLG shock strut. The cylinder itself is attached to the aircraft structure. The nose landing gear retraction actuator has two ports. The rod end of the piston which is installed with bushings and a lubrication fitting. The cylinder end of the actuator which has a ball and race with a lubrication fitting.
1
Figure 32-47. NLG Retraction Actuator 2
FW
D
A
LEGEND 1. NLG Lock Actuator 2. NLG Retraction Actuator. ft130a01.cgm
A
Figure 32-48. NLG Retraction and Lock Actuator
32-52
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
NLG Lock Actuator Refer to Figure 32-49. NLG Lock Actuator. The lock actuator is installed between the airframe fitting and the drag strut pivot tube near the lock links. The NLG Lock Actuator unlocks the drag strut lock links.
NLG Inline Restrictors Refer to Figure 32-50. NLG Inline Restrictor. Two inline restrictors are installed in the tee fittings between the mechanical sequence valve and the retraction actuator. The inline restrictors are two-way fluid fittings that restrict hydraulic flow but not pressure. Figure 32-49. NLG Lock Actuator
Tee Fitting (REF)
FWD
Inline Restrictors
A
Figure 32-50. NLG Inline Restrictor
FOR TRAINING PURPOSES ONLY
32-53
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
MAIN INSTRUMENT PANEL B
OVERHEAD CONSOLE
L. DOOR
N. DOOR R. DOOR
LEFT
NOSE
RIGHT RIGHT
LEFT
NOSE
RIGHT RIGHT LDG GEAR INOP
LANDING GEAR
LANDING GEA R
DN
UP B
LOCK RELEASE
HORN MUTE
TEST
A
Figure 32-51. Landing Gear - Controls and Indications
32-54
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-51. Landing Gear - Controls and Indications. The PSEU controls the sequencing logic for the RCS and indications. The Landing Gear Control Panel indicator lights are as follows: •• LEFT, NOSE, RIGHT green lights indicate the gear is down and locked •• L E F T , N O S E , R I G H T r e d l i g h t s indicate the gear is not locked up, or locked down (Transit) •• L DOOR, N DOOR, R DOOR amber lights indicate landing gear doors not closed. An alternate downlock indication system is available. The green indicator lights (One for each landing gear) indicate a down and locked condition. These lights are installed in the flight compartment floor, under the ALTERNATE EXTENSION door. A fault in the landing gear RCS causes the LDG GEAR INOP caution light on the CAWP to illuminate.
Fault Isolation The CAWP shows the LDG GEAR INOP on when the: •• Proximity sensor electronic unit (PSEU) landing gear control has failed •• Landing Gear Inhibit Switch is not stowed correctly in its normal position. For details see the related fault message on the PSEU face panel.
FOR TRAINING PURPOSES ONLY
32-55
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
MAINTENANCE PRACTICES If gear retraction and extension is required, then make sure: •• That the lower cowl is in the closed position, it is recommended that you close the lower cowl to make sure that it is not damaged during landing gear movement.
NOTE If it is necessary for the lower cowl to be open for other maintenance, you can also remove the lower cowl if it cannot be closed. •• That the fuel tank access-panels are installed. Movement of the landing gear with these panels removed is not permitted. •• To disengage the nose gear ground lock. •• To remove the main landing gear lock pins. •• That the controls in the flight compartment are set as follows: °° The landing-gear selector is in the DN position °° The landing-gear inhibit switch is in the NORMAL position °° The nosewheel steering control is in the NEUTRAL position and the selector switch is in the OFF position °° The FLAPS selector lever to the 0° position °° The POWER levers are at or above the FLT IDLE position.
32-56
WARNING MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE LANDING GEAR AND THE AREA OF DOOR MOVEMENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. To retract the nlg only: •• Open and lock the landing gear doors. •• Install the main landing gear lock pins. •• Engage the nose landing gear ground lock. •• Lift the aircraft at the jacking point near the fuselage, nose only. •• Disengage the nose gear ground lock. •• Disconnect the main landing gear downlock actuator from the forward lock link assembly. •• Secure the downlock actuator to make sure the actuator piston does not make contact with attaching structure or doors during the retraction or extension. •• Install MLG WOW proximity sensor (copper) test target to simulate a target FAR (air) state.
WARNING DO NOT LIFT THE AIRCRAFT ON JACKS IF YOU THINK THE LOAD AT THE NOSEFUSELAGE JACKING POINT WILL BE 4,700 LB (2,132 KG) OR MORE. IF YOU DO, YOU CAN CAUSE DAMAGE TO THE AIRCRAFT STRUCTURE. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT.
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
32-57
32 LANDING GEAR
32-58 SOLENOID A (DOWN)
FROM POWER TRANSFER UNIT
ENERGIZED SOLENOID B (UP)
LEGEND PRESSURE No.2 HYD RETRACT PRESSURE
NO. 2 HYD
LANDING GEAR BYPASS VALVE
RESTRICTOR
DOWN UP
CLOSE
OPEN NOSE DOOR ACTUATOR
TO LEFT MAIN GEAR
ENERGIZED SOLENOID SEQUENCE VALVE
MECHANICAL SEQUENCE VALVE
CLOSE LOCK RELEASE
OPEN MECHANICAL SEQUENCE VALVE
NOSE GEAR RETRACTION ACTUATOR UP
REAR DOOR ACTUATOR
ENERGIZED SOLENOID SEQUENCE VALVE
UPLOCK ACTUATOR
MAIN GEAR RETRACTION ACTUATOR DOWN UP
AUXILIARY ACTUATOR
DOWNLOCK ACTUATOR
DOWN
LOCK ACTUATOR UPLOCK DOWNLOCK RELEASE RELEASE
LOCK RELEASE RIGHT MAIN GEAR
Figure 32-52. (32-31-00) UP Selection Doors Open
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
PRESSURE
CHECK VALVE LANDING GEAR SELECTOR VALVE
DASH 8 Q400
RETURN PRESSURE
(UP SOLENOID ENERGIZED)
TO NOSEWHEEL STEERING SYSTEM
MAINTENANCE TRAINING MANUAL
32-31-00 PRIMARY EXTENSION AND RETRACTION OPERATION Normal System Operation Refer to:
•• MLG wheel well door actuators close aft doors. When MLG wheel well doors are approximately 7% closed the mechanical sequence valve is closed •• Landing gear selector valve UP solenoid is de-energized by PSEU when the associated proximity sensors indicate that all landing gear are up and locked, and all wheel well doors are closed (following a 10 second delay).
•• Figure 32-52. ( 32-31-00) UP Selection Doors Open. •• Figure 32-53. ( 32-31-00) Gear UP and Doors Locked Closed.
MLG Retraction Sequence The main landing gear retraction sequence is as follows: •• L A N D I N G G E A R l o c k r e l e a s e d , selector lever is moved to UP position •• L a n d i n g g e a r s e l e c t o r v a l v e D N solenoid is de-energized and UP solenoid is energized. (Retraction circuit is pressurized) •• MLG solenoid sequence valves remains energized by PSEU from end of extension cycle •• MLG wheel well door actuators open aft doors •• M L G s t a b i l i z e r b r a c e o v e r c e n t e r downlocks are released •• MLG begin to retract slowly through inline restrictors •• W h e n M L G w h e e l d o o r s a r e approximately 93% open, the mechanical sequence valve is opened and the MLG retracts at full rate •• MLG engages uplocks •• MLG solenoid sequence valves are de-energized by PSEU when the uplock proximity sensors indicate that the MLG are up and locked
FOR TRAINING PURPOSES ONLY
32-59
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-60 SOLENOID A (DOWN)
FROM POWER TRANSFER UNIT
SOLENOID B (UP)
LEGEND PRESSURE NO.2 HYD NO.2 HYD
RETURN PRESSURE
RESTRICTOR
DOWN UP
CLOSE OPEN
NOSE DOOR ACTUATOR
TO LEFT MAIN GEAR
SOLENOID SEQUENCE VALVE
MECHANICAL SEQUENCE VALVE
MAIN GEAR RETRACTION ACTUATOR
CLOSE
LOCK RELEASE
OPEN MECHANICAL SEQUENCE VALVE
NOSE GEAR RETRACTION ACTUATOR UP DOWN
REAR DOOR ACTUATOR
SOLENOID SEQUENCE VALVE
UPLOCK ACTUATOR
DOWNLOCK RELEASE
UP
AUXILIARY ACTUATOR
LOCK RELEASE
LOCK ACTUATOR UPLOCK RELEASE
DOWN
STABILIZER STRUT ACTUATOR
RIGHT MAIN GEAR *ALL SOLENOIDS DE-ENERGIZED
Figure 32-53. (32-31-00) Gear UP and Doors Locked Closed
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
PRESSURE
LANDING GEAR BYPASS VALVE
DASH 8 Q400
CHECK VALVE
GEAR UP AND LOCKED (BOTH SOLENOIDS DE-ENERGIZED)
MAINTENANCE TRAINING MANUAL
NLG Retraction Sequence
32 LANDING GEAR
DASH 8 Q400
NOTES
The nose landing gear retraction sequence is as follows: •• LANDING GEAR selector lever is moved to UP position •• L a n d i n g g e a r s e l e c t o r v a l v e D N solenoid is de-energized and UP solenoid is energized (Retraction circuit is pressurized) •• NLG solenoid sequence valve remains energized by PSEU from end of extension cycle •• NLG wheel well door actuator opens forward doors •• NLG drag strut overcenter downlock is released •• NLG begins to retract slowly through inline restrictors •• When NLG wheel doors are approximately 92% open, the mechanical sequence valve is opened and the NLG retracts at full rate NLG drag strut overcenter uplock is energized •• N L G s o l e n o i d s e q u e n c e v a l v e i s de-energized by PSEU when the NGDN and NGLK proximity sensors indicate that the NLG is up and locked •• NLG wheel well door actuator closes forward doors. When NLG wheel well doors are approximately 8% closed the mechanical sequence valve is closed •• Landing gear selector valve UP solenoid is de-energized by PSEU when the associated proximity sensors indicate that all landing gear are up and locked, and all wheel well doors are closed (following a 10 second delay).
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-61
32 LANDING GEAR
32-62 DASH 8 Q400 MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
NOSE WHEEL CENTERED
Figure 32-54. (32-31-00) Landing Gear Retraction (Sheet 1 of 3)
MAINTENANCE TRAINING MANUAL
Landing Gear Retraction
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to: Figure 32-54. (32-31-00) Landing Gear Retraction (Sheet 1 of 3). Before landing gear retraction can start, the PSEU must receive the signals as follows: •• LG control handle is in the RETRACT position •• WOW sensors show that the aircraft is in the air as reported •• LG control is NOT inhibited •• The nosewheel is centered •• The landing gear doors are OPEN. When these conditions are achieved the PSEU de-energizes the EXTEND solenoid and at the same time outputs 28 VDC to Pin L of the LG control panel. Because the LG control handle is in the retract position, the LG selector switch is positioned to output the 28 VDC through Pin R to the RETRACT solenoid of the LG selector valve. Hydraulic pressure through the retract solenoid acts on one end of the hydraulic spool valve. The other end of the hydraulic spool is open to return through the de-energized EXTEND solenoid. The hydraulic spool is moved to the position that allows the hydraulic pressure to be applied to the retract manifold through the bypass valve. At the same time the PSEU energizes the solenoid sequence valves by outputting 28 VDC to each valve, the hydraulic pressure then passes through the valves to the door actuators to open the landing gear doors.
FOR TRAINING PURPOSES ONLY
32-63
32 LANDING GEAR
32-64 J K
K J
LL LL MM MM NN NN
J K GS2
G-
43
LG SAFE
C-
41
NG SAFE
ADVISORY CONTROL UNIT
43
L
L
3C
41
M
M
3E
N
3D
E-
45
45
N
RG NOT SAFE
H-
44
44
P
P
4C
LG NOT SAFE
D-
42
42
R
R
3B
S
NG NOT SAFE
F-
46
46
S
3A
RG DOOR OPEN
D
64
64
T
T
12E
LG DOOR OPEN
F
62
62
U
U
11E
NG DOOR OPEN
E
63
63
V
V
11D
GEAR UNSAFE
A-
47
47
W
W
AFT TOP WING X-OVER
AFT WING ROOT DISC LH
PSEU ATA 32-61
17
X
X
18
Y
Y
U
U
BF
RH U/FLR DISC. X=-18. GS3
FWD WING ROOT DISC RH
R
DE-
R
J-
Z
Z
E40
28VDC CHASSIS
PT-
HORN MUTE SWITCH
V W
HORN TEST
X B-
UP LANDING GEAR CONTROL HANDLE DOWN
A B P R L H
GS7 GS6 GS5
GS4
9A
50
9B
49
5A
A-
A-
B-
B-
68
MAINTENANCE PANEL
C-
C-
65
D-
D-
EFG-
EFG-
WARDROBE
E41
31-41-00 P1A 10J
GS8 GS9
FWD WING ROOT DISC LH
E45 P1B
P1B
E42
10H 1G
DOOR SEQUENCE VALVE
DE-
5E
RETRACT
1F E43
F. D. ABV POWER LEVERS
UPR LHS DISC X=60
1H 5H
A B C
RIGHT LG BAY
E44
2A
FLT. DECK ABV/FLOOR RH 28VDC
L/G SELECTOR VALVE
BF
1K
P1C
A C B
RIGHT WING ROOT
10C
LAMP TEST 1 LAMP TEST 2
A B C
EXTEND
CO-PILOT BLKHD DISC.
Figure 32-55. (32-31-00) Landing Gear Retraction (Sheet 2 of 3)
A B C
DOOR SEQUENCE VALVE LEFT LG BAY
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RG SAFE
A B C
DASH 8 Q400
LANDING GEAR CONTROL AND INDICATION PANEL
MAINTENANCE TRAINING MANUAL
Refer to Figure 32-55. (32-31-00) Landing Gear Retraction (Sheet 2 of 3).
32 LANDING GEAR
DASH 8 Q400
NOTES
The PSEU outputs 28 VDC through Pins 12E, 11D and 11E to the LG Control and Indication Panel to bring on the door OPEN amber lights. Hydraulic pressure is applied through a restrictor to the MLG downlock actuator, the actuator retracts and unlocks the overcenter lock in the stabilizer brace assembly. Pressure is also applied to the NLG lock release actuator to unlock the overcenter lock condition of the upper and lower drag strut assemblies. The PSEU outputs 28 VDC through the advisory control unit for the following: •• MLG unsafe red lights through Pin 4C and Pin 3B to Pins H and D •• NLG unsafe red light through Pin 3A to Pin F •• Light in the control handle through Pin 2A to Pin A on the LG Control and Indication Panel. Before the doors are 93% open, the only pressure going to the retraction actuators passes through the inline restrictors. When the doors are approximately 93% open, the mechanical sequence valve is opened by operation of the door operating mechanism. This allows hydraulic pressure and flow to bypass the inline restrictors, going directly to the retraction actuators. The full on restrictors of the landing gear actuators control the speed of retraction.
FOR TRAINING PURPOSES ONLY
32-65
32 LANDING GEAR
32-66 A
1J
B
NW CENTRED
S04
S18
B
12J
A
12K
D E
B
RIGHT GEAR UP LOCK
PROXIMITY SENSOR INPUT (PSC A)
S19 NOSE GEARDRCL S09
13J
NOSE GEARDN1 S11
13K
NOSE GEARLK1 S03 NOSE GEARWOFW1
NOSE GEAR LOCK 2
S12
S10
NOSE GEAR WOW 1
S03
NOSE GEAR DOOR CLOSED
S19
8G
A
8H
B
7J
A
7K
B
7B
A
7A
B
9D
A
9C
B
13D
A
13C
B
12B
A
12A
LGDLK1
S15
NOSE GEAR DOWN 1
S11
S09
S12 NOSE GEARLK2
RIGHT GEAR DOWN LOCK 2
S01 LGWOW1
PROXIMITY SENSOR INPUT (PSC D)
S08 LGDLK2
S17 LGDRCL S02 LGWOW2
RIGHT WEIGHT-ON WHEELS 2
S13 RGDLK1
28 V DC/OC DISCRETE OUTPUT (PSC A)
DOOR SEQUENCE VALVE
J/P51 A
S16 RGUPLK
S05 RGWOW1
S20 RGDRCL
S06 RGWOW2
LEFT WEIGHT-ON WHEELS 2
LEFT GEAR DOWN LOCK 2
B
DOOR SEQUENCE VALVE
LEFT GEAR DOWN LOCK 1 LEFT GEAR UP LOCK
1H
9B 9A
B
8J
S14
A
8K
PROXIMITY SENSOR INPUT (PSC B)
S06
S13
S05
B
13G
A
13H
B
13B
A
13A
F
8D
G
8C
PROXIMITY SENSOR INPUT (PSC A)
PROXIMITY SENSOR INPUT (PSC D)
PROXIMITY SENSOR INPUT (PSC E)
RGDLK2
LEFT GEAR DOOR CLOSED
1K
B
B A
PROXIMITY SENSOR INPUT (PSC D)
S14
LEFT WEIGHT-ON WHEELS 1 J/P52 A
14A
S04 NOSE GEARWOFW2
RIGHT WEIGHT-ON WHEELS 1
LGUPLK
NOSE GEAR LOCK 1
S10 NOSE GEARDN2
RIGHT GEAR DOWN LOCK 1
S07
14B
NW
PROXIMITY SENSOR INPUT (PSC B)
PROXIMITY SENSOR INPUT (PSC E)
S20
B A
S02
S08
S01
S17
S07
S15
32-61 A1 PROXIMITY SENSOR ELECTRONIC UNIT (PSEU)
Figure 32-56. (32-31-00) Landing Gear Retraction (Sheet 3 of 3)
B
12G
A
12H
B
7G
A
7H
F
7D
G
7C
B
8B
A
8A
B
12D
A
12C
B
14D
A
14C
PROXIMITY SENSOR INPUT (PSC A)
PROXIMITY SENSOR INPUT (PSC E)
PROXIMITY SENSOR INPUT (PSC E)
PROXIMITY SENSOR INPUT (PSC B)
PROXIMITY SENSOR INPUT (PSC D)
32-61 A1 PROXIMITY SENSOR ELECTRONIC UNIT (PSEU)
B
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
NOSE GEAR DOWN 2
B
RIGHT GEAR DOOR CLOSED
S18
S16
DASH 8 Q400
NOSE GEAR WOW 2
28 V DC/OC DISCRETE OUTPUT (PSC A)
MAINTENANCE TRAINING MANUAL
Refer to Figure 32-56. (32-31-00) Landing Gear Retraction (Sheet 3 of 3).
32 LANDING GEAR
DASH 8 Q400
NOTES
When the PSEU gets all the signals listed below: •• RMG uplock sensor at Pin D14A and D14B •• LMG uplock sensor at Pin D14C and D14D •• NG lock 1 at Pins D13C and D13D •• NG lock 2 at Pins B8G and B8H • • The solenoid sequence valves are de-energized. Hydraulic pressure will now be supplied to the close side of the door actuators closing the doors. When the PSEU gets all the signals that follow: •• RMG Door Closed at Pins B9A and B9B •• LMG Door Closed at Pins B8A and B8B •• NG Door Closed at Pins E9C and E9D. The RETRACT solenoid in the LG selector valve is de-energized and the door OPEN amber lights extinguish. The hydraulic pressure is released from the end of the hydraulic spool through the de-energized RETRACT solenoid and, the spool is centralized by the springs. All hydraulic pressure to the landing gear retraction system is removed and both sides of all actuators in the system are open to return.
FOR TRAINING PURPOSES ONLY
32-67
32 LANDING GEAR
32-68 ENERGIZED SOLENOID A (DOWN)
FROM POWER TRANSFER UNIT
SOLENOID B (UP)
LEGEND SYSTEM INPUT PRESSURE EXTEND PRESSURE
NO.2 HYD
CHECK VALVE
LANDING GEAR SELECTOR VALVE (DOWN SOLENOID ENERGIZED)
RESTRICTOR
DOWN UP
CLOSE
OPEN NOSE DOOR ACTUATOR
TO LEFT MAIN GEAR
MECHANICAL SEQUENCE VALVE DE-ENERGIZED SOLENOID SEQUENCE VALVE
MAIN GEAR RETRACTION ACTUATOR
CLOSE
LOCK RELEASE
OPEN MECHANICAL SEQUENCE VALVE
REAR DOOR ACTUATOR NOSE GEAR RETRACTION ACTUATOR
DE-ENERGIZED SOLENOID SEQUENCE VALVE
UPLOCK ACTUATOR
DOWN
AUXILIARY ACTUATOR
UP DOWN
UPLOCK RELEASE
UP
DOWNLOCK ACTUATOR LOCK RELEASE
LOCK ACTUATOR DOWNLOCK RELEASE
RIGHT MAIN GEAR
Figure 32-57. Initial DOWN Selection Doors Opening
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
LANDING GEAR BYPASS VALVE
DASH 8 Q400
TO NOSEWHEEL STEERING SYSTEM
RETURN PRESSURE
MAINTENANCE TRAINING MANUAL
Main Landing Gear Extension
Nose Landing Gear Extension
Refer to:
The nose landing gear extension sequence is as follows:
•• Figure 32-57. I nitial DOWN Selection Doors Opening. •• Figure 32-58. Selection Completed Doors Closed. The main landing gear extension sequence is as follows: •• LANDING GEAR selector lever is moved to DN position •• Landing gear selector valve DN solenoid is energized by PSEU (Normal extension circuit is pressurized) •• MLG solenoid sequence valves remains de-energized by PSEU from end of retraction cycle
•• LANDING GEAR selector lever is moved to DN position •• L a n d i n g g e a r s e l e c t o r v a l v e D N solenoid is energized by PSEU (Normal extension circuit is pressurized) •• NLG solenoid sequence valves remains de-energized by PSEU from end of retraction cycle •• NLG wheel well door actuator opens forward doors •• NLG drag strut over-center uplock is released •• NLG begins to extend slowly through in-line restrictors
•• MLG uplocks are released
•• When NLG wheel doors are approximately 92% open, the mechanical sequence valve is opened and the NLG extends at full rate
•• MLG begin to extend slowly through in-line restrictors
•• NLG drag strut over-center downlock is engaged
•• W h e n M L G w h e e l d o o r s a r e approximately 93% open, the mechanical sequence valve is opened and the MLG extends at full rate
•• N L G s o l e n o i d s e q u e n c e v a l v e i s energized by PSEU when the NGDN and NGLK proximity sensors indicate that the NLG is down and locked
•• MLG stabilizer brace over-center downlocks are engaged
•• NLG wheel well door actuator closes forward doors. When NLG wheel well doors are approximately 8% closed, the mechanical sequence valve is closed
•• MLG wheel well door actuators open aft doors
•• MLG solenoid sequence valves are energized by PSEU when the stabilizer brace proximity sensors indicate that the MLG are down and locked •• MLG wheel well door actuators close aft doors. When MLG wheel well doors are approximately 7% closed the mechanical sequence valve is closed
•• L a n d i n g g e a r s e l e c t o r v a l v e D N solenoid, MLG solenoid sequence valve, and NLG solenoid sequence valve remain energized by PSEU after extension is complete.
•• L a n d i n g g e a r s e l e c t o r v a l v e D N solenoid, MLG solenoid sequence valve, and NLG solenoid sequence valve remain energized by PSEU after extension is complete.
FOR TRAINING PURPOSES ONLY
32-69
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-70 ENERGIZED SOLENOID A (DOWN)
SOLENOID B (UP)
FROM POWER TRANSFER UNIT
LEGEND PRESSURE SYSTEM EXTEND PRESSURE
NO.2 HYD
CHECK VALVE
LANDING GEAR SELECTOR VALVE (DOWN SOLENOID ENERGIZED) LANDING GEAR BYPASS VALVE
RESTRICTOR
DOWN UP
CLOSE TO LEFT MAIN GEAR
OPEN NOSE DOOR ACTUATOR
ENERGIZED SOLENOID SEQUENCE VALVE
MECHANICAL SEQUENCE VALVE
MAIN GEAR RETRACTION ACTUATOR
CLOSE
LOCK RELEASE
OPEN MECHANICAL SEQUENCE VALVE NOSE GEAR RETRACTION ACTUATOR
REAR DOOR ACTUATOR
ENERGIZED SOLENOID SEQUENCE VALVE
UPLOCK ACTUATOR
DOWN
AUXILIARY ACTUATOR
DOWNLOCK ACTUATOR
UP DOWN
LOCK ACTUATOR UPLOCK DOWNLOCK RELEASE RELEASE
UP
LOCK RELEASE
* ALL SOLENOIDS ENERGIZED
Figure 32-58. Selection Completed Doors Closed
RIGHT MAIN GEAR
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
TO NOSEWHEEL STEERING SYSTEM
RETURN PRESSURE
MAINTENANCE TRAINING MANUAL
Landing Gear Normal Extension
32 LANDING GEAR
DASH 8 Q400
NOTES
Before the landing gear normal extension can start, the PSEU must receive the signals that follow: •• EXTCMD discrete input on Pin A10H •• No LDGINH signal at Pin A10K. The PSEU outputs 28 VDC to Pin H of the LG Control and Indication panel. Because the LG control lever is selected, DOWN 28 VDC is output on Pin J to energize the EXTEND solenoid in the LG selector valve. Hydraulic pressure is directed through the EXTEND solenoid to one end of the hydraulic spool, the other end is open to return through the de-energized RETRACT solenoid. The hydraulic spool is positioned to supply hydraulic pressure directly to the EXTEND manifold. The pressure is supplied through the de-energized solenoid sequence valves to the retract side of the door actuators to OPEN the hydraulically operated doors. Pressure is also supplied to the following: •• The extend side of the MLG uplock actuators to release the uplock •• The extend side of the NLG lock release actuator to unlock the overcenter lock in the upper and lower drag strut assembly •• Through the inline restrictors to the retraction/extension actuators. The PSEU outputs 28 VDC through the Advisory Control Unit for the following: •• The MLG unsafe red lights through Pin 4C and Pin 3B to Pins H and D •• NLG unsafe red light through Pin 3A to Pin F •• The light in the control handle through Pin 2A to Pin A on the LG Control and Indication Panel.
FOR TRAINING PURPOSES ONLY
32-71
32 LANDING GEAR
32-72 A
NOSE GEAR DOOR SEQUENCE VALVE
NW CENTRED
S04
S18
B
12J
A
12K
D E
28 V DC/OC DISCRETE OUTPUT (PSC A)
B
RIGHT GEAR UP LOCK
PROXIMITY SENSOR INPUT (PSC A)
S19 NOSE GEARDRCL S09
13J
NOSE GEARDN1 S11
13K
NOSE GEARLK1 S03 NOSE GEARWOFW1
NOSE GEAR LOCK 2
S12
S10
NOSE GEAR WOW 1
S03
NOSE GEAR DOOR CLOSED
S19
8G 8H
B
7J
A
7K
B
7B
A
7A
B
9D
A
9C
B
13D
A
13C
NOSE GEAR DOWN 1
B
12B
S09
A
12A
NOSE GEARDN2 S12 NOSE GEARLK2
RIGHT GEAR DOWN LOCK 2
S07 LGDLK1
S01 LGWOW1
PROXIMITY SENSOR INPUT (PSC D)
S08 LGDLK2
S17 LGDRCL S02 LGWOW2
RIGHT WEIGHT-ON WHEELS 2
S13
A
RGDLK1
28 V DC/OC DISCRETE OUTPUT (PSC A)
DOOR SEQUENCE VALVE
A
S16 RGUPLK
S05 RGWOW1
S20 RGDRCL
S06 RGWOW2
LEFT WEIGHT-ON WHEELS 2
LEFT GEAR DOWN LOCK 2
B
DOOR SEQUENCE VALVE
LEFT GEAR DOWN LOCK 1 LEFT GEAR UP LOCK
1H
9B 9A
S14
B
8J
A
8K
PROXIMITY SENSOR INPUT (PSC B)
S06
S13
S05
B
13G
A
13H
B
13B
A
13A
F
8D
G
8C
PROXIMITY SENSOR INPUT (PSC A)
PROXIMITY SENSOR INPUT (PSC D)
PROXIMITY SENSOR INPUT (PSC E)
RGDLK2
LEFT GEAR DOOR CLOSED
1K
B A
PROXIMITY SENSOR INPUT (PSC D)
S14
LEFT WEIGHT-ON WHEELS 1
B
14A
S04 NOSE GEARWOFW2
RIGHT GEAR DOWN LOCK 1
S15
S11
S10
RIGHT WEIGHT-ON WHEELS 1 PROXIMITY SENSOR INPUT (PSC E)
S20
14B
NWCENT
PROXIMITY SENSOR INPUT (PSC B)
LGUPLK
NOSE GEAR LOCK 1
S18
B A
32-61 A1 PROXIMITY SENSOR ELECTRONIC UNIT (PSEU)
Figure 32-59. (32-31-00) Landing Gear Normal Extension
S02
S08
S01
S17
S07
S15
B
12G
A
12H
B
7G
A
7H
F
7D
G
7C
B
8B
A
8A
B
12D
A
12C
B
14D
A
14C
PROXIMITY SENSOR INPUT (PSC A)
PROXIMITY SENSOR INPUT (PSC E)
PROXIMITY SENSOR INPUT (PSC E)
PROXIMITY SENSOR INPUT (PSC B)
PROXIMITY SENSOR INPUT (PSC D)
32-61 A1 PROXIMITY SENSOR ELECTRONIC UNIT (PSEU)
B
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
NOSE GEAR DOWN 2
B A
RIGHT GEAR DOOR CLOSED
S16
DASH 8 Q400
NOSE GEAR WOW 2
1J
B
MAINTENANCE TRAINING MANUAL
Refer to Figure 32-59. (32-31-00) Landing Gear Normal Extension. When the doors are approximately 93% open, full hydraulic pressure and flow is supplied to the actuators to extend the gear. When the main gear is down and locked, the PSEU receives signals from the MLG sensors that follow:
The mechanical sequence valves are closed by the action of the door operating mechanism and pressure is maintained to the landing actuators and lock actuators through the inline restrictors. The EXTEND solenoid and the solenoid selector valves remain energized.
•• RMG Downlock 1 on Pins E8C and E8D •• RMG Downlock 2 on Pins B8J and B8K •• LMG Downlock 1 on Pins D12C and D12D •• LMG Downlock 2 on Pins E7G and E7H. When the nose gear is down and locked, the PSEU receives signals from the NLG that follow: •• NG Down 1 on Pins D12A and D12B •• NG Lock 1 on Pins D13C and D13D •• NG Down 2 on Pins B7J and B7K •• NG Lock 2 on Pins B8G and B8H. When the PSEU has received the down and locked signals from the LG sensors, it energizes the solenoid sequence valves. Hydraulic pressure is supplied to the extend side of the door actuators closing the doors. The PSEU receives the following signals from the door sensors: •• RG Door Closed on Pins B9A and B9B •• LG Door Closed on Pins B8A and B8B •• NG Door Closed on Pins E9C and E9D. The PSEU turns OFF the amber door lights on the LG control and indication panel.
FOR TRAINING PURPOSES ONLY
32-73
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-74
BY PASS
A
MAIN L/G RELEASE
MAIN DOOR UPLOCK RELEASE
PULL FULLY DOWN
CAUTION ENSURE ALL WHEEL WELLS ARE CLEAR OF OBSTRUCTIONS BEFORE CLOSING ACCESS PANEL TO CLOSE DUMP VALVE.
NOSE DOOR UPLOCK RELEASE A
LEGEND CABLE CIRCUIT CONTROL LINKAGE HYDRAULIC PRESSURE
TO MAIN GEAR AUXILIARY ACTUATORS
LANDING GEAR ALTERNATE RELEASE DOOR (OPEN)
HAND PUMP B
LANDING GEAR ALTERNATE EXTENSION DOOR (OPEN)
fsr81a01.cgm
Figure 32-60. Alternate Extension System Block Diagram
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
B
DASH 8 Q400
MAIN GEAR UPLOCK RELEASE
NOSE GEAR UPLOCK RELEASE
VALVE
MAINTENANCE TRAINING MANUAL
32-34-00 ALTERNATE EXTENSION SYSTEM
32 LANDING GEAR
DASH 8 Q400
NOTES
INTRODUCTION The alternate extension system is used to extend the landing gear when the No.2 hydraulic system or the PSEU is not serviceable. The system can also be used, if the normal extension system fails to lock the landing gear in the down position. The system is also used to open the landing gear doors for service or maintenance.
GENERAL Refer to Figure 32-60. Alternate Extension System Block Diagram. The alternate extension system is a self resetting, cable actuated design. Access to controls for the alternate extension system is through the flight compartment. The alternate extension system includes a bypass valve to isolate the landing gear hydraulics from the No.2 hydraulic system. A manual hand pump hydraulic system is available to assist in lowering the main landing gear (only) into the down and locked position. The landing gear inhibit switch isolates the PSEU from the landing gear selector output when it is selected to the INHIBIT position. The alternate extension system has the listed components: •• Alternate release handles (2) •• Alternate release door •• Alternate extension door •• Alternate extension actuators (2) •• Bypass valve and •• Control cables.
FOR TRAINING PURPOSES ONLY
32-75
32 LANDING GEAR
32-76 HAND PUMP
A
FW
D
A
LANDING GEAR ALTERNATE EXTENSION DOOR (OPEN)
NOTE Left Gear shown. Right Gear similar. EMERGENCY SELECTOR VALVE (CLOSED POSITION)
MLG STABILIZER BRACE ASSEMBLY LEGEND
SUCTION LINE PRESSURE LINE fsr82a01a.cgm
Figure 32-61. Alternate Extension Hydraulic Synoptic
LOWER RIGHT NOSE COMPARTMENT
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
AUXILIARY ACTUATOR
DASH 8 Q400
EMERGENCY HYDRAULIC RESERVOIR 1.25 U.S. QUARTS (1.2 LITRES)
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-61. Alternate Extension Hydraulic Synoptic. The hand pump is located below the flight compartment floor, adjacent to the co-pilot seat. The hand pump is used to lower the landing gear following hydraulic system 2 isolation. A hand pump handle is installed in the flight compartment on the bulkhead behind the co-pilot seat. The handle must be installed into the pump to operate the pump. The MLG extension selector valve is located below the flight compartment floor adjacent to the co-pilot seat. The valve has a 2-way, 2-position control valve, a pressure relief valve, and a filtered inlet and return port. There is a pivoting link that attaches the selector valve to the hand pump access door. The selector valve moves from the normally open position to the closed position when the access door is opened. The pressure relief valve limits the pressure that may be applied to the alternate gear down actuators by relieving the hand pump pressure. The alternate landing gear extension hydraulic reservoir is located in the nose compartment of the aircraft. This reservoir is made from aluminum and has a capacity of 1 US qt (0.95 L). The reservoir has a threaded, vented, removable lid which has three fittings installed. One fitting serves as a fill port; the second fitting is the vent, and the third fitting is the outlet port to the hand pump. The lid also has a dipstick with minimum and maximum volume markings to allow filling of the reservoir to the correct fluid level.
FOR TRAINING PURPOSES ONLY
32-77
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Dust Cap Dipstick
Fill Connection
SAFE
Reservoir
Figure 32-62. Servicing of the Auxiliary System Hydraulic Reservoir
32-78
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Servicing of the Alternate LandingGear Extension Hydraulic Reservoir
32 LANDING GEAR
DASH 8 Q400
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 32-62. Servicing of the Auxiliary System Hydraulic Reservoir. The auxiliary reservoir is for the emergency extension of the main landing gear. It is installed in the bottom right side of the nose compartment. •• Remove the dipstick to check the fluid quantity level. •• If the fluid level is below the SAFE mark, fill the reservoir to the SAFE mark. •• Replace the dipstick in the reservoir. •• Remove the dust cap from the fill connection. •• Connect the quick-disconnect coupling of the fluid dispenser to the fill connection. •• Fill the auxiliary reservoir up to the SAFE mark on the dipstick. •• Replace the dipstick. •• Disconnect the coupling of the fluid dispenser and replace the dust cap. •• Clean the area with the lint free cloth.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-79
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Main Gear Alternate Release Handle Refer to Figure 32-63. Main Gear Alternate Release Handle. The alternate release handle is located in the ceiling of the flight compartment behind the LANDING GEAR ALTERNATE RELEASE door. The handle is connected to the MLG uplocks and the MLG aft doors release mechanisms. A cam mechanism makes sure that the MLG aft doors open before the MLG uplocks release the MLG.
2
3
4
1
5
LEGEND 1. Door Compression Spring 2. Main Gear Alternate Release Handle 3. Cables to Slide Assembly 4. Cables to Bypass Valve 5. Door Pulley 6. Landing Gear Alternate Release Door 7. Landing Gear Inhibit Toggle Switch.
CAUTION ENSURE ALL WHEEL WELLS ARE CLEAR OF OBSTRUCTIONS
BEFORE CLOSING ACCESS PANEL TO CLOSE DUMP VALVE
6
INHIBIT NORMAL
Figure 32-63. Main Gear Alternate Release Handle
32-80
FOR TRAINING PURPOSES ONLY
7
MAINTENANCE TRAINING MANUAL
Nose Gear Alternate Release Handle Refer to Figure 32-64. NLG Alternate Release Handle. The NLG alternate release handle is located in the floor of the flight compartment under the LANDING GEAR ALTERNATE EXTENSION door.
The pulley cam mechanism makes sure that the NLG forward doors open before the NLG uplock is opened to release the NLG. After the alternate release handle has been pulled, gravity and the airstream force the NLG to the down position, the gear locks by the overcenter mechanism of the upper, and lower drag struts.
The handle is connected by cables, turnbuckles and pulleys to the NLG uplock release arm, pulley cam mechanism and to the NLG door release operating arm.
1 A
LEGEND 1. Landing Gear Alternate Extension Door 2. Landing Gear Downlock Verification Lights 3. Landing Gear Downlock Verification Switch 4. Landing Gear Alternate Extend Hand Pump 5. MLG Alternate Extension Actuator Bypass Valve 6. Nose Gear Alternate Release Handle.
6
5
FWD
4
2 A 3
Figure 32-64. NLG Alternate Release Handle
FOR TRAINING PURPOSES ONLY
32-81
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Alternate Extension Actuator Refer to Figure 32-65. Alternate Extension Actuator. The alternate extension actuators are installed in the MLG wheel wells between the nacelle structure and the MLG yoke assembly.
The actuator has a single port for extend pressure only. The alternate extension actuators are used to extend the landing gear to the down and locked position.
They are located on the right side of each MLG yoke. The hydraulic pressure required to operate the actuators is supplied by a hand pump located in the flight compartment floor. A
B
FWD
FWD
A
MLG STABILIZER BRACE AND YOKE ASSEMBLY
Figure 32-65. Alternate Extension Actuator
32-82
FOR TRAINING PURPOSES ONLY
B
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
Alternate Extension Downlock Indicators and Switch Refer to Figure 32-66. Landing Gear Downlock Verification Switch. The alternate extension downlock indicator and switch are installed in a panel located behind the LANDING GEAR ALTERNATE EXTENSION door, in the flight compartment floor. The switch is beside a light panel that contains three green lights. It is a two position, momentary type toggle switch. In the ON position the switch provides a ground to the three alternate down lock lights.
1
A
LEGEND 1. Landing Gear Alternate Extension Door 2. Landing Gear Downlock Verification Lights 3. Landing Gear Downlock Verification Switch.
FWD
2 A
3
Figure 32-66. Landing Gear Downlock Verification Switch
FOR TRAINING PURPOSES ONLY
32-83
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Operating Lever
Pulleys
Bypass Valve
Restrictor
FWD Turnbuckles
Cables From Door Pulley
Figure 32-67. Bypass Valve and Alternate Release Cables
32-84
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Bypass Valve
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-67. Bypass Valve and Alternate Release Cables. The landing gear bypass valve is installed in the forward right wing root area. It is adjacent to the landing gear selector valve. The bypass valve is actuated when the LANDING GEAR ALTERNATE RELEASE door is opened. During alternate extension, the bypass valve isolates the No.2 hydraulic supply lines from the main and nose gear retraction actuators, and connects the pressure lines to the return lines. The union attached to the down port is restricted.
FOR TRAINING PURPOSES ONLY
32-85
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Cable
Cam Mechanism Assembly
Cable
Cable To Uplock Assy
A
Figure 32-68. MLG Alternate Extension System Cam Mechanism Assembly
32-86
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
MLG Alternate Release Control Cables Refer to Figure 32-68. MLG Alternate Extension System Cam Mechanism Assembly. Control cables are routed from the MLG alternate release handle through a slider mechanism, located in the ceiling of the aircraft, forward of the wing root. The slider mechanism lets the full force of the pull be concentrated first on the release of one MLG and then on the other.
•• Release the input lever. Make sure the cam assembly moves smoothly, with no binding or resistance, to its fully rested position •• I f t h e c a m m o v e m e n t i s f u l l a n d unrestricted, no further action is required •• If there is binding or sticking in the cam assembly when you return it to its full rested position, remove the unit and install a new or serviceable unit.
The control cables are then routed through to the engine nacelles to the cam mechanisms. The cam mechanism allows the force of the pull to be concentrated first on the release of the MLG aft doors and then on the MLG uplocks.
Operational Check of the Main Landing Gear Alternate Extension Cam Assembly (MRB#323400-204) The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. The cam assembly is installed on the left side of the nacelle, at approximately Sta. XN 190.524. •• Open and lock the main landing-gear doors •• Use your fingers to move (rotate) the input lever forward, so that the cam assembly is in the fully deployed position
CAUTION Do not pull the alternate release cable to move the cam assembly. This will bend the cable end at the turnbuckle assembly.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-87
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
NLG Alternate Release Control Cables
NOTES
Refer to Figure 32-69. NLG Alternate Release Cable. Control cables are routed from the NLG alternate release handle through a pulley cam mechanism located in the forward fuselage above the nosewheel well. The pulley cam mechanism lets the full force of the pull be concentrated first on the release of the NLG forward doors and then on the NLG uplocks.
3
D
FW A
4
2
LEGEND 1. Front Door Alternate Release Operating Arm and Roller Assembly 2. Pulley Cam Mechanism 3. Nose Gear Alternate Release Handle (Flight Compartment Floor) 4. NLG Uplock Release Arm 5. Pivot Tube (Nose Gear Release) 6. Link Assembly.
5
6
1
A
Figure 32-69. NLG Alternate Release Cable
32-88
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Landing Gear Inhibit Switch Refer to Figure 32-70. Landing Gear Alternate Release - Inhibit Switch. The LANDING GEAR INHIBIT switch is installed in the flight compartment ceiling. The inhibit toggle switch has two positions: INHIBIT and NORMAL. It is guarded to the NORMAL (off) position.
Selecting the switch to the INHIBIT position disables the extension and retraction landing gear control outputs of the PSEU. “LDG INOP” caution light will come on if not already on. This action causes the landing gear selector valve solenoids and all solenoid sequence valves to be de-energized.
A
FWD
FWD
CAUTION
LANDING GEAR
ENSURE ALL WHEEL WELLS ARE CLEAR OF OBSTRUCTIONS BEFORE CLOSING ACCESS PANEL
ALTERNATE RELEASE
TO CLOSE DUMP VALVE
OPEN DOOR FULLY
A
INHIBIT
INHIBIT
NORMAL
NORMAL
DOOR CLOSED
A
DOOR OPEN
Figure 32-70. Landing Gear Alternate Release - Inhibit Switch
FOR TRAINING PURPOSES ONLY
32-89
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Hanger Clip
Lever, Hand-Pump
Figure 32-71. Hydraulic Hand Pump and Hand Pump Lever
32-90
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
29-21-01 HYDRAULIC HAND PUMP
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-71. Hydraulic Hand Pump and Hand Pump Lever. The hand pump is located under the flight compartment floor, near the co-pilot seat. The hand pump is used to extend the main landing gear following isolation, or loss, of the No.2 hydraulic system. The pump draws hydraulic fluid from an auxiliary reservoir located in the nose compartment. Hydraulic fluid pressurizes the alternate landing-gear actuators to extend the main landing gear to the downlock position.
29-21-03 HAND-PUMP LEVER Figure 32-71. Hydraulic Hand Pump and Hand Pump Lever. The hand-pump lever is stowed on the aft bulkhead of the flight compartment, on the co-pilot side with a hanger clip and a rubber stopper on top. The lever is used to operate the Alternate hand pump.
FOR TRAINING PURPOSES ONLY
32-91
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
1 2 1
LEGEND
2
3
13 4
14 5
6 6
7
12
16
8
11
1. Links 2. Washers 3. Cotter Pin 4. Nut 5. Rod End 6. Washers 7. Selector Valve 8. Bracket 9. Hydraulic Line 10. Hydraulic Line 11. Spacers 12. Washers 13. Bolts 14. Bolt. 15. Packing 16. Filter Fitting
15
16 10 9
Figure 32-72. Secondary MLG Selector Valve - Removal and Installation
32-92
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
29-21-06 SECONDARY MLG SELECTOR VALVE
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-72. Secondary MLG Selector Valve - Removal and Installation. The Selector Valve is a 2-way, 2-position control valve located under the flight compartment floor, near the co-pilot seat. The valve has an internal pressure relief and filtered inlet and return ports. There is a pivoting link that attaches the selector valve to the hand pump access door. The selector valve moves from the normally open position to the closed position when the access door is opened. The pressure relief valve limits the pressure that may be applied to the alternate gear down actuators by relieving hand pump pressure to return at 3150 PSI.
FOR TRAINING PURPOSES ONLY
32-93
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
1
A
LEGEND 1. Landing Gear Alternate Extension Door 2. Landing Gear Downlock Verification Lights 3. Landing Gear Downlock Verification Switch.
FWD
2 3
Figure 32-73. LG Downlock Verification Lights - Controls and Indications
32-94
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-73. LG Downlock Verification Lights - Controls and Indications. Below the LANDING GEAR ALTERNATE EXTENSION door is the verification switch and the three green verification lights. An alternate landing gear down and locked verification system is located in the flight compartment, in the aft section of the LANDING GEAR ALTERNATE EXTENSION compartment. The system has a 2-position, momentary type toggle switch, a light panel that contains three green lights, and four proximity sensors. Two of the proximity sensors are used in series and are attached to the NLG. One proximity sensor is installed on each of the MLG. The system components on each landing gear are activated when the downlock verification switch is moved to the ON position. The system indication lights come on as each landing gear is locked down.
FOR TRAINING PURPOSES ONLY
32-95
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
MLG Alternate Extension Control and Inhibit Switch
Proximity Sensor Electronic Unit
NLG Alternate Extension Control amd MLG Hand Pump Landing Gear Selector Lever and Control Panel
Figure 32-74. Landing Gear Extension and Retraction
32-96
FOR TRAINING PURPOSES ONLY
fs571a01.cgm
MAINTENANCE TRAINING MANUAL
OPERATION
The PSEU extinguishes the red lights and illuminates the MLG green safe lights on the control panel.
Alternate Extension Refer to Figure 32-74. Landing Gear Extension and Retraction. The landing gear inhibit switch is set to the inhibit position. A ground is supplied from the switch to the PSEU at Pin A10K. This inhibits Landing Gear Control by Proximity Sensor Card A. Make sure that the LDG GEAR INOP caution light comes on. Open the alternate RELEASE door. The door cable system repositions the bypass valve to open. The open bypass valve causes all of the landing gear actuators to bypass to return. Pulling the alternate release handle operates the cable assembly that unlocks the overcenter lock in the MLG door mechanism. The spring contracts, operating the door mechanism, opening the doors. The PSEU illuminates the MLG door open amber lights on the LG Control and Indication panel.
Pulling upwards on the release handle operates a cable mechanism to unlock the overcenter lock in the NLG door mechanism, allowing the spring to contract, opening the doors. The PSEU will illuminate the door open amber light on the control panel. Pulling the release handle further operates a cable mechanism to a lever in the top of the NLG wheel well. Rotating the lever rotates the pivot tube of the NLG lock system. Rotating the pivot tube unlocks the overcenter lock in the upper and lower lock strut assembly, causing the NLG to free fall to the down and locked position. This is assisted by the airstream and the tension springs in the NLG lock system. The PSEU will illuminate the green NLG safe light on the control panel.
Pulling the alternate release handle to the full down position operates the cable system and mechanically releases the MLG uplocks. The MLG extends by gravity. The PSEU illuminates the MLG unsafe red lights on the control panel. Opening the alternate extension door positions the emergency down selector valve mechanically, and gives access to the hand pump socket. Operating the hand pump supplies hydraulic pressure to the MLG alternate extension actuators. The actuators extend, push on the yoke assemblies ensuring the MLG reaches the down and locked position assisted by the springs of the stabilizer brace assembly. The MLG downlock proximity sensors send target near signals to the PSEU.
FOR TRAINING PURPOSES ONLY
32-97
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
7
MAIN LANDING GEAR
1 2
3 D
FW
4
6
5
A
LEGEND 1. Outer Wheel Half 2. Inner Wheel Half 3. Wheel Insert 4. Heat Shield 5. Bearing Cup (Inner) 6. Performed Packing (Inside) 7. Main Wheel Tires.
fs144a01.cgm
Figure 32-75. Main Wheel and Tire Assembly
32-98
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-41-00 WHEELS GENERAL The wheels support the weight of the aircraft and permit the aircraft to move on the ground. The brakes convert energy necessary to bring the aircraft to a stop.
SYSTEM DESCRIPTION The aircraft has six wheels. Two wheels are installed on the nose landing gear, and two are installed on each main landing gear.
gasket is installed on the outer wheel half for protection. An inflation valve is installed in the outer wheel half. The over inflation plug contains a disk that ruptures, and deflates the tire to zero pressure. Thermal relief plugs are made of fusible metal that melts at a specified temperature. This will release the pressure in the tire and prevent an explosion if the wheel gets too hot. The wheel inserts engage the drive slots in the brake disks. The heatshield decreases the transfer of heat from the brake to the wheel and tire assembly.
Two different wheel assemblies can be used on the main landing gear: •• Main wheel assembly with a 32 × 8.8-16 (227 psi 18 ply) tubeless tire •• Main wheel assembly with a 34×10.75-16 (141 psi 16 ply) tubeless tire. Each nosewheel has a 22×6.50-10 (89 psi 8 ply) tubeless tire.
COMPONENTS DESCRIPTION Main Wheels Refer to Figure 32-75. Main Wheel and Tire Assembly. The main wheels are split type made of forged aluminum wheel halves. The two halves are held together with equally spaced tie bolts, washers, and nuts. A preformed packing is installed on the inner wheel half to prevent air leakage through the wheel mating surfaces. The bearings are lubricated with grease. Bearing seals are installed at the outer surface of the bearings to prevent contamination. A retaining ring holds the outer bearing in place. Grease retainers are installed next to each bearing cup to prevent the flow of grease into the center of the wheel. A hubcap and
FOR TRAINING PURPOSES ONLY
32-99
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
10
8 7
9
6
LEGEND 1. Hub Cap 2. Axle Nut 3. Retaining Ring 4. Outer Bearing Seal 5. Outer Bearing 6. Main Wheel Tire Assembly 7. Inner Bearing 8. Inner Bearing Seal 9. Axle 10. Brake Unit
5 4 3 2 1
NOTE
On aircraft without Modsum 4−126316.
Figure 32-76. Main Wheel and Tire Assembly - Removal and Installation
32-100
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Installation of the Main Wheel and Tire Assembly The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
MLG Axle Bullet Refer to Figure 32-77. MLG Axle Bullet. Used for installation and removal of MLG wheel and brake assembly. Manufactured from aluminum alloy 6061 - T6.
Refer to Figure 32-76. Main Wheel and Tire Assembly - Removal and Installation. •• Visual check for wear damage and cleanliness •• Lubricate bearings, axle and axle nut with grease •• Install axle bullet •• Align wheel inserts with the slots in rotor disks •• Push the wheel on the axle and brake assembly •• Remove axle bullet •• Ensure outer seal is in correct position •• While turning the wheel tighten the axle nut •• Loosen axle nut
Figure 32-77. MLG Axle Bullet
•• While turning the wheel torque the nut to the correct value •• Lock the axle nut •• Engage blade on inside hub cap with clip on wheel speed transducer •• Install hub cap, torque the bolts and lockwire
NOTE Make sure that the drive blade on the hubcap engages with the clip on the wheel speed transducer. •• Apply torque seal on all fasteners •• Fill the tire with nitrogen.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-101
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure 32-78. Nosewheel and Tire Assembly
32-102
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Nosewheels
NOTE
Refer to Figure 32-78. Nosewheel and Tire Assembly. The nosewheels are split type made of forged aluminum wheel halves. The two halves are held together with equally spaced tie bolts, washers, and nuts. A preformed packing is installed on the inner wheel half to prevent air leakage through the wheel mating surfaces. The bearings and cups are lubricated with grease. Bearing seals are installed at the outer surface of the bearings to prevent contamination. A water deflector shield is installed on the inner wheel half assembly to keep water spray away from the bearing seals and bearing. A hubcap and gasket are installed on the outer wheel for protection. An inflation valve is installed in the outer wheel half assembly. An over-inflation plug is installed in the outer wheel half assembly to prevent over-inflation of the tire. The plug contains a disk that ruptures, and deflates the tire to zero pressure.
Installation of the Nosewheel and Tire Assembly The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Do a visual check of the axle for signs of wear and damage.
Install the water shield so that the words THIS SIDE OUT point at the nosewheel strut. •• Carefully put the nosewheel and tire assembly on the axle. •• Install the outer bearing and seal on the axle. Push the outer bearing and seal into the outer side of the nosewheel and tire assembly. •• Lubricate the threads of the axle nut and the axle with grease. •• Install the axle nut on the axle. •• Turn the nosewheel and tire assembly. At the same time, torque the axle nut.
NOTE Turn the nosewheel and tire assembly in the direction that the axle nut is tightened. •• Loosen the axle nut to zero torque. •• Turn the nosewheel and tire assembly. At the same time, re-torque the axle nut. •• If the locking holes are not aligned, tighten the axle nut to the nearest locking hole.
NOTE Turn the nosewheel and tire assembly in the direction that the axle nut is tightened. •• Put the washers on the bolts. Install the bolts through the holes in the axle nut and the axle.
•• Put a layer of wheel bearing grease on the bearing cups.
•• Install the ball seat washers and the nuts on the bolt. Torque the nuts. Safety the nuts.
•• Lubricate the bearings and seals.
•• Apply torque seal to all fasteners.
•• Install the inner bearing, the inner bearing seal, and the water shield in the inner side of the nosewheel and tire assembly.
•• Install the hubcap.
Revision 0.4
•• Torque the screws and apply torque seal.
FOR TRAINING PURPOSES ONLY
32-103
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND 1. Fill Valve Gauge 2. Valve Cap 3. O-ring.
B 3 A 1
2
A B
Figure 32-79. Fill Valve Gauge
32-104
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Fill Valve Gauge (Optional)
Tire Wear
Refer to Figure 32-79. Fill Valve Gauge.
It is acceptable to continue operations for an additional 8 landings after the tire reinforcement cord first becomes visible in the tread area.
The fill valve gauge is installed on each wheel assembly. The fill valve gauge has a built in tire pressure indicator. The tire pressure can be read directly from the analog dial type indicator.
Operating with worn tires to this extended wear allowance may result in the tire casing becoming non-retreadable.
The function of the fill valve gauge is to give the tire pressure indication directly from the wheel assembly.
NOTE The fill valve gauge is installed on Aircraft with Modsum - MS 4-900220. Inflate the tires with nitrogen to the correct pressure with a servicing kit that includes a low pressure regulator.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-105
32 LANDING GEAR
DASH 8 Q400
32-106
DASH 8 Q400 MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
Figure 32-80. Brakes System Hydraulic Synoptic
32 LANDING GEAR
MAINTENANCE TRAINING MANUAL
32-42-00 MAIN LANDING GEAR BRAKE SYSTEM
32 LANDING GEAR
DASH 8 Q400
NOTES
INTRODUCTION The brake system is used to decrease the aircraft speed during ground operations.
GENERAL The MLG brake system is controlled by the pilot’s and co-pilot’s brake pedals. The brake system has the following components: •• Pilot and Co-pilot brake pedals •• Brake control cables •• Brake control valve •• Brake pressure transducer •• Fuse/shuttle valves and •• Main wheel brake units.
SYSTEM DESCRIPTION Refer to Figure 32-80. Brakes System Hydraulic Synoptic. When the brake pedal is pushed, the brake control valve will supply hydraulic pressure to the brake assembly in proportion to the amount of brake pedal travel. The pressure plate assembly pushes the rotor disks, stator disks, and the end plate together. As the disks are pushed together, the friction between the disks causes resistance. The resistance is transmitted from the brake unit to the wheel and tire assemblies causing the wheel to slow down.
FOR TRAINING PURPOSES ONLY
32-107
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure 32-81. Brake Wear Indicator Pins
8 LEGEND 1. Main Wheel-brake Unit 2. Hydraulic Hose 3. Reducer 4. O−Ring 5. Axle 6. Brake Pin Bushing 7. Brake Pin 8. Brake Bleeder Valve
6 2
3
4
5
6
1
7
FWD
Figure 32-82. Main Wheel Brake Unit - Removal and Installation
32-108
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Main Wheel Brake Units
•• Apply hydraulic fluid to the threads of the reducer and the O-ring •• Install the O-ring on the reducer
Refer to Figure 32-81. Brake Wear Indicator Pins. There are two brake units installed on the axle of the main landing gear. The brake pins on the MLG shock strut engage with the bushings in the piston housing assembly to transfer the braking loads to the landing gear. The brake assembly has three primary sub-components: •• Piston housing assembly
•• Install the reducer on the brake unit and torque •• Apply torque seal across the reducer and on the main wheel brake unit •• Carefully install the brake unit on the axle. Make sure that the brake pins engage with the brake pin bushings •• Remove the caps from the hydraulic hose and the reducer and connect the hydraulic hose to the reducer
•• Carbon heat sink stack and
NOTE
•• Torque plate assembly. The piston housing is made of aluminum. It contains six adjuster assemblies, two bleeder valves, and one bleeder plug.
Make sure that you install the elbow of the hydraulic hose vertically in-line with the brake unit or angled a small distance in to the shock strut.
The bleeder valves and bleeder plugs are interchangeable so the brakes can be installed on the left or right side.
•• Torque the hydraulic hose
Two wear indicator pins are attached to the pressure plate assembly and extend out of the piston housing through sleeves to give an indication of brake wear.
•• Apply torque seal across the reducer and onto the wheel brake unit
•• Apply torque seal across the coupling nut of the hydraulic hose and the reducer
•• Install the main wheel and tire assembly
Installation of the Main Wheel Brake Units
•• Lower the MLG main wheel assembly. Remove the jack
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
•• Bleed the main landing-gear brake system.
Refer to Figure 32-82. Main Wheel Brake Unit Removal and Installation.
NOTE Make sure that the surfaces are clean with no corrosion, paint, grease, dirt, or preservation fluid.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-109
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
3 LEGEND 1. 2. 3. 4. 5. 6.
Bleed Screw Washer Bleeder Valve Brake Unit Bleed Hose Container
5
4
NOTE Shock strut and axle not shown.
Figure 32-83. Main Landing Gear Brake System - Bleed
32-110
FOR TRAINING PURPOSES ONLY
2
6
1
MAINTENANCE TRAINING MANUAL
Bleed the Brakes with Main Brake System The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 32-83. Main Landing Gear Brake System - Bleed. This procedure will bleed the brakes from the brake control valve to the brake units. After the replacement of a brake unit you can use this procedure or the procedure to bleed the brakes with the parking brake system.
NOTE After the replacement of a brake unit, it is only necessary to bleed the brake unit that you replaced. You must bleed all of the brake units after the replacement of other brake system components.
NOTE The flow of hydraulic fluid can stop because the fuse/shuttle valve operates. If this occurs, release the brake pedal. Then push and hold the brake pedal again. •• Close the bleeder valves and torque. •• Release the brake pedal. •• Remove the hose from the bleeder valve. •• Install the screw and the washer in the bleeder valve and torque. •• Push the brake pedals. Make sure the operation of the pedals is not soft. If the operation of the brake pedals is soft, do this procedure again. •• Do a visual inspection of the brake line and connections for leaks. •• With the Hydraulic pressure removed, check the quantity in the No.1 hydraulic system.
•• Remove the bleed screw and the washer from the bleeder valve on the main wheel-brake unit. •• Install the bleed hose on the bleeder valve. Put the other end of the bleed hose in the container. •• Open the bleeder valve at the MLG brake unit. •• Lightly push the brake pedal in the flight compartment until hydraulic fluid flows from the bleeder valves. •• Hold t he brake pedal and l e t the hydraulic fluid flow from the bleeder valves until the hydraulic fluid does not contain air bubbles.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-111
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Brake Bleeding Kit Refer to Figure 32-84. Brake Bleeding Kit. PN: G601R324301-1 Used to bleed the brake lines. Pump
Clamp
Hose
Figure 32-84. Brake Bleeding Kit
SYSTEM
ATA SUB-SYSTEM
32---4
32 LANDING GEAR
1.
PART DESCRIPTION
BRAKE ASSEMBLY WEAR INDICATOR PIN
NUMBER OF PARTS REQUIRED FOR ALL FLIGHT CONDITIONS EXCEPT AS PROVIDED IN COLUMN 2.
2. REMARKS AND/OR EXCEPTIONS
8
One may be missing from each brake assembly provided the pin is replaced at the next brake removal.
Figure 32-85. CDL - Brake Assembly Wear Indicator Pin
32-112
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Brake Control Valve Refer to Figure 32-86. Brake Control Valve. The brake control valve is installed in the left wing root on the front spar. The left brake pedals are connected to the left lever of the brake control valve. The right brake pedals are connected to the right lever of the brake control valve.
Hydraulic pressure and return lines connect the brake control valve to the No.1 hydraulic system. Hydraulic lines connect the brake control valve to the anti-skid valves. The function of the brake control valve is to meter hydraulic pressure to the brake units as determined by pedal input.
The brake control valve has two internal metering sections in a common housing.
LEGEND 1. Right Brake Lever 2. Brake Control Valve 3. Hydraulic Line 4. Left Brake Lever 5. Left Brake Cable Turnbuckle.
A
2
1
3
4
FWD
A
5
Figure 32-86. Brake Control Valve
FOR TRAINING PURPOSES ONLY
32-113
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Fuse/Shuttle Valves Refer to: •• Figure 32-87. Fuse - Shuttle Valve. •• Figure 32-88. Fuse - Shuttle Valve. There are two fuse/shuttle valves installed on the left wall of each nacelle. Hydraulic pressure is supplied to the brake units through the skid control valves and the fuse/shuttle valves. The fuse component of the fuse/shuttle valve closes if the fluid flow is more than a specified quantity. This limits the leakage of hydraulic fluid if a brake line or a brake develops a leak. The shuttle component of the valve sends either normal or parking/emergency brake pressure to the brakes.
Figure 32-87. Fuse - Shuttle Valve
FWD
1
A
2
1
NOTE Left component shown. Right component similar.
A
Figure 32-88. Fuse - Shuttle Valve
32-114
FOR TRAINING PURPOSES ONLY
LEGEND 1. Fuse 2. Shuttle Valves.
MAINTENANCE TRAINING MANUAL
Brake Pedals
The brake pedal inputs are applied to the brake control levers.
Refer to Figure 32-89. Brake Pedals.
The linkage attached to the base of the pedals is spring loaded to return the pedals to the off position when the pedals are released.
The brake pedals are installed in the flight compartment and are connected to the brake control valve. The co-pilot’s inputs are transmitted by a cable system to the spring loaded lever arm aft of the pilot’s brake pedal.
1 A 10
2
9 3
4 5 6 8 A 7
LEGEND 1. Co-pilot’s Brake Pedals 2. Tie Rods 3. Brake Control Levers 4. Brake Interconnect Cables 5. Lever Springs 6. Cables to Brake Control Valve 7. Push Rods 8. Spring Rods 9. Tie Rods 10. Pilot’s Brake Pedal.
Figure 32-89. Brake Pedals
FOR TRAINING PURPOSES ONLY
32-115
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Brake Control Cables Refer to Figure 32-90. Brake Control Cables. The brake control cables connect the pilot’s pedals to the two levers on the brake control valve. The brake control valve is installed in the left wing root area.
The cables are routed along the ceiling through grommets at four frame stations. The cables pass through another three pairs of pulleys in the left wing root and then connect to the two levers on the brake control valve.
The cables are routed under the floor along the left side to a pair of pulleys and then upward through a cable guide on the flight compartment bulkhead to another pair of pulleys on the ceiling.
3
5
3
3
6
2
5
3 4 1
3 2 1
1 2
NOTE Flight compartment bulkhead. Left wing root area.
Figure 32-90. Brake Control Cables
32-116
FOR TRAINING PURPOSES ONLY
LEGEND 1. Brake Control Cables 2. Pedal Mechanism 3. Pulleys 4. Cable Guide 5. Grommets 6. Brake Control Valve.
MAINTENANCE TRAINING MANUAL
Brake Pressure Transducers Refer to Figure 32-91. Brake Pressure Transducers. The brake pressure transducers are installed in the left wing root area near to the brake control valve.
The transducers sense the pressure through the brake control valve. The function of these pressure transducers is to send data to the flight data processing system for recording on the FDR.
One transducer senses the left brake system and the other senses the right brake system.
LEGEND 1. Transducers 2. Electrical Connector.
A
2
Brake Control Valve (Ref)
A
1
Figure 32-91. Brake Pressure Transducers
FOR TRAINING PURPOSES ONLY
32-117
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-118 NO. 2 SYSTEM RESERVOIR
NO. 2 SYSTEM PRESSURE
LEGEND PRESSURE RETURN
HIGH PRESSURE AIR CHECK VALVE
FUSE SHUTTLE VALVE ACCUMULATOR PARKING BRAKE CONTROL VALVE
PARKING BRAKE LEVER
HAND PUMP CHARGE VALVE GAUGE ACCUMULATOR PRESSURE TRANSDUCER
TO FUSE/SHUTTLE VALVES AND BRAKE UNITS ON OTHER MAIN LANDING GEAR
PRESSURE RELIEF VALVE NORMAL BRAKE SYSTEM
NORMAL BRAKE SYSTEM
MAIN WHEEL BRAKE UNITS
NOTE SHOWN WITH PARKING BRAKE APPLIED
fs665a01a.cgm
Figure 32-92. Parking Brake Hydraulic System
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RESTRICTOR
DASH 8 Q400
SUCTION
MAINTENANCE TRAINING MANUAL
32-44-00 PARKING BRAKE SYSTEM INTRODUCTION The parking brake system is used to keep hydraulic pressure applied to the brake units. The parking brake system can stop the aircraft on the ground.
GENERAL The parking brake system uses the No.2 hydraulic system. An accumulator in the brake system supplies pressure for parking brake operation when the No.2 hydraulic system pressure is not available. A hand pump is used to manually pressurize the parking brake accumulator. Parking brake pressure is applied equally to all of the brake units.
SYSTEM DESCRIPTION Refer to Figure 32-92. Parking Brake Hydraulic System. When the PARK/EMERG control lever is moved from the stowed toward the PARK position, the park brake control valve is actuated. The parking brake control valve can apply progressive hydraulic pressure to the brakes. The hydraulic pressure from the parking brake control valve causes the shuttle valves to move and block off normal brake pressure to the brakes. The release button on the parking brake lever is pushed in and the lever is moved forward to the stowed position to release the parking brake. The parking brake accumulator is normally pressurized from the No.2 hydraulic system. A fully charged accumulator will supply six parking brake applications.
A PARKING BRAKE caution light on the CAWP in the flight compartment comes on when the parking brake lever is in the PARK position. A parking brake pressure indicator is shown on No.2 MFD as part of the permanent system area No.2. The parking brake system is comprised of the components: •• Parking brake control lever •• Parking brake pressure indication •• Control cable assembly •• Parking brake control valve •• Hand pump •• Accumulator •• Charge valve and gauge.
FOR TRAINING PURPOSES ONLY
32-119
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure 32-93. Park Brake Control Valve
3
1
A
FWD
2
LEGEND 1. Accumulator Pressure Transducer 2. Parking Brake Control Cable 3. Parking Brake Control Valve.
A ft405a01.cgm
Figure 32-94. Park Brake Control Valve
32-120
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
32 LANDING GEAR
DASH 8 Q400
NOTES
Parking Brake Control Valve Refer to: •• Figure 32-93. Park Brake Control Valve. •• Figure 32-94. Park Brake Control Valve. The parking brake control valve is installed in the right wing root. The No.2 hydraulic system pressure is supplied to the parking brake control valve. The pressure is metered to the brake units in proportion to the amount of parking brake lever movement. When the parking brake lever is set in the PARK position, full hydraulic pressure is applied to the four brake units. A pressure transducer, relief valve and two check valves are contained in the brake control valve housing. The function of the parking brake control valve is to meter the No.2 hydraulic system pressure to the brake units.
Parking Brake Hand pump A lever operated hand pump is installed on the right wall in the right engine nacelle. The hand pump handle is spring clipped and pip-pinned in the nacelle. It supplies an alternate method to pressurize the accumulator to 3000 psi (20684 kPa) when the aircraft is on the ground and the engines are not operating. The function of the hand pump is to manually increase the park brake system pressure when No.2 hydraulic system is not available.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-121
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Post SB 84-32-99 Reposition of the Parking Brake Hand Pump Lever to the Nose Compartment
NOTES
Refer to Figure 32-95. Parking Brake Handle Reposition. If the quick release pin is not fully engaged, the potential exists for the pin to migrate out, disengaging, and allowing the pump lever to become dislodged from its installation position in the wheel well. It became necessary to relocate the existing parking brake hand pump lever from RH nacelle to the flight deck web in the RH side of the nose compartment.
Figure 32-95. Parking Brake Handle Reposition
32-122
FOR TRAINING PURPOSES ONLY
SYSTEM
MAINTENANCE TRAINING MANUAL
1.
32 LANDING GEAR
ATA SUB-SYSTEM 32---3
PART DESCRIPTION PARKING BRAKE HANDPUMP HANDLE (Located in the nose compartment equipment bay)
NUMBER OF PARTS REQUIRED FOR ALL FLIGHT CONDITIONS EXCEPT AS PROVIDED IN COLUMN 2.
2. REMARKS AND/OR EXCEPTIONS 1
May be missing with no performance penalty provided: a. Alternate Landing Gear Extension handpump handle must be stowed in its proper location in the flight compartment.
Figure 32-96. CDL - Parking Brake Hand Pump Handle
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-123
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Parking Brake Accumulator Refer to Figure 32-97. Parking Brake Accumulator. The parking brake accumulator is installed in the right wing root area. The accumulator is a cylindrical piston type with a gross rated volume of 50 in³ (820 cm³).
The fluid side is pressurized by the No.2 hydraulic system or the hand pump. The fully charged accumulator will hold enough pressure to supply six full parking brake applications and releases. The function of the accumulator is to supply hydraulic pressure for the parking brake operation when No.2 hydraulic pressure system is not available.
The accumulator is pressurized with nitrogen. The accumulator is pre-charged to 500 psi (3447 kPa).
Figure 32-97. Parking Brake Accumulator
32-124
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Charge Valve and Gauge Refer to: •• Figure 32-98. Charge Valve and Gauge. The charge valve and gauge are installed in the right wing root area. They are connected to the gas pressure side of the parking brake accumulator. The gauge supplies an indication of the accumulator pressure. The charge valve is used to charge the gas side of the accumulator with nitrogen.
Servicing of the Parking Brake Accumulator with Nitrogen The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• R e m o v e t h e v a l v e c a p f r o m t h e accumulator charging valve.
Functional Check of Park Brake Accumulator Pre-Charge Pressure The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
WARNING OBEY ALL HYDRAULIC SAFETY PRECAUTIONS. Do the check as follows: •• Ensure all hydraulic power is OFF. •• Ensure the main wheels are chocked. •• Operate EMERG BRAKE lever until 0 pressure is indicated on MFD #2. •• Place EMERG BRAKE to OFF. •• C h e c k a c c u m u l a t o r p r e - c h a r g e i s 500±25 psi.
•• Connect the hose of the nitrogen servicing kit to the accumulator charging valve. •• Charge the accumulator until the adjacent gauge shows 500 ±25 psi. •• Remove the hose of the nitrogen servicing kit from the accumulator charging valve. •• Install the valve cap on the accumulator charging valve. •• Pressurize the parking brake system to 3000 ±50 psi with the hand pump. •• Operate the parking brake lever in the flight compartment to make sure that the parking brake system is serviceable. •• Use the hand pump to pressurize the parking brake system to 3000 ±50 psi again. •• Make sure that the PK BRK indication from the HYD PRESS readout on the MFD shows 3050 ±50 psi. Revision 0.4
Figure 32-98. Charge Valve and Gauge
FOR TRAINING PURPOSES ONLY
32-125
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Parking Brake Control Quadrant
NOTES
Refer to Figure 32-99. Park Brake Control Quadrant. The parking brake lever is installed in the flight compartment. It is in the emergency brake control quadrant. On left side of the center console. A cable assembly connects the parking brake lever to the parking brake control valve. A release button on the parking brake lever unlocks the lever from the PARK position. The function of the parking brake lever is to supply alternate brake control and to set the parking brake.
3
LEGEND 1. Emergency Brake Lever 2. Emergency Brake ON Position 3. Release Button 4. Control Quadrant (Ref.)
1
R A T I N G
R A T I N G
I
FLIGHT IDLE DISC
I
4
2
Figure 32-99. Park Brake Control Quadrant
32-126
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Parking Brake Control Cable
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-100. Parking Brake Control Cable. The parking brake control cable is a single open loop cable which connects the park brake lever to the parking brake control valve. The cable is routed from the lever quadrant through pulleys under the flight compartment floor to the lever on the parking brake control valve. 6
3 1
1
5
5
4
3
3
2 3
LEGEND 1. Parking Brake Control Cable. 2. Park Brake Lever. 3. Pulleys. 4. Cable Guide. 5. Grommets. 6. Park Brake Control Valve.
1
Figure 32-100. Parking Brake Control Cable
FOR TRAINING PURPOSES ONLY
32-127
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
1 2
LEGEND 1. Park Brake Lever 2. Cable Quadrant 3. Cable 4. Connector 5. Center Console 6. Caution Light Micro-Switch.
3
6
4
5
Figure 32-101. Parking Brake Micro-Switch
32-128
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to: •• Figure 32-101. P arking Brake Micro-Switch. •• Figure 32-102. C ontrols and Indications - Parking Brake System. A 28 VDC electrical power source is needed for the PARK BRAKE pressure indicator and the pressure transmitter to operate. The park brake pressure signal is sent to the Integrated Flight Cabinet (IFC) to be converted from analog to digital data for display on the EIS on the co-pilot MFD. A PARKING BRAKE caution light on the Caution and Warning panel in the flight compartment comes on when the parking brake lever is in the PARK position.
Interfaces The parking brake system is interfaced with: •• The Take-Off Configuration Warning System •• T h e H y d r a u l i c S y s t e m S P U / P T U Automatic Activation •• The Cockpit Voice Recorder Erase Interlock System •• The Caution and Warning System.
FOR TRAINING PURPOSES ONLY
32-129
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
OVERHEAD CONSOLE
B
ELECTRICAL
LEGEND 1. Parking Brake Hydraulic Pressure Indicator 2. Parking Brake (Amber)
ELECTRICAL BATT
LOAD
MAIN +1. 00 AUX - . 34 MAIN - . 00 34 STBY 00 AUX 00 STBY L
¡C
+22 +22 +22
DC BUS
VOLT R
ESS 27.7 MAIN 28.5 ESS SEC 26.1 MAIN S EC
27.7 28.5 26.1
APU GEN
AC GEN 1
LOAD
+1. 00 DC GEN 1
LOAD
+1. 00 1
TRU
LOAD
2
. 06
VOLT
LOAD
A 115 B 115 C 115
. 06 . 06 . 06
AC GEN 2
VOLT
2
+1. 00 +1. 00
LOAD
. 06 . 06 . 06
A 115 B 115 C 115
2 PARKING BRAKE
FLAP
DEG
0 5 10
HYD PRESS
PSIxx 1000 1000 PSI PK BRK STBY 1 2
35
HYD QTY
3
4
1
% x 100
2
3 1
2 0
A
PARKING BRAKE CAUTION LIGHT
1 B
PARKING BRAKE PRESSURE INDICATION
Figure 32-102. Controls and Indications - Parking Brake System
32-130
FOR TRAINING PURPOSES ONLY
0
DASH 8 Q400
Systems & Nos de Sequence système Numbers de série
1. Item - Article
32 LANDING GEAR
MAINTENANCE TRAINING MANUAL
2. Number installed - Nombre d’articles installés 3. Number required for dispatch - Nombre d’articles à expédier 4. Remarks or Exceptions - Remarques ou exceptions
-40-1
Parking Brake Pressure Indications 1) HYD PRESS PK BRK Indication
C
1
0
(M) May be inoperative provided: a) The Aft Wing Root Fairing Indicator is verified operative, and b) Brake pressure is confirmed adequate prior to engine start.
Figure 32-103. CDL - Parking Brake Pressure Indications
FOR TRAINING PURPOSES ONLY
32-131
32 LANDING GEAR
32-132 METERED PRESSURE FROM THE BRAKE CONTROL VALVE
RETURN NO. 1 SYSTEM RESERVOIR ANTI SKID CONTROL VALVE
LEGEND METERED PRESSURE ANTI SKID PRESSURE
STATIC CHECK VALVE SERVO VALVE
FILTER RESTRICTOR FUSE SHUTTLE VALVE
SPOOL AND SLEEVE VALVE
SPOOL AND SLEEVE VALVE
PARKING BRAKE (NO. 2 HYDRAULIC SYSTEM)
fs667a01a.cgm
MAIN WHEEL BRAKE UNITS
NOTE SHOWN WITH BRAKES APPLIED (WHEELS NOT IN SKID CONDITION)
Figure 32-104. Anti-Skid System - Hydraulic Schematic
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SERVO VALVE
DASH 8 Q400
RETURN
MAINTENANCE TRAINING MANUAL
32-46-00 ANTI-SKID SYSTEM
32 LANDING GEAR
DASH 8 Q400
NOTES
INTRODUCTION The anti-skid system modulates hydraulic pressure to the four wheel brake units to supply wheel anti-skid protection.
GENERAL Refer to Figure 32-104. Anti-Skid System Hydraulic Schematic. The brake pedals cause the No.1 hydraulic system pressure to be sent through the brake control valve to the anti-skid control valves. The anti-skid control valves change the hydraulic pressure to the brake units. The anti-skid system operates with the normal brake system. The anti-skid system is comprised of the following components: •• Anti-skid control unit •• Wheel speed transducers •• Skid control valves •• ANTISKID switch.
SYSTEM DESCRIPTION The anti-skid system has the following functions: •• Touchdown protection •• Initialization •• Individual wheel anti-skid •• Locked wheel protection •• System monitoring.
FOR TRAINING PURPOSES ONLY
32-133
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure 32-105. Anti-Skid System Control Unit
A
FWD
A fs140a01.cgm
Figure 32-106. Anti-Skid System Control Unit
32-134
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENTS DESCRIPTION
32 LANDING GEAR
DASH 8 Q400
NOTES
Anti-Skid Control Unit Refer to: •• Figure 32-105. A nti-Skid System Control Unit. •• Figure 32-106. A nti-Skid System Control Unit. The ASCU is installed below the passenger cabin floor at the mid-wing area, on the equipment rails. The ASCU is an electronic box that has two wheel control circuit boards, one for the inboard wheels and one for the outboard wheels. Each wheel board uses a micro-controller and related circuitry to do the digital processing of the control and built-in-test software. The ASCU receives signals from the: •• Anti-skid switch •• Four wheel speed transducers •• Two dual skid control valves •• PSEU (WOW and uplock).
FOR TRAINING PURPOSES ONLY
32-135
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Skid Control Valves Refer to: •• Figure 32-107. Skid Control Valve. •• Figure 32-108. Skid Control Valve. The skid control valves are installed on the left wall of the wheel wells. The skid control valves are two separate valves in one common manifold. Each skid control valve contains a screen on the inlet port. The screen protects the skid control valve components from contaminants larger than 40 microns. The function of the skid control valve is to control the flow to and from the brake unit, as commanded by the Anti Skid Control Unit.
Figure 32-107. Skid Control Valve
A
FWD
fs141a01.cgm
A
Figure 32-108. Skid Control Valve
32-136
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
Wheel Speed Transducer Refer to: •• Figure 32-109. Wheel Speed Transducer. •• Figure 32-110. Wheel Speed Transducer. A wheel speed transducer is installed in each end of the main landing gear axles. The wheel speed transducer is an electrical generating device. The hubcap on the wheel engages with a clip on the wheel speed transducer. When the wheel turns, the wheel speed transducer supplies an AC signal with a frequency of 100 cycles per wheel revolution. Figure 32-109. Wheel Speed Transducer
This signal is changed to a digital signal in the ASCU for anti-skid control use. The function of the wheel speed transducer is to supply wheel speed information to the ASCU.
B
FWD A
MLG WHEEL
A
B
WHEEL SPEED TRANSDUCER
Figure 32-110. Wheel Speed Transducer
FOR TRAINING PURPOSES ONLY
32-137
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A WHITE
1 2
A C B
RIGHT WHEEL SPEED TRANSDUCER
A C B
LEFT WHEEL SPEED TRANSDUCER
WHITE/BLUE WHITE
3 4 WHITE/BLUE LEGEND 1. Wheel-Speed Transducer Harness 2. Electrical Connector 3. Strain Relief Clamp 4. Electrical Connector.
A
B
2
1
VIEW
4
B
Figure 32-111. Wheel Speed Transducer Harness - Removal/Installation
32-138
FOR TRAINING PURPOSES ONLY
ma288a01.dg, kms, nov21/2006
3
MAINTENANCE TRAINING MANUAL
Installation of the Wheel-Speed Transducer Electrical Harness
32 LANDING GEAR
DASH 8 Q400
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 32-111. Wheel Speed Transducer Harness - Removal/Installation. This is the wheel speed transducer harness of the main landing gear (MLG). The harness is installed in the axle of the MLG shock strut.
NOTE Make sure the pins are inserted as tagged on the wheel speed transducer harness. Apply sealant to the mating surfaces of the connector and fill the cavity of the backshell.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-139
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
ANTI-SKID SWITCH Refer to Figure 32-112. Anti-Skid Switch. The ANTI-SKID switch is located on the co-pilot’s glareshield panel. The ANTI-SKID switch is a three position OFF/ON/TEST switch. When the ANTI-SKID switch is set to the ON position, 28 VDC is supplied to the circuit boards in the ASCU. When set to the TEST position, 28 VDC is supplied to the wheel control circuit boards and the system BIT function. When the ANTI-SKID switch is set to OFF, all electrical power is removed from the ASCU. A
The function of the ANTI-SKID switch is to energize and to test the anti-skid system.
LEGEND 1. Anti-Skid Switch
STICK PUSHER SHUT OFF
ENGINE FIRE
ANTI SKID TEST
INHIBIT
TERRAIN INHIBIT
ELEVATOR TRIM SHUT OFF
CAUTION
CF-AEI
PRESS TO RESET
A
Figure 32-112. Anti-Skid Switch
32-140
FOR TRAINING PURPOSES ONLY
1
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
CONTROLS AND INDICATIONS Refer to Figure 32-113. Anti-Skid Caution Lights. Failures of the anti-skid system are annunciated in the flight compartment through two caution lights on the CAWP: •• INBD ANTISKID •• OUTBD ANTISKID. The caution lights also illuminate during the test; six seconds on ground; three seconds in flight.
1
2
A
OVERHEAD CONSOLE INBD ANTISKID
OUTBD ANTISKID
LEGEND 1. Inboard Antiskid (Amber) 2. Outboard Antiskid (Amber) A
Figure 32-113. Anti-Skid Caution Lights
FOR TRAINING PURPOSES ONLY
32-141
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
MAIN WHEEL AND TIRE ASSEMBLY
4 6 5
8
7
3
LEGEND 1. Bleeder valve adapter. 2. Packing. 3. Brake unit. 4. Anti−skid tester. 5. Bolts. 6. Washers. 7. Hubcap. 8. Wheel speed transducer.
2
Figure 32-114. Anti-Skid System Functional Test
32-142
FOR TRAINING PURPOSES ONLY
1
MAINTENANCE TRAINING MANUAL
Functional Test of the Anti-Skid Control System (Built-in Test)
and the OUTBD ANTISKID caution lights come on for 2 to 4 seconds and then go off.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
Refer to Figure 32-114. Anti-Skid System Functional Test.
This test uses the built-in test function of the anti-skid control system.
Make sure that the aircraft is in the configuration that follows: •• The LANDING GEAR selector is in the DN position.
NOTE This test is written with the aircraft on the ground in a weight-on-wheels condition. You can also do this test with the aircraft on jacks if you simulate the weight-on-wheels condition. •• Set the ANTISKID switch in the flight compartment to OFF. •• Make sure that the INBD and OUTBD ANTISKID caution lights come on. •• Set the ANTISKID switch in the flight compartment to ON. •• Make sure that the INBD and OUTBD ANTISKID caution lights go off. •• Momentarily hold the ANTISKID switch in the flight compartment in the TEST position. •• Make sure that the INBD ANTISKID and the OUTBD ANTISKID caution lights come on for 5 to 7 seconds and then go off. •• Put the aircraft in the weight-off-wheels condition as follows: °° Put the de-actuator (copper) targets on the main landing gears. °° Put the actuator (steel) targets on the nose landing gear. °° Momentarily hold the ANTISKID switch in the flight compartment in the TEST position. °° Make sure that the INBD ANTISKID Revision 0.4
°° Remove the targets from the main and the nose landing gears.
•• The lock pins are installed in the main landing gear. •• The nose gear ground lock is engaged. •• EMERG BRAKE lever to the OFF position. •• Connect the anti-skid tester.
Touchdown Protection Test •• ANTI SKID switch to the ON position. •• Aircraft is in a WOFFW condition. •• Fully push the left and right brake pedals. •• No appreciable brake pressure measured at the brake units. (Below 75 psi) • • Incorrect results show a problem with the anti-skid control unit or a problem with the W OW signa ls ( P S E U o r WOW switches).
Wheel Speed Transducer Test Turn the wheel speed transducer at a constant speed between 480 rpm and 2400 rpm.
NOTE The ANTI-SKID INOP caution light may come on momentarily. •• Make sure that the pressure at the selected wheel brake unit increases to more than 500 psi. •• Make sure that the pressure at the other brake units is less than 150 psi.
FOR TRAINING PURPOSES ONLY
32-143
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-144 WOW SW(IB) HMAIN GEAR UP & LOCKED (IB) H
13 WOW SW(IB) 28 MAIN GEAR UP & LOCKED (IB)
WOW SW(OB) T MAIN GEAR UP & LOCKED (OB) N
13 WOW SW(OB) 28 MAIN GEAR UP & LOCKED (OB)
ANTI SKID TEST ON OFF
32-61 A1 PSEU
A
DASH 8 Q400
A (Q5) 3A + 28 V DC R. MAIN
ANTISKID INBD
5
D
4
(OB) FAIL IND 35
(IB) FAIL IND (R5) ANTISKID OUTBD
RIGHT DC CBP
8
F
2
9
ANTISKID TEST
111
13 (IB) FAIL IND
CAUTION AND WARNING PANEL (O/H CONSOLE)
OFF
1
H
3 11
35
ON
C
10
G
12
E
IOM #1
15 17 16
BITE TEST (IB) +28 V DC (IB) RTN
15 17 16
BITE TEST (OB) +28 V DC (OB) RTN
3 4
331 330
HI ANTISKID LO MA A429
B
31-41 A1 IOP #1
ANTISKID SWITCH (GLARESHIELD) 27 ARINC 429 TRANS'M REQUEST B
WST (OB)
A B
32 + 33 -
WST (OB)
RIGHT OUTBOARD WHEEL SPD XDCR
WST (IB) LEGEND METERED PRESSURE
CNTL VALVE (OB)
CNTL VALVE (IB) A B
32 + WST 33 - (IB)
A B
8+ 9 -
+ 23 - 24
1 + 2 -
(OB)
+ 23 - 24
3 + 4 -
(IB)
B
B
SKID CONTROL VALVE
RIGHT INBOARD WHEEL SPD XDCR
RETURN STATIC CHECK VALVE FILTER RESTRICTOR FUSE
WST (OB)
WST (OB)
LEFT OUTBOARD WHEEL SPD XDCR
CNTL VALVE (IB)
SHUTTLE VALVE
WST (IB)
LEFT INBOARD WHEEL SPD XDCR
A B
8+ 9 -
WST (IB)
CNTL VALVE (OB)
+ 11 - 10
1 + 2 -
(IB)
11 10
3 + 4 -
(OB)
B
ANTISKID CONTROL UNIT
Figure 32-115. Anti-Skid System Electrical Schematic
SKID CONTROL VALVE
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
3A
7
35 (OB) FAIL IND
TEST
6
MAINTENANCE TRAINING MANUAL
ANTI-SKID SYSTEM
Initialization
OPERATION
When the aircraft lands, the anti-skid system goes into Initialization Mode when the following signals are received by the ASCU:
Anti-Skid Operation Refer to Figure 32-115. Anti-Skid System Electrical Schematic. When the Anti-Skid Switch is selected ON, Power is supplied from the 28 VDC right main bus through Pins F and D of the switch and out of the switch through Pins C and E to Pin 17 of the Anti-Skid Control Unit. When the aircraft is on the approach for landing, the PSEU sends signals to the AntiSkid Control Unit. The signals are as follows:
•• MLGWOW for > 5 seconds OR •• Wheel speed > 75 knots. Metered hydraulic pressure from the brake control valve is slightly reduced by the servo valves, causing the spool and sleeve valves to open partially, preventing full braking force.
Individual Wheel Individual wheel Anti-Skid Mode starts with the signals that follow:
•• WOFFW to Pins 13
•• MLGWOW > 5 seconds OR
•• Gear NOT Up and Locked to Pins 28.
•• Wheel speed < 70 knots.
The ASCU gets the wheel speed < 35 knots signals from: •• Pins 32 and 33 for right inboard and right outboard transducers •• Pins 8 and 9 for the left inboard and outboard transducers. Touchdown Protection Mode causes a full brake release signal sent from: •• ASCU Pins 23 to right dual skid control valve at Pins 1 and 3 •• ASCU Pins 11 to left dual skid control valve at Pins 1 and 3.
NOTE All the pins mentioned are used throughout all modes of antiskid operation.
Full metered pressure from the brake control valve passes through the servo valves. This pressure operates the brakes. If a skid is detected, the ASCU commands decreased pressure to the affected wheel brake unit, until the wheel speeds up to match the speed of the other wheels.
Locked Wheel If an inboard, or outboard wheel develops a skid producing a difference in speed of < 30% of the reference speed, Locked Wheel Protection is now initiated. All metered pressure, for that brake unit, is released to return by the servo valve until the locked wheel speed is > 35% of reference speed. Reference speed is the speed of the matched inboard or outboard wheel, on the other side of the aircraft.
This causes the servo valve to release all hydraulic pressure into the return line. The brakes receive no pressure and the brakes will release.
FOR TRAINING PURPOSES ONLY
32-145
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Interfaces
NOTES
•• The ASCU receives 28 VDC power from the right main DC circuit breakers (ANTISKID INBD CB Q5 and ANTISKID OUTBD CB R5). The ASCU requires power from the two CBS for correct operation. •• The fault data recorded by the ASCU is transmitted over the ARINC 429 data bus as a series of pages and is shown on the Audio Radio Control Display Unit (ARCDU) as a part of the Central Diagnostic System.
32-146
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
32-147
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
PRESENT OTHER SYSTEM 1
1/2
< EMU
ANTI-SKID >
< FCS
ICE PROTECTION >
< ECS
< TMCU1
MENU
ON / OFF
YES
NO
APU >
TMCU 2 >
Figure 32-116. ARCDU CDS ANTISKID System
Figure 32-117. PSEU - Present Faults
ASC CURRENT FAULTS
1/ 2
LT OUTBOARD WST
Figure 32-118. ASC - Current Faults
32-148
F AU L T S ?
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
MAINTENANCE PRACTICES IMPORTANT TO THE MLG BRAKING SYSTEM The following are abbreviated descriptions of the maintenance practices and is intended for training purposes only. For a more detailed description of the practices, refer to the tasks in the Bombardier AMM PSM 1-84-2.
Refer to Figure 32-118. ASC - Current Faults. •• Do a functional test of the antiskid system •• On the ARCDU, retrieve the data for the antiskid system again •• If there is a message then perform the applicable Fault Isolation Procedure.
FAULT ISOLATION INBD ANTISKID and OUTBD ANTISKID (Caution lights) The INBD or OUTBD ANTISKID light illuminates when there is a loss of ability to command or control the inboard or outboard antiskid system. •• R e t r i e v e D a t a f r o m t h e c e n t r a l diagnostic system (CDS) Refer to Figure 32-116. ARCDU CDS ANTISKID System. •• Retrieve Data from the proximity sensor electronics unit (PSEU) Refer to Figure 32-118. ASC - Current Faults.
NOTE The fault isolation procedures for the above PSEU messages are equivalent to those for the related CDS PSEU AIR/GND or PSEU GEAR UP messages. The Data from the Central Diagnostic System - Anti-Skid System (ANTI-SKID) cannot be erased. When a fault is corrected it will be moved from the ASC CURRENT FAULTS page to the ASC PAST FAULTS page (requires refresh).
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-149
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
ASC CURRENT FAULTS
1/ 2
NO CURRENT FAULTS
Figure 32-119. ASC - No Current Faults
#1 STALL SYST FAIL #2 STALL SYST FAIL
FLT DATA RECORDER GPWS
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
FLAP RIVE
LDG GEAR INOP
WT ON WHEELS
LAP WER
NOSE STEERING
FUELING ON
MAIN BAT HOT
FUSELAGE
X BAT HOT
DOORS
Figure 32-120. Parking Brake Caution Light
32-150
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
PARKING BRAKE, INDICATION DISCREPANCY (CAUTION LIGHT)
32 LANDING GEAR
DASH 8 Q400
NOTES
The CAWP usually shows the PARKING BRAKE light on when the EMERG BRAKE lever is in the PARK position.
NOTE This is not a malfunction condition. Refer to Figure 32-120. Parking Brake Caution Light. There are no related central diagnostic system (CDS) messages. If the PARKING BRAKE caution light is on when the EMERG BRAKE lever is in the OFF position, do the Fault Isolation. •• Remove and replace the parking brake control quadrant •• If the fault still continues, remove and replace the CAWP •• If the fault still continues, do a check of the wiring between the parking brake control lever and the CAWP •• If the wiring is unserviceable, repair the wiring.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-151
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND No. 2 Hydraulic Pressure Steering Pressure Return Electrical
HIGH-SPEED TAXI MODE 8° LEFT AND RIGHT (RUDDER PEDALS) 8° 8°
70°
120°
70°
LOW SPEED TAXI MODE 70° LEFT AND RIGHT (STEERING CONTROL HANDLE)
120°
UNPOWERED (CASTER) MODE 120° LEFT AND RIGHT
STEERING CONTROL HANDLE RUDDER PEDALS
STEERING OFF
NOSEWHEEL STEERING SWITCH
PSEU
ON-GROUND SIGNAL FROM NOSE GEAR WEIGHT ON WHEELS SWITCHES
NOSEWHEEL STEERING CONTROL UNIT (SCU)
STEERING MOTOR
NOSE STEERING CAUTION LIGHT REDUCTION GEARBOX
Figure 32-121. Nosewheel Steering System Schematic
32-152
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-51-00 NOSEWHEEL STEERING SYSTEM
SYSTEM DESCRIPTION
INTRODUCTION
Nosewheel Steering Hand Control
The steering system gives directional control of the aircraft while on the ground. Steering of the nosewheels is for taxi, take-off, and landing.
Full authority steering of the nosewheels is done by the pilot hand control located on the pilot’s side console, in the flight compartment.
The steering system also supplies shimmy damping of the nosewheels.
The pilot hand control is for low speed taxi only.
GENERAL
The steering tiller authority can steer the nosewheels 70° to the left and right of the center position.
The steering system for the nosewheels is electronically controlled and hydraulically powered. Nosewheel Steering can be controlled by the following systems: •• Pilot hand control
Refer to Figure 32-121. Nosewheel Steering System Schematic.
Rudder Pedal Control Limited authority steering of the nosewheels is by the rudder pedals. The rudder pedals allow steering during high speed taxi, take-off, and landing.
•• Rudder pedal control •• Shimmy damping system. Steering of the nosewheels is available when:
The rudder pedals can steer the nosewheel 8° to the left and to the right of the center position.
•• The NLG is down and locked
Shimmy Damping
•• The aircraft has WOW and
The steering system supplies shimmy damping of the nosewheels.
•• The STEERING switch, is set to the STEERING position. The nosewheel steering system includes the listed components: •• Electronic steering control unit •• Nosewheel steering manifold •• Power steering unit •• Rotary variable differential transformer •• Hydraulic steering motor
When the STEERING switch is selected to STEERING, shimmy damping is supplied through the steering manifold. Passive, free castor shimmy damping is supplied when the STEERING switch is in the OFF mode. The free castor mode lets the nosewheels rotate 120° to the left and to the right of the center position.
•• Nosewheel centering mechanism •• Pilot hand control •• Rudder pedal potentiometer •• Steering switch.
FOR TRAINING PURPOSES ONLY
32-153
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure 32-122. Steering Control Unit
1
2 A
FWD
LEGEND 1. SCU 2. Access Panel BITE 3. Electrical Connector.
fs486a01.cgm
A
3
Figure 32-123. Steering Control Unit
32-154
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Steering Control Unit (SCU) Refer to: •• Figure 32-122. Steering Control Unit. •• Figure 32-123. Steering Control Unit. The SCU is an electronic box installed on the outside of the NLG wheel well wall. A quick access panel on the right side of the nose fuselage gives access to the SCU in the equipment bay. The SCU consists of a metal case and cover. On the front face of the unit is a BITE display panel, it is used for diagnostic testing, and an electrical connector to measure the rigging data voltage. The SCU uses input commands from: •• The Pilot Hand Tiller
BITE Test of the Nosewheel Steering System The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
NOTE To retrieve and identify the fault codes for the nosewheel steering system, the NWS switch must be selected to ON. •• On the NWS ECU display, push the BIT switch for approximately 5 seconds and release it. This will start the display. •• Press the BIT switch again and again, and scroll through the menu until ‘READ’ is displayed. •• Push and hold the BIT switch until ‘READ’ is flashing, then release.
•• The Rudder Pedals •• The PSEU
NOTE
•• The Steering Switch •• The Steering Manifold, and •• The RVDT. The SCU supplies output commands to the steering manifold and failure signal to the CAWP. The SCU does Power-Up test, Continuous BIT and diagnostic functions. The SCU can record and store up to 100 failures in a nonvolatile memory for maintenance functions. The last 18 failures are available to line maintenance.
You will see the first fault code when you release the switch. •• If the display reads ‘----’, there are no faults. •• If there are fault codes, record them. •• To complete the BITE test, push the BIT switch again and again. Scroll through the menu until ‘EXIT’ shows. •• Push and hold the BIT switch until ’EXIT’ flashes.
The main function of the SCU is electronic control of the steering system for the nosewheels.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-155
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Nosewheel Steering Hand Control
The hand control has hard stops on either side of the center position. The centering spring returns the pilot hand control to the neutral position when the pilot inputs are removed.
Refer to Figure 32-124. Nosewheel Steering Hand Control. The nosewheel steering hand control is installed on the pilot’s side console in the flight compartment.
The hand control can steer the nosewheels ±70° of center. The function of the tiller is to transfer the steering inputs to the SCU.
The hand control has a potentiometer that sends steering signals to the SCU in proportion to the position of the Pilot Hand Control (PHC).
A
1
LEFT SIDE CONSOLE
2
3
FWD
LEGEND 1. Pilot Hand Control 2. Centering Spring 3. Potentiometer.
A
Figure 32-124. Nosewheel Steering Hand Control
32-156
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Rudder Pedal Potentiometer
The potentiometer is connected to the rudder quadrant with a linkage assembly.
Refer to Figure 32-125. Rudder Forward Assembly (Right Side).
The potentiometer sends signals to the SCU that are in proportion to the position of the rudder pedal position.
The rudder pedal potentiometer is installed on the support structure of the right rudder control quadrant below the flight compartment floor. A panel located on the right side of the nose fuselage gives access to the potentiometer.
The rudder pedals can steer the nosewheel ±8° of center. The potentiometer of the rudder pedal is monitored by the SCU for failure.
The rudder pedal potentiometer is a self contained bolt-on assembly with an electrical connection.
B
A
1 A
RUDDER FORWARD ASSEMBLY
2
FWD
3 4
B
LEGEND 1. Rudder Quadrant 2. Linkage Assembly 3. Rudder Pedal Potentiometer 4. Support Structure.
Figure 32-125. Rudder Forward Assembly (Right Side)
FOR TRAINING PURPOSES ONLY
32-157
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-158
P PRESSURE SWITCH
LEGEND
STEERING MANIFOLD
PRESSURE RETURN MODE SELECTOR VALVE
COMPENSATOR
DASH 8 Q400
POWER-OFF ORIFICE
CHECK VALVE FILTER
ORIFICE RELIEF VALVE
POWER-ON ORIFICE
CHARGE ORIFICE SOLENOID VALVE (NORMALLY CLOSED)
EHSV
LOAD RELIEF VALVES
P R RETURN HYDRAULIC MOTOR
Figure 32-126. Nosewheel Steering Hydraulic Synoptic
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RESTRICTOR ANTI-CAVITATION VALVES
MAINTENANCE TRAINING MANUAL
Nosewheel Steering Manifold Refer to Figure 32-126. Nosewheel Steering Hydraulic Synoptic. The nosewheel steering manifold is a self contained assembly. It is installed on the right front side of the NLG outer cylinder. The Hydraulic Steering Manifold contains the following components: •• Filter/inlet check valve •• Solenoid operated hydraulic valve •• Electro Hydraulic servo valve •• Mode selector valve •• Compensator •• Relief valves (2) •• Shimmy damping orifices (2) (on and off) •• Anti-cavitation check valves (2) •• Pressure switch (LRU) •• Compensator charge orifice
The mode selector valve stops hydraulic pressure to the EHSV when the steering system is in the passive, free castor mode. The SOV is in the closed position until the NLG is compressed when the aircraft lands. The solenoid valve is then energized by signals from the SCU to open the mode selector valve and to configure the steering system for powered steering. The EHSV gets signals from the solenoid valve and converts them into proportional spool displacement. The spool displacement sends hydraulic pressure to the hydraulic motor to drive the reduction gearbox and to steer the nosewheels to the commanded position. Nosewheel position signals are sent to the LVDT installed in the steering manifold, then to the SCU to keep the nosewheels in the commanded steering position. The pressure switch senses any changes in hydraulic pressure that are caused by the failure of the components in the steering manifold. The pressure switch sends a signal to the SCU, when the signal is received. A light on the Caution and Warning panel in the flight compartment illuminates. The pressure switch and the solenoid LRU’s.
•• Case drain check valve •• Return check valve. Hydraulic power is supplied by the No.2 hydraulic system. Two electrical connectors supply power to the steering manifold. The function of the steering manifold is to control the hydraulic pressure to the steering motor for powered steering, and to provide damping. The steering manifold controls hydraulic pressure to the steering hydraulic motor for powered steering of the nosewheels. Hydraulic power for the steering manifold is supplied by the No.2 hydraulic system through the landing gear selector valve extension tubing. Hydraulic fluid is returned to the No.2 hydraulic system through the retraction tubing of the landing gear selector valve. Two electrical connectors supply electric power to the steering manifold. One connector supplies electrical power to the SOV, the EHSV, and to the EHSV LVDT. The second connector supplies electrical power to the pressure switch.
FOR TRAINING PURPOSES ONLY
32-159
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Nosewheel Centering Mechanism Refer to: •• Figure 32-127. N osewheel Centering Actuator. •• Figure 32-128. N osewheel Centering Mechanism. T he nosewheel cent eri ng mecha nism is installed on a collar which is attached to the lower end of the NLG inner cylinder. The spring loaded, centering actuator has a roller bearing that rolls on a race on the NLG outer cylinder. The race has a detent at the centered position. The centering actuator has an attached proximity sensor. The proximity sensor sends a centered signal to the PSEU when the roller is in the detent.
Figure 32-128. Nosewheel Centering Mechanism
NOTE The centering actuator cannot move the nosewheels to the center position.
Figure 32-127. Nosewheel Centering Actuator
32-160
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Power Steering Unit Refer to Figure 32-129. Power Steering Unit. The Power Steering Unit (PSU) is installed on the top of the nose landing gear shock strut. It is a self-contained assembly bolted onto the NLG outer cylinder and keyed to inner cylinder for transmitting torque.
The hydraulic motor operates a reduction gearbox which steers the nosewheels. The function of the power steering unit is to assist the NLG steering system with hydraulic power to steer the nosewheels to the commanded position.
The PSU has a steering manifold, a hydraulic motor, and a reduction gearbox with RVDT’s. Hydraulic pressure to operate the steering is supplied by the No.2 hydraulic system.
1
LEGEND 1. Power Steering Unit 2. Shock Strut. A
2
B
A
B
Figure 32-129. Power Steering Unit
FOR TRAINING PURPOSES ONLY
32-161
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
PAGE INTENTIONALLY LEFT BLANK
32-162
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Removal of Power Steering Unit
32 LANDING GEAR
DASH 8 Q400
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. For full information of the task consult the AMM. 1. Place aircraft in standard configuration for maintenance. 2. Open and lock landing gear doors. 3. Remove steering hydraulic motor. 4. Remove steering feedback assembly. 5. Remove grease and oil from steering gearbox. 6. Remove all bolts and washers securing the gearbox. 7. Remove gearbox using 3 jacking screws designated as AT 31956 NLG Steering Box Puller Kit.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-163
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND 1. Steering Manifold 2. Hydraulic Motor. 1
D
FW
2
Figure 32-130. Hydraulic Steering Motor
Figure 32-131. Steering Feedback Assembly
32-164
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Hydraulic Steering Motor
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-130. Hydraulic Steering Motor. The hydraulic motor is attached to the lower left side of the reduction gearbox. The hydraulic motor drives the feedback gear of the reduction gearbox. The hydraulic motor receives hydraulic pressure through the Electro Hydraulic Servo Valve. The function of the hydraulic motor is to drive the reduction gear assembly to steer the nosewheels to the commanded position.
Steering Feedback Assembly Refer to Figure 32-131. Steering Feedback Assembly. The steering feedback assembly is installed on the top of the NLG shock strut. There are two RVDT’s which are part of the steering feedback assembly. The nosewheel position feedback is accomplished through the previously mentioned RVDT’s. Each RVDT connects to the feedback gear of the reduction gearbox. The SCU uses one RVDT to supply the position of the nosewheels. The SCU uses the second RVDT to check the accuracy of the first RVDT as a fault test. The function of the two RVDT is to provide nosewheel position feedback to the SCU.
FOR TRAINING PURPOSES ONLY
32-165
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND 1. Nosewheel Steering Toggle Switch.
CIR BKR LIGHT
W/S WIPER ICE PILOTS ICE DETECT FLT PNL
STEERING
1
Figure 32-132. Nosewheel Steering Switch
A
OVERHEAD CONSOLE
WT ON WHEELS NOSE STEERING
2 LEGEND 1. Nose Steering (Amber) 2. Weight On Wheels (Amber).
1 A
Figure 32-133. Nosewheel Steering System Caution Lights
32-166
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Steering Switch Refer to Figure 32-132. Nosewheel Steering Switch. The steering switch is located on the pilot side console. The switch is a two position, toggle switch. It has a STEERING and an OFF position. The function of the STEERING switch is to supply 28 VDC to the SCU.
•• Press the BITE switch and scroll through the menu until “NWP1” displays. •• Measure the output voltage at the test jack found at the front of the SCU. The reference indication must be 0 VDC. •• Do the same for “NWP2”. •• This electronically zero’s the two RVDT’s inside the SCU. •• The SCU then electronically sets the travel limits.
CONTROLS AND INDICATIONS Refer to Figure 32-133. Nosewheel Steering System Caution Lights. If any component in the steering system fails, the NOSE STEERING caution light will come on. If the NG WOW sensors or harness are damaged, the WOW caution light will come ON.
Rigging of the RVDT The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
NOTE Make sure that you cannot put a piece of paper between the centering roller and the cam, both sides. •• The STEERING switch must be selected to the ON position
NOTE Make sure that the red dot on top of the RVDT’s is aligned with the black etched line on the base of the RVDT. •• Press the BITE switch and scroll through the menu until “RIG” displays. Hold the switch until “RIG” is flashing.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-167
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-168 AVIONICS RACK C NLG DOWNLOCK NLG WOW 2
11F 2H
7 14
NLG WOW 1 10D
6
NLG DOWNLOCK NLG WOW 2
14 NOSE STEERING
FAIL 5
NLG WOW 1
32-61 A1 PSEU
35 34 36
E
2
1
D
FW
F
WD
F
C
LIMITED AUTHORITY STEERING
NOSE STEERING ARMING SWITCH (FLIGHT COMPARTMENT)
RUDDER PEDAL CONTROL POTENTIOMETER
B
D
FW
A
FULL AUTHORITY STEERING
B
MANIFOLD HANDWHEEL CONTROL POTENTIOMETER
(P5) 28 V DC R MAIN
A
3A
NLG STEER CONT 2
G
8
7
SOLENOID VALVE
3 8
1 2
SOLENOID VALVE
SWITCH CLOSED WHEN HYDRAULIC PRESSURE IS ON PRESS.
1K 9
H
40 32
28V DC IN GND
31 39
4 5
LVDT EXCITATION
16 24
12 11
RVDT EXCITATION
55 54
1 2
SERVO TORQUE MOTOR
SERVO TORQUE MOTOR
PRESSURE SWITCH
C A B
RIGHT DC CBP
(C6) 28 V DC L MAIN
LEFT DC CBP
3A
NLG STEER CONT 1
4 K
5
6
7 8 9
ELECTROHYDRAULIC SERVO VALVE J
NOSE STEERING ARMING SWITCH (FLIGHT COMPARTMENT)
25 47
28V DC IN GND
10
GND
4 1 9 15 23 53 49 50 51 52 46
RVDT #1 4 5 6
PRESSURE ON LVDT POSITION FEEDBACK RVDT 1
RVDT EXCITATION
38 45
1 2
RVDT #2 4 5 6
POSITION FEEDBACK RVDT 2
STEERING CONTROL UNIT
NOSEWHEEL STEERING ASSEMBLY
FW
D
A
Figure 32-134. Nosewheel Steering - Electrical Schematic
C N/C
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
27 29 28
1 2 3
DASH 8 Q400
SOV FAIL 2 A B C
B
CAUTION AND WARNING PANEL (O/H CONSOLE)
MAINTENANCE TRAINING MANUAL
OPERATION NORMAL SYSTEM OPERATION Refer to Figure 32-134. Nosewheel Steering Electrical Schematic.
As the steering motor rotates the NLG inner cylinder, the two RVDT’s send the nosewheel position back to the control unit at Pins 49, 50 and 53 from RVDT 1 and Pins 46, 51 and 52 from RVDT 2.
No.2 Hydraulic pressure is supplied to the nosewheel steering system, through the landing gear selector valve in the DOWN position.
When the feedback signals from the RVDT’s equal the input signals from the potentiometers, the SCU commands the Electro Hydraulic servo valve to the neutral position.
When the nosewheel steering switch is selected ON, power from the left and right main 28 VDC buses is supplied from Pins H and J of the switch, to Pins 40 and 25 of the SCU.
This action causes a hydraulic lock across the steering motor, which holds the steering in the selected position until another input signal is generated.
With WOW, the steering control unit receives inputs from the PSEU as follows:
Operation in the Passive Mode
•• Pin 11F to SCU Pin 7 - NLG Downlock •• Pin 2H to SCU Pin 14 - NLG WOW 2 •• Pin 10D to SCU Pin 6 - NLG WOW 1. The SCU outputs current to the following: •• Solenoid valve •• Servo valve torque motor. The operator input is sensed through the rudder pedal or handwheel control potentiometer output. It is then sent to the SCU. The SCU positions the Electro Hydraulic servo valve to steer left or right. Feedback from the LVDT at Pins 9, 15 and 23, to the SCU confirms servo valve has moved to the correct position. Feedback from the pressure switch on Pins 1 and 4 at the SCU confirms that hydraulic pressure is available.
The system will be in passive mode when any of the following occurs: •• S T E E R I N G s w i t c h s e l e c t e d O F F (requirement for towing) •• SCU de-energized •• SCU receives power from only one CB •• SCU does not receive any of the required inputs from the PSEU •• No hydraulic power •• Landing bypass valve in the bypass position •• NOSE STEERING caution light ON. The mode selector valve is positioned by the valve spring, to connect the hydraulic lines to each side of the hydraulic motor, through the power-off orifice. This allows the hydraulic motor to turn freely when the nosewheel is physically turned by the towbar, or differential engine power while taxiing.
Hydraulic pressure through the solenoid valve acts on the bottom of the Mode Selector Valve (MSV). The MSV sends pressure to the Electro Hydraulic servo valve to drive the steering motor left or right. Return fluid from the other side of the motor returns through the servo valve.
FOR TRAINING PURPOSES ONLY
32-169
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Operational Test of the Nosewheel Steering System
Functional Test of the Nosewheel Steering System
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
Tow the aircraft NLG onto a set of greaseplates and with the nosewheel steering switch selected to ON operate the steering hand control and the rudder pedals.
With the nosewheel steering switch selected to ON operate the steering hand control and the rudder pedals through the full range of motion.
Make sure that the nosewheel position agrees with the position of the steering hand control and rudder pedals.
Using the Protractor measure to ensure full travel of the steering system. Do this with WOW and with WOFFW to test for normal control and indication.
NOTE The steering operation can be sluggish when the hydraulic system is pressurized by the SPU.
CAUTION Make sure that the RVDT’s are adjusted correctly. If the RVDT’s are not adjusted correctly, the nose gear can go through the 70° limit. This can cause damage to the equipment. Install a tow bar and move the NLG to the left and the right 120° stop positions and then back to 0° with the towbar.
NOTE This is to make sure that the NLG can move freely. Make sure the NLG electrical harness has sufficient clearance to not catch on other components and is not stretched.
32-170
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
32-171
32 LANDING GEAR
32-172 FUSELAGE DOOR
LDG INHIBIT FUSE DOORS
WARNING & SYNOPTIC
PSEU
DISCRETE INPUTS PROX SENSOR INP.
CABIN PRESSURE SYSTEM
FUSE DOORS
WOW No. 2 LDG CONTROL & FUSE DOORS
CONTROL DISCRETE OUTPUTS DISCRETE OUTPUTS
WOW No. 2 OUTPUTS
CROSS COMM WOW No. 2 & LDG
LAMP TEST No. 2
PROX SENSOR INP.
DISCRETE INPUTS
FUSE DOORS
PSC B ALTERNATE DOWNLOCK INDICATION & FUSE DOORS
BITE FRONT PANEL KEYPAD & DISPLAY
BITE
WT ON WHEELS
CROSS COMM DISCRETE OUTPUTS
MAINTENANCE DISCRETE OUTPUTS
ADI OUTPUTS CENTRAL MAINTENANCE PANEL PSEU PSS MAINT OPER
LDOOR
NDOOR RDOOR
LEFT
NOSE
RIGHT
LEFT
NOSE
RIGHT
LANDING GEAR
PSC D LAMP TEST No. 1
LDG INDICATION & FUSE DOOR SENSORS
DISCRETE INPUTS
FUSE DOORS
LANDING GEAR INDICATION & FUSE DOORS
fs582a01a.cgm
PROX SENSOR INP.
LDG INDICATIONS LOCK RELEASE
CROSS COMM
HORN MUTE
PROX SENSOR INP.
DISCRETE OUTPUTS PSC E
WOW No. 1, LDG DOORS & FUSE DOOR SENSORS
UP
DN
FUSE DOORS
WOW No. 1 & FUSE DOORS
LDG SELECTOR VALVE
TEST
CROSS COMM DISCRETE OUTPUTS
IFC
WOW No. 1 & LDG
LDG GEAR INOP
Figure 32-135. PSEU Input and Output Block Diagram
LDG DOOR SOLENOID SEQUENCE VALVES
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
ALTERNATE DOWNLOCK & FUSE DOOR SENSORS
AIRCRAFT SYSTEMS REQUIRING WOW & LDG POSITION INPUTS
DASH 8 Q400
WOW No. 2 NOSE CENT & FUSE DOOR SENSORS
PSC A
MAINTENANCE TRAINING MANUAL
32-61-00 PROXIMITY SENSOR SYSTEM
The four discrete inputs to the PSS are: •• Landing gear extension command •• Landing gear retraction command
INTRODUCTION
•• INHIBIT switch set to INHIBIT
The Proximity Sensor System (PSS) is part of the landing gear system.
•• Landing gear lamp test selected.
GENERAL Refer to Figure 32-135. PSEU Input and Output Block Diagram. The PSEU receives signals from 20 landing gear and 11 fuselage door proximity sensors. The PSEU then transmits discrete outputs to the landing gear and door indicators. The Proximity Sensor System has the following components: •• Proximity sensor electronic unit •• Proximity sensors
SYSTEM DESCRIPTION The PSS is a 28 VDC energized, microprocessor based proximity system. The system has signal conditioning, proximity sensing, discrete monitoring, control signals, interface wiring and a BITE keypad with display. The PSS sends discrete outputs as follows: •• Landing gear control •• Landing gear status indication •• Alternate downlock indication •• WOW1 •• Fuselage door indication •• WOW2.
FOR TRAINING PURPOSES ONLY
32-173
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
B
FWD
A
AVIONICS RACK ELECTRICAL INSTALLATION
ME
NU
YE
S
ON OF / F NO
BD
IN
FWD
B
Figure 32-136. Proximity Sensor Electronic Unit
32-174
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
COMPONENT DESCRIPTION Proximity Sensor Electronic Unit Refer to: •• Figure 32-136. P roximity Sensor Electronic Unit. •• Figure 32-137. P roximity Sensor Electronic Unit. The PSEU is installed on the avionics rack. The PSEU receives 28 VDC from the right and left main buses, and the right and left essential buses. The PSEU provides visual indication in the flight compartment for: •• Gear position •• Gear doors position, and •• Fuselage doors status. The primary functions of the PSEU are as follows: •• Monitor, indicate and operate the landing gear extension, and retraction system •• Monitor and supply the uplock, down lock, and WOW data to other systems •• Supply indication for the passenger and baggage doors. The logic circuits of the PSEU use the “near” and “far” condition of the proximity sensors for logic equations.
Figure 32-137. Proximity Sensor Electronic Unit
Built-In-Test-Equipment The PSEU contains BIT and BITE functions. These functions let the PSEU do the maintenance, and functional testing of the PSS. The ON/OFF button turns the BITE display ON or OFF. When you change from OFF to ON, the BITE display always starts at a PRESENT FAULTS? prompt. You will push the menu button to return to the most recent, higher level prompt. The UP button gives you access to the previous fault or status display, when you get a list of displays. The DOWN button sequences to the subsequent fault or status display on the list.
FOR TRAINING PURPOSES ONLY
32-175
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Installation of the Proximity Sensor Electronic-Unit The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Before you touch the PSEU, put on the static wrist strap •• After installation wait 3 minutes, this allows the PSEU to complete the power up test •• On the PSEU, ERASE the FAULT HISTORY if there is one.
NOTE T h e m e s s a g e ERASE IN PROGRESS w i l l a p p e a r , followed by the message FAULT HISTORY ERASE COMPLETE.
Retrieval of Data from the Proximity Sensor Electronic Unit (PSEU) The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• On the PSEU, push the ON/OFF button The PSEU display shows the prompt for the first item on the TOP LEVEL menu, the PRESENT FAULTS?
NOTE The items in the top menu show in the sequence that follows: 1. PRESENT FAULTS 2. FAULT HISTORY 3. RIGGING HELP 4. RIGGING HISTORY 5. SYSTEM STATUS 6. FAULT HISTORY ERASE. •• If you push the MENU button, the PSEU display shows the prompt for the previous item on the top menu
NOTE If there is no BITE keypad activity for 15 minutes the PSEU display will go blank. •• Push the MENU button to show the ERASE FAULT HISTORY? prompt. If the fault clears while the PSEU display shows the fault and there is no keypad activity, the display will show the FAULT NO LONGER PRESENT message. If the fault returns while the PSEU display shows the FAULT NO LONGER PRESENT message and there is no keypad activity, the display will show the applicable fault message.
32-176
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Erase the Data from the Proximity Sensor Electronic Unit (PSEU)
Operational Check of the Proximity Sensor Electronic Unit
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
NOTE The PSEU takes 3 minutes to complete its power-up self test.
•• Push the ON/OFF button on the PSEU and select PRESENT FAULTS •• Push the YES button
NOTE
•• Turn the PSEU ON •• The PRESENT FAULTS prompt is shown
This test is intended to be done without any faults present on the PSEU.
•• Push the NO button again and again until the display shows the ERASE FAULT HISTORY? prompt
•• On the maintenance panel, the PSEU OPER light comes on
•• Select YES, the PSEU will ask ARE YOU SURE?
•• On the maintenance panel, the PSS MAINT (check required) light goes out
•• Select YES, the PSEU display shows the ERASE IN PROGRESS message
•• If the PSS MAINT light stays on, faults are present. Refer to the list of known nuisance faults, see AMM
•• Wait until the PSEU display shows the FAULT HISTORY ERASE COMPLETE message.
Revision 0.4
•• C l e a r a l l f a u l t s a n d t h e n d o t h i s Operational Check again.
FOR TRAINING PURPOSES ONLY
32-177
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
S19 NGDRCL S09 NGDN1 S11 NGLK1 S03 NGWOFW1 S31 PADRCL
PASSENGER AIRSTAIR DOOR
S33 PADRLK
S07 LGDLK1
S08 LGDLK2
S15 LGUPLK
S17 LGDRCL
S01 LGWOW1
AFT PASSENGER DOOR AFT BAGGAGE DOOR
S02 LGWOW2 S37 APDRCL S39 APDRLK S43 ABDRCL S45 ABDRLK
S18 NWCENT S10 NGDN2 S12 NGLK2 S04 NGWOFW2 S34 FBDRCL S36 FBDRLK
FWD BAGGAGE DOOR
S46 EDRCLLK
EMERGENCY EXIT DOOR
S13 RGDLK1
S14 RGDLK2
S16 RGUPLK
S20 RGDRCL
S05 RGWOW1
S06 RGWOW2
S40 ASDRCL S42 ASDRLK
SERVICE DOOR
fs432a01.cgm
Figure 32-138. Proximity Sensors - Locations
32-178
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
Proximity Sensors Refer to: •• Figure 32-138. P roximity Sensors - Locations. •• Figure 32-139. Proximity Sensors. There are 31 proximity sensors. Each main landing gear has six proximity sensors. The nose landing gear has eight. There are eleven sensors that monitor: •• Passenger entrance door •• The baggage compartment doors •• The emergency exit doors, and •• The service door. The proximity sensors are hermetically sealed, variable reluctance, two wire devices. The inductance at the sensor changes with the sensor’s proximity to the target. As the target gets closer to the sensor face, the inductance increases.
Figure 32-139. Proximity Sensors
The proximity sensors are not repairable. The function of the sensors is to supply position data to the PSEU.
FOR TRAINING PURPOSES ONLY
32-179
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Installation of the Proximity Sensors
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• There are many proximity sensors installed on the landing gear and doors in different locations. •• Many have different clearances and wire lead lengths. •• T h e P r o x . s e n s o r s d o n o t c o m e terminated, you will need to cut the wires, terminate them and insert the pins into the connector.
CAUTION Do not bump or scratch the face of the proximity sensor because this can damage the proximity sensor. •• Adjust the clearance between the sensor and the target to match the application and location.
Rigging of the Proximity Sensors The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Adjust the sensors to the nominal clearances specified in the AMM. •• Many sensors have different clearances and therefore inductance. •• At the PSEU, use the SYSTEM STATUS MENU to make sure that the inductance in each sensor, is correct. •• Adjust sensor clearance from the nominal, to achieve the permitted inductance.
32-180
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Landing Gear Control The PSEU provides discrete outputs that are used to control the movement of the landing gear (extend or retract), and landing gear doors (open or close). The PSEU generates seven discrete outputs that provide the landing gear control function. The outputs include the Flight Data Recorder, and the no smoking sign.
Landing Gear Indications The following conditions are monitored by the landing gear indication system: •• Right, left, and nose gear door position •• Right, left, and nose gear position. The outputs of the proximity sensors are processed by the PSEU. The PSEU generates 16 discrete outputs which are sent to the two IOP in the IFC’s, the landing gear control panel, the caution and warning panel, the Antiskid/Brake Control Unit, and the Nosewheel Steering Control Unit. The landing gear control provides visual indication for each of the three landing gears:
32 LANDING GEAR
DASH 8 Q400
ALTERNATE DOWNLOCK INDICATIONS The Alternate Down Lock Indication (ADI) provides a second DOWN and LOCKED indication of the three landing gears. This function is used if the primary landing gear indication function shows an unsafe, or gear disagree condition. ADI is independent from the primary indication. Different sensors and PSC card are used to process inputs. The following conditions are monitored by the ADI: •• Right and left gear down and locked •• Nose gear down and locked. The left and right gears each have an alternate sensor that monitors down and locked. The nose gear has one sensor for the down position and one for locked. The Advisory lamp test on the Passenger Warning panel will cause the ADI lights to come on. Incorrect Landing Gear Configuration/Landing Gear Warning Horn. This information can be found in MTM Vol 1 Chapter 31-62-00 Landing Gear Warning.
•• GEAR DOWN and LOCKED •• GEAR NOT IN COMMANDED POSITION •• GEAR DOOR NOT CLOSED.
FOR TRAINING PURPOSES ONLY
32-181
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
#1 STALL SYST FAIL #2 STALL SYST FAIL
FLT DATA RECORDER GPWS
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LAP RIVE
LDG GEAR INOP
WT ON WHEELS
LAP WER
NOSE STEERING
FUELING ON
MAIN BAT HOT
FUSELAGE
X BAT HOT
DOORS
Figure 32-140. CAWP with WOW Caution
32-182
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
WOW Functions Refer to Figure 32-140. CAWP with WOW Caution. The WOW function provides discrete outputs to other aircraft systems. Two separate channels WOW No.1 and WOW No.2 generate the weight-on-wheels discrete outputs.
PSEU Operating Mode
Condition
WOW
At least four of any of the six conditions that follow: LGWOW1 = True LGWOW2 = True RGWOW1 = True RGWOW2 = True NGWOFW1 = False NGWOFW2 = False
The PSEU generates five types of WOW outputs, they are as follows: •• All three gear (WOW) •• Main gear (MGWOW) NEAR •• Main gear (MGWOFFW) FAR •• Nose gear (NGWOW) FAR •• Nose gear (NGWOFFW) NEAR. There are two discrete outputs supplied by the PSEU that are special to WOW1 and, WOW2 systems. These signals are WOW1 Operational, and WOW2 Operational respectively. These two signals are supplied in the same way. The CAWP uses these two discrete outputs to show that the WOW functions operate correctly. If one of the two signals become deactivated on the CAWP, the WT ON WHEELS caution light illuminates. For this to occur, the WOW Operational discrete output will deactivate in the conditions as follows: •• There is a disagreement between two of the WOW sensors (in the same WOW system), that the aircraft is either on the ground, or in the air. •• A minimum of one proximity sensor becomes defective in each of the WOW1 and WOW2 systems at the same time.
Operational Check of the Weight On Wheels System The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
NOTE You can do this check on either the LH or RH gear. Make sure that all the hydraulic power is off. •• Insert an anti-target (copper) at a main landing-gear proximity sensor to simulate an erroneous far target (“air”) state. •• Make sure the WOW caution light comes on.
NOTE There will be a 30 second delay before the light comes on. •• Remove the anti-target from the WOW proximity sensor. •• Make sure the WOW caution light goes out.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-183
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-00-00 APPENDIX MAINTENANCE CONSIDERATION The following are abbreviated descriptions of the maintenance practices and are intended for training purposes only. For a more detailed description of the practices, refer to the tasks in the Bombardier AMM PSM 1-84-2.
Safety Precautions WARNING
BE CAREFUL WHEN YOU REMOVE THE DOOR LOCKPIN. THE LANDING GEAR DOORS WILL CLOSE IF YOU PRESSURIZE THE HYDRAULIC SYSTEM. IF YOU DO NOT DO THIS, IT CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. WARNING
THE LANDING GEAR DOORS CLOSE QUICKLY WHEN YOU PRESSURIZE THE HYDRAULIC SYSTEM. MAKE SURE THAT ALL PERSONNEL AND EQUIPMENT ARE CLEAR OF THE LANDING GEAR. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. WARNING
DO NOT USE FORCE WHEN YOU ENGAGE THE GROUND LOCK OF THE NOSE LANDING GEAR. IF FORCE IS NECESSARY, THE LANDING GEAR MAY NOT BE SAFE AND CAN RETRACT ACCIDENTALLY. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE AIRCRAFT. 32-184
WARNING
REMOVE THE TOWBAR FROM THE NOSE LANDING GEAR BEFORE YOU SET THE STEERING SWITCH TO THE ON POSITION. IF YOU SET THE STEERING SWITCH TO THE ON POSITION, THE NOSEWHEELS WILL AUTOMATICALLY GO TO THE NEUTRAL POSITION. IF YOU DO NOT REMOVE THE TOWBAR, YOU CAN CAUSE INJURY TO PERSONS OR DAMAGE TO THE EQUIPMENT. WARNING
BEFORE YOU CONNECT THE TOWBAR TO THE AIRCRAFT MAKE SURE YOU SET THE NOSEWHEEL STEERING SWITCH TO THE OFF POSITION. IT MUST STAY IN THE OFF POSITION WHILE YOU TOW THE AIRCRAFT. THE NOSEWHEEL HAS TO BE IN THE MIDDLE POSITION BEFORE YOU DISCONNECT THE TOWBAR. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. WARNING
MAKE SURE THAT THE ALTERNATE RELEASE DOOR AND THE ALTERNATE EXTENSION DOOR ARE FULLY CLOSED BEFORE YOU USE THE PRIMARY RETRACTION OR EXTENSION SYSTEM OF THE LANDING GEAR. IF YOU DO NOT DO THIS, IT CAN CAUSE DAMAGE TO LANDING GEAR SYSTEM COMPONENTS.
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Main Landing Gear Lower Bearing Seal A spare dynamic seal is installed in the shock strut assembly of the main landing gear (MLG). Defective dynamic seals may be replaced with this spare dynamic seal. WARNING
THE SHOCK STRUT ASSEMBLY IS PRESSURIZED WITH NITROGEN GAS. RELEASE THE PRESSURE BEFORE YOU REMOVE THE OIL/NITROGEN FITTINGS OR THE TORQUE LINK PINS. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURY TO PERSONNEL OR DAMAGE TO EQUIPMENT.
Standard Configuration for an ‘On-Jacks’ Weight-On-Wheels (WOW) Condition
Standard Configuration for an ‘On-Ground’ Weight-Off-Wheels (WOFFW) Condition To put the aircraft in the weight-off-wheels configuration: 1. Connect the pitot/static tester to the No.1 and No.2 systems. 2. Put the de-actuator (copper) targets on the main landing gears. 3. Put the actuator (steel) targets on the nose landing gear. 4. Adjust the tester until the primary flight displays show an airspeed of a minimum of 40 kts. 5. Make sure that the airspeed is valid on the PFD’s (indicators DO NOT show red). 6. Make sure that the WT ON WHEELS caution light does not come on.
Tools and Equipment To put the aircraft in the weight-on-wheels configuration: 1. Put the actuator (steel) targets on the main landing gears. 2. Put the de-actuator (copper) targets on the nose landing gear.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-185
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-00-00 SPECIAL TOOL & TEST EQUIPMENT •• GSB0700016 NLG Axle Jack •• GSB0700023 Axle Jack •• GSB0700024 Tail Stand •• GSB0900004 Towhead Assembly •• GSB0900005 Towbar •• GSB1000020 Pin, NLG Door Ground Lock •• GSB1000028 Pin, MLG Door Ground Lock •• GSB2000009 Digital Inclinometer (Protractor) •• GSB2400001 Digital Multimeter - Hand Held •• GSB2400011 Static Wrist Strap •• GSB2400016 or equivalent Electrical and avionics tool kit •• GSB2700007 Cable Tension Meter •• GSB2700008 Rigging Pin Kit •• GSB2700008-09 Rigging Pin, 0.1875-4.00 in. (4.76-101.6 mm) L-Pin •• GSB2700008-15 Rigging Pin •• GSB2700008-16D Target-Actuator (Steel) •• GSB2700008-30 Target-Actuator (Steel) •• GSB2700008-30 Target 0.030 in (0.762 mm) Thick •• GSB2700008-32 Target-De-Actuator (Copper) •• GSB2700008-32 Target 0.040 in (1.02 mm) Thick •• GSB2700009 Cable Tension Meter •• GSB29000YY Unit - Hydraulic Power, 28 - 34 GPM •• GSB3241005 NLG Axle Nut Socket •• GSB3241006 MLG Axle Nut Socket •• GSB3242003 Anti-skid Tester •• GSB3242004 Adapter, Wheel Speed Transducer Spin-Up •• GSB3242005 or R1722 Adapter, Anti-skid Tester •• GSB3240006 or equivalent Tool - Brake Application •• GSB3251006 NLG-Steering Angle Protractor •• GSB3411011 Test Set - Air Data •• Landing Gear P/N AT-31859 Assembly Tool (Used To Torque the Jam Nut at the Gland Nut) •• M83723/31-20 Insert/Extract Tool
32-186
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
•• AT 31791 Assembly Tool •• AT 31792 Metering Pin Tool •• AT 31794 Assembly Tool •• AT 31819 Barrel Nut Tool •• AT 31822 Assembly Tool •• AT 31823 - Use with Gland Nut P/N 47118-1. Assembly Tool •• AT 31956 NLG Steering Box Puller Kit •• AT 32027 Bullet, MLG Axle •• AT 55447 Assembly Tool •• AT 57495 - Use with Gland Nut P/N 47118-3. Assembly Tool •• AT 31849 Tool - Spring Compression, MLG Stabilizer Brace •• AT 56653 Assembly Tool •• AT 56658 Assembly Tool •• AT 56659 Assembly Tool •• GE56987 Arbor •• SA460168 or FTP-323002-001-58 (Local Manufacture) with Jam Nut P/N MS21340-08 (Qty. 2) •• MLG Door Sensor Shop Aid •• Goodrich Landing Gear P/N AT-31838 Assembly Tool (Used To Torque the Jam Nut at the Gland Nut) •• DHC8PROX-RTP-0102 Proximity Sensor De-actuator Test Target •• Local Manufacture Grease Plate •• 05-7024-3600-A3 Hydraulic Power Unit •• CG-56806 Setting Tool - Retract Actuator, MLG •• GC 55979 Latch Wear Measurement Tool (Surface Gauge) •• Commercially Available Brake Bleed Kit •• G601R324301-1 or equivalent Brake Bleed Hose •• Commercially Available Tensiometer •• 964-0446-001 Download Unit •• Commercially Available Insertion/extraction Tool M81969/14-10 (Red/Orange) •• Commercially Available Crimping Tool AF8 or M22520/1-01 •• Commercially Available Positioner TH163 or M22520/1-04 •• Commercially Available Daniels PMBT 1200 Power Miniband Tool or Equivalent
FOR TRAINING PURPOSES ONLY
32-187
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-00-00 MAINTENANCE PRACTICES Refer to the Bombardier AMM PSM 1-84-2 for details on these maintenance procedures: •• AMM 32-00-00-840-801 Open and Lock the Landing Gear Doors •• AMM 32-00-00-840-802 Unlock and Close the Landing Gear Doors •• AMM 32-00-00-840-803 S tandard Configuration for an ’On−Jacks‘ Weight−On−Wheels (WOW) Condition •• AMM 32-00-00-840-804 S tandard Configuration for an ’On−Ground‘ Weight−Off− Wheels (WOW) Condition •• AMM 32-00-00-890-801 Sequence of Operations for a Main Landing Gear Replacement •• AMM 32-00-01-200-801 S equence of Operations for the Nose Landing Gear Replacement •• AMM 32-00-01-200-802 F luid Leakage Inspection of the Nose and Main Landing−Gear Shock−Struts •• AMM 32-00-01-640-801 L ubrication of the Nose and Main Landing Gear (MRB #320001−201) •• AMM 12-20-01-640-802 Lubrication of the Nose Landing Gear •• AMM 12-20-01-640-803 Lubrication of the Main Landing Gear •• AMM 12-20-01-640-804 Lubrication of the Landing Gear Door Hinges and Linkages •• AMM 12-20-01-640-818 L ubrication of the Chrome Piston Surface on Landing Gear Shock−Struts •• AMM 12-10-32-610-802 Servicing of the MLG Shock Strut •• AMM 32-11-01-000-801 Removal of the Shock Strut •• AMM 32-11-01-400-801 Installation of the Shock Strut •• AMM 32-11-01-000-802 Removal of a MLG Dressed Shock Strut •• AMM 32-11-01-400-802 Installation of a MLG Dressed Shock Strut •• AMM 32-11-04-000-801 Removal of the Axles •• AMM 32-11-04-400-801 Installation of the Axles •• AMM 32-11-04-000-802 Removal of the Wheel−Speed Transducer Electrical−Harness •• AMM 32-11-04-400-802 Installation of the Wheel−Speed Transducer Electrical−Harness •• AMM 32-11-21-000-801 Removal of the Yoke •• AMM 32-11-21-400-801 Installation of the Yoke •• AMM 32-11-01-960-801 Replacement of the Main Landing Gear Lower Bearing Seal •• AMM 32-11-01-611-801 S ervice the Main Landing Gear Shock Strut (MRB#321100−203) •• AMM 12-10-32-610-802 Servicing of the MLG Shock Strut
32-188
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
•• AMM 12-10-32-610-804 Servicing of the MLG Shock Strut − Aircraft on Jacks •• AMM 32-12-00-220-801 Detailed Inspection of the MLG Doors Mechanism •• AMM 12-10-32-210-801 Extension Check of the NLG Shock Strut •• AMM 32-21-00-210-801 General Visual Inspection of the Nose Landing Gear •• AMM 32-21-01-000-801 Removal of the NLG Shock Strut •• AMM 32-21-01-400-801 Installation of the NLG Shock Strut •• AMM 32-21-01-611-801 S ervice the Nose Landing Gear Shock Strut (MRB #322100−202) •• AMM 12-10-32-610-801 Servicing of the NLG Shock Strut •• AMM 12-10-32-610-803 Servicing of the NLG Shock Strut − Aircraft on Jacks •• AMM 32-22-11-830-801 Rigging of the NLG Forward Doors •• AMM 32-25-06-710-801 O perational Test of the Nose−Gear Ground−Lock Position Indication System (Modsum 4−429586) •• AMM 32-31-00-867-801 Retract and Extend the Landing Gear •• AMM 32-31-00-867-802 Retract and Extend the Nose Landing Gear •• AMM 32-31-00-870-801 Bleed the Landing Gear Primary Extension and Retraction System •• AMM 29-21-06-830-801 Rigging of the Emergency Release Selector Valve •• AMM 29-21-00-611-801 S ervicing of the Landing Gear Alternate Extension Hydraulic Reservoir (MRB #292000−201) •• AMM 12-10-29-611-803 S ervicing of the Alternate Landing−Gear Extension Hydraulic Reservoir •• AMM 32-34-00-710-801 Operational Test of the Alternate Extension System •• AMM 12-10-32-910-801 Tire Pressure Standard Practices •• AMM 12-10-32-614-803 Filling of the Tires with Nitrogen •• AMM 32-40-00-210-802 G eneral Visual Inspection of the Nose and Main Landing Gear Wheel and Tire Assemblies (MRB #324000−201) •• AMM 32-41-01-000-801 Removal of the Main Wheel and Tire Assembly •• AMM 32-41-01-400-801 Installation of the Main Wheel and Tire Assembly •• AMM 32-41-06-000-801 Removal of the Nose Wheel and Tire Assembly •• AMM 32-41-06-400-801 Installation of the Nose Wheel and Tire Assembly •• AMM 32-40-00-720-801 F unctional Check of the Nose and Main Landing Gear Tire Pressure (MRB #324000−202) •• AMM 32-40-00-210-803 G eneral Visual Inspection of the Brake Wear Pins (MRB #324000−206) •• AMM 32-42-01-000-801 Removal of the Main Wheel Brake Units •• AMM 32-42-01-400-801 Installation of the Main Wheel Brake Units
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-189
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• AMM 32-42-00-870-801 Bleed the Brakes with Main Brake System •• AMM 12-10-32-863-801 Pressurization of the Parking Brake System with the Hand Pump •• AMM 32-40-00-720-802 F unctional Check of the Brake Accumulator Pre−charge Pressure (MRB #324000−208) •• AMM 12-10-32-210-803 Pressure Check of the Parking Brake Accumulator •• AMM 12-10-32-614-801 Servicing of the Parking Brake Accumulator with Nitrogen •• AMM 32-46-00-720-801 Functional Test of the Anti−Skid Control System (Built−in Test) •• AMM 32-51-26-000-801 Removal of the Power Steering Unit •• AMM 32-51-26-400-801 Installation of the Power Steering Unit •• AMM 32-51-00-710-801 Operational Test of the Nose Wheel Steering System •• AMM 32-51-00-720-801 Functional Test of the Nosewheel Steering System •• AMM 32-51-01-742-801 R etrieval of Data from the Nosewheel−Steering Electronic Control−Unit (SCU) •• AMM 32-51-01-743-801 E rase the Data from the Nosewheel−Steering Electronic Control− Unit (SCU) •• AMM 32-61-06-390-801 Application of Sealant to the Landing−Gear Proximity Sensors •• AMM 32-61-01-000-801 Removal of the Proximity Sensor Electronic−Unit •• AMM 32-61-01-400-801 Installation of the Proximity Sensor Electronic−Unit •• AMM 32-61-06-000-802 Removal of the Proximity Sensors •• AMM 32-61-06-400-802 Installation of the Proximity Sensors •• AMM 32-61-00-710-801 O perational Check of the Proximity Sensor Electronic Unit (PSEU) BITE Panel (MRB# 326100−201) •• AMM 32-61-00-742-801 R etrieval of Data from the Proximity Sensor Electronic Unit (PSEU) •• AMM 32-61-00-743-801 Erase the Data from the Proximity Sensor Electronic Unit (PSEU)
32-190
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CHAPTER 27 FLIGHT CONTROLS CONTENTS Page
27-00-00 FLIGHT CONTROLS.................................................................................. 27-1 Introduction......................................................................................................... 27-1 General................................................................................................................ 27-3 27-12-00 AILERON SYSTEM.................................................................................... 27-4 General................................................................................................................ 27-4 System Description.............................................................................................. 27-5 Component Description........................................................................................ 27-6 Aileron Forward Quadrant............................................................................. 27-6 Rigging of Aileron Quadrant Microswitch............................................................ 27-7 Control Column to Control Column Rigging & Control Column to Aileron Quadrant................................................................ 27-7 Aileron Quadrant to Splitter Quadrant.................................................................. 27-9 Aileron Terminal Quadrant................................................................................. 27-11 Aileron Splitter Quadrant to Aileron Terminal Quadrant Rigging....................... 27-11 Aileron Geared Tab..................................................................................... 27-13 Rigging of the Aileron Geared Tab..................................................................... 27-13 Aileron Position LVDT................................................................................ 27-15 Operation.................................................................................................... 27-15 Lubrication of Aileron and Roll Spoiler Control Column Chains....................... 27-15 Aileron LVDT Fail Fault Isolation...................................................................... 27-15
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-i
27 FLIGHT CONTROLS
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
27-13-00 AILERONS TRIM AND CENTERING...................................................... 27-16 General.............................................................................................................. 27-16 Component Description...................................................................................... 27-17 27 FLIGHT CONTROLS
Trim Actuator.............................................................................................. 27-17 Ground Adjustable Trim Tab........................................................................ 27-18 Operation........................................................................................................... 27-19 Normal Operation....................................................................................... 27-19 Abnormal Operation.................................................................................... 27-19 Operational Test of the Aileron Control System.................................................. 27-19 Operational Test of the Aileron Trim System...................................................... 27-19 27-14-00 AILERON SURFACES............................................................................... 27-23 Introduction....................................................................................................... 27-23 General.............................................................................................................. 27-23 Aileron Terminal Quadrant to Aileron Surface Rigging...................................... 27-23 Rigging of the Aileron Control System Stops..................................................... 27-23 Component Description...................................................................................... 27-25 Aileron Control Surfaces............................................................................. 27-25 27-70-00 AILERON GUST LOCK SYSTEM............................................................ 27-27 Introduction....................................................................................................... 27-27 General.............................................................................................................. 27-27 System Description............................................................................................ 27-27 Operational Test of the Aileron Gust Lock System............................................. 27-27 27-61-00 ROLL SPOILERS SYSTEM...................................................................... 27-29
27-ii
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Introduction....................................................................................................... 27-29 General.............................................................................................................. 27-29
Component Description...................................................................................... 27-33 Spoiler Quadrant......................................................................................... 27-33 Spoiler Splitter Quadrant............................................................................. 27-35 Clutch Units................................................................................................ 27-37 Power Control Units (Inboard/Outboard)..................................................... 27-39 Unload Valves............................................................................................. 27-42 Linear Variable Differential Transformer (LVDT)........................................ 27-43 Spoiler Cables Sensor................................................................................. 27-45 Controls and Indications.............................................................................. 27-46 Operation........................................................................................................... 27-51 Roll Spoiler Hydraulics............................................................................... 27-51 Hydraulic Failure........................................................................................ 27-51 Operational Test of the Roll Spoiler System....................................................... 27-51 Flight Mode................................................................................................ 27-53 Roll Spoiler Jam.......................................................................................... 27-53 Operational Test of the Spoiler Jam Detect System................................................................................. 27-57 Operational Check of the Roll Spoiler SPLR 1 & SPLR 2 Push Off Switchlights.......................................................... 27-59 Complete Roll Jam Using Roll Disconnect System..................................... 27-59 Operational Check of the Roll Spoiler Cable Sensor Assembly.......................... 27-61
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-iii
27 FLIGHT CONTROLS
System Description............................................................................................ 27-31
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Roll Spoiler Cable Break (Operating Cable Sensor System)........................ 27-63 27-62-00 SPOILER SYSTEM IN GROUND MODE.................................................. 27-65 Introduction....................................................................................................... 27-65 27 FLIGHT CONTROLS
General.............................................................................................................. 27-65 System Description..................................................................................... 27-69 Component Description...................................................................................... 27-72 Lift Dump Valves........................................................................................ 27-72 Controls and Indications.................................................................................... 27-73 Operational Test of the Ground Spoiler System.................................................. 27-75 27-63-00 SPOILER PANELS.................................................................................... 27-76 27-16-00 ROLL DISCONNECT SYSTEM................................................................ 27-77 Introduction....................................................................................................... 27-77 General.............................................................................................................. 27-77 Component Description...................................................................................... 27-78 Roll Disconnect Handle............................................................................... 27-78 Roll Disconnect Clutch Mechanism............................................................ 27-80 Interfaces.................................................................................................... 27-81 Rigging of the Roll Disconnect System.............................................................. 27-83 Operational Check of the Roll Disconnect Mechanism....................................... 27-83 27-21-00 RUDDER SYSTEM................................................................................... 27-85 Introduction....................................................................................................... 27-85 General.............................................................................................................. 27-85 System Description............................................................................................ 27-87
27-iv
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Component Description...................................................................................... 27-89 Rudder Pedals............................................................................................. 27-89
Adjustment of the Rudder Pedal Position Sensor................................................ 27-91 Rudder Mixer Quadrant............................................................................... 27-92 Rudder Aft Quadrant................................................................................... 27-95 Rig Rudder Pedals to Rudder Forward Quadrant & Rig forward Quadrant to Rudder Mixer Quadrant........................................... 27-95 Rigging of Rudder Mixer Quadrant to the Rudder Aft Quadrant......................... 27-95 Power Control Units.................................................................................... 27-97 Rudder Hinge Moment Limiting (HML)..................................................... 27-97 Rudder Shut-off Valves.............................................................................27-100 PCU Input Bungee....................................................................................27-103 Rigging of the Upper Spring Strut Motion Detector & Rigging of the Lower Spring Strut Motion Detector........................................27-103 Rudder Position LVDT..............................................................................27-104 A rudder position LVDT is located in the vertical stabilizer......................27-104 Controls and Indications............................................................................27-105 Rigging of Rudder PCUs with Hydraulic Power...............................................27-107 Operational Test of the Rudder Shutoff Valves.................................................27-108 Operation.........................................................................................................27-111 Normal System Operation.........................................................................27-111 Operational Test of the Rudder Control System................................................27-113 Abnormal Operation..................................................................................27-115
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-v
27 FLIGHT CONTROLS
Rudder Forward Quadrants.......................................................................... 27-91
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Lower Rudder PCU Jam Operation............................................................27-117 27-22-00 RUDDER FEEL AND SUMMING...........................................................27-119 Introduction.....................................................................................................27-119 27 FLIGHT CONTROLS
General............................................................................................................27-119 Component Description....................................................................................27-122 Trim Actuator............................................................................................27-122 Operational Test of the Rudder Trim System....................................................27-122 Summing-Yaw Damper Actuator...............................................................27-124 Rudder trim operation......................................................................................27-127 Rudder Trimming .....................................................................................27-127 27-23-00 RUDDER SURFACES.............................................................................27-128 General............................................................................................................27-128 System Description..........................................................................................27-128 27-31-00 ELEVATOR SYSTEM..............................................................................27-129 Introduction.....................................................................................................27-129 General............................................................................................................27-129 System Description..........................................................................................27-131 Component description.....................................................................................27-133 Control Columns.......................................................................................27-133 Handwheels...............................................................................................27-133 Left Forward Quadrant..............................................................................27-135 Aft Quadrants............................................................................................27-136 Elevator-Power Control Units (PCU).........................................................27-137
27-vi
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Component Description....................................................................................27-139 Elevator PCU............................................................................................27-139
Torque Tubes.............................................................................................27-141 Centering Device.......................................................................................27-141 Overload Bungees.....................................................................................27-142 Overload Bungees (PCU INPUT)..............................................................27-143 Elevator Position LVDT.............................................................................27-143 Controls and Indications............................................................................27-145 Asymmetry Check of the Elevators..................................................................27-145 Operational Test of the Elevator Control System..............................................27-147 Elevator Droop Rate Check..............................................................................27-147 27-32-00 ELEVATOR FEEL AND TRIM................................................................27-151 Introduction.....................................................................................................27-151 General............................................................................................................27-151 System Description..........................................................................................27-152 Operational Test of the Pitch Feel System........................................................27-153 Dual Pitch Trim Actuator..........................................................................27-155 Pitch Feel Actuators..................................................................................27-155 Controls and Indications..................................................................................27-156 Elevator Trim Indicator.............................................................................27-156 Pitch Trim Split Switch.............................................................................27-157 Elevator Trim Shutoff Switchlights...........................................................27-158
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-vii
27 FLIGHT CONTROLS
Compensator.............................................................................................27-140
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Caution Lights..........................................................................................27-159 Operation.........................................................................................................27-161 Pitch Trim.................................................................................................27-161 27 FLIGHT CONTROLS
Manual Trim..............................................................................................27-161 Abnormal Operation Pitch Trim Runaway.................................................27-163 Autopilot Trim..........................................................................................27-165 Flap Compensation Trim...........................................................................27-165 Operational Test of the Elevator Control System..............................................27-165 27-33-00 STALL WARNING /STICK PUSHER........................................................27-167 Introduction.....................................................................................................27-167 General............................................................................................................27-167 System Description..........................................................................................27-167 Operational test of the Stall Protection Module................................................27-169 Component Description....................................................................................27-170 Stall Protection Modules...........................................................................27-170 Stick Pusher Actuator................................................................................27-171 Stick Pusher Capstan.................................................................................27-173 Stick Pusher Quadrant...............................................................................27-174 Stick Shaker..............................................................................................27-175 Angle of Attack Transducer (AOA)...........................................................27-176 Stick Pusher Shutoff Annunciator Switch..................................................27-177 Stall Warn Test Switch..............................................................................27-177 Inputs........................................................................................................27-179
27-viii
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Outputs.....................................................................................................27-181 Controls and Indications..................................................................................27-185
27-34-00 ELEVATOR SURFACES..........................................................................27-189 Introduction.....................................................................................................27-189 General............................................................................................................27-189 27-38-00 PITCH DISCONNECT SYSTEM.............................................................27-191 Introduction.....................................................................................................27-191 General............................................................................................................27-191 Pitch Disconnect Handle...........................................................................27-191 Pitch Disconnect Clutch Mechanism.........................................................27-191 Operational Check of the Elevator Control Pitch Disconnect Mechanism ........27-192 27-51-00 FLAP CONTROL SYSTEM....................................................................27-195 Introduction.....................................................................................................27-195 General............................................................................................................27-195 Component Description....................................................................................27-197 Flap Control Unit (FCU)...........................................................................27-197 Flap Selector Lever/Quadrant....................................................................27-201 Flap Lever Transducer...............................................................................27-201 Operational Test of the Flap Control Module....................................................27-201 Operation.........................................................................................................27-203 Normal Flap Operation..............................................................................27-203 Wing Flap System Electrical Checks................................................................27-203
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-ix
27 FLIGHT CONTROLS
Tests..........................................................................................................27-188
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Operational Test of the Wing Flaps...................................................................27-204 27-52-00 FLAP DRIVE SYSTEM...........................................................................27-206 Introduction.....................................................................................................27-206 27 FLIGHT CONTROLS
General............................................................................................................27-206 System Description..........................................................................................27-207 Component Description....................................................................................27-209 Flap Power Unit (FPU)..............................................................................27-209 Transmission Shafts..................................................................................27-210 Torsion Bars..............................................................................................27-211 Lubrication of Flap Ball Screw Actuators.........................................................27-212 Flap Tracks................................................................................................27-213 27-53-00 FLAP POSITION INDICATION..............................................................27-217 Introduction.....................................................................................................27-217 General............................................................................................................27-217 System Description..........................................................................................27-218 Component Description....................................................................................27-219 Flap Position Indication Unit (FPIU).........................................................27-219 Flap Position Transducer...........................................................................27-220 Controls and Indications..................................................................................27-221 Operation.........................................................................................................27-223 Normal Flap Position Indication Operation...............................................27-223 27-54-00 FLAP SURFACES....................................................................................27-224
27-x
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Erase the Data from the Central Diagnostic System (CDS) - Flaps System (FLAPS)...........................................................27-225 General.....................................................................................................27-225
Erase the Data from the Central Diagnostic System (CDS) Flight Control System (FCS).....................................................27-226 General.....................................................................................................27-226 Procedure..................................................................................................27-226 Retrieval of Data from the Central Diagnostic System (CDS) Flaps System (FLAPS)..............................................................27-227 General.....................................................................................................27-227 Procedure..................................................................................................27-227 Retrieval of Data from the Central Diagnostic System (CDS) Flight Control System (FCS).....................................................27-229 General............................................................................................................27-229 Procedure.........................................................................................................27-229 27-00-01 FLIGHT CONTROL ELECTRONIC CONTROL UNIT............................. 27-23 Introduction.....................................................................................................27-233 General............................................................................................................27-233 System Description..........................................................................................27-233 Aileron Control System.............................................................................27-235 Rudder Control System.............................................................................27-235 Elevator Control System............................................................................27-237 Flap Control System..................................................................................27-239 Spoiler Control System.............................................................................27-239
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-xi
27 FLIGHT CONTROLS
Procedure..................................................................................................27-225
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Controls and Indications..................................................................................27-241 Caution Lights..........................................................................................27-241 Advisory Lights........................................................................................27-245 27 FLIGHT CONTROLS
Operational Test of the FCECU........................................................................27-245 Maintenance Consideration..............................................................................27-246 System Test...............................................................................................27-246 Interfaces..................................................................................................27-246 27-00-45 CENTRAL DATA STORAGE FLIGHT CONTROLS..............................27-247 Introduction.....................................................................................................27-247 General............................................................................................................27-247 Controls and Indications..................................................................................27-248 27-00-00 SPECIAL TOOL & TEST EQUIPMENT..................................................27-249 27-00-00 MAINTENANCE PRACTICES................................................................27-252
27-xii
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
ILLUSTRATIONS 27-1
Flight Control System................................................................................27-2
27-2
Aileron Control System.............................................................................27-4
27-3
Aileron Control System Synoptic...............................................................27-5
27-4
Aileron Forward Quadrant.........................................................................27-6
27-5
Aileron Splitter Quadrant...........................................................................27-8
27-6
Aileron Terminal Quadrant......................................................................27-10
27-7
Aileron Geared Tab .................................................................................27-12
27-8
Aileron Position LVDT............................................................................27-14
27-9
Aileron Position LVDT ...........................................................................27-14
27-10
Aileron Trim and Centering Unit.............................................................27-16
27-11
Aileron Trim Actuator..............................................................................27-17
27-13
Ground Adjustable Trim Tab....................................................................27-18
27-12
Ground Adjustable Trim Tab ...................................................................27-18
27-14
Aileron Trim Schematic...........................................................................27-20
27-15
Aileron Terminal Quadrant to Aileron Surface Rigging...........................27-22
27-16
Ailerons Control Surfaces........................................................................27-24
27-17
Aileron Gust Lock System.......................................................................27-26
27-18
Spoiler Control System............................................................................27-28
27-19
Spoiler Control System Synoptic.............................................................27-30
27-20
Spoiler Quadrant......................................................................................27-32
27-21
Spoiler Splitter Quadrant.........................................................................27-34
27-22
Spoiler Clutch Units................................................................................27-36
FOR TRAINING PURPOSES ONLY
27-xiii
27 FLIGHT CONTROLS
Figure Title Page
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page
27 FLIGHT CONTROLS
27-23
Spoiler Power Control Unit......................................................................27-38
27-24
Spoiler Power Control Hydraulic Unit.....................................................27-40
27-25
Spoiler Unload Valve...............................................................................27-42
27-26
Spoiler LVDT..........................................................................................27-43
27-27
Spoiler Cables Sensor..............................................................................27-44
27-28
Powered Flight Control Surface Indicator................................................27-46
27-29
Powered Flight Surface Shutoffs..............................................................27-47
27-30
Spoiler Switchlights.................................................................................27-48
27-31
Roll Spoiler Caution Lights.....................................................................27-48
27-32
Inboard Spoiler Hydraulic Schematic......................................................27-50
27-33
Spoiler Panel Indications - Spoiler System Schematic.............................27-52
27-34
Roll Spoilers Operation > 170 KIAS.......................................................27-54
27-35
Left Wing Inboard Spoiler Jam Indicated.................................................27-55
27-36
Left Wing Spoiler Jam Recovery Switchlight Pushed No.1 Unload Valve Energized to Unload......................................27-56
27-37
Roll Spoiler Fuselage Cable Jam Indicated-Roll Disconnect System Activated-50 Degree Travel Switch Closed..................................27-58
27-38 Roll Spoiler Fuselage Cable Jammed-Roll Disconnect Activated 50° Travel Switch Closed-Both Switchlights Pushed-Both Unload Valves Energized to Unload....................................27-60 27-39
Roll Spoiler Cable Sensor Operation.......................................................27-62
27-40
Ground Spoiler System Block Diagram...................................................27-64
27-41
Flight/Taxi Switch...................................................................................27-66
27-42
Roll Spoiler Ground Spoiler Mode Synoptic............................................27-68
27-43
Roll Spoiler in Ground Mode Schematic..................................................27-70
27-xiv
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-44
Spoiler Lift Dump Valve..........................................................................27-72
27-45
Spoiler Surface Indication.......................................................................27-73
27-46
Roll Spoiler in Ground Mode Caution Lights..........................................27-74
27-47
Inboard and Outboard Spoiler Panels.......................................................27-76
27-48
Roll Disconnect System...........................................................................27-77
27-49
Roll Disconnect Handle...........................................................................27-78
27-50
Roll Disconnect Lever Assembly.............................................................27-79
27-51
Roll Disconnect Clutch Mechanism.........................................................27-80
27-52
Aileron Forward Quadrant Microswitch (50°)..........................................27-81
27-53
Spoiler Pushoff Switchlights....................................................................27-82
27-54
Rudder Control System............................................................................27-84
27-55
Rudder Control System Synoptic.............................................................27-86
27-56
Rudder Pedals..........................................................................................27-88
27-57
Co-pilot’s Rudder Forward Quadrant........................................................27-90
27-58 Download Unit - Hand Held Onsite FDR_Series 400...............................27-91 27-59
Rudder Mixer Quadrant...........................................................................27-92
27-60
Rudder Aft Quadrant................................................................................27-94
27-61
Rudder Power Control Unit......................................................................27-96
27-62
Rudder PCU Schematic...........................................................................27-98
27-63 Rudder PCU Fluid Compensator..............................................................27-99 27-64
Rudder Shut-off Valve.......................................................................... 27-100
27-65
Rudder PCU Input Bungee.................................................................... 27-102
27-66
Rudder Position LVDT.......................................................................... 27-104
FOR TRAINING PURPOSES ONLY
27-xv
27 FLIGHT CONTROLS
Figure Title Page
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page
27 FLIGHT CONTROLS
27-67
Rudder Position on MFD...................................................................... 27-105
27-68
Rudder Push Off Switchlights............................................................... 27-106
27-69
FCECU Rudder Inputs and Outputs...................................................... 27-110
27-70
Rudder Control System - Electrical Schematic..................................... 27-112
27-71
Lower Rudder Control Jam Indicated.................................................... 27-114
27-72
Rudder 1 PUSH OFF Switch Pushed.................................................... 27-116
27-73
RUD CTRL Caution Light.................................................................... 27-118
27-74
Rudder Feel and Summing System Block Diagram............................... 27-119
27-75
Rudder Control System Synoptic.......................................................... 27-120
27-76
Rudder Trim Switch and Indicator........................................................ 27-121
27-77
Rudder Trim Actuator........................................................................... 27-122
27-78
Rudder Feel and Summing Unit............................................................ 27-123
27-79
Yaw Damper......................................................................................... 27-124
27-80
Rudder Trim Switch/Indicator Schematic.............................................. 27-126
27-81
Rudder Empennage............................................................................... 27-128
27-82
Elevator Control System....................................................................... 27-129
27-83
Elevator Control System Synoptic........................................................ 27-130
27-84
Elevator Control Column...................................................................... 27-132
27-85
Elevator Right Forward Quadrant.......................................................... 27-134
27-86
Elevator Left Forward Quadrant............................................................ 27-135
27-87
Elevator Aft Quadrants......................................................................... 27-136
27-88
Elevator Power Control Unit................................................................. 27-137
27-89
Elevator PCU Schematic....................................................................... 27-138
27-xvi
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-90
Compensator......................................................................................... 27-140
27-91
Centering Device.................................................................................. 27-141
27-92
Overload Bungee.................................................................................. 27-142
27-93
Elevator Position LVDT and PCU Input Bungee................................... 27-143
27-94
Elevator Position on MFD..................................................................... 27-144
27-95
Pitch Feel and Trim............................................................................... 27-146
27-96
Elevator Position Feedback................................................................... 27-148
27-97
Elevator Caution Lights........................................................................ 27-149
27-98 Pitch Feel and Trim Block Diagram..................................................... 27-150 27-99
Elevator Feel Caution Light.................................................................. 27-152
27-100
Pitch Feel and Trim Units..................................................................... 27-153
27-101
Dual Pitch Trim and Pitch Feel Actuators............................................. 27-154
27-102
Elevator Trim Indicator......................................................................... 27-156
27-103
Pitch Trim Switch................................................................................. 27-157
27-104
Elevator Trim Shutoff Switchlights....................................................... 27-158
27-105
Elevator Caution Lights........................................................................ 27-159
27-106
Elevator Feel and Trim System - Electrical Schematic.......................... 27-160
27-107
Elevator Trim Runaway or Manual Trim > 3 secs.................................. 27-162
27-108
Trim Push/Off Switch Pushed-Pitch Trim Caution Light ON................ 27-164
27-109
SPS Block Diagram.............................................................................. 27-166
27-110
Stall Protection Modules Locator.......................................................... 27-170
27-111
Stick Pusher Actuator Locator.............................................................. 27-171
27-112
Stick Pusher Capstan Locator............................................................... 27-172
FOR TRAINING PURPOSES ONLY
27-xvii
27 FLIGHT CONTROLS
Figure Title Page
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page
27 FLIGHT CONTROLS
27-113
Stick Pusher Quadrant Locator............................................................. 27-174
27-114
Stick Shaker Locator............................................................................ 27-175
27-115
Angle Of Attack Transducer Locator..................................................... 27-176
27-116
SPS Stick Pusher Shutoff Annunciator Switch Locator......................... 27-177
27-117
SPM Inputs........................................................................................... 27-178
27-118
SPM Outputs........................................................................................ 27-180
27-119
Stick Pusher Shutoff Switchlights......................................................... 27-182
27-120
SPM Caution Light Indications............................................................. 27-184
27-121
PFD Low Speed Cue Indications.......................................................... 27-186
27-122
PFD Low Speed Cue Malfunction Indications...................................... 27-187
27-123
Stall Warn Test Toggle Switch............................................................... 27-188
27-124
Elevator Surface................................................................................... 27-189
27-125
Pitch Disconnect Clutch Mechanism Component Location Index......... 27-190
27-126
Wing Flap System................................................................................. 27-194
27-127
Flap Control Unit (FCU)....................................................................... 27-196
27-128
Flap Control Unit Block Diagram......................................................... 27-198
27-129
Flap System Caution Panel................................................................... 27-199
27-130
Flap Selector Quadrant......................................................................... 27-200
27-131
Flap Control System - Electrical Schematic.......................................... 27-202
27-132
Flap Drive............................................................................................. 27-206
27-133
Flap Drive System................................................................................ 27-207
27-134
Flap Power Unit.................................................................................... 27-208
27-135
Flap Power Unit Schematic................................................................... 27-209
27-xviii
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-136
Flap Transmission Shafts...................................................................... 27-210
27-137
Flap Torsion Bars.................................................................................. 27-211
27-138
Flap Tracks........................................................................................... 27-213
27-139
No.3 and 4 Flap Rollers........................................................................ 27-214
27-140
Flap Carriage........................................................................................ 27-215
27-141
Wing Flap System................................................................................. 27-216
27-142
Flap Position Indication Unit................................................................ 27-218
27-143
Flap Position Indication Unit Block Diagram...................................... 27-219
27-144
Flap Position Transducer....................................................................... 27-220
27-145
Flap Position Indication/Multi-Function Display.................................. 27-221
27-146
Flap Position Indication - Electrical Schematic..................................... 27-222
27-147
Flaps..................................................................................................... 27-224
27-148
Task 45-00-27-743-802 CDS System Pages Indications........................ 27-225
27-149
Task 45-00-27-743-801 CDS System Pages Indications........................ 27-226
27-150
Task 45-00-27-742-802 CDS System Pages Indications (1 of 2)........... 27-227
27-151
Task 45-00-27-742-802 CDS System Pages Indications (2 of 2)........... 27-228
27-152
Task 45-00-27-742-801 CDS System Pages Indications (1 of 2)........... 27-229
27-153
Task 45-00-27-742-801 CDS System Pages Indications (2 of 2)........... 27-230
27-154
Flight Control Electronic Control Unit................................................. 27-232
27-155
FCECU/Left Channel Block Diagram................................................... 27-234
27-156
FCECU/Right Channel Block Diagram................................................. 27-236
27-157
FCECU Block Diagram........................................................................ 27-238
27-158
Caution and Warning Panel................................................................... 27-240
FOR TRAINING PURPOSES ONLY
27-xix
27 FLIGHT CONTROLS
Figure Title Page
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page
27 FLIGHT CONTROLS
27-159
Caution and Warning Panel................................................................... 27-242
27-160
Roll Spoiler Advisory Lights................................................................ 27-244
27-161
CDS Interface....................................................................................... 27-247
27-162
CDS Ground Maintenance Toggle Switch Selection.............................. 27-248
27-xx
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
CHAPTER 27 FLIGHT CONTROLS
27-00-00 FLIGHT CONTROLS INTRODUCTION The primary flight control surfaces are operated by cables from the left or right control columns and rudder pedals. This allows the aircraft to be flown from either the pilot or co-pilot positions. The position of the rudder, roll spoilers, and elevators are displayed on the Powered Flight Control Surfaces Indicator (PFCSI). The PFCSI display is on the pilot’s Multi Functional Display. The inputs to the display are provided by the Integrated Flight Cabinet, which receives information on surface position from the Flight Control Electronic Control Unit (FCECU).
FOR TRAINING PURPOSES ONLY
27-1
27 FLIGHT CONTROLS
27-2
Elevator
Aileron Geared Tab Ground Adjustable Tab
Rudder
Outboard Flaps
Outboard Flaps Spoilers Geared Tab Aileron
Flight Control Electronic Unit
fs238a01.cgm
Figure 27-1. Flight Control System
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
Inboard Flaps
DASH 8 Q400
Spoilers
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
GENERAL
WARNING
The spoilers assist the ailerons in providing roll control, and reduce lift after the aircraft touches down. PFCS positions are shown in the Permanent Systems Area (PSA) of Multi-Function Display 1 (MFD1). These PFCS positions are transmitted to the PSA from the control surfaces, through the Integrated Flight Cabinet (IFC). Trim indicators show trim position of the flight controls. Advisory lights indicate system operation, and caution lights indicate flight control malfunctions. Refer to Figure 27-1. Flight Control System. The Flight Control System has the following subsystems: •• FCECU (27-00-01) •• Aileron Control System (27-10-00) •• Rudder Control System (27-20-00)
INSTALL SAFETY DEVICES, WARNING SIGNS AND PLACARDS BEFORE YOU START A PROCEDURE ON, OR AROUND, FLIGHT CONTROLS OR FLIGHT CONTROL SURFACES.
27 FLIGHT CONTROLS
All flight controls may be operated from either the pilot’s or co-pilot’s seat. The rudders provide yaw control, the ailerons and spoilers roll control, and elevators pitch control (Figure 27-1). The rudders, spoilers and elevators are hydraulically powered, and identified as the Powered Flight Control Surfaces (PFCS) on the MFD PSA area. A gust lock system is provided for the aileron controls, to protect the ailerons in strong wind.
MAKE SURE THERE ARE NO PERSONNEL ON OR NEAR THE FLIGHT CONTROLS OR THE SURFACES. ACCIDENTAL MOVEMENT OF THE CONTROLS CAN CAUSE INJURIES TO PERSONNEL AND DAMAGE TO THE EQUIPMENT. THE ABOVE WARNINGS MUST BE OBSERVED DURING ALL FLIGHT CONTROL TASKS. ON AIRCRAFT WITH MODSUM 4Q126279 INSTALLED, ALL PUSH RODS FROM FLIGHT CONTROL INPUTS TO FORWARD QUADRANTS ARE EQUIPPED WITH FORCE SENSORS THAT SEND INFORMATION TO THE FLIGHT DATA RECORDER.
•• Elevator Control System (27-30-00) •• Wing Flaps (27-50-00) •• Spoilers Control System (27-60-00) •• Gust Lock Systems (27-70-00).
FOR TRAINING PURPOSES ONLY
27-3
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-12-00 AILERON SYSTEM
The aileron system is comprised of the following: •• Aileron forward quadrant
GENERAL
•• Aileron splitter quadrant
Refer to Figure 27-2. Aileron Control System. 27 FLIGHT CONTROLS
Movement of the control handwheels causes the aileron surfaces to deflect asymmetrically and in proportion to control handwheel rotation. The aileron system also receives inputs from the Auto Flight Control System and the Aileron Trim and Centering Unit.
•• Aileron terminal quadrant •• Aileron geared tab •• Aileron position LVDT
5
4 6 3 8
2 7
5
1
LEGEND 1. Aileron Forward Quadrant. 2. Aileron Splitter Quadrant. 3. Aileron Terminal Quadrant. 4. Aileron LVDT. 5. Aileron. 6. Aileron Gust Lock Mechanism. 7. Fuselage Cable Turnbuckles. 8. Wing Cable Turnbuckles. fs001a01.cgm
Figure 27-2. Aileron Control System
27-4
FOR TRAINING PURPOSES ONLY
3
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION Refer to Figure 27-3. Aileron Control System Synoptic. The aileron control cables are routed aft from the forward aileron quadrant, up the forward face of the flight compartment bulkhead and aft along the cabin roof. The cables terminate at the aileron splitter quadrant on the aft face of the wing rear spar.
Each aileron control wing cable terminates at an aileron terminal quadrant. Aileron terminal quadrant movement is transmitted to the aileron by a push-rod. Geared tabs are installed on each aileron, and a ground adjustable tab on right hand aileron. 27 FLIGHT CONTROLS
DASH 8 Q400
The aileron control wing cables are routed outboard from the aileron splitter quadrant, with one cable loop along each wing.
ROLL DISCONNECT HANDLE
ROLL DISCONNECT
TO SPOILER CONTROLS
TRIM ACTUATOR
AILERON FORWARD QUADRANT
SPRING TORSION BAR
AILERON TERMINAL QUADRANT
AILERON SPLITTER QUADRANT LEFT AILERON
DN
GEARED TAB
AUTOPILOT SERVO
AILERON TERMINAL QUADRANT
LVDT
GUST LOCK
RIGHT AILERON
GROUND ADJUSTABLE TAB
UP
GEARED TAB
fs179a01.cgm
Figure 27-3. Aileron Control System Synoptic
FOR TRAINING PURPOSES ONLY
27-5
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
The aileron forward quadrant receives inputs from:
Aileron Forward Quadrant
•• Co-pilot control handwheel
Refer to Figure 27-4. Aileron Forward Quadrant.
•• The autopilot
27 FLIGHT CONTROLS
The aileron forward quadrant is installed in the right side of the lower forward fuselage, below the flight compartment floor. The quadrant has two pulleys with secondary travel stops and a lever assembly all installed on a single shaft.
•• The aileron trim • And centering unit. The quadrant outputs the sum of these inputs through the cable system.
A push-rod connects the lever at the base of the co-pilot’s control column to the lever on the aileron forward quadrant. The forward quadrant also contains a 50° travel switch.
LEGEND 1. Aileron Input to Splitter Quadrant. 2. Aileron Autopilot Servo. 3. Cables. 4. Aileron Forward Quadrant. 5. Secondary Stops. 6. Rig Pin. 4
A 3 2
D
FW
1
5
6
A ft003a01.cgm
Figure 27-4. Aileron Forward Quadrant
27-6
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
RIGGING OF AILERON QUADRANT MICROSWITCH The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Pull the ROLL DISC handle •• Control wheel to neutral •• Make sure rigging pin can be installed and removed from the aileron quadrant freely •• Use inclinometer and rotate control wheel so that quadrant rotates 31.5° from neutral position •• Adjust the microswitch plunger to contact the cam at this position
CONTROL COLUMN TO CONTROL COLUMN RIGGING & CONTROL COLUMN TO AILERON QUADRANT The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Install rigging pins in spoiler, aileron and elevator quadrants •• Disconnect the roll interconnect push rods on the pilot and co-pilot sides •• Remove the aileron push rod from the push rod lever •• Align the handwheels horizontally
•• Rotate control wheel in the opposite direction to 31.5°
•• Adjust the interconnect pushrods as necessary and re-connect
•• Adjust microswitch plunger to contact the cam
•• Adjust the aileron pushrod as necessary and re-connect
•• Release the ROLL DISC handle
•• Remove all rigging pins
• Ensure control wheels move together.
•• Pressurize No.1 and No.2 hydraulic systems •• Do an Operational Test of the Aileron Control system •• Do an Operational Test of the Spoiler Control System and of the Spoilers.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-7
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
LEGEND
27 FLIGHT CONTROLS
1. LH Aileron Control Cables. 2. Aileron Splitter Quadrant. 3. RH Aileron Control Cables. 4. Quadrant Input Cables. 5. Gust Lock Plate. 6. Rig Pin Hole. 7. Gust Lock. 8. Gust Lock Control Cable. 9. Wing Rear Spar. 10. Gust Lock Release Springs.
3
2
A
4
1 10
FW
D
9
8
7
ft164a01.cgm
Figure 27-5. Aileron Splitter Quadrant
27-8
FOR TRAINING PURPOSES ONLY
6
5
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Aileron Splitter Quadrant
NOTES
Refer to Figure 27-5. Aileron Splitter Quadrant. The splitter quadrant is installed on the aft face of the wing rear spar. The quadrant has three pulleys installed on a common shaft. 27 FLIGHT CONTROLS
The aileron splitter quadrant transmits aileron cable inputs from the co-pilot’s forward quadrant to the aileron terminal quadrants located in each wing. Gust locking of the ailerons is supplied by an internal spring-loaded lever attached off-center to the bottom of the splitter quadrant. When the gust lock is engaged, a plunger is inserted in the gust lock plate at the base of the splitter quadrant. This locks the ailerons in the neutral position.
AILERON QUADRANT TO SPLITTER QUADRANT The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Pull the ROLL DISC handle and turn through 90° •• Install rigging pins in the aileron forward quadrant and the splitter quadrant •• Engage the gust lock •• Use cable tension meter to measure the tension on each side of the aileron cable •• Adjust the turnbuckles to adjust cable tension as necessary •• Re-check tension after 7 days.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-9
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
A
3
2
4 1
LEGEND 1. Pulley. 2. Cables. 3. Rig Pin. 4. Terminal Quadrant. 5. Rod. 6. Primary Aileron/Roll Spoiler Stops.
6
6
5
A
ft162a01.cgm
Figure 27-6. Aileron Terminal Quadrant
27-10
FOR TRAINING PURPOSES ONLY
FW
D
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
AILERON TERMINAL QUADRANT
NOTES
Refer to Figure 27-6. Aileron Terminal Quadrant. Each aileron terminal quadrant is located on the wing rear spar adjacent to its related aileron. 27 FLIGHT CONTROLS
The quadrant is connected to the aileron by a lever and a control rod. For rigging procedures, a 0.25 in. (6.35 mm) rig pin hole is used to lock the quadrant in neutral. The terminal quadrant transmits aileron cable control from the aileron splitter quadrant to the aileron surface. The quadrant also includes the primary adjustable stops for aileron and roll spoiler movement.
AILERON SPLITTER QUADRANT TO AILERON TERMINAL QUADRANT RIGGING The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Lower the flaps •• Pull the ROLL DISC handle and turn through 90° •• Engage the gust lock •• Install the rigging pins in the aileron splitter quadrant and left and right aileron terminal quadrants •• Check and adjust the cable tension as necessary iaw the AMM.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-11
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
Figure 27-7. Aileron Geared Tab
27-12
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Aileron Geared Tab Refer to Figure 27-7. Aileron Geared Tab. The aileron geared tab is attached by four hinge fittings to the trailing edge of each aileron. The tab is connected to the aileron by a geared linkage so that the geared tab moves 70% of the total aileron movement in the opposite direction. This action gives aerodynamic assistance and reduces the force required to turn the control handwheels. At full aileron deflection of 17°, the aileron geared tab deflects 11.9°. The geared tab linkage is connected to the aileron hinge point to give tab movement, in proportion to aileron movement. Each geared tab has adjustable bolts located on the hinge arm of the tab.
RIGGING OF THE AILERON GEARED TAB The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Install the rigging pins in the terminal quadrants •• Install the aileron rigging tool on the wing and aileron to ensure the ailerons are in neutral •• Install aileron geared tab rigging tool •• Using the rigging board ensure that the geared tab is at neutral (0°).
FOR TRAINING PURPOSES ONLY
27-13
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
27 FLIGHT CONTROLS
D
FW
Figure 27-8. Aileron Position LVDT
Figure 27-9. Aileron Position LVDT
27-14
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Aileron Position LVDT
•• Apply the CONTROL LOCK
Refer to:
•• Open control columns access panels
• • Figure 27-8. A ileron Position LVDT. • Figure 27-9. Aileron Position LVDT. The aileron LVDT is fitted to the control input to the right hand aileron. The LVDT supplies an electrical signal equivalent to the angular position of the flight control surface to the FCECU. The FCECU supplies electrical excitation to the LVDT. The FCECU transmits this data to the Flight Data Recorder (FDR) through the Integrated Flight Cabinet (IFC) No.1 on an ARINC 429 Data Bus.
•• Make a cloth moist with approved cleaning solvent •• Clean contamination from the chains with the wiper cloth • Make sure the area is dry
CAUTION DO NOT MIX GREASE FROM DIFFERENT MANUFACTURERS OR DIFFERENT SPECIFICATIONS. •• Apply a thin film of grease to the chains with your hand •• Close the access panels
AILERON LVDT FAIL FAULT ISOLATION
NOTE The aileron, rudder and elevator LVDTs have the same part number and are interchangeable.
Operation Rotary movement of the co-pilot’s control handwheel is transmitted by a sprocket and chain mechanism to a sprocket and lever assembly. This assembly is at the base of the co-pilot’s control column. A push-rod connects the lever to the aileron forward quadrant.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Energize the electrical system •• Do a fault message retrieval in the CDS for flight control system •• Do an operational test of the aileron control system
Connected to the aileron forward quadrant are inputs from the Aileron trim system and an input from the auto-pilot servo.
•• If the AIL LVDT FAIL message comes on go to the Fault Isolation procedure
LUBRICATION OF AILERON AND ROLL SPOILER CONTROL COLUMN CHAINS
•• Disconnect electrical connector P1 from the FCECU
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
•• Disconnect the electrical connector from the LVDT
•• Check continuity of both connectors •• Re-connect the electrical connectors •• Do a fault confirmation •• If fault continues replace LVDT •• If fault continues replace FCECU.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-15
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-13-00 AILERONS TRIM AND CENTERING GENERAL Refer to Figure 27-10. Aileron Trim and Centering Unit. 27 FLIGHT CONTROLS
Aileron trim is achieved by an electrical actuator located in the aileron trim and centering unit. The trim and centering unit is connected to the aileron forward quadrant by a spring torsion bar that makes sure the aileron surfaces always return to a neutral position. The aileron trim and centering system has the following components: •• Trim actuator •• Centering unit (Torsion bar) • Trim-ground adjustable tab.
1
A FW
D D
FW
LEGEND
2
1. Spring Torsion Bar. 2. Aileron Trim Actuator.
ft008a01.cgm
Figure 27-10. Aileron Trim and Centering Unit
27-16
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Trim Actuator Refer to Figure 27-11. Aileron Trim Actuator.
27 FLIGHT CONTROLS
The trim actuator drives the aileron control system to counter the effects of lateral imbalance. The aileron trim actuator is fitted under the left side flight compartment floor. The actuator has the following: •• Electric motor and linear actuator •• Gearbox •• Circuit cards • LVDT.
A
AILERON TRIM AND CENTRING ASSEMBLY
D
FW
B
FW
D
fs011a01.cgm
Figure 27-11. Aileron Trim Actuator
FOR TRAINING PURPOSES ONLY
27-17
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Ground Adjustable Trim Tab Refer to: •• Figure 27-12. G round Adjustable Trim Tab.
27 FLIGHT CONTROLS
•• Figure 27-13. G round Adjustable Trim Tab. The ground adjustable trim tab is located on the trailing edge of the right aileron, inboard of the geared tab. The adjustment is made on a serrated plate, at the tab end of the geared linkage. The ground adjustable trim tab is used to adjust for any aerodynamic asymmetry between ailerons.
Figure 27-12. Ground Adjustable Trim Tab
GROUND ADJUSTABLE TRIM TAB
FW
D
1 FW
D
LEGEND 1. Connecting Link. 2. Link Bracket. 3. Sleeve.
2 3
ft169a01.cgm
Figure 27-13. Ground Adjustable Trim Tab
27-18
FOR TRAINING PURPOSES ONLY
D
TB
OU
MAINTENANCE TRAINING MANUAL
OPERATION Normal Operation Refer to Figure 27-14. Aileron Trim Schematic. The AILERON trim switch is spring-loaded to return to the center-off position. The aileron trim switch has three positions: •• LWD (left wing down)
When the autopilot is engaged, a message MISTRIM (TRIM L WING DN) or (TRIM R WING DN) is shown on the Primary Flight Display if aileron trim is required.
CAUTION Release control lock when testing aileron trim.
OPERATIONAL TEST OF THE AILERON CONTROL SYSTEM
•• RWD (right wing down) • Center-off. Input commands from the aileron trim actuator to the aileron trim and centering system rotates the aileron forward quadrant. An aileron trim indicator shows aileron trim position. The aileron trim indicator receives its information from a LVDT.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Release CONTROL LOCK •• Pull ROLL DISC handle
The LVDT also transmits aileron trim position data to the FDR.
•• Ensure aileron trim is at neutral
Power for the Aileron Trim Linear Actuator is supplied from the 28 VDC Left essential bus through circuit breakers G8 to pin 7 on the actuator. The ground is supplied through pin 6 on connectors P4.
•• Rotate aileron control wheel to full movement each side of neutral
Power for the Aileron Trim Control Panel is supplied from the 28 VDC Left essential bus through circuit breakers H8 to pin C on the trim panel. The ground is supplied through pins D and E.
Abnormal Operation If the AILERON trim switch fails to the closed position, a limit switch on the trim actuator housing opens the electrical circuit and causes the trim actuator to stop at the maximum trim input. If the limit switch fails to stop the trim actuator, a mechanical stop on the trim actuator housing stops the trim actuator at the maximum trim setting.
•• Hold roll spoiler control wheel in neutral
•• Make sure ailerons move freely from stop to stop • • Check that SPLR1 and SPLR2 powered flight control shutoff lights show PUSH OFF when aileron control wheel is > 50° either side of neutral • Release ROLL DISC handle.
OPERATIONAL TEST OF THE AILERON TRIM SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Release the CONTROL LOCK lever to the OFF position •• Make sure the aileron control surfaces are in the neutral position
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-19
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-20 (G8) AIL TRIM ACT
5A
7 6
+28 VDC +28 VDC RTN
+28 VDC LEFT ESS BUS
(H8) AIL TRIM IND
5A
ROLL DISCONNECT HANDLE
LEFT DC CBP
ROLL DISCONNECT
TO SPOILER CONTROLS
AIL POS
HI LO
+28 VDC DC RETURN CHASSIS GND
AIL I
J/P2 G H
4 HI AIL POS 13 LO
TRIM ACTUATOR
C D E
AILERON FORWARD QUADRANT
SPRING TORSION BAR
AUTOPILOT SERVO
£
TRIM
AILERON
TRIM
AILERON TERMINAL QUADRANT
AILERON TRIM INDICATOR +5 VDC
A B
+5 VDC DC RTN
PANEL LIGHTING
DN
J/P100 H J K L
1 L
2 3
8 10 2 3
AIL AIL AIL AIL
TRIM TRIM TRIM TRIM
RTN EXT RET EN
4 5 R
AILERON SPLITTER QUADRANT
6 2711-S1
AILERON TRIM SWITCH
TRIM CONTROL PANEL (CENTER CONSOLE)
AIL POS HI 414 AIL POS LO 413
AILERON TRIM LINEAR ACTUATOR
31-40 A1 IOM #1
Figure 27-14. Aileron Trim Schematic
GEARED TAB
LEFT AILERON
AILERON TERMINAL QUADRANT
LVDT
GUST LOCK
GROUND ADJUSTABLE TAB
RIGHT AILERON
UP
GEARED TAB
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
DC RTN
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• Select trim switch fully LWD •• Make sure trim indicator is operating correctly
NOTES
•• Make sure left aileron is UP, and right aileron is DOWN
27 FLIGHT CONTROLS
•• Repeat with switch in RWD, check indicator and aileron positions •• Set aileron trim to the neutral position •• Set CONTROL LOCK to ON position.
FOR TRAINING PURPOSES ONLY
27-21
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
2 3
1
27 FLIGHT CONTROLS
LEGEND
6
1. Aileron terminal quadrant. 2. Rigging pin (left wing). 3. Rigging pin (right wing). 4. Aileron. 5. Aileron rigging tool. 6. Aileron control rod.
LH SIDE SHOWN, RH SIDE SIMILAR
1
5
14
4 6
pb165a01.dg, pt/gv, 16/04/02
Figure 27-15. Aileron Terminal Quadrant to Aileron Surface Rigging
27-22
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
27-14-00 AILERON SURFACES INTRODUCTION The aileron surfaces are the primary flight control. The aileron surfaces are assisted by the roll spoilers which give roll control of the aircraft in flight.
GENERAL Refer to Figure 27-15. Aileron Terminal Quadrant to Aileron Surface Rigging. There are two aileron control surfaces. They are installed on the outboard ends of the left and right wing. Aileron travel is ±17º around the neutral position.
AILERON TERMINAL QUADRANT TO AILERON SURFACE RIGGING The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
The maintenance check flight and subsequent GAT and aileron pushrod adjustment makes sure that the aircraft will fly level with the control wheels in the neutral position.
RIGGING OF THE AILERON CONTROL SYSTEM STOPS The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Pull the ROLL DISC handle •• Install rigging pins in left and right aileron terminal quadrants •• Put an inclinometer on the upper surface of the left and right ailerons @ YW 436.02 •• Set the protractors to read 0° •• Install left and right aileron rigging boards •• Remove the rigging pins •• T u r n c o - p i l o t ’ s h a n d w h e e l counterclockwise, stop when the left aileron is at 16.5° to 17° •• Hold the hand wheel in this position
This procedure sets the ailerons to the 0° position on the aileron rigging tool with the rigging pins in the terminal quadrant.
•• Adjust the stop bolts on the terminal quadrants to touch the stop faces
After you do this procedure you must have the aircraft flown and do subsequent adjustments to the Ground Adjustable Trim Tab and the aileron pushrods i.a.w. TASK 27-13-11-830-803.
•• Turn the control wheel fully clockwise and hold
This subsequent aileron pushrod adjustment can change the position of the ailerons, with the rigging pins in the terminal quadrants, to a maximum of 2° either side of 0° on the aileron rigging tool.
•• Record the angle of the aileron
•• Repeat the procedure for the stop bolts •• Make sure the travel of the two ailerons is between 0.5° or less of each other.
This is necessary to compensate for manufacturing tolerances of the aircraft structure.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-23
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
3
1
2
LEGEND 1. Ground Adjustable Trim Tab. 2. RH Aileron Geared Tab. 3. Horn. 4. LH Aileron Geared Tab.
4
Figure 27-16. Ailerons Control Surfaces
27-24
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Aileron Control Surfaces Refer to Figure 27-16. Ailerons Control Surfaces. The aileron consists of following components: 27 FLIGHT CONTROLS
•• Aileron box •• Leading edge •• Trailing edge •• Aileron tip •• Gear tab • Trim tab (right hand aileron only). Aileron movement is defined by the control system and is translated to the aileron by a push rod connected to the aileron actuator bracket. The aileron has a geared tab. The aileron has horn and leading edge mass balance. View holes are located on the bottom of the aileron for visual inspection of the hinge pins. An access panel is located at the center hinge point. A horn with internal mass balance weights is located on the outboard end of each aileron to give aerodynamic balance.
FOR TRAINING PURPOSES ONLY
27-25
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
1 LEGEND
2
27 FLIGHT CONTROLS
1. Control Lock Lever. 2. Control Lock Off Position. 3. Control Lock On Position. 4. Gust Lock Cables. 5. Gust Lock Lever. 6. Gust Lock Mechanism. 7. Rig Pin Hole.
R A T I N G
R A T I N G
I
FLIGHT IDLE DISC
I
7
4
5 AILERON SPLITTER QUADRANT
6
Figure 27-17. Aileron Gust Lock System
27-26
FOR TRAINING PURPOSES ONLY
3
MAINTENANCE TRAINING MANUAL
27-70-00 AILERON GUST LOCK SYSTEM INTRODUCTION The aileron gust lock provides protection against wind gusts, while the aircraft is stationary on the ground.
GENERAL The aileron control system is a mechanically operated system. Gust protection for the ailerons is supplied by a gust lock mechanism operated from the flight compartment. When the CONTROL LOCK lever on the center console is pulled aft to the ON position, the ailerons are locked in neutral. The aileron gust lock system has the following sub-system: • Aileron Gust Lock System Mechanism.
SYSTEM DESCRIPTION Refer to Figure 27-17. Aileron Gust Lock System.
OPERATIONAL TEST OF THE AILERON GUST LOCK SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Make sure the CONTROL LOCK (gust lock) handle is fully forward in the OFF position •• Move the pilot or co-pilot control wheel and make sure that: °° The two control wheels turn in the same direction and at the same time °° The aileron control surfaces move in relation to the control wheel movement °° The ailerons move freely through the full range of travel •• Put the control wheels near their neutral position •• Engage the aileron gust lock.
The CONTROL LOCK lever is located in the flight compartment, on the power quadrant. When the CONTROL LOCK lever release is pulled up (squeezed) and the lever is moved from the OFF to the ON position, the aileron mechanism gust lock lever is pivoted by cable to the locked position. If the ailerons are in the neutral position, the plunger engages in the lock plate slot and prevents the aileron splitter quadrant from rotating. If the ailerons are not in the neutral position, the plunger is compressed against the face of the lock plate. When the ailerons are moved to the neutral position the plunger springs out to the locked position. If a gust lock cable fails, the gust lock mechanism fails safe to the unlocked position. Two tension springs pull the gust lock lever towards the OFF position assuring positive disengagement.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-27
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-28 1
2
DASH 8 Q400
3
4 2
6
1
7
LEGEND 7 6 5 8
fs055a01.cgm
Figure 27-18. Spoiler Control System
1. Outboard Spoiler. 2. Inboard Spoiler. 3. Spoiler Splitter Quadrant. 4. Spoiler Control Cables. 5. Outboard Spoiler PCU. 6. Spoiler Clutch. 7. Inboard Spoiler PCU. 8. Spoiler Forward Quadrant.
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
5
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-61-00 ROLL SPOILERS SYSTEM
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The roll spoilers are hydraulically powered and operate with, and in proportion to, the aileron control system. They assist in lateral control of the aircraft during flight. The roll spoilers also decrease the lift of the wings on landing.
GENERAL Refer to Figure 27-18. Spoiler Control System. There are two hydraulically powered roll spoilers on each wing. Movement of the handwheels operates a cable system connected to Power Control Units (PCU). The PCU extend or retract the spoiler panels. The No.1 hydraulic system supplies the inboard spoilers and the No.2 hydraulic system supplies the outboard spoilers. There are three modes of spoiler operation: •• Flight Mode •• Ground Mode (refer to 27-62-00) and • Taxi Mode. The roll spoiler system includes the following components: •• Spoiler quadrant •• Spoiler splitter quadrant •• Clutch units •• Power control units •• Unload valves •• Spoiler LVDTs •• Spoiler cable sensor • Lift dump valves.
FOR TRAINING PURPOSES ONLY
27-29
27 FLIGHT CONTROLS
27-30 ROLL DISCONNECT HANDLE
NOTE H1 Powered By Number 1 Hydraulic System. H2 Powered By Number 2 Hydraulic System.
POWERED FLIGHT CONTROL SHUTOFFS SPLR 1 SPLR 2
ROLL DISCONNECT MECHANISM
PUSH OFF
PUSH OFF
SPOILER CLUTCH (4)
FROM SPOILER CLUTCH
SPOILER SPLITTER QUADRANT ASYMMETRIC LINKAGE
LH. OUTBD. SPOILER
2H
H1
H1
TO SPLR PUSHOFF SWITCH
TO SPLR PUSHOFF SWITCH
LH. INBD. SPOILER
RH. INBD. SPOILER
fs106a01.cgm
Figure 27-19. Spoiler Control System Synoptic
SPOILER PCU RH. OUTBD. SPOILER
MAINTENANCE TRAINING MANUAL
FROM SPOILER CLUTCH
H2
FOR TRAINING PURPOSES ONLY
SPOILER QUADRANT TENSION REGULATOR
DASH 8 Q400
TO AILERON CONTROLS
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION
NOTES
Refer to Figure 27-19. Spoiler Control System Synoptic.
27 FLIGHT CONTROLS
Rotary movement of the control wheels is transmitted by sprockets, chains, and push-rod to the spoiler quadrant. This is all done through the base of the pilot’s control column. A force sensor is installed between the left control column and the spoiler quadrant. The signal transmitted by the sensor is recorded by the EDR. The control cables are routed from the quadrant below the floor up to the aft pressure bulkhead. They go up then run forward to aft of wing rear spar through the pressure vessel to a splitter quadrant installed on the rear spar. The cables from the splitter quadrant are routed to the spoiler clutches quadrants. The clutches are connected to push-rods, levers, and bell cranks to give mechanical inputs to the hydraulic spoiler actuators. A clutch in the pulley of each mechanism can disengage and isolate either inboard or outboard spoilers if a PCU linkage jams. If the clutch slips, an advisory switchlight illuminates. (PUSH OFF) Pushing the switchlight depressurizes the jammed PCU and the corresponding PCU on the other wing. At high airspeeds the outboard spoilers are locked out. Failure to lock out or re-engage the spoilers will be annunciated to the crew by an illuminated caution light (SPLR OUTB). Hydraulic pressure applied to the PCUs is monitored. Any faults will be displayed in the flight compartment. A roll disconnect system is supplied in the event a cable jam occurs (refer to 27-16-00).
FOR TRAINING PURPOSES ONLY
27-31
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SPOILER CONTROL SYSTEM FLIGHT COMPARTMENT
FW 27 FLIGHT CONTROLS
D
3
2
INB
D
1
D
FW
LEGEND 4 ft095a01.cgm
Figure 27-20. Spoiler Quadrant
27-32
FOR TRAINING PURPOSES ONLY
1. Rig Pin Hole. 2. Pushrod Attachment. 3. Cable Tension Regulator. 4. Mounting Brackets.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Spoiler Quadrant Refer to Figure 27-20. Spoiler Quadrant.
27 FLIGHT CONTROLS
The spoiler quadrant transmits the control column hand wheel inputs to the spoiler cable system. The spoiler quadrant is installed at the base of the pilot's control column and connected to the interconnect rod. It includes a tension regulator, which maintains constant cable tension under all temperature conditions. The attached Hot Normal Cold (H-N-C) scale and pointer is used to rig the tension regulator in accordance with temperature related graphs. The spoiler quadrant includes the secondary control stops, and a rig pin hole.
FOR TRAINING PURPOSES ONLY
27-33
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SPOILER SPLITTER QUADRANT INSTALLATION
27 FLIGHT CONTROLS FWD
2
1
4
3
LEGEND 1. Fuselage Input Quadrant. 2. Rig Pin Hole. 3. Bracket. 4. RH and LH Wing Output Pulley.
ft014a01.cgm
Figure 27-21. Spoiler Splitter Quadrant
27-34
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Spoiler Splitter Quadrant
NOTES
Refer to Figure 27-21. Spoiler Splitter Quadrant. The spoiler splitter quadrant transmits control column roll system inputs to the wing spoiler cable circuits. 27 FLIGHT CONTROLS
The quadrant is attached to the aft face of the wing rear spar. It has two brackets and three pulleys. The larger lower pulley is the attachment point for the control cable from the forward spoiler quadrant. The top pulley inputs the right wing spoilers. The middle pulley inputs the left wing spoilers. There is a rig pin hole to lock the quadrant in neutral.
FOR TRAINING PURPOSES ONLY
27-35
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SURFACE SPOILER CONTROL ASSEMBLY D
FW
D
FW
27 FLIGHT CONTROLS 3
4
5 1 2 6
7
FW
D 8
LEGEND 1. Microswitch (SPLR 1 PUSHOFF). 2. Clutch Spring. 3. Mounting Brackets. 4. Rig Pin Hole.
5. Pushrod Attachment (INBD PCU). 6. Input Quadrant. 7. Cam. 8. Clutch Plate.
NOTE Outbd clutch mechanism on bottom of quadrant.
Figure 27-22. Spoiler Clutch Units
27-36
FOR TRAINING PURPOSES ONLY
ft053a01.cgm
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Clutch Units
NOTES
Refer to Figure 27-22. Spoiler Clutch Units. The clutch units transmit spoiler system inputs to the spoiler PCU.
27 FLIGHT CONTROLS
The clutch units are installed centrally below the two spoiler panels attached to the wing rear spar. The clutch units operate the spoiler PCU input levers through two push-rods and one bellcrank. The units contain two clutch mechanisms to allow for a jam between the clutch unit and the controls to either spoiler panel. If the linkage jams, with a force of approximately 27 lbs (12.25 kg) at the clutch and approximately 12 lbs (6 kg) at control wheel will cause disengagement of the clutch and the clutch will slip. When the clutch slips, it operates a microswitch, causing the inboard or outboard spoiler switchlight (SPLR1 or SPLR 2) PUSH OFF annunciation to illuminate.
FOR TRAINING PURPOSES ONLY
27-37
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SURFACE SPOILER CONTROL ASSEMBLY D
FW
D
FW
27 FLIGHT CONTROLS 5
6
4
3
2 12
D
11
FW 10 9
LEGEND 1. Pushrod Attachment. 2. Bellcrank Assembly. 3. Input Connecting Link Assembly. 4. Crank Connecting Link Assembly. 5. Feedback Link. 6. Summing Link.
8
7
7. Input Crank Lever Assembly. 8. Serrated Insert. 9. Main Control Valve. 10. Rod End Assembly. 11. Spoiler Panel Link. 12. Manual Release Valve.
Figure 27-23. Spoiler Power Control Unit
27-38
FOR TRAINING PURPOSES ONLY
1
ft097a01.cgm
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Power Control Units (Inboard/ Outboard)
NOTES
Refer to Figure 27-23. Spoiler Power Control Unit. The PCU transfer spoiler system input commands into hydraulic outputs to the spoiler panels. 27 FLIGHT CONTROLS
The PCUs are mounted on brackets attached to the wing rear spar below the spoiler panels. The PCU has four ports: •• Extend port •• Retraction or hold down port •• Return port • Lift dump port (Ground Spoiler Mode).
FOR TRAINING PURPOSES ONLY
27-39
27 FLIGHT CONTROLS
27-40 MAIN CONTROL VALVE
THERMAL RELIEF/ RECIRCULATING VALVE
(FROM UNLOAD VALVE)
ACTUATOR ASSEMBLY
RETRACT PORT (SYSTEM PRESSURE)
.
RETURN PORT
MANUAL RELEASE VALVE
fss97a01a.cgm
Figure 27-24. Spoiler Power Control Hydraulic Unit
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
EXTEND PORT
DASH 8 Q400
LIFT DUMP PORT (GROUND MODE)
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-24. Spoiler Power Control Hydraulic Unit.
NOTES
27 FLIGHT CONTROLS
The input lever operates a main control valve. Main control valve input opens the extend port to the actuator piston. The hold down port is pressurized and ported directly to the actuator piston. Hydraulic pressure holds down the spoiler panels. The actuator piston extend port pressure must overcome the actuator piston hold down pressure. The input commands move the actuator rod with an attached feed back linkage. Actuator travel stops when the actuator rod position corresponds to the input lever position. The PCU incorporates a manual release valve to aid in PCU hydraulic bleeding. The spoiler panels can extend to a maximum of 75°. The No.1 or No.2 hydraulic system supplies constant pressure to the retract port of the inboard spoiler PCU, and extend pressure through the de-energized open unload valve. The constantly supplied retract pressure acts on the small surface area of the PCU piston. The extend pressure, when directed by the control valve of the PCU, acts on the larger surface area of the piston, extending the ram, driving the spoiler panel up. Pressure on the retract side opens the thermal relief/recirculating valve in the PCU.
FOR TRAINING PURPOSES ONLY
27-41
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Unload Valves Refer to Figure 27-25. Spoiler Unload Valve. The unload valves supply the PCU with system hydraulic pressure:
27 FLIGHT CONTROLS
•• No.1 unload valve is located on the left side of the fuselage in the wing to fuselage attachment area. The No.2 unload valve is located on the right side of the fuselage also in the wing to fuselage attachment area •• No.1 unload valve supplies hydraulic pressure to both inboard spoiler PCU extend ports •• No.2 unload valve supplies hydraulic pressure to both outboard spoiler PCU extend ports •• No.2 unload valve energized closed by the FCECU, which prevents extension of the outboard spoilers when the airspeed is above 170 kt.
2
3 D
FW
1
FW
D
4
LEGEND
5
1. Solenoid. 2. Electrical Conector. 3. Hydraulic Port Return. 4. Mounting Bracket. 5. Hydraulic Pressure Port.
Figure 27-25. Spoiler Unload Valve
27-42
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Linear Variable Differential Transformer (LVDT) Refer to Figure 27-26. Spoiler LVDT. The spoiler panel position LVDT provides data to the FCECU. 27 FLIGHT CONTROLS
The LVDT is attached to a bracket on the aft face of the wing rear spar and a bracket on the spoiler panel. The FCECU supplies the excitation to the LVDT. The FCECU uses the LVDT data to monitor the serviceability of each actuator. The FCECU also transmits the LVDT data to the Integrated Flight Cabinet (IFC). The IFC transmits this data to the: •• Flight Data Recorder (FDR) and •• Powered Flight Control Surface (PFCS) indicator.
A
A
SPOILER LVDT ASSEMBLY
D
FW
1
Figure 27-26. Spoiler LVDT
FW
D
LEGEND 1. Spoiler Attachment. 2. Rib Assembly Attachment. 3. Ground Strap.
2
FOR TRAINING PURPOSES ONLY
NOTE Left inboard LVDT shown. Other three similar.
27-43
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SPOILER CONTROL SYSTEM FLIGHT COMPARTMENT
A
27 FLIGHT CONTROLS
FW
D
3
2
LEGEND
4
1
1. Anchor Bracket. 2. Micro Switches. 3. Fitting. 4. Roller Arm. 5. Spoiler Cables. 6. Tension Spring.
5
6
fss77a01.cgm
Figure 27-27. Spoiler Cables Sensor
27-44
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Spoiler Cables Sensor
NOTES
Refer to Figure 27-27. Spoiler Cables Sensor.
27 FLIGHT CONTROLS
The spoiler cable sensor is located on the fuselage spoiler cable circuit under the flight deck floor. The spoiler cable sensor assembly consists of a spring-loaded fair lead roller arm latching a leaf spring and two micro switches. If the spoiler cable fails, the spring-loaded arm rotates against its end stop and actuates the two micro switches. The No.1 and No.2 unload valves are then energized. Extend pressure is removed from the actuators. The retract pressure will keep spoilers closed. “ROLL SPLR INBD HYD” and “ROLL SPLR OUTBD HYD” caution lights will then illuminate.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-45
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Controls and Indications Refer to Figure 27-28. Powered Flight Control Surface Indicator. The spoiler surface positions are displayed on the PSA1 on the pilot MFD (MFD1). 27 FLIGHT CONTROLS
The indications are LO, LI, RI, and RO corresponding to left outboard, left inboard, right inboard and right outboard respectively. The indication is analog and displays panel deflection angle.
WX OFF
FMS1 076 00
057
HDG 073°
E
3
160
LEGEND 1. Spoiler Position Indication
VIE
35.0 NM --:--
VCF
YSO
00 ---
TAS 20 GS 0
1
YCF
80
TCAS STBY
ADF1 DME1 H 92.1 NM
ADF2 DME2 92.1 NM
I
1
I
Figure 27-28. Powered Flight Control Surface Indicator
27-46
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to: •• Figure 27-29. P owered Flight Surface Shutoffs. • Figure 27-30. Spoiler Switchlights.
27 FLIGHT CONTROLS
A PCU linkage jam will cause the clutch unit to close a microswitch resulting in the inboard or outboard spoiler switchlights (SPLR1 or SPLR 2) PUSH OFF lights to come on.
A
LEGEND 1. Spoiler 1 Push Off Switchlight. 2. Spoiler 2 Push Off Switchlight.
INSTRUMENT PANEL 1
2
POWERED FLIGHT CONTROL SHUTOFFS
IAS
HSI SEL
fs285a01.cgm
A
Figure 27-29. Powered Flight Surface Shutoffs
FOR TRAINING PURPOSES ONLY
27-47
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LW IB SPLR CLUTCH JAM MICRO SW S7 CLOSED
SPLR 1
RW IB SPLR CLUTCH JAM MICRO SW S8 CLOSED
CDS MSG: N/A
NOT LATCHED
PUSH
SPLR DECLUTCH MICRO SW S3 CLOSED (ROLL DISC)
27 FLIGHT CONTROLS
AILERON DECLUTCH MICRO SW S5 CLOSED (50°)
RW OB SPLR CLUTCH JAM MICRO SW S6 CLOSED
SPLR 2
LW OB SPLR CLUTCH JAM MICRO SW S5 CLOSED
CDS MSG: N/A
NOT LATCHED
PUSH
SPLR DECLUTCH MICRO SW S4 CLOSED (ROLL DISC) AILERON DECLUTCH MICRO SW S5 CLOSED (50°)
NOTES LATCHED - Light will remain illuminated for duration of flight. Will not be reset until fault condition is no longer present NOT LATCHED - Light will extinguish when fault condition is no longer present regardless of phase of flight.
Figure 27-30. Spoiler Switchlights
2
3
1
A OVERHEAD CONSOLE
LEGEND 1. Spoiler Outboard. 2. Roll Spoiler Inboard Hydraulic. 3. Roll Spoiler Outboard Hydraulic.
fsz05a01.cgm
Figure 27-31. Roll Spoiler Caution Lights
27-48
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-31. Roll Spoiler Caution Lights.
NOTES
The FCECU sends signals to the Caution and Warning panel to turn on the following caution lights: 27 FLIGHT CONTROLS
SPLR OUTBD •• If the FCECU fails to lockout the outboard spoilers and airspeed is > 185 knots, or •• If the FCECU locks out the outboard spoilers and airspeed is < 150 knots, or •• Airspeed No.1 disagrees with airspeed No.2 by 17 knots • Internal FCECU fault.
ROLL SPLR INBD HYD •• No.1 Hydraulic system pressure is < 900 psi (6205 kPa). • Roll SPLR cable break
ROLL SPLR OUTBD HYD • • No.2 hydraulic system pressure is < 900 psi (6205 kPa) and air speed < 165 knots •• Roll SPLR cable break
FOR TRAINING PURPOSES ONLY
27-49
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
LEFT I/B SPOILER ACTUATOR RETRACT EXTEND
SPLR #1 PUSH OFF
LIFT DUMP
LIFT DUMP SOLENOID VALVES
RESERVOIR QTY SPOILER ACTUATOR
#1 HYD. SYSTEM PRESSURE
FCECU ENERGIZED OPEN
LIFT DUMP
ISOLATION VALVE UNLOAD VALVE #1
EXTEND RETRACT RIGHT I/B SPOILER ACTUATOR
Figure 27-32. Inboard Spoiler Hydraulic Schematic
27-50
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL TEST OF THE ROLL SPOILER SYSTEM
Roll Spoiler Hydraulics Figure 27-32. Inboard Spoiler Hydraulic Schematic. In ground mode, the hydraulic pressure to the lift dump ports of each PCU passes through lift dump solenoid valves.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Disengage the roll disconnect mechanism.
The valves are hydraulically in series, two for the inboard PCUs and two for the outboard PCUs.
Engage the aileron gust lock.
Hydraulic Failure
Turn the pilots control wheel fully to the left then to right.
If the No.1 hydraulic system fails, the ROLL SPLR INBD HYD caution light illuminates. If the No.2 hydraulic system fails, and the airspeed is < 170 KIAS, the ROLL SPLR OUTBD HYD caution light illuminates. In the event of the hydraulic failure, the spoiler panels go down. They will be driven down by the airflow moving across the wing.
Revision 0.4
This operational check is to confirm that the spoilers, the PFCS indications and the caution lights operate correctly under the following conditions: •• Normal operation •• SPLR 1 Selected off • SPLR 2 Selected off.
FOR TRAINING PURPOSES ONLY
27-51
27 FLIGHT CONTROLS
OPERATION
27 FLIGHT CONTROLS
27-52 SPOILER OB POS LT EXC HI SPOILER OB POS LT EXC LO
97 98
1 SPOILER OB POS LT EXC HI 2 SPOILER OB POS LT EXC LO ROLL DISCONNECT DISCONECT HANDLE
SPOI LER OB POS LT HI SPOILER OB POS LT CT SPOILER OB POS LT LO
90 89 96
H1 H2
5 SPOI LER OB POS LT HI 4 SPOILER OB POS LT CT 3 SPOILER OB POS LT LO
100 93
SPOILER OB POS RT HI SPOILER OB POS RT CT SPOILER OB POS RT LO
92 91 99
B
POWERED FLIGHT CONTROL SHUTOFFS SPLR 1
SPLR 2
PUSH
PUSH
OFF
OFF
ROLL DISCONNECT MECHANISM SPOILER QUADRANT TENSION REGULATOR
FROM SPOILER CLUTCH
1 SPOILER OB POS RT EXC HI 2 SPOILER OB POS RT EXC LO
SPOILER CLUTCH
FROM SPOILER CLUTCH
SPOILER SPLITTER QUADRANT ASYMMETRIC LINKAGE
C
2
53
ROLL SPLR O/B CAUTION
3
69
ROLL SPLR O/B INHIBIT
RIGHT SPOILER OUTBOARD LINEAR VARIABLE DIFFERENTIAL TRANSDUCER (LVDT)
TO SPLR PUSHOFF SWITCH
FROM SHEET 1
70
TO SPLR PUSHOFF SWITCH SPOILER PCU
LH. OUTBD. SPOILER
4
LH. INBD. SPOILER
SPLR O/B PRESS SPOILER IB POS LT EXC HI SPOILER IB POS LT EXC LO
97 98
1 SPOILER IB POS LT EXC HI 2 SPOILER IB POS LT EXC LO
SPOI LER I B POS L T HI SPOILER IB POS LT CT SPOILER IB POS LT LO
90 89 96
5 SPOI LER I B POS L T HI 4 SPOILER IB POS LT CT 3 SPOILER IB POS LT LO
LEFT SPOILER INBOARD LINEAR VARIABLE DIFFERENTIAL TRANSDUCER (LVDT) ROLL SPLR I/B GND CAUTION LT
42
SPOILER IB POS RT EXC HI SPOILER IB POS RT EXC LO
100 93
SPOILER IB POS RT HI SPOILER IB POS RT CT SPOILER IB POS RT LO
92 9 91 99
1 SPOILER IB POS RT EXC HI 2 SPOILER IB POS RT EXC LO 26 ROLL SPLR O/B (GND)
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
D
H 2
SPLR O/B INHIB CAUTION
H1
P/J2 52
H1
1
5 SPOILER OB POS RT HI 4 SPOILER OB POS RT CT 3 SPOILER OB POS RT LO
5 SPOILER IB POS RT HI 4 SPOILER IB POS RT CT 3 SPOILER IB POS RT LO
RIGHT SPOILER INBOARD LINEAR VARIABLE DIFFERENTIAL TRANSDUCER (LVDT)
49 ROLL SPLR I/B (GND)
CAUTION AND WARNING PANEL
Figure 27-33. Spoiler Panel Indications - Spoiler System Schematic
RH. INBD. SPOILER
RH. OUTBD. SPOILER
MAINTENANCE TRAINING MANUAL
SPOILER OB POS RT EXC HI SPOILER OB POS RT EXC LO
A
H 2
FOR TRAINING PURPOSES ONLY
42
E TO AILERON CONTROLS
LEFT SPOILER OUTBOARD LINEAR VARIABLE DIFFERENTIAL TRANSDUCER (LVDT) ROLL SPLR O/B GND CAUTION LT
Powered By Number 1 Hydraulic System. Powered By Number 2 Hydraulic System.
DASH 8 Q400
NOTE
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to:
NOTES
•• Figure 27-33. S poiler Panel Indications - Spoiler System Schematic. •• Figure 27-34. R oll Spoilers Operation > 170 KIAS. 27 FLIGHT CONTROLS
•• Figure 27-35. L eft Wing Inboard Spoiler Jam Indicated.
Flight Mode Above 170 KIAS, the outboard spoilers are disabled by energizing the No.2 actuator unload valve. Power for the valve comes from the right essential bus to Pin A on the valve. The ground to Pin B of the valve is supplied through the FCECU.
Roll Spoiler Jam The “Pilot Flying” (PF) attempts to put in a roll command. One of the main control valve inputs is jammed, resulting in an increase in the force needed to move the control wheel. The clutch controlling the input to the jammed control valve slips and SPLR 1 or SPLR 2 switchlight illuminates. Power is always supplied to the inboard spoiler switchlight from the right essential bus. The ground for the switchlight is from the left wing spoiler jam switch S7. Pushing the switchlight provides a ground for the inboard actuator unload valve removing extend hydraulic pressure. The PUSH goes off in the switchlight OFF, remains on. The ROLL SPLR INBD HYD caution light illuminates through a ground provided by the No.1 flight spoiler low pressure switch.
FOR TRAINING PURPOSES ONLY
27-53
27 FLIGHT CONTROLS
27-54 A
L O/B S5
S11 S10
ON S4 PUSH B
L I/B ROLL DISC HANDLE
S7
A
A
A
A
P/J10 D
A
S3
C
#1 O/B PUSH OFF 1 1 ROLL SPOILER DISC JAM SW
H3
J2
S5
S4
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
E
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
5A
L3
L1
SPLR1 (INBD)
ACU (F6)
B
N
ROLL SPLRS ARM INBD
PUSH
5A
B
A
A
ROLL SPLRS IND
3
OFF
F R
A
A
A
TO SHEET 2 FROM FCECU ROLL SPOILER OUTBD
4
D
OFF
TAXI SWITCH
R I/B
H2 H1
X ADVSY LTS 28 VDC
K1
S8
R O/B
D
D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR2 (OUTBD)
RIGHT DC CBP
2
C G
RIGHT DC CBP
R ESS BUS 28 VDC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1
NO
D
OFF H2
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
CENTER GLARESHIELD PANEL
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
Figure 27-34. Roll Spoilers Operation > 170 KIAS
S V
8 9 24
CAUTION AND WARNING PANEL
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
C
OFF
G
E C U/F FLT COMP
C
F
H1
NC B
A
CABLE SENSORS X-54
LEFT WING SPOILER JAM E
DASH 8 Q400
C
A B C
A
L O/B S5
S11 S10
ON S4
C B
L I/B ROLL DISC HANDLE
S7
B
C
J/P9 A
D
S3
J/P10 C
S4
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
A
5A
A
#1 O/B PUSH OFF 1
H3
H1 1 ROLL SPOILER DISC JAM SW
J2
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
L3
L1
SPLR1 (INBD)
B
N
ROLL SPLRS ARM INBD
PUSH
5A
B
A
A
ROLL SPLRS IND
F A
A
A
TO SHEET 2
3
OFF
4
D
OFF
RIGHT DC CBP
TAXI SWITCH
R I/B
H2 H1
X ADVSY LTS 28 VDC
S8
R O/B
D
J/P34 D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
K1 B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR2 (OUTBD)
RIGHT DC CBP
2
C G
R
R ESS BUS 28 VDC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1 E
D
OFF
ACU (F6)
A
H2
NO S5
OFF
F E C
U/F FLT COMP
C G
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
S V
CENTER GLARESHIELD PANEL
8 9 24
CAUTION AND WARNING PANEL
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
27-55
Figure 27-35. Left Wing Inboard Spoiler Jam Indicated 27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
NC
A
CABLE SENSORS X-54
LEFT WING SPOILER JAM E
A
PUSH
DASH 8 Q400
C
A B
27 FLIGHT CONTROLS
27-56 A
L O/B S5
S11 S10
ON S4
C
PUSH B
L I/B ROLL DISC HANDLE
S7
E C
J/P9 A
D
S3
C
A
A
A
1 ROLL SPOILER DISC JAM SW
S4
H3
J2
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
5A
L3
L1
SPLR 1 (INBD)
ACU (F6)
B
N
ROLL SPLRS ARM INBD
PUSH
5A
B
A
A
ROLL SPLRS IND
A
A
A
TO SHEET 2
3
OFF
F
4
D
OFF
RIGHT DC CBP
TAXI SWITCH
R I/B
H2 H1
X ADVSY LTS 28 VDC
K1
S8
R O/B
D
D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR 2 (OUTBD)
RIGHT DC CBP
2
C G
R
R ESS BUS 28 V DC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1 E
D
OFF H2
#1 O/B PUSH OFF 1
NO S5
OFF
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
CENTER GLARESHIELD PANEL
S V
8 9 24
CAUTION AND WARNING PANEL
Figure 27-36. Left Wing Spoiler Jam Recovery Switchlight Pushed No.1 Unload Valve Energized to Unload
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
C
C G
H1
NC B
A
F
LEFT WING SPOILER JAM E
A
CABLE SENSORS X-54
U/F FLT COMP
DASH 8 Q400
C
A B
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL TEST OF THE SPOILER JAM DETECT SYSTEM
NOTES
27 FLIGHT CONTROLS
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 27-36. Left Wing Spoiler Jam Recovery Switchlight Pushed No.1 Unload Valve Energized to Unload. A mechanical clutch is incorporated at the spoiler clutch assembly, in the outer wing rear spar area of each wing. This clutch gives protection against complete loss of spoiler systems in the event of a jam. It removes the jammed spoiler from the circuit and allows the rest of the system to continue to operate. If a jam occurs, the roller on the pushrod will come out of its detent in the clutch assembly. This causes springs to push the switch plates out and turn on the SPLR1 or SPLR2 push-off switch. The SPLR1 push-off switch when pushed will de-energize the inboard spoiler hydraulic system. The SPLR2 push-off when pushed will de-energize the outboard spoiler hydraulic system. •• Before testing the spoiler jam detection make sure the spoilers operate normally. To simulate a jammed spoiler a rig pin is installed to one of the spoiler linkage lever to prevent movement of that spoiler PCU. This will be done to all four PCU clutches, one at a time.
NOTE A force of approximately 12 lbf (6 kgf) is required to disengage the spoiler clutch. When the spoiler clutch is disengaged, the pilot and co-pilot control wheels turn at their usual force of approximately 4 lbf (2 kgf). When the jam is detected it will cause a SPLR push off light to come on. Selection of the SPLR push off switch will cause the PUSH segment of the light to go out and the ROLL SPLR INBD HYD or the ROLL SPLR OUTBD HYD caution light to come on.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-57
27 FLIGHT CONTROLS
27-58 A
L O/B S5
S10
ON S4
C
PUSH B
L I/B ROLL DISC HANDLE
S7
A
A
A
A
#1 O/B PUSH OFF 1
D
S3
1 ROLL SPOILER DISC JAM SW
H3
J2
S4
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
E
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
L3
L1
SPLR1 (INBD)
ACU (F6)
ROLL SPLRS ARM INBD
B
N
5A PUSH B
ROLL SPLRS IND
A
A
A
A
A
TO SHEET 2
3
OFF
F R
4
D
OFF
RIGHT DC CBP
TAXI SWITCH
R I/B
H2 H1
X ADVSY LTS 28 VDC
K1
S8
R O/B
D
D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR2 (OUTBD)
RIGHT DC CBP
2
C G
5A
R ESS BUS 28 VDC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1
NO S5
D
OFF H2
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
CENTER GLARESHIELD PANEL
S V
8 9 24
CAUTION AND WARNING PANEL
Figure 27-37. Roll Spoiler Fuselage Cable Jam Indicated-Roll Disconnect System Activated-50 Degree Travel Switch Closed
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
C
C
OFF
G
E C U/F FLT COMP
J/P9 A
C
F
H1
NC P/J9 B
A
CABLE SENSORS X-54
LEFT WING SPOILER JAM E
DASH 8 Q400
S11 C
A B
MAINTENANCE TRAINING MANUAL
OPERATIONAL CHECK OF THE ROLL SPOILER SPLR 1 & SPLR 2 PUSH OFF SWITCHLIGHTS The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 27-37. Roll Spoiler Fuselage Cable Jam Indicated-Roll Disconnect System Activated-50 Degree Travel Switch Closed. •• Make sure that the CONTROL LOCK is set to OFF •• Pull the ROLL DISC handle and turn 90° to disconnect the roll spoilers •• Turn the co-pilot handwheel until the SPLR 1 and SPLR 2 switchlights come on (at approximately 50°)
Complete Roll Jam Using Roll Disconnect System Pilot Flying (PF) attempts to put in a roll command, but cannot move the control wheel. PF pulls the roll disconnect handle, this operates the roll disconnect clutch separating roll spoiler and aileron controls. This action also causes two micro-switches (S3 and S4) to arm the 50° travel switch S5. The S5 is on the aileron forward quadrant. To correct the input from a stuck up roll spoiler(s), the co-pilot turns the aileron control wheel 50°, this provides a ground through switch S5. The ground by S5 allows the PUSH OFF indications in SPLR 1 and SPLR 2 switchlights to illuminate.
•• Put the co-pilot handwheel back in the neutral position •• Make sure the two SPLR 1 and SPLR 2 switchlights go off •• Turn the co-pilot handwheel in the opposite direction, of step, until the SPLR 1 and SPLR 2 switchlights come on (at approximately 50°) •• Put the co-pilot handwheel back in the neutral position • Make sure the two SPLR 1 and SPLR 2 switchlights go off.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-59
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-60 FLT COMP A
L O/B S5
S11 S10
ON S4
C
PUSH B
L I/B ROLL DISC HANDLE
S7
A
E C U/F FLT COMP
A
D
S3
C
A
A
A
1 ROLL SPOILER DISC JAM SW
S4
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
H3
J2
E
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
5A
L3
L1
SPLR1 (INBD)
B
N
ROLL SPLRS ARM INBD
PUSH
5A
B
A
A
ROLL SPLRS IND
A
A
A
TO SHEET 2
3
OFF
F
4
D
OFF
RIGHT DC CBP
TAXI SWITCH
H2
P/J177
R I/B
H1
X ADVSY LTS 28 VDC
K1
S8
R O/B
D
D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR2 (OUTBD)
RIGHT DC CBP
2
C G
R
R ESS BUS 28 VDC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1
ACU (F6)
D
OFF H2
#1 O/B PUSH OFF 1
NO S5
OFF
G
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
CENTER GLARESHIELD PANEL
S V
8 9 24
CAUTION AND WARNING PANEL
Figure 27-38. Roll Spoiler Fuselage Cable Jammed-Roll Disconnect Activated 50° Travel Switch Closed-Both Switchlights Pushed-Both Unload Valves Energized to Unload
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
C
C
F
H1
NC B
A
CABLE SENSOR X-54
LEFT WING SPOILER JAM E
DASH 8 Q400
C
A B
MAINTENANCE TRAINING MANUAL
OPERATIONAL CHECK OF THE ROLL SPOILER CABLE SENSOR ASSEMBLY
Refer to Figure 27-38. Roll Spoiler Fuselage Cable Jammed-Roll Disconnect Activated 50° Travel Switch Closed-Both Switchlights PushedBoth Unload Valves Energized to Unload.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
Using this schematic, you can trace the following steps:
This maintenance procedure is for the operational check of the roll-spoiler cable sensor. Slowly pushing down on the top and bottom spoiler cables will allow the roller arm to turn clockwise until the microswitches close. In the flight compartment, make sure that the ROLL SPLR INBD HYD and the ROLL SPLR OUTBD HYD caution lights come on. Release the cables and let them push up on the roller. Make sure that the roller arm stays in the latched condition and that the ROLL SPLR INBD HYD and the ROLL SPLR OUTBD HYD caution lights stay on. Release the roller arm from its latched condition and make sure that the ROLL SPLR INBD HYD and the ROLL SPLR OUTBD HYD caution lights go out.
Revision 0.4
•• Roll Disconnect Activated 50° Travel Switch Closed •• Both Switchlights Pushed • Both Unload Valves Energized to Unload Pushing SPLR 1 switchlight, energizes closed the inboard unload valve providing a ground through contacts J3 to J1 of the switchlight. Pushing SPLR 2 switchlight provides a ground for outboard unload valve through contacts, A2 to A3 of the de-energized relay K1, as well as contacts J3 to J1 of the switchlight. Grounds are maintained for the OFF indications and removed for the PUSH indications in the switchlights. Removing all extend pressure from the spoiler PCUs causes all the roll spoilers to retract.
FOR TRAINING PURPOSES ONLY
27-61
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-62 A
L O/B S5
S11 S10
ON S4
C
PUSH B
L I/B ROLL DISC HANDLE
S7
E C
A
D
S3
C
A
A
A
1 ROLL SPOILER DISC JAM SW
S4
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
H3
J2
E
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
L3
L1
SPLR1 (INBD)
ROLL SPLRS ARM INBD
B
N
5A PUSH
5A
B
A
A
ROLL SPLRS IND
A
A
A
TO SHEET 2
3
OFF
F
4
D
OFF
RIGHT DC CBP
TAXI SWITCH
R I/B
H2 H1
X ADVSY LTS 28 VDC
K1
S8
R O/B
D
D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR2 (OUTBD)
RIGHT DC CBP
2
C G
R
R ESS BUS 28 VDC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1
ACU (F6)
D
OFF H2
#1 O/B PUSH OFF 1
NO S5
OFF
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
CENTER GLARESHIELD PANEL
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
Figure 27-39. Roll Spoiler Cable Sensor Operation
S V
8 9 24
CAUTION AND WARNING PANEL
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
C
C G
H1
NC B
A
F
LEFT WING SPOILER JAM E
A
CABLE SENSORS X-54
U/F FLT COMP
DASH 8 Q400
C
A B
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Roll Spoiler Cable Break (Operating Cable Sensor System)
NOTES
Refer Figure 27-39. Roll Spoiler Cable Sensor Operation.
27 FLIGHT CONTROLS
The PF puts in a roll command and the roll spoiler cable breaks. The lever of the sensor system pivots forward under spring force. This action closes microswitch S10, which provides a ground to energize the K1 relay. The K1 relay, through contacts A2 to A1, supplies the ground to energize the outboard unload valve, removing all extend pressure from the outboard PCUs. Switch S11 closes at the same time as S10. S10 provides the ground for the inboard unload valve through Pin B. The ROLL SPLR INBD HYD and the ROLL SPOILER OUTBD HYD caution lights come on through grounds provided by No.1 and No.2 Spoiler Low pressure switches.
FOR TRAINING PURPOSES ONLY
27-63
27 FLIGHT CONTROLS
27-64 PLA 1 47°
PLA 2 47°
PCU
SPLR RIGHT OUTBD
LVDT
FOR TRAINING PURPOSES ONLY
ADVISORY LIGHTS
DASH 8 Q400
LIFT DUMP VALVE 2
ROLL OUT BD
LIFT DUMP VALVE 1
28 VDC FCECU
PCU
SPLR RIGHT INBD
LVDT
#2 HYD LIFT DUMP VALVE 1
PCU
SPLR LEFT INBD
LVDT
FLIGHT/TAXI SWITCH
GROUND PSEU WOW 1 WOW 2
LIFT DUMP VALVE 2
PCU
#1 HYD
fsu67a01.cgm
Figure 27-40. Ground Spoiler System Block Diagram
SPLR LEFT OUTBD
LVDT
HYDRAULIC ELECTRICAL
MAINTENANCE TRAINING MANUAL
ROLL IN BD
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-62-00 SPOILER SYSTEM IN GROUND MODE
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
All the roll spoilers are automatically deployed on landing. They are deployed when signalled by the Main Gear Weight-On-Wheels (MGWOW) and power lever sensors are made. This action puts all the aircraft weight on the landing gear, so the wheel brakes can slow the aircraft with greater efficiently.
GENERAL Refer to Figure 27-40. Ground Spoiler System Block Diagram. The roll spoiler system automatically changes from the flight mode to the ground mode after the aircraft has landed. Ground mode operation occurs when: •• The Proximity Sensor Electronic Unit (PSEU) sends the MGWOW1 and MGWOW2 signals to the FCECU •• Power levers 1 and 2 are set to less than 47° • The FLIGHT/TAXI switch is in the FLIGHT position. The ground mode spoiler system includes the listed components: • Lift dump valves.
FOR TRAINING PURPOSES ONLY
27-65
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS A
NOTE Left side shown. Right side similar.
GLARESHIELD PANEL 1
LEGEND 1. Flight/Taxi Switch.
STICK PUSHER SHUT OFF
SPOILERS FLIGHT
ENGINE FIRE
A/P DISENG
ROLL INBD
TAXI
CF-AEI
INHIBIT
ELEVATOR TRIM SHUT OFF
TERRAIN INHIBIT
WARNING PRESS TO RESET
fsz09a02.cgm
A
Figure 27-41. Flight/Taxi Switch
27-66
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-41. Flight/Taxi Switch.
NOTES
Selection of the SPOILERS FLIGHT/TAXI switch to TAXI de-energizes all the lift dump solenoids causing spoiler panels to retract. The switch is held in the TAXI position by a magnetic latch solenoid. 27 FLIGHT CONTROLS
The magnetic latch is provided by the FCECU and PSEU WOW. The spring loaded switch returns to the FLIGHT position when: •• Advancing either power lever above flight idle +12° •• Removing electrical power from the aircraft • PSEU sensing WOFW.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-67
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SPOILER ADVISORY LIGHTS FLIGHT ROLL OUTBD
ROLL INBD
FROM No. 1 HYDRAULIC SYSTEM
TAXI
FROM No. 2 HYDRAULIC SYSTEM
FLIGHT IDLE + 12°
27 FLIGHT CONTROLS
FCECU LIFT DUMP VALVES OPEN
AND
LIFT DUMP VALVES OPEN
AND
PSEU MLG WOW
LH OUTBOARD SPOILER
RH INBOARD SPOILER
LH INBOARD SPOILER
RH OUTBOARD SPOILER
SPOILERS EXTENDED - LIFT DUMP VALVES OPEN
FROM No. 1 HYDRAULIC SYSTEM
ROLL OUTBD
SPOILER ADVISORY LIGHTS
ROLL INBD
FLIGHT
FROM No. 2 HYDRAULIC SYSTEM
TAXI
FCECU
LIFT DUMP VALVES CLOSED
LIFT DUMP VALVES CLOSED
PSEU
LH OUTBOARD SPOILER fsf29a02a.cgm
LH INBOARD SPOILER
RH INBOARD SPOILER
RH OUTBOARD SPOILER
SPOILERS RETRACTED - LIFT DUMP VALVES CLOSED
Figure 27-42. Roll Spoiler Ground Spoiler Mode Synoptic
27-68
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
System Description
NOTES
Refer to Figure 27-42. Roll Spoiler Ground Spoiler Mode Synoptic.
27 FLIGHT CONTROLS
When the aircraft lands, the lift dump valves are energized. The lift dump valves send hydraulic pressure to all the spoiler PCU extend ports which extends the spoiler panels to 75°. The FCECU and the PSEU control the lift dump function. The FCECU left channel controls the two inboard lift dump valves and the right channel controls the two outboard lift dump valves. Each pair of lift dump valves are solenoid operated and connected hydraulically in series. The FCECU sends a high side signal (+28 VDC) to the lift dump valve solenoids if both power levers are a less than flight idle plus 12°. The PSEU sends a low side signal (ground) to the lift dump valve solenoids when both MGWOW1 and MGWOW2 signals are present.
FOR TRAINING PURPOSES ONLY
27-69
27 FLIGHT CONTROLS
27-70 PLA LEFT
J5
P1 J1
N
26 26
J3 ROLL SPLR INBD GND
LEFT FCECU CHANNEL
42 42 66 66
CAUTION WARNING J5 PANEL 26
ROLL SPLR OUTBD GND
94 94
P2 J2
J2 P2
42 42
J1
J2
54 54
LIFT DUMP HI LIFT DUMP LO
LIFT DUMP HI LIFT DUMP LO
GLARESHIELD PANEL
PLA RIGHT
B
A B
SPOILER INBOARD VI
SPOILER OUTBOARD VI
J1
ADVISORY LIGHTS 13 CONTROL 14 DIM/TEST 14 UNIT 13
ROLL OUTBD
A
C1D 64 64
C1C
RIGHT FCECU CHANNEL
WOW 1 16 16
J8 N
WOW 2
PROXIMITY SENSOR ELECTRONIC UNIT C1B A6G
A6?
26 26
A4? FLIGHT/TAXI
TAXI SW RTN TAXI SW TAXI SW HOLD
79 79 78 78 94 94 87 87
GLARESHIELD PANEL
LIFT DUMP HI LIFT DUMP LO
LIFT DUMP HI LIFT DUMP LO
FROM FCECU 2 PWR IN
Figure 27-43. Roll Spoiler in Ground Mode Schematic
A B
SPOILER OUTBOARD V2
A B
SPOILER INBOARD V2
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
64 64
FROM ROLL SPLRS IND
ROLL INBD
16 16
DASH 8 Q400
49
J1 P1
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-43. Roll Spoiler in Ground Mode Schematic.
NOTES
The FLIGHT/TAXI switch interfaces with the right channel of the FCECU and is shared with the left channel for redundancy. 27 FLIGHT CONTROLS
When the FLIGHT/TAXI switch is selected to the TAXI position, the spoiler lift dump valves de-energize and the spoilers retract. After retraction plus 6.5 seconds, the FCECU performs a Event-Built-in-Test (EBIT). It energizes each lift dump valve solenoid individually to check if any valve is stuck in the open position. When all four spoiler panels are extended greater than 65° in the ground mode, the FCECU sends a signal to illuminate the spoiler advisory lights (ROLL OUTBD and ROLL INBD). If a solenoid valve fails to energize, the inboard or outboard ground spoilers will not extend. The FCECU illuminates the caution lights ROLL SPLR OUTBD GND and ROLL SPLR INBD GND if the related spoiler panels do not extend after touchdown. These caution lights illuminate after a time delay of 5 seconds. The FCECU illuminates the ground caution lights if the spoilers do not retract in the TAXI mode or if the BIT finds a failure in the lift dump valves.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-71
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Lift Dump Valves Refer to Figure 27-44. Spoiler Lift Dump Valve.
27 FLIGHT CONTROLS
The two lift dump valves for the inboard (No.1) spoiler system are located on the left side of the aircraft in the wing-to-fuselage attachment area. The two lift dump valves for the outboard (No.2) spoiler system are located on the right side of the aircraft also in the wing-to-fuselage attachment area.
Both valves must open to let extend pressure through the unload valve to the related spoiler PCU. This reduces the possibility of in flight symmetric deployment. The lift dump valves provide hydraulic system pressure to the spoiler PCU lift dump port and fully extend each spoiler panel symmetrically.
LEGEND 1. Electrical Connector. 2. Solenoid. 3. Return Port. 4. Pressure Port. 5. Check Valve. 6. Cylinder Port.
2
1
3 6
D
FW
4 5
ft087a01.cgm
Figure 27-44. Spoiler Lift Dump Valve
27-72
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Refer to Figure 27-45. Spoiler Surface Indication.
27 FLIGHT CONTROLS
The spoiler surface positions are displayed on the PFCS on MFD1. The indication displays panel deflection angle. INSTRUMENT PANEL
WX OFF
057
HDG 073°
E
3
160
LEGEND 1. Spoiler Position Indication
FMS1 076 00
VIE
35.0 NM --:--
VCF
YSO
00 ---
TAS 20 GS 0
1
YCF
80
TCAS STBY
ADF1 DME1 H 92.1 NM
ADF2 DME2 92.1 NM
I
1
I
Figure 27-45. Spoiler Surface Indication
FOR TRAINING PURPOSES ONLY
27-73
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
LEGEND 1. Spoiler Outboard. 2. Roll Spoiler Inboard Ground. OVERHEAD CONSOLE 2
1
#1 STALL SYST FAIL #2 STALL SYST FAIL ROLL SPLR INBD HYD
#2 HYD FLUID HOT
FLAP DRIVE
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING
FUELING ON
MAIN BAT HOT
fsz05a01.cgm
Figure 27-46. Roll Spoiler in Ground Mode Caution Lights
27-74
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-46. Roll Spoiler in Ground Mode Caution Lights. The FCECU sends signals to the Caution and Warning panel to illuminate the caution lights that follow:
ROLL SPLR INBD GND •• If the FCECU senses a loss of lift dump valve function, or •• If the lift dump valves are operated but the spoiler panels fail to extend after landing, or •• If the spoiler panels extend when the FCECU carries out the lift dump BIT, with the FLIGHT/TAXI switch set to TAXI •• PLAs disagree, one > 47°, one < 47°, WOW disagree • Internal failure of the FCECU.
ROLL SPLR OUTBD GND •• If the FCECU senses a loss of lift dump valve function, or •• If the lift dump valves are operated but the spoiler panels fail to extend after landing, or •• If the spoiler panels extend when the FCECU carries out the lift dump BIT, with the FLIGHT/TAXI switch set to TAXI •• PLAs disagree, one > 47°, one < 47°, •• WOW disagree • Internal Failure of the FCECU.
OPERATIONAL TEST OF THE GROUND SPOILER SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. This operational test is to confirm that the FLIGHT/TAXI switch, when in the TAXI position, will return to the FLIGHT position when power lever 1 and/or power lever 2 is moved to greater than the flight idle position of +12°. When the FLIGHT/TAXI switch is in TAXI position, observe the following indications: •• The PFCS spoiler indications show all the spoilers retracted •• The spoilers are retracted •• The ROLL INBD and ROLL OUTBD advisory lights go out • The ROLL SPLR INBD GND and ROLL SPLR OUTBD GND caution lights do not come on. When the FLIGHT/TAXI switch returns to FLIGHT that you observe the following indications: •• The PFCS spoiler indications show all the spoilers extended •• The spoilers are extended •• The ROLL INBD and ROLL OUTBD advisory lights come on •• The ROLL SPLR INBD GND and ROLL SPLR OUTBD GND caution lights do not come on
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-75
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-63-00 SPOILER PANELS
The PCUs that are attached to the inboard panels are supplied with hydraulic pressure from the No.1 hydraulic system.
Refer to Figure 27-47. Inboard and Outboard Spoiler Panels.
The PCUs that are attached to the outboard panels are supplied by the No.2 hydraulic system.
27 FLIGHT CONTROLS
All spoilers are flush mounted on the upper surface of the flap shroud, behind the wing rear spar. A spoiler actuator link connects the middle hinge attachment to the actuator on the spoiler PCU. The spoiler panels are flush with the wing top skin when retracted and extend upwards up to a maximum of 75° when operated.
2 1 3
4 LEGEND
6
1. Inboard Hinge Attachment. 2. Inboard Spoiler Panel. 3. Spoiler Actuator Link. 4. Middle Hinge Attachment. 5. Outboard Hinge Attachment. 6. Outboard Spoiler Panel.
5
D
FW
NOTE Left side shown. Right side similar. fs0c2a01.cgm
Figure 27-47. Inboard and Outboard Spoiler Panels
27-76
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-16-00 ROLL DISCONNECT SYSTEM
GENERAL
INTRODUCTION
When disconnected, the pilot control handwheel operates the spoiler control circuit and the co-pilot control handwheel operates the aileron control circuit. When connected, the control connected handwheels operate both circuits at the same time.
The roll disconnect system disengages the aileron and roll spoiler control circuits from each other in the event of a jam in either control circuit. The remaining operational circuit maintains roll control of the aircraft.
The roll disconnect system has the following components: •• Roll disconnect handle •• Roll disconnect lever assembly • Roll disconnect clutch mechanism.
2
1
FW
D
3
LEGEND 1. Roll Control Disconnect Handle. 2. Co-pilot's Control Column. 3. Cables. 4. Spring And Lever Assembly. 5. Roll Spoiler De-Clutch Micro-Switch. 6. Clutch Mechanism.
7
7. Lever Assembly Roll Disconnect.
6
4 5
ft175a01.cgm
Figure 27-48. Roll Disconnect System
FOR TRAINING PURPOSES ONLY
27-77
27 FLIGHT CONTROLS
Refer to Figure 27-48. Roll Disconnect System.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Roll Disconnect Handle Refer to Figure 27-49. Roll Disconnect Handle. The roll disconnect handle is used to operate the roll disconnect system. 27 FLIGHT CONTROLS
The roll disconnect handle is normally in the engaged position. The handle is connected to a clutch mechanism at the base of the co-pilot control column by cables, pulleys, and a springloaded lever assembly.
The roll disconnect mechanism is re-engaged when the pilots and co-pilot handwheels are moved to the same position, and the roll disconnect handle is rotated 90° and released. The spring on the clutch mechanism pulls the handle back to the engaged position. The handle pulls out 2 inches (5 cm) maximum from the center console.
The roll disconnect mechanism is disengaged when the roll disconnect handle is pulled to the stop and rotated by 90°. When the handle is pulled out to the limit and rotated 90°, the pin slides into the slot of the handle shaft to keep the handle locked in the disengaged position.
ROLL
DISC
ROLL
DISC
ENGAGED
DISENGAGED
FW
D CENTER CONSOLE
Figure 27-49. Roll Disconnect Handle
27-78
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Roll Disconnect Lever Assembly Refer to: •• Figure 27-48. Roll Disconnect System. • Figure 27-50. R oll Disconnect Lever Assembly. The roll disconnect lever assembly is used to gain mechanical advantage over the clutch mechanism. The roll disconnect lever assembly is located below the flight compartment floor near the base of the co-pilot control column. The lever assembly is attached by a cable to the roll disconnect handle. Another cable attaches the lever to the engagement spring cover of the clutch mechanism.
At the same time, the rotating lever assembly closes two microswitches which are a part of the roll spoiler advisory light circuit (refer to 27-60-00). A return spring attached to the lever assembly keeps the tension off the cable joining the lever assembly to the clutch mechanism. This prevents the clutch from accidentally disengaging and helps to return the roll disconnect handle to the engaged position.
When the roll disconnect handle is pulled, the lever assembly rotates and pulls the engagement spring cover, which causes the clutch to disengage.
1 2
LEGEND
3
1. Clutch Cable Plate. 2. Pivot Point. 3. Lever. 4. Rig Pin Index Hole. 5. Spring. 6. Microswitches.
FW
D 4 6 5
Figure 27-50. Roll Disconnect Lever Assembly
FOR TRAINING PURPOSES ONLY
27-79
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Roll Disconnect Clutch Mechanism Refer to Figure 27-51. Roll Disconnect Clutch Mechanism.
27 FLIGHT CONTROLS
The roll disconnect clutch mechanism disconnects the roll control of the co-pilot handwheel from the roll control of the pilot handwheel. The roll disconnect clutch mechanism is attached to the base of the co-pilot control column.
When clutch is engaged the chain in the co-pilot control column rotates the sprocket and clutch which drives the clutch plate and lever. The lever part of the clutch plate and lever assembly is attached to the pilot’s control column through the interconnect rod. When the roll disconnect handle is pulled and turned 90°, the clutch plate and lever is separated from the clutch and sprocket. The engagement spring keeps the clutch in the engaged position.
The roll disconnect clutch mechanism consists of an engagement spring, engagement spring cover and a clutch. The clutch is made up of two halves: •• Clutch and sprocket assembly • Clutch plate and lever assembly.
FW
D
1
FW
D 2
3
CO-PILOT CONTROL COLUMN LEGEND 1. Co-pilot Control Column Attachment. 2. Roll Disconnect Clutch Housing. 3. Clutch Mechanism Shaft. 4. Roll Control Lever. ft027a01.cgm
Figure 27-51. Roll Disconnect Clutch Mechanism
27-80
FOR TRAINING PURPOSES ONLY
4
MAINTENANCE TRAINING MANUAL
Interfaces Refer to: •• Figure 27-52. Aileron Forward Quadrant Microswitch (50°). • Figure 27-53. Spoiler Pushoff Switchlights. The roll disconnect system is interfaced with the roll spoiler advisory switchlights (SPLR1 and SPLR2).
When the roll disconnect microswitch and either side of the 50° switches is activated, the SPLR1 and SPLR2 PUSH OFF switchlights come on. Pushing the switchlights depressurizes the spoiler PCU causing the associated spoiler panels to retract flush with the wing surface. This will cause the caution lights to illuminate: 27 FLIGHT CONTROLS
DASH 8 Q400
•• ROLL SPLR INBD HYD • ROLL SPLR OUTBD HYD.
The SPLR1 and SPLR2 switchlights are located on the center glareshield panel. When the roll disconnect handle is pulled, two microswitches are closed by the roll disconnect lever assembly. When the co-pilot control handwheel is rotated more than 50°, the aileron quadrant closes the 50° travel microswitch. This microswitch is located on the aileron forward quadrant.
AILERON FORWARD QUADRANT
FWD
fs174a01.cgm
Figure 27-52. Aileron Forward Quadrant Microswitch (50°)
FOR TRAINING PURPOSES ONLY
27-81
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
GLARESHIELD PANEL
Spoiler 1 Push Off Switchlight
Spoiler 2 Push Off Switchlight
POWERED FLIGHT CONTROL SHUTOFFS
IAS
HSI SEL
Figure 27-53. Spoiler Pushoff Switchlights
fs285a01.cgm
27-82
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
RIGGING OF THE ROLL DISCONNECT SYSTEM
NOTES
27 FLIGHT CONTROLS
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Install rig pins in aileron and spoiler quadrants and disconnect lever assembly •• Push control columns fully fwd and hold •• Adjust cable tensions •• Pull control columns fully aft and hold •• Adjust cable tensions •• Pull ROLL DISC handle •• C h e c k f o r f u l l a n d f r e e r a n g e o f movement of control wheels •• Reset ROLL DISC handle.
OPERATIONAL CHECK OF THE ROLL DISCONNECT MECHANISM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Release the CONTROL LOCK lever to the OFF position •• Pull the ROLL DISC handle and turn it through 90° •• Make sure the control wheels can be turned independently •• Return the control wheels to their neutral positions •• Release ROLL DISC handle to the normal position •• Apply the GUST LOCK.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-83
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
3
4 2
5 6 7
1
LEGEND
8
1. Rudder Pedals. 2. Rudder Mixer Quadrant. 3. Rudder PCUs (2). 4. Trailing Rudder. 5. Fore Rudder. 6. Rudder Aft Quadrant. 7. Rudder Cables.
fs203a01.cgm
Figure 27-54. Rudder Control System
27-84
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-21-00 RUDDER SYSTEM
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The rudder system transmits the yaw commands from the pilot and co-pilot rudder pedals to the rudder control surfaces.
GENERAL Refer to Figure 27-54. Rudder Control System. Movement of the rudder pedals is transmitted to two hydraulic PCUs. The PCUs move the rudder in proportion to the amount of rudder pedal input. The rudder system also has inputs from the automatic flight control system (Yaw Damper) and the rudder trim actuator. The rudder system is comprised of the components listed below: •• Rudder pedals •• Rudder forward quadrants •• Rudder mixer quadrant •• Rudder restrictor •• Rudder aft quadrant •• Power control unit actuator •• Rudder shutoff valves •• PCU input bungee • Rudder position LVDT.
FOR TRAINING PURPOSES ONLY
27-85
27-86
DASH 8 Q400 MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
Figure 27-55. Rudder Control System Synoptic
27 FLIGHT CONTROLS
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION
NOTES
Refer to Figure 27-55. Rudder Control System Synoptic.
27 FLIGHT CONTROLS
There are two pairs of mechanically linked rudder pedals located in the flight compartment. Movement from either the pilot or co-pilot rudder pedals are transmitted simultaneously by two independent cable circuits to the mixer quadrant. From the mixer quadrant, a single cable circuit is routed aft and below the left side of the cabin floor. The cables pass through the pressure seals at the aft bulkhead, then up to the aft quadrant located behind the front spar of the vertical stabilizer. From the aft quadrant, a pushrod actuates two hydraulic PCUs through an artificial feel spring unit.
FOR TRAINING PURPOSES ONLY
27-87
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
6 4
5
7
3 2 1
LEGEND 1. Pedal Column. 2. Rudder Input Connecting Rod. 3. Pedal Adjustment Mechanism. 4. Rudder Pedals. 5. Rudder Control Interconnect Push Rod. 6. Brake Linkages. 7. Input Quadrant Connecting Rod. ft245a01.cgm
Figure 27-56. Rudder Pedals
27-88
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Rudder Pedals Refer to Figure 27-56. Rudder Pedals.
27 FLIGHT CONTROLS
The rudder pedals transmit inputs to the rudder control system and the main brake system. The rudder pedals are attached through levers below the flight compartment floor. Movement of the rudder pedals rotates the rudder forward quadrant. The pilot and co-pilot rudder pedals are connected through an interconnect rod. The rudder pedals are pivot-mounted to brackets below the flight compartment floor. A rudder pedal adjustment handle allows both fore and aft adjustment of the rudder pedals. Each adjustment handle is located on the pedestal between the pilot’s feet.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-89
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
B
A
A
4
RUDDER FORWARD ASSEMBLY
5 3
LEGEND
6
2
7
1 5
ft253a01.cgm
1. Rudder Restrictor Input Lever. 2. Rudder Restrictor. 3. 12 0 Stop. 4. Rudder Input Quadrant. 5. Travel Stop. 6. Mounting Bracket. 7. Rig Pin Hole. NOTE Right Side Shown.
B
Figure 27-57. Co-pilot’s Rudder Forward Quadrant
27-90
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Rudder Forward Quadrants Refer to Figure 27-57. Co-pilot’s Rudder Forward Quadrant. The rudder forward quadrants transmit rudder pedal inputs to the rudder mixer quadrant. Each rudder forward quadrant is located below the flight compartment floor and is attached to the aircraft by two mounting brackets. The co-pilot rudder quadrant has a rudder restrictor mechanism and a potentiometer. The restrictor limits rudder pedal movement to the rudder surface to deflect 12° each side of the aircraft center line. The potentiometer transfers rudder pedal movement to the nose wheel steering system.
ADJUSTMENT OF THE RUDDER PEDAL POSITION SENSOR The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 27-58. Download Unit - Hand Held Onsite FDR_Series 400. •• Energize the electrical system •• Make sure there are no FCECU faults on the ARCDU screen •• Connect the Hand Held Download Unit (HHDLU) to the FDR •• Put the aircraft in Weight Off Wheels condition •• Pressurize the hydraulic systems •• Move the FLAP LEVER to 15° position •• Put the HHDLU in decimal mode and make the appropriate selections •• Check the HHDLU figures at neutral and the other positions listed in the task
HA
ND
•• No adjustment is necessary if the HHDLU readings are correct.
HE
PA LD RT D SE NO. 9 OW NL RIA 64− DA L NO 0446 OAD . TE UN IT UN CODE IT : W E NO M V IGHT :4 OL L TA GE BS M PO A : 11 WE 5V X A MO R: 10 W OR 2 C 40 DS M 8 V HZ TA AC TU AX S 12
34
56
78
91
0
Figure 27-58. Download Unit - Hand Held Onsite FDR_Series 400
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-91
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Rudder Mixer Quadrant Refer to Figure 27-59. Rudder Mixer Quadrant. The rudder mixer quadrant combines rudder control from the two rudder forward quadrants and transmits it to the rudder aft quadrant. 27 FLIGHT CONTROLS
The rudder mixer quadrant consists of a threepulley quadrant installed below the cabin floor, aft of the turbine rotor burst zone. The two pairs of control cables are routed aft from the rudder forward quadrants to the upper two
pulleys of the mixer quadrant. These dual cables ensures continued rudder control if a single cable failure occurs . From the lower pulley of the mixer quadrant, a single pair of cables is routed aft and below the left side of the cabin floor. The cables pass through the pressurization seal at the rear pressure dome in the aft fuselage, then up to the rudder aft quadrant in the vertical stabilizer.
LEGEND 1. RH Forward Quadrant Control Cables. 2. RH Pulley Bracket. 3. Rig Pin Hole. 4. Rudder Mixer Quadrant. 5. LH Pulley Bracket. 6. Aft Rudder Quadrant Control Cables. 7. LH Forward Quadrant Control Cables.
A
2 3
1
4 5
6
7
ft206a01.cgm
A
Figure 27-59. Rudder Mixer Quadrant
27-92
FOR TRAINING PURPOSES ONLY
D
FW
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-93
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
FWD
RUDDER SYSTEM CONTROL VERTICAL STABILIZER
4 6
3
2 1
LEGEND 1. Push Rod. 2. Rudder Aft Quadrant. 3. Rig Pin Hole. 4. Mounting Brackets. 5. Mixing Quadrant Output Cables. 6. Primary Travel Stops.
D
FW
6 5
ft221a01.cgm
Figure 27-60. Rudder Aft Quadrant
27-94
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Rudder Aft Quadrant
left and right
The rudder aft quadrant transmits rudder control inputs from the mixer quadrant to the PCUs. The rudder aft quadrant is located halfway up the vertical stabilizer next to the two PCUs. The rudder aft quadrant has the primary travel stops for the rudder cable system.
RIG RUDDER PEDALS TO RUDDER FORWARD QUADRANT & RIG FORWARD QUADRANT TO RUDDER MIXER QUADRANT The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Remove input push rods to the left and right forward rudder quadrants •• Remove rudder inter-connect pushrod •• Install rigging pins in the left and right rudder output levers •• Install rigging pins in the left and right forward rudder quadrants •• Disconnect the rudder pedals potentiometer •• Rig the rudder pedals
•• Re-connect rudder pedal potentiometer •• Do an operational test of the rudder system.
RIGGING OF RUDDER MIXER QUADRANT TO THE RUDDER AFT QUADRANT The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Install the rigging pins in the rudder feel and trim unit, the rudder aft quadrant, the rudder mixer quadrant and the left and right forward rudder quadrants •• Move the FLAP LEVER to the 35° position •• Disconnect the pushrod from the rudder aft quadrant •• Check cable tensions observing wait times if new cables fitted •• Re-connect the pushrod to the rudder aft quadrant •• Remove all rigging pins •• Operate rudder pedals to full travel left and right •• Do an operational check of the rudder system.
•• Install input push rods to the left and right forward rudder quadrants and inter-connect pushrod •• Install rigging pins in the rudder mixer and aft quadrants •• Check cable tensions •• If new cables were installed follow TASK for wait times between initial and final tension adjustments •• Remove rigging pins •• Operate the rudder control system fully
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-95
27 FLIGHT CONTROLS
Refer to Figure 27-60. Rudder Aft Quadrant.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
RUDDER SYSTEM CONTROL VERTICAL STABILIZER
FWD
27 FLIGHT CONTROLS
2
10
3
4
1
5
FW
D
6
7 9 LEGEND
12
1. PCU Input Bungee. 2. Summing Bar. 3. Pressure Control Valve. 4. Upper PCU. 5. Main Control Valve. 6. Actuator Output Rod. 7. Rudder Connecting Rod. 8. Lower PCU. 9. Compensator. 10. Pressure Transducers. 11. Leak Detection Valves. 12. Compensator level Window (2).
8
11
ft224a01.cgm
Figure 27-61. Rudder Power Control Unit
27-96
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Power Control Units Refer to Figure 27-61. Rudder Power Control Unit. The PCUs transmit rudder inputs to the rudder surfaces. There are two PCUs, they are located above each other in the vertical stabilizer. The PCUs are attached to the fore rudder. The No.2 hydraulic system powers the upper PCU while the No.1 hydraulic system powers the lower PCU. Each PCU is composed of two major assemblies: •• Actuator (ram) assembly with a fully balanced ram • Integral hydraulic manifold assembly. The integral hydraulic manifold assembly contains the following items: •• Pressure port
Rudder Hinge Moment Limiting (HML) The left and right FCECU channels supply rudder Hinge Moment Limiting (HML) commands to the lower and upper rudder PCUs. The HML commands are based on airspeed signals from the Air Data Units (ADUs) 1 and 2. As the airspeed signals change, the FCECU uses the HML commands to regulate the pressure in each rudder Power Control Unit (PCU), by controlling the pressure control valve in the PCU. As airspeed increases, the regulated PCU pressure decreases to reduce total rudder travel at higher airspeeds. The FCECU also receives pressure signals from two pressure sensors located in each PCU. This lets the FCECU monitor the regulated PCU pressure for any failure modes. If a pressure failure occurs, the FCECU commands the rudder PCU shutoff valve to depressurize the PCU and the RUD1 HYD or RUD2 HYD caution lights come on. If No.1 and No.2 hydraulic systems fail the FCECU will cause the RUD CNTRL caution light to come on.
•• Inlet check valve •• Main Control Valve (MCV) •• Pressure Control Valve (PCV) •• Compensator •• Leak detection valve •• Anti-cavitation check valves (2) •• Pressure reference relief valves (2) • Pressure transducers (2).
FOR TRAINING PURPOSES ONLY
27-97
27 FLIGHT CONTROLS
DASH 8 Q400
27-98
Figure 27-62. Rudder PCU Schematic
MAINTENANCE TRAINING MANUAL
COMPENSATOR LEVEL WINDOW FOR TRAINING PURPOSES ONLY
DASH 8 Q400
CENTERING
27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
Refer to: •• Figure 27-62. Rudder PCU Schematic. •• Figure 27-63. R udder PCU Fluid Compensator. The pressure port supplies system hydraulic pressure to the inlet check valve and then to the PCV. The PCV regulates the control pressure as a function of airspeed. The mechanically operated four-way MCV positions the actuator ram. Position feedback is done by a mechanical linkage (summing bar), which compares the commanded ram position with the actual position. Input from the pilot or yaw damper causes the four-way MCV to reposition the ram towards the commanded position. Movement of the ram (and the rudder) stops when the actual ram position is the same as the commanded position nulled by the summing bar. The compensator stores 50 psi in a spring loaded accumulator for use by the PCU in the event of loss of supply pressure to the PCU. This aids in maintaining flutter suppression. The two PCU compensators also perform gust damping when the PCUs are depressurized. A level check window indicates the amount of fluid stored in the compensator.
The return fluid from the failed PCU is c ir c ula te d thr ough the MC V a nd t h e compensator to avoid fluid escape from a failed PCU when driven from the serviceable PCU. Two pressure reference relief valves limit the PCU pressure to 3200 psi. Also, the pressure reference relief valves will crack at 2-8 psi in the event of a MCV jam with the PCU depressurized. Thus allowing a jammed PCU to bypass and be back-driven by the functioning PCU. The two pressure transducers supply PCV HML pressure feedback signals to the FCECU.
A LEAK DETECTION VALVE END CAP
The compensation level window shows green or red if it does not stay pressurized after hydraulic system depressurized. The leak detection valve detects unacceptable PCU internal leakage. The leak detection valve incorporates a 50 psi relief valve to prevent the PCU hydraulic fluid from escaping during a loss of supply pressure. The leak detector valve is checked for open or short with hydraulic systems pressurized indicating leaks. The two anti-cavitation check valves prevent actuator cavitation when one PCU is depressurized. The anti-cavitation valves crack at 2-8 psid to allow the serviceable PCU to overcome the failed unit.
A
FW
D
PCU FLUID COMPENSATOR
FLUID COMPENSATOR VISUAL LEVEL INDICATOR pb529a01.cgm 16 Apr 01
Figure 27-63. R udder PCU Fluid Compensator
FOR TRAINING PURPOSES ONLY
27-99
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Rudder Shut-off Valves Refer to Figure 27-64. Rudder Shut-off Valve. The Rudder Shut-off Valves (SOV) supply hydraulic system pressure to the rudder PCU.
27 FLIGHT CONTROLS
Each rudder PCU is equipped with a rudder SOV to shut down the PCU. The rudder SOVs are located on the vertical stabilizer rear spar below the rudder PCU. Each of the two FCECU channel controls its SOV open and close.
If a PCU pressure regulation failure is detected, the FCECU will command zero pressure to the PCU pressure control valve and command the associated rudder SOV to close. The rudder Push Off switchlight(s) also commands the FCECU to actuate the rudder SOV. De-energized, the rudder SOV de-pressurizes its PCU by porting return pressure to the PCU pressure port for flutter suppression. In the event of complete loss of electrical power on the aircraft, the Rudder SOVs will close.
5
4 RUDDER SHUT-OFF VALVES
FW
D
2
FW
1
D
3 LEGEND
NOTE
1. Solenoid. 2. Electrical Connector. 3. Hydraulic Port Return. 4. Mounting Bracket. 5. Hydraulic Pressure Port.
Left side shown. Right side similar.
fss69a01.cgm
Figure 27-64. Rudder Shut-off Valve
27-100
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-101
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
RUDDER CONTROLS - VERTICAL STABILIZER
FWD
LEGEND 1. Motion Detector Limit Switch. 2. Motion Detector Linkage. 3. Motion Detector Cam Arm. 4. Spring Strut. 3
D
1
FW
2
4 ft214a01.cgm
Figure 27-65. Rudder PCU Input Bungee
27-102
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
PCU Input Bungee Refer to Figure 27-65. Rudder PCU Input Bungee. The PCU input bungees transmit rudder system control feel unit assembly inputs to the rudder PCU. There are two PCU input bungees, one for each rudder PCU. Each PCU input bungee has a spring strut and a motion detector. Each spring strut is installed between the feel unit assembly and its related PCU summing bar. A spring strut motion detector is installed parallel to each spring strut, and has a cam arm, link, and limit switch. During normal operation, each spring strut length stays constant. In the event of a PCU jam or its linkage, any pilot input to the rudder aft quadrant causes an inner spring in the strut to either stretch or compress.
•• Move the sum bars of the upper and lower PCUs forward and aft and check clearances between the switch rollers and the microswitches Observe electrical, hydraulic and moving surfaces warnings •• Connect external DC ground power •• Pressurize No.1 and No.2 hydraulic systems •• Move the sum bars on the PCUs forward and backward checking that the RUD1 and RUD2 PUSH OFF switchlights come ON, and go OFF when the sum bars are in neutral positions •• Make sure that the rudder movement is not greater than 2.5 inches from the rigging point, when moving the sum bars from neutral •• Remove hydraulic and electrical power.
The change in strut length causes the motion detector cam arm to trigger the limit microswitch. The microswitch causes the RUD1 or RUD2 PUSH OFF switchlight on the glareshield panel to illuminate.
RIGGING OF THE UPPER SPRING STRUT MOTION DETECTOR & RIGGING OF THE LOWER SPRING STRUT MOTION DETECTOR The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Adjust the microswitches on the motion detectors to set the switch rollers in the center of the cams •• Make sure that the RUD1 and RUD2 PUSH OFF switchlights do not come on
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-103
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Rudder Position LVDT Refer to Figure 27-66. Rudder Position LVDT. The rudder position LVDT supplies an electrical signal, which is equivalent to the angular position of the rudder to the FCECU. 27 FLIGHT CONTROLS
A rudder position LVDT is located in the vertical stabilizer.
RUDDER POSITION LVDT ASSEMBLY
FWD
FW
D
fs202a01.cgm
Figure 27-66. Rudder Position LVDT
27-104
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Controls and Indications Refer to Figure 27-67. Rudder Position on MFD.
A white rudder position indicator displays against a white scale on MFD1. MAIN INSTRUMENT PANEL
WX OFF
FMS1 076 00
057
HDG 073°
E
3
160
VIE
35.0 NM --:--
VCF
YSO
00 ---
TAS 20 GS 0
YCF
80
TCAS STBY
ADF1 DME1 H 92.1 NM
ADF2 DME2 92.1 NM
I
I
Rudder Position Indication.
Figure 27-67. Rudder Position on MFD
FOR TRAINING PURPOSES ONLY
27-105
27 FLIGHT CONTROLS
The rudder position LVDT transmits the rudder position data to the PFCS indicator on MFD1 and to the FDR.
DASH 8 Q400
OVERHEAD CONSOLE
MAINTENANCE TRAINING MANUAL
#1 Rudder Hydraulic Pressure
#2 Rudder Hydraulic Pressure
ROLL SPLR INBD GND
#1 STALL SYST FAIL #2 STALL SYST FAIL
27 FLIGHT CONTROLS
ROLL SPLR INBD HYD
#2 HYD FLUID HOT
FLAP DRIVE
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING
FUELING ON
MAIN BAT HOT
GLARESHIELD PANEL
RUD 1 Push Off Switchlight.
RUD 2 Push Off Switchlight.
POWERED FLIGHT CONTROL SHUTOFFS
IAS
HSI SEL
Figure 27-68. Rudder Push Off Switchlights
27-106
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-68. Rudder Push Off Switchlights.
Obey all electrical and hydraulic safety precautions and warnings.
When the PCU input bungee limit microswitch has been made, the applicable RUD1 or RUD2 rudder switchlight on the glareshield panel comes on. The PUSH OFF switchlight warns of the jammed condition. The switchlight is pushed to depressurize the jammed system. The illuminated switchlight then shows OFF.
Configure the aircraft as follows:
The switchlights interfaces with the FCECU and are centrally located on the glareshield. Pushing either PUSH OFF switchlight causes the FCECU to command zero pressure in the rudder PCU and also cause the rudder shut off valve to close. The FCECU inhibits both RUD PUSH OFF switchlights from being manually actuated OFF at the same time.
•• PLA 1 and PLA 2 to 80%
Low hydraulic pressure causes the related No.1 RUD HYD or No.2 RUD HYD caution light to come on. The No.1 or No.2 RUD HYD caution light comes on for the following: • Hydraulic system pressure is < 350 +/-50 psi (2413 +/-344.7 kPa) The RUD CNTRL caution light comes on for any of the following: •• FCECU detects a difference of 17 knots or more between the Airspeed 1 and Airspeed 2 from the air data units •• F C E C U l o s e s i t s a b i l i t y t o l i m i t hydraulic pressure •• Both hydraulic systems fail. • Interfaces.
•• Put the aircraft in WOFFW mode •• ADC 1 and ADC 2 to 50kts •• Flap lever to 15° •• Flight/Taxi switch to Flight •• Energize the electrical system •• P r e s s u r i z e t h e h y d r a u l i c s y s t e m s (3000 psi) •• Install rigging pins in the aft quadrant and the feel unit rigging plate •• Push RUD1 PUSH OFF switchlight observe No.1 RUD HYD caution light ON •• Adjust upper spring bungee to center aft rudder on rigging mark •• Push RUD1 PUSH OFF switchlight observe No.1 RUD HYD caution light OFF •• Repeat procedure operating RUD No.2 PUSH OFF •• Safety rod ends of upper and lower spring bungees •• Repeat the operation of RUD1 and RUD2 PUSH OFF switchlights •• Observe correct operation of RUD1 and RUD2 HYD caution lights •• Observe trailing rudder is within tolerance of the rigging mark •• Remove rigging pins
RIGGING OF RUDDER PCUS WITH HYDRAULIC POWER
•• Do operational check of rudder systems.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-107
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL TEST OF THE RUDDER SHUTOFF VALVES
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. 27 FLIGHT CONTROLS
Refer to Figure 27-75. Rudder SOV Hydraulic Schematic. •• Energize the electrical system. •• Pressurize No.1 and No.2 hydraulic systems. •• Make sure the rudder pedals and rudder surfaces are in neutral positions. •• Push RUD1 PUSH OFF switchlight, make sure it shows the word OFF.
NOTE Lower rudder PCU goes into bypass mode, pressure control valve closes, rudder SOV remains open. •• Make sure No.1 RUD HYD caution light comes ON. •• Open and tag C.B. RIGHT DC L6 FCS ECU2 •• NOTE. The FCECU 2 will close the rudder SOV and the pressure control valve for the upper rudder actuator. The actuator will now be hydraulically locked. •• Make sure the ELEVATOR FEEL, PITCH TRIM and ELEVATOR ASYMMETRY caution lights come ON. The No.2 RUD HYD caution may come ON momentarily. •• Make sure that you cannot manually push the rudder to the right or left. •• If the rudder can be manually moved the upper rudder SOV has failed open, and must be replaced. •• Remove the tag and close the C.B. •• Repeat the above for the other rudder SOV. 27-108
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-109
DASH 8 Q400
RUD LIM RT EHV HI B RUD LIM RT EHV LO E
MAINTENANCE TRAINING MANUAL
3 HI RUD LIM RT EHV 11 LO RUD LIM RT EHV
27 FLIGHT CONTROLS
RUD LIM RT 1 DELTA P LO RUD LIM RT 1 DELTA P CT RUD LIM RT 1 DELTA P HI RUD LIM RT 1 EXC HI RUD LIM RT 1 EXC LO
1 5 4 2 3
4 12 13 6 5
LO RUD LIM RT 1 DELTA P CT RUD LIM RT 1 DELTA P HI RUD LIM RT 1 DELTA P HI RUD LIM RT 1 EXC LO RUD LIM RT 1 EXC
RUD LIM RT 2 EXC HI RUD LIM RT 2 EXC LO RUD LIM RT 2 DELTA P LO RUD LIM RT 2 DELTA P CT RUD LIM RT 2 DELTA P HI
2 3 1 5 4
15 7 14 23 24
HI RUD LIM RT 2 EXC LO RUD LIM RT 2 EXC LO RUD LIM RT 2 DELTA P CT RUD LIM RT 2 DELTA P HI RUD LIM RT 2 DELTA P
ADU 2 LO 27 HI 38
UPPER RUDDER PRESSURE CONTROL SERVO VALVE
RUD LIM 2 UP EXC HI A RUD LIM 2 UP EXC LO C
88 HI RUD LIM 2 UP EXC 80 LO RUD LIM 2 UP EXC
UPPER RUDDER SHUTOFF VALVE RUD LIM LT 1 EHV HI 3 RUD LIM LT 1 EHV LO 11
B HI RUD LIM LT 1 EHV E LO RUD LIM LT 1 EHV
RUD LIM LT 1 DELTA P HI RUD LIM LT 1 DELTA P CT RUD LIM LT 1 DELTA P LO RUD LIM LT 1 EXC HI RUD LIM LT 1 EXC LO
13 12 4 6 5
4 5 1 2 3
LO RUD LIM LT 1 DELTA P CT RUD LIM LT 1 DELTA P HI RUD LIM LT 1 DELTA P HI RUD LIM LT 1 EXC LO RUD LIM LT 1 EXC
RUD LIM LT 2 EXC HI RUD LIM LT 2 EXC LO RUD LIM LT 2 DELTA P LO RUD LIM LT 2 DELTA P CT RUD LIM LT 2 DELTA P HI
15 7 14 23 24
2 3 1 5 4
HI RUD LIM LT 2 EXC LO RUD LIM LT 2 EXC LO RUD LIM LT 2 DELTA P CT RUD LIM LT 2 DELTA P HI RUD LIM LT 2 DELTA P
LOWER RUDDER PRESSURE CONTROL SERVO VALVE
ADU 1 27 LO 38 HI
RUD LIM LO SOV HI 88 RUD LIM LO SOV LO 80
A HI RUD LIM LO SOV C LO RUD LIM LO SOV
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU) LOWER RUDDER SHUTOFF VALVE
Figure 27-69. FCECU Rudder Inputs and Outputs
27-110
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATION
NOTES
Normal System Operation Refer to Figure 27-69. FCECU Rudder Inputs and Outputs.
27 FLIGHT CONTROLS
When the FCECU is powered, it energizes open the upper and lower Rudder SOVs. The pressure control servo valves in the PCUs are used by the FCECU to control the pressure supplied to the actuators. The lower rudder servo valve gets inputs from the FCECU as follows: •• From Pins 3 and 11 The upper rudder servo valve gets inputs from the FCECU as follows: •• From Pins 3 and 11 As the airspeed increases, the FCECU decreases the hydraulic pressure providing Hinge Moment Limiting (HML). Airspeed inputs to the FCECU from the ADUs are at the connections that follow: •• ADU1 at Pins 27 and 38 • ADU2 at Pins 27 and 38.
FOR TRAINING PURPOSES ONLY
27-111
27 FLIGHT CONTROLS
27-112 POWERED
SPLR 2
PUSH
PUSH
OFF
OFF
OFF
VS
(E7)
P/J177 L
RUD SYS ISOL
ON
PUSH B
A
A
C
A
D
RUD 2 PUSH OFF
HDG
AP
U/F FWD FUSE
VERT STAB
NAV
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
S3
LEFT DC C/B PNL 24-61-00
NOSE UP
SHUTOFFS
J/P2 HI 45 LO 34 HI 55 CT 44 LO 33
P/J18 1 HI 2 LO 3 HI 4 CT 5 LO
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
DASH 8 Q400
2A
CONTROL
SPLR 1
PUSH
IAS
+28 V DC L MAIN BUS
FLIGHT
RUD 1
G F A
A
H3
H1 J2
J3
J1 K2
L2
3313P/J1 15
NC NO
L3
L1 3313J/P2 15
FORE RUDDER
K3
K1
RH CB CONS
MAINTENANCE TRAINING MANUAL
J/P177 J
CR6
AFT RUDDER
P/J1 32 LEFT RUDDER SHUT-OFF
RUD 1 PUSH OFF SW G
S3 S5
LOWER SPRING BUNGEE JAM SW
PUSH 16
VERTICAL STAB
P/J176 H F
B
A
A
C ON
G
#1 RUDDER HYD CAUTION LT
J/P1 63
F NC
16
NO
A
ACU 31-57-00
UPPER SPRING BUNGEE JAM SW
H1 J2
POWER CONTROL UNIT [PCU(2)]
FORE RUDDER TRAILING RUDDER
J1 K2 K1 L2 L1
HYDRAULIC PRESSURE PCU SUMMING LINK (2) PCU INPUT BUNGEE (2)
A
A
D
OFF H2
S4
H3
J/P2 RUDDER PRESSURE CAUTION LT 43 #2 RUDDER HYD CAUTION LT 63
OFF
J3
CAUTION AND WARNING PANEL (OH CONSOLE) 31-51-00
K3
L3
CR7
J/P176 K
P/J2 32 RIGHT RUDDER SHUT-OFF
RUD 2 PUSH OFF SW
GLARESHIELD PANEL (FLIGHT COMPARTMENT)
3312P/J5 6 #1 RUD HYD 25 RUD PRESSURE 28 #2 RUD HYD
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
Figure 27-70. Rudder Control System - Electrical Schematic
d4s272100_a_003.dg, pg, apr30/2007
FOR TRAINING PURPOSES ONLY
H2
VERTICAL STAB
RUDDER POSITION LINEAR VARIABLE DIFFERENTIAL TRANSFORMER (LVDT)
OFF
OFF
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-70. Rudder Control System - Electrical Schematic.
OPERATIONAL TEST OF THE RUDDER CONTROL SYSTEM
The pressure sensing transducers send delivery pressure information back to the FCECU. The FCECU knows what pressure it has commanded and, with the feedback from the transducers, knows the actual pressure being delivered from the pressure control servo valve.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
Rudder movement is monitored by a LVDT. The FCECU provides the excitation (pins 34 and 45) to the LVDT (pins 1 and 2). The LVDT supplies an electrical signal (from pins 3, 4 and 5), equivalent to the angular position of a flight control surface to the FCECU (pins 33, 44 and 55). The FCECU transmits the rudder position data to the IFC to display the position of the rudder on the PFSCI. Another signal is also sent to the FDR.
Obey all electrical safety precautions and warnings. •• Energize the electrical system •• Pressurize No.1 hydraulic system •• Lower the flaps to 50 •• Push the rudder pedals fully left and right •• Make sure the MFD PFCS indicator shows full travel •• Verify full travel by visual check of rudder positions •• Operate rudder pedal adjustment to the full forward and full aft positions and check full rudder travel •• De-pressurize No.1 hydraulic system •• Pressurize No.2 hydraulic system and repeat checks.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-113
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-114 POWERED
SPLR 2
PUSH
PUSH
OFF
OFF
OFF
VS
(E7) RUD SYS ISOL
L
PUSH B
RUD 2 PUSH OFF
HDG
AP
NAV
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
S3 ON
LEFT DC C/B PNL
NOSE UP
SHUTOFFS
C
HI LO HI CT LO
45 34 55 44 33
1 2 3 4 5
HI LO HI CT LO
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
G F A H2
H3
H1 J2
J3
J1 K2
FORE RUDDER
K3
K1 L2
L3
L1
J
CR6
AFT RUDDER
32 LOWER RUDDER SHUT-OFF
RUD 1 PUSH OFF SW
NC
15
NO
15
G
S1 S5
LOWER SPRING BUNGEE JAM SW
PUSH 16
B
H F
A
A
C ON
G
#1 RUDDER HYD CAUTION LT
63
F NC
A
16
NO
H1
ACU
UPPER SPRING BUNGEE JAM SW
J2
POWER CONTROL UNIT [PCU(2)]
J1
FORE RUDDER
K2
TRAILING RUDDER
K1 L2 L1
HYDRAULIC PRESSURE PCU SUMMING LINK (2)
A
A
D
OFF H2
S2
H3
OFF
RUDDER PRESSURE CAUTION LT 43 #2 RUDDER HYD CAUTION LT 63
J3
CAUTION AND WARNING PANEL
K3
L3
CR7
K
32 UPPER RUDDER SHUT-OFF
RUD 2 PUSH OFF SW
GLARESHIELD PANEL
6 #1 RUD HYD 25 RUD PRESSURE 28 #2 RUD HYD
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
PCU INPUT BUNGEE (2)
Figure 27-71. Lower Rudder Control Jam Indicated
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RUDDER POSITION LINEAR VARIABLE DIFFERENTIAL TRANSFORMER (LVDT)
D OFF
OFF
DASH 8 Q400
2A
CONTROL
SPLR 1
PUSH
IAS
+28 VDC L MAIN BUS
FLIGHT
RUD 1
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Abnormal Operation
NOTES
Refer to Figure 27-71. Lower Rudder Control Jam Indicated.
Rudder Jam
FOR TRAINING PURPOSES ONLY
27 FLIGHT CONTROLS
A jam of the PCU servo valve causes the input bungee to change length. This is detected by the motion detector and closes switch S3 or S4 providing a ground to the RUD1 or RUD2 switchlight.
27-115
27 FLIGHT CONTROLS
27-116 POWERED RUD 1
OFF
IAS
VS
FLIGHT SPLR 1
CONTROL
SHUTOFFS
SPLR 2
RUD 2
PUSH
PUSH
PUSH
OFF
OFF
OFF
NOSE UP
HDG
NAV
2A
RUD SYS ISOL
L
PUSH
ON
LEFT DC C/B PNL
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
S3 B
A
A
C
A
D
HI LO HI CT LO
45 34 55 44 33
1 2 3 4 5
HI LO HI CT LO
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
G F A
RUDDER POSITION LINEAR VARIABLE DIFFERENTIAL TRANSFORMER (LVDT)
OFF H2
H3
H1 J2
J3
J1 K2
FORE RUDDER
K3
K1 L2
L3
L1
J
CR6
AFT RUDDER
32 LOWER RUDDER SHUT-OFF
RUD 1 PUSH OFF SW
NC
15
NO
15
G
S1 S5
LOWER SPRING BUNGEE JAM SW
PUSH 16
B
H F
A
A
C ON
G
#1 RUDDER HYD CAUTION LT
63
F NC
A
16
NO
ACU
UPPER SPRING BUNGEE JAM SW
H1 J2
POWER CONTROL UNIT [PCU(2)]
J1
FORE RUDDER
K2
TRAILING RUDDER
K1 L2 L1
HYDRAULIC PRESSURE PCU SUMMING LINK (2)
A
A
D
OFF H2
S2
H3
OFF
RUDDER PRESSURE CAUTION LT 43 #2 RUDDER HYD CAUTION LT 63
J3
CAUTION AND WARNING PANEL
K3
L3
CR7
K
32 UPPER RUDDER SHUT-OFF
RUD 2 PUSH OFF SW
GLARESHIELD PANEL
6 #1 RUD HYD 25 RUD PRESSURE 28 #2 RUD HYD
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
PCU INPUT BUNGEE (2)
Figure 27-72. Rudder 1 PUSH OFF Switch Pushed
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
A OFF
DASH 8 Q400
(E7) +28 VDC L MAIN BUS
MAINTENANCE TRAINING MANUAL
Lower Rudder PCU Jam Operation
ADU Failure
Refer to Figure 27-72. Rudder 1 PUSH OFF Switch Pushed.
Should the FCECU detect that an ADU has failed, or that there is a difference of greater than 17 knots between the two ADUs , then the FCECU will determine the data is invalid.
The Pilot pushes the RUD1 switchlight to de-energize the shutoff valve and remove the hydraulics from the failed PCU. The No.1 RUD HYD caution light illuminates.
If airspeed is invalid the rudder hydraulic pressure will default to 700 psi.
The HML will double the rudder pressure to the remaining PCU.
Hydraulic Failure With failure of either No.1 or No.2 hydraulic systems, the FCECU de-energizes the rudder, SOV, causing it to close, and sets the pressure control valve of the failed system to zero pressure. The failure will cause a No.1 RUD HYD or a No.2 RUD HYD caution light to illuminate. At the same time, the FCECU increases the pressure to the active PCU to compensate for the loss. The rudder control system will continue to operate if one PCU fails. Failure of both rudder hydraulic systems will cause the three caution lights No.1 RUD HYD, No.2 RUD HYD and RUD CTRL to illuminate. The aircraft will fly without rudder control and the rudder compensator will prevent the rudder from fluttering.
FCECU Failure A failure of a single FCECU channel will de-energize the related rudder shut-off valve and the other system will continue to operate at twice the normal pressure. The pilot indication will be the associated No.1 RUD HYD or a No.2 RUD HYD caution light illuminated. A failure of both FCECU channels closes both rudder SOVs and rudder control is lost. The following caution lights will illuminate: •• No.1 RUD HYD •• No.2 RUD HYD • RUD CTRL FOR TRAINING PURPOSES ONLY
27-117
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-73. RUD CTRL Caution Light. If airspeed and flap position are invalid, the hydraulic pressure will default to 1225 psi. The RUD CTRL caution light illuminates if: 27 FLIGHT CONTROLS
•• FCECU detects a difference of 17 knots (37.06 km/h) or more between the Airspeed 1 and Airspeed 2 from the air data units •• F C E C U l o s e s i t s a b i l i t y t o l i m i t hydraulic pressure • Both hydraulic systems fail.
OVERHEAD CONSOLE
Rudder Control
ROLL SPLR INBD GND
#1 STALL SYST FAIL #2 STALL SYST FAIL
ROLL SPLR INBD HYD
#2 HYD FLUID HOT
FLAP DRIVE
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING MAIN BAT HOT
Figure 27-73. RUD CTRL Caution Light
27-118
FOR TRAINING PURPOSES ONLY
FUELING ON
MAINTENANCE TRAINING MANUAL
27-22-00 RUDDER FEEL AND SUMMING INTRODUCTION The rudder feel and summing unit transmits rudder system artificial feel to the rudder pedals and biases the complete rudder system during rudder trimming or yaw damping. The rudder system is a powered flight control, the unit is used to prevent the pilot from overcontrolling the aircraft in flight.
GENERAL Refer to Figure 27-74. Rudder Feel and Summing System Block Diagram. Rudder pedal feel is artificially produced by feel springs on the rudder feel and summing unit. The rudder feel and summing unit mechanically transmits rudder system commands to the rudder PCUs. The rudder feel and summing system has the following components: •• Trim actuator •• Rudder feel and summing unit •• Summing yaw damper actuator •• Rudder trim switch • Rudder trim indicator.
RUDDER TRIM SWITCH & INDICATOR
TRIM ACTUATOR
RUDDER PEDALS (PILOT & CO-PILOT)
RUDDER FEEL & SUMMING UNIT
RUDDER
SUMMING -YAW DAMPER ACTUATOR FGM 1 & FGM 2 fst11a01.cgm
Figure 27-74. Rudder Feel and Summing System Block Diagram
FOR TRAINING PURPOSES ONLY
27-119
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-120 POWER CONTROL UNIT [PCU(2)]
TRIM ACTUATOR
CO-PILOT'S PEDALS
FORE RUDDER TRAILING RUDDER +36¡
+18¡
0¡ -36¡
-18¡
HYDRAULIC PRESSURE
PILOT STATURE ADJUSTMENT
PCU SUMMING LINK (2) RUDDER AFT QUADRANT
YAW DAMPER SUMMING ARM
PCU INPUT BUNGEE (2)
RUDDER MIXER QUADRANT
RUDDER FORWARD QUADRANTS
NOTE
FORCE APPLIED PILOT'S PEDALS
1
Hydraulic pressure reduces with speed to limit Hinge Moment.
2
Trailing Rudder moves twice as far as the Fore Rudder.
fs277a01.cgm
Figure 27-75. Rudder Control System Synoptic
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
YAW DAMPER ACTUATOR
DASH 8 Q400
FEEL SPRING (DUAL RATE)
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to: • Figure 27-75. R udder Control System Synoptic. •• Figure 27-76. R udder Trim Switch and Indicator. 27 FLIGHT CONTROLS
The rudder trim switch is located on the center console. Turning the RUDDER trim switch fully to the left (L) or right (R) gives trim at a high rate. When the switch is turned to the first graduation line, a slower trim rate is given. The trim actuator can move the rudder surface a maximum of 10°. The rudder trimmed position is shown on the RUDDER trim indicator. Rudder trim indication is transmitted by the trim actuator’s integral LVDT. The LVDT signal is also transmitted to the IFC FDR. If the LVDT fails, the trim actuator stays functional but no trim position is shown on the RUDDER trim indicator.
AIL I
TRIM
TRIM
Rudder Trim Indicator
CENTER CONSOLE
AILERON
Rudder Trim Switch
FW
D
Figure 27-76. Rudder Trim Switch and Indicator
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-121
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Trim Actuator Refer to Figure 27-77. Rudder Trim Actuator.
27 FLIGHT CONTROLS
The trim actuator transmits linear movement to the rudder feel and summing unit to bias the rudder control system for yaw deviations. The trim actuator is attached to the mid-spar of the vertical stabilizer and connected at the rear with two trim arms, that form part of the summing unit. The trim actuator has a DC motor which extends and retracts the actuator. If the actuator extends to its limit, the extend limit switch disconnects power to the motor. The trimming system is powered from the left essential bus, through two circuit breakers, RUD TRIM ACT F7 for the trim actuator and RUD TRIM IND G7 for the RUDDER trim indicator.
OPERATIONAL TEST OF THE RUDDER TRIM SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Energize the external DC power system •• Pressurize No.1 and No.2 hydraulic systems •• Move the rudder fully left and right 3 times stopping in the neutral position •• Turn the rudder trim switch fully left and right •• Make sure trim indicator shows full deflections and neutral when the switch is neutral • Remove hydraulic power and DC electrical power.
FWD
RUDDER CONTROLS - VERTICAL STABILIZER
D
FW
fs252a01.cgm
Figure 27-77. Rudder Trim Actuator
27-122
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Rudder Feel and Summing Unit Refer to Figure 27-78. Rudder Feel and Summing Unit. The rudder feel and summing unit gives artificial feel to the pilots when operating the rudder pedals. The rudder feel and summing unit is installed in series with the rudder control system.
The springs are attached to the feel unit arms at the actuator end, rotation of the shaft actuating arms extends the spring in the direction of rotation while the opposite spring is unaffected. This gives the pilot artificial feel of loading on the rudder pedals. During trimming, the feel springs and trim arms move together.
The rudder feel and summing unit has two feel springs attached to a summing bar that is connected to the rudder hydraulic PCUs.
FWD
RUDDER CONTROLS - VERTICAL STABILIZER 1
2 3
FW
D
4
LEGEND 1. Rudder Trim Actuator. 2. Trim Arms. 3. Feel Springs. 8 4. Summing Bar. 5. PCU Bungee Attachment Points. 6. Quadrant Push Rod Attachment Point. 7. Yaw Damper Attachment Point. 8. Mounting Frame.
5
7 6 ft208a01.cgm
Figure 27-78. Rudder Feel and Summing Unit
FOR TRAINING PURPOSES ONLY
27-123
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Summing-Yaw Damper Actuator Refer to Figure 27-79. Yaw Damper. The summing-yaw damper actuator transmits small inputs to the Rudder Feel Summing Unit (RFSU) to compensate for yaw oscillations in flight. 27 FLIGHT CONTROLS
The yaw damper is a linear servo actuator installed between the rudder aft quadrant and the summing arm. The yaw damper supplies small rudder deflections to compensate for yaw oscillations in flight. Yaw damper authority is 4.5° either side of center. The yaw damper has its own summing arm, which mechanically transmits any yaw damper inputs on to the rudder feel and summing unit.
FW
D
fs251a01.cgm
RUDDER CONTROL SYSTEM VERTICAL STABILIZER
Figure 27-79. Yaw Damper
27-124
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-125
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
RUDDER TRIM ROTARY SWITCH (SLOW TRIM) T
RUDDER TRIM INDICATOR RUDDER TRIM IND
C
27 FLIGHT CONTROLS
PNL LTS H lV (5V LTC) C lV II II
RUDDER TRIM ACTUATOR
T
4B 3F
LT SYS (5V DC)
SHLD
B
RUDDER TRIM ACTUATOR 1
2 3
11 RUDDER LEFT
C
28 VDC LEFT ESS R4 R3 15.0 10.0
A 4
R2 15.0
R1 10.0
172 50 EXT
E F D
T
A B D E
IFC1
SHLD
28 VDC LEFT ESS
T
SHLD F G H
HI (EXT 15 L) Vl WIPER Vl LO Vl (RET 15 R)
AVIONICS RACK
1750 50 RET HALL LIMIT SWITCH EXT
CASE
A
HALL LIMIT SWITCH RET
MOTOR CONTROLLER ELECTRONICS
M
D2
5 D1
6 7
IV 8
B
9
11 RUDDER RIGHT
10
RUDDER TRIM ROTARY SWITCH (RAPID TRIM)
B
RUDDER TRIM ACTUATOR 1
28 VDC LEFT ESS R4 R3 15.0 10.0
2
A 11 RUDDER LEFT
3 4
R1 10.0
R2 15.0
C A
M
D2
D1 IV 8
B
MOTOR CONTROLLER ELECTRONICS
5 6 7
11 RUDDER RIGHT
CASE
28 Vdc 5 Vdc
9
Ground
10
fst02a02a.cgm
Figure 27-80. Rudder Trim Switch/Indicator Schematic
27-126
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
RUDDER TRIM OPERATION
NOTES
Refer to Figure 27-80. Rudder Trim Switch/ Indicator Schematic.
Rudder Trimming 27 FLIGHT CONTROLS
When the rudder trim switch is selected fully to ‘L’ for rapid trim, power is directed by the rudder trim switch from the 28 VDC left essential bus through a normally closed extend limit switch to provide power to drive the actuator in an extend direction rapidly. If the actuator is extended to its limit, the extend limit switch is opened to disconnect power to the motor and connect the motor to a common ground. When the rudder trim switch is selected to the mid graduation L line for slow trim, reduced voltage is directed to the rudder trim actuator through voltage reducing resistors R3 and R4. Extension of the actuator resets the quadrant to bias the complete rudder system to the left. Actuator movement is transmitted through feel unit arms and the link arms to move the feel and trim unit input to the newly trimmed neutral position. As the rudder trim actuator extends the rudder trim LVDT extends and provides a signal to move the rudder trim indicator pointer towards its ‘L’ position as follows: The LVDT information is transmitted to the indicator and to the FDR through the IFC1. When rudder trim switch is selected to ‘R’, operation is similar but in an opposite direction. If power to the indicator is removed, the indicator pointer will go off the scale.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-127
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-23-00 RUDDER SURFACES
SYSTEM DESCRIPTION Rudder surfaces extend almost the entire length of the trailing edge of the vertical stabilizer. The rudders are attached to the aircraft through a series of hinges and safety hinges.
GENERAL Refer to Figure 27-81. Rudder Empennage. 27 FLIGHT CONTROLS
The rudder is a primary flight control surface that is attached to the rear spar of the vertical stabilizer. The rudder is divided into two sections: •• Fore rudder
Each rudder rotates on sealed bearings. The fore rudder is attached to the rear spar of the vertical stabilizer and is actuated by two PCUs. The aft rudder is attached to the fore rudder by hinges and is actuated by push-rods so that the aft rudder deflects twice as far as the fore rudder. Unrestricted rudder travel equals 18° left/right movement as measured at the fore rudder.
• Trailing rudder.
1
2 3
Upper Dual Load Path
4
1
3
2
LEGEND 1. Vertical Stabilizer. 2. Fore Rudder. 3. Trailing Rudder. 4. Rear Fuselage Section.
Lower Dual Load Path
fs223a01.cgm
Figure 27-81. Rudder Empennage
27-128
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
27-31-00 ELEVATOR SYSTEM
The elevator system has the following components: •• Control columns
INTRODUCTION
•• Handwheels
The elevator surfaces move in proportion to the amount of control column movement.
•• Left forward quadrant
GENERAL
•• Elevator tension regulators
•• Right forward quadrant •• Left aft quadrant
Refer to Figure 27-82. Elevator Control System.
•• Right aft quadrant
The left and right elevators are installed on the trailing edge of the left and right horizontal stabilizers, respectively.
•• Elevator power control unit/actuators •• Compensator •• Torque tubes
The elevators are positioned by commands from either the pilot control system or the AFCS. Trim control and surface position indication is also supplied for each elevator.
•• Centering device •• Overload bungees •• Elevator position LVDT.
The PCUs move the elevators using hydraulic system pressure. 3
LEGEND 1. Elevator Autopilot Servo. 2. Elevator PCU’s. 3. Elevators. 4. Pitch Feel and Trim Unit. 5. Control Cables. 6. Stick Pusher. 7. Elevator Forward Quadrant. 8. Pitch Disconnect Handle. 9. Control Column.
2
1 2 4
5
6
9 8
7
Figure 27-82. Elevator Control System FOR TRAINING PURPOSES ONLY
27-129
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-130 PCU INPUT BUNGEE (17 LBS)
TORQUE TUBE CENTRING SPRING
H1 H 2
00
H3
20
STANDBY PCU
RIGHT ELEVATOR SURFACE
RIGHT FEEL UNIT PITCH DISCONNECT
PUSHER QUADRANT
PILOT CONTROL COLUMN
TENSION REGULATOR FORWARD QUADRANT
AFT QUADRANT
0
TRIM ACTUATOR (DUAL)
PITCH FEEL ACTUATORS
BEAM SPRING
AUTOPILOT QUADRANT
LEFT FEEL UNIT -30° OVERLOAD BUNGEE
STICK PUSHER CAPSTAN
H3 0° H2
AUTOPILOT SERVO
20°
H1 TORQUE TUBE CENTRING SPRING fs549a01.cgm
Figure 27-83. Elevator Control System Synoptic
PCU INPUT BUNGEE (17 LBS)
ELEVATOR SURFACE
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
OVERLOAD BUNGEE (75 LBS)
PITCH DISCONNECT HANDLE
0
DASH 8 Q400
CO-PILOT CONTROL COLUMN
-30
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION Refer to Figure 27-83. Elevator Control System Synoptic. Fore and aft movement of the pilot and co-pilot control columns is transmitted simultaneously to the pilot and co-pilot elevator control circuits. The two elevator control circuits are routed independently on the left and right side of the aircraft. This independent routing prevents loss of manual pitch control in the event of an engine rotor burst.
An elevator PCU compensator installed in the return line of the No.3 hydraulic system gives hydraulic gust lock protection. The compensator also gives elevator flutter suppression during flight.
27 FLIGHT CONTROLS
DASH 8 Q400
The pilot and co-pilot control columns are connected to each other by the pitch disconnect system (refer to 27-38-00). Control column input is transferred by pushrods to the left/right forward elevator quadrants below the flight compartment floor. The two forward elevator quadrants also act as cable tension regulators. The left forward (pilot’s) elevator quadrant has an input from the stick pusher system (refer to 27-33-00). The elevator cables are routed from the forward elevator quadrants aft below the flight compartment and cabin floor to the rear fuselage. The cables terminate at the two aft (left and right) elevator quadrants in the vertical stabilizer. Elevator control cables pass through seals in the rear pressure dome to prevent loss of cabin pressure. The aft quadrants transfer the pitch control movement through the overload bungees to the PCU input torque tubes. The left aft elevator quadrant has input from the AFCS servo actuator. The torque tubes transfer the pitch control movement through the PCU input bungees to the elevator PCU which are attached to the elevator control surfaces. There are three identical elevator PCUs connected to each elevator surface.
FOR TRAINING PURPOSES ONLY
27-131
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
Pitch Trim Switch
Hand Wheel
FW
D
Control Column
NOTE Co-pilot Control Column Shown. Pilot Opposite. fs625a01.cgm
Figure 27-84. Elevator Control Column
27-132
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Control Columns Refer to Figure 27-84. Elevator Control Column.
27 FLIGHT CONTROLS
Each control column provides the operational control of the elevators. The pilot control column operates the left elevator through the left elevator circuit. The co-pilot’s control column operates the right elevator through the right elevator circuit. Each column is attached to a lateral torque tube with bolts, which is installed in bearings below the flight compartment floor. The torque tube has a clutch, which can be disconnected in the event of a jam in either elevator control circuit to allow for individual control column operation of the elevators. A stick shaker for the stall warning system is attached to the forward face of each control column (refer to 27-33-00).
Handwheels The handwheels provide the physical input to the control columns. A hand operated control wheel is pivot-mounted to the top of each control column. A pitch trim split switch is located in the center of the outboard handgrip of each control handwheel.
FOR TRAINING PURPOSES ONLY
27-133
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
LEGEND 1. Mounting Bracket. 2. Quadrant. 3. Push Rod. 4. Secondary Stops. 5. Rig Pin Hole. 6. Tension Indicator.
1 2 6 HN C
3
4
D
INB FW
D
5 ft113a01.cgm
Figure 27-85. Elevator Right Forward Quadrant
27-134
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Left Forward Quadrant
The secondary stops provide a backup travel stop in the event of malfunction of the elevator system. The stick pusher quadrant is attached to the left forward quadrant. A rig pin point is located in the quadrant.
Refer to: • Figure 27-85. E levator Right Forward Quadrant. •• Figure 27-86. E levator Left Forward Quadrant.
The right forward quadrant is identical but without a pusher quadrant.
The left forward quadrant transmits the pilots control column inputs to the left aft quadrant.
The attached H-N-C scale and pointer is used to rig the tension regulator in accordance with temperature related graphs.
The left forward quadrant is located below the flight compartment floor. There are springs installed in the left forward quadrant to supply tension regulation of the cable system. There are fixed secondary stops integral with the tension regulator.
3
2
1
4
5
D
FW
8
6 7
LEGEND 1. 2. 3. 4.
Push Rod. LH Cable Tension Regulator (Quadrant). Stick Pusher Quadrant. Centering Spring.
5. 6. 7. 8.
Mounting Bracket. LH Tension Regulator Secondary Stops. Rig Pin Hole. Stick Pusher Quadrant Stop.
ft189a01.cgm
Figure 27-86. Elevator Left Forward Quadrant
FOR TRAINING PURPOSES ONLY
27-135
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Aft Quadrants Refer to Figure 27-87. Elevator Aft Quadrants. The left aft quadrant transmits pilot pitch commands to the left elevator PCU.
The elevator autopilot quadrant is directly attached to the left aft quadrant with input from the autopilot servo. A rig pin point is located in both quadrants. The right aft quadrant has the primary stops.
27 FLIGHT CONTROLS
The right aft quadrant transmits pilot pitch commands to the right elevator PCU. The aft quadrants are located in the vertical stabilizer. The quadrants are made of aluminum and rotate on a sealed bearing. They transmit the pilot’s pitch control commands from the forward quadrants through a series of pushrods, torque tubes and linkages to the six elevator PCUs. ELEVATOR CONTROL SYSTEM VERTICAL STABILIZER D
FW
2
3
LEGEND 1. Quadrant Primary Stop. 2. Left Autopilot Quadrant. 3. Elevator Quadrant. 4. Primary Stops Elevator.
4
1
ft178a01.cgm
Figure 27-87. Elevator Aft Quadrants
27-136
FOR TRAINING PURPOSES ONLY
D
FW
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Elevator-Power Control Units (PCU) Refer to Figure 27-88. Elevator Power Control Unit.
27 FLIGHT CONTROLS
The elevator PCU transmit system inputs to move the elevator surfaces. The elevator control system has six identical elevator PCUs; three attached to each elevator surface and the horizontal stabilizer rear spar. The PCU is a hydro-mechanical servo actuator. They receive input commands from the PCU input bungees and the PCU input torque tubes. The PCU actuator body is attached to the elevator control surface.
FW
D
ELEVATOR CONTROL SYSTEM HORIZONTAL STABILIZER
2
LEGEND 1. Elevator Attachment. 2. Horizontal Rear Spar Attachment. 3. MCV.
D
FW
NOTE Left Elevator Shown. Right Elevator Similar.
1
3
Three PCUs Per Elevator. fs396a01.cgm
Figure 27-88. Elevator Power Control Unit
FOR TRAINING PURPOSES ONLY
27-137
27 FLIGHT CONTROLS
27-138 INLET CHECK VALVE
PRESSURE PORT AND INLET SCREEN
DASH 8 Q400
RETURN PORT
ANTICAVITATION CHECK VALVE
ANTICAVITATION CHECK VALVE
LOAD LIMIT RELIEF VALVE
LOAD LIMIT RELIEF VALVE
ACTUATOR ASSEMBLY
ACTUATOR ASSEMBLY
fss99a01a.cgm
Figure 27-89. Elevator PCU Schematic
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
MAIN CONTROL VALVE
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Refer to Figure 27-89. Elevator PCU Schematic.
Elevator PCU Each PCU is composed of two sub assemblies: 27 FLIGHT CONTROLS
•• Actuator assembly with a balanced area cylinder and a translating body • Integral hydraulic manifold assembly. The Integral hydraulic manifold assembly contains the following: •• Pressure port •• Inlet check valve •• MCV •• Anti-cavitation check valves (2) • Load limit relief valves (2). The pressure port supplies system hydraulic pressure to the inlet check valve and then to the MCV. Pitch input from the torque tube causes the MCV to port up or down pressure to the actuator to command elevator position. The MCV moves the actuator balanced area cylinder and then PCU body moves to null the input. The two anti-cavitation check valves prevent actuator cavitation. The anti-cavitation valves crack at 2-8 psid to allow the serviceable PCU to overcome the jammed unit. The PCU actuator balance area cylinder fluid is then circulated through the anti-cavitation valves to the other side of the cylinder. The two load limit relief valves limit the PCU pressure to 3600 psid.
FOR TRAINING PURPOSES ONLY
27-139
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Compensator Refer to Figure 27-90. Compensator. The elevator compensator keeps hydraulic fluid 50 psi (344.7 KPa) pressure in both inboard PCUs, to give gust damping on the ground. 27 FLIGHT CONTROLS
The compensator is installed in the return line of the No.3 hydraulic system on the front spar of the vertical stabilizer. This limits PCU movement to prevent structural damage during windy conditions. The compensator also maintains a positive pressure to supply flutter suppression when the PCUs are depressurized in flight. It compensates for changes in fluid volume due to thermal expansion and contraction.
INL
ET
FW
D
fs360a01.cgm
Figure 27-90. Compensator
27-140
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Torque Tubes
Centering Device
Refer to Figure 27-91. Centering Device.
Refer to Figure 27-91. Centering Device.
There are two PCU input torque tubes. One is installed in the pilot elevator control circuit in the left horizontal stabilizer. The other is installed in the co-pilot elevator control circuit in the right horizontal stabilizer. The torque tubes are mass balanced and an attachment is provided for a centering spring.
The centering spring assists the springs of the Pitch Feel and Trim Unit to return the torque tube to neutral.
If the elevator circuit up-stream from the torque tube is disconnected from the centering spring, a balancing mass will prevent the torque tube from rotating, thus preventing elevator surface runaway. Attachment is provided for three PCU input bungees and an LVDT on each torque tube. A rig pin point is located in the outboard bellcrank of each PCU input torque tube.
A centering spring is installed in each PCU input torque tube. When the PCU input torque tube rotates, a load is placed on the centering spring causing the spring to increase tension. After the pilot releases the input command, the load exerted by the centering spring causes the control column to return to the neutral position.
ELEVATOR CONTROL SYSTEM HORIZONTAL STABILIZER 7
FWD
5
6
7
4
LEGEND 1. Adjusting Plate. 2. Pin Drive. 3. Torque Shaft Support Pin. 4. Spring. 5. Cover. 6. Retaining Ring. 7. Torque Tube.
3 2
1
FWD
ft409a01.cgm
NOTE Left Component Shown. Right Component Similar.
Figure 27-91. Centering Device
FOR TRAINING PURPOSES ONLY
27-141
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Overload Bungees Refer to Figure 27-92. Overload Bungee. The overload bungees contract or expand to compensate for excessive deflections. There is one overload bungee for each elevator.
The breakout force of the bungee is 75 ± 5 lbs. The unaffected elevator will then continue to move. This prevents structural damage to the elevators, cable circuits and the surrounding structure.
D
ELEVATOR CONTROL SYSTEM HORIZONTAL STABILIZER
FW
27 FLIGHT CONTROLS
The overload bungee is located between the aft quadrant and its torque tube. The other six input bungees are installed between the two torque tubes and the six elevator PCUs.
The overload bungee between the aft quadrants and its related torque tube function as a pushrod until there is a linkage jam downstream of the bungee.
NOTE D
TB
OU
Left Component Shown. Right Component Similar. fs392a01.cgm
Figure 27-92. Overload Bungee
27-142
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Overload Bungees (PCU INPUT)
Elevator Position LVDT
Refer to Figure 27-93. Elevator Position LVDT and PCU Input Bungee.
Refer to Figure 27-93. Elevator Position LVDT and PCU Input Bungee.
The PCU input overload bungees contract or expand to compensate for a PCU main control valve jam. There are three input bungees for each elevator.
The LVDT is a single channel, single sensor LVDT. It senses the elevator surface position and transmits the position data to the FCECU to IFC, and to the PFCSI on MFD1. There are two LVDTs located in the horizontal stabilizer; one attached to each elevator surface.
Three PCU input bungees are installed in series between the three elevator PCU and the PCU input torque tubes. They function as a pushrod until there is a PCU main control valve jam downstream of the bungee. The breakout force of the PCU input bungee is 17 ± 1.5 lbs. The unaffected elevator PCU continue to control the elevator surface.
FW
D
ELEVATOR CONTROL SYSTEM HORIZONTAL STABILIZER
PCU input bungee
Elevator position LVDT
FW
D
Figure 27-93. Elevator Position LVDT and PCU Input Bungee
FOR TRAINING PURPOSES ONLY
27-143
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OVERHEAD CONSOLE
MAIN INSTRUMENT PANEL
27 FLIGHT CONTROLS
WX OFF
FMS1 076 00
057
HDG 073°
E
3
160
VIE
CAUTION PANEL
PITCH TRIM
VCF
YSO
00 ---
TAS 20 GS 0
YCF
80
TCAS STBY
ADF1 DME1 H 92.1 NM
ADF2 DME2 92.1 NM
EMER LTS DISARMED CABIN PRESS
I
I
2
LEGEND
1
1. Left Elevator Position Indication. 2. Right Elevator Position Indication.
Figure 27-94. Elevator Position on MFD
27-144
35.0 NM --:--
FOR TRAINING PURPOSES ONLY
2
MAINTENANCE TRAINING MANUAL
Controls and Indications Refer to Figure 27-94. Elevator Position on MFD. Elevator position is normally shown on the pilot Multi-Function Display (MFD1). If a disagreement occurs between elevator surface position indications, the ELEVATOR ASYMMETRY caution light illuminates on the Caution and Warning panel. For the caution light to illuminate, the difference in elevator position must be greater than: •• 4 ± 1.6° for airspeed > 215 kts. • 6 ± 1.6° for airspeed < 215 kts.
ASYMMETRY CHECK OF THE ELEVATORS The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
•• Install an inclinometer on the top surface of the left elevator at a right angle to the trailing edge and adjust the inclinometer to a 0° indication •• Hold the pilot and co-pilot control column in the elevator neutral position. In the flight compartment, pull and turn the PITCH disconnect handle •• In the flight compartment, slowly pull the pilot’s control column aft until the ELEVATOR ASYMMETRY caution light comes on. Make sure that the indication is 6.0° ±1.0° •• Repeat the procedure for the right elevator •• Adjust the airspeed test set to 220 kts and repeat the procedure for the left and right elevator •• Make sure that the indication is 4.5° ±1.0°.
•• Connect the airspeed test set to the left and right primary pitot-static probes. Adjust the airspeed test set to 60 kts. •• Install the four deactivation targets on the proximity sensors on the main landing gear to simulate a weight-offwheels condition •• In the flight compartment, set the configuration that follows: °° Set the FLAPS selector to the 0° position °° Set the FLIGHT/TAXI switch to the FLIGHT position °° Set the No.1 and No.2 POWER lever to a position more than 12° above FLIGHT IDLE
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-145
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-146 FMS #2
HI LO
GPDB2 A429
DASH 8 Q400
4 5
TMCU #2 (G4) 3A 28 VDC L ESS BUS
PITCH TRIM ACT 1
G5 A1
D3
D1
C4 B1
7 6
FCS ECU 1
47 HI 24 LO
67 +28 VDC RTN
GPDB2 A429
ECS
RELAY JUNCTION BOX NO. 1
ELEVATOR
35 CHASSIS GND ADU #1
MAINT CLEAR NVM
27 38
74
41
PITCH TRIM LT POS'N
HI LO
PITCH TRIM LT EXTEND PITCH TRIM LT RETRACT PITCH TRIM LT DISCRETE REF PITCH TRIM LT ENABLE PITCH TRIM LT SPEED MAINT CLEAR NVM
1 9 17 18 8 10 2
4 13 10 2 8 3 1
HI PITCH TRIM LT POS'N LO PITCH TRIM LT EXTEND PITCH TRIM LT RETRACT PITCH TRIM LT DISCRETE REF PITCH TRIM LT ENABLE PITCH TRIM LT SPEED
203 HI 204 LO
FCS ECU R A429 (IN)
31-41 A1 IOP #1
LEFT PITCH TRIM ACTUATOR
AHARS
MAINTENANCE PANEL
ADU #2
27 38
FCS ECU RA429 (OUT) GRDB2 A429 (IN) FCS ECU A429
31 41 30 21 22
TB-B/D2 TB-B/B1 TB-B/D1 TB-A/B2 TB-B/A2 FMS #1
ELEVATOR TRIM CONT SWITCH PILOT'S CONTROL HANDWHEEL
PILOT PILOT PILOT PILOT PILOT
48 HI 49 LO
TRIM TRIM TRIM TRIM TRIM
HI LO HI LO
47 37 48 49
HI LO
47 37
331 HI 332 LO
31-41 A2 IOP #2
RETURN NOSE UP 1 NOSE DOWN 1 NOSE UP 2 NOSE DOWN 2
233 HI 232 LO
PITCH FEEL LT EXTEND 19 PITCH FEEL LT RETRACT 20 PITCH FEEL LT DISCRETE REF 28 PITCH FEEL LT ENABLE 40 PITCH FEEL LT SPEED 50
10 2 8 3 1
PITCH PITCH PITCH PITCH PITCH
HI 29 LO 39
4 13
HI LO
7 6
3A
FEEL FEEL FEEL FEEL FEEL
LT LT LT LT LT
EXTEND RETRACT DISCRETE REF ENABLE SPEED
LEFT PITCH FEEL ACTUATOR
(F4) 3A
7 5
PITCH FEEL LT POS'N
+28 VDC +28 VDC RTN
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU) PITCH FEEL ACT 1
FCS ECU L A429 (IN)
31-41 A1 IOP #1
GENERAL PURPOSE DATA BUS IFC RECV'D
PITCH FEEL LT POS'N
(H4)
GPDB2 A429 (OUT)
PITCH TRIM IND
LEFT DC CBP
Figure 27-95. Pitch Feel and Trim
ELEVATOR
HI LO
FCS ECU L A429
10 +28 VDC 12 +28 VDC RTN
PITCH TRIM INDICATOR
# 1 & 2
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
56 +28 VDC
LEFT DC CBP
28 VDC L ESS BUS
+28 VDC RTN
2-K1
(M3) 5A
D2
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-95. Pitch Feel and Trim. The FCECU uses airspeed information from the ADUs and acceleration from the AHARS to control pitch feel, by controlling the Pitch Feel Actuators. As airspeed and acceleration increase, the FCECU commands the two independent feel actuators to extend. This action, through the levers in the PFTU, increases the force required to rotate the aft quadrants. This force is felt back through the cable system, to the front quadrants and the control columns increasing the feel to the pilots. As airspeed and acceleration decrease, feel is decreased, by reversing the process. Rotating the torque tubes transfers the pitch control movement through the PCU input bungees to the elevator PCUs. Extension or retraction of the PCUs moves the elevator surfaces. The outboard PCU is powered by No.1 hydraulic system, the center PCU by No.2 hydraulic system, and the inboard PCU by the No.3 hydraulic system, when necessary. As the PCUs extend or retract, it is the body of the PCU that moves, to displace the elevators, thereby returning the servo valve towards the null position as the PCU moves.
OPERATIONAL TEST OF THE ELEVATOR CONTROL SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Move the control column to the neutral position. •• Make sure the PFCS indicator shows both elevators in neutral.
Revision 0.4
•• Move the control column fully forward and aft, 3 times, making sure the elevators move smoothly to full deflections. •• Make sure full deflections are shown on the PFCS indicator. • Move control column to neutral position.
ELEVATOR DROOP RATE CHECK The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• The procedure that follows is to check the droop rate of the elevator and to make sure that the elevator Power Control Unit (PCU) internal leakage is within the flutter requirements, even though the droop rate exceeds the threshold when all the systems are depressurized. • This task must be done in the hanger or outside with zero wind conditions.
NOTE Use the Standby Power Unit (SPU) and Power Transfer Unit (PTU) first, and then STNDBY No.3 by itself to have the systems pressurized. •• Set the elevators to a neutral position and shut off the No.1, No.2 and No.3 hydraulic system •• On the (CDS) proceed to page 3 of the FCECU diagnostic page. •• Record the LH elevator position and RH elevator position as “LH No.1 and RH No.1”. Record the time as “t1”. •• Wait for 10 minutes and repeat step 3. •• Record the LH elevator position and RH elevator position as “LH No.2 and RH No.2”.
FOR TRAINING PURPOSES ONLY
27-147
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• Record the time as “t1+10”.
Refer to:
•• Subtract the recorded values and divide by 10 to calculate the droop rate.
•• Figure 27-96. Elevator Position Feedback. • Figure 27-97. Elevator Caution Lights.
•• If the droop rate exceeds 0.12°/minute proceed to TASK 27-31-36-720-801
As the elevator moves, the position is shown on the MFD1 by means of LVDTs attached to each elevator surface.
27 FLIGHT CONTROLS
ELEVATOR HI POSITION EXC LO
76 66
1 HI 2 LO
ELEVATOR POSITION EXC
ELEVATOR POSITION LEFT
85 75 65
3 HI 4 CT 5 LO
ELEVATOR POSITION LEFT
HI CT LO
LEFT ELEVATOR
LEFT ELEVATOR LINEAR VARIABLE DIFFERENTIAL TRANSFORMER (LVDT) +28 VDC L ESS BUS
(M3) 5A
FCS ECU 1
56 67
+28 VDC DC RTN
35
CHASSIS GND NOSE UP CMD NOSE DOWN CMD
LEFT DC C/B PNL
72 73
420 419
NOSE UP CMD NOSE DOWN CMD
22-00 A1 FGM #1 +28 VDC R ESS BUS
(L6) 5A
RIGHT DC C/B PNL
FCS ECU 2
56 67
+28 VDC DC RTN ELEVATOR HI POSITION EXC LO
76 66
1 HI 2 LO
ELEVATOR HI POSITION CT RIGHT LO
85 75 65
3 4 5
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
ELEVATOR POSITION EXC
HI ELEVATOR CT POSITION LO RIGHT
RIGHT ELEVATOR LINEAR VARIABLE DIFFERENTIAL TRANSFORMER (LVDT)
Figure 27-96. Elevator Position Feedback
27-148
FOR TRAINING PURPOSES ONLY
RIGHT ELEVATOR
AIRCRAFT AIRSPEED > 215 KTS LEFT AND RIGHT ELEV SURFACES DISAG BY MORE THAN 4.0 DEGREES
LATCHED - IN AIR NOT LATCHED - ON GND ELEVATOR ASYMMETRY CAUTION LIGHT CDS MSG: LT ELEVATOR LVDT FAILURE
FCECU CH No.1 DETECTS A VOLTAGE FAILURE OF LT ELEV SURFACE LVDT AIRCRAFT ON GND FCECU CH No.2 DETECTS A VOLTAGE FAILURE OF RT ELEV SURFACE LVDT
NOT LATCHED
CDS MSG: RT ELEVATOR LVDT FAILURE NOTES LATCHED - Caution light will remain illuminated for duration of flight. Will not be reset until FCECU power is cycled and fault condition is no longer present. NOT LATCHED - Caution light will extinguish when fault condition is no longer present regardles of phase of flight.
27-149
Figure 27-97. Elevator Caution Lights 27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
AIRCRAFT AIRSPEED < 215 KTS
DASH 8 Q400
LEFT AND RIGHT ELEV SURFACES DISAG BY MORE THAN 6.0 DEGREES
CDS MSG: ELEV ASYM FAILURE
27 FLIGHT CONTROLS
27-150 COPILOT CONTROL COLUMN
FCECU AUTOPILOT TRIM
RIGHT PITCH FEEL ACTUATOR LEFT PITCH FEEL ACTUATOR
AHARS ACCELERATION
PILOT CONTROL COLUMN fst20a01.cgm
Figure 27-98. Pitch Feel and Trim Block Diagram
PFTU
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
DUAL PITCH TRIM ACTUATOR
TRIM INDICATOR
PILOT PITCH TRIM SWITCHES
DASH 8 Q400
COPILOT PITCH TRIM SWITCHES
ADU AIRSPEED
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-32-00 ELEVATOR FEEL AND TRIM
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The input commands from the control columns to the elevator PCU move the elevator surfaces. Therefore the pilot is unable to feel the aerodynamic forces acting on the elevator surfaces. The elevator control system incorporates an artificial feel/trim. The elevator Pitch Feel and Trim Unit (PFTU) provides artificial feel and trimming to counter the effects of longitudinal pitch control changes during flight. The artificial feel acts on the control column to help prevent the pilot from over-controlling the aircraft. Trim counters the effects of changes to the aircraft center of gravity, airspeed and lift during flap extension or retraction.
GENERAL Refer to Figure 27-98. Pitch Feel and Trim Block Diagram. The dual PFTU which inputs to both elevator surfaces. The PFTU is located near the aft elevator quadrants in the vertical stabilizer. The elevator feel and trim system has the following components: •• Pitch Feel and Trim Units (PFTUs) •• Dual pitch trim actuator • Pitch Feel Actuators (PFAs).
FOR TRAINING PURPOSES ONLY
27-151
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION Refer to: •• Figure 27-99. Elevator Feel Caution Light. • Figure 27-100. Pitch Feel and Trim Units.
If one pitch feel actuator fails, the elevator control system continues to operate using the operational actuator but with reduced artificial feel. In this case, the ELEVATOR FEEL caution light illuminates to advise the crew of this condition.
27 FLIGHT CONTROLS
The input commands from the control columns are transferred to the elevator PCU which, in turn, move the elevator surfaces. Therefore, the pilot is unable to feel the aerodynamic forces acting on the elevator surfaces. The PFTU increases elevator control column forces with column displacement as a function of airspeed and normal acceleration of the aircraft. The Air Data Units (ADU) send the airspeed information to the FCECU. The Altitude Heading and Reference System (AHRS) send the acceleration information to the FCECU.
OVERHEAD CONSOLE
Elevator Feel.
PITCH TRIM
EMER LTS DISARMED
INTERNAL DOORS
CABIN PRESS
CHK FIRE DET
Figure 27-99. Elevator Feel Caution Light
27-152
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL TEST OF THE PITCH FEEL SYSTEM
•• Holding the column forward, make sure an opposite force is felt toward the neutral position
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
•• Increase test set to 200 kts make sure the opposite force increases
•• Make sure the PITCH DISC is engaged
•• Move the column full aft and repeat the above sequence
•• Install the air data test set on the pitotstatic tubes
•• On completion remove the test set.
•• Move control columns full forward and hold in position •• Program the air data test set to 100 kts, check ASI increases to 100 kts ELEVATOR CONTROL SYSTEM VERTICAL STABILIZER D
FW
2 3
4 5 LEGEND D
FW
1
6
1. Pitch Feel Actuator RH. 2. Trim Bellcrank RH. 3. Trim Bellcrank LH. 4. Trim Push Rods. 5. Trim Actuators. 6. Pitch Feel Actuator LH.
ft226a01.cgm
Figure 27-100. Pitch Feel and Trim Units
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-153
27 FLIGHT CONTROLS
•• Program test set to 0 kts and move columns to the neutral position
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
PITCH FEEL AND TRIM UNIT
27 FLIGHT CONTROLS D
FW
2 3
1
4
5
D
FW
LEGEND 1. Motor Controller Circuit Card LH. 2. Motor Controller Circuit Card RH. 3. Pitch Trim Actuator RH. 4. Actuator Housing. 5. Pitch Trim Actuator LH.
Figure 27-101. Dual Pitch Trim and Pitch Feel Actuators
27-154
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Dual Pitch Trim Actuator
Pitch Feel Actuators
Refer to Figure 27-101. Dual Pitch Trim and Pitch Feel Actuators.
Refer to Figure 27-101. Dual Pitch Trim and Pitch Feel Actuators.
The dual pitch trim actuator reduces the aerodynamic forces acting on the control columns.
The pitch feel actuators provide PFTU with FCECU commanded inputs to create elevator control column artificial feel.
The dual pitch trim unit is installed on the front face of the PFTU. The pitch trim actuator is a single electro-mechanical unit that includes: •• DC motors (2) •• Motor control cards (2)
The left and right pitch feel actuators are located in the PFTU. The pitch feel actuators extend or retract as commanded by the FCECU in relation to the airspeed and acceleration of the aircraft. Each pitch feel actuator is a single electromechanical unit which has:
•• Gears (1 set) •• Driveshaft
•• DC motor
•• Actuators (2) and
•• Motor controller circuit card
• LVDTs (2).
•• Gears (1 set)
Only one motor is needed at any time to operate the two actuators. A motor rotates the single shaft which drives the gear set. The gears operate both the left and right pitch trim actuators at the same time. The pitch trim actuators are powered by left essential and right essential buses TRIM ACT 1 and TRIM ACT 2 circuit breakers. The FCECU commands the dual pitch trim actuator. Pitch trim signals from the NOSE DN/NOSE UP split trim switches on the control handwheels, or from the autopilot, are prioritized by the FCECU in this order:
•• Actuator and • LVDT. The pitch feel actuators are powered by the left and right essential buses through the FEEL ACT 1 and FEEL ACT 2 circuit breakers. The left motor controller receives its commands from the FCECU channel 1, and the right motor controller receives its commands from the FCECU channel 2. Each FCECU channel supplies three signals to its related motor controller: •• Enable “ON or OFF”
•• Pilot
•• Motor direction
•• Co-pilot and
• Motor speed.
• Autopilot.
NOTE Maximum elevator trim is 13° nose up and 10° nose down.
The two LVDT located in the pitch feel actuators supply feedback signals to the FCECU. The FCECU monitors the position and speed of the pitch feel actuators. The airspeed is supplied by the ADUs and the acceleration information is supplied by the AHRS. This data is shared between channels 1 and 2 of the FCECU so that an identical
FOR TRAINING PURPOSES ONLY
27-155
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
signal is sent to each pitch feel actuator. This reduces mistrack or asymmetry between the pitch feel actuators. Both pitch feel actuators are normally in the active mode. 27 FLIGHT CONTROLS
The failure of a pitch feel actuator is sensed by the FCECU through the LVDT feedback signals. The FCECU then switches the enable signal of the failed actuator to the “OFF” position. The FCECU continues to supply the enable “ON” signal to the other actuator. The aircraft will continue to operate with a degraded pitch feel.
CONTROLS AND INDICATIONS
The LVDT located in the pitch trim actuators send their signals to the IFC and the FCECU which then supplies the signal to the elevator trim indicator. The indicator is labelled: •• “NU” for nose up, •• “ND” for nose down and • “TO” for take-off. A white band next to the “TO” setting shows the amount of elevator trim that is acceptable for take-off. An aural warning sounds if the power levers are advanced above Flight Idle plus 12°, with the elevator trim position outside the take-off range.
Elevator Trim Indicator Refer to Figure 27-102. Elevator Trim Indicator. The elevator trim indicator displays the elevator dual pitch trim actuator position. The elevator trim indicator is an analog type gauge located in the flight compartment on the center console.
LEGEND 1. Nose Down Range. 2. Take-Off Range. 3. Nose Up Range. 4. Indicator. R A T I N G
R A T I N G
FLIGHT IDLE
1 DISC
2
I
3
4
Figure 27-102. Elevator Trim Indicator
27-156
FOR TRAINING PURPOSES ONLY
I
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Pitch Trim Split Switch Refer to Figure 27-103. Pitch Trim Switch.
27 FLIGHT CONTROLS
The pitch trim switches give manual control of the elevator pitch trim. A pitch trim split switch is located in the center of the outboard hand grip of each control handwheel. The pitch trim switches are split in two; both halves of the switches must be activated for the pitch trim command to proceed. This prevents manual pitch trim runaway in the case of a single switch contact failure. The switches are spring-loaded to the centeroff position. When the switches are pushed forward, a nose-down trim is commanded, and when the switches are pulled aft, a nose-up trim is commanded.
TCS
PTT
FW
D
A/P
NOSE DN
D/S
INHP
NOTE Pilot Control Column shown. Co-pilot similar.
NOSE UP
FW
D
fs110a01.cgm
Figure 27-103. Pitch Trim Switch
FOR TRAINING PURPOSES ONLY
27-157
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Elevator Trim Shutoff Switchlights Refer to Figure 27-104. Elevator Trim Shutoff Switchlights. The ELEVATOR TRIM SHUTOFF (PUSH OFF) switchlights provide shutdown indication and control of elevator dual pitch trim actuator. 27 FLIGHT CONTROLS
The PUSH OFF switchlights are located on both sides of the glareshield panel. They indicate “PUSH OFF” if the FCECU detects a pitch trim command that persists for longer than 3 seconds. An aural alert will sound during this fault. The aural warning will stop and the PUSH OFF indication will cancel when the pitch trim command is removed or the switchlight is pushed. Selecting the PUSH OFF switchlight will isolate the dual pitch trim actuator from the FCECU and cause the PITCH TRIM caution light on the Caution and Warning panel to illuminate.
NOTE: LH Glareshield shown. RH Glareshield similar. SPOILERS
STICK PUSHER SHUT OFF
FLIGHT A/P DISENG
ROLL INBD
TAXI
CF-AEI
INHIBIT
ELEVATOR TRIM SHUT OFF
TERRAIN INHIBIT
WARNING PRESS TO RESET
Elevator Trim Shut Off Switchlight.
Figure 27-104. Elevator Trim Shutoff Switchlights
27-158
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Caution Lights Refer to Figure 27-105. Elevator Caution Lights. The FCECU sends signals to the Caution and Warning panel to bring on the caution lights that follow: 27 FLIGHT CONTROLS
ELEVATOR FEEL •• Left or right Pitch Feel Actuator fails, or •• Airspeed No.1 and Airspeed No.2 disagree, or • Acceleration No.1 and Acceleration No.2 disagree. PITCH TRIM •• One pitch trim motor, or its control card fails, or •• Elevator trim shutoffs switch light pressed, or •• Airspeed No.1 disagrees with Airspeed No.2, or • When on ground, Pitch trim input commands disagree.
OVERHEAD CONSOLE
CAUTION PANEL 1 PITCH TRIM
EMER LTS DISARMED CABIN PRESS
2
LEGEND 1. Pitch Trim. 2. Elevator Feel.
Figure 27-105. Elevator Caution Lights
FOR TRAINING PURPOSES ONLY
27-159
27 FLIGHT CONTROLS
27-160 9811RJB1-P/J1F
(G4)
(M3) 5A
56 +28 V DC
HI 1 LO 9 PITCH TRIM LT EXTEND 17 PITCH TRIM LT RETRACT 18 PITCH TRIM LT DISCRETE REF 8 PITCH TRIM LT ENABLE 10 PITCH TRIM LT SPEED 2 PITCH TRIM LT POS'N
(WARDROBE)
41
P/J2 74
MAINT CLEAR NVM
3061 P/J2-2 4 HI 5 LO
UNDERFLOOR - CENTER ELEVATOR 4 13 10 2 8 3 1
HI PITCH TRIM LT POS'N LO PITCH TRIM LT EXTEND PITCH TRIM LT RETRACT PITCH TRIM LT DISCRETE REF PITCH TRIM LT ENABLE PITCH TRIM LT SPEED
3141P/J1A-A1 203 HI 204 LO
LEFT PITCH TRIM ACTUATOR
3141P/J1C-A2 331 HI 332 LO
J/P2 FCS ECU RA429 (OUT)
SIGNAL CONDITIONING UNIT
GRDB2 A429 (IN)
PILOT'S CONTROL HANDWHEEL
FCS ECU A429 P/J1 31 41 30 21 22 FMS #1 (34-61-00)
ELEVATOR TRIM CONT SWITCH
PILOT PILOT PILOT PILOT PILOT
48 HI 49 LO
TRIM TRIM TRIM TRIM TRIM
HI LO HI LO
47 37 48 49 J/P1 HI 47 LO 37
3A
FCS ECU L A429 (IN)
31-41 A1 IOP #1 31-41-00
GENERAL PURPOSE DATA BUS IFC RECV'D
J/P1 PITCH FEEL LT EXTEND 19 PITCH FEEL LT RETRACT 20 PITCH FEEL LT DISCRETE REF 28 PITCH FEEL LT ENABLE 40 PITCH FEEL LT SPEED 50 HI 29 LO 39
P/J11 10 PITCH 2 PITCH 8 PITCH 3 PITCH 1 PITCH 4 13
HI LO
CTR PED - LH SIDE FEEL FEEL FEEL FEEL FEEL
LT LT LT LT LT
EXTEND RETRACT DISCRETE REF ENABLE SPEED
P/J100 7 5
PITCH FEEL LT POS'N
+28 V DC +28 V DC RTN
LEFT PITCH FEEL ACTUATOR
(F4) 3A
3141P/J1C-A1 233 HI 232 LO
VERTICAL STAB
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU) PITCH FEEL ACT 1
GPDB2 A429 (OUT)
AVIONICS RACK
7 6
28V DC L ESS BUS
FCS ECU R A429 (IN)
31-41 A2 IOP #2 31-41-00
RETURN NOSE UP 1 NOSE DOWN 1 NOSE UP 2 NOSE DOWN 2
PITCH FEEL LT POS'N
(H4)
GPDB2 A429
31-41 A1 IOP #1 31-41-00 AVIONICS RACK
51 50 49 36
TB-B/D2 TB-B/B1 TB-B/D1 TB-A/B2 TB-B/A2
2100P/J2 47 HI 24 LO
ECS 21-00-00 AVIONICS RACK
3133J/P10 PLT TRIM NOSE UP 1 PLT TRIM NOSE DOWN 1 PLT TRIM NOSE UP 2 PLT TRIM NOSE DOWN 2
GPDB2 A429
TMCU #2 30-61-00
MAINTENANCE PANEL 45-45-00
AFT AVIONICS RACK
UNDERFLOOR - CENTER
PITCH TRIM IND
LEFT DC CBP 24-61-00
Figure 27-106. Elevator Feel and Trim System - Electrical Schematic
ELEVATOR
HI LO
FCS ECU L A429
10 +28 V DC 12 +28 V DC RTN
PITCH TRIM INDICATOR
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
9811J/P340
C4 B1
J/P1
35 CHASSIS GND
MAINT CLEAR NVM
D1
RELAY JUNCTION BOX NO. 1
67 +28 V DC RTN
LEFT DC CBP 24-61-00
A1
2-K1
P/J1
FCS ECU 1
G5
P/J9 7 +28 V DC 6 RTN
DASH 8 Q400
CENTER FUSELAGE - UNDERFLOOR
D2
34-61-00 FMS #2
VERTICAL STAB
9811RJB1-J/P1F
d4s273200_a_004.dg, nr, apr22/2008
3A 28V DC L ESS BUS
PITCH TRIM ACT 1
D3
MAINTENANCE TRAINING MANUAL
OPERATION Refer to Figure 27-106. Elevator Feel and Trim System - Electrical Schematic.
Pitch Trim Pitch trim is prioritized by the FCECU in the following order. •• Pilot
The FCECU matches the trim speed to the airspeed as follows: •• Airspeed < 150 KIAS high speed trim 0.75°/sec. •• Airspeed > 250 KIAS low speed trim 0.10°/sec. • Trim speed is “increased proportionally” between the two airspeed limits. If airspeed is invalid and both flap positions are < 5°, trim speed is 0.1°/sec.
•• Co-pilot • Autopilot. The command with the highest priority is used by the FCECU for trim control.
If airspeed is invalid and both flap positions are > 5°, trim speed is 0.75°/sec. If airspeed and flap position are invalid trim speed is 0.75°/sec.
Manual Trim When the pitch trim switch is pushed/pulled to the Nose up/ Nose down position the FCECU commands the Dual pitch trim actuator extend or retract using the left motor. The right motor is in standby mode.
If any of the above discrepancies occur the “PITCH TRIM”, caution light will illuminate.
The FCECU controls trim speed and also supplies a pitch trim enable signal. Trim inputs move the trim pushrods and stabilizing linkage, in the PFTU, and move the trim bellcrank. Moving the bellcrank rotates the elevator aft quadrants, through the input bungees, pushrods and torque tubes which extends or retracts the PCUs. This moves the elevators to match the trim input. The trim input is felt back through the cable system to the forward quadrants, rotating the quadrants, and through the push rods, moves the control columns.
FOR TRAINING PURPOSES ONLY
27-161
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-162 S7 PUSH A
9811-GM103 M NORMAL
A
A
A
C
A
38 39 58 59 63 64 74 73
H2
H3
P-
J3
J1
PUSH OFF PITCH PITCH PUSH OFF PITCH PITCH
TRIM TRIM TRIM TRIM
ACU
G 9811-GM103 B
K2
K3
K1 L2
11
L3
L1
PITCH TRIM
CAUTION AND WARNING PANEL
ELEVATOR TRIM DISC (PILOT) 9811-GM102 B
B-
S8 PUSH
NORMAL
A
OFF TRIM AURAL WRNG
54
PITCH TRIM DISC RELAY ENG
81
PITCH TRIM DISC RELAY ENG PITCH TRIM CAUTION
B
9811-GM102 A
H2 H1 J2 J1
9811-GM102
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
A
A
A
A
C G
A
F
B
D
OFF
69 43
B
E 9811-GM102 F
K2 K1 L2 L1
SEE SHT. 1
H5 G5 A1 H4
SEE SHT. 2
G4 A7
H3 9811-GM102 G
D3
D2
D1 C3
C2
C1
C-
J3 9811-GM102 H
CR1
CR 2
G3
B3
B2
L3
ELEVATOR TRIM DISC (CO-PILOT)
C3 A8
SEE SHT. 2
C2 CR 3
A3
A2 K3 K4 K5
SEE SHT. 1
B1
K3 Q-
D4 C4 B1 D3
A1
X1
NC
G1 H1 J1
X2 2-K1
A10
GLARESHIELD PANEL RELAY JUNCTION BOX NO. 1
Figure 27-107. Elevator Trim Runaway or Manual Trim > 3 secs
B10
CR4
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
A
E
D
J2
OFF
K-
OFF
H1
9811-GM103
G F
DASH 8 Q400
B
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Abnormal Operation Pitch Trim Runaway
NOTES
Refer to Figure 27-107. Elevator Trim Runaway or Manual Trim > 3 secs.
27 FLIGHT CONTROLS
A pitch trim runaway, or manual trim selection, for > 3 seconds will cause the following: •• An audible warning in the form of “clicks” •• A ground signal from the FCECU to contacts in co-pilot’s elevator trim disconnect switchlight (S8). Then to the Advisory Control Unit (ACU). The ACU outputs grounds for the ELEVATOR TRIM SHUTOFF switchlights PUSH and OFF. Pushing either switchlight causes the following: •• A ground is provided by the operated switchlight to energize relay 2-K1. This relay removes power to the pitch trim actuators, and removes the ground for the PITCH TRIM caution light, causing the light to illuminate. The PUSH goes off and the OFF stays on in the switchlight.
FOR TRAINING PURPOSES ONLY
27-163
27 FLIGHT CONTROLS
27-164 S7 PUSH A
B
A
A
C
A
E
38 39 58 59 63 64 74 73
D
H2
P-
J3
G
J1
PUSH OFF PITCH PITCH PUSH OFF PITCH PITCH
TRIM TRIM TRIM TRIM
ACU
B
K2
K3
K1 L2
11
L3
L1
CAUTION AND WARNING PANEL
ELEVATOR TRIM DISC (PILOT)
B
PITCH TRIM
B-
S8 PUSH
NORMAL
OFF TRIM AURAL WRNG
54
PITCH TRIM DISC RELAY ENG
81
PITCH TRIM DISC RELAY ENG
69
PITCH TRIM CAUTION
43
B
B
A H2
A
H1 J2 J1
E
K2 K1
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
F
L2 L1
A
A
A
A OFF
C G
A
F
B
D
H5 G5 A1 H4
H3 G
G4 A7
C2
G3
B2
D1
H
CR1
CR 2
C1 B3
L3
ELEVATOR TRIM DISC (CO-PILOT)
CR 3
A3
A2 K3 K4 K5
C2
B1
K3 Q-
C3 A8
C3
C-
J3
D4 C4 B1 D3
D3
D2
A1
X1
NC
G1 H1 J1
X2 2-K1
A10
GLARESHIELD PANEL RELAY JUNCTION BOX NO. 1
Figure 27-108. Trim Push/Off Switch Pushed-Pitch Trim Caution Light ON
B10
CR4
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
H3
J2
A
K-
OFF
H1 OFF
G F
DASH 8 Q400
M NORMAL
A
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-108. Trim Push/Off Switch Pushed-Pitch Trim Caution Light ON.
NOTES
Autopilot Trim
27 FLIGHT CONTROLS
When flying on autopilot, the FGM monitors the amount of torque required on the pitch control capstan to keep the longitudinal trim correct. If the torque force exceeds the threshold, the FGM sends a signal to the FCECU. The FCECU will command pitch trim until the torque forces are removed at the pitch control capstan.
Flap Compensation Trim During flap extension or retraction, with the autopilot Off, flap compensation pitch trim is provided. As the flaps extend or retract, the center of lift on the wing moves forward or backward, causing the aircraft nose to rise or fall. To prevent this from happening the signal comes from the FGM to the FCECU to command the pitch trim actuators to move the elevators to the required positions.
OPERATIONAL TEST OF THE ELEVATOR CONTROL SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Use pilot's or co-pilot's control column •• Pitch disconnect handle in •• Elevator trim NEUTRAL •• Move control columns to neutral, fully fwd and fully aft •• Make sure elevator control surfaces follow, and movement is smooth.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-165
27-166
DASH 8 Q400 MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
Figure 27-109. SPS Block Diagram
27 FLIGHT CONTROLS
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-33-00 STALL WARNING /STICK PUSHER
SYSTEM DESCRIPTION The SPS operates in the following modes: •• Initialization (INIT)
INTRODUCTION
•• Power-On Self Test (POST)
When the aircraft is in a stall condition, the SPS gives a positive input to the flight controls to help the flight crew regain aircraft control.
GENERAL Refer to Figure 27-109. SPS Block Diagram. The SPS has the following units: •• SPM1 and SPM2 •• Stick Pusher Actuator •• Stick Pusher Capstan •• Stick Pusher Quadrant •• Stick Shaker •• Angle of Attack Transducer •• STICK PUSHER SHUTOFF Annunciator Switch •• STALL WARN TEST Switch. The SPS has two primary functions: •• Stick shakers •• Stick pusher. Stick Shakers: Stick shakers give tactile and aural indication of a near stall condition. Stick Pusher: A stick pusher moves the elevators reducing the angle of attack when the aircraft is in a stall condition.
•• Operational (OPER) •• Maintenance •• Teleloading. Initialization Mode: The SPS operates in this mode after an electrical power interruption to initialize the hardware and software. After a successful INIT the SPS progresses to the POST mode. Power-On Self Test: The SPS does a POST after a long power interruption while the aircraft is on the ground. The POST senses SPS hardware malfunctions that are not continuously monitored in the operational mode or apparent to the flight crew. The results of the 25 second POST are saved in the BITE and are sent to the Central Diagnostic System (CDS). Each SPM does a POST twice before a malfunction condition is set. If the POST senses a malfunction, the SPM prevents related Stick Shaker and Stick Pusher operation. The SPM does not do a POST when the aircraft is not on ground. It will use the saved POST results to calculate its status. Operational Mode: The SPS uses two Stall Protection Modules to control their related Stick Shakers. Both Stall Protection Modules operate together to control the Stick Pusher. The operational mode is divided into two sub-modes: •• Pre-Flight Test •• In flight. Pre-Flight Test: The STALL WARN toggle switch located on the pilot side console is set to the TEST1 position and then to TEST2 to do an operational test of the SPMs. The switch is held at the set position during the test.
FOR TRAINING PURPOSES ONLY
27-167
27 FLIGHT CONTROLS
The Stall Protection System (SPS) gives indications when the aircraft is near a stall condition.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
In-Flight Operational Mode: The stick shaker and stick pusher only operate when the aircraft is airborne. The stick pusher operation is inhibited when the calibrated airspeed is greater than 215 Kts (399 km/h), and the Above Ground Level (AGL) altitude is less than 200 ft (60.8 m). 27 FLIGHT CONTROLS
To calculate a near a stall condition and actuate the stick shakers, the SPMs use the following parameters: •• Angle of attack data
Besides self or internal monitoring, the SPS does the following monitoring: •• External Input Monitoring •• Stick Shaker Monitoring
•• Flap position
•• Stick Pusher Monitoring.
•• Mach number
External Input Monitoring: Each SPM monitors the following external inputs:
•• Engine torque •• Icing status. To calculate a stall condition and actuate the stick pusher the SPMs use the above mentioned parameters as well as: •• Power lever angle
•• AOA (Transducers and Correction Data) •• FPIU (Flap Position Data) •• REF SPEEDS (Toggle Switch) •• PSEU (Weight On Wheels Data)
•• Condition lever angle.
•• ADU Data
Each SPM uses its related AOA transducer angle input for stick shaker calculations and an average of the two for the stick pusher calculations. The SPM will use the same input as the other SPM if any related data inputs shown above have malfunctioned. If no data is available, the SPM will then use default data. An AOA malfunction or difference is the only input that prevents the stick pusher from operating. When the aircraft is in icing conditions, the lift supplied by the wings can be decreased enough to cause the aircraft to stall at a lower angle of attack. The stall operating angle of the stick shaker and stick pusher is set to a lower angle of attack when in icing conditions. The SPS receives icing condition data from the REF SPEEDS toggle switch in the ICE PROTECTION Control Panel. The Electronic Instrument System (EIS) shows an [INCR REF SPEED] message.
27-168
Maintenance Mode: The BITE uses the Central Diagnostic System (CDS) to report the condition of the unit and saves faults in a Non Volatile Memory (NVM) for reporting to line and shop maintenance. The SPM does a test when it receives a maintenance discrete command through IOM1while the air speed is less than 50 Kts (93 km/h) and the aircraft is on the ground.
•• AHRS Data •• Radio Altimeter Data •• FADEC Engine Data. AOA Transducer Monitoring: The AOA transducer angles are critical parameters for the SPS functions. If an AOA transducer malfunctions, each SPM will use the serviceable transducer to make its stick shaker calculation. The Stick Pusher will not operate. These malfunctions will be apparent to the flight crew in the form of the following caution lights: •• No.1 STALL SYST FAIL •• No.2 STALL SYST FAIL. Non-critical malfunctions do not show in flight. The caution light(s) comes on after the aircraft has landed and slowed to less than 50kts.
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Non-critical malfunctions are as follows: •• Flap Position data •• PSEU WOW Data
OPERATIONAL TEST OF THE STALL PROTECTION MODULE
•• ADU Data •• AHRS •• RAD ALT •• FADEC. Stick Shaker Monitoring: The SPMs monitor their related stick shakers for the following malfunctions: •• Current
•• Energize DC and AC electrical systems. Initiate a POST of the SPMs by resetting their applicable circuit breakers •• Make sure that the SPS caution lights are off •• Set and hold the STALL WARN switch in the TEST 1 position and observe the following:
•• Open Circuit •• Short Circuit Stick Pusher Monitoring: Monitoring of the stick pusher is by the SPMs and the stick pusher actuator. The SPMs monitor for the following: •• Un-Commanded Stick Push •• No Stick Push When Commanded •• SPM Stick Pusher Driver Failure The stick pusher actuator monitors for the following:
°° The left stick shaker operates °° No.1 STALL SYST FAIL caution light ON °° PUSHER SYST FAIL caution light ON •• Release the test switch and make sure that the stick shaker stops and the caution lights go OFF •• Repeat the test selecting TEST 2 position on the STALL WARN switch.
•• Loss of the 28 VDC Main Power input to the stick pusher actuator •• Difference between the PUSH1 and PUSH2 commands from the SPMs •• S e l e c t i o n o f e i t h e r / b o t h S T I C K PUSHER SHUTOFF switches •• Internal malfunction of the stick pusher actuator. When a malfunction is sensed, the stick pusher actuator sets its FAIL signal output discrete signal. Teleloading Mode: The teleloading mode supplies new operational software to the SPMs (Shop Only).
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-169
27 FLIGHT CONTROLS
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Stall Protection Modules Refer to Figure 27-110. Stall Protection Modules Locator.
27 FLIGHT CONTROLS
Each SPM is guided into the Integrated Flight Cabinet (IFC1, IFC2) using a guide rail and guide pins. The top and bottom guide pins at the IFC back panel make sure that the module and the back panel come together precisely in the correct location. The SPM are held in place using front locking levers. This gives easy installation and removal of the Line Replaceable Unit (LRU) without tools.
B
A
D
FW
A
AVIONICS RACK ELECTRICAL INSTALLATION
C
B
INTEGRATED FLIGHT CABINET
fs899a01.cgm
Figure 27-110. Stall Protection Modules Locator
27-170
FOR TRAINING PURPOSES ONLY
C
MAINTENANCE TRAINING MANUAL
Stick Pusher Actuator Refer to Figure 27-111. Stick Pusher Actuator Locator.
The stick pusher actuator needs two independent PUSH input signals from the SPMs to operate.
The stick pusher actuator mounts to the stick pusher capstan with four mounting bolts.
The PUSH1 signal operates the motor and the PUSH2 signal engages an electromechanical clutch. The output torque is nominally set to approximately 32 kilograms (kg) of column force.
The actuator turns an output pinion to move the capstan that moves the control columns forward.
NOTE The stick pusher actuator can operate against a stalling load for only a short time before overheating. The SPS has software protection to limit the stick pusher operation to a maximum of 15 seconds, with a time delay of 1 minute before the stick pusher can be activated again.
The stick pusher actuator uses two, 28 VDC electrical power sources. One supplies motor current and the other supplies the monitor circuits.
FW
D
FW
D
fs983a01.cgm
FW
D
STICK PUSHER CAPSTAN
Figure 27-111. Stick Pusher Actuator Locator
FOR TRAINING PURPOSES ONLY
27-171
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS FW
D
fs984a01.cgm
FW
D
STICK PUSHER CAPSTAN
Figure 27-112. Stick Pusher Capstan Locator
27-172
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Stick Pusher Capstan
NOTES
Refer to Figure 27-112. Stick Pusher Capstan Locator.
27 FLIGHT CONTROLS
The stick pusher capstan mounts to the aircraft structure and connects to the elevator control system with cables. Two aircraft cables attach to the capstan pulley using staged ball fittings that anchor to pockets in the pulley. The stick pusher capstan gives the mechanical interface with the elevator control system. The capstan has an adjustable override slip clutch that lets the cable pulley turn if the stick pusher actuator cannot move due to a mechanical malfunction.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-173
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Stick Pusher Quadrant Refer to Figure 27-113. Stick Pusher Quadrant Locator. The stick pusher quadrant is located below the left flight compartment floor and inputs to the pilots’ elevator forward quadrant. 27 FLIGHT CONTROLS
D
FW
FW
D
A
A
LEFT ELEVATOR FORWARD QUADRANT ASSEMBLY
D
FW
fsa09a01.cgm
A
Figure 27-113. Stick Pusher Quadrant Locator
27-174
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Stick Shaker Refer to Figure 27-114. Stick Shaker Locator.
27 FLIGHT CONTROLS
The stick shaker mounts to the control column with a bracket. The stick shaker has a housing that contains an electrical motor that turns an unbalanced weight.
NOTE Pilot Side Shown. Co-pilot Side Similar.
CONTROL COLUMN ASSEMBLY
FWD
Figure 27-114. Stick Shaker Locator
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-175
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Angle of Attack Transducer (AOA) Refer to Figure 27-115. Angle Of Attack Transducer Locator. Each AOA transducer mounts to the aircraft with five screws and two locating pins. 27 FLIGHT CONTROLS
The transducer has a fixed body that attaches to the aircraft and a transducer that moves by the relative airflow. The transducer connects to a shaft that turns freely. A counterweight and a damper attach to the shaft to balance the transducer. The transducer has two resolvers that send angular data to the SPMs. A self-regulated heater prevents icing. The body is not heated.
4 D
FW
5 1
A
LEGEND 1. Angle of Attack Transducer. 2. Cover plate. 3. Screws. 4. Sealing ring. 5. Connector.
2 FW
D
A
A
NOTE Left side shown. Right side similar.
3
Figure 27-115. Angle Of Attack Transducer Locator
27-176
FOR TRAINING PURPOSES ONLY
st019b01.cgm
MAINTENANCE TRAINING MANUAL
Stick Pusher Shutoff Annunciator Switch
Stall Warn Test Switch
Refer to Figure 27-116. SPS Stick Pusher Shutoff Annunciator Switch Locator.
The STALL WARN TEST switch mounts to the pilot’s side console panel.
The two STICK PUSHER SHUT OFF annunciator switches attach to the glareshield panel assembly.
The TEST switch provides operational tests. The switch is a positive break, double pole, toggle switch with a lever that springs back to the center OFF position.
If either switch is pushed, the stick pusher actuator will not operate and the OFF light in the switch comes on.
GLARESHIELD PANEL
OF
F fs982a01.cgm
Figure 27-116. SPS Stick Pusher Shutoff Annunciator Switch Locator
FOR TRAINING PURPOSES ONLY
27-177
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-178
ADU #1-2 A429 (OUT)
HI 16 LO 49
107 HI 108 LO
ADU #1-2 A429
ADU #1 301 GND AHRS #1-2 A429 (OUT)
223 HI 222 LO
HI D17 LO D12
135 CH GND 2 435 CH GND 4
AHRS #1
IOP #1-1
J / P1- A3 7 HI HEATER 1 115 V AC 8 LO 1 HI SPM #1 EXCITATION 2 LO 7.5 V AC 2500 HZ 22 GND
H
17 16 4 3
435 434 432 433
HI LO HI LO
AOA #1 MEAS 1 COS
201 227 226 132
HI 213 LO 212
GND HI IOP #1-1 A429 LO POST IFC #1 NG WOW 1
DASH 8 Q400
FROM IRPS TIMER & MONITOR
SEE SH 2
AHRS #1-2 A429
IOP #1
AOA #1 MEAS 1 SIN P/J1A-A1
ANGLE OF ATTACK #1 VANE
SEE SH 2
426 P PGM SP INHIB 7 8 1 2
J
HI LO HI LO
HEATER 2 115 V AC SPM #1 EXCITATION 7.5 V AC 2500 HZ
17 16 4 3
22
335 334 332 333 308 201 401
HI AOA #2 MEAS 1 COS LO HI AOA #2 MEAS 1 SIN LO PUSHER GND REF GND GND
ANGLE OF ATTACK #2 VANE
ADU #2-4 A429 (OUT)
125 HI 124 LO
129 HI 128 LO
IOP #2
POST NG WOW1 2A IFC #1 NG WOW2 8J
104 POST IFC #1 NG WOW 2
ADU #2-4 A429
HI C5 LO C10
213 HI 214 LO
W
200 FT. ALT TRIP #1
101 GND 401 GND
ADU #2
AHRS #2-3 A429 IN
425
HI LO HI DOWNLOAD C LO SPM #1 LOAD REQD DOWNLOAD D
71
329 REF SPEED
(IRPS) PANEL L VANE HEATER B FAIL P/J3 R VANE HEATER L FAIL
IRPS TIMER AND MONITOR UNIT
PRE-FLIGHT TEST
427 L VANE HEATER FAIL
FLAP POSITION INDICATION (27-53-00)
F-
327 431 430 331 330 428 328
R VANE HEATER FAIL HI FLAP POS L LO HI FLAP POS R LO FLAP HEALTHY L FLAP HEALTHY R
423 PRE FLIGHT TEST
PILOTS SIDE CONSOLE STALL PROTECTION MODULE (SPM) #1 INPUTS
200 FT. ALT TRIP #1
RADIO ALT #1
AHRS #2
REF SPEED
IOP #2-1 A429
PSEU
HI 14 LO 47
AHRS #2-3 A429 (OUT)
HI 213 LO 212
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
FROM IRPS TIMER & MONITOR
IOP #2-1
6 7 14 15 2
TEST SOCKETS
211 212 221 222 115 114 232
HI LO HI LO HI LO SPM
FLIGHT TEST A429 IN DOWNLOAD D DOWNLOAD C #1 LOAD REQD
PMAT DOWNLOAD RS422 CONNECTOR
PUSHER FAIL PUSHER PUSH
STICK PUSHER
STALL PROTECTION MODULE (SPM) #1
Figure 27-117. SPM Inputs
C U
422 408
PUSHER FAIL PUSHER PUSH
STALL PROTECTION MODULE (SPM) #1
STALL PROTECTION MODULE (SPM) #1 INPUTS
C
MAINTENANCE TRAINING MANUAL
Inputs Refer to Figure 27-117. SPM Inputs. Air Data Units: Each SPM receives an ARINC 429 data bus from both ADC No.1 and ADC No.2. The SPS uses the Mach number and the True Airspeed to perform the stall warning and stall identification calculations. The SPS uses the Calibrated Airspeed to inhibit the Stick Pusher at airspeeds greater than 215 knots, and to inhibit AOA Vane comparison monitoring at airspeeds below 60 knots. Attitude & Heading Reference System: The AHRS inputs are used to compute the angleof-attack rate of the aircraft. When the aircraft angle-of-attack rate exceeds 3° per second, the SPS computes a stick pusher advance term that is added to the angle-of-attack when determining if the stick pusher firing angle is exceeded. The stick pusher advance term is intended to compensate for the dynamics of a rapid approach to stall by activating the Stick Pusher earlier, to prevent a large overshoot into the stall. Angle Of Attack Vanes: Each of the left and right AOA Vanes contains 2 synchro resolvers, one for each SPS channel. The outputs of the AOA Vanes are AC voltages equivalent to the sine and cosine of the AOA Vane angles. The SPMs use the AOA Vane angles to determine when to activate the Stick-Shakers and the Stick Pusher. Stall Protection Module: Each SPM transmits an ARINC 429 data bus to the other SPM for internal SPS communication between the two channels. The data transmitted on these buses includes the validity status of each channel. The SPMs cross-exchange hardware discretes that indicate the healthy status of each SPM, and indicate when each SPM is ready to command a stick push. IRPS Panel: The selection of the REF SPEEDS toggle switch inputs to the SPM to set a new reference for stall warning actuations.
Timer Monitor Unit: The SPMs receive the status of the left and right AOA Vane heaters from the TMU. If the AOA vane is not heated, the SPMs prevent the SPS from using its inputs. TEST Switch: Input to SPM and Radio Altimeter to initiate a Stall Warning Test. IOP: Each SPM receives an ARINC 429 data bus from each of the IOP data concentrators. These buses transmit the Radio Altitude and FADEC data to the SPMs. The SPMs use engine torque in the Stick-Shaker firing angle computations and Power Lever Angle and Condition Lever Angle in the Stick Pusher firing angle computations. PSEU: Each SPM receives WOW1 and WOW2 discretes that indicate air/ground status based on the two nose gear Weight on Wheels proximity sensors. The SPS uses the WOW discretes to inhibit the Stick-Shakers and the Stick Pusher when the aircraft is on-ground, and to prevent the SPMs from performing POST following a power interrupt, when the aircraft is airborne. Inc. Ref Speed: The SPS uses the Inc Ref Speed switch selection in the Stick-Shaker and Stick Pusher firing angle computations. Radio Altimeter: The SPMs receive a RA TRIP discrete when the radio Altitude is less than 200 feet to inhibit the Stick Pusher below 200 feet. The SPMs also receive Radio Altitude indirectly via the IOPs. The SPS uses the actual Radio Altitude to determine aircraft air/ground status when the Weight On Wheels inputs from the PSEU disagree. PMAT: Software download. Stick Pusher: The outputs from the Stick Pusher Actuator to the SPMs are the PUSH discrete, which indicates the Stick Pusher is pushing, and the FAIL discrete, which indicates that the Stick Pusher Actuator internal monitoring is invalid, or the flight crew has depressed a Stick Pusher Shutoff switchlight.
FOR TRAINING PURPOSES ONLY
27-179
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-180 SPM #1 EXCITATION SPM #1 EXCITATION
HI LO HI LO
301 302 403 404
H
SEE SH. 1
J
CAUTION AND WARNING PANEL
FOR TRAINING PURPOSES ONLY
SHAKER FB CMD 405 CMD 305 RTN 306
A CMD B RTN
SHAKER 1
420 421 419 305 306 303 304 433 434 313 423 307 308 314 418 431 432
33 16 19 1 21 62 43 63 44 9 20 65 46 11 29 64 45 36
DECISION HEIGHT L/GEAR DOWN GND BACKCOURSE HI ROLL ATT SYNCRO LO HI BARO ALT RATE LO HI AIRSPEED IN LO BARO ALT RATE VAL G/S SELECT GND HI GS DEV LO
G/S VALID RADIO ALT +28 VDC HI RADIO ALT INPUT LO GPWS AUDIO SUPPRESS
GPWC
SHAKER 1 GPWS AUDIO SUPPRESS 312
STICK SHAKER #1 LANDING FLAP POS 1 422 LANDING FLAP POS 3 424 LANDING FLAP POS 2 312 REF GND B PUSHER CMD N SH 3
M
SPM #1-1 FT A429
+28 VDC L MAIN BUS
(K6) STICK PUSHER
TEST SOCKETS
SPM #1-1 FT A429
IOP #1
SPM #1-1 A429
HI 121 LO 122
STICK PUSH READY 313 SPM #1 HEALTHY 108
STICK PUSHER
+28 VDC 7.5A R MAIN BUS
111 HI 112 LO
HI 217 LO 218
L +28 VDC IN G +28 VDC RTN
7.5A
AVIONICS CBP
HYDRAULIC/FLAP OVERRIDE CONTROL PANEL
307 PUSHER CMD MOTOR 407 PUSHER CMD FDBK
M +28 VDC IN T +28 VDC RTN
(K1) STICK PUSHER
111 HI 112 LO
209 HI 210 LO
SPM #1-1 A429
413 STICK PUSH READY 235 SPM #1 HEALTHY
SPM #1-1 FT A429
27-30 A2 STALL PROTECTION MODULE (SPM) #2
IOP #2 SH 3
F LANDING FLAP POS 1 H- LANDING FLAP POS 3 G- LANDING FLAP POS 2
N
405 AP DISCONNECT
FGM #1
RA TEST ENABLE 414 HI 303 LO 304
R/A TEST SIG
STALL PROTECTION MODULE (SPM) #1
302 AP DISCONNECT AP DISCONNECT 310
FGM #2 STALL PROTECTION MODULE (SPM) #1
STALL PROTECTION MODULE (SPM) #1 OUTPUTS
Figure 27-118. SPM Outputs
NM- HI A- LO
RA TEST ENABLE R/A TEST SIG
RADIO ALT # 1
STALL PROTECTION MODULE (SPM) #1 OUTPUTS
MAINTENANCE TRAINING MANUAL
DECISION HEIGHT L/GEAR DOWN GND BACKCOURSE HI LO HI BARO ALT RATE LO HI AIRSPEED IN LO BARO ALT RATE VAL G/S SELECT GND HI GS DEV LO G/S VALID RADIO ALT +28 VDC HI RADIO ALT OUTPUT LO ROLL ATT SYNCRO
DASH 8 Q400
30 #1 STALL SYST FAIL 31 PUSHER SYST FAIL
STALL 1 NO WARNING 324 PUSHER SYSTEM NOT FAIL 323 STALL 1 NO WARNING FBA 424
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Flap Position: Each SPM receives left and right Flap Positions and a FLAP HEALTHY discrete from the FPIU. The SPS uses the Flap Positions to determine the Stick-Shaker and Stick Pusher firing angles.
NOTES
27 FLIGHT CONTROLS
Aircraft Configuration Module: Each SPM receives installation correction values for each AOA Vane from the ACMs. The installation correction values are specific to the individual aircraft, and are intended to compensate for errors of up to 2° in the mounting of the vanes.
Outputs Refer to Figure 27-118. SPM Outputs. Caution and Warning Panel: No.1 STALL SYST FAIL, No.2 STALL SYST FAIL and PUSHER SYST FAIL. Stick Pusher Actuator: A PUSH command from SPM No.1 to the motor, and a PUSH command from SPM No.2 to the clutch. Stick Shaker: A 2-wire connection, one wire for 28 VDC, and one wire for Return, which allows the SPMs to both command and monitor the Stick-Shaker motors. Auto Pilot: Each SPM sends a discrete to the AFCS to disengage the Autopilot when the aircraft angle-of-attack has reached the stall warning condition. EGPWS: Each SPM sends a discrete to the Enhanced Ground Proximity Warning System to inhibit the “Pull-up” aural warning when the aircraft has reached the stall warning condition. IOP 1 and IOP 2: The SPS outputs data to the FDR via IOP No.1. Each SPM outputs Left AOA, Right AOA, Left or Right Stick-Shaker Event, and Stick Pusher Event. AOA Vanes: Excitation for AOA resolvers. SPM: Cross talk between the two SPMs. Data includes health status and a discrete that indicates when each SPM is ready to command a push.
FOR TRAINING PURPOSES ONLY
27-181
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
PUSH C 'PUSH OFF CO-PILOT LT' TO ACU, 3313-P/J2, PIN 106 (22-11-00) (SEE SH. 3) +28V DC
N
28 V
L
A
A
B
A
A
A
G NORMAL
M
D
OFF H2
H3
H1 J2
J3
K
OFF
J1
P
P SP PILOT RELEASE R SP CO-PILOT RELEASE
K2
K3
STICK PUSHER
K1 L2
L3
L1 PILOTS GLARESHIELD STICK PUSHER
PUSH C 'PUSH OFF PLT LT' TO ACU, 3313-P/J2, PIN 105 (22-11-00) (SEE SH. 3)
+28V DC
M
H-
G
G-
D
A
A
B
A
A
A
NORMAL OFF H3
J3
F-
K3
L3
H2 H1
OFF
J2 J1
J-
K2 K1 L2 L1
CO-PILOTS GLARESHIELD STICK PUSHER
I-
'OFF PLT LT CMD' TO ACU, 3313-P/J1, PIN 105
N
'OFF CO-PLT LT CMD' TO ACU, 3313-P/J1, PIN 106
GLARESHIELD PANEL
Figure 27-119. Stick Pusher Shutoff Switchlights
27-182
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-119. Stick Pusher Shutoff Switchlights.
NOTES
27 FLIGHT CONTROLS
Stick Pusher Shutoff Switchlights: The Stick Pusher Shutoff switchlights are used to disable the stick pusher. If either switchlight is depressed a ground is applied to the stick pusher to disable the internal drive circuitry. The “OFF” indications in both switchlights will come on. The Stick Pusher actuator electronic circuits supply a discrete “FAIL” signal to the SPMs to cause the Pusher System Fail caution light to come on.
FOR TRAINING PURPOSES ONLY
27-183
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OVERHEAD CONSOLE
27 FLIGHT CONTROLS 1
2
3
#1 STALL SYST FAIL #2 STALL SYST FAIL
LEGEND 1. Pusher System Fail (Amber). 2. # 2 Stall System Fail (Amber). 3. # 1 Stall System Fail (Amber).
FLAP DRIVE
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING MAIN BAT HOT
Figure 27-120. SPM Caution Light Indications
27-184
FOR TRAINING PURPOSES ONLY
FUELING ON
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS
NOTES
Refer to Figure 27-120. SPM Caution Light Indications. The stall protection system malfunctions are shown with the caution lights that follow: 27 FLIGHT CONTROLS
•• No.1 STALL SYST FAIL •• No.2 STALL SYST FAIL • PUSHER SYST FAIL. The No.1 STALL SYST FAIL, No.2 STALL SYST FAIL: The No.1 STALL SYST FAIL or No.2 STALL SYST FAIL caution light comes on if a malfunction condition of the SPS prevents stick shaker operation. The No.1 STALL SYST FAIL or No.2 STALL SYST FAIL caution light comes on immediately, while the aircraft is on the ground or airborne, for the malfunction conditions that follow: •• Related SPM •• The two stick shakers • The two Angle of Attack transducers (AOA). Malfunctions of not critical parameters are not shown in flight. The No.1 STALL SYST FAIL or No.2 STALL SYST FAIL caution light will come on 30 seconds after the aircraft is on the ground for the malfunction of non-critical parameters. PUSHER SYST FAIL: The PUSHER SYST FAIL caution light comes on when a STICK PUSHER SHUTOFF annunciator switch is set to OFF or for any malfunction that prevents stick pusher operation. The PUSHER SYST FAIL caution light also comes on if a malfunction condition of the SPS prevents stick shaker operation.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-185
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-121. PFD Low Speed Cue Indications. A Low Speed Cue (LSC) is calculated by the SPS to show the minimum operating speed. It is a red and black band that starts with a red edge at the low speed value and extends to the bottom of the IAS scale.
WING LVL
GA ALT SEL
14000 10
200 160 IAS 120
60
5 40 20
100
0
80 140 151
073
3
6
E
12
N
HDG
0 1013 HPA TCAS STBY
VOR1 350 H 113. 50 92.1 NM
15
30
S
W
DME1 H
24
ADF1
92.1 NM
Figure 27-121. PFD Low Speed Cue Indications
27-186
FOR TRAINING PURPOSES ONLY
21
27 FLIGHT CONTROLS
It is out of view when the aircraft is on the ground.
ADF2 DME2
92.1
NM
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-122. PFD Low Speed Cue Malfunction Indications.
NOTE If AHRS1 or AHRS2 malfunctions, a CUE flag is shown on the related IAS indicator.
The two Indicated Air Speed (IAS) indicators show a vertical yellow CUE flag for the malfunction conditions that follow:
NOTE
•• Left or right AOA transducer
The AOA CUE flag is out of view when the aircraft is on the ground and the KIAS is less than 60 kts.
•• Left or right AOA transducer heat •• ADC1 or ADC2
27 FLIGHT CONTROLS
DASH 8 Q400
•• FADEC1 (A and B channels) or FADEC2 (A and B channels) • Left and right flap position.
WING LVL
GA ALT SEL
14000 10
200 160 IAS 120
60
5 40 20
100 80 140 151
0
073
3
6
0 1013 HPA TCAS STBY E
12
N
HDG
C U E
VOR1 350 H 113. 50 92.1 NM
15
30
S
24
W
DME1 H
21
ADF1
92.1 NM
ADF2 DME2
92.1
NM
Figure 27-122. PFD Low Speed Cue Malfunction Indications
FOR TRAINING PURPOSES ONLY
27-187
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Tests Refer to Figure 27-123. Stall Warn Test Toggle Switch.
27 FLIGHT CONTROLS
The STALL WARN toggle switch is set to the TEST1 position for more than 10 seconds and then to the TEST2 position to do a SPS operational test. The test has the indications that follow: •• Related STALL SYST FAIL caution light comes on •• PUSHER SYST FAIL caution light comes on •• Related stick shaker operates • Related stick pusher does not operate.
NOTE On aircraft with two Radio Altimeters (RA): When the STALL WARN toggle switch is set to the TEST1 or TEST2 position, the RA indications in the related Electronic Attitude Direction Indicators (ATT1, ATT2) shows 500 ft and then 50 ft.
CIR BKR LIGHT
W/S WIPER ICE DETECT
PILOTS FLT PNL
STEERING
LEFT SIDE CONSOLE
Stall Warn Test Toggle Switch
fs985a01.cgm
Figure 27-123. Stall Warn Test Toggle Switch
27-188
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-34-00 ELEVATOR SURFACES
GENERAL
INTRODUCTION
There are two elevator surfaces installed on the trailing edge of the left and right horizontal stabilizers. Three elevator PCUs are attached to each elevator surface to drive the elevators. A LVDT is also attached to the front of each elevator surface.
The elevator surfaces give longitudinal control of the aircraft in flight, around the lateral axis.
LEGEND
A
1. Inboard Elevator Hinge 2. LVDT Attachment 3. Inboard PCU Attachment 4. Inboard Center Hinge 5. Middle PCU Attachment 6. Outboard PCU Attachment 7. Outboard Center Hinge 8. Elevator Surface 9. Outboard Elevator Hinge 10. Static Discharge Wicks.
FWD 1
2 3
4 5 6 A
10 7 8
NOTE Left Side Shown, right Side Similar. 9
Figure 27-124. Elevator Surface
FOR TRAINING PURPOSES ONLY
27-189
27 FLIGHT CONTROLS
Refer to Figure 27-124. Elevator Surface.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS CABLE SYSTEM
PITCH DISCONNECT CLUTCH MECHANISM
Figure 27-125. Pitch Disconnect Clutch Mechanism Component Location Index
27-190
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
27-38-00 PITCH DISCONNECT SYSTEM INTRODUCTION The pitch disconnect system allows the left and right elevator control circuits to be disconnected from each other in the event of a jam. The remaining operational circuit controls the pitch of the aircraft.
GENERAL Refer to Figure 27-125. Pitch Disconnect Clutch Mechanism Component Location Index. If a jam occurs in either control circuit, the PITCH DISC handle in the flight compartment is pulled. This will disconnect the left elevator circuit from the right elevator circuit. The pitch disconnect system has the following components: •• Pitch disconnect handle • Pitch disconnect clutch mechanism.
Pitch Disconnect Handle
Pitch Disconnect Clutch Mechanism Refer to Figure 27-125. Pitch Disconnect Clutch Mechanism Component Location Index. The clutch mechanism connects the left and right sides of the torque tube. The clutch mechanism is located in the torque tube connecting the two control columns below the flight compartment floor. When the PITCH DISC handle is pulled to the limit and rotated 90°, the cable operates the clutch lever and cam assembly. The cam followers withdraw the spring loaded clutch from the clutch plate. This disconnects the two columns. When the handle is in the engaged “IN” position, the clutch and clutch plate are kept in positive contact with each other by the clutch spring. To re-engage the pitch disconnect mechanism, the pilot and co-pilot control columns must be placed in the neutral position. Then rotate The PITCH DISC handle 90° and lower to the engaged position. When the control columns are properly aligned, the clutch returns to the engaged position by the clutch springs.
Refer to Figure 27-125. Pitch Disconnect Clutch Mechanism Component Location Index. The PITCH DISC handle operates the pitch disconnect system. The PITCH DISC handle is located in the flight compartment, on the left side of the center console. A pin in the shaft of the pitch disconnect handle rides in a slot in the shaft housing. When the handle is pulled out and rotated 90° the pin moves into the slot to keep the handle locked in the disengaged position. The PITCH DISC handle has a cable routed below the flight compartment floor and is connected to the clutch. When the handle is pulled, the clutch is disengaged. Adjustment of the pitch disconnect system is by a turnbuckle installed in the cable.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-191
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL CHECK OF THE ELEVATOR CONTROL PITCH DISCONNECT MECHANISM
NOTES
27 FLIGHT CONTROLS
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. The operational check of the pitch disconnect system is done with hydraulic power is off. Pull the pitch disconnect handle and turn 90° counterclockwise to disconnect the pitch control system. •• Move the pilot control column fully forward and aft, make sure the co-pilot control column does not move. •• Move the co-pilot control column fully forward and aft, make sure the pilot control column does not move. Turn the pitch disconnect handle 90° clockwise and make sure the pitch disconnect handle is fully retracts. •• Move the pilot or co-pilot control column fully forward and aft to make sure the pitch disconnect clutch and the control columns move together.
27-192
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-193
27 FLIGHT CONTROLS
27-194 L FLAP POSITION INDICATION
0 5
R FLAP POSITION INDICATION
FLAP INDICATOR
10
5
10
FPIU
15 35
0
FCECU
ARMING SWITCH
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
FLAP LEVER
35
IFC 1 IFC 2
FLAP LEVER RVDT
FLAP
MAINTENANCE TRAINING MANUAL
DRIVE C & W PANEL FLAP
ARM COMMAND
POWER
WOW PSEU
LANDING GEAR WARNING HORN RIGHT FLAP POSITION FEEDBACK
LEFT FLAP POSITION FEEDBACK PTU
#1 ENG
FCU
HYD PUMP
ON > 5° STBY HYD PUMP
SUPPLY HYDRAULIC POWER
#9
#8
#7
#4 FLAP POSITION DUAL RVDT
fs794a01.cgm
#6 #3
LEFT OUTBOARD FLAP
FPU
RETURN
TRANSMISSION SHAFTS
#5
#4
#3
#2
#2
ACTUATORS
#1
#3
#4
LEFT INBOARD FLAP
RIGHT INBOARD FLAP TORSION BAR
#5 #2
#1
#1
TORSION BAR
Figure 27-126. Wing Flap System
#6
#7
#8
#9
#3
#4
RIGHT OUTBOARD FLAP
FLAP POSITION DUAL RVDT
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-51-00 FLAP CONTROL SYSTEM
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The flap control system operates the flaps during extension, retraction from the selected position. The flap control system uses a digital position control loop to operate the flap surfaces by modulating the flow to the hydraulic motor of the flap power unit.
GENERAL Refer to Figure 27-126. Wing Flap System. The flap control system monitors flap position, selection signals and produces the output signals to the Flap Power Unit (FPU) to control flap movement. The flap control is comprised of the following components: •• Flap Control Unit (FCU) •• Flap selector lever/quadrant • Flap lever transducer.
FOR TRAINING PURPOSES ONLY
27-195
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
FCECU
27 FLIGHT CONTROLS
FCU
D
FW
UNDERFLOOR TRAY
3
LEGEND 2
1. Electrical Connectors. 2. Mounting Bracket. 3. Flap Control Unit Box.
1
D
FW
ft196a01.cgm
Figure 27-127. Flap Control Unit (FCU)
27-196
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Flap Control Unit (FCU) Refer to: •• Figure 27-127. F lap Control Unit (FCU). 27 FLIGHT CONTROLS
• Figure 27-128. F lap Control Unit Block Diagram. The FCU provides control, monitoring, and caution indications of the flap control system. The FCU is located below the cabin floor. The FCU receives its power from the 28 VDC left essential FLAP CONT circuit breaker.
FOR TRAINING PURPOSES ONLY
27-197
27 FLIGHT CONTROLS
27-198 Flap Selector RVDT
Flap Selector Arming Switch Ground
PSEU WOW
Maint Panel NVM Reset
Left Wing RVDT
Flap Position Select
Solenoid Valve on FPU
Flap Control Unit
Flap Power
Servo Valve in FPU
Flap Drive
Pressure Switch in FPU
EDP No.1 Pressure ARINC 429
Take Off Warning
fs0c0a01.cgm
Figure 27-128. Flap Control Unit Block Diagram
MAINTENANCE TRAINING MANUAL
RH Wing RVDT
DASH 8 Q400
FOR TRAINING PURPOSES ONLY
28 VDC
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-129. Flap System Caution Panel.
The FLAP DRIVE caution light illuminates for the faults that follow:
Continuous Monitoring is performed by the FCU to check for system failures. Flap failures detected by the FCU command FPU shutdown through the following actions:
•• Hydraulic pressure at FPU without selection command •• Flap stall •• Flap position output from the FCU is not valid
•• De-energizing the FPU solenoid valve • De-energizing the FPU EHSV. If a failure locks the flap system, the FLAP POWER caution light will illuminate. All further flap movements are inhibited. If an asymmetry or uncommanded movement is detected, the FCU latch relay is opened. The latch relay can only be reset with the aircraft on the ground. This is done with the maintenance panel NVM reset button after mechanically correcting the fault. The FLAP POWER caution light will remain on. It is reset at the next on ground FCU Power On BIT.
•• ARINC 429 transmission integrity. Only during Power-On BIT and functional checks • Read Only Memory failure in microprocessor of FCU. The power On Built-In-Test is performed for 5 seconds at each on ground power up. It will check the FCU components for dormant failures.
OVERHEAD CONSOLE
LEGEND 1. Flap Drive (Amber). 2. Flap Power (Amber).
The FLAP POWER caution light will illuminate for the following faults: •• Flap asymmetry
#1 STALL STAL T L F L FAI SYST FAIL
•• Flap un-commanded movement
#2 STALL STAL T L F L FAI SYST FAIL
•• Flap position transducer failure •• Flap lever transducer failure •• No hydraulic pressure after selection command •• Select command and no arm signal
1 2
FLAP DRIVE
•• Electrical power loss
PUSHER F L FAI SYST FAIL
PARKIN P G PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING
FUELING ON
MAIN BAT A HOT
•• Servo valve drive failure •• Micro-controller failure (Watch dog intervention)
CAUTION PANEL
• Latch relay open status.
Figure 27-129. Flap System Caution Panel
If the flap system is operated in a degraded mode, then the FLAP DRIVE caution light will illuminate. The caution light will not extinguish until the fault resets itself, or no longer exists.
FOR TRAINING PURPOSES ONLY
27-199
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
MIN
Flap Selector Position R A T I N G
R A T I N G
Flap Selector Lever I
FLIGHT IDLE DISC
I
Figure 27-130. Flap Selector Quadrant
27-200
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Flap Selector Lever/Quadrant Refer to Figure 27-130. Flap Selector Quadrant. The flap selector lever provides the flap selection command. The flap selector lever is located on the right side of the center console. The flap selector lever moves in a detented cam from 0° (fully retracted) through detents at 5°, 10°, 15° to a 35° setting (fully extended). The flap selector lever must stop at each detent in order to be moved to the next detent. The lever has a spring-loaded cam follower, which engages the cam detents at each selected position. The cam follower is released from the detents by a trigger on the lever. The flap selector lever mechanically operates the flap lever transducer, which sends the flap position demand signal to the FCU. An arming switch is located on the flap selector lever. If the lever is in one of the five detented positions and the arming switch is enabled, then the enable signal to the FCU allows the flaps to move to the selected position.
OPERATIONAL TEST OF THE FLAP CONTROL MODULE The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Observe all electrical safety precautions and energize the aircraft electrical systems. •• Observe all safety precautions regarding moving control surfaces. •• Pressurize No.1 hydraulic system. •• Make sure you cannot move the FLAP selector lever until you lift the trigger. •• Move the lever to all the flap selectable positions. • Do the electrical checks in all flap positions refer to TASK 27-50-00-760-801
The flap selector lever is mechanically connected to the rudder restrictor mechanism, which restricts the rudder travel to 12 when the flap lever is in the 0° position.
Flap Lever Transducer Refer to Figure 27-130. Flap Selector Quadrant. The flap lever transducer is a single section, fivewire type RVDT. The RVDT is mechanically operated by the flap selector lever, it receives excitation from the FCU. The RVDT senses the angular position of the flap selector lever. The RVDT sends the position data to the FCU. The FCU will also receives secondary output signals from the flap position sensors and calculates the difference between the two signals. This difference is used by the FCU to move the flaps to the selected position.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-201
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-202 (L7) 28 VDC L ESS BUS
FLAP CONT
5A
A +28 VDC IN B +28 VDC RTN
RW H RW L
U V
A RW H B RW L
RW A RW B RW C
Y Z A-
C RW A E RW B D RW C
ROTARY VARIABLE DIFFERENTIAL TRANSFORMER (RVDT)
LEFT DC CBP
C
4A
WOW ARINC 429
U
114
FLAP MAINT
32-61 A1 PSEU 31-40 A1 IOM #1
T I-
1 3 2
B- FL1 A C- FL1 B D- FL1 C
9 10 NO
RIGHT FLAPS
FL1 H FL1 L SOL VALVE CRET DEHSVH EHSVL
33-11-00
6
D
ARM SW
C D
EDP NOP STBY HYD
PRESS SW PRESS RET
Z Y AB-
A SOL VALVE B RET E EHSVH F EHSVL D PRESS SW C PRESS RET
FLAP POWER UNIT (FPU)
C ARM SWITCH
29-11-00
FLAP LEVER ROTARY VARIABLE DIFFERENTIAL TRANSFORMER (RVDT)
NVM RESET A4
A1
GS1
S5
FLAP 101
MAINTENANCE PANEL
W X
A LW H B LW L
LW A V LW B W LW C X
E LW A C LW B D LW C
LW H LW L
DECK 1 C 102
51
L
ASYFLTRST
FLAP CONTROL UNIT
ROTARY VARIABLE DIFFERENTIAL TRANSFORMER (RVDT)
Figure 27-131. Flap Control System - Electrical Schematic
LEFT FLAPS
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
4 12
DASH 8 Q400
GND/DC DISCRETE O/P
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• Remove hydraulic pressure •• On the maintenance panel do as follows:
OPERATION
•• Set CDS GND MAINT
Refer to Figure 27-131. Flap Control System Electrical Schematic. When the flap lever is moved to a new selected position the FCU receives feedback from the following: •• The flap lever RVDT • A ground from the arming switch. THE FCU outputs signals to, and receives feedback from the following: •• The open solenoid that allows hydraulic pressure to the FPU. The pressure switch signals the FCU that hydraulic pressure is available. •• The Electro Hydraulic Shutoff Valve (EHSV) that is positioned to either extend or retract the flaps by the FCU. As the flaps either extend or retract, the Channel A of the RVDTs at flap actuators No.4 in each wing, feedback flap position to the FCU. When the flaps reach the position required, the FCU removes the signal, to de-energize the solenoid valve, and commands the EHSV to the neutral position. Hydraulic pressure is removed from the FPU and the irreversible flap actuators hold the flaps in the new position.
WING FLAP SYSTEM ELECTRICAL CHECKS
•• Set selector switch to the FLAP position •• Push and hold NVM RESET switch for 2 seconds •• After 10 seconds open FLAPS CONT CB (L7) •• Close the CB (L7) •• After approximately 5 seconds make sure the FLAP POWER and FLAP DRIVE caution lights come ON for approximately 3 seconds •• On ARCDU select FLAPS page •• Make sure there are no PRESENT FAULTS and no faults in FAULT HISTORY •• M a k e s u r e t h a t o n t h e S Y S T E M CALIBRATION page the values are within correct range •• Do the above check in all the other flap lever positions •• R E M E M B E R : M o v e m e n t o f t h e FLAP selector lever with no hydraulic pressure will cause faults to show on the FAULTS page •• Each time you move the FLAPS selector lever you must make the OTHER SYSTEMS and FLAPS page selection on the CDS again •• This will show the new values of the flap lever transducer • Retract the flaps.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Move the flaps to the 35° position
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-203
27 FLIGHT CONTROLS
Normal Flap Operation
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL TEST OF THE WING FLAPS
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. 27 FLIGHT CONTROLS
•• Pressurize No.1 hydraulic system
NOTE A crew member is necessary near the flaps to monitor flap movement.
NOTE Start the test with the flaps at the 0º position •• Obtain visual clearance to lower the flaps •• Make sure the FLAP POWER and FLAP DRIVE caution lights do not come on during the test. •• Select the flap lever to the 5º, 10º, 15º and 35º • • Make sure the flaps move smoothly to the selected positions with no unusual noises. •• Start the flap retraction test at the 350 position and then move to all selected positions. •• Make sure flaps retract smoothly and with no unusual noises.
27-204
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-205
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-52-00 FLAP DRIVE SYSTEM INTRODUCTION
The flap drive system has the following components: •• FPU •• Transmission shafts
27 FLIGHT CONTROLS
The flap drive system is responsible for moving the flaps to new selections and holding that position.
GENERAL
•• Torsion bars •• Flap actuators • Flap tracks.
Refer to Figure 27-132. Flap Drive. The system is electronically controlled and hydro-mechanically operated. It is designed to move the four flap sections together to the position set by the flap selector lever.
No. 1 Flap Track.
No. 1 Flap Actuator.
No. 2 Flap Actuator.
No. 2 Flap Track.
No. 3 Flap Track.
No. 3 Flap Actuator.
No. 4 Flap Track.
Transmission Shafts.
No. 5 Flap Track.
ft525a01.cgm
Figure 27-132. Flap Drive
27-206
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
SYSTEM DESCRIPTION Refer to Figure 27-133. Flap Drive System.
The energized solenoid valve allows the No.1 hydraulic pressure to spool the FPU SOV open. This ports hydraulic pressure to the FPU EHSV.
The FPU turns two torsion bars that turn 16 transmission shafts installed on the wing aft spars. The transmission shafts operate eight irreversible ballscrew flap actuators which drive the four sections of flap. The 4 sections of flap move along 10 tracks located under the wings.
The new flap position from the flap lever transducer is processed by the FCU and converted into a ramp command. The FCU generates the analog EHSV current command to control the hydraulic fluid flow to the FPU hydraulic motor for direction and speed of actuation.
Flap actuation begins when the FCU receives the input signals from the flap lever transducer and the wing flap position transducers. Based on flap lever transducer and flap position transducer signals, the FCU commands the FPU solenoid valve and the FPU EHSV.
At the end of actuation, the FCU de-energizes the FPU solenoid valve. This ports hydraulic system to return closing the FPU SOV.
Left Wing Rear Spar.
Right Torsion Bar.
Flap Power Unit. Left Torsion Bar. Flap Transmission Shaft No. 1. Flap Transmission Shaft No. 2.
Flap Actuator No. 1. Flap Transmission Shaft No. 3. Flap Transmission Shaft No. 4. FW
D Flap Actuator No. 2.
ft204a01.cgm
Figure 27-133. Flap Drive System
FOR TRAINING PURPOSES ONLY
27-207
27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
FLAP POWER UNIT
FW
D
27 FLIGHT CONTROLS Mounting Bracket Solenoid
Pressure Switch Electrical Connector
FW
D
EHSV
Splined Coupling
Pressure Port
Return Port Drain Port ft093a01.cgm
Figure 27-134. Flap Power Unit
27-208
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
Refer to Figure 27-135. Flap Power Unit Schematic.
Flap Power Unit (FPU) Refer to Figure 27-134. Flap Power Unit. The FPU converts No.1 hydraulic system pressure to rotary mechanical power to operate the flap actuators. The FPU is located on the wing aft spar, to the right of the aircraft center line. The FPU has a hydraulic module and a gearbox. The hydraulic module includes the following components:
Hydraulic fluid is sent through a filter and a restrictor at the inlet port. A return line carries the hydraulic fluid back to the system reservoir. A plastic drain line carries any internal fluid leakage from the FPU to an overboard drain. The pressure switch is located downstream of the shutoff valve monitors No.1 hydraulic system pressure. This is a feedback signal to the FCU of solenoid and shutoff valve status. The FCU commands the two-stage EHSV to actuate the flap drive system. The motor is a cartridge construction axial piston. The motor drives the gearbox at rated speed of 7500 RPM.
•• Inlet filter •• Solenoid and shutoff valve •• Pressure switch
The gearbox has a two-stage spur reduction geartrain housed in an aluminum casing. The total speed reduction equals a ratio of 1:10 and output speed is 750 RPM.
•• Two-stage EHSV • Hydraulic motor.
The gearbox is lubricated for life. TORQUE MOTOR
SOLENOID VALVE
HYDRAULIC POWER SUPPLY
RETURN
SERVO VALVE
PRESSURE SWITCH
FLAP EXTEND LINE
INLET FILTER SHUT-OFF VALVE
FLAP RETRACT LINE
HYDRAULIC MOTOR
MOTOR DRAIN fsu74a01a.cgm
Figure 27-135. Flap Power Unit Schematic
FOR TRAINING PURPOSES ONLY
27-209
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Transmission Shafts Refer to Figure 27-136. Flap Transmission Shafts. The transmission shafts transmit the mechanical power generated from the FPU to the eight flap actuators. 27 FLIGHT CONTROLS
The 16 transmission shafts are located along the aft spars of the wings. Nine shafts extend outward from the FPU along the left wing aft spar to the four flap actuators. Seven shafts extend outward from the FPU along the right wing to the four right flap actuators. The shafts are high strength aluminum tube assemblies.
FW
D
NOTE No. 1 Shaft Shown. No. 8 Shaft (LH and RH) Similar.
ft212a01.cgm
Figure 27-136. Flap Transmission Shafts
27-210
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Torsion Bars Refer to Figure 27-137. Flap Torsion Bars. The two torsion bars transmit the high speed, low torque rotating force generated by the FPU to the transmission shafts and flap actuators. 27 FLIGHT CONTROLS
Each torsion bar is an aluminum alloy shaft with external splined connections.
FW
D
Flap Power Unit Assembly
3 1 2
1
D
2
FW
ft085a01.cgm
Figure 27-137. Flap Torsion Bars
FOR TRAINING PURPOSES ONLY
27-211
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Flap Actuators The flap actuators move the flap surfaces to a selected position. They also keep the selected position against the aerodynamic forces acting on the flap surfaces. 27 FLIGHT CONTROLS
There are four flap actuators installed on each wing. The flap actuators are mechanical units designed to a convert high speed, low torque rotary drive to a low speed, high torque linear drive. Each actuator transfers the rotary force to the next actuator. The No.1 and No.2 flap actuators on each wing are identical and operate the inboard flap section. The No.3 and No.4 flap actuators on each wing are constructed slightly different from each other and operate the outboard flap section. Each flap actuator includes the listed components: •• No-back/torque limiter device •• Wormgear
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Observe all hydraulic precautions •• Pressurize No.1 hydraulic system •• Observe all moving control surfaces precautions •• Move the flaps to 35º position •• Remove hydraulic pressure •• With a cloth moistened in approved cleaning solvent, remove contamination around grease fittings. Make sure the area is dry •• Check for excessive amount of grease on the ballscrew shaft (seal failure) •• Clean the ballscrew shaft with lint free cloth
• Ballscrew and ballnut. The no-back/torque limiter device limits the load transferred from the transmission shaft to the flap actuator and supplies irreversibility in both directions of rotation. The no-back device consists of two springs with input and output elements. The spring provides the irreversibility. The torque limiter device trips before reaching loads that would damage the system. The rotary motion of the worm gear disengages the no-back/torque limiter device and is transmitted to the ballnut. The ballnut changes the rotary motion into linear motion of the ballscrew. The ballscrew shaft moves the flap surfaces in the flap tracks forward or aft. The dog stops of the ballnut are machined to provide ice scrapping. Once the movement of the flap surface has stopped the no-back/torque limiter device reengages to supply irreversibility. Maximum flap travel is limited by end stops.
27-212
LUBRICATION OF FLAP BALL SCREW ACTUATORS
•• Install grease dams to the ballnut and ballscrew shaft •• Install and tighten clamp.
CAUTION: DO NOT MIX GREASE FROM DIFFERENT MANUFACTURERS OR SPECIFICATIONS. •• Use a grease gun to pump grease into the fitting until new grease comes out of the vent hole •• Remove the clamps, grease dams and excess grease •• With the grease gun apply more grease to the fittings •• Check for grease leakage at the dynamic seal of the ballnut.
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Flap Tracks
cantilever type, roller carriage tracks attached to the wing rear spar extending aft from the bottom of the wing surface.
Refer to: •• Figure 27-138. Flap Tracks. • Figure 27-140. Flap Carriage. The flap tracks control the incidence angle of the flaps during flap deployment. There are five flap tracks on each wing. Flap tracks No.1 and No.2 are cam type tracks, which support the inboard flap section. Flap track No.1 is located on the side of the fuselage. Flap track No.2 is located on the inboard side of the nacelle. The inboard flaps rollers engage in tracks No.1 and No.2. The rollers give support for the flap and allow for smooth extension and retraction of the flap. Flap tracks No.3, No.4 and No.5 support the outboard flap section. Flap track No.3 is a cam type track and is located on the outboard side of the nacelle. Flap tracks No.4 and No.5 are
The three remaining rollers are used during flight. Sideload rollers prevent lateral movement of the flaps. “0 to 16°” rollers support the flaps to the 15° decent position. “16 to 35°” rollers support the flaps from the 15° decent position to full extension of 35°. In the event of roller failure, the outboard flap is retained to tracks No.3 and No.5 by fail-safe cables, the inboard flap is retained to tracks No.1 and No.2 by fail-safe fittings. Rubbing pads are supplied to prevent excessive side movement of the flaps in the tracks. In the fully retracted position, the leading edge of the flap aligns with the upper flap shroud on the wing to give an aerodynamically smooth wing surface.
5
LEGEND 1. No. 1 Flap Track. 2. No. 2 Flap Track. 3. No. 3 Flap Track. 4. No. 4 Flap Track. 5. No. 5 Flap Track.
4 3 2
1 2 3 4 5
fsq01a01.cgm
Figure 27-138. Flap Tracks
FOR TRAINING PURPOSES ONLY
27-213
27 FLIGHT CONTROLS
The roller carriage assemblies use four different types of rollers to support the flaps. Deadweight rollers are used for support when the aircraft is on the ground.
•• Figure 27-139. No.3 and 4 Flap Rollers.
27 FLIGHT CONTROLS
27-214 LEGEND D
A A
1
8
2
8
7
FWD
3
INB
D D
FW
A fst41a01.cgm
6
A
4
VIEW LOOKING AT OUTBOARD FLAP END
A
Figure 27-139. No.3 and 4 Flap Rollers
5
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
1. Deadweight Roller. 2. 0° Roller. 3. Sideload Roller. 4. 35° Roller. 5. Deadweight Roller. 6. 16° Roller. 7. No. 4 Flap Track Carriage. 8. No. 3 Flap Track Rollers.
FW
2 3
4
5 6
LEGEND 1. Cable. 2. Deadweight Roller. 3. Cable. 4. Serrated Plate. 5. Cable Fitting. 6. 0° Rollers. 7. Cable Fitting. 8. Sideload Roller. 9. 35° Roller. 10. Deadweight Rollers. 11. Serrated Plate. 12. 16° Rollers. 13. No. 5 Flap Track Carriage.
13
7
IN
BD D
FW
8
12 9 11 A
10
27-215
Figure 27-140. Flap Carriage 27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
1
DASH 8 Q400
A
27 FLIGHT CONTROLS
27-216 L FLAP POSITION INDICATION
0 5
R FLAP POSITION INDICATION
FLAP INDICATOR
10
5
10
FPIU
15 35
0
FCECU
ARMING SWITCH
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
FLAP LEVER
35
IFC 1 IFC 2
FLAP LEVER RVDT
FLAP
MAINTENANCE TRAINING MANUAL
DRIVE C & W PANEL FLAP
ARM COMMAND
POWER
WOW PSEU
LANDING GEAR WARNING HORN RIGHT FLAP POSITION FEEDBACK
LEFT FLAP POSITION FEEDBACK PTU
#1 ENG
FCU
HYD PUMP
ON > 5° STBY HYD PUMP
SUPPLY HYDRAULIC POWER
#9
#8
#7
#4 FLAP POSITION DUAL RVDT
fs794a01.cgm
#6 #3
LEFT OUTBOARD FLAP
FPU
RETURN
TRANSMISSION SHAFTS
#5
#4
#3
#2
#2
ACTUATORS
#1
#3
#4
LEFT INBOARD FLAP
RIGHT INBOARD FLAP TORSION BAR
#5 #2
#1
#1
TORSION BAR
Figure 27-141. Wing Flap System
#6
#7
#8
#9
#3
#4
RIGHT OUTBOARD FLAP
FLAP POSITION DUAL RVDT
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-53-00 FLAP POSITION INDICATION
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The flap position indication system supplies flap position data to the flight compartment indicator and interfaces with other aircraft systems.
GENERAL Refer to Figure 27-141. Wing Flap System. This system supplies data to the: •• FCU •• FCECU and • IFCs. The data is used for flap position monitoring and recording. The flap position indication system is comprised of the following components: •• Flap Position Indication Unit (FPIU) • Flap position transducer.
FOR TRAINING PURPOSES ONLY
27-217
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION Refer to Figure 27-142. Flap Position Indication Unit. The FPIU is located below the cabin floor. The two flap position transducers are installed on the outboard flap actuators. 27 FLIGHT CONTROLS
The FPIU sends RVDT analog signals to the Flight Data Processing System (FDPS) in IFC1 and 2. The FDPS then converts these analog signals into digital signals for display on MFD2 as flap degrees of indication. The FCU uses RVDT channel A signals with flap position command signals to calculate and monitor the speed and direction of the flaps to the new position.
D
FW
UNDER FLOOR AREA
Flap Position Indication Unit
Mounting Bracket
D
FW
Electrical Connectors
ft239a01.cgm
Figure 27-142. Flap Position Indication Unit
27-218
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Flap Position Indication Unit (FPIU) Refer to Figure 27-143. Flap Position Indication Unit Block Diagram. The FPIU supplies flap position data to the MFD indicator and interfaces with other aircraft systems. The FPIU is divided into two separate and independent analog channels (Left and Right) on a single printed circuit board. Each channel in the FPIU performs the following functions: •• Gives flap position indication to the IFC and the FCECU •• Interfaces with, and supplies electrical excitation to the flap position RVDT
The FPIU sends the analog position signals to IFC1-2 for Stall Protection Modules (SPM) 1-2 to calculate the stall angle. The FPIU sends signals to the FCECU for scheduling default values when airspeed is not valid. This FPIU data is also used for flap compensation trim to the elevator. The FPIU sends discrete signals to IFC1-2 and FCECU for flap position health. The flap indication system FPIU converts RVDT analog position signals of > 7.5 and > 25 into digital format and sends these signals to the ADU 1-2. The ADU 1-2 need to correct for the errors created to static air pressure at > 7.5 and > 25 flap. The ADU 1-2 use these signals for corrections to airspeed and altitude.
•• Demodulates the signal from the flap position RVDT •• Performs an analog monitor of its applicable RVDT • Supplies signals to the SPM 1-2 and ADU 1-2.
Left Flap Position
IFC 1
IFC 2
ADU 1
RVDT Left B
Channel 2
Right Flap Position
Left Flap Position
Right Flap Position
Left Position Healthy
Right Position Healthy
Left Flap Position FCECU Left
Channel 1
Left Position Healthy
FPIU
IFC 2
Right Flap Position Right Position Healthy
Left Flap > 7.5º
Right Flap > 7.5º
Left Flap > 25º
Right Flap > 25º
Left Flap Position
IFC 1
Right Flap Position
FCECU Right
ADU 2
RVDT Right B
Figure 27-143. Flap Position Indication Unit Block Diagram fs0c3a01.cgm
FOR TRAINING PURPOSES ONLY
27-219
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Flap Position Transducer Refer to Figure 27-144. Flap Position Transducer. The flap position transducers provide the actual flap position to the FPIU and the FCU.
27 FLIGHT CONTROLS
The two flap position transducers are installed on the outboard flap actuator of each wing. Each flap position transducer is a two section RVDT consisting of channel A and B. Channel A is electrically supplied by the FCU and supplies flap position feedback to the flap control loop. Channel B is electrically supplied by the FPIU and supplies flap position data for indication purposes.
NOTE
A
Right side shown. Left side similar. B
D
FW
A
OUTBOARD FLAP ACTUATOR ASSEMBLY
1 2 3
C
LEGEND
BD
T OU
1. Red Dot On Transducer Shaft. 2. 0° Flaps. 3. Red Band On Transducer Housing. 4. 35° Flaps.
4 B
FLAP POSITION TRANSDUCER
C
ftc01a01.cgm
Figure 27-144. Flap Position Transducer
27-220
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Refer to Figure 27-145. Flap Position Indication/Multi-Function Display.
27 FLIGHT CONTROLS
The MFD2 FLAP DEG indicator displays flap angle in degrees of incidence as an analog indication. The gauge scale has the following degree indication positions; 0°, 5°, 10°, 15°, and 35°. The FDPS displays an arrow indicator to the appropriate degree of flap incidence as signalled by the FPIU.
ELECTRICAL
MAIN AUX STBY
00 00 00
ESS MAIN SEC
PSI x 1000
Flap Position Inidication
Figure 27-145. Flap Position Indication/Multi-Function Display
FOR TRAINING PURPOSES ONLY
27-221
27 FLIGHT CONTROLS
27-222 2A
FLAP POS IND R
D 28VL2 E 28VL2RET
RIGHT DC CBP
RIGHT WING
IFC1R F IFC1RET G
67 66
SPM #1/IOM #1
IFC2R H IFC2RRET J
56 55
SPM #2/IOM #2
RFPHEAL1 M
57
SPM #2/IOM #2
MAIN +1. 00
U RWMH V RWML
RWMA H RWMB J RWMC K
W RWMA X RWMB Y RWMC
LEFT WING
LWMH F LWML G
U LWMH V LWML
LWMA J LWMB H LWMC K
W LWMA X LWMB Y LWMC
- . 34
+22
STBY
- . 34
+22
L
31-41 A2 IOP #2 IFC1L F IFC1LRET G
68 67
SPM #1/IOM #1
IFC2L H IFC2LRET J
57 56
SPM #2/IOM #2
LFPHEAL1 M
58
SPM 1/IOM 2/IOM 1
ARINC A429 MFD 2
HI 315 LO 314
DC BUS VOLT R
ESS 28. 1
28. 1
MAIN 28. 1
28. 1
SEC 28. 1
28. 1
HI LO
C 115
. 06
. 06
+1. 00
AC GEN 1 VOLT LOAD
TRU
A 115
. 06
LOAD 2
B 115
. 06
C 115
. 06
1 +1. 00
+1. 00
ARINC A429 MFD 2
FLAP DEG
SPOILERS
0 5 10 LO
(M7)
RUD
LI
RI
L ELEV
HYD PRESS PSI PK BRK STBY 1 2 3000
LEFT DC CBP
. 06 . 06
AVIONICS RACK HIRF ENCLOSURE
ROTARY VARIABLE DIFFERENTIAL TRANSFORMER (RVDT)
FLAP POS IND L
DC GEN 1 LOAD 2
A 115 B 115
31-41 A1 IOP #1
35
2A
AC GEN 1 VOLT LOAD
+1. 00
+22
AUX
HI 315 LO 314
APU GEN LOAD
0
3000
3000
3
1 0
HYD QTY % 2 3
100
100
CO-PILOT MFD PAGE 1 REFER ALSO TO CO-PILOT MFD PAGE 2 D 28VL1 E 28VL1RET FCELFT N FCELRET P
51 61
(HI) FLAP POS L (LO)
LFPHEAL2 R
62
FLAP HEALTHY L
FCERGT N FCERRET P
51 61
HI LO
RFPHEAL2 R
62
FLAP HEALTHY R
FLAP POS R
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU) FLAP POSITION INDICATION UNIT (FPIU)
Figure 27-146. Flap Position Indication - Electrical Schematic
RO
R ELEV
100
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RWMH F RWML G
POWER
BATT LOAD ¡ C
ARINC A429 MFD 2
ROTARY VARIABLE DIFFERENTIAL TRANSFORMER (RVDT)
+28 VDC L ESS BUS
AC EXT
POWER
DASH 8 Q400
+28 VDC R ESS BUS
ELECTRICAL
DC EXT
(F7)
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATION
NOTES
Normal Flap Position Indication Operation Refer to Figure 27-146. Flap Position Indication - Electrical Schematic.
FOR TRAINING PURPOSES ONLY
27 FLIGHT CONTROLS
The FPIU sends excitation current to, and receives feedback from the RVDT’s at No.4 flap actuator on each wing. The right side signal is sent to the MFD for the flap position display. The left side is used if the right side fails.
27-223
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-54-00 FLAP SURFACES
NOTES
Refer to Figure 27-147. Flaps.
27 FLIGHT CONTROLS
The flaps are single slotted, high lift Fowler type flap. The inboard flaps have a constant chord cross-section of approximately 39% of the total wing chord. The outboard flaps have a tapered chord cross-section of approximately 39% of the total wing chord. In the fully retracted position, the flap leading edge aligns with the wing to give an aerodynamically surface.
LEGEND 1. Outboard Flap. 2. Inboard Flap.
2
1 NOTE Left side shown. Right side similar. fs525a01.cgm
Figure 27-147. Flaps
27-224
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
General •• Obey all the electrical/electronic safety precautions. •• Energize the aircraft electrical system. • Put the aircraft in the weight-on-wheels condition.
Procedure •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “up” position and make sure the CDS GND MAINT light comes on. On the CDS Maintenance panel, turn the system selector rotary switch to the FLAP position. Make sure the system selector LED is on. Push the NVM RESET (Guarded) switch. On the FLAP DRIVE SYSTEM PRESENT FAULTS page, make sure the CDS shows the NO FAULTS REPORTED message. •• On the CDS Maintenance panel, turn the system selector rotary switch to the OFF position. Make sure the system selector LED is off. •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “down” position and make sure the CDS GND MAINT light goes off. •• De-energize the electrical system. •• Remove all tools, equipment, and unwanted materials from the work area.
ON
#1 NVM RESET
ECS AUTO FAIL
OFF
FLAP PROP DEICE 2
CPC ECS
FLT CTL
2/7 ECS PRESENT FLT R CH 1/3 FLAP DRIVE SYSTEM
PROP DEICE CAL
CDS GND MAINT
PROP DEICE 1 AFR DEICE
PAA TEST
#2 PSEU
PSS MAINT
PSEU OPER
28 VDC
PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV NO FAULTS REPORTED XXXX - APU DIFF PR XXXX - CAB ACM XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
Figure 27-148. Task 45-00-27-743-802 CDS System Pages Indications
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-225
27 FLIGHT CONTROLS
ERASE THE DATA FROM THE CENTRAL DIAGNOSTIC SYSTEM (CDS) - FLAPS SYSTEM (FLAPS)
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
ERASE THE DATA FROM THE CENTRAL DIAGNOSTIC SYSTEM (CDS) FLIGHT CONTROL SYSTEM (FCS)
27 FLIGHT CONTROLS
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
General •• Obey all the electrical/electronic safety precautions. •• Energize the aircraft electrical system. • Put the aircraft in the weight-on-wheels condition.
the FLT CTL position. Make sure the system selector LED is on. Push the NVM RESET (Guarded) switch. On the FCECU PRESENT FAULTS page, make sure the CDS shows the NO FAULT REPORTED message. •• On the CDS Maintenance panel, turn the system selector rotary switch to the OFF position. Make sure the system selector LED is off. •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “down” position and make sure the CDS GND MAINT light goes off. •• De-energize the electrical system. •• Remove all tools, equipment, and unwanted materials from the work area.
Procedure •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “up” position and make sure the CDS GND MAINT light comes on. On the CDS Maintenance panel, turn the system selector rotary switch to
ON
#1 NVM RESET
ECS AUTO FAIL
OFF
FLAP PROP DEICE 2
CPC ECS
FLT CTL
FCECU SYS FAULTS PRESENT FAULTS
PROP DEICE CAL
CDS GND MAINT
PAA TEST
1/4
#2 PSEU
PSS MAINT
PSEU OPER
NO FAULTS REPORTED
28 VDC
PROP DEICE 1 AFR DEICE
Figure 27-149. Task 45-00-27-743-801 CDS System Pages Indications
27-226
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
RETRIEVAL OF DATA FROM THE CENTRAL DIAGNOSTIC SYSTEM (CDS) FLAPS SYSTEM (FLAPS) The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
The CDS main menu is displayed as follows: •• Push the LSK 2L to access the OTHER SYSTEM menu. Page 1 of the CDS OTHER SYSTEMS menu is displayed. Push the NEXT key to access page 2 of 2. Push the LSK 1L to access the FLAP DRIVE SYSTEM PRESENT FAULTS page, 1 of 3. If no faults are reported, the CDS will show a NO FAULTS REPORTED message.
General •• Obey all the electrical/electronic safety precautions •• Energize the aircraft electrical system • Put the aircraft in the weight-on-wheels condition.
Procedure •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “up” position and make sure the CDS GND MAINT light comes on. •• Set either ARCDU to the ON position and push the MAINT key.
2/7 ECS OTHER PRESENT FLT R SYSTEM 1 CH 1/2
< EMU XXXX - ECU DIG CH 2 ANTI-SKID > XXXX - R NAPRSOV XXXX - APU DIFF PR < FCS- CAB ACMICE PROTECTION > XXXX XXXX - CAB OLT MISCMP XXXX - CAB TSOV < ECS APU > XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP < TMCU1 XXXX - SEC OLT MISCMP TMCU2 > XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP I
2/7 ECS OTHER PRESENT FLT R SYSTEM 2 CH 2/2
< FLAPS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV XXXX - APU DIFF PR < CABIN PRESS XXXX - CAB ACM CONTROL XXXX - CAB OLT MISCMP XXXX - CAB TSOV < AUXILIARY XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
CDS < AVIONICS
I
2/7 ECS PRESENT FLT R CH 1/ FLAP DRIVE SYSTEM
< OTHER SYSTEMS
PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV NO FAULTS REPORTED XXXX - APU DIFF PR XXXX - CAB ACM
< AVIONICS DATA
XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP I
Figure 27-150. Task 45-00-27-742-802 CDS System Pages Indications (1 of 2)
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-227
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
•• If faults are recorded the menu shows the present list of faults in the order of newest fault at the top, to the oldest fault at the bottom. Push the NEXT key on the ARCDU to get to the FLAP DRIVE SYSTEM FAULT HISTORY page, 2 of 3. If no faults are reported, the CDS will show a NO FAULT REPORTED message. If faults are recorded the menu shows the list of faults in the order of newest fault at the top, to the oldest fault at the bottom. Push the NEXT key to show the FLAP DRIVE SYSTEM, SYSTEM CALIBRATION page 3 of 3. The number below the TRANSDUCERS indicate the angular position of the flap in degrees and the number associated with the FLAP LEVER TRANSDUCER indicate the angular position of the flap lever in degrees.
•• On the maintenance panel, set the CDS GND MAINT toggle switch to the “down” position and make sure the CDS GND MAINT light goes off. •• De-energize the electrical system. •• Remove all tools, equipment, and unwanted materials from the work area.
2/7 ECS PRESENT FLT R CH 1/3 FLAP DRIVE SYSTEM
PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV UNCOMMANDED MOVEMENT XXXX - APU DIFF PR XXXX - CAB ACM XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
I
2/7 ECS PRESENT FLT R CH 3/3 FLAP DRIVE SYSTEM
2/7 ECS PRESENT FLT R CH 2/3 FLAP DRIVE SYSTEM
PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV NO FAULTS REPORTED XXXX - APU DIFF PR XXXX - CAB ACM XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
SYSTEM CALIBRATION XXXX - ECU DIG CH RANGE OF 2SIGNALS XXXX - R NAPRSOV - 1 TO 11 XXXX - APU DIFF PR LEFT -POSITION XXXX CAB ACM TRANSDUCER 72 XXXX - CAB OLT MISCMP XXXX - CAB TSOV RIGHT- ECU POSITION TRANSDUCER XXXX ANLG CH 2 7 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP FLAP LEVER TRANSDUCER XXXX - SEC OLT MISCMP XXXX - CAB CMP -OLT TMP XXXX - CAB MAN OLT TMP I
Figure 27-151. Task 45-00-27-742-802 CDS System Pages Indications (2 of 2)
27-228
FOR TRAINING PURPOSES ONLY
I
DASH 8 Q400
RETRIEVAL OF DATA FROM THE CENTRAL DIAGNOSTIC SYSTEM (CDS) FLIGHT CONTROL SYSTEM (FCS) The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
•• Push the LSK 2L to access the OTHER SYSTEM menu. Page 1 of the CDS OTHER SYSTEMS menu is displayed. Push the LSK 2L to access page 1 of 4, the FCS list of recorded faults. If no faults are reported, the CDS will show a NO PRESENT FAULTS message. If faults are recorded the menu shows the present list of faults in the order of oldest fault at the top, to the newest fault at the bottom.
GENERAL •• Obey all the electrical/electronic safety precautions. •• Energize the aircraft electrical system. • Put the aircraft in the weight-on-wheels condition.
PROCEDURE •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “up” position and make sure the CDS GND MAINT light comes on. • O n t h e c e n t e r c o n s o l e s e t e i t h e r ARCDU to the ON position and push the MAINT key. The CDS main menu is displayed as follows:
FCECU SYS FAULTS PRESENT FAULTS
1/
2/7 ECS OTHER PRESENT FLT R SYSTEM 1 CH 1/2
< EMU XXXX - ECU DIG CH 2 ANTI-SKID > XXXX - R NAPRSOV XXXX - APU DIFF PR < FCS- CAB ACMICE PROTECTION > XXXX XXXX - CAB OLT MISCMP XXXX - CAB TSOV < ECS APU > XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP < TMCU1 XXXX - SEC OLT MISCMP TMCU2 > XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP I
2/7 ECS PRESENT FLT R CH 1/ FCECU FAULTS PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV XXXX - APU DIFF PR XXXX - CAB ACM NO FAULTS REPORTED XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP I
2/7 ECS PRESENT FLT R CH 1/
NO FAULTS REPORTED
FCECU FAULTS PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV PIL TRIM SW FAILURE XXXX - APU DIFF PR XXXX - CAB ACM
XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP I
Figure 27-152. Task 45-00-27-742-801 CDS System Pages Indications (1 of 2)
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-229
27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
•• Push the NEXT key on the ARCDU to get to the FCECU SYS FAULTS 2 of 4 FAULT HISTORY. If no faults are reported, the CDS will show a NO FAULTS REPORTED message. If faults are recorded the menu shows the list of faults in the order of newest fault at the top, to the oldest fault at the bottom. A maximum number of 10 faults can be displayed. Push the NEXT key on the ARCDU to get to the FCECU ANLG I/O STATUS 3 of 4. Push the NEXT key on the ARCDU to get to the FCECU ANLG I/O STATUS 4 of 4.
•• On the maintenance panel, set the CDS GND MAINT toggle switch to the “down” position and make sure the CDS GND MAINT light goes off. •• De-energize the electrical system. •• Remove all tools, equipment, and unwanted materials from the work area.
2/7 ECSS PRESENT FCECU S FAULTS FLT R CH 2/ FAULT HISTOR XXXX - ECU DIG CH 2 XXXX - R NAPRSOV IFC FAILURE XXXX - APU DIFF PR IFC FAILURE XXXX - CAB ACM ADC FAILURE ADC FAILURE XXXX - CAB OLT MISCMP ADC FAILURE XXXX - CAB TSOV XXXX - ECU ANLG CH 2 ADC FAILURE XXXX - R HP BLD SW ADC FAILURE XXXX - COMP TMP MISCMP ADC FAILURE XXXX - SEC OLT MISCMP ADC FAILURE XXXX - CABDCMP OLT TMP FCECU XXXX - CAB MAN OLT TMP I
ECS PRESENT R CH 2/7 FCECU ANLG I OFLT STATUS /
ECS PRESENT R CH 2/7 FCECU ANLG I OFLT STATUS / XXXX - ECU DIG CH 2 XXXX - R NAPRSOV L DELTA PRESS 2 7 PSI XXXX - APU DIFF PR R DELTA PRESS PSI XXXX - CAB ACM L ELEV DEG R ELEV XXXX - CAB OLT MISCMP - 7 DEG L PFEEL 7 IN XXXX - CAB TSOV R PFEEL 7 2 IN XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW RUDDER 7 DE G XXXX - COMP TMP MISCMP XXXX - SEC OLT DO NOT RIG A/CMISCMP WITH DATA XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
XXXX - ECU DIG CH 2 XXXX - R NAPRSOV L IB SPOIL XXXX - APU DIFF PR R IB SPOIL XXXX CAB ACM L OB -SPOIL R OB-SPOIL XXXX CAB OLT MISCMP L PTRIM XXXX - CAB TSOV R PTRIM XXXX - ECU ANLG CH 2 XXXX R HP BLD SW AILERON XXXX - COMP TMP MISCMP XXXX - SEC OLT DO NOT RIG A/CMISCMP WITH DATA XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
2 DEG DE G 2 DEG 2 DEG DEG DEG 2 DEG
I
Figure 27-153. Task 45-00-27-742-801 CDS System Pages Indications (2 of 2)
27-230
FOR TRAINING PURPOSES ONLY
I
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-231
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
Figure 27-154. Flight Control Electronic Control Unit
27-232
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-00-01 FLIGHT CONTROL ELECTRONIC CONTROL UNIT
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The FCECU receives electronic inputs and supplies electronic outputs for all of the primary and secondary flight control systems.
GENERAL The FCECU is a single unit divided into two channels, (referred to as the left and right channels). The left and right channels receive inputs from the pilot and/or co-pilot flight controls. The two channels function separately from each other throughout the system. The FCECU channels communicate with each other on a cross communication data link.
SYSTEM DESCRIPTION Refer to Figure 27-154. Fl i ght Co ntr ol Electronic Control Unit. The FCECU is located under the passenger cabin floor, forward of the rotor burst zone. Channel 1 (left) is powered by the 28 VDC left essential bus through the FCS ECU 1 circuit breaker (M3). Channel 2 (right) is powered by the 28 VDC right essential bus through the FCS ECU 2 circuit breaker (L6). The FCECU is an analog control unit with the digital hardware for data processing, logic control and logic monitoring. Each channel is partitioned into a command path and a monitor path.
FOR TRAINING PURPOSES ONLY
27-233
27 FLIGHT CONTROLS
27-234 Caution Lights ELEVATOR FEEL
ELEVATOR ASYMMETRY
ROLL SPLR INBD GND
#1 RUD HYD
PITCH TRIM
ROLL SPLR INBD HYD RUDDER SOV
PLA Left
Rudder Hinge Moment Limiter Lower PCU
Flap Posn Left FPIU
P Feel Actuator Left
FLIGHT CONTROL ELECTRONIC CONTROL UNIT CHANNEL #1 (LEFT)
ADU #1 AHRS #1 MFD IFC #1 A/P Trim
P Trim Actuator Active Left STBY Right I/B Spoiler L I/B Spoiler R Elevator L Aileron R
FDR Pilot Trim Switches
PSEU WOW 1
Pitch Disconnect Relay
ELEVATOR TRIM SHUTOFF (Pilot/Co-Pilot) Pushoff Switchlights
RUD 1
ROLL INBD Advisory Lights
fs793a01.cgm
Figure 27-155. FCECU/Left Channel Block Diagram
LVDTS
Inboard Spoiler Lift Dump Solenoid Valve Inboard Spoiler Lift Dump Solenoid Valve
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
28 VDC
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-155. FCECU/Left Channel Block Diagram. The FCECU functions with the flight control systems listed below:
•• Increases the pressure to the operating rudder PCU if one of the rudder PCU fails or is depressurized • Sends signals to the rudder caution lights to indicate system malfunctions.
•• Aileron Control System 27 FLIGHT CONTROLS
•• Rudder Control System •• Elevator Control System •• Flap Control System • Spoiler Control System.
Aileron Control System The FCECU does the following functions: •• Supplies electrical excitation of the LVDT attached to the right aileron. • Receives right aileron position data from the LVDT. The FCECU transmits this position data on an ARINC 429 data bus to the FDR through the IFC.
Rudder Control System The FCECU carries out the functions listed below: •• Supplies electrical excitation of the rudder position LVDT •• Receives position data from the rudder LVDT. The FCECU transmits this position to the FDR and EFIS •• Limits the rudder hinge movement by regulating the pressure in the rudder PCU according to aircraft speed • • Monitors the airspeed signals for a mismatch condition and sets the rudder PCU regulated pressure to a default mode •• Monitors the regulated pressure in the rudder PCU for discrepancies and depressurizes the PCU if it is faulty •• Depressurizes the relevant rudder PCU if either of the RUD1 or RUD2 PUSH OFF switchlight is pushed
FOR TRAINING PURPOSES ONLY
27-235
27 FLIGHT CONTROLS
27-236
Caution Lights ROLL SPLR OUTBD GRD
ROLL SPLR OUTBD HYD
RUD CNTRL
SPLR OUTBD
#2 RUD HYD
RUDDER SOV Rudder Hinge Moment Limiter Upper PCU
PLA Right
ADU #2 AHRS #2
FLIGHT CONTROL ELECTRONIC CONTROL UNIT CHANNEL #2 (RIGHT)
IFC #2 Co-pilot Trim S/ws
P Feel Actuator Right P Trim Actuator Act/Stby Right EXCITATION
POSITION DATA
O/B Spoiler L O/B Spoiler R Elevator R Rudder
LVDTS
Flight/Taxi Switch Maintenance Panel
TO LEFT CHANNEL
PSEU WOW 2
Outboard Spoiler SOV
RUD 2
ROLL OUTBD (Spoiler)
Pushoff Switchlights
Advisory Lights
fs792a01.cgm
Figure 27-156. FCECU/Right Channel Block Diagram
Outboard Spoiler Lift Dump SOV Outboard Spoiler Lift Dump SOV
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
Flap Posn Right FPIU
DASH 8 Q400
28 VDC
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Elevator Control System
NOTES
Refer to Figure 27-156. FCECU/Right Channel Block Diagram. The FCECU carries out the following functions:
27 FLIGHT CONTROLS
•• Supplies electrical excitation to the left and right elevator position LVDT • • Receives position data from the left and right elevator LVDT. The FCECU transmits this position data to the FDR and EFIS •• Changes the elevator feel forces on the control columns as a function of airspeed and acceleration •• Changes manual pitch trim rate as a function of airspeed •• Supplies automatic pitch trim when in the autopilot mode or when the flaps are extended or retracted (15° to 35°) •• Prioritizes all valid pitch trim commands in the following order: pilot, co-pilot, and then autopilot •• Monitors pitch trim actuator failures and sends a signal to the PITCH TRIM caution light and the ELEVATOR TRIM SHUTOFF switchlights • • Supplies elevator trim position to the warning tone generator in the IFC. An aural warning on takeoff is produced if the elevator trim is outside the takeoff range •• Monitors elevator asymmetry and supplies a signal to the ELEVATOR ASYMMETRY caution light •• Monitors elevator feel actuator failures and supplies a signal to the ELEVATOR FEEL caution light • Monitors the airspeed and acceleration signals for a mismatch condition and sets the pitch trim and elevator feel to a default mode.
FOR TRAINING PURPOSES ONLY
27-237
27 FLIGHT CONTROLS
27-238
PITCH TRIM
MAINTENANCE INTERFACE TO CDS
SPOILER LIFT-DUMP FCECU
BUILT-IN-TEST (BIT)
OUTBOARD SPOILER LOCKOUT
FLIGHT CONTROL SYSTEM CAUTION AND WARNING
AURAL TAKE-OFF WARNING
FLIGHT CONTROL SURFACE POSITION fss56a01.cgm
Figure 27-157. FCECU Block Diagram
MAINTENANCE TRAINING MANUAL
ELEVATOR FEEL
DASH 8 Q400
FOR TRAINING PURPOSES ONLY
RUDDER HINGE MOMENT LIMITING (HML)
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Flap Control System Refer to Figure 27-157. FCECU Block Diagram. The FCECU carries out the listed function:
•• Flight Control System caution and warning signals •• Built-In-Test • Maintenance interface to CDS.
27 FLIGHT CONTROLS
• Receives left and right flap position data from the FPIU for scheduling default values when airspeed is not valid.
Spoiler Control System The FCECU performs the listed functions: •• Locks out the outboard spoilers for airspeeds greater than 170 kt (315 km/h) •• Sends the high side signal to the inboard and outboard spoilers lift dump valves to dump the lift from the wings when the aircraft lands •• Sends a signal to the spoiler caution lights to indicate system malfunctions •• Supplies electrical excitation to all the spoiler position LVDT •• Receives position data from all the spoiler LVDT. The FCECU transmits this position data to the FDR and EFIS •• Sends a low side discrete to the magnetic coil of the FLIGHT/TAXI switch • Sends a signal to the spoiler advisory lights. Refer to Figure 27-157. FCECU Block Diagram. The FCECU functions of the flight control systems (FCS) are: •• Rudder HML •• Pitch trim •• Elevator feel •• Spoiler Lift-dump •• Outboard spoiler lockout •• Aural take-off warning •• Flight control surface position reporting to the FDR and the PFCSI through IFC
FOR TRAINING PURPOSES ONLY
27-239
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OVERHEAD CONSOLE
27 FLIGHT CONTROLS Elevator Asymmetry Elevator Feel
Roll Spoiler Inboard Ground.
Pitch Trim
Roll Spoiler Outboard Ground.
ROLL SPLR INBD GND
PIT H TRIM
STALL #1 STAL T L FAIL SYST FAI F L STALL #2 STAL T L FAIL SYST FAI F L
ROLL SPLR INBD HYD
#2 HYD FLUID HOT
FLAP DRIVE
PUSHER FAIL SYST FAI F L
PARKING PARKIN P G BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP
EMER LT L S LTS DISARMED
NOSE STEERING
ABIN PRESS
MAIN BAT A HOT
CAUTION PANEL
Figure 27-158. Caution and Warning Panel
27-240
FOR TRAINING PURPOSES ONLY
FUELING ON
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Caution Lights Refer to Figure 27-158. Caution and Warning Panel. The FCECU sends signals to the Caution and Warning panel to illuminate the caution lights that follow:
ELEVATOR FEEL •• Left or Right Pitch Feel Actuator fails, or •• Airspeed No.1 and Airspeed No.2 disagree by +/- 17 kts., or
ROLL SPLR INBD GND •• If the FCECU senses a loss of lift dump valve function, or •• If the lift dump valves are operated but the spoiler panels fail to extend after landing, or • If the spoiler panels extend when the FCECU carries out the lift dump BIT, with the FLIGHT/TAXI switch set to TAXI.
ROLL SPLR OUTBD GND •• If the FCECU senses a loss of lift dump valve function, or
• Acceleration No.1 and Acceleration No.2 disagree by +/- 0.35g for > 6 seconds.
•• If the lift dump valves are operated but the spoiler panels fail to extend after landing, or
PITCH TRIM •• One pitch trim motor, or its control card fails, or
• If the spoiler panels extend when the FCECU carries out the lift dump BIT, with the FLIGHT/TAXI switch set to TAXI.
•• Elevator trim shutoff switch light pressed, or •• Airspeed No.1 disagrees with Airspeed No.2 by +/- 17 kts., or Pitch trim input commands disagree a/c on ground.
ELEVATOR ASYMMETRY •• 4.0 ± 1.6° for airspeed > 215 kts., or • 6.0 ± 1.6° for airspeed < 215 kts.
FOR TRAINING PURPOSES ONLY
27-241
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OVERHEAD CONSOLE
27 FLIGHT CONTROLS Rudder Control
Spoiler Outboard
#1 Rudder Hydraulic Pressure
Roll Spoiler Outboard Hydraulic
Roll Spoiler Inboard Hydraulic
#2 Rudder Hydraulic Pressure
ROLL SPLR INBD GND
STALL #1 STAL T L FAIL SYST FAI F L STALL #2 STAL T L FAIL SYST FAI F L
ROLL SPLR INBD HYD
#2 HYD FLUID HOT
FLAP DRIVE
PUSHER FAIL SYST FAI F L
PARKING PARKIN P G BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING MAIN BAT A HOT
Figure 27-159. Caution and Warning Panel
27-242
FOR TRAINING PURPOSES ONLY
FUELING ON
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-159. Caution and Warning Panel.
NOTES
The FCECU sends signals to the Caution and Warning panel to turn on the caution lights that follow: 27 FLIGHT CONTROLS
SPLR OUTBD •• If the FCECU fails to lockout the outboard spoilers and airspeed is > 185 knots, or •• If the FCECU locks out the outboard spoilers and airspeed is < 150 knots, or •• Airspeed No.1 disagrees with Airspeed No.2 by +/- 17 kts
ROLL SPLR INBD HYD •• No.1 hydraulic system pressure is < 900 psi. • Roll spoiler cable breaks
ROLL SPLR OUTBD HYD •• No.2 hydraulic system pressure is < 900 psi and airspeed is < 165 knots, or •• If FCECU detects the outboard spoilers are inadvertently locked out and airspeed is < 165 knots • Roll spoiler cable breaks
No.1 RUD HYD •• No.1 hydraulic system pressure is < 350+/-50 psi. No.2 RUD HYD •• No.2 hydraulic system pressure is < 350+/-50 psi. RUD CTRL •• Airspeed No.1 and Airspeed No.2 disagree by +/- 17 kts., or •• F C E C U l o s e s i t s a b i l i t y t o l i m i t hydraulic pressure, or • Both hydraulic systems fail.
FOR TRAINING PURPOSES ONLY
27-243
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
A
LEGEND 1. Roll Outboard Annunciator Light. 2. Roll Inboard Annunciator Light.
GLARESHIELD PANEL
1
NOTE Left side shown. Right side similar.
SPOILERS
STI P SHER SH T O
LIGHT
ENGINE IRE
AP DISENG
ROLL IN D
TA I
INHI IT
ELE ATOR TRI SH T O
AEI
TERRAIN INHI IT
A RNING
PRESS TO RESET
2 fsz09a02.cgm
A
Figure 27-160. Roll Spoiler Advisory Lights
27-244
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Advisory Lights
NOTES
Refer to Figure 27-160. Roll Spoiler Advisory Lights. The FCECU sends signals to illuminate the following advisory lights: 27 FLIGHT CONTROLS
ROLL OUTBD (spoiler) • Both outboard spoiler LVDT > 65 ROLL INBD (spoiler). • Both inboard spoiler LVDT > 65
OPERATIONAL TEST OF THE FCECU The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Open then close the FCS ECU 1 and FCS ECU 2 CB's to let the system do a BIT •• M a k e s u r e t h e C D S s h o w s N O PRESENT FAULTS •• Apply pressure to No.1 and No.2 hydraulic systems •• By moving the controls, check the PFCS for full movement of the following: °° Inboard and outboard roll spoilers °° Left and right elevators °° Rudder °° Check flap movement on MFD No.2 °° Do an operational test of the pitch trim system °° Do an operational test of the ground spoiler system °° Do an operational test of the roll spoiler SPLR1 and SPLR2 PUSH OFF switchlights °° Remove hydraulic pressure.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-245
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
MAINTENANCE CONSIDERATION
Interfaces The FCECU has these interfaces:
System Test
27 FLIGHT CONTROLS
SOURCE
PARAMETER
Power-Up Built-In-Test (PBIT)
Air Data Units
Airspeed
The FCECU does a Power-Up Built-In-Test (PBIT) to verify operation of the hardware monitors. Any errors found during PBIT will be annunciated by the caution and warning system. If PBIT is interrupted, the PBIT will then be cancelled and, no faults stored. PBIT is commanded if both WOW inputs are active and both PLA microswitches indicate < PLA 47.
Attitude Heading And Reference System
Acceleration
Flap Position Indication Unit
Flap Position
Flap Control Unit
Flaps In Motion Signal
Manual Pitch Trim Switches
Pilot/Co-pilot Pitch Trim Command
Pitch Trim Disconnect Relay
Engaged/Disengaged Signal
Flight Guidance Modules
Autopilot Pitch Trim And Flap Auto Trim Commands
Power Lever Angle Microswitches
Flight Idle +12 Signal
Flight/Taxi Switch
Flight Or Taxi Mode Signals
Lvdt
Flight Control Surface Position
Maintenance Panel
Flight Control System Failures
Rudder Pcu Pressure Sensors
Rudder Pcu Pressure
Pseu
Wow
Pushoff Switchlights
Switch On/Off Signal
Continuous Built-In-Test (CBIT) Continuous Built-In-Test (CBIT) constantly monitors the FCECU hardware performance. It monitors actuator performance to the level required to meet system safety requirements. CBIT is implemented in the FCECU hardware and does not involve software. Failures are annunciated to the flight compartment.
Event-Initiated Built-In-Test (EBIT) Event-Initiated Built-In-Test (EBIT) is initiated 6.4 seconds after the aircraft has landed and the pilot has set the FLIGHT/TAXI switch to TAXI. The FCECU checks for hidden failures of the spoiler lift dump solenoids.
27-246
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-00-45 CENTRAL DATA STORAGE FLIGHT CONTROLS INTRODUCTION 27 FLIGHT CONTROLS
The CDS monitors, records, tests, and shows the condition of the: •• Flight Control System and • Flap Control System.
GENERAL Refer to Figure 27-161. CDS Interface.
CDS (IOP 1) FCECU
Flap Control Unit
IOP 2
fsq72a01.cgm
Figure 27-161. CDS Interface
FOR TRAINING PURPOSES ONLY
27-247
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Refer to Figure 27-162. CDS Ground Maintenance Toggle Switch Selection. With the CDS GRD MAINT toggle switch set, the CDS rotary selector switch is selected to a system. 27 FLIGHT CONTROLS
An amber LED will come on to show that a system is armed to erase the contents of its NVRAM. The NVRAM RESET push-button switch is pushed for 1 second and then released to erase the NVRAM.
D
FW
The rotary selector switch is set back to OFF which causes the LED to go out. The Other System pages must be viewed again to verify that there are no malfunction messages shown.
AVIONICS RACK ELECTRICAL INSTALLATION
CDS GND MAINT LED
ENGINE MAINTENANCE
PROP DEICE CAL
CDS GND MAINT
UNFEATHER
A #2
#1
RIG TRIM
CDS GND MAINT Toggle Switch
MAINT DISC
A
ON
ECS AUTO FAIL
A
A OFF
FLAP PROP DEICE 2
A
NVRAM RESET ARM LED
#2 PSEU A
G
PSS MAINT
PSEU OPER
PAA TEST
28VDC
PROP DEICE 1
CPC ECS
A
#1 NVM RESET
FLT CTL
AFR DEICE
CDS Rotary Selector
NVM RESET Push Button
Figure 27-162. CDS Ground Maintenance Toggle Switch Selection
27-248
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-00-00 SPECIAL TOOL & TEST EQUIPMENT •• GSB2700008 Rigging Pin Kit •• GSB2700008-03 Rigging Pin, 0.25 - 3.00 in. (6.35-76.20 mm) L-Pin •• GSB2700008-04 Rigging Pin, 0.25 - 4.50 in (6.35-114.3 mm) L-Pin •• GSB2700008-05 Rigging Pin, 0.25 - 6.00 in. (6.35-152.4 mm) L-Pin 27 FLIGHT CONTROLS
•• GSB2700008-05 Rigging Pin, 0.25 - 8.00 in (6.35-203.2 mm) L-Pin •• GSB2700008-06 Rigging Pin, 0.25 - 8.00 in. (6.35-203.2 mm) L-Pin •• GSB2700008-09 Rigging Pin, 0.1875 - 4.00 in. (4.76-101.6 mm) L-Pin •• GSB2700008-10 Rigging Pin, 0.1875 - 12.0 in (4.71-304.8 mm) L-Pin •• GSB2700008-16D Target - Actuator (Steel) •• GSB2700008-16D C279TARGET •• GSB2700008-27 Elevator Tension Regulator Spacer •• GSB2700008-28 Spoiler Tension Regulator Spacer Tool •• GSB2700008-29 Rigging Pin, 0.1875 - 3.00 in. (4.7-76.2 mm) L-Pin •• GSB2700008-32 Target-De-Actuator (Copper) •• GSB2700009 (or equivalent) Cable Tension Meter •• GSB3411001 Test Set - Air Data •• GSB3411011 Air Data Test Set (or equivalent) •• GSB3411012 AIR DATA KIT •• GSB3411012 or GSB3411013 Pitot/Static Pressure Test Adapter •• GSB2000009 Digital Inclinometer •• GSB2715001 Left Gear Tab Rigging Board •• GSB2715002 Right Gear Tab Rigging Board •• GSB2715002 Gear Tab Rigging Tool •• GSB2715003 Left Elevator Rigging Boards •• GSB2715004 Right Elevator Rigging Boards •• GSB2715005 Aileron Rigging Tool •• GSB2733002 Rigging Fixture - Control Column (half moon) •• GSB2733003-1 Left AOA Vane Alignment Template •• GSB2733003-2 Right AOA Vane Alignment Template •• GSB2000024 Force Meter 0-100 lbf (0-xxx Kgf) •• GSB2000024 Force Meter 0-100 lbf (0-444.82 N) (may be substituted with commercially available unit with minimum 40 lbf (177.92 N) capacity) •• 964-0446-001 Hand-held Download Unit (HHDLU)
FOR TRAINING PURPOSES ONLY
27-249
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• Commercially available Laptop computer with Flightscape software (or equivalent) installed •• GSB2715005 Aileron Rigging Tool •• GSB2400001 Multimeter, Digital Volt/ohm •• GSB2400001 Digital Multimeter-Hand Held •• PBA P/N 390600TF2-101 Extend Jam Fixture 27 FLIGHT CONTROLS
•• PBA P/N 390600TF2-103 Retract Jam Fixture •• PBA P/N 390500TF3-109 Retract Jam Fixture •• PBA P/N 390500TF3-111 Extend Jam Fixture •• 376060GSE1-1001 Cable - Rudder PCU Internal Leak Detect Valve Electrical Test •• 376060GSE1-1001 or Alternate: G700-271105-1 Test Cable •• GSB2700010 Cable, Interface for rigging and trouble shooting •• 964-0446-001 Hand-Held Download Unit (HHDLU) •• GSB2440002 DC Rectifier •• GSB2440006 DC Rectifier •• Commercially Available Spring Scale (0 - 50 Lbs, 0 - 22.68 Kg) •• GSB2900001 Hydraulic Power Unit •• GSB3240006 or equivalent Tool - Brake Application •• MHI 02F99205 or equivalent Rudder Sling •• DHC8PROX-RTP-0102 Target Proximity Sensor De-Actuator Test •• Commercially Available Force gage, mechanical spring scale •• GSB27330002 or equivalent Control Column Rigging Tool •• Commercially Available Wire Pin Removal/Insertion Tool •• 11-8073-1010 DC Ground Power Unit •• Commercially Available Hydraulic Power Unit •• GSB5180001 or GSB5180005 Electrical Bonding Tester •• Commercially Available Liquid dispenser with 0.010 inch (0.254 mm) needle (Wheller FD21D, or equivalent) •• DRUCK 405F Air Data Test Set •• GPU-600, GSB2440006 DC Ground Power Cart •• H102, GSB2900001 Hydraulic Ground Power Cart •• MITUTOYO 950-315 Clinometer •• Commercially Available Switch Insertion/Removal Tool •• (2) GSB3411012 or GSB3411013 Pitot/Static Pressure Test Adapter •• Commercially Available Dial Indicator - 0.001 in. (0.0254 mm) resolution
27-250
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• Hewlett Packard HP4328A or equivalent Milliohmeter •• GSB2000009 Digital Inclinometer, Protractor •• GSB2000016 Micrometer Kit, Optical Depth •• DFM-100 Digital Force Meter, 1-100 LB •• GSB2750003 or equivalent Flap Drive Adapter 27 FLIGHT CONTROLS
•• CD-8 Cap, Protective Pressure Inlet ¾ -16 •• CD-6 Cap, Protective Pressure Inlet 9/16-18 •• GPN610-U3 Cap, Protective Tube Drain •• GPN610-U14 Kapsto Cap, Protective •• Commercially Available Removal Tool, Wire Pin •• 390700GSE1-1001 (Parker) Alignment Fixture, Spoiler Actuator Installation •• 390700GSE2-1001 (Parker) Spoiler Lock Collar •• 18-234 Extraction Tool (Vivisun)
FOR TRAINING PURPOSES ONLY
27-251
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-00-00 MAINTENANCE PRACTICES Refer to the Bombardier AMM PSM 1-84-2 for details on these maintenance procedures: •• AMM 45-00-27-742-801 R etrieval of Data from the Central Diagnostic System (CDS) − Flight Control System (FCS) 27 FLIGHT CONTROLS
•• AMM 27-00-01-710-802 O perational Test of the Flight Control Electronic Control Unit (FCECU) •• AMM 27-10-00-830-802 Control Column to Control Column Rigging •• AMM 27-10-00-830-803 Control Column to Aileron Quadrant Rigging •• AMM 27-10-00-830-804 Aileron Quadrant to Splitter Quadrant Rigging •• AMM 27-10-00-830-805 Aileron Splitter Quadrant to Aileron Terminal Quadrant Rigging •• AMM 27-10-00-830-806 Aileron Terminal Quadrant to Aileron Surface Rigging •• AMM 27-10-00-830-807 Rigging of the Aileron Control System Stops •• AMM 27-12-01-830-802 Rigging of the Aileron Quadrant Microswitch •• AMM 27-12-16-830-801 Rigging of the Aileron Geared Tab •• AMM 27-12-21-830-802 Rigging of the Aileron Position LVDT •• AMM 12-20-01-640-812 Lubrication of the Aileron and Roll Spoiler Chains •• FIM 27-10-00-810-801 AIL LVDT FAIL (Status) −Fault Isolation •• AMM 27-10-00-710-801 Operational Test of the Aileron Control System •• AMM 27-13-00-710-802 Operational Test of the Aileron Trim System •• AMM 27-16-00-830-801 Rigging of the Roll Disconnect System •• AMM 27-16-00-710-802 O perational Check of the Roll Disconnect Mechanism (CMR# 271000−106) •• AMM 27-21-26-000-801 Removal of the Power Control Unit/Actuator •• AMM 27-21-26-400-801 Installation of the Power Control Unit/Actuator •• AMM 27-21-00-830-810 Rigging of the Rudder Pedals to the Rudder Forward Quadrants •• AMM 27-21-00-830-811 Rigging of the Forward Quadrant to the Rudder Mixer Quadrant •• AMM 27-21-00-830-812 Rigging of the Rudder Mixer Quadrant to the Rudder Aft Quadrant •• AMM 27-21-00-830-815 Rigging of the Upper Servo Spring Strut Motion Detector •• AMM 27-21-00-830-809 Rigging of the Rudder PCUs with Hydraulic Power •• AMM 27-21-00-830-817 Rigging of the Rudder Feel and Summing Unit •• AMM 27-21-03-820-801 Adjustment of the Rudder Pedal Position−Sensor •• AMM 27-21-26-830-801 Rigging of the Rudder Power Control Units •• AMM 27-20-00-710-801 O perational Check of the Rudder Control Shut−Off Valves (CMR#272000−111)
27-252
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• AMM 27-20-00-710-802 Operational Test of the Rudder Control System •• AMM 27-20-00-710-803 Operational Check of the Rudder Control System (CMR#272000-108) •• AMM 27-21-28-710-801 Operational Test of the Rudder Shut–Off Valves •• AMM 27-22-00-710-801 Operational Test of the Rudder Trim System •• AMM 27-31-00-790-801 Elevator Droop Rate Check •• AMM 27-30-00-710-801 Operational Test of the Elevator Control System •• AMM 27-30-00-710-803 O perational Check of the Elevator Control Pitch Disconnect Mechanism (MRB# 273000−204) •• AMM 27-32-00-710-801 Operational Test of the Pitch Feel System •• AMM 27-33-26-000-801 Removal of the Angle of Attack Transducer •• AMM 27-33-26-400-801 Installation of the Angle of Attack Transducer •• AMM 27-33-00-830-801 Rigging of the Stick Pusher System •• AMM 27-38-00-710-801 Operational Test of the Pitch Disconnect System •• AMM 27-50-00-760-801 Wing Flaps System, Electrical Checks •• AMM 45-00-27-742-802 R etrieval of Data from the Central Diagnostic System (CDS) − Flaps System (FLAPS) •• AMM 27-50-00-710-801 Operational Test of the Wing Flaps •• AMM 27-51-06-710-801 Operational Test of the Flap Control Module •• AMM 27-52-00-640-801 Lubrication of the Flap Actuator Ballscrews (MRB #275000−201) •• AMM 27-61-00-710-801 Operational Test of the Roll Spoiler System •• AMM 27-61-00-710-803 Operational Test of the Spoiler Jam Detect System •• AMM 27-61-00-710-804 O perational Check of the Roll Spoiler SPLR 1 & SPLR 2 Push Off Switchlights (MRB #276000−205) •• AMM 27-61-00-710-805 O perational Check of the Roll Spoiler Cable Sensor Assembly (CMR#276000−106) •• AMM 27-61-00-710-806 O perational Check of the Spoiler Cable Disconnect Sensor (MRB#276000−208) •• AMM 27-61-03-720-801 Functional Test of the Spoiler Force Sensor •• AMM 27-62-00-710-801 Operational Test of the Ground Spoiler System •• AMM 27-71-00-710-801 Operational Test of the Aileron Gust Lock System
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-253
27 FLIGHT CONTROLS
•• AMM 27-31-00-750-801 Asymmetry Check of the Elevators
FOR TRAINING PURPOSES ONLY
NOTICE The material contained in this training manual is based on information obtained from the aircraft manufacturer’s Maintenance Manuals and Pilot Manuals. It is to be used for familiarization and training purposes only. At the time of printing it contained then-current information. In the event of conflict between data provided herein and that in publications issued by the manufacturer or the FAA, that of the manufacturer or the FAA shall take precedence. We at FlightSafety want you to have the best training possible. We welcome any suggestions you might have for improving this manual or any other aspect of our training program.
FOR TRAINING PURPOSES ONLY NOTICE These commodities, t echnology o r softwar e were exported from t he U nited States i n acco rdance w ith t he Expor t Administration Regulations. Diversion contrary to U.S. law is prohibited.
Courses for the Dash 8 Series and other deHavilland aircraft are taught at the following FlightSafety International learning centers:
FlightSafety International Toronto Learning Center 95 Garratt Boulevard Downsview, Ontario M3K 2A5
For course information please contact us:
1-416-638-9313 1-877-FLY-DASH [email protected] www.flightsafety.com
Copyright © 2015 FlightSafety International, Inc. Unauthorized reproduction or distribution is prohibited. All rights reserved.
INSERT LATEST REVISED PAGES, DESTROY SUPERSEDED PAGES LIST OF EFFECTIVE PAGES Dates of issue for original and changed pages are: Second Edition..... 0.............. August 2013 Revision............... 0.1............... April 2014 Revision............... 0.2........... August 2014
Revision............... 0.3............... April 2015 Revision............... 0.4......... October 2015
THIS PUBLICATION CONSISTS OF THE FOLLOWING: Page *Revision No. No.
Page *Revision No. No.
32-i - xi.................................................... 0.4 32-xii - 32-6............................................. 0.3 32-7......................................................... 0.4 32-8 - 32-22............................................ 0.3 32-23....................................................... 0.4 32-24 - 32-42.......................................... 0.3 32-43....................................................... 0.4 32-44 - 32-60.......................................... 0.3 32-61....................................................... 0.4 32-62 - 32-78.......................................... 0.3 32-79....................................................... 0.4 32-80 - 32-86.......................................... 0.3 32-87....................................................... 0.4 32-88 - 32-100........................................ 0.3 32-101..................................................... 0.4 32-102..................................................... 0.3 32-103..................................................... 0.4 32-104..................................................... 0.3 32-105..................................................... 0.4 32-106 - 32-108...................................... 0.3 32-109..................................................... 0.4 32-110..................................................... 0.3 32-111 - 32-112...................................... 0.4 32-113 - 32-120...................................... 0.3 32-121..................................................... 0.4 32-122..................................................... 0.3 32-123..................................................... 0.4 32-124..................................................... 0.3
32-125..................................................... 0.4 32-126 - 32-138...................................... 0.3 32-139..................................................... 0.4 32-140 - 32-142...................................... 0.3 32-143..................................................... 0.4 32-144 - 32-148...................................... 0.3 32-149..................................................... 0.4 32-150..................................................... 0.3 32-151..................................................... 0.4 32-152 - 32-154...................................... 0.3 32-155..................................................... 0.4 32-156 - 32-161...................................... 0.3 32-162 - 32-163..................................... 0.4 32-164 - 32-166...................................... 0.3 32-167..................................................... 0.4 32-168 - 32-169...................................... 0.3 32-170..................................................... 0.4 32-171 - 32-175...................................... 0.3 32-176 - 32-177...................................... 0.4 32-178 - 32-179...................................... 0.3 32-180..................................................... 0.4 32-181 - 32-182...................................... 0.3 32-183 - 32-185...................................... 0.4 32-186 - 32-187...................................... 0.3 32-188 - 190............................................ 0.4 27-i - 27-xii.............................................. 0.4 27-xiii - 27-6............................................ 0.3 27-7......................................................... 0.4
Page *Revision No. No.
Page *Revision No. No.
27-8......................................................... 0.3 27-9......................................................... 0.4 27-10....................................................... 0.3 27-11....................................................... 0.4 27-12 - 27-14.......................................... 0.3 27-15....................................................... 0.4 27-16 - 27-18.......................................... 0.3 27-19....................................................... 0.4 27-20 - 27-22.......................................... 0.3 27-23....................................................... 0.4 27-24 - 27-26.......................................... 0.3 27-27....................................................... 0.4 27-28 - 27-44.......................................... 0.3 27-45....................................................... 0.4 27-46 - 27-50.......................................... 0.3 27-51....................................................... 0.4 27-52 - 27-56.......................................... 0.3 27-57....................................................... 0.4 27-58....................................................... 0.3 27-59....................................................... 0.4 27-60....................................................... 0.3 27-61....................................................... 0.4 27-62 - 27-66.......................................... 0.3 27-67....................................................... 0.4 27-68 - 27-70.......................................... 0.3 27-71....................................................... 0.4 27-72 - 27-74.......................................... 0.3 27-75....................................................... 0.4 27-76 - 27-82.......................................... 0.3 27-83....................................................... 0.4 27-84 - 27-88.......................................... 0.3 27-89....................................................... 0.4 27-90....................................................... 0.3 27-91....................................................... 0.4 27-92 - 27-94.......................................... 0.3 27-95....................................................... 0.4 27-96 - 27-102........................................ 0.3 27-103..................................................... 0.4 27-104 - 27-106...................................... 0.3 27-107..................................................... 0.4
27-108..................................................... 0.4 27-109 - 27-112...................................... 0.3 27-113..................................................... 0.4 27-114 - 27-120...................................... 0.3 27-121 - 27-122...................................... 0.4 27-123 - 27-126...................................... 0.3 27-127..................................................... 0.4 27-128 - 27-144...................................... 0.3 27-145..................................................... 0.4 27-146..................................................... 0.3 27-147..................................................... 0.4 27-148 - 27-152...................................... 0.3 27-153..................................................... 0.4 27-154 - 27-164...................................... 0.3 27-165..................................................... 0.4 27-166 - 27-168...................................... 0.3 27-169..................................................... 0.4 27-170 - 27-172...................................... 0.3 27-173..................................................... 0.4 27-174..................................................... 0.3 27-175..................................................... 0.4 27-176 - 27-184...................................... 0.3 27-185..................................................... 0.4 27-186 - 27-190...................................... 0.3 27-191 - 27-192...................................... 0.4 27-193 - 27-200...................................... 0.3 27-201..................................................... 0.4 27-202..................................................... 0.3 27-203 - 27-204...................................... 0.4 27-205 - 27-211...................................... 0.3 27-212..................................................... 0.4 27-213 - 27-224...................................... 0.3 27-225 - 22-227...................................... 0.4 27-228..................................................... 0.3 27-229..................................................... 0.4 27-230 - 27-244...................................... 0.3 27-245..................................................... 0.4 27-246 - 27-251...................................... 0.3 27-252 - 27-253...................................... 0.4
CONTENTS VOLUME 3B Chapter Title LANDING GEAR FLIGHT CONTROLS
ATA Number 32 27
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
CHAPTER 32 LANDING GEAR CONTENTS
Page
32-00-00 INTRODUCTION........................................................................................ 32-1 General................................................................................................................ 32-1 32-11-00 MAIN LANDING GEAR............................................................................. 32-5 General ............................................................................................................... 32-5 System Description.............................................................................................. 32-5 Component Description........................................................................................ 32-6 Shock Strut................................................................................................... 32-6 Installation of the MLG Electrical Harness................................................... 32-7 Axles............................................................................................................. 32-8 Shock Strut Torque Links.............................................................................. 32-9 Drag Strut .................................................................................................. 32-10 Stabilizer Brace........................................................................................... 32-11 Yoke............................................................................................................ 32-12 Shock Strut Fairings.................................................................................... 32-12 32-12-00 MAIN LANDING GEAR DOORS............................................................. 32-14 Introduction....................................................................................................... 32-14 General.............................................................................................................. 32-14 System Description............................................................................................ 32-15 Component Description...................................................................................... 32-16
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-i
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page Aft MLG Doors........................................................................................... 32-16 Aft MLG Doors Connecting Rods............................................................... 32-16 Aft Door Mechanism................................................................................... 32-17 Forward MLG Doors................................................................................... 32-18 32-12-00 DVI MAIN LANDING GEAR DOOR MECHANISMS............................. 32-19 Controls and Indications.................................................................................... 32-21 Open and Lock the Landing Gear Doors..................................................... 32-23 Installation of the Main Landing Gear Lock Pins........................................ 32-23 32-20-00 NOSE LANDING GEAR AND DOORS.................................................... 32-27 Introduction....................................................................................................... 32-27 General.............................................................................................................. 32-28 Component Description...................................................................................... 32-31 Nose Landing Gear Shock Strut.................................................................. 32-31 Nose Landing Gear Trailing Arm................................................................ 32-32 NLG Drag Strut.......................................................................................... 32-32 NLG Electrical Harness.............................................................................. 32-34 32-22-00 NOSE LANDING GEAR DOORS............................................................. 32-35 Introduction....................................................................................................... 32-35 General.............................................................................................................. 32-35 System Description............................................................................................ 32-35 Component Description...................................................................................... 32-37 Aft NLG Doors........................................................................................... 32-37
32-ii
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Page Aft NLG Doors Connecting Rods................................................................ 32-37 NLG Forward Doors ................................................................................... 32-39 NLG Forward Doors Connecting Rods........................................................ 32-39 32-22-00 DVI NOSE LANDING GEAR DOOR MECHANISMS.............................. 32-39 Controls and Indications.................................................................................... 32-41 32-25-00 NOSE LANDING GEAR GROUND LOCK............................................... 32-42 Introduction....................................................................................................... 32-42 General ............................................................................................................. 32-42 System Description ........................................................................................... 32-42 Component Description...................................................................................... 32-43 Nose Gear Ground-Lock Position Indication System (Optional).................. 32-43 32-30-00 LANDING GEAR EXTENSION AND RETRACTION.............................. 32-45 Introduction....................................................................................................... 32-45 General.............................................................................................................. 32-45 System Description............................................................................................ 32-45 32-31-00 PRIMARY EXTENSION AND RETRACTION.......................................... 32-45 Introduction....................................................................................................... 32-45 General.............................................................................................................. 32-45 Component Description...................................................................................... 32-46 Landing Gear Selector Valve....................................................................... 32-46 MLG Retraction Actuator............................................................................ 32-47 MLG Downlock Actuator............................................................................ 32-48
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-iii
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page MLG Uplock Assembly............................................................................... 32-49 Mechanical Sequence Valve........................................................................ 32-50 Inline Restrictors......................................................................................... 32-50 MLG Solenoid Sequence Valve .................................................................. 32-51 NLG Solenoid Sequence Valve.................................................................... 32-51 NLG Retraction Actuator ........................................................................... 32-52 NLG Lock Actuator..................................................................................... 32-53 NLG Inline Restrictors................................................................................ 32-53 Controls and Indications.................................................................................... 32-55 Fault Isolation............................................................................................. 32-55 Maintenance Practices........................................................................................ 32-56 32-31-00 PRIMARY EXTENSION AND RETRACTION.......................................... 32-59 Operation........................................................................................................... 32-59 Normal System Operation........................................................................... 32-59 MLG Retraction Sequence.......................................................................... 32-59 NLG Retraction Sequence........................................................................... 32-61 Landing Gear Retraction............................................................................. 32-63 Nose Landing Gear Extension..................................................................... 32-69 Landing Gear Normal Extension................................................................. 32-71 32-34-00 ALTERNATE EXTENSION SYSTEM....................................................... 32-75 Introduction....................................................................................................... 32-75 General ............................................................................................................. 32-75
32-iv
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Page System Description ........................................................................................... 32-77 Servicing of the Alternate Landing-Gear Extension Hydraulic Reservoir.................................................................... 32-79 Component Description...................................................................................... 32-80 Main Gear Alternate Release Handle........................................................... 32-80 Nose Gear Alternate Release Handle........................................................... 32-81 Alternate Extension Actuator...................................................................... 32-82 Alternate Extension Downlock Indicators and Switch................................. 32-83 Bypass Valve............................................................................................... 32-85 MLG Alternate Release Control Cables....................................................... 32-87 Operational Check of the Main Landing Gear Alternate Extension Cam Assembly (MRB#323400-204)............................ 32-87 NLG Alternate Release Control Cables....................................................... 32-88 Landing Gear Inhibit Switch....................................................................... 32-89 29-21-01 HYDRAULIC HAND PUMP..................................................................... 32-91 29-21-03 HAND-PUMP LEVER............................................................................... 32-91 29-21-06 SECONDARY MLG SELECTOR VALVE.................................................. 32-93 Operation........................................................................................................... 32-97 Alternate Extension..................................................................................... 32-97 32-41-00 WHEELS................................................................................................... 32-99 General.............................................................................................................. 32-99 System Description............................................................................................ 32-99 Components Description.................................................................................... 32-99
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-v
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page Main Wheels............................................................................................... 32-99 Installation of the Main Wheel and Tire Assembly....................................32-101 MLG Axle Bullet......................................................................................32-101 Nosewheels...............................................................................................32-103 Installation of the Nosewheel and Tire Assembly.......................................32-103 Fill Valve Gauge (Optional).......................................................................32-105 Tire Wear..................................................................................................32-105 32-42-00 MAIN LANDING GEAR BRAKE SYSTEM...........................................32-107 Introduction.....................................................................................................32-107 General............................................................................................................32-107 System Description .........................................................................................32-107 Component Description....................................................................................32-109 Main Wheel Brake Units...........................................................................32-109 Installation of the Main Wheel Brake Units...............................................32-109 Bleed the Brakes with Main Brake System................................................32-111 Brake Bleeding Kit....................................................................................32-112 Brake Control Valve..................................................................................32-113 Fuse/Shuttle Valves...................................................................................32-114 Brake Pedals.............................................................................................32-115 Brake Control Cables................................................................................32-116 Brake Pressure Transducers.......................................................................32-117 32-44-00 PARKING BRAKE SYSTEM..................................................................32-119
32-vi
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Page Introduction.....................................................................................................32-119 General............................................................................................................32-119 System Description..........................................................................................32-119 Component Description....................................................................................32-121 Parking Brake Control Valve.....................................................................32-121 Parking Brake Hand pump.........................................................................32-121 Post SB 84-32-99 Reposition of the Parking Brake Hand Pump Lever to the Nose Compartment...................................32-122 Charge Valve and Gauge...........................................................................32-125 Servicing of the Parking Brake Accumulator with Nitrogen......................32-125 Functional Check of Park Brake Accumulator Pre-Charge Pressure..........32-125 Parking Brake Control Quadrant...............................................................32-126 Parking Brake Control Cable.....................................................................32-127 Controls and Indications .................................................................................32-129 Interfaces..................................................................................................32-129 32-46-00 ANTI-SKID SYSTEM.............................................................................32-133 Introduction.....................................................................................................32-133 General............................................................................................................32-133 System Description .........................................................................................32-133 Components Description..................................................................................32-135 Anti-Skid Control Unit..............................................................................32-135 Skid Control Valves...................................................................................32-136 Wheel Speed Transducer...........................................................................32-137
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-vii
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page Installation of the Wheel-Speed Transducer Electrical Harness.................32-139 Anti-Skid Switch..............................................................................................32-140 Controls and Indications .................................................................................32-141 Functional Test of the Anti-Skid Control System (Built-in Test)................32-143 Touchdown Protection Test........................................................................32-143 Wheel Speed Transducer Test....................................................................32-143 ANTI-SKID SYSTEM............................................................................................32-145 Operation.........................................................................................................32-145 Anti-Skid Operation..................................................................................32-145 Initialization..............................................................................................32-145 Individual Wheel.......................................................................................32-145 Locked Wheel...........................................................................................32-145 Interfaces..................................................................................................32-146 MAINTENANCE PRACTICES IMPORTANT TO THE MLG BRAKING SYSTEM.......................................................................32-149 Fault Isolation..................................................................................................32-149 INBD ANTISKID and OUTBD ANTISKID (Caution lights).....................32-149 PARKING BRAKE, indication discrepancy (Caution Light).....................32-151 32-51-00 NOSEWHEEL STEERING SYSTEM......................................................32-153 Introduction.....................................................................................................32-153 General............................................................................................................32-153 System Description..........................................................................................32-153 Nosewheel Steering Hand Control.............................................................32-153 32-viii
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Page Rudder Pedal Control................................................................................32-153 Shimmy Damping......................................................................................32-153 Component Description....................................................................................32-155 Steering Control Unit (SCU).....................................................................32-155 BITE Test of the Nosewheel Steering System............................................32-155 Nosewheel Steering Hand Control.............................................................32-156 Rudder Pedal Potentiometer......................................................................32-157 Nosewheel Steering Manifold....................................................................32-159 Nosewheel Centering Mechanism..............................................................32-160 Power Steering Unit..................................................................................32-161 Removal of Power Steering Unit................................................................32-163 Steering Feedback Assembly.....................................................................32-165 Steering Switch.........................................................................................32-167 Controls and Indications .................................................................................32-167 Rigging of the RVDT................................................................................32-167 Operation.........................................................................................................32-169 Normal System Operation................................................................................32-169 Operation in the Passive Mode..................................................................32-169 Operational Test of the Nosewheel Steering System..................................32-170 Functional Test of the Nosewheel Steering System....................................32-170 32-61-00 PROXIMITY SENSOR SYSTEM ...........................................................32-173 Introduction.....................................................................................................32-173
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-ix
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page General ...........................................................................................................32-173 System Description .........................................................................................32-173 Component Description....................................................................................32-175 Proximity Sensor Electronic Unit..............................................................32-175 Built-In-Test-Equipment............................................................................32-175 Installation of the Proximity Sensor Electronic-Unit.................................32-176 Retrieval of Data from the Proximity Sensor Electronic Unit (PSEU).......32-176 Erase the Data from the Proximity Sensor Electronic Unit (PSEU)...........32-177 Operational Check of the Proximity Sensor Electronic Unit......................32-177 Proximity Sensors.....................................................................................32-179 Installation of the Proximity Sensors.........................................................32-180 Rigging of the Proximity Sensors..............................................................32-180 Controls and Indications..................................................................................32-181 Landing Gear Control................................................................................32-181 Landing Gear Indications..........................................................................32-181 Alternate Downlock Indications.......................................................................32-181 Operational Check of the Weight On Wheels System ...............................32-183 32-00-00 APPENDIX..............................................................................................32-184 Maintenance Consideration..............................................................................32-184 Safety Precautions.....................................................................................32-184 Main Landing Gear Lower Bearing Seal....................................................32-185 Standard Configuration for an ‘On-Jacks’ Weight-On-Wheels (WOW) Condition.......................................................32-185 32-x
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Page Standard Configuration for an ‘On-Ground’ Weight-Off-Wheels (WOFFW) Condition.................................................32-185 32-00-00 SPECIAL TOOL & TEST EQUIPMENT..................................................32-186 32-00-00 MAINTENANCE PRACTICES................................................................32-188
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-xi
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
ILLUSTRATIONS Figure Title Page 32-1
Landing Gear Functional Block Diagram...................................................32-2
32-2
Main Landing Gears - Details....................................................................32-4
32-4
Main Landing Gear - Shock Strut..............................................................32-6
32-3
Shock Strut................................................................................................32-6
32-5
MLG Axle.................................................................................................32-8
32-6
Shock Strut Torque Links...........................................................................32-9
32-7
MLG Drag Strut .....................................................................................32-10
32-9
MLG Stabilizer Brace..............................................................................32-11
32-8
MLG Ground Lock Pin............................................................................32-11
32-10
MLG Yoke and Actuator..........................................................................32-12
32-11
Shock Strut Fairings................................................................................32-12
32-12
CDL - MLG Shock Strut Fairings............................................................32-13
32-13
Main Gear Doors.....................................................................................32-14
32-14
MLG Doors - Detail................................................................................32-15
32-15
MLG Aft Doors and Connecting Rods.....................................................32-16
32-16
MLG Doors and Connecting Rods...........................................................32-17
32-17
Forward MLG Doors and Connecting Rods.............................................32-18
32-18
Landing Gear Control Panel....................................................................32-20
32-19
Proximity Sensor.....................................................................................32-21
32-20
Landing Gear Doors - Open and Lock/Unlock and Close (1 of 2)............32-22
32-21
Landing Gear Doors - Open and Lock/Unlock and Close (2 of 2)............32-24
FOR TRAINING PURPOSES ONLY
32-xiii
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-22
Nose Landing Gear and Doors.................................................................32-26
32-23
NLG Dressed Shock Strut Assembly (1 of 2)...........................................32-28
32-24
NLG Dressed Shock Strut Assembly (2 of 2)...........................................32-29
32-25
NLG Shock Strut Assembly.....................................................................32-30
32-26
NLG Shock Strut Assembly.....................................................................32-31
32-27
NLG Trailing Arm...................................................................................32-32
32-28
NLG Drag Strut.......................................................................................32-32
32-29
NLG Drag Strut.......................................................................................32-33
32-30
NLG Latest Electrical Harness................................................................32-34
32-31
NLG Aft Doors and Connecting Rods......................................................32-36
32-32
CDL - Nose Landing Gear Aft Doors.......................................................32-37
32-33
NLG Forward Doors and Connecting Rods..............................................32-38
32-34
Main Landing Gear Control Panel...........................................................32-40
32-35
NLG Door Proximity Sensor....................................................................32-41
32-36
NLG Ground-Lock Control Handle..........................................................32-42
32-37
Nose Gear Ground-Lock Position Indication System...............................32-43
32-38
Landing Gear Block Diagram..................................................................32-44
32-39
Landing Gear Selector Valve - Detail.......................................................32-46
32-40
MLG Retraction Actuator - Detail...........................................................32-47
32-41
MLG Downlock Actuator - Detail............................................................32-48
32-43
MLG Uplock Actuator - Detail................................................................32-49
32-42
MLG Uplock Assembly...........................................................................32-49
32-xiv
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-44
MLG Doors Inline Restrictors.................................................................32-50
32-45
Landing Gear Doors Solenoid Sequence Valve........................................32-51
32-46
NLG Doors Sequence Valve.....................................................................32-51
32-48
NLG Retraction and Lock Actuator.........................................................32-52
32-47
NLG Retraction Actuator.........................................................................32-52
32-50
NLG Inline Restrictor..............................................................................32-53
32-49
NLG Lock Actuator.................................................................................32-53
32-51
Landing Gear - Controls and Indications.................................................32-54
32-52
(32-31-00) UP Selection Doors Open......................................................32-58
32-53
(32-31-00) Gear UP and Doors Locked Closed........................................32-60
32-54
(32-31-00) Landing Gear Retraction (Sheet 1 of 3)..................................32-62
32-55
(32-31-00) Landing Gear Retraction (Sheet 2 of 3)..................................32-64
32-56
(32-31-00) Landing Gear Retraction (Sheet 3 of 3)..................................32-66
32-57
Initial DOWN Selection Doors Opening..................................................32-68
32-58
Selection Completed Doors Closed..........................................................32-70
32-59
(32-31-00) Landing Gear Normal Extension............................................32-72
32-60
Alternate Extension System Block Diagram............................................32-74
32-61
Alternate Extension Hydraulic Synoptic..................................................32-76
32-62
Servicing of the Auxiliary System Hydraulic Reservoir...........................32-78
32-63
Main Gear Alternate Release Handle.......................................................32-80
32-64
NLG Alternate Release Handle................................................................32-81
32-65
Alternate Extension Actuator...................................................................32-82
FOR TRAINING PURPOSES ONLY
32-xv
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-66
Landing Gear Downlock Verification Switch...........................................32-83
32-67
Bypass Valve and Alternate Release Cables.............................................32-84
32-68
MLG Alternate Extension System Cam Mechanism Assembly.................32-86
32-69
NLG Alternate Release Cable..................................................................32-88
32-70
Landing Gear Alternate Release - Inhibit Switch.....................................32-89
32-71
Hydraulic Hand Pump and Hand Pump Lever..........................................32-90
32-72
Secondary MLG Selector Valve - Removal and Installation.....................32-92
32-73
LG Downlock Verification Lights - Controls and Indications...................32-94
32-74
Landing Gear Extension and Retraction...................................................32-96
32-75
Main Wheel and Tire Assembly...............................................................32-98
32-76
Main Wheel and Tire Assembly - Removal and Installation.................. 32-100
32-77
MLG Axle Bullet.................................................................................. 32-101
32-78 Nosewheel and Tire Assembly............................................................... 32-102 32-79
Fill Valve Gauge................................................................................... 32-104
32-80
Brakes System Hydraulic Synoptic....................................................... 32-106
32-82
Main Wheel Brake Unit - Removal and Installation.............................. 32-108
32-81
Brake Wear Indicator Pins.................................................................... 32-108
32-83
Main Landing Gear Brake System - Bleed............................................ 32-110
32-84
Brake Bleeding Kit............................................................................... 32-112
32-85
CDL - Brake Assembly Wear Indicator Pin........................................... 32-112
32-86
Brake Control Valve.............................................................................. 32-113
32-88
Fuse - Shuttle Valve.............................................................................. 32-114
32-xvi
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-87
Fuse - Shuttle Valve.............................................................................. 32-114
32-89
Brake Pedals......................................................................................... 32-115
32-90
Brake Control Cables............................................................................ 32-116
32-91
Brake Pressure Transducers.................................................................. 32-117
32-92
Parking Brake Hydraulic System.......................................................... 32-118
32-93
Park Brake Control Valve...................................................................... 32-120
32-94
Park Brake Control Valve...................................................................... 32-120
32-95
Parking Brake Handle Reposition......................................................... 32-122
32-96
CDL - Parking Brake Hand Pump Handle............................................. 32-123
32-97
Parking Brake Accumulator.................................................................. 32-124
32-98
Charge Valve and Gauge....................................................................... 32-125
32-99
Park Brake Control Quadrant................................................................ 32-126
32-100
Parking Brake Control Cable................................................................ 32-127
32-101
Parking Brake Micro-Switch................................................................. 32-128
32-102
Controls and Indications - Parking Brake System................................. 32-130
32-103
CDL - Parking Brake Pressure Indications............................................ 32-131
32-104
Anti-Skid System - Hydraulic Schematic.............................................. 32-132
32-105
Anti-Skid System Control Unit............................................................. 32-134
32-106
Anti-Skid System Control Unit ............................................................ 32-134
32-108
Skid Control Valve ............................................................................... 32-136
32-107
Skid Control Valve................................................................................ 32-136
32-110
Wheel Speed Transducer....................................................................... 32-137
FOR TRAINING PURPOSES ONLY
32-xvii
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-109
Wheel Speed Transducer....................................................................... 32-137
32-111
Wheel Speed Transducer Harness - Removal/Installation...................... 32-138
32-112
Anti-Skid Switch.................................................................................. 32-140
32-113
Anti-Skid Caution Lights...................................................................... 32-141
32-114
Anti-Skid System Functional Test......................................................... 32-142
32-115
Anti-Skid System Electrical Schematic................................................. 32-144
32-116 ARCDU CDS ANTISKID System........................................................ 32-148 32-118
ASC - Current Faults............................................................................ 32-148
32-117
PSEU - Present Faults........................................................................... 32-148
32-119
ASC - No Current Faults....................................................................... 32-150
32-120
Parking Brake Caution Light................................................................ 32-150
32-121
Nosewheel Steering System Schematic................................................. 32-152
32-122
Steering Control Unit............................................................................ 32-154
32-123
Steering Control Unit............................................................................ 32-154
32-124
Nosewheel Steering Hand Control ....................................................... 32-156
32-125
Rudder Forward Assembly (Right Side)................................................ 32-157
32-126
Nosewheel Steering Hydraulic Synoptic............................................... 32-158
32-127 Nosewheel Centering Actuator.............................................................. 32-160 32-128 Nosewheel Centering Mechanism......................................................... 32-160 32-129
Power Steering Unit.............................................................................. 32-161
32-130
Hydraulic Steering Motor..................................................................... 32-164
32-131
Steering Feedback Assembly................................................................. 32-164
32-xviii
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Figure Title Page 32-132
Nosewheel Steering Switch................................................................... 32-166
32-133
Nosewheel Steering System Caution Lights.......................................... 32-166
32-134
Nosewheel Steering - Electrical Schematic........................................... 32-168
32-135
PSEU Input and Output Block Diagram................................................ 32-172
32-136
Proximity Sensor Electronic Unit......................................................... 32-174
32-137 Proximity Sensor Electronic Unit......................................................... 32-175 32-138
Proximity Sensors - Locations.............................................................. 32-178
32-139
Proximity Sensors................................................................................. 32-179
32-140
CAWP with WOW Caution................................................................... 32-182
FOR TRAINING PURPOSES ONLY
32-xix
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CHAPTER 32 LANDING GEAR
32-00-00 INTRODUCTION The landing gear supports the weight of the aircraft on the ground. It is also used to maneuver the aircraft while on the ground.
GENERAL The landing gear is electrically controlled, hydraulically operated and mechanically locked.
if the gear is not extended and the aircraft is in a landing configuration.
The tricycle gear is a retractable dual wheel installation. The main gear retract aft into the nacelles, with the nose gear retracting forward into the nose section. The gear doors completely enclose the landing gear when it is retracted and partially enclose the gear bays when it is extended. Flight compartment advisory lights show position of gear and doors. An aural warning sounds
A Proximity Sensor Electronics Unit (PSEU) monitors and controls the operation of the landing gear components. An alternate landing gear extension system can be used to extend the gear if the primary extension system fails. There is also an alternate down lock verification system.
FOR TRAINING PURPOSES ONLY
32-1
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-2 PILOT HAND CONTROL
RUDDER PEDALS
SELECTOR VALVE
LANDING GEAR CONTROL & INDICATION
NLG SOLENOID SEQUENCE VALVE
PSEU
ANTI-SKID CONTROL UNIT
MLG SOLENOID SEQUENCE VALVES
RIGHT MLG UPLOCK DOWNLOCK 1 DOWNLOCK 2
LEFT MLG UPLOCK DOWNLOCK 1 DOWNLOCK 2
LEFT MLG AFT DOOR
NOSE DOOR
NGDL 1 NGDL 2 NGL 1 NGL 2
Figure 32-1. Landing Gear Functional Block Diagram
RIGHT MLG AFT DOOR
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
STEERING CONTROL UNIT
DASH 8 Q400
ALTERNATE EXTENSION INDICATION
NW CENTER
WOW 1 WOW 2
MAINTENANCE TRAINING MANUAL
Refer to Figure 32-1. Landing Gear Functional Block Diagram.
32 LANDING GEAR
DASH 8 Q400
NOTES
The landing gear system is comprised of the following subsystems: •• Main Landing Gear (MLG) and doors •• Nose Landing Gear (NLG) and doors •• Landing gear extension and retraction •• Wheels and brakes •• Steering system •• Position and warning.
FOR TRAINING PURPOSES ONLY
32-3
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
NOTE Left gear shown. Right gear similar.
6
A
7
5 8 4 9
3
LEGEND 1. Drag Strut 2. Shock Strut 3. Stabilizer Brace 4. Stabilizer Lock 5. Alternate Extension Actuator 6. Yoke 7. Retraction Actuator 8. Uplock Assembly 9. Door Operative Mechanism.
FWD 2
1
A
Figure 32-2. Main Landing Gears - Details
32-4
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-11-00 MAIN LANDING GEAR
An up-lock assembly is attached to the top aft section of the wheel well. It locks the MLG in the retracted position.
GENERAL
The shock strut piston absorbs landing forces.
Refer to Figure 32-2. Main Landing Gears - Details. Each MLG assembly is installed on the airframe structure in the wheel well of the related engine nacelle. Each of the MLG has two wheel and tire assemblies. The main landing gear includes the listed components: •• Drag strut •• Shock strut
A jack pad on the bottom of the shock strut allows for jacking the aircraft from a single point. Proximity sensors send signals to the PSEU of the status of the MLG. A proximity sensor on the uplock assembly signals the gear is up and locked. Two proximity sensors on the stabilizer brace send signals to the PSEU when the MLG is down and locked. Two proximity sensors on the torque links send signals to the PSEU of Weight-OnWheels (WOW) or a Weight-Off-Wheels (WOFW) condition.
•• Stabilizer brace •• Lock actuator •• Alternate extension actuator •• Yoke assembly •• Retraction actuator •• Uplock assembly •• Door operating mechanism.
SYSTEM DESCRIPTION Refer to Figure 32-2. Main Landing Gears - Details. A retraction actuator is attached to the yoke and the shock strut, it is used to extend and retract the MLG. A locking actuator on the stabilizer brace holds the MLG in the down position, it will also unlock the stabilizer brace to allow the main gear to be retracted. An auxiliary extension actuator is attached between aircraft structure in the aft section of the wheel well, and to the forward face of the yoke. The auxiliary extension actuator extends the MLG during an alternate extension sequence.
FOR TRAINING PURPOSES ONLY
32-5
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Shock Strut Refer to: •• Figure 32-3. Shock Strut. •• Figure 32-4. M ain Landing Gear Shock Strut. The shock strut is part of the main gear assembly. The dressed shock strut is attached between the yoke and the drag. The shock strut outer cylinder is a Y-shaped component with a single stage nitrogen and oil filled shock absorbing piston fitted inside a cylinder. The function of the shock strut is to absorb the landing forces of aircraft landings.
Figure 32-3. Shock Strut
1
FWD
10
2
11
3
12
4 5 6 7
13
8
14 9
LEGEND 1. Electrical Harness 2. Drag Strut 3. Hydraulic Brake Line 4. Shock Strut 5. Upper Torque Link 6. Shock Strut Piston 7. Lower Torque Link 8. Axle 9. Jack Pad 10. Fairings 11. Electrical Harness 12. Uplock Roller 13. Proximity Sensors 14. Wheel and Brake Assembly 15. Hydraulic Brake Line.
15
Figure 32-4. Main Landing Gear - Shock Strut
32-6
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Installation of the MLG Electrical Harness
32 LANDING GEAR
DASH 8 Q400
NOTES
The main landing-gear (MLG) electrical harnesses includes the weight-on-wheels and the wheel speed sensors electrical harnesses are installed on the drag strut. You can also find them on the shock strut. The downlock electrical harness is installed on the MLG stabilizer brace assembly.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-7
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Axles
NOTES
Refer to Figure 32-5. MLG Axle. The axle is attached to the shock strut piston with a barrel nut and piston plug. The axle is made of steel with chrome-plated bearing surfaces. The axle is removable and interchangeable.
Figure 32-5. MLG Axle
32-8
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Shock Strut Torque Links
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-6. Shock Strut Torque Links. The lower torque link is attached to two lugs on the rear of the shock strut piston. The upper torque link is attached to two lugs on the bottom of the outer cylinder. The torque links, made of heat-treated steel, are the structural link between the shock strut outer cylinder and the piston. Rotation of the shock strut piston and the axle is prevented by these torque links. The upper torque links are the targets for the WOW sensors.
LEGEND 1. Lower Torque Link 2. Upper Torque Link 3. Axle.
2 1 3
Figure 32-6. Shock Strut Torque Links
FOR TRAINING PURPOSES ONLY
32-9
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Drag Strut Refer to Figure 32-7. MLG Drag Strut. The drag strut is attached at the lower end to the shock strut outer cylinder. It is attached with a lubricated hinge point. The upper end of the drag strut is attached to the airframe structure of the forward section of the wheel well with a lubricated hinge point.
The electrical harnesses for the proximity sensors, wheel speed transducers, and hydraulic pipes for the brakes attach to the drag strut with brackets. A grounding point is fitted to the top of the drag strut. The landing gear pivots at the drag strut upper end hinge during retraction and extension.
The drag strut is a fixed length tubular component. A bracket assembly near the top end provides an attach point for the forward door linkage. 1 2
FWD
A
FWD
3
MAIN LANDING GEAR 4
LEGEND 1. Grounding Point 2. Electrical Harness 3. Drag Strut 4. Hydraulic Brake Line 5. Shock Strut.
5
NOTE Left gear shown. Right gear similar.
Figure 32-7. MLG Drag Strut
32-10
FOR TRAINING PURPOSES ONLY
A
DASH 8 Q400
32 LANDING GEAR
MAINTENANCE TRAINING MANUAL
Stabilizer Brace Refer to: •• Figure 32-9. MLG Stabilizer Brace. •• Figure 32-8. MLG Ground Lock Pin. The stabilizer brace is attached to the airframe structure in the forward section of the wheel well with two lubricated hinge points. The aft section of the stabilizer strut is attached to the yoke with two lubricated hinge points. The stabilizer strut has an overcenter link attached between the two sections of the stabilizer strut. The overcenter link supplies a mechanical lock for the MLG in the down position.
Figure 32-8. MLG Ground Lock Pin
LEGEND 1. Downlock Actuator 2. Overcenter Link 3. Yoke 4. Lock Spring 5. Proximity Sensors 6. Stabilizer Brace.
A 2
FWD 1 3
MAIN LANDING GEAR
6
5
NOTE Left gear shown. Right gear similar.
FWD
4
A
Figure 32-9. MLG Stabilizer Brace
FOR TRAINING PURPOSES ONLY
32-11
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Yoke
Shock Strut Fairings
Refer to Figure 32-10. MLG Yoke and Actuator.
Refer to Figure 32-11. Shock Strut Fairings.
The top of the yoke is attached to the rear spar by two lubricated hinge points. The bottom of the yoke is attached to the top of the shock strut by two lubricated hinge points.
The shock strut fairings are installed on the shock struts of the MLG.
The yoke attaches to the stabilizer brace at the cross beam with two lubricated hinge points. The retraction actuator cylinder attaches to the cross beam of the yoke with two lubricated hinge points.
Mounting lugs on the outer cylinder of the shock strut allow installation of the aluminum fairings to the MLG with standard hardware. The function of the fairings is to reduce the aerodynamic drag induced by the extended MLG in flight.
The rod end of the alternate retraction actuator is attached to lugs at the top of the yoke with lubricated hinge points. The yoke assembly is an H-shaped structural component.
2
1
Aft Fairings
Fwd Fairings
LEGEND 1. Aft Fairings 2. Fwd Fairings.
Figure 32-10. MLG Yoke and Actuator
32-12
Figure 32-11. Shock Strut Fairings
FOR TRAINING PURPOSES ONLY
SYSTEM
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
1.
ATA SUB-SYSTEM
PART DESCRIPTION
32---1
MLG SHOCK STRUT FAIRINGS
32 LANDING GEAR
DASH 8 Q400
NUMBER OF PARTS REQUIRED FOR ALL FLIGHT CONDITIONS EXCEPT AS PROVIDED IN COLUMN 2.
2. REMARKS AND/OR EXCEPTIONS
14
All MLG fairings may be missing provided performance limited weights obtained from the DOT approved Airplane Flight Manual, excluding Sub-Sections 5.7, 5.11 and 5.12, are reduced by 450 kg (1,000 lb). Any or all of the following MLG fairings may be missing provided performance limited weights obtained from the DOT approved Airplane Flight Manual, excluding Sub-Sections 5.7, 5.11 and 5.12, are reduced by 340 kg (750 lb). 46712 46702 46703 or 46730 46711 or 46731
Leading Edge, Center Trailing Edge, Sides Center Aft Lower NOTE 1. MLG fairings 46702, 46703 or 46730, and, 46711 or 46731, must be removed if MLG fairing 46712 is removed. 2. MLG fairing 46711 or 46731 must be removed if MLG fairing 46703 or 46730 is removed.
Any or all of the following MLG fairings may be missing provided performance limited weights obtained from the DOT approved Airplane Flight Manual, excluding Sub-Sections 5.7, 5.11 and 5.12, are reduced by 160 kg (350 lb). 46709 Leading Edge, Upper Center 46710 Trailing Edge, Upper Center
Figure 32-12. CDL - MLG Shock Strut Fairings
FOR TRAINING PURPOSES ONLY
32-13
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-12-00 MAIN LANDING GEAR DOORS
The status of the doors is shown on the LANDING GEAR control panel in the flight compartment. The MLG in Figure 32-13 include the components that are listed below:
INTRODUCTION
1. Forward door
The four doors on each engine nacelle provide an aerodynamic enclosure for the MLG when it is in the retracted position.
2. Aft door 3. Push rods
GENERAL
4. Aft door 5. Door seal
Refer to Figure 32-13. Main Gear Doors.
6. Forward door
Two mechanically operated doors enclose the forward section of the MLG wheel well and open and close with movement of the gear.
7. Door seal 8. Door seal 9. Forward door connecting rods
Two hydraulically operated doors enclose the aft section of the MLG wheel well. The aft doors are closed when the MLG is fully retracted and extended. They will open whenever the gear is in transition.
10. Door seal.
3 2
4
FWD 1
5 6
10
9
8
7
Figure 32-13. Main Gear Doors
32-14
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION
The aft doors are opened and closed by a single hydraulic actuator, with a mechanical sequence valve.
Refer to Figure 32-14. MLG Doors - Detail. The forward doors are operated by mechanical links attached to the drag strut.
Lock links supply an overcenter lock for the doors in the closed position. A proximity sensor sends a signal to the PSEU.
When the MLG is extended the forward doors will open. When the MLG is retracted the doors will close.
4
5
6
3
7 8 9
10 2
1
FWD
NOTE Left gear shown. Right gear similar.
LEGEND 1. Forward Doors Connecting Rods 2. Forward Door 3. Alternate Extension Actuator 4. Yoke 5. Mechanical Sequence Valve 6. Retraction Actuator 7. Uplock Assembly 8. Aft Doors Mechanism 9. Alternate Release Arm 10. Aft Door.
Figure 32-14. MLG Doors - Detail
FOR TRAINING PURPOSES ONLY
32-15
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
Aft MLG Doors Connecting Rods
Aft MLG Doors
Refer to Figure 32-15. MLG Aft Doors and Connecting Rods.
Refer to Figure 32-15. MLG Aft Doors and Connecting Rods. The two aft doors have a hinge on both the forward and aft corners. The doors are symmetrical and meet at the center line when closed.
The connecting rods are installed between the pivot arm assembly and attached to the forward hinges of the aft doors.
The aft doors are opened and closed by a single hydraulic actuator and a linkage mechanism. The mechanism is attached to the forward hinges of the doors. 1 2
3
4 A
8
7
FWD
5
LEGEND 1. Mechanical Sequence Valve 2. Pivot Arm 3. Tension Spring 4. Actuator 5. Lock Link 6. Aft Door 7. Proximity Sensor 8. Connecting Rods.
NOTE Left side shown. Right side similar. 6 fs661a01.cgm
A
Figure 32-15. MLG Aft Doors and Connecting Rods
32-16
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Aft Door Mechanism
During the alternate extension of the MLG, the alternate release arm rotates to move the lock links out from an over center position. A tension spring attached to the pivot arm and to the side of the aft section of the wheel well, provides the force to open the doors in alternate operation.
Refer to Figure 32-16. MLG Doors and Connecting Rods. The pivot arm is attached to a frame assembly on the left side aft section of the wheel well. The pivot arm has hinge points to form a bell crank between the push rods and the lock links.
The system also utilizes a proximity sensor which is installed on 2 brackets below the lock link.
The lock links are attached to the bottom of the pivot arm as well as the side of the aft section of the wheel well.
The function of the aft MLG doors mechanism is to open and close the aft MLG doors.
1
3
2
4
5 6
8 7
LEGEND 1. Mechanical Sequence Valve 2. Pivot Arm 3. Tension Spring 4. Actuator 5. Lock Link 6. Proximity Sensor 7. Connecting Rods 8. Alternate Release Arm.
Figure 32-16. MLG Doors and Connecting Rods
FOR TRAINING PURPOSES ONLY
32-17
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Forward MLG Doors Refer to Figure 32-17. Forward MLG Doors and Connecting Rods. The doors are connected to the bottom of the center section of the engine nacelle by hinges. Each door has a hinge on the forward and aft corner. The doors are symmetrical and meet at the engine nacelle center line when closed. The forward doors are operated by adjustable connecting rods attached between the drag strut and the forward doors.
A
LEGEND 1. Door Fitting 2. Push Rods 3. Forward Door 4. Bracket Assembly 5. Drag Strut.
B
D
FW
A
MLG DOOR
1
2
3
4 5
FWD B
Figure 32-17. Forward MLG Doors and Connecting Rods
32-18
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-12-00 DVI MAIN LANDING GEAR DOOR MECHANISMS
32 LANDING GEAR
DASH 8 Q400
NOTES
Inspect the door mechanisms for: •• Damage •• Corrosion •• Cracks •• Failure •• Defects •• Hydraulic Leaks •• Correct Installation •• Security.
FOR TRAINING PURPOSES ONLY
32-19
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
L. DOOR
N. DOOR R. DOOR
LEFT
NOSE
RIGHT RIGHT
LEFT
NOSE
RIGHT RIGHT
MAIN INSTRUMENT PANEL “Amber” Door Open
LANDING GEAR
LANDING GEA R
DN
LOCK RELEASE
UP
HORN MUTE
TEST
fs507a01.cgm
Figure 32-18. Landing Gear Control Panel
32-20
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Refer to: •• Figure 32-18. Landing Gear Control Panel. •• Figure 32-19. Proximity Sensor.
The proximity sensor sends a signal to the PSEU, which will send a signal to the LANDING GEAR control panel. This will show the status of the aft doors. When the doors are open the amber L DOOR and R DOOR lights come on.
A proximity sensor for the aft doors is installed on a bracket below the aft door mechanism.
1 2
3
4
LEGEND 1. Mechanical Sequence Valve 2. Pivot Arm 3. Tension Spring 4. Actuator 5. Lock Link 6. Aft Door 7. Proximity Sensor 8. Push Rods.
8
7
5
FWD
6 fs661a01.cgm
Figure 32-19. Proximity Sensor
FOR TRAINING PURPOSES ONLY
32-21
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
B 1
2
A
A
3
6 4
5 B
VIEW LOOKING UP DOOR OPEN
B
VIEW LOOKING UP DOOR CLOSED
Figure 32-20. Landing Gear Doors - Open and Lock/Unlock and Close (1 of 2)
32-22
FOR TRAINING PURPOSES ONLY
br842a01.dg, gg, 04/01/99
LEGEND 1. Handle 2. Access Door 3. Access Door 4. Guard 5. Switch 6. Handle.
MAINTENANCE TRAINING MANUAL
Open and Lock the Landing Gear Doors The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to: •• Figure 32-20. Landing Gear Doors - Open and Lock/Unlock and Close (1 of 2). •• Figure 32-21. Landing Gear Doors - Open and Lock/Unlock and Close (2 of 2). WARNING
MAKE SURE THAT THE AREA AROUND THE NOSE LANDING GEAR (NLG) DOORS IS CLEAR OF PERSONNEL AND EQUIPMENT. DO THIS BEFORE YOU OPERATE THE ALTERNATE EXTENSION RELEASE HANDLE OF THE NLG. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. Open the landing gear doors as follows: 1. In the flight compartment ceiling, above the co-pilot position, lift the guard then set the LG DOWN SELECT INHIBIT switch to the INHIBIT position. 2. I n t h e f l i g h t c o m p a r t m e n t c e i l i n g , above the co-pilot position, fully open the LANDING GEAR ALTERNATE RELEASE access door.
5. At the forward end of the LANDING GEAR ALTERNATE EXTENSION access door pull the NOSE L/G RELEASE handle to open the NLG doors. 6. Install the lock pin through the hole in the guard and the door mechanism in the NLG wheel well. 7. Install the lock pins in the hole in the brackets of the MLG doors. Make sure that the lock pins go through the hole in the brackets.
Installation of the Main Landing Gear Lock Pins The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. WARNING
DO NOT USE FORCE WHEN YOU INSTALL OR REMOVE THE LOCKPIN. IF FORCE IS NECESSARY, THE LANDING GEAR MAY NOT BE SAFE AND CAN RETRACT ACCIDENTALLY. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE AIRCRAFT. 1. Install the MLG lockpins in the lockpin holes of the stabilizer down-lock mechanism. 2. If you cannot put the MLG lockpin in its hole easily, the main landing gear is not safe. To ensure the safety of the aircraft and personnel, support the weight of the aircraft with the appropriate nose or main jack BEFORE investigating the cause of the problem.
3. Behind the access door, pull the MAIN L/R RELEASE handle to open the MLG doors. 4. On the flight compartment floor, open the LANDING GEAR ALTERNATE EXTENSION access door.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-23
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Bracket
Lock Pin
Hide
TRONAIR
REMOV E
Lock Pin
REMOVE Figure 32-21. Landing Gear Doors - Open and Lock/Unlock and Close (2 of 2)
32-24
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
32-25
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
2
A
3 1
LEGEND 1. Forward Door 2. Forward Door Operating Mechanism 3. Shock Strut Assembly 4. Aft Door 5. Aft Door Actuating Linkage.
4
FWD
5
A
Figure 32-22. Nose Landing Gear and Doors
32-26
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-20-00 NOSE LANDING GEAR AND DOORS
32 LANDING GEAR
DASH 8 Q400
NOTES
INTRODUCTION Refer to Figure 32-22. Nose Landing Gear and Doors. The NLG absorbs the shock of landing and gives stability and direction control during aircraft taxi. The NLG doors enclose the retracted NLG and add to the aerodynamic efficiency of the aircraft.
FOR TRAINING PURPOSES ONLY
32-27
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-21-00 NOSE LANDING GEAR
The nose landing gear assembly is comprised of the following: •• Shock strut assembly
GENERAL
•• Drag strut assembly and
The NLG is installed in the wheel well in the nose fuselage. It is located forward of the forward pressure bulkhead.
•• Harness electrical.
The NLG retracts forward. When retracted, the aft doors will enclose it in the wheel well.
Electrical Harness Electrical Harness Steering Gearbox
Upper Cable Guide Assembly Trunnion Arm Taxi Light Location Centering Actuator WOW Proximity Switch Cover
Tow-Fitting Assembly
Figure 32-23. NLG Dressed Shock Strut Assembly (1 of 2)
32-28
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
A
Outer Cylinder
Jacking Point
Inner Cylinder
Trailing Arm A
Piston Assembly
Link
DETAIL A-A
Figure 32-24. NLG Dressed Shock Strut Assembly (2 of 2)
FOR TRAINING PURPOSES ONLY
32-29
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND 1. Downlock Actuator. 2. Upper Cable Guide Assembly. 3. Upper Drag Strut. 4. Lower Drag Strut. 5. Steering Hydraulic Lines. 6. Taxi Light. 7. Proximity Sensor Cover. 8. Tow-Fitting Assembly. 9. Trailing Arm. 10. Wheels.
11. Electrical Harness. 12. Retraction Actuator. 13. Steering Gearbox. 14. Trunnion Arms. 15. Outer Cylinder. 16. Centering Spring. 17. Piston Assembly. 18. Link. 19. Axle. 20. Jacking Point.
A
1
FWD 11
2 12 3 13
14
4 5
15 6
16 7 17 8 18
NOTE Left wheel removed for clarity.
9 19 20
10 A
ft273a02.cgm
Figure 32-25. NLG Shock Strut Assembly
32-30
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Nose Landing Gear Shock Strut
A low pressure valve located on the top surface of the inner cylinder, is used to service the piston assembly with hydraulic fluid and dry nitrogen.
Refer to: •• Figure 32-25. N LG Shock Strut Assembly. •• Figure 32-26. N LG Shock Strut Assembly. The NLG shock strut is attached to the NLG wheel well structure, retraction actuator, and the NLG drag strut. The shock strut has an outer cylinder, inner cylinder, piston assembly, a link and a trailing arm. The trailing arm has a jacking point for jacking of the NLG. Two trunnion arms are installed at the upper rear portion of the outer cylinder. The retraction actuator is attached to the mounting lugs on the top of the right trunnion arm. At the top forward side of the outer cylinder, there are two mounting lugs. The lower drag strut is attached to these two mounting lugs. The taxi light is installed on the bottom right side of the outer cylinder.
Figure 32-26. NLG Shock Strut Assembly
The power steering hydraulic motor and gearbox assembly are installed on the top of the shock strut between the trunnion arms. The NLG steering centering actuator assembly, steering sensor, and the centering cam are installed on the aft lower side of the outer cylinder. The outer cylinder has attachment points for the electrical harnesses. The WOW proximity sensors are installed on the inner cylinder above the tow fitting assembly. The piston assembly in the inner cylinder is attached to a link. This link is installed between two lugs on the trailing arm.
FOR TRAINING PURPOSES ONLY
32-31
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Nose Landing Gear Trailing Arm
NLG Drag Strut
Refer to Figure 32-27. NLG Trailing Arm.
Refer to:
•• The NLG Trailing Arm is part of the nose gear shock strut assembly. •• The forward end of the trailing arm is attached to the steerable inner cylinder. •• The midpoint of the trailing arm is attached to the shock strut piston assembly with a link assembly. •• The link assembly is installed between two lugs on the trailing arm. •• The aft end of the trailing arm carries the removable nosewheels and axle. •• The trailing arm has a jacking point for jacking the NLG, for tire change, and servicing. •• The link assembly transmits ground loads from the trailing arm to the piston assembly.
Figure 32-27. NLG Trailing Arm
32-32
•• Figure 32-28. NLG Drag Strut. •• Figure 32-29. NLG Drag Strut. The NLG drag strut is attached to the wheel well structure, retraction actuator, lock actuator, and the shock strut. The drag strut assembly contains the following subcomponents: •• Upper drag strut •• Lower drag strut •• Pivot tube assembly •• Spring assemblies (2) •• Link assembly •• Upper lock link and •• Lower lock link.
Figure 32-28. NLG Drag Strut
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
The two spring and the pivot tube assemblies are installed on the upper drag strut. The pivot tube assembly has six arms: •• Two for the spring assemblies
The lower lock link is installed on the lower drag strut and is connected to the upper lock link. The upper lock link is installed on the upper drag strut and is connected to the lock link assembly. The over centering action of the upper and lower lock links makes a mechanical lock when the gear is in the retracted and the extended positions.
•• One for the downlock actuator •• One for the link assembly •• One for the emergency uplock release mechanism and •• One for the ground lock mechanism.
The function of the drag strut assembly is to stabilize the shock strut in either the retracted or the extended position.
FWD B A
2
1
A
NOSE LANDING GEAR
10 3 9 4
8 5
FWD 7 6
ft149a01.cgm
B
LEGEND 1. Pivot Tube Assembly 2. Pivot Tube Arm Downlock Actuator for Ground Lock Attachment Point 3. Pivot Tube Arm for Emergency Uplock Release 4. Lock Link Assembly 5. NLG Alternate Lock Proximity Sensor 6. Lower Drag Strut 7. NLG Primary-Lock Proximity Sensor 8. Upper Lock Link 9. Upper Drag Strut 10. Spring Assembly.
Figure 32-29. NLG Drag Strut
FOR TRAINING PURPOSES ONLY
32-33
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
NLG Electrical Harness The Nose Landing Gear electrical harnesses are attached to the NLG wheel well structure, shock strut, and the drag strut. Three harnesses on the shock strut give power/ signal input for the listed components: •• WOW1/Taxi light harness •• WOW2/Centering actuator harness and •• Nosewheel steering harness.
Figure 32-30. NLG Latest Electrical Harness
32-34
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-22-00 NOSE LANDING GEAR DOORS
32 LANDING GEAR
DASH 8 Q400
NOTES
INTRODUCTION The NLG doors enclose the retracted NLG in the forward fuselage wheel well. They add to the aerodynamic efficiency of the aircraft.
GENERAL The NLG doors are comprised of the following components: •• NLG forward doors •• NLG forward doors connecting rods •• NLG aft doors and •• NLG aft doors connecting rods.
SYSTEM DESCRIPTION The two NLG forward doors are hydraulically operated and close after the gear is extended or retracted. The two NLG aft doors are connected to the NLG shock strut. They travel with the NLG on extension and retraction.
FOR TRAINING PURPOSES ONLY
32-35
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
LEGEND 1. Aft Doors Connecting Rods 2. Aft Doors.
1
2
FWD A
Figure 32-31. NLG Aft Doors and Connecting Rods
32-36
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
Aft NLG Doors Connecting Rods
Aft NLG Doors
Refer to Figure 32-31. NLG Aft Doors and Connecting Rods.
Refer to Figure 32-31. NLG Aft Doors and Connecting Rods.
The two adjustable connecting rods connect the NLG shock strut to the doors for mechanical operation. This allows the doors be rigged correctly, in the closed position.
The two aft, NLG doors are hinged to the fuselage. Each door is made of an inner and outer skin. The two NLG aft doors are connected to the NLG shock strut by two adjustable connecting rod assemblies. These doors are open when the NLG is extended and closed when the NLG is retracted. Each NLG aft door is hinged to the fuselage at two places. The NLG AFT doors provide an aerodynamic fairing following nose gear retraction.
SYSTEM
1.
32 LANDING
ATA SUB-SYSTEM 32---2
GEAR
PART DESCRIPTION NOSE LANDING GEAR AFT DOORS (714, 715)
NUMBER OF PARTS REQUIRED FOR ALL FLIGHT CONDITIONS EXCEPT AS PROVIDED IN COLUMN 2.
2. REMARKS AND/OR EXCEPTIONS 2
One may be missing provided the airspeed is limited to a maximum of 190 KIAS and operable headsets are made available to each pilot. NOTE LRC cruise data may be used for flight planning. Where LRC speed is greater than 190 KIAS, LRC fuel flow data for a given weight, altitude and temperature condition may be conservatively used when flying at 190 KIAS.
Figure 32-32. CDL - Nose Landing Gear Aft Doors
FOR TRAINING PURPOSES ONLY
32-37
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND 1. Door Attachment Bracket 2. Toggle Link Assembly 3. Forward Door Actuator Assembly 4. Link Assembly 5. Mechanical Sequence Valve 6. Alternate Release Cable 7. Bell Crank 8. Spring Assembly 9. Door Attachment Bracket 10. Forward Door 11. Forward Door 12. Forward Doors Connecting Rods.
4
5
A
7
6
8 9
3
10
13 2
1
12
FWD 11
Figure 32-33. NLG Forward Doors and Connecting Rods
32-38
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
NLG Forward Doors Refer to Figure 32-33. NLG Forward Doors and Connecting Rods. The two NLG forward doors are hinged to the fuselage at two places. The forward hinges form the attachment brackets for the operating mechanism.
32-22-00 DVI NOSE LANDING GEAR DOOR MECHANISMS Inspect the door mechanisms for: •• Damage
Each door is made up of an inner skin and an outer skin. The inner skin is contoured to give clearance for the nosewheels in the retracted position.
•• Corrosion
The operating mechanism is comprised of the following;
•• Defects
•• Two adjustable connecting rods •• Extension spring
•• Cracks •• Failure •• Hydraulic Leaks •• Correct Installation •• Security.
•• Bell crank •• Toggle link assembly •• Link assembly •• Mechanical sequence valve •• Hydraulic actuator. This operating mechanism is attached to the forward wall of the nosewheel bay and is protected by a removable debris guard.
NLG Forward Doors Connecting Rods Refer to Figure 32-33. NLG Forward Doors and Connecting Rods. The two adjustable connecting rods connect the bell crank to the doors. To be rigged correctly the doors must be in the closed position.
FOR TRAINING PURPOSES ONLY
32-39
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
L. DOOR
N. DOOR R. DOOR
LEFT
NOSE
RIGHT RIGHT
LEFT
NOSE
RIGHT RIGHT
MAIN INSTRUMENT PANEL “Amber” Door Open
LANDING GEAR
LANDING GEA R
DN
LOCK RELEASE
UP
HORN MUTE
TEST
fs507a01.cgm
Figure 32-34. Main Landing Gear Control Panel
32-40
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Refer to: •• Figure 32-34. M ain Landing Gear Control Panel.
The PSEU sends a signal to the LANDING GEAR control panel, to show the status of the forward doors. When the doors are open the amber N DOOR light comes on.
•• Figure 32-35. N LG Door Proximity Sensor. A proximity sensor is installed on the forward wall of the nosewheel bay. The target of the proximity sensor is on the toggle link assembly. The toggle link assembly is part of the NLG door mechanism. When the doors operate the toggle link assembly moves. This movement is sensed by the proximity sensor. The proximity sensor sends the signal to the PSEU.
Figure 32-35. NLG Door Proximity Sensor
FOR TRAINING PURPOSES ONLY
32-41
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-25-00 NOSE LANDING GEAR GROUND LOCK INTRODUCTION A remotely operated nose gear ground lock mechanism is controlled from the outside of the aircraft.
GENERAL The ground lock control is on the left side nose fuselage. The ground lock mechanically prevents NLG retraction.
The ground-lock control handle has a momentary action pushbutton. Pushing the pushbutton releases the nose gear control handle from the fuselage. This will cause the control handle to spring partly out. The control handle must be pulled fully out and rotated 90º clockwise to point the chevrons towards the ground. This will lock the nose gear. The nose gear ground-lock is engaged when the downlock arm of the pivot tube assembly is on the drag strut of the NLG. When the control handle is in and flush with the fuselage, the nose gear is unlocked.
SYSTEM DESCRIPTION
CAUTION
Refer to Figure 32-36. NLG Ground-Lock Control Handle. The nose gear ground-lock control handle engages the downlock safety lever.
A
If the nose gear ground-lock cannot be engaged, support the aircraft with the nose fuselage jack before investigation.
PRESS BUTTON TO RELEASE PULL AND TURN TO GROUND LOCK NOSE GEAR
PRESS BUTTON TO RELEASE PULL AND TURN TO GROUND LOCK NOSE GEAR
ENGAGED (FULLY EXTENDED)
DISENGAGED (FULLY RETRACTED)
A
Figure 32-36. NLG Ground-Lock Control Handle
32-42
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
COMPONENT DESCRIPTION Nose Gear Ground-Lock Position Indication System (Optional) Refer to Figure 32-37. Nose Gear Ground-Lock Position Indication System. This system is optional for aircraft with Modsum 4-429586. The switch and, cable assembly are located in the nose landing gear wheel well. The ground-lock position indication system is connected to the ground lock control system. A
When you engage the ground-lock system, an advisory indication shows on the pilot’s side panel. 4
LEGEND 1. Cable Switch Assembly 2. Lever Assembly 3. Striker Plate 4. Advisory Light.
2 NOSE GEAR LOCK
3 B
1 A bram44a01.dg, sw, 17/06/02
Figure 32-37. Nose Gear Ground-Lock Position Indication System
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-43
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
PROXIMITY SENSOR ELECTRONIC UNIT
LDG GEAR INOP
CAUTION & WARNING PANEL CONTROL SEQUENCING
GEAR POSITION AND LOCKED INDICATION
MAIN/NOSE GEAR AND DOOR CONTROL VALVES
MAIN/NOSE GEAR AND DOOR POSITIONS
WEIGHT-ON-WHEELS LOGIC PROCESSING
AIRCRAFT SYSTEMS
Figure 32-38. Landing Gear Block Diagram
32-44
FOR TRAINING PURPOSES ONLY
MAIN GEAR ASSEMBLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
32-30-00 LANDING GEAR EXTENSION AND RETRACTION
32-31-00 PRIMARY EXTENSION AND RETRACTION
INTRODUCTION
INTRODUCTION
The landing gear Retraction Control System (RCS) controls the hydraulic retraction and extension of the landing gear. The RCS shows the landing gear and landing gear door status in the flight compartment.
The Primary RCS controls the extension and retraction of the landing gear and the landing gear doors.
GENERAL
There are three conditions required for the PSEU to activate the selector valve. These conditions are as follows:
The main gear retracts aft. The nose gear retracts forward. There is an alternate method for extending the landing gear. Advisory lights give extension/retraction and fail/safe information.
GENERAL
•• Landing gear selector lever is moved to the UP position
SYSTEM DESCRIPTION
•• PSEU receives the signal that the aircraft is WOFW
Refer to Figure 32-38. Landing Gear Block Diagram.
•• NLG is centered.
The LANDING GEAR selector lever and the PSEU control the operation of the landing gear. The No.2 hydraulic system supplies the power to move the landing gear. Hydraulic retraction and extension starts when the landing gear selector lever is unlocked and moved to the desired position. The PSEU checks the landing gear and landing gear door status, comparing the status of both to the position selected. The PSEU then controls the hydraulic sequences to either fully extend or fully retract the landing gear. The indicator lights installed on the landing gear control panel assembly show the landing gear and the landing gear door status. A LDG GEAR INOP caution light is shown on the flight compartment caution and warning panel in the event of a system malfunction.
FOR TRAINING PURPOSES ONLY
32-45
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Landing Gear Selector Valve Refer to Figure 32-39. Landing Gear Selector Valve - Detail. The landing gear selector valve is installed in the right wing to fuselage area. The valve is a self contained assembly which has two solenoid valves. The valve controls the supply of hydraulic pressure to either the extend or retract hydraulic circuits of the landing gear system.
3
2 A
1
LEGEND 1. Electrical Connector 2. Hydraulic Line 3. Selector Valve.
FWD
2
Figure 32-39. Landing Gear Selector Valve - Detail
32-46
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
MLG Retraction Actuator Refer to Figure 32-40. MLG Retraction Actuator - Detail. The MLG retraction actuator cylinder is attached to the lower front of the MLG yoke cross beam. The rod end is attached to the center top of the MLG shock strut. The actuator is a hydraulic device that has two ports. There are restrictors in both ports. The rod end of the actuator piston has a ball and race with a lubrication fitting.
A
FWD
1
MAIN LANDING GEAR (MLG)
2 4
3
A
FWD
LEGEND 1. Retraction Actuator 2. Hydraulic Line Extension 3. Hydraulic Line Retraction 4. Yoke Assembly.
Figure 32-40. MLG Retraction Actuator - Detail
FOR TRAINING PURPOSES ONLY
32-47
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
MLG Downlock Actuator Refer to Figure 32-41. MLG Downlock Actuator - Detail. The MLG downlock actuator is attached to the MLG stabilizer brace assembly. The MLG downlock actuator has two ports. The rod end of the actuator has a ball and race with a lubrication fitting. Hydraulic lines are attached to the two ports and are sealed with O-rings. The MLG downlock actuator locks the landing gear in the down position. A A
FWD
MAIN LANDING GEAR
A
A
Figure 32-41. MLG Downlock Actuator - Detail
32-48
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
MLG Uplock Assembly Refer to: •• Figure 32-42. MLG Uplock Assembly. •• Figure 32-43. M LG Uplock Actuator - Detail. The uplock assembly is attached to a frame at the top of the wheel well. The uplock roller of the MLG engages the inner face of the latch assembly. The latch assembly pivots into the locked position assisted by the two extension springs of the uplock assembly. A lock link prevents the latch assembly from rotating to the UNLOCK position until the piston of the uplock actuator extends during a MLG extension.
Figure 32-42. MLG Uplock Assembly
A
1
FWD
FWD 2
MLG UPLOCK ACTUATOR
LEGEND 1. MLG Uplock Assembly 2. External Spring 3. MLG Uplock Actuator. 3
Figure 32-43. MLG Uplock Actuator - Detail
FOR TRAINING PURPOSES ONLY
32-49
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Mechanical Sequence Valve
Inline Restrictors
The mechanical sequence valve is installed at the forward end of the MLG aft doors. The MLG mechanical sequence valve is a bolt-on assembly.
Refer to Figure 32-44. MLG Doors Inline Restrictors.
The function of the mechanical sequence valve is to correctly sequence the operation of the MLG uplock release and the MLG retraction actuators.
1
Two inline restrictors are installed in the hydraulic lines. Between the mechanical sequence valves and the retraction actuators. The MLG door inline restrictors reduce the flow of hydraulic pressure to the retraction actuators until the gear doors are almost fully open.
A
MLG DOORS
LEGEND 1. Inline Restrictors 2. Mechanical Sequence.
FWD
2
A
Figure 32-44. MLG Doors Inline Restrictors
32-50
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
MLG Solenoid Sequence Valve Refer to Figure 32-45. Landing Gear Doors Solenoid Sequence Valve. The MLG solenoid sequence valves are located in the wheel-well on the left side, they are forward of the aft doors actuator.
The NLG sequence valve is a bolt-on assembly with four ports. The valve is operated by a single coil solenoid. The NLG solenoid sequence valve controls the opening and closing of the doors by porting hydraulic fluid to the door actuator.
The valve is a self contained, bolt-on assembly. It is directly operated by a single coil solenoid. The valve controls opening and closing of aft doors. This is done by porting hydraulic fluid to the door actuators.
NLG Solenoid Sequence Valve Refer to: •• Figure 32-45. L a n d i n g G e a r D o o r s Solenoid Sequence Valve. •• Figure 32-46. N LG Doors Sequence Valve.
Figure 32-46. NLG Doors Sequence Valve
The NLG solenoid sequence valve is located in the lower right section of the NLG bay, on the outer wall.
FWD
A A
fs133a01.cgm
Figure 32-45. Landing Gear Doors Solenoid Sequence Valve
FOR TRAINING PURPOSES ONLY
32-51
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
NLG Retraction Actuator Refer to: •• Figure 32-47. NLG Retraction Actuator. •• Figure 32-48. NLG Retraction and Lock Actuator. The NLG retraction actuator piston is attached to the top right side of the NLG shock strut. The cylinder itself is attached to the aircraft structure. The nose landing gear retraction actuator has two ports. The rod end of the piston which is installed with bushings and a lubrication fitting. The cylinder end of the actuator which has a ball and race with a lubrication fitting.
1
Figure 32-47. NLG Retraction Actuator 2
FW
D
A
LEGEND 1. NLG Lock Actuator 2. NLG Retraction Actuator. ft130a01.cgm
A
Figure 32-48. NLG Retraction and Lock Actuator
32-52
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
NLG Lock Actuator Refer to Figure 32-49. NLG Lock Actuator. The lock actuator is installed between the airframe fitting and the drag strut pivot tube near the lock links. The NLG Lock Actuator unlocks the drag strut lock links.
NLG Inline Restrictors Refer to Figure 32-50. NLG Inline Restrictor. Two inline restrictors are installed in the tee fittings between the mechanical sequence valve and the retraction actuator. The inline restrictors are two-way fluid fittings that restrict hydraulic flow but not pressure. Figure 32-49. NLG Lock Actuator
Tee Fitting (REF)
FWD
Inline Restrictors
A
Figure 32-50. NLG Inline Restrictor
FOR TRAINING PURPOSES ONLY
32-53
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
MAIN INSTRUMENT PANEL B
OVERHEAD CONSOLE
L. DOOR
N. DOOR R. DOOR
LEFT
NOSE
RIGHT RIGHT
LEFT
NOSE
RIGHT RIGHT LDG GEAR INOP
LANDING GEAR
LANDING GEA R
DN
UP B
LOCK RELEASE
HORN MUTE
TEST
A
Figure 32-51. Landing Gear - Controls and Indications
32-54
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-51. Landing Gear - Controls and Indications. The PSEU controls the sequencing logic for the RCS and indications. The Landing Gear Control Panel indicator lights are as follows: •• LEFT, NOSE, RIGHT green lights indicate the gear is down and locked •• L E F T , N O S E , R I G H T r e d l i g h t s indicate the gear is not locked up, or locked down (Transit) •• L DOOR, N DOOR, R DOOR amber lights indicate landing gear doors not closed. An alternate downlock indication system is available. The green indicator lights (One for each landing gear) indicate a down and locked condition. These lights are installed in the flight compartment floor, under the ALTERNATE EXTENSION door. A fault in the landing gear RCS causes the LDG GEAR INOP caution light on the CAWP to illuminate.
Fault Isolation The CAWP shows the LDG GEAR INOP on when the: •• Proximity sensor electronic unit (PSEU) landing gear control has failed •• Landing Gear Inhibit Switch is not stowed correctly in its normal position. For details see the related fault message on the PSEU face panel.
FOR TRAINING PURPOSES ONLY
32-55
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
MAINTENANCE PRACTICES If gear retraction and extension is required, then make sure: •• That the lower cowl is in the closed position, it is recommended that you close the lower cowl to make sure that it is not damaged during landing gear movement.
NOTE If it is necessary for the lower cowl to be open for other maintenance, you can also remove the lower cowl if it cannot be closed. •• That the fuel tank access-panels are installed. Movement of the landing gear with these panels removed is not permitted. •• To disengage the nose gear ground lock. •• To remove the main landing gear lock pins. •• That the controls in the flight compartment are set as follows: °° The landing-gear selector is in the DN position °° The landing-gear inhibit switch is in the NORMAL position °° The nosewheel steering control is in the NEUTRAL position and the selector switch is in the OFF position °° The FLAPS selector lever to the 0° position °° The POWER levers are at or above the FLT IDLE position.
32-56
WARNING MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE LANDING GEAR AND THE AREA OF DOOR MOVEMENT. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. To retract the nlg only: •• Open and lock the landing gear doors. •• Install the main landing gear lock pins. •• Engage the nose landing gear ground lock. •• Lift the aircraft at the jacking point near the fuselage, nose only. •• Disengage the nose gear ground lock. •• Disconnect the main landing gear downlock actuator from the forward lock link assembly. •• Secure the downlock actuator to make sure the actuator piston does not make contact with attaching structure or doors during the retraction or extension. •• Install MLG WOW proximity sensor (copper) test target to simulate a target FAR (air) state.
WARNING DO NOT LIFT THE AIRCRAFT ON JACKS IF YOU THINK THE LOAD AT THE NOSEFUSELAGE JACKING POINT WILL BE 4,700 LB (2,132 KG) OR MORE. IF YOU DO, YOU CAN CAUSE DAMAGE TO THE AIRCRAFT STRUCTURE. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT.
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
32-57
32 LANDING GEAR
32-58 SOLENOID A (DOWN)
FROM POWER TRANSFER UNIT
ENERGIZED SOLENOID B (UP)
LEGEND PRESSURE No.2 HYD RETRACT PRESSURE
NO. 2 HYD
LANDING GEAR BYPASS VALVE
RESTRICTOR
DOWN UP
CLOSE
OPEN NOSE DOOR ACTUATOR
TO LEFT MAIN GEAR
ENERGIZED SOLENOID SEQUENCE VALVE
MECHANICAL SEQUENCE VALVE
CLOSE LOCK RELEASE
OPEN MECHANICAL SEQUENCE VALVE
NOSE GEAR RETRACTION ACTUATOR UP
REAR DOOR ACTUATOR
ENERGIZED SOLENOID SEQUENCE VALVE
UPLOCK ACTUATOR
MAIN GEAR RETRACTION ACTUATOR DOWN UP
AUXILIARY ACTUATOR
DOWNLOCK ACTUATOR
DOWN
LOCK ACTUATOR UPLOCK DOWNLOCK RELEASE RELEASE
LOCK RELEASE RIGHT MAIN GEAR
Figure 32-52. (32-31-00) UP Selection Doors Open
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
PRESSURE
CHECK VALVE LANDING GEAR SELECTOR VALVE
DASH 8 Q400
RETURN PRESSURE
(UP SOLENOID ENERGIZED)
TO NOSEWHEEL STEERING SYSTEM
MAINTENANCE TRAINING MANUAL
32-31-00 PRIMARY EXTENSION AND RETRACTION OPERATION Normal System Operation Refer to:
•• MLG wheel well door actuators close aft doors. When MLG wheel well doors are approximately 7% closed the mechanical sequence valve is closed •• Landing gear selector valve UP solenoid is de-energized by PSEU when the associated proximity sensors indicate that all landing gear are up and locked, and all wheel well doors are closed (following a 10 second delay).
•• Figure 32-52. ( 32-31-00) UP Selection Doors Open. •• Figure 32-53. ( 32-31-00) Gear UP and Doors Locked Closed.
MLG Retraction Sequence The main landing gear retraction sequence is as follows: •• L A N D I N G G E A R l o c k r e l e a s e d , selector lever is moved to UP position •• L a n d i n g g e a r s e l e c t o r v a l v e D N solenoid is de-energized and UP solenoid is energized. (Retraction circuit is pressurized) •• MLG solenoid sequence valves remains energized by PSEU from end of extension cycle •• MLG wheel well door actuators open aft doors •• M L G s t a b i l i z e r b r a c e o v e r c e n t e r downlocks are released •• MLG begin to retract slowly through inline restrictors •• W h e n M L G w h e e l d o o r s a r e approximately 93% open, the mechanical sequence valve is opened and the MLG retracts at full rate •• MLG engages uplocks •• MLG solenoid sequence valves are de-energized by PSEU when the uplock proximity sensors indicate that the MLG are up and locked
FOR TRAINING PURPOSES ONLY
32-59
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-60 SOLENOID A (DOWN)
FROM POWER TRANSFER UNIT
SOLENOID B (UP)
LEGEND PRESSURE NO.2 HYD NO.2 HYD
RETURN PRESSURE
RESTRICTOR
DOWN UP
CLOSE OPEN
NOSE DOOR ACTUATOR
TO LEFT MAIN GEAR
SOLENOID SEQUENCE VALVE
MECHANICAL SEQUENCE VALVE
MAIN GEAR RETRACTION ACTUATOR
CLOSE
LOCK RELEASE
OPEN MECHANICAL SEQUENCE VALVE
NOSE GEAR RETRACTION ACTUATOR UP DOWN
REAR DOOR ACTUATOR
SOLENOID SEQUENCE VALVE
UPLOCK ACTUATOR
DOWNLOCK RELEASE
UP
AUXILIARY ACTUATOR
LOCK RELEASE
LOCK ACTUATOR UPLOCK RELEASE
DOWN
STABILIZER STRUT ACTUATOR
RIGHT MAIN GEAR *ALL SOLENOIDS DE-ENERGIZED
Figure 32-53. (32-31-00) Gear UP and Doors Locked Closed
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
PRESSURE
LANDING GEAR BYPASS VALVE
DASH 8 Q400
CHECK VALVE
GEAR UP AND LOCKED (BOTH SOLENOIDS DE-ENERGIZED)
MAINTENANCE TRAINING MANUAL
NLG Retraction Sequence
32 LANDING GEAR
DASH 8 Q400
NOTES
The nose landing gear retraction sequence is as follows: •• LANDING GEAR selector lever is moved to UP position •• L a n d i n g g e a r s e l e c t o r v a l v e D N solenoid is de-energized and UP solenoid is energized (Retraction circuit is pressurized) •• NLG solenoid sequence valve remains energized by PSEU from end of extension cycle •• NLG wheel well door actuator opens forward doors •• NLG drag strut overcenter downlock is released •• NLG begins to retract slowly through inline restrictors •• When NLG wheel doors are approximately 92% open, the mechanical sequence valve is opened and the NLG retracts at full rate NLG drag strut overcenter uplock is energized •• N L G s o l e n o i d s e q u e n c e v a l v e i s de-energized by PSEU when the NGDN and NGLK proximity sensors indicate that the NLG is up and locked •• NLG wheel well door actuator closes forward doors. When NLG wheel well doors are approximately 8% closed the mechanical sequence valve is closed •• Landing gear selector valve UP solenoid is de-energized by PSEU when the associated proximity sensors indicate that all landing gear are up and locked, and all wheel well doors are closed (following a 10 second delay).
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-61
32 LANDING GEAR
32-62 DASH 8 Q400 MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
NOSE WHEEL CENTERED
Figure 32-54. (32-31-00) Landing Gear Retraction (Sheet 1 of 3)
MAINTENANCE TRAINING MANUAL
Landing Gear Retraction
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to: Figure 32-54. (32-31-00) Landing Gear Retraction (Sheet 1 of 3). Before landing gear retraction can start, the PSEU must receive the signals as follows: •• LG control handle is in the RETRACT position •• WOW sensors show that the aircraft is in the air as reported •• LG control is NOT inhibited •• The nosewheel is centered •• The landing gear doors are OPEN. When these conditions are achieved the PSEU de-energizes the EXTEND solenoid and at the same time outputs 28 VDC to Pin L of the LG control panel. Because the LG control handle is in the retract position, the LG selector switch is positioned to output the 28 VDC through Pin R to the RETRACT solenoid of the LG selector valve. Hydraulic pressure through the retract solenoid acts on one end of the hydraulic spool valve. The other end of the hydraulic spool is open to return through the de-energized EXTEND solenoid. The hydraulic spool is moved to the position that allows the hydraulic pressure to be applied to the retract manifold through the bypass valve. At the same time the PSEU energizes the solenoid sequence valves by outputting 28 VDC to each valve, the hydraulic pressure then passes through the valves to the door actuators to open the landing gear doors.
FOR TRAINING PURPOSES ONLY
32-63
32 LANDING GEAR
32-64 J K
K J
LL LL MM MM NN NN
J K GS2
G-
43
LG SAFE
C-
41
NG SAFE
ADVISORY CONTROL UNIT
43
L
L
3C
41
M
M
3E
N
3D
E-
45
45
N
RG NOT SAFE
H-
44
44
P
P
4C
LG NOT SAFE
D-
42
42
R
R
3B
S
NG NOT SAFE
F-
46
46
S
3A
RG DOOR OPEN
D
64
64
T
T
12E
LG DOOR OPEN
F
62
62
U
U
11E
NG DOOR OPEN
E
63
63
V
V
11D
GEAR UNSAFE
A-
47
47
W
W
AFT TOP WING X-OVER
AFT WING ROOT DISC LH
PSEU ATA 32-61
17
X
X
18
Y
Y
U
U
BF
RH U/FLR DISC. X=-18. GS3
FWD WING ROOT DISC RH
R
DE-
R
J-
Z
Z
E40
28VDC CHASSIS
PT-
HORN MUTE SWITCH
V W
HORN TEST
X B-
UP LANDING GEAR CONTROL HANDLE DOWN
A B P R L H
GS7 GS6 GS5
GS4
9A
50
9B
49
5A
A-
A-
B-
B-
68
MAINTENANCE PANEL
C-
C-
65
D-
D-
EFG-
EFG-
WARDROBE
E41
31-41-00 P1A 10J
GS8 GS9
FWD WING ROOT DISC LH
E45 P1B
P1B
E42
10H 1G
DOOR SEQUENCE VALVE
DE-
5E
RETRACT
1F E43
F. D. ABV POWER LEVERS
UPR LHS DISC X=60
1H 5H
A B C
RIGHT LG BAY
E44
2A
FLT. DECK ABV/FLOOR RH 28VDC
L/G SELECTOR VALVE
BF
1K
P1C
A C B
RIGHT WING ROOT
10C
LAMP TEST 1 LAMP TEST 2
A B C
EXTEND
CO-PILOT BLKHD DISC.
Figure 32-55. (32-31-00) Landing Gear Retraction (Sheet 2 of 3)
A B C
DOOR SEQUENCE VALVE LEFT LG BAY
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RG SAFE
A B C
DASH 8 Q400
LANDING GEAR CONTROL AND INDICATION PANEL
MAINTENANCE TRAINING MANUAL
Refer to Figure 32-55. (32-31-00) Landing Gear Retraction (Sheet 2 of 3).
32 LANDING GEAR
DASH 8 Q400
NOTES
The PSEU outputs 28 VDC through Pins 12E, 11D and 11E to the LG Control and Indication Panel to bring on the door OPEN amber lights. Hydraulic pressure is applied through a restrictor to the MLG downlock actuator, the actuator retracts and unlocks the overcenter lock in the stabilizer brace assembly. Pressure is also applied to the NLG lock release actuator to unlock the overcenter lock condition of the upper and lower drag strut assemblies. The PSEU outputs 28 VDC through the advisory control unit for the following: •• MLG unsafe red lights through Pin 4C and Pin 3B to Pins H and D •• NLG unsafe red light through Pin 3A to Pin F •• Light in the control handle through Pin 2A to Pin A on the LG Control and Indication Panel. Before the doors are 93% open, the only pressure going to the retraction actuators passes through the inline restrictors. When the doors are approximately 93% open, the mechanical sequence valve is opened by operation of the door operating mechanism. This allows hydraulic pressure and flow to bypass the inline restrictors, going directly to the retraction actuators. The full on restrictors of the landing gear actuators control the speed of retraction.
FOR TRAINING PURPOSES ONLY
32-65
32 LANDING GEAR
32-66 A
1J
B
NW CENTRED
S04
S18
B
12J
A
12K
D E
B
RIGHT GEAR UP LOCK
PROXIMITY SENSOR INPUT (PSC A)
S19 NOSE GEARDRCL S09
13J
NOSE GEARDN1 S11
13K
NOSE GEARLK1 S03 NOSE GEARWOFW1
NOSE GEAR LOCK 2
S12
S10
NOSE GEAR WOW 1
S03
NOSE GEAR DOOR CLOSED
S19
8G
A
8H
B
7J
A
7K
B
7B
A
7A
B
9D
A
9C
B
13D
A
13C
B
12B
A
12A
LGDLK1
S15
NOSE GEAR DOWN 1
S11
S09
S12 NOSE GEARLK2
RIGHT GEAR DOWN LOCK 2
S01 LGWOW1
PROXIMITY SENSOR INPUT (PSC D)
S08 LGDLK2
S17 LGDRCL S02 LGWOW2
RIGHT WEIGHT-ON WHEELS 2
S13 RGDLK1
28 V DC/OC DISCRETE OUTPUT (PSC A)
DOOR SEQUENCE VALVE
J/P51 A
S16 RGUPLK
S05 RGWOW1
S20 RGDRCL
S06 RGWOW2
LEFT WEIGHT-ON WHEELS 2
LEFT GEAR DOWN LOCK 2
B
DOOR SEQUENCE VALVE
LEFT GEAR DOWN LOCK 1 LEFT GEAR UP LOCK
1H
9B 9A
B
8J
S14
A
8K
PROXIMITY SENSOR INPUT (PSC B)
S06
S13
S05
B
13G
A
13H
B
13B
A
13A
F
8D
G
8C
PROXIMITY SENSOR INPUT (PSC A)
PROXIMITY SENSOR INPUT (PSC D)
PROXIMITY SENSOR INPUT (PSC E)
RGDLK2
LEFT GEAR DOOR CLOSED
1K
B
B A
PROXIMITY SENSOR INPUT (PSC D)
S14
LEFT WEIGHT-ON WHEELS 1 J/P52 A
14A
S04 NOSE GEARWOFW2
RIGHT WEIGHT-ON WHEELS 1
LGUPLK
NOSE GEAR LOCK 1
S10 NOSE GEARDN2
RIGHT GEAR DOWN LOCK 1
S07
14B
NW
PROXIMITY SENSOR INPUT (PSC B)
PROXIMITY SENSOR INPUT (PSC E)
S20
B A
S02
S08
S01
S17
S07
S15
32-61 A1 PROXIMITY SENSOR ELECTRONIC UNIT (PSEU)
Figure 32-56. (32-31-00) Landing Gear Retraction (Sheet 3 of 3)
B
12G
A
12H
B
7G
A
7H
F
7D
G
7C
B
8B
A
8A
B
12D
A
12C
B
14D
A
14C
PROXIMITY SENSOR INPUT (PSC A)
PROXIMITY SENSOR INPUT (PSC E)
PROXIMITY SENSOR INPUT (PSC E)
PROXIMITY SENSOR INPUT (PSC B)
PROXIMITY SENSOR INPUT (PSC D)
32-61 A1 PROXIMITY SENSOR ELECTRONIC UNIT (PSEU)
B
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
NOSE GEAR DOWN 2
B
RIGHT GEAR DOOR CLOSED
S18
S16
DASH 8 Q400
NOSE GEAR WOW 2
28 V DC/OC DISCRETE OUTPUT (PSC A)
MAINTENANCE TRAINING MANUAL
Refer to Figure 32-56. (32-31-00) Landing Gear Retraction (Sheet 3 of 3).
32 LANDING GEAR
DASH 8 Q400
NOTES
When the PSEU gets all the signals listed below: •• RMG uplock sensor at Pin D14A and D14B •• LMG uplock sensor at Pin D14C and D14D •• NG lock 1 at Pins D13C and D13D •• NG lock 2 at Pins B8G and B8H • • The solenoid sequence valves are de-energized. Hydraulic pressure will now be supplied to the close side of the door actuators closing the doors. When the PSEU gets all the signals that follow: •• RMG Door Closed at Pins B9A and B9B •• LMG Door Closed at Pins B8A and B8B •• NG Door Closed at Pins E9C and E9D. The RETRACT solenoid in the LG selector valve is de-energized and the door OPEN amber lights extinguish. The hydraulic pressure is released from the end of the hydraulic spool through the de-energized RETRACT solenoid and, the spool is centralized by the springs. All hydraulic pressure to the landing gear retraction system is removed and both sides of all actuators in the system are open to return.
FOR TRAINING PURPOSES ONLY
32-67
32 LANDING GEAR
32-68 ENERGIZED SOLENOID A (DOWN)
FROM POWER TRANSFER UNIT
SOLENOID B (UP)
LEGEND SYSTEM INPUT PRESSURE EXTEND PRESSURE
NO.2 HYD
CHECK VALVE
LANDING GEAR SELECTOR VALVE (DOWN SOLENOID ENERGIZED)
RESTRICTOR
DOWN UP
CLOSE
OPEN NOSE DOOR ACTUATOR
TO LEFT MAIN GEAR
MECHANICAL SEQUENCE VALVE DE-ENERGIZED SOLENOID SEQUENCE VALVE
MAIN GEAR RETRACTION ACTUATOR
CLOSE
LOCK RELEASE
OPEN MECHANICAL SEQUENCE VALVE
REAR DOOR ACTUATOR NOSE GEAR RETRACTION ACTUATOR
DE-ENERGIZED SOLENOID SEQUENCE VALVE
UPLOCK ACTUATOR
DOWN
AUXILIARY ACTUATOR
UP DOWN
UPLOCK RELEASE
UP
DOWNLOCK ACTUATOR LOCK RELEASE
LOCK ACTUATOR DOWNLOCK RELEASE
RIGHT MAIN GEAR
Figure 32-57. Initial DOWN Selection Doors Opening
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
LANDING GEAR BYPASS VALVE
DASH 8 Q400
TO NOSEWHEEL STEERING SYSTEM
RETURN PRESSURE
MAINTENANCE TRAINING MANUAL
Main Landing Gear Extension
Nose Landing Gear Extension
Refer to:
The nose landing gear extension sequence is as follows:
•• Figure 32-57. I nitial DOWN Selection Doors Opening. •• Figure 32-58. Selection Completed Doors Closed. The main landing gear extension sequence is as follows: •• LANDING GEAR selector lever is moved to DN position •• Landing gear selector valve DN solenoid is energized by PSEU (Normal extension circuit is pressurized) •• MLG solenoid sequence valves remains de-energized by PSEU from end of retraction cycle
•• LANDING GEAR selector lever is moved to DN position •• L a n d i n g g e a r s e l e c t o r v a l v e D N solenoid is energized by PSEU (Normal extension circuit is pressurized) •• NLG solenoid sequence valves remains de-energized by PSEU from end of retraction cycle •• NLG wheel well door actuator opens forward doors •• NLG drag strut over-center uplock is released •• NLG begins to extend slowly through in-line restrictors
•• MLG uplocks are released
•• When NLG wheel doors are approximately 92% open, the mechanical sequence valve is opened and the NLG extends at full rate
•• MLG begin to extend slowly through in-line restrictors
•• NLG drag strut over-center downlock is engaged
•• W h e n M L G w h e e l d o o r s a r e approximately 93% open, the mechanical sequence valve is opened and the MLG extends at full rate
•• N L G s o l e n o i d s e q u e n c e v a l v e i s energized by PSEU when the NGDN and NGLK proximity sensors indicate that the NLG is down and locked
•• MLG stabilizer brace over-center downlocks are engaged
•• NLG wheel well door actuator closes forward doors. When NLG wheel well doors are approximately 8% closed, the mechanical sequence valve is closed
•• MLG wheel well door actuators open aft doors
•• MLG solenoid sequence valves are energized by PSEU when the stabilizer brace proximity sensors indicate that the MLG are down and locked •• MLG wheel well door actuators close aft doors. When MLG wheel well doors are approximately 7% closed the mechanical sequence valve is closed
•• L a n d i n g g e a r s e l e c t o r v a l v e D N solenoid, MLG solenoid sequence valve, and NLG solenoid sequence valve remain energized by PSEU after extension is complete.
•• L a n d i n g g e a r s e l e c t o r v a l v e D N solenoid, MLG solenoid sequence valve, and NLG solenoid sequence valve remain energized by PSEU after extension is complete.
FOR TRAINING PURPOSES ONLY
32-69
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-70 ENERGIZED SOLENOID A (DOWN)
SOLENOID B (UP)
FROM POWER TRANSFER UNIT
LEGEND PRESSURE SYSTEM EXTEND PRESSURE
NO.2 HYD
CHECK VALVE
LANDING GEAR SELECTOR VALVE (DOWN SOLENOID ENERGIZED) LANDING GEAR BYPASS VALVE
RESTRICTOR
DOWN UP
CLOSE TO LEFT MAIN GEAR
OPEN NOSE DOOR ACTUATOR
ENERGIZED SOLENOID SEQUENCE VALVE
MECHANICAL SEQUENCE VALVE
MAIN GEAR RETRACTION ACTUATOR
CLOSE
LOCK RELEASE
OPEN MECHANICAL SEQUENCE VALVE NOSE GEAR RETRACTION ACTUATOR
REAR DOOR ACTUATOR
ENERGIZED SOLENOID SEQUENCE VALVE
UPLOCK ACTUATOR
DOWN
AUXILIARY ACTUATOR
DOWNLOCK ACTUATOR
UP DOWN
LOCK ACTUATOR UPLOCK DOWNLOCK RELEASE RELEASE
UP
LOCK RELEASE
* ALL SOLENOIDS ENERGIZED
Figure 32-58. Selection Completed Doors Closed
RIGHT MAIN GEAR
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
TO NOSEWHEEL STEERING SYSTEM
RETURN PRESSURE
MAINTENANCE TRAINING MANUAL
Landing Gear Normal Extension
32 LANDING GEAR
DASH 8 Q400
NOTES
Before the landing gear normal extension can start, the PSEU must receive the signals that follow: •• EXTCMD discrete input on Pin A10H •• No LDGINH signal at Pin A10K. The PSEU outputs 28 VDC to Pin H of the LG Control and Indication panel. Because the LG control lever is selected, DOWN 28 VDC is output on Pin J to energize the EXTEND solenoid in the LG selector valve. Hydraulic pressure is directed through the EXTEND solenoid to one end of the hydraulic spool, the other end is open to return through the de-energized RETRACT solenoid. The hydraulic spool is positioned to supply hydraulic pressure directly to the EXTEND manifold. The pressure is supplied through the de-energized solenoid sequence valves to the retract side of the door actuators to OPEN the hydraulically operated doors. Pressure is also supplied to the following: •• The extend side of the MLG uplock actuators to release the uplock •• The extend side of the NLG lock release actuator to unlock the overcenter lock in the upper and lower drag strut assembly •• Through the inline restrictors to the retraction/extension actuators. The PSEU outputs 28 VDC through the Advisory Control Unit for the following: •• The MLG unsafe red lights through Pin 4C and Pin 3B to Pins H and D •• NLG unsafe red light through Pin 3A to Pin F •• The light in the control handle through Pin 2A to Pin A on the LG Control and Indication Panel.
FOR TRAINING PURPOSES ONLY
32-71
32 LANDING GEAR
32-72 A
NOSE GEAR DOOR SEQUENCE VALVE
NW CENTRED
S04
S18
B
12J
A
12K
D E
28 V DC/OC DISCRETE OUTPUT (PSC A)
B
RIGHT GEAR UP LOCK
PROXIMITY SENSOR INPUT (PSC A)
S19 NOSE GEARDRCL S09
13J
NOSE GEARDN1 S11
13K
NOSE GEARLK1 S03 NOSE GEARWOFW1
NOSE GEAR LOCK 2
S12
S10
NOSE GEAR WOW 1
S03
NOSE GEAR DOOR CLOSED
S19
8G 8H
B
7J
A
7K
B
7B
A
7A
B
9D
A
9C
B
13D
A
13C
NOSE GEAR DOWN 1
B
12B
S09
A
12A
NOSE GEARDN2 S12 NOSE GEARLK2
RIGHT GEAR DOWN LOCK 2
S07 LGDLK1
S01 LGWOW1
PROXIMITY SENSOR INPUT (PSC D)
S08 LGDLK2
S17 LGDRCL S02 LGWOW2
RIGHT WEIGHT-ON WHEELS 2
S13
A
RGDLK1
28 V DC/OC DISCRETE OUTPUT (PSC A)
DOOR SEQUENCE VALVE
A
S16 RGUPLK
S05 RGWOW1
S20 RGDRCL
S06 RGWOW2
LEFT WEIGHT-ON WHEELS 2
LEFT GEAR DOWN LOCK 2
B
DOOR SEQUENCE VALVE
LEFT GEAR DOWN LOCK 1 LEFT GEAR UP LOCK
1H
9B 9A
S14
B
8J
A
8K
PROXIMITY SENSOR INPUT (PSC B)
S06
S13
S05
B
13G
A
13H
B
13B
A
13A
F
8D
G
8C
PROXIMITY SENSOR INPUT (PSC A)
PROXIMITY SENSOR INPUT (PSC D)
PROXIMITY SENSOR INPUT (PSC E)
RGDLK2
LEFT GEAR DOOR CLOSED
1K
B A
PROXIMITY SENSOR INPUT (PSC D)
S14
LEFT WEIGHT-ON WHEELS 1
B
14A
S04 NOSE GEARWOFW2
RIGHT GEAR DOWN LOCK 1
S15
S11
S10
RIGHT WEIGHT-ON WHEELS 1 PROXIMITY SENSOR INPUT (PSC E)
S20
14B
NWCENT
PROXIMITY SENSOR INPUT (PSC B)
LGUPLK
NOSE GEAR LOCK 1
S18
B A
32-61 A1 PROXIMITY SENSOR ELECTRONIC UNIT (PSEU)
Figure 32-59. (32-31-00) Landing Gear Normal Extension
S02
S08
S01
S17
S07
S15
B
12G
A
12H
B
7G
A
7H
F
7D
G
7C
B
8B
A
8A
B
12D
A
12C
B
14D
A
14C
PROXIMITY SENSOR INPUT (PSC A)
PROXIMITY SENSOR INPUT (PSC E)
PROXIMITY SENSOR INPUT (PSC E)
PROXIMITY SENSOR INPUT (PSC B)
PROXIMITY SENSOR INPUT (PSC D)
32-61 A1 PROXIMITY SENSOR ELECTRONIC UNIT (PSEU)
B
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
NOSE GEAR DOWN 2
B A
RIGHT GEAR DOOR CLOSED
S16
DASH 8 Q400
NOSE GEAR WOW 2
1J
B
MAINTENANCE TRAINING MANUAL
Refer to Figure 32-59. (32-31-00) Landing Gear Normal Extension. When the doors are approximately 93% open, full hydraulic pressure and flow is supplied to the actuators to extend the gear. When the main gear is down and locked, the PSEU receives signals from the MLG sensors that follow:
The mechanical sequence valves are closed by the action of the door operating mechanism and pressure is maintained to the landing actuators and lock actuators through the inline restrictors. The EXTEND solenoid and the solenoid selector valves remain energized.
•• RMG Downlock 1 on Pins E8C and E8D •• RMG Downlock 2 on Pins B8J and B8K •• LMG Downlock 1 on Pins D12C and D12D •• LMG Downlock 2 on Pins E7G and E7H. When the nose gear is down and locked, the PSEU receives signals from the NLG that follow: •• NG Down 1 on Pins D12A and D12B •• NG Lock 1 on Pins D13C and D13D •• NG Down 2 on Pins B7J and B7K •• NG Lock 2 on Pins B8G and B8H. When the PSEU has received the down and locked signals from the LG sensors, it energizes the solenoid sequence valves. Hydraulic pressure is supplied to the extend side of the door actuators closing the doors. The PSEU receives the following signals from the door sensors: •• RG Door Closed on Pins B9A and B9B •• LG Door Closed on Pins B8A and B8B •• NG Door Closed on Pins E9C and E9D. The PSEU turns OFF the amber door lights on the LG control and indication panel.
FOR TRAINING PURPOSES ONLY
32-73
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-74
BY PASS
A
MAIN L/G RELEASE
MAIN DOOR UPLOCK RELEASE
PULL FULLY DOWN
CAUTION ENSURE ALL WHEEL WELLS ARE CLEAR OF OBSTRUCTIONS BEFORE CLOSING ACCESS PANEL TO CLOSE DUMP VALVE.
NOSE DOOR UPLOCK RELEASE A
LEGEND CABLE CIRCUIT CONTROL LINKAGE HYDRAULIC PRESSURE
TO MAIN GEAR AUXILIARY ACTUATORS
LANDING GEAR ALTERNATE RELEASE DOOR (OPEN)
HAND PUMP B
LANDING GEAR ALTERNATE EXTENSION DOOR (OPEN)
fsr81a01.cgm
Figure 32-60. Alternate Extension System Block Diagram
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
B
DASH 8 Q400
MAIN GEAR UPLOCK RELEASE
NOSE GEAR UPLOCK RELEASE
VALVE
MAINTENANCE TRAINING MANUAL
32-34-00 ALTERNATE EXTENSION SYSTEM
32 LANDING GEAR
DASH 8 Q400
NOTES
INTRODUCTION The alternate extension system is used to extend the landing gear when the No.2 hydraulic system or the PSEU is not serviceable. The system can also be used, if the normal extension system fails to lock the landing gear in the down position. The system is also used to open the landing gear doors for service or maintenance.
GENERAL Refer to Figure 32-60. Alternate Extension System Block Diagram. The alternate extension system is a self resetting, cable actuated design. Access to controls for the alternate extension system is through the flight compartment. The alternate extension system includes a bypass valve to isolate the landing gear hydraulics from the No.2 hydraulic system. A manual hand pump hydraulic system is available to assist in lowering the main landing gear (only) into the down and locked position. The landing gear inhibit switch isolates the PSEU from the landing gear selector output when it is selected to the INHIBIT position. The alternate extension system has the listed components: •• Alternate release handles (2) •• Alternate release door •• Alternate extension door •• Alternate extension actuators (2) •• Bypass valve and •• Control cables.
FOR TRAINING PURPOSES ONLY
32-75
32 LANDING GEAR
32-76 HAND PUMP
A
FW
D
A
LANDING GEAR ALTERNATE EXTENSION DOOR (OPEN)
NOTE Left Gear shown. Right Gear similar. EMERGENCY SELECTOR VALVE (CLOSED POSITION)
MLG STABILIZER BRACE ASSEMBLY LEGEND
SUCTION LINE PRESSURE LINE fsr82a01a.cgm
Figure 32-61. Alternate Extension Hydraulic Synoptic
LOWER RIGHT NOSE COMPARTMENT
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
AUXILIARY ACTUATOR
DASH 8 Q400
EMERGENCY HYDRAULIC RESERVOIR 1.25 U.S. QUARTS (1.2 LITRES)
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-61. Alternate Extension Hydraulic Synoptic. The hand pump is located below the flight compartment floor, adjacent to the co-pilot seat. The hand pump is used to lower the landing gear following hydraulic system 2 isolation. A hand pump handle is installed in the flight compartment on the bulkhead behind the co-pilot seat. The handle must be installed into the pump to operate the pump. The MLG extension selector valve is located below the flight compartment floor adjacent to the co-pilot seat. The valve has a 2-way, 2-position control valve, a pressure relief valve, and a filtered inlet and return port. There is a pivoting link that attaches the selector valve to the hand pump access door. The selector valve moves from the normally open position to the closed position when the access door is opened. The pressure relief valve limits the pressure that may be applied to the alternate gear down actuators by relieving the hand pump pressure. The alternate landing gear extension hydraulic reservoir is located in the nose compartment of the aircraft. This reservoir is made from aluminum and has a capacity of 1 US qt (0.95 L). The reservoir has a threaded, vented, removable lid which has three fittings installed. One fitting serves as a fill port; the second fitting is the vent, and the third fitting is the outlet port to the hand pump. The lid also has a dipstick with minimum and maximum volume markings to allow filling of the reservoir to the correct fluid level.
FOR TRAINING PURPOSES ONLY
32-77
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Dust Cap Dipstick
Fill Connection
SAFE
Reservoir
Figure 32-62. Servicing of the Auxiliary System Hydraulic Reservoir
32-78
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Servicing of the Alternate LandingGear Extension Hydraulic Reservoir
32 LANDING GEAR
DASH 8 Q400
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 32-62. Servicing of the Auxiliary System Hydraulic Reservoir. The auxiliary reservoir is for the emergency extension of the main landing gear. It is installed in the bottom right side of the nose compartment. •• Remove the dipstick to check the fluid quantity level. •• If the fluid level is below the SAFE mark, fill the reservoir to the SAFE mark. •• Replace the dipstick in the reservoir. •• Remove the dust cap from the fill connection. •• Connect the quick-disconnect coupling of the fluid dispenser to the fill connection. •• Fill the auxiliary reservoir up to the SAFE mark on the dipstick. •• Replace the dipstick. •• Disconnect the coupling of the fluid dispenser and replace the dust cap. •• Clean the area with the lint free cloth.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-79
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Main Gear Alternate Release Handle Refer to Figure 32-63. Main Gear Alternate Release Handle. The alternate release handle is located in the ceiling of the flight compartment behind the LANDING GEAR ALTERNATE RELEASE door. The handle is connected to the MLG uplocks and the MLG aft doors release mechanisms. A cam mechanism makes sure that the MLG aft doors open before the MLG uplocks release the MLG.
2
3
4
1
5
LEGEND 1. Door Compression Spring 2. Main Gear Alternate Release Handle 3. Cables to Slide Assembly 4. Cables to Bypass Valve 5. Door Pulley 6. Landing Gear Alternate Release Door 7. Landing Gear Inhibit Toggle Switch.
CAUTION ENSURE ALL WHEEL WELLS ARE CLEAR OF OBSTRUCTIONS
BEFORE CLOSING ACCESS PANEL TO CLOSE DUMP VALVE
6
INHIBIT NORMAL
Figure 32-63. Main Gear Alternate Release Handle
32-80
FOR TRAINING PURPOSES ONLY
7
MAINTENANCE TRAINING MANUAL
Nose Gear Alternate Release Handle Refer to Figure 32-64. NLG Alternate Release Handle. The NLG alternate release handle is located in the floor of the flight compartment under the LANDING GEAR ALTERNATE EXTENSION door.
The pulley cam mechanism makes sure that the NLG forward doors open before the NLG uplock is opened to release the NLG. After the alternate release handle has been pulled, gravity and the airstream force the NLG to the down position, the gear locks by the overcenter mechanism of the upper, and lower drag struts.
The handle is connected by cables, turnbuckles and pulleys to the NLG uplock release arm, pulley cam mechanism and to the NLG door release operating arm.
1 A
LEGEND 1. Landing Gear Alternate Extension Door 2. Landing Gear Downlock Verification Lights 3. Landing Gear Downlock Verification Switch 4. Landing Gear Alternate Extend Hand Pump 5. MLG Alternate Extension Actuator Bypass Valve 6. Nose Gear Alternate Release Handle.
6
5
FWD
4
2 A 3
Figure 32-64. NLG Alternate Release Handle
FOR TRAINING PURPOSES ONLY
32-81
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Alternate Extension Actuator Refer to Figure 32-65. Alternate Extension Actuator. The alternate extension actuators are installed in the MLG wheel wells between the nacelle structure and the MLG yoke assembly.
The actuator has a single port for extend pressure only. The alternate extension actuators are used to extend the landing gear to the down and locked position.
They are located on the right side of each MLG yoke. The hydraulic pressure required to operate the actuators is supplied by a hand pump located in the flight compartment floor. A
B
FWD
FWD
A
MLG STABILIZER BRACE AND YOKE ASSEMBLY
Figure 32-65. Alternate Extension Actuator
32-82
FOR TRAINING PURPOSES ONLY
B
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
Alternate Extension Downlock Indicators and Switch Refer to Figure 32-66. Landing Gear Downlock Verification Switch. The alternate extension downlock indicator and switch are installed in a panel located behind the LANDING GEAR ALTERNATE EXTENSION door, in the flight compartment floor. The switch is beside a light panel that contains three green lights. It is a two position, momentary type toggle switch. In the ON position the switch provides a ground to the three alternate down lock lights.
1
A
LEGEND 1. Landing Gear Alternate Extension Door 2. Landing Gear Downlock Verification Lights 3. Landing Gear Downlock Verification Switch.
FWD
2 A
3
Figure 32-66. Landing Gear Downlock Verification Switch
FOR TRAINING PURPOSES ONLY
32-83
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Operating Lever
Pulleys
Bypass Valve
Restrictor
FWD Turnbuckles
Cables From Door Pulley
Figure 32-67. Bypass Valve and Alternate Release Cables
32-84
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Bypass Valve
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-67. Bypass Valve and Alternate Release Cables. The landing gear bypass valve is installed in the forward right wing root area. It is adjacent to the landing gear selector valve. The bypass valve is actuated when the LANDING GEAR ALTERNATE RELEASE door is opened. During alternate extension, the bypass valve isolates the No.2 hydraulic supply lines from the main and nose gear retraction actuators, and connects the pressure lines to the return lines. The union attached to the down port is restricted.
FOR TRAINING PURPOSES ONLY
32-85
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Cable
Cam Mechanism Assembly
Cable
Cable To Uplock Assy
A
Figure 32-68. MLG Alternate Extension System Cam Mechanism Assembly
32-86
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
MLG Alternate Release Control Cables Refer to Figure 32-68. MLG Alternate Extension System Cam Mechanism Assembly. Control cables are routed from the MLG alternate release handle through a slider mechanism, located in the ceiling of the aircraft, forward of the wing root. The slider mechanism lets the full force of the pull be concentrated first on the release of one MLG and then on the other.
•• Release the input lever. Make sure the cam assembly moves smoothly, with no binding or resistance, to its fully rested position •• I f t h e c a m m o v e m e n t i s f u l l a n d unrestricted, no further action is required •• If there is binding or sticking in the cam assembly when you return it to its full rested position, remove the unit and install a new or serviceable unit.
The control cables are then routed through to the engine nacelles to the cam mechanisms. The cam mechanism allows the force of the pull to be concentrated first on the release of the MLG aft doors and then on the MLG uplocks.
Operational Check of the Main Landing Gear Alternate Extension Cam Assembly (MRB#323400-204) The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. The cam assembly is installed on the left side of the nacelle, at approximately Sta. XN 190.524. •• Open and lock the main landing-gear doors •• Use your fingers to move (rotate) the input lever forward, so that the cam assembly is in the fully deployed position
CAUTION Do not pull the alternate release cable to move the cam assembly. This will bend the cable end at the turnbuckle assembly.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-87
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
NLG Alternate Release Control Cables
NOTES
Refer to Figure 32-69. NLG Alternate Release Cable. Control cables are routed from the NLG alternate release handle through a pulley cam mechanism located in the forward fuselage above the nosewheel well. The pulley cam mechanism lets the full force of the pull be concentrated first on the release of the NLG forward doors and then on the NLG uplocks.
3
D
FW A
4
2
LEGEND 1. Front Door Alternate Release Operating Arm and Roller Assembly 2. Pulley Cam Mechanism 3. Nose Gear Alternate Release Handle (Flight Compartment Floor) 4. NLG Uplock Release Arm 5. Pivot Tube (Nose Gear Release) 6. Link Assembly.
5
6
1
A
Figure 32-69. NLG Alternate Release Cable
32-88
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Landing Gear Inhibit Switch Refer to Figure 32-70. Landing Gear Alternate Release - Inhibit Switch. The LANDING GEAR INHIBIT switch is installed in the flight compartment ceiling. The inhibit toggle switch has two positions: INHIBIT and NORMAL. It is guarded to the NORMAL (off) position.
Selecting the switch to the INHIBIT position disables the extension and retraction landing gear control outputs of the PSEU. “LDG INOP” caution light will come on if not already on. This action causes the landing gear selector valve solenoids and all solenoid sequence valves to be de-energized.
A
FWD
FWD
CAUTION
LANDING GEAR
ENSURE ALL WHEEL WELLS ARE CLEAR OF OBSTRUCTIONS BEFORE CLOSING ACCESS PANEL
ALTERNATE RELEASE
TO CLOSE DUMP VALVE
OPEN DOOR FULLY
A
INHIBIT
INHIBIT
NORMAL
NORMAL
DOOR CLOSED
A
DOOR OPEN
Figure 32-70. Landing Gear Alternate Release - Inhibit Switch
FOR TRAINING PURPOSES ONLY
32-89
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Hanger Clip
Lever, Hand-Pump
Figure 32-71. Hydraulic Hand Pump and Hand Pump Lever
32-90
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
29-21-01 HYDRAULIC HAND PUMP
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-71. Hydraulic Hand Pump and Hand Pump Lever. The hand pump is located under the flight compartment floor, near the co-pilot seat. The hand pump is used to extend the main landing gear following isolation, or loss, of the No.2 hydraulic system. The pump draws hydraulic fluid from an auxiliary reservoir located in the nose compartment. Hydraulic fluid pressurizes the alternate landing-gear actuators to extend the main landing gear to the downlock position.
29-21-03 HAND-PUMP LEVER Figure 32-71. Hydraulic Hand Pump and Hand Pump Lever. The hand-pump lever is stowed on the aft bulkhead of the flight compartment, on the co-pilot side with a hanger clip and a rubber stopper on top. The lever is used to operate the Alternate hand pump.
FOR TRAINING PURPOSES ONLY
32-91
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
1 2 1
LEGEND
2
3
13 4
14 5
6 6
7
12
16
8
11
1. Links 2. Washers 3. Cotter Pin 4. Nut 5. Rod End 6. Washers 7. Selector Valve 8. Bracket 9. Hydraulic Line 10. Hydraulic Line 11. Spacers 12. Washers 13. Bolts 14. Bolt. 15. Packing 16. Filter Fitting
15
16 10 9
Figure 32-72. Secondary MLG Selector Valve - Removal and Installation
32-92
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
29-21-06 SECONDARY MLG SELECTOR VALVE
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-72. Secondary MLG Selector Valve - Removal and Installation. The Selector Valve is a 2-way, 2-position control valve located under the flight compartment floor, near the co-pilot seat. The valve has an internal pressure relief and filtered inlet and return ports. There is a pivoting link that attaches the selector valve to the hand pump access door. The selector valve moves from the normally open position to the closed position when the access door is opened. The pressure relief valve limits the pressure that may be applied to the alternate gear down actuators by relieving hand pump pressure to return at 3150 PSI.
FOR TRAINING PURPOSES ONLY
32-93
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
1
A
LEGEND 1. Landing Gear Alternate Extension Door 2. Landing Gear Downlock Verification Lights 3. Landing Gear Downlock Verification Switch.
FWD
2 3
Figure 32-73. LG Downlock Verification Lights - Controls and Indications
32-94
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-73. LG Downlock Verification Lights - Controls and Indications. Below the LANDING GEAR ALTERNATE EXTENSION door is the verification switch and the three green verification lights. An alternate landing gear down and locked verification system is located in the flight compartment, in the aft section of the LANDING GEAR ALTERNATE EXTENSION compartment. The system has a 2-position, momentary type toggle switch, a light panel that contains three green lights, and four proximity sensors. Two of the proximity sensors are used in series and are attached to the NLG. One proximity sensor is installed on each of the MLG. The system components on each landing gear are activated when the downlock verification switch is moved to the ON position. The system indication lights come on as each landing gear is locked down.
FOR TRAINING PURPOSES ONLY
32-95
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
MLG Alternate Extension Control and Inhibit Switch
Proximity Sensor Electronic Unit
NLG Alternate Extension Control amd MLG Hand Pump Landing Gear Selector Lever and Control Panel
Figure 32-74. Landing Gear Extension and Retraction
32-96
FOR TRAINING PURPOSES ONLY
fs571a01.cgm
MAINTENANCE TRAINING MANUAL
OPERATION
The PSEU extinguishes the red lights and illuminates the MLG green safe lights on the control panel.
Alternate Extension Refer to Figure 32-74. Landing Gear Extension and Retraction. The landing gear inhibit switch is set to the inhibit position. A ground is supplied from the switch to the PSEU at Pin A10K. This inhibits Landing Gear Control by Proximity Sensor Card A. Make sure that the LDG GEAR INOP caution light comes on. Open the alternate RELEASE door. The door cable system repositions the bypass valve to open. The open bypass valve causes all of the landing gear actuators to bypass to return. Pulling the alternate release handle operates the cable assembly that unlocks the overcenter lock in the MLG door mechanism. The spring contracts, operating the door mechanism, opening the doors. The PSEU illuminates the MLG door open amber lights on the LG Control and Indication panel.
Pulling upwards on the release handle operates a cable mechanism to unlock the overcenter lock in the NLG door mechanism, allowing the spring to contract, opening the doors. The PSEU will illuminate the door open amber light on the control panel. Pulling the release handle further operates a cable mechanism to a lever in the top of the NLG wheel well. Rotating the lever rotates the pivot tube of the NLG lock system. Rotating the pivot tube unlocks the overcenter lock in the upper and lower lock strut assembly, causing the NLG to free fall to the down and locked position. This is assisted by the airstream and the tension springs in the NLG lock system. The PSEU will illuminate the green NLG safe light on the control panel.
Pulling the alternate release handle to the full down position operates the cable system and mechanically releases the MLG uplocks. The MLG extends by gravity. The PSEU illuminates the MLG unsafe red lights on the control panel. Opening the alternate extension door positions the emergency down selector valve mechanically, and gives access to the hand pump socket. Operating the hand pump supplies hydraulic pressure to the MLG alternate extension actuators. The actuators extend, push on the yoke assemblies ensuring the MLG reaches the down and locked position assisted by the springs of the stabilizer brace assembly. The MLG downlock proximity sensors send target near signals to the PSEU.
FOR TRAINING PURPOSES ONLY
32-97
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
7
MAIN LANDING GEAR
1 2
3 D
FW
4
6
5
A
LEGEND 1. Outer Wheel Half 2. Inner Wheel Half 3. Wheel Insert 4. Heat Shield 5. Bearing Cup (Inner) 6. Performed Packing (Inside) 7. Main Wheel Tires.
fs144a01.cgm
Figure 32-75. Main Wheel and Tire Assembly
32-98
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-41-00 WHEELS GENERAL The wheels support the weight of the aircraft and permit the aircraft to move on the ground. The brakes convert energy necessary to bring the aircraft to a stop.
SYSTEM DESCRIPTION The aircraft has six wheels. Two wheels are installed on the nose landing gear, and two are installed on each main landing gear.
gasket is installed on the outer wheel half for protection. An inflation valve is installed in the outer wheel half. The over inflation plug contains a disk that ruptures, and deflates the tire to zero pressure. Thermal relief plugs are made of fusible metal that melts at a specified temperature. This will release the pressure in the tire and prevent an explosion if the wheel gets too hot. The wheel inserts engage the drive slots in the brake disks. The heatshield decreases the transfer of heat from the brake to the wheel and tire assembly.
Two different wheel assemblies can be used on the main landing gear: •• Main wheel assembly with a 32 × 8.8-16 (227 psi 18 ply) tubeless tire •• Main wheel assembly with a 34×10.75-16 (141 psi 16 ply) tubeless tire. Each nosewheel has a 22×6.50-10 (89 psi 8 ply) tubeless tire.
COMPONENTS DESCRIPTION Main Wheels Refer to Figure 32-75. Main Wheel and Tire Assembly. The main wheels are split type made of forged aluminum wheel halves. The two halves are held together with equally spaced tie bolts, washers, and nuts. A preformed packing is installed on the inner wheel half to prevent air leakage through the wheel mating surfaces. The bearings are lubricated with grease. Bearing seals are installed at the outer surface of the bearings to prevent contamination. A retaining ring holds the outer bearing in place. Grease retainers are installed next to each bearing cup to prevent the flow of grease into the center of the wheel. A hubcap and
FOR TRAINING PURPOSES ONLY
32-99
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
10
8 7
9
6
LEGEND 1. Hub Cap 2. Axle Nut 3. Retaining Ring 4. Outer Bearing Seal 5. Outer Bearing 6. Main Wheel Tire Assembly 7. Inner Bearing 8. Inner Bearing Seal 9. Axle 10. Brake Unit
5 4 3 2 1
NOTE
On aircraft without Modsum 4−126316.
Figure 32-76. Main Wheel and Tire Assembly - Removal and Installation
32-100
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Installation of the Main Wheel and Tire Assembly The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
MLG Axle Bullet Refer to Figure 32-77. MLG Axle Bullet. Used for installation and removal of MLG wheel and brake assembly. Manufactured from aluminum alloy 6061 - T6.
Refer to Figure 32-76. Main Wheel and Tire Assembly - Removal and Installation. •• Visual check for wear damage and cleanliness •• Lubricate bearings, axle and axle nut with grease •• Install axle bullet •• Align wheel inserts with the slots in rotor disks •• Push the wheel on the axle and brake assembly •• Remove axle bullet •• Ensure outer seal is in correct position •• While turning the wheel tighten the axle nut •• Loosen axle nut
Figure 32-77. MLG Axle Bullet
•• While turning the wheel torque the nut to the correct value •• Lock the axle nut •• Engage blade on inside hub cap with clip on wheel speed transducer •• Install hub cap, torque the bolts and lockwire
NOTE Make sure that the drive blade on the hubcap engages with the clip on the wheel speed transducer. •• Apply torque seal on all fasteners •• Fill the tire with nitrogen.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-101
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure 32-78. Nosewheel and Tire Assembly
32-102
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Nosewheels
NOTE
Refer to Figure 32-78. Nosewheel and Tire Assembly. The nosewheels are split type made of forged aluminum wheel halves. The two halves are held together with equally spaced tie bolts, washers, and nuts. A preformed packing is installed on the inner wheel half to prevent air leakage through the wheel mating surfaces. The bearings and cups are lubricated with grease. Bearing seals are installed at the outer surface of the bearings to prevent contamination. A water deflector shield is installed on the inner wheel half assembly to keep water spray away from the bearing seals and bearing. A hubcap and gasket are installed on the outer wheel for protection. An inflation valve is installed in the outer wheel half assembly. An over-inflation plug is installed in the outer wheel half assembly to prevent over-inflation of the tire. The plug contains a disk that ruptures, and deflates the tire to zero pressure.
Installation of the Nosewheel and Tire Assembly The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Do a visual check of the axle for signs of wear and damage.
Install the water shield so that the words THIS SIDE OUT point at the nosewheel strut. •• Carefully put the nosewheel and tire assembly on the axle. •• Install the outer bearing and seal on the axle. Push the outer bearing and seal into the outer side of the nosewheel and tire assembly. •• Lubricate the threads of the axle nut and the axle with grease. •• Install the axle nut on the axle. •• Turn the nosewheel and tire assembly. At the same time, torque the axle nut.
NOTE Turn the nosewheel and tire assembly in the direction that the axle nut is tightened. •• Loosen the axle nut to zero torque. •• Turn the nosewheel and tire assembly. At the same time, re-torque the axle nut. •• If the locking holes are not aligned, tighten the axle nut to the nearest locking hole.
NOTE Turn the nosewheel and tire assembly in the direction that the axle nut is tightened. •• Put the washers on the bolts. Install the bolts through the holes in the axle nut and the axle.
•• Put a layer of wheel bearing grease on the bearing cups.
•• Install the ball seat washers and the nuts on the bolt. Torque the nuts. Safety the nuts.
•• Lubricate the bearings and seals.
•• Apply torque seal to all fasteners.
•• Install the inner bearing, the inner bearing seal, and the water shield in the inner side of the nosewheel and tire assembly.
•• Install the hubcap.
Revision 0.4
•• Torque the screws and apply torque seal.
FOR TRAINING PURPOSES ONLY
32-103
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND 1. Fill Valve Gauge 2. Valve Cap 3. O-ring.
B 3 A 1
2
A B
Figure 32-79. Fill Valve Gauge
32-104
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Fill Valve Gauge (Optional)
Tire Wear
Refer to Figure 32-79. Fill Valve Gauge.
It is acceptable to continue operations for an additional 8 landings after the tire reinforcement cord first becomes visible in the tread area.
The fill valve gauge is installed on each wheel assembly. The fill valve gauge has a built in tire pressure indicator. The tire pressure can be read directly from the analog dial type indicator.
Operating with worn tires to this extended wear allowance may result in the tire casing becoming non-retreadable.
The function of the fill valve gauge is to give the tire pressure indication directly from the wheel assembly.
NOTE The fill valve gauge is installed on Aircraft with Modsum - MS 4-900220. Inflate the tires with nitrogen to the correct pressure with a servicing kit that includes a low pressure regulator.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-105
32 LANDING GEAR
DASH 8 Q400
32-106
DASH 8 Q400 MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
Figure 32-80. Brakes System Hydraulic Synoptic
32 LANDING GEAR
MAINTENANCE TRAINING MANUAL
32-42-00 MAIN LANDING GEAR BRAKE SYSTEM
32 LANDING GEAR
DASH 8 Q400
NOTES
INTRODUCTION The brake system is used to decrease the aircraft speed during ground operations.
GENERAL The MLG brake system is controlled by the pilot’s and co-pilot’s brake pedals. The brake system has the following components: •• Pilot and Co-pilot brake pedals •• Brake control cables •• Brake control valve •• Brake pressure transducer •• Fuse/shuttle valves and •• Main wheel brake units.
SYSTEM DESCRIPTION Refer to Figure 32-80. Brakes System Hydraulic Synoptic. When the brake pedal is pushed, the brake control valve will supply hydraulic pressure to the brake assembly in proportion to the amount of brake pedal travel. The pressure plate assembly pushes the rotor disks, stator disks, and the end plate together. As the disks are pushed together, the friction between the disks causes resistance. The resistance is transmitted from the brake unit to the wheel and tire assemblies causing the wheel to slow down.
FOR TRAINING PURPOSES ONLY
32-107
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure 32-81. Brake Wear Indicator Pins
8 LEGEND 1. Main Wheel-brake Unit 2. Hydraulic Hose 3. Reducer 4. O−Ring 5. Axle 6. Brake Pin Bushing 7. Brake Pin 8. Brake Bleeder Valve
6 2
3
4
5
6
1
7
FWD
Figure 32-82. Main Wheel Brake Unit - Removal and Installation
32-108
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Main Wheel Brake Units
•• Apply hydraulic fluid to the threads of the reducer and the O-ring •• Install the O-ring on the reducer
Refer to Figure 32-81. Brake Wear Indicator Pins. There are two brake units installed on the axle of the main landing gear. The brake pins on the MLG shock strut engage with the bushings in the piston housing assembly to transfer the braking loads to the landing gear. The brake assembly has three primary sub-components: •• Piston housing assembly
•• Install the reducer on the brake unit and torque •• Apply torque seal across the reducer and on the main wheel brake unit •• Carefully install the brake unit on the axle. Make sure that the brake pins engage with the brake pin bushings •• Remove the caps from the hydraulic hose and the reducer and connect the hydraulic hose to the reducer
•• Carbon heat sink stack and
NOTE
•• Torque plate assembly. The piston housing is made of aluminum. It contains six adjuster assemblies, two bleeder valves, and one bleeder plug.
Make sure that you install the elbow of the hydraulic hose vertically in-line with the brake unit or angled a small distance in to the shock strut.
The bleeder valves and bleeder plugs are interchangeable so the brakes can be installed on the left or right side.
•• Torque the hydraulic hose
Two wear indicator pins are attached to the pressure plate assembly and extend out of the piston housing through sleeves to give an indication of brake wear.
•• Apply torque seal across the reducer and onto the wheel brake unit
•• Apply torque seal across the coupling nut of the hydraulic hose and the reducer
•• Install the main wheel and tire assembly
Installation of the Main Wheel Brake Units
•• Lower the MLG main wheel assembly. Remove the jack
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
•• Bleed the main landing-gear brake system.
Refer to Figure 32-82. Main Wheel Brake Unit Removal and Installation.
NOTE Make sure that the surfaces are clean with no corrosion, paint, grease, dirt, or preservation fluid.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-109
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
3 LEGEND 1. 2. 3. 4. 5. 6.
Bleed Screw Washer Bleeder Valve Brake Unit Bleed Hose Container
5
4
NOTE Shock strut and axle not shown.
Figure 32-83. Main Landing Gear Brake System - Bleed
32-110
FOR TRAINING PURPOSES ONLY
2
6
1
MAINTENANCE TRAINING MANUAL
Bleed the Brakes with Main Brake System The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 32-83. Main Landing Gear Brake System - Bleed. This procedure will bleed the brakes from the brake control valve to the brake units. After the replacement of a brake unit you can use this procedure or the procedure to bleed the brakes with the parking brake system.
NOTE After the replacement of a brake unit, it is only necessary to bleed the brake unit that you replaced. You must bleed all of the brake units after the replacement of other brake system components.
NOTE The flow of hydraulic fluid can stop because the fuse/shuttle valve operates. If this occurs, release the brake pedal. Then push and hold the brake pedal again. •• Close the bleeder valves and torque. •• Release the brake pedal. •• Remove the hose from the bleeder valve. •• Install the screw and the washer in the bleeder valve and torque. •• Push the brake pedals. Make sure the operation of the pedals is not soft. If the operation of the brake pedals is soft, do this procedure again. •• Do a visual inspection of the brake line and connections for leaks. •• With the Hydraulic pressure removed, check the quantity in the No.1 hydraulic system.
•• Remove the bleed screw and the washer from the bleeder valve on the main wheel-brake unit. •• Install the bleed hose on the bleeder valve. Put the other end of the bleed hose in the container. •• Open the bleeder valve at the MLG brake unit. •• Lightly push the brake pedal in the flight compartment until hydraulic fluid flows from the bleeder valves. •• Hold t he brake pedal and l e t the hydraulic fluid flow from the bleeder valves until the hydraulic fluid does not contain air bubbles.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-111
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Brake Bleeding Kit Refer to Figure 32-84. Brake Bleeding Kit. PN: G601R324301-1 Used to bleed the brake lines. Pump
Clamp
Hose
Figure 32-84. Brake Bleeding Kit
SYSTEM
ATA SUB-SYSTEM
32---4
32 LANDING GEAR
1.
PART DESCRIPTION
BRAKE ASSEMBLY WEAR INDICATOR PIN
NUMBER OF PARTS REQUIRED FOR ALL FLIGHT CONDITIONS EXCEPT AS PROVIDED IN COLUMN 2.
2. REMARKS AND/OR EXCEPTIONS
8
One may be missing from each brake assembly provided the pin is replaced at the next brake removal.
Figure 32-85. CDL - Brake Assembly Wear Indicator Pin
32-112
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Brake Control Valve Refer to Figure 32-86. Brake Control Valve. The brake control valve is installed in the left wing root on the front spar. The left brake pedals are connected to the left lever of the brake control valve. The right brake pedals are connected to the right lever of the brake control valve.
Hydraulic pressure and return lines connect the brake control valve to the No.1 hydraulic system. Hydraulic lines connect the brake control valve to the anti-skid valves. The function of the brake control valve is to meter hydraulic pressure to the brake units as determined by pedal input.
The brake control valve has two internal metering sections in a common housing.
LEGEND 1. Right Brake Lever 2. Brake Control Valve 3. Hydraulic Line 4. Left Brake Lever 5. Left Brake Cable Turnbuckle.
A
2
1
3
4
FWD
A
5
Figure 32-86. Brake Control Valve
FOR TRAINING PURPOSES ONLY
32-113
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Fuse/Shuttle Valves Refer to: •• Figure 32-87. Fuse - Shuttle Valve. •• Figure 32-88. Fuse - Shuttle Valve. There are two fuse/shuttle valves installed on the left wall of each nacelle. Hydraulic pressure is supplied to the brake units through the skid control valves and the fuse/shuttle valves. The fuse component of the fuse/shuttle valve closes if the fluid flow is more than a specified quantity. This limits the leakage of hydraulic fluid if a brake line or a brake develops a leak. The shuttle component of the valve sends either normal or parking/emergency brake pressure to the brakes.
Figure 32-87. Fuse - Shuttle Valve
FWD
1
A
2
1
NOTE Left component shown. Right component similar.
A
Figure 32-88. Fuse - Shuttle Valve
32-114
FOR TRAINING PURPOSES ONLY
LEGEND 1. Fuse 2. Shuttle Valves.
MAINTENANCE TRAINING MANUAL
Brake Pedals
The brake pedal inputs are applied to the brake control levers.
Refer to Figure 32-89. Brake Pedals.
The linkage attached to the base of the pedals is spring loaded to return the pedals to the off position when the pedals are released.
The brake pedals are installed in the flight compartment and are connected to the brake control valve. The co-pilot’s inputs are transmitted by a cable system to the spring loaded lever arm aft of the pilot’s brake pedal.
1 A 10
2
9 3
4 5 6 8 A 7
LEGEND 1. Co-pilot’s Brake Pedals 2. Tie Rods 3. Brake Control Levers 4. Brake Interconnect Cables 5. Lever Springs 6. Cables to Brake Control Valve 7. Push Rods 8. Spring Rods 9. Tie Rods 10. Pilot’s Brake Pedal.
Figure 32-89. Brake Pedals
FOR TRAINING PURPOSES ONLY
32-115
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Brake Control Cables Refer to Figure 32-90. Brake Control Cables. The brake control cables connect the pilot’s pedals to the two levers on the brake control valve. The brake control valve is installed in the left wing root area.
The cables are routed along the ceiling through grommets at four frame stations. The cables pass through another three pairs of pulleys in the left wing root and then connect to the two levers on the brake control valve.
The cables are routed under the floor along the left side to a pair of pulleys and then upward through a cable guide on the flight compartment bulkhead to another pair of pulleys on the ceiling.
3
5
3
3
6
2
5
3 4 1
3 2 1
1 2
NOTE Flight compartment bulkhead. Left wing root area.
Figure 32-90. Brake Control Cables
32-116
FOR TRAINING PURPOSES ONLY
LEGEND 1. Brake Control Cables 2. Pedal Mechanism 3. Pulleys 4. Cable Guide 5. Grommets 6. Brake Control Valve.
MAINTENANCE TRAINING MANUAL
Brake Pressure Transducers Refer to Figure 32-91. Brake Pressure Transducers. The brake pressure transducers are installed in the left wing root area near to the brake control valve.
The transducers sense the pressure through the brake control valve. The function of these pressure transducers is to send data to the flight data processing system for recording on the FDR.
One transducer senses the left brake system and the other senses the right brake system.
LEGEND 1. Transducers 2. Electrical Connector.
A
2
Brake Control Valve (Ref)
A
1
Figure 32-91. Brake Pressure Transducers
FOR TRAINING PURPOSES ONLY
32-117
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-118 NO. 2 SYSTEM RESERVOIR
NO. 2 SYSTEM PRESSURE
LEGEND PRESSURE RETURN
HIGH PRESSURE AIR CHECK VALVE
FUSE SHUTTLE VALVE ACCUMULATOR PARKING BRAKE CONTROL VALVE
PARKING BRAKE LEVER
HAND PUMP CHARGE VALVE GAUGE ACCUMULATOR PRESSURE TRANSDUCER
TO FUSE/SHUTTLE VALVES AND BRAKE UNITS ON OTHER MAIN LANDING GEAR
PRESSURE RELIEF VALVE NORMAL BRAKE SYSTEM
NORMAL BRAKE SYSTEM
MAIN WHEEL BRAKE UNITS
NOTE SHOWN WITH PARKING BRAKE APPLIED
fs665a01a.cgm
Figure 32-92. Parking Brake Hydraulic System
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RESTRICTOR
DASH 8 Q400
SUCTION
MAINTENANCE TRAINING MANUAL
32-44-00 PARKING BRAKE SYSTEM INTRODUCTION The parking brake system is used to keep hydraulic pressure applied to the brake units. The parking brake system can stop the aircraft on the ground.
GENERAL The parking brake system uses the No.2 hydraulic system. An accumulator in the brake system supplies pressure for parking brake operation when the No.2 hydraulic system pressure is not available. A hand pump is used to manually pressurize the parking brake accumulator. Parking brake pressure is applied equally to all of the brake units.
SYSTEM DESCRIPTION Refer to Figure 32-92. Parking Brake Hydraulic System. When the PARK/EMERG control lever is moved from the stowed toward the PARK position, the park brake control valve is actuated. The parking brake control valve can apply progressive hydraulic pressure to the brakes. The hydraulic pressure from the parking brake control valve causes the shuttle valves to move and block off normal brake pressure to the brakes. The release button on the parking brake lever is pushed in and the lever is moved forward to the stowed position to release the parking brake. The parking brake accumulator is normally pressurized from the No.2 hydraulic system. A fully charged accumulator will supply six parking brake applications.
A PARKING BRAKE caution light on the CAWP in the flight compartment comes on when the parking brake lever is in the PARK position. A parking brake pressure indicator is shown on No.2 MFD as part of the permanent system area No.2. The parking brake system is comprised of the components: •• Parking brake control lever •• Parking brake pressure indication •• Control cable assembly •• Parking brake control valve •• Hand pump •• Accumulator •• Charge valve and gauge.
FOR TRAINING PURPOSES ONLY
32-119
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure 32-93. Park Brake Control Valve
3
1
A
FWD
2
LEGEND 1. Accumulator Pressure Transducer 2. Parking Brake Control Cable 3. Parking Brake Control Valve.
A ft405a01.cgm
Figure 32-94. Park Brake Control Valve
32-120
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
32 LANDING GEAR
DASH 8 Q400
NOTES
Parking Brake Control Valve Refer to: •• Figure 32-93. Park Brake Control Valve. •• Figure 32-94. Park Brake Control Valve. The parking brake control valve is installed in the right wing root. The No.2 hydraulic system pressure is supplied to the parking brake control valve. The pressure is metered to the brake units in proportion to the amount of parking brake lever movement. When the parking brake lever is set in the PARK position, full hydraulic pressure is applied to the four brake units. A pressure transducer, relief valve and two check valves are contained in the brake control valve housing. The function of the parking brake control valve is to meter the No.2 hydraulic system pressure to the brake units.
Parking Brake Hand pump A lever operated hand pump is installed on the right wall in the right engine nacelle. The hand pump handle is spring clipped and pip-pinned in the nacelle. It supplies an alternate method to pressurize the accumulator to 3000 psi (20684 kPa) when the aircraft is on the ground and the engines are not operating. The function of the hand pump is to manually increase the park brake system pressure when No.2 hydraulic system is not available.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-121
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Post SB 84-32-99 Reposition of the Parking Brake Hand Pump Lever to the Nose Compartment
NOTES
Refer to Figure 32-95. Parking Brake Handle Reposition. If the quick release pin is not fully engaged, the potential exists for the pin to migrate out, disengaging, and allowing the pump lever to become dislodged from its installation position in the wheel well. It became necessary to relocate the existing parking brake hand pump lever from RH nacelle to the flight deck web in the RH side of the nose compartment.
Figure 32-95. Parking Brake Handle Reposition
32-122
FOR TRAINING PURPOSES ONLY
SYSTEM
MAINTENANCE TRAINING MANUAL
1.
32 LANDING GEAR
ATA SUB-SYSTEM 32---3
PART DESCRIPTION PARKING BRAKE HANDPUMP HANDLE (Located in the nose compartment equipment bay)
NUMBER OF PARTS REQUIRED FOR ALL FLIGHT CONDITIONS EXCEPT AS PROVIDED IN COLUMN 2.
2. REMARKS AND/OR EXCEPTIONS 1
May be missing with no performance penalty provided: a. Alternate Landing Gear Extension handpump handle must be stowed in its proper location in the flight compartment.
Figure 32-96. CDL - Parking Brake Hand Pump Handle
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-123
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Parking Brake Accumulator Refer to Figure 32-97. Parking Brake Accumulator. The parking brake accumulator is installed in the right wing root area. The accumulator is a cylindrical piston type with a gross rated volume of 50 in³ (820 cm³).
The fluid side is pressurized by the No.2 hydraulic system or the hand pump. The fully charged accumulator will hold enough pressure to supply six full parking brake applications and releases. The function of the accumulator is to supply hydraulic pressure for the parking brake operation when No.2 hydraulic pressure system is not available.
The accumulator is pressurized with nitrogen. The accumulator is pre-charged to 500 psi (3447 kPa).
Figure 32-97. Parking Brake Accumulator
32-124
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Charge Valve and Gauge Refer to: •• Figure 32-98. Charge Valve and Gauge. The charge valve and gauge are installed in the right wing root area. They are connected to the gas pressure side of the parking brake accumulator. The gauge supplies an indication of the accumulator pressure. The charge valve is used to charge the gas side of the accumulator with nitrogen.
Servicing of the Parking Brake Accumulator with Nitrogen The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• R e m o v e t h e v a l v e c a p f r o m t h e accumulator charging valve.
Functional Check of Park Brake Accumulator Pre-Charge Pressure The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
WARNING OBEY ALL HYDRAULIC SAFETY PRECAUTIONS. Do the check as follows: •• Ensure all hydraulic power is OFF. •• Ensure the main wheels are chocked. •• Operate EMERG BRAKE lever until 0 pressure is indicated on MFD #2. •• Place EMERG BRAKE to OFF. •• C h e c k a c c u m u l a t o r p r e - c h a r g e i s 500±25 psi.
•• Connect the hose of the nitrogen servicing kit to the accumulator charging valve. •• Charge the accumulator until the adjacent gauge shows 500 ±25 psi. •• Remove the hose of the nitrogen servicing kit from the accumulator charging valve. •• Install the valve cap on the accumulator charging valve. •• Pressurize the parking brake system to 3000 ±50 psi with the hand pump. •• Operate the parking brake lever in the flight compartment to make sure that the parking brake system is serviceable. •• Use the hand pump to pressurize the parking brake system to 3000 ±50 psi again. •• Make sure that the PK BRK indication from the HYD PRESS readout on the MFD shows 3050 ±50 psi. Revision 0.4
Figure 32-98. Charge Valve and Gauge
FOR TRAINING PURPOSES ONLY
32-125
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Parking Brake Control Quadrant
NOTES
Refer to Figure 32-99. Park Brake Control Quadrant. The parking brake lever is installed in the flight compartment. It is in the emergency brake control quadrant. On left side of the center console. A cable assembly connects the parking brake lever to the parking brake control valve. A release button on the parking brake lever unlocks the lever from the PARK position. The function of the parking brake lever is to supply alternate brake control and to set the parking brake.
3
LEGEND 1. Emergency Brake Lever 2. Emergency Brake ON Position 3. Release Button 4. Control Quadrant (Ref.)
1
R A T I N G
R A T I N G
I
FLIGHT IDLE DISC
I
4
2
Figure 32-99. Park Brake Control Quadrant
32-126
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Parking Brake Control Cable
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-100. Parking Brake Control Cable. The parking brake control cable is a single open loop cable which connects the park brake lever to the parking brake control valve. The cable is routed from the lever quadrant through pulleys under the flight compartment floor to the lever on the parking brake control valve. 6
3 1
1
5
5
4
3
3
2 3
LEGEND 1. Parking Brake Control Cable. 2. Park Brake Lever. 3. Pulleys. 4. Cable Guide. 5. Grommets. 6. Park Brake Control Valve.
1
Figure 32-100. Parking Brake Control Cable
FOR TRAINING PURPOSES ONLY
32-127
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
1 2
LEGEND 1. Park Brake Lever 2. Cable Quadrant 3. Cable 4. Connector 5. Center Console 6. Caution Light Micro-Switch.
3
6
4
5
Figure 32-101. Parking Brake Micro-Switch
32-128
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to: •• Figure 32-101. P arking Brake Micro-Switch. •• Figure 32-102. C ontrols and Indications - Parking Brake System. A 28 VDC electrical power source is needed for the PARK BRAKE pressure indicator and the pressure transmitter to operate. The park brake pressure signal is sent to the Integrated Flight Cabinet (IFC) to be converted from analog to digital data for display on the EIS on the co-pilot MFD. A PARKING BRAKE caution light on the Caution and Warning panel in the flight compartment comes on when the parking brake lever is in the PARK position.
Interfaces The parking brake system is interfaced with: •• The Take-Off Configuration Warning System •• T h e H y d r a u l i c S y s t e m S P U / P T U Automatic Activation •• The Cockpit Voice Recorder Erase Interlock System •• The Caution and Warning System.
FOR TRAINING PURPOSES ONLY
32-129
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
OVERHEAD CONSOLE
B
ELECTRICAL
LEGEND 1. Parking Brake Hydraulic Pressure Indicator 2. Parking Brake (Amber)
ELECTRICAL BATT
LOAD
MAIN +1. 00 AUX - . 34 MAIN - . 00 34 STBY 00 AUX 00 STBY L
¡C
+22 +22 +22
DC BUS
VOLT R
ESS 27.7 MAIN 28.5 ESS SEC 26.1 MAIN S EC
27.7 28.5 26.1
APU GEN
AC GEN 1
LOAD
+1. 00 DC GEN 1
LOAD
+1. 00 1
TRU
LOAD
2
. 06
VOLT
LOAD
A 115 B 115 C 115
. 06 . 06 . 06
AC GEN 2
VOLT
2
+1. 00 +1. 00
LOAD
. 06 . 06 . 06
A 115 B 115 C 115
2 PARKING BRAKE
FLAP
DEG
0 5 10
HYD PRESS
PSIxx 1000 1000 PSI PK BRK STBY 1 2
35
HYD QTY
3
4
1
% x 100
2
3 1
2 0
A
PARKING BRAKE CAUTION LIGHT
1 B
PARKING BRAKE PRESSURE INDICATION
Figure 32-102. Controls and Indications - Parking Brake System
32-130
FOR TRAINING PURPOSES ONLY
0
DASH 8 Q400
Systems & Nos de Sequence système Numbers de série
1. Item - Article
32 LANDING GEAR
MAINTENANCE TRAINING MANUAL
2. Number installed - Nombre d’articles installés 3. Number required for dispatch - Nombre d’articles à expédier 4. Remarks or Exceptions - Remarques ou exceptions
-40-1
Parking Brake Pressure Indications 1) HYD PRESS PK BRK Indication
C
1
0
(M) May be inoperative provided: a) The Aft Wing Root Fairing Indicator is verified operative, and b) Brake pressure is confirmed adequate prior to engine start.
Figure 32-103. CDL - Parking Brake Pressure Indications
FOR TRAINING PURPOSES ONLY
32-131
32 LANDING GEAR
32-132 METERED PRESSURE FROM THE BRAKE CONTROL VALVE
RETURN NO. 1 SYSTEM RESERVOIR ANTI SKID CONTROL VALVE
LEGEND METERED PRESSURE ANTI SKID PRESSURE
STATIC CHECK VALVE SERVO VALVE
FILTER RESTRICTOR FUSE SHUTTLE VALVE
SPOOL AND SLEEVE VALVE
SPOOL AND SLEEVE VALVE
PARKING BRAKE (NO. 2 HYDRAULIC SYSTEM)
fs667a01a.cgm
MAIN WHEEL BRAKE UNITS
NOTE SHOWN WITH BRAKES APPLIED (WHEELS NOT IN SKID CONDITION)
Figure 32-104. Anti-Skid System - Hydraulic Schematic
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
SERVO VALVE
DASH 8 Q400
RETURN
MAINTENANCE TRAINING MANUAL
32-46-00 ANTI-SKID SYSTEM
32 LANDING GEAR
DASH 8 Q400
NOTES
INTRODUCTION The anti-skid system modulates hydraulic pressure to the four wheel brake units to supply wheel anti-skid protection.
GENERAL Refer to Figure 32-104. Anti-Skid System Hydraulic Schematic. The brake pedals cause the No.1 hydraulic system pressure to be sent through the brake control valve to the anti-skid control valves. The anti-skid control valves change the hydraulic pressure to the brake units. The anti-skid system operates with the normal brake system. The anti-skid system is comprised of the following components: •• Anti-skid control unit •• Wheel speed transducers •• Skid control valves •• ANTISKID switch.
SYSTEM DESCRIPTION The anti-skid system has the following functions: •• Touchdown protection •• Initialization •• Individual wheel anti-skid •• Locked wheel protection •• System monitoring.
FOR TRAINING PURPOSES ONLY
32-133
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure 32-105. Anti-Skid System Control Unit
A
FWD
A fs140a01.cgm
Figure 32-106. Anti-Skid System Control Unit
32-134
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENTS DESCRIPTION
32 LANDING GEAR
DASH 8 Q400
NOTES
Anti-Skid Control Unit Refer to: •• Figure 32-105. A nti-Skid System Control Unit. •• Figure 32-106. A nti-Skid System Control Unit. The ASCU is installed below the passenger cabin floor at the mid-wing area, on the equipment rails. The ASCU is an electronic box that has two wheel control circuit boards, one for the inboard wheels and one for the outboard wheels. Each wheel board uses a micro-controller and related circuitry to do the digital processing of the control and built-in-test software. The ASCU receives signals from the: •• Anti-skid switch •• Four wheel speed transducers •• Two dual skid control valves •• PSEU (WOW and uplock).
FOR TRAINING PURPOSES ONLY
32-135
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Skid Control Valves Refer to: •• Figure 32-107. Skid Control Valve. •• Figure 32-108. Skid Control Valve. The skid control valves are installed on the left wall of the wheel wells. The skid control valves are two separate valves in one common manifold. Each skid control valve contains a screen on the inlet port. The screen protects the skid control valve components from contaminants larger than 40 microns. The function of the skid control valve is to control the flow to and from the brake unit, as commanded by the Anti Skid Control Unit.
Figure 32-107. Skid Control Valve
A
FWD
fs141a01.cgm
A
Figure 32-108. Skid Control Valve
32-136
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
Wheel Speed Transducer Refer to: •• Figure 32-109. Wheel Speed Transducer. •• Figure 32-110. Wheel Speed Transducer. A wheel speed transducer is installed in each end of the main landing gear axles. The wheel speed transducer is an electrical generating device. The hubcap on the wheel engages with a clip on the wheel speed transducer. When the wheel turns, the wheel speed transducer supplies an AC signal with a frequency of 100 cycles per wheel revolution. Figure 32-109. Wheel Speed Transducer
This signal is changed to a digital signal in the ASCU for anti-skid control use. The function of the wheel speed transducer is to supply wheel speed information to the ASCU.
B
FWD A
MLG WHEEL
A
B
WHEEL SPEED TRANSDUCER
Figure 32-110. Wheel Speed Transducer
FOR TRAINING PURPOSES ONLY
32-137
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A WHITE
1 2
A C B
RIGHT WHEEL SPEED TRANSDUCER
A C B
LEFT WHEEL SPEED TRANSDUCER
WHITE/BLUE WHITE
3 4 WHITE/BLUE LEGEND 1. Wheel-Speed Transducer Harness 2. Electrical Connector 3. Strain Relief Clamp 4. Electrical Connector.
A
B
2
1
VIEW
4
B
Figure 32-111. Wheel Speed Transducer Harness - Removal/Installation
32-138
FOR TRAINING PURPOSES ONLY
ma288a01.dg, kms, nov21/2006
3
MAINTENANCE TRAINING MANUAL
Installation of the Wheel-Speed Transducer Electrical Harness
32 LANDING GEAR
DASH 8 Q400
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 32-111. Wheel Speed Transducer Harness - Removal/Installation. This is the wheel speed transducer harness of the main landing gear (MLG). The harness is installed in the axle of the MLG shock strut.
NOTE Make sure the pins are inserted as tagged on the wheel speed transducer harness. Apply sealant to the mating surfaces of the connector and fill the cavity of the backshell.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-139
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
ANTI-SKID SWITCH Refer to Figure 32-112. Anti-Skid Switch. The ANTI-SKID switch is located on the co-pilot’s glareshield panel. The ANTI-SKID switch is a three position OFF/ON/TEST switch. When the ANTI-SKID switch is set to the ON position, 28 VDC is supplied to the circuit boards in the ASCU. When set to the TEST position, 28 VDC is supplied to the wheel control circuit boards and the system BIT function. When the ANTI-SKID switch is set to OFF, all electrical power is removed from the ASCU. A
The function of the ANTI-SKID switch is to energize and to test the anti-skid system.
LEGEND 1. Anti-Skid Switch
STICK PUSHER SHUT OFF
ENGINE FIRE
ANTI SKID TEST
INHIBIT
TERRAIN INHIBIT
ELEVATOR TRIM SHUT OFF
CAUTION
CF-AEI
PRESS TO RESET
A
Figure 32-112. Anti-Skid Switch
32-140
FOR TRAINING PURPOSES ONLY
1
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
CONTROLS AND INDICATIONS Refer to Figure 32-113. Anti-Skid Caution Lights. Failures of the anti-skid system are annunciated in the flight compartment through two caution lights on the CAWP: •• INBD ANTISKID •• OUTBD ANTISKID. The caution lights also illuminate during the test; six seconds on ground; three seconds in flight.
1
2
A
OVERHEAD CONSOLE INBD ANTISKID
OUTBD ANTISKID
LEGEND 1. Inboard Antiskid (Amber) 2. Outboard Antiskid (Amber) A
Figure 32-113. Anti-Skid Caution Lights
FOR TRAINING PURPOSES ONLY
32-141
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
MAIN WHEEL AND TIRE ASSEMBLY
4 6 5
8
7
3
LEGEND 1. Bleeder valve adapter. 2. Packing. 3. Brake unit. 4. Anti−skid tester. 5. Bolts. 6. Washers. 7. Hubcap. 8. Wheel speed transducer.
2
Figure 32-114. Anti-Skid System Functional Test
32-142
FOR TRAINING PURPOSES ONLY
1
MAINTENANCE TRAINING MANUAL
Functional Test of the Anti-Skid Control System (Built-in Test)
and the OUTBD ANTISKID caution lights come on for 2 to 4 seconds and then go off.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
Refer to Figure 32-114. Anti-Skid System Functional Test.
This test uses the built-in test function of the anti-skid control system.
Make sure that the aircraft is in the configuration that follows: •• The LANDING GEAR selector is in the DN position.
NOTE This test is written with the aircraft on the ground in a weight-on-wheels condition. You can also do this test with the aircraft on jacks if you simulate the weight-on-wheels condition. •• Set the ANTISKID switch in the flight compartment to OFF. •• Make sure that the INBD and OUTBD ANTISKID caution lights come on. •• Set the ANTISKID switch in the flight compartment to ON. •• Make sure that the INBD and OUTBD ANTISKID caution lights go off. •• Momentarily hold the ANTISKID switch in the flight compartment in the TEST position. •• Make sure that the INBD ANTISKID and the OUTBD ANTISKID caution lights come on for 5 to 7 seconds and then go off. •• Put the aircraft in the weight-off-wheels condition as follows: °° Put the de-actuator (copper) targets on the main landing gears. °° Put the actuator (steel) targets on the nose landing gear. °° Momentarily hold the ANTISKID switch in the flight compartment in the TEST position. °° Make sure that the INBD ANTISKID Revision 0.4
°° Remove the targets from the main and the nose landing gears.
•• The lock pins are installed in the main landing gear. •• The nose gear ground lock is engaged. •• EMERG BRAKE lever to the OFF position. •• Connect the anti-skid tester.
Touchdown Protection Test •• ANTI SKID switch to the ON position. •• Aircraft is in a WOFFW condition. •• Fully push the left and right brake pedals. •• No appreciable brake pressure measured at the brake units. (Below 75 psi) • • Incorrect results show a problem with the anti-skid control unit or a problem with the W OW signa ls ( P S E U o r WOW switches).
Wheel Speed Transducer Test Turn the wheel speed transducer at a constant speed between 480 rpm and 2400 rpm.
NOTE The ANTI-SKID INOP caution light may come on momentarily. •• Make sure that the pressure at the selected wheel brake unit increases to more than 500 psi. •• Make sure that the pressure at the other brake units is less than 150 psi.
FOR TRAINING PURPOSES ONLY
32-143
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-144 WOW SW(IB) HMAIN GEAR UP & LOCKED (IB) H
13 WOW SW(IB) 28 MAIN GEAR UP & LOCKED (IB)
WOW SW(OB) T MAIN GEAR UP & LOCKED (OB) N
13 WOW SW(OB) 28 MAIN GEAR UP & LOCKED (OB)
ANTI SKID TEST ON OFF
32-61 A1 PSEU
A
DASH 8 Q400
A (Q5) 3A + 28 V DC R. MAIN
ANTISKID INBD
5
D
4
(OB) FAIL IND 35
(IB) FAIL IND (R5) ANTISKID OUTBD
RIGHT DC CBP
8
F
2
9
ANTISKID TEST
111
13 (IB) FAIL IND
CAUTION AND WARNING PANEL (O/H CONSOLE)
OFF
1
H
3 11
35
ON
C
10
G
12
E
IOM #1
15 17 16
BITE TEST (IB) +28 V DC (IB) RTN
15 17 16
BITE TEST (OB) +28 V DC (OB) RTN
3 4
331 330
HI ANTISKID LO MA A429
B
31-41 A1 IOP #1
ANTISKID SWITCH (GLARESHIELD) 27 ARINC 429 TRANS'M REQUEST B
WST (OB)
A B
32 + 33 -
WST (OB)
RIGHT OUTBOARD WHEEL SPD XDCR
WST (IB) LEGEND METERED PRESSURE
CNTL VALVE (OB)
CNTL VALVE (IB) A B
32 + WST 33 - (IB)
A B
8+ 9 -
+ 23 - 24
1 + 2 -
(OB)
+ 23 - 24
3 + 4 -
(IB)
B
B
SKID CONTROL VALVE
RIGHT INBOARD WHEEL SPD XDCR
RETURN STATIC CHECK VALVE FILTER RESTRICTOR FUSE
WST (OB)
WST (OB)
LEFT OUTBOARD WHEEL SPD XDCR
CNTL VALVE (IB)
SHUTTLE VALVE
WST (IB)
LEFT INBOARD WHEEL SPD XDCR
A B
8+ 9 -
WST (IB)
CNTL VALVE (OB)
+ 11 - 10
1 + 2 -
(IB)
11 10
3 + 4 -
(OB)
B
ANTISKID CONTROL UNIT
Figure 32-115. Anti-Skid System Electrical Schematic
SKID CONTROL VALVE
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
3A
7
35 (OB) FAIL IND
TEST
6
MAINTENANCE TRAINING MANUAL
ANTI-SKID SYSTEM
Initialization
OPERATION
When the aircraft lands, the anti-skid system goes into Initialization Mode when the following signals are received by the ASCU:
Anti-Skid Operation Refer to Figure 32-115. Anti-Skid System Electrical Schematic. When the Anti-Skid Switch is selected ON, Power is supplied from the 28 VDC right main bus through Pins F and D of the switch and out of the switch through Pins C and E to Pin 17 of the Anti-Skid Control Unit. When the aircraft is on the approach for landing, the PSEU sends signals to the AntiSkid Control Unit. The signals are as follows:
•• MLGWOW for > 5 seconds OR •• Wheel speed > 75 knots. Metered hydraulic pressure from the brake control valve is slightly reduced by the servo valves, causing the spool and sleeve valves to open partially, preventing full braking force.
Individual Wheel Individual wheel Anti-Skid Mode starts with the signals that follow:
•• WOFFW to Pins 13
•• MLGWOW > 5 seconds OR
•• Gear NOT Up and Locked to Pins 28.
•• Wheel speed < 70 knots.
The ASCU gets the wheel speed < 35 knots signals from: •• Pins 32 and 33 for right inboard and right outboard transducers •• Pins 8 and 9 for the left inboard and outboard transducers. Touchdown Protection Mode causes a full brake release signal sent from: •• ASCU Pins 23 to right dual skid control valve at Pins 1 and 3 •• ASCU Pins 11 to left dual skid control valve at Pins 1 and 3.
NOTE All the pins mentioned are used throughout all modes of antiskid operation.
Full metered pressure from the brake control valve passes through the servo valves. This pressure operates the brakes. If a skid is detected, the ASCU commands decreased pressure to the affected wheel brake unit, until the wheel speeds up to match the speed of the other wheels.
Locked Wheel If an inboard, or outboard wheel develops a skid producing a difference in speed of < 30% of the reference speed, Locked Wheel Protection is now initiated. All metered pressure, for that brake unit, is released to return by the servo valve until the locked wheel speed is > 35% of reference speed. Reference speed is the speed of the matched inboard or outboard wheel, on the other side of the aircraft.
This causes the servo valve to release all hydraulic pressure into the return line. The brakes receive no pressure and the brakes will release.
FOR TRAINING PURPOSES ONLY
32-145
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Interfaces
NOTES
•• The ASCU receives 28 VDC power from the right main DC circuit breakers (ANTISKID INBD CB Q5 and ANTISKID OUTBD CB R5). The ASCU requires power from the two CBS for correct operation. •• The fault data recorded by the ASCU is transmitted over the ARINC 429 data bus as a series of pages and is shown on the Audio Radio Control Display Unit (ARCDU) as a part of the Central Diagnostic System.
32-146
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
32-147
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
PRESENT OTHER SYSTEM 1
1/2
< EMU
ANTI-SKID >
< FCS
ICE PROTECTION >
< ECS
< TMCU1
MENU
ON / OFF
YES
NO
APU >
TMCU 2 >
Figure 32-116. ARCDU CDS ANTISKID System
Figure 32-117. PSEU - Present Faults
ASC CURRENT FAULTS
1/ 2
LT OUTBOARD WST
Figure 32-118. ASC - Current Faults
32-148
F AU L T S ?
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
MAINTENANCE PRACTICES IMPORTANT TO THE MLG BRAKING SYSTEM The following are abbreviated descriptions of the maintenance practices and is intended for training purposes only. For a more detailed description of the practices, refer to the tasks in the Bombardier AMM PSM 1-84-2.
Refer to Figure 32-118. ASC - Current Faults. •• Do a functional test of the antiskid system •• On the ARCDU, retrieve the data for the antiskid system again •• If there is a message then perform the applicable Fault Isolation Procedure.
FAULT ISOLATION INBD ANTISKID and OUTBD ANTISKID (Caution lights) The INBD or OUTBD ANTISKID light illuminates when there is a loss of ability to command or control the inboard or outboard antiskid system. •• R e t r i e v e D a t a f r o m t h e c e n t r a l diagnostic system (CDS) Refer to Figure 32-116. ARCDU CDS ANTISKID System. •• Retrieve Data from the proximity sensor electronics unit (PSEU) Refer to Figure 32-118. ASC - Current Faults.
NOTE The fault isolation procedures for the above PSEU messages are equivalent to those for the related CDS PSEU AIR/GND or PSEU GEAR UP messages. The Data from the Central Diagnostic System - Anti-Skid System (ANTI-SKID) cannot be erased. When a fault is corrected it will be moved from the ASC CURRENT FAULTS page to the ASC PAST FAULTS page (requires refresh).
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-149
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
ASC CURRENT FAULTS
1/ 2
NO CURRENT FAULTS
Figure 32-119. ASC - No Current Faults
#1 STALL SYST FAIL #2 STALL SYST FAIL
FLT DATA RECORDER GPWS
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
FLAP RIVE
LDG GEAR INOP
WT ON WHEELS
LAP WER
NOSE STEERING
FUELING ON
MAIN BAT HOT
FUSELAGE
X BAT HOT
DOORS
Figure 32-120. Parking Brake Caution Light
32-150
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
PARKING BRAKE, INDICATION DISCREPANCY (CAUTION LIGHT)
32 LANDING GEAR
DASH 8 Q400
NOTES
The CAWP usually shows the PARKING BRAKE light on when the EMERG BRAKE lever is in the PARK position.
NOTE This is not a malfunction condition. Refer to Figure 32-120. Parking Brake Caution Light. There are no related central diagnostic system (CDS) messages. If the PARKING BRAKE caution light is on when the EMERG BRAKE lever is in the OFF position, do the Fault Isolation. •• Remove and replace the parking brake control quadrant •• If the fault still continues, remove and replace the CAWP •• If the fault still continues, do a check of the wiring between the parking brake control lever and the CAWP •• If the wiring is unserviceable, repair the wiring.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-151
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND No. 2 Hydraulic Pressure Steering Pressure Return Electrical
HIGH-SPEED TAXI MODE 8° LEFT AND RIGHT (RUDDER PEDALS) 8° 8°
70°
120°
70°
LOW SPEED TAXI MODE 70° LEFT AND RIGHT (STEERING CONTROL HANDLE)
120°
UNPOWERED (CASTER) MODE 120° LEFT AND RIGHT
STEERING CONTROL HANDLE RUDDER PEDALS
STEERING OFF
NOSEWHEEL STEERING SWITCH
PSEU
ON-GROUND SIGNAL FROM NOSE GEAR WEIGHT ON WHEELS SWITCHES
NOSEWHEEL STEERING CONTROL UNIT (SCU)
STEERING MOTOR
NOSE STEERING CAUTION LIGHT REDUCTION GEARBOX
Figure 32-121. Nosewheel Steering System Schematic
32-152
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32-51-00 NOSEWHEEL STEERING SYSTEM
SYSTEM DESCRIPTION
INTRODUCTION
Nosewheel Steering Hand Control
The steering system gives directional control of the aircraft while on the ground. Steering of the nosewheels is for taxi, take-off, and landing.
Full authority steering of the nosewheels is done by the pilot hand control located on the pilot’s side console, in the flight compartment.
The steering system also supplies shimmy damping of the nosewheels.
The pilot hand control is for low speed taxi only.
GENERAL
The steering tiller authority can steer the nosewheels 70° to the left and right of the center position.
The steering system for the nosewheels is electronically controlled and hydraulically powered. Nosewheel Steering can be controlled by the following systems: •• Pilot hand control
Refer to Figure 32-121. Nosewheel Steering System Schematic.
Rudder Pedal Control Limited authority steering of the nosewheels is by the rudder pedals. The rudder pedals allow steering during high speed taxi, take-off, and landing.
•• Rudder pedal control •• Shimmy damping system. Steering of the nosewheels is available when:
The rudder pedals can steer the nosewheel 8° to the left and to the right of the center position.
•• The NLG is down and locked
Shimmy Damping
•• The aircraft has WOW and
The steering system supplies shimmy damping of the nosewheels.
•• The STEERING switch, is set to the STEERING position. The nosewheel steering system includes the listed components: •• Electronic steering control unit •• Nosewheel steering manifold •• Power steering unit •• Rotary variable differential transformer •• Hydraulic steering motor
When the STEERING switch is selected to STEERING, shimmy damping is supplied through the steering manifold. Passive, free castor shimmy damping is supplied when the STEERING switch is in the OFF mode. The free castor mode lets the nosewheels rotate 120° to the left and to the right of the center position.
•• Nosewheel centering mechanism •• Pilot hand control •• Rudder pedal potentiometer •• Steering switch.
FOR TRAINING PURPOSES ONLY
32-153
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure 32-122. Steering Control Unit
1
2 A
FWD
LEGEND 1. SCU 2. Access Panel BITE 3. Electrical Connector.
fs486a01.cgm
A
3
Figure 32-123. Steering Control Unit
32-154
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Steering Control Unit (SCU) Refer to: •• Figure 32-122. Steering Control Unit. •• Figure 32-123. Steering Control Unit. The SCU is an electronic box installed on the outside of the NLG wheel well wall. A quick access panel on the right side of the nose fuselage gives access to the SCU in the equipment bay. The SCU consists of a metal case and cover. On the front face of the unit is a BITE display panel, it is used for diagnostic testing, and an electrical connector to measure the rigging data voltage. The SCU uses input commands from: •• The Pilot Hand Tiller
BITE Test of the Nosewheel Steering System The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
NOTE To retrieve and identify the fault codes for the nosewheel steering system, the NWS switch must be selected to ON. •• On the NWS ECU display, push the BIT switch for approximately 5 seconds and release it. This will start the display. •• Press the BIT switch again and again, and scroll through the menu until ‘READ’ is displayed. •• Push and hold the BIT switch until ‘READ’ is flashing, then release.
•• The Rudder Pedals •• The PSEU
NOTE
•• The Steering Switch •• The Steering Manifold, and •• The RVDT. The SCU supplies output commands to the steering manifold and failure signal to the CAWP. The SCU does Power-Up test, Continuous BIT and diagnostic functions. The SCU can record and store up to 100 failures in a nonvolatile memory for maintenance functions. The last 18 failures are available to line maintenance.
You will see the first fault code when you release the switch. •• If the display reads ‘----’, there are no faults. •• If there are fault codes, record them. •• To complete the BITE test, push the BIT switch again and again. Scroll through the menu until ‘EXIT’ shows. •• Push and hold the BIT switch until ’EXIT’ flashes.
The main function of the SCU is electronic control of the steering system for the nosewheels.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-155
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Nosewheel Steering Hand Control
The hand control has hard stops on either side of the center position. The centering spring returns the pilot hand control to the neutral position when the pilot inputs are removed.
Refer to Figure 32-124. Nosewheel Steering Hand Control. The nosewheel steering hand control is installed on the pilot’s side console in the flight compartment.
The hand control can steer the nosewheels ±70° of center. The function of the tiller is to transfer the steering inputs to the SCU.
The hand control has a potentiometer that sends steering signals to the SCU in proportion to the position of the Pilot Hand Control (PHC).
A
1
LEFT SIDE CONSOLE
2
3
FWD
LEGEND 1. Pilot Hand Control 2. Centering Spring 3. Potentiometer.
A
Figure 32-124. Nosewheel Steering Hand Control
32-156
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Rudder Pedal Potentiometer
The potentiometer is connected to the rudder quadrant with a linkage assembly.
Refer to Figure 32-125. Rudder Forward Assembly (Right Side).
The potentiometer sends signals to the SCU that are in proportion to the position of the rudder pedal position.
The rudder pedal potentiometer is installed on the support structure of the right rudder control quadrant below the flight compartment floor. A panel located on the right side of the nose fuselage gives access to the potentiometer.
The rudder pedals can steer the nosewheel ±8° of center. The potentiometer of the rudder pedal is monitored by the SCU for failure.
The rudder pedal potentiometer is a self contained bolt-on assembly with an electrical connection.
B
A
1 A
RUDDER FORWARD ASSEMBLY
2
FWD
3 4
B
LEGEND 1. Rudder Quadrant 2. Linkage Assembly 3. Rudder Pedal Potentiometer 4. Support Structure.
Figure 32-125. Rudder Forward Assembly (Right Side)
FOR TRAINING PURPOSES ONLY
32-157
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-158
P PRESSURE SWITCH
LEGEND
STEERING MANIFOLD
PRESSURE RETURN MODE SELECTOR VALVE
COMPENSATOR
DASH 8 Q400
POWER-OFF ORIFICE
CHECK VALVE FILTER
ORIFICE RELIEF VALVE
POWER-ON ORIFICE
CHARGE ORIFICE SOLENOID VALVE (NORMALLY CLOSED)
EHSV
LOAD RELIEF VALVES
P R RETURN HYDRAULIC MOTOR
Figure 32-126. Nosewheel Steering Hydraulic Synoptic
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RESTRICTOR ANTI-CAVITATION VALVES
MAINTENANCE TRAINING MANUAL
Nosewheel Steering Manifold Refer to Figure 32-126. Nosewheel Steering Hydraulic Synoptic. The nosewheel steering manifold is a self contained assembly. It is installed on the right front side of the NLG outer cylinder. The Hydraulic Steering Manifold contains the following components: •• Filter/inlet check valve •• Solenoid operated hydraulic valve •• Electro Hydraulic servo valve •• Mode selector valve •• Compensator •• Relief valves (2) •• Shimmy damping orifices (2) (on and off) •• Anti-cavitation check valves (2) •• Pressure switch (LRU) •• Compensator charge orifice
The mode selector valve stops hydraulic pressure to the EHSV when the steering system is in the passive, free castor mode. The SOV is in the closed position until the NLG is compressed when the aircraft lands. The solenoid valve is then energized by signals from the SCU to open the mode selector valve and to configure the steering system for powered steering. The EHSV gets signals from the solenoid valve and converts them into proportional spool displacement. The spool displacement sends hydraulic pressure to the hydraulic motor to drive the reduction gearbox and to steer the nosewheels to the commanded position. Nosewheel position signals are sent to the LVDT installed in the steering manifold, then to the SCU to keep the nosewheels in the commanded steering position. The pressure switch senses any changes in hydraulic pressure that are caused by the failure of the components in the steering manifold. The pressure switch sends a signal to the SCU, when the signal is received. A light on the Caution and Warning panel in the flight compartment illuminates. The pressure switch and the solenoid LRU’s.
•• Case drain check valve •• Return check valve. Hydraulic power is supplied by the No.2 hydraulic system. Two electrical connectors supply power to the steering manifold. The function of the steering manifold is to control the hydraulic pressure to the steering motor for powered steering, and to provide damping. The steering manifold controls hydraulic pressure to the steering hydraulic motor for powered steering of the nosewheels. Hydraulic power for the steering manifold is supplied by the No.2 hydraulic system through the landing gear selector valve extension tubing. Hydraulic fluid is returned to the No.2 hydraulic system through the retraction tubing of the landing gear selector valve. Two electrical connectors supply electric power to the steering manifold. One connector supplies electrical power to the SOV, the EHSV, and to the EHSV LVDT. The second connector supplies electrical power to the pressure switch.
FOR TRAINING PURPOSES ONLY
32-159
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Nosewheel Centering Mechanism Refer to: •• Figure 32-127. N osewheel Centering Actuator. •• Figure 32-128. N osewheel Centering Mechanism. T he nosewheel cent eri ng mecha nism is installed on a collar which is attached to the lower end of the NLG inner cylinder. The spring loaded, centering actuator has a roller bearing that rolls on a race on the NLG outer cylinder. The race has a detent at the centered position. The centering actuator has an attached proximity sensor. The proximity sensor sends a centered signal to the PSEU when the roller is in the detent.
Figure 32-128. Nosewheel Centering Mechanism
NOTE The centering actuator cannot move the nosewheels to the center position.
Figure 32-127. Nosewheel Centering Actuator
32-160
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Power Steering Unit Refer to Figure 32-129. Power Steering Unit. The Power Steering Unit (PSU) is installed on the top of the nose landing gear shock strut. It is a self-contained assembly bolted onto the NLG outer cylinder and keyed to inner cylinder for transmitting torque.
The hydraulic motor operates a reduction gearbox which steers the nosewheels. The function of the power steering unit is to assist the NLG steering system with hydraulic power to steer the nosewheels to the commanded position.
The PSU has a steering manifold, a hydraulic motor, and a reduction gearbox with RVDT’s. Hydraulic pressure to operate the steering is supplied by the No.2 hydraulic system.
1
LEGEND 1. Power Steering Unit 2. Shock Strut. A
2
B
A
B
Figure 32-129. Power Steering Unit
FOR TRAINING PURPOSES ONLY
32-161
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
PAGE INTENTIONALLY LEFT BLANK
32-162
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Removal of Power Steering Unit
32 LANDING GEAR
DASH 8 Q400
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. For full information of the task consult the AMM. 1. Place aircraft in standard configuration for maintenance. 2. Open and lock landing gear doors. 3. Remove steering hydraulic motor. 4. Remove steering feedback assembly. 5. Remove grease and oil from steering gearbox. 6. Remove all bolts and washers securing the gearbox. 7. Remove gearbox using 3 jacking screws designated as AT 31956 NLG Steering Box Puller Kit.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-163
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND 1. Steering Manifold 2. Hydraulic Motor. 1
D
FW
2
Figure 32-130. Hydraulic Steering Motor
Figure 32-131. Steering Feedback Assembly
32-164
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Hydraulic Steering Motor
32 LANDING GEAR
DASH 8 Q400
NOTES
Refer to Figure 32-130. Hydraulic Steering Motor. The hydraulic motor is attached to the lower left side of the reduction gearbox. The hydraulic motor drives the feedback gear of the reduction gearbox. The hydraulic motor receives hydraulic pressure through the Electro Hydraulic Servo Valve. The function of the hydraulic motor is to drive the reduction gear assembly to steer the nosewheels to the commanded position.
Steering Feedback Assembly Refer to Figure 32-131. Steering Feedback Assembly. The steering feedback assembly is installed on the top of the NLG shock strut. There are two RVDT’s which are part of the steering feedback assembly. The nosewheel position feedback is accomplished through the previously mentioned RVDT’s. Each RVDT connects to the feedback gear of the reduction gearbox. The SCU uses one RVDT to supply the position of the nosewheels. The SCU uses the second RVDT to check the accuracy of the first RVDT as a fault test. The function of the two RVDT is to provide nosewheel position feedback to the SCU.
FOR TRAINING PURPOSES ONLY
32-165
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LEGEND 1. Nosewheel Steering Toggle Switch.
CIR BKR LIGHT
W/S WIPER ICE PILOTS ICE DETECT FLT PNL
STEERING
1
Figure 32-132. Nosewheel Steering Switch
A
OVERHEAD CONSOLE
WT ON WHEELS NOSE STEERING
2 LEGEND 1. Nose Steering (Amber) 2. Weight On Wheels (Amber).
1 A
Figure 32-133. Nosewheel Steering System Caution Lights
32-166
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Steering Switch Refer to Figure 32-132. Nosewheel Steering Switch. The steering switch is located on the pilot side console. The switch is a two position, toggle switch. It has a STEERING and an OFF position. The function of the STEERING switch is to supply 28 VDC to the SCU.
•• Press the BITE switch and scroll through the menu until “NWP1” displays. •• Measure the output voltage at the test jack found at the front of the SCU. The reference indication must be 0 VDC. •• Do the same for “NWP2”. •• This electronically zero’s the two RVDT’s inside the SCU. •• The SCU then electronically sets the travel limits.
CONTROLS AND INDICATIONS Refer to Figure 32-133. Nosewheel Steering System Caution Lights. If any component in the steering system fails, the NOSE STEERING caution light will come on. If the NG WOW sensors or harness are damaged, the WOW caution light will come ON.
Rigging of the RVDT The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
NOTE Make sure that you cannot put a piece of paper between the centering roller and the cam, both sides. •• The STEERING switch must be selected to the ON position
NOTE Make sure that the red dot on top of the RVDT’s is aligned with the black etched line on the base of the RVDT. •• Press the BITE switch and scroll through the menu until “RIG” displays. Hold the switch until “RIG” is flashing.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-167
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
32-168 AVIONICS RACK C NLG DOWNLOCK NLG WOW 2
11F 2H
7 14
NLG WOW 1 10D
6
NLG DOWNLOCK NLG WOW 2
14 NOSE STEERING
FAIL 5
NLG WOW 1
32-61 A1 PSEU
35 34 36
E
2
1
D
FW
F
WD
F
C
LIMITED AUTHORITY STEERING
NOSE STEERING ARMING SWITCH (FLIGHT COMPARTMENT)
RUDDER PEDAL CONTROL POTENTIOMETER
B
D
FW
A
FULL AUTHORITY STEERING
B
MANIFOLD HANDWHEEL CONTROL POTENTIOMETER
(P5) 28 V DC R MAIN
A
3A
NLG STEER CONT 2
G
8
7
SOLENOID VALVE
3 8
1 2
SOLENOID VALVE
SWITCH CLOSED WHEN HYDRAULIC PRESSURE IS ON PRESS.
1K 9
H
40 32
28V DC IN GND
31 39
4 5
LVDT EXCITATION
16 24
12 11
RVDT EXCITATION
55 54
1 2
SERVO TORQUE MOTOR
SERVO TORQUE MOTOR
PRESSURE SWITCH
C A B
RIGHT DC CBP
(C6) 28 V DC L MAIN
LEFT DC CBP
3A
NLG STEER CONT 1
4 K
5
6
7 8 9
ELECTROHYDRAULIC SERVO VALVE J
NOSE STEERING ARMING SWITCH (FLIGHT COMPARTMENT)
25 47
28V DC IN GND
10
GND
4 1 9 15 23 53 49 50 51 52 46
RVDT #1 4 5 6
PRESSURE ON LVDT POSITION FEEDBACK RVDT 1
RVDT EXCITATION
38 45
1 2
RVDT #2 4 5 6
POSITION FEEDBACK RVDT 2
STEERING CONTROL UNIT
NOSEWHEEL STEERING ASSEMBLY
FW
D
A
Figure 32-134. Nosewheel Steering - Electrical Schematic
C N/C
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
27 29 28
1 2 3
DASH 8 Q400
SOV FAIL 2 A B C
B
CAUTION AND WARNING PANEL (O/H CONSOLE)
MAINTENANCE TRAINING MANUAL
OPERATION NORMAL SYSTEM OPERATION Refer to Figure 32-134. Nosewheel Steering Electrical Schematic.
As the steering motor rotates the NLG inner cylinder, the two RVDT’s send the nosewheel position back to the control unit at Pins 49, 50 and 53 from RVDT 1 and Pins 46, 51 and 52 from RVDT 2.
No.2 Hydraulic pressure is supplied to the nosewheel steering system, through the landing gear selector valve in the DOWN position.
When the feedback signals from the RVDT’s equal the input signals from the potentiometers, the SCU commands the Electro Hydraulic servo valve to the neutral position.
When the nosewheel steering switch is selected ON, power from the left and right main 28 VDC buses is supplied from Pins H and J of the switch, to Pins 40 and 25 of the SCU.
This action causes a hydraulic lock across the steering motor, which holds the steering in the selected position until another input signal is generated.
With WOW, the steering control unit receives inputs from the PSEU as follows:
Operation in the Passive Mode
•• Pin 11F to SCU Pin 7 - NLG Downlock •• Pin 2H to SCU Pin 14 - NLG WOW 2 •• Pin 10D to SCU Pin 6 - NLG WOW 1. The SCU outputs current to the following: •• Solenoid valve •• Servo valve torque motor. The operator input is sensed through the rudder pedal or handwheel control potentiometer output. It is then sent to the SCU. The SCU positions the Electro Hydraulic servo valve to steer left or right. Feedback from the LVDT at Pins 9, 15 and 23, to the SCU confirms servo valve has moved to the correct position. Feedback from the pressure switch on Pins 1 and 4 at the SCU confirms that hydraulic pressure is available.
The system will be in passive mode when any of the following occurs: •• S T E E R I N G s w i t c h s e l e c t e d O F F (requirement for towing) •• SCU de-energized •• SCU receives power from only one CB •• SCU does not receive any of the required inputs from the PSEU •• No hydraulic power •• Landing bypass valve in the bypass position •• NOSE STEERING caution light ON. The mode selector valve is positioned by the valve spring, to connect the hydraulic lines to each side of the hydraulic motor, through the power-off orifice. This allows the hydraulic motor to turn freely when the nosewheel is physically turned by the towbar, or differential engine power while taxiing.
Hydraulic pressure through the solenoid valve acts on the bottom of the Mode Selector Valve (MSV). The MSV sends pressure to the Electro Hydraulic servo valve to drive the steering motor left or right. Return fluid from the other side of the motor returns through the servo valve.
FOR TRAINING PURPOSES ONLY
32-169
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Operational Test of the Nosewheel Steering System
Functional Test of the Nosewheel Steering System
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
Tow the aircraft NLG onto a set of greaseplates and with the nosewheel steering switch selected to ON operate the steering hand control and the rudder pedals.
With the nosewheel steering switch selected to ON operate the steering hand control and the rudder pedals through the full range of motion.
Make sure that the nosewheel position agrees with the position of the steering hand control and rudder pedals.
Using the Protractor measure to ensure full travel of the steering system. Do this with WOW and with WOFFW to test for normal control and indication.
NOTE The steering operation can be sluggish when the hydraulic system is pressurized by the SPU.
CAUTION Make sure that the RVDT’s are adjusted correctly. If the RVDT’s are not adjusted correctly, the nose gear can go through the 70° limit. This can cause damage to the equipment. Install a tow bar and move the NLG to the left and the right 120° stop positions and then back to 0° with the towbar.
NOTE This is to make sure that the NLG can move freely. Make sure the NLG electrical harness has sufficient clearance to not catch on other components and is not stretched.
32-170
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
32-171
32 LANDING GEAR
32-172 FUSELAGE DOOR
LDG INHIBIT FUSE DOORS
WARNING & SYNOPTIC
PSEU
DISCRETE INPUTS PROX SENSOR INP.
CABIN PRESSURE SYSTEM
FUSE DOORS
WOW No. 2 LDG CONTROL & FUSE DOORS
CONTROL DISCRETE OUTPUTS DISCRETE OUTPUTS
WOW No. 2 OUTPUTS
CROSS COMM WOW No. 2 & LDG
LAMP TEST No. 2
PROX SENSOR INP.
DISCRETE INPUTS
FUSE DOORS
PSC B ALTERNATE DOWNLOCK INDICATION & FUSE DOORS
BITE FRONT PANEL KEYPAD & DISPLAY
BITE
WT ON WHEELS
CROSS COMM DISCRETE OUTPUTS
MAINTENANCE DISCRETE OUTPUTS
ADI OUTPUTS CENTRAL MAINTENANCE PANEL PSEU PSS MAINT OPER
LDOOR
NDOOR RDOOR
LEFT
NOSE
RIGHT
LEFT
NOSE
RIGHT
LANDING GEAR
PSC D LAMP TEST No. 1
LDG INDICATION & FUSE DOOR SENSORS
DISCRETE INPUTS
FUSE DOORS
LANDING GEAR INDICATION & FUSE DOORS
fs582a01a.cgm
PROX SENSOR INP.
LDG INDICATIONS LOCK RELEASE
CROSS COMM
HORN MUTE
PROX SENSOR INP.
DISCRETE OUTPUTS PSC E
WOW No. 1, LDG DOORS & FUSE DOOR SENSORS
UP
DN
FUSE DOORS
WOW No. 1 & FUSE DOORS
LDG SELECTOR VALVE
TEST
CROSS COMM DISCRETE OUTPUTS
IFC
WOW No. 1 & LDG
LDG GEAR INOP
Figure 32-135. PSEU Input and Output Block Diagram
LDG DOOR SOLENOID SEQUENCE VALVES
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
ALTERNATE DOWNLOCK & FUSE DOOR SENSORS
AIRCRAFT SYSTEMS REQUIRING WOW & LDG POSITION INPUTS
DASH 8 Q400
WOW No. 2 NOSE CENT & FUSE DOOR SENSORS
PSC A
MAINTENANCE TRAINING MANUAL
32-61-00 PROXIMITY SENSOR SYSTEM
The four discrete inputs to the PSS are: •• Landing gear extension command •• Landing gear retraction command
INTRODUCTION
•• INHIBIT switch set to INHIBIT
The Proximity Sensor System (PSS) is part of the landing gear system.
•• Landing gear lamp test selected.
GENERAL Refer to Figure 32-135. PSEU Input and Output Block Diagram. The PSEU receives signals from 20 landing gear and 11 fuselage door proximity sensors. The PSEU then transmits discrete outputs to the landing gear and door indicators. The Proximity Sensor System has the following components: •• Proximity sensor electronic unit •• Proximity sensors
SYSTEM DESCRIPTION The PSS is a 28 VDC energized, microprocessor based proximity system. The system has signal conditioning, proximity sensing, discrete monitoring, control signals, interface wiring and a BITE keypad with display. The PSS sends discrete outputs as follows: •• Landing gear control •• Landing gear status indication •• Alternate downlock indication •• WOW1 •• Fuselage door indication •• WOW2.
FOR TRAINING PURPOSES ONLY
32-173
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
B
FWD
A
AVIONICS RACK ELECTRICAL INSTALLATION
ME
NU
YE
S
ON OF / F NO
BD
IN
FWD
B
Figure 32-136. Proximity Sensor Electronic Unit
32-174
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
COMPONENT DESCRIPTION Proximity Sensor Electronic Unit Refer to: •• Figure 32-136. P roximity Sensor Electronic Unit. •• Figure 32-137. P roximity Sensor Electronic Unit. The PSEU is installed on the avionics rack. The PSEU receives 28 VDC from the right and left main buses, and the right and left essential buses. The PSEU provides visual indication in the flight compartment for: •• Gear position •• Gear doors position, and •• Fuselage doors status. The primary functions of the PSEU are as follows: •• Monitor, indicate and operate the landing gear extension, and retraction system •• Monitor and supply the uplock, down lock, and WOW data to other systems •• Supply indication for the passenger and baggage doors. The logic circuits of the PSEU use the “near” and “far” condition of the proximity sensors for logic equations.
Figure 32-137. Proximity Sensor Electronic Unit
Built-In-Test-Equipment The PSEU contains BIT and BITE functions. These functions let the PSEU do the maintenance, and functional testing of the PSS. The ON/OFF button turns the BITE display ON or OFF. When you change from OFF to ON, the BITE display always starts at a PRESENT FAULTS? prompt. You will push the menu button to return to the most recent, higher level prompt. The UP button gives you access to the previous fault or status display, when you get a list of displays. The DOWN button sequences to the subsequent fault or status display on the list.
FOR TRAINING PURPOSES ONLY
32-175
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Installation of the Proximity Sensor Electronic-Unit The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Before you touch the PSEU, put on the static wrist strap •• After installation wait 3 minutes, this allows the PSEU to complete the power up test •• On the PSEU, ERASE the FAULT HISTORY if there is one.
NOTE T h e m e s s a g e ERASE IN PROGRESS w i l l a p p e a r , followed by the message FAULT HISTORY ERASE COMPLETE.
Retrieval of Data from the Proximity Sensor Electronic Unit (PSEU) The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• On the PSEU, push the ON/OFF button The PSEU display shows the prompt for the first item on the TOP LEVEL menu, the PRESENT FAULTS?
NOTE The items in the top menu show in the sequence that follows: 1. PRESENT FAULTS 2. FAULT HISTORY 3. RIGGING HELP 4. RIGGING HISTORY 5. SYSTEM STATUS 6. FAULT HISTORY ERASE. •• If you push the MENU button, the PSEU display shows the prompt for the previous item on the top menu
NOTE If there is no BITE keypad activity for 15 minutes the PSEU display will go blank. •• Push the MENU button to show the ERASE FAULT HISTORY? prompt. If the fault clears while the PSEU display shows the fault and there is no keypad activity, the display will show the FAULT NO LONGER PRESENT message. If the fault returns while the PSEU display shows the FAULT NO LONGER PRESENT message and there is no keypad activity, the display will show the applicable fault message.
32-176
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Erase the Data from the Proximity Sensor Electronic Unit (PSEU)
Operational Check of the Proximity Sensor Electronic Unit
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
NOTE The PSEU takes 3 minutes to complete its power-up self test.
•• Push the ON/OFF button on the PSEU and select PRESENT FAULTS •• Push the YES button
NOTE
•• Turn the PSEU ON •• The PRESENT FAULTS prompt is shown
This test is intended to be done without any faults present on the PSEU.
•• Push the NO button again and again until the display shows the ERASE FAULT HISTORY? prompt
•• On the maintenance panel, the PSEU OPER light comes on
•• Select YES, the PSEU will ask ARE YOU SURE?
•• On the maintenance panel, the PSS MAINT (check required) light goes out
•• Select YES, the PSEU display shows the ERASE IN PROGRESS message
•• If the PSS MAINT light stays on, faults are present. Refer to the list of known nuisance faults, see AMM
•• Wait until the PSEU display shows the FAULT HISTORY ERASE COMPLETE message.
Revision 0.4
•• C l e a r a l l f a u l t s a n d t h e n d o t h i s Operational Check again.
FOR TRAINING PURPOSES ONLY
32-177
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
S19 NGDRCL S09 NGDN1 S11 NGLK1 S03 NGWOFW1 S31 PADRCL
PASSENGER AIRSTAIR DOOR
S33 PADRLK
S07 LGDLK1
S08 LGDLK2
S15 LGUPLK
S17 LGDRCL
S01 LGWOW1
AFT PASSENGER DOOR AFT BAGGAGE DOOR
S02 LGWOW2 S37 APDRCL S39 APDRLK S43 ABDRCL S45 ABDRLK
S18 NWCENT S10 NGDN2 S12 NGLK2 S04 NGWOFW2 S34 FBDRCL S36 FBDRLK
FWD BAGGAGE DOOR
S46 EDRCLLK
EMERGENCY EXIT DOOR
S13 RGDLK1
S14 RGDLK2
S16 RGUPLK
S20 RGDRCL
S05 RGWOW1
S06 RGWOW2
S40 ASDRCL S42 ASDRLK
SERVICE DOOR
fs432a01.cgm
Figure 32-138. Proximity Sensors - Locations
32-178
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
Proximity Sensors Refer to: •• Figure 32-138. P roximity Sensors - Locations. •• Figure 32-139. Proximity Sensors. There are 31 proximity sensors. Each main landing gear has six proximity sensors. The nose landing gear has eight. There are eleven sensors that monitor: •• Passenger entrance door •• The baggage compartment doors •• The emergency exit doors, and •• The service door. The proximity sensors are hermetically sealed, variable reluctance, two wire devices. The inductance at the sensor changes with the sensor’s proximity to the target. As the target gets closer to the sensor face, the inductance increases.
Figure 32-139. Proximity Sensors
The proximity sensors are not repairable. The function of the sensors is to supply position data to the PSEU.
FOR TRAINING PURPOSES ONLY
32-179
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Installation of the Proximity Sensors
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• There are many proximity sensors installed on the landing gear and doors in different locations. •• Many have different clearances and wire lead lengths. •• T h e P r o x . s e n s o r s d o n o t c o m e terminated, you will need to cut the wires, terminate them and insert the pins into the connector.
CAUTION Do not bump or scratch the face of the proximity sensor because this can damage the proximity sensor. •• Adjust the clearance between the sensor and the target to match the application and location.
Rigging of the Proximity Sensors The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Adjust the sensors to the nominal clearances specified in the AMM. •• Many sensors have different clearances and therefore inductance. •• At the PSEU, use the SYSTEM STATUS MENU to make sure that the inductance in each sensor, is correct. •• Adjust sensor clearance from the nominal, to achieve the permitted inductance.
32-180
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Landing Gear Control The PSEU provides discrete outputs that are used to control the movement of the landing gear (extend or retract), and landing gear doors (open or close). The PSEU generates seven discrete outputs that provide the landing gear control function. The outputs include the Flight Data Recorder, and the no smoking sign.
Landing Gear Indications The following conditions are monitored by the landing gear indication system: •• Right, left, and nose gear door position •• Right, left, and nose gear position. The outputs of the proximity sensors are processed by the PSEU. The PSEU generates 16 discrete outputs which are sent to the two IOP in the IFC’s, the landing gear control panel, the caution and warning panel, the Antiskid/Brake Control Unit, and the Nosewheel Steering Control Unit. The landing gear control provides visual indication for each of the three landing gears:
32 LANDING GEAR
DASH 8 Q400
ALTERNATE DOWNLOCK INDICATIONS The Alternate Down Lock Indication (ADI) provides a second DOWN and LOCKED indication of the three landing gears. This function is used if the primary landing gear indication function shows an unsafe, or gear disagree condition. ADI is independent from the primary indication. Different sensors and PSC card are used to process inputs. The following conditions are monitored by the ADI: •• Right and left gear down and locked •• Nose gear down and locked. The left and right gears each have an alternate sensor that monitors down and locked. The nose gear has one sensor for the down position and one for locked. The Advisory lamp test on the Passenger Warning panel will cause the ADI lights to come on. Incorrect Landing Gear Configuration/Landing Gear Warning Horn. This information can be found in MTM Vol 1 Chapter 31-62-00 Landing Gear Warning.
•• GEAR DOWN and LOCKED •• GEAR NOT IN COMMANDED POSITION •• GEAR DOOR NOT CLOSED.
FOR TRAINING PURPOSES ONLY
32-181
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
#1 STALL SYST FAIL #2 STALL SYST FAIL
FLT DATA RECORDER GPWS
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LAP RIVE
LDG GEAR INOP
WT ON WHEELS
LAP WER
NOSE STEERING
FUELING ON
MAIN BAT HOT
FUSELAGE
X BAT HOT
DOORS
Figure 32-140. CAWP with WOW Caution
32-182
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
WOW Functions Refer to Figure 32-140. CAWP with WOW Caution. The WOW function provides discrete outputs to other aircraft systems. Two separate channels WOW No.1 and WOW No.2 generate the weight-on-wheels discrete outputs.
PSEU Operating Mode
Condition
WOW
At least four of any of the six conditions that follow: LGWOW1 = True LGWOW2 = True RGWOW1 = True RGWOW2 = True NGWOFW1 = False NGWOFW2 = False
The PSEU generates five types of WOW outputs, they are as follows: •• All three gear (WOW) •• Main gear (MGWOW) NEAR •• Main gear (MGWOFFW) FAR •• Nose gear (NGWOW) FAR •• Nose gear (NGWOFFW) NEAR. There are two discrete outputs supplied by the PSEU that are special to WOW1 and, WOW2 systems. These signals are WOW1 Operational, and WOW2 Operational respectively. These two signals are supplied in the same way. The CAWP uses these two discrete outputs to show that the WOW functions operate correctly. If one of the two signals become deactivated on the CAWP, the WT ON WHEELS caution light illuminates. For this to occur, the WOW Operational discrete output will deactivate in the conditions as follows: •• There is a disagreement between two of the WOW sensors (in the same WOW system), that the aircraft is either on the ground, or in the air. •• A minimum of one proximity sensor becomes defective in each of the WOW1 and WOW2 systems at the same time.
Operational Check of the Weight On Wheels System The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
NOTE You can do this check on either the LH or RH gear. Make sure that all the hydraulic power is off. •• Insert an anti-target (copper) at a main landing-gear proximity sensor to simulate an erroneous far target (“air”) state. •• Make sure the WOW caution light comes on.
NOTE There will be a 30 second delay before the light comes on. •• Remove the anti-target from the WOW proximity sensor. •• Make sure the WOW caution light goes out.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-183
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-00-00 APPENDIX MAINTENANCE CONSIDERATION The following are abbreviated descriptions of the maintenance practices and are intended for training purposes only. For a more detailed description of the practices, refer to the tasks in the Bombardier AMM PSM 1-84-2.
Safety Precautions WARNING
BE CAREFUL WHEN YOU REMOVE THE DOOR LOCKPIN. THE LANDING GEAR DOORS WILL CLOSE IF YOU PRESSURIZE THE HYDRAULIC SYSTEM. IF YOU DO NOT DO THIS, IT CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. WARNING
THE LANDING GEAR DOORS CLOSE QUICKLY WHEN YOU PRESSURIZE THE HYDRAULIC SYSTEM. MAKE SURE THAT ALL PERSONNEL AND EQUIPMENT ARE CLEAR OF THE LANDING GEAR. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. WARNING
DO NOT USE FORCE WHEN YOU ENGAGE THE GROUND LOCK OF THE NOSE LANDING GEAR. IF FORCE IS NECESSARY, THE LANDING GEAR MAY NOT BE SAFE AND CAN RETRACT ACCIDENTALLY. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE AIRCRAFT. 32-184
WARNING
REMOVE THE TOWBAR FROM THE NOSE LANDING GEAR BEFORE YOU SET THE STEERING SWITCH TO THE ON POSITION. IF YOU SET THE STEERING SWITCH TO THE ON POSITION, THE NOSEWHEELS WILL AUTOMATICALLY GO TO THE NEUTRAL POSITION. IF YOU DO NOT REMOVE THE TOWBAR, YOU CAN CAUSE INJURY TO PERSONS OR DAMAGE TO THE EQUIPMENT. WARNING
BEFORE YOU CONNECT THE TOWBAR TO THE AIRCRAFT MAKE SURE YOU SET THE NOSEWHEEL STEERING SWITCH TO THE OFF POSITION. IT MUST STAY IN THE OFF POSITION WHILE YOU TOW THE AIRCRAFT. THE NOSEWHEEL HAS TO BE IN THE MIDDLE POSITION BEFORE YOU DISCONNECT THE TOWBAR. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO THE EQUIPMENT. WARNING
MAKE SURE THAT THE ALTERNATE RELEASE DOOR AND THE ALTERNATE EXTENSION DOOR ARE FULLY CLOSED BEFORE YOU USE THE PRIMARY RETRACTION OR EXTENSION SYSTEM OF THE LANDING GEAR. IF YOU DO NOT DO THIS, IT CAN CAUSE DAMAGE TO LANDING GEAR SYSTEM COMPONENTS.
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Main Landing Gear Lower Bearing Seal A spare dynamic seal is installed in the shock strut assembly of the main landing gear (MLG). Defective dynamic seals may be replaced with this spare dynamic seal. WARNING
THE SHOCK STRUT ASSEMBLY IS PRESSURIZED WITH NITROGEN GAS. RELEASE THE PRESSURE BEFORE YOU REMOVE THE OIL/NITROGEN FITTINGS OR THE TORQUE LINK PINS. IF YOU DO NOT DO THIS, YOU CAN CAUSE INJURY TO PERSONNEL OR DAMAGE TO EQUIPMENT.
Standard Configuration for an ‘On-Jacks’ Weight-On-Wheels (WOW) Condition
Standard Configuration for an ‘On-Ground’ Weight-Off-Wheels (WOFFW) Condition To put the aircraft in the weight-off-wheels configuration: 1. Connect the pitot/static tester to the No.1 and No.2 systems. 2. Put the de-actuator (copper) targets on the main landing gears. 3. Put the actuator (steel) targets on the nose landing gear. 4. Adjust the tester until the primary flight displays show an airspeed of a minimum of 40 kts. 5. Make sure that the airspeed is valid on the PFD’s (indicators DO NOT show red). 6. Make sure that the WT ON WHEELS caution light does not come on.
Tools and Equipment To put the aircraft in the weight-on-wheels configuration: 1. Put the actuator (steel) targets on the main landing gears. 2. Put the de-actuator (copper) targets on the nose landing gear.
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-185
32 LANDING GEAR
DASH 8 Q400
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-00-00 SPECIAL TOOL & TEST EQUIPMENT •• GSB0700016 NLG Axle Jack •• GSB0700023 Axle Jack •• GSB0700024 Tail Stand •• GSB0900004 Towhead Assembly •• GSB0900005 Towbar •• GSB1000020 Pin, NLG Door Ground Lock •• GSB1000028 Pin, MLG Door Ground Lock •• GSB2000009 Digital Inclinometer (Protractor) •• GSB2400001 Digital Multimeter - Hand Held •• GSB2400011 Static Wrist Strap •• GSB2400016 or equivalent Electrical and avionics tool kit •• GSB2700007 Cable Tension Meter •• GSB2700008 Rigging Pin Kit •• GSB2700008-09 Rigging Pin, 0.1875-4.00 in. (4.76-101.6 mm) L-Pin •• GSB2700008-15 Rigging Pin •• GSB2700008-16D Target-Actuator (Steel) •• GSB2700008-30 Target-Actuator (Steel) •• GSB2700008-30 Target 0.030 in (0.762 mm) Thick •• GSB2700008-32 Target-De-Actuator (Copper) •• GSB2700008-32 Target 0.040 in (1.02 mm) Thick •• GSB2700009 Cable Tension Meter •• GSB29000YY Unit - Hydraulic Power, 28 - 34 GPM •• GSB3241005 NLG Axle Nut Socket •• GSB3241006 MLG Axle Nut Socket •• GSB3242003 Anti-skid Tester •• GSB3242004 Adapter, Wheel Speed Transducer Spin-Up •• GSB3242005 or R1722 Adapter, Anti-skid Tester •• GSB3240006 or equivalent Tool - Brake Application •• GSB3251006 NLG-Steering Angle Protractor •• GSB3411011 Test Set - Air Data •• Landing Gear P/N AT-31859 Assembly Tool (Used To Torque the Jam Nut at the Gland Nut) •• M83723/31-20 Insert/Extract Tool
32-186
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
•• AT 31791 Assembly Tool •• AT 31792 Metering Pin Tool •• AT 31794 Assembly Tool •• AT 31819 Barrel Nut Tool •• AT 31822 Assembly Tool •• AT 31823 - Use with Gland Nut P/N 47118-1. Assembly Tool •• AT 31956 NLG Steering Box Puller Kit •• AT 32027 Bullet, MLG Axle •• AT 55447 Assembly Tool •• AT 57495 - Use with Gland Nut P/N 47118-3. Assembly Tool •• AT 31849 Tool - Spring Compression, MLG Stabilizer Brace •• AT 56653 Assembly Tool •• AT 56658 Assembly Tool •• AT 56659 Assembly Tool •• GE56987 Arbor •• SA460168 or FTP-323002-001-58 (Local Manufacture) with Jam Nut P/N MS21340-08 (Qty. 2) •• MLG Door Sensor Shop Aid •• Goodrich Landing Gear P/N AT-31838 Assembly Tool (Used To Torque the Jam Nut at the Gland Nut) •• DHC8PROX-RTP-0102 Proximity Sensor De-actuator Test Target •• Local Manufacture Grease Plate •• 05-7024-3600-A3 Hydraulic Power Unit •• CG-56806 Setting Tool - Retract Actuator, MLG •• GC 55979 Latch Wear Measurement Tool (Surface Gauge) •• Commercially Available Brake Bleed Kit •• G601R324301-1 or equivalent Brake Bleed Hose •• Commercially Available Tensiometer •• 964-0446-001 Download Unit •• Commercially Available Insertion/extraction Tool M81969/14-10 (Red/Orange) •• Commercially Available Crimping Tool AF8 or M22520/1-01 •• Commercially Available Positioner TH163 or M22520/1-04 •• Commercially Available Daniels PMBT 1200 Power Miniband Tool or Equivalent
FOR TRAINING PURPOSES ONLY
32-187
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
32-00-00 MAINTENANCE PRACTICES Refer to the Bombardier AMM PSM 1-84-2 for details on these maintenance procedures: •• AMM 32-00-00-840-801 Open and Lock the Landing Gear Doors •• AMM 32-00-00-840-802 Unlock and Close the Landing Gear Doors •• AMM 32-00-00-840-803 S tandard Configuration for an ’On−Jacks‘ Weight−On−Wheels (WOW) Condition •• AMM 32-00-00-840-804 S tandard Configuration for an ’On−Ground‘ Weight−Off− Wheels (WOW) Condition •• AMM 32-00-00-890-801 Sequence of Operations for a Main Landing Gear Replacement •• AMM 32-00-01-200-801 S equence of Operations for the Nose Landing Gear Replacement •• AMM 32-00-01-200-802 F luid Leakage Inspection of the Nose and Main Landing−Gear Shock−Struts •• AMM 32-00-01-640-801 L ubrication of the Nose and Main Landing Gear (MRB #320001−201) •• AMM 12-20-01-640-802 Lubrication of the Nose Landing Gear •• AMM 12-20-01-640-803 Lubrication of the Main Landing Gear •• AMM 12-20-01-640-804 Lubrication of the Landing Gear Door Hinges and Linkages •• AMM 12-20-01-640-818 L ubrication of the Chrome Piston Surface on Landing Gear Shock−Struts •• AMM 12-10-32-610-802 Servicing of the MLG Shock Strut •• AMM 32-11-01-000-801 Removal of the Shock Strut •• AMM 32-11-01-400-801 Installation of the Shock Strut •• AMM 32-11-01-000-802 Removal of a MLG Dressed Shock Strut •• AMM 32-11-01-400-802 Installation of a MLG Dressed Shock Strut •• AMM 32-11-04-000-801 Removal of the Axles •• AMM 32-11-04-400-801 Installation of the Axles •• AMM 32-11-04-000-802 Removal of the Wheel−Speed Transducer Electrical−Harness •• AMM 32-11-04-400-802 Installation of the Wheel−Speed Transducer Electrical−Harness •• AMM 32-11-21-000-801 Removal of the Yoke •• AMM 32-11-21-400-801 Installation of the Yoke •• AMM 32-11-01-960-801 Replacement of the Main Landing Gear Lower Bearing Seal •• AMM 32-11-01-611-801 S ervice the Main Landing Gear Shock Strut (MRB#321100−203) •• AMM 12-10-32-610-802 Servicing of the MLG Shock Strut
32-188
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
32 LANDING GEAR
DASH 8 Q400
•• AMM 12-10-32-610-804 Servicing of the MLG Shock Strut − Aircraft on Jacks •• AMM 32-12-00-220-801 Detailed Inspection of the MLG Doors Mechanism •• AMM 12-10-32-210-801 Extension Check of the NLG Shock Strut •• AMM 32-21-00-210-801 General Visual Inspection of the Nose Landing Gear •• AMM 32-21-01-000-801 Removal of the NLG Shock Strut •• AMM 32-21-01-400-801 Installation of the NLG Shock Strut •• AMM 32-21-01-611-801 S ervice the Nose Landing Gear Shock Strut (MRB #322100−202) •• AMM 12-10-32-610-801 Servicing of the NLG Shock Strut •• AMM 12-10-32-610-803 Servicing of the NLG Shock Strut − Aircraft on Jacks •• AMM 32-22-11-830-801 Rigging of the NLG Forward Doors •• AMM 32-25-06-710-801 O perational Test of the Nose−Gear Ground−Lock Position Indication System (Modsum 4−429586) •• AMM 32-31-00-867-801 Retract and Extend the Landing Gear •• AMM 32-31-00-867-802 Retract and Extend the Nose Landing Gear •• AMM 32-31-00-870-801 Bleed the Landing Gear Primary Extension and Retraction System •• AMM 29-21-06-830-801 Rigging of the Emergency Release Selector Valve •• AMM 29-21-00-611-801 S ervicing of the Landing Gear Alternate Extension Hydraulic Reservoir (MRB #292000−201) •• AMM 12-10-29-611-803 S ervicing of the Alternate Landing−Gear Extension Hydraulic Reservoir •• AMM 32-34-00-710-801 Operational Test of the Alternate Extension System •• AMM 12-10-32-910-801 Tire Pressure Standard Practices •• AMM 12-10-32-614-803 Filling of the Tires with Nitrogen •• AMM 32-40-00-210-802 G eneral Visual Inspection of the Nose and Main Landing Gear Wheel and Tire Assemblies (MRB #324000−201) •• AMM 32-41-01-000-801 Removal of the Main Wheel and Tire Assembly •• AMM 32-41-01-400-801 Installation of the Main Wheel and Tire Assembly •• AMM 32-41-06-000-801 Removal of the Nose Wheel and Tire Assembly •• AMM 32-41-06-400-801 Installation of the Nose Wheel and Tire Assembly •• AMM 32-40-00-720-801 F unctional Check of the Nose and Main Landing Gear Tire Pressure (MRB #324000−202) •• AMM 32-40-00-210-803 G eneral Visual Inspection of the Brake Wear Pins (MRB #324000−206) •• AMM 32-42-01-000-801 Removal of the Main Wheel Brake Units •• AMM 32-42-01-400-801 Installation of the Main Wheel Brake Units
Revision 0.4
FOR TRAINING PURPOSES ONLY
32-189
32 LANDING GEAR
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• AMM 32-42-00-870-801 Bleed the Brakes with Main Brake System •• AMM 12-10-32-863-801 Pressurization of the Parking Brake System with the Hand Pump •• AMM 32-40-00-720-802 F unctional Check of the Brake Accumulator Pre−charge Pressure (MRB #324000−208) •• AMM 12-10-32-210-803 Pressure Check of the Parking Brake Accumulator •• AMM 12-10-32-614-801 Servicing of the Parking Brake Accumulator with Nitrogen •• AMM 32-46-00-720-801 Functional Test of the Anti−Skid Control System (Built−in Test) •• AMM 32-51-26-000-801 Removal of the Power Steering Unit •• AMM 32-51-26-400-801 Installation of the Power Steering Unit •• AMM 32-51-00-710-801 Operational Test of the Nose Wheel Steering System •• AMM 32-51-00-720-801 Functional Test of the Nosewheel Steering System •• AMM 32-51-01-742-801 R etrieval of Data from the Nosewheel−Steering Electronic Control−Unit (SCU) •• AMM 32-51-01-743-801 E rase the Data from the Nosewheel−Steering Electronic Control− Unit (SCU) •• AMM 32-61-06-390-801 Application of Sealant to the Landing−Gear Proximity Sensors •• AMM 32-61-01-000-801 Removal of the Proximity Sensor Electronic−Unit •• AMM 32-61-01-400-801 Installation of the Proximity Sensor Electronic−Unit •• AMM 32-61-06-000-802 Removal of the Proximity Sensors •• AMM 32-61-06-400-802 Installation of the Proximity Sensors •• AMM 32-61-00-710-801 O perational Check of the Proximity Sensor Electronic Unit (PSEU) BITE Panel (MRB# 326100−201) •• AMM 32-61-00-742-801 R etrieval of Data from the Proximity Sensor Electronic Unit (PSEU) •• AMM 32-61-00-743-801 Erase the Data from the Proximity Sensor Electronic Unit (PSEU)
32-190
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CHAPTER 27 FLIGHT CONTROLS CONTENTS Page
27-00-00 FLIGHT CONTROLS.................................................................................. 27-1 Introduction......................................................................................................... 27-1 General................................................................................................................ 27-3 27-12-00 AILERON SYSTEM.................................................................................... 27-4 General................................................................................................................ 27-4 System Description.............................................................................................. 27-5 Component Description........................................................................................ 27-6 Aileron Forward Quadrant............................................................................. 27-6 Rigging of Aileron Quadrant Microswitch............................................................ 27-7 Control Column to Control Column Rigging & Control Column to Aileron Quadrant................................................................ 27-7 Aileron Quadrant to Splitter Quadrant.................................................................. 27-9 Aileron Terminal Quadrant................................................................................. 27-11 Aileron Splitter Quadrant to Aileron Terminal Quadrant Rigging....................... 27-11 Aileron Geared Tab..................................................................................... 27-13 Rigging of the Aileron Geared Tab..................................................................... 27-13 Aileron Position LVDT................................................................................ 27-15 Operation.................................................................................................... 27-15 Lubrication of Aileron and Roll Spoiler Control Column Chains....................... 27-15 Aileron LVDT Fail Fault Isolation...................................................................... 27-15
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-i
27 FLIGHT CONTROLS
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
27-13-00 AILERONS TRIM AND CENTERING...................................................... 27-16 General.............................................................................................................. 27-16 Component Description...................................................................................... 27-17 27 FLIGHT CONTROLS
Trim Actuator.............................................................................................. 27-17 Ground Adjustable Trim Tab........................................................................ 27-18 Operation........................................................................................................... 27-19 Normal Operation....................................................................................... 27-19 Abnormal Operation.................................................................................... 27-19 Operational Test of the Aileron Control System.................................................. 27-19 Operational Test of the Aileron Trim System...................................................... 27-19 27-14-00 AILERON SURFACES............................................................................... 27-23 Introduction....................................................................................................... 27-23 General.............................................................................................................. 27-23 Aileron Terminal Quadrant to Aileron Surface Rigging...................................... 27-23 Rigging of the Aileron Control System Stops..................................................... 27-23 Component Description...................................................................................... 27-25 Aileron Control Surfaces............................................................................. 27-25 27-70-00 AILERON GUST LOCK SYSTEM............................................................ 27-27 Introduction....................................................................................................... 27-27 General.............................................................................................................. 27-27 System Description............................................................................................ 27-27 Operational Test of the Aileron Gust Lock System............................................. 27-27 27-61-00 ROLL SPOILERS SYSTEM...................................................................... 27-29
27-ii
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Introduction....................................................................................................... 27-29 General.............................................................................................................. 27-29
Component Description...................................................................................... 27-33 Spoiler Quadrant......................................................................................... 27-33 Spoiler Splitter Quadrant............................................................................. 27-35 Clutch Units................................................................................................ 27-37 Power Control Units (Inboard/Outboard)..................................................... 27-39 Unload Valves............................................................................................. 27-42 Linear Variable Differential Transformer (LVDT)........................................ 27-43 Spoiler Cables Sensor................................................................................. 27-45 Controls and Indications.............................................................................. 27-46 Operation........................................................................................................... 27-51 Roll Spoiler Hydraulics............................................................................... 27-51 Hydraulic Failure........................................................................................ 27-51 Operational Test of the Roll Spoiler System....................................................... 27-51 Flight Mode................................................................................................ 27-53 Roll Spoiler Jam.......................................................................................... 27-53 Operational Test of the Spoiler Jam Detect System................................................................................. 27-57 Operational Check of the Roll Spoiler SPLR 1 & SPLR 2 Push Off Switchlights.......................................................... 27-59 Complete Roll Jam Using Roll Disconnect System..................................... 27-59 Operational Check of the Roll Spoiler Cable Sensor Assembly.......................... 27-61
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-iii
27 FLIGHT CONTROLS
System Description............................................................................................ 27-31
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Roll Spoiler Cable Break (Operating Cable Sensor System)........................ 27-63 27-62-00 SPOILER SYSTEM IN GROUND MODE.................................................. 27-65 Introduction....................................................................................................... 27-65 27 FLIGHT CONTROLS
General.............................................................................................................. 27-65 System Description..................................................................................... 27-69 Component Description...................................................................................... 27-72 Lift Dump Valves........................................................................................ 27-72 Controls and Indications.................................................................................... 27-73 Operational Test of the Ground Spoiler System.................................................. 27-75 27-63-00 SPOILER PANELS.................................................................................... 27-76 27-16-00 ROLL DISCONNECT SYSTEM................................................................ 27-77 Introduction....................................................................................................... 27-77 General.............................................................................................................. 27-77 Component Description...................................................................................... 27-78 Roll Disconnect Handle............................................................................... 27-78 Roll Disconnect Clutch Mechanism............................................................ 27-80 Interfaces.................................................................................................... 27-81 Rigging of the Roll Disconnect System.............................................................. 27-83 Operational Check of the Roll Disconnect Mechanism....................................... 27-83 27-21-00 RUDDER SYSTEM................................................................................... 27-85 Introduction....................................................................................................... 27-85 General.............................................................................................................. 27-85 System Description............................................................................................ 27-87
27-iv
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Component Description...................................................................................... 27-89 Rudder Pedals............................................................................................. 27-89
Adjustment of the Rudder Pedal Position Sensor................................................ 27-91 Rudder Mixer Quadrant............................................................................... 27-92 Rudder Aft Quadrant................................................................................... 27-95 Rig Rudder Pedals to Rudder Forward Quadrant & Rig forward Quadrant to Rudder Mixer Quadrant........................................... 27-95 Rigging of Rudder Mixer Quadrant to the Rudder Aft Quadrant......................... 27-95 Power Control Units.................................................................................... 27-97 Rudder Hinge Moment Limiting (HML)..................................................... 27-97 Rudder Shut-off Valves.............................................................................27-100 PCU Input Bungee....................................................................................27-103 Rigging of the Upper Spring Strut Motion Detector & Rigging of the Lower Spring Strut Motion Detector........................................27-103 Rudder Position LVDT..............................................................................27-104 A rudder position LVDT is located in the vertical stabilizer......................27-104 Controls and Indications............................................................................27-105 Rigging of Rudder PCUs with Hydraulic Power...............................................27-107 Operational Test of the Rudder Shutoff Valves.................................................27-108 Operation.........................................................................................................27-111 Normal System Operation.........................................................................27-111 Operational Test of the Rudder Control System................................................27-113 Abnormal Operation..................................................................................27-115
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-v
27 FLIGHT CONTROLS
Rudder Forward Quadrants.......................................................................... 27-91
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Lower Rudder PCU Jam Operation............................................................27-117 27-22-00 RUDDER FEEL AND SUMMING...........................................................27-119 Introduction.....................................................................................................27-119 27 FLIGHT CONTROLS
General............................................................................................................27-119 Component Description....................................................................................27-122 Trim Actuator............................................................................................27-122 Operational Test of the Rudder Trim System....................................................27-122 Summing-Yaw Damper Actuator...............................................................27-124 Rudder trim operation......................................................................................27-127 Rudder Trimming .....................................................................................27-127 27-23-00 RUDDER SURFACES.............................................................................27-128 General............................................................................................................27-128 System Description..........................................................................................27-128 27-31-00 ELEVATOR SYSTEM..............................................................................27-129 Introduction.....................................................................................................27-129 General............................................................................................................27-129 System Description..........................................................................................27-131 Component description.....................................................................................27-133 Control Columns.......................................................................................27-133 Handwheels...............................................................................................27-133 Left Forward Quadrant..............................................................................27-135 Aft Quadrants............................................................................................27-136 Elevator-Power Control Units (PCU).........................................................27-137
27-vi
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Component Description....................................................................................27-139 Elevator PCU............................................................................................27-139
Torque Tubes.............................................................................................27-141 Centering Device.......................................................................................27-141 Overload Bungees.....................................................................................27-142 Overload Bungees (PCU INPUT)..............................................................27-143 Elevator Position LVDT.............................................................................27-143 Controls and Indications............................................................................27-145 Asymmetry Check of the Elevators..................................................................27-145 Operational Test of the Elevator Control System..............................................27-147 Elevator Droop Rate Check..............................................................................27-147 27-32-00 ELEVATOR FEEL AND TRIM................................................................27-151 Introduction.....................................................................................................27-151 General............................................................................................................27-151 System Description..........................................................................................27-152 Operational Test of the Pitch Feel System........................................................27-153 Dual Pitch Trim Actuator..........................................................................27-155 Pitch Feel Actuators..................................................................................27-155 Controls and Indications..................................................................................27-156 Elevator Trim Indicator.............................................................................27-156 Pitch Trim Split Switch.............................................................................27-157 Elevator Trim Shutoff Switchlights...........................................................27-158
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-vii
27 FLIGHT CONTROLS
Compensator.............................................................................................27-140
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Caution Lights..........................................................................................27-159 Operation.........................................................................................................27-161 Pitch Trim.................................................................................................27-161 27 FLIGHT CONTROLS
Manual Trim..............................................................................................27-161 Abnormal Operation Pitch Trim Runaway.................................................27-163 Autopilot Trim..........................................................................................27-165 Flap Compensation Trim...........................................................................27-165 Operational Test of the Elevator Control System..............................................27-165 27-33-00 STALL WARNING /STICK PUSHER........................................................27-167 Introduction.....................................................................................................27-167 General............................................................................................................27-167 System Description..........................................................................................27-167 Operational test of the Stall Protection Module................................................27-169 Component Description....................................................................................27-170 Stall Protection Modules...........................................................................27-170 Stick Pusher Actuator................................................................................27-171 Stick Pusher Capstan.................................................................................27-173 Stick Pusher Quadrant...............................................................................27-174 Stick Shaker..............................................................................................27-175 Angle of Attack Transducer (AOA)...........................................................27-176 Stick Pusher Shutoff Annunciator Switch..................................................27-177 Stall Warn Test Switch..............................................................................27-177 Inputs........................................................................................................27-179
27-viii
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Outputs.....................................................................................................27-181 Controls and Indications..................................................................................27-185
27-34-00 ELEVATOR SURFACES..........................................................................27-189 Introduction.....................................................................................................27-189 General............................................................................................................27-189 27-38-00 PITCH DISCONNECT SYSTEM.............................................................27-191 Introduction.....................................................................................................27-191 General............................................................................................................27-191 Pitch Disconnect Handle...........................................................................27-191 Pitch Disconnect Clutch Mechanism.........................................................27-191 Operational Check of the Elevator Control Pitch Disconnect Mechanism ........27-192 27-51-00 FLAP CONTROL SYSTEM....................................................................27-195 Introduction.....................................................................................................27-195 General............................................................................................................27-195 Component Description....................................................................................27-197 Flap Control Unit (FCU)...........................................................................27-197 Flap Selector Lever/Quadrant....................................................................27-201 Flap Lever Transducer...............................................................................27-201 Operational Test of the Flap Control Module....................................................27-201 Operation.........................................................................................................27-203 Normal Flap Operation..............................................................................27-203 Wing Flap System Electrical Checks................................................................27-203
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-ix
27 FLIGHT CONTROLS
Tests..........................................................................................................27-188
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Operational Test of the Wing Flaps...................................................................27-204 27-52-00 FLAP DRIVE SYSTEM...........................................................................27-206 Introduction.....................................................................................................27-206 27 FLIGHT CONTROLS
General............................................................................................................27-206 System Description..........................................................................................27-207 Component Description....................................................................................27-209 Flap Power Unit (FPU)..............................................................................27-209 Transmission Shafts..................................................................................27-210 Torsion Bars..............................................................................................27-211 Lubrication of Flap Ball Screw Actuators.........................................................27-212 Flap Tracks................................................................................................27-213 27-53-00 FLAP POSITION INDICATION..............................................................27-217 Introduction.....................................................................................................27-217 General............................................................................................................27-217 System Description..........................................................................................27-218 Component Description....................................................................................27-219 Flap Position Indication Unit (FPIU).........................................................27-219 Flap Position Transducer...........................................................................27-220 Controls and Indications..................................................................................27-221 Operation.........................................................................................................27-223 Normal Flap Position Indication Operation...............................................27-223 27-54-00 FLAP SURFACES....................................................................................27-224
27-x
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Erase the Data from the Central Diagnostic System (CDS) - Flaps System (FLAPS)...........................................................27-225 General.....................................................................................................27-225
Erase the Data from the Central Diagnostic System (CDS) Flight Control System (FCS).....................................................27-226 General.....................................................................................................27-226 Procedure..................................................................................................27-226 Retrieval of Data from the Central Diagnostic System (CDS) Flaps System (FLAPS)..............................................................27-227 General.....................................................................................................27-227 Procedure..................................................................................................27-227 Retrieval of Data from the Central Diagnostic System (CDS) Flight Control System (FCS).....................................................27-229 General............................................................................................................27-229 Procedure.........................................................................................................27-229 27-00-01 FLIGHT CONTROL ELECTRONIC CONTROL UNIT............................. 27-23 Introduction.....................................................................................................27-233 General............................................................................................................27-233 System Description..........................................................................................27-233 Aileron Control System.............................................................................27-235 Rudder Control System.............................................................................27-235 Elevator Control System............................................................................27-237 Flap Control System..................................................................................27-239 Spoiler Control System.............................................................................27-239
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-xi
27 FLIGHT CONTROLS
Procedure..................................................................................................27-225
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Page
Controls and Indications..................................................................................27-241 Caution Lights..........................................................................................27-241 Advisory Lights........................................................................................27-245 27 FLIGHT CONTROLS
Operational Test of the FCECU........................................................................27-245 Maintenance Consideration..............................................................................27-246 System Test...............................................................................................27-246 Interfaces..................................................................................................27-246 27-00-45 CENTRAL DATA STORAGE FLIGHT CONTROLS..............................27-247 Introduction.....................................................................................................27-247 General............................................................................................................27-247 Controls and Indications..................................................................................27-248 27-00-00 SPECIAL TOOL & TEST EQUIPMENT..................................................27-249 27-00-00 MAINTENANCE PRACTICES................................................................27-252
27-xii
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
ILLUSTRATIONS 27-1
Flight Control System................................................................................27-2
27-2
Aileron Control System.............................................................................27-4
27-3
Aileron Control System Synoptic...............................................................27-5
27-4
Aileron Forward Quadrant.........................................................................27-6
27-5
Aileron Splitter Quadrant...........................................................................27-8
27-6
Aileron Terminal Quadrant......................................................................27-10
27-7
Aileron Geared Tab .................................................................................27-12
27-8
Aileron Position LVDT............................................................................27-14
27-9
Aileron Position LVDT ...........................................................................27-14
27-10
Aileron Trim and Centering Unit.............................................................27-16
27-11
Aileron Trim Actuator..............................................................................27-17
27-13
Ground Adjustable Trim Tab....................................................................27-18
27-12
Ground Adjustable Trim Tab ...................................................................27-18
27-14
Aileron Trim Schematic...........................................................................27-20
27-15
Aileron Terminal Quadrant to Aileron Surface Rigging...........................27-22
27-16
Ailerons Control Surfaces........................................................................27-24
27-17
Aileron Gust Lock System.......................................................................27-26
27-18
Spoiler Control System............................................................................27-28
27-19
Spoiler Control System Synoptic.............................................................27-30
27-20
Spoiler Quadrant......................................................................................27-32
27-21
Spoiler Splitter Quadrant.........................................................................27-34
27-22
Spoiler Clutch Units................................................................................27-36
FOR TRAINING PURPOSES ONLY
27-xiii
27 FLIGHT CONTROLS
Figure Title Page
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page
27 FLIGHT CONTROLS
27-23
Spoiler Power Control Unit......................................................................27-38
27-24
Spoiler Power Control Hydraulic Unit.....................................................27-40
27-25
Spoiler Unload Valve...............................................................................27-42
27-26
Spoiler LVDT..........................................................................................27-43
27-27
Spoiler Cables Sensor..............................................................................27-44
27-28
Powered Flight Control Surface Indicator................................................27-46
27-29
Powered Flight Surface Shutoffs..............................................................27-47
27-30
Spoiler Switchlights.................................................................................27-48
27-31
Roll Spoiler Caution Lights.....................................................................27-48
27-32
Inboard Spoiler Hydraulic Schematic......................................................27-50
27-33
Spoiler Panel Indications - Spoiler System Schematic.............................27-52
27-34
Roll Spoilers Operation > 170 KIAS.......................................................27-54
27-35
Left Wing Inboard Spoiler Jam Indicated.................................................27-55
27-36
Left Wing Spoiler Jam Recovery Switchlight Pushed No.1 Unload Valve Energized to Unload......................................27-56
27-37
Roll Spoiler Fuselage Cable Jam Indicated-Roll Disconnect System Activated-50 Degree Travel Switch Closed..................................27-58
27-38 Roll Spoiler Fuselage Cable Jammed-Roll Disconnect Activated 50° Travel Switch Closed-Both Switchlights Pushed-Both Unload Valves Energized to Unload....................................27-60 27-39
Roll Spoiler Cable Sensor Operation.......................................................27-62
27-40
Ground Spoiler System Block Diagram...................................................27-64
27-41
Flight/Taxi Switch...................................................................................27-66
27-42
Roll Spoiler Ground Spoiler Mode Synoptic............................................27-68
27-43
Roll Spoiler in Ground Mode Schematic..................................................27-70
27-xiv
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-44
Spoiler Lift Dump Valve..........................................................................27-72
27-45
Spoiler Surface Indication.......................................................................27-73
27-46
Roll Spoiler in Ground Mode Caution Lights..........................................27-74
27-47
Inboard and Outboard Spoiler Panels.......................................................27-76
27-48
Roll Disconnect System...........................................................................27-77
27-49
Roll Disconnect Handle...........................................................................27-78
27-50
Roll Disconnect Lever Assembly.............................................................27-79
27-51
Roll Disconnect Clutch Mechanism.........................................................27-80
27-52
Aileron Forward Quadrant Microswitch (50°)..........................................27-81
27-53
Spoiler Pushoff Switchlights....................................................................27-82
27-54
Rudder Control System............................................................................27-84
27-55
Rudder Control System Synoptic.............................................................27-86
27-56
Rudder Pedals..........................................................................................27-88
27-57
Co-pilot’s Rudder Forward Quadrant........................................................27-90
27-58 Download Unit - Hand Held Onsite FDR_Series 400...............................27-91 27-59
Rudder Mixer Quadrant...........................................................................27-92
27-60
Rudder Aft Quadrant................................................................................27-94
27-61
Rudder Power Control Unit......................................................................27-96
27-62
Rudder PCU Schematic...........................................................................27-98
27-63 Rudder PCU Fluid Compensator..............................................................27-99 27-64
Rudder Shut-off Valve.......................................................................... 27-100
27-65
Rudder PCU Input Bungee.................................................................... 27-102
27-66
Rudder Position LVDT.......................................................................... 27-104
FOR TRAINING PURPOSES ONLY
27-xv
27 FLIGHT CONTROLS
Figure Title Page
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page
27 FLIGHT CONTROLS
27-67
Rudder Position on MFD...................................................................... 27-105
27-68
Rudder Push Off Switchlights............................................................... 27-106
27-69
FCECU Rudder Inputs and Outputs...................................................... 27-110
27-70
Rudder Control System - Electrical Schematic..................................... 27-112
27-71
Lower Rudder Control Jam Indicated.................................................... 27-114
27-72
Rudder 1 PUSH OFF Switch Pushed.................................................... 27-116
27-73
RUD CTRL Caution Light.................................................................... 27-118
27-74
Rudder Feel and Summing System Block Diagram............................... 27-119
27-75
Rudder Control System Synoptic.......................................................... 27-120
27-76
Rudder Trim Switch and Indicator........................................................ 27-121
27-77
Rudder Trim Actuator........................................................................... 27-122
27-78
Rudder Feel and Summing Unit............................................................ 27-123
27-79
Yaw Damper......................................................................................... 27-124
27-80
Rudder Trim Switch/Indicator Schematic.............................................. 27-126
27-81
Rudder Empennage............................................................................... 27-128
27-82
Elevator Control System....................................................................... 27-129
27-83
Elevator Control System Synoptic........................................................ 27-130
27-84
Elevator Control Column...................................................................... 27-132
27-85
Elevator Right Forward Quadrant.......................................................... 27-134
27-86
Elevator Left Forward Quadrant............................................................ 27-135
27-87
Elevator Aft Quadrants......................................................................... 27-136
27-88
Elevator Power Control Unit................................................................. 27-137
27-89
Elevator PCU Schematic....................................................................... 27-138
27-xvi
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-90
Compensator......................................................................................... 27-140
27-91
Centering Device.................................................................................. 27-141
27-92
Overload Bungee.................................................................................. 27-142
27-93
Elevator Position LVDT and PCU Input Bungee................................... 27-143
27-94
Elevator Position on MFD..................................................................... 27-144
27-95
Pitch Feel and Trim............................................................................... 27-146
27-96
Elevator Position Feedback................................................................... 27-148
27-97
Elevator Caution Lights........................................................................ 27-149
27-98 Pitch Feel and Trim Block Diagram..................................................... 27-150 27-99
Elevator Feel Caution Light.................................................................. 27-152
27-100
Pitch Feel and Trim Units..................................................................... 27-153
27-101
Dual Pitch Trim and Pitch Feel Actuators............................................. 27-154
27-102
Elevator Trim Indicator......................................................................... 27-156
27-103
Pitch Trim Switch................................................................................. 27-157
27-104
Elevator Trim Shutoff Switchlights....................................................... 27-158
27-105
Elevator Caution Lights........................................................................ 27-159
27-106
Elevator Feel and Trim System - Electrical Schematic.......................... 27-160
27-107
Elevator Trim Runaway or Manual Trim > 3 secs.................................. 27-162
27-108
Trim Push/Off Switch Pushed-Pitch Trim Caution Light ON................ 27-164
27-109
SPS Block Diagram.............................................................................. 27-166
27-110
Stall Protection Modules Locator.......................................................... 27-170
27-111
Stick Pusher Actuator Locator.............................................................. 27-171
27-112
Stick Pusher Capstan Locator............................................................... 27-172
FOR TRAINING PURPOSES ONLY
27-xvii
27 FLIGHT CONTROLS
Figure Title Page
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page
27 FLIGHT CONTROLS
27-113
Stick Pusher Quadrant Locator............................................................. 27-174
27-114
Stick Shaker Locator............................................................................ 27-175
27-115
Angle Of Attack Transducer Locator..................................................... 27-176
27-116
SPS Stick Pusher Shutoff Annunciator Switch Locator......................... 27-177
27-117
SPM Inputs........................................................................................... 27-178
27-118
SPM Outputs........................................................................................ 27-180
27-119
Stick Pusher Shutoff Switchlights......................................................... 27-182
27-120
SPM Caution Light Indications............................................................. 27-184
27-121
PFD Low Speed Cue Indications.......................................................... 27-186
27-122
PFD Low Speed Cue Malfunction Indications...................................... 27-187
27-123
Stall Warn Test Toggle Switch............................................................... 27-188
27-124
Elevator Surface................................................................................... 27-189
27-125
Pitch Disconnect Clutch Mechanism Component Location Index......... 27-190
27-126
Wing Flap System................................................................................. 27-194
27-127
Flap Control Unit (FCU)....................................................................... 27-196
27-128
Flap Control Unit Block Diagram......................................................... 27-198
27-129
Flap System Caution Panel................................................................... 27-199
27-130
Flap Selector Quadrant......................................................................... 27-200
27-131
Flap Control System - Electrical Schematic.......................................... 27-202
27-132
Flap Drive............................................................................................. 27-206
27-133
Flap Drive System................................................................................ 27-207
27-134
Flap Power Unit.................................................................................... 27-208
27-135
Flap Power Unit Schematic................................................................... 27-209
27-xviii
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-136
Flap Transmission Shafts...................................................................... 27-210
27-137
Flap Torsion Bars.................................................................................. 27-211
27-138
Flap Tracks........................................................................................... 27-213
27-139
No.3 and 4 Flap Rollers........................................................................ 27-214
27-140
Flap Carriage........................................................................................ 27-215
27-141
Wing Flap System................................................................................. 27-216
27-142
Flap Position Indication Unit................................................................ 27-218
27-143
Flap Position Indication Unit Block Diagram...................................... 27-219
27-144
Flap Position Transducer....................................................................... 27-220
27-145
Flap Position Indication/Multi-Function Display.................................. 27-221
27-146
Flap Position Indication - Electrical Schematic..................................... 27-222
27-147
Flaps..................................................................................................... 27-224
27-148
Task 45-00-27-743-802 CDS System Pages Indications........................ 27-225
27-149
Task 45-00-27-743-801 CDS System Pages Indications........................ 27-226
27-150
Task 45-00-27-742-802 CDS System Pages Indications (1 of 2)........... 27-227
27-151
Task 45-00-27-742-802 CDS System Pages Indications (2 of 2)........... 27-228
27-152
Task 45-00-27-742-801 CDS System Pages Indications (1 of 2)........... 27-229
27-153
Task 45-00-27-742-801 CDS System Pages Indications (2 of 2)........... 27-230
27-154
Flight Control Electronic Control Unit................................................. 27-232
27-155
FCECU/Left Channel Block Diagram................................................... 27-234
27-156
FCECU/Right Channel Block Diagram................................................. 27-236
27-157
FCECU Block Diagram........................................................................ 27-238
27-158
Caution and Warning Panel................................................................... 27-240
FOR TRAINING PURPOSES ONLY
27-xix
27 FLIGHT CONTROLS
Figure Title Page
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Figure Title Page
27 FLIGHT CONTROLS
27-159
Caution and Warning Panel................................................................... 27-242
27-160
Roll Spoiler Advisory Lights................................................................ 27-244
27-161
CDS Interface....................................................................................... 27-247
27-162
CDS Ground Maintenance Toggle Switch Selection.............................. 27-248
27-xx
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
CHAPTER 27 FLIGHT CONTROLS
27-00-00 FLIGHT CONTROLS INTRODUCTION The primary flight control surfaces are operated by cables from the left or right control columns and rudder pedals. This allows the aircraft to be flown from either the pilot or co-pilot positions. The position of the rudder, roll spoilers, and elevators are displayed on the Powered Flight Control Surfaces Indicator (PFCSI). The PFCSI display is on the pilot’s Multi Functional Display. The inputs to the display are provided by the Integrated Flight Cabinet, which receives information on surface position from the Flight Control Electronic Control Unit (FCECU).
FOR TRAINING PURPOSES ONLY
27-1
27 FLIGHT CONTROLS
27-2
Elevator
Aileron Geared Tab Ground Adjustable Tab
Rudder
Outboard Flaps
Outboard Flaps Spoilers Geared Tab Aileron
Flight Control Electronic Unit
fs238a01.cgm
Figure 27-1. Flight Control System
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
Inboard Flaps
DASH 8 Q400
Spoilers
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
GENERAL
WARNING
The spoilers assist the ailerons in providing roll control, and reduce lift after the aircraft touches down. PFCS positions are shown in the Permanent Systems Area (PSA) of Multi-Function Display 1 (MFD1). These PFCS positions are transmitted to the PSA from the control surfaces, through the Integrated Flight Cabinet (IFC). Trim indicators show trim position of the flight controls. Advisory lights indicate system operation, and caution lights indicate flight control malfunctions. Refer to Figure 27-1. Flight Control System. The Flight Control System has the following subsystems: •• FCECU (27-00-01) •• Aileron Control System (27-10-00) •• Rudder Control System (27-20-00)
INSTALL SAFETY DEVICES, WARNING SIGNS AND PLACARDS BEFORE YOU START A PROCEDURE ON, OR AROUND, FLIGHT CONTROLS OR FLIGHT CONTROL SURFACES.
27 FLIGHT CONTROLS
All flight controls may be operated from either the pilot’s or co-pilot’s seat. The rudders provide yaw control, the ailerons and spoilers roll control, and elevators pitch control (Figure 27-1). The rudders, spoilers and elevators are hydraulically powered, and identified as the Powered Flight Control Surfaces (PFCS) on the MFD PSA area. A gust lock system is provided for the aileron controls, to protect the ailerons in strong wind.
MAKE SURE THERE ARE NO PERSONNEL ON OR NEAR THE FLIGHT CONTROLS OR THE SURFACES. ACCIDENTAL MOVEMENT OF THE CONTROLS CAN CAUSE INJURIES TO PERSONNEL AND DAMAGE TO THE EQUIPMENT. THE ABOVE WARNINGS MUST BE OBSERVED DURING ALL FLIGHT CONTROL TASKS. ON AIRCRAFT WITH MODSUM 4Q126279 INSTALLED, ALL PUSH RODS FROM FLIGHT CONTROL INPUTS TO FORWARD QUADRANTS ARE EQUIPPED WITH FORCE SENSORS THAT SEND INFORMATION TO THE FLIGHT DATA RECORDER.
•• Elevator Control System (27-30-00) •• Wing Flaps (27-50-00) •• Spoilers Control System (27-60-00) •• Gust Lock Systems (27-70-00).
FOR TRAINING PURPOSES ONLY
27-3
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-12-00 AILERON SYSTEM
The aileron system is comprised of the following: •• Aileron forward quadrant
GENERAL
•• Aileron splitter quadrant
Refer to Figure 27-2. Aileron Control System. 27 FLIGHT CONTROLS
Movement of the control handwheels causes the aileron surfaces to deflect asymmetrically and in proportion to control handwheel rotation. The aileron system also receives inputs from the Auto Flight Control System and the Aileron Trim and Centering Unit.
•• Aileron terminal quadrant •• Aileron geared tab •• Aileron position LVDT
5
4 6 3 8
2 7
5
1
LEGEND 1. Aileron Forward Quadrant. 2. Aileron Splitter Quadrant. 3. Aileron Terminal Quadrant. 4. Aileron LVDT. 5. Aileron. 6. Aileron Gust Lock Mechanism. 7. Fuselage Cable Turnbuckles. 8. Wing Cable Turnbuckles. fs001a01.cgm
Figure 27-2. Aileron Control System
27-4
FOR TRAINING PURPOSES ONLY
3
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION Refer to Figure 27-3. Aileron Control System Synoptic. The aileron control cables are routed aft from the forward aileron quadrant, up the forward face of the flight compartment bulkhead and aft along the cabin roof. The cables terminate at the aileron splitter quadrant on the aft face of the wing rear spar.
Each aileron control wing cable terminates at an aileron terminal quadrant. Aileron terminal quadrant movement is transmitted to the aileron by a push-rod. Geared tabs are installed on each aileron, and a ground adjustable tab on right hand aileron. 27 FLIGHT CONTROLS
DASH 8 Q400
The aileron control wing cables are routed outboard from the aileron splitter quadrant, with one cable loop along each wing.
ROLL DISCONNECT HANDLE
ROLL DISCONNECT
TO SPOILER CONTROLS
TRIM ACTUATOR
AILERON FORWARD QUADRANT
SPRING TORSION BAR
AILERON TERMINAL QUADRANT
AILERON SPLITTER QUADRANT LEFT AILERON
DN
GEARED TAB
AUTOPILOT SERVO
AILERON TERMINAL QUADRANT
LVDT
GUST LOCK
RIGHT AILERON
GROUND ADJUSTABLE TAB
UP
GEARED TAB
fs179a01.cgm
Figure 27-3. Aileron Control System Synoptic
FOR TRAINING PURPOSES ONLY
27-5
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
The aileron forward quadrant receives inputs from:
Aileron Forward Quadrant
•• Co-pilot control handwheel
Refer to Figure 27-4. Aileron Forward Quadrant.
•• The autopilot
27 FLIGHT CONTROLS
The aileron forward quadrant is installed in the right side of the lower forward fuselage, below the flight compartment floor. The quadrant has two pulleys with secondary travel stops and a lever assembly all installed on a single shaft.
•• The aileron trim • And centering unit. The quadrant outputs the sum of these inputs through the cable system.
A push-rod connects the lever at the base of the co-pilot’s control column to the lever on the aileron forward quadrant. The forward quadrant also contains a 50° travel switch.
LEGEND 1. Aileron Input to Splitter Quadrant. 2. Aileron Autopilot Servo. 3. Cables. 4. Aileron Forward Quadrant. 5. Secondary Stops. 6. Rig Pin. 4
A 3 2
D
FW
1
5
6
A ft003a01.cgm
Figure 27-4. Aileron Forward Quadrant
27-6
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
RIGGING OF AILERON QUADRANT MICROSWITCH The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Pull the ROLL DISC handle •• Control wheel to neutral •• Make sure rigging pin can be installed and removed from the aileron quadrant freely •• Use inclinometer and rotate control wheel so that quadrant rotates 31.5° from neutral position •• Adjust the microswitch plunger to contact the cam at this position
CONTROL COLUMN TO CONTROL COLUMN RIGGING & CONTROL COLUMN TO AILERON QUADRANT The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Install rigging pins in spoiler, aileron and elevator quadrants •• Disconnect the roll interconnect push rods on the pilot and co-pilot sides •• Remove the aileron push rod from the push rod lever •• Align the handwheels horizontally
•• Rotate control wheel in the opposite direction to 31.5°
•• Adjust the interconnect pushrods as necessary and re-connect
•• Adjust microswitch plunger to contact the cam
•• Adjust the aileron pushrod as necessary and re-connect
•• Release the ROLL DISC handle
•• Remove all rigging pins
• Ensure control wheels move together.
•• Pressurize No.1 and No.2 hydraulic systems •• Do an Operational Test of the Aileron Control system •• Do an Operational Test of the Spoiler Control System and of the Spoilers.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-7
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
LEGEND
27 FLIGHT CONTROLS
1. LH Aileron Control Cables. 2. Aileron Splitter Quadrant. 3. RH Aileron Control Cables. 4. Quadrant Input Cables. 5. Gust Lock Plate. 6. Rig Pin Hole. 7. Gust Lock. 8. Gust Lock Control Cable. 9. Wing Rear Spar. 10. Gust Lock Release Springs.
3
2
A
4
1 10
FW
D
9
8
7
ft164a01.cgm
Figure 27-5. Aileron Splitter Quadrant
27-8
FOR TRAINING PURPOSES ONLY
6
5
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Aileron Splitter Quadrant
NOTES
Refer to Figure 27-5. Aileron Splitter Quadrant. The splitter quadrant is installed on the aft face of the wing rear spar. The quadrant has three pulleys installed on a common shaft. 27 FLIGHT CONTROLS
The aileron splitter quadrant transmits aileron cable inputs from the co-pilot’s forward quadrant to the aileron terminal quadrants located in each wing. Gust locking of the ailerons is supplied by an internal spring-loaded lever attached off-center to the bottom of the splitter quadrant. When the gust lock is engaged, a plunger is inserted in the gust lock plate at the base of the splitter quadrant. This locks the ailerons in the neutral position.
AILERON QUADRANT TO SPLITTER QUADRANT The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Pull the ROLL DISC handle and turn through 90° •• Install rigging pins in the aileron forward quadrant and the splitter quadrant •• Engage the gust lock •• Use cable tension meter to measure the tension on each side of the aileron cable •• Adjust the turnbuckles to adjust cable tension as necessary •• Re-check tension after 7 days.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-9
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
A
3
2
4 1
LEGEND 1. Pulley. 2. Cables. 3. Rig Pin. 4. Terminal Quadrant. 5. Rod. 6. Primary Aileron/Roll Spoiler Stops.
6
6
5
A
ft162a01.cgm
Figure 27-6. Aileron Terminal Quadrant
27-10
FOR TRAINING PURPOSES ONLY
FW
D
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
AILERON TERMINAL QUADRANT
NOTES
Refer to Figure 27-6. Aileron Terminal Quadrant. Each aileron terminal quadrant is located on the wing rear spar adjacent to its related aileron. 27 FLIGHT CONTROLS
The quadrant is connected to the aileron by a lever and a control rod. For rigging procedures, a 0.25 in. (6.35 mm) rig pin hole is used to lock the quadrant in neutral. The terminal quadrant transmits aileron cable control from the aileron splitter quadrant to the aileron surface. The quadrant also includes the primary adjustable stops for aileron and roll spoiler movement.
AILERON SPLITTER QUADRANT TO AILERON TERMINAL QUADRANT RIGGING The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Lower the flaps •• Pull the ROLL DISC handle and turn through 90° •• Engage the gust lock •• Install the rigging pins in the aileron splitter quadrant and left and right aileron terminal quadrants •• Check and adjust the cable tension as necessary iaw the AMM.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-11
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
Figure 27-7. Aileron Geared Tab
27-12
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Aileron Geared Tab Refer to Figure 27-7. Aileron Geared Tab. The aileron geared tab is attached by four hinge fittings to the trailing edge of each aileron. The tab is connected to the aileron by a geared linkage so that the geared tab moves 70% of the total aileron movement in the opposite direction. This action gives aerodynamic assistance and reduces the force required to turn the control handwheels. At full aileron deflection of 17°, the aileron geared tab deflects 11.9°. The geared tab linkage is connected to the aileron hinge point to give tab movement, in proportion to aileron movement. Each geared tab has adjustable bolts located on the hinge arm of the tab.
RIGGING OF THE AILERON GEARED TAB The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Install the rigging pins in the terminal quadrants •• Install the aileron rigging tool on the wing and aileron to ensure the ailerons are in neutral •• Install aileron geared tab rigging tool •• Using the rigging board ensure that the geared tab is at neutral (0°).
FOR TRAINING PURPOSES ONLY
27-13
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
A
27 FLIGHT CONTROLS
D
FW
Figure 27-8. Aileron Position LVDT
Figure 27-9. Aileron Position LVDT
27-14
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Aileron Position LVDT
•• Apply the CONTROL LOCK
Refer to:
•• Open control columns access panels
• • Figure 27-8. A ileron Position LVDT. • Figure 27-9. Aileron Position LVDT. The aileron LVDT is fitted to the control input to the right hand aileron. The LVDT supplies an electrical signal equivalent to the angular position of the flight control surface to the FCECU. The FCECU supplies electrical excitation to the LVDT. The FCECU transmits this data to the Flight Data Recorder (FDR) through the Integrated Flight Cabinet (IFC) No.1 on an ARINC 429 Data Bus.
•• Make a cloth moist with approved cleaning solvent •• Clean contamination from the chains with the wiper cloth • Make sure the area is dry
CAUTION DO NOT MIX GREASE FROM DIFFERENT MANUFACTURERS OR DIFFERENT SPECIFICATIONS. •• Apply a thin film of grease to the chains with your hand •• Close the access panels
AILERON LVDT FAIL FAULT ISOLATION
NOTE The aileron, rudder and elevator LVDTs have the same part number and are interchangeable.
Operation Rotary movement of the co-pilot’s control handwheel is transmitted by a sprocket and chain mechanism to a sprocket and lever assembly. This assembly is at the base of the co-pilot’s control column. A push-rod connects the lever to the aileron forward quadrant.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Energize the electrical system •• Do a fault message retrieval in the CDS for flight control system •• Do an operational test of the aileron control system
Connected to the aileron forward quadrant are inputs from the Aileron trim system and an input from the auto-pilot servo.
•• If the AIL LVDT FAIL message comes on go to the Fault Isolation procedure
LUBRICATION OF AILERON AND ROLL SPOILER CONTROL COLUMN CHAINS
•• Disconnect electrical connector P1 from the FCECU
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
•• Disconnect the electrical connector from the LVDT
•• Check continuity of both connectors •• Re-connect the electrical connectors •• Do a fault confirmation •• If fault continues replace LVDT •• If fault continues replace FCECU.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-15
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-13-00 AILERONS TRIM AND CENTERING GENERAL Refer to Figure 27-10. Aileron Trim and Centering Unit. 27 FLIGHT CONTROLS
Aileron trim is achieved by an electrical actuator located in the aileron trim and centering unit. The trim and centering unit is connected to the aileron forward quadrant by a spring torsion bar that makes sure the aileron surfaces always return to a neutral position. The aileron trim and centering system has the following components: •• Trim actuator •• Centering unit (Torsion bar) • Trim-ground adjustable tab.
1
A FW
D D
FW
LEGEND
2
1. Spring Torsion Bar. 2. Aileron Trim Actuator.
ft008a01.cgm
Figure 27-10. Aileron Trim and Centering Unit
27-16
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Trim Actuator Refer to Figure 27-11. Aileron Trim Actuator.
27 FLIGHT CONTROLS
The trim actuator drives the aileron control system to counter the effects of lateral imbalance. The aileron trim actuator is fitted under the left side flight compartment floor. The actuator has the following: •• Electric motor and linear actuator •• Gearbox •• Circuit cards • LVDT.
A
AILERON TRIM AND CENTRING ASSEMBLY
D
FW
B
FW
D
fs011a01.cgm
Figure 27-11. Aileron Trim Actuator
FOR TRAINING PURPOSES ONLY
27-17
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Ground Adjustable Trim Tab Refer to: •• Figure 27-12. G round Adjustable Trim Tab.
27 FLIGHT CONTROLS
•• Figure 27-13. G round Adjustable Trim Tab. The ground adjustable trim tab is located on the trailing edge of the right aileron, inboard of the geared tab. The adjustment is made on a serrated plate, at the tab end of the geared linkage. The ground adjustable trim tab is used to adjust for any aerodynamic asymmetry between ailerons.
Figure 27-12. Ground Adjustable Trim Tab
GROUND ADJUSTABLE TRIM TAB
FW
D
1 FW
D
LEGEND 1. Connecting Link. 2. Link Bracket. 3. Sleeve.
2 3
ft169a01.cgm
Figure 27-13. Ground Adjustable Trim Tab
27-18
FOR TRAINING PURPOSES ONLY
D
TB
OU
MAINTENANCE TRAINING MANUAL
OPERATION Normal Operation Refer to Figure 27-14. Aileron Trim Schematic. The AILERON trim switch is spring-loaded to return to the center-off position. The aileron trim switch has three positions: •• LWD (left wing down)
When the autopilot is engaged, a message MISTRIM (TRIM L WING DN) or (TRIM R WING DN) is shown on the Primary Flight Display if aileron trim is required.
CAUTION Release control lock when testing aileron trim.
OPERATIONAL TEST OF THE AILERON CONTROL SYSTEM
•• RWD (right wing down) • Center-off. Input commands from the aileron trim actuator to the aileron trim and centering system rotates the aileron forward quadrant. An aileron trim indicator shows aileron trim position. The aileron trim indicator receives its information from a LVDT.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Release CONTROL LOCK •• Pull ROLL DISC handle
The LVDT also transmits aileron trim position data to the FDR.
•• Ensure aileron trim is at neutral
Power for the Aileron Trim Linear Actuator is supplied from the 28 VDC Left essential bus through circuit breakers G8 to pin 7 on the actuator. The ground is supplied through pin 6 on connectors P4.
•• Rotate aileron control wheel to full movement each side of neutral
Power for the Aileron Trim Control Panel is supplied from the 28 VDC Left essential bus through circuit breakers H8 to pin C on the trim panel. The ground is supplied through pins D and E.
Abnormal Operation If the AILERON trim switch fails to the closed position, a limit switch on the trim actuator housing opens the electrical circuit and causes the trim actuator to stop at the maximum trim input. If the limit switch fails to stop the trim actuator, a mechanical stop on the trim actuator housing stops the trim actuator at the maximum trim setting.
•• Hold roll spoiler control wheel in neutral
•• Make sure ailerons move freely from stop to stop • • Check that SPLR1 and SPLR2 powered flight control shutoff lights show PUSH OFF when aileron control wheel is > 50° either side of neutral • Release ROLL DISC handle.
OPERATIONAL TEST OF THE AILERON TRIM SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Release the CONTROL LOCK lever to the OFF position •• Make sure the aileron control surfaces are in the neutral position
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-19
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-20 (G8) AIL TRIM ACT
5A
7 6
+28 VDC +28 VDC RTN
+28 VDC LEFT ESS BUS
(H8) AIL TRIM IND
5A
ROLL DISCONNECT HANDLE
LEFT DC CBP
ROLL DISCONNECT
TO SPOILER CONTROLS
AIL POS
HI LO
+28 VDC DC RETURN CHASSIS GND
AIL I
J/P2 G H
4 HI AIL POS 13 LO
TRIM ACTUATOR
C D E
AILERON FORWARD QUADRANT
SPRING TORSION BAR
AUTOPILOT SERVO
£
TRIM
AILERON
TRIM
AILERON TERMINAL QUADRANT
AILERON TRIM INDICATOR +5 VDC
A B
+5 VDC DC RTN
PANEL LIGHTING
DN
J/P100 H J K L
1 L
2 3
8 10 2 3
AIL AIL AIL AIL
TRIM TRIM TRIM TRIM
RTN EXT RET EN
4 5 R
AILERON SPLITTER QUADRANT
6 2711-S1
AILERON TRIM SWITCH
TRIM CONTROL PANEL (CENTER CONSOLE)
AIL POS HI 414 AIL POS LO 413
AILERON TRIM LINEAR ACTUATOR
31-40 A1 IOM #1
Figure 27-14. Aileron Trim Schematic
GEARED TAB
LEFT AILERON
AILERON TERMINAL QUADRANT
LVDT
GUST LOCK
GROUND ADJUSTABLE TAB
RIGHT AILERON
UP
GEARED TAB
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
DC RTN
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• Select trim switch fully LWD •• Make sure trim indicator is operating correctly
NOTES
•• Make sure left aileron is UP, and right aileron is DOWN
27 FLIGHT CONTROLS
•• Repeat with switch in RWD, check indicator and aileron positions •• Set aileron trim to the neutral position •• Set CONTROL LOCK to ON position.
FOR TRAINING PURPOSES ONLY
27-21
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
2 3
1
27 FLIGHT CONTROLS
LEGEND
6
1. Aileron terminal quadrant. 2. Rigging pin (left wing). 3. Rigging pin (right wing). 4. Aileron. 5. Aileron rigging tool. 6. Aileron control rod.
LH SIDE SHOWN, RH SIDE SIMILAR
1
5
14
4 6
pb165a01.dg, pt/gv, 16/04/02
Figure 27-15. Aileron Terminal Quadrant to Aileron Surface Rigging
27-22
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
27-14-00 AILERON SURFACES INTRODUCTION The aileron surfaces are the primary flight control. The aileron surfaces are assisted by the roll spoilers which give roll control of the aircraft in flight.
GENERAL Refer to Figure 27-15. Aileron Terminal Quadrant to Aileron Surface Rigging. There are two aileron control surfaces. They are installed on the outboard ends of the left and right wing. Aileron travel is ±17º around the neutral position.
AILERON TERMINAL QUADRANT TO AILERON SURFACE RIGGING The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
The maintenance check flight and subsequent GAT and aileron pushrod adjustment makes sure that the aircraft will fly level with the control wheels in the neutral position.
RIGGING OF THE AILERON CONTROL SYSTEM STOPS The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Pull the ROLL DISC handle •• Install rigging pins in left and right aileron terminal quadrants •• Put an inclinometer on the upper surface of the left and right ailerons @ YW 436.02 •• Set the protractors to read 0° •• Install left and right aileron rigging boards •• Remove the rigging pins •• T u r n c o - p i l o t ’ s h a n d w h e e l counterclockwise, stop when the left aileron is at 16.5° to 17° •• Hold the hand wheel in this position
This procedure sets the ailerons to the 0° position on the aileron rigging tool with the rigging pins in the terminal quadrant.
•• Adjust the stop bolts on the terminal quadrants to touch the stop faces
After you do this procedure you must have the aircraft flown and do subsequent adjustments to the Ground Adjustable Trim Tab and the aileron pushrods i.a.w. TASK 27-13-11-830-803.
•• Turn the control wheel fully clockwise and hold
This subsequent aileron pushrod adjustment can change the position of the ailerons, with the rigging pins in the terminal quadrants, to a maximum of 2° either side of 0° on the aileron rigging tool.
•• Record the angle of the aileron
•• Repeat the procedure for the stop bolts •• Make sure the travel of the two ailerons is between 0.5° or less of each other.
This is necessary to compensate for manufacturing tolerances of the aircraft structure.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-23
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
3
1
2
LEGEND 1. Ground Adjustable Trim Tab. 2. RH Aileron Geared Tab. 3. Horn. 4. LH Aileron Geared Tab.
4
Figure 27-16. Ailerons Control Surfaces
27-24
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Aileron Control Surfaces Refer to Figure 27-16. Ailerons Control Surfaces. The aileron consists of following components: 27 FLIGHT CONTROLS
•• Aileron box •• Leading edge •• Trailing edge •• Aileron tip •• Gear tab • Trim tab (right hand aileron only). Aileron movement is defined by the control system and is translated to the aileron by a push rod connected to the aileron actuator bracket. The aileron has a geared tab. The aileron has horn and leading edge mass balance. View holes are located on the bottom of the aileron for visual inspection of the hinge pins. An access panel is located at the center hinge point. A horn with internal mass balance weights is located on the outboard end of each aileron to give aerodynamic balance.
FOR TRAINING PURPOSES ONLY
27-25
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
1 LEGEND
2
27 FLIGHT CONTROLS
1. Control Lock Lever. 2. Control Lock Off Position. 3. Control Lock On Position. 4. Gust Lock Cables. 5. Gust Lock Lever. 6. Gust Lock Mechanism. 7. Rig Pin Hole.
R A T I N G
R A T I N G
I
FLIGHT IDLE DISC
I
7
4
5 AILERON SPLITTER QUADRANT
6
Figure 27-17. Aileron Gust Lock System
27-26
FOR TRAINING PURPOSES ONLY
3
MAINTENANCE TRAINING MANUAL
27-70-00 AILERON GUST LOCK SYSTEM INTRODUCTION The aileron gust lock provides protection against wind gusts, while the aircraft is stationary on the ground.
GENERAL The aileron control system is a mechanically operated system. Gust protection for the ailerons is supplied by a gust lock mechanism operated from the flight compartment. When the CONTROL LOCK lever on the center console is pulled aft to the ON position, the ailerons are locked in neutral. The aileron gust lock system has the following sub-system: • Aileron Gust Lock System Mechanism.
SYSTEM DESCRIPTION Refer to Figure 27-17. Aileron Gust Lock System.
OPERATIONAL TEST OF THE AILERON GUST LOCK SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Make sure the CONTROL LOCK (gust lock) handle is fully forward in the OFF position •• Move the pilot or co-pilot control wheel and make sure that: °° The two control wheels turn in the same direction and at the same time °° The aileron control surfaces move in relation to the control wheel movement °° The ailerons move freely through the full range of travel •• Put the control wheels near their neutral position •• Engage the aileron gust lock.
The CONTROL LOCK lever is located in the flight compartment, on the power quadrant. When the CONTROL LOCK lever release is pulled up (squeezed) and the lever is moved from the OFF to the ON position, the aileron mechanism gust lock lever is pivoted by cable to the locked position. If the ailerons are in the neutral position, the plunger engages in the lock plate slot and prevents the aileron splitter quadrant from rotating. If the ailerons are not in the neutral position, the plunger is compressed against the face of the lock plate. When the ailerons are moved to the neutral position the plunger springs out to the locked position. If a gust lock cable fails, the gust lock mechanism fails safe to the unlocked position. Two tension springs pull the gust lock lever towards the OFF position assuring positive disengagement.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-27
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-28 1
2
DASH 8 Q400
3
4 2
6
1
7
LEGEND 7 6 5 8
fs055a01.cgm
Figure 27-18. Spoiler Control System
1. Outboard Spoiler. 2. Inboard Spoiler. 3. Spoiler Splitter Quadrant. 4. Spoiler Control Cables. 5. Outboard Spoiler PCU. 6. Spoiler Clutch. 7. Inboard Spoiler PCU. 8. Spoiler Forward Quadrant.
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
5
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-61-00 ROLL SPOILERS SYSTEM
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The roll spoilers are hydraulically powered and operate with, and in proportion to, the aileron control system. They assist in lateral control of the aircraft during flight. The roll spoilers also decrease the lift of the wings on landing.
GENERAL Refer to Figure 27-18. Spoiler Control System. There are two hydraulically powered roll spoilers on each wing. Movement of the handwheels operates a cable system connected to Power Control Units (PCU). The PCU extend or retract the spoiler panels. The No.1 hydraulic system supplies the inboard spoilers and the No.2 hydraulic system supplies the outboard spoilers. There are three modes of spoiler operation: •• Flight Mode •• Ground Mode (refer to 27-62-00) and • Taxi Mode. The roll spoiler system includes the following components: •• Spoiler quadrant •• Spoiler splitter quadrant •• Clutch units •• Power control units •• Unload valves •• Spoiler LVDTs •• Spoiler cable sensor • Lift dump valves.
FOR TRAINING PURPOSES ONLY
27-29
27 FLIGHT CONTROLS
27-30 ROLL DISCONNECT HANDLE
NOTE H1 Powered By Number 1 Hydraulic System. H2 Powered By Number 2 Hydraulic System.
POWERED FLIGHT CONTROL SHUTOFFS SPLR 1 SPLR 2
ROLL DISCONNECT MECHANISM
PUSH OFF
PUSH OFF
SPOILER CLUTCH (4)
FROM SPOILER CLUTCH
SPOILER SPLITTER QUADRANT ASYMMETRIC LINKAGE
LH. OUTBD. SPOILER
2H
H1
H1
TO SPLR PUSHOFF SWITCH
TO SPLR PUSHOFF SWITCH
LH. INBD. SPOILER
RH. INBD. SPOILER
fs106a01.cgm
Figure 27-19. Spoiler Control System Synoptic
SPOILER PCU RH. OUTBD. SPOILER
MAINTENANCE TRAINING MANUAL
FROM SPOILER CLUTCH
H2
FOR TRAINING PURPOSES ONLY
SPOILER QUADRANT TENSION REGULATOR
DASH 8 Q400
TO AILERON CONTROLS
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION
NOTES
Refer to Figure 27-19. Spoiler Control System Synoptic.
27 FLIGHT CONTROLS
Rotary movement of the control wheels is transmitted by sprockets, chains, and push-rod to the spoiler quadrant. This is all done through the base of the pilot’s control column. A force sensor is installed between the left control column and the spoiler quadrant. The signal transmitted by the sensor is recorded by the EDR. The control cables are routed from the quadrant below the floor up to the aft pressure bulkhead. They go up then run forward to aft of wing rear spar through the pressure vessel to a splitter quadrant installed on the rear spar. The cables from the splitter quadrant are routed to the spoiler clutches quadrants. The clutches are connected to push-rods, levers, and bell cranks to give mechanical inputs to the hydraulic spoiler actuators. A clutch in the pulley of each mechanism can disengage and isolate either inboard or outboard spoilers if a PCU linkage jams. If the clutch slips, an advisory switchlight illuminates. (PUSH OFF) Pushing the switchlight depressurizes the jammed PCU and the corresponding PCU on the other wing. At high airspeeds the outboard spoilers are locked out. Failure to lock out or re-engage the spoilers will be annunciated to the crew by an illuminated caution light (SPLR OUTB). Hydraulic pressure applied to the PCUs is monitored. Any faults will be displayed in the flight compartment. A roll disconnect system is supplied in the event a cable jam occurs (refer to 27-16-00).
FOR TRAINING PURPOSES ONLY
27-31
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SPOILER CONTROL SYSTEM FLIGHT COMPARTMENT
FW 27 FLIGHT CONTROLS
D
3
2
INB
D
1
D
FW
LEGEND 4 ft095a01.cgm
Figure 27-20. Spoiler Quadrant
27-32
FOR TRAINING PURPOSES ONLY
1. Rig Pin Hole. 2. Pushrod Attachment. 3. Cable Tension Regulator. 4. Mounting Brackets.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Spoiler Quadrant Refer to Figure 27-20. Spoiler Quadrant.
27 FLIGHT CONTROLS
The spoiler quadrant transmits the control column hand wheel inputs to the spoiler cable system. The spoiler quadrant is installed at the base of the pilot's control column and connected to the interconnect rod. It includes a tension regulator, which maintains constant cable tension under all temperature conditions. The attached Hot Normal Cold (H-N-C) scale and pointer is used to rig the tension regulator in accordance with temperature related graphs. The spoiler quadrant includes the secondary control stops, and a rig pin hole.
FOR TRAINING PURPOSES ONLY
27-33
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SPOILER SPLITTER QUADRANT INSTALLATION
27 FLIGHT CONTROLS FWD
2
1
4
3
LEGEND 1. Fuselage Input Quadrant. 2. Rig Pin Hole. 3. Bracket. 4. RH and LH Wing Output Pulley.
ft014a01.cgm
Figure 27-21. Spoiler Splitter Quadrant
27-34
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Spoiler Splitter Quadrant
NOTES
Refer to Figure 27-21. Spoiler Splitter Quadrant. The spoiler splitter quadrant transmits control column roll system inputs to the wing spoiler cable circuits. 27 FLIGHT CONTROLS
The quadrant is attached to the aft face of the wing rear spar. It has two brackets and three pulleys. The larger lower pulley is the attachment point for the control cable from the forward spoiler quadrant. The top pulley inputs the right wing spoilers. The middle pulley inputs the left wing spoilers. There is a rig pin hole to lock the quadrant in neutral.
FOR TRAINING PURPOSES ONLY
27-35
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SURFACE SPOILER CONTROL ASSEMBLY D
FW
D
FW
27 FLIGHT CONTROLS 3
4
5 1 2 6
7
FW
D 8
LEGEND 1. Microswitch (SPLR 1 PUSHOFF). 2. Clutch Spring. 3. Mounting Brackets. 4. Rig Pin Hole.
5. Pushrod Attachment (INBD PCU). 6. Input Quadrant. 7. Cam. 8. Clutch Plate.
NOTE Outbd clutch mechanism on bottom of quadrant.
Figure 27-22. Spoiler Clutch Units
27-36
FOR TRAINING PURPOSES ONLY
ft053a01.cgm
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Clutch Units
NOTES
Refer to Figure 27-22. Spoiler Clutch Units. The clutch units transmit spoiler system inputs to the spoiler PCU.
27 FLIGHT CONTROLS
The clutch units are installed centrally below the two spoiler panels attached to the wing rear spar. The clutch units operate the spoiler PCU input levers through two push-rods and one bellcrank. The units contain two clutch mechanisms to allow for a jam between the clutch unit and the controls to either spoiler panel. If the linkage jams, with a force of approximately 27 lbs (12.25 kg) at the clutch and approximately 12 lbs (6 kg) at control wheel will cause disengagement of the clutch and the clutch will slip. When the clutch slips, it operates a microswitch, causing the inboard or outboard spoiler switchlight (SPLR1 or SPLR 2) PUSH OFF annunciation to illuminate.
FOR TRAINING PURPOSES ONLY
27-37
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SURFACE SPOILER CONTROL ASSEMBLY D
FW
D
FW
27 FLIGHT CONTROLS 5
6
4
3
2 12
D
11
FW 10 9
LEGEND 1. Pushrod Attachment. 2. Bellcrank Assembly. 3. Input Connecting Link Assembly. 4. Crank Connecting Link Assembly. 5. Feedback Link. 6. Summing Link.
8
7
7. Input Crank Lever Assembly. 8. Serrated Insert. 9. Main Control Valve. 10. Rod End Assembly. 11. Spoiler Panel Link. 12. Manual Release Valve.
Figure 27-23. Spoiler Power Control Unit
27-38
FOR TRAINING PURPOSES ONLY
1
ft097a01.cgm
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Power Control Units (Inboard/ Outboard)
NOTES
Refer to Figure 27-23. Spoiler Power Control Unit. The PCU transfer spoiler system input commands into hydraulic outputs to the spoiler panels. 27 FLIGHT CONTROLS
The PCUs are mounted on brackets attached to the wing rear spar below the spoiler panels. The PCU has four ports: •• Extend port •• Retraction or hold down port •• Return port • Lift dump port (Ground Spoiler Mode).
FOR TRAINING PURPOSES ONLY
27-39
27 FLIGHT CONTROLS
27-40 MAIN CONTROL VALVE
THERMAL RELIEF/ RECIRCULATING VALVE
(FROM UNLOAD VALVE)
ACTUATOR ASSEMBLY
RETRACT PORT (SYSTEM PRESSURE)
.
RETURN PORT
MANUAL RELEASE VALVE
fss97a01a.cgm
Figure 27-24. Spoiler Power Control Hydraulic Unit
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
EXTEND PORT
DASH 8 Q400
LIFT DUMP PORT (GROUND MODE)
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-24. Spoiler Power Control Hydraulic Unit.
NOTES
27 FLIGHT CONTROLS
The input lever operates a main control valve. Main control valve input opens the extend port to the actuator piston. The hold down port is pressurized and ported directly to the actuator piston. Hydraulic pressure holds down the spoiler panels. The actuator piston extend port pressure must overcome the actuator piston hold down pressure. The input commands move the actuator rod with an attached feed back linkage. Actuator travel stops when the actuator rod position corresponds to the input lever position. The PCU incorporates a manual release valve to aid in PCU hydraulic bleeding. The spoiler panels can extend to a maximum of 75°. The No.1 or No.2 hydraulic system supplies constant pressure to the retract port of the inboard spoiler PCU, and extend pressure through the de-energized open unload valve. The constantly supplied retract pressure acts on the small surface area of the PCU piston. The extend pressure, when directed by the control valve of the PCU, acts on the larger surface area of the piston, extending the ram, driving the spoiler panel up. Pressure on the retract side opens the thermal relief/recirculating valve in the PCU.
FOR TRAINING PURPOSES ONLY
27-41
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Unload Valves Refer to Figure 27-25. Spoiler Unload Valve. The unload valves supply the PCU with system hydraulic pressure:
27 FLIGHT CONTROLS
•• No.1 unload valve is located on the left side of the fuselage in the wing to fuselage attachment area. The No.2 unload valve is located on the right side of the fuselage also in the wing to fuselage attachment area •• No.1 unload valve supplies hydraulic pressure to both inboard spoiler PCU extend ports •• No.2 unload valve supplies hydraulic pressure to both outboard spoiler PCU extend ports •• No.2 unload valve energized closed by the FCECU, which prevents extension of the outboard spoilers when the airspeed is above 170 kt.
2
3 D
FW
1
FW
D
4
LEGEND
5
1. Solenoid. 2. Electrical Conector. 3. Hydraulic Port Return. 4. Mounting Bracket. 5. Hydraulic Pressure Port.
Figure 27-25. Spoiler Unload Valve
27-42
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Linear Variable Differential Transformer (LVDT) Refer to Figure 27-26. Spoiler LVDT. The spoiler panel position LVDT provides data to the FCECU. 27 FLIGHT CONTROLS
The LVDT is attached to a bracket on the aft face of the wing rear spar and a bracket on the spoiler panel. The FCECU supplies the excitation to the LVDT. The FCECU uses the LVDT data to monitor the serviceability of each actuator. The FCECU also transmits the LVDT data to the Integrated Flight Cabinet (IFC). The IFC transmits this data to the: •• Flight Data Recorder (FDR) and •• Powered Flight Control Surface (PFCS) indicator.
A
A
SPOILER LVDT ASSEMBLY
D
FW
1
Figure 27-26. Spoiler LVDT
FW
D
LEGEND 1. Spoiler Attachment. 2. Rib Assembly Attachment. 3. Ground Strap.
2
FOR TRAINING PURPOSES ONLY
NOTE Left inboard LVDT shown. Other three similar.
27-43
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SPOILER CONTROL SYSTEM FLIGHT COMPARTMENT
A
27 FLIGHT CONTROLS
FW
D
3
2
LEGEND
4
1
1. Anchor Bracket. 2. Micro Switches. 3. Fitting. 4. Roller Arm. 5. Spoiler Cables. 6. Tension Spring.
5
6
fss77a01.cgm
Figure 27-27. Spoiler Cables Sensor
27-44
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Spoiler Cables Sensor
NOTES
Refer to Figure 27-27. Spoiler Cables Sensor.
27 FLIGHT CONTROLS
The spoiler cable sensor is located on the fuselage spoiler cable circuit under the flight deck floor. The spoiler cable sensor assembly consists of a spring-loaded fair lead roller arm latching a leaf spring and two micro switches. If the spoiler cable fails, the spring-loaded arm rotates against its end stop and actuates the two micro switches. The No.1 and No.2 unload valves are then energized. Extend pressure is removed from the actuators. The retract pressure will keep spoilers closed. “ROLL SPLR INBD HYD” and “ROLL SPLR OUTBD HYD” caution lights will then illuminate.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-45
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Controls and Indications Refer to Figure 27-28. Powered Flight Control Surface Indicator. The spoiler surface positions are displayed on the PSA1 on the pilot MFD (MFD1). 27 FLIGHT CONTROLS
The indications are LO, LI, RI, and RO corresponding to left outboard, left inboard, right inboard and right outboard respectively. The indication is analog and displays panel deflection angle.
WX OFF
FMS1 076 00
057
HDG 073°
E
3
160
LEGEND 1. Spoiler Position Indication
VIE
35.0 NM --:--
VCF
YSO
00 ---
TAS 20 GS 0
1
YCF
80
TCAS STBY
ADF1 DME1 H 92.1 NM
ADF2 DME2 92.1 NM
I
1
I
Figure 27-28. Powered Flight Control Surface Indicator
27-46
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to: •• Figure 27-29. P owered Flight Surface Shutoffs. • Figure 27-30. Spoiler Switchlights.
27 FLIGHT CONTROLS
A PCU linkage jam will cause the clutch unit to close a microswitch resulting in the inboard or outboard spoiler switchlights (SPLR1 or SPLR 2) PUSH OFF lights to come on.
A
LEGEND 1. Spoiler 1 Push Off Switchlight. 2. Spoiler 2 Push Off Switchlight.
INSTRUMENT PANEL 1
2
POWERED FLIGHT CONTROL SHUTOFFS
IAS
HSI SEL
fs285a01.cgm
A
Figure 27-29. Powered Flight Surface Shutoffs
FOR TRAINING PURPOSES ONLY
27-47
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
LW IB SPLR CLUTCH JAM MICRO SW S7 CLOSED
SPLR 1
RW IB SPLR CLUTCH JAM MICRO SW S8 CLOSED
CDS MSG: N/A
NOT LATCHED
PUSH
SPLR DECLUTCH MICRO SW S3 CLOSED (ROLL DISC)
27 FLIGHT CONTROLS
AILERON DECLUTCH MICRO SW S5 CLOSED (50°)
RW OB SPLR CLUTCH JAM MICRO SW S6 CLOSED
SPLR 2
LW OB SPLR CLUTCH JAM MICRO SW S5 CLOSED
CDS MSG: N/A
NOT LATCHED
PUSH
SPLR DECLUTCH MICRO SW S4 CLOSED (ROLL DISC) AILERON DECLUTCH MICRO SW S5 CLOSED (50°)
NOTES LATCHED - Light will remain illuminated for duration of flight. Will not be reset until fault condition is no longer present NOT LATCHED - Light will extinguish when fault condition is no longer present regardless of phase of flight.
Figure 27-30. Spoiler Switchlights
2
3
1
A OVERHEAD CONSOLE
LEGEND 1. Spoiler Outboard. 2. Roll Spoiler Inboard Hydraulic. 3. Roll Spoiler Outboard Hydraulic.
fsz05a01.cgm
Figure 27-31. Roll Spoiler Caution Lights
27-48
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-31. Roll Spoiler Caution Lights.
NOTES
The FCECU sends signals to the Caution and Warning panel to turn on the following caution lights: 27 FLIGHT CONTROLS
SPLR OUTBD •• If the FCECU fails to lockout the outboard spoilers and airspeed is > 185 knots, or •• If the FCECU locks out the outboard spoilers and airspeed is < 150 knots, or •• Airspeed No.1 disagrees with airspeed No.2 by 17 knots • Internal FCECU fault.
ROLL SPLR INBD HYD •• No.1 Hydraulic system pressure is < 900 psi (6205 kPa). • Roll SPLR cable break
ROLL SPLR OUTBD HYD • • No.2 hydraulic system pressure is < 900 psi (6205 kPa) and air speed < 165 knots •• Roll SPLR cable break
FOR TRAINING PURPOSES ONLY
27-49
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
LEFT I/B SPOILER ACTUATOR RETRACT EXTEND
SPLR #1 PUSH OFF
LIFT DUMP
LIFT DUMP SOLENOID VALVES
RESERVOIR QTY SPOILER ACTUATOR
#1 HYD. SYSTEM PRESSURE
FCECU ENERGIZED OPEN
LIFT DUMP
ISOLATION VALVE UNLOAD VALVE #1
EXTEND RETRACT RIGHT I/B SPOILER ACTUATOR
Figure 27-32. Inboard Spoiler Hydraulic Schematic
27-50
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL TEST OF THE ROLL SPOILER SYSTEM
Roll Spoiler Hydraulics Figure 27-32. Inboard Spoiler Hydraulic Schematic. In ground mode, the hydraulic pressure to the lift dump ports of each PCU passes through lift dump solenoid valves.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Disengage the roll disconnect mechanism.
The valves are hydraulically in series, two for the inboard PCUs and two for the outboard PCUs.
Engage the aileron gust lock.
Hydraulic Failure
Turn the pilots control wheel fully to the left then to right.
If the No.1 hydraulic system fails, the ROLL SPLR INBD HYD caution light illuminates. If the No.2 hydraulic system fails, and the airspeed is < 170 KIAS, the ROLL SPLR OUTBD HYD caution light illuminates. In the event of the hydraulic failure, the spoiler panels go down. They will be driven down by the airflow moving across the wing.
Revision 0.4
This operational check is to confirm that the spoilers, the PFCS indications and the caution lights operate correctly under the following conditions: •• Normal operation •• SPLR 1 Selected off • SPLR 2 Selected off.
FOR TRAINING PURPOSES ONLY
27-51
27 FLIGHT CONTROLS
OPERATION
27 FLIGHT CONTROLS
27-52 SPOILER OB POS LT EXC HI SPOILER OB POS LT EXC LO
97 98
1 SPOILER OB POS LT EXC HI 2 SPOILER OB POS LT EXC LO ROLL DISCONNECT DISCONECT HANDLE
SPOI LER OB POS LT HI SPOILER OB POS LT CT SPOILER OB POS LT LO
90 89 96
H1 H2
5 SPOI LER OB POS LT HI 4 SPOILER OB POS LT CT 3 SPOILER OB POS LT LO
100 93
SPOILER OB POS RT HI SPOILER OB POS RT CT SPOILER OB POS RT LO
92 91 99
B
POWERED FLIGHT CONTROL SHUTOFFS SPLR 1
SPLR 2
PUSH
PUSH
OFF
OFF
ROLL DISCONNECT MECHANISM SPOILER QUADRANT TENSION REGULATOR
FROM SPOILER CLUTCH
1 SPOILER OB POS RT EXC HI 2 SPOILER OB POS RT EXC LO
SPOILER CLUTCH
FROM SPOILER CLUTCH
SPOILER SPLITTER QUADRANT ASYMMETRIC LINKAGE
C
2
53
ROLL SPLR O/B CAUTION
3
69
ROLL SPLR O/B INHIBIT
RIGHT SPOILER OUTBOARD LINEAR VARIABLE DIFFERENTIAL TRANSDUCER (LVDT)
TO SPLR PUSHOFF SWITCH
FROM SHEET 1
70
TO SPLR PUSHOFF SWITCH SPOILER PCU
LH. OUTBD. SPOILER
4
LH. INBD. SPOILER
SPLR O/B PRESS SPOILER IB POS LT EXC HI SPOILER IB POS LT EXC LO
97 98
1 SPOILER IB POS LT EXC HI 2 SPOILER IB POS LT EXC LO
SPOI LER I B POS L T HI SPOILER IB POS LT CT SPOILER IB POS LT LO
90 89 96
5 SPOI LER I B POS L T HI 4 SPOILER IB POS LT CT 3 SPOILER IB POS LT LO
LEFT SPOILER INBOARD LINEAR VARIABLE DIFFERENTIAL TRANSDUCER (LVDT) ROLL SPLR I/B GND CAUTION LT
42
SPOILER IB POS RT EXC HI SPOILER IB POS RT EXC LO
100 93
SPOILER IB POS RT HI SPOILER IB POS RT CT SPOILER IB POS RT LO
92 9 91 99
1 SPOILER IB POS RT EXC HI 2 SPOILER IB POS RT EXC LO 26 ROLL SPLR O/B (GND)
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
D
H 2
SPLR O/B INHIB CAUTION
H1
P/J2 52
H1
1
5 SPOILER OB POS RT HI 4 SPOILER OB POS RT CT 3 SPOILER OB POS RT LO
5 SPOILER IB POS RT HI 4 SPOILER IB POS RT CT 3 SPOILER IB POS RT LO
RIGHT SPOILER INBOARD LINEAR VARIABLE DIFFERENTIAL TRANSDUCER (LVDT)
49 ROLL SPLR I/B (GND)
CAUTION AND WARNING PANEL
Figure 27-33. Spoiler Panel Indications - Spoiler System Schematic
RH. INBD. SPOILER
RH. OUTBD. SPOILER
MAINTENANCE TRAINING MANUAL
SPOILER OB POS RT EXC HI SPOILER OB POS RT EXC LO
A
H 2
FOR TRAINING PURPOSES ONLY
42
E TO AILERON CONTROLS
LEFT SPOILER OUTBOARD LINEAR VARIABLE DIFFERENTIAL TRANSDUCER (LVDT) ROLL SPLR O/B GND CAUTION LT
Powered By Number 1 Hydraulic System. Powered By Number 2 Hydraulic System.
DASH 8 Q400
NOTE
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to:
NOTES
•• Figure 27-33. S poiler Panel Indications - Spoiler System Schematic. •• Figure 27-34. R oll Spoilers Operation > 170 KIAS. 27 FLIGHT CONTROLS
•• Figure 27-35. L eft Wing Inboard Spoiler Jam Indicated.
Flight Mode Above 170 KIAS, the outboard spoilers are disabled by energizing the No.2 actuator unload valve. Power for the valve comes from the right essential bus to Pin A on the valve. The ground to Pin B of the valve is supplied through the FCECU.
Roll Spoiler Jam The “Pilot Flying” (PF) attempts to put in a roll command. One of the main control valve inputs is jammed, resulting in an increase in the force needed to move the control wheel. The clutch controlling the input to the jammed control valve slips and SPLR 1 or SPLR 2 switchlight illuminates. Power is always supplied to the inboard spoiler switchlight from the right essential bus. The ground for the switchlight is from the left wing spoiler jam switch S7. Pushing the switchlight provides a ground for the inboard actuator unload valve removing extend hydraulic pressure. The PUSH goes off in the switchlight OFF, remains on. The ROLL SPLR INBD HYD caution light illuminates through a ground provided by the No.1 flight spoiler low pressure switch.
FOR TRAINING PURPOSES ONLY
27-53
27 FLIGHT CONTROLS
27-54 A
L O/B S5
S11 S10
ON S4 PUSH B
L I/B ROLL DISC HANDLE
S7
A
A
A
A
P/J10 D
A
S3
C
#1 O/B PUSH OFF 1 1 ROLL SPOILER DISC JAM SW
H3
J2
S5
S4
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
E
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
5A
L3
L1
SPLR1 (INBD)
ACU (F6)
B
N
ROLL SPLRS ARM INBD
PUSH
5A
B
A
A
ROLL SPLRS IND
3
OFF
F R
A
A
A
TO SHEET 2 FROM FCECU ROLL SPOILER OUTBD
4
D
OFF
TAXI SWITCH
R I/B
H2 H1
X ADVSY LTS 28 VDC
K1
S8
R O/B
D
D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR2 (OUTBD)
RIGHT DC CBP
2
C G
RIGHT DC CBP
R ESS BUS 28 VDC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1
NO
D
OFF H2
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
CENTER GLARESHIELD PANEL
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
Figure 27-34. Roll Spoilers Operation > 170 KIAS
S V
8 9 24
CAUTION AND WARNING PANEL
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
C
OFF
G
E C U/F FLT COMP
C
F
H1
NC B
A
CABLE SENSORS X-54
LEFT WING SPOILER JAM E
DASH 8 Q400
C
A B C
A
L O/B S5
S11 S10
ON S4
C B
L I/B ROLL DISC HANDLE
S7
B
C
J/P9 A
D
S3
J/P10 C
S4
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
A
5A
A
#1 O/B PUSH OFF 1
H3
H1 1 ROLL SPOILER DISC JAM SW
J2
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
L3
L1
SPLR1 (INBD)
B
N
ROLL SPLRS ARM INBD
PUSH
5A
B
A
A
ROLL SPLRS IND
F A
A
A
TO SHEET 2
3
OFF
4
D
OFF
RIGHT DC CBP
TAXI SWITCH
R I/B
H2 H1
X ADVSY LTS 28 VDC
S8
R O/B
D
J/P34 D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
K1 B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR2 (OUTBD)
RIGHT DC CBP
2
C G
R
R ESS BUS 28 VDC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1 E
D
OFF
ACU (F6)
A
H2
NO S5
OFF
F E C
U/F FLT COMP
C G
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
S V
CENTER GLARESHIELD PANEL
8 9 24
CAUTION AND WARNING PANEL
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
27-55
Figure 27-35. Left Wing Inboard Spoiler Jam Indicated 27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
NC
A
CABLE SENSORS X-54
LEFT WING SPOILER JAM E
A
PUSH
DASH 8 Q400
C
A B
27 FLIGHT CONTROLS
27-56 A
L O/B S5
S11 S10
ON S4
C
PUSH B
L I/B ROLL DISC HANDLE
S7
E C
J/P9 A
D
S3
C
A
A
A
1 ROLL SPOILER DISC JAM SW
S4
H3
J2
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
5A
L3
L1
SPLR 1 (INBD)
ACU (F6)
B
N
ROLL SPLRS ARM INBD
PUSH
5A
B
A
A
ROLL SPLRS IND
A
A
A
TO SHEET 2
3
OFF
F
4
D
OFF
RIGHT DC CBP
TAXI SWITCH
R I/B
H2 H1
X ADVSY LTS 28 VDC
K1
S8
R O/B
D
D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR 2 (OUTBD)
RIGHT DC CBP
2
C G
R
R ESS BUS 28 V DC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1 E
D
OFF H2
#1 O/B PUSH OFF 1
NO S5
OFF
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
CENTER GLARESHIELD PANEL
S V
8 9 24
CAUTION AND WARNING PANEL
Figure 27-36. Left Wing Spoiler Jam Recovery Switchlight Pushed No.1 Unload Valve Energized to Unload
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
C
C G
H1
NC B
A
F
LEFT WING SPOILER JAM E
A
CABLE SENSORS X-54
U/F FLT COMP
DASH 8 Q400
C
A B
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL TEST OF THE SPOILER JAM DETECT SYSTEM
NOTES
27 FLIGHT CONTROLS
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 27-36. Left Wing Spoiler Jam Recovery Switchlight Pushed No.1 Unload Valve Energized to Unload. A mechanical clutch is incorporated at the spoiler clutch assembly, in the outer wing rear spar area of each wing. This clutch gives protection against complete loss of spoiler systems in the event of a jam. It removes the jammed spoiler from the circuit and allows the rest of the system to continue to operate. If a jam occurs, the roller on the pushrod will come out of its detent in the clutch assembly. This causes springs to push the switch plates out and turn on the SPLR1 or SPLR2 push-off switch. The SPLR1 push-off switch when pushed will de-energize the inboard spoiler hydraulic system. The SPLR2 push-off when pushed will de-energize the outboard spoiler hydraulic system. •• Before testing the spoiler jam detection make sure the spoilers operate normally. To simulate a jammed spoiler a rig pin is installed to one of the spoiler linkage lever to prevent movement of that spoiler PCU. This will be done to all four PCU clutches, one at a time.
NOTE A force of approximately 12 lbf (6 kgf) is required to disengage the spoiler clutch. When the spoiler clutch is disengaged, the pilot and co-pilot control wheels turn at their usual force of approximately 4 lbf (2 kgf). When the jam is detected it will cause a SPLR push off light to come on. Selection of the SPLR push off switch will cause the PUSH segment of the light to go out and the ROLL SPLR INBD HYD or the ROLL SPLR OUTBD HYD caution light to come on.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-57
27 FLIGHT CONTROLS
27-58 A
L O/B S5
S10
ON S4
C
PUSH B
L I/B ROLL DISC HANDLE
S7
A
A
A
A
#1 O/B PUSH OFF 1
D
S3
1 ROLL SPOILER DISC JAM SW
H3
J2
S4
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
E
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
L3
L1
SPLR1 (INBD)
ACU (F6)
ROLL SPLRS ARM INBD
B
N
5A PUSH B
ROLL SPLRS IND
A
A
A
A
A
TO SHEET 2
3
OFF
F R
4
D
OFF
RIGHT DC CBP
TAXI SWITCH
R I/B
H2 H1
X ADVSY LTS 28 VDC
K1
S8
R O/B
D
D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR2 (OUTBD)
RIGHT DC CBP
2
C G
5A
R ESS BUS 28 VDC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1
NO S5
D
OFF H2
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
CENTER GLARESHIELD PANEL
S V
8 9 24
CAUTION AND WARNING PANEL
Figure 27-37. Roll Spoiler Fuselage Cable Jam Indicated-Roll Disconnect System Activated-50 Degree Travel Switch Closed
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
C
C
OFF
G
E C U/F FLT COMP
J/P9 A
C
F
H1
NC P/J9 B
A
CABLE SENSORS X-54
LEFT WING SPOILER JAM E
DASH 8 Q400
S11 C
A B
MAINTENANCE TRAINING MANUAL
OPERATIONAL CHECK OF THE ROLL SPOILER SPLR 1 & SPLR 2 PUSH OFF SWITCHLIGHTS The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 27-37. Roll Spoiler Fuselage Cable Jam Indicated-Roll Disconnect System Activated-50 Degree Travel Switch Closed. •• Make sure that the CONTROL LOCK is set to OFF •• Pull the ROLL DISC handle and turn 90° to disconnect the roll spoilers •• Turn the co-pilot handwheel until the SPLR 1 and SPLR 2 switchlights come on (at approximately 50°)
Complete Roll Jam Using Roll Disconnect System Pilot Flying (PF) attempts to put in a roll command, but cannot move the control wheel. PF pulls the roll disconnect handle, this operates the roll disconnect clutch separating roll spoiler and aileron controls. This action also causes two micro-switches (S3 and S4) to arm the 50° travel switch S5. The S5 is on the aileron forward quadrant. To correct the input from a stuck up roll spoiler(s), the co-pilot turns the aileron control wheel 50°, this provides a ground through switch S5. The ground by S5 allows the PUSH OFF indications in SPLR 1 and SPLR 2 switchlights to illuminate.
•• Put the co-pilot handwheel back in the neutral position •• Make sure the two SPLR 1 and SPLR 2 switchlights go off •• Turn the co-pilot handwheel in the opposite direction, of step, until the SPLR 1 and SPLR 2 switchlights come on (at approximately 50°) •• Put the co-pilot handwheel back in the neutral position • Make sure the two SPLR 1 and SPLR 2 switchlights go off.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-59
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-60 FLT COMP A
L O/B S5
S11 S10
ON S4
C
PUSH B
L I/B ROLL DISC HANDLE
S7
A
E C U/F FLT COMP
A
D
S3
C
A
A
A
1 ROLL SPOILER DISC JAM SW
S4
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
H3
J2
E
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
5A
L3
L1
SPLR1 (INBD)
B
N
ROLL SPLRS ARM INBD
PUSH
5A
B
A
A
ROLL SPLRS IND
A
A
A
TO SHEET 2
3
OFF
F
4
D
OFF
RIGHT DC CBP
TAXI SWITCH
H2
P/J177
R I/B
H1
X ADVSY LTS 28 VDC
K1
S8
R O/B
D
D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR2 (OUTBD)
RIGHT DC CBP
2
C G
R
R ESS BUS 28 VDC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1
ACU (F6)
D
OFF H2
#1 O/B PUSH OFF 1
NO S5
OFF
G
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
CENTER GLARESHIELD PANEL
S V
8 9 24
CAUTION AND WARNING PANEL
Figure 27-38. Roll Spoiler Fuselage Cable Jammed-Roll Disconnect Activated 50° Travel Switch Closed-Both Switchlights Pushed-Both Unload Valves Energized to Unload
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
C
C
F
H1
NC B
A
CABLE SENSOR X-54
LEFT WING SPOILER JAM E
DASH 8 Q400
C
A B
MAINTENANCE TRAINING MANUAL
OPERATIONAL CHECK OF THE ROLL SPOILER CABLE SENSOR ASSEMBLY
Refer to Figure 27-38. Roll Spoiler Fuselage Cable Jammed-Roll Disconnect Activated 50° Travel Switch Closed-Both Switchlights PushedBoth Unload Valves Energized to Unload.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
Using this schematic, you can trace the following steps:
This maintenance procedure is for the operational check of the roll-spoiler cable sensor. Slowly pushing down on the top and bottom spoiler cables will allow the roller arm to turn clockwise until the microswitches close. In the flight compartment, make sure that the ROLL SPLR INBD HYD and the ROLL SPLR OUTBD HYD caution lights come on. Release the cables and let them push up on the roller. Make sure that the roller arm stays in the latched condition and that the ROLL SPLR INBD HYD and the ROLL SPLR OUTBD HYD caution lights stay on. Release the roller arm from its latched condition and make sure that the ROLL SPLR INBD HYD and the ROLL SPLR OUTBD HYD caution lights go out.
Revision 0.4
•• Roll Disconnect Activated 50° Travel Switch Closed •• Both Switchlights Pushed • Both Unload Valves Energized to Unload Pushing SPLR 1 switchlight, energizes closed the inboard unload valve providing a ground through contacts J3 to J1 of the switchlight. Pushing SPLR 2 switchlight provides a ground for outboard unload valve through contacts, A2 to A3 of the de-energized relay K1, as well as contacts J3 to J1 of the switchlight. Grounds are maintained for the OFF indications and removed for the PUSH indications in the switchlights. Removing all extend pressure from the spoiler PCUs causes all the roll spoilers to retract.
FOR TRAINING PURPOSES ONLY
27-61
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-62 A
L O/B S5
S11 S10
ON S4
C
PUSH B
L I/B ROLL DISC HANDLE
S7
E C
A
D
S3
C
A
A
A
1 ROLL SPOILER DISC JAM SW
S4
AILERON QUADRANT SWITCH ( CO-PILOT HANDWHEEL >50 º )
H3
J2
E
2 ROLL SPOILER DISC JAM SW
K2
#2 I/B PUSH OFF 2
L2
L3
L1
SPLR1 (INBD)
ROLL SPLRS ARM INBD
B
N
5A PUSH
5A
B
A
A
ROLL SPLRS IND
A
A
A
TO SHEET 2
3
OFF
F
4
D
OFF
RIGHT DC CBP
TAXI SWITCH
R I/B
H2 H1
X ADVSY LTS 28 VDC
K1
S8
R O/B
D
D F GND E
#2 FLIGHT SPOILER LOW PRESSURE SWITCH
S6
RIGHT WING SPOILER JAM
B2
A2 X2 X1
B3 B1
T
J2 J1
A3
K2
A1
K1 L2 L1
H3
J3
D
B A
K3
U
OUTBOARD (#2) UNLOAD VALVE
L3
W
SPLR2 (OUTBD)
RIGHT DC CBP
2
C G
R
R ESS BUS 28 VDC
1
ON
S6 R ESS BUS 28 VDC (H6)
A B
INBOARD (#1) UNLOAD VALVE
K3
K1
ROLL SPOILER DE-CLUTCH SWITCH
P
J3
J1
ACU (F6)
D
OFF H2
#1 O/B PUSH OFF 1
NO S5
OFF
(G6) ROLL SPLRS ARM OUTBD 5A
GND E D
CENTER GLARESHIELD PANEL
#1 FLIGHT SPOILER LOW PRESSURE SWITCH
Figure 27-39. Roll Spoiler Cable Sensor Operation
S V
8 9 24
CAUTION AND WARNING PANEL
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
C
C G
H1
NC B
A
F
LEFT WING SPOILER JAM E
A
CABLE SENSORS X-54
U/F FLT COMP
DASH 8 Q400
C
A B
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Roll Spoiler Cable Break (Operating Cable Sensor System)
NOTES
Refer Figure 27-39. Roll Spoiler Cable Sensor Operation.
27 FLIGHT CONTROLS
The PF puts in a roll command and the roll spoiler cable breaks. The lever of the sensor system pivots forward under spring force. This action closes microswitch S10, which provides a ground to energize the K1 relay. The K1 relay, through contacts A2 to A1, supplies the ground to energize the outboard unload valve, removing all extend pressure from the outboard PCUs. Switch S11 closes at the same time as S10. S10 provides the ground for the inboard unload valve through Pin B. The ROLL SPLR INBD HYD and the ROLL SPOILER OUTBD HYD caution lights come on through grounds provided by No.1 and No.2 Spoiler Low pressure switches.
FOR TRAINING PURPOSES ONLY
27-63
27 FLIGHT CONTROLS
27-64 PLA 1 47°
PLA 2 47°
PCU
SPLR RIGHT OUTBD
LVDT
FOR TRAINING PURPOSES ONLY
ADVISORY LIGHTS
DASH 8 Q400
LIFT DUMP VALVE 2
ROLL OUT BD
LIFT DUMP VALVE 1
28 VDC FCECU
PCU
SPLR RIGHT INBD
LVDT
#2 HYD LIFT DUMP VALVE 1
PCU
SPLR LEFT INBD
LVDT
FLIGHT/TAXI SWITCH
GROUND PSEU WOW 1 WOW 2
LIFT DUMP VALVE 2
PCU
#1 HYD
fsu67a01.cgm
Figure 27-40. Ground Spoiler System Block Diagram
SPLR LEFT OUTBD
LVDT
HYDRAULIC ELECTRICAL
MAINTENANCE TRAINING MANUAL
ROLL IN BD
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-62-00 SPOILER SYSTEM IN GROUND MODE
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
All the roll spoilers are automatically deployed on landing. They are deployed when signalled by the Main Gear Weight-On-Wheels (MGWOW) and power lever sensors are made. This action puts all the aircraft weight on the landing gear, so the wheel brakes can slow the aircraft with greater efficiently.
GENERAL Refer to Figure 27-40. Ground Spoiler System Block Diagram. The roll spoiler system automatically changes from the flight mode to the ground mode after the aircraft has landed. Ground mode operation occurs when: •• The Proximity Sensor Electronic Unit (PSEU) sends the MGWOW1 and MGWOW2 signals to the FCECU •• Power levers 1 and 2 are set to less than 47° • The FLIGHT/TAXI switch is in the FLIGHT position. The ground mode spoiler system includes the listed components: • Lift dump valves.
FOR TRAINING PURPOSES ONLY
27-65
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS A
NOTE Left side shown. Right side similar.
GLARESHIELD PANEL 1
LEGEND 1. Flight/Taxi Switch.
STICK PUSHER SHUT OFF
SPOILERS FLIGHT
ENGINE FIRE
A/P DISENG
ROLL INBD
TAXI
CF-AEI
INHIBIT
ELEVATOR TRIM SHUT OFF
TERRAIN INHIBIT
WARNING PRESS TO RESET
fsz09a02.cgm
A
Figure 27-41. Flight/Taxi Switch
27-66
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-41. Flight/Taxi Switch.
NOTES
Selection of the SPOILERS FLIGHT/TAXI switch to TAXI de-energizes all the lift dump solenoids causing spoiler panels to retract. The switch is held in the TAXI position by a magnetic latch solenoid. 27 FLIGHT CONTROLS
The magnetic latch is provided by the FCECU and PSEU WOW. The spring loaded switch returns to the FLIGHT position when: •• Advancing either power lever above flight idle +12° •• Removing electrical power from the aircraft • PSEU sensing WOFW.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-67
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SPOILER ADVISORY LIGHTS FLIGHT ROLL OUTBD
ROLL INBD
FROM No. 1 HYDRAULIC SYSTEM
TAXI
FROM No. 2 HYDRAULIC SYSTEM
FLIGHT IDLE + 12°
27 FLIGHT CONTROLS
FCECU LIFT DUMP VALVES OPEN
AND
LIFT DUMP VALVES OPEN
AND
PSEU MLG WOW
LH OUTBOARD SPOILER
RH INBOARD SPOILER
LH INBOARD SPOILER
RH OUTBOARD SPOILER
SPOILERS EXTENDED - LIFT DUMP VALVES OPEN
FROM No. 1 HYDRAULIC SYSTEM
ROLL OUTBD
SPOILER ADVISORY LIGHTS
ROLL INBD
FLIGHT
FROM No. 2 HYDRAULIC SYSTEM
TAXI
FCECU
LIFT DUMP VALVES CLOSED
LIFT DUMP VALVES CLOSED
PSEU
LH OUTBOARD SPOILER fsf29a02a.cgm
LH INBOARD SPOILER
RH INBOARD SPOILER
RH OUTBOARD SPOILER
SPOILERS RETRACTED - LIFT DUMP VALVES CLOSED
Figure 27-42. Roll Spoiler Ground Spoiler Mode Synoptic
27-68
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
System Description
NOTES
Refer to Figure 27-42. Roll Spoiler Ground Spoiler Mode Synoptic.
27 FLIGHT CONTROLS
When the aircraft lands, the lift dump valves are energized. The lift dump valves send hydraulic pressure to all the spoiler PCU extend ports which extends the spoiler panels to 75°. The FCECU and the PSEU control the lift dump function. The FCECU left channel controls the two inboard lift dump valves and the right channel controls the two outboard lift dump valves. Each pair of lift dump valves are solenoid operated and connected hydraulically in series. The FCECU sends a high side signal (+28 VDC) to the lift dump valve solenoids if both power levers are a less than flight idle plus 12°. The PSEU sends a low side signal (ground) to the lift dump valve solenoids when both MGWOW1 and MGWOW2 signals are present.
FOR TRAINING PURPOSES ONLY
27-69
27 FLIGHT CONTROLS
27-70 PLA LEFT
J5
P1 J1
N
26 26
J3 ROLL SPLR INBD GND
LEFT FCECU CHANNEL
42 42 66 66
CAUTION WARNING J5 PANEL 26
ROLL SPLR OUTBD GND
94 94
P2 J2
J2 P2
42 42
J1
J2
54 54
LIFT DUMP HI LIFT DUMP LO
LIFT DUMP HI LIFT DUMP LO
GLARESHIELD PANEL
PLA RIGHT
B
A B
SPOILER INBOARD VI
SPOILER OUTBOARD VI
J1
ADVISORY LIGHTS 13 CONTROL 14 DIM/TEST 14 UNIT 13
ROLL OUTBD
A
C1D 64 64
C1C
RIGHT FCECU CHANNEL
WOW 1 16 16
J8 N
WOW 2
PROXIMITY SENSOR ELECTRONIC UNIT C1B A6G
A6?
26 26
A4? FLIGHT/TAXI
TAXI SW RTN TAXI SW TAXI SW HOLD
79 79 78 78 94 94 87 87
GLARESHIELD PANEL
LIFT DUMP HI LIFT DUMP LO
LIFT DUMP HI LIFT DUMP LO
FROM FCECU 2 PWR IN
Figure 27-43. Roll Spoiler in Ground Mode Schematic
A B
SPOILER OUTBOARD V2
A B
SPOILER INBOARD V2
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
64 64
FROM ROLL SPLRS IND
ROLL INBD
16 16
DASH 8 Q400
49
J1 P1
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-43. Roll Spoiler in Ground Mode Schematic.
NOTES
The FLIGHT/TAXI switch interfaces with the right channel of the FCECU and is shared with the left channel for redundancy. 27 FLIGHT CONTROLS
When the FLIGHT/TAXI switch is selected to the TAXI position, the spoiler lift dump valves de-energize and the spoilers retract. After retraction plus 6.5 seconds, the FCECU performs a Event-Built-in-Test (EBIT). It energizes each lift dump valve solenoid individually to check if any valve is stuck in the open position. When all four spoiler panels are extended greater than 65° in the ground mode, the FCECU sends a signal to illuminate the spoiler advisory lights (ROLL OUTBD and ROLL INBD). If a solenoid valve fails to energize, the inboard or outboard ground spoilers will not extend. The FCECU illuminates the caution lights ROLL SPLR OUTBD GND and ROLL SPLR INBD GND if the related spoiler panels do not extend after touchdown. These caution lights illuminate after a time delay of 5 seconds. The FCECU illuminates the ground caution lights if the spoilers do not retract in the TAXI mode or if the BIT finds a failure in the lift dump valves.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-71
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Lift Dump Valves Refer to Figure 27-44. Spoiler Lift Dump Valve.
27 FLIGHT CONTROLS
The two lift dump valves for the inboard (No.1) spoiler system are located on the left side of the aircraft in the wing-to-fuselage attachment area. The two lift dump valves for the outboard (No.2) spoiler system are located on the right side of the aircraft also in the wing-to-fuselage attachment area.
Both valves must open to let extend pressure through the unload valve to the related spoiler PCU. This reduces the possibility of in flight symmetric deployment. The lift dump valves provide hydraulic system pressure to the spoiler PCU lift dump port and fully extend each spoiler panel symmetrically.
LEGEND 1. Electrical Connector. 2. Solenoid. 3. Return Port. 4. Pressure Port. 5. Check Valve. 6. Cylinder Port.
2
1
3 6
D
FW
4 5
ft087a01.cgm
Figure 27-44. Spoiler Lift Dump Valve
27-72
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Refer to Figure 27-45. Spoiler Surface Indication.
27 FLIGHT CONTROLS
The spoiler surface positions are displayed on the PFCS on MFD1. The indication displays panel deflection angle. INSTRUMENT PANEL
WX OFF
057
HDG 073°
E
3
160
LEGEND 1. Spoiler Position Indication
FMS1 076 00
VIE
35.0 NM --:--
VCF
YSO
00 ---
TAS 20 GS 0
1
YCF
80
TCAS STBY
ADF1 DME1 H 92.1 NM
ADF2 DME2 92.1 NM
I
1
I
Figure 27-45. Spoiler Surface Indication
FOR TRAINING PURPOSES ONLY
27-73
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
LEGEND 1. Spoiler Outboard. 2. Roll Spoiler Inboard Ground. OVERHEAD CONSOLE 2
1
#1 STALL SYST FAIL #2 STALL SYST FAIL ROLL SPLR INBD HYD
#2 HYD FLUID HOT
FLAP DRIVE
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING
FUELING ON
MAIN BAT HOT
fsz05a01.cgm
Figure 27-46. Roll Spoiler in Ground Mode Caution Lights
27-74
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-46. Roll Spoiler in Ground Mode Caution Lights. The FCECU sends signals to the Caution and Warning panel to illuminate the caution lights that follow:
ROLL SPLR INBD GND •• If the FCECU senses a loss of lift dump valve function, or •• If the lift dump valves are operated but the spoiler panels fail to extend after landing, or •• If the spoiler panels extend when the FCECU carries out the lift dump BIT, with the FLIGHT/TAXI switch set to TAXI •• PLAs disagree, one > 47°, one < 47°, WOW disagree • Internal failure of the FCECU.
ROLL SPLR OUTBD GND •• If the FCECU senses a loss of lift dump valve function, or •• If the lift dump valves are operated but the spoiler panels fail to extend after landing, or •• If the spoiler panels extend when the FCECU carries out the lift dump BIT, with the FLIGHT/TAXI switch set to TAXI •• PLAs disagree, one > 47°, one < 47°, •• WOW disagree • Internal Failure of the FCECU.
OPERATIONAL TEST OF THE GROUND SPOILER SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. This operational test is to confirm that the FLIGHT/TAXI switch, when in the TAXI position, will return to the FLIGHT position when power lever 1 and/or power lever 2 is moved to greater than the flight idle position of +12°. When the FLIGHT/TAXI switch is in TAXI position, observe the following indications: •• The PFCS spoiler indications show all the spoilers retracted •• The spoilers are retracted •• The ROLL INBD and ROLL OUTBD advisory lights go out • The ROLL SPLR INBD GND and ROLL SPLR OUTBD GND caution lights do not come on. When the FLIGHT/TAXI switch returns to FLIGHT that you observe the following indications: •• The PFCS spoiler indications show all the spoilers extended •• The spoilers are extended •• The ROLL INBD and ROLL OUTBD advisory lights come on •• The ROLL SPLR INBD GND and ROLL SPLR OUTBD GND caution lights do not come on
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-75
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-63-00 SPOILER PANELS
The PCUs that are attached to the inboard panels are supplied with hydraulic pressure from the No.1 hydraulic system.
Refer to Figure 27-47. Inboard and Outboard Spoiler Panels.
The PCUs that are attached to the outboard panels are supplied by the No.2 hydraulic system.
27 FLIGHT CONTROLS
All spoilers are flush mounted on the upper surface of the flap shroud, behind the wing rear spar. A spoiler actuator link connects the middle hinge attachment to the actuator on the spoiler PCU. The spoiler panels are flush with the wing top skin when retracted and extend upwards up to a maximum of 75° when operated.
2 1 3
4 LEGEND
6
1. Inboard Hinge Attachment. 2. Inboard Spoiler Panel. 3. Spoiler Actuator Link. 4. Middle Hinge Attachment. 5. Outboard Hinge Attachment. 6. Outboard Spoiler Panel.
5
D
FW
NOTE Left side shown. Right side similar. fs0c2a01.cgm
Figure 27-47. Inboard and Outboard Spoiler Panels
27-76
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-16-00 ROLL DISCONNECT SYSTEM
GENERAL
INTRODUCTION
When disconnected, the pilot control handwheel operates the spoiler control circuit and the co-pilot control handwheel operates the aileron control circuit. When connected, the control connected handwheels operate both circuits at the same time.
The roll disconnect system disengages the aileron and roll spoiler control circuits from each other in the event of a jam in either control circuit. The remaining operational circuit maintains roll control of the aircraft.
The roll disconnect system has the following components: •• Roll disconnect handle •• Roll disconnect lever assembly • Roll disconnect clutch mechanism.
2
1
FW
D
3
LEGEND 1. Roll Control Disconnect Handle. 2. Co-pilot's Control Column. 3. Cables. 4. Spring And Lever Assembly. 5. Roll Spoiler De-Clutch Micro-Switch. 6. Clutch Mechanism.
7
7. Lever Assembly Roll Disconnect.
6
4 5
ft175a01.cgm
Figure 27-48. Roll Disconnect System
FOR TRAINING PURPOSES ONLY
27-77
27 FLIGHT CONTROLS
Refer to Figure 27-48. Roll Disconnect System.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Roll Disconnect Handle Refer to Figure 27-49. Roll Disconnect Handle. The roll disconnect handle is used to operate the roll disconnect system. 27 FLIGHT CONTROLS
The roll disconnect handle is normally in the engaged position. The handle is connected to a clutch mechanism at the base of the co-pilot control column by cables, pulleys, and a springloaded lever assembly.
The roll disconnect mechanism is re-engaged when the pilots and co-pilot handwheels are moved to the same position, and the roll disconnect handle is rotated 90° and released. The spring on the clutch mechanism pulls the handle back to the engaged position. The handle pulls out 2 inches (5 cm) maximum from the center console.
The roll disconnect mechanism is disengaged when the roll disconnect handle is pulled to the stop and rotated by 90°. When the handle is pulled out to the limit and rotated 90°, the pin slides into the slot of the handle shaft to keep the handle locked in the disengaged position.
ROLL
DISC
ROLL
DISC
ENGAGED
DISENGAGED
FW
D CENTER CONSOLE
Figure 27-49. Roll Disconnect Handle
27-78
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Roll Disconnect Lever Assembly Refer to: •• Figure 27-48. Roll Disconnect System. • Figure 27-50. R oll Disconnect Lever Assembly. The roll disconnect lever assembly is used to gain mechanical advantage over the clutch mechanism. The roll disconnect lever assembly is located below the flight compartment floor near the base of the co-pilot control column. The lever assembly is attached by a cable to the roll disconnect handle. Another cable attaches the lever to the engagement spring cover of the clutch mechanism.
At the same time, the rotating lever assembly closes two microswitches which are a part of the roll spoiler advisory light circuit (refer to 27-60-00). A return spring attached to the lever assembly keeps the tension off the cable joining the lever assembly to the clutch mechanism. This prevents the clutch from accidentally disengaging and helps to return the roll disconnect handle to the engaged position.
When the roll disconnect handle is pulled, the lever assembly rotates and pulls the engagement spring cover, which causes the clutch to disengage.
1 2
LEGEND
3
1. Clutch Cable Plate. 2. Pivot Point. 3. Lever. 4. Rig Pin Index Hole. 5. Spring. 6. Microswitches.
FW
D 4 6 5
Figure 27-50. Roll Disconnect Lever Assembly
FOR TRAINING PURPOSES ONLY
27-79
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Roll Disconnect Clutch Mechanism Refer to Figure 27-51. Roll Disconnect Clutch Mechanism.
27 FLIGHT CONTROLS
The roll disconnect clutch mechanism disconnects the roll control of the co-pilot handwheel from the roll control of the pilot handwheel. The roll disconnect clutch mechanism is attached to the base of the co-pilot control column.
When clutch is engaged the chain in the co-pilot control column rotates the sprocket and clutch which drives the clutch plate and lever. The lever part of the clutch plate and lever assembly is attached to the pilot’s control column through the interconnect rod. When the roll disconnect handle is pulled and turned 90°, the clutch plate and lever is separated from the clutch and sprocket. The engagement spring keeps the clutch in the engaged position.
The roll disconnect clutch mechanism consists of an engagement spring, engagement spring cover and a clutch. The clutch is made up of two halves: •• Clutch and sprocket assembly • Clutch plate and lever assembly.
FW
D
1
FW
D 2
3
CO-PILOT CONTROL COLUMN LEGEND 1. Co-pilot Control Column Attachment. 2. Roll Disconnect Clutch Housing. 3. Clutch Mechanism Shaft. 4. Roll Control Lever. ft027a01.cgm
Figure 27-51. Roll Disconnect Clutch Mechanism
27-80
FOR TRAINING PURPOSES ONLY
4
MAINTENANCE TRAINING MANUAL
Interfaces Refer to: •• Figure 27-52. Aileron Forward Quadrant Microswitch (50°). • Figure 27-53. Spoiler Pushoff Switchlights. The roll disconnect system is interfaced with the roll spoiler advisory switchlights (SPLR1 and SPLR2).
When the roll disconnect microswitch and either side of the 50° switches is activated, the SPLR1 and SPLR2 PUSH OFF switchlights come on. Pushing the switchlights depressurizes the spoiler PCU causing the associated spoiler panels to retract flush with the wing surface. This will cause the caution lights to illuminate: 27 FLIGHT CONTROLS
DASH 8 Q400
•• ROLL SPLR INBD HYD • ROLL SPLR OUTBD HYD.
The SPLR1 and SPLR2 switchlights are located on the center glareshield panel. When the roll disconnect handle is pulled, two microswitches are closed by the roll disconnect lever assembly. When the co-pilot control handwheel is rotated more than 50°, the aileron quadrant closes the 50° travel microswitch. This microswitch is located on the aileron forward quadrant.
AILERON FORWARD QUADRANT
FWD
fs174a01.cgm
Figure 27-52. Aileron Forward Quadrant Microswitch (50°)
FOR TRAINING PURPOSES ONLY
27-81
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
GLARESHIELD PANEL
Spoiler 1 Push Off Switchlight
Spoiler 2 Push Off Switchlight
POWERED FLIGHT CONTROL SHUTOFFS
IAS
HSI SEL
Figure 27-53. Spoiler Pushoff Switchlights
fs285a01.cgm
27-82
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
RIGGING OF THE ROLL DISCONNECT SYSTEM
NOTES
27 FLIGHT CONTROLS
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Install rig pins in aileron and spoiler quadrants and disconnect lever assembly •• Push control columns fully fwd and hold •• Adjust cable tensions •• Pull control columns fully aft and hold •• Adjust cable tensions •• Pull ROLL DISC handle •• C h e c k f o r f u l l a n d f r e e r a n g e o f movement of control wheels •• Reset ROLL DISC handle.
OPERATIONAL CHECK OF THE ROLL DISCONNECT MECHANISM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Release the CONTROL LOCK lever to the OFF position •• Pull the ROLL DISC handle and turn it through 90° •• Make sure the control wheels can be turned independently •• Return the control wheels to their neutral positions •• Release ROLL DISC handle to the normal position •• Apply the GUST LOCK.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-83
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
3
4 2
5 6 7
1
LEGEND
8
1. Rudder Pedals. 2. Rudder Mixer Quadrant. 3. Rudder PCUs (2). 4. Trailing Rudder. 5. Fore Rudder. 6. Rudder Aft Quadrant. 7. Rudder Cables.
fs203a01.cgm
Figure 27-54. Rudder Control System
27-84
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-21-00 RUDDER SYSTEM
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The rudder system transmits the yaw commands from the pilot and co-pilot rudder pedals to the rudder control surfaces.
GENERAL Refer to Figure 27-54. Rudder Control System. Movement of the rudder pedals is transmitted to two hydraulic PCUs. The PCUs move the rudder in proportion to the amount of rudder pedal input. The rudder system also has inputs from the automatic flight control system (Yaw Damper) and the rudder trim actuator. The rudder system is comprised of the components listed below: •• Rudder pedals •• Rudder forward quadrants •• Rudder mixer quadrant •• Rudder restrictor •• Rudder aft quadrant •• Power control unit actuator •• Rudder shutoff valves •• PCU input bungee • Rudder position LVDT.
FOR TRAINING PURPOSES ONLY
27-85
27-86
DASH 8 Q400 MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
Figure 27-55. Rudder Control System Synoptic
27 FLIGHT CONTROLS
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION
NOTES
Refer to Figure 27-55. Rudder Control System Synoptic.
27 FLIGHT CONTROLS
There are two pairs of mechanically linked rudder pedals located in the flight compartment. Movement from either the pilot or co-pilot rudder pedals are transmitted simultaneously by two independent cable circuits to the mixer quadrant. From the mixer quadrant, a single cable circuit is routed aft and below the left side of the cabin floor. The cables pass through the pressure seals at the aft bulkhead, then up to the aft quadrant located behind the front spar of the vertical stabilizer. From the aft quadrant, a pushrod actuates two hydraulic PCUs through an artificial feel spring unit.
FOR TRAINING PURPOSES ONLY
27-87
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
6 4
5
7
3 2 1
LEGEND 1. Pedal Column. 2. Rudder Input Connecting Rod. 3. Pedal Adjustment Mechanism. 4. Rudder Pedals. 5. Rudder Control Interconnect Push Rod. 6. Brake Linkages. 7. Input Quadrant Connecting Rod. ft245a01.cgm
Figure 27-56. Rudder Pedals
27-88
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Rudder Pedals Refer to Figure 27-56. Rudder Pedals.
27 FLIGHT CONTROLS
The rudder pedals transmit inputs to the rudder control system and the main brake system. The rudder pedals are attached through levers below the flight compartment floor. Movement of the rudder pedals rotates the rudder forward quadrant. The pilot and co-pilot rudder pedals are connected through an interconnect rod. The rudder pedals are pivot-mounted to brackets below the flight compartment floor. A rudder pedal adjustment handle allows both fore and aft adjustment of the rudder pedals. Each adjustment handle is located on the pedestal between the pilot’s feet.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-89
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
B
A
A
4
RUDDER FORWARD ASSEMBLY
5 3
LEGEND
6
2
7
1 5
ft253a01.cgm
1. Rudder Restrictor Input Lever. 2. Rudder Restrictor. 3. 12 0 Stop. 4. Rudder Input Quadrant. 5. Travel Stop. 6. Mounting Bracket. 7. Rig Pin Hole. NOTE Right Side Shown.
B
Figure 27-57. Co-pilot’s Rudder Forward Quadrant
27-90
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Rudder Forward Quadrants Refer to Figure 27-57. Co-pilot’s Rudder Forward Quadrant. The rudder forward quadrants transmit rudder pedal inputs to the rudder mixer quadrant. Each rudder forward quadrant is located below the flight compartment floor and is attached to the aircraft by two mounting brackets. The co-pilot rudder quadrant has a rudder restrictor mechanism and a potentiometer. The restrictor limits rudder pedal movement to the rudder surface to deflect 12° each side of the aircraft center line. The potentiometer transfers rudder pedal movement to the nose wheel steering system.
ADJUSTMENT OF THE RUDDER PEDAL POSITION SENSOR The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. Refer to Figure 27-58. Download Unit - Hand Held Onsite FDR_Series 400. •• Energize the electrical system •• Make sure there are no FCECU faults on the ARCDU screen •• Connect the Hand Held Download Unit (HHDLU) to the FDR •• Put the aircraft in Weight Off Wheels condition •• Pressurize the hydraulic systems •• Move the FLAP LEVER to 15° position •• Put the HHDLU in decimal mode and make the appropriate selections •• Check the HHDLU figures at neutral and the other positions listed in the task
HA
ND
•• No adjustment is necessary if the HHDLU readings are correct.
HE
PA LD RT D SE NO. 9 OW NL RIA 64− DA L NO 0446 OAD . TE UN IT UN CODE IT : W E NO M V IGHT :4 OL L TA GE BS M PO A : 11 WE 5V X A MO R: 10 W OR 2 C 40 DS M 8 V HZ TA AC TU AX S 12
34
56
78
91
0
Figure 27-58. Download Unit - Hand Held Onsite FDR_Series 400
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-91
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Rudder Mixer Quadrant Refer to Figure 27-59. Rudder Mixer Quadrant. The rudder mixer quadrant combines rudder control from the two rudder forward quadrants and transmits it to the rudder aft quadrant. 27 FLIGHT CONTROLS
The rudder mixer quadrant consists of a threepulley quadrant installed below the cabin floor, aft of the turbine rotor burst zone. The two pairs of control cables are routed aft from the rudder forward quadrants to the upper two
pulleys of the mixer quadrant. These dual cables ensures continued rudder control if a single cable failure occurs . From the lower pulley of the mixer quadrant, a single pair of cables is routed aft and below the left side of the cabin floor. The cables pass through the pressurization seal at the rear pressure dome in the aft fuselage, then up to the rudder aft quadrant in the vertical stabilizer.
LEGEND 1. RH Forward Quadrant Control Cables. 2. RH Pulley Bracket. 3. Rig Pin Hole. 4. Rudder Mixer Quadrant. 5. LH Pulley Bracket. 6. Aft Rudder Quadrant Control Cables. 7. LH Forward Quadrant Control Cables.
A
2 3
1
4 5
6
7
ft206a01.cgm
A
Figure 27-59. Rudder Mixer Quadrant
27-92
FOR TRAINING PURPOSES ONLY
D
FW
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-93
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
FWD
RUDDER SYSTEM CONTROL VERTICAL STABILIZER
4 6
3
2 1
LEGEND 1. Push Rod. 2. Rudder Aft Quadrant. 3. Rig Pin Hole. 4. Mounting Brackets. 5. Mixing Quadrant Output Cables. 6. Primary Travel Stops.
D
FW
6 5
ft221a01.cgm
Figure 27-60. Rudder Aft Quadrant
27-94
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Rudder Aft Quadrant
left and right
The rudder aft quadrant transmits rudder control inputs from the mixer quadrant to the PCUs. The rudder aft quadrant is located halfway up the vertical stabilizer next to the two PCUs. The rudder aft quadrant has the primary travel stops for the rudder cable system.
RIG RUDDER PEDALS TO RUDDER FORWARD QUADRANT & RIG FORWARD QUADRANT TO RUDDER MIXER QUADRANT The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Remove input push rods to the left and right forward rudder quadrants •• Remove rudder inter-connect pushrod •• Install rigging pins in the left and right rudder output levers •• Install rigging pins in the left and right forward rudder quadrants •• Disconnect the rudder pedals potentiometer •• Rig the rudder pedals
•• Re-connect rudder pedal potentiometer •• Do an operational test of the rudder system.
RIGGING OF RUDDER MIXER QUADRANT TO THE RUDDER AFT QUADRANT The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Install the rigging pins in the rudder feel and trim unit, the rudder aft quadrant, the rudder mixer quadrant and the left and right forward rudder quadrants •• Move the FLAP LEVER to the 35° position •• Disconnect the pushrod from the rudder aft quadrant •• Check cable tensions observing wait times if new cables fitted •• Re-connect the pushrod to the rudder aft quadrant •• Remove all rigging pins •• Operate rudder pedals to full travel left and right •• Do an operational check of the rudder system.
•• Install input push rods to the left and right forward rudder quadrants and inter-connect pushrod •• Install rigging pins in the rudder mixer and aft quadrants •• Check cable tensions •• If new cables were installed follow TASK for wait times between initial and final tension adjustments •• Remove rigging pins •• Operate the rudder control system fully
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-95
27 FLIGHT CONTROLS
Refer to Figure 27-60. Rudder Aft Quadrant.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
RUDDER SYSTEM CONTROL VERTICAL STABILIZER
FWD
27 FLIGHT CONTROLS
2
10
3
4
1
5
FW
D
6
7 9 LEGEND
12
1. PCU Input Bungee. 2. Summing Bar. 3. Pressure Control Valve. 4. Upper PCU. 5. Main Control Valve. 6. Actuator Output Rod. 7. Rudder Connecting Rod. 8. Lower PCU. 9. Compensator. 10. Pressure Transducers. 11. Leak Detection Valves. 12. Compensator level Window (2).
8
11
ft224a01.cgm
Figure 27-61. Rudder Power Control Unit
27-96
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Power Control Units Refer to Figure 27-61. Rudder Power Control Unit. The PCUs transmit rudder inputs to the rudder surfaces. There are two PCUs, they are located above each other in the vertical stabilizer. The PCUs are attached to the fore rudder. The No.2 hydraulic system powers the upper PCU while the No.1 hydraulic system powers the lower PCU. Each PCU is composed of two major assemblies: •• Actuator (ram) assembly with a fully balanced ram • Integral hydraulic manifold assembly. The integral hydraulic manifold assembly contains the following items: •• Pressure port
Rudder Hinge Moment Limiting (HML) The left and right FCECU channels supply rudder Hinge Moment Limiting (HML) commands to the lower and upper rudder PCUs. The HML commands are based on airspeed signals from the Air Data Units (ADUs) 1 and 2. As the airspeed signals change, the FCECU uses the HML commands to regulate the pressure in each rudder Power Control Unit (PCU), by controlling the pressure control valve in the PCU. As airspeed increases, the regulated PCU pressure decreases to reduce total rudder travel at higher airspeeds. The FCECU also receives pressure signals from two pressure sensors located in each PCU. This lets the FCECU monitor the regulated PCU pressure for any failure modes. If a pressure failure occurs, the FCECU commands the rudder PCU shutoff valve to depressurize the PCU and the RUD1 HYD or RUD2 HYD caution lights come on. If No.1 and No.2 hydraulic systems fail the FCECU will cause the RUD CNTRL caution light to come on.
•• Inlet check valve •• Main Control Valve (MCV) •• Pressure Control Valve (PCV) •• Compensator •• Leak detection valve •• Anti-cavitation check valves (2) •• Pressure reference relief valves (2) • Pressure transducers (2).
FOR TRAINING PURPOSES ONLY
27-97
27 FLIGHT CONTROLS
DASH 8 Q400
27-98
Figure 27-62. Rudder PCU Schematic
MAINTENANCE TRAINING MANUAL
COMPENSATOR LEVEL WINDOW FOR TRAINING PURPOSES ONLY
DASH 8 Q400
CENTERING
27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
Refer to: •• Figure 27-62. Rudder PCU Schematic. •• Figure 27-63. R udder PCU Fluid Compensator. The pressure port supplies system hydraulic pressure to the inlet check valve and then to the PCV. The PCV regulates the control pressure as a function of airspeed. The mechanically operated four-way MCV positions the actuator ram. Position feedback is done by a mechanical linkage (summing bar), which compares the commanded ram position with the actual position. Input from the pilot or yaw damper causes the four-way MCV to reposition the ram towards the commanded position. Movement of the ram (and the rudder) stops when the actual ram position is the same as the commanded position nulled by the summing bar. The compensator stores 50 psi in a spring loaded accumulator for use by the PCU in the event of loss of supply pressure to the PCU. This aids in maintaining flutter suppression. The two PCU compensators also perform gust damping when the PCUs are depressurized. A level check window indicates the amount of fluid stored in the compensator.
The return fluid from the failed PCU is c ir c ula te d thr ough the MC V a nd t h e compensator to avoid fluid escape from a failed PCU when driven from the serviceable PCU. Two pressure reference relief valves limit the PCU pressure to 3200 psi. Also, the pressure reference relief valves will crack at 2-8 psi in the event of a MCV jam with the PCU depressurized. Thus allowing a jammed PCU to bypass and be back-driven by the functioning PCU. The two pressure transducers supply PCV HML pressure feedback signals to the FCECU.
A LEAK DETECTION VALVE END CAP
The compensation level window shows green or red if it does not stay pressurized after hydraulic system depressurized. The leak detection valve detects unacceptable PCU internal leakage. The leak detection valve incorporates a 50 psi relief valve to prevent the PCU hydraulic fluid from escaping during a loss of supply pressure. The leak detector valve is checked for open or short with hydraulic systems pressurized indicating leaks. The two anti-cavitation check valves prevent actuator cavitation when one PCU is depressurized. The anti-cavitation valves crack at 2-8 psid to allow the serviceable PCU to overcome the failed unit.
A
FW
D
PCU FLUID COMPENSATOR
FLUID COMPENSATOR VISUAL LEVEL INDICATOR pb529a01.cgm 16 Apr 01
Figure 27-63. R udder PCU Fluid Compensator
FOR TRAINING PURPOSES ONLY
27-99
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Rudder Shut-off Valves Refer to Figure 27-64. Rudder Shut-off Valve. The Rudder Shut-off Valves (SOV) supply hydraulic system pressure to the rudder PCU.
27 FLIGHT CONTROLS
Each rudder PCU is equipped with a rudder SOV to shut down the PCU. The rudder SOVs are located on the vertical stabilizer rear spar below the rudder PCU. Each of the two FCECU channel controls its SOV open and close.
If a PCU pressure regulation failure is detected, the FCECU will command zero pressure to the PCU pressure control valve and command the associated rudder SOV to close. The rudder Push Off switchlight(s) also commands the FCECU to actuate the rudder SOV. De-energized, the rudder SOV de-pressurizes its PCU by porting return pressure to the PCU pressure port for flutter suppression. In the event of complete loss of electrical power on the aircraft, the Rudder SOVs will close.
5
4 RUDDER SHUT-OFF VALVES
FW
D
2
FW
1
D
3 LEGEND
NOTE
1. Solenoid. 2. Electrical Connector. 3. Hydraulic Port Return. 4. Mounting Bracket. 5. Hydraulic Pressure Port.
Left side shown. Right side similar.
fss69a01.cgm
Figure 27-64. Rudder Shut-off Valve
27-100
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-101
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
RUDDER CONTROLS - VERTICAL STABILIZER
FWD
LEGEND 1. Motion Detector Limit Switch. 2. Motion Detector Linkage. 3. Motion Detector Cam Arm. 4. Spring Strut. 3
D
1
FW
2
4 ft214a01.cgm
Figure 27-65. Rudder PCU Input Bungee
27-102
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
PCU Input Bungee Refer to Figure 27-65. Rudder PCU Input Bungee. The PCU input bungees transmit rudder system control feel unit assembly inputs to the rudder PCU. There are two PCU input bungees, one for each rudder PCU. Each PCU input bungee has a spring strut and a motion detector. Each spring strut is installed between the feel unit assembly and its related PCU summing bar. A spring strut motion detector is installed parallel to each spring strut, and has a cam arm, link, and limit switch. During normal operation, each spring strut length stays constant. In the event of a PCU jam or its linkage, any pilot input to the rudder aft quadrant causes an inner spring in the strut to either stretch or compress.
•• Move the sum bars of the upper and lower PCUs forward and aft and check clearances between the switch rollers and the microswitches Observe electrical, hydraulic and moving surfaces warnings •• Connect external DC ground power •• Pressurize No.1 and No.2 hydraulic systems •• Move the sum bars on the PCUs forward and backward checking that the RUD1 and RUD2 PUSH OFF switchlights come ON, and go OFF when the sum bars are in neutral positions •• Make sure that the rudder movement is not greater than 2.5 inches from the rigging point, when moving the sum bars from neutral •• Remove hydraulic and electrical power.
The change in strut length causes the motion detector cam arm to trigger the limit microswitch. The microswitch causes the RUD1 or RUD2 PUSH OFF switchlight on the glareshield panel to illuminate.
RIGGING OF THE UPPER SPRING STRUT MOTION DETECTOR & RIGGING OF THE LOWER SPRING STRUT MOTION DETECTOR The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Adjust the microswitches on the motion detectors to set the switch rollers in the center of the cams •• Make sure that the RUD1 and RUD2 PUSH OFF switchlights do not come on
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-103
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Rudder Position LVDT Refer to Figure 27-66. Rudder Position LVDT. The rudder position LVDT supplies an electrical signal, which is equivalent to the angular position of the rudder to the FCECU. 27 FLIGHT CONTROLS
A rudder position LVDT is located in the vertical stabilizer.
RUDDER POSITION LVDT ASSEMBLY
FWD
FW
D
fs202a01.cgm
Figure 27-66. Rudder Position LVDT
27-104
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Controls and Indications Refer to Figure 27-67. Rudder Position on MFD.
A white rudder position indicator displays against a white scale on MFD1. MAIN INSTRUMENT PANEL
WX OFF
FMS1 076 00
057
HDG 073°
E
3
160
VIE
35.0 NM --:--
VCF
YSO
00 ---
TAS 20 GS 0
YCF
80
TCAS STBY
ADF1 DME1 H 92.1 NM
ADF2 DME2 92.1 NM
I
I
Rudder Position Indication.
Figure 27-67. Rudder Position on MFD
FOR TRAINING PURPOSES ONLY
27-105
27 FLIGHT CONTROLS
The rudder position LVDT transmits the rudder position data to the PFCS indicator on MFD1 and to the FDR.
DASH 8 Q400
OVERHEAD CONSOLE
MAINTENANCE TRAINING MANUAL
#1 Rudder Hydraulic Pressure
#2 Rudder Hydraulic Pressure
ROLL SPLR INBD GND
#1 STALL SYST FAIL #2 STALL SYST FAIL
27 FLIGHT CONTROLS
ROLL SPLR INBD HYD
#2 HYD FLUID HOT
FLAP DRIVE
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING
FUELING ON
MAIN BAT HOT
GLARESHIELD PANEL
RUD 1 Push Off Switchlight.
RUD 2 Push Off Switchlight.
POWERED FLIGHT CONTROL SHUTOFFS
IAS
HSI SEL
Figure 27-68. Rudder Push Off Switchlights
27-106
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-68. Rudder Push Off Switchlights.
Obey all electrical and hydraulic safety precautions and warnings.
When the PCU input bungee limit microswitch has been made, the applicable RUD1 or RUD2 rudder switchlight on the glareshield panel comes on. The PUSH OFF switchlight warns of the jammed condition. The switchlight is pushed to depressurize the jammed system. The illuminated switchlight then shows OFF.
Configure the aircraft as follows:
The switchlights interfaces with the FCECU and are centrally located on the glareshield. Pushing either PUSH OFF switchlight causes the FCECU to command zero pressure in the rudder PCU and also cause the rudder shut off valve to close. The FCECU inhibits both RUD PUSH OFF switchlights from being manually actuated OFF at the same time.
•• PLA 1 and PLA 2 to 80%
Low hydraulic pressure causes the related No.1 RUD HYD or No.2 RUD HYD caution light to come on. The No.1 or No.2 RUD HYD caution light comes on for the following: • Hydraulic system pressure is < 350 +/-50 psi (2413 +/-344.7 kPa) The RUD CNTRL caution light comes on for any of the following: •• FCECU detects a difference of 17 knots or more between the Airspeed 1 and Airspeed 2 from the air data units •• F C E C U l o s e s i t s a b i l i t y t o l i m i t hydraulic pressure •• Both hydraulic systems fail. • Interfaces.
•• Put the aircraft in WOFFW mode •• ADC 1 and ADC 2 to 50kts •• Flap lever to 15° •• Flight/Taxi switch to Flight •• Energize the electrical system •• P r e s s u r i z e t h e h y d r a u l i c s y s t e m s (3000 psi) •• Install rigging pins in the aft quadrant and the feel unit rigging plate •• Push RUD1 PUSH OFF switchlight observe No.1 RUD HYD caution light ON •• Adjust upper spring bungee to center aft rudder on rigging mark •• Push RUD1 PUSH OFF switchlight observe No.1 RUD HYD caution light OFF •• Repeat procedure operating RUD No.2 PUSH OFF •• Safety rod ends of upper and lower spring bungees •• Repeat the operation of RUD1 and RUD2 PUSH OFF switchlights •• Observe correct operation of RUD1 and RUD2 HYD caution lights •• Observe trailing rudder is within tolerance of the rigging mark •• Remove rigging pins
RIGGING OF RUDDER PCUS WITH HYDRAULIC POWER
•• Do operational check of rudder systems.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-107
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL TEST OF THE RUDDER SHUTOFF VALVES
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. 27 FLIGHT CONTROLS
Refer to Figure 27-75. Rudder SOV Hydraulic Schematic. •• Energize the electrical system. •• Pressurize No.1 and No.2 hydraulic systems. •• Make sure the rudder pedals and rudder surfaces are in neutral positions. •• Push RUD1 PUSH OFF switchlight, make sure it shows the word OFF.
NOTE Lower rudder PCU goes into bypass mode, pressure control valve closes, rudder SOV remains open. •• Make sure No.1 RUD HYD caution light comes ON. •• Open and tag C.B. RIGHT DC L6 FCS ECU2 •• NOTE. The FCECU 2 will close the rudder SOV and the pressure control valve for the upper rudder actuator. The actuator will now be hydraulically locked. •• Make sure the ELEVATOR FEEL, PITCH TRIM and ELEVATOR ASYMMETRY caution lights come ON. The No.2 RUD HYD caution may come ON momentarily. •• Make sure that you cannot manually push the rudder to the right or left. •• If the rudder can be manually moved the upper rudder SOV has failed open, and must be replaced. •• Remove the tag and close the C.B. •• Repeat the above for the other rudder SOV. 27-108
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-109
DASH 8 Q400
RUD LIM RT EHV HI B RUD LIM RT EHV LO E
MAINTENANCE TRAINING MANUAL
3 HI RUD LIM RT EHV 11 LO RUD LIM RT EHV
27 FLIGHT CONTROLS
RUD LIM RT 1 DELTA P LO RUD LIM RT 1 DELTA P CT RUD LIM RT 1 DELTA P HI RUD LIM RT 1 EXC HI RUD LIM RT 1 EXC LO
1 5 4 2 3
4 12 13 6 5
LO RUD LIM RT 1 DELTA P CT RUD LIM RT 1 DELTA P HI RUD LIM RT 1 DELTA P HI RUD LIM RT 1 EXC LO RUD LIM RT 1 EXC
RUD LIM RT 2 EXC HI RUD LIM RT 2 EXC LO RUD LIM RT 2 DELTA P LO RUD LIM RT 2 DELTA P CT RUD LIM RT 2 DELTA P HI
2 3 1 5 4
15 7 14 23 24
HI RUD LIM RT 2 EXC LO RUD LIM RT 2 EXC LO RUD LIM RT 2 DELTA P CT RUD LIM RT 2 DELTA P HI RUD LIM RT 2 DELTA P
ADU 2 LO 27 HI 38
UPPER RUDDER PRESSURE CONTROL SERVO VALVE
RUD LIM 2 UP EXC HI A RUD LIM 2 UP EXC LO C
88 HI RUD LIM 2 UP EXC 80 LO RUD LIM 2 UP EXC
UPPER RUDDER SHUTOFF VALVE RUD LIM LT 1 EHV HI 3 RUD LIM LT 1 EHV LO 11
B HI RUD LIM LT 1 EHV E LO RUD LIM LT 1 EHV
RUD LIM LT 1 DELTA P HI RUD LIM LT 1 DELTA P CT RUD LIM LT 1 DELTA P LO RUD LIM LT 1 EXC HI RUD LIM LT 1 EXC LO
13 12 4 6 5
4 5 1 2 3
LO RUD LIM LT 1 DELTA P CT RUD LIM LT 1 DELTA P HI RUD LIM LT 1 DELTA P HI RUD LIM LT 1 EXC LO RUD LIM LT 1 EXC
RUD LIM LT 2 EXC HI RUD LIM LT 2 EXC LO RUD LIM LT 2 DELTA P LO RUD LIM LT 2 DELTA P CT RUD LIM LT 2 DELTA P HI
15 7 14 23 24
2 3 1 5 4
HI RUD LIM LT 2 EXC LO RUD LIM LT 2 EXC LO RUD LIM LT 2 DELTA P CT RUD LIM LT 2 DELTA P HI RUD LIM LT 2 DELTA P
LOWER RUDDER PRESSURE CONTROL SERVO VALVE
ADU 1 27 LO 38 HI
RUD LIM LO SOV HI 88 RUD LIM LO SOV LO 80
A HI RUD LIM LO SOV C LO RUD LIM LO SOV
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU) LOWER RUDDER SHUTOFF VALVE
Figure 27-69. FCECU Rudder Inputs and Outputs
27-110
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATION
NOTES
Normal System Operation Refer to Figure 27-69. FCECU Rudder Inputs and Outputs.
27 FLIGHT CONTROLS
When the FCECU is powered, it energizes open the upper and lower Rudder SOVs. The pressure control servo valves in the PCUs are used by the FCECU to control the pressure supplied to the actuators. The lower rudder servo valve gets inputs from the FCECU as follows: •• From Pins 3 and 11 The upper rudder servo valve gets inputs from the FCECU as follows: •• From Pins 3 and 11 As the airspeed increases, the FCECU decreases the hydraulic pressure providing Hinge Moment Limiting (HML). Airspeed inputs to the FCECU from the ADUs are at the connections that follow: •• ADU1 at Pins 27 and 38 • ADU2 at Pins 27 and 38.
FOR TRAINING PURPOSES ONLY
27-111
27 FLIGHT CONTROLS
27-112 POWERED
SPLR 2
PUSH
PUSH
OFF
OFF
OFF
VS
(E7)
P/J177 L
RUD SYS ISOL
ON
PUSH B
A
A
C
A
D
RUD 2 PUSH OFF
HDG
AP
U/F FWD FUSE
VERT STAB
NAV
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
S3
LEFT DC C/B PNL 24-61-00
NOSE UP
SHUTOFFS
J/P2 HI 45 LO 34 HI 55 CT 44 LO 33
P/J18 1 HI 2 LO 3 HI 4 CT 5 LO
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
DASH 8 Q400
2A
CONTROL
SPLR 1
PUSH
IAS
+28 V DC L MAIN BUS
FLIGHT
RUD 1
G F A
A
H3
H1 J2
J3
J1 K2
L2
3313P/J1 15
NC NO
L3
L1 3313J/P2 15
FORE RUDDER
K3
K1
RH CB CONS
MAINTENANCE TRAINING MANUAL
J/P177 J
CR6
AFT RUDDER
P/J1 32 LEFT RUDDER SHUT-OFF
RUD 1 PUSH OFF SW G
S3 S5
LOWER SPRING BUNGEE JAM SW
PUSH 16
VERTICAL STAB
P/J176 H F
B
A
A
C ON
G
#1 RUDDER HYD CAUTION LT
J/P1 63
F NC
16
NO
A
ACU 31-57-00
UPPER SPRING BUNGEE JAM SW
H1 J2
POWER CONTROL UNIT [PCU(2)]
FORE RUDDER TRAILING RUDDER
J1 K2 K1 L2 L1
HYDRAULIC PRESSURE PCU SUMMING LINK (2) PCU INPUT BUNGEE (2)
A
A
D
OFF H2
S4
H3
J/P2 RUDDER PRESSURE CAUTION LT 43 #2 RUDDER HYD CAUTION LT 63
OFF
J3
CAUTION AND WARNING PANEL (OH CONSOLE) 31-51-00
K3
L3
CR7
J/P176 K
P/J2 32 RIGHT RUDDER SHUT-OFF
RUD 2 PUSH OFF SW
GLARESHIELD PANEL (FLIGHT COMPARTMENT)
3312P/J5 6 #1 RUD HYD 25 RUD PRESSURE 28 #2 RUD HYD
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
Figure 27-70. Rudder Control System - Electrical Schematic
d4s272100_a_003.dg, pg, apr30/2007
FOR TRAINING PURPOSES ONLY
H2
VERTICAL STAB
RUDDER POSITION LINEAR VARIABLE DIFFERENTIAL TRANSFORMER (LVDT)
OFF
OFF
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-70. Rudder Control System - Electrical Schematic.
OPERATIONAL TEST OF THE RUDDER CONTROL SYSTEM
The pressure sensing transducers send delivery pressure information back to the FCECU. The FCECU knows what pressure it has commanded and, with the feedback from the transducers, knows the actual pressure being delivered from the pressure control servo valve.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
Rudder movement is monitored by a LVDT. The FCECU provides the excitation (pins 34 and 45) to the LVDT (pins 1 and 2). The LVDT supplies an electrical signal (from pins 3, 4 and 5), equivalent to the angular position of a flight control surface to the FCECU (pins 33, 44 and 55). The FCECU transmits the rudder position data to the IFC to display the position of the rudder on the PFSCI. Another signal is also sent to the FDR.
Obey all electrical safety precautions and warnings. •• Energize the electrical system •• Pressurize No.1 hydraulic system •• Lower the flaps to 50 •• Push the rudder pedals fully left and right •• Make sure the MFD PFCS indicator shows full travel •• Verify full travel by visual check of rudder positions •• Operate rudder pedal adjustment to the full forward and full aft positions and check full rudder travel •• De-pressurize No.1 hydraulic system •• Pressurize No.2 hydraulic system and repeat checks.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-113
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-114 POWERED
SPLR 2
PUSH
PUSH
OFF
OFF
OFF
VS
(E7) RUD SYS ISOL
L
PUSH B
RUD 2 PUSH OFF
HDG
AP
NAV
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
S3 ON
LEFT DC C/B PNL
NOSE UP
SHUTOFFS
C
HI LO HI CT LO
45 34 55 44 33
1 2 3 4 5
HI LO HI CT LO
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
G F A H2
H3
H1 J2
J3
J1 K2
FORE RUDDER
K3
K1 L2
L3
L1
J
CR6
AFT RUDDER
32 LOWER RUDDER SHUT-OFF
RUD 1 PUSH OFF SW
NC
15
NO
15
G
S1 S5
LOWER SPRING BUNGEE JAM SW
PUSH 16
B
H F
A
A
C ON
G
#1 RUDDER HYD CAUTION LT
63
F NC
A
16
NO
H1
ACU
UPPER SPRING BUNGEE JAM SW
J2
POWER CONTROL UNIT [PCU(2)]
J1
FORE RUDDER
K2
TRAILING RUDDER
K1 L2 L1
HYDRAULIC PRESSURE PCU SUMMING LINK (2)
A
A
D
OFF H2
S2
H3
OFF
RUDDER PRESSURE CAUTION LT 43 #2 RUDDER HYD CAUTION LT 63
J3
CAUTION AND WARNING PANEL
K3
L3
CR7
K
32 UPPER RUDDER SHUT-OFF
RUD 2 PUSH OFF SW
GLARESHIELD PANEL
6 #1 RUD HYD 25 RUD PRESSURE 28 #2 RUD HYD
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
PCU INPUT BUNGEE (2)
Figure 27-71. Lower Rudder Control Jam Indicated
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RUDDER POSITION LINEAR VARIABLE DIFFERENTIAL TRANSFORMER (LVDT)
D OFF
OFF
DASH 8 Q400
2A
CONTROL
SPLR 1
PUSH
IAS
+28 VDC L MAIN BUS
FLIGHT
RUD 1
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Abnormal Operation
NOTES
Refer to Figure 27-71. Lower Rudder Control Jam Indicated.
Rudder Jam
FOR TRAINING PURPOSES ONLY
27 FLIGHT CONTROLS
A jam of the PCU servo valve causes the input bungee to change length. This is detected by the motion detector and closes switch S3 or S4 providing a ground to the RUD1 or RUD2 switchlight.
27-115
27 FLIGHT CONTROLS
27-116 POWERED RUD 1
OFF
IAS
VS
FLIGHT SPLR 1
CONTROL
SHUTOFFS
SPLR 2
RUD 2
PUSH
PUSH
PUSH
OFF
OFF
OFF
NOSE UP
HDG
NAV
2A
RUD SYS ISOL
L
PUSH
ON
LEFT DC C/B PNL
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
S3 B
A
A
C
A
D
HI LO HI CT LO
45 34 55 44 33
1 2 3 4 5
HI LO HI CT LO
RUDDER POS'N EXC RUDDER POS'N EXC RUDDER POSITION RUDDER POSITION RUDDER POSITION
G F A
RUDDER POSITION LINEAR VARIABLE DIFFERENTIAL TRANSFORMER (LVDT)
OFF H2
H3
H1 J2
J3
J1 K2
FORE RUDDER
K3
K1 L2
L3
L1
J
CR6
AFT RUDDER
32 LOWER RUDDER SHUT-OFF
RUD 1 PUSH OFF SW
NC
15
NO
15
G
S1 S5
LOWER SPRING BUNGEE JAM SW
PUSH 16
B
H F
A
A
C ON
G
#1 RUDDER HYD CAUTION LT
63
F NC
A
16
NO
ACU
UPPER SPRING BUNGEE JAM SW
H1 J2
POWER CONTROL UNIT [PCU(2)]
J1
FORE RUDDER
K2
TRAILING RUDDER
K1 L2 L1
HYDRAULIC PRESSURE PCU SUMMING LINK (2)
A
A
D
OFF H2
S2
H3
OFF
RUDDER PRESSURE CAUTION LT 43 #2 RUDDER HYD CAUTION LT 63
J3
CAUTION AND WARNING PANEL
K3
L3
CR7
K
32 UPPER RUDDER SHUT-OFF
RUD 2 PUSH OFF SW
GLARESHIELD PANEL
6 #1 RUD HYD 25 RUD PRESSURE 28 #2 RUD HYD
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
PCU INPUT BUNGEE (2)
Figure 27-72. Rudder 1 PUSH OFF Switch Pushed
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
A OFF
DASH 8 Q400
(E7) +28 VDC L MAIN BUS
MAINTENANCE TRAINING MANUAL
Lower Rudder PCU Jam Operation
ADU Failure
Refer to Figure 27-72. Rudder 1 PUSH OFF Switch Pushed.
Should the FCECU detect that an ADU has failed, or that there is a difference of greater than 17 knots between the two ADUs , then the FCECU will determine the data is invalid.
The Pilot pushes the RUD1 switchlight to de-energize the shutoff valve and remove the hydraulics from the failed PCU. The No.1 RUD HYD caution light illuminates.
If airspeed is invalid the rudder hydraulic pressure will default to 700 psi.
The HML will double the rudder pressure to the remaining PCU.
Hydraulic Failure With failure of either No.1 or No.2 hydraulic systems, the FCECU de-energizes the rudder, SOV, causing it to close, and sets the pressure control valve of the failed system to zero pressure. The failure will cause a No.1 RUD HYD or a No.2 RUD HYD caution light to illuminate. At the same time, the FCECU increases the pressure to the active PCU to compensate for the loss. The rudder control system will continue to operate if one PCU fails. Failure of both rudder hydraulic systems will cause the three caution lights No.1 RUD HYD, No.2 RUD HYD and RUD CTRL to illuminate. The aircraft will fly without rudder control and the rudder compensator will prevent the rudder from fluttering.
FCECU Failure A failure of a single FCECU channel will de-energize the related rudder shut-off valve and the other system will continue to operate at twice the normal pressure. The pilot indication will be the associated No.1 RUD HYD or a No.2 RUD HYD caution light illuminated. A failure of both FCECU channels closes both rudder SOVs and rudder control is lost. The following caution lights will illuminate: •• No.1 RUD HYD •• No.2 RUD HYD • RUD CTRL FOR TRAINING PURPOSES ONLY
27-117
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-73. RUD CTRL Caution Light. If airspeed and flap position are invalid, the hydraulic pressure will default to 1225 psi. The RUD CTRL caution light illuminates if: 27 FLIGHT CONTROLS
•• FCECU detects a difference of 17 knots (37.06 km/h) or more between the Airspeed 1 and Airspeed 2 from the air data units •• F C E C U l o s e s i t s a b i l i t y t o l i m i t hydraulic pressure • Both hydraulic systems fail.
OVERHEAD CONSOLE
Rudder Control
ROLL SPLR INBD GND
#1 STALL SYST FAIL #2 STALL SYST FAIL
ROLL SPLR INBD HYD
#2 HYD FLUID HOT
FLAP DRIVE
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING MAIN BAT HOT
Figure 27-73. RUD CTRL Caution Light
27-118
FOR TRAINING PURPOSES ONLY
FUELING ON
MAINTENANCE TRAINING MANUAL
27-22-00 RUDDER FEEL AND SUMMING INTRODUCTION The rudder feel and summing unit transmits rudder system artificial feel to the rudder pedals and biases the complete rudder system during rudder trimming or yaw damping. The rudder system is a powered flight control, the unit is used to prevent the pilot from overcontrolling the aircraft in flight.
GENERAL Refer to Figure 27-74. Rudder Feel and Summing System Block Diagram. Rudder pedal feel is artificially produced by feel springs on the rudder feel and summing unit. The rudder feel and summing unit mechanically transmits rudder system commands to the rudder PCUs. The rudder feel and summing system has the following components: •• Trim actuator •• Rudder feel and summing unit •• Summing yaw damper actuator •• Rudder trim switch • Rudder trim indicator.
RUDDER TRIM SWITCH & INDICATOR
TRIM ACTUATOR
RUDDER PEDALS (PILOT & CO-PILOT)
RUDDER FEEL & SUMMING UNIT
RUDDER
SUMMING -YAW DAMPER ACTUATOR FGM 1 & FGM 2 fst11a01.cgm
Figure 27-74. Rudder Feel and Summing System Block Diagram
FOR TRAINING PURPOSES ONLY
27-119
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-120 POWER CONTROL UNIT [PCU(2)]
TRIM ACTUATOR
CO-PILOT'S PEDALS
FORE RUDDER TRAILING RUDDER +36¡
+18¡
0¡ -36¡
-18¡
HYDRAULIC PRESSURE
PILOT STATURE ADJUSTMENT
PCU SUMMING LINK (2) RUDDER AFT QUADRANT
YAW DAMPER SUMMING ARM
PCU INPUT BUNGEE (2)
RUDDER MIXER QUADRANT
RUDDER FORWARD QUADRANTS
NOTE
FORCE APPLIED PILOT'S PEDALS
1
Hydraulic pressure reduces with speed to limit Hinge Moment.
2
Trailing Rudder moves twice as far as the Fore Rudder.
fs277a01.cgm
Figure 27-75. Rudder Control System Synoptic
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
YAW DAMPER ACTUATOR
DASH 8 Q400
FEEL SPRING (DUAL RATE)
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to: • Figure 27-75. R udder Control System Synoptic. •• Figure 27-76. R udder Trim Switch and Indicator. 27 FLIGHT CONTROLS
The rudder trim switch is located on the center console. Turning the RUDDER trim switch fully to the left (L) or right (R) gives trim at a high rate. When the switch is turned to the first graduation line, a slower trim rate is given. The trim actuator can move the rudder surface a maximum of 10°. The rudder trimmed position is shown on the RUDDER trim indicator. Rudder trim indication is transmitted by the trim actuator’s integral LVDT. The LVDT signal is also transmitted to the IFC FDR. If the LVDT fails, the trim actuator stays functional but no trim position is shown on the RUDDER trim indicator.
AIL I
TRIM
TRIM
Rudder Trim Indicator
CENTER CONSOLE
AILERON
Rudder Trim Switch
FW
D
Figure 27-76. Rudder Trim Switch and Indicator
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-121
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Trim Actuator Refer to Figure 27-77. Rudder Trim Actuator.
27 FLIGHT CONTROLS
The trim actuator transmits linear movement to the rudder feel and summing unit to bias the rudder control system for yaw deviations. The trim actuator is attached to the mid-spar of the vertical stabilizer and connected at the rear with two trim arms, that form part of the summing unit. The trim actuator has a DC motor which extends and retracts the actuator. If the actuator extends to its limit, the extend limit switch disconnects power to the motor. The trimming system is powered from the left essential bus, through two circuit breakers, RUD TRIM ACT F7 for the trim actuator and RUD TRIM IND G7 for the RUDDER trim indicator.
OPERATIONAL TEST OF THE RUDDER TRIM SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Energize the external DC power system •• Pressurize No.1 and No.2 hydraulic systems •• Move the rudder fully left and right 3 times stopping in the neutral position •• Turn the rudder trim switch fully left and right •• Make sure trim indicator shows full deflections and neutral when the switch is neutral • Remove hydraulic power and DC electrical power.
FWD
RUDDER CONTROLS - VERTICAL STABILIZER
D
FW
fs252a01.cgm
Figure 27-77. Rudder Trim Actuator
27-122
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
Rudder Feel and Summing Unit Refer to Figure 27-78. Rudder Feel and Summing Unit. The rudder feel and summing unit gives artificial feel to the pilots when operating the rudder pedals. The rudder feel and summing unit is installed in series with the rudder control system.
The springs are attached to the feel unit arms at the actuator end, rotation of the shaft actuating arms extends the spring in the direction of rotation while the opposite spring is unaffected. This gives the pilot artificial feel of loading on the rudder pedals. During trimming, the feel springs and trim arms move together.
The rudder feel and summing unit has two feel springs attached to a summing bar that is connected to the rudder hydraulic PCUs.
FWD
RUDDER CONTROLS - VERTICAL STABILIZER 1
2 3
FW
D
4
LEGEND 1. Rudder Trim Actuator. 2. Trim Arms. 3. Feel Springs. 8 4. Summing Bar. 5. PCU Bungee Attachment Points. 6. Quadrant Push Rod Attachment Point. 7. Yaw Damper Attachment Point. 8. Mounting Frame.
5
7 6 ft208a01.cgm
Figure 27-78. Rudder Feel and Summing Unit
FOR TRAINING PURPOSES ONLY
27-123
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Summing-Yaw Damper Actuator Refer to Figure 27-79. Yaw Damper. The summing-yaw damper actuator transmits small inputs to the Rudder Feel Summing Unit (RFSU) to compensate for yaw oscillations in flight. 27 FLIGHT CONTROLS
The yaw damper is a linear servo actuator installed between the rudder aft quadrant and the summing arm. The yaw damper supplies small rudder deflections to compensate for yaw oscillations in flight. Yaw damper authority is 4.5° either side of center. The yaw damper has its own summing arm, which mechanically transmits any yaw damper inputs on to the rudder feel and summing unit.
FW
D
fs251a01.cgm
RUDDER CONTROL SYSTEM VERTICAL STABILIZER
Figure 27-79. Yaw Damper
27-124
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-125
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
RUDDER TRIM ROTARY SWITCH (SLOW TRIM) T
RUDDER TRIM INDICATOR RUDDER TRIM IND
C
27 FLIGHT CONTROLS
PNL LTS H lV (5V LTC) C lV II II
RUDDER TRIM ACTUATOR
T
4B 3F
LT SYS (5V DC)
SHLD
B
RUDDER TRIM ACTUATOR 1
2 3
11 RUDDER LEFT
C
28 VDC LEFT ESS R4 R3 15.0 10.0
A 4
R2 15.0
R1 10.0
172 50 EXT
E F D
T
A B D E
IFC1
SHLD
28 VDC LEFT ESS
T
SHLD F G H
HI (EXT 15 L) Vl WIPER Vl LO Vl (RET 15 R)
AVIONICS RACK
1750 50 RET HALL LIMIT SWITCH EXT
CASE
A
HALL LIMIT SWITCH RET
MOTOR CONTROLLER ELECTRONICS
M
D2
5 D1
6 7
IV 8
B
9
11 RUDDER RIGHT
10
RUDDER TRIM ROTARY SWITCH (RAPID TRIM)
B
RUDDER TRIM ACTUATOR 1
28 VDC LEFT ESS R4 R3 15.0 10.0
2
A 11 RUDDER LEFT
3 4
R1 10.0
R2 15.0
C A
M
D2
D1 IV 8
B
MOTOR CONTROLLER ELECTRONICS
5 6 7
11 RUDDER RIGHT
CASE
28 Vdc 5 Vdc
9
Ground
10
fst02a02a.cgm
Figure 27-80. Rudder Trim Switch/Indicator Schematic
27-126
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
RUDDER TRIM OPERATION
NOTES
Refer to Figure 27-80. Rudder Trim Switch/ Indicator Schematic.
Rudder Trimming 27 FLIGHT CONTROLS
When the rudder trim switch is selected fully to ‘L’ for rapid trim, power is directed by the rudder trim switch from the 28 VDC left essential bus through a normally closed extend limit switch to provide power to drive the actuator in an extend direction rapidly. If the actuator is extended to its limit, the extend limit switch is opened to disconnect power to the motor and connect the motor to a common ground. When the rudder trim switch is selected to the mid graduation L line for slow trim, reduced voltage is directed to the rudder trim actuator through voltage reducing resistors R3 and R4. Extension of the actuator resets the quadrant to bias the complete rudder system to the left. Actuator movement is transmitted through feel unit arms and the link arms to move the feel and trim unit input to the newly trimmed neutral position. As the rudder trim actuator extends the rudder trim LVDT extends and provides a signal to move the rudder trim indicator pointer towards its ‘L’ position as follows: The LVDT information is transmitted to the indicator and to the FDR through the IFC1. When rudder trim switch is selected to ‘R’, operation is similar but in an opposite direction. If power to the indicator is removed, the indicator pointer will go off the scale.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-127
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-23-00 RUDDER SURFACES
SYSTEM DESCRIPTION Rudder surfaces extend almost the entire length of the trailing edge of the vertical stabilizer. The rudders are attached to the aircraft through a series of hinges and safety hinges.
GENERAL Refer to Figure 27-81. Rudder Empennage. 27 FLIGHT CONTROLS
The rudder is a primary flight control surface that is attached to the rear spar of the vertical stabilizer. The rudder is divided into two sections: •• Fore rudder
Each rudder rotates on sealed bearings. The fore rudder is attached to the rear spar of the vertical stabilizer and is actuated by two PCUs. The aft rudder is attached to the fore rudder by hinges and is actuated by push-rods so that the aft rudder deflects twice as far as the fore rudder. Unrestricted rudder travel equals 18° left/right movement as measured at the fore rudder.
• Trailing rudder.
1
2 3
Upper Dual Load Path
4
1
3
2
LEGEND 1. Vertical Stabilizer. 2. Fore Rudder. 3. Trailing Rudder. 4. Rear Fuselage Section.
Lower Dual Load Path
fs223a01.cgm
Figure 27-81. Rudder Empennage
27-128
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
27-31-00 ELEVATOR SYSTEM
The elevator system has the following components: •• Control columns
INTRODUCTION
•• Handwheels
The elevator surfaces move in proportion to the amount of control column movement.
•• Left forward quadrant
GENERAL
•• Elevator tension regulators
•• Right forward quadrant •• Left aft quadrant
Refer to Figure 27-82. Elevator Control System.
•• Right aft quadrant
The left and right elevators are installed on the trailing edge of the left and right horizontal stabilizers, respectively.
•• Elevator power control unit/actuators •• Compensator •• Torque tubes
The elevators are positioned by commands from either the pilot control system or the AFCS. Trim control and surface position indication is also supplied for each elevator.
•• Centering device •• Overload bungees •• Elevator position LVDT.
The PCUs move the elevators using hydraulic system pressure. 3
LEGEND 1. Elevator Autopilot Servo. 2. Elevator PCU’s. 3. Elevators. 4. Pitch Feel and Trim Unit. 5. Control Cables. 6. Stick Pusher. 7. Elevator Forward Quadrant. 8. Pitch Disconnect Handle. 9. Control Column.
2
1 2 4
5
6
9 8
7
Figure 27-82. Elevator Control System FOR TRAINING PURPOSES ONLY
27-129
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-130 PCU INPUT BUNGEE (17 LBS)
TORQUE TUBE CENTRING SPRING
H1 H 2
00
H3
20
STANDBY PCU
RIGHT ELEVATOR SURFACE
RIGHT FEEL UNIT PITCH DISCONNECT
PUSHER QUADRANT
PILOT CONTROL COLUMN
TENSION REGULATOR FORWARD QUADRANT
AFT QUADRANT
0
TRIM ACTUATOR (DUAL)
PITCH FEEL ACTUATORS
BEAM SPRING
AUTOPILOT QUADRANT
LEFT FEEL UNIT -30° OVERLOAD BUNGEE
STICK PUSHER CAPSTAN
H3 0° H2
AUTOPILOT SERVO
20°
H1 TORQUE TUBE CENTRING SPRING fs549a01.cgm
Figure 27-83. Elevator Control System Synoptic
PCU INPUT BUNGEE (17 LBS)
ELEVATOR SURFACE
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
OVERLOAD BUNGEE (75 LBS)
PITCH DISCONNECT HANDLE
0
DASH 8 Q400
CO-PILOT CONTROL COLUMN
-30
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION Refer to Figure 27-83. Elevator Control System Synoptic. Fore and aft movement of the pilot and co-pilot control columns is transmitted simultaneously to the pilot and co-pilot elevator control circuits. The two elevator control circuits are routed independently on the left and right side of the aircraft. This independent routing prevents loss of manual pitch control in the event of an engine rotor burst.
An elevator PCU compensator installed in the return line of the No.3 hydraulic system gives hydraulic gust lock protection. The compensator also gives elevator flutter suppression during flight.
27 FLIGHT CONTROLS
DASH 8 Q400
The pilot and co-pilot control columns are connected to each other by the pitch disconnect system (refer to 27-38-00). Control column input is transferred by pushrods to the left/right forward elevator quadrants below the flight compartment floor. The two forward elevator quadrants also act as cable tension regulators. The left forward (pilot’s) elevator quadrant has an input from the stick pusher system (refer to 27-33-00). The elevator cables are routed from the forward elevator quadrants aft below the flight compartment and cabin floor to the rear fuselage. The cables terminate at the two aft (left and right) elevator quadrants in the vertical stabilizer. Elevator control cables pass through seals in the rear pressure dome to prevent loss of cabin pressure. The aft quadrants transfer the pitch control movement through the overload bungees to the PCU input torque tubes. The left aft elevator quadrant has input from the AFCS servo actuator. The torque tubes transfer the pitch control movement through the PCU input bungees to the elevator PCU which are attached to the elevator control surfaces. There are three identical elevator PCUs connected to each elevator surface.
FOR TRAINING PURPOSES ONLY
27-131
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
Pitch Trim Switch
Hand Wheel
FW
D
Control Column
NOTE Co-pilot Control Column Shown. Pilot Opposite. fs625a01.cgm
Figure 27-84. Elevator Control Column
27-132
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Control Columns Refer to Figure 27-84. Elevator Control Column.
27 FLIGHT CONTROLS
Each control column provides the operational control of the elevators. The pilot control column operates the left elevator through the left elevator circuit. The co-pilot’s control column operates the right elevator through the right elevator circuit. Each column is attached to a lateral torque tube with bolts, which is installed in bearings below the flight compartment floor. The torque tube has a clutch, which can be disconnected in the event of a jam in either elevator control circuit to allow for individual control column operation of the elevators. A stick shaker for the stall warning system is attached to the forward face of each control column (refer to 27-33-00).
Handwheels The handwheels provide the physical input to the control columns. A hand operated control wheel is pivot-mounted to the top of each control column. A pitch trim split switch is located in the center of the outboard handgrip of each control handwheel.
FOR TRAINING PURPOSES ONLY
27-133
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
LEGEND 1. Mounting Bracket. 2. Quadrant. 3. Push Rod. 4. Secondary Stops. 5. Rig Pin Hole. 6. Tension Indicator.
1 2 6 HN C
3
4
D
INB FW
D
5 ft113a01.cgm
Figure 27-85. Elevator Right Forward Quadrant
27-134
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Left Forward Quadrant
The secondary stops provide a backup travel stop in the event of malfunction of the elevator system. The stick pusher quadrant is attached to the left forward quadrant. A rig pin point is located in the quadrant.
Refer to: • Figure 27-85. E levator Right Forward Quadrant. •• Figure 27-86. E levator Left Forward Quadrant.
The right forward quadrant is identical but without a pusher quadrant.
The left forward quadrant transmits the pilots control column inputs to the left aft quadrant.
The attached H-N-C scale and pointer is used to rig the tension regulator in accordance with temperature related graphs.
The left forward quadrant is located below the flight compartment floor. There are springs installed in the left forward quadrant to supply tension regulation of the cable system. There are fixed secondary stops integral with the tension regulator.
3
2
1
4
5
D
FW
8
6 7
LEGEND 1. 2. 3. 4.
Push Rod. LH Cable Tension Regulator (Quadrant). Stick Pusher Quadrant. Centering Spring.
5. 6. 7. 8.
Mounting Bracket. LH Tension Regulator Secondary Stops. Rig Pin Hole. Stick Pusher Quadrant Stop.
ft189a01.cgm
Figure 27-86. Elevator Left Forward Quadrant
FOR TRAINING PURPOSES ONLY
27-135
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Aft Quadrants Refer to Figure 27-87. Elevator Aft Quadrants. The left aft quadrant transmits pilot pitch commands to the left elevator PCU.
The elevator autopilot quadrant is directly attached to the left aft quadrant with input from the autopilot servo. A rig pin point is located in both quadrants. The right aft quadrant has the primary stops.
27 FLIGHT CONTROLS
The right aft quadrant transmits pilot pitch commands to the right elevator PCU. The aft quadrants are located in the vertical stabilizer. The quadrants are made of aluminum and rotate on a sealed bearing. They transmit the pilot’s pitch control commands from the forward quadrants through a series of pushrods, torque tubes and linkages to the six elevator PCUs. ELEVATOR CONTROL SYSTEM VERTICAL STABILIZER D
FW
2
3
LEGEND 1. Quadrant Primary Stop. 2. Left Autopilot Quadrant. 3. Elevator Quadrant. 4. Primary Stops Elevator.
4
1
ft178a01.cgm
Figure 27-87. Elevator Aft Quadrants
27-136
FOR TRAINING PURPOSES ONLY
D
FW
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Elevator-Power Control Units (PCU) Refer to Figure 27-88. Elevator Power Control Unit.
27 FLIGHT CONTROLS
The elevator PCU transmit system inputs to move the elevator surfaces. The elevator control system has six identical elevator PCUs; three attached to each elevator surface and the horizontal stabilizer rear spar. The PCU is a hydro-mechanical servo actuator. They receive input commands from the PCU input bungees and the PCU input torque tubes. The PCU actuator body is attached to the elevator control surface.
FW
D
ELEVATOR CONTROL SYSTEM HORIZONTAL STABILIZER
2
LEGEND 1. Elevator Attachment. 2. Horizontal Rear Spar Attachment. 3. MCV.
D
FW
NOTE Left Elevator Shown. Right Elevator Similar.
1
3
Three PCUs Per Elevator. fs396a01.cgm
Figure 27-88. Elevator Power Control Unit
FOR TRAINING PURPOSES ONLY
27-137
27 FLIGHT CONTROLS
27-138 INLET CHECK VALVE
PRESSURE PORT AND INLET SCREEN
DASH 8 Q400
RETURN PORT
ANTICAVITATION CHECK VALVE
ANTICAVITATION CHECK VALVE
LOAD LIMIT RELIEF VALVE
LOAD LIMIT RELIEF VALVE
ACTUATOR ASSEMBLY
ACTUATOR ASSEMBLY
fss99a01a.cgm
Figure 27-89. Elevator PCU Schematic
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
MAIN CONTROL VALVE
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Refer to Figure 27-89. Elevator PCU Schematic.
Elevator PCU Each PCU is composed of two sub assemblies: 27 FLIGHT CONTROLS
•• Actuator assembly with a balanced area cylinder and a translating body • Integral hydraulic manifold assembly. The Integral hydraulic manifold assembly contains the following: •• Pressure port •• Inlet check valve •• MCV •• Anti-cavitation check valves (2) • Load limit relief valves (2). The pressure port supplies system hydraulic pressure to the inlet check valve and then to the MCV. Pitch input from the torque tube causes the MCV to port up or down pressure to the actuator to command elevator position. The MCV moves the actuator balanced area cylinder and then PCU body moves to null the input. The two anti-cavitation check valves prevent actuator cavitation. The anti-cavitation valves crack at 2-8 psid to allow the serviceable PCU to overcome the jammed unit. The PCU actuator balance area cylinder fluid is then circulated through the anti-cavitation valves to the other side of the cylinder. The two load limit relief valves limit the PCU pressure to 3600 psid.
FOR TRAINING PURPOSES ONLY
27-139
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Compensator Refer to Figure 27-90. Compensator. The elevator compensator keeps hydraulic fluid 50 psi (344.7 KPa) pressure in both inboard PCUs, to give gust damping on the ground. 27 FLIGHT CONTROLS
The compensator is installed in the return line of the No.3 hydraulic system on the front spar of the vertical stabilizer. This limits PCU movement to prevent structural damage during windy conditions. The compensator also maintains a positive pressure to supply flutter suppression when the PCUs are depressurized in flight. It compensates for changes in fluid volume due to thermal expansion and contraction.
INL
ET
FW
D
fs360a01.cgm
Figure 27-90. Compensator
27-140
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Torque Tubes
Centering Device
Refer to Figure 27-91. Centering Device.
Refer to Figure 27-91. Centering Device.
There are two PCU input torque tubes. One is installed in the pilot elevator control circuit in the left horizontal stabilizer. The other is installed in the co-pilot elevator control circuit in the right horizontal stabilizer. The torque tubes are mass balanced and an attachment is provided for a centering spring.
The centering spring assists the springs of the Pitch Feel and Trim Unit to return the torque tube to neutral.
If the elevator circuit up-stream from the torque tube is disconnected from the centering spring, a balancing mass will prevent the torque tube from rotating, thus preventing elevator surface runaway. Attachment is provided for three PCU input bungees and an LVDT on each torque tube. A rig pin point is located in the outboard bellcrank of each PCU input torque tube.
A centering spring is installed in each PCU input torque tube. When the PCU input torque tube rotates, a load is placed on the centering spring causing the spring to increase tension. After the pilot releases the input command, the load exerted by the centering spring causes the control column to return to the neutral position.
ELEVATOR CONTROL SYSTEM HORIZONTAL STABILIZER 7
FWD
5
6
7
4
LEGEND 1. Adjusting Plate. 2. Pin Drive. 3. Torque Shaft Support Pin. 4. Spring. 5. Cover. 6. Retaining Ring. 7. Torque Tube.
3 2
1
FWD
ft409a01.cgm
NOTE Left Component Shown. Right Component Similar.
Figure 27-91. Centering Device
FOR TRAINING PURPOSES ONLY
27-141
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Overload Bungees Refer to Figure 27-92. Overload Bungee. The overload bungees contract or expand to compensate for excessive deflections. There is one overload bungee for each elevator.
The breakout force of the bungee is 75 ± 5 lbs. The unaffected elevator will then continue to move. This prevents structural damage to the elevators, cable circuits and the surrounding structure.
D
ELEVATOR CONTROL SYSTEM HORIZONTAL STABILIZER
FW
27 FLIGHT CONTROLS
The overload bungee is located between the aft quadrant and its torque tube. The other six input bungees are installed between the two torque tubes and the six elevator PCUs.
The overload bungee between the aft quadrants and its related torque tube function as a pushrod until there is a linkage jam downstream of the bungee.
NOTE D
TB
OU
Left Component Shown. Right Component Similar. fs392a01.cgm
Figure 27-92. Overload Bungee
27-142
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Overload Bungees (PCU INPUT)
Elevator Position LVDT
Refer to Figure 27-93. Elevator Position LVDT and PCU Input Bungee.
Refer to Figure 27-93. Elevator Position LVDT and PCU Input Bungee.
The PCU input overload bungees contract or expand to compensate for a PCU main control valve jam. There are three input bungees for each elevator.
The LVDT is a single channel, single sensor LVDT. It senses the elevator surface position and transmits the position data to the FCECU to IFC, and to the PFCSI on MFD1. There are two LVDTs located in the horizontal stabilizer; one attached to each elevator surface.
Three PCU input bungees are installed in series between the three elevator PCU and the PCU input torque tubes. They function as a pushrod until there is a PCU main control valve jam downstream of the bungee. The breakout force of the PCU input bungee is 17 ± 1.5 lbs. The unaffected elevator PCU continue to control the elevator surface.
FW
D
ELEVATOR CONTROL SYSTEM HORIZONTAL STABILIZER
PCU input bungee
Elevator position LVDT
FW
D
Figure 27-93. Elevator Position LVDT and PCU Input Bungee
FOR TRAINING PURPOSES ONLY
27-143
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OVERHEAD CONSOLE
MAIN INSTRUMENT PANEL
27 FLIGHT CONTROLS
WX OFF
FMS1 076 00
057
HDG 073°
E
3
160
VIE
CAUTION PANEL
PITCH TRIM
VCF
YSO
00 ---
TAS 20 GS 0
YCF
80
TCAS STBY
ADF1 DME1 H 92.1 NM
ADF2 DME2 92.1 NM
EMER LTS DISARMED CABIN PRESS
I
I
2
LEGEND
1
1. Left Elevator Position Indication. 2. Right Elevator Position Indication.
Figure 27-94. Elevator Position on MFD
27-144
35.0 NM --:--
FOR TRAINING PURPOSES ONLY
2
MAINTENANCE TRAINING MANUAL
Controls and Indications Refer to Figure 27-94. Elevator Position on MFD. Elevator position is normally shown on the pilot Multi-Function Display (MFD1). If a disagreement occurs between elevator surface position indications, the ELEVATOR ASYMMETRY caution light illuminates on the Caution and Warning panel. For the caution light to illuminate, the difference in elevator position must be greater than: •• 4 ± 1.6° for airspeed > 215 kts. • 6 ± 1.6° for airspeed < 215 kts.
ASYMMETRY CHECK OF THE ELEVATORS The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
•• Install an inclinometer on the top surface of the left elevator at a right angle to the trailing edge and adjust the inclinometer to a 0° indication •• Hold the pilot and co-pilot control column in the elevator neutral position. In the flight compartment, pull and turn the PITCH disconnect handle •• In the flight compartment, slowly pull the pilot’s control column aft until the ELEVATOR ASYMMETRY caution light comes on. Make sure that the indication is 6.0° ±1.0° •• Repeat the procedure for the right elevator •• Adjust the airspeed test set to 220 kts and repeat the procedure for the left and right elevator •• Make sure that the indication is 4.5° ±1.0°.
•• Connect the airspeed test set to the left and right primary pitot-static probes. Adjust the airspeed test set to 60 kts. •• Install the four deactivation targets on the proximity sensors on the main landing gear to simulate a weight-offwheels condition •• In the flight compartment, set the configuration that follows: °° Set the FLAPS selector to the 0° position °° Set the FLIGHT/TAXI switch to the FLIGHT position °° Set the No.1 and No.2 POWER lever to a position more than 12° above FLIGHT IDLE
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-145
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-146 FMS #2
HI LO
GPDB2 A429
DASH 8 Q400
4 5
TMCU #2 (G4) 3A 28 VDC L ESS BUS
PITCH TRIM ACT 1
G5 A1
D3
D1
C4 B1
7 6
FCS ECU 1
47 HI 24 LO
67 +28 VDC RTN
GPDB2 A429
ECS
RELAY JUNCTION BOX NO. 1
ELEVATOR
35 CHASSIS GND ADU #1
MAINT CLEAR NVM
27 38
74
41
PITCH TRIM LT POS'N
HI LO
PITCH TRIM LT EXTEND PITCH TRIM LT RETRACT PITCH TRIM LT DISCRETE REF PITCH TRIM LT ENABLE PITCH TRIM LT SPEED MAINT CLEAR NVM
1 9 17 18 8 10 2
4 13 10 2 8 3 1
HI PITCH TRIM LT POS'N LO PITCH TRIM LT EXTEND PITCH TRIM LT RETRACT PITCH TRIM LT DISCRETE REF PITCH TRIM LT ENABLE PITCH TRIM LT SPEED
203 HI 204 LO
FCS ECU R A429 (IN)
31-41 A1 IOP #1
LEFT PITCH TRIM ACTUATOR
AHARS
MAINTENANCE PANEL
ADU #2
27 38
FCS ECU RA429 (OUT) GRDB2 A429 (IN) FCS ECU A429
31 41 30 21 22
TB-B/D2 TB-B/B1 TB-B/D1 TB-A/B2 TB-B/A2 FMS #1
ELEVATOR TRIM CONT SWITCH PILOT'S CONTROL HANDWHEEL
PILOT PILOT PILOT PILOT PILOT
48 HI 49 LO
TRIM TRIM TRIM TRIM TRIM
HI LO HI LO
47 37 48 49
HI LO
47 37
331 HI 332 LO
31-41 A2 IOP #2
RETURN NOSE UP 1 NOSE DOWN 1 NOSE UP 2 NOSE DOWN 2
233 HI 232 LO
PITCH FEEL LT EXTEND 19 PITCH FEEL LT RETRACT 20 PITCH FEEL LT DISCRETE REF 28 PITCH FEEL LT ENABLE 40 PITCH FEEL LT SPEED 50
10 2 8 3 1
PITCH PITCH PITCH PITCH PITCH
HI 29 LO 39
4 13
HI LO
7 6
3A
FEEL FEEL FEEL FEEL FEEL
LT LT LT LT LT
EXTEND RETRACT DISCRETE REF ENABLE SPEED
LEFT PITCH FEEL ACTUATOR
(F4) 3A
7 5
PITCH FEEL LT POS'N
+28 VDC +28 VDC RTN
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU) PITCH FEEL ACT 1
FCS ECU L A429 (IN)
31-41 A1 IOP #1
GENERAL PURPOSE DATA BUS IFC RECV'D
PITCH FEEL LT POS'N
(H4)
GPDB2 A429 (OUT)
PITCH TRIM IND
LEFT DC CBP
Figure 27-95. Pitch Feel and Trim
ELEVATOR
HI LO
FCS ECU L A429
10 +28 VDC 12 +28 VDC RTN
PITCH TRIM INDICATOR
# 1 & 2
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
56 +28 VDC
LEFT DC CBP
28 VDC L ESS BUS
+28 VDC RTN
2-K1
(M3) 5A
D2
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-95. Pitch Feel and Trim. The FCECU uses airspeed information from the ADUs and acceleration from the AHARS to control pitch feel, by controlling the Pitch Feel Actuators. As airspeed and acceleration increase, the FCECU commands the two independent feel actuators to extend. This action, through the levers in the PFTU, increases the force required to rotate the aft quadrants. This force is felt back through the cable system, to the front quadrants and the control columns increasing the feel to the pilots. As airspeed and acceleration decrease, feel is decreased, by reversing the process. Rotating the torque tubes transfers the pitch control movement through the PCU input bungees to the elevator PCUs. Extension or retraction of the PCUs moves the elevator surfaces. The outboard PCU is powered by No.1 hydraulic system, the center PCU by No.2 hydraulic system, and the inboard PCU by the No.3 hydraulic system, when necessary. As the PCUs extend or retract, it is the body of the PCU that moves, to displace the elevators, thereby returning the servo valve towards the null position as the PCU moves.
OPERATIONAL TEST OF THE ELEVATOR CONTROL SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Move the control column to the neutral position. •• Make sure the PFCS indicator shows both elevators in neutral.
Revision 0.4
•• Move the control column fully forward and aft, 3 times, making sure the elevators move smoothly to full deflections. •• Make sure full deflections are shown on the PFCS indicator. • Move control column to neutral position.
ELEVATOR DROOP RATE CHECK The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• The procedure that follows is to check the droop rate of the elevator and to make sure that the elevator Power Control Unit (PCU) internal leakage is within the flutter requirements, even though the droop rate exceeds the threshold when all the systems are depressurized. • This task must be done in the hanger or outside with zero wind conditions.
NOTE Use the Standby Power Unit (SPU) and Power Transfer Unit (PTU) first, and then STNDBY No.3 by itself to have the systems pressurized. •• Set the elevators to a neutral position and shut off the No.1, No.2 and No.3 hydraulic system •• On the (CDS) proceed to page 3 of the FCECU diagnostic page. •• Record the LH elevator position and RH elevator position as “LH No.1 and RH No.1”. Record the time as “t1”. •• Wait for 10 minutes and repeat step 3. •• Record the LH elevator position and RH elevator position as “LH No.2 and RH No.2”.
FOR TRAINING PURPOSES ONLY
27-147
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• Record the time as “t1+10”.
Refer to:
•• Subtract the recorded values and divide by 10 to calculate the droop rate.
•• Figure 27-96. Elevator Position Feedback. • Figure 27-97. Elevator Caution Lights.
•• If the droop rate exceeds 0.12°/minute proceed to TASK 27-31-36-720-801
As the elevator moves, the position is shown on the MFD1 by means of LVDTs attached to each elevator surface.
27 FLIGHT CONTROLS
ELEVATOR HI POSITION EXC LO
76 66
1 HI 2 LO
ELEVATOR POSITION EXC
ELEVATOR POSITION LEFT
85 75 65
3 HI 4 CT 5 LO
ELEVATOR POSITION LEFT
HI CT LO
LEFT ELEVATOR
LEFT ELEVATOR LINEAR VARIABLE DIFFERENTIAL TRANSFORMER (LVDT) +28 VDC L ESS BUS
(M3) 5A
FCS ECU 1
56 67
+28 VDC DC RTN
35
CHASSIS GND NOSE UP CMD NOSE DOWN CMD
LEFT DC C/B PNL
72 73
420 419
NOSE UP CMD NOSE DOWN CMD
22-00 A1 FGM #1 +28 VDC R ESS BUS
(L6) 5A
RIGHT DC C/B PNL
FCS ECU 2
56 67
+28 VDC DC RTN ELEVATOR HI POSITION EXC LO
76 66
1 HI 2 LO
ELEVATOR HI POSITION CT RIGHT LO
85 75 65
3 4 5
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
ELEVATOR POSITION EXC
HI ELEVATOR CT POSITION LO RIGHT
RIGHT ELEVATOR LINEAR VARIABLE DIFFERENTIAL TRANSFORMER (LVDT)
Figure 27-96. Elevator Position Feedback
27-148
FOR TRAINING PURPOSES ONLY
RIGHT ELEVATOR
AIRCRAFT AIRSPEED > 215 KTS LEFT AND RIGHT ELEV SURFACES DISAG BY MORE THAN 4.0 DEGREES
LATCHED - IN AIR NOT LATCHED - ON GND ELEVATOR ASYMMETRY CAUTION LIGHT CDS MSG: LT ELEVATOR LVDT FAILURE
FCECU CH No.1 DETECTS A VOLTAGE FAILURE OF LT ELEV SURFACE LVDT AIRCRAFT ON GND FCECU CH No.2 DETECTS A VOLTAGE FAILURE OF RT ELEV SURFACE LVDT
NOT LATCHED
CDS MSG: RT ELEVATOR LVDT FAILURE NOTES LATCHED - Caution light will remain illuminated for duration of flight. Will not be reset until FCECU power is cycled and fault condition is no longer present. NOT LATCHED - Caution light will extinguish when fault condition is no longer present regardles of phase of flight.
27-149
Figure 27-97. Elevator Caution Lights 27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
AIRCRAFT AIRSPEED < 215 KTS
DASH 8 Q400
LEFT AND RIGHT ELEV SURFACES DISAG BY MORE THAN 6.0 DEGREES
CDS MSG: ELEV ASYM FAILURE
27 FLIGHT CONTROLS
27-150 COPILOT CONTROL COLUMN
FCECU AUTOPILOT TRIM
RIGHT PITCH FEEL ACTUATOR LEFT PITCH FEEL ACTUATOR
AHARS ACCELERATION
PILOT CONTROL COLUMN fst20a01.cgm
Figure 27-98. Pitch Feel and Trim Block Diagram
PFTU
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
DUAL PITCH TRIM ACTUATOR
TRIM INDICATOR
PILOT PITCH TRIM SWITCHES
DASH 8 Q400
COPILOT PITCH TRIM SWITCHES
ADU AIRSPEED
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-32-00 ELEVATOR FEEL AND TRIM
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The input commands from the control columns to the elevator PCU move the elevator surfaces. Therefore the pilot is unable to feel the aerodynamic forces acting on the elevator surfaces. The elevator control system incorporates an artificial feel/trim. The elevator Pitch Feel and Trim Unit (PFTU) provides artificial feel and trimming to counter the effects of longitudinal pitch control changes during flight. The artificial feel acts on the control column to help prevent the pilot from over-controlling the aircraft. Trim counters the effects of changes to the aircraft center of gravity, airspeed and lift during flap extension or retraction.
GENERAL Refer to Figure 27-98. Pitch Feel and Trim Block Diagram. The dual PFTU which inputs to both elevator surfaces. The PFTU is located near the aft elevator quadrants in the vertical stabilizer. The elevator feel and trim system has the following components: •• Pitch Feel and Trim Units (PFTUs) •• Dual pitch trim actuator • Pitch Feel Actuators (PFAs).
FOR TRAINING PURPOSES ONLY
27-151
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION Refer to: •• Figure 27-99. Elevator Feel Caution Light. • Figure 27-100. Pitch Feel and Trim Units.
If one pitch feel actuator fails, the elevator control system continues to operate using the operational actuator but with reduced artificial feel. In this case, the ELEVATOR FEEL caution light illuminates to advise the crew of this condition.
27 FLIGHT CONTROLS
The input commands from the control columns are transferred to the elevator PCU which, in turn, move the elevator surfaces. Therefore, the pilot is unable to feel the aerodynamic forces acting on the elevator surfaces. The PFTU increases elevator control column forces with column displacement as a function of airspeed and normal acceleration of the aircraft. The Air Data Units (ADU) send the airspeed information to the FCECU. The Altitude Heading and Reference System (AHRS) send the acceleration information to the FCECU.
OVERHEAD CONSOLE
Elevator Feel.
PITCH TRIM
EMER LTS DISARMED
INTERNAL DOORS
CABIN PRESS
CHK FIRE DET
Figure 27-99. Elevator Feel Caution Light
27-152
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL TEST OF THE PITCH FEEL SYSTEM
•• Holding the column forward, make sure an opposite force is felt toward the neutral position
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
•• Increase test set to 200 kts make sure the opposite force increases
•• Make sure the PITCH DISC is engaged
•• Move the column full aft and repeat the above sequence
•• Install the air data test set on the pitotstatic tubes
•• On completion remove the test set.
•• Move control columns full forward and hold in position •• Program the air data test set to 100 kts, check ASI increases to 100 kts ELEVATOR CONTROL SYSTEM VERTICAL STABILIZER D
FW
2 3
4 5 LEGEND D
FW
1
6
1. Pitch Feel Actuator RH. 2. Trim Bellcrank RH. 3. Trim Bellcrank LH. 4. Trim Push Rods. 5. Trim Actuators. 6. Pitch Feel Actuator LH.
ft226a01.cgm
Figure 27-100. Pitch Feel and Trim Units
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-153
27 FLIGHT CONTROLS
•• Program test set to 0 kts and move columns to the neutral position
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
PITCH FEEL AND TRIM UNIT
27 FLIGHT CONTROLS D
FW
2 3
1
4
5
D
FW
LEGEND 1. Motor Controller Circuit Card LH. 2. Motor Controller Circuit Card RH. 3. Pitch Trim Actuator RH. 4. Actuator Housing. 5. Pitch Trim Actuator LH.
Figure 27-101. Dual Pitch Trim and Pitch Feel Actuators
27-154
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Dual Pitch Trim Actuator
Pitch Feel Actuators
Refer to Figure 27-101. Dual Pitch Trim and Pitch Feel Actuators.
Refer to Figure 27-101. Dual Pitch Trim and Pitch Feel Actuators.
The dual pitch trim actuator reduces the aerodynamic forces acting on the control columns.
The pitch feel actuators provide PFTU with FCECU commanded inputs to create elevator control column artificial feel.
The dual pitch trim unit is installed on the front face of the PFTU. The pitch trim actuator is a single electro-mechanical unit that includes: •• DC motors (2) •• Motor control cards (2)
The left and right pitch feel actuators are located in the PFTU. The pitch feel actuators extend or retract as commanded by the FCECU in relation to the airspeed and acceleration of the aircraft. Each pitch feel actuator is a single electromechanical unit which has:
•• Gears (1 set) •• Driveshaft
•• DC motor
•• Actuators (2) and
•• Motor controller circuit card
• LVDTs (2).
•• Gears (1 set)
Only one motor is needed at any time to operate the two actuators. A motor rotates the single shaft which drives the gear set. The gears operate both the left and right pitch trim actuators at the same time. The pitch trim actuators are powered by left essential and right essential buses TRIM ACT 1 and TRIM ACT 2 circuit breakers. The FCECU commands the dual pitch trim actuator. Pitch trim signals from the NOSE DN/NOSE UP split trim switches on the control handwheels, or from the autopilot, are prioritized by the FCECU in this order:
•• Actuator and • LVDT. The pitch feel actuators are powered by the left and right essential buses through the FEEL ACT 1 and FEEL ACT 2 circuit breakers. The left motor controller receives its commands from the FCECU channel 1, and the right motor controller receives its commands from the FCECU channel 2. Each FCECU channel supplies three signals to its related motor controller: •• Enable “ON or OFF”
•• Pilot
•• Motor direction
•• Co-pilot and
• Motor speed.
• Autopilot.
NOTE Maximum elevator trim is 13° nose up and 10° nose down.
The two LVDT located in the pitch feel actuators supply feedback signals to the FCECU. The FCECU monitors the position and speed of the pitch feel actuators. The airspeed is supplied by the ADUs and the acceleration information is supplied by the AHRS. This data is shared between channels 1 and 2 of the FCECU so that an identical
FOR TRAINING PURPOSES ONLY
27-155
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
signal is sent to each pitch feel actuator. This reduces mistrack or asymmetry between the pitch feel actuators. Both pitch feel actuators are normally in the active mode. 27 FLIGHT CONTROLS
The failure of a pitch feel actuator is sensed by the FCECU through the LVDT feedback signals. The FCECU then switches the enable signal of the failed actuator to the “OFF” position. The FCECU continues to supply the enable “ON” signal to the other actuator. The aircraft will continue to operate with a degraded pitch feel.
CONTROLS AND INDICATIONS
The LVDT located in the pitch trim actuators send their signals to the IFC and the FCECU which then supplies the signal to the elevator trim indicator. The indicator is labelled: •• “NU” for nose up, •• “ND” for nose down and • “TO” for take-off. A white band next to the “TO” setting shows the amount of elevator trim that is acceptable for take-off. An aural warning sounds if the power levers are advanced above Flight Idle plus 12°, with the elevator trim position outside the take-off range.
Elevator Trim Indicator Refer to Figure 27-102. Elevator Trim Indicator. The elevator trim indicator displays the elevator dual pitch trim actuator position. The elevator trim indicator is an analog type gauge located in the flight compartment on the center console.
LEGEND 1. Nose Down Range. 2. Take-Off Range. 3. Nose Up Range. 4. Indicator. R A T I N G
R A T I N G
FLIGHT IDLE
1 DISC
2
I
3
4
Figure 27-102. Elevator Trim Indicator
27-156
FOR TRAINING PURPOSES ONLY
I
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Pitch Trim Split Switch Refer to Figure 27-103. Pitch Trim Switch.
27 FLIGHT CONTROLS
The pitch trim switches give manual control of the elevator pitch trim. A pitch trim split switch is located in the center of the outboard hand grip of each control handwheel. The pitch trim switches are split in two; both halves of the switches must be activated for the pitch trim command to proceed. This prevents manual pitch trim runaway in the case of a single switch contact failure. The switches are spring-loaded to the centeroff position. When the switches are pushed forward, a nose-down trim is commanded, and when the switches are pulled aft, a nose-up trim is commanded.
TCS
PTT
FW
D
A/P
NOSE DN
D/S
INHP
NOTE Pilot Control Column shown. Co-pilot similar.
NOSE UP
FW
D
fs110a01.cgm
Figure 27-103. Pitch Trim Switch
FOR TRAINING PURPOSES ONLY
27-157
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Elevator Trim Shutoff Switchlights Refer to Figure 27-104. Elevator Trim Shutoff Switchlights. The ELEVATOR TRIM SHUTOFF (PUSH OFF) switchlights provide shutdown indication and control of elevator dual pitch trim actuator. 27 FLIGHT CONTROLS
The PUSH OFF switchlights are located on both sides of the glareshield panel. They indicate “PUSH OFF” if the FCECU detects a pitch trim command that persists for longer than 3 seconds. An aural alert will sound during this fault. The aural warning will stop and the PUSH OFF indication will cancel when the pitch trim command is removed or the switchlight is pushed. Selecting the PUSH OFF switchlight will isolate the dual pitch trim actuator from the FCECU and cause the PITCH TRIM caution light on the Caution and Warning panel to illuminate.
NOTE: LH Glareshield shown. RH Glareshield similar. SPOILERS
STICK PUSHER SHUT OFF
FLIGHT A/P DISENG
ROLL INBD
TAXI
CF-AEI
INHIBIT
ELEVATOR TRIM SHUT OFF
TERRAIN INHIBIT
WARNING PRESS TO RESET
Elevator Trim Shut Off Switchlight.
Figure 27-104. Elevator Trim Shutoff Switchlights
27-158
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Caution Lights Refer to Figure 27-105. Elevator Caution Lights. The FCECU sends signals to the Caution and Warning panel to bring on the caution lights that follow: 27 FLIGHT CONTROLS
ELEVATOR FEEL •• Left or right Pitch Feel Actuator fails, or •• Airspeed No.1 and Airspeed No.2 disagree, or • Acceleration No.1 and Acceleration No.2 disagree. PITCH TRIM •• One pitch trim motor, or its control card fails, or •• Elevator trim shutoffs switch light pressed, or •• Airspeed No.1 disagrees with Airspeed No.2, or • When on ground, Pitch trim input commands disagree.
OVERHEAD CONSOLE
CAUTION PANEL 1 PITCH TRIM
EMER LTS DISARMED CABIN PRESS
2
LEGEND 1. Pitch Trim. 2. Elevator Feel.
Figure 27-105. Elevator Caution Lights
FOR TRAINING PURPOSES ONLY
27-159
27 FLIGHT CONTROLS
27-160 9811RJB1-P/J1F
(G4)
(M3) 5A
56 +28 V DC
HI 1 LO 9 PITCH TRIM LT EXTEND 17 PITCH TRIM LT RETRACT 18 PITCH TRIM LT DISCRETE REF 8 PITCH TRIM LT ENABLE 10 PITCH TRIM LT SPEED 2 PITCH TRIM LT POS'N
(WARDROBE)
41
P/J2 74
MAINT CLEAR NVM
3061 P/J2-2 4 HI 5 LO
UNDERFLOOR - CENTER ELEVATOR 4 13 10 2 8 3 1
HI PITCH TRIM LT POS'N LO PITCH TRIM LT EXTEND PITCH TRIM LT RETRACT PITCH TRIM LT DISCRETE REF PITCH TRIM LT ENABLE PITCH TRIM LT SPEED
3141P/J1A-A1 203 HI 204 LO
LEFT PITCH TRIM ACTUATOR
3141P/J1C-A2 331 HI 332 LO
J/P2 FCS ECU RA429 (OUT)
SIGNAL CONDITIONING UNIT
GRDB2 A429 (IN)
PILOT'S CONTROL HANDWHEEL
FCS ECU A429 P/J1 31 41 30 21 22 FMS #1 (34-61-00)
ELEVATOR TRIM CONT SWITCH
PILOT PILOT PILOT PILOT PILOT
48 HI 49 LO
TRIM TRIM TRIM TRIM TRIM
HI LO HI LO
47 37 48 49 J/P1 HI 47 LO 37
3A
FCS ECU L A429 (IN)
31-41 A1 IOP #1 31-41-00
GENERAL PURPOSE DATA BUS IFC RECV'D
J/P1 PITCH FEEL LT EXTEND 19 PITCH FEEL LT RETRACT 20 PITCH FEEL LT DISCRETE REF 28 PITCH FEEL LT ENABLE 40 PITCH FEEL LT SPEED 50 HI 29 LO 39
P/J11 10 PITCH 2 PITCH 8 PITCH 3 PITCH 1 PITCH 4 13
HI LO
CTR PED - LH SIDE FEEL FEEL FEEL FEEL FEEL
LT LT LT LT LT
EXTEND RETRACT DISCRETE REF ENABLE SPEED
P/J100 7 5
PITCH FEEL LT POS'N
+28 V DC +28 V DC RTN
LEFT PITCH FEEL ACTUATOR
(F4) 3A
3141P/J1C-A1 233 HI 232 LO
VERTICAL STAB
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU) PITCH FEEL ACT 1
GPDB2 A429 (OUT)
AVIONICS RACK
7 6
28V DC L ESS BUS
FCS ECU R A429 (IN)
31-41 A2 IOP #2 31-41-00
RETURN NOSE UP 1 NOSE DOWN 1 NOSE UP 2 NOSE DOWN 2
PITCH FEEL LT POS'N
(H4)
GPDB2 A429
31-41 A1 IOP #1 31-41-00 AVIONICS RACK
51 50 49 36
TB-B/D2 TB-B/B1 TB-B/D1 TB-A/B2 TB-B/A2
2100P/J2 47 HI 24 LO
ECS 21-00-00 AVIONICS RACK
3133J/P10 PLT TRIM NOSE UP 1 PLT TRIM NOSE DOWN 1 PLT TRIM NOSE UP 2 PLT TRIM NOSE DOWN 2
GPDB2 A429
TMCU #2 30-61-00
MAINTENANCE PANEL 45-45-00
AFT AVIONICS RACK
UNDERFLOOR - CENTER
PITCH TRIM IND
LEFT DC CBP 24-61-00
Figure 27-106. Elevator Feel and Trim System - Electrical Schematic
ELEVATOR
HI LO
FCS ECU L A429
10 +28 V DC 12 +28 V DC RTN
PITCH TRIM INDICATOR
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
9811J/P340
C4 B1
J/P1
35 CHASSIS GND
MAINT CLEAR NVM
D1
RELAY JUNCTION BOX NO. 1
67 +28 V DC RTN
LEFT DC CBP 24-61-00
A1
2-K1
P/J1
FCS ECU 1
G5
P/J9 7 +28 V DC 6 RTN
DASH 8 Q400
CENTER FUSELAGE - UNDERFLOOR
D2
34-61-00 FMS #2
VERTICAL STAB
9811RJB1-J/P1F
d4s273200_a_004.dg, nr, apr22/2008
3A 28V DC L ESS BUS
PITCH TRIM ACT 1
D3
MAINTENANCE TRAINING MANUAL
OPERATION Refer to Figure 27-106. Elevator Feel and Trim System - Electrical Schematic.
Pitch Trim Pitch trim is prioritized by the FCECU in the following order. •• Pilot
The FCECU matches the trim speed to the airspeed as follows: •• Airspeed < 150 KIAS high speed trim 0.75°/sec. •• Airspeed > 250 KIAS low speed trim 0.10°/sec. • Trim speed is “increased proportionally” between the two airspeed limits. If airspeed is invalid and both flap positions are < 5°, trim speed is 0.1°/sec.
•• Co-pilot • Autopilot. The command with the highest priority is used by the FCECU for trim control.
If airspeed is invalid and both flap positions are > 5°, trim speed is 0.75°/sec. If airspeed and flap position are invalid trim speed is 0.75°/sec.
Manual Trim When the pitch trim switch is pushed/pulled to the Nose up/ Nose down position the FCECU commands the Dual pitch trim actuator extend or retract using the left motor. The right motor is in standby mode.
If any of the above discrepancies occur the “PITCH TRIM”, caution light will illuminate.
The FCECU controls trim speed and also supplies a pitch trim enable signal. Trim inputs move the trim pushrods and stabilizing linkage, in the PFTU, and move the trim bellcrank. Moving the bellcrank rotates the elevator aft quadrants, through the input bungees, pushrods and torque tubes which extends or retracts the PCUs. This moves the elevators to match the trim input. The trim input is felt back through the cable system to the forward quadrants, rotating the quadrants, and through the push rods, moves the control columns.
FOR TRAINING PURPOSES ONLY
27-161
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-162 S7 PUSH A
9811-GM103 M NORMAL
A
A
A
C
A
38 39 58 59 63 64 74 73
H2
H3
P-
J3
J1
PUSH OFF PITCH PITCH PUSH OFF PITCH PITCH
TRIM TRIM TRIM TRIM
ACU
G 9811-GM103 B
K2
K3
K1 L2
11
L3
L1
PITCH TRIM
CAUTION AND WARNING PANEL
ELEVATOR TRIM DISC (PILOT) 9811-GM102 B
B-
S8 PUSH
NORMAL
A
OFF TRIM AURAL WRNG
54
PITCH TRIM DISC RELAY ENG
81
PITCH TRIM DISC RELAY ENG PITCH TRIM CAUTION
B
9811-GM102 A
H2 H1 J2 J1
9811-GM102
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
A
A
A
A
C G
A
F
B
D
OFF
69 43
B
E 9811-GM102 F
K2 K1 L2 L1
SEE SHT. 1
H5 G5 A1 H4
SEE SHT. 2
G4 A7
H3 9811-GM102 G
D3
D2
D1 C3
C2
C1
C-
J3 9811-GM102 H
CR1
CR 2
G3
B3
B2
L3
ELEVATOR TRIM DISC (CO-PILOT)
C3 A8
SEE SHT. 2
C2 CR 3
A3
A2 K3 K4 K5
SEE SHT. 1
B1
K3 Q-
D4 C4 B1 D3
A1
X1
NC
G1 H1 J1
X2 2-K1
A10
GLARESHIELD PANEL RELAY JUNCTION BOX NO. 1
Figure 27-107. Elevator Trim Runaway or Manual Trim > 3 secs
B10
CR4
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
A
E
D
J2
OFF
K-
OFF
H1
9811-GM103
G F
DASH 8 Q400
B
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Abnormal Operation Pitch Trim Runaway
NOTES
Refer to Figure 27-107. Elevator Trim Runaway or Manual Trim > 3 secs.
27 FLIGHT CONTROLS
A pitch trim runaway, or manual trim selection, for > 3 seconds will cause the following: •• An audible warning in the form of “clicks” •• A ground signal from the FCECU to contacts in co-pilot’s elevator trim disconnect switchlight (S8). Then to the Advisory Control Unit (ACU). The ACU outputs grounds for the ELEVATOR TRIM SHUTOFF switchlights PUSH and OFF. Pushing either switchlight causes the following: •• A ground is provided by the operated switchlight to energize relay 2-K1. This relay removes power to the pitch trim actuators, and removes the ground for the PITCH TRIM caution light, causing the light to illuminate. The PUSH goes off and the OFF stays on in the switchlight.
FOR TRAINING PURPOSES ONLY
27-163
27 FLIGHT CONTROLS
27-164 S7 PUSH A
B
A
A
C
A
E
38 39 58 59 63 64 74 73
D
H2
P-
J3
G
J1
PUSH OFF PITCH PITCH PUSH OFF PITCH PITCH
TRIM TRIM TRIM TRIM
ACU
B
K2
K3
K1 L2
11
L3
L1
CAUTION AND WARNING PANEL
ELEVATOR TRIM DISC (PILOT)
B
PITCH TRIM
B-
S8 PUSH
NORMAL
OFF TRIM AURAL WRNG
54
PITCH TRIM DISC RELAY ENG
81
PITCH TRIM DISC RELAY ENG
69
PITCH TRIM CAUTION
43
B
B
A H2
A
H1 J2 J1
E
K2 K1
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU)
F
L2 L1
A
A
A
A OFF
C G
A
F
B
D
H5 G5 A1 H4
H3 G
G4 A7
C2
G3
B2
D1
H
CR1
CR 2
C1 B3
L3
ELEVATOR TRIM DISC (CO-PILOT)
CR 3
A3
A2 K3 K4 K5
C2
B1
K3 Q-
C3 A8
C3
C-
J3
D4 C4 B1 D3
D3
D2
A1
X1
NC
G1 H1 J1
X2 2-K1
A10
GLARESHIELD PANEL RELAY JUNCTION BOX NO. 1
Figure 27-108. Trim Push/Off Switch Pushed-Pitch Trim Caution Light ON
B10
CR4
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
H3
J2
A
K-
OFF
H1 OFF
G F
DASH 8 Q400
M NORMAL
A
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-108. Trim Push/Off Switch Pushed-Pitch Trim Caution Light ON.
NOTES
Autopilot Trim
27 FLIGHT CONTROLS
When flying on autopilot, the FGM monitors the amount of torque required on the pitch control capstan to keep the longitudinal trim correct. If the torque force exceeds the threshold, the FGM sends a signal to the FCECU. The FCECU will command pitch trim until the torque forces are removed at the pitch control capstan.
Flap Compensation Trim During flap extension or retraction, with the autopilot Off, flap compensation pitch trim is provided. As the flaps extend or retract, the center of lift on the wing moves forward or backward, causing the aircraft nose to rise or fall. To prevent this from happening the signal comes from the FGM to the FCECU to command the pitch trim actuators to move the elevators to the required positions.
OPERATIONAL TEST OF THE ELEVATOR CONTROL SYSTEM The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Use pilot's or co-pilot's control column •• Pitch disconnect handle in •• Elevator trim NEUTRAL •• Move control columns to neutral, fully fwd and fully aft •• Make sure elevator control surfaces follow, and movement is smooth.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-165
27-166
DASH 8 Q400 MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
Figure 27-109. SPS Block Diagram
27 FLIGHT CONTROLS
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-33-00 STALL WARNING /STICK PUSHER
SYSTEM DESCRIPTION The SPS operates in the following modes: •• Initialization (INIT)
INTRODUCTION
•• Power-On Self Test (POST)
When the aircraft is in a stall condition, the SPS gives a positive input to the flight controls to help the flight crew regain aircraft control.
GENERAL Refer to Figure 27-109. SPS Block Diagram. The SPS has the following units: •• SPM1 and SPM2 •• Stick Pusher Actuator •• Stick Pusher Capstan •• Stick Pusher Quadrant •• Stick Shaker •• Angle of Attack Transducer •• STICK PUSHER SHUTOFF Annunciator Switch •• STALL WARN TEST Switch. The SPS has two primary functions: •• Stick shakers •• Stick pusher. Stick Shakers: Stick shakers give tactile and aural indication of a near stall condition. Stick Pusher: A stick pusher moves the elevators reducing the angle of attack when the aircraft is in a stall condition.
•• Operational (OPER) •• Maintenance •• Teleloading. Initialization Mode: The SPS operates in this mode after an electrical power interruption to initialize the hardware and software. After a successful INIT the SPS progresses to the POST mode. Power-On Self Test: The SPS does a POST after a long power interruption while the aircraft is on the ground. The POST senses SPS hardware malfunctions that are not continuously monitored in the operational mode or apparent to the flight crew. The results of the 25 second POST are saved in the BITE and are sent to the Central Diagnostic System (CDS). Each SPM does a POST twice before a malfunction condition is set. If the POST senses a malfunction, the SPM prevents related Stick Shaker and Stick Pusher operation. The SPM does not do a POST when the aircraft is not on ground. It will use the saved POST results to calculate its status. Operational Mode: The SPS uses two Stall Protection Modules to control their related Stick Shakers. Both Stall Protection Modules operate together to control the Stick Pusher. The operational mode is divided into two sub-modes: •• Pre-Flight Test •• In flight. Pre-Flight Test: The STALL WARN toggle switch located on the pilot side console is set to the TEST1 position and then to TEST2 to do an operational test of the SPMs. The switch is held at the set position during the test.
FOR TRAINING PURPOSES ONLY
27-167
27 FLIGHT CONTROLS
The Stall Protection System (SPS) gives indications when the aircraft is near a stall condition.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
In-Flight Operational Mode: The stick shaker and stick pusher only operate when the aircraft is airborne. The stick pusher operation is inhibited when the calibrated airspeed is greater than 215 Kts (399 km/h), and the Above Ground Level (AGL) altitude is less than 200 ft (60.8 m). 27 FLIGHT CONTROLS
To calculate a near a stall condition and actuate the stick shakers, the SPMs use the following parameters: •• Angle of attack data
Besides self or internal monitoring, the SPS does the following monitoring: •• External Input Monitoring •• Stick Shaker Monitoring
•• Flap position
•• Stick Pusher Monitoring.
•• Mach number
External Input Monitoring: Each SPM monitors the following external inputs:
•• Engine torque •• Icing status. To calculate a stall condition and actuate the stick pusher the SPMs use the above mentioned parameters as well as: •• Power lever angle
•• AOA (Transducers and Correction Data) •• FPIU (Flap Position Data) •• REF SPEEDS (Toggle Switch) •• PSEU (Weight On Wheels Data)
•• Condition lever angle.
•• ADU Data
Each SPM uses its related AOA transducer angle input for stick shaker calculations and an average of the two for the stick pusher calculations. The SPM will use the same input as the other SPM if any related data inputs shown above have malfunctioned. If no data is available, the SPM will then use default data. An AOA malfunction or difference is the only input that prevents the stick pusher from operating. When the aircraft is in icing conditions, the lift supplied by the wings can be decreased enough to cause the aircraft to stall at a lower angle of attack. The stall operating angle of the stick shaker and stick pusher is set to a lower angle of attack when in icing conditions. The SPS receives icing condition data from the REF SPEEDS toggle switch in the ICE PROTECTION Control Panel. The Electronic Instrument System (EIS) shows an [INCR REF SPEED] message.
27-168
Maintenance Mode: The BITE uses the Central Diagnostic System (CDS) to report the condition of the unit and saves faults in a Non Volatile Memory (NVM) for reporting to line and shop maintenance. The SPM does a test when it receives a maintenance discrete command through IOM1while the air speed is less than 50 Kts (93 km/h) and the aircraft is on the ground.
•• AHRS Data •• Radio Altimeter Data •• FADEC Engine Data. AOA Transducer Monitoring: The AOA transducer angles are critical parameters for the SPS functions. If an AOA transducer malfunctions, each SPM will use the serviceable transducer to make its stick shaker calculation. The Stick Pusher will not operate. These malfunctions will be apparent to the flight crew in the form of the following caution lights: •• No.1 STALL SYST FAIL •• No.2 STALL SYST FAIL. Non-critical malfunctions do not show in flight. The caution light(s) comes on after the aircraft has landed and slowed to less than 50kts.
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Non-critical malfunctions are as follows: •• Flap Position data •• PSEU WOW Data
OPERATIONAL TEST OF THE STALL PROTECTION MODULE
•• ADU Data •• AHRS •• RAD ALT •• FADEC. Stick Shaker Monitoring: The SPMs monitor their related stick shakers for the following malfunctions: •• Current
•• Energize DC and AC electrical systems. Initiate a POST of the SPMs by resetting their applicable circuit breakers •• Make sure that the SPS caution lights are off •• Set and hold the STALL WARN switch in the TEST 1 position and observe the following:
•• Open Circuit •• Short Circuit Stick Pusher Monitoring: Monitoring of the stick pusher is by the SPMs and the stick pusher actuator. The SPMs monitor for the following: •• Un-Commanded Stick Push •• No Stick Push When Commanded •• SPM Stick Pusher Driver Failure The stick pusher actuator monitors for the following:
°° The left stick shaker operates °° No.1 STALL SYST FAIL caution light ON °° PUSHER SYST FAIL caution light ON •• Release the test switch and make sure that the stick shaker stops and the caution lights go OFF •• Repeat the test selecting TEST 2 position on the STALL WARN switch.
•• Loss of the 28 VDC Main Power input to the stick pusher actuator •• Difference between the PUSH1 and PUSH2 commands from the SPMs •• S e l e c t i o n o f e i t h e r / b o t h S T I C K PUSHER SHUTOFF switches •• Internal malfunction of the stick pusher actuator. When a malfunction is sensed, the stick pusher actuator sets its FAIL signal output discrete signal. Teleloading Mode: The teleloading mode supplies new operational software to the SPMs (Shop Only).
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-169
27 FLIGHT CONTROLS
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Stall Protection Modules Refer to Figure 27-110. Stall Protection Modules Locator.
27 FLIGHT CONTROLS
Each SPM is guided into the Integrated Flight Cabinet (IFC1, IFC2) using a guide rail and guide pins. The top and bottom guide pins at the IFC back panel make sure that the module and the back panel come together precisely in the correct location. The SPM are held in place using front locking levers. This gives easy installation and removal of the Line Replaceable Unit (LRU) without tools.
B
A
D
FW
A
AVIONICS RACK ELECTRICAL INSTALLATION
C
B
INTEGRATED FLIGHT CABINET
fs899a01.cgm
Figure 27-110. Stall Protection Modules Locator
27-170
FOR TRAINING PURPOSES ONLY
C
MAINTENANCE TRAINING MANUAL
Stick Pusher Actuator Refer to Figure 27-111. Stick Pusher Actuator Locator.
The stick pusher actuator needs two independent PUSH input signals from the SPMs to operate.
The stick pusher actuator mounts to the stick pusher capstan with four mounting bolts.
The PUSH1 signal operates the motor and the PUSH2 signal engages an electromechanical clutch. The output torque is nominally set to approximately 32 kilograms (kg) of column force.
The actuator turns an output pinion to move the capstan that moves the control columns forward.
NOTE The stick pusher actuator can operate against a stalling load for only a short time before overheating. The SPS has software protection to limit the stick pusher operation to a maximum of 15 seconds, with a time delay of 1 minute before the stick pusher can be activated again.
The stick pusher actuator uses two, 28 VDC electrical power sources. One supplies motor current and the other supplies the monitor circuits.
FW
D
FW
D
fs983a01.cgm
FW
D
STICK PUSHER CAPSTAN
Figure 27-111. Stick Pusher Actuator Locator
FOR TRAINING PURPOSES ONLY
27-171
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS FW
D
fs984a01.cgm
FW
D
STICK PUSHER CAPSTAN
Figure 27-112. Stick Pusher Capstan Locator
27-172
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Stick Pusher Capstan
NOTES
Refer to Figure 27-112. Stick Pusher Capstan Locator.
27 FLIGHT CONTROLS
The stick pusher capstan mounts to the aircraft structure and connects to the elevator control system with cables. Two aircraft cables attach to the capstan pulley using staged ball fittings that anchor to pockets in the pulley. The stick pusher capstan gives the mechanical interface with the elevator control system. The capstan has an adjustable override slip clutch that lets the cable pulley turn if the stick pusher actuator cannot move due to a mechanical malfunction.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-173
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Stick Pusher Quadrant Refer to Figure 27-113. Stick Pusher Quadrant Locator. The stick pusher quadrant is located below the left flight compartment floor and inputs to the pilots’ elevator forward quadrant. 27 FLIGHT CONTROLS
D
FW
FW
D
A
A
LEFT ELEVATOR FORWARD QUADRANT ASSEMBLY
D
FW
fsa09a01.cgm
A
Figure 27-113. Stick Pusher Quadrant Locator
27-174
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Stick Shaker Refer to Figure 27-114. Stick Shaker Locator.
27 FLIGHT CONTROLS
The stick shaker mounts to the control column with a bracket. The stick shaker has a housing that contains an electrical motor that turns an unbalanced weight.
NOTE Pilot Side Shown. Co-pilot Side Similar.
CONTROL COLUMN ASSEMBLY
FWD
Figure 27-114. Stick Shaker Locator
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-175
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Angle of Attack Transducer (AOA) Refer to Figure 27-115. Angle Of Attack Transducer Locator. Each AOA transducer mounts to the aircraft with five screws and two locating pins. 27 FLIGHT CONTROLS
The transducer has a fixed body that attaches to the aircraft and a transducer that moves by the relative airflow. The transducer connects to a shaft that turns freely. A counterweight and a damper attach to the shaft to balance the transducer. The transducer has two resolvers that send angular data to the SPMs. A self-regulated heater prevents icing. The body is not heated.
4 D
FW
5 1
A
LEGEND 1. Angle of Attack Transducer. 2. Cover plate. 3. Screws. 4. Sealing ring. 5. Connector.
2 FW
D
A
A
NOTE Left side shown. Right side similar.
3
Figure 27-115. Angle Of Attack Transducer Locator
27-176
FOR TRAINING PURPOSES ONLY
st019b01.cgm
MAINTENANCE TRAINING MANUAL
Stick Pusher Shutoff Annunciator Switch
Stall Warn Test Switch
Refer to Figure 27-116. SPS Stick Pusher Shutoff Annunciator Switch Locator.
The STALL WARN TEST switch mounts to the pilot’s side console panel.
The two STICK PUSHER SHUT OFF annunciator switches attach to the glareshield panel assembly.
The TEST switch provides operational tests. The switch is a positive break, double pole, toggle switch with a lever that springs back to the center OFF position.
If either switch is pushed, the stick pusher actuator will not operate and the OFF light in the switch comes on.
GLARESHIELD PANEL
OF
F fs982a01.cgm
Figure 27-116. SPS Stick Pusher Shutoff Annunciator Switch Locator
FOR TRAINING PURPOSES ONLY
27-177
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-178
ADU #1-2 A429 (OUT)
HI 16 LO 49
107 HI 108 LO
ADU #1-2 A429
ADU #1 301 GND AHRS #1-2 A429 (OUT)
223 HI 222 LO
HI D17 LO D12
135 CH GND 2 435 CH GND 4
AHRS #1
IOP #1-1
J / P1- A3 7 HI HEATER 1 115 V AC 8 LO 1 HI SPM #1 EXCITATION 2 LO 7.5 V AC 2500 HZ 22 GND
H
17 16 4 3
435 434 432 433
HI LO HI LO
AOA #1 MEAS 1 COS
201 227 226 132
HI 213 LO 212
GND HI IOP #1-1 A429 LO POST IFC #1 NG WOW 1
DASH 8 Q400
FROM IRPS TIMER & MONITOR
SEE SH 2
AHRS #1-2 A429
IOP #1
AOA #1 MEAS 1 SIN P/J1A-A1
ANGLE OF ATTACK #1 VANE
SEE SH 2
426 P PGM SP INHIB 7 8 1 2
J
HI LO HI LO
HEATER 2 115 V AC SPM #1 EXCITATION 7.5 V AC 2500 HZ
17 16 4 3
22
335 334 332 333 308 201 401
HI AOA #2 MEAS 1 COS LO HI AOA #2 MEAS 1 SIN LO PUSHER GND REF GND GND
ANGLE OF ATTACK #2 VANE
ADU #2-4 A429 (OUT)
125 HI 124 LO
129 HI 128 LO
IOP #2
POST NG WOW1 2A IFC #1 NG WOW2 8J
104 POST IFC #1 NG WOW 2
ADU #2-4 A429
HI C5 LO C10
213 HI 214 LO
W
200 FT. ALT TRIP #1
101 GND 401 GND
ADU #2
AHRS #2-3 A429 IN
425
HI LO HI DOWNLOAD C LO SPM #1 LOAD REQD DOWNLOAD D
71
329 REF SPEED
(IRPS) PANEL L VANE HEATER B FAIL P/J3 R VANE HEATER L FAIL
IRPS TIMER AND MONITOR UNIT
PRE-FLIGHT TEST
427 L VANE HEATER FAIL
FLAP POSITION INDICATION (27-53-00)
F-
327 431 430 331 330 428 328
R VANE HEATER FAIL HI FLAP POS L LO HI FLAP POS R LO FLAP HEALTHY L FLAP HEALTHY R
423 PRE FLIGHT TEST
PILOTS SIDE CONSOLE STALL PROTECTION MODULE (SPM) #1 INPUTS
200 FT. ALT TRIP #1
RADIO ALT #1
AHRS #2
REF SPEED
IOP #2-1 A429
PSEU
HI 14 LO 47
AHRS #2-3 A429 (OUT)
HI 213 LO 212
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
FROM IRPS TIMER & MONITOR
IOP #2-1
6 7 14 15 2
TEST SOCKETS
211 212 221 222 115 114 232
HI LO HI LO HI LO SPM
FLIGHT TEST A429 IN DOWNLOAD D DOWNLOAD C #1 LOAD REQD
PMAT DOWNLOAD RS422 CONNECTOR
PUSHER FAIL PUSHER PUSH
STICK PUSHER
STALL PROTECTION MODULE (SPM) #1
Figure 27-117. SPM Inputs
C U
422 408
PUSHER FAIL PUSHER PUSH
STALL PROTECTION MODULE (SPM) #1
STALL PROTECTION MODULE (SPM) #1 INPUTS
C
MAINTENANCE TRAINING MANUAL
Inputs Refer to Figure 27-117. SPM Inputs. Air Data Units: Each SPM receives an ARINC 429 data bus from both ADC No.1 and ADC No.2. The SPS uses the Mach number and the True Airspeed to perform the stall warning and stall identification calculations. The SPS uses the Calibrated Airspeed to inhibit the Stick Pusher at airspeeds greater than 215 knots, and to inhibit AOA Vane comparison monitoring at airspeeds below 60 knots. Attitude & Heading Reference System: The AHRS inputs are used to compute the angleof-attack rate of the aircraft. When the aircraft angle-of-attack rate exceeds 3° per second, the SPS computes a stick pusher advance term that is added to the angle-of-attack when determining if the stick pusher firing angle is exceeded. The stick pusher advance term is intended to compensate for the dynamics of a rapid approach to stall by activating the Stick Pusher earlier, to prevent a large overshoot into the stall. Angle Of Attack Vanes: Each of the left and right AOA Vanes contains 2 synchro resolvers, one for each SPS channel. The outputs of the AOA Vanes are AC voltages equivalent to the sine and cosine of the AOA Vane angles. The SPMs use the AOA Vane angles to determine when to activate the Stick-Shakers and the Stick Pusher. Stall Protection Module: Each SPM transmits an ARINC 429 data bus to the other SPM for internal SPS communication between the two channels. The data transmitted on these buses includes the validity status of each channel. The SPMs cross-exchange hardware discretes that indicate the healthy status of each SPM, and indicate when each SPM is ready to command a stick push. IRPS Panel: The selection of the REF SPEEDS toggle switch inputs to the SPM to set a new reference for stall warning actuations.
Timer Monitor Unit: The SPMs receive the status of the left and right AOA Vane heaters from the TMU. If the AOA vane is not heated, the SPMs prevent the SPS from using its inputs. TEST Switch: Input to SPM and Radio Altimeter to initiate a Stall Warning Test. IOP: Each SPM receives an ARINC 429 data bus from each of the IOP data concentrators. These buses transmit the Radio Altitude and FADEC data to the SPMs. The SPMs use engine torque in the Stick-Shaker firing angle computations and Power Lever Angle and Condition Lever Angle in the Stick Pusher firing angle computations. PSEU: Each SPM receives WOW1 and WOW2 discretes that indicate air/ground status based on the two nose gear Weight on Wheels proximity sensors. The SPS uses the WOW discretes to inhibit the Stick-Shakers and the Stick Pusher when the aircraft is on-ground, and to prevent the SPMs from performing POST following a power interrupt, when the aircraft is airborne. Inc. Ref Speed: The SPS uses the Inc Ref Speed switch selection in the Stick-Shaker and Stick Pusher firing angle computations. Radio Altimeter: The SPMs receive a RA TRIP discrete when the radio Altitude is less than 200 feet to inhibit the Stick Pusher below 200 feet. The SPMs also receive Radio Altitude indirectly via the IOPs. The SPS uses the actual Radio Altitude to determine aircraft air/ground status when the Weight On Wheels inputs from the PSEU disagree. PMAT: Software download. Stick Pusher: The outputs from the Stick Pusher Actuator to the SPMs are the PUSH discrete, which indicates the Stick Pusher is pushing, and the FAIL discrete, which indicates that the Stick Pusher Actuator internal monitoring is invalid, or the flight crew has depressed a Stick Pusher Shutoff switchlight.
FOR TRAINING PURPOSES ONLY
27-179
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-180 SPM #1 EXCITATION SPM #1 EXCITATION
HI LO HI LO
301 302 403 404
H
SEE SH. 1
J
CAUTION AND WARNING PANEL
FOR TRAINING PURPOSES ONLY
SHAKER FB CMD 405 CMD 305 RTN 306
A CMD B RTN
SHAKER 1
420 421 419 305 306 303 304 433 434 313 423 307 308 314 418 431 432
33 16 19 1 21 62 43 63 44 9 20 65 46 11 29 64 45 36
DECISION HEIGHT L/GEAR DOWN GND BACKCOURSE HI ROLL ATT SYNCRO LO HI BARO ALT RATE LO HI AIRSPEED IN LO BARO ALT RATE VAL G/S SELECT GND HI GS DEV LO
G/S VALID RADIO ALT +28 VDC HI RADIO ALT INPUT LO GPWS AUDIO SUPPRESS
GPWC
SHAKER 1 GPWS AUDIO SUPPRESS 312
STICK SHAKER #1 LANDING FLAP POS 1 422 LANDING FLAP POS 3 424 LANDING FLAP POS 2 312 REF GND B PUSHER CMD N SH 3
M
SPM #1-1 FT A429
+28 VDC L MAIN BUS
(K6) STICK PUSHER
TEST SOCKETS
SPM #1-1 FT A429
IOP #1
SPM #1-1 A429
HI 121 LO 122
STICK PUSH READY 313 SPM #1 HEALTHY 108
STICK PUSHER
+28 VDC 7.5A R MAIN BUS
111 HI 112 LO
HI 217 LO 218
L +28 VDC IN G +28 VDC RTN
7.5A
AVIONICS CBP
HYDRAULIC/FLAP OVERRIDE CONTROL PANEL
307 PUSHER CMD MOTOR 407 PUSHER CMD FDBK
M +28 VDC IN T +28 VDC RTN
(K1) STICK PUSHER
111 HI 112 LO
209 HI 210 LO
SPM #1-1 A429
413 STICK PUSH READY 235 SPM #1 HEALTHY
SPM #1-1 FT A429
27-30 A2 STALL PROTECTION MODULE (SPM) #2
IOP #2 SH 3
F LANDING FLAP POS 1 H- LANDING FLAP POS 3 G- LANDING FLAP POS 2
N
405 AP DISCONNECT
FGM #1
RA TEST ENABLE 414 HI 303 LO 304
R/A TEST SIG
STALL PROTECTION MODULE (SPM) #1
302 AP DISCONNECT AP DISCONNECT 310
FGM #2 STALL PROTECTION MODULE (SPM) #1
STALL PROTECTION MODULE (SPM) #1 OUTPUTS
Figure 27-118. SPM Outputs
NM- HI A- LO
RA TEST ENABLE R/A TEST SIG
RADIO ALT # 1
STALL PROTECTION MODULE (SPM) #1 OUTPUTS
MAINTENANCE TRAINING MANUAL
DECISION HEIGHT L/GEAR DOWN GND BACKCOURSE HI LO HI BARO ALT RATE LO HI AIRSPEED IN LO BARO ALT RATE VAL G/S SELECT GND HI GS DEV LO G/S VALID RADIO ALT +28 VDC HI RADIO ALT OUTPUT LO ROLL ATT SYNCRO
DASH 8 Q400
30 #1 STALL SYST FAIL 31 PUSHER SYST FAIL
STALL 1 NO WARNING 324 PUSHER SYSTEM NOT FAIL 323 STALL 1 NO WARNING FBA 424
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Flap Position: Each SPM receives left and right Flap Positions and a FLAP HEALTHY discrete from the FPIU. The SPS uses the Flap Positions to determine the Stick-Shaker and Stick Pusher firing angles.
NOTES
27 FLIGHT CONTROLS
Aircraft Configuration Module: Each SPM receives installation correction values for each AOA Vane from the ACMs. The installation correction values are specific to the individual aircraft, and are intended to compensate for errors of up to 2° in the mounting of the vanes.
Outputs Refer to Figure 27-118. SPM Outputs. Caution and Warning Panel: No.1 STALL SYST FAIL, No.2 STALL SYST FAIL and PUSHER SYST FAIL. Stick Pusher Actuator: A PUSH command from SPM No.1 to the motor, and a PUSH command from SPM No.2 to the clutch. Stick Shaker: A 2-wire connection, one wire for 28 VDC, and one wire for Return, which allows the SPMs to both command and monitor the Stick-Shaker motors. Auto Pilot: Each SPM sends a discrete to the AFCS to disengage the Autopilot when the aircraft angle-of-attack has reached the stall warning condition. EGPWS: Each SPM sends a discrete to the Enhanced Ground Proximity Warning System to inhibit the “Pull-up” aural warning when the aircraft has reached the stall warning condition. IOP 1 and IOP 2: The SPS outputs data to the FDR via IOP No.1. Each SPM outputs Left AOA, Right AOA, Left or Right Stick-Shaker Event, and Stick Pusher Event. AOA Vanes: Excitation for AOA resolvers. SPM: Cross talk between the two SPMs. Data includes health status and a discrete that indicates when each SPM is ready to command a push.
FOR TRAINING PURPOSES ONLY
27-181
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
PUSH C 'PUSH OFF CO-PILOT LT' TO ACU, 3313-P/J2, PIN 106 (22-11-00) (SEE SH. 3) +28V DC
N
28 V
L
A
A
B
A
A
A
G NORMAL
M
D
OFF H2
H3
H1 J2
J3
K
OFF
J1
P
P SP PILOT RELEASE R SP CO-PILOT RELEASE
K2
K3
STICK PUSHER
K1 L2
L3
L1 PILOTS GLARESHIELD STICK PUSHER
PUSH C 'PUSH OFF PLT LT' TO ACU, 3313-P/J2, PIN 105 (22-11-00) (SEE SH. 3)
+28V DC
M
H-
G
G-
D
A
A
B
A
A
A
NORMAL OFF H3
J3
F-
K3
L3
H2 H1
OFF
J2 J1
J-
K2 K1 L2 L1
CO-PILOTS GLARESHIELD STICK PUSHER
I-
'OFF PLT LT CMD' TO ACU, 3313-P/J1, PIN 105
N
'OFF CO-PLT LT CMD' TO ACU, 3313-P/J1, PIN 106
GLARESHIELD PANEL
Figure 27-119. Stick Pusher Shutoff Switchlights
27-182
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-119. Stick Pusher Shutoff Switchlights.
NOTES
27 FLIGHT CONTROLS
Stick Pusher Shutoff Switchlights: The Stick Pusher Shutoff switchlights are used to disable the stick pusher. If either switchlight is depressed a ground is applied to the stick pusher to disable the internal drive circuitry. The “OFF” indications in both switchlights will come on. The Stick Pusher actuator electronic circuits supply a discrete “FAIL” signal to the SPMs to cause the Pusher System Fail caution light to come on.
FOR TRAINING PURPOSES ONLY
27-183
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OVERHEAD CONSOLE
27 FLIGHT CONTROLS 1
2
3
#1 STALL SYST FAIL #2 STALL SYST FAIL
LEGEND 1. Pusher System Fail (Amber). 2. # 2 Stall System Fail (Amber). 3. # 1 Stall System Fail (Amber).
FLAP DRIVE
PUSHER SYST FAIL
PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING MAIN BAT HOT
Figure 27-120. SPM Caution Light Indications
27-184
FOR TRAINING PURPOSES ONLY
FUELING ON
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS
NOTES
Refer to Figure 27-120. SPM Caution Light Indications. The stall protection system malfunctions are shown with the caution lights that follow: 27 FLIGHT CONTROLS
•• No.1 STALL SYST FAIL •• No.2 STALL SYST FAIL • PUSHER SYST FAIL. The No.1 STALL SYST FAIL, No.2 STALL SYST FAIL: The No.1 STALL SYST FAIL or No.2 STALL SYST FAIL caution light comes on if a malfunction condition of the SPS prevents stick shaker operation. The No.1 STALL SYST FAIL or No.2 STALL SYST FAIL caution light comes on immediately, while the aircraft is on the ground or airborne, for the malfunction conditions that follow: •• Related SPM •• The two stick shakers • The two Angle of Attack transducers (AOA). Malfunctions of not critical parameters are not shown in flight. The No.1 STALL SYST FAIL or No.2 STALL SYST FAIL caution light will come on 30 seconds after the aircraft is on the ground for the malfunction of non-critical parameters. PUSHER SYST FAIL: The PUSHER SYST FAIL caution light comes on when a STICK PUSHER SHUTOFF annunciator switch is set to OFF or for any malfunction that prevents stick pusher operation. The PUSHER SYST FAIL caution light also comes on if a malfunction condition of the SPS prevents stick shaker operation.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-185
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-121. PFD Low Speed Cue Indications. A Low Speed Cue (LSC) is calculated by the SPS to show the minimum operating speed. It is a red and black band that starts with a red edge at the low speed value and extends to the bottom of the IAS scale.
WING LVL
GA ALT SEL
14000 10
200 160 IAS 120
60
5 40 20
100
0
80 140 151
073
3
6
E
12
N
HDG
0 1013 HPA TCAS STBY
VOR1 350 H 113. 50 92.1 NM
15
30
S
W
DME1 H
24
ADF1
92.1 NM
Figure 27-121. PFD Low Speed Cue Indications
27-186
FOR TRAINING PURPOSES ONLY
21
27 FLIGHT CONTROLS
It is out of view when the aircraft is on the ground.
ADF2 DME2
92.1
NM
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-122. PFD Low Speed Cue Malfunction Indications.
NOTE If AHRS1 or AHRS2 malfunctions, a CUE flag is shown on the related IAS indicator.
The two Indicated Air Speed (IAS) indicators show a vertical yellow CUE flag for the malfunction conditions that follow:
NOTE
•• Left or right AOA transducer
The AOA CUE flag is out of view when the aircraft is on the ground and the KIAS is less than 60 kts.
•• Left or right AOA transducer heat •• ADC1 or ADC2
27 FLIGHT CONTROLS
DASH 8 Q400
•• FADEC1 (A and B channels) or FADEC2 (A and B channels) • Left and right flap position.
WING LVL
GA ALT SEL
14000 10
200 160 IAS 120
60
5 40 20
100 80 140 151
0
073
3
6
0 1013 HPA TCAS STBY E
12
N
HDG
C U E
VOR1 350 H 113. 50 92.1 NM
15
30
S
24
W
DME1 H
21
ADF1
92.1 NM
ADF2 DME2
92.1
NM
Figure 27-122. PFD Low Speed Cue Malfunction Indications
FOR TRAINING PURPOSES ONLY
27-187
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Tests Refer to Figure 27-123. Stall Warn Test Toggle Switch.
27 FLIGHT CONTROLS
The STALL WARN toggle switch is set to the TEST1 position for more than 10 seconds and then to the TEST2 position to do a SPS operational test. The test has the indications that follow: •• Related STALL SYST FAIL caution light comes on •• PUSHER SYST FAIL caution light comes on •• Related stick shaker operates • Related stick pusher does not operate.
NOTE On aircraft with two Radio Altimeters (RA): When the STALL WARN toggle switch is set to the TEST1 or TEST2 position, the RA indications in the related Electronic Attitude Direction Indicators (ATT1, ATT2) shows 500 ft and then 50 ft.
CIR BKR LIGHT
W/S WIPER ICE DETECT
PILOTS FLT PNL
STEERING
LEFT SIDE CONSOLE
Stall Warn Test Toggle Switch
fs985a01.cgm
Figure 27-123. Stall Warn Test Toggle Switch
27-188
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-34-00 ELEVATOR SURFACES
GENERAL
INTRODUCTION
There are two elevator surfaces installed on the trailing edge of the left and right horizontal stabilizers. Three elevator PCUs are attached to each elevator surface to drive the elevators. A LVDT is also attached to the front of each elevator surface.
The elevator surfaces give longitudinal control of the aircraft in flight, around the lateral axis.
LEGEND
A
1. Inboard Elevator Hinge 2. LVDT Attachment 3. Inboard PCU Attachment 4. Inboard Center Hinge 5. Middle PCU Attachment 6. Outboard PCU Attachment 7. Outboard Center Hinge 8. Elevator Surface 9. Outboard Elevator Hinge 10. Static Discharge Wicks.
FWD 1
2 3
4 5 6 A
10 7 8
NOTE Left Side Shown, right Side Similar. 9
Figure 27-124. Elevator Surface
FOR TRAINING PURPOSES ONLY
27-189
27 FLIGHT CONTROLS
Refer to Figure 27-124. Elevator Surface.
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS CABLE SYSTEM
PITCH DISCONNECT CLUTCH MECHANISM
Figure 27-125. Pitch Disconnect Clutch Mechanism Component Location Index
27-190
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
27-38-00 PITCH DISCONNECT SYSTEM INTRODUCTION The pitch disconnect system allows the left and right elevator control circuits to be disconnected from each other in the event of a jam. The remaining operational circuit controls the pitch of the aircraft.
GENERAL Refer to Figure 27-125. Pitch Disconnect Clutch Mechanism Component Location Index. If a jam occurs in either control circuit, the PITCH DISC handle in the flight compartment is pulled. This will disconnect the left elevator circuit from the right elevator circuit. The pitch disconnect system has the following components: •• Pitch disconnect handle • Pitch disconnect clutch mechanism.
Pitch Disconnect Handle
Pitch Disconnect Clutch Mechanism Refer to Figure 27-125. Pitch Disconnect Clutch Mechanism Component Location Index. The clutch mechanism connects the left and right sides of the torque tube. The clutch mechanism is located in the torque tube connecting the two control columns below the flight compartment floor. When the PITCH DISC handle is pulled to the limit and rotated 90°, the cable operates the clutch lever and cam assembly. The cam followers withdraw the spring loaded clutch from the clutch plate. This disconnects the two columns. When the handle is in the engaged “IN” position, the clutch and clutch plate are kept in positive contact with each other by the clutch spring. To re-engage the pitch disconnect mechanism, the pilot and co-pilot control columns must be placed in the neutral position. Then rotate The PITCH DISC handle 90° and lower to the engaged position. When the control columns are properly aligned, the clutch returns to the engaged position by the clutch springs.
Refer to Figure 27-125. Pitch Disconnect Clutch Mechanism Component Location Index. The PITCH DISC handle operates the pitch disconnect system. The PITCH DISC handle is located in the flight compartment, on the left side of the center console. A pin in the shaft of the pitch disconnect handle rides in a slot in the shaft housing. When the handle is pulled out and rotated 90° the pin moves into the slot to keep the handle locked in the disengaged position. The PITCH DISC handle has a cable routed below the flight compartment floor and is connected to the clutch. When the handle is pulled, the clutch is disengaged. Adjustment of the pitch disconnect system is by a turnbuckle installed in the cable.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-191
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL CHECK OF THE ELEVATOR CONTROL PITCH DISCONNECT MECHANISM
NOTES
27 FLIGHT CONTROLS
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. The operational check of the pitch disconnect system is done with hydraulic power is off. Pull the pitch disconnect handle and turn 90° counterclockwise to disconnect the pitch control system. •• Move the pilot control column fully forward and aft, make sure the co-pilot control column does not move. •• Move the co-pilot control column fully forward and aft, make sure the pilot control column does not move. Turn the pitch disconnect handle 90° clockwise and make sure the pitch disconnect handle is fully retracts. •• Move the pilot or co-pilot control column fully forward and aft to make sure the pitch disconnect clutch and the control columns move together.
27-192
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-193
27 FLIGHT CONTROLS
27-194 L FLAP POSITION INDICATION
0 5
R FLAP POSITION INDICATION
FLAP INDICATOR
10
5
10
FPIU
15 35
0
FCECU
ARMING SWITCH
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
FLAP LEVER
35
IFC 1 IFC 2
FLAP LEVER RVDT
FLAP
MAINTENANCE TRAINING MANUAL
DRIVE C & W PANEL FLAP
ARM COMMAND
POWER
WOW PSEU
LANDING GEAR WARNING HORN RIGHT FLAP POSITION FEEDBACK
LEFT FLAP POSITION FEEDBACK PTU
#1 ENG
FCU
HYD PUMP
ON > 5° STBY HYD PUMP
SUPPLY HYDRAULIC POWER
#9
#8
#7
#4 FLAP POSITION DUAL RVDT
fs794a01.cgm
#6 #3
LEFT OUTBOARD FLAP
FPU
RETURN
TRANSMISSION SHAFTS
#5
#4
#3
#2
#2
ACTUATORS
#1
#3
#4
LEFT INBOARD FLAP
RIGHT INBOARD FLAP TORSION BAR
#5 #2
#1
#1
TORSION BAR
Figure 27-126. Wing Flap System
#6
#7
#8
#9
#3
#4
RIGHT OUTBOARD FLAP
FLAP POSITION DUAL RVDT
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-51-00 FLAP CONTROL SYSTEM
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The flap control system operates the flaps during extension, retraction from the selected position. The flap control system uses a digital position control loop to operate the flap surfaces by modulating the flow to the hydraulic motor of the flap power unit.
GENERAL Refer to Figure 27-126. Wing Flap System. The flap control system monitors flap position, selection signals and produces the output signals to the Flap Power Unit (FPU) to control flap movement. The flap control is comprised of the following components: •• Flap Control Unit (FCU) •• Flap selector lever/quadrant • Flap lever transducer.
FOR TRAINING PURPOSES ONLY
27-195
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
FCECU
27 FLIGHT CONTROLS
FCU
D
FW
UNDERFLOOR TRAY
3
LEGEND 2
1. Electrical Connectors. 2. Mounting Bracket. 3. Flap Control Unit Box.
1
D
FW
ft196a01.cgm
Figure 27-127. Flap Control Unit (FCU)
27-196
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
NOTES
Flap Control Unit (FCU) Refer to: •• Figure 27-127. F lap Control Unit (FCU). 27 FLIGHT CONTROLS
• Figure 27-128. F lap Control Unit Block Diagram. The FCU provides control, monitoring, and caution indications of the flap control system. The FCU is located below the cabin floor. The FCU receives its power from the 28 VDC left essential FLAP CONT circuit breaker.
FOR TRAINING PURPOSES ONLY
27-197
27 FLIGHT CONTROLS
27-198 Flap Selector RVDT
Flap Selector Arming Switch Ground
PSEU WOW
Maint Panel NVM Reset
Left Wing RVDT
Flap Position Select
Solenoid Valve on FPU
Flap Control Unit
Flap Power
Servo Valve in FPU
Flap Drive
Pressure Switch in FPU
EDP No.1 Pressure ARINC 429
Take Off Warning
fs0c0a01.cgm
Figure 27-128. Flap Control Unit Block Diagram
MAINTENANCE TRAINING MANUAL
RH Wing RVDT
DASH 8 Q400
FOR TRAINING PURPOSES ONLY
28 VDC
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-129. Flap System Caution Panel.
The FLAP DRIVE caution light illuminates for the faults that follow:
Continuous Monitoring is performed by the FCU to check for system failures. Flap failures detected by the FCU command FPU shutdown through the following actions:
•• Hydraulic pressure at FPU without selection command •• Flap stall •• Flap position output from the FCU is not valid
•• De-energizing the FPU solenoid valve • De-energizing the FPU EHSV. If a failure locks the flap system, the FLAP POWER caution light will illuminate. All further flap movements are inhibited. If an asymmetry or uncommanded movement is detected, the FCU latch relay is opened. The latch relay can only be reset with the aircraft on the ground. This is done with the maintenance panel NVM reset button after mechanically correcting the fault. The FLAP POWER caution light will remain on. It is reset at the next on ground FCU Power On BIT.
•• ARINC 429 transmission integrity. Only during Power-On BIT and functional checks • Read Only Memory failure in microprocessor of FCU. The power On Built-In-Test is performed for 5 seconds at each on ground power up. It will check the FCU components for dormant failures.
OVERHEAD CONSOLE
LEGEND 1. Flap Drive (Amber). 2. Flap Power (Amber).
The FLAP POWER caution light will illuminate for the following faults: •• Flap asymmetry
#1 STALL STAL T L F L FAI SYST FAIL
•• Flap un-commanded movement
#2 STALL STAL T L F L FAI SYST FAIL
•• Flap position transducer failure •• Flap lever transducer failure •• No hydraulic pressure after selection command •• Select command and no arm signal
1 2
FLAP DRIVE
•• Electrical power loss
PUSHER F L FAI SYST FAIL
PARKIN P G PARKING BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING
FUELING ON
MAIN BAT A HOT
•• Servo valve drive failure •• Micro-controller failure (Watch dog intervention)
CAUTION PANEL
• Latch relay open status.
Figure 27-129. Flap System Caution Panel
If the flap system is operated in a degraded mode, then the FLAP DRIVE caution light will illuminate. The caution light will not extinguish until the fault resets itself, or no longer exists.
FOR TRAINING PURPOSES ONLY
27-199
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
MIN
Flap Selector Position R A T I N G
R A T I N G
Flap Selector Lever I
FLIGHT IDLE DISC
I
Figure 27-130. Flap Selector Quadrant
27-200
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
Flap Selector Lever/Quadrant Refer to Figure 27-130. Flap Selector Quadrant. The flap selector lever provides the flap selection command. The flap selector lever is located on the right side of the center console. The flap selector lever moves in a detented cam from 0° (fully retracted) through detents at 5°, 10°, 15° to a 35° setting (fully extended). The flap selector lever must stop at each detent in order to be moved to the next detent. The lever has a spring-loaded cam follower, which engages the cam detents at each selected position. The cam follower is released from the detents by a trigger on the lever. The flap selector lever mechanically operates the flap lever transducer, which sends the flap position demand signal to the FCU. An arming switch is located on the flap selector lever. If the lever is in one of the five detented positions and the arming switch is enabled, then the enable signal to the FCU allows the flaps to move to the selected position.
OPERATIONAL TEST OF THE FLAP CONTROL MODULE The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Observe all electrical safety precautions and energize the aircraft electrical systems. •• Observe all safety precautions regarding moving control surfaces. •• Pressurize No.1 hydraulic system. •• Make sure you cannot move the FLAP selector lever until you lift the trigger. •• Move the lever to all the flap selectable positions. • Do the electrical checks in all flap positions refer to TASK 27-50-00-760-801
The flap selector lever is mechanically connected to the rudder restrictor mechanism, which restricts the rudder travel to 12 when the flap lever is in the 0° position.
Flap Lever Transducer Refer to Figure 27-130. Flap Selector Quadrant. The flap lever transducer is a single section, fivewire type RVDT. The RVDT is mechanically operated by the flap selector lever, it receives excitation from the FCU. The RVDT senses the angular position of the flap selector lever. The RVDT sends the position data to the FCU. The FCU will also receives secondary output signals from the flap position sensors and calculates the difference between the two signals. This difference is used by the FCU to move the flaps to the selected position.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-201
27 FLIGHT CONTROLS
DASH 8 Q400
27 FLIGHT CONTROLS
27-202 (L7) 28 VDC L ESS BUS
FLAP CONT
5A
A +28 VDC IN B +28 VDC RTN
RW H RW L
U V
A RW H B RW L
RW A RW B RW C
Y Z A-
C RW A E RW B D RW C
ROTARY VARIABLE DIFFERENTIAL TRANSFORMER (RVDT)
LEFT DC CBP
C
4A
WOW ARINC 429
U
114
FLAP MAINT
32-61 A1 PSEU 31-40 A1 IOM #1
T I-
1 3 2
B- FL1 A C- FL1 B D- FL1 C
9 10 NO
RIGHT FLAPS
FL1 H FL1 L SOL VALVE CRET DEHSVH EHSVL
33-11-00
6
D
ARM SW
C D
EDP NOP STBY HYD
PRESS SW PRESS RET
Z Y AB-
A SOL VALVE B RET E EHSVH F EHSVL D PRESS SW C PRESS RET
FLAP POWER UNIT (FPU)
C ARM SWITCH
29-11-00
FLAP LEVER ROTARY VARIABLE DIFFERENTIAL TRANSFORMER (RVDT)
NVM RESET A4
A1
GS1
S5
FLAP 101
MAINTENANCE PANEL
W X
A LW H B LW L
LW A V LW B W LW C X
E LW A C LW B D LW C
LW H LW L
DECK 1 C 102
51
L
ASYFLTRST
FLAP CONTROL UNIT
ROTARY VARIABLE DIFFERENTIAL TRANSFORMER (RVDT)
Figure 27-131. Flap Control System - Electrical Schematic
LEFT FLAPS
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
4 12
DASH 8 Q400
GND/DC DISCRETE O/P
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• Remove hydraulic pressure •• On the maintenance panel do as follows:
OPERATION
•• Set CDS GND MAINT
Refer to Figure 27-131. Flap Control System Electrical Schematic. When the flap lever is moved to a new selected position the FCU receives feedback from the following: •• The flap lever RVDT • A ground from the arming switch. THE FCU outputs signals to, and receives feedback from the following: •• The open solenoid that allows hydraulic pressure to the FPU. The pressure switch signals the FCU that hydraulic pressure is available. •• The Electro Hydraulic Shutoff Valve (EHSV) that is positioned to either extend or retract the flaps by the FCU. As the flaps either extend or retract, the Channel A of the RVDTs at flap actuators No.4 in each wing, feedback flap position to the FCU. When the flaps reach the position required, the FCU removes the signal, to de-energize the solenoid valve, and commands the EHSV to the neutral position. Hydraulic pressure is removed from the FPU and the irreversible flap actuators hold the flaps in the new position.
WING FLAP SYSTEM ELECTRICAL CHECKS
•• Set selector switch to the FLAP position •• Push and hold NVM RESET switch for 2 seconds •• After 10 seconds open FLAPS CONT CB (L7) •• Close the CB (L7) •• After approximately 5 seconds make sure the FLAP POWER and FLAP DRIVE caution lights come ON for approximately 3 seconds •• On ARCDU select FLAPS page •• Make sure there are no PRESENT FAULTS and no faults in FAULT HISTORY •• M a k e s u r e t h a t o n t h e S Y S T E M CALIBRATION page the values are within correct range •• Do the above check in all the other flap lever positions •• R E M E M B E R : M o v e m e n t o f t h e FLAP selector lever with no hydraulic pressure will cause faults to show on the FAULTS page •• Each time you move the FLAPS selector lever you must make the OTHER SYSTEMS and FLAPS page selection on the CDS again •• This will show the new values of the flap lever transducer • Retract the flaps.
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Move the flaps to the 35° position
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-203
27 FLIGHT CONTROLS
Normal Flap Operation
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATIONAL TEST OF THE WING FLAPS
NOTES
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. 27 FLIGHT CONTROLS
•• Pressurize No.1 hydraulic system
NOTE A crew member is necessary near the flaps to monitor flap movement.
NOTE Start the test with the flaps at the 0º position •• Obtain visual clearance to lower the flaps •• Make sure the FLAP POWER and FLAP DRIVE caution lights do not come on during the test. •• Select the flap lever to the 5º, 10º, 15º and 35º • • Make sure the flaps move smoothly to the selected positions with no unusual noises. •• Start the flap retraction test at the 350 position and then move to all selected positions. •• Make sure flaps retract smoothly and with no unusual noises.
27-204
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-205
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-52-00 FLAP DRIVE SYSTEM INTRODUCTION
The flap drive system has the following components: •• FPU •• Transmission shafts
27 FLIGHT CONTROLS
The flap drive system is responsible for moving the flaps to new selections and holding that position.
GENERAL
•• Torsion bars •• Flap actuators • Flap tracks.
Refer to Figure 27-132. Flap Drive. The system is electronically controlled and hydro-mechanically operated. It is designed to move the four flap sections together to the position set by the flap selector lever.
No. 1 Flap Track.
No. 1 Flap Actuator.
No. 2 Flap Actuator.
No. 2 Flap Track.
No. 3 Flap Track.
No. 3 Flap Actuator.
No. 4 Flap Track.
Transmission Shafts.
No. 5 Flap Track.
ft525a01.cgm
Figure 27-132. Flap Drive
27-206
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
SYSTEM DESCRIPTION Refer to Figure 27-133. Flap Drive System.
The energized solenoid valve allows the No.1 hydraulic pressure to spool the FPU SOV open. This ports hydraulic pressure to the FPU EHSV.
The FPU turns two torsion bars that turn 16 transmission shafts installed on the wing aft spars. The transmission shafts operate eight irreversible ballscrew flap actuators which drive the four sections of flap. The 4 sections of flap move along 10 tracks located under the wings.
The new flap position from the flap lever transducer is processed by the FCU and converted into a ramp command. The FCU generates the analog EHSV current command to control the hydraulic fluid flow to the FPU hydraulic motor for direction and speed of actuation.
Flap actuation begins when the FCU receives the input signals from the flap lever transducer and the wing flap position transducers. Based on flap lever transducer and flap position transducer signals, the FCU commands the FPU solenoid valve and the FPU EHSV.
At the end of actuation, the FCU de-energizes the FPU solenoid valve. This ports hydraulic system to return closing the FPU SOV.
Left Wing Rear Spar.
Right Torsion Bar.
Flap Power Unit. Left Torsion Bar. Flap Transmission Shaft No. 1. Flap Transmission Shaft No. 2.
Flap Actuator No. 1. Flap Transmission Shaft No. 3. Flap Transmission Shaft No. 4. FW
D Flap Actuator No. 2.
ft204a01.cgm
Figure 27-133. Flap Drive System
FOR TRAINING PURPOSES ONLY
27-207
27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
FLAP POWER UNIT
FW
D
27 FLIGHT CONTROLS Mounting Bracket Solenoid
Pressure Switch Electrical Connector
FW
D
EHSV
Splined Coupling
Pressure Port
Return Port Drain Port ft093a01.cgm
Figure 27-134. Flap Power Unit
27-208
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION
Refer to Figure 27-135. Flap Power Unit Schematic.
Flap Power Unit (FPU) Refer to Figure 27-134. Flap Power Unit. The FPU converts No.1 hydraulic system pressure to rotary mechanical power to operate the flap actuators. The FPU is located on the wing aft spar, to the right of the aircraft center line. The FPU has a hydraulic module and a gearbox. The hydraulic module includes the following components:
Hydraulic fluid is sent through a filter and a restrictor at the inlet port. A return line carries the hydraulic fluid back to the system reservoir. A plastic drain line carries any internal fluid leakage from the FPU to an overboard drain. The pressure switch is located downstream of the shutoff valve monitors No.1 hydraulic system pressure. This is a feedback signal to the FCU of solenoid and shutoff valve status. The FCU commands the two-stage EHSV to actuate the flap drive system. The motor is a cartridge construction axial piston. The motor drives the gearbox at rated speed of 7500 RPM.
•• Inlet filter •• Solenoid and shutoff valve •• Pressure switch
The gearbox has a two-stage spur reduction geartrain housed in an aluminum casing. The total speed reduction equals a ratio of 1:10 and output speed is 750 RPM.
•• Two-stage EHSV • Hydraulic motor.
The gearbox is lubricated for life. TORQUE MOTOR
SOLENOID VALVE
HYDRAULIC POWER SUPPLY
RETURN
SERVO VALVE
PRESSURE SWITCH
FLAP EXTEND LINE
INLET FILTER SHUT-OFF VALVE
FLAP RETRACT LINE
HYDRAULIC MOTOR
MOTOR DRAIN fsu74a01a.cgm
Figure 27-135. Flap Power Unit Schematic
FOR TRAINING PURPOSES ONLY
27-209
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Transmission Shafts Refer to Figure 27-136. Flap Transmission Shafts. The transmission shafts transmit the mechanical power generated from the FPU to the eight flap actuators. 27 FLIGHT CONTROLS
The 16 transmission shafts are located along the aft spars of the wings. Nine shafts extend outward from the FPU along the left wing aft spar to the four flap actuators. Seven shafts extend outward from the FPU along the right wing to the four right flap actuators. The shafts are high strength aluminum tube assemblies.
FW
D
NOTE No. 1 Shaft Shown. No. 8 Shaft (LH and RH) Similar.
ft212a01.cgm
Figure 27-136. Flap Transmission Shafts
27-210
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Torsion Bars Refer to Figure 27-137. Flap Torsion Bars. The two torsion bars transmit the high speed, low torque rotating force generated by the FPU to the transmission shafts and flap actuators. 27 FLIGHT CONTROLS
Each torsion bar is an aluminum alloy shaft with external splined connections.
FW
D
Flap Power Unit Assembly
3 1 2
1
D
2
FW
ft085a01.cgm
Figure 27-137. Flap Torsion Bars
FOR TRAINING PURPOSES ONLY
27-211
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Flap Actuators The flap actuators move the flap surfaces to a selected position. They also keep the selected position against the aerodynamic forces acting on the flap surfaces. 27 FLIGHT CONTROLS
There are four flap actuators installed on each wing. The flap actuators are mechanical units designed to a convert high speed, low torque rotary drive to a low speed, high torque linear drive. Each actuator transfers the rotary force to the next actuator. The No.1 and No.2 flap actuators on each wing are identical and operate the inboard flap section. The No.3 and No.4 flap actuators on each wing are constructed slightly different from each other and operate the outboard flap section. Each flap actuator includes the listed components: •• No-back/torque limiter device •• Wormgear
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Observe all hydraulic precautions •• Pressurize No.1 hydraulic system •• Observe all moving control surfaces precautions •• Move the flaps to 35º position •• Remove hydraulic pressure •• With a cloth moistened in approved cleaning solvent, remove contamination around grease fittings. Make sure the area is dry •• Check for excessive amount of grease on the ballscrew shaft (seal failure) •• Clean the ballscrew shaft with lint free cloth
• Ballscrew and ballnut. The no-back/torque limiter device limits the load transferred from the transmission shaft to the flap actuator and supplies irreversibility in both directions of rotation. The no-back device consists of two springs with input and output elements. The spring provides the irreversibility. The torque limiter device trips before reaching loads that would damage the system. The rotary motion of the worm gear disengages the no-back/torque limiter device and is transmitted to the ballnut. The ballnut changes the rotary motion into linear motion of the ballscrew. The ballscrew shaft moves the flap surfaces in the flap tracks forward or aft. The dog stops of the ballnut are machined to provide ice scrapping. Once the movement of the flap surface has stopped the no-back/torque limiter device reengages to supply irreversibility. Maximum flap travel is limited by end stops.
27-212
LUBRICATION OF FLAP BALL SCREW ACTUATORS
•• Install grease dams to the ballnut and ballscrew shaft •• Install and tighten clamp.
CAUTION: DO NOT MIX GREASE FROM DIFFERENT MANUFACTURERS OR SPECIFICATIONS. •• Use a grease gun to pump grease into the fitting until new grease comes out of the vent hole •• Remove the clamps, grease dams and excess grease •• With the grease gun apply more grease to the fittings •• Check for grease leakage at the dynamic seal of the ballnut.
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Flap Tracks
cantilever type, roller carriage tracks attached to the wing rear spar extending aft from the bottom of the wing surface.
Refer to: •• Figure 27-138. Flap Tracks. • Figure 27-140. Flap Carriage. The flap tracks control the incidence angle of the flaps during flap deployment. There are five flap tracks on each wing. Flap tracks No.1 and No.2 are cam type tracks, which support the inboard flap section. Flap track No.1 is located on the side of the fuselage. Flap track No.2 is located on the inboard side of the nacelle. The inboard flaps rollers engage in tracks No.1 and No.2. The rollers give support for the flap and allow for smooth extension and retraction of the flap. Flap tracks No.3, No.4 and No.5 support the outboard flap section. Flap track No.3 is a cam type track and is located on the outboard side of the nacelle. Flap tracks No.4 and No.5 are
The three remaining rollers are used during flight. Sideload rollers prevent lateral movement of the flaps. “0 to 16°” rollers support the flaps to the 15° decent position. “16 to 35°” rollers support the flaps from the 15° decent position to full extension of 35°. In the event of roller failure, the outboard flap is retained to tracks No.3 and No.5 by fail-safe cables, the inboard flap is retained to tracks No.1 and No.2 by fail-safe fittings. Rubbing pads are supplied to prevent excessive side movement of the flaps in the tracks. In the fully retracted position, the leading edge of the flap aligns with the upper flap shroud on the wing to give an aerodynamically smooth wing surface.
5
LEGEND 1. No. 1 Flap Track. 2. No. 2 Flap Track. 3. No. 3 Flap Track. 4. No. 4 Flap Track. 5. No. 5 Flap Track.
4 3 2
1 2 3 4 5
fsq01a01.cgm
Figure 27-138. Flap Tracks
FOR TRAINING PURPOSES ONLY
27-213
27 FLIGHT CONTROLS
The roller carriage assemblies use four different types of rollers to support the flaps. Deadweight rollers are used for support when the aircraft is on the ground.
•• Figure 27-139. No.3 and 4 Flap Rollers.
27 FLIGHT CONTROLS
27-214 LEGEND D
A A
1
8
2
8
7
FWD
3
INB
D D
FW
A fst41a01.cgm
6
A
4
VIEW LOOKING AT OUTBOARD FLAP END
A
Figure 27-139. No.3 and 4 Flap Rollers
5
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
1. Deadweight Roller. 2. 0° Roller. 3. Sideload Roller. 4. 35° Roller. 5. Deadweight Roller. 6. 16° Roller. 7. No. 4 Flap Track Carriage. 8. No. 3 Flap Track Rollers.
FW
2 3
4
5 6
LEGEND 1. Cable. 2. Deadweight Roller. 3. Cable. 4. Serrated Plate. 5. Cable Fitting. 6. 0° Rollers. 7. Cable Fitting. 8. Sideload Roller. 9. 35° Roller. 10. Deadweight Rollers. 11. Serrated Plate. 12. 16° Rollers. 13. No. 5 Flap Track Carriage.
13
7
IN
BD D
FW
8
12 9 11 A
10
27-215
Figure 27-140. Flap Carriage 27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
1
DASH 8 Q400
A
27 FLIGHT CONTROLS
27-216 L FLAP POSITION INDICATION
0 5
R FLAP POSITION INDICATION
FLAP INDICATOR
10
5
10
FPIU
15 35
0
FCECU
ARMING SWITCH
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
FLAP LEVER
35
IFC 1 IFC 2
FLAP LEVER RVDT
FLAP
MAINTENANCE TRAINING MANUAL
DRIVE C & W PANEL FLAP
ARM COMMAND
POWER
WOW PSEU
LANDING GEAR WARNING HORN RIGHT FLAP POSITION FEEDBACK
LEFT FLAP POSITION FEEDBACK PTU
#1 ENG
FCU
HYD PUMP
ON > 5° STBY HYD PUMP
SUPPLY HYDRAULIC POWER
#9
#8
#7
#4 FLAP POSITION DUAL RVDT
fs794a01.cgm
#6 #3
LEFT OUTBOARD FLAP
FPU
RETURN
TRANSMISSION SHAFTS
#5
#4
#3
#2
#2
ACTUATORS
#1
#3
#4
LEFT INBOARD FLAP
RIGHT INBOARD FLAP TORSION BAR
#5 #2
#1
#1
TORSION BAR
Figure 27-141. Wing Flap System
#6
#7
#8
#9
#3
#4
RIGHT OUTBOARD FLAP
FLAP POSITION DUAL RVDT
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-53-00 FLAP POSITION INDICATION
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The flap position indication system supplies flap position data to the flight compartment indicator and interfaces with other aircraft systems.
GENERAL Refer to Figure 27-141. Wing Flap System. This system supplies data to the: •• FCU •• FCECU and • IFCs. The data is used for flap position monitoring and recording. The flap position indication system is comprised of the following components: •• Flap Position Indication Unit (FPIU) • Flap position transducer.
FOR TRAINING PURPOSES ONLY
27-217
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
SYSTEM DESCRIPTION Refer to Figure 27-142. Flap Position Indication Unit. The FPIU is located below the cabin floor. The two flap position transducers are installed on the outboard flap actuators. 27 FLIGHT CONTROLS
The FPIU sends RVDT analog signals to the Flight Data Processing System (FDPS) in IFC1 and 2. The FDPS then converts these analog signals into digital signals for display on MFD2 as flap degrees of indication. The FCU uses RVDT channel A signals with flap position command signals to calculate and monitor the speed and direction of the flaps to the new position.
D
FW
UNDER FLOOR AREA
Flap Position Indication Unit
Mounting Bracket
D
FW
Electrical Connectors
ft239a01.cgm
Figure 27-142. Flap Position Indication Unit
27-218
FOR TRAINING PURPOSES ONLY
MAINTENANCE TRAINING MANUAL
COMPONENT DESCRIPTION Flap Position Indication Unit (FPIU) Refer to Figure 27-143. Flap Position Indication Unit Block Diagram. The FPIU supplies flap position data to the MFD indicator and interfaces with other aircraft systems. The FPIU is divided into two separate and independent analog channels (Left and Right) on a single printed circuit board. Each channel in the FPIU performs the following functions: •• Gives flap position indication to the IFC and the FCECU •• Interfaces with, and supplies electrical excitation to the flap position RVDT
The FPIU sends the analog position signals to IFC1-2 for Stall Protection Modules (SPM) 1-2 to calculate the stall angle. The FPIU sends signals to the FCECU for scheduling default values when airspeed is not valid. This FPIU data is also used for flap compensation trim to the elevator. The FPIU sends discrete signals to IFC1-2 and FCECU for flap position health. The flap indication system FPIU converts RVDT analog position signals of > 7.5 and > 25 into digital format and sends these signals to the ADU 1-2. The ADU 1-2 need to correct for the errors created to static air pressure at > 7.5 and > 25 flap. The ADU 1-2 use these signals for corrections to airspeed and altitude.
•• Demodulates the signal from the flap position RVDT •• Performs an analog monitor of its applicable RVDT • Supplies signals to the SPM 1-2 and ADU 1-2.
Left Flap Position
IFC 1
IFC 2
ADU 1
RVDT Left B
Channel 2
Right Flap Position
Left Flap Position
Right Flap Position
Left Position Healthy
Right Position Healthy
Left Flap Position FCECU Left
Channel 1
Left Position Healthy
FPIU
IFC 2
Right Flap Position Right Position Healthy
Left Flap > 7.5º
Right Flap > 7.5º
Left Flap > 25º
Right Flap > 25º
Left Flap Position
IFC 1
Right Flap Position
FCECU Right
ADU 2
RVDT Right B
Figure 27-143. Flap Position Indication Unit Block Diagram fs0c3a01.cgm
FOR TRAINING PURPOSES ONLY
27-219
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Flap Position Transducer Refer to Figure 27-144. Flap Position Transducer. The flap position transducers provide the actual flap position to the FPIU and the FCU.
27 FLIGHT CONTROLS
The two flap position transducers are installed on the outboard flap actuator of each wing. Each flap position transducer is a two section RVDT consisting of channel A and B. Channel A is electrically supplied by the FCU and supplies flap position feedback to the flap control loop. Channel B is electrically supplied by the FPIU and supplies flap position data for indication purposes.
NOTE
A
Right side shown. Left side similar. B
D
FW
A
OUTBOARD FLAP ACTUATOR ASSEMBLY
1 2 3
C
LEGEND
BD
T OU
1. Red Dot On Transducer Shaft. 2. 0° Flaps. 3. Red Band On Transducer Housing. 4. 35° Flaps.
4 B
FLAP POSITION TRANSDUCER
C
ftc01a01.cgm
Figure 27-144. Flap Position Transducer
27-220
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Refer to Figure 27-145. Flap Position Indication/Multi-Function Display.
27 FLIGHT CONTROLS
The MFD2 FLAP DEG indicator displays flap angle in degrees of incidence as an analog indication. The gauge scale has the following degree indication positions; 0°, 5°, 10°, 15°, and 35°. The FDPS displays an arrow indicator to the appropriate degree of flap incidence as signalled by the FPIU.
ELECTRICAL
MAIN AUX STBY
00 00 00
ESS MAIN SEC
PSI x 1000
Flap Position Inidication
Figure 27-145. Flap Position Indication/Multi-Function Display
FOR TRAINING PURPOSES ONLY
27-221
27 FLIGHT CONTROLS
27-222 2A
FLAP POS IND R
D 28VL2 E 28VL2RET
RIGHT DC CBP
RIGHT WING
IFC1R F IFC1RET G
67 66
SPM #1/IOM #1
IFC2R H IFC2RRET J
56 55
SPM #2/IOM #2
RFPHEAL1 M
57
SPM #2/IOM #2
MAIN +1. 00
U RWMH V RWML
RWMA H RWMB J RWMC K
W RWMA X RWMB Y RWMC
LEFT WING
LWMH F LWML G
U LWMH V LWML
LWMA J LWMB H LWMC K
W LWMA X LWMB Y LWMC
- . 34
+22
STBY
- . 34
+22
L
31-41 A2 IOP #2 IFC1L F IFC1LRET G
68 67
SPM #1/IOM #1
IFC2L H IFC2LRET J
57 56
SPM #2/IOM #2
LFPHEAL1 M
58
SPM 1/IOM 2/IOM 1
ARINC A429 MFD 2
HI 315 LO 314
DC BUS VOLT R
ESS 28. 1
28. 1
MAIN 28. 1
28. 1
SEC 28. 1
28. 1
HI LO
C 115
. 06
. 06
+1. 00
AC GEN 1 VOLT LOAD
TRU
A 115
. 06
LOAD 2
B 115
. 06
C 115
. 06
1 +1. 00
+1. 00
ARINC A429 MFD 2
FLAP DEG
SPOILERS
0 5 10 LO
(M7)
RUD
LI
RI
L ELEV
HYD PRESS PSI PK BRK STBY 1 2 3000
LEFT DC CBP
. 06 . 06
AVIONICS RACK HIRF ENCLOSURE
ROTARY VARIABLE DIFFERENTIAL TRANSFORMER (RVDT)
FLAP POS IND L
DC GEN 1 LOAD 2
A 115 B 115
31-41 A1 IOP #1
35
2A
AC GEN 1 VOLT LOAD
+1. 00
+22
AUX
HI 315 LO 314
APU GEN LOAD
0
3000
3000
3
1 0
HYD QTY % 2 3
100
100
CO-PILOT MFD PAGE 1 REFER ALSO TO CO-PILOT MFD PAGE 2 D 28VL1 E 28VL1RET FCELFT N FCELRET P
51 61
(HI) FLAP POS L (LO)
LFPHEAL2 R
62
FLAP HEALTHY L
FCERGT N FCERRET P
51 61
HI LO
RFPHEAL2 R
62
FLAP HEALTHY R
FLAP POS R
FLIGHT CONTROL SYSTEM (FCS) ELECTRONIC CONTROL UNIT (ECU) FLAP POSITION INDICATION UNIT (FPIU)
Figure 27-146. Flap Position Indication - Electrical Schematic
RO
R ELEV
100
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
RWMH F RWML G
POWER
BATT LOAD ¡ C
ARINC A429 MFD 2
ROTARY VARIABLE DIFFERENTIAL TRANSFORMER (RVDT)
+28 VDC L ESS BUS
AC EXT
POWER
DASH 8 Q400
+28 VDC R ESS BUS
ELECTRICAL
DC EXT
(F7)
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OPERATION
NOTES
Normal Flap Position Indication Operation Refer to Figure 27-146. Flap Position Indication - Electrical Schematic.
FOR TRAINING PURPOSES ONLY
27 FLIGHT CONTROLS
The FPIU sends excitation current to, and receives feedback from the RVDT’s at No.4 flap actuator on each wing. The right side signal is sent to the MFD for the flap position display. The left side is used if the right side fails.
27-223
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-54-00 FLAP SURFACES
NOTES
Refer to Figure 27-147. Flaps.
27 FLIGHT CONTROLS
The flaps are single slotted, high lift Fowler type flap. The inboard flaps have a constant chord cross-section of approximately 39% of the total wing chord. The outboard flaps have a tapered chord cross-section of approximately 39% of the total wing chord. In the fully retracted position, the flap leading edge aligns with the wing to give an aerodynamically surface.
LEGEND 1. Outboard Flap. 2. Inboard Flap.
2
1 NOTE Left side shown. Right side similar. fs525a01.cgm
Figure 27-147. Flaps
27-224
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
General •• Obey all the electrical/electronic safety precautions. •• Energize the aircraft electrical system. • Put the aircraft in the weight-on-wheels condition.
Procedure •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “up” position and make sure the CDS GND MAINT light comes on. On the CDS Maintenance panel, turn the system selector rotary switch to the FLAP position. Make sure the system selector LED is on. Push the NVM RESET (Guarded) switch. On the FLAP DRIVE SYSTEM PRESENT FAULTS page, make sure the CDS shows the NO FAULTS REPORTED message. •• On the CDS Maintenance panel, turn the system selector rotary switch to the OFF position. Make sure the system selector LED is off. •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “down” position and make sure the CDS GND MAINT light goes off. •• De-energize the electrical system. •• Remove all tools, equipment, and unwanted materials from the work area.
ON
#1 NVM RESET
ECS AUTO FAIL
OFF
FLAP PROP DEICE 2
CPC ECS
FLT CTL
2/7 ECS PRESENT FLT R CH 1/3 FLAP DRIVE SYSTEM
PROP DEICE CAL
CDS GND MAINT
PROP DEICE 1 AFR DEICE
PAA TEST
#2 PSEU
PSS MAINT
PSEU OPER
28 VDC
PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV NO FAULTS REPORTED XXXX - APU DIFF PR XXXX - CAB ACM XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
Figure 27-148. Task 45-00-27-743-802 CDS System Pages Indications
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-225
27 FLIGHT CONTROLS
ERASE THE DATA FROM THE CENTRAL DIAGNOSTIC SYSTEM (CDS) - FLAPS SYSTEM (FLAPS)
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
ERASE THE DATA FROM THE CENTRAL DIAGNOSTIC SYSTEM (CDS) FLIGHT CONTROL SYSTEM (FCS)
27 FLIGHT CONTROLS
The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
General •• Obey all the electrical/electronic safety precautions. •• Energize the aircraft electrical system. • Put the aircraft in the weight-on-wheels condition.
the FLT CTL position. Make sure the system selector LED is on. Push the NVM RESET (Guarded) switch. On the FCECU PRESENT FAULTS page, make sure the CDS shows the NO FAULT REPORTED message. •• On the CDS Maintenance panel, turn the system selector rotary switch to the OFF position. Make sure the system selector LED is off. •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “down” position and make sure the CDS GND MAINT light goes off. •• De-energize the electrical system. •• Remove all tools, equipment, and unwanted materials from the work area.
Procedure •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “up” position and make sure the CDS GND MAINT light comes on. On the CDS Maintenance panel, turn the system selector rotary switch to
ON
#1 NVM RESET
ECS AUTO FAIL
OFF
FLAP PROP DEICE 2
CPC ECS
FLT CTL
FCECU SYS FAULTS PRESENT FAULTS
PROP DEICE CAL
CDS GND MAINT
PAA TEST
1/4
#2 PSEU
PSS MAINT
PSEU OPER
NO FAULTS REPORTED
28 VDC
PROP DEICE 1 AFR DEICE
Figure 27-149. Task 45-00-27-743-801 CDS System Pages Indications
27-226
FOR TRAINING PURPOSES ONLY
Revision 0.4
MAINTENANCE TRAINING MANUAL
RETRIEVAL OF DATA FROM THE CENTRAL DIAGNOSTIC SYSTEM (CDS) FLAPS SYSTEM (FLAPS) The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
The CDS main menu is displayed as follows: •• Push the LSK 2L to access the OTHER SYSTEM menu. Page 1 of the CDS OTHER SYSTEMS menu is displayed. Push the NEXT key to access page 2 of 2. Push the LSK 1L to access the FLAP DRIVE SYSTEM PRESENT FAULTS page, 1 of 3. If no faults are reported, the CDS will show a NO FAULTS REPORTED message.
General •• Obey all the electrical/electronic safety precautions •• Energize the aircraft electrical system • Put the aircraft in the weight-on-wheels condition.
Procedure •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “up” position and make sure the CDS GND MAINT light comes on. •• Set either ARCDU to the ON position and push the MAINT key.
2/7 ECS OTHER PRESENT FLT R SYSTEM 1 CH 1/2
< EMU XXXX - ECU DIG CH 2 ANTI-SKID > XXXX - R NAPRSOV XXXX - APU DIFF PR < FCS- CAB ACMICE PROTECTION > XXXX XXXX - CAB OLT MISCMP XXXX - CAB TSOV < ECS APU > XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP < TMCU1 XXXX - SEC OLT MISCMP TMCU2 > XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP I
2/7 ECS OTHER PRESENT FLT R SYSTEM 2 CH 2/2
< FLAPS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV XXXX - APU DIFF PR < CABIN PRESS XXXX - CAB ACM CONTROL XXXX - CAB OLT MISCMP XXXX - CAB TSOV < AUXILIARY XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
CDS < AVIONICS
I
2/7 ECS PRESENT FLT R CH 1/ FLAP DRIVE SYSTEM
< OTHER SYSTEMS
PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV NO FAULTS REPORTED XXXX - APU DIFF PR XXXX - CAB ACM
< AVIONICS DATA
XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP I
Figure 27-150. Task 45-00-27-742-802 CDS System Pages Indications (1 of 2)
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-227
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
•• If faults are recorded the menu shows the present list of faults in the order of newest fault at the top, to the oldest fault at the bottom. Push the NEXT key on the ARCDU to get to the FLAP DRIVE SYSTEM FAULT HISTORY page, 2 of 3. If no faults are reported, the CDS will show a NO FAULT REPORTED message. If faults are recorded the menu shows the list of faults in the order of newest fault at the top, to the oldest fault at the bottom. Push the NEXT key to show the FLAP DRIVE SYSTEM, SYSTEM CALIBRATION page 3 of 3. The number below the TRANSDUCERS indicate the angular position of the flap in degrees and the number associated with the FLAP LEVER TRANSDUCER indicate the angular position of the flap lever in degrees.
•• On the maintenance panel, set the CDS GND MAINT toggle switch to the “down” position and make sure the CDS GND MAINT light goes off. •• De-energize the electrical system. •• Remove all tools, equipment, and unwanted materials from the work area.
2/7 ECS PRESENT FLT R CH 1/3 FLAP DRIVE SYSTEM
PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV UNCOMMANDED MOVEMENT XXXX - APU DIFF PR XXXX - CAB ACM XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
I
2/7 ECS PRESENT FLT R CH 3/3 FLAP DRIVE SYSTEM
2/7 ECS PRESENT FLT R CH 2/3 FLAP DRIVE SYSTEM
PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV NO FAULTS REPORTED XXXX - APU DIFF PR XXXX - CAB ACM XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
SYSTEM CALIBRATION XXXX - ECU DIG CH RANGE OF 2SIGNALS XXXX - R NAPRSOV - 1 TO 11 XXXX - APU DIFF PR LEFT -POSITION XXXX CAB ACM TRANSDUCER 72 XXXX - CAB OLT MISCMP XXXX - CAB TSOV RIGHT- ECU POSITION TRANSDUCER XXXX ANLG CH 2 7 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP FLAP LEVER TRANSDUCER XXXX - SEC OLT MISCMP XXXX - CAB CMP -OLT TMP XXXX - CAB MAN OLT TMP I
Figure 27-151. Task 45-00-27-742-802 CDS System Pages Indications (2 of 2)
27-228
FOR TRAINING PURPOSES ONLY
I
DASH 8 Q400
RETRIEVAL OF DATA FROM THE CENTRAL DIAGNOSTIC SYSTEM (CDS) FLIGHT CONTROL SYSTEM (FCS) The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2.
•• Push the LSK 2L to access the OTHER SYSTEM menu. Page 1 of the CDS OTHER SYSTEMS menu is displayed. Push the LSK 2L to access page 1 of 4, the FCS list of recorded faults. If no faults are reported, the CDS will show a NO PRESENT FAULTS message. If faults are recorded the menu shows the present list of faults in the order of oldest fault at the top, to the newest fault at the bottom.
GENERAL •• Obey all the electrical/electronic safety precautions. •• Energize the aircraft electrical system. • Put the aircraft in the weight-on-wheels condition.
PROCEDURE •• On the maintenance panel, set the CDS GND MAINT toggle switch to the “up” position and make sure the CDS GND MAINT light comes on. • O n t h e c e n t e r c o n s o l e s e t e i t h e r ARCDU to the ON position and push the MAINT key. The CDS main menu is displayed as follows:
FCECU SYS FAULTS PRESENT FAULTS
1/
2/7 ECS OTHER PRESENT FLT R SYSTEM 1 CH 1/2
< EMU XXXX - ECU DIG CH 2 ANTI-SKID > XXXX - R NAPRSOV XXXX - APU DIFF PR < FCS- CAB ACMICE PROTECTION > XXXX XXXX - CAB OLT MISCMP XXXX - CAB TSOV < ECS APU > XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP < TMCU1 XXXX - SEC OLT MISCMP TMCU2 > XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP I
2/7 ECS PRESENT FLT R CH 1/ FCECU FAULTS PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV XXXX - APU DIFF PR XXXX - CAB ACM NO FAULTS REPORTED XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP I
2/7 ECS PRESENT FLT R CH 1/
NO FAULTS REPORTED
FCECU FAULTS PRESENT FAULTS XXXX - ECU DIG CH 2 XXXX - R NAPRSOV PIL TRIM SW FAILURE XXXX - APU DIFF PR XXXX - CAB ACM
XXXX - CAB OLT MISCMP XXXX - CAB TSOV XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW XXXX - COMP TMP MISCMP XXXX - SEC OLT MISCMP XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP I
Figure 27-152. Task 45-00-27-742-801 CDS System Pages Indications (1 of 2)
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-229
27 FLIGHT CONTROLS
MAINTENANCE TRAINING MANUAL
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
•• Push the NEXT key on the ARCDU to get to the FCECU SYS FAULTS 2 of 4 FAULT HISTORY. If no faults are reported, the CDS will show a NO FAULTS REPORTED message. If faults are recorded the menu shows the list of faults in the order of newest fault at the top, to the oldest fault at the bottom. A maximum number of 10 faults can be displayed. Push the NEXT key on the ARCDU to get to the FCECU ANLG I/O STATUS 3 of 4. Push the NEXT key on the ARCDU to get to the FCECU ANLG I/O STATUS 4 of 4.
•• On the maintenance panel, set the CDS GND MAINT toggle switch to the “down” position and make sure the CDS GND MAINT light goes off. •• De-energize the electrical system. •• Remove all tools, equipment, and unwanted materials from the work area.
2/7 ECSS PRESENT FCECU S FAULTS FLT R CH 2/ FAULT HISTOR XXXX - ECU DIG CH 2 XXXX - R NAPRSOV IFC FAILURE XXXX - APU DIFF PR IFC FAILURE XXXX - CAB ACM ADC FAILURE ADC FAILURE XXXX - CAB OLT MISCMP ADC FAILURE XXXX - CAB TSOV XXXX - ECU ANLG CH 2 ADC FAILURE XXXX - R HP BLD SW ADC FAILURE XXXX - COMP TMP MISCMP ADC FAILURE XXXX - SEC OLT MISCMP ADC FAILURE XXXX - CABDCMP OLT TMP FCECU XXXX - CAB MAN OLT TMP I
ECS PRESENT R CH 2/7 FCECU ANLG I OFLT STATUS /
ECS PRESENT R CH 2/7 FCECU ANLG I OFLT STATUS / XXXX - ECU DIG CH 2 XXXX - R NAPRSOV L DELTA PRESS 2 7 PSI XXXX - APU DIFF PR R DELTA PRESS PSI XXXX - CAB ACM L ELEV DEG R ELEV XXXX - CAB OLT MISCMP - 7 DEG L PFEEL 7 IN XXXX - CAB TSOV R PFEEL 7 2 IN XXXX - ECU ANLG CH 2 XXXX - R HP BLD SW RUDDER 7 DE G XXXX - COMP TMP MISCMP XXXX - SEC OLT DO NOT RIG A/CMISCMP WITH DATA XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
XXXX - ECU DIG CH 2 XXXX - R NAPRSOV L IB SPOIL XXXX - APU DIFF PR R IB SPOIL XXXX CAB ACM L OB -SPOIL R OB-SPOIL XXXX CAB OLT MISCMP L PTRIM XXXX - CAB TSOV R PTRIM XXXX - ECU ANLG CH 2 XXXX R HP BLD SW AILERON XXXX - COMP TMP MISCMP XXXX - SEC OLT DO NOT RIG A/CMISCMP WITH DATA XXXX - CAB CMP OLT TMP XXXX - CAB MAN OLT TMP
2 DEG DE G 2 DEG 2 DEG DEG DEG 2 DEG
I
Figure 27-153. Task 45-00-27-742-801 CDS System Pages Indications (2 of 2)
27-230
FOR TRAINING PURPOSES ONLY
I
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
DASH 8 Q400
PAGE INTENTIONALLY LEFT BLANK
FOR TRAINING PURPOSES ONLY
27-231
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
Figure 27-154. Flight Control Electronic Control Unit
27-232
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-00-01 FLIGHT CONTROL ELECTRONIC CONTROL UNIT
NOTES
INTRODUCTION 27 FLIGHT CONTROLS
The FCECU receives electronic inputs and supplies electronic outputs for all of the primary and secondary flight control systems.
GENERAL The FCECU is a single unit divided into two channels, (referred to as the left and right channels). The left and right channels receive inputs from the pilot and/or co-pilot flight controls. The two channels function separately from each other throughout the system. The FCECU channels communicate with each other on a cross communication data link.
SYSTEM DESCRIPTION Refer to Figure 27-154. Fl i ght Co ntr ol Electronic Control Unit. The FCECU is located under the passenger cabin floor, forward of the rotor burst zone. Channel 1 (left) is powered by the 28 VDC left essential bus through the FCS ECU 1 circuit breaker (M3). Channel 2 (right) is powered by the 28 VDC right essential bus through the FCS ECU 2 circuit breaker (L6). The FCECU is an analog control unit with the digital hardware for data processing, logic control and logic monitoring. Each channel is partitioned into a command path and a monitor path.
FOR TRAINING PURPOSES ONLY
27-233
27 FLIGHT CONTROLS
27-234 Caution Lights ELEVATOR FEEL
ELEVATOR ASYMMETRY
ROLL SPLR INBD GND
#1 RUD HYD
PITCH TRIM
ROLL SPLR INBD HYD RUDDER SOV
PLA Left
Rudder Hinge Moment Limiter Lower PCU
Flap Posn Left FPIU
P Feel Actuator Left
FLIGHT CONTROL ELECTRONIC CONTROL UNIT CHANNEL #1 (LEFT)
ADU #1 AHRS #1 MFD IFC #1 A/P Trim
P Trim Actuator Active Left STBY Right I/B Spoiler L I/B Spoiler R Elevator L Aileron R
FDR Pilot Trim Switches
PSEU WOW 1
Pitch Disconnect Relay
ELEVATOR TRIM SHUTOFF (Pilot/Co-Pilot) Pushoff Switchlights
RUD 1
ROLL INBD Advisory Lights
fs793a01.cgm
Figure 27-155. FCECU/Left Channel Block Diagram
LVDTS
Inboard Spoiler Lift Dump Solenoid Valve Inboard Spoiler Lift Dump Solenoid Valve
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
28 VDC
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-155. FCECU/Left Channel Block Diagram. The FCECU functions with the flight control systems listed below:
•• Increases the pressure to the operating rudder PCU if one of the rudder PCU fails or is depressurized • Sends signals to the rudder caution lights to indicate system malfunctions.
•• Aileron Control System 27 FLIGHT CONTROLS
•• Rudder Control System •• Elevator Control System •• Flap Control System • Spoiler Control System.
Aileron Control System The FCECU does the following functions: •• Supplies electrical excitation of the LVDT attached to the right aileron. • Receives right aileron position data from the LVDT. The FCECU transmits this position data on an ARINC 429 data bus to the FDR through the IFC.
Rudder Control System The FCECU carries out the functions listed below: •• Supplies electrical excitation of the rudder position LVDT •• Receives position data from the rudder LVDT. The FCECU transmits this position to the FDR and EFIS •• Limits the rudder hinge movement by regulating the pressure in the rudder PCU according to aircraft speed • • Monitors the airspeed signals for a mismatch condition and sets the rudder PCU regulated pressure to a default mode •• Monitors the regulated pressure in the rudder PCU for discrepancies and depressurizes the PCU if it is faulty •• Depressurizes the relevant rudder PCU if either of the RUD1 or RUD2 PUSH OFF switchlight is pushed
FOR TRAINING PURPOSES ONLY
27-235
27 FLIGHT CONTROLS
27-236
Caution Lights ROLL SPLR OUTBD GRD
ROLL SPLR OUTBD HYD
RUD CNTRL
SPLR OUTBD
#2 RUD HYD
RUDDER SOV Rudder Hinge Moment Limiter Upper PCU
PLA Right
ADU #2 AHRS #2
FLIGHT CONTROL ELECTRONIC CONTROL UNIT CHANNEL #2 (RIGHT)
IFC #2 Co-pilot Trim S/ws
P Feel Actuator Right P Trim Actuator Act/Stby Right EXCITATION
POSITION DATA
O/B Spoiler L O/B Spoiler R Elevator R Rudder
LVDTS
Flight/Taxi Switch Maintenance Panel
TO LEFT CHANNEL
PSEU WOW 2
Outboard Spoiler SOV
RUD 2
ROLL OUTBD (Spoiler)
Pushoff Switchlights
Advisory Lights
fs792a01.cgm
Figure 27-156. FCECU/Right Channel Block Diagram
Outboard Spoiler Lift Dump SOV Outboard Spoiler Lift Dump SOV
MAINTENANCE TRAINING MANUAL
FOR TRAINING PURPOSES ONLY
Flap Posn Right FPIU
DASH 8 Q400
28 VDC
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Elevator Control System
NOTES
Refer to Figure 27-156. FCECU/Right Channel Block Diagram. The FCECU carries out the following functions:
27 FLIGHT CONTROLS
•• Supplies electrical excitation to the left and right elevator position LVDT • • Receives position data from the left and right elevator LVDT. The FCECU transmits this position data to the FDR and EFIS •• Changes the elevator feel forces on the control columns as a function of airspeed and acceleration •• Changes manual pitch trim rate as a function of airspeed •• Supplies automatic pitch trim when in the autopilot mode or when the flaps are extended or retracted (15° to 35°) •• Prioritizes all valid pitch trim commands in the following order: pilot, co-pilot, and then autopilot •• Monitors pitch trim actuator failures and sends a signal to the PITCH TRIM caution light and the ELEVATOR TRIM SHUTOFF switchlights • • Supplies elevator trim position to the warning tone generator in the IFC. An aural warning on takeoff is produced if the elevator trim is outside the takeoff range •• Monitors elevator asymmetry and supplies a signal to the ELEVATOR ASYMMETRY caution light •• Monitors elevator feel actuator failures and supplies a signal to the ELEVATOR FEEL caution light • Monitors the airspeed and acceleration signals for a mismatch condition and sets the pitch trim and elevator feel to a default mode.
FOR TRAINING PURPOSES ONLY
27-237
27 FLIGHT CONTROLS
27-238
PITCH TRIM
MAINTENANCE INTERFACE TO CDS
SPOILER LIFT-DUMP FCECU
BUILT-IN-TEST (BIT)
OUTBOARD SPOILER LOCKOUT
FLIGHT CONTROL SYSTEM CAUTION AND WARNING
AURAL TAKE-OFF WARNING
FLIGHT CONTROL SURFACE POSITION fss56a01.cgm
Figure 27-157. FCECU Block Diagram
MAINTENANCE TRAINING MANUAL
ELEVATOR FEEL
DASH 8 Q400
FOR TRAINING PURPOSES ONLY
RUDDER HINGE MOMENT LIMITING (HML)
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Flap Control System Refer to Figure 27-157. FCECU Block Diagram. The FCECU carries out the listed function:
•• Flight Control System caution and warning signals •• Built-In-Test • Maintenance interface to CDS.
27 FLIGHT CONTROLS
• Receives left and right flap position data from the FPIU for scheduling default values when airspeed is not valid.
Spoiler Control System The FCECU performs the listed functions: •• Locks out the outboard spoilers for airspeeds greater than 170 kt (315 km/h) •• Sends the high side signal to the inboard and outboard spoilers lift dump valves to dump the lift from the wings when the aircraft lands •• Sends a signal to the spoiler caution lights to indicate system malfunctions •• Supplies electrical excitation to all the spoiler position LVDT •• Receives position data from all the spoiler LVDT. The FCECU transmits this position data to the FDR and EFIS •• Sends a low side discrete to the magnetic coil of the FLIGHT/TAXI switch • Sends a signal to the spoiler advisory lights. Refer to Figure 27-157. FCECU Block Diagram. The FCECU functions of the flight control systems (FCS) are: •• Rudder HML •• Pitch trim •• Elevator feel •• Spoiler Lift-dump •• Outboard spoiler lockout •• Aural take-off warning •• Flight control surface position reporting to the FDR and the PFCSI through IFC
FOR TRAINING PURPOSES ONLY
27-239
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OVERHEAD CONSOLE
27 FLIGHT CONTROLS Elevator Asymmetry Elevator Feel
Roll Spoiler Inboard Ground.
Pitch Trim
Roll Spoiler Outboard Ground.
ROLL SPLR INBD GND
PIT H TRIM
STALL #1 STAL T L FAIL SYST FAI F L STALL #2 STAL T L FAIL SYST FAI F L
ROLL SPLR INBD HYD
#2 HYD FLUID HOT
FLAP DRIVE
PUSHER FAIL SYST FAI F L
PARKING PARKIN P G BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP
EMER LT L S LTS DISARMED
NOSE STEERING
ABIN PRESS
MAIN BAT A HOT
CAUTION PANEL
Figure 27-158. Caution and Warning Panel
27-240
FOR TRAINING PURPOSES ONLY
FUELING ON
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Caution Lights Refer to Figure 27-158. Caution and Warning Panel. The FCECU sends signals to the Caution and Warning panel to illuminate the caution lights that follow:
ELEVATOR FEEL •• Left or Right Pitch Feel Actuator fails, or •• Airspeed No.1 and Airspeed No.2 disagree by +/- 17 kts., or
ROLL SPLR INBD GND •• If the FCECU senses a loss of lift dump valve function, or •• If the lift dump valves are operated but the spoiler panels fail to extend after landing, or • If the spoiler panels extend when the FCECU carries out the lift dump BIT, with the FLIGHT/TAXI switch set to TAXI.
ROLL SPLR OUTBD GND •• If the FCECU senses a loss of lift dump valve function, or
• Acceleration No.1 and Acceleration No.2 disagree by +/- 0.35g for > 6 seconds.
•• If the lift dump valves are operated but the spoiler panels fail to extend after landing, or
PITCH TRIM •• One pitch trim motor, or its control card fails, or
• If the spoiler panels extend when the FCECU carries out the lift dump BIT, with the FLIGHT/TAXI switch set to TAXI.
•• Elevator trim shutoff switch light pressed, or •• Airspeed No.1 disagrees with Airspeed No.2 by +/- 17 kts., or Pitch trim input commands disagree a/c on ground.
ELEVATOR ASYMMETRY •• 4.0 ± 1.6° for airspeed > 215 kts., or • 6.0 ± 1.6° for airspeed < 215 kts.
FOR TRAINING PURPOSES ONLY
27-241
27 FLIGHT CONTROLS
DASH 8 Q400
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
OVERHEAD CONSOLE
27 FLIGHT CONTROLS Rudder Control
Spoiler Outboard
#1 Rudder Hydraulic Pressure
Roll Spoiler Outboard Hydraulic
Roll Spoiler Inboard Hydraulic
#2 Rudder Hydraulic Pressure
ROLL SPLR INBD GND
STALL #1 STAL T L FAIL SYST FAI F L STALL #2 STAL T L FAIL SYST FAI F L
ROLL SPLR INBD HYD
#2 HYD FLUID HOT
FLAP DRIVE
PUSHER FAIL SYST FAI F L
PARKING PARKIN P G BRAKE
INBD ANTISKID
OUTBD ANTISKID
LDG GEAR INOP NOSE STEERING MAIN BAT A HOT
Figure 27-159. Caution and Warning Panel
27-242
FOR TRAINING PURPOSES ONLY
FUELING ON
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Refer to Figure 27-159. Caution and Warning Panel.
NOTES
The FCECU sends signals to the Caution and Warning panel to turn on the caution lights that follow: 27 FLIGHT CONTROLS
SPLR OUTBD •• If the FCECU fails to lockout the outboard spoilers and airspeed is > 185 knots, or •• If the FCECU locks out the outboard spoilers and airspeed is < 150 knots, or •• Airspeed No.1 disagrees with Airspeed No.2 by +/- 17 kts
ROLL SPLR INBD HYD •• No.1 hydraulic system pressure is < 900 psi. • Roll spoiler cable breaks
ROLL SPLR OUTBD HYD •• No.2 hydraulic system pressure is < 900 psi and airspeed is < 165 knots, or •• If FCECU detects the outboard spoilers are inadvertently locked out and airspeed is < 165 knots • Roll spoiler cable breaks
No.1 RUD HYD •• No.1 hydraulic system pressure is < 350+/-50 psi. No.2 RUD HYD •• No.2 hydraulic system pressure is < 350+/-50 psi. RUD CTRL •• Airspeed No.1 and Airspeed No.2 disagree by +/- 17 kts., or •• F C E C U l o s e s i t s a b i l i t y t o l i m i t hydraulic pressure, or • Both hydraulic systems fail.
FOR TRAINING PURPOSES ONLY
27-243
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27 FLIGHT CONTROLS
A
LEGEND 1. Roll Outboard Annunciator Light. 2. Roll Inboard Annunciator Light.
GLARESHIELD PANEL
1
NOTE Left side shown. Right side similar.
SPOILERS
STI P SHER SH T O
LIGHT
ENGINE IRE
AP DISENG
ROLL IN D
TA I
INHI IT
ELE ATOR TRI SH T O
AEI
TERRAIN INHI IT
A RNING
PRESS TO RESET
2 fsz09a02.cgm
A
Figure 27-160. Roll Spoiler Advisory Lights
27-244
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
Advisory Lights
NOTES
Refer to Figure 27-160. Roll Spoiler Advisory Lights. The FCECU sends signals to illuminate the following advisory lights: 27 FLIGHT CONTROLS
ROLL OUTBD (spoiler) • Both outboard spoiler LVDT > 65 ROLL INBD (spoiler). • Both inboard spoiler LVDT > 65
OPERATIONAL TEST OF THE FCECU The following is an abbreviated description of the maintenance practice and is intended for training purposes only. For a more detailed description of the practice, refer to the task in the Bombardier AMM PSM 1-84-2. •• Open then close the FCS ECU 1 and FCS ECU 2 CB's to let the system do a BIT •• M a k e s u r e t h e C D S s h o w s N O PRESENT FAULTS •• Apply pressure to No.1 and No.2 hydraulic systems •• By moving the controls, check the PFCS for full movement of the following: °° Inboard and outboard roll spoilers °° Left and right elevators °° Rudder °° Check flap movement on MFD No.2 °° Do an operational test of the pitch trim system °° Do an operational test of the ground spoiler system °° Do an operational test of the roll spoiler SPLR1 and SPLR2 PUSH OFF switchlights °° Remove hydraulic pressure.
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-245
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
MAINTENANCE CONSIDERATION
Interfaces The FCECU has these interfaces:
System Test
27 FLIGHT CONTROLS
SOURCE
PARAMETER
Power-Up Built-In-Test (PBIT)
Air Data Units
Airspeed
The FCECU does a Power-Up Built-In-Test (PBIT) to verify operation of the hardware monitors. Any errors found during PBIT will be annunciated by the caution and warning system. If PBIT is interrupted, the PBIT will then be cancelled and, no faults stored. PBIT is commanded if both WOW inputs are active and both PLA microswitches indicate < PLA 47.
Attitude Heading And Reference System
Acceleration
Flap Position Indication Unit
Flap Position
Flap Control Unit
Flaps In Motion Signal
Manual Pitch Trim Switches
Pilot/Co-pilot Pitch Trim Command
Pitch Trim Disconnect Relay
Engaged/Disengaged Signal
Flight Guidance Modules
Autopilot Pitch Trim And Flap Auto Trim Commands
Power Lever Angle Microswitches
Flight Idle +12 Signal
Flight/Taxi Switch
Flight Or Taxi Mode Signals
Lvdt
Flight Control Surface Position
Maintenance Panel
Flight Control System Failures
Rudder Pcu Pressure Sensors
Rudder Pcu Pressure
Pseu
Wow
Pushoff Switchlights
Switch On/Off Signal
Continuous Built-In-Test (CBIT) Continuous Built-In-Test (CBIT) constantly monitors the FCECU hardware performance. It monitors actuator performance to the level required to meet system safety requirements. CBIT is implemented in the FCECU hardware and does not involve software. Failures are annunciated to the flight compartment.
Event-Initiated Built-In-Test (EBIT) Event-Initiated Built-In-Test (EBIT) is initiated 6.4 seconds after the aircraft has landed and the pilot has set the FLIGHT/TAXI switch to TAXI. The FCECU checks for hidden failures of the spoiler lift dump solenoids.
27-246
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-00-45 CENTRAL DATA STORAGE FLIGHT CONTROLS INTRODUCTION 27 FLIGHT CONTROLS
The CDS monitors, records, tests, and shows the condition of the: •• Flight Control System and • Flap Control System.
GENERAL Refer to Figure 27-161. CDS Interface.
CDS (IOP 1) FCECU
Flap Control Unit
IOP 2
fsq72a01.cgm
Figure 27-161. CDS Interface
FOR TRAINING PURPOSES ONLY
27-247
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
CONTROLS AND INDICATIONS Refer to Figure 27-162. CDS Ground Maintenance Toggle Switch Selection. With the CDS GRD MAINT toggle switch set, the CDS rotary selector switch is selected to a system. 27 FLIGHT CONTROLS
An amber LED will come on to show that a system is armed to erase the contents of its NVRAM. The NVRAM RESET push-button switch is pushed for 1 second and then released to erase the NVRAM.
D
FW
The rotary selector switch is set back to OFF which causes the LED to go out. The Other System pages must be viewed again to verify that there are no malfunction messages shown.
AVIONICS RACK ELECTRICAL INSTALLATION
CDS GND MAINT LED
ENGINE MAINTENANCE
PROP DEICE CAL
CDS GND MAINT
UNFEATHER
A #2
#1
RIG TRIM
CDS GND MAINT Toggle Switch
MAINT DISC
A
ON
ECS AUTO FAIL
A
A OFF
FLAP PROP DEICE 2
A
NVRAM RESET ARM LED
#2 PSEU A
G
PSS MAINT
PSEU OPER
PAA TEST
28VDC
PROP DEICE 1
CPC ECS
A
#1 NVM RESET
FLT CTL
AFR DEICE
CDS Rotary Selector
NVM RESET Push Button
Figure 27-162. CDS Ground Maintenance Toggle Switch Selection
27-248
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-00-00 SPECIAL TOOL & TEST EQUIPMENT •• GSB2700008 Rigging Pin Kit •• GSB2700008-03 Rigging Pin, 0.25 - 3.00 in. (6.35-76.20 mm) L-Pin •• GSB2700008-04 Rigging Pin, 0.25 - 4.50 in (6.35-114.3 mm) L-Pin •• GSB2700008-05 Rigging Pin, 0.25 - 6.00 in. (6.35-152.4 mm) L-Pin 27 FLIGHT CONTROLS
•• GSB2700008-05 Rigging Pin, 0.25 - 8.00 in (6.35-203.2 mm) L-Pin •• GSB2700008-06 Rigging Pin, 0.25 - 8.00 in. (6.35-203.2 mm) L-Pin •• GSB2700008-09 Rigging Pin, 0.1875 - 4.00 in. (4.76-101.6 mm) L-Pin •• GSB2700008-10 Rigging Pin, 0.1875 - 12.0 in (4.71-304.8 mm) L-Pin •• GSB2700008-16D Target - Actuator (Steel) •• GSB2700008-16D C279TARGET •• GSB2700008-27 Elevator Tension Regulator Spacer •• GSB2700008-28 Spoiler Tension Regulator Spacer Tool •• GSB2700008-29 Rigging Pin, 0.1875 - 3.00 in. (4.7-76.2 mm) L-Pin •• GSB2700008-32 Target-De-Actuator (Copper) •• GSB2700009 (or equivalent) Cable Tension Meter •• GSB3411001 Test Set - Air Data •• GSB3411011 Air Data Test Set (or equivalent) •• GSB3411012 AIR DATA KIT •• GSB3411012 or GSB3411013 Pitot/Static Pressure Test Adapter •• GSB2000009 Digital Inclinometer •• GSB2715001 Left Gear Tab Rigging Board •• GSB2715002 Right Gear Tab Rigging Board •• GSB2715002 Gear Tab Rigging Tool •• GSB2715003 Left Elevator Rigging Boards •• GSB2715004 Right Elevator Rigging Boards •• GSB2715005 Aileron Rigging Tool •• GSB2733002 Rigging Fixture - Control Column (half moon) •• GSB2733003-1 Left AOA Vane Alignment Template •• GSB2733003-2 Right AOA Vane Alignment Template •• GSB2000024 Force Meter 0-100 lbf (0-xxx Kgf) •• GSB2000024 Force Meter 0-100 lbf (0-444.82 N) (may be substituted with commercially available unit with minimum 40 lbf (177.92 N) capacity) •• 964-0446-001 Hand-held Download Unit (HHDLU)
FOR TRAINING PURPOSES ONLY
27-249
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• Commercially available Laptop computer with Flightscape software (or equivalent) installed •• GSB2715005 Aileron Rigging Tool •• GSB2400001 Multimeter, Digital Volt/ohm •• GSB2400001 Digital Multimeter-Hand Held •• PBA P/N 390600TF2-101 Extend Jam Fixture 27 FLIGHT CONTROLS
•• PBA P/N 390600TF2-103 Retract Jam Fixture •• PBA P/N 390500TF3-109 Retract Jam Fixture •• PBA P/N 390500TF3-111 Extend Jam Fixture •• 376060GSE1-1001 Cable - Rudder PCU Internal Leak Detect Valve Electrical Test •• 376060GSE1-1001 or Alternate: G700-271105-1 Test Cable •• GSB2700010 Cable, Interface for rigging and trouble shooting •• 964-0446-001 Hand-Held Download Unit (HHDLU) •• GSB2440002 DC Rectifier •• GSB2440006 DC Rectifier •• Commercially Available Spring Scale (0 - 50 Lbs, 0 - 22.68 Kg) •• GSB2900001 Hydraulic Power Unit •• GSB3240006 or equivalent Tool - Brake Application •• MHI 02F99205 or equivalent Rudder Sling •• DHC8PROX-RTP-0102 Target Proximity Sensor De-Actuator Test •• Commercially Available Force gage, mechanical spring scale •• GSB27330002 or equivalent Control Column Rigging Tool •• Commercially Available Wire Pin Removal/Insertion Tool •• 11-8073-1010 DC Ground Power Unit •• Commercially Available Hydraulic Power Unit •• GSB5180001 or GSB5180005 Electrical Bonding Tester •• Commercially Available Liquid dispenser with 0.010 inch (0.254 mm) needle (Wheller FD21D, or equivalent) •• DRUCK 405F Air Data Test Set •• GPU-600, GSB2440006 DC Ground Power Cart •• H102, GSB2900001 Hydraulic Ground Power Cart •• MITUTOYO 950-315 Clinometer •• Commercially Available Switch Insertion/Removal Tool •• (2) GSB3411012 or GSB3411013 Pitot/Static Pressure Test Adapter •• Commercially Available Dial Indicator - 0.001 in. (0.0254 mm) resolution
27-250
FOR TRAINING PURPOSES ONLY
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• Hewlett Packard HP4328A or equivalent Milliohmeter •• GSB2000009 Digital Inclinometer, Protractor •• GSB2000016 Micrometer Kit, Optical Depth •• DFM-100 Digital Force Meter, 1-100 LB •• GSB2750003 or equivalent Flap Drive Adapter 27 FLIGHT CONTROLS
•• CD-8 Cap, Protective Pressure Inlet ¾ -16 •• CD-6 Cap, Protective Pressure Inlet 9/16-18 •• GPN610-U3 Cap, Protective Tube Drain •• GPN610-U14 Kapsto Cap, Protective •• Commercially Available Removal Tool, Wire Pin •• 390700GSE1-1001 (Parker) Alignment Fixture, Spoiler Actuator Installation •• 390700GSE2-1001 (Parker) Spoiler Lock Collar •• 18-234 Extraction Tool (Vivisun)
FOR TRAINING PURPOSES ONLY
27-251
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
27-00-00 MAINTENANCE PRACTICES Refer to the Bombardier AMM PSM 1-84-2 for details on these maintenance procedures: •• AMM 45-00-27-742-801 R etrieval of Data from the Central Diagnostic System (CDS) − Flight Control System (FCS) 27 FLIGHT CONTROLS
•• AMM 27-00-01-710-802 O perational Test of the Flight Control Electronic Control Unit (FCECU) •• AMM 27-10-00-830-802 Control Column to Control Column Rigging •• AMM 27-10-00-830-803 Control Column to Aileron Quadrant Rigging •• AMM 27-10-00-830-804 Aileron Quadrant to Splitter Quadrant Rigging •• AMM 27-10-00-830-805 Aileron Splitter Quadrant to Aileron Terminal Quadrant Rigging •• AMM 27-10-00-830-806 Aileron Terminal Quadrant to Aileron Surface Rigging •• AMM 27-10-00-830-807 Rigging of the Aileron Control System Stops •• AMM 27-12-01-830-802 Rigging of the Aileron Quadrant Microswitch •• AMM 27-12-16-830-801 Rigging of the Aileron Geared Tab •• AMM 27-12-21-830-802 Rigging of the Aileron Position LVDT •• AMM 12-20-01-640-812 Lubrication of the Aileron and Roll Spoiler Chains •• FIM 27-10-00-810-801 AIL LVDT FAIL (Status) −Fault Isolation •• AMM 27-10-00-710-801 Operational Test of the Aileron Control System •• AMM 27-13-00-710-802 Operational Test of the Aileron Trim System •• AMM 27-16-00-830-801 Rigging of the Roll Disconnect System •• AMM 27-16-00-710-802 O perational Check of the Roll Disconnect Mechanism (CMR# 271000−106) •• AMM 27-21-26-000-801 Removal of the Power Control Unit/Actuator •• AMM 27-21-26-400-801 Installation of the Power Control Unit/Actuator •• AMM 27-21-00-830-810 Rigging of the Rudder Pedals to the Rudder Forward Quadrants •• AMM 27-21-00-830-811 Rigging of the Forward Quadrant to the Rudder Mixer Quadrant •• AMM 27-21-00-830-812 Rigging of the Rudder Mixer Quadrant to the Rudder Aft Quadrant •• AMM 27-21-00-830-815 Rigging of the Upper Servo Spring Strut Motion Detector •• AMM 27-21-00-830-809 Rigging of the Rudder PCUs with Hydraulic Power •• AMM 27-21-00-830-817 Rigging of the Rudder Feel and Summing Unit •• AMM 27-21-03-820-801 Adjustment of the Rudder Pedal Position−Sensor •• AMM 27-21-26-830-801 Rigging of the Rudder Power Control Units •• AMM 27-20-00-710-801 O perational Check of the Rudder Control Shut−Off Valves (CMR#272000−111)
27-252
FOR TRAINING PURPOSES ONLY
Revision 0.4
DASH 8 Q400
MAINTENANCE TRAINING MANUAL
•• AMM 27-20-00-710-802 Operational Test of the Rudder Control System •• AMM 27-20-00-710-803 Operational Check of the Rudder Control System (CMR#272000-108) •• AMM 27-21-28-710-801 Operational Test of the Rudder Shut–Off Valves •• AMM 27-22-00-710-801 Operational Test of the Rudder Trim System •• AMM 27-31-00-790-801 Elevator Droop Rate Check •• AMM 27-30-00-710-801 Operational Test of the Elevator Control System •• AMM 27-30-00-710-803 O perational Check of the Elevator Control Pitch Disconnect Mechanism (MRB# 273000−204) •• AMM 27-32-00-710-801 Operational Test of the Pitch Feel System •• AMM 27-33-26-000-801 Removal of the Angle of Attack Transducer •• AMM 27-33-26-400-801 Installation of the Angle of Attack Transducer •• AMM 27-33-00-830-801 Rigging of the Stick Pusher System •• AMM 27-38-00-710-801 Operational Test of the Pitch Disconnect System •• AMM 27-50-00-760-801 Wing Flaps System, Electrical Checks •• AMM 45-00-27-742-802 R etrieval of Data from the Central Diagnostic System (CDS) − Flaps System (FLAPS) •• AMM 27-50-00-710-801 Operational Test of the Wing Flaps •• AMM 27-51-06-710-801 Operational Test of the Flap Control Module •• AMM 27-52-00-640-801 Lubrication of the Flap Actuator Ballscrews (MRB #275000−201) •• AMM 27-61-00-710-801 Operational Test of the Roll Spoiler System •• AMM 27-61-00-710-803 Operational Test of the Spoiler Jam Detect System •• AMM 27-61-00-710-804 O perational Check of the Roll Spoiler SPLR 1 & SPLR 2 Push Off Switchlights (MRB #276000−205) •• AMM 27-61-00-710-805 O perational Check of the Roll Spoiler Cable Sensor Assembly (CMR#276000−106) •• AMM 27-61-00-710-806 O perational Check of the Spoiler Cable Disconnect Sensor (MRB#276000−208) •• AMM 27-61-03-720-801 Functional Test of the Spoiler Force Sensor •• AMM 27-62-00-710-801 Operational Test of the Ground Spoiler System •• AMM 27-71-00-710-801 Operational Test of the Aileron Gust Lock System
Revision 0.4
FOR TRAINING PURPOSES ONLY
27-253
27 FLIGHT CONTROLS
•• AMM 27-31-00-750-801 Asymmetry Check of the Elevators
More Documents from "ashspiky"
Dash 8 Q400 Maintenance Training Manual
January 2021 0
Q400_mtm_vol3a_epub
January 2021 0
Q400_mtm_vol1_epub
January 2021 0