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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.2. DOORS PASSENGER AND CARGO COMPARTMENT DOORS General Passenger Doors A319 / A320 Emergency Exit Doors A321 Emergency Exit Doors Cargo Compartment Doors Bulk Cargo Doors
DATE: JUNE 2003
Page 1
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS PASSENGER AND CARGO COMPARTMENT DOORS General
The fuselage has four passenger doors, four additional emergency exits in the cabin for the A320 / A321 and two for the A319, crew emergency exits, two cargo compartment doors plus one bulk cargo compartment door on the A320 / A321, landing gear bay doors. Necessary access for servicing and maintenance is also provided.
BULK CARGO DOOR AFT CARGO DOOR
FWD CARGO DOOR
FWD PASSENGER DOOR
AFT PASSENGER DOOR
OVERWING EMERGENCY EXITS
CREW DOOR
MENU
PASSENGER & CARGO DOORS - General
EXIT 2
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Passenger Doors
Each of the four doors is 0,81 m (32 in) wide and 1,85 m (73 in) high (clear opening dimension), and has an observation window. The doors are of fail safe plug-type construction and are impossible to open in normal cruise flight with the aircraft pressurized.
Frames
16 20
PASSENGER & CARGO DOORS - Passenger / Crew Doors - Location
66 68
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Passenger Doors (cont’d)
The door structure is conventional, consisting primarily of an outer skin, a surrounding frame and an inner skin. There is an internal structure of webs and inter-costals to provide rigidity for the doors and fixing points for the hinge and locking mechanisms. The loads resulting from cabin pressure are transferred by 7 stops located on each side of the door. A rubber pressure seal is installed around the periphery of the door and a sealing section on the door frame.
Outer skin
Outer Skin
Aluminum alloy (2024)
View A
Edge members Sealed housing Door stops
A
Inner skin (not shown)
Rooler guide
Beams
Cross members (frame segments)
PASSENGER & CARGO DOORS - Passenger / Crew Doors - Location (cont ’d)
MENU
EXIT 4
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Passenger Doors (cont’d)
Aluminum alloy (2024 / 7175) Outer skin
Cross-members View A
Beam 7 A Beam 6 Beam 5
Beam 4 Typical construction (FWD Doors) Beam 3
Beam 2
Beam 1
PASSENGER & CARGO DOORS - Passenger / Crew Doors - Location (cont ’d)
MENU
EXIT 5
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Passenger Doors (cont’d)
Beams & Junction plates Aluminum alloy (7175) View B Beam 7 B Beam 6
Beam 5
Beam 4 Typical construction (FWD Doors) Beam 3
Beams Beam 2 Junction plates Beam 1
PASSENGER & CARGO DOORS - Passenger / Crew Doors - Location (cont ’d)
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Passenger Doors (cont’d)
Edge Members
Fitting
Plate Aluminum alloy (2024) View C
C
Channel seal
FWD edge member Typical construction (FWD Doors) Aft edge member
PASSENGER & CARGO DOORS - Passenger / Crew Doors - Location (cont ’d)
MENU
EXIT 7
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS A319 / A320 Emergency Exit Doors A319
Two additional type III emergency exits, one on each side of the fuselage, are provided over the wing between frames 40 and 41. They are 1,02 m (40 in) high and 0,51 m (20 in) wide. These emergency exits are of conventional plug type construction and contain a standard size passenger cabin window. A320 Four additional type III emergency exits, two on each side of the fuselage, are provided over the wing between frames 38 and 39 and between frames 40 and 41. They are 1,02 m (40 in) high and 0,51 m (20 in) wide. These emergency exits are of conventional plug type construction and contain a standard size passenger cabin window. These emergency exits are of conventional plug-type construction and are operated like the passenger doors. The slide (optionally slide raft) is installed in a compartment below each door.
40 41 Beam 1
Beam 2 38 39
40 41
Window frame
Beam 3
A320
Beam 4
Beam 5
Beam 6
PASSENGER & CARGO DOORS - A319 / A320 Emergency Exit Doors
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS A321 Emergency Exit Doors A321
Four additional type “C” emergency exits, two on each side of the fuselage, are provided on the fuselage sections 14A and 16A between frames 35.1 and 35.3A and between frames 47.2A and 47.4. They are 1,52 m (60 in) high and 0,76 m (30 in) except for the left hand side exit in section 14A which has a height of 1,85 m (73 in). These emergency exits are of conventional plug-type construction and are operated like the passenger doors. The slide (optionally slide raft) is installed in a compartment below each door.
Section 14A Door size: 73 ’’ x 30 ’’
35.1
35.3A
47.2A 47.4
Section 16A Door size: 60 ’’ x 30 ’’
LH side
Section 16A Door size: 60 ’’ x 30 ’’
47.4
47.2A
35.3A 35.1
Section 14A Door size: 60 ’’ x 30 ’’
RH side
PASSENGER & CARGO DOORS - A321 Emergency Exit Doors
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Cargo Compartment Doors
Two doors in the lower RH side of the fuselage provide access to the cargo holds. The forward door is located between frames 24A and 28. The position of the aft cargo hold door is between frames 52A and 56 for the A320 / A321 and between frames 55A and 59 for the A319. Both doors are 1,82 m (71.5 in) wide and 1,24 m (49 in) high. The doors are opened outwards and upwards hydraulically and extend over the entire height of the holds. The doors are manually locked and unlocked from outside and retained by a multi-hook system in the closing position. The cargo doors are designed to carry the hoop tension loads from internal pressure. With this consideration they are of conventional design having an outer and inner skin with an internal structure of vertical beams and machined frames, the upper ends of which connect to the piano hinge and the lower ends attachment for the locking hooks. The door frames are in line with the main fuselage frames and with auxiliary frames.
FWD FWD cargo door
A320 / A321 Fr. 24A Fr. 28
AFT cargo door
Fr. 52A Fr. 56 Bulk Cargo door
Fr. 60 Fr. 62 FWD cargo door
A319
Fr. 24A
AFT cargo door
Fr. 28
Fr. 55A
Fr. 24A
Fr. 52A Fr. 55A
Fr. 59
PASSENGER & CARGO DOORS - Cargo Doors - General
FWD cargo door A319 / A320 / A321 AFT cargo door A320 / A321 A319
MENU
Fr. 28
Fr. 56 Fr. 59
EXIT 10
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Cargo Compartment Doors (cont’d)
Beam 1 Piano hinge assembly
Actuator fittings Beam 2
Inner skin
Beam 3
Beam 4
Frames
Outer skin Fittings inner assembly Edge members E.g: FWD Cargo Door
Cover Assembly
PASSENGER & CARGO DOORS - Cargo Doors - Construction Details
MENU
EXIT 11
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Cargo Compartment Doors (cont’d)
Frame details Outer skin
Aluminum alloy (2024)
Beam 1
Aluminum alloy (7010)
Example of outer skin thickness (SRM extract) Beam 2 Frames
Beam 3
Beam 4
Frame forks
PASSENGER & CARGO DOORS - Cargo Doors - Construction Details (cont ’d)
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Bulk Cargo Doors The bulk cargo door is basic for the A320 and A321.
It is a conventional plug-type door, situated at the rear of the bulk compartment between frames 60 and 62. The size is 0,86 m (34 in) in width and 0,94 m (37 in) in height. The door is operated, locked and unlocked manually. It is opened by being pushed inwards and upwards and is locked in the open position on the ceiling of the compartment. (In this compartment nets are provided to maintain the area clear for the door to open). The weight of the door is compensated by a torsion bar. The door is connected to the door locking warning system. It is possible to open the door from the inside.
62
A320 / A321 Hinge fitting 61
60
Beam 1
Hinge fitting Beam 2
Bulk Cargo door Beam 3
Fr. 60 Fr. 62
Beam 4
Beam 5
Door stops
Inner handle Hook Outer handle
Frame segments
Locking shaft
PASSENGER & CARGO DOORS - Bulk Cargo Door - Construction Details
MENU
EXIT 13
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STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.2. DOORS LANDING GEAR DOORS General Nose Landing Gear Doors Main Landing Gear Doors
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS LANDING GEAR DOORS General
The Nose Landing Gear doors (Forward and Aft doors) are of sandwich construction with Nomex honeycomb core and CFRP (Carbon Fiber Reinforced Plastic) outer and inner skins. An Additional Bronze mesh is bonded as last layer on the outer skin (between CFRP skin and paint scheme) for electrical continuity reasons (lightning strike protection). In the fitting areas, bonding braids ensure the electrical connection to the metallic fuselage structure. The Main Landing gear doors consists of: - A main door, hinged to the center fuselage keel beam, - A leg fairing door, attached to the main landing gear, All these doors are of sandwich construction with Nomex honeycomb core with CFRP skins.
MAIN DOORS
HINGED DOOR LEG FAIRING DOOR
MAIN DOOR
NLG DOORS
HINGED DOOR LEG FAIRING DOOR MENU
LANDING GEAR DOORS - General
EXIT 16
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Nose Landing Gear Doors The nose landing gear doors have five parts:
- Two forward doors, hydraulically actuated, which can be closed with the gear in the extended or retracted position. These doors are of sandwich construction with a skin made of carbon fiber reinforced plastic. They are hinged to the landing gear bay longitudinal edges. - Two aft doors, which are also of sandwich construction with a skin made of carbon fiber reinforced plastic. - One leg door made of aluminum alloy.
Fr.9 NOSE GEAR DOORS: 52.82.00
Fr.20
FITTING
AFT DOORS CFRP
OUTER
BRONZE Mesh CFRP Skin
FWD DOORS CFRP
CFRP Skin
INNER
LANDING GEAR DOORS - Nose Landing Gear Doors
MENU
EXIT 17
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Main Landing Gear Doors
The main landing gear doors, constructed from carbon fiber composite materials for each gear, have three parts: - A main door, hydraulically actuated, which is hinged to the fuselage keel beam parallel to the aircraft center line and can be closed with the gear in the extended or retracted position. - A door attached to the gear leg. - A small door hinged to the wing structure in the neighborhood of the upper end of the main leg. All doors form part of the fuselage belly fairing and the wing lower surface when in closed position.
MAIN GEAR DOORS: 52.81.00 OUTER CFRP Skin
INNER
HINGED DOOR CFRP (52.81.11)
CFRP Skin
GEAR LEG CFRP (52.81.13)
MAIN DOOR CFRP (52.81.14)
LANDING GEAR DOORS - Main Landing Gear Doors
MENU
EXIT 18
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STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.3. FUSELAGE FUSELAGE GENERAL DESIGN PRINCIPLES General Layout A319 Fuselage Sections A320 Fuselage Sections A321 Fuselage Sections Typical Section Structure Arrangement Skin Panels Skin / Frame / Stringer Typical Attachment Longitudinal Skin Joints Circumferencial Skin Joints Passenger Compartment Floor Structure Cargo Compartments Cabin Windows
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS FUSELAGE GENERAL DESIGN PRINCIPLES General Layout
Frames from section 13/14 and 4 frames from section 16/17. One of the over wing emergency exists is removed. Due to the shortened fuselage the rear cargo door is relocated and the belly fairing is modified because of the cargo door location. The A321-100 is a stretched variant of the A320-200 aircraft, achieved by the addition of two new fuselage sections 14A and 16A, placed forward and aft of the center fuselage section. Each of these new sections includes a pair of emergency exits. The four exits of fuselage section 15 are deleted. Due to weight increase, other parts e.g. wing, center wing box or center fuselage are strengthened or redesigned.
14A 14A
16A 16A
13/14
A321
12
24
18 18
16/17 16/17 35
35.8
47
47.5
64
70
+ 5 frames
+ 8 frames
A320 16/17 16/17
13/14 13/14 35
32
47
18 18
51 - 4 frames
- 3 frames
A319 13/14 13/14 - 1 frame
18 18
16/17 16/17 - 0.5 frame - 3 frames
A318 16/17 16/17
13/14 13/14 FUSELAGE GENERAL DESIGN PRINCIPLES - General Layout
18 18 MENU
EXIT 22
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS A319 Fuselage Sections
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Fuselage Sections
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS A321 Fuselage Sections
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Typical Section Structure Arrangement
The main structure of fusleage typical sections is primary, made of aluminum-alloy. It has skin plates, frames, stringers and skin stiffeners, they are riveted together to make the fuselage shell. Top beams and seat tracks, riveted to crossbeams make the cabin floor stronger. Support struts and diagonal braces make the fuselage structure stronger.
LONGITUDINAL SKIN JOINT
SKIN PANELS
CIRCONFERENCIAL SKIN JOINT
SKIN, STRINGER & FRAME ASSEMBLY
FLOOR STRUCTURE / FUSELAGE SHELL ATTACHMENTS FLOOR STRUCTURE
CARGO FLOOR STRUCTURE
FUSELAGE GENERAL DESIGN PRINCIPLES - Structure General
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Skin Panels General Arrangement
FUSELAGE GENERAL DESIGN PRINCIPLES - Skin Panels - Arrangement
MENU
EXIT 27
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Skin Panels (cont’d) Materials Summary
SKIN
A 320
Stretch - Formed or Rolled plates
Stretch - Formed or Rolled plates chemically milled
Integrally machined parts METALLIC MATERIALS Skins - single curvature - double curvature - machined Stringers
Frames - standard - machined
FWD Bulkhead - skin - stringers Rear Bulkhead - frame - segments
Keel beam elements sheet extrusion sheet
7175 7050 7175 7075 7075 7175 7175 7010 7175 2024 7175 2024 7050 7475
T73 T76511 T73511 T76511 T76511 T6511 T73XX T73651 T7351 T351 T7351 T351 T76511 T7611
T3 T7310
THS actuator fitting
7075
T7351
T73651 T42
Vert. Stab. Attach. Fittings
7010/7050
T735
sheet sheet plate
2024 2024 7075
T3/T351C T42 T7351
sheet extrusion
2024 2024
T351 T351X
sheet plate
2024 7010/7050 2024 7075 7175
T351/T42 T73651 T351 T7351 T7351
sheet extrusion
2024 7175
plate sheet
7010/7050 2024
Window frame Floor beams
forging extrusion
Floor struts Seat tracks
extrusion extrusion
Windscreen frame
forging or plate
NLG bay
plate
plate
forgings
FUSELAGE GENERAL DESIGN PRINCIPLES - Skin panels - Materials Summary
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Skin Panels (cont’d) Chemically Milled Skins
SKIN
A 320
Stretch - Formed or Rolled plates
Stretch - Formed or Rolled plates chemically milled
Integrally machined parts EXAMPLE OF CHEMICALLY MILLED PANEL
FUSELAGE GENERAL DESIGN PRINCIPLES - Skin panels - Chemical Milling
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Skin / Frame / Stringer Typical Attachment
General Design The skin plates are made of aluminum-alloy sheets and stringers which are riveted to them make them stronger. Skin plates are preformed to the contour of the fuselage before they are riveted to the frames. The frames are the stiffeners that go around the fuselage shell. They are made of aluminum-alloy sections which are formed or machined. Clips, with cut-outs for stringers, are riveted between the frames and the skin plates. Door frames and beams make the frame structure stronger in the area of theaft passenger/crew and cargo compartment(s) doors. The stringers are the longitudinal stiffeners of the fuselage shell. They are made of aluminum-alloy Z-sections which are formed, extruded or machined. They are riveted between the frames and the skin plates. Skin stiffeners make the skin stronger in areas where there are no stringers. The skin stiffeners are riveted to the skin.
A-A
Frame profile Frame Skin Frame cleat
Stringer
Cleat Skin
A
A FUSELAGE GENERAL DESIGN PRINCIPLES - Skin/Frame/Stringer Attachments
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Skin / Frame / Stringer Typical Attachment (cont’d) Frame Splicing
B
Fuselage skin Frame profile Cleat
Splice
Frame
Splice
B
FUSELAGE GENERAL DESIGN PRINCIPLES - Skin/Frame/Stringer Attachments
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Longitudinal Skin Joints Location
1
12 11
24
35
12
47
13/14
15
64 16/17
70 18
77 19
Stgr 6
Stgr 30
Stgr 18
Stgr 6
Stgr 16
Stgr 25 Stgr 32 Stgr 41 19 77
Stgr 32
Stgr 18
Stgr 32
18 70
16/17 64
58
Stgr 16
Stgr 32 Stgr 41 15 47
13/14 35
12 24
11 12
1
E.g: A320 FUSELAGE GENERAL DESIGN PRINCIPLES - Longitudinal Skin Joints - Location
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Longitudinal Skin Joints (cont’d) Details
A-A Ti Crack stopper
Upper panel
A
41 STGR 18
22
A Frame 21 25 Lower panel
Stringer
Crack stopper
60mm Wedge
Top Fuselage
Upper panel
Upper rivet row
Lower rivet row
FUSELAGE GENERAL DESIGN PRINCIPLES - Longitudinal Skin Joints - Details
MENU
Lower panel
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Circumferencial Skin Joints Location
2 2
A321
12
2
2
35
24
3
3
35.8
47
64
70
2 2
2
2
35
32
2
47
- 1 frame
51 - 4 frames
2
2
2
2
- 3 frames
A319
47.5 + 5 frames
+ 8 frames
A320
2
3
3
2
2
- 0.5 frame - 3 frames
A318
2
2
2
3
2
FUSELAGE GENERAL DESIGN PRINCIPLES - Circum. Skin Joints - Location
2
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Circumferencial Skin Joints (cont’d)
Details Typical design: 2 fastener rows each side of the joint. Three fastener rows each side of the joint starting at window line for: - A319 at frame 47, - A321 at frames 35.8, 47 and 47.5.
CONNECTING SECTION E.g: 2 fastener rows circumferential joint (A320)
Frame
Cleat
Flight direction
stringer
3 fastener rows above window line: - at frames 35.8, 47 and 47.5 for A321, - at frame47 for A319.
Junction fitting
Skin
stringer
Buttstrap
Skin
FUSELAGE GENERAL DESIGN PRINCIPLES - Circum. Skin joints - Details
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Passenger Compartment Floor Structure
The cabin floor structure includes: - cross beams (Y), - seat tracks and false (or dummy) seat tracks (X). The longitudinal floor members are bolted on top of the cross beams and the floor panels on the longitudinal beams. Seat tracks and cross beams are made from Aluminum Alloy extruded sections. Floor panels are made of composite sandwich construction. The cross beams are supported on each side of th ecargo compartment by extruded Aluminum ‘C’-section struts.
Seat rail
Cross beam
Support struts
Cross beam to frame attachment
Cross beam
Seat tracks Dummy or false seat tracks
Support struts
FUSELAGE GENERAL DESIGN PRINCIPLES - Passenger Cabin Floor Structure
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Passenger Compartment Floor Structure (cont’d)
Section C-C
Detail A
Detail B
C
C
Detail C
A
Cross beam
B Seat tracks Dummy or false seat tracks
Support struts
C
FUSELAGE GENERAL DESIGN PRINCIPLES - Passenger Cabin Floor Structure
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Passenger Compartment Floor Structure (cont’d)
False track splicing
‘ X ’ load fittings
FUSELAGE GENERAL DESIGN PRINCIPLES - Passenger Cabin Floor Structure
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Cargo Compartments
General The floor of the two cargo compartments is of sandwich construction. The panels being attached by bolts are easily removable.
FWD GARGO COMPARTMENT Side wall Side wall lining panels Net strut 34 31
Partition 28
AFT GARGO COMPARTMENT 63 Standard version 59 Side wall 56 panels 53 52A
65
24A 50 47 Partition Tie down points
Door net Standard version
Floor panels Tie down points Floor panels Version with C.L.S.
Roller track Ball mats Version with C.L.S.
Roller track
Ball mats
FUSELAGE GENERAL DESIGN PRINCIPLES - Cargo Compartments
MENU
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XSM13A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Cargo Compartments (cont’d)
Floor Structure The floor is supported by an aluminum alloy structure attached to each fuselage frame. The structure consists of a transverse beam attached to the frame and is supported by a trusswork.
E.g. Rear Fuselage
FWD
E.g. FWD Fuselage
Fr.30
FWD Fr.31 Fr.32 Fr.33
Cross beams Fr.34
Fittings
Webs Posts FUSELAGE GENERAL DESIGN PRINCIPLES - Cargo Compartment Floor Structure MENU
EXIT 40
DATE: JUNE 2003
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XSM13A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Cabin Windows
The cabin windows are 230 mm (9.1 in.) wide and 330 mm (13 in.) high, and are fitted between the frames at intervals of 533.4 mm (21 in.). Window frames: The main window frame is made from a drop-forging which has a T-shaped cross section. To achieve good fatigue and damage tolerant properties, the window frame is designed on the basis of the following criteria: - the inner flange of the forging accommodating the panes is free from holes since it is necessary to keep this flange free from stress raisers to ensure a good fatigue life, - the outer flange is riveted to the structure and has a varying cross section which gives good load distribution characteristics, - the third flange is a stiffener and serves as a crack-stopper, - an integrally machined doubler. Window panes: Each window is made with three panes. The inner pane, which is decorative and non load-carrying, is incorporated in the interior cabin lining.
Eye Bolts
Window frame
Seal
Retainer ring 4 mm thick Inner pane
9.5 mm thick outer pane
FUSELAGE GENERAL DESIGN PRINCIPLES - Cabin Windows
MENU
EXIT 41
DATE: JUNE 2003
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XSM13A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Cabin Windows (cont’d)
Window panes (cont’d): Each of the outer panes can carry the full differential cabin pressure (fail safe). These panes are made of stretched acrylic. Their thickness are 9.5 mm for the outer and 4mm for the inner pane. These panes are mounted in a dir-cast seal and fitted into the frames by means of a retainer ring which is fixed by six bolts to the frame. Near the bottom of the inner pane, at the centre, there is asmall vent hole to ventilate the gap between the two structural plies and to pressurized the outer panel only. However, in the event of a failure of the outer pane, the inner pane is able of carrying the full differential pressure.
Window frame Seal
6 eye Bolts 4 mm thick Inner pane
Retainer ring
9.5 mm thick outer pane
FUSELAGE GENERAL DESIGN PRINCIPLES - Cabin Windows (cont’d)
MENU
EXIT 42
DATE: JUNE 2003
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XSM13A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Cabin Windows (cont’d)
Window panes (cont’d): Each of the outer panes can carry the full differential cabin pressure (fail safe). These panes are made of stretched acrylic. Their thickness are 9.5 mm for the outer and 4mm for the inner pane. These panes are mounted in a dir-cast seal and fitted into the frames by means of a retainer ring which is fixed by six bolts to the frame. Near the bottom of the inner pane, at the centre, there is asmall vent hole to ventilate the gap between the two structural plies and to pressurized the outer panel only. However, in the event of a failure of the outer pane, the inner pane is able of carrying the full differential pressure.
DATE: JUNE 2003
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XSM13A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Cabin Windows (cont’d)
Window panes (cont’d): Each of the outer panes can carry the full differential cabin pressure (fail safe). These panes are made of stretched acrylic. Their thickness are 9.5 mm for the outer and 4mm for the inner pane. These panes are mounted in a dir-cast seal and fitted into the frames by means of a retainer ring which is fixed by six bolts to the frame. Near the bottom of the inner pane, at the centre, there is a small vent hole to ventilate the gap between the two structural plies and to pressurized the outer panel only. However, in the event of a failure of the outer pane, the inner pane is able of carrying the full differential pressure.
DATE: JUNE 2003
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XSM13A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.3. FUSELAGE
FUSELAGE SECTIONS 13/14 & 14A General Typical Construction
DATE: JUNE 2003
Page 45
XSM13B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS FUSELAGE SECTIONS 13/14 & 14A General
This region of the fuselage lies between frames 24 and 35. On A319, the section 13/14 is shorter by three frames than on A320/A321. It contains the front part of the passenger cabin and, beneath the cabin floor, the forward freight compartment. The forward cargo door is on the starboard side. The ends of the cabin floor cross beams are attached to the frames, supported on each side of the cargo compartment by extruded aluminum alloys struts. In the lower region of each frame, an aluminum alloy structure is installed to support the cargo compartment floor. A321 section 14A: The A321 section 14A extends from frame 35 to frame 35.8. It provides part of the passenger cabin in the upper section, and beneath the cabin floor, the rear part of the forward cargo compartment. Section 14A is of similar construction to section 13/14 but incorporates the emergency exit cut-outs (one on each side of the fuselage) between frames 35.1 and 35.2A. The cut-out has a size of 73in x 30in on the left and 60in x 30in on the right. The slide/slide-raft is installed in a separate compartment below each door. In the lower aft area of this section, attachments are provided for the forward belly fairing assembly.
35
A319
Section 13 / 14
24
35.8
35
Section 13 / 14
A321
35 24
A320 24
Section 14A
Section 13 / 14
MENU
SECTIONS 13/14 & 14A - General
EXIT 46
DATE: JUNE 2003
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XSM13B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Typical Construction
This section is of conventional construction consisting primarily of chemically milled skin panels, frames and stringers formed from sheet metal. The ends of the cabin floor cross beams are attached to the frames, supported on each side of the cargo compartment by extruded aluminum alloys struts. In the lower region of each frame, an aluminum alloy structure is installed to support the cargo compartment floor. The fuselage frames are arranged at regular intervals of 533.3mm (21in). The standard frames have a common Z-shaped section made from formed sheet, which provides a continuous structural member attached to the skin and stringers by sheet metal cleats.
Skin panels longitudinal joints
Typical frames Windows
Floor panels
Typical stringers
Forward part of belly fairing
Cargo compartment fixed partitions
Seat rails Skin panels
Vertical struts Floor cross beams MENU
SECTIONS 13/14 & 14A - Typical Construction
EXIT 47
DATE: JUNE 2003
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XSM13B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Typical Construction (cont’d)
The cargo door surrounding frames are machined and stabilized by longitudinal webs. In addition, the lower section is reinforced by a box type structure.
FWD CARGO DOOR SURROUNDING STRUCTURE
Fr. 27
Fr. 24
Fr. 28
Fr. 26
Stgr 23RH Fr. 24A
Stgr 39RH
SECTIONS 13/14 & 14A - Typical Construction (cont’d)
MENU
EXIT 48
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.3. FUSELAGE
NOSE FORWARD SECTION 11/12 General Layout Radome Forward Pressure Bulkhead Frames Windshield Flight Deck Structure Lower Fuselage Upper Fuselage (cabin part)
DATE: JUNE 2003
Page 51
XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS NOSE FORWARD FUSELAGE 11/12 General Layout
This section of the fuselage extends from the radome nose to frame 24. It includes the following elements: - the radome for the weather radar antenna, - the forward pressure bulkhead, - the flight deck in the upper region (frame 1 to 11) and the windshield structure, - the upper fuselage aft of frame 11 which forms the forward passenger compartment and contains two passenger doors, - the lower fuselage from frame 1 to frame 24 with the electronic compartment and the nose landing gear bay. A321: Section 11/12 of the A321 is basically common with the A320 section, but incorporates 4 reinforcements: - reinforcement of the fuselage panel below the passenger doors, increase of thickness for the lateral stringer between frame 20 and 21 below the pax door, - reinforcement of the vertical beam at frame 19, - reinforcement of the vertical beam lateral panel junction, - these reinforcements only apply to R/H side. SECTION GENERAL LAYOUT (1/2)
CABIN
FLIGHT DECK
12 8
1
20
16 14
2
4 3
6 5
10 7
9
13
18 15
17
23 22
19
21
11 Passenger door cutout
FWD pressure bulkhead Radome
Nose landing gear bay MENU
SECTION 11/12 - General Layout
EXIT 52
DATE: JUNE 2003
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XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS General Layout (cont’d)
Basically the skin panels are chemically milled from 2024 clad aluminum alloy, with the exception of the titanium plates above and below the windshield frame. (Bird impact protection). Longitudinal joints are reinforced with extruded stringer in the same way as for the other fuselage joints.
SECTION GENERAL LAYOUT (2/2)
Titanium plates FLIGHT DECK FLOOR SUPPORT WINDSHIELD
UPPER FUSELAGE
CABIN FLOOR STRUCTURE
SKIN PANELS
NOSE LANDING GEAR BAY
LOWER FUSELAGE
MENU
SECTION 11/12 - General Layout (cont’d)
EXIT 53
DATE: JUNE 2003
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XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Radome
The radome serves as a protective dome for the radar antenna and has been adapted to the aerodynamics of the fuselage nose. The design of such a unit is subject to the requirements of the radar optics. These are high transmission, low reflection and low absorption.
RADOME
Quartz Radome
Hinge Fitting
Radome panel (Quartz) Hinge fittings
Frame Arrester pick-up fittings Lightning strike protection strips Copper MENU
SECTION 11/12 - Radome
EXIT 54
DATE: JUNE 2003
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XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Forward Pressure Bulkhead
The forward pressure bulkhead assembly comprises a flat sheet (1.6 mm thick) reinforced by horizontal profiles on the front face and vertical beams on the rear face.This sheet is riveted to frame 1 bent section and vertical beams are picked-up by webs attached to upper and lower skin panel.
FWD PRESSURE BULKHEAD
A
Section A-A
Fr. 1 Radar antenna support
Section B-B
B
B
Bird impact protection Radome hinge points
Frame 1 Radome lock fitting
Horizontal stiffeners
Fr. 1
A
A A Fr. 2
Flat panel Radome lock fittings
Lower skin MENU
SECTION 11/12 - FWD Pressure Bulkhead
EXIT 55
DATE: JUNE 2003
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XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Frames
This part of the fuselage is mainly dimensioned by internal pressure and landing cases. Consequently the following principles have been adopted: - From frame 1 to frame 21 the mean frame pitch is 230 mm (approximately half the typical pitch in the main fuselage sections). In the lower fuselage from frame 9 to frame 21 and in the upper fuselage from frame 16 skin panels are stabilized by stringers interrupted at each frame intersection. - From frame 21 to frame 24 the typical frame pitch is 533.4 mm and continuous stringers are riveted to the skin panels with a pitch of 150 mm. - The primary structure incorporates the following machined frames: Frame 2:
machined in its upper region, it supports the lower horizontal windshield frame.
Frame 3:
picks up the oblique windshield post.
Frame 8:
forms the windshield side post.
Frame 9:
machined in the lower region, picks up the nose landing gear bay forward panel.
Frames 11 to 20:
in the lower region form the landing gear bay arch members.
Frames 16 and 20:
in the upper region form the passenger door frames.
FRAMES (1/2)
2
Frame 4
Frame 2
12 8
1
16
20
23
Frame 1
14 18 22 4 6 10 13 15 17 19 21 3 5 7 9 11
Frame 8
Frame 11
Frame 9
MENU
SECTION 11/12 - Frames
EXIT 56
DATE: JUNE 2003
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XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Frames (cont’d)
FRAMES (2/2)
Frame 12
12 8
1 2
16
20
Frame 16
23
14 18 22 4 6 10 13 15 17 19 21 9 11 3 5 7
Frame 18
Frame 20
Frame 23
MENU
SECTION 11/12 - Frames (cont’d)
EXIT 57
DATE: JUNE 2003
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XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Windshield
In the forward section, upper and lower machined horizontal beams complete the windshield structure, together with machined windshield frames.
DATE: JUNE 2003
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XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Windshield (cont’d)
DATE: JUNE 2003
Page 59
XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Windshield (cont’d)
DATE: JUNE 2003
Page 60
XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Flight Deck Structure
In the flight deck area the floor support takes the form of a box structure in association with transversal and longitudinal beams attached to the pressure bulkhead vertical members.
FLIGHT DECK STRUCTURE
FWD pressure bulkhead vertical members
Box structure Frames
Cross beams Frame 2 Longitudinal beams
Frame 1 Vertical members Side skin panels
Longitudinal beams
Box structure
FWD pressure bulkhead MENU
SECTION 11/12 - Flight Deck Structure
EXIT 61
DATE: JUNE 2003
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XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Lower Fuselage
This part of section 11/12 contains the nose landing gear bay, access and service door cutouts. The nose landing gear bay is formed by flat panels integrally machined and stabilized laterally and longitudinally by struts attached respectively to frames and crossbeams.
LOWER FUSELAGE Transversal beams
B
Vertical struts
Nose landing gear bay
A
A
B
MENU
SECTION 11/12 - Lower Part
EXIT 62
DATE: JUNE 2003
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XSM13C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Upper Fuselage
Aft of frame 11, floors beams have a similar design to those in the passenger compartment but with wider spacing due to the lower loads in this area.The passenger door surrounding structure comprises the upper and lower boxes. The surrounding panel being reinforced at each corner with a thick doubler.
UPPER FUSELAGE (CABIN PART)
FWD PASSENGER DOOR CUT OUT
B A
A
B
MENU
SECTION 11/12 - Upper Part
EXIT 63
DATE: JUNE 2003
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STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.3. FUSELAGE
SECTION 15 - CENTER FUSELAGE General Layout Construction General Upper Region Pressure Boundaries Lower Fuselage Assembly Pressure Bulkhead - Frame 35 Horizontal Pressure Panel Pressure Diaphragm Assembly (between Fr. 42 and Fr. 46) Aft Pressure Bulkhead (frame 46 lower part) Keel Beam Slanded Panels Floor Structure / Seat Rails
DATE: JUNE 2003
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS SECTION 15 - CENTER FUSELAGE General Layout
The fuselage center section extends from frame 35 to frame 47 for A320, (from frame 35.8 to frame 47 for A321 and frame 35 to frame 47/51 for A319).
A320 CENTER FUSELAGE FR 47
A321
FR 35.8
FR 47
A320
FR 35
FR 47
A319 FR 47/51
FR 35
Belly fairing
FR 35
MENU
CENTER FUSELAGE - General Layout
EXIT 66
DATE: JUNE 2003
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Construction General
The section 15 provides part of the passenger cabin in the upper region and, beneath the floor, the air conditioning, hydraulic and main landing gear bays, together with the integration structure for the center wing box. In the upper region the structure incorporates the necessary reinforcements to allow for the installation of two type III emergency exits on each side, between frame 38 and 41 for A320 and none for A319. On the external surfaces, all around the wing profile attachment, provision is made for the belly fairing structure. COMPARISON WITH A321 Section 15 of the A321 uses the same design principles as those employed for A320: - moving of emergency exits in section 14A/16A, - modified lower/upper lateral panels, - changes of wing root cruciform shape, - new thicknesses for most of the elements. COMPARISON WITH A319 - deletion of one emergency exit.
A320 CENTER FUSELAGE
FWD
FWD
Fr. 47
Fr. 46
Keel beam
Fr. 35 Center wing box MENU
CENTER FUSELAGE - General Construction
EXIT 67
DATE: JUNE 2003
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Upper Region
In the upper region the structure incorporates the necessary reinforcements to allow for the installation of two type III emergency exits on each side, between frame 38 and 41 for A320 and none for A319. FRAMES Typical frames in the pressurized area are only machined in their lower region, up to stringer 18 for frames 37, 43, 45 and 46 and up to stringer 8 for the emergency exit door frames. In their upper region these frames are formed from sheet metal. At the interface with sections 13/14 and 17, frames 35 and 47 are machined up to stringer 29. Frames 36 and 42, which provide attachment for the center wing box to the center fuselage, are completely machined. SKINS AND STRINGERS In the upper region and in the landing gear bay area skin panels are chemically lilled and have riveted stringers. In addition a riveted machined doubler reinforces the emergency exits cut-outs. In the lower region, the panel riveted to the keel beam is integrally machined.
SKIN PANELS
35
B 36 37
Crack stoppers Titanium
A
38 39 40
Skin panel 41 Stringers
42
43 44 45 46 47
Window frames
View A
CENTER FUSELAGE - Upper Region Construction Details
MENU
EXIT 68
DATE: JUNE 2003
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Upper Region (cont’d)
Fr. 42 Reinforcing plate thickness examples
DATE: JUNE 2003
Page 69
XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Pressure Boundaries
The zone beneath the cabin floor is not pressurised, the actual pressure boundary being formed by center wing box upper panels and a pressure diaphragm extending from the center box rear spar to frame 46. The forward pressure boundary is formed by frame 35 lower region which is connected to the center box lower front skin by an articulated horizontal pressure panel. This method of construction prevents center wing box bending deflections from being transmitted into the fuselage structure. The aft pressure boundary is formed by an inclined machined bulkhead reinforced on its aft face by 6 vertical machined members.
FWD horizontal pressure floor
Pressure floor
Center wing box
Aft pressure bulkhead (fr. 46 lower part)
42
FWD 36 37
38
39 40
41
43
44
45 46
35
47
FWD pressure bulkhead (lower part)
PRESSURE BOUNDARIES
MENU
CENTER FUSELAGE - Pressure Boundaries
EXIT 70
DATE: JUNE 2003
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Lower Fuselage Assembly
Aft of the center wing box, beneath the cabin floor, space is provided for the main landing gear wheels when retracted. Longitudinal structural continuity of the lower fuselage in this area is maintained by a keel beam which transmits the overall fuselage vertical bending loads. This beam is a box structure providing attachments for the main landing gear doors and door actuators. In its center region, the keel beam side walls are connected to the wing box aft lower panel. The pressure ceiling of the bay is constructed from 6 drop forged portal frames on the flange of which are riveted pressure resisting curved diaphragms. On each side of the fuselage, between stringers 25 and 26, from the center box rear spar to the aft pressure bulkead, a box type structure is installed to which the upper frames are attached.
FR. 47
Pressure floor FR. 42
FR. 36
Aft pressure bulkhead Fr. 46
Portal frames
Pressure floor
Aft lateral panel FR. 35
Floor structure
Fwd pressure bulkhead (fr. 35 lower part) CENTER WING BOX
Keel beam
LOWER FUSELAGE ASSEMBLY
MENU
CENTER FUSELAGE - Lower Part General Layout
EXIT 71
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Pressure Bulkhead - Frame 35
35
36
FWD
42
46
47
Thickness examples:
FWD PRESSURE BULKHEAD (fr. 35 lower part)
View A Rear view looking FWD
A
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Horizontal Pressure Panel
35
36
FWD
HORIZONTAL PRESSURE FLOOR
42
A
A
46
47
Center wing box bottom panel
Center wing box Fr 36 B
Fr. 35
B
FWD Bottom view
B-B
A-A
Fr.35 FWD Pressure Bulkhead
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Pressure Diaphragm Assembly (between Fr. 42 and Fr. 46)
35
36
FWD
42
46
47
REAR PRESSURE DIAPHRAGM
DATE: JUNE 2003
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Aft Pressure Bulkhead (frame 46 lower part)
35
36
FWD
42
46
47
AFT PRESSURE BULKHEAD (fr. 46 lower part)
Rear view looking FWD
A
DATE: JUNE 2003
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Keel Beam
C B C A
B C-C
A
A-A
B-B DATE: JUNE 2003
Page 76
XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Keel Beam (cont’d)
DATE: JUNE 2003
Page 77
XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Slanded Panels
FWD
A-A
View C
B
FWD
A C
B-B
B
A
DATE: JUNE 2003
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Floor Structure / Seat Rails
The area below the passenger compartment floor-structure is unpressurized. The floor pressure limit-zone consists of the top-skin panel of the wing center-box and two adjacent diaphragms. The diaphragms forward of the wing box connect with a pressure bulkhead installed in the lower part of FR35. The rear diaphragm (which is also the top panel of the main landing-gear bay) connects with the pressure bulkhead at FR46. Longitudinal beams extend the length of the center fuselage and hold the passenger compartment floor above the pressure limit structure. The forward beam section is supported between a cross beam installed at FR35 and the wing center box. The rear beam section is supported between the wing box and a crossbeam installed at FR47/51. Support struts are attached to the crossbeams at each end. Seat and floor support tracks are installed on the longitudinal beams and screws attach floor panels to the track structure. The longitudinal beams, crossbeams, support-struts, seat-tracks and floor support tracks are made of aluminum alloy. They are either extruded or milled. The floor panels are made of honeycomb core which is bonded between Glassfiber Reinforced Plastic (GFRP).
FLOOR STRUCTURE / SEAT RAILS In between Fr. 35 and Fr. 42
Over center wing box beams
42
36 35
MENU
CENTER FUSELAGE - Floor Structure / Seat Rails
EXIT 79
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Floor Structure / Seat Rails (cont’d)
DATE: JUNE 2003
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Floor Structure / Seat Rails (cont’d)
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
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XSM13D01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.3. FUSELAGE
SECTION 16/17 - 18 - 19 A320 / A319 General Layout A321 General Layout Structure Details Section 19 General Layout Section 18 - 19 Joint - Frame 70 Rear Pressure Bulkhead Vertical Stabilizer Attachment Fittings Horizontal Stabilizer Attachment Structure Frame 77 - Tail Cone Attachment Fittings Tail Cone
DATE: JUNE 2003
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XSM13F01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS SECTION 16/17 - 18 - 19 A320 / A319 General Layout The rear fuselage is divided into two sections: - section 16/17 between frame 47 and frame 64, - section 18 between frames 64 and 70.
Section 16/17 contains part of the passenger cabin and underneath the cabin floor and the aft cargo compartment, including the aft cargo door cut-out. Section 18 contains the rearmost part of the passenger cabin and the rear passenger doors. The design of section 16/17 is similar to that of forward fuselage sections. Skin panels of the lower region provide support attachment structures for the belly fairing rear part. This region of the fuselage lies between frame 47 (A320/A321), 51 (A319) and 64. Section 16/17 is on A319 shorter by four frames than on A320/A321.
A320 / A319 General Layout
64
Section 18
A320
Rear pax door cutout
Section 16/17 70 Rear pax door cutout
47 Floor structure
Section 18 64
47
70
A319 Section 16/17
FUSELAGE SECTIONS 16/17 - 18 & 19 - A320 / A319 General Layout
MENU
EXIT 84
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS A321 General Layout A321 Section 16A
This section of the A321 fuselage extends from frame 47 to frame 47.5. The section 16A provides part of the passenger cabin in the upper section, and beneath the cabin floor, the forward part of the rear cargo compartment. The section 16A is of similar construction to section 16/17 but incorporates the emergency exit cut-outs 60in x 30in (one on each side of the fuselage) between frames 47.2A and 47.4. The slide/slide-raft is installed in a separate compartment below each door.
A321 General Layout
Section 18 64
Section 16/17
A321
70 47.5
47.5 47
Section 16A
FUSELAGE SECTIONS 16/17 - 18 & 19 - A321 General Layout
MENU
EXIT 85
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Structure Details
DATE: JUNE 2003
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XSM13F01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Section 19 General Layout
This section comprises the unpressurized part of the rear fuselage aft of frame 70. It includes the mounting structure for the vertical and horizontal stabilizers and houses the Auxiliary Power Unit (APU). Ti is divided into two main sections: - section 19 between frame 70 and 77, - section 19.1 aft of frame 77. Section 19 is of conventional monocoque design which consists of chemically milled skins, riveted stringers and frames. The frame pitch varies from 400 mm to 450 mm. Side panels incorporate the horizontal stabilizer cut-out and the lower panel an access door to this section where a maintenance floor is installed. In addition a jacking point is provided at the bottom center line between frames 73 and 74.
SECTION 19 GENERAL LAYOUT
Fr. 83
Vertical Stabilizer Attachment Fittings Fr. 87
Section 19.1
Fr. 77
THS Attachment structure Section 19
Rear pressure bulkhead Fr. 70 FUSELAGE SECTIONS 16/17 - 18 & 19 - Section 19 General Layout
MENU
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Section 19 General Layout (cont’d)
DATE: JUNE 2003
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XSM13F01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Section 18 - 19 Joint - Frame 70 The frame 70 design - Aft pressure bulkhead comprises: - a ring frame (Frame 70), - the forward fin box attachment, - system arrangements, - and the interface between fuselage sections 18 and 19.
The machined ring frame is made of 7010 / 7050 T73651 aluminium alloy and consists of four segments and supports the two forward fuselage/fin attachment fittings in its upper part. The lip extension on the ring frame provides attachment for the membrane. The spherical curved membrane consists of four sheet metal segments (2024T42) joined together on the inner surface by four I-profiles. Four additional I-sections are used to stiffen the membrane skin radially on the outer surface
SECTION 18 - 19 JOINT - FRAME 70 A
71
Frame 70
A
Electric
Safety valves
Flight controls
Electric
B
Hydraurlic (green)
Hydraurlic (yellow) Hydraurlic (blue)
Bleed air
APU fuel
B
FUSELAGE SECTIONS 16/17 - 18 & 19 - Section 18 - 19 Joint - Frame 70
MENU
EXIT 89
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Section 18 - 19 Joint - Frame 70 (cont’d)
The interface in between sections 18 and 19 is achieved by the outer flange of the ring frame which is attached to be fuselage skins and to each stringer of the section 19.
SECTION 18 - 19 JOINT - FRAME 70
Section A-A
Section B-B
Bulkhead Fr. 70
Bulkhead
FWD
FUSELAGE SECTIONS 16/17 - 18 & 19 - Section 18-19 Joint - Frame 70 (cont’d)
MENU
EXIT 90
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Section 18 - 19 Joint - Frame 70 (cont’d)
DATE: JUNE 2003
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XSM13F01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rear Pressure Bulkhead
The spherical curved membrane consists of four sheet metal segments (2024T42) joined together on the inner surface by four I-profiles.
FWD
FWD
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Vertical Stabilizer Attachment Fittings
The vertical stabilizer spar box attachment fittings are located at frames 70, 72 and 74. Their upper segment is made of integrally machined plates for spar box to fuselage load carrying. The attachment structure consists of three pairs of fail safe yokes which transmit vertical stabilizer spar box loads to fuselage via shear bolts.
VERTICAL STABILIZER ATTACHMENT STRUCTURE
Fr. 74
Fr. 72
Fr. 70
FUSELAGE SECTIONS 16/17 - 18 & 19 - Vertical Stabilizer Attachment Fittings
MENU
EXIT 93
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Vertical Stabilizer Attachment fittings (cont’d)
FWD
FWD
DATE: JUNE 2003
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XSM13F01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Vertical Stabilizer Attachment fittings (cont’d)
VERTICAL STABILIZER ATTACHMENT STRUCTURE FWD Fairing attachment profile
Fr. 70
Bulkhead
Attachment fitting Fr. 70
Upper skin panel cutout
FUSELAGE SECTIONS 16/17 - 18 & 19 - Vertical Stabilizer Attachment Fittings
MENU
EXIT 95
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Vertical Stabilizer Attachment Fittings (cont’d)
DATE: JUNE 2003
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XSM13F01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Vertical Stabilizer Attachment Fittings (cont’d)
VERTICAL STABILIZER ATTACHMENT STRUCTURE Fr. 70 Fr. 70
FWD
A
View A
FUSELAGE SECTIONS 16/17 - 18 & 19 - Vertical Stabilizer Attachment Fittings
MENU
EXIT 97
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Horizontal Stabilizer Attachment Structure
To house the trimming tail plane, a large cut-out is provided in the fuselage between frames 74 and 77. To increase the fuselage rigidity in this area, the cut-out is surrounded by machined beam and a system of diagonal struts is provided in the horizontal plane in the upper and lower areas. The machined frame 77 supports the tail plane hinge bearings and the lateral load fittings which introduce horizontal stabilizer loads into the fuselage structure via the central bracing structure and the upper and lower bracing structures. Frame 77 also incorporates four lugs for the attachment of the tail cone unit.
THS ATTACHMENT STRUCTURE
Fuselage Cutout
76
70
71
72
73
74
77
75
THS actuator jack attachment fitting
THS main hinge fitting
FUSELAGE SECTIONS 16/17 - 18 & 19 - Horizontal Stabilizer Attach. Structure
MENU
EXIT 98
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Horizontal Stabilizer Attachment Structure (cont’d)
THS ATTACHMENT STRUCTURE (cont’d) Fr. 77 Bracing structure - Upper
Lugs Diagonal rods
LH side
THS hinge bearing
Vertical Members
Bracing structure - lower
FUSELAGE SECTIONS 16/17 - 18 & 19 - Horizontal Stabilizer Attach. Structure
MENU
EXIT 99
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Frame 77 - Tail Cone Attachment Fittings
FRAME 77 - TAIL CONE ATTACHMENT
Spigot LH side shown
Fr. 77 lugs Fr. 78 lugs
LH side shown
FUSELAGE SECTIONS 16/17 - 18 & 19 - Frame 77 - Tail Cone Attach. Fittings
MENU
EXIT 100
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Tail Cone
The tail cone unit is located aft of frame 77 and houses the APU (Auxiliary Power Unit). This section is connected to section 19 by means of four lugs and one spigot.
TAIL CONE (1/2) 78
79
83 80
81
84
85
86
Spigot bearing
82
Frame 78
Ventilation (LH only)
Lugs
Service door Air intake
Plates Tubes
MENU
FUSELAGE SECTIONS 16/17 - 18 & 19 - Tail Cone
EXIT 101
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Tail Cone (cont’d)
The APU compartment is locally designed to inhibit an accidental fire. Fire walls are made from titanium, and the compartment is doubled skinned, the inner titanium skin being separated from the outer aluminium alloy skin.
TAIL CONE (2/2) 77 78
80
84 Ventilation (LH only)
Fire extinguishing bottle
Bleed air duct
Exhaust duct APU access doors Fuel line
APU Compartment
Air intake Diverter FUSELAGE SECTIONS 16/17 - 18 & 19 - Tail Cone (cont’d)
MENU
EXIT 102
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE TRAINING MANUAL STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.4. PYLONS / NACELLES
PYLONS / NACELLES Pylon General Layout Pylon Primary Structure Pylon to Wing Attachment Fittings Engine to Pylon Attachment Structure Pylon Secondary Structure Engine Cowls
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
PYLONS / NACELLES Pylon General Layout The engine mounting pylons are convertible to accept the CFM56 or V2500 engines. The role of the pylon, mounted underneath each wing is: - to support the engine, - to transmit the loads to the outer wing box, - to support and route systems between the nacelle and the wing.
SECONDARY STRUCTURES
PYLON TO ENGINE ATTACHMENTS
PYLON TO WING ATTACHMENTS
PRIMARY STRUCTURE
MENU
PYLONS / NACELLES - Pylon General Layout
EXIT 106
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
Pylon Primary Structure The primary structure comprises: - The lower spar, - The forward and upper spars, - Major ribs (ribs 1, 3, 4 and 10). Rib 1 includes the front pyramid for the engine front mount), - Current ribs 2, 5, 6, 7, 8 and 9, - Machined side panels. The lower spar and the pyramid are made of stainless steel. The upper spars are made of special carbon steel cadmium plated and painted. All other components (i.e. Ribs and side panels) are made of Titanium. The primary structure is fitted with: - Reverser cowl hinge brackets, - Attachment bracket for reverser cowl opening jack, - Attachment bracket for the aft secondary structure and bottom pylon fairing.
REAR UPPER SPAR RIB 10 SIDE PANELS
9 8 7 6 5 4 FORWARD UPPER SPAR 3 LOWER SPAR 2
FRONT PYRAMID
ADAPTOR RIB 1
(ENGINE REAR MOUNT)
MENU
PYLONS / NACELLES - Pylon Primary Structure
EXIT 107
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
Pylon to Wing Attachments Fittings FORWARD ATTACHMENT:
WING SIDE
FORWARD ATTACHMENT
WING FITTING SLEEVE
SPIGOT FITTING (WING)
FAIL SAFE BOLTS LOCK WASHER
SPECIAL NOCHED NUTS FAIL SAFE LUGS
SPIGOT FITTINGS SPIGIT BEARING
RIB 4
PYLONS / NACELLES - Pylon to Wing Attachments Fittings
MENU
EXIT 108
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
Pylon to Wing Attachments Fittings (cont’d) REAR ATTACHMENT:
Wing bottom skin
AFT ATTACHMENT
Wing fail safe fitting Sleeve Fail safe bolts
Fail safe links
Special noched nuts
Spherical bearings Fail safe links
Rib 10
Rib 10
Wing side
PYLONS / NACELLES - Pylon to Wing Attachments Fittings (cont’d)
MENU
EXIT 109
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
Engine to Pylon Attachments Structure
Pylon attachment Pylon adapter beam
AFT ENGINE MOUNT
Cross beam assembly
FORWARD ENGINE MOUNT Support beam assembly
Cross beam assembly
Shear pin
ENGINE
Shear pin
Link assembly
Link assembly Engine fan frame
FWD
Pylon attachment Engine attachment bracket PYLONS / NACELLES - Engine to Pylon Attachments Structure
MENU
EXIT 110
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
Pylon Secondary Structure The secondary structure houses most of the system components. It is divided into four main sections.
PYLON TO WING CENTER FILLETS AFRP
AFT MOVABLE FAIRING
FORWARD SECTION Stainless steel
AFRP
AFT SECTION Aluminum alloy LOWER FAIRING Aluminum alloy
MENU
PYLONS / NACELLES - Pylon Secondary Structure
EXIT 111
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
Pylon Secondary Structure (cont’d) FORWARD FAIRING: The forward section provides the aerodynamic profile between the engine nose cowl upper section and the wing leading edge. It is mainly constructed from stainless steel. PYLON TO WING CENTER FILLETS: The pylon to wing center fillets, which provide aerodynamic profile between the primary structure and the wing, and consisting of AFRP (Aramid Fiber Reinforced Plastic) skinned sandwich panels, fastened on aluminum alloy ribs.
FORWARD FAIRING
A
B A
Panels & Doors
Ribs
Junction boxes
Frames
Cantilever structure
B
PYLON TO WING CENTER FILLETS
Panels & Doors PYLONS / NACELLES - Pylon Secondary Structure (cont’d)
MENU
EXIT 112
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STRUCTURE TRAINING MANUAL STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
Pylon Secondary Structure (cont’d) AFT FAIRINGS: The aft section is made of AFRP for the movable fairing and aluminum alloy construction for the main body. LOWER FAIRING: Thee lower fairing between the lower spar and the engine comprises an aluminum alloy center section and stainless steel front and rear sections.
E D
AFT MOVABLE FAIRING
E
Ribs & Spars
C
Skin panels AFRP AFT FIXED FAIRING D
LOWER FAIRING
C
Panel Steel Skin panels Frame
Panel 2024 Panel Steel
PYLONS / NACELLES - Pylon Secondary Structure (cont’d)
MENU
EXIT 113
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STRUCTURE TRAINING MANUAL STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
Engine Cowls CFM 56 ENGINES
ENGINE MOUNTS
SYSTEM INSTALLATIONS
PRIMARY NOZZLE
PLUG
AIR INLET
PIVOTING DOOR THRUST REVERSER FAN COWL DOORS
ENGINE NACELLES (CFM56-5 ENGINE)
MENU
PYLONS / NACELLES - Engine Cowls
EXIT 114
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
Engine Cowls (cont’d) V2500 ENGINES
ENGINE MOUNTS
SYSTEM INSTALLATIONS
ENGINE NACELLES (V2500 ENGINE)
CASCADE THRUST REVERSER
FAN COWL DOORS AIR INLET MENU
PYLONS / NACELLES - Engine Cowls (cont’d)
EXIT 115
DATE: JUNE 2003
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1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.5. STABILIZERS VERTICAL STABILIZER General Main Box Construction Leading Edge Tip Trailing Edge Rudder
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS VERTICAL STABILIZER General
The fin is made in composite material. The fin comprises a main box, a removable leading edge, rear shrouds, a tip and a single unit rudder.
TIP
LEADING EDGE
RUDDER
MAIN BOX
TRAILING EDGE FAIRINGS
MENU
VERTICAL STABILIZER - General
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Main Box Construction
The main box is of carbon fiber composite design. It has a front and rear spar and an additional short center spar between the fin root and rib 2. This design has been chosen for minimum weight compatible with fail safe design criteria. Both the left and right hand panels are fabricated from integrated skins, I-section stringers, spar caps, rib cleats and fully laminated fuselage attachment lugs. The thicknesses of the skins, the stringer flanges and webs are determined by the stress distributions from the various loading cases. The fin is attached to the fuselage by means of double attachment fittings positioned at fuselage frames 70, 72 and 74. The attachments consist of a pair of lugs connected to the fuselage fittings by fail safe shear bolts to carry the vertical loads and a pair of fail safe transverse rods to carry the lateral loads. Seven rudder hinge fittings are bolted to the main box rear spar. The rudder is actuated by three actuators connected to three actuator fitting bolted to the rear spar (between ribs 4 and 7).
Rib11
FIN BOX CONSTRUCTION
Rear spar Ribs (11) Side panels with integrated stiffeners
Front spar
Rudder actuator attachment fittings (3)
Center spar Rudder hinge fittings (7)
Main box to Fuselage attachment fittings MENU
VERTICAL STABILIZER - Main Box Construction
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Main Box Construction (cont’d) Main box assembly. Side panels & ribs assembly.
MAIN MAIN BOX BOX ASSEMBLY ASSEMBLY Attachment Attachment fittings fittings
Ribs Ribs
Side Side panels panels
VERTICAL STABILIZER - Main Box Construction (cont ’d)
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Main Box Construction (cont’d) Main box assembly. Fuselage attachment fittings - CFRP lugs.
FUSELAGE FUSELAGE ATTACHMENT ATTACHMENT FITTINGS FITTINGS
Before bonding with the skin
VERTICAL STABILIZER - Main Box Construction (cont ’d)
DATE: JUNE 2003
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STRUCTURE MAINTENANCE FOR TECHNICIANS Main Box Construction (cont’d) Main box assembly. Typical CFRP ribs.
RIBS RIBS
VERTICAL STABILIZER - Main Box Construction (cont ’d)
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Main Box Construction (cont’d) Main box assembly. Rudder actuator and hinge fittings.
REAR REAR SPAR SPAR // RUDDER RUDDER ATTACHMENT ATTACHMENT FITTINGS FITTINGS
Main Main box box rear rear spar spar
Actuator Actuator attachment attachment brackets brackets Hinge Hinge fittings fittings Access Access holes holes
VERTICAL STABILIZER - Main Box Construction (cont ’d)
DATE: JUNE 2003
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STRUCTURE MAINTENANCE FOR TECHNICIANS Main Box Construction (cont’d) Main box assembly.
Side panels: one shot bonding manufacturing technique and differential design. One shot bonding technique: Wet skin, stringers and rib shear ties cured in one shot. Differential design: Pre-cured stringers are bonded to the wet skin. Rib ties are then installed by riveting
Before Before mod. mod. 26500K4924 26500K4924 MSN MSN 00010001- 0832 0832
Side Side panels panels
After After mod. mod. 26500K4924 26500K4924 MSN MSN 0833 0833 -- 9999 9999
Differential design
One shot bonding - Modular process
Typical stringer shape
Typical stringer shape
- wet skin - bonded pre cured stringer - riveted pre cured rib ties
- wet skin, - wet stringers, - wet rib shear tie
Bonded pre-cured Stringer
Rib
Riveted shear ties
Stringer skin
Rib shear tie VERTICAL STABILIZER - Main Box Construction (cont ’d)
DATE: JUNE 2003
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MENU
EXIT 124
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Leading Edge
The removable leading edge is made in three spanwise sections to ease handling of individual parts and thus replacement procedures. It is of sandwich type construction. The front part is reinforced for hail and bird impact protection. The outer fiber layer is coated with a special paint to prevent erosion and for static discharge. The leading edge section is attached to main box front spar. Material: GFRP (Glass Fiber Reinforced Plastic) A dorsal fin of glass fiber sandwich construction forms the interface of the fin loading edge to the fuselage contour and provides the continuity of the fin to fuselage side fairings. Material: GFRP
Steel Steel cover: cover: 25247K3657, 25247K3657, 28484K6104, 28484K6104, SB SB 55-1016 55-1016
Leading Leading edge edge
Before modification
After modification
Steel cover
MENU
VERTICAL STABILIZER - Leading Edge
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Tip
The tip of the fin is of sandwich construction and is bolted to the top rib of the fin main box. Material: GFRP Trailing edge The trailing edge of the vertical stabilizer is formed by shrouds panels made of carbon fiber (sandwich construction). These panels are designed as access panels, to give access to hydraulics, control servos, rods and hinge fittings.
Tip
Tip (GFRP, sandwich)
Lightning strike protection strap
Leading edge
Rudder Main box
MENU
VERTICAL STABILIZER - Tip
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Trailing Edge
The trailing edge of the vertical stabilizer is formed by shrouds panels made of carbon fiber (sandwich construction). These panels are designed as access panels, to give access to hydraulics, control servos, rods and hinge fittings.
Trailing edge panels A 4
A
B
3
2
B
1
A
Panel support frame Main box Flange rear spar Panel 1 Panel 2 Piano hinge
Main box side panel
Side panel
Piano hinge MENU
VERTICAL STABILIZER - Trailing Edge
DATE: JUNE 2003
Access panel (CFRP, sandwich)
EXIT 127
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rudder
The rudder is designed as a single unit with a maximum deflection of 30° to each side. It is attached to the fin box via seven hinges and is operated by three hydraulic servos. The composite rudder hinges are accessible through inspection panels. The bearings can be replaced without removing the rudder. The rudder is manufactured from honeycomb carbon fiber composite faced material similar to that on the A310. It consists mainly of one front spar, two side panels with integrated leading edge and a top and bottom closing rib. For lightning strike protection the rudder tip and trailing edge is of aluminum alloy construction.
CFRP skins
Upper rib
Tip (Al. alloy) Honeycomb core Trailing edge profile (Al. Alloy)
Hinge fittings (CFRP, solid laminate) Trailing edge profile (Al. Alloy) Hoisting point
Side panels
Side panels (CFRP, sandwich)
Actuator fittings (CFRP, solid laminate)
Rudder hinge fitting
Hinge fittings
Spar
(CFRP, solid laminate) Hoisting point
Spar
Hinge fitting
MENU
VERTICAL STABILIZER - Rudder
DATE: JUNE 2003
Lower closing rib EXIT 128
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rudder (cont’d)
RUDDER RUDDER -- General General
Trailing Trailing edge edge profile profile Side Side panel panel
Leading Leading edge edge Front Front spar spar
Closing Closing rib rib Tip Tip
VERTICAL STABILIZER - Rudder (cont ’d)
DATE: JUNE 2003
129
Page 129
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rudder (cont’d)
RUDDER RUDDER ASSEMBLY ASSEMBLY PROCESS PROCESS Side Side panel panel
Side Side panel panel
Spar Spar
MENU
VERTICAL STABILIZER - Rudder (cont ’d)
DATE: JUNE 2003
EXIT 130
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XSM15A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rudder (cont’d) Attachment fittings:
Side panel
Spar
Side panel
Actuator attachment fittings
Hinge attachment fittings
MENU
VERTICAL STABILIZER - Rudder (cont ’d)
DATE: JUNE 2003
EXIT 131
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STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.5. STABILIZERS HORIZONTAL STABILIZER General Main Spar Box Main Fittings Elevator Fittings Leading Edge & Tip Trailing Edge Panels Elevator - General Elevator Box Elevator Actuator & Hinge Fittings Elevator Tips
DATE: JUNE 2003
Page 133
XSM15B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS HORIZONTAL STABILIZER General The horizontal stabilizer is composed of: - Two main spar boxes, - Two elevators, - A leading edge, - A trailing edge, - Tips.
Rear support fitting Hinge arms
Access panels
Elevator Main box
Center joint
Jack screw fitting
Tip Lex fairing
Two part leading edge
MENU
HORIZONTAL STABILIZER - General
EXIT 134
DATE: JUNE 2003
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XSM15B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Main Spar Box
The two spar boxes are joined together at rib1 by titanium fittings. Each spar box is a full CFRP monolithic structure which consists of: - A top and a bottom self-stiffened panel (with integrated “I” shaped stringers), - A front and a rear spar with integrated vertical stiffeners, - Thirteen ribs, - Two elevator actuator attachment fittings (at ribs 7 & 8), - Six hinge attachment fittings, - A screw jack fitting, - A rear support fitting, - A side load fitting.
Screw jack attachment fitting TYPICAL RIB Rib 1
Front spar
Rib 7 Rib 8
Ribs
Rear support fitting
Center joint
Elevator Hinge Fittings (6) Rear spar End rib Side load fitting
Actuator attachment fittings (2)
Self-stiffened rib
HORIZONTAL STABILIZER - Main Spar Box Construction
MENU
EXIT 135
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Main Spar Box (cont’d)
MAIN BOX CONSTRUCTION Upper panel
Rear spar
Lower panel Ribs
Front spar
Ribs
HORIZONTAL STABILIZER - Main Spar Box Construction (cont ’d)
MENU
EXIT 136
DATE: JUNE 2003
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XSM15B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Main Spar Box (cont’d)
Self stiffened panel
Rib 1
Rib 2
Self stiffened panel
MENU
HORIZONTAL STABILIZER - Main Spar Box
EXIT 137
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Main Spar Box (cont’d)
Titanium fitting
Center joint
HORIZONTAL STABILIZER - Main Spar Box (cont ’d)
MENU
EXIT 138
DATE: JUNE 2003
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XSM15B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Main Fittings
The main box is attached to the fuselage via: - two screw jack fittings (carbon fiber), bolted to the front spar, - two rear support fittings (one on each outer box) and bolted to the rear spar at rib 3 and linked by upper and lower reinforcements bolted to the upper and lower skins (carbon fiber), - two side loads fittings (one on each outer box) made out of carbon fiber.
SCREW JACK ATTACHMENT
Actuator fittings (2)
Elevator hinge fittings (6)
REAR SUPPORT FITTINGS MENU
HORIZONTAL STABILIZER - Main Fittings
EXIT 139
DATE: JUNE 2003
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XSM15B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Main Fittings (cont’d)
Inboard Inboard
Rear spar
Rear support fittings FWD attachment fittings
Front spar
MENU
HORIZONTAL STABILIZER - Main Fittings (cont ’d)
EXIT 140
DATE: JUNE 2003
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XSM15B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Elevator Fittings
Each elevator is actuated by two actuators which are connected to jack fittings bolted to ribs 7 and 8 through the main box rear spar. Six hinge fittings are also attached to the main box rear spar. All these fittings are made out of carbon fiber.
Actuator fittings (2) A
Elevator hinge fittings (6) (CFRP)
A
Fitting (Al alloy)
Actuator fittings (2) (CFRP)
MENU
HORIZONTAL STABILIZER - Elevator Fittings
EXIT 141
DATE: JUNE 2003
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XSM15B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Leading Edge and Tip
Each leading edge is divided into three sections which are of sandwich construction shinned with CFRP layers, except the nose section where the outer and inner skins join together to form a monolithic area reinforced by additional CFRP layers for bird impact protection. The nose area is also protected against erosion and impact by a metallic plate.
Front spar
Metallic sheet
CFRP Skins
Main spar box
TIP
Leading edge rib
LEADING EDGE Tip Aluminum alloy
Main spar box Front spar
Leading edge Metallic plate
MENU
HORIZONTAL STABILIZER - Leading Edge & Tip
EXIT 142
DATE: JUNE 2003
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XSM15B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Leading Edge and Tip (cont’d)
Leading edge ribs Front spar
Tip
HORIZONTAL STABILIZER - Leading Edge & Tip (cont ’d)
MENU
EXIT 143
DATE: JUNE 2003
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XSM15B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Trailing Edge Panels
Each side, the trailing edge is divided in four removable upper panels and eight removable lower panels. These panels are supported by ten CFRP monolithic ribs. Each panel is of sandwich construction skinned with CFRP layers.
TRAILING EDGE ACCESS PANELS & RIBS
334AT (344AT)
Main box
Top panel FWD
334BT (344BT) 334CT (344CT) 334AB (344AB) 334DT (344DT)
334BB (344BB) 334CB (344CB) 334DB (344DB) 334EB (344EB) 334FB (344FB) 334GB (344GB) 334HB(344HB)
Rear spar
Bottom panel
Trailing edge ribs
MENU
HORIZONTAL STABILIZER - Trailing Edge Panels
EXIT 144
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Elevators - General
Each elevator is composed of: - An upper and a lower skin panel (sandwich construction, carbon fiber skins + glass honeycomb core), - A front spar (sandwich construction, carbon fiber skins), - Ribs (CFRP monolithic construction), - A trailing edge profile(Aluminum alloy for lightning strike protection, - An inner tip (sandwich construction, CFRP skins), - An outer tip (Metallic construction for lightning strike protection), - Actuators and hinge fittings, - Lightning strips, - Hoisting points.
Hoisting points (3) Lightning strike strips
Rib 1 Rib 4 Inboard cap
Rib 5
Upper panel
Hinge fittings (6) Actuator fittings (2)
Outer tip Leading edge ribs
Front spar
Lower panel MENU
HORIZONTAL STABILIZER - Elevators - General
EXIT 145
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Elevator Box
The elevator box is made of two sandwich carbon fiber panels bolted to the front spar and fastened together in the trailing edge area through inserts. A riveted aluminium trailing edge completes the lightning strike protection of the elevator.
Honeycomb core
CFRP Skin
TRAILING TRAILING EDGE EDGE
Fastener
Insert
Metallic profile
UPPER UPPER PANEL PANEL
LOWER LOWER PANEL PANEL Front spar
MENU
HORIZONTAL STABILIZER - Elevator Box (1/2)
EXIT 146
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Elevator Box (cont’d)
Only 4 carbon ribs numbered as shown in the picture are riveted to the front spar and skins panels ensure the rigidity of the box. Ribs are riveted directly to the skin panels.
Rib 4 Rib 5
Rib 1 Front spar Rib 10
Rib 1
Rib 4
Lightning strike strips
Rib 5
Rib 10
LIGHTNING STRIKE STRIPS
MENU
HORIZONTAL STABILIZER - Elevator Box (2/2)
EXIT 147
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Elevator Box (cont’d)
Lightning Lightning strike strike Strip Strip
Skin Skin Panel Panel
Trailing Trailing edge edge profile profile
MENU
HORIZONTAL STABILIZER - Elevator Box (cont ’d)
EXIT 148
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Elevator Actuator & Hinge Fittings The elevator fittings are bolted to the front spar and consist of: - Two actuator fittings (carbon fiber), - Six hinge fittings (aluminum alloy).
Actuator fittings
Hinge fittings
HORIZONTAL STABILIZER - Elevator Actuator & Hinge Fittings
MENU
EXIT 149
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Elevator Tips Removable tips are screwed to this box structure.
The inner tip is a single carbon fiber sandwich construction bolted to the inner closing rib. The outer tip is made out of aluminium alloy.
Inner cap (CFRP)
INNER CAP (CFRP, sandwich)
OUTER TIP (Aluminium alloy) Elevator box
A
MENU
HORIZONTAL STABILIZER - Elevator Tips
EXIT 150
DATE: JUNE 2003
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STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 /A321 STRUCTURE DESCRIPTION 1.6. WINGS
CENTER WING BOX General Skin Panels Front Spar Rear Spar Frame 36 Frame 42 Internal Rib Structure Wing Root Joint
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS CENTER WING BOX General
The center section of the wing extends across the width of the fuselage and forms an integral fuel tank. It is bounded by the front and rear spars, the upper and lower skins and the root ribs (rib 1). Internally there are six spanwise truss type ribs extending from the front spar to the rear spar. The two spars are combined with frames, forming the fuselage frames 36 and 42. The center wing box provides external attachments and internal supports at the root ribs for the fuselage frames 37, 38, 39, 40 and 41. The entire assembly reacts external wing bending moment and transmits external wing shear and torsion into the fuselage at the root ribs through the above mentioned frames, but principally through frames 36 and 42.
FRAME36 FRAME36
FRAME FRAME 42 42
Upper Upper skin skin panels panels
Cruciform Cruciform fitting fitting
Rear Rear spar spar
Front Front spar spar Root Root rib rib 11
Lower Lower TT fitting fitting
MENU
CENTER WING BOX - General
EXIT 154
DATE: JUNE 2003
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XSM16A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Skin Panels
The upper and lower skins consist of machined plates stiffened by internal spanwise stringers, made from extruded I-sections, attached to the skins by means of a Drivmatic Automatic Riveter. Upper skin: On the upper skin these stringers are stabilised at intervals by a series of machined brackets. An additional system of stiffeners on the upper skin provided in the chordwise direction, consisting of an external set of fabricated ribs which also support the cabin floor of structure. The upper skin is fabricated from two panels, whereas the lower skin consists of three panels.
A-A Stringer
Fwd upper panel
Aft upper panel
Fwd upper panel 7010T6
B-B
Aft upper panel 7010T651
Stringer
C-C
Stringer
FWD
MENU
CENTER WING BOX - Skin Panels
EXIT 155
DATE: JUNE 2003
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XSM16A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Skin Panels (cont’d) Lower skin:
B-B
Center panel Stiffener 8 Rear spar
Aft panel
Stiffener 11
Fwd panel
Front spar
Stringer
Aft panel
Center panel panel
A-A
Stringer
Fwd panel Triform fitting
MENU
CENTER WING BOX - Skin Panels (cont’d)
EXIT 156
DATE: JUNE 2003
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XSM16A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Front Spar
The front spar is fabricated from extruded booms, a machined web and vertical heavy machined stiffeners on the aft face of the web and horizontal stiffeners, stabilised at intervals by small brackets, on the upper forward face. This heavy stiffening being required because the spar, apart from its other functions, also acts as a cabin pressure bulkhead. At the bottom of the front spar are attached a series of longitudinal beams supporting a horizontal pressure diaphragm which connects the pressure bulkhead at frame 35 to the wing structure. The rear spar is a monolithic element machined from forged stretched plate. The attachment of the main front and rear spars to the fuselage frames 36 and 42 is by means of pairs of fail safe elements machined from forgings which are assembled to the center wing box before assembly to the fuselage.
Frame 36 ref.
Upper skin panel
Front spar web
Lower skin panel Horizontal pressure bulkhead MENU
CENTER WING BOX - Front Spar
EXIT 157
DATE: JUNE 2003
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XSM16A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Front Spar (cont’d)
Front spar
MENU
CENTER WING BOX - Front Spar (cont’d)
EXIT 158
DATE: JUNE 2003
Page 158
XSM16A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rear Spar
The rear spar is a monolithic element machined from forged stretched plate. The attachment of the main front and rear spars to the fuselage frames 36 and 42 is by means of pairs of fail safe elements machined from forgings which are assembled to the center wing box before assembly to the fuselage.
Frame 42
Rear spar
- Rear spars MENU
CENTER WING BOX - Rear Spar
EXIT 159
DATE: JUNE 2003
Page 159
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rear Spar (cont’d)
Rear spar
Top skin panel
Rib 1
Rib 1
Rear spar MENU
CENTER WING BOX - Rear Spar (cont’d)
EXIT 160
DATE: JUNE 2003
Page 160
XSM16A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rear Spar (cont’d)
Rear spar
Door
MENU
CENTER WING BOX - Rear Spar (cont’d)
EXIT 161
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Frame 36
Frame 36
MENU
CENTER WING BOX - Frame 36
EXIT 162
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Frame 42
Frame 42
MENU
CENTER WING BOX - Frame 42
EXIT 163
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Internal Rib Structure
A rod arrangement inside the wing center box is used to connect the upper and lower skin panels and to stiffen the entire box structure. These (lattice) ribs are fabricated from special light alloy rods and heavy machined beans.
Rod upper attachment
Fwd
Rib 1 A-A
B-B Lower skin panel Rod
Rod
Lower skin panel MENU
CENTER WING BOX - Internal Rib Structure
EXIT 164
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Internal Rib Structure (cont’d)
A rod arrangement inside the wing center box is used to connect the upper and lower skin panels and to stiffen the entire box structure. These (lattice) ribs are fabricated from special light alloy rods and heavy machined beans.
CENTER WING BOX - Internal Rib Structure (cont’d) 165
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Wing Root Joint
At the root joint, the wing box presents a dihedral and sweep angle to the center box, which necessitates a complete joint at rib 1 (stringers, skin panels and spar joints). Skin Panel joints. The upper and lower wing skin panels (outer wing box) are joined to the center wing box (inside the fuselage) by means of forged fittings: - A cruciform fitting for the upper skin panels. - A “T” fitting and an external fail safe butt strap for the lower skin panels.
Cruciform fitting
OUTER WING BOX
CENTER WING BOX
Rib 1 datum
Triform Fitting
MENU
CENTER WING BOX - Wing Root Joint
EXIT 166
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Wing Root Joint (cont’d) Upper skin joint - cruciform fitting
The four flanges of the cruciform fitting are tapered in cross section with their thicknesses progressively increasing from front to rear to account for the load distribution. The “horizontal” flanges are joined to the wing skins, to produce a shear joint, and the “vertical” flange to the fuselage skin and to the web of the root rib 1. The cruciform fitting also acts as the upper boom of rib 1. The inner flanges of the top skin panel stringers (from center wing box and exterior wing box) are connected together by means of “crown-fittings” joined by tension bolts through the vertical flange of the cruciform fitting.
View on F
Center wing box upper skin panel
Center wing box stiffener
Rib 1
Crown fitting
Cruciform fitting Outer wing box upper skin panel Center wing box upper skin panel
F
Outer wing box stringer OUTER WING BOX TOP SKIN PANELS JOINT
Center wing box stringer
Crown fitting
CENTER WING BOX Root rib 1
MENU
CENTER WING BOX - Wing Root Joint (cont’d)
EXIT 167
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Wing Root Joint (cont’d) Lower skin joint - ‘T fitting and fail safe butt strap.
The lower skins of the center and exterior wing boxes are joined in the following fail safe manner: - with an inner T-fitting, - with an outer fail safe strap. The three flanges of the T-fitting and the flanges of the butt strap fitting are tapered in cross-section with their thicknesses progressively increasing from front to rear to account for the variation of the loading. The vertical flange of the T-fitting is attached to the web of the rib 1, which allows this fitting to act as a boom for rib 1. The fail safe strap is also divided chordwise in three positions, which gives additional fail safety. In order to minimise local bending effects at the joint, the inner flanges of the stringers and the webs are progressively tapered while the skin flanges are progressively enlarged laterally as the stringer approaches the intersection. Throughout the joint, the skin is also tapered as the horizontal flange of the T-fitting and the outer fail safe trap tapers in the opposite direction, in order to enhance the load diffusion of the skin joint.
Rib 1
Triform fitting
OUTER WING BOX Stringer
CENTER WING BOX Rib 1 Triform fitting Stringer
Outer wing box lower skin panel
BOTTOM SKIN PANELS JOINT
Lower 3 parts butt strap
Center wing box lower skin panel
MENU
CENTER WING BOX - Wing Root Joint (cont’d)
EXIT 168
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Wing Root Joint (cont’d) Skin joints at frame location
Fuselage skin
Frame foot fittings Cruciform fitting Upper skin Stringer
Rib 1
Crown fitting
Rib 1
Vertical fittings CENTER WING BOX
Triform fitting Lower skin
Stringer
MENU
CENTER WING BOX - Wing Root Joint (cont’d)
EXIT 169
DATE: JUNE 2003
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XSM16A01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Wing Root Joint (cont’d) Spar joints.
Rear spar web
Frame 42
Vertical tee fitting
Frame 42
CENTER CENTER WING WING BOX BOX
Internal corner fitting Bottom skin panel
Internal corner fitting
External corner fitting
Vertical tee fitting
Triform fitting
CENTER CENTER WING WING BOX BOX
Bottom strap
A
Rear spar boom
A
Vertical tee fitting
External corner fitting OUTER OUTER WING WING BOX BOX
Frame 42 External corner fitting
Internal corner fitting OUTER OUTER WING WING BOX BOX
Triform fitting
B
B
Bottom strap Bottom skin Triform fitting panel
SPAR JOINTS
Bottom strap
Internal corner fitting MENU
CENTER WING BOX - Wing Root Joint (cont’d)
EXIT 170
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS STUDENTS’ NOTES
DATE: JUNE 2003
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STRUCTURE MAINTENANCE FOR TECHNICIANS
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.6. WINGS
OUTER WING BOX General Dry Bay / Collector Cell Drip Fence Engine Pylon Attachments Top Skin Panels Bottom Skin Panels Wing Access Panels Spars - General Front Spar Slat Track Cans Rear Spar Jacking Points Rear False Spar / Main Landing Gear Support Structure Ribs
DATE: JUNE 2003
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS OUTER WING BOX General Each outer wing comprises: A main load-carrying box structure composed of: - Top skins (2 panels), - Bottom skins (3 panels), - A Front spar (1 single piece), - A rear spar (3 pieces), - Twenty six ribs (rib 2 to 27, - a mounting structure for the engine pylon.
- A fixed leading edge and the support structure for the slats (forward of the front spar), - A trailing edge (aft of the rear spar), forms the attachment structure for the flaps, spoilers, shrouds and aileron as well as the main landing gear attachment structure cantilevered aft of rear spar, - A wing tip which incorporates a winglet.
Tip fence
Main box (Skin panels, stringers, spars, ribs)
Fixed trailing edge structure
Fixed leading edge
Main landing gear attachment structure
MENU
OUTER WING BOX - General
EXIT 174
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Dry Bay / Collector Cell
A dry bay is built into the front of the fuel tank between ribs 5 and 6 to protect against turbine disc failure. The closed area between rib 1 and rib 2 forms a collector cell for the main fuel pumps.
Top skin panels COLLECTOR CELL
Front spar Rib 6 Rib 2
Rib 2 Rib 5
DRY BAY
COLLECTOR COLLECTOR CELL CELL Bottom skin panels
Front spar
Rib 27
Root rib 1
Rear spar
MENU
OUTER WING BOX - Dry Bay / Collector
EXIT 175
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Drip Fence
A drip fence is installed on the bottom skin at rib 22, inboard of the NACA intake access panel. The drip fence is an aluminium alloy angle which prevents fuel (out of NACA intake) from flowing down the wing surface to the pylon area. The angle stops the flow of fuel and causes it to drop to the ground.
DRIP FENCE
Rib 21
Rib 23
Rib 22
MENU
OUTER WING BOX - Drip Fence
EXIT 176
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Engine Pylon Attachments
The engine pylon is attached to the main wing box using four main components: - Two forward brackets, - Thrust spigot, - Rear mounting bracket. The forward brackets are cantilevered off the forward face of the front spar and support the links attached to the forward lugs on the pylon. Each bracket consist of a pair of back to back components bolted together, providing a fail safe capability. The brackets take vertical loads only. The spigot is attached to the bottom flanges of the forward brackets and picks up with the top deck of the pylon. It takes thrust and side loads. There is a fail safe pin down the center of the spigot.
FORWARD FORWARD ATTACHMENT ATTACHMENT
Pylon forward pick-up attachments
Top skin panel
Front spar
FORWARD
Rib 7 Rib 8
Reinforcing plate
Reinforcing plate
Spigot (Trust)
Bottom skin panel MENU
OUTER WING BOX - Engine Pylon Attachments
EXIT 177
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Engine Pylon Attachments (cont’d)
The rear pylon mounting is a simple point attachment to a spherical bearing which picks up with the rear top deck of the pylon. Attachment to the wing is via an inter-costal between ribs 7 and 8.
REAR REAR ATTACHMENT ATTACHMENT
Top skin panel Rib 7 Rib 8 Pylon Pylon rear rear fitting fitting
Simple lug bracket
Bottom skin panel
OUTER WING BOX - Engine Pylon Attachments (cont’d)
MENU
EXIT 178
DATE: JUNE 2003
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Top Skin Panels
The top skin is made from zinc bearing aluminium alloy (type 7150) material. The high proof strength of this type of material makes it ideal for a surface predominantly in compression. Due account is taken of the reserve bending loads to ensure that there are no fatigue problems. The skin consists of mainly “ “ section stringers attached to a two panel skin. Stringer 13 and 14 are “ “ section and are capped between rib 2 and 22 to form a duct leading into the surge tank. Outboard of rib 22 the “ “section stringers blends into “ “ sections. Skin panels and stringers are fully machined to produce minimum weight components with optimum grading of skin thickness and stringer area to ensure satisfactory stability of the upper surface. The skin panels are locally increased in thickness at pylon, flap track and aileron attachments and there is also an internal doubler plate at the forward pylon attachments and fail safe chordwise straps at ribs 7 and 8. Stringers are attached to the skin using rivets except at joints and rib stations where interference fit bolts are used. A standard emergency fuel filler hole, suitably reinforced, is provided between ribs 19 and 20.
Typical Typical stringer stringer shape shape
Main landing gear reinforcing plate MENU
OUTER WING BOX - Top Skin Panels
EXIT 179
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Top Skin Panels (cont’d)
The skin panels are locally increased in thickness at pylon, flap track and aileron attachments and there is also an internal doubler plate at the forward pylon attachments and fail safe chordwise straps at ribs 7 and 8. Stringers are attached to the skin using rivets except at joints and rib stations where interference fit bolts are used. A standard emergency fuel filler hole, suitably reinforced, is provided between ribs 19 and 20.
Top Top skin skin reinforcing reinforcing plate plate (pylon) (pylon)
Top skin reinforcement (inside)
MENU
OUTER WING BOX - Top Skin Panels (cont’d)
EXIT 180
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Bottom Skin Panels
The bottom skin, which is predominantly in tension, is made from copper bearing aluminum alloy (type 2024) material and consists of fifteen stringers attached to a three panel skin. The skin panels are joined at stringer 8 and 11 by two spanwise butt straps extending to approximately rib 21. The cover is designed to meet the demanding fatigue requirements and fully exploits the excellent fatigue resistance and slow crack propagation rates of the 2024 alloy. The skins are extensively machined on the inner surface to produce minimum weight components. They are shot peen formed after machining. The center skin panel contains the main access holes. The stringers are made from extrusions and fully machined to provide optimum sections. The stringers are joint-free and are attached to the skin using interference fit bolts. In the pylon and undercarriage regions the skin is reinforced by doubler plates bolted to its external surface.
Typical Typical stringer stringer shape shape
2 Front spar 1
4 3
6 5
12 14
8 7
11
FWD
13 15
Stringers Rear spar Ribs 1
9
2 10
3 4 5 6
Skin panel 1
7 8
Skin panel 2 Stgr 8
9 Skin panel 3
10
Stgr 11 11 MENU
OUTER WING BOX - Bottom Skin Panels
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DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Bottom Skin Panels (cont’d)
In the pylon and undercarriage regions the skin is reinforced by doubler plates bolted to its external surface.
MLG reinforcing plate
REINFORCING PLATES
Rear spar ref. False rear spar ref.
Pylon reinforcing plate
Pylon reinforcing plate Main landing gear reinforcing plate
7 8
MENU
OUTER WING BOX - Bottom Skin Panels (cont’d)
EXIT 182
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Bottom Skin Panels (cont’d)
Bottom skin reinforcing plates in pylon and main landing gear attachment areas.
Bottom Bottom skin skin reinforcing reinforcing plate plate (pylon) (pylon) Front spar datum
Main Main landing landing gear gear reinforcing reinforcing plate plate Gear rib datum
Rib 5
Gear rib datum Rear spar datum
Rib 7 Taper indicated thus
Rib 8
Taper change Rib 8 Rib 7 Rib 5 datum
MENU
OUTER WING BOX - Bottom Skin Panels (cont’d)
EXIT 183
DATE: JUNE 2003
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Wing Access Panels
One integral fuel tank is formed in each wing between rib 1 and rib 22. All bolting in the primary structure is of the interference fit type with the exception of the rib to spar bolts and those for the attachment of access doors. The interference fit type bolts are used to improve structural fatigue life and ensure adequate sealing of the fuel tanks. Interchangeable manhole access panels in the lower wing skin provide access to the internal structure during build and in-service maintenance. The manhole access panels are of load carrying and non-load carrying types. The non-load carrying panels are used between ribs 1 and 13 and load carrying panels outboard of this rib. All panels are sealed by replaceable seals.
Rib 13
Clamped doors
Rib 13
Bolted doors
Outboard
Inboard
Outside
CLAMPED DOORS BOLTED DOORS
Inside Man hole doors additional information
MENU
OUTER WING BOX - Wing Access Panels
EXIT 184
DATE: JUNE 2003
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Wing Access Panels (cont’d)
MENU
OUTER WING BOX - Wing Access Panels (cont’d)
EXIT 185
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Spars - General The outer wing contains three spars: - a front spar (single piece), - a rear spar (three piece), - a rear false spar (aft of the rear spar).
All spars are made from aluminum alloy (7010) using rolled stretched plates.
Rib 6
Front spar
Rib 22
Rib 27 Rear spar Rear spar joint at rib 22
joint at rib 6 Rear spar 3 sections
False rear spar
MENU
OUTER WING BOX - Spars - General
EXIT 186
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Front Spar
The front spar is machined in a single piece and contains rib posts, stiffeners, panels, crack-stopper, cutouts for slat tracks, reinforcement etc. The integral crack-stopper extends out to rib 24 and is continuous except for a portion in the region of the pylon (ribs 6B to 8) where it is replaced by a bolt-on titanium alloy strap. The crack-stopper is located at approximately on third panel height from the bottom flange. The innermost portion of the front spar contains a cut-out which is used for wing join-up by a permanently bolted on ‘build door ’which forms part of the shear web.
Aft view, looking forward Crack stopper Track 4
Top flange
Track 1
Track 3 Track 2
BoltBolt-on titanium alloy strap ( front face)
Spar web
Bottom flange
Track 10
Rib 21
Rib 8
Rib 20
Rib 6
Rib 7 Track 9 Rib 19
Rib 5
Rib 4
Rib 3
Rib 2
Vertical stiffeners Rib 18
Additional Information
MENU
OUTER WING BOX - Front Spar
EXIT 187
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Front Spar (cont’d) Additional information - Typical spar thicknesses
FRONT SPAR
MENU
OUTER WING BOX - Front Spar (cont’d)
EXIT 188
DATE: JUNE 2003
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Front Spar (cont’d) Additional information - Typical spar thicknesses
FRONT SPAR
MENU
OUTER WING BOX - Front Spar (cont’d)
EXIT 189
DATE: JUNE 2003
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Front Spar (cont’d) Additional information - Typical spar thicknesses
MENU
OUTER WING BOX - Front Spar (cont’d)
EXIT 190
DATE: JUNE 2003
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Slat Track Cans
Track cans 11 and 12 are made from pressed aluminum alloy and aluminum alloy plate welded together. The remaining cans are made from an aluminum alloy tube and aluminum alloy plate welded together. The track cans are held in position by: - the brackets and the cleats attached to the top skin, - the flanges attached to the front spar. Train pieces are attached to the track cans and let liquid come out through the bottom skin.
Ribs 1
Bottom wing
2
Track can 4
8
9 Slat
19
10
Slat track
18
11 12
14
17
16
8
5
7
9
6 12
2 3
5 4
6
Track cans location
7
3
10 11
13
15
20 22
21
23 25
24
26 27
Front spar
Slat track can
MENU
OUTER WING BOX - Slat Track Cans
EXIT 191
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rear Spar The rear spar is made is three pieces: - Inner rear spar (from rib 1 to 6), - Mid rear spar (from rib 6 to 22), - Outer rear spar (from rib 22 to 27).
The rear spars contains an integral crack stopper out of the rib bay 24-25, which is again located at approximately one third panel height from the bottom flange. Between ribs 4 and 6 the integral crack-stopper is reinforced by a bolt-on titanium alloy strap.
Rib 2
Rib 3
Rib 4 Top flange
Vertical stiffeners
Rib 5
Bottom flange
Crack stopper
Spar Web
Additional information
MENU
OUTER WING BOX - Rear Spar
EXIT 192
DATE: JUNE 2003
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rear Spar (cont’d) Rear spar additional information - Typical thicknesses
MENU
OUTER WING BOX - Rear Spar (cont’d)
EXIT 193
DATE: JUNE 2003
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rear Spar (cont’d) Rear spar additional information - Typical thicknesses
MENU
OUTER WING BOX - Rear Spar (cont’d)
EXIT 194
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rear Spar (cont’d) Rear spar joints at rib 6 and 22.
Spar Spar joint joint assembly assembly at at rib rib 66
Rib 6 Middle spar
Rib 22
Rib 6
Inner spar Titanium reinforcing strap
Joint plate
Gusset bracket
Spar Spar joint joint assembly assembly at at rib rib 22 22
Integral crack stopper
Rib 22 datum
Outer spar datum
Middle spar datum
MENU
OUTER WING BOX - Rear Spar (cont’d)
EXIT 195
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rear Spar (cont’d)
On the inner rear spar, the bottom flange is reinforced by additional angles bolted to the back of the spar high shear area due to the load input from the main landing gear. At approximately rib 4, the inner spar web is recessed to accommodate the pintle fittings which houses the bearing supporting the forward attachment point of the main landing gear.
Rear spar
Pintle fitting Jack fitting Pintle fitting
Recess for pintle fitting
Aft angle (outer)
Aft angle (mid)
Side stay fitting
Aft angle
Inside view
MENU
OUTER WING BOX - Rear Spar (cont’d)
EXIT 196
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Jacking Points
A jacking point is provided on the lower surface of the wing at the intersection of the rear spar and rib 9.
Jacking bracket
Rib 9 datum
A
Lower inside skin line Middle spar
Rib 9 datum
Jacking bracket
Middle spar datum
MENU
OUTER WING BOX - Jacking Points
EXIT 197
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Rear False Spar / Main Landing Gear Support Structure
A false rear spar connects the aft end of the gear rib to the wing box between ribs 8 and 9. This spar, together with the skins, the gear rib and internal riblets forms a torque box. The sidestay is attached, via a spherical bearing and steel cardan pin, to the sidestay fitting on the rear spar at rib 9. Retraction jack loads (jack predominantly in compression during retraction) are taken via bearing to the jack fitting lying along the rear spar between ribs 2 and 3.
Top skin stiffeners Gear support rib 5 Pintle fitting Retraction jack fitting
False rear spar
Gear rib 5
Aft attachment
Aft attachment
Pintle fitting
Side stay fitting
Jack fitting Aft angles
OUTER WING BOX - Rear False Spar / MLG Support Structure
MENU
EXIT 198
DATE: JUNE 2003
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Ribs
The twenty-six ribs are positioned to give a near optimum spacing for supporting the top and bottom skins achieving the best position for those ribs carrying the loads from the main landing gear, engine pylon, flap tracks. All ribs are integrally machined using rolled stretched plate of aluminium alloy 7010. In the inner wing, rib 1 to 8 contain cut-outs used for inter-bay access. Ribs 15 (only for A321 and A320), 22 and 27 are fuel bulkheads whilst rib 2 is partially sealed to keep the fuel pumps submerged. All ribs are attached to the skins by interference fit bolts.
2 3
4 5
6
7 8 9
10 11 12 13
Rib Rib to to spar spar assembly assembly 15
14 16
17 18
19 20
21 22
Rib
23 25 24 26
Spar 27
Rib Rib to to top top skin skin assembly assembly Rib
Top skin Additional information
MENU
OUTER WING BOX - Ribs
EXIT 199
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Ribs (cont’d) Additional information - Example of rib thicknesses.
Typical Typical rib rib thickness thickness example example -- Rib Rib 44 MENU
OUTER WING BOX - Ribs (cont’d)
EXIT 200
DATE: JUNE 2003
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Ribs (cont’d) Flap track ribs.
Flap Flap track track rib rib
Flap track rib
MENU
OUTER WING BOX - Ribs (cont’d)
EXIT 201
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
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XSM16B01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
1 - A319 / A320 / A321 STRUCTURE DESCRIPTION 1.6. WINGS
WING LEADING EDGE & TRAILING EDGE Leading Edge and Leading Edge Devices Leading Edge Fixed Structures Slats - General Slats Construction Trailing Edge Fixed Structures A319 / A320 Flaps A321 Flaps Flap Track Fairings Spoilers Ailerons
DATE: JUNE 2003
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XSM16C01
STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS WING LEADING EDGE & TRAILING EDGE Leading Edge and Leading Edge Devices
The leading edge, forward of the wing box front spar and between the wing root rib 1 and rib 27 includes: - The fixed leading edge structure, - Five control surfaces - Slats 1 to 5, - Slat 1, inboard of the engine pylon, - Slats 2 thru 5, outboard of the engine pylon. The five slats are connected to the fixed leading edge by slat tracks. The fixed leading edge houses the following systems: - The environmental protection system (ATA 36-14-00) between the wing root and rib 12, - The wing ice protection (ATA 30-11-00), - The engine bleed air supply system - Ducting - (ATA 36-11-00), - The electrical, hydraulic and pneumatic installations.
Leading edge (57 - 41 - 00)
Slat 1 (57 - 42 - 21)
Slat 2 (57 - 43 - 21)
Slat 3 (57 - 44 - 21)
Slat 4 (57 - 45 - 21)
Slat 5 (57 - 46 - 21)
WING LEADING & TRAILING EGDES - Leading Edge General
MENU
EXIT 204
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Leading Edge Fixed Structures
The fixed leading edge consists of machined ribs, cantilevered from the wing box front spar, supporting a Dnose skin and spar assembly fabricated from aluminium alloy sheet. Access is provided by means of detachable panels along the underside between the front spar and sub-spar. The cantilever ribs are machined from aluminum alloy plate material and consist of: - Main ribs, in pairs, which carry slat track rollers. There are twelve pairs of ribs, four for slat 1 and two each for slats 2 to 5. - Intermediate ribs between the track ribs provide additional support for D-nose assembly and the bottom access panel and provide mid-support for slats 2 to 5, ensuring the slat profile matches that of the wing. The to skin is of conventional aluminum alloy sheet stiffened with rolled stringers. The bottom surface access panels are of sandwich construction (carbon fiber / Nomex honeycomb core) and are attached with quick release fasteners. The panels inboard of the anti-icing telescope are designed to blow out in case of duct burst, when the panels are retained at their forward edges. The D-nose components (skin, spar and ribs) are made from aluminum alloy sheet material.
Nose ribs
Wing front spar
Track 4
Stiffeners
Track 3
Spars Track 2
Track ribs
Track 1
Track 12 Track11
Intermediate Track 10 ribs Track 9
Skins
Track 8
Lower access panels Track 7
Track 6
Track ribs Spar Intermediate ribs
Wing box front spar
Track 5
WING LEADING & TRAILING EGDES - Leading Edge Fixed Structure
MENU
EXIT 205
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Leading Edge Fixed Structures (cont’d)
Doubler
Wing front spar Track 4
Stiffeners
Track 3
Spars Track 2
Track ribs
Track 1
Spreader plate
Wing front spar
Skins
Intermediate ribs Finger plate
Lower access panels Cleat - stringer
Spar
Track ribs
Corner plate
Rib Angle Skin Stiffener Spar
Plate WING LEADING & TRAILING EGDES - Leading Edge Fixed Structure (cont’d)
MENU
EXIT 206
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Leading Edge Fixed Structures (cont’d)
Wing front spar Stiffeners
Track 4
Pylon Fwd Attachment area
Track 3
Spars Track 2
Track ribs
Track 1
Intermediate ribs
Doubler Skins Leading edge skin assembly
Track rib
WING LEADING & TRAILING EGDES - Leading Edge Fixed Structure (cont’d)
Wing box front spar
MENU
Pylon inner outer leading edge ribs
EXIT 207
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Slats - General The five slats forms the movable part of the wing leading edge.
Slat 1 covers the fixed leading edge between the wing root and the engine pylon. Slats 2 to 5 cover the leading edge between the engine pylon and the wing tip. When the slats are rested against the wing in cruise fight, seals prevent airflow between slat and the wing. The slat is kept in position by a hold down device engaged with a stop in the fixed leading edge and it ensures that the shape of the slat conforms closely to that of the deformed wing. There are no requirements to de-ice slat 1 and 2, but the ribs in slats 3, 4 and 5 contains cut-outs to accommodate the piccolo tube.
Track 4
Track 3
A
Slat 1
Track 2
Track 1
Main riveted structure
Slat 2 Slat 3 Slat 4 Slat 5
Track rib 3
Track rib 4
Track rib 2
Hoisting lug
Outboard end rib A
Trailing edge structure
Intermediate ribs
Slat 1 structure
Track rib 1
Inboard end rib
Section A-A Stringer Track rib
Track 1
Rear spar Track 2
Top skin
Trailing edge structure
Lower skin
Trailing edge Fairing
Track 3
Trailing edge structure
Track 4 Top skin
Lower girder
Top skin Rear spar Trailing edge profile Bottom skin Honeycomb core
WING LEADING & TRAILING EGDES - Slats - General
MENU
EXIT 208
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Slats Construction
The main structure of each slat is a riveted assembly of aluminum alloy skin, stringers and ribs. The track ribs are machined from plate while the intermediate ribs and skins are formed from sheet material. The slat trailing edge structure is made from aluminum alloy and includes a honeycomb core sandwich between face sheets and closed at its aft tip by a machined edge member. In order to meet the fail safe requirements, slat 1 is mounted using four tracks, the middle two tracks being driven. Failure of any one track will not result in the slat becoming detached. Slats 2, 3, 4 and 5 have two tracks, both being driven.
Hoisting lug Slat 1
Track rib 7
A
SLAT 3 DETAILED
Front spar
Slat 2
Trailing edge structure
Slat 3 Slat 4
C
Inboard end rib
Slat 5
Hoisting lug Outboard end rib
Intermediate rib
Seal
Main riveted structure
C
Elbows A Seal
Track rib 8
Top plate Seal
Piccolo tube and plate C-C Hold down rib
Rear spar
Front spar Bottom skin
Finger strip Lower girder
Piccolo tube plate WING LEADING & TRAILING EGDES - Slats Construction
Honeycomb core
Seal
Piccolo tube ref. Piccolo tube
Trailing edge profile
Upper girder
Top skin
Rubbing bock
Exhaust air holes
Rubbing block
Stop Hold down bracket MENU
EXIT 209
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Trailing Edge Fixed Structures
The trailing edge is the area aft of the rear spar, between root rib 1 and rib 27. It bears the supports and attachments for the movable surfaces (two flaps, five spoilers and one aileron) and their drive mechanisms. In addition: the trailing edge structure consists of an over-wing and an under-wing panel, a shroud box and a fixed shroud.
Overwing panel
Overwing panel
Underwing panel
Underwing panel False rear spar
Shroud box - Top and bottom skin
Flap drive 2 bracket
Fixed shroud - Top and bottom skin Spoiler 2 hinge fitting
Trailing edge falsework - top and bottom panels
Shroud box structure Wing rear spar
Trailing edge falsework - top skin panel
Spoiler 1 hinge fitting
Spoiler 4 hinge fitting Fixed panel assembly aileron
Fixed shroud structure
Flap drive 3 bracket
Spoiler 5 hinge fitting
Spoiler 3 hinge fitting Flap support rib
Strips, closing plates & seals Flap drive 3 bracket Aileron hinge fittings
Aileron support structure Access panels
WING LEADING & TRAILING EGDES - Fixed Trailing Edge
MENU
EXIT 210
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Trailing Edge Fixed Structures (cont’d)
The trailing edge is the area aft of the rear spar, between root rib 1 and rib 27. It bears the supports and attachments for the movable surfaces (two flaps, five spoilers and one aileron) and their drive mechanisms. In addition: the trailing edge structure consists of an over-wing and an under-wing panel, a shroud box and a fixed shroud.
Trailing edge falsework
False rear spar
Riblets Pylon attachment fittings
Spoiler 1 hinge fitting
Ribs
Spoiler 2 hinge fitting
Wing box rear spart Riblets
Flap drive 2 bracket
WING LEADING & TRAILING EGDES - Fixed Trailing Edge (cont’d)
Flap drive 3 bracket MENU
EXIT 211
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS A319/A320 Flaps
Each inner and outer flap (for A319 and A320) are divided into three main parts: - A leading edge, - A flap box, - A trailing edge.
Rubbing strips Rear spar Front spar Trailing edge structure
A319 / A320 FLAPS
Flap box
Rib 1 Inner flap
Rib 5
Flap track fairing
Leading edge
Flap track fairing
Flap track fairing
Rib 9 Rubbing strips
Flap track 2
Rib 14
Flap track 3 Flap track 4
Outer flap
Flap box
Rib 1
Trailing edge structure
Rib 4
Rear spar
Rib 8
Front spar Rib 11 Leading edge Rib 15 Rib 18 WING LEADING & TRAILING EGDES - A319/A320 Flaps
MENU
EXIT 212
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS A319/A320 Flaps (cont’d) Leading Edge:
The leading edge is of sandwich construction. The inner and outer skins are made of carbon fiber composite and are bonded to an over expanded honeycomb core. Flap Box: The flap box consist of: - Upper and lower panels, - CFRP front and rear spars, - CFRP Ribs, - CFRP doublers for local reinforcements. The upper and lower panels of the inner and outer flaps are of the same design. Each panel is build from CFRP (Carbon Fiber Reinforced Plastic) and integrates the skin, and “U”section stringers.
Adjustable seal
Ribs Trailing edge
Rear spar Inner and outer rib 5 Rib 6 Front spar
Lower skin Inner and outer rib 14
A319 A319 // A320 A320 Flaps Flaps -Construction Construction principles principles Hoisting fitting
Rib 15
Leading edge Upper skin Top skin with integrated stiffeners Front spar CFRP, monolithic CFRP, monolithic Rear spar CFRP, monolithic Trailing edge structure Aluminum alloy
Leading edge CFRP, sandwich
Bottom skin with integrated stiffeners CFRP, monolithic
WING LEADING & TRAILING EGDES - A319/A320 Flaps (cont’d)
MENU
EXIT 213
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS A321 Flaps
The trailing edge flap system comprises an inner and outer flap. Each of these flaps has two elements: a main flap and an aft tab to provide a double slotted arrangement. The inner flap and its tab are made of aluminum alloy, whereas the outer flap is made of CFRP and its tab made of aluminum alloy. The main flaps are supported on four track beams, two for each flap. The outboard three beams are fixed beneath the wing torque box, while the fourth is mounted on the fuselage side. The flap connection to the track beam uses a fail safe pivot to a carriage fitted with needle roller bearings, which run on straight track members fitted to the track beams. Lateral load reactions are provided at track 2 for the inner flap, and track 3 for the outer flap. Tracks 1 and 4 use wing link connections of flap to carriage, to allow for lateral relative movements. The flaps are powered by rotary actuators driven by a spanwise torque shaft. The aft tab is supported off the main flap by additional hinges each formed by two links. The inner flap has three tab hinges, while the outer flap has five. The tabs are driven at the flap tracks 2, 3 and 4 by drive rods connected to the carriages at hinge 1A, where the tab drive mechanism is earthed at the wing fixed trailing edge structure. In the event of a disconnection of any link connecting the tab to the flap or carriage, the tab will remain connected to the main flap.
Rear spar A321 A321 Flaps Flaps
Inner flap tab
Front spar
Inboard Inboard flap flap
Rubbing strips Flap tab
Inner flap
Trailing edge structure
Outer flap
Flap box
Outer flap tab
Rib 1
Rib 7 Leading edge 1B Flap track fairing
Flap track 4
1A Rib 13
3A 3C
Inner flap Rubbing strips
3B
Tab hinges
Rib 1 Flap track 3
Flap track fairing
Rib 2
Outboard Outboard flap flap
Flap tab
Rib 4
Flap track 2
Rib 8
Flap box
Leading edge Rib 11 Rib 15
A321 Flap Construction details
Rib 18 MENU
WING LEADING & TRAILING EGDES - A321 Flaps
EXIT 214
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS A321 Flaps (cont’d)
Additional information: A321 flap construction details (ribs and spars).
Rib 1 Ribs Ribs Rear Rear spar spar
Rib 1
Rib 13
Front Front spar spar Rib 9 Rib 10
Rib 13 WING LEADING & TRAILING EGDES - A321 Flaps (cont’d)
MENU
EXIT 215
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS A321 Flaps (cont’d)
Additional information: A321 flap construction details (upper skin).
Upper Upper skin skin
WING LEADING & TRAILING EGDES - A321 Flaps (cont’d)
MENU
EXIT 216
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS A321 Flaps (cont’d)
Additional information: A321 flap construction details (bottom skin).
Bottom Bottom skin skin
WING LEADING & TRAILING EGDES - A321 Flaps (cont’d)
MENU
EXIT 217
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Flap Track Fairings
The flap track fairing (e.g. No. 2) is divided into two parts, a forward fixed portion attached to the wing bottom skin and a hinged aft part driven by a link from the flap and supported on the flap beam. The fairing shell is of CFRP / Honeycomb sandwich construction.
A319 / A320 FLAPS TRACK FAIRINGS
R
WING LEADING & TRAILING EGDES - Flap Track Fairings
MENU
R
EXIT 218
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Spoilers
There are five spoilers on the upper surface of the wing trailing edge which have the following functions: - Roll function, speed-brake function, ground spoiler function, - Spoiler 1 is connected to the rear false spar, - Spoilers 2 to 5 are connected to wing rear spar.
A321 SPOILERS
A319 / A320 SPOILERS
Spoiler 2
Spoiler 1 Spoiler 2
Spoiler 3
Spoiler 1
Spoiler 3
Spoiler 4
Spoiler 4
Spoiler 5
Spoiler 5
MENU
WING LEADING & TRAILING EGDES - Spoilers
EXIT 219
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Spoilers (cont’d)
The five surfaces are of similar construction consisting of a sandwich structure bonded using carbon fiber composite skins, and Nomex honeycomb core. The central hinge fitting, integral with the actuator attachment is machined from aluminum alloy, as are the end hinge fittings.
Outer hinge bracket
B Honeycomb core
B D
C
C D Center hinge bracket
Trailing edge
Outer hinge bracket Seal Honeycomb core
Actuator attachment fitting
Skins (CFRP)
Link
Seal
Details
WING LEADING & TRAILING EGDES - Spoilers (cont’d)
MENU
EXIT 220
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Spoilers (cont’d)
WING LEADING & TRAILING EGDES - Spoilers (cont’d)
MENU
EXIT 221
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Ailerons
The aileron is located outboard of the outer flap and is connected to the wing box rear spar between ribs 22 and 27. It is manufacturer using CFRP skin, spar and ribs. The center area of the top and bottom skins are of sandwich construction with honeycomb core and CFRP skins for stability reasons. The aileron is fitted with 2 aluminum alloy attachment fittings and 5 hinge fittings.
Ribs
Construction details
Hinge fitting Actuator fitting
Top skin panel
Hinge fitting Actuator fitting Hinge fitting
Trailing edge profile
Diaphragms (upper, lower)
Hinge fitting Hinge fitting Bottom skin panel Outboard rib Upper diaphragm
Top skin panel
Trailing edge profile Lower diaphragm
Spar
Bottom skin panel
Rib MENU
WING LEADING & TRAILING EGDES - Ailerons
EXIT 222
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Ailerons (cont’d)
Trailing edge
Closing rib
Ribs, Ribs, skin skin panels panels
WING LEADING & TRAILING EGDES - Ailerons (cont’d)
MENU
EXIT 223
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Ailerons (cont’d)
Top skin panel
Hinge Hinge fitting fitting Actuator fittings
Spar
Rib
Diaphragms
Hinge fitting
Bottom skin panel Actuator Actuator fitting fitting Top skin panel
Rib
Spar Rib
Bottom skin panel
WING LEADING & TRAILING EGDES - Ailerons (cont’d)
MENU
EXIT 224
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS Ailerons (cont’d)
Actuator fittings
Hinge fitting Diaphragms
Diaphragms
Upper diaphragm Diaphragms Diaphragms
Bottom skin panel
Spar
Leading edge Lower skin panel Lower diaphragm
WING LEADING & TRAILING EGDES - Ailerons (cont’d)
MENU
EXIT 225
DATE: JUNE 2003
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STRUCTURE TRAINING MANUAL 1 - A319 / A320 / A321 STRUCTURE DESCRIPTION
STRUCTURE MAINTENANCE FOR TECHNICIANS
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DATE: JUNE 2003
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