Highlights

To: Holders of A318/A319/A320/A321 Evacuation Slide Forward and Aft Doors (P/N D31516-Series and D31517-Series) manufactured by Air Cruisers; Component Maintenance Manual 25-60-56. Revision No. 24, 04 Dec 2018 HIGHLIGHTS Revision No. 24 of Component Maintenance Manual 25-60-56 reflects pages which have been revised, added, or deleted. The revisions are outlined below. Please discard the manual now in your possession, replace with the attached revised manual, and enter your initials for Revision No. 24 dated 04 Dec 2018 to the Record of Revisions.

CHAPTER/SECTION PAGE NUMBER

DESCRIPTION OF CHANGE

DOCUMENT ENTIRETY Relocated NOTEs and CAUTIONs where necessary to comply with priority order specified in iSpec 2200. TITLE PAGE T-1

Updated revision, date, and copyright year.

RECORD OF REVISIONS RR-2

Added listing for Revision 24.

SERVICE BULLETIN RECORD SB-2

Updated S.B. A320 004-25-64 to Revision 4, updated SB A320-004-97 to Revision 2, Added S.B. A320 002-25-105 “Required Replacement of O-Ring For Gage Adapter Fitting on Valve/ Regulator Assembly”.

25-60-56

HIGHLIGHTS Page 1 of 18

CHAPTER/SECTION PAGE NUMBER SERVICE INFORMATION LETTER RECORD SIL-3

DESCRIPTION OF CHANGE

Added SIL 25-373 “Improved Packboard Assemblies, SIL 25-374 “Improved Packboard Assemblies”, SIL 25-389 “Shelf Life of Green Tape P/N PPP-T-60-Series”.

LIST OF EFFECTIVE PAGES LEP-1 through LEP-8

Updated to reflect this revision.

INTRODUCTION INTRO-1

Updated Table of Contents for this revision.

INTRO-2

Paragraph 1.D: Updated page numbers for list of Abbreviations.

INTRO-4

Table INTRO-1: Added table name and number (Ref. current Air Cruisers guidelines).

INTRO-6 through INTRO-10

Text relocation, additional revisions listed below.

INTRO-7 through INTRO-9

Updated entries to reflect plural usage, AMM, DOM, EASA, mA, MIL-PRF, PDF, ZAES newly added (Ref. current Air Cruisers Guidelines), “mb” was “mb Hg” and “Celsius” was “Centigrade” (correction).

INTRO-11 through INTRO-17

Paragraph 8 Entirety: Section revised to add information on Extended Maintenance for Aged Evacuation Systems and to clearly delineate maintenance tasks required in Standard and Extended Maintenance. (Ref. current Air Cruisers guidelines).

DESCRIPTION AND OPERATION 1

Table of Contents updated for this revision.

25-60-56

HIGHLIGHTS Page 2 of 18

CHAPTER/SECTION PAGE NUMBER DESCRIPTION AND OPERATION (Cont’d) 10

TESTING AND FAULT ISOLATION 1001

DESCRIPTION OF CHANGE

Paragraph 4: “Limitations” was “Installation Limitations” (Ref current Air Cruisers Guidelines). Paragraph 4.B: Revised to refer to Assembly section for storage information. Paragraph 4:C: Newly Added (Ref current Air Cruisers Guidelines).

Table of Contents updated for this revision. Paragraph 4 “Additional Testing for Extended Maintenance of Aged Evacuation Systems” newly added, subsequent paragraphs renumbered. (Ref. current Air Cruisers guidelines).

1002 through 1039

Text relocation, additional revisions listed below.

1002 through 1005

Second NOTE: “Equivalent substitutes may be used” was “Equivalent substitutes may be used for item when marked by the following symbol ” (Ref. current Air Cruisers guidelines). Table 1001: Removed  symbol where applicable (Ref. current Air Cruisers guidelines), changed source for Test Set TU-12 or TU-14 to “Astronics DME LLC”, changed quantity for Brush, 1 In. to “As Required”, added Spatula (Ref. current Air Cruisers guidelines), for Test Set TS-420, added listing to differentiate U.S. domestic version and International version (Ref. ECN 25-60-56 Rev. 23a, MC20260), added Aspirator Fork (Ref. ECN 25-60-56 Rev. 23f, MC20268).

1006

Second WARNING: Newly added (Ref. current Air Cruisers guidelines). CAUTION: Newly added (Ref. ECN 25-60-56 Rev. 23f, MC20268).

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HIGHLIGHTS Page 3 of 18

CHAPTER/SECTION PAGE NUMBER TESTING AND FAULT ISOLATION (Cont’d) 1007

DESCRIPTION OF CHANGE

CAUTION: Newly added (Ref. current Air Cruisers guidelines).

1008

Second NOTE: Expanded to explain recommendations for use of other floor materials (Ref. current Air Cruisers guidelines). Paragraph 3.B.(1).(a): Newly added (Ref. current Air Cruisers guidelines).

1009

WARNING: Newly added (Ref. current Air Cruisers guidelines). Paragraph 3.B.(7): Reduced metric equivalent to single decimal place (Ref. current Air Cruisers guidelines).

1010

NOTE and second CAUTION: Newly added (Ref. current Air Cruisers guidelines).

1014

Paragraph 3.C.(2).(c) and (g): Reduced metric equivalent to single decimal place (Ref. current Air Cruisers guidelines).

1018

First NOTE: Newly added (Ref. current Air Cruisers guidelines). Paragraph 3.D.(1) and (4): Added table reference for Brush (Ref. current Air Cruisers guidelines). Third NOTE: “replace aspirator” was “replace or return to factory” (correction).

1024

NOTE: Added leading zero before decimal (Ref. current Air Cruisers guidelines). Paragraph 3.F.(8): Newly added (Ref. current Air Cruisers guidelines).

1030

Second NOTE: Added table reference for 220 VAC wall adapter (Ref. ECN 25-60-56 Rev. 23a, MC20260).

1031

Second NOTE: Newly added (Ref current Air Cruisers guidelines).

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HIGHLIGHTS Page 4 of 18

CHAPTER/SECTION PAGE NUMBER TESTING AND FAULT ISOLATION (Cont’d) 1034 through 1037

DISASSEMBLY 3001

DESCRIPTION OF CHANGE

Paragraph 4 Entirety: Newly added (Ref. current Air Cruisers guidelines), subsequent paragraphs renumbered.

Table of contents updated for this revision.

3002

NOTE: “Equivalent substitutes may be used” was “Equivalent substitutes may be used for item when marked by the following symbol ” (Ref. current Air Cruisers guidelines). Table 3001: Removed  symbol where applicable (Ref. current Air Cruisers guidelines), updated description and source for Tool, Valve Core to allow other commercially available versions (Ref. current Air Cruisers guidelines).

3002 through 3033

Text relocation, additional revisions listed below.

3003

CAUTION and NOTE: Newly added (Ref. current Air Cruisers guidelines).

3005

Paragraph 3.D: Added Figure 3002A (Ref. ECN MC20546). Paragraph 3.E Entirety: Expanded paragraph to differentiate between systems using Pull Handle 24C17380-105 and those using Pull Handle 24C29245-103 (Ref. ECN MC20546).

3007

Figure 3002A: Newly added (Ref. ECN MC20546).

3012

Paragraph 3.M “Cut and remove all breakaway thread” was “Cut breakaway thread” (Ref. ECN 25-60-56 Rev 23e, MC20262). Figure 3006: Added “and remove” to breakaway thread call-outs (2 places), added depiction of assemblies with breakaway thread (Ref. ECN 25-60-56 Rev 23e, MC20262).

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HIGHLIGHTS Page 5 of 18

CHAPTER/SECTION PAGE NUMBER CLEANING 4001

DESCRIPTION OF CHANGE

Table of contents updated for this revision.

4002

NOTE: “Equivalent substitutes may be used” was “Equivalent substitutes may be used for item when marked by the following symbol ” (Ref. current Air Cruisers guidelines). Table 4001: Removed  symbol where applicable (Ref. current Air Cruisers guidelines), changed quantity for Clean Soft Cloth, Stiff Bristle Brush and Soft Bristle Brush to “As Required” (Ref. current Air Cruisers guidelines).

4003 through 4004

Text relocation, additional revisions listed below.

4003

CAUTION: Expanded to include information about thermobonded seams and patches (Ref. current Air Cruisers guidelines).

4004

Paragraph 3.A.(1) and 4.B: Added table reference for soft bristle brush (Ref. current Air Cruisers guidelines). Paragraph 3.B.(1) and (2): Added table reference for cloth (Ref. current Air Cruisers guidelines).

4005

Paragraph 6.A.(1): Added table reference for soft bristle brush (Ref. current Air Cruisers guidelines). Paragraph 6.B.(1) and (2): Added table reference for cloth (Ref. current Air Cruisers guidelines).

4006

Paragraph 7.A.(1) and 8.A.(1): Added table reference for soft bristle brush (Ref. current Air Cruisers guidelines). Paragraph 7.A.(1) and (2), 8.B.(1) and (2), 9.A.(1) and (2), and 10.A and B: Added table reference for cloth (Ref. current Air Cruisers guidelines).

CHECK 5001

Table of contents updated for this revision, added Paragraph 9 “Check: Extended Maintenance” (Ref. current Air Cruisers guidelines).

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CHAPTER/SECTION PAGE NUMBER CHECK (Cont’d) 5002

DESCRIPTION OF CHANGE

Third NOTE and Paragraph 1.C: Newly added (Ref. current Air Cruisers guidelines).

5003 through 5013

Text relocation, additional revisions listed below.

5003 through 5004

Table 5001: New conditions added for Tube and floor fabric seams to identify items that may require Extended Maintenance procedures and to include checks for thermobonded or welded seams and patches (Ref. current Air Cruisers guidelines). Second sheet added.

5008

Table 5003: Component “Cord Loops for Girt Bar” newly added (Ref. ECN 25-60-56 Rev 23b, MC20261).

5014 through 5020

Paragraph 9 Entirety and Figures 5001 through 5005: Newly added (Ref. current Air Cruisers guidelines).

REPAIR 6001

6003

Table of contents updated for this revision, Added Paragraphs 33 “Replacement or Reattachment of Packboard Mounting Hole Reinforcement Plate on 62366-Series and 62370Series Packboards” (Ref. ECN 25-60-56 Rev 23d), 34 “Replacement of a Torn or Damaged Maintenance Record Pocket on Lacing Cover” (Ref. ECN 25-60-56 Rev 23g) and 35 “Replacement of Non-Air-Holding Accessories and System Components” (Ref. current Air Cruisers guidelines). Table 6001: Expanded use for Isopropyl Alcohol to include “cleaning packboard for reinforcement plate attachment” (Ref. ECN 25-60-56 Rev 23g).

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HIGHLIGHTS Page 7 of 18

CHAPTER/SECTION PAGE NUMBER REPAIR (Cont’d) 6004

DESCRIPTION OF CHANGE

Second NOTE: “Equivalent substitutes may be used” was “Equivalent substitutes may be used for item when marked by the following symbol ” (Ref. current Air Cruisers guidelines). Table 6002: Removed  symbol where applicable (Ref. current Air Cruisers guidelines), “Caster” was “Castor”, (correction) changed quantity for brush to “As Required” (Ref. current Air Cruisers guidelines), added Aspirator Fork (Ref. ECN 25-60-56 Rev 23f, MC20268).

6005 through 6010

Second NOTE: “Equivalent substitutes may be used” was “Equivalent substitutes may be used for item when marked by the following symbol ” (Ref. current Air Cruisers guidelines). Table 6003: Removed  symbol where applicable (Ref. current Air Cruisers guidelines), added Polyurethane paint, additional CAGE code for High Strength Laminating Resin/Hardener, updated quantity to “As Required” for Butyl Gloves, Masking Tape, and Scour Cloth. Rearranged description for Scour Cloth to put generic description first. (Ref. current Air Cruisers guidelines), added Polyurethane Paint (Ref. current Air Cruisers guidelines), Maintenance Log Pocket (Ref. ECN 25-60-56 Rev. 23g) and Reinforcement Plate (Rev. 25-60-56 Rev 23d).

6011through 6118

Text relocation, additional revisions listed below.

6011through 6012

NOTE: “Equivalent substitutes may be used” was “Equivalent substitutes may be used for item when marked by the following symbol ” (Ref. current Air Cruisers guidelines). Table 6004: Removed  symbol where applicable, changed quantity for Brush to “As Required” (Ref. current Air Cruisers guidelines).

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HIGHLIGHTS Page 8 of 18

CHAPTER/SECTION PAGE NUMBER REPAIR (Cont’d) 6013

DESCRIPTION OF CHANGE

NOTE: Newly added (previously omitted). Table 6005: Removed  symbol where applicable (Ref. current Air Cruisers guidelines).

6014

Paragraph 2.A through D.(1): Previously Paragraph 2.A, revised and expanded (Ref. current Air Cruisers guidelines). CAUTION: Newly added (Ref. current Air Cruisers guidelines).

6015

Paragraph 2.D.(2) and (3): Revised and expanded (Ref. current Air Cruisers guidelines). Paragraph 2.E: Newly added (Ref. current Air Cruisers guidelines), subsequent paragraphs renumbered.

6016

Paragraph 2.G.(2): Expanded Celsius listing to single decimal accuracy (Ref. current Air Cruisers guidelines).

6020

Paragraph 3.A.(3) and Figure 6002: “yellow side of patch” was “bottom side of patch” (Ref. current Air Cruisers guidelines).

6025

Paragraph 3.B.(4): “yellow side of the patch” was “underside of the patch” (Ref. current Air Cruisers guidelines). Paragraph 3.B.(6): “yellow side of the fabric patch” was “inside surface of the fabric patch” (Ref. current Air Cruisers guidelines).

6026

Paragraph 3.B.(7): “onto the yellow side of the patch” was “onto the patch” (Ref. current Air Cruisers guidelines).

6029

Paragraph 3.B.(17): “yellow side of patch” was “bottom side of patch” (Ref. current Air Cruisers guidelines).

6033

Paragraph 5.A.(2): Added table reference for cloth (Ref. current Air Cruisers guidelines).

6035

Blank page newly added to maintain format consistency.

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HIGHLIGHTS Page 9 of 18

CHAPTER/SECTION PAGE NUMBER REPAIR (Cont’d) 6036

DESCRIPTION OF CHANGE

NOTE: Added table reference for Masking Tape (Ref. current Air Cruisers guidelines). Paragraph 6.B.(2): Added drying time between sealant coats (Ref. current Air Cruisers guidelines).

6037

Paragraph 6.B.(3): “polyurethane paint” was “conductive paint”, added drying time between coats (Ref. current Air Cruisers guidelines). Figure 6015: “Polyurethane Paint” was “Conductive Paint” (Ref. current Air Cruisers guidelines).

6040

Figure 6018: Added call-outs to differentiate grommet use in girts manufactured prior to May 2009 and May 2009 and subsequent (previously omitted).

6053

Figure 6026: Added leading zero before decimal (6 places) (correction).

6071

Figure 6033: Added leading zero before decimal (2 places) (correction).

6082

Paragraph 20.B.(8): Differentiated rivet use by packboard part number (Ref. ECN 62378 Rev BC).

6088

Paragraph 22.B: Added reference to Item 160A (Ref. ECN 62378 Rev BC).

6090

Paragraph 22.F: Added reference to Item 160A (Ref. ECN 62378 Rev BC).

6094

Paragraph 23.B.(4): Added reference to Item 160A (Ref. ECN 62378 Rev BC).

6111

Paragraph 30: “Replacement of Aspirator AntiChafe Coating” was “Aspirator Anti-Chafe Coating” (Ref. current Air Cruisers guidelines). Paragraph 30.A: Newly added (Ref. current Air Cruisers guidelines), subsequent paragraphs renumbered.

6119

Blank page newly added to maintain format consistency.

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HIGHLIGHTS Page 10 of 18

CHAPTER/SECTION PAGE NUMBER REPAIR (Cont’d) 6120 through 6121

DESCRIPTION OF CHANGE

Paragraph 33 Entirety and Figure 6060: Newly added (Ref. ECN 25-60-56 Rev 23d).

6122 through 6123

Paragraph 34 Entirety and Figure 6061: Newly added (Ref. ECN 25-60-56 Rev 23g).

6124 through 6126

Paragraph 35: Newly added (Ref. current Air Cruisers guidelines).

ASSEMBLY 7002

Second NOTE: “Equivalent substitutes may be used” was “Equivalent substitutes may be used for item when marked by the following symbol ” (Ref. current Air Cruisers guidelines). Table 7001: Removed  symbol where applicable (Ref. current Air Cruisers guidelines), updated description and source for Tool - Valve Core to allow commercially available alternatives (Ref. current Air Cruisers guidelines).

7014

NOTE: Added P/N D31882-103 (previously omitted).

7017 through 7018

Updated storage information with greater detail (Ref. current Air Cruisers guidelines), text relocation included.

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT 9001

Table of contents updated for this revision.

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HIGHLIGHTS Page 11 of 18

CHAPTER/SECTION PAGE NUMBER SPECIAL TOOLS, FIXTURES, AND EQUIPMENT (Cont’d) 9002 through 9008

DESCRIPTION OF CHANGE

Second NOTE: “Equivalent substitutes may be used” was “Equivalent substitutes may be used for item when marked by the following symbol ” (Ref. current Air Cruisers guidelines). Table 9001: Removed  symbol where applicable (Ref. current Air Cruisers guidelines), updated description and source for Tool - Valve Core to allow commercially available alternatives (Ref. current Air Cruisers guidelines), changed source for Test Set TU-12 or TU-14 to “Astronics DME LLC”, changed quantity for Brush, 1 In. to “As Required”, added Testing to Use (Section) for Spatula (Ref. current Air Cruisers guidelines), corrected description for Vacuum, Industrial Type, for Test Set TS-420, added listing to differentiate U.S. domestic version and International version (Ref. ECN 25-60-56 Rev. 23a, MC20260) Added Aspirator Fork TO9878-101 (Ref. ECN 25-60-56 Rev. 23f, MC20268).

9009 through 9016

Figure relocation, additional revisions listed below.

9009

Figure 9001: Added depiction of Aspirator Fork TO9878-101 (Ref. ECN 25-60-56 Rev. 23f, MC20268).

ILLUSTRATED PARTS LIST 10007, 10008

Table 10001: Updated vendor criteria. Paragraph 7.A: Updated page listings.

10009 through 10031

Numerical index updated to reflect this revision, text relocation included.

10033

IPL Figure 1, Sheet 1: Added depictions for Item 130C and 170B, updated call-outs to show Items 140A and 170A (Ref. ECN MC20546).

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HIGHLIGHTS Page 12 of 18

CHAPTER/SECTION PAGE NUMBER ILLUSTRATED PARTS LIST (Cont’d) 10035

DESCRIPTION OF CHANGE

IPL Figure 1, Sheet 3: Corrected call-out for Lower Lacing Cover Assembly, “30B” was “30A” (correction).

10037 through 10127

Figure/Text relocation, additional revisions listed below.

10037

Item 1, 1A, 1B: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10038

Item 5, 6, 6A: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10039

Item 6B, 6C, 6D: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10040

Item 6E, 6F, 6G, 6H: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10041

Item 6J, 6K, 6L: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10042

Item 6M, 6N, 6P: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10043

Item 6R, 6T, 6U, 6V: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10044

Item 6W, 6X, 6Y, 6Z: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10045

Item 6AA, 6AB, 6AC, 6AD: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

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HIGHLIGHTS Page 13 of 18

CHAPTER/SECTION PAGE NUMBER ILLUSTRATED PARTS LIST (Cont’d) 10046

DESCRIPTION OF CHANGE

Item 6AE, 6AF, 6AG, 6AH: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10047

Item 10, 10A, 10B, 11: Expanded nomenclature to better identify units for the field (Ref. ECN 2560-56 Rev 23c).

10048

Item 12, 12A, 12B: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10049

Item 12C, 12D, 12E: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10050

Item 12F, 12G, 12H, 12J: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10051

Item 12K, 12L, 12M: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10052

Item 12N, 12P, 12R, 12T: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10053

Item 12U, 12V, 12W, 12X: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10054

Item 12Y, 12Z, 12AA, 21AB: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10055

Item 12AC, 12AD, 12AE, 12AF: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10056

Item 12AG, 12AH, 20: Expanded nomenclature to better identify units for the field (Ref. ECN 2560-56 Rev 23c).

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HIGHLIGHTS Page 14 of 18

CHAPTER/SECTION PAGE NUMBER ILLUSTRATED PARTS LIST (Cont’d) 10057

DESCRIPTION OF CHANGE

Item 20A, 21, 21A, 21B: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10058

Item 21C: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c). Item 25: Relocated below Item 21D and 21E, expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10059

Item 25A, 26, 26A, 26B: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10060

Item 26C: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c). Item 30: “Supsd by Item 30C” was “Supsd by Item 30A” (correction). Item 30A: “Supsds Item 30C” was “Supsds Item 30” (correction). Item 30C: Newly added (previously omitted).

10062

Item 130B: Added supersession information (Ref. ECN MC20546). Item 130C: Newly added (Ref. ECN MC20546). Item 140: Changed quantity to 1 (Ref. ECN MC20546).

10063

Item 140A: Newly added (Ref. ECN MC20546). Item 170: Changed quantity to 1 (Ref. ECN MC20546). Item 170A: Newly added (Ref. ECN MC20546). Item 170B: Newly added (Ref. ECN MC20546). Item 190: Added supersession information (previously omitted).

10064

Item 190A, 195, 195A: Added supersession information (previously omitted).

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CHAPTER/SECTION PAGE NUMBER ILLUSTRATED PARTS LIST (Cont’d) 10065

DESCRIPTION OF CHANGE

Item 200, 200A, 200B: Expanded nomenclature to better identify units for the field (Ref. ECN 2560-56 Rev 23c).

10066

Item 210, 210A, 210B: Expanded nomenclature to better identify units for the field (Ref. ECN 2560-56 Rev 23c).

10067

Item 210C, 210D, 210E, 210F: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10068

Item 210G, 210H, 210J, 210K: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10069

Item 210L, 210M, 210N, 210P, 210Q, 210R: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10072

Item 280A: Added “Item Not Illustrated” marking (previously omitted).

10077

Item 1, 1A, 1B, 1C: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10078

Item 1D, 1E, 1F, 1G, 1H: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10079

Item 1J, 1K, 10, 10A, 10B: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10080

Item 10C, 10D, 10E, 10F, 10G: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10081

Item 10H, 10J, 10K: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

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CHAPTER/SECTION PAGE NUMBER ILLUSTRATED PARTS LIST (Cont’d) 10084

DESCRIPTION OF CHANGE

Item 100: Updated effectivity codes (Ref. ECN 25-60-56 Rev 23c). Item 110: Added “Item Not Illustrated” symbol (previously omitted)

10086

Item 200: Added “Item Not Illustrated” symbol (previously omitted)

10089

Item 1, 1A, 1B: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10090

Item 1C, 1D, 1E: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10091

Item 1F, 1G, 1H, 1J: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10092

Item 1K, 1L, 1M, 1N: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10093

Item 1P, 1Q, 1R, 1T: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10094

Item 1U, 1V: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10098

Blank page newly added to maintain format consistency.

10102

Item 1, 1A, 5: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

10103

Item 5A, 10: Expanded nomenclature to better identify units for the field (Ref. ECN 25-60-56 Rev 23c).

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CHAPTER/SECTION PAGE NUMBER ILLUSTRATED PARTS LIST (Cont’d) 10104

DESCRIPTION OF CHANGE

Item 10A, 15, 15A: Expanded nomenclature to better identify units for the field (Ref. ECN 25-6056 Rev 23c).

10106

Item 55, 56, 57: Added effectivity codes (Ref. ECN 25-60-56 Rev 23c). Item 92A: Added “Item Not Illustrated” marking (previously omitted).

10112

Blank page newly added to maintain format consistency.

10114

IPL Figure 4A, Sheet 2: Added call-out for Item 80B (previously omitted).

10122

IPL Figure 4B, Sheet 2: Added call-out for Item 160A (Ref. ECN 62378 Rev. BC).

10126

Item 160: Added effectivity codes (Ref. ECN 62378 Rev. BC). Item 160A: Newly added (Ref. ECN 62378 Rev. BC).

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Zodiac Aero Evacuation Systems 1747 State Route 34 Wall Township, NJ 07727-3935 USA CAGE CODE 70167

Zodiac Aerosafety Systems 61 Rue Pierre CURIE 78370 PLAISIR FRANCE CAGE CODE F6101

A318/A319/A320/A321 EVACUATION SLIDE WITH DECORATIVE COVER MANUFACTURED BY AIR CRUISERS (DOING BUSINESS AS ZODIAC AERO EVACUATION SYSTEMS) FORWARD DOOR SLIDE D31516-101 D31516-103 D31516-105 D31516-107 D31516-109 D31516-111 D31516-113 D31516-115 D31516-117 D31516-119 D31516-121 D31516-311 D31516-313 D31516-315 D31516-317 D31516-415 D31516-417 D31516-519 D31516-521 D31516-523 D31516-525 D31516-615 D31516-617 D31516-619 D31516-621 D31516-623 D31516-625 D31516-715 D31516-717 D31516-719 D31516-721 D31516-723 D31516-725

AFT DOOR SLIDE D31517-101 D31517-103 D31517-105 D31517-107 D31517-109 D31517-111 D31517-113 D31517-115 D31517-117 D31517-119 D31517-121 D31517-311 D31517-313 D31517-315 D31517-317 D31517-415 D31517-417 D31517-519 D31517-521 D31517-523 D31517-525 D31517-615 D31517-617 D31517-619 D31517-621 D31517-623 D31517-625 D31517-715 D31517-717 D31517-719 D31517-721 D31517-723 D31517-725

COMPONENT MAINTENANCE MANUAL WITH ILLUSTRATED PARTS LIST The end item product(s)/commodity(s) described in the Component Maintenance Manual (CMM) is controlled for export under the jurisdiction of the United States Department of Commerce, Bureau of Industry and Security Export Administration Regulation (EAR). Zodiac Aero Evacuation Systems (ZAES) believes the proper Export Control Classification Number (ECCN) for the described product is 9A991. This CMM is also subject to the EAR. ZAES believes the proper ECCN for this CMM is 9E991. An export license may be required before this technology (CMM) is used for development, production, or use by foreign persons from specific countries. The user of this technology (CMM) has the individual responsibility to abide by all U.S. export laws and regulations. ORIGINAL ISSUE: 17 AUG 1987 REVISION NO. 24 DATED: 04 DEC 2018 Zodiac Aero Evacuation Systems, Copyright 2018

25-60-56

T-1

COMPONENT MAINTENANCE MANUAL D31516 D31517

RECORD OF REVISIONS RETAIN THIS RECORD IN THE FRONT OF THE MANUAL. UPON RECEIPT OF A REVISION, INSERT THE REVISED PAGES INTO THE MANUAL, ENTER THE DATE INSERTED, AND YOUR INITIALS. REVISION NO.

REVISION DATE

ENGINEER INITIALS

WRITERS INITIALS

Original Issue

17 Aug 1987

ACC

1

14 Mar 1988

ACC

2

17 Jul 1989

ACC

3

03 May 1991

ACC

4

30 Jun 1993

ACC

5

30 Nov 1994

ACC

6

28 Aug 1998

RJB

7

29 Oct 1999

RJB

MAL

8

21 Dec 2001

RJB

MAL

9

22 Mar 2002

RJB

MAL

10

31 Oct 2003

RJB

MJS

11

21 Jul 2004

RJB

MJS

12

28 Sep 2006

RJB

MJS

13

01 Jun 2007

RJB

MJS

14

10 Oct 2008

RJB

MJS

15

11 Jan 2010

RJB

MJS

16

25 Feb 2011

MKT

MJS

17

08 Jun 2012

MKT

MJS

18

06 Sep 2013

DDO

MJS

19

31 Mar 2014

DDO

MJS

25-60-56

DATE INITIALS INSERTED

RR-1 11 Dec 2015

COMPONENT MAINTENANCE MANUAL D31516 D31517

REVISION NO.

REVISION DATE

ENGINEER INITIALS

WRITERS INITIALS

20

11 Apr 2014

DDO

JCG

21

22 Jan 2015

FF

MJS

22

11 Dec 2015

MKT

MJS

23

09 Jan 2017

MKT

MJS

24

04 Dec 2018

MKT

JCG

25-60-56

DATE INITIALS INSERTED

RR-2 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

TEMPORARY REVISION RECORD

TEMP. REV. NO.

ISSUE DATE

DATE INCORPORATED INTO CMM

TR25-1

09 Feb 1995

28 Aug 1998

TR25-2

22 Feb 1996

28 Aug 1998

INSERTED DATE

25-60-56

BY

REMOVED DATE

BY

TR-1 11 Dec 2015

COMPONENT MAINTENANCE MANUAL D31516 D31517

SERVICE BULLETIN RECORD

SERVICE BULLETIN / REVISION NUMBER

ISSUE DATE

DATE INCORPORATED

004-25-1

12 Jan 1989

17 Jul 1989

Electric Harness Routing Modification

004-25-4

16 Jan 1989

17 Jul 1989

Lock Pin Modification

004-25-07 / R2

04 Dec 1989

03 May 1991

Reservoir Sling Replacement

004-25-13

27 Feb 1991

03 May 1991

Replacement of Foam Pads on Packboard

004-25-18

22 Jul 1991

30 Jun 1993

Optional Relocation of Lock Pin Stowage Pocket

004-25-23

04 Sep 1992

30 Jun 1993

Removal of Lacing Cover Knots

004-25-28

01 Feb 1993

30 Jun 1993

Decorative Cover Seal Improvement

004-25-30

16 Apr 1993

30 Jun 1993

Modification, Retention Improvement of Decorative Cover to Packboard

004-25-35 / R2

24 Oct 2006

11 Jan 2010

Stiffener Bracket Inspection/ Replacement

004-25-41 / R2 FAA AD 97-23-13

01 Nov 2002

31 Oct 2003

Release Cable Inspection/Replacement

004-25-43 / R2

12 Oct 1998

29 Oct 1999

Inspection / Fabric Interference with Aspirator Inlet

004-25-46

25 Jul 1997

28 Aug 1998

Optional Modification of Lower Lacing Cover

004-25-47 / R2

10 Oct 2007

10 Oct 2008

Optional Replacement of Lower Lacing Cover

004-25-51 / R2 07 Feb 2003 FAA AD 2001-15-06 DGAC AD 2000-359-152(B)

31 Oct 2003

Installation of Frangible Link Restraint

TITLE

004-25-52 / R1

28 Jan 2000

21 Dec 2000

Installation of Girt Chafing Patch

A320 004-25-57 / R2

08 Feb 2013

06 Sep 2013

Optional Re-Entry Strap Installation

25-60-56

SB-1 11 Dec 2015

COMPONENT MAINTENANCE MANUAL D31516 D31517 SERVICE BULLETIN / REVISION NUMBER

ISSUE DATE

DATE INCORPORATED

A320 004-25-61 / R3

08 Feb 2008

10 Oct 2008

Improved Packboard and Decorative Cover Attachment

A320 004-25-64 / R4

01 Aug 2017

04 Dec 2018

LED Illumination Harness Installation

A320 004-25-71

10 Jul 2003

31 Oct 2003

Optional Floor Seal Replacement

A320 004-25-72 / R1 Airbus S.B. A320-25-1338 AD2004-26-07

28 Oct 2003

21 Jul 2004

Incorporation of Hose Retainer

A320 004-25-74 / R2

20 Nov 2007

10 Oct 2008

Optional Replacement of Inflatable Assembly with Thermobonded Seam Construction

A320 004-25-75 / R2

10 Oct 2007

10 Oct 2008

Treatment and/or Replacement of Lower Mounting Brackets on Packboard

A320 004-25-76

24 May 2004

28 Sep 2006

Optional Packboard and Decorative Cover Attachment to Dual Lock Fasteners

A320 004-25-78 / R2

10 Oct 2007

10 Oct 2008

Treatment and/or Replacement of Lower Mounting Brackets on Packboard

A320 004-25-89 / R1

10 Dec 2010

08 Jun 2012

Replacement or Modification of Release Cable

A320 004-25-97 / R2

01 Sep 2016

04 Dec 2018

Installation of System Wrapper

A320 004-25-105 / R1

09 Feb 2018

04 Dec 2018

Required Replacement of O-Ring For Gage Adapter Fitting on Valve/ Regulator Assembly

25-60-56

TITLE

SB-2 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

SERVICE INFORMATION LETTER RECORD

SERVICE INFORMATION LETTER / REVISION NUMBER

ISSUE DATE

DATE INCORPORATED

25-82 / R5

16 Oct 2001

09 Jan 2017

Recommended Hydrostatic Test Intervals- Inflation Hose Assemblies

25-98 / R5

12 Nov 2007

10 Oct 2008

Maintenance Interval Recommendation

25-102 / R26

31 Jan 2014

22 Jan 2015

Authorized Repair/Service Facilities

25-103

14 Mar 1996

28 Aug 1998

Optional Release Mechanism Replacement

25-113 / R1

12 Nov 1999

21 Dec 2001

Instruction for Replacing an Individual Lamp Housing on an Existing Lamp Harness

25-136

25 Aug 1999

21 Dec 2001

Fastener Retention on Packboard and Decorative Covers

25-141 / R2

28 Jan 2011

08 Jun 2012

Methodology of A319/A320/A321 Serial Numbers

25-152

02 Mar 2001

21 Dec 2001

Improved Heat Reflective Coating Compound

25-160 / R1

20 Jun 2003

28 Sep 2006

Use of Teflon Tape as a Sealant on Pipe Threads Only

25-166 / R1

05 Dec 2002

01 Jun 2007

Lighting System Test Unit; Approval of Basewest Model TS-420 as an Acceptable Alternative to DME Corporation Model TU-14.

25-171

28 Mar 2003

31 Oct 2003

Introduction of an LED Repair Kit

25-175 / R1

08 Sep 2003

31 Oct 2003

Superseding Aspirator Assemblies

25-177 / R1

08 Sep 2003

31 Oct 2003

Superseding Aspirator Assembly

25-178

13 Aug 2003

31 Oct 2003

Incorporation of Inflation Hose Retainer

25-188

07 Jun 2004

28 Sep 2006

Implementation of New Reservoir and Valve Assemblies

SUBJECT

25-60-56

SIL-1 09 Jan 2017

COMPONENT MAINTENANCE MANUAL D31516 D31517 SERVICE INFORMATION LETTER / REVISION NUMBER

ISSUE DATE

DATE INCORPORATED

25-193 / R1

24 Nov 2004

11 Jan 2010

Pentabromodiphenyl and Octabromodiphenyl Ether

25-200

16 Mar 2005

28 Sep 2006

Introduction of Slide Assemblies with Thermobonded Seam Construction

25-201

07 Apr 2005

01 Jun 2007

Supersession of Polymer Adhesive with High-Strength Laminating Resin/Hardener

25-206

24 Jan 2006

01 Jun 2007

Increased Width of Electrical Harness Stowage Fastener

25-208

03 Apr 2006

01 Jun 2007

Packboard Lower Mounting Bracket Corrosion Damage

25-210

20 Mar 2006

01 Jun 2007

Spare Adhesive Nomenclature and Packaging

25-212 / R1

04 Sep 2007

11 Jan 2010

O-Ring Installation Tool Kit

25-218 / R3

31 Mar 2014

31 Mar 2014

Methodology of A319/A320/A321 Serial Numbers

25-224

05 Dec 2007

10 Oct 2008

Decorative Cover Improvements

25-230

28 Jul 2008

11 Jan 2010

Packboard Release Mechanism Rear Support Corrosion

25-236

12 Mar 2009

11 Jan 2010

Electrical Cable Assembly Product Improvement

25-239

22 May 2009

11 Jan 2010

Electrical Cable Assembly Additional Check and Repair Criteria

25-240

17 Jun 2009

11 Jan 2010

Mexico Supplied Parts with Country of Origin Marking

25-243

29 May 2009

13 Jul 2009

Inside Coating of Evacuation Systems, Non-OEM Approved Repair Procedure

25-244

03 Aug 2009

25 Feb 2011

Change of Address

25-252 / R1

14 May 2010

25 Feb 2011

Replacement of Fire-Retardant Tape

SUBJECT

25-60-56

SIL-2 09 Jan 2017

COMPONENT MAINTENANCE MANUAL D31516 D31517 SERVICE INFORMATION LETTER / REVISION NUMBER

ISSUE DATE

DATE INCORPORATED

25-254 / R2

03 Aug 2012

06 Sep 2013

Replacement of Cable Disconnect 26C15091-1

25-274 / R1

09 Dec 2011

08 Jun 2012

Introduction of New Hose Assembly

25-291

18 Jan 2013

06 Sep 2013

New Packboard Tray Assembly for FWD Door Slide Systems

25-292

29 Oct 2012

06 Sep 2013

New Cable Assembly Adapter Used for Testing Lights

25-337 / R1

21 Aug 2015

11 Dec 2015

New Slide Evacuation Systems with a System Wrapper

25-342

17 Jul 2015

11 Dec 2015

Improved Inflation Hose Assembly

25-348

10 Jul 2015

11 Dec 2015

New Electrical Cable Assembly

25-350

21 Aug 2015

11 Dec 2015

Availability of New Packing Fixtures

25-373

12 Jul 2017

04 Dec 2018

Improved Packboard Assemblies

25-374

12 Jul 2017

04 Dec 2018

Improved Packboard Assemblies

25-389

07 Aug 2017

04 Dec 2018

Shelf Life of Green Tape P/N PPPT-60-Series

SUBJECT

25-60-56

SIL-3 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

LIST OF EFFECTIVE PAGES SECTION Title Page

PAGE T-1

SECTION

DATE 04 Dec 18

Record of Revisions RR-1 RR-2

11 Dec 15 04 Dec 18

Temporary Revision TR-1

11 Dec 15

Service Bulletin Record

SB-1 SB-2

11 Dec 15 04 Dec 18

Service Information Letter Record

SIL-1 SIL-2 SIL-3

09 Jan 17 09 Jan 17 04 Dec 18

List of Effective Pages

LEP-1 LEP-2 LEP-3 LEP-4 LEP-5 LEP-6 LEP-7 LEP-8

04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

Table of Contents

T/C-1

11 Dec 15

Introduction

INTRO-1 INTRO-2 INTRO-3 INTRO-4 INTRO-5 INTRO-6

04 Dec 18 04 Dec 18 11 Dec 15 04 Dec 18 11 Dec 15 04 Dec 18

PAGE

DATE

Introduction (Cont’d)

INTRO-7 INTRO-8 INTRO-9 INTRO-10 INTRO-11 INTRO-12 INTRO-13 INTRO-14 INTRO-15 INTRO-16 INTRO-17 INTRO-18

04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

Description and Operation

1 2 3 4 5 6 7 8 9 10

04 Dec 18 09 Jan 17 11 Dec 15 11 Dec 15 11 Dec 15 11 Dec 15 09 Jan 17 11 Dec 15 04 Dec 18 04 Dec 18

Testing and Fault Isolation

1001 1002 1003 1004 1005 1006 1007 1008

04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

25-60-56

LEP-1 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

SECTION Testing and Fault Isolation (Cont’d)

PAGE 1009 1010 1011 1012 1013 1014 1015 1016 1017 1018 1019 1020 1021 1022 1023 1024 1025 1026 1027 1028 1029 1030 1031 1032 1033 1034 1035 1036 1037 1038 1039 1040

DATE 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 Blank

SECTION Disassembly

25-60-56

PAGE 3001 3002 3003 3004 3005 3006 3007 3008 3009 3010 3011 3012 3013 3014 3015 3016 3017 3018 3019 3020 3021 3022 3023 3024 3025 3026 3027 3028 3029 3030 3031 3032

DATE 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

LEP-2 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

SECTION

PAGE

DATE

Disassembly (Cont’d)

3033 3034

04 Dec 18 Blank

Cleaning

4001 4002 4003 4004 4005 4006

04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

Check

5001 5002 5003 5004 5005 5006 5007 5008 5009 5010 5011 5012 5013 5014 5015 5016 5017 5018 5019 5020

04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

SECTION Repair

25-60-56

PAGE 6001 6002 6003 6004 6005 6006 6007 6008 6009 6010 6011 6012 6013 6014 6015 6016 6017 6018 6019 6020 6021 6022 6023 6024 6025 6026 6027 6028 6029 6030 6031 6032

DATE 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

LEP-3 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

SECTION Repair (Cont’d)

PAGE 6033 6034 6035 6036 6037 6038 6039 6040 6041 6042 6043 6044 6045 6046 6047 6048 6049 6050 6051 6052 6053 6054 6055 6056 6057 6058 6059 6060 6061 6062 6063 6064

DATE 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

SECTION Repair (Cont’d)

25-60-56

PAGE 6065 6066 6067 6068 6069 6070 6071 6072 6073 6074 6075 6076 6077 6078 6079 6080 6081 6082 6083 6084 6085 6086 6087 6088 6089 6090 6091 6092 6093 6094 6095 6096

DATE 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

LEP-4 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

SECTION Repair (Cont’d)

PAGE 6097 6098 6099 6100 6101 6102 6103 6104 6105 6106 6107 6108 6109 6110 6111 6112 6113 6114 6115 6116 6117 6118 6119 6120 6121 6122 6123 6124 6125 6126

DATE 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

SECTION Assembly

PAGE

DATE

7001 7002 7003 7004 7005 7006 7007 7008 7009 7010 7011 7012 7013 7014 7015 7016 7017 7018

11 Dec 15 04 Dec 18 09 Jan 17 11 Dec 15 11 Dec 15 11 Dec 15 11 Dec 15 11 Dec 15 11 Dec 15 11 Dec 15 11 Dec 15 11 Dec 15 11 Dec 15 04 Dec 18 11 Dec 15 11 Dec 15 04 Dec 18 04 Dec 18

Fits and Clearances 8001 8002

11 Dec 15 09 Jan 17

Special Tools, Fixtures, and Equipment

04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

25-60-56

9001 9002 9003 9004 9005 9006 9007 9008 9009 9010

LEP-5 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

SECTION Special Tools, Fixtures, and Equipment (Cont’d)

PAGE 9011 9012 9013 9014 9015 9016

Illustrated Parts List 10001 10002 10003 10004 10005 10006 10007 10008 10009 10010 10011 10012 10013 10014 10015 10016 10017 10018 10019 10020 10021 10022 10023 10024 10025

DATE 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 11 Dec 15 11 Dec 15 11 Dec 15 11 Dec 15 11 Dec 15 11 Dec 15 04 Dec 18 04 Dec 18 11 Dec 15 09 Jan 17 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

SECTION

PAGE

Illustrated Parts List 10026 (Cont’d) 10027 10028 10029 10030 10031 10032 10033 10034 10035 10036 10037 10038 10039 10040 10041 10042 10043 10044 10045 10046 10047 10048 10049 10050 10051 10052 10053 10054 10055 10056 10057

25-60-56

DATE 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 09 Jan 17 04 Dec 18 09 Jan 17 04 Dec 18 09 Jan 17 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

LEP-6 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

SECTION

PAGE

Illustrated Parts List 10058 (Cont’d) 10059 10060 10061 10062 10063 10064 10065 10066 10067 10068 10069 10070 10071 10072 10073 10074 10075 10076 10077 10078 10079 10080 10081 10082 10083 10084 10085 10086 10087 10088 10089

DATE 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

SECTION

PAGE

Illustrated Parts List 10090 (Cont’d) 10091 10092 10093 10094 10095 10096 10097 10098 10099 10100 10101 10102 10103 10104 10105 10106 10107 10108 10109 10110 10111 10112 10113 10114 10115 10116 10117 10118 10119 10120 10121

25-60-56

DATE 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18

LEP-7 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

SECTION

PAGE

DATE

Illustrated Parts List 10122 (Cont’d) 10123 10124 10125 10126 10127 10128

04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 04 Dec 18 Blank

Appendix

11 Dec 15 Blank

APPX-1 APPX-2

25-60-56

LEP-8 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

TABLE OF CONTENTS Page INTRODUCTION

INTRO-1

DESCRIPTION AND OPERATION

1

TESTING AND FAULT ISOLATION

1001

DISASSEMBLY

3001

CLEANING

4001

CHECK

5001

REPAIR

6001

ASSEMBLY

7001

FITS AND CLEARANCES

8001

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT

9001

ILLUSTRATED PARTS LIST

10001

FOLDING PROCEDURE APPENDICES

25-60-56

APPX-1

T/C-1 11 Dec 2015

COMPONENT MAINTENANCE MANUAL D31516 D31517

TABLE OF CONTENTS INTRODUCTION Page 1. General Information

INTRO-2

2. Document Distribution

INTRO-3

3. Qualification Dates

INTRO-3

4. Abbreviations and Symbols

INTRO-7

5. Listing of Authorized Service Centers

INTRO-10

6. Identifying Revised Material

INTRO-10

7. Maintenance Inspection Log/Maintenance Release Record

INTRO-10

8. Summary of Air Cruisers Maintenance Tasks

INTRO-11

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INTRO-1 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

1. General Information A. This manual provides Description and Operation, Disassembly, Assembly, Repair, and Testing Instructions for approved mechanics, and an Illustrated Parts List for the A318/A319/A320/A321 Aircraft Evacuation Slide Assemblies (Forward and Aft Doors). The equipment is manufactured by Air Cruisers, 1747 State Route 34, Wall Township, NJ 07727-3935, United States of America - CAGE Code 70167, and by Aerazur, 61 Rue Pierre CURIE, 78370 PLAISIR, France - CAGE Code F6101. B. To facilitate use of this manual, data that is particular to a specific configuration(s) is presented separately by subsection within each major section of the manual. The Table of Contents at the beginning of the manual tabulates all major sections. A more detailed Table of Contents is provided at the beginning of each section. C. Throughout the manual pay particular attention to the WARNINGS, CAUTIONS, and NOTES; their intentions are as follows: WARNING: TO CALL ATTENTION TO METHODS AND PROCEDURES WHICH MUST BE FOLLOWED PRECISELY TO AVOID INJURY TO PERSONS. CAUTION: TO CALL ATTENTION TO METHODS AND PROCEDURES WHICH MUST BE FOLLOWED TO AVOID DAMAGE TO EQUIPMENT. NOTE: To call attention to methods which make the job easier. D. Pages INTRO-7 through INTRO-9 consist of a list of Abbreviations and Symbols used throughout this manual. E. Comments, suggestions, or improvements to this document, including those of an editorial nature, can be sent to: Zodiac Aero Evacuation Systems Technical Publications Department, 1747 State Route 34, Wall Township, NJ 07727-3935 Tel. (732) 681-3527, Fax. (732) 681-9163 E-mail: [email protected] www.zodiacaerospace.com

25-60-56

INTRO-2 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

2. Document Distribution A. Copies of non restricted Component Maintenance Manuals (CMM), Service Bulletins (SB), Service Information Letters (SIL), and Folding Procedures are available on the Technical Publications Index (TPI) through Zodiac Services website: http://tpi.services.zodiacaerospace.com/technical/tpi The documents will be in PDF format and can be read on-line or downloaded at the customer's convenience. To subscribe for this service, contact Zodiac Services using link: http://tpi.services.zodiacaerospace.com/subscribe/form For additional information, please visit: www.services.zodiacaerospace.com

3. Qualification Dates VERIFICATION

DATE

Testing and Fault Isolation

17 Aug 1987

Disassembly

17 Aug 1987

Assembly

17 Aug 1987

25-60-56

INTRO-3 11 Dec 2015

COMPONENT MAINTENANCE MANUAL D31516 D31517

A. Refer to Air Cruisers Component Maintenance Manual 25-65-17 for maintenance of Reservoir and Valve Inflation Assembly. Listed below is a cross reference tabulation between the Evacuation Slide Assemblies and the Reservoir and Valve Assemblies.

AIRCRAFT DOOR DESIGNATION

Forward Door Slide

Aft Door Slide

EVACUATION SLIDE P/N

D31516-101, -103, -105, -107, -109, -111, -113, -115, -117, -119, -121, -311, -313, -315, -317, -415, -417, -519, -521, -523, -525, -615, -617, -619, -621, -623, -625, -715, -717, -719, -721, -723, -725 D31517-101, -103, -105, -107, -109, -111, -113, -115, -117, -119, -121, -311, -313, -315, -317, -415, -417, -519, -521, -523, -525, -615, -617, -619, -621, -623, -625, -715, -717, -719, -721, -723, -725

RESERVOIR FOLDING AND VALVE INFLATION PROCEDURE ASSEMBLY CMM P/N

P-11895

D18309-101, -201

25-65-17

P-11895

D18309-101, -201

25-65-17

CROSS REFERENCE TABULATION TABLE INTRO-1

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B. Methodology of A318/A319/A320/A321 Serial Numbers (Reference S.I.L.s 25-141 and 25-218) For Forward Door Slide System, D31516-Series, and Sub Assembly, D31910-Series, and Aft Door Slide System, D31517-Series, and Sub Assembly, D31910-Series, there are two (2) serial numbers, one for the sub-assembly and one for the system. The reasons are described below: When developing this program, commonality was a goal between forward and aft doors. In keeping with this strategy, both the forward and aft door sub-assemblies are identical. The sub-assembly part numbers (see table) are given their own serial numbers, since the inflatable can be used on either a forward or aft door system. This sub-assembly serial number is located on the girt placard. Once the sub-assembly is mated with its system level components (e.g. packboard, reservoir and valve, hose etc.), a system serial number is established. This system serial number is located on the upper lacing cover’s placard. This methodology is used on the A318/A319/A320/A321 systems manufactured by Air Cruisers, Belmar (Slides S/N C0001 through C0023 and Slide/Rafts S/N C001 through C0070) and later Aerazur, France. Starting in November 2006, Air Cruisers began manufacturing A318/ A319/A320/A321 systems in Liberty, Mississippi, USA, in 2010 in Wall Township, New Jersey, USA, and in 2012 in Chihuahua, Mexico. The serial number methodology for each of these systems are two (2) serial numbers, one for the sub-assembly and one for the system. Unlike the previous methodology, both these serial numbers are the same when shipped from the factory. See the following table for the serial number effectivity from each location.

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COMPONENT MAINTENANCE MANUAL D31516 D31517

SUBLIBERTY SYSTEM DESCRIPTION ASSEMBLY S/N AND PART NUMBER PART NUMBER SUBS Forward Door Slide Aft Door Slide

WALL MEXICO TWP. S/N AND S/N AND SUBS SUBS

D31516-Series

D31910-Series

L20000

C0024

M8001

D31517-Series

D31910-Series

L20000

C0024

M8001

When a system is returned to a Zodiac Services Repair Center and the inflatable is replaced a new sub-assembly serial number is assigned. An “RP” suffix is then added to the existing system serial number located on the upper lacing cover. The “RP” suffix denotes that components from the original returned system were reused. Lastly, the date of manufacture on the lacing cover is updated to match the date of manufacture of the new inflatable sub-assembly.

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4. Abbreviations and Symbols AD AMM AR Assy. Approx. @ BKDN cc CFE CFM CFR CGA CL cm CMM Cont’d CO2 Csk. Cu. Ft. Cu. In. DCR Dia. DOM DOT EASA ECN EFF ELT etc. o C o F FAA FAR FIG. Ft. Ft. Lb. g Hg

Airworthiness Directive Aircraft Maintenance Manual As Required Assembly Approximate At Breakdown Cubic Centimeter(s) Customer Furnished Equipment Customer Furnished Material Code of Federal Regulations Compressed Gas Association Centerline Centimeter(s) Component Maintenance Manual Continued Carbon Dioxide Countersunk Cubic Foot/Feet Cubic Inch(es) Document Change Request Diameter Date of Manufacture Department of Transportation European Aviation Safety Association Engineering Change Notice Effectivity Emergency Locator Transmitter Etcetera Degrees Celsius Degrees Fahrenheit Federal Aviation Administration Federal Aviation Regulation Figure Foot or Feet Foot Pound(s) Gram(s) Mercury

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COMPONENT MAINTENANCE MANUAL D31516 D31517

ICC I.D. In. In. Hg In. Lb. IPL kg kg/Sec Lb. Lb./Sec L.H. L.S. m mA Max. MEK Min. MIL-PRF MIL-STD mm MS N N/A N/cm2 N-m NAS NHA NO. NP O. D. P/N Para. PDF PERM Post Pre psig QTY R Rd. Hd.

Interstate Commerce Commission Inside Diameter Inch(es) Inch(es) of Mercury Inch Pound(s) Illustrated Parts List Kilogram(s) Kilogram(s) per Second Pound(s) Pound(s) per Second Left Hand Left Side Meter(s) Milliampere Maximum Methyl Ethyl Ketone Minimum Military Performance Standard Military Standard Millimeter(s) Military Standard Newton(s) Not Applicable Newton(s) per Square Centimeter Newton-Meter(s) National Aircraft Standard Next Higher Assembly Number Not Procurable Outside Diameter Part Number Paragraph Portable Document Format Permanent Subsequent to Prior to Pound(s) per Square Inch Gage Quantity Revised Round Head

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COMPONENT MAINTENANCE MANUAL D31516 D31517

REE REV RF or REF. R.H. R.S. S.B. (SB) SCFM Sec. S.I.L. (SIL) S/N SRB Subs Supsd Supsds Temp. Rev. or T. R. TSO Ty. TYP. V ZAES ***



Rejection Elastic Expansion Revision Reference Right Hand Right Side Service Bulletin Standard Cubic Feet per Minute Second(s) Service Information Letter Serial Number Survival Radio Beacon Subsequent Superseded Supersedes Temporary Revision Technical Standard Order Type Typical Vendor Zodiac Aero Evacuation Systems Denotes end of Attaching Hardware Denotes Item Not Illustrated Denotes Intentionally Left Blank

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COMPONENT MAINTENANCE MANUAL D31516 D31517

5. Listing of Authorized Service Centers For a complete list of authorized service centers refer to S.I.L. 25-102.

6. Identifying Revised Material NOTE: A revision to a page is defined as any change to the printed matter that existed previously. A. Revisions, additions, and deletions shall be identified by a vertical black line along the left hand margin of the page opposite only that portion of the printed matter that has changed. B. A black line in the left hand margin opposite the page number and date, will indicate that the text was unchanged but the material was relocated to a different page. C. For the detailed parts listing an individual code letter “R”, instead of a vertical black line, shall be used on each line to identify revisions. D. Each page of a complete manual change is assigned the new revision date.

7. Maintenance Inspection Log/Maintenance Release Record A. A maintenance inspection log/record is shipped with each system and is generally located in a maintenance pocket on the outside of a carrying case, lacing cover, container, and/or between a girt assembly depending on the system configuration. It is recommended that the inspection log/record be kept with the system at all times. NOTE: It is recommended that indelible ink be used for recording. The inspection log/record is for the recording of both scheduled and non-scheduled maintenance that has been performed. This information is vital to personnel performing maintenance and/or incorporation of service bulletins.

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8. Summary of Air Cruisers Maintenance Tasks CAUTION: FAILURE TO FOLLOW MANUFACTURER’S RECOMMENDATIONS INCREASE THE RISK OF UNDETECTED CONDITIONS THAT MAY IMPACT SLIDE PERFORMANCE AND CAN POTENTIALLY RESULT IN INJURY TO USERS DURING EMERGENCY SITUATIONS. SLIDES OLDER THAN 15 YEARS OF AGE MUST BE INSPECTED CAREFULLY FOR SIGNS OF DETERIORATION THAT MAY NOT BE READILY APPARENT. A. Periodic In-Service Inspection (1). Perform the following check on the slide evacuation system during service at the intervals to be determined by consultation with the aircraft manufacturer, the aircraft owner or operator, and/or the appropriate governmental or regulatory agency.

TASK

REFERENCE

(a). Check pressure Pressure indicating needle must be gage for acceptable within the green “GO” band. If not, pressure. recheck in two hours with the system in a stable temperature environment. If still not acceptable, refer to CMM 25-65-17. PERIODIC IN-SERVICE INSPECTION TABLE INTRO-2

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B. Standard Maintenance for Evacuation Systems (1). For Evacuation Systems, perform the following Standard Maintenance every 3 years up to and including 15 years. After system has been in service for more than 15 years the following should be done each year (annually), if the inflatable and hose are not replaced at 15 years. NOTE: The first maintenance shall be performed 3 years from the evacuation system’s date of manufacture. Subsequent maintenance shall be performed at intervals based on the date of manufacture and the date of prior maintenance. Systems in service that are not due for maintenance at year 15 from DOM may remain in service until year 16 from DOM, at which point annual maintenance should be performed. For example, the next maintenance would be at year 16 from DOM for a system that had prior maintenance at year 14 from DOM. NOTE: The last day of the month is considered to be the end of the maintenance interval for the listed month and year. NOTE: If the inflatable and inflation hose are replaced, then the 3 year maintenance interval for Standard Maintenance is reinstated for the next 15 years. The date of manufacture of the new inflatable becomes the new applicable date of manufacture of the evacuation system. (2). Standard Maintenance includes the following tests and inspections (if applicable to system):

TASK

REFERENCE

(a). Trial Deployment or Floor Run Functional Test

See Testing section.

(b). Inflatable Integrity Verification Tests 1. Overpressure Test 2. Leakage Test

See Testing section.

STANDARD MAINTENANCE FOR EVACUATION SYSTEMS TABLE INTRO-3 (SHEET 1 OF 2)

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TASK

REFERENCE

(c). Component Tests 1. Aspirator and Pressure Valve Leakage Test 2. Hose Integrity Verification 3. Light System Test

See Testing section.

(d). Visual Checks 1. Slide Assembly 2. Girt Assembly and Release Assemblies 3. Aspirator and Worm Drive Clamp 4. Hose Assembly 5. Decorative Cover and Packboard Assembly (e). Verify incorporation of all outstanding Airworthiness Directives, recommended Service Bulletins, and Service Information Letters. Consult owner/operator regarding incorporation of optional Service Bulletins.

See Check section and, when needed, Disassembly section.

Refer to Introduction section (Para. 2) of this CMM for technical publication index and document sources.

STANDARD MAINTENANCE FOR EVACUATION SYSTEMS TABLE INTRO-3 (SHEET 2 OF 2)

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C. Extended Maintenance for Aged Evacuation Systems NOTE: If system is not due for maintenance at year 15, these checks should commence at the next scheduled maintenance. NOTE: The Inflatable Integrity Overpressure Test as recommended below, using a higher test pressure, is a replacement of the Overpressure Test at the lower test pressure that is referenced for Standard Maintenance. A higher test pressure is recommended for overpressure testing to verify inflatable integrity for aged evacuation systems 15 years and older. (1). Once the evacuation system reaches 15 years of age, Standard Maintenance should be performed with the following additional inspections and criteria:

TASK

REFERENCE

(a). Trial Deployment or Floor Run Functional Test as See Testing section for testing of outlined in Standard Main- inflatable system. tenance (b). Inflatable Integrity Overpressure Test using a Higher Test Pressure

See Additional Testing for Extended Maintenance in Testing section for higher test pressure to be used.

(c). Seam and Patch Check

See Additional Testing for Extended Maintenance in Testing section and Visual Check Tables in Check section.

(d). Previous Repairs Check (e). Sliding Floor Check

(f). Inflatable Integrity Leakage See Testing section for Testing of Inflatable System. Test as outlined in Standard Maintenance (g). Component Test as outlined in Standard Maintenance

See Testing section for Testing of Inflatable System and Check section.

EXTENDED MAINTENANCE FOR AGED EVACUATION SYSTEMS TABLE INTRO-4 (SHEET 1 OF 2)

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TASK

REFERENCE

(h). Visual Checks as outlined See Check section. in Standard Maintenance (i). Aspirator Mounting Flange Check (can be performed prior to Overpressure Testing or after Leakage Testing)

See Additional Testing for Extended Maintenance in Testing section and Visual Check Tables in Check section. This Check can be performed whenever the slide is deflated, and is recommended to be performed prior to Inflatable Integrity Testing.

(j). Verify incorporation of all Airworthiness Directives, Service Bulletins, etc.

Refer to the Introduction section.

EXTENDED MAINTENANCE FOR AGED EVACUATION SYSTEMS TABLE INTRO-4 (SHEET 2 OF 2)

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D. Standard Maintenance for Reservoir and Valve Assemblies NOTE: The first maintenance shall be performed 3 years from the evacuation system’s date of manufacture. Subsequent maintenance shall be performed 3 years from the prior maintenance date. NOTE: Instructions detailed herein serve as a general guideline for reservoir requalification (i.e. Visual Inspection, Hydrostatic Testing, etc.). All inspection and testing shall be performed in accordance with the applicable governing DOT Regulations by DOT-Approved Facilities. (1). Standard Maintenance includes the following tests and inspections (if applicable to system):

TASK

REFERENCE

(a). Verify incorporation of all outstanding Airworthiness Directives, recommended Service Bulletins, and Service Information Letters. Consult owner/operator regarding incorporation of optional Service Bulletins.

Refer to Introduction section (Para. 2) of CMM 25-65-17 for technical publication index and document sources.

(b). Reservoir 1. Reservoir Requalification

See Testing section of CMM 25-65-17.

2. Visual Check

See Check section of CMM 25-65-17.

(c). Valve/Regulator Assembly 1. Visual Check

See Check section of CMM 25-65-17.

2. Valve/Regulator Assem- See Testing section of CMM bly Leakage Test 25-65-17. STANDARD MAINTENANCE FOR RESERVOIR AND VALVE ASSEMBLIES TABLE INTRO-5 (SHEET 1 OF 2)

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TASK

REFERENCE

(c). Valve/Regulator Assembly (Cont’d) 4. Inflation Valve Pull Force See Testing section of CMM Test 25-65-17. (d). Reservoir and Valve Assembly 1. Valve/Regulator Reser- See Disassembly and Assembly sections of CMM 25-65-17. voir Fitting Replacement 2. Visual Check

See Check section of CMM 25-65-17.

3. Reservoir and Valve See Testing section of CMM Assembly Leakage Test 25-65-17. STANDARD MAINTENANCE FOR RESERVOIR AND VALVE ASSEMBLIES TABLE INTRO-5 (SHEET 2 OF 2)

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E. Extended Maintenance for Aged Valve/Regulator Assemblies NOTE: These tasks may be performed within 1 year either before or after the 15 year service mark to align with evacuation system maintenance schedules. (1). Perform the following at 15 year intervals from date of manufacture of the valve assembly, in addition to the Standard Reservoir and Valve Assembly Maintenance.

TASK

REFERENCE

(a). Fully disassemble and inspect valve/regulator assembly.

See Disassembly and Check sections of CMM 25-65-17.

(b). Replace all O-rings.

See Disassembly and Assembly sections of CMM 25-65-17.

(c). Regulator Calibration.

See Testing section of CMM 25-65-17.

EXTENDED MAINTENANCE FOR AGED VALVE/REGULATOR ASSEMBLIES TABLE INTRO-6

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TABLE OF CONTENTS DESCRIPTION AND OPERATION Page 1. Leading Particulars

2

2. Description

6

3. Operation

9

4. Limitations

10

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1. Leading Particulars

ITEM

DESCRIPTION/VALUE

A318/A319/A320/A321 Aircraft Evacuation System

Forward and Aft Slides

Type of Slide and deployment

Single lane, automatic

Slide material (body)

Nylon, reflective polyether urethane coated, single ply, airholding, silver

Floor material

Nylon elastomer coated, silver

Lacing Cover material

Nylon, urethane coated, yellow

Packboard material

Honeycomb Kevlar composite

Length of Slide

267 ± 5 In. (6782 ± 127 mm)

Inflated volume

119 Cu. Ft. (3370 liters)

Operating pressure at 70°F (21.1°C)

2.50 - 3.55 psig (1.72 - 2.45 N/cm2)

System weight

56.4 Lb. (25.8 kg)

Lighting system (D31516-Series, D31517-Series; Pre S.B. A320 004-25-64 and Amendment #4)

Incandescent lamps

Lighting system (D31516-Series, D31517-Series; Post S.B. A320 004-25-64 and Amendment #4)

LED Harness Assembly (Light Emitting Diodes)

LEADING PARTICULARS TABLE 1

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COMPONENT MAINTENANCE MANUAL D31516 D31517

INFLATION PULL HANDLE

SILL END

GIRT

HOOK KNIFE (CEMENTED INFLATABLE)

HOOK KNIFE (THERMOBONDED INFLATABLE)

FRANGIBLE LINK (C19347-107) FRANGIBLE LINK (C19347-121) (2 PLACES) LED/LAMP HARNESS

FRANGIBLE LINK (C19749-103) POST S.B. 004-25-51, FAA AD 2001-15-06, AND DGAC AD 2000-359-152(B)

RE-ENTRY TAPE FRANGIBLE LINK (C19347-104) (2 PLACES)

ASPIRATOR FLOTATION HANDLE FRANGIBLE LINK C19347-104 C19347-107 C19347-121 C19749-103

SLIDING SURFACE

COLOR DECELERATION PAD

BLACK BLACK/NATURAL O. D. GREEN/NATURAL BLACK/ORANGE NO FAIL HANDLE

RUNWAY END

TRACKING RESTRAINTS

EVACUATION SLIDE SYSTEM, TOP VIEW FIGURE 1

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COMPONENT MAINTENANCE MANUAL D31516 D31517

SIDE WRAPPER (2 PLACES)*

WRAPPER*

HOSE ASSEMBLY

RESERVOIR AND VALVE ASSEMBLY RESERVOIR SLING

FLOTATION HANDLE

INTERMEDIATE RESTRAINT

*POST S.B. A320 004-25-97, D31516-719 THROUGH -725, AND D31517-719 THROUGH -725 ONLY

NO FAIL HANDLE

EVACUATION SLIDE SYSTEM, BOTTOM VIEW FIGURE 2

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DECORATIVE COVER

SLIDE ASSEMBLY (PACKED)

PACKBOARD ASSEMBLY

GAGE VIEWING WINDOW

EVACUATION SLIDE SYSTEM, PACKED FIGURE 3

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2. Description NOTE: See Figures 1, 2 and 3 for typical Evacuation Slide System. A. The A318/A319/A320/A321 evacuation slide system is designed to provide a reliable and efficient means of rapid egress from the aircraft to the ground in case of emergency. The basic design for the forward and aft evacuation slide systems are identical. The major subsystems include an inflatable slide assembly, a stored gas reservoir and valve inflation assembly, a composite construction packboard, and a light weight composite decorative hard cover. The evacuation slide system conforms to FAA TSO-C69a. B. The single lane inflatable is an uncomplicated though efficient rectangular structure formed by a pair of longitudinal body tubes connected by mitered intersections to the sill and runway tubes. Supplemental support tubes at the sill end provide the required contact area at the fuselage interface. Additional structural members are limited to an intermediate cross tube which minimizes body tube twist or “roll” motions under load to prevent the sliding lane from being formed into a trough which would adversely affect the evacuation rate. The sliding surface or “floor” of the slide is attached as a taut membrane to the longitudinal tubes transitionally from atop, to somewhat between, to again atop, the tubes along the length of the slide. This composite tube/floor structure can handle up to four evacuees at one time without collapsing. The excellent puncture and abrasion resistance of the highstrength sliding surface fabric make the probability remote for penetration of the airholding chamber by evacuee footwear or other sharp objects. Approximately the lower one-fourth of the slide body is curved to form a “hook” contour for the angle of the sliding surface at the runway end. This transition supplements the braking action of the urethane-coated deceleration panel at the runway end. The deceleration panel, coated with a durable high-friction elastomeric coating, provides positive deceleration to the evacuee and assures the evacuee is brought to an upright position and is able to walk off the slide. Supplemental “vertical” tubes are attached to both ends of the sill tube to provide the required stability of the slide under 25 knot wind conditions. These tubes are contoured to match the curvature of the fuselage adjacent to the door opening.

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Forward Slide System (D31516-Series, S/Ns A15001 and Subs) and Aft Slide Systems (D31517-Series, S/Ns A15000 and Subs) will be manufactured of thermobonded seam construction (a fabric welding process) which supersedes the previously cemented seam construction. Thermobonded inflatable assemblies are completely interchangeable with the previously cemented inflatable assemblies. Form, fit, and function of the complete evacuation slide systems are not affected and repairs can be accomplished with existing CMM procedures. However, if a replacement inflatable assembly is required for retrofit (on systems prior to the S/Ns listed above), a new inflatable assembly using thermobonded seam construction will be shipped. Upon replacement, the system must be reidentified per S.B. A320 004-25-74 and repacked per Folding Procedure P-11895 Rev. T or later. C. The inflation reservoir is installed in a gray urethane-coated nylon fabric sling which is attached by means of white webbing straps permanently attached to the inflatable. Refer to Air Cruisers Component Maintenance Manual 25-65-17 for maintenance of the inflation reservoirs. D. A pull handle on the girt for manual inflation serves as a backup system should the slide fail to inflate automatically upon deployment. The pull handle is triangular in shape and is constructed of white webbing with a red placard reading “PULL” in white letters. The inflation valve release cable is attached to the pull handle with a quick disconnect. E. The aspirator is located on the inflatable’s upper right hand side body tube. It is comprised of an inlet housing section containing a nozzle array, and a cylindrical diffuser/mixing tube. The inlet housing is equipped with one-way flappers which act as a check valve. The expansion of high pressure stored gas through the nozzle array creates a vacuum in the aspirator, causing the flappers to open and ambient air to rush into the inflatable. Thus, inflation time is rapid, and reservoir size is minimized. The aspirator is mounted on the inflatable by clamping it into a molded urethane rubber flange. A worm drive clamp retains the aspirator in the molded flange. The band clamp is covered with electrical tape to prevent the clamp from chafing the inflatable. F. The flexible, braided hose connects the reservoir and valve/regulator assembly to the aspirator and transfers the output gas of the reservoir to the aspirator. The hose assembly is equipped with aluminum swivel end fittings.

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NOTE: The decorative cover is prime coated; finish coats to match aircraft interior color must be applied by operator. Procure paint and/or finished covers from Airbus. G. A composite decorative cover encapsulates the packboard assembly and the packed inflatable. To remove the decorative cover from the packboard assembly, pull sides inboard to release side spring clips (located at bottom of decorative cover). Pull inward and up at bottom of the cover to disengage dual lock fasteners and clips at top. For slide systems -311 and subsequent, or systems modified per S.B. A320 004-25-61, the decorative cover is equipped with a male sliding latch type attachment that attaches to the female latch type attachment on the packboard. The decorative cover has a pressure gage viewing window to permit monitoring of the gas charge pressure of the inflation reservoir. H. The packboard is of composite construction and serves several functions. It has mounting brackets which attach the structure onto the aircraft door. In conjunction with the lacing cover, it retains the folded inflatable and inflation system. I.

The two-piece lacing cover assembly is constructed of yellow urethane coated nylon fabric and is permanently attached to the top edge of the packboard. The lacing cover release mechanism permits the lacing cover to be freed from the lower edge of the packboard, to enable the inflatable to drop outboard (deploy). The bottom and top sections of the lacing cover are joined together with lacing cord to provide a take-up means for positively restraining the packed inflatable.

J.

In ditching, separation of the inflatable slide from the aircraft is accomplished using a release handle located beneath a cover flap on the girt. When the handle is pulled free, the girt separates from the girt bar. The slide can now drift away from the aircraft until the mooring line becomes taut. A mooring line is stowed in a separate sheath between the girt halves. In order to facilitate use of the slide as a flotation device, it is equipped with webbing grasp lines for survivors in the water. They are constructed of nylon webbing and are permanently attached at intervals along each side of the unit.

K. A floating knife is provided to cut the mooring line. It is located in a pocket on the upper sill tube.

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L. Configurations D31516-103, -107, -111 and D31517-103, -107, -111 or systems modified to S.B. 004-25-57, possess a re-entry tape which is located along the right side of the unit permitting passengers to climb back up the slide and re-enter the aircraft. M. Prior to S.B. A320 004-25-64, and prior to Amendment #4, the electrical harness and lamps are attached to the slide by 1 1/2 In. (38.1 mm) wide tape cemented along the sliding surface and runway tube of the inflatable. Post S.B. A320 004-25-64 and Amendment #4, slide systems have LEDs and are installed into fabric wire guides. There are two electrical harnesses - each run down one side and across the runway tube of the inflatable. The lights are actuated automatically during the deployment cycle of the slide with electrical power provided by the aircraft. The lamp harness consists of miniature incandescent halogen filled lamps interconnected by flat “ribbon” wire connectors with a miniature quick connect plug. The LEDs consist of Light Emitting Diodes positioned between twisted wire with a miniature quick connect plug. The plug is easily connected to its aircraft per the Aircraft Maintenance Manual. 3. Operation Under emergency conditions, the operating sequence is as follows: The girt bar is automatically engaged in the floor fittings when the closed door is placed in emergency mode. As the door opens outboard, the pack release cable is pulled free, and the packed slide drops outboard of the door. The automatic inflation cable tensions and opens the valve inflation assembly, initiating inflation. A pull handle is attached to the right side of the girt assembly to manually actuate the valve inflation assembly in the event that automatic inflation does not occur. The packboard and lacing cover remain attached to the aircraft door. As regulated stored gas flows through the hose to the aspirator, a partial vacuum is created in the mixing section of the aspirator by the highvelocity gas as it leaves the nozzles inboard of the flapper valves. As a result, ambient air enters through the flapper valves and combines with the high velocity gas in the venturi to provide for rapid inflation, using a minimum sized reservoir. When the inflation cycle has progressed to a predetermined internal slide pressure, the flapper valves close and the remaining stored gas is used to “top off” the slide to final operating pressure. The aspirator is equipped with a pressure test valve for checking tube pressure and for inflating the slide during maintenance.

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During inflation, restraint devices are used to control the deployment sequence by restraining the unit, so that it remains folded in thirds until it becomes sufficiently pressurized to assure that it is fully extended when it first contacts the ground. The primary restraint mechanism is a precision tension fuse (frangible link) which separates at a pre-determined force value. Supplemental Velcro panels are used in conjunction with the tension fuses to assure repeatable, reliable deployment characteristics. These supplemental panels are sewn to webbing straps which are permanently attached to the inflatable adjacent to the frangible link attachment points. 4. Limitations A. The slide system is installed on the applicable aircraft door in accordance with Aircraft Maintenance Manual (AMM). The conditions and tests required for TSO approval of this article are minimum performance standards. It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. TSO articles must be approved for installation. This article may be installed only if the installation is performed in accordance with 14 CFR part 43 or the applicable airworthiness requirements. B. Storage recommendations can be found in Paragraph 10 of the Assembly section. C. Operational Limitations Evacuation slide D31516-Series is designed for installation on A318/ A319/A320/A321 Forward Doors and must be installed in accordance with aircraft maintenance documentation. Evacuation slide D31617-Series is designed for installation on A318/ A319/A320/A321 Aft Doors and must be installed in accordance with aircraft maintenance documentation. This system has been designed, tested and approved for use in accordance with the requirements of FAA TSO-C69a. The system will operate when subjected to temperatures from -40° C to 71.1° C (-40° F to 160° F).

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TABLE OF CONTENTS TESTING AND FAULT ISOLATION Page 1. Testing Materials/Equipment

1002

2. Test Setup

1006

3. Testing of Inflatable System

1007

A. Trial Inflation (Functional Deployment Test)

1007

B. Floor Run Functional Test

1008

C. Inflatable Integrity Verification Tests

1010

D. Aspirator and Pressure Test Valve Leakage Test

1018

E. Hose Integrity Verification

1022

F. Light System Test (TU-12 Test Unit)

1023

G. Light System Test (TU-14 Test Set)

1026

H. Light System Test (TS-420 Test Set)

1030

4. Additional Testing for Extended Maintenance of Aged Evacuation Systems

1034

5. Fault Isolation

1038

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1. Testing Materials/Equipment (Table 1001) NOTE: Drawings of equipment/tools manufactured by Air Cruisers are available from Air Cruisers upon request. NOTE: Equivalent substitutes may be used.  ITEM/DESCRIPTION

QUANTITY

Leak Test Solution, Clear Ivory Hand Washing Dish Liquid Detergent

As Required

SOURCE

USE

Commercially Determines leakage of Available inflatable assemblies.

One ounce (29.6 milliliters) of detergent mixed to every 64 ounces (1.9 liters) of water Pipe Thread Sealing Compound No. 2 PLS2*

As Required

Federal Process Corp. V3CKH7

Aspirator pressure test valve installation leakage deterrent.

Nickel Coated Teflon Tape M12243*

As Required

Air Cruisers V70167

Aspirator pressure test valve installation leakage deterrent.

Teflon Tape AA-58092-2-1*

As Required

Commercially Aspirator pressure test Available valve installation leakage deterrent.

Barometer [Scale increments not more than 0.10 In. (2.5 mm)] 

1

Commercially Measures ambient Available pressure.

Thermometer [Scale increments not more than 1°F (0.6 °C)]

1

Commercially Measures ambient temAvailable perature.

Test Set (Light System) Model TU-12 or TU-14

1

Astronics DME Verifies power unit voltLLC age and lamp/LED harV55827 ness amperage.

* Alternatives for aspirator pressure test valve installation only. TESTING MATERIALS/EQUIPMENT TABLE 1001 (SHEET 1 OF 4)

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ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Test Set (Light System) Model TS-420 (Alternative to TU-14) US Domestic version 4-1020-102

1

BaseWest, Inc. Verifies power unit voltV0MF00 age and lamp/LED harness amperage. Domestic version includes BaseWest 115-120VAC battery charger P/N 36-1002, with a 2 prong Type A plug.

Test Set (Light System) Model TS-420 (Alternative to TU-14) International version 4-1020-202

1

BaseWest, Inc. Verifies power unit voltV0MF00 age and lamp/LED harness amperage. International version includes BaseWest 220VAC battery charger P/N 36-1005, with a 2 prong Type A plug and a 2 prong Type C adapter (adapters to fit other electrical systems must be purchased locally).

Brush, 1 In. (25.4 mm)

As Required

Commercially Applies leak test soluAvailable tion.

Hydrostatic Test Machine TO4853

1

Air Cruisers V70167

Overpressure tests hose assemblies.

Tool - Adapter, Pressure Test Valve C37099-103

1

Air Cruisers V70167

Connects manometer/ pressure gage to pressure test valve for inflatable assembly pressure reading.

Fixture, Overpressure TO6762-1

1

Air Cruisers V70167

Personnel safety equipment used during overpressure testing.

TESTING MATERIALS/EQUIPMENT TABLE 1001 (SHEET 2 OF 4)

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ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Manometer (water) 0 to 5.0 psig (0 to 3.4 N/cm2) *

1

Commercially Measures pressure of Available inflatable assembly.

Manometer (Meriam Fluid) 0.5 to 5.0 psig (0.3 to 3.4 N/cm2) [9.4 in. (238.8 mm) M. F. per 1.0 psig (0.7 N/cm2)] *

1

Commercially Measures pressure of Available inflatable assembly.

Pressure Gage (Mechanical/Digital) Scale Range 0 to 15 psig (0 to 10.3 N/cm2) * 2.0% Accuracy

1

Commercially Measures pressure of Available inflatable assembly.

Stopwatch, Plain Timer (1/10 Seconds Graduations)

1

Commercially Measures inflation time Available of system during functional deployment test.

Adapter/Cable Assembly, Electric 60159-101, 65037-1, or 69525-1

1

Protective Blanket Furniture Moving Type (Quilted polyester fabric with cotton stuffing) Minimum Approximate size 80 x 72 In. (2032 x 1829 mm) and weight 6.25 Lb. (2.8 kg)

1

Air Cruisers V70167

Used with TU-12, TU-14, or TS-420, for lamp/LED harness amperage verification.

Commercially Personnel safety equipAvailable ment used during overpressure testing.

* Alternatives TESTING MATERIALS/EQUIPMENT TABLE 1001 (SHEET 3 OF 4)

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ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Aspirator Fork TO7898-101 (Optional)

1

Air Cruisers V70167

Maintains an open aspirator inlet to allow air to escape the inflatable after testing or during packing.

Spatula (Pusher) PA-1 (or similar tool with a dull blade)

1

Air Cruisers V70167

Used to verify adequate bonding strength of cemented seams and accessories.

TESTING MATERIALS/EQUIPMENT TABLE 1001 (SHEET 4 OF 4)

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2. Test Setup A. Testing of components is accomplished on the inflatable with all components assembled as an operational system. WARNING: USE EYE, FACE, AND EAR PROTECTION WHEN USING HIGH PRESSURE AIR TO PROTECT PERSONNEL FROM POSSIBLE INJURY. WARNING: EXERCISE CAUTION WHEN USING LEAK TEST SOLUTION DUE TO RISK OF PERSONAL INJURY FROM SLIPS AND FALLS. NOTE: The shop compressed air source should be free of oil and moisture and incorporate a 20 micron filter. B. Attachment of inflation shop air source or manometer testing equipment to the inflatable is accomplished using pressure test valve adapter (Table 1001) connected to pressure test valve on the aspirator. CAUTION: ASPIRATOR FORK (TABLE 101) MAY BE USED TO SECURE THE FLAPPER INLET VALVES ON THE ASPIRATOR IN THE OPEN POSITION TO ALLOW ENTRAPPED AIR TO ESCAPE THE SLIDE ASSEMBLY. SPRING CLAMPS OR OTHER DEVICES SHOULD NOT BE USED DUE TO POTENTIAL DAMAGE TO THE CLOSING MECHANISM OR SEALING SURFACES OF THE FLAPPER VALVES. ENSURE ASPIRATOR FORK IS REMOVED FROM THE ASPIRATOR DURING SUBSEQUENT STEPS OF THE PACKING PROCESS.

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3. Testing of Inflatable System NOTE: There are two acceptable Functional Tests: 3.A, Trial Inflation (Functional Deployment Test), an actual trial inflation performed off the aircraft or 3.B, Floor Run Functional Test, a trial inflation performed on a shop floor. A. Trial Inflation (Functional Deployment Test) (1). A system function test may be performed by deploying the slide from the aircraft at time of removal for maintenance check. CAUTION: CONSULT AIRCRAFT MAINTENANCE MANUAL FOR RECOMMENDATIONS FOR PROTECTION OF THE AIRCRAFT. PROTECTIVE MEASURES MUST BE SECURED ADEQUATELY ON ALL SIDES TO PREVENT INGESTION INTO THE ASPIRATOR WHICH MAY RESULT IN AN UNSUCCESSFUL SLIDE DEPLOYMENT OR POSSIBLE DAMAGE TO AIRCRAFT OR SLIDE COMPONENTS. NOTE: If an aircraft is unavailable, see Paragraph 3.B, Floor Run Test. (2). The deployment area should be covered with carpeting or other protective material. (3). Check reservoir and valve inflation assembly pressure gage for proper gas charge reading prior to deployment. See Check section. (4). Place door in armed mode, open the door, and deploy the slide. At +77°F ± 18°F (25°C ± 10°C) ambient temperature, the slide system should inflate to a pressure of 1.5 psig (1.03 N/cm2) within 3.5 seconds. (5). Inflation time, 3.5 seconds maximum, can be obtained by measuring, with a stopwatch, the time from initiation of inflation until the inflatable is fully extended. (6). Normal operating pressure for the evacuation slide is 2.5 to 3.55 psig (1.72 to 2.45 N/cm2). Check immediately after deployment with manometer or pressure gage (Table 1001) connected to pressure test valve on aspirator via adapter (Table 1001).

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(7). If performance requirements are not met, the equipment is not functioning properly. Isolate the cause (see Paragraph 4, Fault Isolation) and correct the problem(s) before returning the slide assembly to service. (8). Remove the slide from aircraft. See Aircraft Maintenance Manual. B. Floor Run Functional Test CAUTION: ENSURE FRANGIBLE LINKS ARE DISCONNECTED (SEE DISASSEMBLY SECTION). NOTE: Use this procedure to functionally test a system on the shop floor as an alternative to deploying from an aircraft. NOTE: The inflation test area is recommended to be carpeted to protect slide components from damage by abrasion or impact due to contact with the floor. Other surface materials are acceptable, provided they have a smooth, clean surface that will not abrade or otherwise damage slide components. Test area should be clean and free of sharp objects and potential chafe hazards. NOTE: A minimum of three persons is recommended to support the test. • Test director to initiate inflation and to time the process • One person to hold the aspirator • One person to read the pressure measuring instrument (1). Remove the slide from the packboard and unfold per the Disassembly section. (a). Slide lighting operation and amperage checks should be performed in accordance with the light system tests outlines in Paragraphs 3.F, 3.G, or 3.H. (2). Extend slide to its full length and width with floor side up.

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WARNING: REMOVE TAPE FROM THREADED CONNECTIONS ON THE INFLATION HOSE AT THE ASPIRATORS AND INFLATION VALVE AND VERIFY THAT THE CONNECTIONS ARE PROPERLY THREADED AND TORQUED. REMOVE TAPE FROM WORM DRIVE CLAMP AROUND ASPIRATOR AND VERIFY THAT THE CLAMP IS PROPERLY SEATED AND SECURED. LOOSE OR INADEQUATELY SECURED COMPONENTS ARE A DANGER TO PERSONNEL DURING FLOOR RUN FUNCTIONAL TESTS AND INFLATABLE INTEGRITY TESTING. (3). Separate inflation cable from girt. Remove quick disconnect fitting and pull handle, remove cable from grommet tab and reattach pull handle and fitting. (4). Check pressure gage on reservoir to insure gage pointer is above minimum pressure. WARNING: HOLD ASPIRATOR AT ARMS LENGTH AND OFF THE FLOOR WITH OPENING AWAY FROM THE FACE AND AWAY FROM LOOSE OBJECTS WITHIN 6 Ft. (1.8 m) TO PREVENT DAMAGE OR INJURY FROM HIGH PRESSURE AIR. (5). Remove the lock pin from valve, if applicable. NOTE: Record time in seconds to when slide is fully formed. (6). Initiate inflation by pulling the inflation cable from the valve and record time to when slide is fully formed. Time should be 3.5 seconds maximum. (7). Within one to five minutes following gas discharge, connect adapter (Table 1001) and manometer (Table 1001) or pressure gage (Table 1001) to the pressure test valve and record pressure. Pressure should be 2.5 psig (1.7 N/cm2) minimum. (8). If performance requirements are not met, the equipment is not functioning properly. Isolate the cause (see Paragraph 4, Fault Isolation) and correct the problem(s) before returning the slide assembly to service.

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C. Inflatable Integrity Verification Tests (Figure 1001) CAUTION: PERFORM A LEAKAGE TEST AND AN OVERPRESSURE TEST AFTER ANY REPAIR WHICH COULD AFFECT AIR RETENTION CAPABILITIES. THIS WOULD NOT INCLUDE REPLACEMENT OF ASPIRATORS. CAUTION: BEFORE AND AFTER OVERPRESSURE TEST, TIGHTEN ASPIRATOR ASSEMBLY WORM DRIVE CLAMP (REFERENCE FIGURE 7004 AND TABLE 8001). NOTE: When performing an Overpressure Test in situations where Extended Maintenance of Aged Evacuation Systems applies, reference Paragraph 4.A for Overpressure Test requirements. The Overpressure Test on Aged Evacuation Systems uses a higher test pressure to verify inflatable integrity for aged systems 15 years and older. The Overpressure Test for Aged Evacuation Systems replaces the Overpressure Test for Standard Maintenance (which is performed at a lower test pressure as referenced below). (1). Overpressure Test (a). Hold the aspirator flapper valves open; position shop air nozzle approximately 3 to 4 In. (76.2 to 101.6 mm) away from the aspirator inlet (flapper valve); add air until slide inflates (rounds out) to design shape. Allow aspirator flapper valves to close. WARNING:PLACE OVERPRESSURE FIXTURE (TABLE 1001) OVER AND IN FRONT OF ASPIRATOR TO PROTECT PERSONNEL FROM POSSIBLE INJURY. WARNING:PLACE PROTECTIVE BLANKET (TABLE 1001) OVER INFLATABLE TO PROTECT PERSONNEL FROM POSSIBLE INJURY. (b).Place protective blanket (Table 1001) over inflatable. (c). Position overpressure fixture (Table 1001; Figure 1002) in front of aspirator. CAUTION: CHECK INFLATABLE PRESSURE TO ASSURE THAT THE MAXIMUM SPECIFIED VALUE IS NOT EXCEEDED. (d). Remove the cap from the pressure test valve, located on the aspirator. Install pressure test valve adapter (Table 1001) and attach air line to adapter. (e). Increase the tube pressure to 3.9 psig (2.7 N/cm2).

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(f). Remove air line. NOTE: Measure the pressure with a manometer or gage (Table 1001) calibrated in increments not greater than 0.1 psig (0.07 N/cm2) connected to the pressure test valve on the aspirator. (g). Record slide pressure and time. (h). Allow the slide assembly to stand undisturbed for a time interval of five minutes. (i). Check slide for structure degradation, lifts, seam separation, or material fatigue. None is permitted. There shall be no evidence of construction or material failure. All seams and accessories shall remain intact and show no evidence of separation. (j). At the conclusion of the test, the inflation and measurement adapter will be removed, and the pressure test valve cap reinstalled. (k). Remove protective blanket and overpressure fixture from slide. (l). Deflate the slide assembly or proceed to Leakage Test.

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COMPONENT MAINTENANCE MANUAL D31516 D31517

ASPIRATOR

SLIDE ASSEMBLY SHOP AIR HOSE

FLAPPER VALVE

ASPIRATOR SHOP AIR HOSE

INFLATABLE INTEGRITY VERIFICATION TESTS FIGURE 1001

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OVERPRESSURE FIXTURE

SLIDE (TYP.)

OVERPRESSURE FIXTURE PLACEMENT (TYPICAL) FIGURE 1002

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(2). Leakage Test (Figure 1003) CAUTION: PERFORM AN OVERPRESSURE TEST AND A LEAKAGE TEST AFTER ANY REPAIR WHICH COULD EFFECT AIR RETENTION CAPABILITIES. THIS WOULD NOT INCLUDE REPLACEMENT OF ASPIRATORS. NOTE: If pressure test was previously conducted and system is inflated, proceed to Paragraph 3.C.(2).(b) for “inflated state” instructions. (a). Hold the aspirator flapper valves open; position the air nozzle approximately 3 to 4 In. (76.2 to 101.6 mm) away from the aspirator inlet (flapper valves). Add air until the slide inflates (rounds out) to design shape. Allow the aspirator flapper valves to close. NOTE: Measure pressure with a manometer or gage (Table 1001) calibrated in increments not greater than 0.1 psig (0.07 N/cm2) connected to the pressure test valve on aspirator, via adapter (Table 1001). (b). From a deflated state, inflate the unit 0.25 psig (0.17 N/cm2) over the required on-test pressure. From an inflated state (i.e. overpressure test), deflate the unit 0.25-0.50 psig (0.17-0.35 N/cm2) below the required on-test pressure. (c). Remove the cap from the pressure test valve, located on the aspirator. Install pressure test valve adapter (Table 1001), attach air line to adapter, and add air. Top-off tube pressure to 2.5 psig (1.7 N/cm2). (d). Remove air line. (e). Note time. (f). Allow the slide to stabilize for one hour. (g). After one hour, check and readjust the pressure to 2.5 psig (1.7 N/cm2) if necessary. (h). Record slide pressure, temperature, barometric pressure, and time.

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(i). Allow the slide assembly to stand undisturbed for the desired test interval (four hours minimum is recommended). Record the slide pressure, temperature, barometric pressure, and time of day at the end of the pressure test.

INFLATABLE PRESSURE, PSIG

2.5

2.0

1.5

1.25

1.0 0

2

4

6

8

10

12

TIME ON TEST, HOURS

MINIMUM ALLOWABLE SLIDE PRESSURE VERSUS TEST DURATION FIGURE 1003

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CAUTION: TO PREVENT MOLD OR MILDEW GROWTH, OR THE POSSIBLE DISCOLORATION OR COLOR TRANSFER FROM VARIOUS COMPONENTS, UNITS SHOULD BE ALLOWED TO DRY THOROUGHLY PRIOR TO ROLLING UP FOR TEMPORARY STORAGE OR FINAL PACKING. NOTE: The minimum permissible slide pressure is shown in Figure 1003 after correction for temperature and pressure variations. Correct for temperature variations by subtracting 0.1 psig (0.07 N/cm2) for every 3°F (1.7°C) rise in temperature or by adding 0.1 psig (0.07 N/cm2) for every 3°F (1.7°C) fall. Correct for barometric changes. If the barometric pressure decreased subtract 0.1 psig (0.07 N/cm2) to the final gage reading for every 0.2 In. of mercury decrease (6.8 mb). If the barometric pressure increased add 0.1 psig (0.07 N/cm2) to the final gage reading for every 0.2 In. of mercury increase (6.8 mb). (j). If the corrected pressure has fallen below specified limits in Figure 1003, reinflate the slide to 2.5 psig (1.7 N/cm2). Check for aspirator and pressure test valve leakage per Paragraph 3.D. Check for inflatable leaks by swabbing the tubes with leak test solution (Table 1001) using a soft brush, or cloth.

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D. Aspirator and Pressure Test Valve Leakage Test (Figures 1004 and 1005) NOTE: This test may be conducted at the beginning of the Inflatable Integrity Leakage Test, and should be performed when the inflatable pressure is 2.0 psig (1.4 N/cm2) minimum. NOTE: Perform this test after aspirator replacement. (1). Using a brush (Table 1001), apply leak test solution (Table 1001) at sealing flange. (2). Check joint between inlet housing and sealing flange. (3). If bubbling occurs at the sealing flange (indicating a leak) tighten worm drive clamp screw (Table 8001). NOTE: If leakage is detected, replace aspirator. (4). Apply leak test solution (Table 1001) with a brush (Table 1001) to the flapper valve seat area of ambient air inlet. If bubbling occurs (Indicating a leak), replace the aspirator. CAUTION: WHEN DRYING PARTS WITH COMPRESSED AIR JET, AVOID DIRECTING THE AIR ONTO THE FLAPPER VALVES SINCE THE VALVES MAY UNSEAT, CAUSING SLIDE PRESSURE TO DROP. (5). Dry parts using compressed air.

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COMPONENT MAINTENANCE MANUAL D31516 D31517

BRUSH

SEALING FLANGE

LEAK TEST SOLUTION

INLET HOUSING

ASPIRATOR

WORM DRIVE CLAMP SCREW

FLAPPER VALVE SEAT BRUSH LEAK TEST SOLUTION

ASPIRATOR AND PRESSURE TEST VALVE LEAKAGE TEST FIGURE 1004

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(6). Remove pressure test valve cap. (7). Apply leak test solution (Table 1001) with a brush to the valve body and the valve base. If bubbling occurs at the base (indicating a leak), remove valve body and apply sealing compound or teflon tape (Table 1001) to threads. If Teflon tape is used, apply as follows: (a). Thoroughly clean and degrease male and female threads assuring the removal of all previously applied anti-seize compound or tape. CAUTION: IN NO CASE WILL THE TAPE BE PERMITTED TO EXTEND BEYOND THE FIRST THREAD. NOTE: Apply tension on tape while wrapping. (b). Wrap tape tightly in direction of the thread spiral of the male pipe thread beginning with the first thread. (c). Using care not to contaminate tape, encircle the threads and join together with a very slight overlap, not more than half of the tape width. (d). Press tightly on tape. Cut tape using scissors. Ensure tape is tight and remains at the first thread of fitting. Loose ends are not permitted. Pipe thread is now ready for joining. (8). If removal of Teflon tape is necessary, hold valve at such an angle as to ensure that any loose Teflon tape fragments cannot fall into valve or adjacent components. (9).

Re-install and/or replace valve. Tighten per Table 8001.

CAUTION: WHEN DRYING PARTS WITH COMPRESSED AIR JET, AVOID DIRECTING AIR ONTO FLAPPER VALVES SINCE, THE VALVES MAY UNSEAT, CAUSING SLIDE PRESSURE TO DROP. (10). Dry parts using compressed air. (11). Replace cap and hand tighten.

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VALVE BASE VALVE BODY

ASPIRATOR

PRESSURE TEST VALVE CAP BRUSH LEAK TEST SOLUTION

ASPIRATOR AND PRESSURE TEST VALVE LEAKAGE TEST FIGURE 1005

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E. Hose Integrity Verification (1). Perform a hose integrity verification test every three years coincident with system level maintenance. NOTE: The recommended hydrostatic test and inspection schedule is every three years, up to and including 15 years. After 15 years of age, test annually. (2). Perform a hydrostatic test using hydrostatic test machine (Table 1001) at 900 psig (620.5 N/cm2) for a time period of three to five minutes. Replace the hose if evidence of permanent distortion or leakage is observed.

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F.

Light System Test (TU-12 Test Unit) (Figure 1006) CAUTION: WHEN CONNECTING/DISCONNECTING THE EXTENSION CABLES, ALWAYS GRASP THE CONNECTOR BODY INSTEAD OF PULLING ON THE CABLE WIRE TO PREVENT DAMAGE TO THE CONNECTORS/CABLES. NOTE: Applicable to Slide System configurations -101 through -117 only. NOTE: TU-12 Test Unit is no longer available from DME Corporation. TU-14 is available as a higher reliability test set. See Paragraph 3.G. NOTE: Typically two tests are conducted. While the unit is inflated an amperage reading will be taken and recorded. A visual check will be performed to verify that each lamp is lit. The first amperage reading is compared to a second reading taken when the packing procedure is complete. (1). Check that all electrical connections between the slide cable assembly and the test adapter cable assembly (Table 1001) are secure. (2). Set load selector knob to B. (3). Install the four-pin test connector from the test adapter cable assembly into the receptacle of the TU-12 test unit. (4). Move the TU-12 arm switch to the “arm” position. (5). Depress the TU-12 activate push button to activate test unit. (6). Move the switch on the test adapter cable box to the “lamp” position.

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NOTE: An ammeter reading below the acceptable amperage range or a Post-pack ammeter reading differing from the Pre-pack reading by greater than 0.030 amperes indicates a possible broken or burned out lamp in the THS lamp harness. An ammeter reading that is higher than the acceptable amperage range indicates the possibility of a short circuit. To replace a lamp or entire lamp harness see Repair section. (7). Depress the TU-12 lamp test button until the digital ammeter reading is stabilized and record the reading in amperes. Release the test button. If the amperage reading is between 0.810 and 0.922 amperes, the lamp harnesses are serviceable. If the reading falls below the limits, check the slide lamp harness for broken or burned out lamps. (8). If this is a Post-pack test, verify that the reading is within 0.030 amperes of the Pre-pack reading.

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25-60-56

D

F

E

ARM

ACTIVATE

OFF

MODEL TU-12 TEST UNIT

MODEL TU-12 TEST UNIT

A LOAD SELECTOR

B

C

AMMETER

LAMP

GAGE

GAGE

GREEN LIGHT INDICATES “GO” GAGE STATUS

LAMP

GREEN LIGHT NDICATES “GO” AGE STATUS

SLIDE CABLE ASSEMBLY

COMPONENT MAINTENANCE MANUAL D31516 D31517

ADAPTER CABLE ASSEMBLY (60159-101 OR 65037-1) ADAPTER CABLE ASSEMBLY (69525-1)

TU-12 TEST UNIT FIGURE 1006

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G. Light System Test (TU-14 Test Set) (Table 1002, Figures 1007 and 1008) NOTE: Typically two tests are conducted. Pre S.B. A320 004-25-64, and Pre Amendment #4, slide systems are equipped with incandescent lights. While the unit is inflated an amperage reading will be taken and recorded. A visual check will be performed to verify that each lamp is lit. The first amperage reading is compared to a second reading taken when the packing procedure is complete. Post S.B. A320 004-25-64 and Amendment #4, slide systems are equipped with LED light harnesses and a visual check is performed prior to packing to verify each LED is functioning. A post pack amperage reading is also taken and compared to minimum and maximum average amperage requirements. (1). Check the condition of the TU-14 internal rechargeable battery as follows: (a). Press the ON/OFF power switch S1and release when the ON indicator LED illuminates. See the chart below for battery status LED indicator light indications. TU-14 BATTERY STATUS LIGHTS

INDICATION

No battery status, all LEDs are illuminated

OK for test; Battery charge is OK

YELLOW ON (Flashing)

Rechargeable battery pack has reached its near-end-of-useful-charge at 11.2 loaded volts. Use of the TU-14 may continue for a short time.

RED ON

Rechargeable battery pack has reached its end-of useful-charge at 10.0 volts. Use of the TU-14 should be discontinued until the battery pack is recharged. TU-14 readings obtained while this LED is illuminated are unreliable.

GREEN ON

Internal battery charging is in progress.

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NOTE: The TU-14 internal rechargeable battery pack is charged at a 120mA rate when the TU-14 is connected, via the TU-14 115 VAC line cord, to a 115 VAC source. Charging is indicated by the illumination of the CHARGING (green) LED. The TU-14 rechargeable battery pack should return to full charge within approximately sixteen hours of charging. NOTE: To prevent damage to the connectors/cables when connecting and disconnecting the test or extension cables, grasp the connector body instead of pulling on the cable wire. (2). Connect slide cable assembly to adapter cable assembly (Table 1001). Check that all electrical connections are secure. (3). Connect the four-pin test connector from the test adapter cable assembly to the test receptacle J3 on the front panel. (4). Rotate the Load selector switch S6 to load range “B”. Move switch on test adapter cable box to “Lamp” position. (5). Press and hold the Lamp Harness test switch S4. (a). For a pre-pack test, allow three seconds for stabilization and record the TU-14 ammeter reading. Verify that all lamps/LEDs are illuminated. The acceptable amperage ranges are listed below. LIGHT HARNESS ASSEMBLY

AMPERAGE RANGE

Incandescent Light Harness

0.820 to 1.025 amperes

LED Light Harness

0.840 to 0.990 amperes TABLE 1002

(b). For a post-pack reading, verify that the ammeter reading is within ± 0.030 amperes of the pre-pack reading. NOTE: A post-pack reading which falls beyond the above range indicates the possibility of a system short, and/or a broken or defective lamp/LED. NOTE: To replace an individual lamp/LED or an entire lamp/LED harness, refer to the Repair section. (6). Release Lamp Harness test switch S4. Test is complete.

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YELLOW

TU-14 BATTERY NEEDS CHARGE

GREEN CHARGING RED LOW

WARNING-SHOCK HAZARD UNPLUG POWER CORD BEFORE SERVICING INSIDE UNIT

CORPORATION FORT LAUDERDALE J4 FLORIDA J-1

115 VAC

E-1

E-2

J-3

MODEL TU-14 TEST SET

TU-14 BATTERY NEEDS CHARGE

FUSE 1 AMP

CHARGING

C

D

LOW

S-6

B

E A

VOLTMETER VOLTS

F LOAD

S-5

AMMETER AMPS S-2

BAS LOAD

S-4 LAMP HARNESS

BATTERY TEST

ON S-3 TS-10 PROCEDURE

S-1

POWER

TEST

TU-14 TEST SET FIGURE 1007

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B

S-6

A

C

FUSE 1 AMP

LOAD

115 VAC

F

D

UNPLUG POWER CORD BEFORE SERVICING INSIDE UNIT

E

WARNING-SHOCK HAZARD

CORPORATION

VOLTMETER VOLTS

BAS LOAD BATTERY TEST

S-5

FORT LAUDERDALE J4 FLORIDA J-1

25-60-56 LAMP HARNESS

S-4

TEST

AMMETER AMPS

E-2

J-3

S-3

ON S-1 POWER

LOW

CHARGING

NEEDS CHARGE

TU-14 BATTERY

TS-10 PROCEDURE

E-1

MODEL TU-14 TEST SET

S-2

MODEL TU-14 TEST SET

LAMP

GAGE

GAGE

GREEN LIGHT INDICATES “GO” GAGE STATUS

LAMP

GREEN LIGHT NDICATES “GO” AGE STATUS

SLIDE CABLE ASSEMBLY (GAGE/LAMPS)

COMPONENT MAINTENANCE MANUAL D31516 D31517

ADAPTER CABLE ASSEMBLY (60159-101 OR 65037-1) ADAPTER CABLE ASSEMBLY (69525-1)

TU-14 TEST SET FIGURE 1008

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H. Light System Test (TS-420 Test Set) (Table 1003, Figures 1009 and 1010) NOTE: Prior to packing, perform a visual check to verify that each lamp/LED is operating; “pre-pack” amperage (current) readings are compared to readings taken “post-pack” to ensure that all lamps/LEDs are operating. (1). Check the condition of the TS-420 internal rechargeable battery as follows: (a). Place the mode selector switch into the AMMETER position. (b). Push the PRESS TO TEST button. Observe the SELF TEST and LOW BATT indicators for the following indications:

SELF TEST INDICATOR

BATTERY STATUS INDICATOR

INDICATION

GREEN

OFF

OK for test; battery charge is OK.

GREEN

YELLOW

OK for test; battery is getting low. Recharge soon.

RED

YELLOW

Do not use for test; battery is low. Recharge immediately.

RED or OFF

OFF

Do not use for test; unit is inoperative. Return for service.

NOTE: The TS-420 internal rechargeable battery pack is charged at a 200mA nominal rate when the TS-420 is connected, via its accessory 115 VAC source (a 220 VAC wall adapter is also available, see Table 1001). A charging indicator light is not provided. Full charge of a completely depleted battery requires approximately eight hours. The TS-420 test set has overcharge protection and may be left on charge for extended periods; although this is not recommended.

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NOTE: To prevent damage to the connectors/cables when connecting and disconnecting the test or extension cables, grasp the connector body instead of pulling on the cable wire. NOTE: Amperage readings may fluctuate as the lighting circuitry warms up. The initial test set reading as noted below will determine acceptability for service. (2). Connect slide cable assembly to adapter cable assembly (Table 1001). Check that all electrical connections are secure. (3). Connect the four-pin test connector from the test adapter cable assembly to the test receptacle on the front panel. (4). Shift the Mode Selector rocker switch to the AMMETER position for pre-and post-pack testing of the lamp harness amperage. (5). Press the PRESS TO TEST button firmly and release. The set will remain ON for about 20 seconds, allowing ample time to verify that all lamps/LEDs illuminate. (a). After a three second stabilization period, record the ammeter reading. The acceptable amperage ranges are listed below.

LIGHT HARNESS ASSEMBLY

AMPERAGE RANGE

Incandescent Light Harness

820 to 1025 milliamperes

LED Light Harness

840 to 990 milliamperes TABLE 1003

(6). Verify that the post pack ammeter reading is within ± 30 milliamperes of the pre-pack reading. (7). Test is complete NOTE: A post-pack reading which falls beyond the above range indicates the possibility of a system short, and/or a broken or defective lamp/LED. NOTE: To replace an individual lamp/LED or an entire lamp/LED harness, refer to the Repair section.

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CONNECTOR BLOCK (VIEW A-A, SEE FIGURE 1010) A

A

LCD METER AC CHARGER RECEPTACLE SELF TEST

(5VDC POWER SUPPLY)

LOW BATT (INTERNAL BATTERY)

BASEWEST

SELF TEST INDICATOR (GREEN/RED LIGHT)

BATTERY STATUS INDICATOR (YELLOW LIGHT)

TS-420 TEST SET Escape Slide Lighting Systems Digital Voltmeter/Ammeter with 5VDC Power Supply

MODE SELECTOR SWITCH (VOLTMETER/ AMMETER)

LOAD SELECTOR SWITCH

VOLTMETER C D B A NO LOAD

AMMETER

PRESS TO TEST

E F

LOAD SELECTOR

PRESS TO TEST BUTTON

TS-420 TEST SET FIGURE 1009

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VIEW A-A : CONNECTOR BLOCK

AMMETER (+)

SYSTEM TEST

(-)

VOLTMETER (+)

(-)

FOUR-CONTACT RECEPTACLE

TS-420 TEST SET FIGURE 1010

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4. Additional Testing for Extended Maintenance of Aged Evacuation Systems A. Perform Inflatable Integrity Overpressure Test at 4.6 psig (3.2 N/cm2). WARNING: USE EYE, FACE, AND EAR PROTECTION WHEN PERFORMING THIS TEST TO PROTECT PERSONNEL FROM POSSIBLE INJURY. WARNING:PLACE OVERPRESSURE FIXTURE (TABLE 1001; FIGURE 1002) OVER AND IN FRONT OF ASPIRATOR TO PROTECT PERSONNEL FROM POSSIBLE INJURY. WARNING: PLACE PROTECTIVE BLANKET (TABLE 1001) OVER MIDDLE OF LEFT AND RIGHT SIDES OF TOP TUBE TO PROTECT PERSONNEL FROM POSSIBLE INJURY. WARNING: CHECK INFLATABLE PRESSURE TO ASSURE THAT THE MAXIMUM SPECIFIED VALUE IS NOT EXCEEDED. NOTE: Perform the Inflatable Integrity Overpressure test with this higher test pressure at the interval recommended in the Introduction section. (1). Follow standard Overpressure Test procedure as outlined in Paragraph 3.C. Increase test pressure to 4.6 psig (3.2 N/cm2), and allow slide to stand undisturbed for 5 minutes. (2). Check slide for structure degradation, lifts, seam separation, or material fatigue. None is permitted. There shall be no evidence of construction or material failure. All seams and accessories shall remain intact and show no evidence of separation. (3). Deflate slide assembly or decrease pressure to approximately 2.5 psig (1.7 N/cm2) to begin preparation for Seam and Patch Check per Paragraph 4.B. Remove protective blanket, and overpressure fixture. B. Seam and Patch Check NOTE: Perform this inspection check after the Inflatable Integrity Overpressure Test at the intervals recommended in the Introduction section. CAUTION: SEAMS AND PATCHES THAT USE CEMENT FOR BONDING PURPOSES REQUIRE METICULOUS VISUAL INSPECTION, WITH EXTENSIVE CHECKS OF BOND LINE STRENGTH IN MULTIPLE AREAS.

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NOTE: Seams in the airholding structure are constructed using either cement or a thermobonding process of assembly. Cemented seams can be identified by their overlapping fabric panel design. These seams typically have evidence of cement along the seam edge, and they are typically covered with reflective coating compound. The overlapping seam is expected to be fully bonded along its edges. See Figure 1011 for seam design. NOTE: Thermobonded seams can be identified by a layer of fabric tape over the seam. Some thermobonded seams are coated with reflective coating compound. Due to the assembly process, a narrow, unbonded area may exist along the edges of the thermobonded seam. This is acceptable as long as it does not exceed Check limits. Seam design is shown in Figure 1011. CEMENT

FABRIC PANEL

FABRIC PANEL

CROSS SECTION OF A CEMENTED SEAM

WELD AREA

OUTSIDE TAPE

FABRIC PANEL

FABRIC PANEL

CROSS SECTION OF A THERMOBONDED SEAM

SEAM DESIGN FIGURE 1011

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NOTE: Attachment patches that are bonded to the slide assembly using cement typically have evidence of cement along the edges of the attachment patch, and the patches are fully bonded to the slide assembly. Reflective coating compound is also typically applied to the cement margins. NOTE: Attachment patches that are bonded to the slide assembly using welding assembly processes do not need reflective coating compound, although it may be applied in some cases. These assembly processes typically leave an unbonded margin of 0.10 In. (2.5 mm) or less along the edge of the attachment patch. This is normal and does not indicate an incomplete bond. (1). Inflate the unit or adjust pressure to 2.5 psig (1.7 N/cm2). Visually inspect all seams and attachment patches for lifted areas and signs of deterioration. (2). Test various sections of the airholding structural seams on the slide assembly, the girt attachment to the slide assembly, the attachment patches, and all visible repair patches for bond strength by attempting to lightly insert a spatula (Table 1001) or dull bladed tool between bonded fabric layers.Carefully pull outward or upward while moving the blade along the edges of the bonded area. (3). Bond areas that separate, lift away, or allow insertion of a spatula or dull bladed tool are considered degraded. Using the spatula or dull bladed tool, establish the full extent of all weakened areas. Identify and mark those areas for reference when determining slide condition and suitability for continued use. The age, repair history, and overall condition of the slide assembly should be considered in all decisions regarding repair and continuation of use in service. See Check section for disposition and repair limits. C. Previous Repairs Check (1). Visually check all obvious repair patches for lifted areas and signs of deterioration. Check bonded areas for strength, using the methods and criteria outlined in Paragraphs 4.B.(2) and (3).

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D. Sliding Floor Check (1). Visually check sliding surface for areas of wear, coating delamination, or other damage. (2). Test various sections of the bonded area between the sliding floor and the inflatable structure for bond strength using the methods and criteria outlined in Paragraphs 4.B.(2) and (3). E. Check of Aspirator Mounting Flange NOTE: The following check of the aspirator mounting flange may be performed at any point during maintenance on a particular unit. See the Check section for disposition and repair limits. (1). Deflate unit. (2). Remove aspirator from its mounting flange on the slide assembly. (3). Manually squeeze flange inward approximately 2 In. (50.8 mm). (a). Inspect for gaps occurring between the flange and the slide fabric. (b). Listen for a cracking noise, which indicates dried out or debonded areas within the interior bond between flange and fabric. (4). Gently check along the outside boned edge, probing for weak areas, by attempting to lightly inserting a spatula (Table 1001) or dull bladed tool between the bonded fabric and the mounting flange. Carefully pull outward or upward while moving the blade along the edge of the bonded area. (5). Consult Check section tables for disposition. (6). Reinstall aspirator into flange per the Assembly section and continue with maintenance.

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5. Fault Isolation A. Refer to Table 1004 for the fault, most probable cause, and remedy. The faulty component is determined by isolating the fault to a particular assembly, and then to the defective part.

FAULT Slide Assembly will not maintain pressure.

Slide inflates too slowly.

PROBABLE CAUSE

REMEDY

Aspirator flapper valve not closing properly.

Replace aspirator. See Assembly section.

Leaking at aspirator mounting flange.

Tighten worm drive clamp screw, replace if stripped. See Assembly section.

Leaking pressure test valve on aspirator.

Tighten pressure test valve core. See Assembly section.

Hole in fabric.

Repair hole. See Repair section.

Tear in fabric.

Repair tear. See Repair section.

Open seam.

Repair seam. See Repair section.

Frangible links not properly installed/located.

For installation, follow Folding Procedure (Appendix 1).

Improper gas flow to slide.

Check for proper rigging. See Folding Procedure (Appendix-1). Check for proper valve regulator setting (see CMM 25-65-17).

Loose hose connections.

Check O-ring condition and hose connection torque. See Assembly section.

FAULT ISOLATION TABLE 1004 (SHEET 1 OF 2)

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FAULT

PROBABLE CAUSE

REMEDY

Slide inflates too slowly. (Cont’d)

Fabric/foreign object ingestion, improper folding.

See Folding Procedure (Appendix 1).

Slide will not inflate.

Inflation cable not properly routed or connected.

Route cable then connect cable to cable disconnect. See Folding Procedure (Appendix 1).

Inflation assembly not armed.

Arm inflation assembly. See Assembly section in CMM 25-65-17.

Inflation assembly not charged.

Determine reason. See Check and Testing sections. Charge inflation assembly per CMM 25-65-17.

Hose assembly not connected to aspirator or inflation valve assembly.

Install hose. See Assembly section.

Excessive force required to pull valve actuating cable.

Valve actuating cable restricted (improper rigging). Damaged or incorrectly assembled inflation valve assembly.

See Assembly section in CMM 25-65-17.

Inoperative lighting system.

Defective harness assembly or connections (all lamps/LEDs out).

Replace applicable harness per Repair section. Retest per Testing section.

Poor harness wire connections.

Replace applicable harness per Repair section. Retest per Testing section.

Broken or defective lamp/LED.

Repair individual lamp/LED per Repair section.

FAULT ISOLATION TABLE 1004 (SHEET 2 OF 2)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

TABLE OF CONTENTS DISASSEMBLY Page 1. Disassembly Materials/Tools

3002

2. General Information

3003

3. Remove Slide Assembly from Packboard

3004

4. Remove Reservoir and Valve Assembly

3015

5. Unfold Slide

3018

6. Lamp/LED Harness Disassembly

3024

7. Girt Bar Removal

3026

8. Hose from Aspirator

3027

9. Aspirator Disassembly

3028

10. Aspirator Pressure Test Valve Disassembly

3029

11. Lacing Cover Disassembly

3030

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1. Disassembly Materials/Tools (Table 3001) NOTE: Equivalent substitutes may be used.  ITEM/DESCRIPTION

QUANTITY

Tool - Valve Core 6914V-SD (or equivalent Schraderstyle valve core extractor tool)

1

Safety Plug (Valve Outlet Port) AN814-10 or AS5169-10

1

SOURCE

USE

Rus Industries Inc. Installs/removes valve V8S111 core from pressure or Commercially test valve assemblies. Available Commercially Available

Seals valve outlet port to prohibit damage and contamination.

DISASSEMBLY TOOLS/MATERIALS TABLE 3001

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COMPONENT MAINTENANCE MANUAL D31516 D31517

2. General Information A. Decision to disassemble generally should be based on presence of leaks, visible damage, or functional discrepancies discovered in performance of procedures outlined in Check or Testing and Fault Isolation sections. Disassemble only to the extent necessary to complete local repair or replacement. Complete disassembly of all components covered in this section is neither necessary nor recommended. CAUTION: USE ONLY BRASS OR PLASTIC TOOLS TO REMOVE THE O-RINGS, TOOLS NOT MADE OF BRASS OR PLASTIC CAN SCRATCH THE O-RING GROOVES, CAUSING LEAKAGE AND POSSIBLE CORROSION. NOTE: A small bead of green or white torque marker may have been applied to the connected joint between specific components. This torque marker is used in some cases to identify joints that have been torqued per specific requirements. The marker subsequently provides an indication that the joint has not loosened or been adjusted after inspection during the manufacturing/ assembly process. This marker is not required during field maintenance (unless otherwise instructed per documented Testing or Assembly criteria). B. When disassembly is necessary, replace all O-rings and gaskets. Replacement of other items should be guided by sound inspection criteria; see Check section. C. The working area should be covered with clean carpeting or other suitable material and be free of hardware, tools, and sharp projections. Do not stand or walk on the inflatable.

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3. Remove Slide Assembly from Packboard (Figures 3001 through 3008) (IPL Figure 1) WARNING: TO PREVENT ACCIDENTAL INFLATION, EXERCISE EXTREME CARE WHEN DISCONNECTING INFLATION CABLE FROM PACKED SYSTEMS SINCE THE VALVE INFLATION ASSEMBLY IS ARMED AND THE RESERVOIR IS CHARGED. DO NOT KNEEL ON THE GIRT BEFORE THE CABLE IS DISCONNECTED. WARNING: TO PREVENT ACCIDENTAL INFLATION, ENSURE THAT THE VALVE LOCK PIN IS FULLY INSERTED INTO THE VALVE INFLATION ASSEMBLY HOUSING OF THE RESERVOIR AND VALVE INFLATION ASSEMBLY. A. Install the lock pin into the valve pulley housing. B. Unfasten Velcro fasteners on the upper and lower lacing covers. C. Disconnect the electrical harness assembly at female fitting. VELCRO FASTENER MALE FITTING FEMALE FITTING

ELECTRICAL CABLE ASSEMBLY (GAGE AND LIGHTS)

VELCRO FASTENER ELECTRICAL HARNESS ASSEMBLY (DOOR CONNECTIONS)

REMOVE SLIDE ASSEMBLY FROM PACKBOARD FIGURE 3001

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D. Remove the electrical harness assembly from the Velcro fasteners on upper and lower lacing covers. Coil the electrical harness assembly as shown in Figure 3002 and 3002A. NOTE: It is important that the quick disconnect fitting remains with the pull handle assembly so that tension on the valve release cable will not occur. E. Disconnect the pull handle assembly from the inflation cable. (1). For pull handle assembly 24C17380-105 (130B) disengage quick disconnect (140A) or disconnect body assembly (170A) as shown in figure 3002. CAUTION: DO NOT USE PLIERS FOR LOOSENING NUT ON CHAIN CONNECTOR. (2). For pull handle assembly 24C29245-103 (130C) open the chain connector (170B) using a 7mm wrench and remove the chain connector from the inflation cable loop as shown in Figure 3002A. F.

Remove the inflation cable from bottom half of the girt. Coil the inflation cable.

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ELECTRICAL HARNESS ASSEMBLY

SEE DETAIL “A” INFLATION CABLE

INFLATION CABLE PULL HANDLE CABLE

PULL HANDLE CABLE

SLEEVE LOCK NUT

BODY

SLEEVE

CABLE DISCONNECT (P/N 26C15091-1)

BODY DISCONNECT BODY ASSEMBLY (P/N 68660-101)

VELCRO FASTENER

GIRT

PULL HANDLE VELCRO FASTENER DETAIL “A”

DISCONNECT VALVE RELEASE CABLE FIGURE 3002

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ELECTRICAL HARNESS ASSEMBLY

SEE DETAIL “A”

INFLATION CABLE

CONNECTOR

VELCRO FASTENER

GIRT

PULL HANDLE VELCRO FASTENER DETAIL “A”

DISCONNECT VALVE RELEASE CABLE FIGURE 3002A

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G. Cut and remove safety wire from around disc and notch in pawl. Remove disc. H. Remove lower lacing cover (30B) from retaining pins and girt assembly.

COVER RELEASE CABLE

DISC

WIRE LOWER LACING COVER

CABLE

BALL GIRT

GROMMET

RETAINING PINS

REMOVE DISC FIGURE 3003

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I.

Cut and remove lacing cord between upper and lower lacing covers. Remove lower lacing cover.

LACING CORD UPPER LACING COVER

LOWER LACING COVER

REMOVE LOWER LACING COVER FIGURE 3004

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J.

Post S.B. A320 004-25-97, D31516-719 through -725, and D31517719 through -725 only, cut and remove lacing cord between wrapper (290, IPL Figure 3) and side wrappers (290). Remove side wrappers by disengaging Velcro fasteners.

SIDE WRAPPER (TYP. BOTH SIDES)

WRAPPER

CUT AND DISCARD ALL LACING CORDS BETWEEN GROMMETS

DISENGAGE VELCRO FASTENERS (TYP. BOTH SIDES)

D31516 (FWD) SHOWN; D31517 (AFT) SIMILAR

REMOVE SIDE WRAPPERS (POST S.B. A320 004-25-97 ONLY) FIGURE 3004A

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K. Remove the inflation cable from the cable guide and from between girt halves. L. Coil inflation cable as shown in Figure 3005.

TOP HALF OF GIRT GROMMET

GROMMET

CABLE GUIDE

BOTTOM HALF OF GIRT INFLATION CABLE

REMOVE RELEASE CABLE ASSEMBLY FROM GIRT ASSEMBLY FIGURE 3005

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M. Cut and remove all breakaway thread (two places) on remote gage assembly and electrical cable assembly. Disconnect male fitting from female fitting as shown. REMOTE GAGE ASSEMBLY MALE FITTING ELECTRICAL CABLE ASSEMBLY (LIGHTS AND GAGE) FEMALE FITTING

GAGE

BREAKAWAY THREAD (CUT AND REMOVE)

BREAKAWAY THREAD (CUT AND REMOVE)

WRAPPER (POST S.B. A320 004-25-97, D31516-719 THROUGH -725, AND D31517-719 THROUGH -725 ONLY)

DISCONNECT ELECTRICAL ASSEMBLY FIGURE 3006

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N. Remove lock pin assembly from valve regulator. O. Lift reservoir and valve assembly (40A, IPL Figure 1) from inside packboard and reinstall lock pin in valve regulator (without going through upper lacing cover) as shown in Figure 3007.

HOLE UPPER LACING COVER

UPPER LACING COVER

LOCK PIN ASSEMBLY

LOCK PIN ASSEMBLY WRAPPER (POST S.B. A320 004-25-97, D31516-719 THROUGH -725, AND D31517-719 THROUGH -725 ONLY)

REMOVE/REINSTALL LOCK PIN FIGURE 3007

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P.

Lift folded slide assembly from packboard. WARNING: TO PREVENT DAMAGE TO EQUIPMENT AND INJURY TO PERSONNEL, EXERCISE EXTREME CARE WHEN HANDLING THE RESERVOIR AND VALVE INFLATION ASSEMBLY. ENSURE THAT THE VALVE LOCK PIN IS FULLY INSERTED INTO THE VALVE INFLATION ASSEMBLY HOUSING. WRAPPER (POST S.B. A320 004-25-97, D31516-719 THROUGH -725, AND D31517-719 THROUGH -725 ONLY)

SLIDE ASSEMBLY

PACKBOARD ASSEMBLY

REMOVE SLIDE FROM PACKBOARD FIGURE 3008

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4. Remove Reservoir and Valve Assembly (Figures 3009 through 3011) (IPL Figure 1) WARNING: THE RESERVOIR AND VALVE INFLATION ASSEMBLY CONTAINS COMPRESSED GAS; DO NOT APPLY FORCE TO THE VALVE RELEASE CABLE OR ACCIDENTAL INFLATION MAY OCCUR. A. Remove gage protector (80A).

GAGE PROTECTOR

GAGE

VALVE ASSEMBLY

REMOVE GAGE PROTECTOR FIGURE 3009

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B. Remove tape (two places) from hose nut and from cable guide nut. WARNING: TO PREVENT POSSIBLE INJURY, INSTALL SAFETY PLUG IN VALVE OUTLET PORT SINCE RESERVOIR AND VALVE ASSEMBLY MAY BE CHARGED AND ARMED. C. Disconnect hose assembly (50, 50A, 50B, 50C IPL Figure 1) from threaded port on valve assembly. Install safety plug (Table 3001) in the valve outlet port, hand tight. D. Remove O-ring from hose fitting and discard. E. Install dust cap on hose fitting.

LOCK PIN ASSEMBLY

SAFETY PLUG TAPE OUTLET PORT

DUST CAP HOSE ASSEMBLY

HOSE NUT

DISCONNECT HOSE ASSEMBLY FIGURE 3010

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F.

Disengage snap fasteners and webbing strap from the neck of the reservoir.

G. Remove the reservoir and valve assembly (40A) from reservoir sling.

RESERVOIR SLING

SNAP FASTENER RESERVOIR AND VALVE ASSEMBLY

STRAP

SNAP FASTENER

REMOVAL OF RESERVOIR AND VALVE ASSEMBLY FIGURE 3011

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5. Unfold Slide (Figures 3012 through 3016) (IPL Figure 1) A. Unroll slide and unfold sides. B. Remove hose assembly from hose retainer.

UNROLL SLIDE

HOSE RETAINER (S/N A1400 AND SUBS)

UNFOLD SLIDE

UNFOLD SLIDE FIGURE 3012

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C. Unfasten positioners on sides of the body tubes (center of slide) as shown in Detail “A”. D. Fold sides outboard.

SLIDE ASSEMBLY

SEE DETAIL “A”

GIRT FEMALE POSITIONER

MALE POSITIONER

DETAIL “A”

UNFOLD SLIDE FIGURE 3013

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E. Disengage the three frangible links (260A, 260B, IPL Figure 1) at the girt end.

SLIDE ASSEMBLY

GIRT FRANGIBLE LINK

UNFOLD SLIDE FIGURE 3014

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F.

Unfold slide assembly from the girt end to the runway end to expose the tracking restraints.

G. Disengage tracking restraint frangible links (260) and unfold remainder of slide to runway end.

SLIDE ASSEMBLY TRACKING RESTRAINT

TRACKING RESTRAINT

UNFOLD SLIDE FIGURE 3015

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H. Fold girt over the slide to gain access to rail positioners on the sill support log. I.

Disengage rail positioners (see Detail “A”), and fold support logs outboard. NOTE: Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B), frangible link (260C) is attached to tracking restraint (180, IPL Figure 3) and color code tracking restraint (170, IPL Figure 3) in lieu of rail positioners. See Detail “B”.

SLIDE ASSEMBLY

GIRT

SEE DETAIL “A” SILL SUPPORT LOG TRACKING RESTRAINT FRANGIBLE LINK

FEMALE RAIL POSITIONER MALE RAIL POSITIONER

DETAIL “A”

COLOR CODE TRACKING RESTRAINT DETAIL “B”

DISENGAGE RAIL POSITIONERS FIGURE 3016

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6. Lamp/LED Harness Disassembly (Figure 3017) A. Untie (do not cut) the tie-off cord holding the electrical harness assembly (110, 110A, 120, IPL Figure 1) to the cord loop. B. Disconnect lamp/LED harness (50A, 50B, 50C, IPL Figure 3) female connectors from male connectors on the electrical harness assembly (door connections). C. Pull lamp/LED harness connectors back through the wire guide located between top and bottom layers of the girt.

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WIRE GUIDE

GIRT HALVES ELECTRICAL HARNESS CONNECTORS ELECTRICAL HARNESS CONNECTORS

WIRE GUIDE LAMP/LED HARNESS CONNECTORS

LOOP

TIE-OFF CORD

LAMP/LED HARNESS CONNECTORS

LAMP/LED HARNESS DISASSEMBLY FIGURE 3017

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7. Girt Bar Removal (Figure 3018) (IPL Figure 1) A. Open girt flap and disengage hook and pile fasteners. B. Cut breakaway tie on parachute pin of girt release cable (70). Remove parachute pin from loop. C. Disengage interlocking loops. Pull loops through grommets to release girt bar. D. Unfasten Velcro fasteners securing mooring line (180). Remove mooring line loop from end of girt bar.

VELCRO FASTENER

PARACHUTE PIN BREAKAWAY TIE

MOORING LINE

CORD LOOP

GIRT BAR

GIRT FLAP MOORING LINE LOOP

GIRT BAR

CORD LOOP

GIRT BAR REMOVAL FIGURE 3018

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8. Hose from Aspirator (Figure 3019) (IPL Figure 1) A. Remove tape from inlet fitting and hose nut on aspirator (225). B. Disconnect hose assembly (50, 50A, 50B, 50C) from the aspirator. C. Install suitable cap plugs on both ends of the hose assembly.

ASPIRATOR

INLET FITTING HOSE ASSEMBLY

TAPE

HOSE FROM ASPIRATOR FIGURE 3019

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9. Aspirator Disassembly (Figure 3020) (IPL Figure 1) WARNING: DEFLATE SLIDE PRIOR TO REMOVAL OF ASPIRATOR TO PREVENT INJURY TO PERSONNEL. A. Remove all tape from worm drive clamp (240). B. Unscrew worm drive clamp screw and remove from aspirator mounting flange. C. Carefully remove aspirator (225) from the aspirator mounting flange.

TAPE

WORM DRIVE CLAMP

MOUNTING FLANGE

ASPIRATOR

MOUNTING BLISTER

ASPIRATOR REMOVAL FIGURE 3020

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10. Aspirator Pressure Test Valve Disassembly (Figure 3021) (IPL Figure 1) A. Remove tube (238) and cap (233) from pressure test valve stem. B. Insert tool (Table 3001) into pressure test valve stem. Twist tool counter-clockwise to remove pressure test valve core (235).

PRESSURE TEST VALVE CORE

VALVE CORE TOOL

ASPIRATOR

INLET FITTING

PRESSURE TEST VALVE PRESSURE TEST VALVE CORE

TUBE CAP

PRESSURE TEST VALVE DISASSEMBLY FIGURE 3021

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11. Lacing Cover Disassembly (Figures 3022 through 3024) (IPL Figure 1) NOTE: Lacing cover assembly (P/N D31882-105) (Post S.B. 004-2547) allows the removal of the tie bar assembly for replacement as well as replacing individual release cables. Pre S.B. 004-2547 the lacing cover assembly (P/N D31882-101) does not allow this option. A. Unfasten Velcro fasteners securing the tie bar assembly inside the sleeve of the lacing cover (30B). B. Remove the tie bar assembly (31) from the sleeve of lacing cover (30B).

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VELCRO FASTENERS

LACING COVER

TIE BAR ASSEMBLY

SLEEVE

LACING COVER DISASSEMBLY FIGURE 3022

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CAUTION: WHEN REMOVING ROLL PIN BE CAREFUL NOT TO DEFORM TUBE. C. Using a punch pin and a hammer remove roll pins (32), two places, from each end of the tube. D. Slide spacer (33) out of tube. E. Remove release cables (34), six places, from tube (35) by pushing the larger ball shank end of cable through the larger hole in tube.

ROLL PIN (2 PLACES)

HOLE AT TUBE END TIE BAR ASSEMBLY

TIE BAR DISASSEMBLY FIGURE 3023

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TUBE SMALLER BALL SHANK END

SPACER LARGER BALL SHANK END

RELEASE CABLE (6 PLACES)

LARGER HOLE

TUBE

TIE BAR DISASSEMBLY FIGURE 3024

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TABLE OF CONTENTS CLEANING Page 1. Cleaning Materials

4002

2. General Information

4003

3. Slide Assembly

4004

4. Aspirator Assembly

4004

5. Hose Assembly

4005

6. Packboard, Lacing Cover, and Girt Assemblies

4005

7. Decorative Cover

4005

8. Pull Handle Assembly

4006

9. Worm Drive Clamp, Quick Disconnect, Disconnect Body Assembly, and Girt Release Cables

4006

10. Lamp/LED Harness Assembly

4006

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1. Cleaning Materials (Table 4001) NOTE: Equivalent substitutes may be used.  ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Fabric Cleaning Solution Moderate Duty: Clear Ivory Hand Washing Dish Liquid Detergent

As Required

Commercially Moderate cleaning of Available fabric surfaces.

Fabric Cleaning Solution Heavy Duty: 50% Isopropyl Alcohol ((CH3)2CHOH) and 50% Toluene (C6H5CH3) by Volume

As Required

Commercially Heavy duty cleaning Available of fabric surfaces.

Cleaning Solvent for Metal Parts: MIL-PRF-680 or Clear Mineral Spirits

As Required

Clean Soft Cloth

As Required

Commercially Application of soluAvailable tions/solvent; drying.

Stiff Bristle Brush

As Required

Commercially Application of soluAvailable tions/solvents.

Soft Bristle Brush

As Required

Commercially Application of soluAvailable tions/solvents.

Commercial Cleaning of metal Standard surfaces.

CLEANING MATERIALS TABLE 4001

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2. General Information WARNING: WHEN USING SOLVENTS, CEMENTS, OR OTHER CHEMICAL BASED PRODUCTS, REFER TO THE APPLICABLE MATERIAL SAFETY DATA SHEET (MSDS) FOR SPECIFIC GUIDELINES ON PROPER PERSONAL PROTECTIVE EQUIPMENT, STORAGE, HANDLING, AND VENTILATION REQUIREMENTS TO PREVENT SICKNESS OR INJURY TO PERSONNEL. WARNING: USE EYE, FACE, AND EAR PROTECTION WHEN USING HIGH PRESSURE AIR TO PROTECT PERSONNEL FROM POSSIBLE INJURY. WARNING: TO PREVENT POSSIBLE INJURY, ENSURE AIR NOZZLE IS POSITIONED AWAY FROM BODY OR OTHER PERSONNEL AND ENSURE A 30 PSIG (20.7 N/cm2), OR LESS, AIR NOZZLE IS ATTACHED TO AIR HOSE. CAUTION: WHEN WASHING THE SLIDE FABRIC, DO NOT ALLOW EXCESS SOLVENT TO COLLECT AT EDGES OF SEAMS. AVOID WASHING OVER DECALS OR STENCIL MARKINGS (WHEN POSSIBLE) AS THEY WILL BE REMOVED BY THE SOLVENT. SOLVENTS WILL DEGRADE THERMOBONDED SEAMS AND PATCHES THAT WERE ATTACHED USING WELDING ASSEMBLY PROCESSES. DO NOT APPLY EXCESSIVE FORCE OR PRESSURE TO THESE AREAS WHEN SOLVENTS ARE UTILIZED. A. Observe all shop safety precautions and practices. As applicable, parts should be dried using a compressed air source free of oil and moisture which is filtered through a 20-micron filter.

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3. Slide Assembly A. For removal of light to moderate concentrations of dust and dirt on slide tube chambers and anti-skid compound areas, use a solution of detergent (Table 4001) and water. (1). Apply solution with a soft bristle brush (Table 4001) or a clean cloth (Table 4001). (2). Thoroughly rinse with clean water and blow dry with compressed air. B. For removal of heavy concentrations of dirt and grease on the slide tube chambers and anti-skid compound areas, use the cleaning solution (Table 4001). CAUTION: DO NOT USE THE CLEANING SOLUTIONS MEK OR ETHYL ACETATE ON ANTI-SKID COMPOUND AREAS, OR COATING MAY BE REMOVED. CAUTION: DO NOT ALLOW PUDDLING OR DRIPPING OF SOLUTION, AS LIFTING OF CEMENTED AREAS MAY RESULT. (1). Apply solution with a clean, soft cloth (Table 4001) or a soft bristle brush (Table 4001) for local areas of oil, dust, or dirt. (2). Immediately remove excess solution with a clean cloth (Table 4001) and dry using compressed air.

4. Aspirator Assembly CAUTION: FLAPPER VALVES MUST BE OPENED AND CLOSED SIMULTANEOUSLY TO PREVENT DAMAGE TO THE CLOSING MECHANISM COMPONENTS. A. Under normal conditions, internal and external surfaces may be cleaned using compressed air; ensure that air directed through the inlet fitting flows freely from all orifices in the nozzle assembly. CAUTION: MINIMIZE ASPIRATOR CONTACT TIME WITH ALL CLEANING AGENTS. B. Under extreme conditions, clean external surfaces with cleaning solvent (Table 4001) and a soft bristle brush (Table 4001); clean internal surfaces with a solution of detergent (Table 4001) and water. Rinse with clean water. Thoroughly blow dry with compressed air.

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5. Hose Assembly CAUTION: INSTALL PROTECTIVE PLASTIC CAP PLUG ON HOSE FITTINGS. A. Clean hose external surfaces using a clean cloth (Table 4001) dampened in detergent (Table 4001) and water solution. Rinse with clean water. B. Blow dry using compressed air. Ensure that all moisture is removed from inside of hose.

6. Packboard, Lacing Cover, and Girt Assemblies A. For removal of light to moderate concentrations of dust and dirt, use a solution of detergent (Table 4001) and water. (1). Apply solution with a soft bristle brush (Table 4001) or a clean cloth (Table 4001). (2). Thoroughly rinse with clean water and blow dry with compressed air. B. For removal of heavy concentrations of dirt and grease, use the heavy duty cleaning solution (Table 4001). CAUTION: DO NOT ALLOW PUDDLING OR DRIPPING OF SOLUTION, AS LIFTING OF CEMENTED AREAS MAY RESULT. (1). Apply solution with a clean, soft cloth (Table 4001) or a soft bristle brush (Table 4001) for local areas of oil, dust, or dirt. (2). Immediately remove excess solution with a clean cloth (Table 4001) and dry using compressed air.

7. Decorative Cover CAUTION: THE ONLY ACCEPTABLE CLEANING SOLVENT FOR HEAVY CONCENTRATION OF DIRT AND/OR GREASE ON THE DECORATIVE COVER IS ISOPROPYL ALCOHOL. A. Use a solution of detergent (Table 4001) and water for removal of light to moderate concentrations of dust and dirt.

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(1). Apply solution with a clean, soft cloth (Table 4001) or soft bristle brush (Table 4001) to local areas of oil, or dirt. (2). Immediately remove excess solution with clean cloth (Table 4001) and dry using compressed air.

8. Pull Handle Assembly A. Use a solution of detergent (Table 4001) and water for removal of light to moderate concentrations of dust and dirt. (1). Apply solution with a soft bristle brush (Table 4001) or a clean cloth (Table 4001). (2). Thoroughly rinse with clean water and blow dry with compressed air. B. For removal of heavy concentrations of dirt and grease, use the heavy duty cleaning solution (Table 4001). (1). Apply solution with a clean, soft cloth (Table 4001) or a soft bristle brush (Table 4001) for local areas of oil, dust, or dirt. (2). Immediately remove excess solution with a clean cloth (Table 4001) and dry using compressed air.

9. Worm Drive Clamp, Quick Disconnect, Disconnect Body Assembly, and Girt Release Cables A. For removal of concentrations of dirt and grease, use the cleaning solvent (Table 4001). (1). Apply solvent with clean soft cloth (Table 4001) or soft bristle brush (Table 4001) for local areas of oil, dust, or dirt. (2). Immediately remove excess solvent with a clean cloth (Table 4001) and dry using compressed air.

10. Lamp/LED Harness Assembly A. Each lamp/LED on the harness may be cleaned with a water (only) dampened cloth (Table 4001). B. Wipe lamps/LEDs thoroughly with a clean dry cloth (Table 4001).

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TABLE OF CONTENTS CHECK Page 1. System Check

5002

2. Inflation Assembly Check

5002

3. Visual Check: Slide Assembly

5003

4. Visual Check: Slide Components

5005

5. Visual Check: Girt Assembly and Release Assemblies

5007

6. Visual Check: Aspirator and Worm Drive Clamp

5009

7. Visual Check: Hose Assembly

5010

8. Visual Check: Decorative Cover and Packboard Assembly

5011

9. Visual Check: Extended Maintenance

5014

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1. System Check WARNING: USE EYE, FACE, AND EAR PROTECTION WHEN USING HIGH PRESSURE AIR TO PROTECT PERSONNEL FROM POSSIBLE INJURY. NOTE: Refer to Tables 5001 through 5006 for visual checking of the slide assembly and related components. NOTE: When the disposition is replace refer to the Disassembly section for the disassembly of the component and to the Assembly section for the assembly of the component. NOTE: Refer to Table 5007 for visual checking of the slide assembly and related components during Extended Maintenance for Aged Evacuation Systems, in addition to referencing Tables 5001 through 5006. A. The work area must be covered with a clean tarpaulin, carpeting, or other protective material and must be clean and well lighted. B. The check can be made without the aid of special optical devices, unless otherwise indicated herein. C. The age of the slide assembly, its current condition, and its repair history should be considered in all decisions regarding continuation of use in service.

2. Inflation Assembly Check A. Refer to the Reservoir and Valve Inflation Assembly Component Maintenance Manual 25-65-17 Assembly and Check sections for check and verification of proper gas charge.

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3. Visual Check: Slide Assembly (Table 5001) COMPONENT

Tubes and floor fabric/ seams

CONDITION

DISPOSITION

Cuts, tears, punctures, or abrasions; mark with chalk if discrepant.

See Repair section. If beyond limits call or consult your Zodiac Services Representative for repair.

Inspect stencilled markings for legibility and correctness.

Re-stencil.

Lifted, detached, or other signs of deterioration along edges of seams and attachment patches that use cement for bonding purposes on the slide assembly.

See Repair section. When 2 or more lifts or weak bond areas are found, perform Extended Maintenance and consult Table 5007.

Signs of persistent moisture, or evidence of mold or mildew. Areas of exposed cement that are yellow, discolored, or crumbling. Lifted or detached sections along the edges where girt is bonded to the slide assembly.

Perform Extended Maintenance and consult Table 5007.

Areas of delamination of sliding floor fabric. VISUAL CHECK: SLIDE ASSEMBLY TABLE 5001 (SHEET 1 OF 2)

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COMPONENT

CONDITION

DISPOSITION

Lifts along edges of thermobonded seams with a depth of greater than 0.25 In. (6.4 mm). Tubes and floor fabric/ seams (Cont’d)

Lifts along edge of thermobonded or welded seams of attachments on the slide assembly with a depth greater than 0.10 In. (2.5 mm).

See Repair section.

Restraints, mounting patches, handles, Velcro and snap fasteners, attachment patches, reservoir sling, no-fail handles, re-entry strap, etc.

Check general condition, looseness or malfunction as applicable; mark with chalk if discrepant.

Re-cement lifted area. See Repair section. For replacement, call or consult your Zodiac Services Representative.

Attachment Patches

Delamination of fabric coating.

Perform Extended Maintenance and consult Table 5007.

Mounting Flange for Aspirator

Check general condition of bond between slide assembly fabric and mounting flange, where visible. No gaps or lifts permitted. Width of bond must be 0.5 In. (12.7 mm) or greater.

A specialized repair may be possible, depending on age and condition of slide assembly. Contact your Zodiac Services Representative.

Grommets

Grommet attachment (tightness) or sharp projections.

Replace. See Repair section.

VISUAL CHECK: SLIDE ASSEMBLY TABLE 5001 (SHEET 2 OF 2)

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4. Visual Check: Slide Components (Table 5002)

COMPONENT Frangible Links

CONDITION Wires exposed, frayed cord loops, or broken threads.

DISPOSITION Replace frangible link per Folding Procedure (Appendix 1).

Test System for operation. See Testing section. See Testing section.

Lamp/LED Harness Assembly

Lifts or tears of the fabric Re-cement lifted areas. tape. Loose lamp/LED har- Replace tape as necesness. sary. See Repair section. Broken or burned out light. Replace lamp/LED housing. See Repair section. Loose or broken wires or any damage which would impair function.

Replace lamp/LED harness assembly. See Repair section.

Potting migration from slid- Repair lamp/LED haring lane housing. ness. See Repair section. Scratches to black anodize Clean, repair corroded layer, surface corrosion. areas and apply Alodine treatment followed by epoxy primer per Repair Electrical Cable Assembly section. Damage which exceeds above condition. Missing and/or damaged connector pins. Hook Knife

Broken handle or blade.

Replace.

Replace.

VISUAL CHECK: SLIDE COMPONENTS TABLE 5002 (SHEET 1 OF 2)

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COMPONENT

CONDITION

DISPOSITION

Sheath

Loose sheath, rips or tears. Improper closure around knife.

Re-cement lifted or torn areas. See Repair section.

Mooring Line

Frayed cord, cuts, or loose Replace. stitching. VISUAL CHECK: SLIDE COMPONENTS TABLE 5002 (SHEET 2 OF 2)

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5. Visual Check: Girt Assembly and Release Assemblies (Table 5003) COMPONENT

Girt Assembly

CONDITION

DISPOSITION

Minor cuts or tears that do not intersect seams, hinge tapes, or reinforcements.

See Repair section.

Tears that intersect or overlap hinge tapes or reinforcement webbing.

Call or consult your Zodiac Services Representative for repair or girt replacement.

Tears that run parallel to the reinforcement webbing along the girt perimeter.

Call or consult your Zodiac Services Representative for repair or girt replacement.

Worn or broken threads on seams, turn backs, loose Velcro fasteners or webbings.

Machine sew using V-T295 size “F” or A-A-59826 size “F” nylon thread in accordance with Federal Specification 751 Type 301, MIL STD AIR9207 R65EC/R80EC, or Air Cruisers P/N M11944-1.

Grommet attachment (tightness) or sharp projections.

Replace. See Repair section.

Coating abrasion, flaking, or exposure of threads.

Re-coat. See Repair section.

Chafing in the area around girt release cable.

See Repair section. Add chafing. Post S.B. 004-25-52

VISUAL CHECK: GIRT ASSEMBLY AND RELEASE ASSEMBLIES TABLE 5003 (SHEET 1 OF 2)

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COMPONENT Cord Loops for Girt Bar

CONDITION Fraying cord, tears or cuts in the cord loop or the attachment to the girt.

DISPOSITION Call or consult your Zodiac Services Representative for repair or girt replacement.

Hook fastener damaged, cable frayed, or ball end of cable not uniform. Pull Handle Assembly

Unreadable printed material.

Replace.

Fraying, cuts, or tears, of webbing or Velcro. Quick Disconnect, Disconnect Body Assembly

Cross-threading and/or attachment groove deformity.

Replace.

Fraying, cuts, or tears of webbing or Velcro. Girt Release Cable

Loose or damaged nicopress sleeve or parachute pin.

Replace.

VISUAL CHECK: GIRT ASSEMBLY AND RELEASE ASSEMBLIES TABLE 5003 (SHEET 2 OF 2)

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6. Visual Check: Aspirator and Worm Drive Clamp (Table 5004)

COMPONENT

CONDITION

DISPOSITION

Housing is not concentric. Cracks, cross-threading, or Replace aspirator. stripping of threaded fittings. Pressure test valve leaks at Replace valve core. stem. Pressure test valve leaks at Replace pressure test base. valve. Aspirator

Positive closing device malfunction (60461 aspirators only). Excessive compression or damage to the flapper valve sealing surface. Delamination. Loose or damaged antichafe coating around circumference of aspirator outlet.

Replace aspirator.

See Repair section.

Stripped worm drive clamp screw. Worm Drive Clamp

Cracks, concentricity, or sharp edges.

Replace.

VISUAL CHECK: ASPIRATOR AND WORM DRIVE CLAMP TABLE 5004

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COMPONENT MAINTENANCE MANUAL D31516 D31517

7. Visual Check: Hose Assembly (Table 5005)

COMPONENT

Hose Assembly

CONDITION

DISPOSITION

Cracks or damage to hose fittings or threads.

Replace.

Perform a hydrostatic test to 900 psig (620.5 N/cm2). Reference S.I.L. 25-82. See Testing section.

If the hose fails the hydrostatic test, replace.

Hose does not swivel through 360°. Obstructions in I. D. of hose caused by bulging or damage to inner liner. Obstructions in I. D. of hose caused by foreign matter/dirt. Verify clear passage by blowing shop air at 100 psig (69 N/cm2) through hose.

Replace.

Remove obstructions using compressed air. Determine source of foreign matter prior to returning system to service.

VISUAL CHECK: HOSE ASSEMBLY TABLE 5005

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COMPONENT MAINTENANCE MANUAL D31516 D31517

8. Visual Check: Decorative Cover and Packboard Assembly (Table 5006)

COMPONENT

Decorative Cover

Packboard Assembly

CONDITION

DISPOSITION

Cracks or imperfections.

Call or consult your Zodiac Services Representative for repair, or repair per Repair section.

Bonding of hardware and attaching parts for integrity and ease of operation.

Replace.

Improper attachment of gage viewing window or opaque gage window.

Re-attach or replace. See Repair section.

Loose floor seal bond.

Re-cement. See Repair section.

Cloudy pressure gage window.

Replace as necessary. See Repair section.

Cracks, burrs, or sharp projections.

See Repair section.

Cracks, dents, welds, or loose screws on packboard.

Call or consult your Zodiac Services Representative for repair.

Corrosion or cracking of lower mounting brackets.

Replace.

Looseness or insecurity. Malfunction of parts.

Replace fittings as necessary.

VISUAL CHECK: DECORATIVE COVER AND PACKBOARD ASSEMBLY TABLE 5006 (SHEET 1 OF 3)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

COMPONENT

CONDITION

Housing/Shaft Assembly

DISPOSITION

Imperfections which impair proper functioning, particularly cable ball holes, locking pin hole and free turning shaft.

Replace.

Spreading or distortion of pins, dents, burrs, or sharp projections.

Remove burrs or sharp projections, otherwise replace.

Rough or difficult rotation of release assembly shaft.

Replace.

Corrosion, localized pitting.

Clean, repair corroded areas and apply Alodine treatment followed by protective paint per Repair section.

Seized or limited range of motion.

Replace.

Pawl Assembly

Corrosion

Replace release assembly if corrosion is found on inner portion of housing where pawl rotates or where pawl rotation may be affected.

Lacing Cover Assembly

Rips or tears of fabric; loose stitching.

Repair small areas by machine sewing and/or cemented patches. See Repair section.

Sharp projections or loose grommets.

Replace grommet. See Repair section.

Release Mechanism Assembly

Release Mechanism Rear Support

VISUAL CHECK: DECORATIVE COVER AND PACKBOARD ASSEMBLY TABLE 5006 (SHEET 2 OF 3)

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COMPONENT

CONDITION

DISPOSITION

Lacing Cover Assembly (Cont’d)

Loose or damaged hook and pile fasteners.

Repair by machine sewing or call or consult your Zodiac Services Representative for repair.

Release Cable C37103-101 C37103-103

Prior to S/N 6013, distorted swage on release cable.

Inspect and/or replace per S.B. 004-25-41. (AD-97-23-13)

VISUAL CHECK: DECORATIVE COVER AND PACKBOARD ASSEMBLY TABLE 5006 (SHEET 3 OF 3)

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9. Visual Check: Extended Maintenance (Table 5007) (Figures 5001 through 5005)

COMPONENT

CONDITION

DISPOSITION

Cemented seams on all airholding sections of the inflatable (where accessible)

Lifted or detached sections, or other signs of deterioration or weakness. Reference Figures 5001 and 5002.

Up to two small areas may be repaired per Repair section. Large areas or several distinct areas of degradation or deterioration indicate slide inflatable should be replaced. Slide age and overall condition should be factored into all repair decisions - degradation or deterioration found in areas on older slides is more significant than that on newer slides.

All cemented attachment patches for restraints, mounting patches, handles, Velcro and snap fasteners, reservoir sling, straps, wrapper, etc.

Lifted or detached sections, or other signs of deterioration or weakness. Reference Figure 5003.

See Repair section. Consider slide age and overall condition. The number and scope of repairs may indicate that the slide inflatable should be replaced.

Girt attachment areas.

Lifted or detached sections, or other signs of deterioration or weakness.

Consider slide age and overall condition. Contact your Zodiac Services Representative for possible girt replacement or replace slide inflatable.

VISUAL CHECK: EXTENDED MAINTENANCE TABLE 5007 (SHEET 1 OF 2)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

COMPONENT

CONDITION Areas with delaminated coating on fabric. Reference Figure 504.

Sliding Floor

DISPOSITION Contact your Zodiac Services representative for possible floor replacement or replace slide assembly.

Tears, punctures, areas of See Repair section, or obvious wear. contact your Zodiac Services representative for possible floor replacement, or replace slide assembly. Loss of adhesion to slide Contact your Zodiac Serassembly. vices representative for possible floor replacement or replace slide assembly.

Gaps or lifted/detached areas between flange and slide assembly. Reference Aspirator Mounting Flange Figure 5005. Air leaks around flange.

Previous repairs to airhold- Lifts, detached areas, or ing tube structures other signs of deterioration or weakness.

Consider slide age and overall condition. Contact your Zodiac Services representative for possible specialized repair. Condition may indicate slide assembly should be replaced. See Repair section. Condition may indicate slide assembly should be replaced.

VISUAL CHECK: EXTENDED MAINTENANCE TABLE 5007 (SHEET 2 OF 2)

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EXAMPLES OF ADHESIVE BOND FAILURE WITHIN A CEMENTED SEAM. THE COATING ON THE FABRIC WITHIN THE SEAM REMAINS INTACT, WITH THE SEAM FAILURE OCCURRING WITHIN THE ADHESIVE LAYER. SEAMS WITH THIS CONDITION ARE RELATIVELY EASY TO PULL APART.

AREA OF ADHESIVE BOND FAILURE YELLOWED CEMENT WITH LOW ADHESION TO ADJOINING FABRIC OR FABRIC COATING LAYER

ADHESIVE BOND FAILURE: CEMENTED SEAMS FIGURE 5001

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EXAMPLE OF A DELAMINATION FAILURE WHERE COATING HAS PULLED OFF BASE LAYER OF FABRIC

COATING PULLED OFF BASE LAYER OF FABRIC COATING LAYER REMAINS BONDED TO OPPOSITE SIDE OF PATCH (SEAM SIMILAR)

NOTE: When evaluating weak areas, establish full extent of weakened area by attempting to gently pull apart each end of lifted or detached section. Strength must be greater than 5 Lb. (2.3 kg) per inch of bond line or seam width in compliance with TSO miniumum requirements.

DELAMINATION FAILURE: CEMENTED SEAMS FIGURE 5002

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ADHESIVE BOND FAILURE: SLIDE/RAFT ACCESSORIES/ATTACHMENT PATCHES FIGURE 5003

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DELAMINATION OF FABRIC COATING FIGURE 5004

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ADHESIVE BOND FAILURE: ASPIRATOR MOUNTING FLANGE FIGURE 5005

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TABLE OF CONTENTS REPAIR Page 1. Repair Materials/Equipment

6003

2. General Information - Limits (In Field)

6014

3. Patching Airholding Tubes

6018

4. Floor Repairs

6032

5. Reflective Finish

6033

6. Girt Assembly

6036

7. Grommet Replacement

6038

8. Lacing Cover, Chafing, and Dust Flap Patching

6043

9. Lamp Harness Replacement (Pre S.B. A320 0074-25-64 and Amendment 4)

6044

10. LED Harness Assembly Replacement (Post S.B. A320 004-25-64 and Amendment 4)

6050

11. Individual Lamp Housing Replacement (Pre S.B. A320 004-25-64 and Amendment #4)

6052

12. LED Lane Lighting Replacement (Post S.B. A320 004-25-64 and Amendment #4)

6057

13. Individual LED Housing Replacement (Post S.B. A320 004-25-64 and Amendment #4)

6058

14. Gage Viewing Port Replacement

6060

15. Packboard and Decorative Cover

6062

16. Optional Relocation of Lock Pin Stowage Pocket (Post S.B. 004-25-18)

6064

17. Removal of Lacing Cover Knots (Figure 6031) (Post S.B. 004-25-23)

6066

18. Decorative Cover Seal Improvements (Per S.B. 004-25-28)

6068

19. Decorative Cover Seal Improvement (Per S.B. A320 004-25-71 and Amendment #2)

6072

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COMPONENT MAINTENANCE MANUAL D31516 D31517

TABLE OF CONTENTS (Cont’d) REPAIR (Cont’d) Page 20. Release Mechanism Replacement

6076

A. Forward Door Only (E15366-Series; 62366-101, -103, -105)

6076

B. Aft Door Only (E15367-Series; 62370-101, -103, -105)

6080

21. Release Mechanism Replacement (Forward Door 62366-301 and Subs) 6084 22. Release Mechanism Replacement (Aft Door 62370-301 and Subs)

6088

23. Lower Mounting Bracket Replacement

6093

24. Girt Chafing Installation (Post S.B. 004-25-52)

6096

25. Pawl Assembly Replacement (Forward Door 62366-Series; Aft Door 62370-Series)

6099

26. Inflatable Slide Assembly Replacement

6100

27. Corrosion Repair to Aluminum Components

6101

28. Electrical Cable Assembly Repair

6104

29. Cylinder Chock Assembly Replacement (Aft Door Packboard)

6107

30. Replacement of Aspirator Anti-Chafe Coating

6111

31. Replacement of Strip Reinforcement Under Girt Mooring Line Grommets

6114

32. Re-Bonding or Replacement of Rubber Pads on Packboards

6116

33. Replacement or Reattachment of Packboard Mounting Hole Reinforcement Plate on 62366-Series and 62370-Series Packboards

6120

34. Replacement of a Torn or Damaged Maintenance Record Pocket on Lacing Cover

6122

35. Replacement of Non-Air-Holding Accessories and System Components 6124

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COMPONENT MAINTENANCE MANUAL D31516 D31517

1. Repair Materials/Equipment (Tables 6001 through 6005) NOTE: Equivalent substitutes may be used for items when marked with the following symbol  ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Urethane Cement Specification No. M11628

As Required

Air Cruisers V70167

Solvent, Washing Urethane Ethyl Acetate (CH3COOC2H5)

As Required

Commercially Cleans fabric. Available

Activating Agent, Urethane Methyl Ethyl Ketone (MEK) (CH3COC2H5) *

As Required

Commercially Activates urethane Available cement for bonding.

Activating Agent, Urethane As Ethyl Acetate/Acetone Solu- Required tion (CH3COOC2H5)/ (CH3COCH3) *

Commercially Activates urethane Available cement for bonding.

Fabric bonding adhesive.

* Two parts Ethyl Acetate one part Acetone by volume; may be used as an alternative to Methyl Ethyl Ketone. Toluene (C6H5CH3)

As Required

Commercially Thinner for reflective Available coating compound.

Leak Test Solution, Clear Ivory Hand Washing Dish Liquid Detergent 

As Required

Commercially Determines leakage of Available inflatable assemblies.

One ounce (29.6 milliliters) of detergent mixed to every 64 ounces (1.9 liters) of water. Isopropyl Alcohol ((CH3)2CHOH)

As Required

Commercially Cleaning of aspirator Available outlet end for new protective edge coating, cleaning packboard for reinforcement plate attachment.

REPAIR SOLVENTS AND CEMENTS TABLE 6001

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Page 6003 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

NOTE: Drawings of equipment/tools manufactured by Air Cruisers are available from Air Cruisers upon request. NOTE: Equivalent substitutes may be used.

ITEM/DESCRIPTION

QUANTITY

Hand Roller/Caster Wheel MR02040 (2 In. (50.8 mm) dia. x 2 In. (50.8 mm) wide with handle)

1

Brush 1 In. (25.4 mm) Spatula (Pusher) PA-1 Cloth, Cotton

As Required 1

As Required

Scissors, Blunt Nose, Plated, 5 In. (127 mm)

1

Aspirator Fork

1

SOURCE

USE

Everhard Distributes pressure Products, Inc. along bonded fabric V72274 repairs.

Commercially Applies cement. Available Air Cruisers V70167

Evenly distributes, and removes wrinkles from, bonded fabric repairs.

Commercially Applies solvents/soluAvailable tions. Commercially Cuts fabric. Available Air Cruisers V70167

Maintains an open aspirator inlet to allow air to escape the inflatable after testing or during packing.

REPAIR TOOLS TABLE 6002

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Page 6004 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

NOTE: Variations in fabric color shades is normal and acceptable. NOTE: Equivalent substitutes may be used.  ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Stencil Ink M11853

As Required

Air Cruisers V70167

Used for identification/ instruction markings.

Slide and Chafing Fabric (Urethane) M11849-5 (Slide Assemblies D31910-101 through -123; cemented construction)* M12040 (Slide Assemblies D31910-125, -127, and Subs; thermobonded construction)*

As Required

Air Cruisers V70167

Inflatable sub-assembly tube and chafing fabric.

Floor Fabric (Urethane) M11673

As Required

Air Cruisers V70167

Inflatable sub-assembly sliding lane or chafing fabric.

Girt Fabric M11480

As Required

Air Cruisers V70167

Girt/Girt extension fabric.

Lacing Cover Fabric M11481

As Required

Air Cruisers V70167

Lacing cover fabric.

Fabric Tape (Lamp Harness) M11849-1½ 1½ In. (38.1 mm) wide (Available by the yard)

As Required

Air Cruisers V70167

Fabric tape for covering exposed lamp/LED harness wires on inflatable sub-assembly.

Reflective Coating Compound M11787 or M12159 (Slide Assemblies D31910101 through -123; cemented construction)

As Required

Air Cruisers V70167

Coating for accessible seams, crotch tapes, attaching surfaces of cemented-on accessories, exposed threads, and adhesive margins.

* Either fabric may be used for patching. REPAIR MATERIALS TABLE 6003 (SHEET 1 OF 6)

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Page 6005 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Reflective Coating Compound M12229 (Slide Assemblies D31910125, -127, and Subs; thermobonded construction)

As Required

Air Cruisers V70167

Coating for accessible seams, crotch tapes, attaching surfaces of cemented-on accessories, exposed threads, and adhesive margins.

Mounting Patch, Lamp B31233-3 (Pre S.B. A320 004-25-64 and Amendment #4)

As Required

Air Cruisers V70167

Secures lamp housings.

Conductive Paint M11463

As Required

Air Cruisers V70167

Used during girt fabric repair.

Polyurethane Paint M12447 (Previous paint M11463 may be used until stock is depleted).

As Required

Air Cruisers V70167

Used during girt fabric repair.

1

Air Cruisers V70167

Provides chafe protection.

Sealant, Clear H119077

As Required

Air Cruisers V70167

Used during girt fabric repair.

Urethane Adhesive 3M Scotch Weld 3532 B/A

As Required

3M Co. V04963

Used during gage viewing port replacement on cover.

High Strength Laminating Resin/Hardener Epocast 50-A1/946

As Required

Fiberglass Cloth 1581-6 or 7781-6

As Required

Girt Chafing Patch 62553-17

Huntsman Adv. Packboard (tray/shell) Materials repair. VD8274 or V02684 or V99384 Commercially Used during packAvailable board repair.

REPAIR MATERIALS TABLE 6003 (SHEET 2 OF 6)

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Page 6006 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Talc or Powdered Soapstone

As Required

Commercially Prevents joining of Available areas of exposed cement, reflective coating compound, or stencil ink.

Butyl Rubber Gloves

As Required

Commercially Protects hands from Available solvent/epoxies.

Scour Cloth Brillo 3M Scotch Brite 7447

As Required

Commercially Used to roughen floor Available fabric prior to cementing.

Masking Tape 2 In. (50.8 mm)

As Required

Commercially Masks “boundaries” for Available cement/sealant/reflective coating compound application during repair. Secures LED/ lamp harness during replacement.

Sandpaper 50 Grit 80-120 Grit 180 Grit (or finer)

As Required

Commercially Roughens packboard/ Available decorative cover surfaces during repair.

Adhesive, Threadlocker Loctite 222

As Required

Loctite Removable threadCorporation locker applied to screw V05972 or threads. Commercially Available

Abrasive Paper Cloth (Silicon Carbide Grit or #400 Aluminum Oxide)

As Required

Commercially Removes corrosion Available from packboard release mechanism rear support.

REPAIR MATERIALS TABLE 6003 (SHEET 3 OF 6)

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Page 6007 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Aluminum Liquid Devcon F-2

As Required

Commercially Repairs localized pitAvailable ting on packboard release mechanism rear support.

Touch-Up Pen Alodine 1132

As Required

Commercially Pre-treats abraded Available areas on packboard release mechanism rear support.

Epoxy Primer (per AIMS 04-04-001)*

As Required

Commercially Final coating applied Available following repairs of packboard release mechanism rear support.

Super Koropon 515K011*

As Required

Commercially Final coating applied Available following repairs of packboard release mechanism rear support.

Deft 026N058*

As Required

Commercially Final coating applied Available following repairs of packboard release mechanism rear support.

Tape, Green 1.0 In. (25.4 mm) wide PPP-T-60-1

As Required

Commercially Provides chafe protecAvailable tion from metal fittings.

Tape, Black Fire Retardant 1.0 In. (25.4 mm) wide M12397-1 (Reference S.I.L. 25-252)

As Required

Air Cruisers V70167

Provides chafe protection from metal fittings.

*Alternatives REPAIR MATERIALS TABLE 6003 (SHEET 4 OF 6)

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Page 6008 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Primer F938 HP**

As Required

Plasti Dip, Int’l Primer for protective V0B629 or coating for edge of Commercially aspirator outlet. Available

Primer, Plasti-Dip 41209-6**

As Required

Plasti Dip, Int’l V0B629 or Commercially Available

Air Dry Plastic Coating F-866, Black

As Required

Plasti Dip, Int’l Protective coating for V0B629 or edge of aspirator outCommercially let. Available

Adhesive Primer CONAP AD-1147C

As Required

Commercially Used during replaceAvailable ment of mooring line grommet strip reinforcement.

Epoxy Adhesive, Scotch Weld DP-190 Gray***

As Required

3M Company Used to bond replaceV04963 ment parts to packboard as specified.

Epoxy Adhesive, Scotch Weld DP-110 Translucent***

As Required

3M Company Used to bond replaceV04963 ment parts to packboard as specified.

Epoxy Adhesive, Scotch Weld EC-7210***

As Required

3M Company Used to bond replaceV04963 ment parts to packboard as specified.

Epoxy Adhesive, Scotch Weld 2216 B/A Gray***

As Required

3M Company Used to bond replaceV04963 ment parts to packboard as specified.

Alternative primer for protective coating for edge of aspirator outlet.

**Alternatives ***Alternatives REPAIR MATERIALS TABLE 6003 (SHEET 5 OF 6)

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Page 6009 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Adhesive M11055 Style P

As Required

Air Cruisers V70167

Used to bond replacement parts to packboard as specified.

Maintenance Log Pocket B31544-101

As Required

Air Cruisers V70167

Used for replacement of a damaged Maintenance Release Record pocket on lacing cover.

Reinforcement Plate B15481-3

As Required

Air Cruisers V70167

For replacement purposes - mounted on packboard.

REPAIR MATERIALS TABLE 6003 (SHEET 6 OF 6)

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Page 6010 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

NOTE: Equivalent substitutes may be used.  ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Soldering Iron 600°-800°F Heat Range (315.6°-426.7°C)

1

Commercially Heats solder for appliAvailable cation.

Soldering Iron Tip Screwdriver or Chisel Tip

1

Commercially Melts mylar insulation. Available

Soldering Iron Tip Conical or Pencil Tip

1

Commercially Applies solder. Available

Solder QQ-S-571 SN60/40Pb Rosin Core, Mildly Activated

As Required

Commercially Alloy used to join Available metal.

Desoldering Bulb Vacuum Action, Teflon Tip

1

Commercially Removes solder. Available

Marker Black Ink, Permanent, Fine Tip

1

Commercially Traces outline of damAvailable aged lamp housing ends.

Knife, Precision Blade

1

Commercially Removes heat shrink Available coverings from lamp housings.

Shield, Wood ¼ x 12 x 12 In. (6.4 x 304.8 x 304.8 mm) (Approximate dimensions)

1

Commercially Protects fabric from Available soldering iron.

Pliers, Slip-Lock 1½ In. (38.1 mm) opening min.

1

Commercially Breaks ultra-sonic Available welds.

INDIVIDUAL LAMP REPLACEMENT REPAIR MATERIALS (PRE S.B. A320 004-25-64 AND AMENDMENT #4) TABLE 6004 (SHEET 1 OF 2)

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Page 6011 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

Magnifier, Eye Loupe 10X power

1

SOURCE

USE

Commercially Used for precise examAvailable ination of lamp housing.

Isopropyl Alcohol ((CH3)2CHOH)

As Required

Commercially Available

Brush, small stiff bristles

As Required

Commercially Solvent/solution appliAvailable cator.

Bottle, Dispensing, with spout or pump

1

Tape, Mylar 3/8-3/4 In. (9.5-19.1 mm) wide, 2 mils (0.002 In.) thick

As Required

Removal of solder flux from solder joints.

Commercially Solvent/solution disAvailable penser. Commercially Used to wrap solder Available joints and flat conductors.

INDIVIDUAL LAMP REPLACEMENT REPAIR MATERIALS (PRE S.B. A320 004-25-64 AND AMENDMENT #4) TABLE 6004 (SHEET 2 OF 2)

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Page 6012 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

NOTE:  Equivalent substitutes may be used. ITEM/DESCRIPTION

QUANTITY

LED Repair Kit 1 65996-3 (dual LED) (per each 65996-5 (single 90° LED) LED) 66250-1 (multiple 90° LED)

SOURCE

USE

Air Cruisers V70167

Contains replacement LED, four splices, and four heat shrink tubings.

Tool - Crimping TR-490

1

Wire Stripper, Klein 26-16 AWG 11046*

1

Commercially Used to remove proAvailable tective coating from wire leads.

Wire Stripper, Ideal 26-16 AWG 45-121*

1

Commercially Used to remove proAvailable tective coating from wire leads.

Heat Gun, Master PH-1100

1

Commercially Used to apply heat for Available shrink tubing installation.

Cord, Nylon MIL-C-5040 Type III or M11029-2

As Required

Commercially Used to remove/install Available or LED harness. Air Cruisers V70167

Fabric Tape (Lamp Harness) M11849-1½ 1½ In. (38.1 mm) wide (Available by the yard)

As Required

Minnesota Mining & Mfg. Co. V2H942

Air Cruisers V70167

Used to splice/crimp harness lead wires together.

Fabric tape for covering exposed LED harness wires.

*Alternatives INDIVIDUAL LED REPLACEMENT REPAIR MATERIALS (POST S.B. A320 004-25-64 AND AMENDMENT #4) TABLE 6005

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Page 6013 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

2. General Information - Limits (In Field) NOTE: If doubt exists as to the capability of local facilities to accomplish satisfactory repairs, it is recommended that the inflatable or components be returned to a Zodiac Services Repair Center for repair (reference S.I.L. 25-102). A. In general, confer repairs on the inflatable to patching of tears or punctures in the airholding panels. Replacement of a complete section such as a tube, the floor, etc., should never be attempted in the field. B. Although slightly damaged areas in the fabric can be repaired, removal and replacement of any component bonded directly to an airholding fabric panel is generally not recommended due to the risk of damage to the underlying fabric. Should replacement be attempted, care must be taken to avoid damaging the fabric and compromising the airholding capability. CAUTION: WHEN WORKING NEAR SEAMS, PATCHES, OR COMPONENTS THAT HAVE BEEN INSTALLED USING WELDING METHODS, USE EXTREME CARE WITH SOLVENTS. DO NOT AGGRESSIVELY STRESS OR PULL ON WELDED BONDS WHEN SOLVENTS ARE IN CLOSE PROXIMITY. SOLVENTS WILL SOFTEN AND DEGRADE THESE BONDS. C. Slight lifting of any part bonded directly to a fabric panel may be repaired per the general cement instructions detailed in Paragraphs 3.A.(2) through (11). (1). Use urethane cement (Table 6001) to bond edges back into place. (2). Welding processes typically leave a thin, unbonded margin along the perimeter of the bonded area. This is an acceptable condition. Lifted or detached areas greater than the limits noted in the Check section can be secured back into place using urethane cement (Table 6001). D. Lifted, detached, or separated seams without fabric tears on or about the area may also be repaired per the general cement instructions detailed in Paragraphs 3.A.(2) through (11). (1). Use urethane cement (Table 6001) to bond edges back into place on both cemented and thermobonded seams.

25-60-56

Page 6014 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

(2). The thermobonded seam assembly process may leave a thin, unbonded margin along the bonded area. This is an acceptable condition. Lifted or detached areas greater than the limits notes in the Check section can be secured into place using urethane cement (Table 6001). (3). Consult your Zodiac Services Representative for repair of any seam that intersects a mitered corner. CAUTION: THE AGE OF THE SLIDE ASSEMBLY AND ITS REPAIR HISTORY SHOULD BE CONSIDERED IN ALL DECISIONS REGARDING REPAIR FOR CONTINUATION OF USE IN SERVICE. E. The following factors may indicate that the slide inflatable should be replaced. (1). Adhesive bond failure, where the coating on the fabric in the seam area remains intact. (2). Unusual or pronounced areas of wear. (3). Adhesive bond failures of slide accessories where mounted on the slide system. (4). Number an scope of required repairs. WARNING: WHEN USING SOLVENTS, CEMENTS, OR OTHER CHEMICAL BASED PRODUCTS, REFER TO THE APPLICABLE MATERIAL SAFETY DATA SHEET (MSDS) FOR SPECIFIC GUIDELINES ON PROPER PERSONAL PROTECTIVE EQUIPMENT, STORAGE, HANDLING, AND VENTILATION REQUIREMENTS TO PREVENT SICKNESS OR INJURY TO PERSONNEL. WARNING: USE EYE, FACE, AND EAR PROTECTION WHEN USING HIGH PRESSURE AIR TO PROTECT PERSONNEL FROM POSSIBLE INJURY. WARNING: EXERCISE CAUTION WHEN USING LEAK TEST SOLUTIONS DUE TO THE RISK OF PERSONAL INJURY FROM SLIPS AND FALLS. CAUTION: WHEN USING A SOLUTION TO INSPECT FOR LEAKS USE LEAK TEST SOLUTION (TABLE 6001) ONLY OR AN ELECTRONIC LISTENING DEVICE. F.

Following repairs to the airholding tubes, an inflatable integrity verification test must be accomplished. See Testing section.

25-60-56

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COMPONENT MAINTENANCE MANUAL D31516 D31517

CAUTION: ASPIRATOR FORK (TABLE 6002) MAY BE USED TO SECURE THE FLAPPER INLET VALVES ON THE ASPIRATOR IN THE OPEN POSITION TO ALLOW ENTRAPPED AIR TO ESCAPE THE SLIDE ASSEMBLY. SPRING CLAMPS OR OTHER DEVICES SHOULD NOT BE USED DUE TO POTENTIAL DAMAGE TO THE CLOSING MECHANISM OR SEALING SURFACES OF THE FLAPPER VALVES. ENSURE ASPIRATOR FORK IS REMOVED FROM THE ASPIRATOR DURING SUBSEQUENT STEPS OF THE PACKING PROCESS. NOTE: Subsequent to repair, wash off leak test solution with clean water. G. Facility Conditions for Repairs (1). Work areas used for cementing must be clean, free of dust and dirt. CAUTION: COLD TEMPERATURES WHERE DEW OR FROST IS PRESENT CAN CAUSE A PROBLEM OF MOISTURE ON THE FABRIC, WHICH WOULD PROHIBIT PROPER BOND FROM BEING MADE. HIGH HEAT AND/OR HUMIDITY CAN RESULT IN EFFECTS OF CONDENSATION OF MOISTURE (WHITE AREAS ON CEMENT) CAUSED BY EVAPORATING SOLVENTS. (2). Recommended temperature to apply cement should be between 55 - 80°F (12.8 - 26.7°C) with relative humidity (65% maximum). H. Cement/Accelerator Storage (1). Cement/accelerator shall be stored under conditions where excessive heat, humidity or cold are not present. Once opened, if the accelerator is exposed to moisture present in high humidity areas, it will cause flake like particles in the product. Accelerator should not be used if flake like particles are present indicating degradation. It is suggested to use what is opened, because resealed containers may contain enough moisture to react with the accelerator.

25-60-56

Page 6016 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

I.

Mixing Instructions for Reflective Paint (1). M11787 or M12159 is supplied in two parts in order to maintain a workable shelf/pot life. Prior to use, it is important to thoroughly mix the two components. The base component (Part A) should be stirred/agitated to ensure that the ingredients are homogeneous. Note that settling does occur and the product must be uniform prior to use. Part B takes additional care when mixing. The aluminum portion forms a paste-like consistency on the bottom of the container. To mix properly, this product should be agitated and then stirred. Once no sedimentation is observed, a proper mix has occurred. At this point, the two components should be combined to the proper ratio. Any combined unused portions shall be disposed of on a daily basis. (2). M12229 is supplied in two parts in order to maintain a workable shelf/pot life. Prior to use, it is important to thoroughly mix the two components both individually and in combination. The base component (Part A) should be stirred/agitated to ensure that the ingredients are homogenous. Note that settling does occur and the product must be uniform prior to use. Part B requires additional care when mixing. The reflective portion forms a paste-like consistency on the bottom of the container. To mix properly this product must be agitated and then stirred. Once a uniform consistency has been achieved, components A and B should be combined at the proper ratio. The paint must be stirred manually every 15 minutes to prevent settling of the reflective component. Any combined portions and containers should be disposed of on a daily basis.

25-60-56

Page 6017 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

3. Patching Airholding Tubes A. Tube Punctures up to 2 In. (50.8 mm) in length. NOTE: Use a round patch on the outer fabric surface only. Repair patches should be die cut, when size permits. (1). Cut a patch large enough to allow an overlap beyond the puncture edges as follows:

Puncture Limits

Minimum Overlap of Damaged Area Should Be:

Up to 1/8 In. (3.2 mm)

1 In. (25.4 mm)

1/8 to 1 In. (3.2 to 25.4 mm)

2 In. (50.8 mm)

Over 1 In. but less than 2 In. (25.4 to 50.8 mm)

3 In. (76.2 mm)

CAUTION: WHEN WASHING THE TUBE FABRIC, DO NOT ALLOW EXCESS SOLVENT TO COLLECT AT THE EDGES OF SEAMS. DO NOT APPLY SOLVENT TO DECALS OR STENCIL MARKINGS (WHENEVER POSSIBLE) SINCE THEY CAN BE REMOVED BY THE SOLVENT. IF STENCIL MARKINGS NEED TO BE REPLACED, USE THE STENCIL INK LISTED IN TABLE 6003.

25-60-56

Page 6018 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

(2). Thoroughly wash the fabric around the puncture and the bottom side of patch (Figure 6001) with a cloth (Table 6002) dampened in solvent (Table 6001). Do not damage the fabric.

TUBE FABRIC

WASH BOTTOM OF PATCH

PUNCTURE IN TUBE FABRIC

WASH AREA AROUND PUNCTURE

PATCHING TUBE PUNCTURES FIGURE 6001

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Page 6019 04 Dec 2018

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CAUTION: DISCARD UNUSED CEMENT 4 HOURS (POT LIFE) AFTER MIXING. NOTE: The cement line must be even and uniform to within ½ In. (12.7 mm) beyond the edge of repair. (3). Brush three coats of cement (Table 6001) around the puncture and onto yellow side of the patch (Figure 6002); cover an area slightly larger than the patch. Apply cement in medium, even coats. Allow 15 minutes drying time between coats. Remove effects of condensation (white areas on cement) by swabbing with a cloth (Table 6002) lightly dampened in solvent (Table 6001).

CEMENT YELLOW SIDE OF PATCH (3 COATS)

BRUSH

TUBE FABRIC CEMENT AREA AROUND PUNCTURE (3 COATS)

PATCHING TUBE PUNCTURES FIGURE 6002

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COMPONENT MAINTENANCE MANUAL D31516 D31517

CAUTION: DO NOT EXCEED ONE HOUR BETWEEN CEMENT APPLICATION AND JOINING OF SURFACE. APPLY A FOURTH COAT TO SURFACES IF TIME IS EXCEEDED. (4). Within one hour after cement application, dampen a clean cloth (Table 6002) with activating agent (Table 6001). Wipe cemented surfaces to make them tacky and ready for joining. NOTE: Fabric weave on patch and tube do not have to be in alignment. CAUTION: JOIN SURFACES IMMEDIATELY (WITHIN 60 SECONDS) AFTER ACTIVATING TO MAXIMIZE BOND. (5). Immediately join the cemented patch to the cemented tube fabric. (6). The patch should be laid on gradually from the center to the edges (Figure 6003) to minimize the possibility of air bubbles being trapped beneath the patch.

TUBE FABRIC PATCH

CENTER LINE OF CEMENTED AREA

CEMENTED AREA

PATCHING TUBE PUNCTURES FIGURE 6003

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COMPONENT MAINTENANCE MANUAL D31516 D31517

NOTE: Pressure is important for a good bond. (7). Apply pressure evenly with a spatula (Table 6002) to eliminate entrapped air bubbles and wrinkles to ensure firm attachment (Figure 6004). (8). When all wrinkles and air bubbles are eliminated uniformly roll the joined areas (Figure 6005) using a hand roller (Table 6002).

SPATULA (PUSHER)

PATCH

TUBE FABRIC

PATCHING TUBE PUNCTURES FIGURE 6004

HAND ROLLER

PATCH

TUBE FABRIC

PATCHING TUBE PUNCTURES FIGURE 6005

25-60-56

Page 6022 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

(9). Allow cement to cure for a minimum of four hours. (10). If the repair has been performed on an airholding tube, perform inflatable integrity verification tests. See Testing section. (11). Apply reflective finish to the repaired area per the instructions in Paragraph 5. B. Repair of Tube Tears, Up to 2 Ft. (0.610 m) Repairs to tube fabric tears should be limited to 2 Ft. (0.610 m) maximum, if the tear does not intersect a seam or a miter joint. If these are part of the tear, call or consult your Zodiac Services Representative for repair. CAUTION: REPAIR TUBE TEARS BY PATCHING BOTH THE INSIDE AND OUTSIDE SURFACES OF THE TUBE FABRIC PRIOR TO INFLATING THE UNIT. (1). Trim off any loose threads (Figure 6006) with scissors (Table 6002).

SCISSORS TO TRIM OFF LOOSE THREADS

TEAR IN FABRIC

PATCHING TUBE TEARS FIGURE 6006

25-60-56

Page 6023 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

(2). Spread a handful of soapstone or talc (Table 6003) inside the tube opening on the tube fabric opposite the tear area (Figure 6007) to prevent joining the inside of the fabric together.

TRIMMED TEAR IN FABRIC

HANDFUL OF SOAPSTONE

PATCHING TUBE TEARS FIGURE 6007 (3). Cut a patch large enough to allow a 2 In. (50.8 mm) overlap beyond the tear edges CAUTION: WHEN WASHING THE TUBE FABRIC, DO NOT ALLOW EXCESS SOLVENT TO COLLECT AT EDGES OF SEAMS. DO NOT APPLY SOLVENT TO DECALS OR STENCIL MARKINGS (WHENEVER POSSIBLE) SINCE THEY CAN BE REMOVED BY THE SOLVENT.

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(4). Thoroughly wash the inside surface of the fabric around the tear (Figure 6008) and the yellow side of the patch with a cloth (Table 6002) dampened in solvent (Table 6001).

TUBE FABRIC

CLOTH DAMPENED IN SOLVENT TEAR

PATCHING TUBE TEARS FIGURE 6008 CAUTION: DO NOT EXCEED ONE HOUR BETWEEN CEMENT APPLICATION AND JOINING OF SURFACE. APPLY A FOURTH COAT TO SURFACES IF TIME IS EXCEEDED. CAUTION: DISCARD UNUSED CEMENT 4 HOURS (POT LIFE) AFTER MIXING. (5). Brush three coats of cement (Table 6001) on the inside surface of the tube fabric. Cover an area slightly larger than the size of the patch. Apply cement in medium, even coats. Allow 15 minutes between coats. Remove effects of condensation (white areas on cement) by swabbing with a cloth (Table 6002) lightly dampened in solvent (Table 6001). (6). Thoroughly wash the yellow side of the fabric patch with a cloth (Table 6002) dampened in solvent (Table 6001). Do not damage the fabric.

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(7). Brush three coats of cement (Table 6001) onto the yellow side of the patch. Apply cement in medium, even coats. Allow 15 minutes between coats. Remove effects of condensation (white areas of cement) by swabbing with a cloth (Table 6002) lightly dampened in solvent (Table 6001). CAUTION: JOIN SURFACES IMMEDIATELY (WITHIN 60 SECONDS) AFTER ACTIVATING TO PREVENT INADEQUATE BOND. (8). Within one hour after the cement application, dampen a clean cloth (Table 6002) in activating agent (Table 6001). Wipe cemented surfaces to reactivate them. This brings up the tack and makes the surfaces ready for joining. (9). Fold the patch in half lengthwise, pass it through the tear, and install it cement side up on the inside surface of the tube fabric directly under the tear (Figure 6009).

HALF OF PATCH LOCATED UNDER HALF OF TRIMMED TEAR

TRIMMED TEAR

WASH/CEMENT (3 COATS) ACTIVATION AREA OF PATCH

PATCHING TUBE TEARS FIGURE 6009

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(10). Join the torn section of the tube fabric onto the patch per Figure 6009. NOTE: Pressure is important for a good bond. (11). Apply pressure evenly with a spatula (Table 6002) to eliminate entrapped air bubbles and wrinkles to ensure firm attachment. (12). When all wrinkles and air bubbles are eliminated uniformly roll the joined areas (Figure 6010) using a hand roller (Table 6002).

HAND ROLLER TUBE FABRIC

PATCHING TUBE TEARS FIGURE 6010

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(13). Cut a patch large enough to allow a 2 In. (50.8 mm) overlap beyond the tear edges. CAUTION: WHEN WASHING THE TUBE FABRIC, DO NOT DAMAGE THE FABRIC, DO NOT ALLOW EXCESS SOLVENT TO COLLECT AT THE EDGES OF THE SEAMS. DO NOT APPLY SOLVENT TO DECALS OR STENCIL MARKINGS (WHENEVER POSSIBLE) SINCE THEY CAN BE REMOVED BY THE SOLVENT. (14). Thoroughly wash the outside surface around the tear (Figure 6011) with a cloth (Table 6002) dampened in solvent (Table 6001).

TUBE FABRIC

CLOTH DAMPENED IN SOLVENT

CEMENTED AREA

PATCHING TUBE TEARS FIGURE 6011

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(15). Brush three coats of cement (Table 6001) on the outside of the tube fabric (Figure 6012) per the cement instructions detailed in Paragraph 3.A.(3).

BRUSH

CEMENTED AREA

TUBE FABRIC

PATCHING TUBE TEARS FIGURE 6012 (16). Thoroughly wash the fabric on the patch with a cloth (Table 6002) dampened in solvent (Table 6001). Do not damage the fabric. (17). Brush three coats of cement (Table 6001) onto yellow side of the patch. Apply cement in medium, even coats. Allow 15 minutes between coats. Remove effects of condensation (white areas of cement) by swabbing with a cloth (Table 6002) lightly dampened in solvent (Table 6001). CAUTION: JOIN SURFACES IMMEDIATELY (WITHIN 60 SECONDS) AFTER ACTIVATING TO PREVENT DRY AREAS. (18). Within one hour after cement application, dampen a cloth (Table 6002) in activating agent (Table 6001). Wipe cemented surfaces to reactivate them. This brings up the tack and makes the surfaces ready for joining.

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NOTE: Fabric weave on patch and tube do not have to be in alignment. (19). Join the cemented surface of the patch to the outside surface of the tube fabric (Figure 6013). (20). Apply pressure evenly with a spatula (Table 6002) to eliminate entrapped air bubbles and wrinkles to ensure firm attachment. (21). When all wrinkles and air bubbles are eliminated uniformly roll the joined areas (Figure 6014) using a hand roller (Table 6002). (22). Allow cement to cure for a minimum of four hours. (23). If the repair has been performed on an airholding tube, perform inflatable integrity verification tests. See Testing section. (24). Apply reflective finish to the repaired area per the instructions in Paragraph 5.

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PATCH LOCATED ON TOP OF TRIMMED TEAR

PATCHING TUBE TEARS FIGURE 6013

HAND ROLLER

PATCH LOCATED ON TOP OF TRIMMED TEAR

PATCHING TUBE TEARS FIGURE 6014

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4. Floor Repairs Repairs to the floor surface should be limited to punctures and tears up to 3 In. (76.2 mm). If the damaged area exceeds these limitations, call or consult your Zodiac Services Representative for repair. A. Trim off loose threads with scissors (Table 6002). NOTE: Sliding surface of system is silver/gray in color, underside is silver in color. Install patch to the underside (silver side) of floor surface. B. Cut a patch of floor fabric (Table 6003) large enough to allow an overlap beyond the puncture per Paragraph 3.A.(1), or large enough to allow a 2 In. (50.8 mm) overlap beyond the tear edges. C. Buff patch, (silver/gray), and damaged area of floor fabric with dry scour cloth (Table 6002). CAUTION: WHEN WASHING THE FLOOR FABRIC, DO NOT ALLOW EXCESS SOLVENT TO COLLECT AT EDGES OF SEAMS. D. Thoroughly wash the floor fabric (silver side) around the damaged area with a cloth (Table 6002) dampened in solvent (Table 6001). E. Apply three coats of cement (Table 6001) on the silver side of the floor fabric per the general cement instructions detailed in Paragraph 3.A.(3). F.

Prepare the patch, silver/gray, with a cloth (Table 6002) dampened in solvent (Table 6001).

G. Apply three coats of cement (Table 6001) on the silver/gray side of the patch per general cement instructions detailed in Paragraph 3.A.(3). CAUTION: JOIN SURFACES IMMEDIATELY (WITHIN 60 SECONDS) AFTER ACTIVATING TO PREVENT INADEQUATE BOND. H. Activate and join the patch to the floor fabric per the general cement instructions detailed in Paragraphs 3.A.(4) through (9). I.

Apply reflective finish per Paragraph 5.

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5. Reflective Finish A. Preparation of the fabric surface. (1). Prior to applying the reflective finish, all dust, dirt, and grease are to be removed from the surface to be coated using a cloth (Table 6002) dampened in solvent (Table 6001). (2). Remove excess solvent from the surface of the tube structures with a dry cloth (Table 6002). (3). The cleaned surface will require a minimum drying time of one hour. Before proceeding further, verify that the surface is clean and dry. B. Coating Compound CAUTION: THE COMPOUND MUST BE STIRRED PERIODICALLY (EVERY 10 MINUTES) TO KEEP ALUMINUM PLATELETS SUSPENDED IN THE SOLUTION. IF THE COATING THICKENS DURING APPLICATION, ADD TOLUENE. (1). The compound (Table 6003) should be thoroughly mixed to ensure that all of the pigments are evenly dispersed and suspended in the solution. (2). The coating should be a viscosity for brushing. Toluene (Table 6001) may be added to maintain viscosity. C. Inflatable Pressure During Coating (1). After the cleaned surfaces have dried, the unit is to be inflated to 1.5 psig (1.0 N/cm2). CAUTION: REWORKED AREAS MUST CURE FOR FOUR HOURS, BE DUSTED WITH SOAPSTONE, AND BE ALLOWED TO AIR DRY FOR A MINIMUM OF 16 HOURS BEFORE DEFLATING AND PACKING.

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D. Application of Coating (1). Apply the coating with a soft nylon brush (Table 6002). Apply coating sparingly, brushing any sags or drips. The repaired areas, including exposed cement areas, are to be covered with one coat using even strokes. (2). Allow the unit to cure for four hours, then dust with soapstone or talc. (3). Allow to air dry for a minimum of 16 hours before deflating and packing.

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6. Girt Assembly Repairs to the girt assembly should be limited to punctures, tears less than 3 In. (76.2 mm), and replacing grommets. If the damaged area exceeds these limitations or occurs at or along the perimeter of the girt assembly, call or consult your Zodiac Services Representative for repair. A. Girt Repair (1). Follow the basic cementing instructions outlined in Paragraph 3.A for punctures or tears, except use the girt assembly patching fabric (Table 6003). B. Recoating of Girt Assembly (Coating abrasion, flaking, or exposure of threads). CAUTION: IF ANY DAMAGE TO FABRIC SUBSTRATE IS NOTICED, THE GIRT MUST BE REPLACED. CALL OR CONSULT YOUR ZODIAC SERVICES REPRESENTATIVE FOR REPLACEMENT INSTRUCTIONS. NOTE: Use masking tape (Table 6003) to control edges of coated areas. (1). Before applying sealant, prepare fabric surface per Paragraphs 5.A.(1) through (3). (2). Apply three coats of sealant (Table 6003) to girt fabric. Sealant must be applied in well defined squared off areas (Figure 6015). Allow 60 minutes dry time between coats. Remove tape and discard. Allow sealant to dry 14 hours.

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(3). Apply two coats of polyurethane paint (Table 6003) over the entire sealant area. The paint must overlap the sealant edges by ¾ In. (19.1 mm) minimum. Allow 30 minutes dry time between coats. Allow four hours curing time.

POLYURETHANE PAINT

APPLY SEALANT TO WORN GIRT

MASKING TAPE AREA

RECOAT GIRT FABRIC FIGURE 6015

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7. Grommet Replacement NOTE: For grommet identification, see Figures 6018 through 6020. A. If the grommet is damaged, mark location, remove and discard grommet. Measure hole in fabric left by grommet. NOTE: If the fabric is stretched, frayed, or cut around the grommet hole, it may be necessary to cut a larger diameter fabric disc to sufficiently cover the damaged area [at least ¾ In. (19.1 mm) larger]. Fabric disc will be cut from the same fabric as item to be repaired. B. Bond two fabric discs (Table 6003), ¾ In. (19.1 mm) in diameter larger than the damaged area, to both the top side and underside of the area to be repaired (Figure 6016). C. Brush three coats of urethane cement (Table 6001) onto the disc, and onto the area to be repaired. D. Install the disc per Paragraphs 3.A.(3) through (9).

DISC

MISSING GROMMET FABRIC (TOP) DISC

CEMENT AREA

DISC

GROMMET REPLACEMENT FIGURE 6016

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E. Allow the cement to cure for two hours minimum. NOTE: Use an appropriate size punch for punching hole. F.

Punch a hole through fabric in marked location using an appropriate size punch.

G. Install the grommet per Figure 6017.

MALLET

PUNCH

GROMMET (TOP)

PUNCHED HOLE

GROMMET (BOTTOM)

GROMMET REPLACEMENT FIGURE 6017

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EYELET A1170 WASHER C587 (2 PLACES)

WASHER 16A1502A-2 EYELET A2127 (2 PLACES) (GIRTS MFG MAY 2009 AND SUBS.)

MS22048C2 (12 PLACES)

MS20230BPS10 (2 PLACES) EYELET A1170 WASHER C587 (8 PLACES - GIRTS MFG BEFORE MAY 2009) (6 PLACES - GIRTS MFG MAY 2009 AND SUBS.)

GIRT ASSEMBLY

GROMMET IDENTIFICATION FIGURE 6018

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A1170 (18 PLACES)

LACING COVER ASSEMBLY

GROMMET IDENTIFICATION FIGURE 6019

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A1170 (18 PLACES)

PACKBOARD UPPER LACING COVER

GROMMET IDENTIFICATION FIGURE 6020

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8. Lacing Cover, Chafing, and Dust Flap Patching A. If the material is otherwise in good condition, tears in the fabric can be repaired by simple machine sewing or patching. B. To repair small holes use round patches. C. Cut patches in accordance with Paragraph 3.A.(1). CAUTION: WHEN WASHING THE FABRIC, DO NOT ALLOW EXCESS SOLVENT TO COLLECT ON THE MATERIAL. DO NOT APPLY SOLVENT TO DECALS OR STENCIL MARKINGS (WHENEVER POSSIBLE) SINCE THEY CAN BE REMOVED BY THE SOLVENT. CAUTION: ALLOW FABRIC TO DRY BEFORE APPLYING ADHESIVE. THE FIRST COAT OF CEMENT SHOULD BE APPLIED WITHIN ONE HOUR OF CLEANING. IF MORE THAN ONE HOUR ELAPSES, RECLEAN SURFACES. D. Follow the basic cementing instructions outlined in Paragraphs 3.A.(3) through (9) for punctures and tears except use the appropriate patching fabric (Table 6003).

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9. Lamp Harness Replacement (Figures 6021 through 6024) (IPL Figure 3) (Pre S.B. A320 0074-25-64 and Amendment 4) A. Remove Lamp Harness (1). Separate the girt halves and untie the electrical cable assembly tie-off cord from the cord loop. (2). Disconnect lamp harness female connectors from the male connectors on the electrical cable assembly. (3). Route the lamp harness through wire guide in girt toward the outside edge of girt. (4). Remove/peel mounting tape and lamp mounting patches from the slide body tube and ramp and save for re-use. (5). Remove lamp harness.

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WIRE GUIDE

GIRT HALVES ELECTRICAL HARNESS CONNECTORS ELECTRICAL HARNESS CONNECTORS

WIRE GUIDE LAMP HARNESS CONNECTORS

LOOP

TIE-OFF CORD

LAMP HARNESS CONNECTORS

REMOVE LAMP HARNESS FIGURE 6021

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B. Install Lamp Harness (1). If the original tape is damaged during removal, replace it with M11849-1½ tape (Table 6003). (2). Apply cement to the yellow side of the mounting tape and lamp mounting patches per the cementing instructions in Paragraph 3.A.(3) in preparation for installing the new harness, see Figure 6023 Detail “A”. (3). Apply cement to the slide in previous attachment areas, using ½ In. (12.7 mm) wide masking tape, see Figure 6023 Detail “B”. (4). Position the new harness with the lamps located in the same location as the previous harness as shown in Figure 6024. NOTE: Use ½ In. (12.7 mm) wide masking tape, 2 In. (50.8 mm) long, to temporarily hold the lamp in place. Remove prior to bonding. NOTE: Lamp harness is folded in a 90° pleat at corners, see Figure 6023 Detail “C”. NOTE: Start the bonding at the runway end and proceed in both directions. (5). Bond the mounting tape and mounting patches (Table 6003) in place in accordance with the cementing instructions in Paragraphs 3.A.(3) through (11). (6). Apply reflective coating compound (Table 6003) to the tape margins per Paragraph 5.

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LAMP HARNESS

SLIDE ASSEMBLY

LAMP HARNESS REPLACEMENT FIGURE 6022

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MOUNTING TAPE

DETAIL “C”

FOLD LAMP HARNESS TAPE TO GO AROUND EACH CORNER

MASKING TAPE SLIDE TUBE

CEMENT

CEMENT

MASKING TAPE

NO CEMENT

MOUNTING TAPE (YELLOW SIDE) NO CEMENT

DETAIL “B” DETAIL “A”

LAMP HARNESS REPLACEMENT FIGURE 6023

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MASKING TAPE

19.3 In. (489 mm) CL LAMP HARNESS

4.5 In. (114 mm) CL OF SLIDE

LAMP MOUNTING PATCH (TYPICAL) REPLACEMENT TAPE (YELLOW SIDE)

LAMP HARNESS REPLACEMENT FIGURE 6024

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10. LED Harness Assembly Replacement (IPL Figure 3) (Post S.B. A320 004-25-64 and Amendment 4) A. Removal and Installation of LED Harness (1). Separate the girt halves and untie the electrical cable assembly tie-off cord from the cord loop. (2). Disconnect LED harness female connectors from the male connectors on the electrical cable assembly. (3). Route the LED harness from both sides of the girt through the girt wire guide and tape sleeve towards outside edge of the girt (typical both sides). (4). Remove/peel LED 90 degree mounting patches (240), ECM mounting patch (250), runway mounting patches (260, 270) and mounting patches (230). (5). Remove/peel fabric tape covering wires in transition areas. (6). Cut two lengths of thin cord, M11029-1 (Table 6005), 25 Ft. (7.6 m) long and tie onto the end of each LED harness at the runway end of the inflatable. (7). Slowly pull the LED harnesses through the wire guides starting at ECM patch on each side of slide, allowing the cord to remain in the wire guides. (8). Untie the cord from the LED harnesses and tie to the same end of the LED harnesses to be installed. (9). Pull each LED harness into wire guides. Allow the LED harnesses to enter the wire guides at the ECM location, pulling from the runway end of the inflatable. (10). When all LED housings are visible through the wire guide windows, remove cord from harness and discard. Reinstall LED mounting patches and ECM patches. (11). Reinstall fabric bias tape, M11849-1½ (Table 6005), in transition areas. (12). Stow excess conductor length into wire guide on body tube and install corner patches.

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(13). Route the LED harnesses from the outside edges of the girt through the wire guide toward center of the girt. (14). Connect LED harness female connectors to the male connectors on the electrical cable assembly. (15). Separate the girt halves and tie the electrical cable assembly tieoff cord to the cord loop.

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11. Individual Lamp Housing Replacement (Figures 6025 through 6027) (IPL Figure 3) (Pre S.B. A320 004-25-64 and Amendment #4) NOTE: *Individual replacement lamps, P/N A3-06-0761-007, A3-060761-008, A3-06-0195-102, and A3-06-0195-103 are no longer being manufactured. Entire lamp harness must be replaced. A. Lamp housing assemblies which fail to illuminate after system deployments, or testing shall be repaired per the following procedure. There is no limit to the number of lamp assemblies which may be replaced on any single lamp harness. B. To determine the replacement lamp housing part number, examine the lamp to be repaired and compare it with the illustrations in Figures 6025 and 6026. 2 1/8 In. (54 mm) A

B A

1 1/16 In. (27 mm) SECTION A-A

B

SECTION B-B

*A3-06-0195 -102 ASSEMBLY Replacement Lamp Assembly, Channel, without Shield, Tubular Lamp 2 1/8 In. (54 mm) A

B A

B

1 1/16 In. (27 mm) SECTION A-A

SHIELD

SECTION B-B

*A3-06-0195 -103 ASSEMBLY

Replacement Lamp Assembly, Channel, with Shield, Tubular Lamp

REPLACEMENT LAMPS FIGURE 6025

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LAMP

0.12 In. (3.0 mm)

0.12 In. (3.0 mm)

6.0 ± 0.5 In. (152.4 ± 12.7 mm)

6.0 ± 0.5 In. (152.4 ± 12.7 mm)

LAMP

A3-06-0761 -001 ASSEMBLY Replacement Lamp Assembly, Welded, without Porches, One T1 Lamp

A3-06-0761 -004 ASSEMBLY Replacement Lamp Assembly, Welded, without Porches, Two T1 Lamps

PORCH

0.12 In. (3.0 mm)

0.12 In. (3.0 mm)

6.0 ± 0.5 In. (152.4 ± 12.7 mm)

6.0 ± 0.5 In. (152.4 ± 12.7 mm)

A3-06-0761 -005 ASSEMBLY Replacement Lamp Assembly, Welded, with Porches, One T1 Lamp

A3-06-0761 -006 ASSEMBLY Replacement Lamp Assembly, Welded, with Porches, Two T1 Lamps

0.12 In. (3.0 mm)

0.12 In. (3.0 mm)

6.0 ± 0.5 In. (152.4 ± 12.7 mm)

6.0 ± 0.5 In. (152.4 ± 12.7 mm)

*A3-06-0761 -007 ASSEMBLY Replacement Lamp Assembly, Welded, with Porches, Two LEDs

*A3-06-0761 -008 ASSEMBLY Replacement Lamp Assembly, Welded, with Porches, One Tubular Lamp

REPLACEMENT LAMPS FIGURE 6026

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C. Replace Lamp Housing (Figure 6027) (1). Disconnect lamp harness (50A) from the electrical light cable connectors. (2). Remove fabric tape and lamp mounting patch (Table 6003) from approximately 9 In. (228.6 mm) on either side of the damaged lamp housing. CAUTION: PROTECT SYSTEM FABRIC FROM BEING BURNED BY SOLDERING IRON OR HOT SOLDER BY USING A NONABRASIVE SHIELD AND DAMP PAPER TOWEL BETWEEN SYSTEM AND LAMP HARNESS. (3). Use a small sharp knife (Table 6004) to carefully remove all heat shrink coverings on the existing lamp housing. See Figure 6027. NOTE: It is important to position replacement lamp housing in the same location as the existing housing. (4). Use an indelible black marker (Table 6004) to trace the outline of the ends of the lamp housing containing the damaged lamp. These outlines will be used to help locate the replacement lamp housing assembly. (5). Use a pair of slip lock pliers (Table 6004) to break the ultrasonic welds between the upper and lower housing halves. Separate using a flat head screwdriver. CAUTION: EXCESSIVE HEAT FROM SOLDERING IRON CAN DAMAGE FLAT CONDUCTOR. (6). Remove the lamp by desoldering. Use an appropriate solder remover (Table 6004), approximately 600°F (315.6°C), to eliminate any protruding solder. (7). Remove the reflector. (8). Overlay the replacement lamp housing assembly on the existing flat conductor, position the replacement lamp housing so that the black marker tracings are aligned with the new housing.

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(9). Mark the location of the exposed tin plated copper conductor of the replacement lamp housing on the existing flat conductor (four places). NOTE: Visually examine each tin plated copper conductor to verify that the mylar has been completely removed. (10). Using a soldering iron with a screwdriver or chisel tip (Table 6004) to carefully melt away the upper layer of mylar insulation for approximately 3/8 In. (9.5 mm). over each tin plated copper conductor on the existing flat conductor where marked. NOTE: Visually verify that the solder has not bridged or shorted the tin plated copper conductors. (11). Deposit a small amount of solder on each of the four exposed tin plated copper conductors on the existing flat conductor using a soldering iron with a conical soldering tip (Table 6004). (12). Position the replacement lamp housing assembly over the existing flat conductor, hold in position, and solder the replacement lamp housing assembly to the existing flat conductor using a conical soldering tip (Table 6004). NOTE: Assure that all solder flux has been removed from the solder joints, with alcohol, within one hour of the soldering operation. (13). Visually examine the solder joints for solder bridging, protrusions, dewetting, insufficient or excessive solder, solder droplets, solder balls or embedded flux. (14). Test lamp harness using a TU-14 or TS-420 Test Set (Table 1001) to assure proper solder joint. (15). Wrap the joints and the surrounding flat conductor with a minimum of three wraps of Mylar tape (Table 6004). The wrapping must extend a minimum of 1 In. (25.4 mm) past the centerline of the solder joints in each direction. (16). Retest the lighting system per instructions outlined in the Testing section. (17). Bond fabric tape and lamp mounting patch (Table 6003) to original area in accordance with the cementing instructions in Paragraphs 3.A.(3) through (11).

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1. HEAT SHRINK

EXISTING LAMP ASSEMBLY

MARK EDGE OF LAMP HOUSING ON FLAT CONDUCTOR, BOTH SIDES

HOUSING

REFLECTOR 2.

LAMP (PIGTAIL SHOWN) MARKINGS

SOLDER WICK (SOLDER REMOVAL MATERIAL)

SOLDERING IRON CONICAL TIP

REPLACEMENT LAMP ASSEMBLY

SOLDERING IRON CHISEL TIP 3.

SOLDER (TYPICAL)

REMOVE UPPER LAYER OF MYLAR MARK LOCATION FOR MYLAR REMOVAL

MARKINGS

EXISTING FLAT CABLE POSITION REPLACEMENT LAMP ASSEMBLY AND SOLDER TO EXISTING FLAT CONDUCTOR

EXISTING 4.

DEPOSIT SOLDER

5.

VISUALLY INSPECT SOLDER JOINTS TAPE (3 TURNS MIN.)

LAMP REPAIR SEQUENCE FIGURE 6027

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12. LED Lane Lighting Replacement (Post S.B. A320 004-25-64 and Amendment #4) A. Deflate unit to relieve tension on harnesses. B. Remove mounting patches from lane lighting and ECM. Remove 1.5 In. wide tape from ECM. C. Pull 4 to 6 In. (101.6 to 152.4 mm) of slack from the runway and girt ends of the lane lighting. D. Cut the wire leads 4 In. (101.6 mm) from the center of each end LED, keeping the 4 to 6 In. (101.6 to 152.4 mm) of slack outside the wire guides. E. Cut a 25 Ft. (7.6 m) length of thin cord (Table 6005) and tie onto the end of the lane lighting to be removed. F.

Slowly pull the LED lane lighting through the wire guides, allowing the cord to remain in the wire guides.

G. Untie the cord from the damaged lane lighting and tie to same end of the replacement lane lighting. Check that the 90° lighting is oriented correctly and will shine toward the lane. H. Pull the replacement lighting into the wire guides. I.

When all housings are visible through the wire guide windows, remove cord from the harness and discard.

J.

Splice the replacement lane lighting lead wires at the runway and girt ends. See Individual LED Housing Replacement section for splicing instructions.

K. Reinstall LED mounting patches, ECM mounting patch, and associated tape per the instructions in Paragraphs 3.A.(3) through (11).

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13. Individual LED Housing Replacement (Figure 6028) (Post S.B. A320 004-25-64 and Amendment #4) NOTE: For repair materials, see Table 6005. A. Tape down the wire leads to the slide surface on either side of the LED to be removed, approximately 6 In. (152.4 mm) from the center of the LED on both sides. B. Clip out the inoperable LED approximately 4 In. (101.6 mm) from the center of the LED, both sides (See Figure 6028, Step 1). C. Using the removed LED as a template, trim the wire leads of the replacement LED to be 2 In. (50.8 mm) longer than the removed LED on both sides. After initial trimming, cut back the white wire 2.5 In. (63.5 mm) on one side of the replacement LED, and cut back the blue wire 2.5 In. (63.5 mm) on the other side. Strip trimmed wire leads on the replacement LED back ¼ to 5/16 In. (6.4 to 7.9 mm) (See Figure 6028, Step 2). D. Place the trimmed LED centered and properly oriented over the repair area; mark and trim the harness wire leads to match the replacement LED, 4 places. Strip the trimmed wire leads back ¼ In. (6.4 mm) (See Figure 6028, Step 2). CAUTION: ENSURE TO MATCH COLOR (WHITE TO WHITE, BLUE TO BLUE). E. Pre-install one 1 In. (25.4 mm) piece of heat shrink tubing on the loose ends of the harness wire leads, 4 places (See Figure 6028, Step 3). NOTE: Accomplish Paragraphs 13.F and 13.G on one wire at a time. F.

Join the stripped wire leads from the harness and the replacement LED together, one wire at a time, overlapping inside the parallel splice. This is a fairly close fit; it is sometimes easier to partially insert one wire at each end of the splice and work the wires in together until the stripped ends are fully inside the splice connector. CAUTION: ENSURE TO MATCH COLOR (WHITE TO WHITE, BLUE TO BLUE).

G. Carefully, while ensuring that the wires are fully inside the splice, set the crimping tool with the tang opposite the braze line on the splice connector, centered on the splice, and set the crimp fully, until the ratchet mechanism releases the handle. Repeat Paragraphs 13.F and 13.G for the remaining three splices.

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H. Center all four heat shrink tubing pieces over the splices and heat shrink in place (See Figure 6028, Step 4).

DAMAGED LED HOUSING 1

CUT LEAD WIRES

2

CUT LEAD WIRES

APPROX. 6 In. (152.4 mm) ¼ In. (6.4 mm) (4 PLACES)

2.5 In. (63.5 mm)

HEAT SHRINK TUBING (4 PLACES) 3

¼ In. (6.4 mm) (4 PLACES)

2.5 In. (63.5 mm)

2.5 In. (63.5 mm)

HEAT SHRINK TUBING (4 PLACES)

PARALLEL SPLICE (4 PLACES)

4

2.5 In. (63.5 mm)

PARALLEL SPLICE/ HEAT SHRINK TUBING (INSTALLED, 4 PLACES)

INSTALLATION COMPLETE

LED REPAIR SEQUENCE FIGURE 6028

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14. Gage Viewing Port Replacement (Figure 6029) (IPL Figure 2) CAUTION: DO NOT DAMAGE DECORATIVE COVER. A. Remove old window by applying pressure to window from outside of decorative cover. B. Discard old window. C. With 50 grit sandpaper (Table 6003) remove old cement from around window opening (inside surface) of decorative cover. D. Sand mounting flange area of viewing window (70, 70A, 70B, 70C, 70D, 70E) using 50 grit sandpaper (Table 6003) to remove shine. NOTE: For a good bond, both surfaces must be roughened. E. Position the new viewing window on hard cover and trace around the perimeter. Remove window. NOTE: Follow manufacturer’s instructions for the application and cure time of urethane adhesive. F.

Apply urethane adhesive (Table 6003) within the area previously outlined and to the mating surface on the viewing window. CAUTION: THE VIEW PORT GAGE IS TO BE FREE OF ADHESIVE, VISUAL IMPERFECTIONS, AND MUST COVER THE COVER CUTOUT. NOTE: Pressure is important for a good bond.

G. Position the viewing window on the decorative cover and apply pressure and allow to cure per the urethane adhesive manufacturer’s instructions.

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WINDOW

SANDPAPER

MOUNTING FLANGE

WINDOW

HARD COVER

SANDPAPER

GAGE VIEWING PORT REPLACEMENT FIGURE 6029

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15. Packboard and Decorative Cover CAUTION: REPAIR AREA AND PARTS TO BE BONDED SHOULD BE CLEAN AND DRY TO ACHIEVE GOOD ADHESION. NOTE: Per S.B. 004-25-30, remove Velcro from decorative cover and packboard assemblies and replace with dual lock fastener P/N SJ3551. NOTE: Per S.B. A320 004-25-61, remove Velcro/dual lock fasteners from decorative cover and packboard assemblies and replace with stainless steel latch components. A. Repair Cracks (1). Using 80-120 grit sandpaper (Table 6003) roughen the surface by sanding the inside and outside surface area around the crack. CAUTION: REMOVE ALL FRACTURED MATERIAL ALONG CRACK. (2). Clean the sanded area, approximately 2 to 3 In. (50.8 to 76.2 mm) from the crack, on both sides of the packboard, and on decorative cover using methyl ethyl ketone (MEK) or ethyl acetate (Table 6001). NOTE: Allow approximately 1/16 In. (1.6 mm) gap at the crack or as necessary to provide proper alignment. (3). Use clamps to align the cracked portions of the packboard or decorative cover. WARNING: WEAR BUTYL RUBBER GLOVES (TABLE 6003) WHEN HANDLING RESIN TO PREVENT SICKNESS OR INJURY TO PERSONNEL. CAUTION: MIX THE RESIN PER THE MANUFACTURER’S INSTRUCTIONS. (4). Apply polyester resin to both surfaces around the crack. (5). Cut two pieces of fiberglass cloth (Table 6003) to overlap the crack by approximately 1.5 In. (38.1 mm). Soak the fiberglass cloth in the polyester resin. (6). Apply one piece of the soaked fiberglass cloth to the inside surface of the packboard or decorative cover and over the cracked area.

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(7). Apply another coat of resin on the fiberglass cloth to ensure a total adhesive bond. (8). Apply a second layer of fiberglass cloth, followed by a final application of polyester resin. (9). After curing, a light sanding of the outside surface may be required. (10). If desired, touch up repaired area using a compatible paint. (11). If replacement of floor seal is necessary, loosen screws to remove both adjacent plate nuts. (12). Remove previous floor seal, and cement following the basic instructions detailed in Paragraphs 3.A.(3) through (8). (13). Align new floor seal on cover exactly as previous one had been placed. (14). Re-attach both plate nuts by securing the screws.

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16. Optional Relocation of Lock Pin Stowage Pocket (Figure 6030) (Post S.B. 004-25-18) A. Cut stitching on existing lock pin stowage pocket and remove pocket from lacing cover. Remove all loose threads. B. With ball point pen and using new stowage pocket (P/N 61539-101) as a guide, mark location of stowage pocket on lacing cover. C. Using a soft cloth dampened with ethyl acetate (Table 6001) clean the underside of the new lock pin stowage pocket (P/N 61539-101) and the area on lacing cover to which pocket will be cemented. D. Apply three coats of urethane cement (Table 6001) to the underside of stowage pocket and to lacing cover per the general cementing instructions detailed in Paragraphs 3.A.(3) through (8). E. Mark “Modified per S.B. 004-25-18” in ¼ In. (6.4 mm) minimum height characters using contrasting color indelible ink adjacent to identification placard on girt assembly.

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REMOVE EXISTING POCKET

PACKED SLIDE

UNLACE SIDE FLAP

INSTALL LOCK PIN POCKET P/N 61539-101 .12 In. (3 mm)

1.25 In. (31.8 mm)

INSTALLATION OF LOCK PIN POCKET FIGURE 6030

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17. Removal of Lacing Cover Knots (Figure 6031) (Post S.B. 004-25-23) A. Using scissors (Table 6002) cut off the knots in cord M11029-2, which are located on the upper corners of the packboard. B. Identify slide evacuation system by marking “Mod per S.B. 004-25-23” in ¼ In. (6.4 mm) minimum height contrasting color ink adjacent to the identification placard on the lacing cover.

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CUT OFF KNOTS (BOTH SIDES)

KNOTS IN CORD (M11029-2)

LACING COVER

REMOVAL OF LACING COVER KNOTS FIGURE 6031

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18. Decorative Cover Seal Improvements (Per S.B. 004-25-28) (Figures 6032 and 6033) (IPL Figure 2) A. Remove Floor Seal NOTE: Per S.B. 004-25-28, remove floor seal from decorative cover and replace with new floor seal (160). (1). Remove the two nut plates (120) by removing screws (130) with a Phillips head screwdriver. CAUTION: REMOVE FLOOR SEAL WITHOUT DAMAGING THE DECORATIVE COVER. (2). Begin peeling back the old floor seal by carefully using a hook knife then grasp the edge with pliers and peel off and discard the old floor seal.

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DECORATIVE COVER FWD P/N D15358-103 AFT P/N D15359-103

REMOVE SCREWS (4 PLACES) REMOVE NUT PLATE (2 PLACES)

REMOVE OLD SEAL

REMOVE FLOOR SEAL FIGURE 6032

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B. Install Floor Seal (1). Wash the fabric and the decorative cover with a cloth (Table 6002) dampened in Ethyl Acetate (Table 6001). (2). Mark the center of both the new floor seal (160) and the decorative cover and scribe a line along the bottom edge of the cover, 1/8 In. (3.2 mm) from the edge. (3). Brush three coats of urethane cement (Table 6001) onto the fabric and decorative cover. Allow 15 minutes between coats. If water condensation occurs during cement drying, remove condensation by swabbing with a cloth (Table 6002) dampened in solvent (Table 6001). CAUTION: JOIN SURFACES IMMEDIATELY (WITHIN 60 SECONDS) AFTER ACTIVATING TO PREVENT INADEQUATE BOND. (4). Within one hour of cement application, dampen a clean cloth (Table 6002) in MEK (Table 6001). Wipe cemented surfaces to reactivate them. This prepares the surfaces for joining. (5). Immediately join the cemented surfaces at the previously scribed center line marks, with the seal turn back parallel with the line scribed along the edge of the decorative cover to the dimensions shown (Figure 6033). (6). The seal should be laid on gradually from the center to the edges to minimize the possibility of air bubbles being trapped beneath the seal. (7). Apply pressure with a spatula to eliminate entrapped air. (8). Use a soldering iron to burn plate screw holes, eight places, through the floor seal, using the existing holes in decorative cover as a guide. (9). Replace nut plates (120) and screws (130).

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A

A MARK CENTER LINE ON NEW FLOOR SEAL AND DECORATIVE COVER CEMENT COVER SEAL TURN BACK SEAL 0.125 TO 0.25 In. (3.2 TO 6.4 mm)

ALIGN SEAL WITH EDGE OF DECORATIVE COVER

VIEW A-A

BURN THROUGH HOLES (8 PLACES)

INSTALL FLOOR SEAL FIGURE 6033

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19. Decorative Cover Seal Improvement (Per S.B. A320 004-25-71 and Amendment #2) (Figures 6034 through 6036) (IPL Figure 2) NOTE: Cover gage window with masking tape during modification to prevent damage. A. If applicable, remove the two nut plates (120) by removing the screws (130) with a screwdriver, see Figure 6034. Set aside for re-use. CAUTION: USE CAUTION WHEN REMOVING THE FLOOR SEAL. DO NOT DAMAGE THE DECORATIVE COVER. B. Remove existing floor seal assembly from cover using acetone and scraping tool. C. Fold new floor seal (160A, 160B) to find center and mark center using pencil. Using a tape measure, locate interior cover lower edge center and mark. D. Place new floor seal (160A, 160B) on interior cover with floor seal hem located per Figures 6035 or 60036. This location is applicable for the entire lower perimeter of the decorative cover. Trace outer perimeter of seal on cover. E. Buff outer surface of new floor seal assembly in area to be cemented using Scotch Brite (Table 6003). F.

Abrade inner surface of decorative cover in area to be cemented using 80 grit sandpaper (Table 6003).

G. Clean cement areas of floor seal and decorative cover with Ethyl Acetate (Table 6001) prior to cementing. H. Apply cement (Table 6001) to cover and new floor seal following cementing instructions in the Repair section. I.

Activate cement and place new floor seal assembly in place starting at center of decorative cover inner surface.

J.

Allow cement to dry and trim new floor seal assembly edges following existing outboard contours of cover. NOTE: Apply a medium coat of cement (Table 6001) over a 1 In. (25.4 mm) area on the inside surface of floor seal over any stitches cut during trimming.

K. Burn holes in floor seal at nut plate locations using a hot soldering iron. L. If applicable, reinstall nut plates (120) using existing hardware (130). M. Remove masking tape from gage window.

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SCREWS NUT PLATE

DECORATIVE COVER

NUT PLATE TYPICAL BOTH SIDES (IF APPLICABLE)

FLOOR SEAL

REMOVE NUT PLATES AND FLOOR SEAL FIGURE 6034

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NUT PLATE TYPICAL BOTH SIDES (IF APPLICABLE)

FLOOR SEAL

DECORATIVE COVER

0.2 TO 0.1 In. (5.1 TO 2.5 mm) THIS DIMENSION APPLIES TO ENTIRE LOWER PERIMETER OF COVER.

A

FLOOR SEAL

SECTION A - A

A

FLOOR SEAL

BOND NEW FLOOR SEAL TO AFT DECORATIVE COVER FIGURE 6035

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DECORATIVE COVER DECORATIVE COVER

B 0.2 TO 0.1 In. (5.1 TO 2.5 mm) THIS DIMENSION APPLIES TO ENTIRE LOWER PERIMETER OF COVER.

FLOOR SEAL

SECTION B - B TRIM FLOOR SEAL TO EDGE

B

BOND NEW FLOOR SEAL TO FORWARD DECORATIVE COVER FIGURE 6036

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20. Release Mechanism Replacement (IPL Figure 4) A. Forward Door Only (E15366-Series; 62366-101, -103, -105) (Figures 6037 through 6039) CAUTION: WHEN REMOVING RIVETS DO NOT ENLARGE (ELONGATE) HOLES IN PACKBOARD. NOTE: Using a center punch, mark drill center location in center of rivet head. When rivets are to be removed, weaken the rivet head by drilling. Use a drill of the same size as the rivet. Drilling must be exact center and to the base of the head only. After drilling, break off the head with a pin punch and carefully drive out the shank. Removal of rivet heads with a cold chisel and hammer is not recommended because skin damage and distorted rivet holes will probably result. (1). Remove six rivets and six washers along lower edge of packboard using a #22 drill bit (0.157 In. diameter). (2). Remove four rivets joining support bracket and step bracket with a #30 drill bit (0.1285 In. diameter), two places each side of the packboard. (3). Remove four screws, MS24693-C52, and four self locking nuts, MS21083-C08, from center attachment of support bracket. (4). Slide existing release mechanism (380) out and discard.

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USING A #22 DRILL BIT REMOVE SIX RIVETS AND SIX WASHERS

REMOVE FOUR SELF LOCKING NUTS

STEP BRACKET (2 PLACES)

PACKBOARD REMOVE FOUR SCREWS REMOVE OLD RELEASE MECHANISM

USING A #30 DRILL BIT REMOVE FOUR RIVETS (TWO EACH SIDE)

RELEASE MECHANISM REPLACEMENT (FWD DOOR) FIGURE 6037

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(5). Insert new release mechanism (380) where the old was removed and align holes. (6). Re-install the four screws, MS24693-C52, and four self locking nuts, MS21083-C08, in previous locations. (7). Install six rivets, MS20426AD5-7, with six washers, NAS1169DD8, along lower edge of packboard. (8). Install four rivets, MS20470AD4-8 (two places each side of packboard) to join release mechanism and step brackets.

PACKBOARD (LOWER EDGE)

INSTALL NEW RELEASE MECHANISM

RELEASE MECHANISM REPLACEMENT (FWD DOOR) FIGURE 6038

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INSTALL RIVETS (MS20426AD5-7; 6 PLACES) AND WASHERS (NAS1169DD8; 6 PLACES) PACKBOARD

STEP BRACKET (2 PLACES)

RE-INSTALL LOCKING NUTS (MS21083C08; 4 PLACES)

RE-INSTALL SCREWS (MS24693C52; 4 PLACES)

INSTALL RIVETS (MS20470AD4-8; 4 PLACES, 2 EACH SIDE)

RELEASE MECHANISM REPLACEMENT (FWD DOOR) FIGURE 6039

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B. Aft Door Only (E15367-Series; 62370-101, -103, -105) (Figures 6040 through 6042) CAUTION: WHEN REMOVING RIVETS DO NOT ENLARGE (ELONGATE) HOLES IN PACKBOARD. NOTE: Using a center punch, mark drill center location in center of rivet head. When rivets are to be removed, weaken the rivet head by drilling. Use a drill of the same size as the rivet. Drilling must be exact center and to the base of the head only. After drilling, break off the head with a pin punch and carefully drive out the shank. Removal of rivet heads with a cold chisel and hammer is not recommended because skin damage and distorted rivet holes will probably result. (1). Remove six rivets and six washers along lower edge of packboard using a #22 drill bit (0.157 In. diameter). (2). Remove 12 rivets joining support bracket and mounting bracket with a #30 drill bit (0.1285 In. diameter), six places each side of the packboard. (3). Remove four screws, MS24693-C52, and four self locking nuts, MS21083-C08, from center attachment of support bracket. (4). Remove existing release mechanism (390) and discard.

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USING A #22 DRILL BIT, REMOVE SIX RIVETS AND SIX WASHERS

REMOVE FOUR SELF LOCKING NUTS

MOUNTING BRACKET (2 PLACES) PACKBOARD USING A #30 DRILL BIT, REMOVE 12 RIVETS (SIX EACH SIDE)

REMOVE FOUR SCREWS REMOVE OLD RELEASE MECHANISM

RELEASE MECHANISM REPLACEMENT (AFT DOOR) FIGURE 6040

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(5). Insert new release mechanism (390) where the old was removed and align holes. (6). Re-install the four screws, MS24693-C52, and four self locking nuts, MS21083-C08, in previous locations. (7). Install six rivets, MS20426B5-7, and six washers, NAS1169DD8, along lower edge of packboard. (8). Install 12 rivets, MS20470AD4-11 for E15367-Series, 62370-101, -103 packboards or MS20470AD4-8 for 62370-105 packboards, (six places each side of packboard) to join release mechanism and mounting brackets.

PACKBOARD (LOWER EDGE)

INSTALL NEW RELEASE MECHANISM

RELEASE MECHANISM REPLACEMENT (AFT DOOR) FIGURE 6041

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INSTALL RIVETS (MS20426B5-7) AND WASHERS (NAS1169DD8) (6 PLACES) PACKBOARD RE-INSTALL LOCKING NUTS (MS21083C08; 4 PLACES)

MOUNTING BRACKET (2 PLACES)

RE-INSTALL SCREWS (MS24693C52; 4 PLACES)

INSTALL RIVETS (MS20470AD4-8; 4 PLACES; 2 EACH SIDE)

RELEASE MECHANISM REPLACEMENT (AFT DOOR) FIGURE 6042

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21. Release Mechanism Replacement (Forward Door 62366-301 and Subs) (Figures 6043 through 6045) (IPL Figure 4A) CAUTION: WHEN REMOVING RIVETS DO NOT ENLARGE (ELONGATE) HOLES IN PACKBOARD. NOTE: Using a center punch, mark drill center location in center of rivet head. When rivets are to be removed, weaken the rivet head by drilling. Use a drill of the same size as the rivet. Drilling must be exact center and to the base of the head only. After drilling, break off the head with a pin punch and carefully drive out the shank. Removal of rivet heads with a cold chisel and hammer is not recommended because skin damage and distorted rivet holes will probably result. A. Remove six rivets (170A) and dimpled washers (160) along lower edge of packboard using a #22 drill bit (0.157 In. diameter). B. Remove four rivets (190) and dimpled washers (180) joining support bracket and step bracket with a #30 drill bit (0.1285 In. diameter), two places each side of the packboard. C. Slide existing release mechanism (70) out and discard.

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USING A #22 DRILL BIT REMOVE SIX RIVETS AND DIMPLED WASHERS

PACKBOARD USING A #30 DRILL BIT REMOVE FOUR RIVETS AND DIMPLED WASHERS (TWO EACH SIDE) REMOVE OLD RELEASE MECHANISM

RELEASE MECHANISM REPLACEMENT (FWD DOOR) FIGURE 6043

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D. Insert new release mechanism (70) where the old was removed and align holes. E. Install six rivets (170A) and six dimpled washers (160) along lower edge of packboard. F.

Install four rivets (190) and four dimpled washers (180) (two places each side of packboard) to join release mechanism to packboard.

PACKBOARD (LOWER EDGE)

INSTALL NEW RELEASE MECHANISM

RELEASE MECHANISM REPLACEMENT (FWD DOOR) FIGURE 6044

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INSTALL SIX RIVETS AND DIMPLED WASHERS

PACKBOARD RELEASE MECHANISM INSTALL FOUR RIVETS AND DIMPLED WASHERS (TWO EACH SIDE)

RELEASE MECHANISM REPLACEMENT (FWD DOOR) FIGURE 6045

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22. Release Mechanism Replacement (Aft Door 62370-301 and Subs) (Figures 6046 through 6048) (IPL Figure 4B) CAUTION: WHEN REMOVING RIVETS DO NOT ENLARGE (ELONGATE) HOLES IN PACKBOARD. NOTE: Using a center punch, mark drill center location in center of rivet head. When rivets are to be removed, weaken the rivet head by drilling. Use a drill of the same size as the rivet. Drilling must be exact center and to the base of the head only. After drilling, break off the head with a pin punch and carefully drive out the shank. Removal of rivet heads with a cold chisel and hammer is not recommended because skin damage and distorted rivet holes will probably result. A. Remove six rivets (150A) and dimpled washers (140) along lower edge of packboard using a #22 drill bit (0.157 In. diameter). B. Remove 12 rivets (160, 160A) joining support bracket, mounting bracket and back-up plates with a #30 drill bit (0.1285 In. diameter), six places each side of the packboard. C. Remove existing release mechanism (70) and discard.

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USING A #22 DRILL BIT, REMOVE SIX RIVETS AND DIMPLED WASHERS

MOUNTING BRACKET (2 PLACES) PACKBOARD

REMOVE OLD RELEASE MECHANISM

USING A #30 DRILL BIT, REMOVE 12 RIVETS AND FOUR BACK-UP PLATES (BOTH SIDES OF PACKBOARD)

RELEASE MECHANISM REPLACEMENT (AFT DOOR) FIGURE 6046

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D. Insert new release mechanism (70) where the old was removed and align holes. E. Install six rivets (150A) and six dimpled washers (140) along lower edge of packboard. F.

Install 12 rivets (160, 160A; six places each side of packboard) and four back-up plates (60), (two places each side of packboard) to join release mechanism and mounting brackets.

PACKBOARD (LOWER EDGE)

INSTALL NEW RELEASE MECHANISM

RELEASE MECHANISM REPLACEMENT (AFT DOOR) FIGURE 6047

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INSTALL SIX RIVETS AND DIMPLED WASHERS

MOUNTING BRACKET (2 PLACES) PACKBOARD

INSTALL NEW RELEASE MECHANISM

INSTALL SIX RIVETS AND TWO BACK-UP PLATES (BOTH SIDES OF PACKBOARD)

RELEASE MECHANISM REPLACEMENT (AFT DOOR) FIGURE 6048

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23. Lower Mounting Bracket Replacement (Figure 6049) CAUTION: WHEN REMOVING RIVETS DO NOT ENLARGE (ELONGATE) HOLES IN PACKBOARD. NOTE: Using a center punch, mark drill center location in center of rivet head. When rivets are to be removed, weaken the rivet head by drilling. Use a drill of the same size as the rivet. Drilling must be exact center and to the base of the head only. After drilling, break off the head with a pin punch and carefully drive out the shank. Removal of rivet heads with a cold chisel and hammer is not recommended because skin damage and distorted rivet holes will probably result. NOTE: It may be necessary to tension the bracket and release mechanism to align existing holes for the installation of countersunk head rivets. A clamp may be used to draw the step bracket against the packboard between sequence 2 and 3 in Figure 6049. CAUTION: WHEN PERFORMING RIVETING OPERATIONS ENSURE TO FOLLOW THE SEQUENCES SHOWN IN FIGURE 6049. A. Forward Door Only (62366-301 and Subs) (IPL Figure 4A) (1). Remove existing retaining rings and mounting pins from old mounting brackets for reuse on new mounting brackets. (2). Remove twelve rivets attaching each mounting bracket to packboard, six places each side, using a #30 (0.1285 in. diameter) drill bit. (3). Remove four rivets and four washers attaching each mounting bracket to release mechanism, two places each side, using a #30 (0.1285 in. diameter) drill bit. (4). Remove two countersunk screws attaching each mounting bracket to release mechanism, two places, using a #28 (0.1405 in. diameter) drill bit. (5). Replace mounting brackets and stiffener with new step brackets (90, 100, Pre S.B. A320 004-25-75 and Amendment #5; 90A, 100A, Post S.B. A320 004-25-75 and Amendment #5, Pre Amendment #7; 90B, Post Amendment #7).

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(6). Install twelve rivets (150), six each side, attaching each step bracket (90, 100, Pre S.B. A320 004-25-75 and Amendment #5; 90A, 100A, Post S.B. A320 004-25-75 and Amendment #5) to packboard. (7). Install four rivets (190, Pre S.B. A320 004-25-75 and Amendment #5; 190A, Post S.B. A320 004-25-75 and Amendment #5) and four washers (180), two each side, attaching each step bracket to release mechanism. (8). Reinstall existing retaining rings, mounting pins, and spacers (145, Post Amendment #7) from old mounting brackets onto new mounting brackets. B. Aft Doors (62370-301 and Subs) (IPL Figure 4B) (1). Remove existing retaining rings and mounting pins from old mounting brackets for reuse on new mounting brackets. (2). Remove twelve rivets attaching each mounting bracket to packboard, six places each side, using a #30 (0.1285 in. diameter) drill bit. (3). Replace mounting brackets with new mounting brackets (120A, 130A, Pre S.B. A320 004-25-78 and Amendment #5; 120B, 130B, Post S.B. A320 004-25-78 and Amendment #5, Pre Amendment #7; 130C, 130D, Post Amendment #7). (4). Install twelve rivets (160, 160A) attaching each mounting bracket to packboard, six places each side. (5). Reinstall existing retaining rings, mounting pins, and spacers (115, Post Amendment #6) from old mounting brackets onto new mounting brackets.

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RETAINING RINGS

MOUNTING PIN

SEQUENCE #1: INSTALL (3) RIVETS HERE, REPEAT FOR OTHER SIDE

SEQUENCE #2: INSTALL (3) RIVETS HERE, REPEAT FOR OTHER SIDE

SPACER (POST AMENDS. #6 AND #7)

MOUNTING BRACKET RIVETS (6 PLACES EACH SIDE)

SEQUENCE #3:

BACKUP PLATES (2 PLACES EACH SIDE) RIVETS AND DIMPLED WASHERS (FORWARD DOOR ONLY, 2 PLACES EACH SIDE)

(FORWARD DOORS ONLY) INSTALL (2) RIVETS AND (2) DIMPLED WASHERS HERE, REPEAT FOR OTHER SIDE

LOWER MOUNTING BRACKET REPLACEMENT LH SIDE SHOWN, RH SIDE OPPOSITE FIGURE 6049

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24. Girt Chafing Installation (Post S.B. 004-25-52) (Figures 6050 and 6051) A. Turn system upside down, with sliding surface facing down. B. Lay girt assembly out flat. C. Using Ethyl Acetate (Table 6001) wash the underside, yellow side of the chafing patch, 62553-17 (Table 6003) and the underside of the girt assembly. D. Using chafing patch, 62553-17, (Table 6003) as a template, and No. 2 soft lead pencil, trace around chafing to mark location on girt assembly. E. Measure in 1 In. (25.4 mm) from the marked line and mark another pencil line to establish a cement margin. F.

On underside of chafing patch measure in 1 In. (25.4 mm) from outer edge, see Figure 6050, and mark a pencil line to establish a cement margin on the chafing patch.

G. Bond chafing patch to the girt as shown in Figure 6051 following cementing instructions in Paragraphs 3.A.(2) through (11). H. Allow the system to air dry for a minimum of 4 hours before deflating and packing. I.

Lightly dust cemented area with talc or powdered soapstone (Table 6003).

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YELLOW SIDE OF CHAFING PATCH APPROXIMATELY 1 In. (25.4 mm)

CEMENT AREA

GIRT CHAFING INSTALLATION (POST S.B. 004-25-52) FIGURE 6050

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CHAFING PATCH, P/N 62553-17

C L OF GIRT

GIRT ASSEMBLY BOTTOM VIEW

GIRT CHAFING INSTALLATION (POST S.B. 004-25-52) FIGURE 6051

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25. Pawl Assembly Replacement (Forward Door 62366-Series; Aft Door 62370-Series) (IPL Figures 4A and 4B) (Figure 6052) A. Remove screws (77) from packboard release assembly; 4 places. B. Remove existing pawl assembly and replace with new pawl assembly (75). C. Apply adhesive threadlocker (Table 6003) to screws (77). D. Reinstall screws into packboard release assembly.

PACKBOARD RELEASE ASSEMBLY

PAWL ASSEMBLY

SCREWS (4 PLACES) (APPLY ADHESIVE THREADLOCKER PRIOR TO INSTALLATION)

PAWL ASSEMBLY REPLACEMENT FIGURE 6052

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26. Inflatable Slide Assembly Replacement NOTE: For inflatable slide assembly replacement, reference Service Bulletin A320 004-25-74 and S.I.L. 25-200. A. If a replacement inflatable assembly is required for retrofit into an existing evacuation system, the replacement inflatable assembly will use thermobonded seam construction (a fabric welding process) which supersedes the previously cemented seam construction. Thermobonded inflatable assemblies are completely interchangeable with the previously cemented inflatable assemblies. Form, fit, and function of the complete evacuation system are not affected and repairs can be made using existing CMM procedures. However, upon replacement, the system must be reidentified per S.B. A320 004-25-74 and re-packed per Folding Procedure P-11895 Rev. T or later.

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27. Corrosion Repair to Aluminum Components (IPL Figures 4, 4A, 4B) (Figure 6053) CAUTION: AVOID ENTRAPMENT OF CLEANING SOLUTION AND RINSE WATER BETWEEN THE COMPOSITE PACKBOARD AND ALUMINUM REAR SUPPORT. THIS MAY BE ACCOMPLISHED BY MAINTAINING A VERTICAL WORKING SURFACE. A. Clean oil and dirt from affected surfaces with cleaner in accordance with MIL-C-87936 Type 1, MIL-PRF-87937 Type II or Type IV, or equivalent. Use a mixing concentration of one (1) part compound, four (4) parts water. CAUTION: DO NOT ALLOW COMPOUND SOLUTION TO DRY BEFORE RINSING WITH RUNNING WATER SINCE POOR CLEANING MAY RESULT. B. Allow solution to remain on the affected surface for several minutes while agitating with a brush. Rinse thoroughly with water. C. After dry, inspect surfaces for presence of corrosion or traces of contamination, see Figure 6053. D. If no corrosion is evident, proceed to Paragraphs 27.G and 27.H for epoxy primer application. Proceed to Paragraph 27.E if corrosion is present. NOTE: In the case where corrosion is present directly adjacent to a cable guide hole, coinciding with a wear groove produced by contact between one of the tie bar cables and the rear support, verify the material in this area has not been reduced to less than 0.134 In. (3.4 mm) at either the front or rear faces of the rear support. If this limit is exceeded, the release mechanism must be replaced. See Figure 6053. Remove/blend all rough edges. E. Remove all traces of corrosion by mechanical method such as nonmetallic abrasive mat in accordance with MIL-A-9962, or number 400 aluminum oxide or silicon carbide grit abrasive paper cloth (Table 6003), or abrasive blasting with fine abrasives as appropriate.

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CAUTION: DO NOT USE ANY ABRASIVES OR ABRASIVE TOOLS CONTAINING STEEL. FAILURE TO ADEQUATELY CLEAN ALL RESIDUES WILL PERMIT CORROSION TO CONTINUE. F.

Re-clean surface as described in Paragraphs 27.A and 27.B and let dry.

G. Localized pitting may be repaired by filling with Devcon Aluminum Liquid F-2 (Table 6003). Follow manufacturer’s mixing and application/curing instructions. When cured, product may be sanded flush with surrounding surfaces using abrasive mat described in Paragraph 27.E. H. Remainder of abraded areas shall be given a pre-treatment with Alodine 1132 touch-up pen (Table 6003) in accordance with MIL-DTL81706. CAUTION: DO NOT APPLY EPOXY PRIMER TO ANY AREAS THAT MAY IMPEDE REQUIRED MOVEMENT OF COMPONENT PARTS. I.

After dry, paint repair areas or exposed areas of rear support per Figure 6053 using epoxy primer per AIMS 04-04-001 or equivalent alternative such as PRC-Desoto Superkoropon 515K011 or Deft 026N058 (Table 6003). Follow manufacturers mixing and application/curing instructions.

J.

Verify proper operation of any moving parts if they are part of the repair component (i/e/ release mechanism and pawl).

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PACKBOARD

EXPOSED AREAS OF REAR SUPPORT

ENSURE COVERAGE AROUND CUTOUT RADII

REAR SUPPORT

CABLE GUIDE HOLE, TYPICAL

PRIME TOP SURFACE AND FRONT EDGE

RELEASE MECHANISM SHOWN REMOVED FOR CLARITY 0.134 In. (3.4 mm) MINIMUM REMAINING

RELEASE MECHANISM REAR SUPPORT FIGURE 6053

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28. Electrical Cable Assembly Repair (Figure 6054) CAUTION: INSTALL APPLICABLE PROTECTIVE CAP TO PROTECT CONNECTOR PINS PRIOR TO REPAIR. A. Clean oil and dirt from affected surfaces with cleaner in accordance with MIL-C-87936 Type 1, MIL-PRF-87937 Type II or Type IV, or equivalent. Use a mixing concentration of one (1) part compound, four (4) parts water. CAUTION: DO NOT ALLOW COMPOUND SOLUTION TO DRY BEFORE RINSING WITH RUNNING WATER SINCE POOR CLEANING MAY RESULT. DO NOT IMMERSE THE CONNECTOR IN WATER. B. Allow solution to remain on the affected surface for several minutes while agitating with a brush. Rinse thoroughly with water. C. After dry, inspect for presence of corrosion, see Figure 6054. If no corrosion is evident, proceed to Paragraph 28.G for epoxy primer application. Proceed to Paragraph 28.D if corrosion is present. D. Remove all traces of corrosion by mechanical method such as nonmetallic abrasive mat in accordance with MIL-A-9962, or number 400 aluminum oxide or silicon carbide grit abrasive paper cloth or abrasive blasting with fine abrasives as appropriate. CAUTION: DO NOT USE ANY ABRASIVES OR ABRASIVE TOOLS CONTAINING STEEL. FAILURE TO ADEQUATELY CLEAN ALL RESIDUES WILL PERMIT CORROSION TO CONTINUE. E. Re-clean surface as described in Paragraphs 28.A and 28.B and let dry. F.

Remainder of abraded areas shall be given a pre-treatment with Alodine 1132 touch-up pen (Table 6003) in accordance with MIL-DTL81706.

G. After dry, paint exposed areas using epoxy primer per AIMS 04-04-001 or equivalent alternative such as PRC-Desoto Superkoropon 515K011 or Deft 026N058 (Table 6003). Follow manufacturers mixing and application/curing instructions. H. Following repair, ensure free rotation of connector sleeve.

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CONNECTOR

60040-101 CABLE SHOWN (65026-1, 67993-1, 70164-1 CABLES SIMILAR)

CONNECTOR SLEEVE CONNECTOR

BACK SHELL (60040-101 ONLY)

TYPICAL ELECTRICAL CABLE ASSEMBLY FIGURE 6054

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29. Cylinder Chock Assembly Replacement (Aft Door Packboard) (IPL Figures 4 and 4B) (Figure 6055) A. For 62370-101, -103, -301, -303 only (Pre Amendment #6): CAUTION: WHEN REMOVING RIVETS, DO NOT ENLARGE (ELONGATE) HOLES IN PACKBOARD. NOTE: Using a center punch, mark drill center location in center of rivet head. When rivets are to be removed, weaken the rivet head by drilling. Use a drill of the same size as the rivet. Drilling must be exact center and to the base of the head only. After drilling, break off the head with a pin punch and carefully drive out the shank. Due to the potential for packboard damage and distorted rivet holes, a cold chisel and hammer is not recommended. (1). Remove existing cylinder chock assembly (92, IPL Figure 4; 284, IPL Figure 4B) or broken rivets by removing rivets (93, IPL Figure 4; 286, IPL Figure 4B) and dimpled washers (94, IPL Figure 4; 288, IPL Figure 4B) using a #30 (0.1285 In. diameter) drill bit. Use caution to prevent enlarging or deforming the packboard holes. (2). Re-install existing or new cylinder chock assembly (92, IPL Figure 4; 284, IPL Figure 4B) using rivets (93, IPL Figure 4; 286, IPL Figure 4B) and dimpled washers (94, IPL Figure 4; 288, IPL Figure 4B). Should the existing holes in the packboard tray and chock assembly be slightly worn or deformed, the next higher diameter rivet (MS20426A5-8) may be used if necessary. (3). Apply one layer of green tape (Table 6003), followed by one layer of black tape (Table 6003), to top section and cylinder contact surface of the cylinder chock assembly.

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B. For 62370-105, -305 only (Post Amendment #6): (1). Remove existing cylinder chock assembly (92A, IPL Figure 4; 284A, IPL Figure 4B) by removing screws (94A, IPL Figure 4; 287, IPL Figure 4B) and nuts (94B, IPL Figure 4; 289, IPL Figure 4B). (2). Install new cylinder chock assembly (92A, IPL Figure 4; 284A, IPL Figure 4B) by installing screws (94A, IPL Figure 4; 287, IPL Figure 4B) and nuts (94B, IPL Figure 4; 289, IPL Figure 4B). (3). Apply one layer of green tape (Table 6003), followed by one layer of black tape (Table 6003), to top section and cylinder contact surface of the cylinder chock assembly.

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CYLINDER CHOCK ASSEMBLY

PACKBOARD

A

A

VIEW A-A

PACKBOARD

RIVETS/WASHERS (6 PLACES) (62370-101, -103, -301, -303 ONLY; PRE AMEND. #6)

SCREWS/NUTS (6 PLACES) (62370-105, -305 ONLY; POST AMEND. #6)

CYLINDER CHOCK ASSEMBLY REPLACEMENT FIGURE 6055

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30. Replacement of Aspirator Anti-Chafe Coating (Figure 6056) (IPL Figure 1) A. Remove loose pieces of black plastic coating from outlet end of aspirator. CAUTION: ALL SURFACES TO BE COATED MUST BE THOROUGHLY CLEANED. B. Wash the area of the aspirator (220, 220A, 225) to be coated with a clean, soft cloth dampened in isopropyl alcohol (Table 6001). C. Thoroughly dry the aspirator with a clean cloth or using compressed air. WARNING: FOLLOW MANUFACTURER’S INSTRUCTIONS WITH RESPECT TO HANDLING, PERSONAL PROTECTION, AND APPLICATION OF PRIMERS TO PREVENT INJURY TO PERSONNEL. CAUTION: FAILURE TO MASK INTERNAL COMPONENTS OF ASPIURATOR WHEN USING AN AEROSOL FORM OF PRIMER MAY DEGRADE ASPIRATOR PERFORMANCE DUE TO BLOCKED INTERNAL NOZZLE AND REDUCED FUNCTIONALITY OF THE INLET VALVE MECHANISMS. D. Apply Plasti Dip primer (Table 6003) to bottom edge of aspirator outlet in a band 0.75 In. (19 mm) wide on both inside and outside surfaces. (1). If F938 HP primer (Table 6003) is used, follow manufacturer’s instructions for application and allow to cure fro 20-30 minutes (or until dry to the touch). (2). If 41209-6 plasti-dip primer (Table 6003) in aerosol form is used, mask off aspirator internal components and other areas where primer will not be applied. Follow manufacturer’s instructions for application and cure time. CAUTION: DO NOT THIN PLASTIC COATING OR STIR VIGOROUSLY. E. Stir plastic coating (Table 6003) gently and slowly to avoid air entrapment. CAUTION: DO NOT USE AN ALUMINUM OR GALVANIZED CONTAINER FOR STORAGE OR AS A DIP PAN. NOTE: Immersion/withdrawal rate should be less than 1 In. (25.4 mm) every five seconds.

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F.

Holding the aspirator flapper valves open, immerse the aspirator slowly to the depth specified in Figure 6056. NOTE: Allow a minimum of 30 minutes between applications.

G. Immerse the aspirator slowly a second time to the depth specified in Figure 6056. NOTE: Two applications of coating requires 12 to 24 hours of cure time to dry. Temperature range for drying should be 60°F to 90°F (15.6°C to 32.2°C). H. Suspend aspirator to dry with the coated end pointing downward. I.

Check the coating thickness, see Figure 6056.

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A

A

SECTION A-A (60461-101, -107)

OUTLET END OF ASPIRATOR

SECTION A-A (66068-101)

0.5 ± 0.13 In. (12.7 ± 3.3 mm)

0.5 ± 0.13 In. (12.7 ± 3.3 mm)

PLASTIC COATING

PLASTIC COATING 0.14 ± 0.02 In. (3.5 ± 0.5 mm)

0.23 ± 0.03 In. (5.8 ± 0.8 mm)

APPLICATION OF COATING FIGURE 6056

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31. Replacement of Strip Reinforcement Under Girt Mooring Line Grommets (Figure 6057) A. Carefully remove the two existing mooring line grommets from girt (212, IPL Figure 1), avoiding damage to the girt fabric. B. With a blunt-edged knife, carefully peel off the fabric patch that holds the strip reinforcement in place on the underside of the upper girt panel. If stitching for the mooring line pocket goes through this fabric patch, leave the stitching in place and trim off the fabric patch around the stitched area. Retain patch as a pattern for a replacement patch. C. With a blunt-edged knife, carefully remove the existing strip reinforcement and discard. D. Using existing patch as a pattern, cut new reinforcement patch from M11480 girt fabric (Table 6003). Round off corners of new patch. Discard old patch. E. Place new strip reinforcement (214, IPL Figure 1), at previous strip reinforcement location, to match it up with existing girt grommet holes. Place new reinforcement patch, gray side facing outward, over Reinforcement Strip. Butt the edge of the patch to the edge of the existing girt crotch tape and center over strip reinforcement. Trim patch if necessary to align with girt edge and mooring line pocket stitching. F.

Mark outline of new patch on girt. Mark location of the girt grommet holes on the patch. Punch new grommet holes in patch.

G. Prepare strip reinforcement for cementing by wiping with Ethyl Acetate/ Acetone (Table 6001) and allowing it to dry. Prime with two coats of CONAP AD-1147C metal primer (Table 6003), with a minimum of onehalf hour drying time between coats. Allow to dry for a minimum of one hour after final coat of primer. Bake strip reinforcement at 160o F (71.1° C) for one-half hour to cure primer, then allow it to cool. H. Following procedures in Paragraphs 3.A.(3) through (5) of this section, align grommet holes and cement strip reinforcement to girt. I.

Following procedures in Paragraphs 3.A.(3) through (7) of this section, cement replacement reinforcement patch over strip reinforcement, lining up grommet holes and outline marks.

J.

Install replacement mooring line grommets per Paragraph 7.

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GIRT ASSEMBLY

STRIP REINFORCEMENT (60116-1)

MOORING LINE GROMMETS

MOORING LINE GROMMET STRIP REINFORCEMENT IDENTIFICATION FIGURE 6057

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32. Re-Bonding or Replacement of Rubber Pads on Packboards (IPL Figure 4) (Figures 6058 and 6059) A. Using an appropriate marker, outline the location of the existing pad (290A) to be bonded back into place or removed (the dimensions shown within Figure 6058 or 6059 can also be used to locate new pads). CAUTION: USE CARE WHEN REMOVING PADS FROM PACKBOARD AND PREPARING SURFACE FOR BONDING TO AVOID DAMAGE TO PACKBOARD SURFACE. B. Remove damaged pad from packboard with a sharp edged tool. C. Buff packboard surface with sandpaper (80-120 grit, Table 6003) to remove remnants of old adhesive and to provide a dull, slightly rough surface. D. Abrade the back of the replacement rubber pad with sandpaper (180 grit or finer, Table 6003) to obtain a dull, slightly rough surface (the top surface of the pad has a “skin”). E. Cleaned roughened surfaces of packboard and rubber pad with isopropyl alcohol (Table 6001) and allow surfaces to dry. F.

Following manufacturer’s instructions, apply either 3M Scotch Weld DP-190G epoxy adhesive, 3M Scotch Weld DP-110T epoxy adhesive, 3M Scotch Weld EC-7210 epoxy adhesive, 3M Scotch Weld 2216 B/A epoxy adhesive, or M11055 Style P (Table 6003) to the contact area between the pad and the packboard.

G. Bond pad to packboard and apply adequate clamping force to secure pad in place. Allow bond to cure in accordance with manufacturer’s recommendations.

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SKIN (SMOOTH SURFACE) THIS SIDE (TYP)

6.0 In. (152.4 mm)

2.5 In. (63.5 mm) (TYP)

10.5 mm (266.7 mm)

3.0 In. (76.2 mm) (REF)

RUBBER PADS

PACKBOARD RUBBER PADS - FORWARD DOOR PACKBOARD FIGURE 6058

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SKIN (SMOOTH SURFACE) THIS SIDE (TYP)

5.0 In. (127.0 mm)

3.8 In. (96.5 mm) (TYP)

10.2 mm (259.1 mm)

3.0 In. (76.2 mm) (REF)

RUBBER PADS

PACKBOARD RUBBER PADS - AFT DOOR PACKBOARD FIGURE 6059

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33. Replacement or Reattachment of Packboard Mounting Hole Reinforcement Plate on 62366-Series and 62370-Series Packboards A. If reinforcement plate B15481-3, as shown in Figure 6060, is worn or has lost its adhesion to the packboard, carefully pry the reinforcement plate completely from the packboard. Follow instructions below for the installation of a replacement plate. CAUTION: IF PACKBOARD IS CRACKED OR DAMAGED IN THE HOLE AREA, THE PACKBOARD TRAY MUST BE REPLACED. B. Remove traces of old adhesive from packboard surface around mounting hole using mechanical means (such as sanding). Clean sanded area with isoproply alcohol (Table 6001). C. If reinforcement plate is to be reused, remove traces of old adhesive from surface to be bonded using mechanical means (such as sanding). Clean sanded area with isopropyl alcohol (Table 6001) and overcoat with chemical conversion coating (such as Alodine 1132 Touch-Up Pen (Table 6003). D. It a new reinforcement plate (Table 6003) is to be installed, clean bonding surface of the plate with isopropyl alcohol (Table 6001). E. Bond reinforcement plate to packboard using either 3M Scotch Weld Epoxy Adhesive DP 190 Gray (Table 6003) or 3M Scotch Weld Epoxy Adhesive DP-110 Translucent (Table 6003). The plate must be centered around the mounting hole and perpendicular to the mounting hole centerline. Final plate height must be within the range shown in Figure 6060. Follow manufacturers instructions for epoxy application and cure. F.

If any packboard composite fibers remain exposed in the sanded area, seal the exposed area with epoxy.

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REINFORCEMENT PLATE B15481-3 CEMENTED OVER PACKBOARD MOUNTING HOLES

FINAL HEIGHT OF PLATE MUST BE WITHIN NOTED RANGE 0.30 ± 0.04 In. PLATE B15481-3 PACKBOARD

X X X X X X X EPOXY ADHESIVE DP-190 GREY OR DP-110 TRANSLUCENT

MOUNTING HOLE REINFORCEMENT PLATES FIGURE 6060

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34. Replacement of a Torn or Damaged Maintenance Release Record Pocket on the Lacing Cover CAUTION: TO PREVENT CEMENT FROM SEEPING THROUGH STITCHES AND BONDING WITH INFLATABLE FABRIC, THIS REPAIR SHOULD BE PERFORMED WITH THE PACKBOARD/LACING COVER REMOVED FROM THE SLIDE PACK. A. Note location and orientation of existing pocket. Reference Figure 6061. B. Carefully remove existing pocket by trimming away the stitching around the edges of the pocket. Remove and discard pocket and stitching threads. C. Cement new pocket B31544-101 (Table 6003) in approximately same location and orientation, using M11628 cement (Table 6001). Follow the general cement instructions detailed in Paragraphs 3.A.(4) through (9).

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POCKET FOR MAINTENANCE RELEASE RECORD (LOCATION MAY VARY)

MAINTENANCE RELEASE RECORD FIGURE 6061

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35. Replacement of Non-Airholding Accessories and System Components A. Accessories and system components that are attached to the slide assembly (but are not required to maintain evacuation slide pressure) may be replaced, if they are identified by part number in the CMM Repair Materials Table or the IPL. These parts are required for functional use of the slide assembly, but they are not part of the airholding structure of the slide assembly. Regardless of the original component attachment method (i.e. cement or welding processes), cement (Table 6001) will be used for field replacement of original components. The following steps provided the general procedure that should be followed when replacing these accessories and components. NOTE: These procedures may be performed with the unit deflated or inflated to normal operating pressure. B. If necessary, clean the repair area using the materials and procedures listed in the Cleaning section of this CMM. Adhere to all listed CAUTIONs and WARNINGs. C. Using a dull pencil, outline the existing attachment base or patch to mark the replacement location on the slide assembly. Note any pertinent details with respect to the orientation of the accessory that will be replaced. Note use of reflective coating compound on, or surrounding, the attachment base or patch. CAUTION: USE CARE WHEN REMOVING DAMAGED ACCESSORIES TO AVOID PUNCTURING, TEARING, OR OTHERWISE DAMAGING THE UNDERLYING FABRIC STRUCTURE. D. Using a spatula (Table 6002) or a tool with a flat, dull edge, carefully work along the edges of the attachment base or patch to lift and peel away the damaged accessory or component. CAUTION: WHEN WORKING NEAR SEAMS, PATCHES, OR OTHER COMPONENTS THAT HAVE BEEN INSTALLED USING WELDING METHODS, USE EXTREME CARE WITH SOLVENTS. DO NOT AGGRESSIVELY STRESS OR PULL ON THESE WELDED BONDS WHEN SOLVENTS ARE IN CLOSE PROXIMITY. SOLVENTS WILL SOFTEN AND DEGRADE THESE BONDS.

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CAUTION: WHEN WASHING THE TUBE FABRIC, DO NOT ALLOW EXCESS SOLVENT TO COLLECT AT THE EDGES OF SEAMS. DO NOT APPLY SOLVENT TO DECALS OR STENCIL MARKINGS (WHENEVER POSSIBLE) SINCE THEY CAN BE REMOVED BY THE SOLVENT. IF STENCIL MARKINGS NEED TO BE REPLACED, USE THE STENCIL INK LISTED IN TABLE 6003. E. Thoroughly wash the fabric around the repair area and the underside of the attachment base or patch with a cloth (Table 6002) dampened in solvent (Table 6001). Do not damage the fabric or existing intact bonds with aggressive rubbing. Remove any reflective coating compound around repair area to provide a clean, minimum ½ In. (12.7 mm) wide cement margin. CAUTION: DISCARD UNUSED CEMENT 4 HOURS (POT LIFE) AFTER MIXING. NOTE: The cement line must be even and uniform to within ½ In. (12.7 mm) beyond the edge of repair. F.

Brush three coats of cement (Table 6001) around the area for the new attachment base or patch and the underside of the base or patch; cover an area slightly larger than the base or patch. Apply cement in medium, even coats. Allow 15 minutes of drying time between coats. Remove effects of condensation (white areas on cement) by swabbing with a cloth (Table 6002) lightly dampened in solvent (Table 6001). CAUTION: DO NOT EXCEED ONE HOUR BETWEEN CEMENT APPLICATION AND JOINING OF SURFACE. APPLY A FOURTH COAT TO SURFACES IF TIME IS EXCEEDED.

G. Within one hour after cement application, dampen a clean cloth (Table 6002) with activating agent (Table 6001). Wipe cemented surfaces to make them tacky and ready for joining. CAUTION: JOIN SURFACES IMMEDIATELY (WITHIN 60 SECONDS) AFTER ACTIVATING TO MAXIMIZE BOND. NOTE: Fabric weave on patch and tube fabric do not have to be in alignment. H. Immediately join the cemented patch to the cemented tube fabric at same location and orientation as the original item. I.

The patch should be laid on gradually from the center to the edges to minimize the possibility of air bubbles being trapped beneath the patch.

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COMPONENT MAINTENANCE MANUAL D31516 D31517

NOTE: Pressure is important for a good bond. J.

Apply pressure evenly with a spatula (Table 6002) to eliminate entrapped air bubbles and wrinkles to ensure firm attachment.

K. When all wrinkles and air bubbles are eliminated, uniformly roll the joined areas using a hand roller (Table 6002). L. Allow cement to cure for a minimum of four hours. M. Perform Overpressure and Leakage Testing of the slide assembly, using the procedures for Inflatable Integrity Testing in the Testing section of this CMM, if the replacement part is cemented to the airholding structure of the slide assembly. Replacement parts cemented to nonairholding areas (girts, floors, etc.) do not require these tests. N. Reapply reflective coating compound (Table 6003) as needed using the materials and procedures outlined in Paragraph 5 of the CMM Repair section. Reflective coating compound should be applied over the cemented repair area in addition to the same outlying area as the original installation. O. Lightly apply soapstone or talc (Table 6003) to repair area to minimize any residual tackiness.

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COMPONENT MAINTENANCE MANUAL D31516 D31517

TABLE OF CONTENTS ASSEMBLY Page 1. Assembly Materials/Equipment

7002

2. Preparatory Safety Instructions

7003

3. Aspirator Pressure Test Valve Assembly

7004

4. Aspirator Installation

7006

5. Hook Knife Installation

7010

6. Hose Installation

7011

7. Re-Entry Strap Attachment to Tube

7012

8. Lacing Cover Assembly

7014

9. Slide Folding

7017

10. Storage Instructions

7017

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1. Assembly Materials/Equipment (Table 7001) NOTE: Drawings of equipment/tools manufactured by Air Cruisers are available from Air Cruisers upon request. NOTE: Equivalent substitutes may be used.  ITEM/DESCRIPTION

QUANTITY

SOURCE

Tape, Black Fire Retardant 1.0 In. (25.4 mm) wide M12397-1 (Reference S.I.L. 25-252)

As Required

Air Cruisers V70167

Tape, Green 1.0 In. (25.4 mm) wide PPP-T-60-1

As Required

Commercially Provides chafe proAvailable tection from metal fittings.

Talc or Powdered Soapstone

As Required

Commercially Prevents joining of Available areas of exposed cement, reflective coating compound, or stencil ink.

Cord M11029-1 60 In. (1524 mm)

As Required

Thread and Detent Lubricant McLube 1190

As Required

McGee Threaded fitting lubriIndustries, Inc. cant. V04672

1

Rus Industries Installs/removes valve Inc. core from pressure V8S111 or test valve assemblies. Commercially Available

Tool - Valve Core 6914V-SD (or equivalent Schrader-style valve core extractor tool)

Air Cruisers V70167

USE Provides fittings with fire retardancy.

Used for hook knife installation.

ASSEMBLY MATERIALS/EQUIPMENT TABLE 7001 (SHEET 1 OF 2)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE

Pipe Thread Sealing Compound No. 2 PLS2*

As Required

Federal Process Corp. V3CKH7

Prevents leakage from pipe threaded fittings.

Nickel Coated Teflon Tape M12243* ½ In. (12.7 mm) wide

As Required

Air Cruisers V70167

Prevents leakage from pipe threaded fittings.

Teflon Tape AA-58092-2-1* ¼ In. (6.4 mm) wide

As Required

Commercially Prevents leakage Available from pipe threaded fittings.

*Alternatives for aspirator pressure test valve installation only. ASSEMBLY MATERIALS/EQUIPMENT TABLE 7001 (SHEET 2 OF 2)

2. Preparatory Safety Instructions WARNING: WHEN USING SOLVENTS, CEMENTS, OR OTHER CHEMICAL BASED PRODUCTS, REFER TO THE APPLICABLE MATERIAL SAFETY DATA SHEET (MSDS) FOR SPECIFIC GUIDELINES ON PROPER PERSONAL PROTECTIVE EQUIPMENT, STORAGE, HANDLING, AND VENTILATION REQUIREMENTS TO PREVENT SICKNESS OR INJURY TO PERSONNEL. WARNING: USE EYE, FACE, AND EAR PROTECTION WHEN USING HIGH PRESSURE AIR TO PROTECT PERSONNEL FROM POSSIBLE INJURY.

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3. Aspirator Pressure Test Valve Assembly (Figure 7001) (IPL Figure 1) A. Apply PLS2 sealing compound or Teflon tape (Table 7001) to threads on valve body/base. If Teflon tape is used, apply as follows: (1). Thoroughly clean and degrease male and female threads assuring the removal of all previously applied anti-seize compound or tape. CAUTION: IN NO CASE WILL THE TAPE BE PERMITTED TO EXTEND BEYOND THE FIRST THREAD. NOTE: Apply tension on tape while wrapping. (2). Wrap tape tightly in direction of the thread spiral of the male pipe thread beginning with the first thread. (3). Using care not to contaminate tape, encircle the threads and join together with a very slight overlap, not more than half of the tape width. (4). Press tightly on tape. Cut tape using scissors. Ensure tape is tight and remains at the first thread of fitting. Loose ends are not permitted. Pipe thread is now ready for joining. B. If removal of Teflon tape is necessary, hold valve at such an angle as to ensure that any loose Teflon tape fragments cannot fall into valve or adjacent components. C. Install valve body/base into inlet fitting on aspirator. Tighten per Table 8001. D. Install the pressure test valve core into valve body/base using valve core tool (Table 7001). E. Engage shoulder of pressure test valve core and hand tighten. F.

Install cap onto pressure test valve, hand tight.

G. Install tube (238) onto pressure test valve.

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COMPONENT MAINTENANCE MANUAL D31516 D31517

PRESSURE TEST VALVE CORE

VALVE CORE TOOL

ASPIRATOR

INLET FITTING SEALING COMPOUND OR TEFLON TAPE PRESSURE TEST VALVE

TUBE

PRESSURE TEST VALVE CORE CAP

PRESSURE TEST VALVE ASSEMBLY FIGURE 7001

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4. Aspirator Installation (Figures 7002 through 7005) (IPL Figure 1) CAUTION: DO NOT DAMAGE MOUNTING FLANGE SEALING SURFACE OF MOUNTING BLISTER. NOTE: Pour approximately two tablespoons of talc or powdered soapstone (Table 7001) into mounting blister opening before installing aspirator. A. Carefully insert aspirator (225) into mounting blister. Engage mounting lip on aspirator in annular groove, inside blister rubber seal.

MOUNTING BLISTER

ASPIRATOR MOUNTING LIP ANNULAR GROOVE SOAPSTONE

ASPIRATOR INSTALLATION FIGURE 7002

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NOTE: Wipe flapper support ring (inside) of aspirator with a clean, wet cloth to remove any foreign substance. B. Orient the aspirator (225) so that the inlet fitting is at a 4 o’clock position as viewed when facing the aspirator.

ASPIRATOR

FLAPPER SUPPORT RING

INLET FITTING

ASPIRATOR ALIGNMENT FIGURE 7003

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C. Install worm drive clamp (240) in the annular groove in the rubber seal; center the clamp screw under centerline of inlet fitting. Tighten screw, torque per Table 8001.

MOUNTING BLISTER

CLAMP SCREW

ASPIRATOR

WORM DRIVE CLAMP INLET FITTING

MOUNTING LIP

ANNULAR GROOVE

INLET FITTING

CLAMP SCREW

INSTALL WORM DRIVE CLAMP FIGURE 7004

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COMPONENT MAINTENANCE MANUAL D31516 D31517

D. Wrap worm drive clamp screw with three layers of green tape (Table 7001), overlap 1 In. (25.4 mm) on either side of clamp screw. Wrap entire worm drive clamp (240) with three layers of black tape (Table 7001).

INLET FITTING

CLAMP SCREW HOUSING

THREE LAYERS OF GREEN TAPE

WORM DRIVE CLAMP EXTEND 1 In. (25.4 mm) BOTH SIDES

THREE LAYERS OF BLACK TAPE

ASPIRATOR INSTALLATION FIGURE 7005

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COMPONENT MAINTENANCE MANUAL D31516 D31517

5. Hook Knife Installation (Figure 7006) (IPL Figure 1) A. Attach one end of cord M11029-1 (Table 7001), 60 In. (1524 mm), through cutout on back of sheath (70, IPL Figure 3). Tie off with bowline knot and overhand knot. B. Tie the other end of cord to handle of knife (250) as shown in Figure 7006. Tie off with bowline knot and overhand knot. C. Fake excess of cord and install into Velcro pocket. D. Insert knife into sheath and join Velcro fasteners.

BOWLINE KNOT AND OVERHAND KNOT KNIFE

CORD

SHEATH

BOWLINE KNOT OVERHAND KNOT POCKET

BOWLINE KNOT AND OVERHAND KNOT

VELCRO FASTENER

VELCRO FASTENER

HOOK KNIFE INSTALLATION FIGURE 7006

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6. Hose Installation (Figure 7007) (IPL Figure 1) CAUTION: ROUTE HOSE ASSEMBLY THROUGH HOSE RETAINER ADJACENT ASPIRATOR MOUNTING BLISTER (S/N 1400 AND SUBS). A. Coat the first three threads of the aspirator inlet fitting with McLube 1190 (Table 7001). B. Install hose assembly (50, 50A, 50B, 50C) to inlet fitting and torque per Table 8001. CAUTION: ENSURE TAPE DOES NOT IMPEDE SWIVEL ACTION OF HOSE. C. Wrap edges of aspirator inlet fitting and hose nut with three layers of green tape (Table 7001). Over wrap with two layers of black tape (Table 7001).

ASPIRATOR

INLET FITTING HOSE ASSEMBLY

TAPE

HOSE TO ASPIRATOR INSTALLATION FIGURE 7007

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COMPONENT MAINTENANCE MANUAL D31516 D31517

7. Re-Entry Strap Attachment to Tube (Figure 7008) (IPL Figure 3) (Configurations D31516-103, -107, -111, 311 and D31517-103, -107, -111, and -311 only, or modified per S.B. 004-25-57) A. Attach re-entry strap (120) by engaging snaps and Velcro fasteners along the right hand side of tube. B. Ensure that Velcro is securely attached and properly aligned on the tube. NOTE: Strap will not function properly if twisted.

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RE-ENTRY STRAP

RE-ENTRY STRAP

ENGAGE SNAP FASTENERS

SLIDE TUBE ASSEMBLY

ENGAGE VELCRO FASTENERS

RE-ENTRY STRAP ATTACHMENT FIGURE 7008

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8. Lacing Cover Assembly (Figures 7009 and 7010) (IPL Figure 1) NOTE: Lacing cover assembly (P/N D31882-105; Post S.B. 004-2547) allows the removal of the tie bar assembly for replacement as well as replacing individual release cables. Pre S.B. 004-2547 the lacing cover assembly (P/N D31882-101 or D31882103) does not allow this option. A. Install release cables (34), six places, into tube (35) by passing smaller ball shank end of cable first through larger hole in tube then through smaller hole in tube. B. Slide spacer (33) into tube. CAUTION: WHEN INSTALLING ROLL PIN BE CAREFUL NOT TO DEFORM TUBE. C. Install roll pins (32), two places, into hole at each end of tube. Using punch pin and hammer, install roll pins flush with tube.

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COMPONENT MAINTENANCE MANUAL D31516 D31517

SMALLER BALL SHANK END LARGER HOLE RELEASE CABLE (6 PLACES)

SMALLER HOLE

TUBE

TUBE

ROLL PIN (2 PLACES)

HOLE AT TUBE END

SPACER

TIE BAR ASSEMBLY

TIE BAR ASSEMBLY FIGURE 7009

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D. Install tie bar assembly into sleeve of lacing cover (30B) and route release cables (34) through holes in lacing cover. E. Secure tie bar assembly by fastening Velcro fasteners (two places) on the inside of lacing cover sleeve.

VELCRO FASTENERS

LACING COVER

TIE BAR ASSEMBLY

SLEEVE

LACING COVER ASSEMBLY FIGURE 7010

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COMPONENT MAINTENANCE MANUAL D31516 D31517

9. Slide Folding A. Use Folding Procedure P-11895 (Appendix 1) for folding slide.

10. Storage Instructions A. Store the system in a cool, dry location in original shipping container or equivalent protective container, secured with banders. Store separate components in clean protective containers. Avoid storage of the system and individual components in direct sunlight. Extended storage outside of the following conditions is not recommended.

RECOMMENDED STORAGE CONDITIONS DURATION

COMMENTS TEMPERATURE RANGE

Up to 30 days either on aircraft or in storage

40° to 130°F (4.4° to 54°C)

HUMIDITY <70%

These recommended temperature ranges may be exceeded on a temporary basis for no more Remove from aircraft after 30 days and store in a than 48 consecutive hours. location under controlled environmental conditions. However, the maximum storage temperatures shall not exceed After 31 days 40° to 90°F <60% the range of -67° to 185°F (-55° in storage (4.4° to 32°C) to 85°C). Long term storage under conditions outside of recommended limits may affect the longevity and expected performance of the evacuation system. Consequently, maintenance of evacuation systems exposed to storage conditions outside of the recommended limits should include additional tests and inspections required of older evacuation systems as listed within this CMM.

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NOTE: Storage outside of allowable conditions may activate pressure relief devices (Frangible Discs and/or Fusible Plugs if so equipped). B. A periodic check of inflation assembly pressure is recommended, particularly when equipment is subject to extremes of permissible storage conditions. WARNING: RESERVOIRS ARE FULLY CHARGED. HANDLE WITH CARE TO PROTECT PERSONNEL FROM POSSIBLE INJURY. C. During storage, the system should be handled with extreme care so as not to chafe, cut, or otherwise damage the fabric. D. For shipment, pack the folded system in the original shipping container or equivalent in accordance with best commercial shipping practices. Observe all Department of Transportation (DOT, U. S. A.) recommendations for shipment of charged gas reservoirs.

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TABLE OF CONTENTS FITS AND CLEARANCES Page 1. Torque Wrench Instructions

8002

2. Torque Limits

8002

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COMPONENT MAINTENANCE MANUAL D31516 D31517

1. Torque Wrench Instructions CAUTION: DO NOT EXCEED TORQUE VALUE NOTED. IF MAXIMUM TORQUE IS EXCEEDED, THREAD COULD BE DAMAGED AND/OR SEALING SURFACES DISTORTED. A. Torque wrenches must be calibrated at frequent intervals using weights and a measured lever arm to preclude inaccuracies due to mishandling or considerable usage. Do not check one wrench against another.

2. Torque Limits

ITEM/DESCRIPTION Hose Assembly to Aspirator

TORQUE MINIMUM

TORQUE MAXIMUM

230 In. Lb. 19.2 Ft. Lb. (26.0 N-m)

250 In. Lb. 20.8 Ft. Lb. (28.1 N-m)

Outlet Port Plug

Hand tight.

Worm Drive Clamp Screw

28 In. Lb. 2.3 Ft. Lb. (3.2 N-m)

32 In. Lb. 2.7 Ft. Lb. (3.6 N-m)

Pressure Test Valve Body/Base to Aspirator Inlet Fitting

2½ turns beyond hand tight.

Cylinder Chock Assembly Screws (62370-105, -305 only, Post Amendment #6)

9.0 In. Lb. 0.8 Ft. Lb. (1.0 N-m)

11.0 In. Lb. 0.9 Ft. Lb. (1.2 N-m)

TABLE OF TORQUE LIMITS TABLE 8001

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COMPONENT MAINTENANCE MANUAL D31516 D31517

TABLE OF CONTENTS SPECIAL TOOLS, FIXTURES, AND EQUIPMENT Page 1. General Information

9002

2. Special Tools, Fixtures, and Equipment

9002

3. Special Tools, Fixtures, and Equipment Illustrated

9009

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COMPONENT MAINTENANCE MANUAL D31516 D31517

1. General Information A. The tools, fixtures, and equipment listed in Table 9001 and shown in Figures 9001 through 9008 are recommended for use during Testing, Disassembly, Cleaning, Repair, and Assembly.

2. Special Tools, Fixtures, and Equipment (Table 9001) NOTE: Drawings of equipment/tools manufactured by Air Cruisers are available from Air Cruisers upon request. NOTE: Equivalent substitutes may be used.  ITEM/DESCRIPTION

QUANTITY

SOURCE

USE (SECTION)

Tool - Adapter, Pressure Test Valve C37099-103

1

Air Cruisers V70167

Connects manometer/ pressure gage to pressure test valve for inflatable assembly pressure reading. (Testing)

Adapter/Cable Assembly, Electric 60159-101, 65037-1, or 69525-1

1

Air Cruisers V70167

Used with TU-12, TU-14, or TS-420 for lamp/LED harness amperage verification. (Testing)

Tool - Valve Core 6914V-SD (or equivalent Schrader-style valve core extractor tool)

1

Rus Industries Inc. V8S111 or Commercially Available

Installs/removes valve core from pressure test valve assemblies. (Disassembly, Assembly)

Soldering Iron 600°-800° F (315.6°-426.7°C) Heat Range (Pre S.B. A320 004-25-64 and Amendment #4)

1

Commercially Heats solder for applicaAvailable tion. (Repair)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT TABLE 9001 (SHEET 1 OF 7)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE (SECTION)

Soldering Iron Tip Screwdriver or Chisel Tip (Pre S.B. A320 004-25-64 and Amendment #4)

1

Commercially Melts mylar insulation. Available (Repair)

Soldering Iron Tip Conical or Pencil Tip (Pre S.B. A320 004-25-64 and Amendment #4)

1

Commercially Applies solder. (Repair) Available

Desoldering Bulb Vacuum Action, Teflon Tip (Pre S.B. A320 004-25-64 and Amendment #4)

1

Commercially Removes solder. (Repair) Available

Shield, Wood 1/4 x 12 x 12 In. (6.35 x 304.8 x 304.8 mm) (Approximate dimensions) (Pre S.B. A320 004-25-64 and Amendment #4)

1

Commercially Protects fabric from solAvailable dering iron. (Repair)

Bottle, Dispensing, with spout or pump (Pre S.B. A320 004-25-64 and Amendment #4)

1

Commercially Solvent/solution disAvailable penser. (Repair)

Hand Roller/Caster Wheel MR02040 (2 In. (50.8 mm) dia. x 2 In. (50.8 mm) wide with handle)

1

Everhard Distributes pressure Products, Inc. along bonded fabric V72274 repairs. (Repair)

Spatula (Pusher) PA-1

1

Air Cruisers V70167

Evenly distributes, and removes wrinkles from, bonded fabric repairs. (Testing, Repair)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT TABLE 9001 (SHEET 2 OF 7)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE (SECTION)

Hydrostatic Test Machine TO4853

1

Air Cruisers V70167

Overpressure tests hose assemblies. (Testing)

Test Set (Light System) Model TU-12 or TU-14

1

Astronics DME Verifies power unit voltLLC age and lamp/LED harV55827 ness amperage. (Testing)

Test Set (Light System) Model TS-420 (Alternative to TU-14) US Domestic version 4-1020-102

1

BaseWest, Inc. Verifies power unit voltV0MF00 age and lamp/LED harness amperage. Domestic version includes BaseWest 115120VAC battery charger P/N 36-1002, with a 2 prong Type A plug. (Testing)

Test Set (Light System) Model TS-420 (Alternative to TU-14) International version 4-1020-202

1

BaseWest, Inc. Verifies power unit voltV0MF00 age and lamp/LED harness amperage. International version includes BaseWest 220VAC battery charger P/N 36-1005, with a 2 prong Type A plug and a 2 prong Type C adapter (adapters to fit other electrical systems must be purchased locally). (Testing)

Barometer [Scale increments not more than 0.10 In. (2.5 mm)]

1

Commercially Measures ambient presAvailable sure. (Testing)

Thermometer [Scale increments not more than 1°F (0.6 °C)]

1

Commercially Measures ambient temAvailable perature. (Testing)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT TABLE 9001 (SHEET 3 OF 7)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE (SECTION)

Manometer (water) 0 to 5.0 psig (0 to 3.4 N/cm2) *

1

Commercially Measures pressure of Available inflatable assembly. (Testing)

Manometer (Meriam Fluid) 0.5 to 5.0 psig (0.3 to 3.4 N/cm2) [9.4 in. (238.8 mm) M. F. per 1.0 psig (0.7 N/cm2)] *

1

Commercially Measures pressure of Available inflatable assembly. (Testing)

Pressure Gage (Mechanical/Digital) Scale Range 0 to 15 psig (0 to 10.3 N/cm2) * 2.0% Accuracy

1

Commercially Measures pressure of Available inflatable assembly. (Testing)

Safety Plug (Valve Outlet Port) AN814-10 or AS5169-10

1

Commercially Seals valve outlet port to Available prohibit damage and contamination. (Disassembly)

Heat Gun, Master PH-1100 (Post S.B. A320 04-25-64 and Amendment #4)

1

Commercially Used to apply heat for Available shrink tubing installation. (Repair)

Tool - Crimping TR-490 (Post S.B. A320 04-25-64 and Amendment #4)

1

Minnesota Mining & Mfg. Co. V2H942

Used to splice/crimp harness lead wires together. (Repair)

Kit, O-Ring Tools 67189-1

1

Air Cruisers V70167

Protects O-rings from threaded fittings during installation. (Folding Procedure)

* Alternatives SPECIAL TOOLS, FIXTURES, AND EQUIPMENT TABLE 9001 (SHEET 4 OF 7)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE (SECTION)

Wire Stripper, Klein 26-16 AWG 11046* (Post S.B. A320 04-25-64 and Amendment #4)

1

Commercially Used to remove protecAvailable tive coating from wire leads. (Repair)

Wire Stripper, Ideal 26-16 AWG 45-121* (Post S.B. A320 04-25-64 and Amendment #4)

1

Commercially Used to remove protecAvailable tive coating from wire leads. (Repair)

Adapter, Vacuum D14089-101

1

Air Cruisers V70167

Adapts vacuum to aspirator to remove air from inflatable sub-assembly. (Folding Procedure)

Vacuum, Industrial Type Model R2103 25-26 In. H2O (62-65 mb)

1

Gast Mfg. VZY311 or Air Cruisers V70167

Removes air from inflatable sub-assembly. (Folding Procedure)

Cloth Clamp 3539

2

Packing Fixture Forward Door D31516-( ) 211651-0 or 69968-101

1

Singer Indus- Holds fabric folds in place trial Sewing during folding procedure. Products (Folding Procedure) Cutters Exchange Division V1CHP3 Air Cruisers V70167 or Aerazur VF6101

Enclosure into which a system is packed/compressed. (Folding Procedure)

* Alternatives SPECIAL TOOLS, FIXTURES, AND EQUIPMENT TABLE 9001 (SHEET 5 OF 7)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE (SECTION)

Packing Fixture Aft Door D31517-( ) 211652-0 or 69967-101

1

Air Cruisers V70167 or Aerazur VF6101

Enclosure into which a system is packed/compressed. (Folding Procedure)

Fold/Pack Bander B19319-0

6

Air Cruisers V70167

Buckle/belt assembly used for compression. (Folding Procedure)

Tool - Lacing Hook B17583-1

2

Air Cruisers V70167

Cord tightening aid. (Folding Procedure)

Banding Board, Wooden (10 x 29 x 2 In.) (254 x 737 x 51 mm)

2

Fabricate Locally

Compression aid. (Folding Procedure)

Banding Board 215590-0 or 69969-1

2

Air Cruisers V70167 or Aerazur VF6101

Compression aid. (Folding Procedure)

Protective Blanket Furniture Moving Type (Quilted polyester fabric with cotton stuffing) Minimum Approximate size 80 x 72 In. (2032 x 1829 mm) and weight 6.25 Lb. (2.8 kg)

1

Fixture, Overpressure TO6762-1

1

Air Cruisers V70167

Personnel safety equipment used during overpressure testing. (Testing)

Envelope Gage, Forward Door D31516-( ) 67514-101

1

Air Cruisers V70167 or Aerazur VF6101

Verifies pack maximum envelope limits. (Folding Procedure)

Commercially Personnel safety equipAvailable ment used during overpressure testing. (Testing)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT TABLE 9001 (SHEET 6 OF 7)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

ITEM/DESCRIPTION

QUANTITY

SOURCE

USE (SECTION)

Envelope Gage, Aft Door D31517-( ) 67515-101

1

Air Cruisers V70167 or Aerazur VF6101

Verifies pack maximum envelope limits. (Folding Procedure)

Temporary Ties (Webbing, Green) M11213-13 or MIL-4088 Type II 3 m x 25.4 mm (10 Ft. x 1 In.)

6

Banding Aid TO7284

1

Air Cruisers V70167

Compression aid. (Folding Procedure)

Aspirator Fork TO7898-101 (Optional)

1

Air Cruisers V70167

Maintains an open aspirator inlet to allow air to escape the inflatable after testing or during packing. (Testing, Repair, Folding Procedure)

Air Cruisers Retains fabric folds in V70167 or place during packing Commercially (Folding Procedure) Available

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT TABLE 9001 (SHEET 7 OF 7)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

3. Special Tools, Fixtures, and Equipment Illustrated

ASPIRATOR FORK (TO7898-101)

SPATULA/PUSHER (PA-1)

HAND ROLLER (MR02040)

O-RING TOOL (TYP.) VALVE OUTLET PORT PLUG (AN814-10 OR AS5169-10)

SPECIAL TOOLS, FIXTURES AND EQUIPMENT ILLUSTRATED FIGURE 9001

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ADAPTER CABLE ASSEMBLY (60159-101 OR 65037-1)

GAGE

ADAPTER CABLE ASSEMBLY (69525-1)

LAMP

GREEN LIGHT INDICATES “GO” GAGE STATUS

LAMP

GAGE

COMPONENT MAINTENANCE MANUAL D31516 D31517

MANOMETER

VALVE CORE TOOL (6914V-SD)

PRESSURE TEST VALVE ADAPTER (C37099-103)

SPECIAL TOOLS, FIXTURES AND EQUIPMENT ILLUSTRATED FIGURE 9002

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COMPONENT MAINTENANCE MANUAL D31516 D31517

TEST CONNECTORS VOLTMETER

POWER UNIT TEST ONLY

PUSH TO TEST POWER UNIT

PUSH TO TEST LAMP HARNESS

AMMETER

POWER UNIT AND LAMP TEST

PUSH TO TEST TS-10 PROCEDURE

D

C

TS-10 PROCEDURE ONLY

E

OFF B

ARM

MODEL TU-12 TEST UNIT

F A

LOAD SELECTOR

ACTIVATE

TEST UNIT MODEL TU-12

WARNING-SHOCK HAZARD UNPLUG POWER CORD BEFORE SERVICING INSIDE UNIT CORPORATION FORT LAUDERDALE J4 FLORIDA J-1

115 VAC

E-1

MODEL TU-14 TEST SET

E-2

J-3

TU-14 BATTERY NEEDS CHARGE

FUSE 1 AMP

CHARGING

C

D

LOW

S-6

B

E A

VOLTMETER VOLTS

F LOAD

S-5

AMMETER AMPS S-2

BAS LOAD

S-4 LAMP HARNESS

BATTERY TEST

ON S-3 TS-10 PROCEDURE

S-1

POWER

TEST

TEST SET MODEL TU-14

SPECIAL TOOLS, FIXTURES AND EQUIPMENT ILLUSTRATED FIGURE 9003

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COMPONENT MAINTENANCE MANUAL D31516 D31517

TS-420 TEST SET

SELF TEST

(5VDC POWER SUPPLY)

LOW BATT (INTERNAL BATTERY)

BASEWEST TS-420 TEST SET Escape Slide Lighting Systems Digital Voltmeter/Ammeter with 5VDC Power Supply

VOLTMETER B A NO LOAD

AMMETER

PRESS TO TEST

C D E F

LOAD SELECTOR

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT ILLUSTRATED FIGURE 9004

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COMPONENT MAINTENANCE MANUAL D31516 D31517

CLOTH CLAMP (3539)

FOLD/PACK BANDER (B19319-0)

LACING HOOK (B17583-1)

VACUUM ADAPTER (D14089-101)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT ILLUSTRATED FIGURE 9005

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COMPONENT MAINTENANCE MANUAL D31516 D31517

HYDROSTATIC TEST MACHINE (TO4853)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT ILLUSTRATED FIGURE 9006

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COMPONENT MAINTENANCE MANUAL D31516 D31517

OVERPRESSURE FIXTURE (TO6762-1)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT ILLUSTRATED FIGURE 9007

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COMPONENT MAINTENANCE MANUAL D31516 D31517

ENVELOPE GAGE (67514-101)

ENVELOPE GAGE (67515-101)

SPECIAL TOOLS, FIXTURES, AND EQUIPMENT ILLUSTRATED FIGURE 9008

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COMPONENT MAINTENANCE MANUAL D31516 D31517

TABLE OF CONTENTS ILLUSTRATED PARTS LIST Page 1. General

10002

2. Material Arrangement

10002

3. How to Use the Parts List

10004

4. List of Abbreviations/Symbols/Terms/Definitions

10005

5. Vendor Codes

10007

6. Numerical Index

10008

7. Detailed Parts List

10008

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COMPONENT MAINTENANCE MANUAL D31516 D31517

1. General This parts list (IPL) contains the complete listing of all replaceable parts of the inflatable assembly.

2. Material Arrangement This IPL is comprised of the following sections. A. Introduction The introduction contains all the information necessary for the use of this IPL. It also contains a list of abbreviations used in the detailed parts list, and a list of manufacturer codes, names, and addresses. B. Numerical Index This section has a list of all part numbers in the detailed parts list in alpha-numerical sequence with cross-reference to the IPL Fig./Item numbers as well as the quantity. Sequence as follows: (1). Letters A through Z (“O” to be considered zero). (2). Numerals 0 through 9. C. Detailed Parts List The detailed parts list illustrates all parts attached by means other than riveting, sewing, or cementing. Parts attached by these means are included when the next higher assembly is replaced. (1). Column FIG/ITEM The first number in the first line of a page indicates the number of the first figure illustrating the part. The second number indicates the item number by which the part is identifiable on the illustration. A dash (-) placed before the item number indicates that the part is not illustrated. (2). Column PART NUMBER The part number column contains the original manufacturer part number. When standard parts are used, the standard part number is listed in this column. (3). Column AIRLINE PART NUMBER This column is left blank for airline use.

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COMPONENT MAINTENANCE MANUAL D31516 D31517

(4). Column NOMENCLATURE (a). Indenture System The indenture system shows the relationship of parts and assemblies to next higher assemblies or installations, as follows: 1234567 Assembly or installation assembly (RF) number Attaching parts for assembly or installation .Detail parts for assembly Sub-assembly Attaching parts for sub assembly ..Detailed parts for sub-assembly Sub-sub-assembly Attaching parts for sub-sub-assembly ...Detailed parts for sub-sub-assembly (b). Attaching Parts Attaching parts are captioned ATTACHING PARTS and are listed immediately following the parts attached. The *** symbol follows the last item of the attaching parts group. (c). Vendor Code Parts manufactured by companies other than Air Cruisers are identified by an appropriate vendor code following the nomenclature. Vendor codes are in accordance with current issues of Federal Supply Codes for Manufacturers Catalog handbooks H4-1, H4-2, and H4-3, and are preceded by the letter “V”. Standard parts such as AN, MS, etc. are not identified by vendor code.

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COMPONENT MAINTENANCE MANUAL D31516 D31517

(5). Column EFF CODE The Effectivity Code Column establishes part relationships with units or assemblies which are essentially the same but have minor deviations. These units or assemblies are assigned reference letters such as A, B, C, etc. Parts which are not common to all configurations but are associated with one or more of the coded lead items carry the letter or letters assigned to the lead item with which it is associated. Where a part is common to all lead items, the effectivity column is left blank. (6). Column UNITS PER ASSEMBLY This column contains the quantity of a specific catalog sequence numbered part required in the build sequence of only one (where more than one exists), next higher sub-sub-assembly, subassembly, assembly or installation level as applicable. For bulk items, the letters “AR” are inserted in the quantity column to indicate “as required”. Where items are listed for reference purposes, “RF” is inserted.

3. How to Use the Parts List A. If the part number is known (1). Find the part number in the Numerical Index. Note the Figure and item number. (2). Turn to the Figure. (3). Locate the part on the illustration and in the parts list by item number. B. The part number is unknown (1). Refer to the applicable Figure and look for the illustration of the part. (2). Note the item number. (3). Turn to the applicable parts list and refer to the corresponding item number.

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COMPONENT MAINTENANCE MANUAL D31516 D31517

4. List of Abbreviations/Symbols/Terms/Definitions A. Abbreviations, Symbols The following abbreviations/symbols are the more commonly used in this IPL. This list is to be used in conjunction with the Glossary of Abbreviations and Symbols, Introduction section.

AR

As Required

NO.

Number

ASSY.

Assembly

NP

Not Procurable

BKDN

Breakdown

R

Revised

CMM

Component Maintenance Manual

RF.

Reference

EFF.

Effectivity

R.H.

Right Hand

FIG.

Figure

R.S.

Right Side

IPL

Illustrated Parts List

SUBS

Subsequent

L.H.

Left Hand

***

End of Attaching Hardware

L.S.

Left Side

-

Item Not Illustrated

NHA

Next Higher Assembly



Denotes Intentionally Left Blank

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COMPONENT MAINTENANCE MANUAL D31516 D31517

B. Interchangeability Terms, Abbreviations, and Definitions

TERM

ABBREVIATION

DEFINITION

Superseded by

SUPSD BY

The part is superseded by and is one-way interchangeable with the item number shown (old part number can be used as replacement only where old part number was installed).

Supersedes

SUPSDS

The part supersedes and is one-way interchangeable with the item number shown (new part number is acceptable replacement for old or new part number).

Service Bulletins

SB PRE SB POST

Identifies when a service bulletin (SB) has an effect on a part. PRE shows the condition of the part before the work in the service bulletin is done; POST shows the condition after the work is done.

Alternate

ALT

The part agrees with all functional and structural specifications, but the external dimensions, connection installation, and/or mounting provisions are different. Rework or possible changes can be necessary.

Replaced by

REPLD

The part is replaced and is two-way interchangeable with the item number shown (old part number can replace either old or new part number when removed).

Replaces

REPLS

The part replaces and is two-way interchangeable with the item number shown (new part number is acceptable replacement for old or new part number).

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COMPONENT MAINTENANCE MANUAL D31516 D31517

5. Vendor Codes Table 10001 lists the CAGE code for vendors whose code appears in all chapters of the CMM and also listed in the Nomenclature Column of the Detailed Parts List. Absence of a vendor code following a part number in the Detailed Parts List identifies an Air Cruisers part.

CODE

NAME/ADDRESS

CODE

NAME/ADDRESS

V55827 Astronics DME LLC 6830 N. W. 16th Terrace Fort Lauderdale, FL 33309-1518 USA

V76381 Minnesota Mining & Manufacturing Co. 3M Center, Bldg. 220, 11W-02 St. Paul, MN 55144-1001 USA

V27783 Schrader-Bridgeport International Inc. 1609 Airport Road Monroe, NC 28110-7393 USA

V99017 Caplugs, LLC 2150 Elmwood Avenue Buffalo, NY 14207-1910 USA

V3J371 Diamond Fasteners, Incorporated 20B Commerce Drive Hauppauge, NY 11788-3910 USA

V99742 Nitto, Incorporated 1990 Rutgers University Boulevard Lakewood, NJ 08701-4537 USA

V70167 Air Cruisers 1747 State Route 34 Wall Township, NJ 07727-3935 USA

V3CKH7 Federal Process Corporation 4520 Richmond Road Cleveland, OH 44128-5757 USA

V0MF00 BaseWest Incorporated 4240 116th Terrace N Clearwater, FL 33762-4971 USA

V8S111 Rus Industries, Incorporated 3255 Lockport Road Niagara Falls, NY 14305-2309 USA

V72274 Everhard Products Incorporated 1016 9th Street SW Canton, OH 44707-4108 USA

V05972 Loctite Corporation 1001 Henkel Way Rocky Hill, CT 06067-3582 USA

V04963 3M Company - Adhesives, Coatings, and Sealers Division 3M Center St. Paul, MN 55144-1000 USA

VD8274 Huntsman Advanced Materials Deutschland GMBH & Co. KG Trottaecker 22-24 Bad Saeckingen 79713 DEU

V02684 Huntsman Int’l Trading Corporation Div. Huntsman Advanced Materials Americas LLC 4917 Dawn Avenue East Lansing, MI 48823-5605 USA

V1CHP3 Singer Industrial Sewing Products Cutters Exchange Division 1224 Heil Quaker Boulevard La Vergne, TN 37086-3515 USA

VENDOR INFORMATION TABLE 10001 (SHEET 1 OF 2)

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COMPONENT MAINTENANCE MANUAL D31516 D31517 CODE

NAME/ADDRESS

CODE

NAME/ADDRESS

V2H942 3M Company - Electronics and Commu- V04672 McGee Industries Incorporated nications Manufacturing DBA McLube 1700 N Minnesota Street 9 Crozerville Road New Ulm, MN 56073-1216 USA Aston, PA 19014-1431 USA VZY311 Gast Manufacturing Corporation 82 Reserve Road Artarmon, NSW 2064 AUS

VF6101 Aerazur 61 Rue Pierre CURIE 78370 PLAISIR, FRA

V0B629 Plasti Dip International 3920 Pheasant Ridge Drive Blaine, MN 55449-4528 USA

V99384 Huntsman Advanced Materials Americas LLC 51215 S. San Fernando Road W Los Angeles, CA 90039-1011 USA

VENDOR INFORMATION TABLE 10001 (SHEET 2 OF 2)

6. Numerical Index A. Numerical index listed on pages 10009 through 10031.

7. Detailed Parts List A. Detailed parts listed on pages 10033 through 10127.

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Page 10008 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER A3-06-0746-101 SUPSD BY P2-01-0035-001 OR D39011-101 ABA45

AIRLINE IPL PART NUMBER FIGURE 3

AN960C10L

B14056-910 B15216-1 B15216-3 B15216-5 SUPSD BY B15216-7 B15216-7 SUPSDS B15216-5 B15449-1 B15450-1 B15452-1 B15463-1 SUPSD BY 62351-1 B15468-1 B15472-101 SUPSD BY B15472-103 B15472-103 SUPSDS B15472-101 SUPSD BY 66606-101 B15473-1 B15474-1 B15475-1 B15476-1 SUPSD BY 66604-3 B15497-1

25-60-56

50

TOTAL REQUIRED 2

4 4A 4B 4 4A 4B 1 2 2 2 2 2

280 310 280 320 30 30 60 70 70B 70A 70C 70D

12 8 8 1 1 1 1 1 1 1 1 1

2

70E

1

4 4 4 4

160 250 110 260

1 2 1 3

4A 4B 2

200 180 40

2 2 2

2

40A

2

4A 4B 2 4 2

60 60 20 400 60

4 4 2 2 2

4

290

2

ITEM

Page 10009 11 Dec 2015

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER B15497-3 B16045-1

AIRLINE IPL PART NUMBER FIGURE 4 1 3

DELETED B16865-1 B16954-1

B16961-1 DELETED B16961-2 DELETED B19882-1 DELETED B19958-101 DELETED B30299-511 B31238-105 B31561-101 C15451-1 C15457-1 C15457-2 C15494-101 C15494-105 C16866-1 C16870-1 C16870-2 C19347-104 DELETED C19347-107 DELETED C19347-111 DELETED

25-60-56

ITEM 290A 240 40

TOTAL REQUIRED 2 1

4 4 4A 4B 4B

180 350 130 110 120

6 2 2 2

4B

130

3

110

1 3

250 60

1

3 3 1 4 4 4 4 4B 4 4B 4 4 4 1 3

150 280 180 190 70 90 92 284 92A 284A 100 60 80 260 80A

4 1 1 2 1 1 1 1 1 1 1 1 1 2

1 3

260A 90

1

3

80

Page 10010 09 Jan 2017

COMPONENT MAINTENANCE MANUAL D31516 D31517

AIRLINE IPL PART NUMBER FIGURE 1 3

PART NUMBER C19347-121 DELETED C19749-103 C19763-1 C19763-3 C19988-101 C25177-1 SUPSD BY 70189-105 C25177-3 C25177-5 C25177-6 C31523-101 C36128-101 SUPSD BY 61813-101 C37103-101 SUPSD BY 68605-101 C37103-103 SUPSD BY 68605-103 D15358-101

ITEM 260B 100

TOTAL REQUIRED 2

1 2 2 3 1

260C 80 81 70 270

1 1 1 1 1

1 1 1 1 1

270A 270B 270C 70 150

1 1 1 1 2

1

190

1

1

195

1

2

1

RF

2

1A

RF

2

1B

RF

2

10

RF

2

10A

RF

2

10B

RF

4

150

4

140

SUPSD BY D15358-103 & 62443-101

D15358-103 SUPSD BY D15358-105 & 62443-103

D15358-105 SUPSDS D15358-103 SUPSD BY 62367-101 D15359-101 SUPSD BY D15359-103 & 62444-101

D15359-103 SUPSDS D15359-101 SUPSD BY 62444-103 D15359-105 SUPSDS D15359-103 SUPSD BY 62371-101 D15445-1 DELETED D15467-1

25-60-56

1

Page 10011 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER D16955-101 DELETED

AIRLINE IPL PART NUMBER FIGURE 4

SUPSD BY 66826-1 D16955-102 DELETED SUPSD BY 66826-2 D16961-1 D16961-2 D18309-101 SUPSD BY D18309-201 D18309-201 SUPSDS D18309-101 D19701-109 SUPSD BY 63983-101 D31202-111 D31516-101 SUPSD BY D31516-105 D31516-103 SUPSD BY D31516-107 D31516-105 SUPSDS D31516-101 SUPSD BY D31516-109 D31516-107 SUPSDS D31516-103 SUPSD BY D31516-111 D31516-109 SUPSDS D31516-105 SUPSD BY D31516-113 D31516-111 SUPSDS D31516-107 SUPSD BY D31516-119 D31516-113 SUPSDS D31516-109 SUPSD BY D31516-121

25-60-56

ITEM

TOTAL REQUIRED

392

4B

80

1

4

392A

4B

90

1

4 4B 4 4B 1

394 120A 394A 130A 40

1 1 1 1 1

1

40A

1

1

80

1

3 1

120 1

1 RF

1

1A

RF

1

1B

RF

1

5

RF

1

6

RF

1

6A

RF

1

6B

RF

Page 10012 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER D31516-115 SUPSD BY D31516-123 D31516-117 SUPSD BY D31516-125 D31516-119 SUPSDS D31516-111 SUPSD BY D31516-519 D31516-121 SUPSDS D31516-113 SUPSD BY D31516-521 D31516-123 SUPSDS D31516-115 SUPSD BY D31516-523 D31516-125 SUPSDS D31516-117 SUPSD BY D31516-525 D31516-311 SUPSD BY D31516-315 D31516-313 SUPSD BY D31516-317 D31516-315 SUPSDS D31516-311 SUPSD BY D31516-415 D31516-317 SUPSDS D31516-313 SUPSD BY D31516-417 D31516-415 SUPSDS D31516-315 SUPSD BY D31516-715 D31516-417 SUPSDS D31516-317 SUPSD BY D31516-717 D31516-519 SUPSDS D31516-119 SUPSD BY D31516-719 D31516-521 SUPSDS D31516-121 SUPSD BY D31516-721

AIRLINE IPL PART NUMBER FIGURE 1

25-60-56

6C

TOTAL REQUIRED RF

1

6D

RF

1

6G

RF

1

6H

RF

1

6L

RF

1

6M

RF

1

6E

RF

1

6F

RF

1

6J

RF

1

6K

RF

1

6R

RF

1

6T

RF

1

6N

RF

1

6P

RF

ITEM

Page 10013 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER D31516-523 SUPSDS D31516-123 D31516-525 SUPSDS D31516-125 D31516-615 D31516-617 D31516-619 D31516-621 D31516-623 D31516-625 D31516-715 SUPSDS D31516-415 D31516-717 SUPSDS D31516-417 D31516-719 SUPSDS D31516-519 D31516-721 SUPSDS D31516-521 D31516-723 D31516-725 D31517-101 SUPSD BY D31517-105 D31517-103 SUPSD BY D31517-107 D31517-105 SUPSDS D31517-101 SUPSD BY D31517-109 D31517-107 SUPSDS D31517-103 SUPSD BY D31517-111 D31517-109 SUPSDS D31517-105 SUPSD BY D31517-113 D31517-111 SUPSDS D31517-107 SUPSD BY D31517-119

AIRLINE IPL PART NUMBER FIGURE 1

25-60-56

6U

TOTAL REQUIRED RF

1

6V

RF

1 1 1 1 1 1 1

6AE 6AF 6AA 6AB 6AC 6AD 6W

RF RF RF RF RF RF RF

1

6X

RF

1

6Y

RF

1

6Z

RF

1 1 1

6AG 6AH 10

RF RF RF

1

10A

RF

1

10B

RF

1

11

RF

1

12

RF

1

12A

RF

ITEM

Page 10014 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER D31517-113 SUPSDS D31517-109 SUPSD BY D31517-121 D31517-115 SUPSD BY D31517-123 D31517-117 SUPSD BY D31517-125 D31517-119 SUPSDS D31517-111 SUPSD BY D31517-519 D31517-121 SUPSDS D31517-113 SUPSD BY D31517-521 D31517-123 SUPSDS D31517-115 SUPSD BY D31517-523 D31517-125 SUPSDS D31517-117 SUPSD BY D31517-525 D31517-311 SUPSD BY D31517-315 D31517-313 SUPSD BY D31517-317

AIRLINE IPL PART NUMBER FIGURE 1

D31517-315 SUPSDS D31517-311 SUPSD BY D31517-415 D31517-317 SUPSDS D31517-313 SUPSD BY D31517-417 D31517-415 SUPSDS D31517-315 SUPSD BY D31517-715 D31517-417 SUPSDS D31517-317 SUPSD BY D31517-717

25-60-56

12B

TOTAL REQUIRED RF

1

12C

RF

1

12D

RF

1

12G

RF

1

12H

RF

1

12L

RF

1

12M

RF

1

12E

RF

1

12F

RF

1

12J

RF

1

12K

RF

1

12R

RF

1

12T

RF

ITEM

Page 10015 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER D31517-519 SUPSDS D31517-119 SUPSD BY D31517-719 D31517-521 SUPSDS D31517-121 SUPSD BY D31517-721 D31517-523 SUPSDS D31517-123 D31517-525 SUPSDS D31517-125 D31517-615 D31517-617 D31517-619 D31517-621 D31517-623 D31517-625 D31517-715 SUPSDS D31517-415 D31517-717 SUPSDS D31517-417 D31517-719 SUPSDS D31517-519 D31517-721 SUPSDS D31517-521 D31517-723 D31517-725 D31871-101 D31880-101

AIRLINE IPL PART NUMBER FIGURE 1

D31882-101 SUPSD BY D31882-103 D31882-103 SUPSDS D31882-101 SUPSD BY D31882-105 D31882-105 SUPSDS D31882-103 SUPSD BY D31882-107

25-60-56

12N

TOTAL REQUIRED RF

1

12P

RF

1

12U

RF

1

12V

RF

1 1 1 1 1 1 1

12AE 12AF 12AA 12AB 12AC 12AD 12W

RF RF RF RF RF RF RF

1

12X

RF

1

12Y

RF

1

12Z

RF

1 1 1 4 4A 4B 1

12AG 12AH 212 270 240 210 30

RF RF 1 1 1 1 1

1

30C

1

1

30A

1

ITEM

Page 10016 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER D31882-107 SUPSDS D31882-105 D31910-101 SUPSD BY D31910-105, -113

AIRLINE IPL PART NUMBER FIGURE 1

SUPSD BY D31910-105, -113 D31910-103 SUPSD BY D31910-107, -115 SUPSD BY D31910-107, -115 D31910-105 SUPSDS D31910-101 SUPSD BY D31910-109, -117 SUPSDS D31910-101 SUPSD BY D31910-109, -117 D31910-107 SUPSDS D31910-103 SUPSD BY D31910-111, -119 SUPSDS D31910-103 SUPSD BY D31910-111, -119 D31910-109 SUPSDS D31910-105 SUPSD BY D31910-121 SUPSDS D31910-105 SUPSD BY D31910-121 D31910-111 SUPSDS D31910-107 SUPSD BY D31910-123 SUPSDS D31910-107 SUPSD BY D31910-123 D31910-113 SUPSDS D31910-101

30B

TOTAL REQUIRED 1

1

200

1

3

1

RF

1

210

1

3

1A

RF

1

200A

1

3

1B

RF

1

210A

1

3

1C

RF

1

200B

1

3

1D

RF

1

210B

1

3

1E

RF

1

210E

1

3

2F

RF

ITEM

SUPSDS D31910-101

25-60-56

Page 10017 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER D31910-115 SUPSDS D31910-103

AIRLINE IPL PART NUMBER FIGURE 1

SUPSDS D31910-103 D31910-117 SUPSDS D31910-105 SUPSDS D31910-105 D31910-119 SUPSDS D31910-107 SUPSDS D31910-107 D31910-121 SUPSDS D31910-109 SUPSD BY D31910-125 SUPSDS D31910-109 SUPSD BY D31910-125 D31910-123 SUPSDS D31910-111 SUPSD BY D31910-127 SUPSDS D31910-111 SUPSD BY D31910-127 D31910-125 SUPSDS D31910-121 SUPSD BY D31910-129 SUPSDS D31910-121 SUPSD BY D31910-129 D31910-127 SUPSDS D31910-123 SUPSD BY D31910-131

210F

TOTAL REQUIRED 1

3

1G

RF

1

210G

1

3

1K

RF

1

210H

1

3

1L

RF

1

210C

1

3

1H

RF

1

210D

1

3

1J

RF

1

210J

1

3

1M

RF

1

210K

1

3

1N

RF

ITEM

SUPSDS D31910-123 SUPSD BY D31910-131

25-60-56

Page 10018 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER D31910-129 SUPSDS D31910-125

AIRLINE IPL PART NUMBER FIGURE 1

SUPSDS D31910-125 D31910-131 SUPSDS D31910-127 SUPSDS D31910-127 D31910-217 D31910-219 D31910-221 D31910-223 D37085-101 SUPSD BY 68906-101 D37091-101 DELETED D39011-101 SUPSDS A3-06-0746-101 E15366-101 SUPSD BY 62366-101 SUPSD BY 62366-101 E15366-301 E15367-101 SUPSD BY 62370-101 SUPSD BY 62370-101 E15367-301 E15425-101 E15426-101 E15426-103 E15428-101

25-60-56

210L

TOTAL REQUIRED 1

3

1P

RF

1

210M

1

3

1Q

RF

3 1 1 3 1 3 1 3 1

210Q 1U 210R 1V 210N 1R 210P 210P 50

1 RF 1 RF 1 RF 1 RF 1

3

10

3

50A

2

1

20

1

4

1

RF

1 4 1

20A 1A 25

1 RF 1

4

10

RF

1 4 4 2 2 2

25A 10A 95A 220 220A 210

1 RF 1 1 1 1

ITEM

Page 10019 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER E15428-103 E15429-101 F22NKM02

MILF218401BP

MS16624-4025

MS16624-4031

MS171496 MS171532 MS171534 MS20426AD4-4 MS20426AD4-6 MS20426AD4-8

MS20426AD4-9 MS20426B4-4 MS20426B4-5 SUPSDS MS20426B4-6 MS20426B4-6 SUPSDS MS20426B4-8 SUPSD BY MS20426B4-5 MS20426B4-8

AIRLINE IPL PART NUMBER FIGURE 2 4 4 4A 4B 2 3 3 4 4 4 4A 4B 4 4A 4B 1 4 4 4 2 2 4 4 4A 4B 4A 2 2

210A 95 330 20 20 100 130 140 40 50 340A 110A 100A 340B 110B 100B 32 170 200 130 50C 190 410 93 190 286 190A 30A 50B

TOTAL REQUIRED 1 1 1 1 1 1 1 6 1 4 2 2 2 2 2 2 2 1 12 1 2 4 4 6 4 6 4 4 4

2

50A

4

2 2

30 50

4 4

2

90

4

ITEM

SUPSD BY MS20426B4-6

25-60-56

Page 10020 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER MS20426B5-6 SUPSD BY MS20426B5-7

AIRLINE IPL PART NUMBER FIGURE 4A

SUPSD BY MS20426B5-7 MS20426B5-7 SUPSDS MS20426B4-6 SUPSDS MS20426B4-6 MS20470A4-4 SUPSD BY MS20470AD4-5

170

TOTAL REQUIRED 6

4B

150

6

4A

170A

6

4B

150A

6

4

370

8

4A

220

8

4B

190

4

4B 4

200 370A

4 8

4A

230

8

4B

200A

8

4A 4B 4B 4 4A 4B 4 4 4B 4 4B 4A 2

150 160A 160 435 290 260 240 94B 281 94A 289 140 130

12 12 12 4 4 4 4 6 6 6 6 4 4

ITEM

SUPSD BY MS20470AD4-5 SUPSD BY MS20470AD4-5 MS20470A4-5 MS20470AD4-5 SUPSDS MS20470AD4-4 SUPSDS MS20470AD4-4 SUPSDS MS20470A4-4 & MS20470A4-5 MS20470AD4-8 MS20470AD4-11 MS21083C04

MS21083C08 MS21083D06 MS24693A29 MS24693C23 MS24693C25

25-60-56

Page 10021 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER MS24693C5 SUPSDS MS24693C6

AIRLINE IPL PART NUMBER FIGURE 4A

SUPSDS MS24693C6 MS24693C6 SUPSD BY MS24693C5 SUPSD BY MS24693C5 MS24693C7 MS24693C51 DELETED MS24693C52 MS25281F2 SUPSD BY MS25281R3 MS25281R3 SUPSDS MS25281F2

MS3215-4031

MS35338-135 MS51957-13 MS51958-64

M12397-1 SUPSDS P-29-1 & P-295-1 SUPSDS P-29-1 & P-295-1 NAS1169DD6

NAS1149C0332R

NAS1169DD8

25-60-56

300A

TOTAL REQUIRED 4

4B

270A

4

4A

300

4

4B

270

4

4 4

430 230

4

4 4

230A 300

4 1

4

300A

1

4A 4B 4 4A 4B 4 4 4 4A 4B 4

10 10 340 110 100 220 210 310 40 40 39B

1 1 2 4 2 12 12 1 1 1 A/R

4B

54B

A/R

4 4A 4B 4 4A 4B 4A 4B

94 180 288 320A 30A 30A 160 140

6 4 6 1 1 1 6 6

ITEM

Page 10022 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER P2-01-0035-001 SUPSDS A3-06-0746-101 P29-1 SUPSD BY M12397-1

AIRLINE IPL PART NUMBER FIGURE 3

SUPSD BY M12397-1 P295-1 SUPSD BY M12397-1 SUPSD BY M12397-1 PL9

PPPT60-1 SJ3551

VC218-8 12B11347-0 15A17168-1 24C17380-105 SUPSD BY 24C17380-109 SUPSDS 24C17380-109 SUPSD BY 24C29245-103 24C17380-109 SUPSD BY 24C17380-105 24C29245-103 SUPSDS 24C17380-105 26C15091-1 SUPSD BY 8947T24 26C15091-6 SUPSD BY 61812-1

25-60-56

50A

TOTAL REQUIRED 2

4

39

A/R

4B

54

A/R

4

39A

A/R

4B

54A

A/R

4 4A 4B 4 4B 2 2 4 4 4 2 1 1 1

120 77 77 37 52 140 150 55 56 57 200 235 238 130

4 4 4 A/R A/R 1 2 1 2 2 2 1 1 1

1

130B

1

1

130A

1

1

130C

1

1 1

140 140A

1 1

1

160

2

ITEM

Page 10023 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER 8947T24 SUPSDS 26C15091-1 AND 68660-101 9166L5 SUPSD BY 65216-101

AIRLINE IPL PART NUMBER FIGURE 1

DELETED 2525 DELETED 60040-101 60108-101 SUPSD BY 60040-101 OR 65026-1 60112-101 SUPSD BY 60115-101 OR 65035-1 60115-101 60142-101 SUPSD BY 62377-101 60143-101 SUPSD BY 62378-101 60157-101 60157-103 60300-1 60327-1

60406-1 60461-101 SUPSD BY 60461-107 DELETED 60461-107 SUPSDS 60461-101 SUPSD BY 66068-101 60887-101 SUPSD BY 62338-101 61398-101

25-60-56

170B

TOTAL REQUIRED 1

1

230

1

3

20

3

30

1 1

90 100

1 1

1

120

1

1 4

110 20

1 1

4

30

1

3 3 4A 4 4A 4B 2 1

160 160A 120 360 210 170 120 220

1 1 1 4 4 4 2 1

3

15

1

1

220A

1

2

110

1

1

280

1

ITEM

Page 10024 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER 61398-103 61399-101 61399-103 61812-1 SUPSDS 26C15091-6 61813-101 SUPSDS C36128-101 62338-101 SUPSDS 60887-101 62338-103 62338-105 62351-1

AIRLINE IPL PART NUMBER FIGURE 1 1 1 1

SUPSDS B15463-1 62351-3 62366-101 SUPSDS E15366-101 SUPSDS E15366-101 62366-103 SUPSD BY 62366-105 SUPSD BY 62366-105 62366-105 SUPSDS 62366-103 SUPSDS 62366-103 62366-301 62366-303 SUPSD BY 62366-305

280A 275 275A 165

TOTAL REQUIRED 1 1 1 2

1

155

2

2

160

1

2 2 4 4A 4B

160A 160B 265 270 250

1 1 3 1 1

4A 4B 1

270A 250A 21

2 2 1

4

5

RF

1

21B

1

4

5A

RF

1

21D

1

4

5B

RF

1 4A 1

21A 1 21C

1 RF 1

4A

1A

RF

ITEM

SUPSD BY 62366-305

25-60-56

Page 10025 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER 62366-305 SUPSDS 62366-303

AIRLINE IPL PART NUMBER FIGURE 1

SUPSDS 62366-303 62367-101 SUPSDS D15358-105 SUPSD BY 62367-103 62367-103 SUPSDS 62367-101 62367-301 SUPSD BY 62367-303 62367-303 SUPSDS 62367-301 62370-101 SUPSDS E15367-101 SUPSDS E15367-101 62370-103 SUPSD BY 62370-105 SUPSD BY 62370-105 62370-105 SUPSDS 62370-103 SUPSDS 62370-103 62370-301 62370-303 SUPSD BY 62370-305 SUPSD BY 62370-305 62370-305 SUPSDS 62370-303 SUPSDS 62370-303 62371-101 SUPSDS D15359-108 SUPSD BY 62371-103

25-60-56

21E

TOTAL REQUIRED 1

4A

1B

RF

2

1E

RF

2

1J

RF

2

1F

RF

2

1K

RF

1

26

1

4

15

RF

1 4

26B 15A

1 RF

1

26D

1

4

15B

RF

1 4B 1

26A 1 26C

1 RF 1

4B

1A

RF

1

26E

1

4B

1B

RF

2

10E

RF

ITEM

Page 10026 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER 62371-103 SUPSDS 62371-101 62371-301 SUPSD BY 62371-303 62371-303 SUPSDS 62371-301 62377-101 SUPSDS 60142-101 62377-103 62377-105 62377-301 62377-303 62377-305 62378-101 SUPSDS 60143-101 62378-103 62378-105 62378-301 62378-303 62378-305 62443-101 SUPSDS D15358-101 62443-103 SUPSDS D15358-103 62443-301 62443-303 62444-101 SUPSDS D15359-101 62444-103 SUPSDS D15359-103 62444-301 62444-303 62678-101 62699-101 62753-101

AIRLINE IPL PART NUMBER FIGURE 2

62753-103

25-60-56

10J

TOTAL REQUIRED RF

2

10F

RF

2

10K

RF

4

25

1

4 4 4A 4A 4A 4

25A 25B 50 50A 50B 35

1 1 1 1 1 1

4 4 4B 4B 4B 2

35A 35B 50 50A 50B 1C

1 1 1 1 1 RF

2

1D

RF

2 2 2

1G 1H 10C

RF RF RF

2

10D

RF

2 2 1 3 4 4A 4 4A

10G 10H 34 180 382 80 382A 80A

RF RF 6 1 1 1 1 1

ITEM

Page 10027 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER 62754-1 62754-2 63433-101 63434-101 63667-101 SUPSD BY 63667-103 63667-103 SUPSDS 63667-101 63865-1 63893-101 63894-1 63983-101 SUPSDS D19701-109 64211-101 SUPSD BY 64211-103 64211-103 SUPSDS 64211-101 64211-301 SUPSD BY 64211-303 64211-303 SUPSDS 64211-301 64212-101 64212-301 64328-101 64946-1 64946-3 64946-5 64946-7 64948-1 64948-3 64948-5 64948-7 65026-1 SUPSD BY 67993-1

AIRLINE IPL PART NUMBER FIGURE 4 4A 4 4A 4 4A 4 4B 1

25-60-56

384 90 384A 100 380 70 390 70 50A

TOTAL REQUIRED 1 1 1 1 1 1 1 1 1

1

50B

1

1 1 1 1

35 31 33 80A

1 1 1 1

4

95B

1

4

95D

1

4A

320

1

4A

320A

1

4 4B 3 2 2 2 2 2 2 2 2 1

95C 290 170 220B 220C 220D 220E 210B 210C 210D 210E 90A

1 1 1 1 1 1 1 1 1 1 1 1

ITEM

Page 10028 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER 65031-101 SUPSD BY 66095-1 65031-102 SUPSD BY 66095-2 65032-1

AIRLINE IPL PART NUMBER FIGURE 2

170

TOTAL REQUIRED 1

2

180

1

4 4A

425 280

2

4B

240

1 1

110A 230A

1 1

1 1 3 3 3 3 3 3 4 4A

232 233 50B 50C 190 200 210 220 415 250

1 1 1 1 1 1 1 1 1 1

4B

220

1

4 4A

420 260

1 1

4B

230

1

3 3 3 3 3 1

230 250 260 270 240 225

6 2 1 1 8 1

ITEM

DELETED DELETED 65035-1 65216-101 SUPSDS 9166L5 65217-1 65217-3 65349-3 65349-1 65424-101 65424-103 65424-105 65424-107 65460-1 SUPSD BY 66094-1 SUPSD BY 66094-1 65460-2 SUPSD BY 66094-2 SUPSD BY 66094-2 65475-101 65476-101 65477-101 65488-101 65489-101 66068-101 SUPSDS 64061-101

25-60-56

Page 10029 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER 66094-1 SUPSDS 65460-1

AIRLINE IPL PART NUMBER FIGURE 4A

SUPSDS 65460-1 66094-2 SUPSDS 65460-2 SUPSDS 65460-2 66095-1 SUPSDS 65031-101 66095-2 SUPSDS 65031-102 66604-3 SUPSDS B15476-1 66606-101 SUPSDS B15472-103 66623-101 66825-1 66825-2 66826-1 SUPSDS D16955-101 66826-2 SUPSDS D16955-102 67993-1 SUPSDS 65026-1 SUPSD BY 70164-1 68605-101 SUPSDS C37103-101 68605-103 SUPSDS C37103-103 68660-101 68660-101 SUPSD BY 8947T24

25-60-56

260A

TOTAL REQUIRED 1

4B

230A

1

4A

260B

1

4B

230B

1

2

180A

1

2

180B

1

2

60A

2

2

40B

2

4A 4B 4 4A 4 4A 4 4B

75 75 384B 90A 384C 100A 394B 120B

1 1 1 1 1 1 1 1

4 4B

394C 130B

1 1

1

90B

1

1

190A

1

1

195A

1

1 1

170 170A

1 1

ITEM

Page 10030 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

PART NUMBER 68906-1 SUPSDS D17085-101 70164-1 SUPSDS 67993-1 70189-105 SUPSDS C25177-1 70221-101 70223-101 70837-1

AIRLINE IPL PART NUMBER FIGURE 1

70838-1

70839-1 70839-2 70840-1 70840-2 70841-101 70847-1 70847-3 70869-1 70869-3

25-60-56

50C

TOTAL REQUIRED 1

1

90C

1

1

270D

1

1 3 4 4A 4B 4 4A 4B 4 4A 4 4A 4 4B 4 4B 4 4A 4 4B 4 4A

290 290 345 145 115 350A 130A 110A 384D 90B 384E 100B 394D 120C 394E 130C 382B 80B 95F 290A 95E 320B

2 1 2 2 2 2 2 2 1 1 1 1 1 1 1 1 1 1 1 1 1 1

ITEM

Page 10031 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

This page intentionally left blank.

25-60-56

Page 10032 09 Jan 2017

COMPONENT MAINTENANCE MANUAL D31516 D31517

6N, 6P, 6R, 6T, 6W, 6X, 6Y, 6Z

275, 280

140A 155

INFLATION CABLE (REF.)

165

INFLATION CABLE (REF.)

130B 130C

INFLATION CABLE (REF.)

170A

170B

FORWARD AND AFT DOOR SLIDES IPL FIGURE 1 (SHEET 1 OF 4)

25-60-56

Page 10033 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

DECORATIVE COVER (REFERENCE ONLY)

WRAPPER (REF.) (POST S.B. A320 004-25-97, D31516-719 THROUGH -725, AND D31517-719 THROUGH -725 ONLY)

290* (TYP. BOTH SIDES)

210J, 210K, 210L, 210M

180

70 190, 195 140 165

155 21C, 21E 190A, 195A 170

FORWARD AND AFT DOOR SLIDES IPL FIGURE 1 (SHEET 2 OF 4)

25-60-56

Page 10034 09 Jan 2017

COMPONENT MAINTENANCE MANUAL D31516 D31517

31

30B VIEW A-A

32

33 35 A 34 A

110, 110A, 120

90, 90A, 90B, 90C, 100 80A 40A

50, 50A, 50B, 50C

60

FORWARD AND AFT DOOR SLIDES IPL FIGURE 1 (SHEET 3 OF 4)

25-60-56

Page 10035 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

250 260

260B

260A 260B

210E, 210F

240 225

260C POST S.B. 004-25-51, FAA AD 2001-15-06, AND DGAC AD 2000-359-152(B)

230A, 232, 233, 235 238

FORWARD AND AFT DOOR SLIDES IPL FIGURE 1 (SHEET 4 OF 4)

25-60-56

Page 10036 09 Jan 2017

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

A

RF

C

RF

E

RF

1 R

-1 D31516-101

R

-1A D31516-103

R

-1B D31516-105

Slide, Forward Door without Re-Entry tape, with Velcro method of decorative cover attachment (NP) (Supsd by Item 1B) (Pre S.B. 004-25-1) Slide, Forward Door with Re-Entry tape and the Velcro method of decorative cover attachment (NP) (Supsd by Item 5) (Pre S.B. 004-25-30) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) Slide, Forward Door without Re-Entry tape, with the Velcro method of decorative cover attachment (NP) (Supsds Item 1) (Post S.B. 004-25-1) (Supsd by Item 6) (Pre S.B. 004-25-30) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B))

- Item Not Illustrated

25-60-56

Page 10037 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

G

RF

H

RF

L

RF

1 R

-5 D31516-107

R

-6 D31516-109

R

-6A D31516-111

Slide, Forward Door with Re-Entry tape and the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 1A) (Post S.B. 004-25-30) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Supsd by Item 6A) Slide, Forward Door without Re-Entry tape, with the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 1B) (Post S.B. 004-25-30) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Supsd by Item 6B) Slide, Forward Door with Re-Entry tape and the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 5) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Pre S.B. A320 004-25-61) (Supsd by Item 6G) (Pre S.B. A320 004-25-72)

- Item Not Illustrated

25-60-56

Page 10038 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -6B D31516-113

R

-6C D31516-115

R

-6D D31516-117

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Forward Door without Re-Entry tape, with the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 6) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Pre S.B. A320 004-25-61) (Supsd by Item 6H) (Pre S.B. A320 004-25-72) Slide, Forward Door with Re-Entry tape and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Pre S.B. A320 004-25-61) (Pre S.B. A320 004-25-72) (Supsd by Item 6L) Slide, Forward Door without Re-Entry tape, with Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Pre S.B. A320 004-25-61) (Pre S.B. A320 004-25-72) (Supsd by Item 6M)

EFF. CODE

UNITS PER ASSY.

M

RF

R

RF

S

RF

- Item Not Illustrated

25-60-56

Page 10039 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -6E D31516-311

R

-6F D31516-313

R

-6G D31516-119

R

-6H D31516-121

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Forward Door with Re-Entry tape and the Latch method of decorative cover attachment (NP) (Post S.B. A320 004-25-61) (Supsd by Item 6J) (Pre S.B. A320 004-25-72) Slide, Forward Door without Re-Entry tape, with Latch method of decorative cover attachment (NP) (Post S.B. A320 004-25-61) (Supsd by Item 6K) (Pre S.B. A320 004-25-72) Slide, Forward Door with Re-Entry Tape and the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 6A) (Post S.B. A320 004-25-72) (Supsd by Item 6N) (Pre S.B. A320 004-25-97) Slide, Forward Door without Re-Entry Tape, using the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 6B) (Post S.B. A320 004-25-72) (Supsd by Item 6P) (Pre S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

W

RF

Y

RF

AC

RF

AD

RF

- Item Not Illustrated

25-60-56

Page 10040 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -6J D31516-315

R

-6K D31516-317

R

-6L D31516-123

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Forward Door with Re-Entry Tape and the Latch method of decorative cover attachment (NP) (Supsds Item 6E) (Post S.B. A320 004-25-72) (Supsd by Item 6R) (Pre S.B. A320 004-25-97) Slide, Forward Door without Re-Entry Tape, with the Latch method of decorative cover attachment (NP) (Supsds Item 6F) (Post S.B. A320 004-25-72) (Supsd by Item 6T) (Pre S.B. A320 004-25-97) Slide, Forward Door without Re-Entry tape, using the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-72) (Supsds Item 6C) (Pre S.B. A320 004-25-74) (Supsd by Item 6U) (Pre S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

AE

RF

AF

RF

AG

RF

- Item Not Illustrated

25-60-56

Page 10041 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -6M D31516-125

R

6N D31516-519

R

6P D31516-521

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Forward Door without Re-Entry tape, using the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-72) (Supsds Item 6D) (Pre S.B. A320 004-25-74) (Supsd by Item 6V) (Pre S.B. A320 004-25-97) Slide, Forward Door with Re-Entry tape, thermobond construction, and the Dual Lock Fastener method of decorative cover attachment (Supsds Item 6G) (Supsd by Item 6Y) (Pre S.B. A320 004-25-97) Slide, Forward Door without Re-Entry tape, with thermobond construction, and the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 6H) (Supsd by Item 6Z) (Pre S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

AH

RF

AN

RF

AP

RF

- Item Not Illustrated

25-60-56

Page 10042 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 6R D31516-415

R

6T D31516-417

R

-6U D31516-523

R

-6V D31516-525

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Forward Door with Re-Entry tape, thermobond construction, and the Latch method of decorative cover attachment (NP) (Supsds Item 6J) (Supsd by Item 6W) (Pre S.B. A320 004-25-97) Slide, Forward Door without Re-Entry tape, with Latch method of decorative cover attachment (NP) (Supsds Item 6K) (Supsd by Item 6X) (Pre S.B. A320 004-25-97) Slide, Forward Door with Re-Entry tape, thermobond construction, and the Velcro method of decorative cover attachment (NP, Field Configuration part number only (Post S.B. A320 004-25-74) (Supsds Item 6L) Slide, Forward Door without Re-Entry tape, with thermobond construction, and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-74) (Supsds Item 6M) (Pre S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

AR

RF

AT

RF

BC

RF

BD

RF

- Item Not Illustrated

25-60-56

Page 10043 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 6W D31516-715

R

6X D31516-717

R

6Y D31516-719

R

6Z D31516-721

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Forward Door with Re-Entry tape and the Latch method of decorative cover attachment (Supsds Item 6R) (Post S.B. A320 004-25-97) Slide, Forward Door without Re-Entry tape, thermobond construction, a wrapper, and the Latch method of decorative cover attachment (Supsds Item 6T) (Post S.B. A320 004-25-97) Slide, Forward Door with Re-Entry tape, thermobond construction, and the Dual Lock Fastener method of decorative cover attachment (Supsds Item 6N) (Post S.B. A320 004-25-97) Slide, Forward Door without Re-Entry tape, with thermobond construction, a wrapper, and the Dual Lock Fastener method of decorative cover attachment (Supsds Item 6P) (Post S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

BG

RF

BH

RF

BJ

RF

BK

RF

- Item Not Illustrated

25-60-56

Page 10044 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -6AA D31516-619

R

-6AB D31516-621

R

-6AC D31516-623

R

-6AD D31516-625

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Forward Door with Re-Entry tape, a wrapper, and the Dual Lock Fastener method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Slide, Forward Door without Re-Entry tape, with a wrapper, and the Dual Lock Fastener method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Slide, Forward Door with Re-Entry tape, a wrapper, and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Slide, Forward Door without Re-Entry tape, with a wrapper, and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

BQ

RF

BR

RF

BT

RF

BU

RF

- Item Not Illustrated

25-60-56

Page 10045 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -6AE D31516-615

R

-6AF D31516-617

R

-6AG D31516-723

R

-6AH D31516-725

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Forward Door with Re-Entry tape, a wrapper, and the Latch method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Slide, Forward Door without Re-Entry tape, with a wrapper, and the Latch method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Slide, Forward Door with Re-Entry tape, thermobond construction, a wrapper, and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Slide, Forward Door without Re-Entry tape, with thermobond construction, a wrapper, and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

BV

RF

BW

RF

BY

RF

BZ

RF

- Item Not Illustrated

25-60-56

Page 10046 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -10 D31517-101

R

-10A D31517-103

R

-10B D31517-105

R

-11 D31517-107

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Aft Door without Re-Entry tape and with the Velcro method of decorative cover attachment (NP) (Supsd by Item 10B) Slide, Aft Door with Re-Entry tape and the Velcro method of decorative cover attachment (NP) (Supsd by Item 11) (Pre S.B. 004-25-30) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) Slide, Aft Door without ReEntry tape, with the Velcro method of decorative cover attachment (NP) (Supsds Item 10) (Supsd by Item 12) (Pre S.B. 004-25-30) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) Slide, Aft Door with Re-Entry tape and the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 10A) (Post S.B. 004-25-30) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Supsd by Item 12A)

EFF. CODE

UNITS PER ASSY.

B

RF

D

RF

F

RF

J

RF

- Item Not Illustrated

25-60-56

Page 10047 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -12 D31517-109

R

-12A D31517-111

R

-12B D31517-113

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Aft Door without Re-Entry tape, with the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 10B) (Post S.B. 004-25-30) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Supsd by Item 12B) Slide, Aft Door with Re-Entry tape and the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 11) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Pre S.B. A320 004-25-61) (Supsd by Item 12G) (Pre S.B. A320 004-25-72) Slide, Aft Door without Re-Entry tape, with the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 12) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Pre S.B. A320 004-25-61) (Supsd by Item 12H) (Pre S.B. A320 004-25-72)

EFF. CODE

UNITS PER ASSY.

K

RF

N

RF

P

RF

- Item Not Illustrated

25-60-56

Page 10048 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -12C D31517-115

R

-12D D31517-117

R

-12E D31517-311

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Aft Door with Re-Entry tape and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Pre S.B. A320 004-25-61) (Supsd By Item 12L) (Pre S.B. A320 004-25-72) Slide, Aft Door without Re-Entry tape, with the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Pre S.B. A320 004-25-61) (Supsd by Item 12M) (Pre S.B. A320 004-25-72) Slide, Aft Door with Re-Entry tape and the Latch method of decorative cover attachment (NP) (Post S.B. A320 004-25-61) (Supsd by Item 12J) (Pre S.B. A320 004-25-72)

EFF. CODE

UNITS PER ASSY.

T

RF

V

RF

AA

RF

- Item Not Illustrated

25-60-56

Page 10049 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -12F D31517-313

R

-12G D31517-119

R

-12H D31517-121

R

-12J D31517-315

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Aft Door without Re-Entry tape, with the Latch method of decorative cover attachment (NP) (Post S.B. A320 004-25-61) (Supsd by Item 12K) (Pre S.B. A320 004-25-72) Slide, Aft Door with Re-Entry tape and the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 12A) (Post S.B. A320 004-25-72) (Supsd by Item 12N) (Pre S.B. A320 004-25-97) Slide, Aft Door without ReEntry tape, using the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 12B) (Post S.B. A320 004-25-72) (Supsd by Item 12P) (Pre S.B. A320 004-25-97) Slide, Aft Door with Re-Entry tape and the Latch method of decorative cover attachment (NP) (Supsds Item 12E) (Post S.B. A320 004-25-72) (Supsd by Item 12R) (Pre S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

AB

RF

AJ

RF

AK

RF

AL

RF

- Item Not Illustrated

25-60-56

Page 10050 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -12K D31517-317

R

-12L D31517-123

R

-12M D31517-125

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Aft Door without Re-Entry Tape, with the Latch method of decorative cover attachment (NP) (Supsds Item 12F) (Post S.B. A320 004-25-72) (Supsd by Item 12T) (Pre S.B. A320 004-25-97) Slide, Aft Door without Re-Entry tape, using the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-72) (Supsds Item 12C) (Pre S.B. A320 004-25-74) (Supsd by Item 12U) (Pre S.B. A320 004-25-97) Slide, Aft Door without Re-Entry tape, using the Velcro method of decorative cover attachment (NP) (Field identified only) (Post S.B. A320 04-25-72) (Supsds Item 12D) (Pre S.B. A320 004-25-74) (Supsd by Item 12V) (Pre S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

AM

RF

AU

RF

AV

RF

- Item Not Illustrated

25-60-56

Page 10051 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -12N D31517-519

R

-12P D31517-521

R

-12R D31517-415

R

-12T D31517-417

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Aft Door with Re-Entry tape, thermobond construction, and the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 12G) (Supsd by Item 12Y) (Pre S.B. A320 004-25-97) Slide, Aft Door without Re-Entry tape, with thermobond construction, and the Dual Lock Fastener method of decorative cover attachment (NP) (Supsds Item 12H) (Supsd by Item 12Z) (Pre S.B. A320 004-25-97) Slide, Aft Door with Re-Entry tape, thermobond construction, and the Latch method of decorative cover attachment (NP) (Supsds Item 12J) (Supsd by Item 12W) (Pre S.B. A320 004-25-97) Slide, Aft Door without Re-Entry tape, with the Latch method of decorative cover attachment (NP) (Supsds Item 12K) (Supsd by Item 12X) (Pre S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

AW

RF

AY

RF

BA

RF

BB

RF

- Item Not Illustrated

25-60-56

Page 10052 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -12U D31517-523

R

-12V D31517-525

R

-12W D31517-715

R

-12X D31517-717

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Aft Door with Re-Entry tape, thermobond construction, and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-74) (Supsds Item 12L) (Pre S.B. A320 004-25-97) Slide, Aft Door without Re-Entry tape, with thermobond construction, and the Velcro method of decoratve cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-74) (Supsds Item 12M) (Pre S.B. A320 004-25-97) Slide, Aft Door with Re-Entry tape and the Latch method of decorative cover attachment (NP) (Supsds Item 12R) (Post S.B. A320 004-25-97) Slide, Aft Door without Re-Entry tape, with thermobond construction, a wrapper, and the Latch method of decorative cover attachment (Supsds Item 12T) (Post S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

BE

RF

BF

RF

BL

RF

BM

RF

- Item Not Illustrated

25-60-56

Page 10053 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -12Y D31517-719

R

-12Z D31517-721

R -12AA D31517-619

R -12AB D31517-621

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Aft Door with Re-Entry tape, thermobond construction, a wrapper, and the Dual Lock Fastener method of decorative cover attachment (Supsds Item 12N) (Post S.B. A320 004-25-97) Slide, Aft Door without Re-Entry tape, with thermobond construction, a wrapper, and the Dual Lock Fastener method of decorative cover attachment (Supsds Item 12P) (Post S.B. A320 004-25-97) Slide, Aft Door with Re-Entry tape, a wrapper, and the Dual Lock Fastener method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Slide, Aft Door without ReEntry tape, with a wrapper, and the Dual lock Fastener method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97)

EFF. CODE

UNITS PER ASSY.

BN

RF

BP

RF

CA

RF

CB

RF

- Item Not Illustrated

25-60-56

Page 10054 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

1 R -12AC D31517-623

R -12AD D31517-625

R -12AE D31517-615

R -12AF D31517-617

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Aft Door with Re-Entry tape, a wrapper, and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Slide, Aft Door without Re-Entry tape, with a wrapper, and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Slide, Aft Door with Re-Entry tape, with a wrapper, and the Latch method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Slide, Aft Door without Re-Entry tape, with a wrapper, and the Latch method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Item

EFF. CODE

UNITS PER ASSY.

CC

RF

CD

RF

CE

RF

CF

RF

- Item Not Illustrated

25-60-56

Page 10055 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

1 R -12AG D31517-723

R -12AH D31517-725

R

-20 E15366-101

AIRLINE PART NO.

NOMENCLATURE 1234567 Slide, Aft Door with Re-Entry tape, thermobond construction, a wrapper, and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) Slide, Aft Door without Re-Entry tape, with thermobond construction, a wrapper, and the Velcro method of decorative cover attachment (NP, Field Configuration part number only) (Post S.B. A320 004-25-97) .Packboard Assembly, Forward Door (Pre S.B. 004-25-30, with the Velcro method of decorative cover attachment; Post S.B. 004-25-30 with the Dual Lock Fastener method of decorative cover attachment) (Incorporated large diameter lock pin holes, Post S.B. 004-25-4; ACC S/N C0023 and Subs, ARZ S/N A5043 and Subs) (See IPL Figure 4 for BKDN) (Pre S.B. A320 004-25-61) (Supsd by Item 21)

EFF. CODE

UNITS PER ASSY.

CG

RF

CH

RF

A,C,E,G, H,L,M,R, S,AC,AD, AG,AH, AN,AP. BC,BD, BJ,BK, BQ,BR, BT,BU, BY,BZ

1

- Item Not Illustrated

25-60-56

Page 10056 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -20A E15366-301

R

-21 62366-101

R

-21A 62366-301

R

-21B 62366-103

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

.Packboard Assembly, W,Y,AE, Forward Door (with the Latch AF,AR, method of decorative cover AT,BH, attachment BJ,BV, (See IPL Figure 4 for BKDN) BW (Post S.B. A320 004-25-61)

1

.Packboard Assembly, Forward Door (with the Dual Lock Fastener method of decorative cover attachment) (NP) (See IPL Figure 4 for BKDN) (Supsds Item 20) (Pre S.B. A430 004-25-61) (Pre S.B. A320 004-25-75 and Amendment #5) .Packboard Assembly, Fwd Door, (with Latch method of decorative cover attachment) (NP) (See IPL Figure 4A for BKDN) (Post S.B. A320 004-25-61) (Pre S.B. A320 004-25-75 and Amendment #5) .Packboard Assembly, Forward Door (with the Dual Lock Fastener method of decorative cover attachment) (See IPL Figure 4 for BKDN) (Post S.B. A320 004-25-75 and Amendment #5) (Pre Amendment #7) (Supsd by Item 21D)

G,H,L,M, AC,AD, AN,AP, BJ,BK, BQ,BR

1

Y,W,AE, AF,AR, AT,BG, BH,BV, BW

1

G,H,L,M, AC,AD AN,AP, BJ,BK, BQ,BR

1

- Item Not Illustrated

25-60-56

Page 10057 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM R

PART NUMBER

1 21C 62366-303

-21D 62366-105

21E 62366-305

R

-25 E15367-101

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

.Packboard Assembly, Fwd Y,W,AE, Door (with the Latch method AF,AR, of decorative cover attachAT,BG, ment) BH,BV (See IPL Figure 4A for BW BKDN) (Post S.B. A320 00425-75 and Amendment #5) (Pre Amendment #7) (Supsd by Item 21E) .Packboard Assembly, A,C,E,G, Forward Door H,L,M, (See IPL Figure 4 for BKDN) AC,AD (Post Amendment #7) AN,AP, (Supsds Item 21B) BJ,BK, BQ,BR .Packboard Assembly, Fwd Y,W,AE, Door, Latch Configuration AF,AR, (See IPL Figure 4A for AT,BG, BKDN) (Post Amendment BH,BV #7) (Supsds Item 21C) BW .Packboard Assembly, B,D,F,J,K, Aft Door (with the Velcro N,P,T,V, method of decorative cover AJ,AK, attachment - Pre S.B. AU,AV, 004-25-30) (with the Dual AW,AY, Lock Fastener method of BE,BF, decorative cover attachment BN,BP, - Post S.B. 004-25-30) CA,CB, (See IPL Figure 4 for BKDN) CC,CD, (Pre S.B. A320 004-25-61) CG,CH (Supsd by Item 26)

- Item Not Illustrated

25-60-56

Page 10058 04 Dec 2018

1

1

1

1

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 -25A E15367-301

R

-26 62370-101

R

-26A 62370-301

R

-26B 62370-103

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

.Packboard Assembly, AA,AB, Aft Door (with the Latch AL,AM, method of decorative cover BA,BB, attachment) BL,BM, (See IPL Figure 4 for BKDN) CE,CF (Post S.B. A320 004-25-61) .Packboard Assembly, J,K,N,P, Aft Door (with the Dual Lock AJ,AK, Fastener method of decora- AW,AY, tive cover attachment) (NP) BN,BP, (See IPL Figure 4 for BKDN) CA,CB (Supsds Item 25) (Pre S.B. A320 004-25-78 and Amendment #5) .Packboard Assembly, Aft AA,AB, Door (with the Latch method AL,AM, of decorative cover attachBA,BB, ment) (NP) BL,BM, (See IPL Figure 4B for CE,CF BKDN) (Pre S.B. A320 00425-78 and Amendment #5) .Packboard Assembly, J,K,N,P, Aft Door (with the Dual Lock AJ,AK, Fastener method of decora- AW,AY, tive cover attachment) BN,BP, (See IPL Figure 4 for BKDN) CA,CB (Post S.B. A320 004-25-78 and Amendment #5) (Pre Amendment #6) (Supsd by Item 26D)

- Item Not Illustrated

25-60-56

Page 10059 04 Dec 2018

1

1

1

1

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM R

PART NUMBER

1 -26C 62370-303

-26D 62370-105

-26E 62370-305

R

-30 D31882-101

R

-30A D31882-105

30B D31882-107 R

-30C D31882-103

31 63893-101 32 MS171496 - Item Not Illustrated

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

.Packboard Assembly, Aft AA,AB, Door (with the Latch method AL,AM, of decorative cover attachBA,BB, ment) BL,BM, (See IPL Figure 4B for CE,CF BKDN) (Post S.B. A320 004 -25-78 and Amendment #5) (Pre Amendment #6) (Supsd by Item 26E) .Packboard Assembly, B,D,F,J, Aft Door K,N,P,AJ, (See IPL Figure 4 for BKDN) AK,AW, (Post Amendment #6) AY,BN, (Supsds Item 26B) BP,CA CB .Packboard Assembly, Aft AA,AB, Door, Latch Configuration AL,AM, (See IPL Figure 4B for BA,BB, BKDN) (Post Amendment BL,BM, #6) (Supsds Item 26C) CE,CF .Lower Lacing Cover Assembly (Supsd by Item 30C) (Pre S.B. 004-25-47) .Lower Lacing Cover Assembly (Supsds Item 30C) (Post S.B. 004-25-47) (Supsd by Item 30B) .Lower Lacing Cover Assembly (Supsds Item 30A) .Lower Lacing Cover Assembly (Supsds Item 30) (Supsd by Item 30A) ..Tie Bar Assembly ...Roll Pin

25-60-56

Page 10060 04 Dec 2018

1

1

1

1

1

1 1

1 2

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

1 33 34 35 -40

63894-1 62678-101 63865-1 D18309-101

40A D18309-201

50 D37085-101

50A 63667-101

50B 63667-103

50C 68906-101

60 B14056-910 70 C31523-101 -80 D19701-109 80A 63983-101 90 60040-101 90A 65026-1

...Spacer ...Release Cable ...Tube .Reservoir and Valve Assembly (See CMM 25-65-17 for BKDN) (Supsd by Item 40A) .Reservoir and Valve Assembly (See CMM 25-65-17 for BKDN) (Supsds Item 40) .Hose Assembly (Supsd by Item 50C) (ALT to Items 50B and 50C) .Hose Assembly (ALT to Item 50) (Supsd by Item 50B) .Hose Assembly (ALT to Items 50 and 50C) (Supsds Item 50A) .Hose Assembly (Supsds Item 50) (ALT to Items 50 and 50B) .O-Ring .Girt Release Cable .Gage Protector (Supsd by Item 80A) .Gage Protector (Supsds Item 80) .Cable Assembly, Electrical (Gage and Lights) .Cable Assembly, Electrical (Gage and Lights) (Interchangeable Alternate to Item 90) (Supsd by Item 90B)

- Item Not Illustrated

25-60-56

Page 10061 04 Dec 2018

1 6 1 1

1

1

1

1

1

1 1 1 1 1 1

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

1 90B 67993-1

90C 70164-1 100 60108-101

110 60115-101 110A 65035-1

120 60112-101

-130 24C17380-105 -130A 24C17380-109 R 130B 24C17380-105

R

130C 24C29245-103

R

140 26C15091-1

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

.Cable Assembly, Electrical (Supsds Item 90A) (Supsd by Item 900C) .Cable Assembly, Electrical (Supsds Item 90B) .Cable Assembly, Electrical (Gage and Lights) (Interchangeable Alternate to Item 90) (Supsd by Items 90 or 90A) .Cable Assembly, Electrical Harness (Door Connections) .Cable Assembly, Electrical Harness (Door Connections) (Interchangeable alternative to Item 110) .Cable Assembly, Electrical Harness (Door Connections) (Interchangeable Alternative to Item 110) (Supsd by Items 110 or 110A) .Pull Handle Assembly (Supsd by Item 130A) .Pull Handle Assembly (Supsd by Item 130B) .Pull Handle Assembly (Supsds Item 130A) (Supsd by Item 130C) .Pull Handle Assembly (Supsds Item 130B) .Quick Disconnect

- Item Not Illustrated

25-60-56

Page 10062 04 Dec 2018

1

1 1

1 1

1

1 1 1

1 1

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM R

PART NUMBER

1 140A 26C15091-1

-150 C36128-101 155 61813-101 -160 26C15091-6 165 61812-1 R

170 68660-101

R

170A 68660-101

R

170B 8947T24

R

180 B31561-101 190 C37103-101

AIRLINE PART NO.

NOMENCLATURE 1234567 .Quick Disconnect (Used with Items 130, 130A, 130B) (Supsd by Item 170B) ..Disconnect Body (Supsd by Item 155) ..Disconnect Body (Supsds Item 150) ..Disconnect Sleeve (Supsd by Item 165) ..Disconnect Sleeve (Supsds Item 160) .Disconnect Body Assembly (ALT to Item 140) .Disconnect Body Assembly (ALT to Item 140A) (Used with Items 130, 130A, 130B) (Supsd by Item 170B) .Chain Connector (Supersedes Items 140A, 170A) .Mooring Line .Release Cable (Pre S.B. A320 004-25-89) (Supsd by Item 190A)

EFF. CODE

UNITS PER ASSY. 1

1 1 1 1 1 1

1

B,D,F,J, K,N,P, AA,AB, AJ-AM, AU-BB, BE,BF, BL-BP, CA-CF

- Item Not Illustrated

25-60-56

Page 10063 04 Dec 2018

1 1

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM R

R

R

PART NUMBER

1 190A 68605-101

195 C37103-103

195A 68605-103

AIRLINE PART NO.

NOMENCLATURE 1234567 .Release Cable (Post S.B. A320 004-25-89) (Supsds Item 190)

.Release Cable (Pre S.B. A320 004-25-89) (Supsd by Item 195A)

.Release Cable (Post S.B. A320 004-25-89) (Supsd by Item 195)

25-60-56

EFF. CODE

UNITS PER ASSY.

B,D,F,J, K,N,P, AA,AB, AJ-AM, AU-BB, BE,BF, BL,BM, BN,BP, CA-CF A,C,E,G, H,L,M,R, S,Y,W, AC-AH, AN-AT, BC,BD, BG,BH, BJ,BK, BQ-BZ A,C,E,G, H,L,M,R, S,Y,W, AC-AH, AN-AT, BC,BD, BG,BH, BJ,BK, BQ-BZ

Page 10064 04 Dec 2018

1

1

1

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM R

PART NUMBER

1 -200 D31910-101

R -200A D31910-105

R -200B D31910-109

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

.Slide Assembly, without A,B,E,F, Re-Entry tape (NP) H,K (See IPL Figure 3 for BKDN) (Supsd by Item 200A) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Pre S.B. A320 004-25-64 and Amendment #4) (Supsd by Item 210E) M,P,S,V, .Slide Assembly, without Re-Entry tape (NP) Y,AB (See IPL Figure 3 for BKDN) (Supsds Item 200) (Post S.B. 004-25-51, FAA AD 2001-1506, and DGAC AD 2000-359152(B)) (Pre S.B. A320 004-25-64 and Amendment #4) (Supsd by Item 200B) (Pre S.B. A320 004-25-72) (Supsd by Item 210G) .Slide Assembly, with LED M,P,Y,AB slide lighting and without Re-Entry tape (NP) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-64 and Amendment #4) (Supsds Item 200A) (Pre S.B. A320 004-25-72) (Supsd by Item 210C)

- Item Not Illustrated

25-60-56

Page 10065 04 Dec 2018

1

1

1

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM R

PART NUMBER

1 -210 D31910-103

R -210A D31910-107

R -210B D31910-111

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

.Slide Assembly, with C,D,G,J Re-Entry tape (NP) (See IPL Figure 3 for BKDN) (Supsd by Item 210A) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Pre S.B. A320 004- 25-64 and Amendment #4) (Supsd by Item 210F) .Slide Assembly, with L,N,R,T, Re-Entry tape (NP) W, AA (See IPL Figure 3 for BKDN) (Supsds Item 210) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Pre S.B. A320 004-25-64 and Amendment #4) (Supsd by Item 210B) (Pre S.B. A320 004-25-72) (Supsd by Item 210H) .Slide Assembly, with LED L,N,R,T, slide lighting and Re-Entry W,AA tape (NP) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-64 and Amendment #4) (Supsds Item 210A) (Pre S.B. A320 004-25-72) (Supsd by Item 210D)

- Item Not Illustrated

25-60-56

Page 10066 04 Dec 2018

1

1

1

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

1 R -210C D31910-121

R -210D D31910-123

R

210E D31910-113

R

210F D31910-115

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

.Slide Assembly, with LED AD,AF, lights and without Re-Entry AH,AV, tape (NP) AK,AM (Post S.B. A320 00425-72) (Supsds Item 200B) (Pre S.B. A320 004-25-74) (Pre S.B. A320 004-25-97) .Slide Assembly, with LED AC,AE, lights and Re-Entry tape AG,AU, (NP) AJ,AL (Post S.B. A320 004-25-72) (Supsds Item 210B) (Pre S.B. A320 004-25-74) (Pre S.B. A320 004-25-97) A,B,E,F, .Slide Assembly, with LED lights and without Re-Entry H,K tape (NP, Field Configuration part number only) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-64 and Amendment #4) (Supsds Item 200) .Slide Assembly, with LED C,D,G,J lights and Re-Entry tape (NP, Field Configuration part number only) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-64 and Amendment #4) (Supsds Item 210)

- Item Not Illustrated

25-60-56

Page 10067 04 Dec 2018

1

1

1

1

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

1 R -210G D31910-117

R -210H D31910-119

R

210J D31910-125

R

210K D31910-127

AIRLINE PART NO.

UNITS PER ASSY.

NOMENCLATURE 1234567

EFF. CODE

.Slide Assembly, without Re-Entry tape (NP, Field Configuration part number only) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-72) (Supsds Item 200A) (Pre S.B. A320 004-25-97) .Slide Assembly, with Re-Entry tape (NP, Field Configuration part number only) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-72) (Supsds Item 210A) (Pre S.B. A320 004-25-97) .Slide Assembly, with thermobond construction, LED lights, and without Re-Entry tape (NP) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-74) (Supsd by Item 210L) (Pre S.B. A320 004-25-97) .Slide Assembly, with thermobond construction, LED lights, and Re-Entry tape (NP) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-74) (Supsd by Item 210M) (Pre S.B. A320 004-25-97)

AD,AF, AH,AK, AM,AV

1

AC,AE, AG,AJ, AL,AU

1

AP,AT, AY,BB, BD,BF

1

AN,AR, AW,BA, BC,BE

1

- Item Not Illustrated

25-60-56

Page 10068 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

1 210L D31910-129

R

210M D31910-131

R -210N D31910-221

R -210P D31910-223

R -210Q D31910-217

R -210R D31910-219

AIRLINE PART NO.

UNITS PER ASSY.

NOMENCLATURE 1234567

EFF. CODE

.Slide Assembly, with thermobond construction, LED lights, a wrapper, and without Re-Entry tape (See IPL Figure 3 for BKDN) (Supsds Item 210J) (Post S.B. A320 004-25-97) .Slide Assembly, with thermobond construction, LED lights, a wrapper, and Re-Entry tape (See IPL Figure 3 for BKDN) (Supsds Item 210K) (Post S.B. A320 004-25-97) .Slide Assembly, with LED lights, a wrapper, and without Re-Entry tape (NP, Field Configuration part number only) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-97) .Slide Assembly with LED lights, a wrapper, and Re-Entry tape (NP, Field Configuration part number only) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-97) .Slide Assembly (NP) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-97) .Slide Assembly (NP) (See IPL Figure 3 for BKDN) (Post S.B. A320 004-25-97)

BH,BK, BM,BP, BZ,CH

1

BG,BJ, BL,BN, BY,CG

1

BR,BU, BW,CB, CD,CF

1

BQ,BT, BV,CA, CC,CE

1

BR,BW, BU,CB, CD,CF BQ,BT, BV,CA, CC,CE

1

- Item Not Illustrated

25-60-56

Page 10069 04 Dec 2018

1

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

1 -212 D31871-101 -214 60116-1 -220 60461-101 -220A 60461-107

225 66068-101 -230 9166L5

230A 65216-101 232 233 235 238 240 250 260 260A

65217-1 65217-3 12B11347-0 15A17168-1 B16045-1 B19958-101 C19347-104 C19347-107

260B C19347-121 260C C19749-103

AIRLINE PART NO.

NOMENCLATURE 1234567

EFF. CODE

UNITS PER ASSY.

..Girt Assembly ...Strip, Reinforcement .Aspirator (Supsd by Item 220A) .Aspirator (Supsds Item 220) (Supsd by Item 225) .Aspirator (Supsds Item 220A) ..Pressure Test Valve with Cap (V27783) (Supsd by Item 230A) ..Valve and Cap Assembly (Supsds Item 230) ...Valve ...Cap ....Core, Check Valve .Tube .Clamp, Worm Drive .Floating Knife .Frangible Link (Black) .Frangible Link (Natural/Black) .Frangible Link (Natural/Green) .Frangible Link (Black/Orange) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B))

1 1 1 1

1 1

1 1 1 1 1 1 1 2 1 2 1

- Item Not Illustrated

25-60-56

Page 10070 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

1 -270 C25177-1

-270A C25177-3 -270B C25177-5

AIRLINE PART NO.

NOMENCLATURE 1234567 .Record, Maintenance Release (Air Cruisers) (Supsd by Item 270D) .Record, Maintenance Release (Aerazur) .Record, Maintenance Release (Aerazur) (Interchangeable alternative with Item 270A)

-270C C25177-6

.Record, Maintenance Release (Aerazur) (Interchangeable alternative with Item 270A)

-270D 70189-105

.Record, Maintenance Release (Air Cruisers) (Supsds Item 270)

275 61399-101

.Placard, Identification (Air Cruisers)

EFF. CODE

UNITS PER ASSY. 1

1 A,C,E,G, H,L,M,R, S,Y,W, AC-AH, AN-AT, BC,BD, BG-BK B,D,F,J, K,N,P,T,V, AA,AB, AJ-AM, AU-BB, BE,BF, BL-BP

1

1

A,C,E,G, H,L,M,R, S,Y,W, AC-AH, AN-AT, BC,BD, BG-BK

- Item Not Illustrated

25-60-56

1

Page 10071 04 Dec 2018

1

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

1 -275A 61399-103

AIRLINE PART NO.

NOMENCLATURE 1234567 .Placard, Identification (Air Cruisers)

280 61398-101

.Placard, Identification (Aerazur)

R -280A 61398-103

.Placard, Identification (Aerazur)

290 70221-101

.Wrapper, Side

EFF. CODE

UNITS PER ASSY.

B,D,F,J, K,N,P,T, V,AA,AB, AJ-AM, AU-BB, BE,BF, BL-BP A,C,E,G, H,L,M,R, S,Y,W, AC-AH, AN-AT, BC,BD, BG-BK B,D,F,J, K,N,P,T, V,AA,AB, AJ-AM, AU-BB, BE,BF, BL-BP BG,BH, BJ,BK, BL,BM, BN,BP, BQ,BR, BT,BU, BV,BW, BY,BZ, CA,CB, CC,CD, CE,CF, CG,CH

- Item Not Illustrated

25-60-56

Page 10072 04 Dec 2018

1

1

1

2

COMPONENT MAINTENANCE MANUAL D31516 D31517

1E, 1J, 10E, 10J

DECORATIVE COVER FORWARD AND AFT IPL FIGURE 2 (SHEET 1 OF 4)

25-60-56

Page 10073 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

Forward Door (Typical Both Sides) Prior to S/N 2395 (Mfg by Air Cruisers) Prior to S/N A5767 (Mfg. by Aerazur) Aft Door (Typical Both Sides) Prior to S/N 2593 (Mfg. by Air Cruisers) Prior to S/N A5839 (Mfg. by Aerazur)

60

Forward Door (Typical Both Sides) S/N 2395 and Subs (Mfg by Air Cruisers) S/N A5767 and Subs (Mfg. by Aerazur) Aft Door (Typical Both Sides) S/N 2593 and Subs (Mfg. by Air Cruisers) S/N A5839 and Subs (Mfg. by Aerazur)

60A 40A

40B 50B (2 PLACES)

50B (2 PLACES)

50C

70, 70A, 70B, 70C, 70E

150 140 160, 160A

150

81

90

20 (TYPICAL BOTH SIDES)

120

130 (2 PLACES)

30, 30A (2 PLACES; TYPICAL BOTH SIDES)

Forward Door (Typical Both Sides) Prior to S/N 2395 (Mfg by Air Cruisers) Prior to S/N A5767 (Mfg. by Aerazur) Aft Door (Typical Both Sides) Prior to S/N 2593 (Mfg. by Air Cruisers) Prior to S/N A5839 (Mfg. by Aerazur)

DECORATIVE COVER FORWARD AND AFT IPL FIGURE 2 (SHEET 2 OF 4)

25-60-56

Page 10074 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

IF, 1K, 10F, 10K

DECORATIVE COVER FORWARD AND AFT IPL FIGURE 2 (SHEET 3 OF 4)

25-60-56

Page 10075 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

Forward Door (Typical Both Sides) Prior to S/N 2395 (Mfg by Air Cruisers) Prior to S/N A5767 (Mfg. by Aerazur) Aft Door (Typical Both Sides) Prior to S/N 2593 (Mfg. by Air Cruisers) Prior to S/N A5839 (Mfg. by Aerazur)

Forward Door (Typical Both Sides) S/N 2395 and Subs (Mfg by Air Cruisers) S/N A5767 and Subs (Mfg. by Aerazur) Aft Door (Typical Both Sides) S/N 2593 and Subs (Mfg. by Air Cruisers) S/N A5839 and Subs (Mfg. by Aerazur)

60A

60 40A

40B

50B

50B

50C 70A, 70C 190 (2 PLACES) 160, 160B 170, 180A 90

180, 180B

81 190 2 PLACES

120

130 (2 PLACES)

Forward Door (Typical Both Sides) Prior to S/N 2395 (Mfg by Air Cruisers) Prior to S/N A5767 (Mfg. by Aerazur) Aft Door (Typical Both Sides) Prior to S/N 2593 (Mfg. by Air Cruisers) Prior to S/N A5839 (Mfg. by Aerazur)

DECORATIVE COVER FORWARD AND AFT IPL FIGURE 2 (SHEET 4 OF 4)

25-60-56

Page 10076 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

AIRLINE PART NO.

NOMENCLATURE 1234567

UNITS EFF. PER CODE ASSY.

2 R

-1 D15358-101

R

-1A D15358-103

R

-1B D15358-105

R

-1C 62443-101

Decorative Cover, Forward Door, Velcro attachment configuration (NP) (Supsd by Item 1A) (Pre S.B. 004-25-30) (Supsd by Item 1C) (Pre S.B. A320 004-25-61) Decorative Cover, Forward Door, Velcro attachment configuration (NP) (Supsd by Item 1B) (Pre S.B. 004-25-30) (Supsd by Item 1D) (Pre S.B. A320 004-25-61) Decorative Cover, Forward Door, Velcro attachment configuration (NP) (Supsds Item 1A) (Pre S.B. 004-25-30) (Supsd by Item 1E) (Pre S.B. A320 004-25-61) Decorative Cover, Forward Door, Dual Lock Fastener attachment configuration (NP, Field Configuration part number only) (Supsds Item 1) (Post S.B. 004-25-30) (Pre S.B. A320 004-25-61)

A

RF

B

RF

E

RF

G

RF

- Item Not Illustrated

25-60-56

Page 10077 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

2 -1D 62443-103

R

1E 62367-101

R

1F 62367-301

R

-1G 62443-301

R

-1H 62443-303

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

Decorative Cover, Forward Door, Dual Lock Fastener attachment configuration (NP, Field Configuration part number only) (Supsds Item 1A) (Post S.B. 004-25-30) (Pre S.B. A320 004-25-61) Decorative Cover, Forward Door, Dual Lock Fastener attachment configuration (NP) (Supsds Item 1B) (Post S.B. 004-25-30) (Pre S.B. A320 004-25-61) (Supsd by Item 1J) Decorative Cover, Forward Door, Latch attachment configuration (NP) (Post S.B. A320 004-25-61) (Supsd by Item 1K) Decorative Cover, Forward Door, Latch attachment configuration (NP, Field Configuration part number only) (Post S.B. A320 004-25-61) Decorative Cover, Forward Door, Latch attachemnt configuration (NP, Field Configuration part number only) (Post S.B. A320 004-25-61)

H

RF

J

RF

P

RF

Q

RF

R

RF

- Item Not Illustrated

25-60-56

Page 10078 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

2 R

1J 62367-103

R

1K 62367-303

R

-10 D15359-101

R

-10A D15359-103

R

-10B D15359-105

Decorative Cover, Forward Door, Dual Lock Fastener attachment configuration (Fiberglass construction) (Supsds Item 1E) Decorative Cover, Forward Door, Latch attachment configuration (Fiberglass construction) (Supsds Item 1F) Decorative Cover, Aft Door, Velcro attachment configuration (NP) (Supsd by Item 10A) (Pre S.B. 004-25-30) (Supsd by Item 10C) (Pre S.B. A320 004-25-61) Decorative Cover, Aft Door, Velcro attachment configuration (NP) (Supsds Item 10) (Pre S.B. 004-25-30) (Supsd by Item 10D) (Pre S.B. A320 004-25-61) Decorative Cover, Aft Door, Velcro attachment configuration (NP) (Supsds Item 10A) (Pre S.B. 004-25-30) (Supsd by Item 10E) (Pre S.B. A320 004-25-61)

U

RF

V

RF

C

RF

D

RF

F

RF

- Item Not Illustrated

25-60-56

Page 10079 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

2 -10C 62444-101

R

-10D 62444-103

R

10E 62371-101

R

10F 62371-301

R

-10G 62444-301

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

Decorative Cover, Aft Door, Dual Lock Fastener attachment configuration (NP, Field Configuration part number only) (Supsds Item 10) (Post S.B. 004-25-30) (Pre S.B. A320 004-25-61) Decorative Cover, Aft Door, Dual Lock Fastener attachment configuration (NP, Field Configuration part number only) (Supsds Item 10A) (Post S.B. 004-25-30) (Pre S.B. A320 004-25-61) Decorative Cover, Aft Door, Dual Lock Fastener attachment configuration (NP) (Supsds Item 10B) (Post S.B. 004-25-30) (Pre S.B. A320 004-25-61) (Supsd by Item 10J) Decorative Cover, Aft Door, Latch attachment configuration (NP) (Post S.B. A320 004-25-61) (Supsd by Item 10K) Decorative Cover, Aft Door, Latch attachment configuration (NP, Field Configuration part number only) (Post S.B. A320 004-25-61)

K

RF

L

RF

M

RF

N

RF

S

RF

- Item Not Illustrated

25-60-56

Page 10080 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

2 -10H 62444-303

R

10J 62371-103

R

10K 62371-303

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

20 B15474-1

Decorative Cover, Aft Door, Latch attachment configuration (NP, Field Configuration part number only) (Post S.B. A320 004-25-61) Decorative Cover, Aft Door, Dual Lock Fastener attachment configuration (Fiberglass construction) (Supsds Item 10E) Decorative Cover, Aft Door, Latch attachment configuration (Fiberglass construction) (Supsds Item 10F) .Clip

30 MS20426B4-8

ATTACHING PARTS .Rivet

30A MS20426B4-4

.Rivet

T

RF

W

RF

Y

RF

A-M, Q-W

2

A-H,L, Q-T,V J,M,U, W

4 4

*** -40 B15472-101

.Spring Clip (Supsd by Item 40A)

2

- Item Not Illustrated

25-60-56

Page 10081 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

2 40A B15472-103

40B 66606-101

-50 MS20426B4-8 -50A MS20426B4-6

50B MS20426B4-5

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

.Spring Clip (Supsds Item 40) (Fwd Door Cover prior to S/N 2395 mfg. by Air Cruisers or prior to S/N A5767 mfg. by Aerazur) (Aft Door Cover prior to S/N 2593 mfg. by Air Cruisers or prior to S/N A5839 mfg. by Aerazur) (Used in conjunction with Item 60) (Supsd by Item 40B) .Spring Clip (Supsds Item 40A) (Fwd Door Cover S/N 2395 and Subs mfg. by Air Cruisers or S/N A5767 and Subs mfg. by Aerazur) (Aft Door Cover S/N 2593 and Subs mfg. by Air Cruisers or S/N A5839 and Subs mfg. by Aerazur) (Used in conjunction with Items 50C and 60A) (Supsds Item 40A) ATTACHING PARTS .Rivet (Supsd by Item 50A .Rivet (Supsds Item 50) (Supsd by Item 50B) .Rivet (Supsds Item 50A)

2

2

4 4

4

- Item Not Illustrated

25-60-56

Page 10082 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

2 50C MS20426AD4-4

60 B15476-1

60A 66604-3

70 B15216-1

70A B15216-3

70B B15216-1

70C B15216-3

-70D B15216-5 70E B15216-7

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

.Rivet (See Item 40B for S/N effectivity) (Used in conjunction with Items 40B and 60A) .Spacer (See Item 40A for S/N effectivity) (Used in conjunction with Item 40A) (Supsd by Item 60A) .Strip, Reinforcement (See Item 40B for S/N effectivity) (Used in conjunction with Items 40B and 50C) (Supsds Item 60) *** .Gage Viewing Port Forward Door (Prior to S/N 657) .Gage Viewing Port Forward Door (S/N 657 and Subs) .Gage Viewing Port Aft Door (Prior to S/N 611) .Gage Viewing Port Aft Door (S/N 611 and Subs) .Gage Viewing Port (Supsd by Item 70E) .Gage Viewing Port (Supsds by Item 70D)

2

2

2

A,B,E, G,H,J

1

A,B,E, G,H,J, P,Q,R C,D,F, K,L,M

1

1

C,D,F, K,L,M, N,S,T

1

U-Y

1

U-Y

1

- Item Not Illustrated

25-60-56

Page 10083 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

AIRLINE PART NO.

NOMENCLATURE 1234567

2 -80 C19763-1

.Transition Collar (NP)

81 C19763-3

.Transition Collar (NP)

90 MS20426B4-8

ATTACHING PARTS .Rivet (NP)

R

-100 MILF218401BP

R

-110 60887-101

120 60406-1

*** .Velcro Hook, Black, 1 In. (25.4 mm) Wide x 15 In. (381 mm) Long (Pre S.B. 004-25-30) .Floor Seal Assembly (Supsd by Item 160) (Pre S.B. 004-25-28) .Plate, Nut (Fwd Door - prior to S/N 2395 mfg. by Air Cruisers or A5767 mfg. by Aerazur) (Aft Door - prior to S/N 2593 mfg. by Air Cruisers or A5839 mfg. by Aerazur) (Used in conjunction with Item 130)

UNITS EFF. PER CODE ASSY. A,C,G, K,Q,S B,D,E, F,H,L, R,T

1

A-H, K,L, Q-T,V

4

A,B,C, D,E,F

1

B,D,H, L,R,T

1

B,D,E, F,H,R, T

2

1

- Item Not Illustrated

25-60-56

Page 10084 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

2 130 MS24693C25

140 SJ3551

150 SJ3551

160 62338-101

160A 62338-103

160B 62338-105

170 65031-101

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

.Screw, Flat Head B,D,E, #6-32 x 0.83 F,H,R, (Fwd Door - prior to S/N T 2395 mfg. by Air Cruisers or A5767 mfg. by Aerazur) (Aft Door - prior to S/N 2593 mfg. by Air Cruisers or A5839 mfg. by Aerazur) (Used in conjunction with Item 120) (True P/N is MS24693-C25) .Dual Lock Fastener, 15 In. G,H,J, (381 mm) Long (V76381) K,L,M, (Post S.B. 004-25-30) U,W .Dual Lock Fastener, 2.5 In. G,H,J, (63.5 mm) Long (V76381) K,L,M, (Post S.B. 004-25-30) U,W .Floor Seal Assembly E,F, (Supsds Item 110) P,N,V,Y (Post S.B. 004-25-28) (Pre S.B. A320 004-25-71) .Floor Seal Assembly J,P,U,V (Post Optional S.B. A320 004-25-71 and Amendment #2) .Floor Seal Assembly M,N, (Post Optional S.B. A320 W,Y 004-25-71 and Amendment #2)

4

.Latch, Male (Post S.B. A320 004-25-71) (Supsd by Item 180A)

1

25-60-56

N-T, V,Y

1

2

1

1

1

Page 10085 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

2 180 65031-102

180A 66095-1 180B 66095-2

190 MS20426AD4-4

R

-200 VC218-8 -210 E15428-101 -210A E15428-103 -210B -210C -210D -210E -220 -220A -220B -220C -220D -220E

64948-1 64948-3 64948-5 64948-7 E15426-101 E15426-103 64946-1 64946-3 64946-5 64946-7

AIRLINE PART NO.

NOMENCLATURE 1234567

UNITS EFF. PER CODE ASSY.

.Latch, Male N-T, (Post S.B. A320 004-25-71) V,Y (Supsd by Item 180B) .Latch, Male N,P,V,Y (Supsds Item 170) .Latch, Male N,P,V,Y (Supsds Item 180) ATTACHING PARTS .Rivet N-T, V,Y *** .Cap Plug (V99017) N,P,V,Y (True P/N is VC-218-8) .Hard Cover Assembly A,G,Q .Hard Cover Assembly B,E,H, R .Hard Cover Assembly J .Hard Cover Assembly P .Hard Cover Assembly U .Hard Cover Assembly V .Hard Cover Assembly C,K,S .Hard Cover Assembly D,F,L,T .Hard Cover Assembly M .Hard Cover Assembly N .Hard Cover Assembly W .Hard Cover Assembly Y

1

1 1

4

2 1 1 1 1 1 1 1 1 1 1 1 1

- Item Not Illustrated

25-60-56

Page 10086 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

50A (PRE S.B. A320 004-25-64 AND AMENDMENT #4)

120

1B, 1C

180 (POST S.B. 004-25-51, FAA AD 2001-15-06, AND DGAC AD 2000-359-152(B))

170 (POST S.B. 004-25-51, FAA AD 2001-15-06, AND DGAC AD 2000-359-152(B))

70

SLIDE ASSEMBLY IPL FIGURE 3 (SHEET 1 OF 2)

25-60-56

Page 10087 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

270* *POST S.B. A320 004-25-64 AND AMENDMENT #4

210*

230* (6 PLACES)

220* 190 50B* 260*

250*

240* (8 PLACES) 200* 250* 50C*

120

1H,1J,1M, 1N, 1P, 1Q 280 (S/N 1400 and Subs) (POST S.B. A320 004-25-72)

180

290 (POST S.B. A320 004-25-97 AND D31910-129, -131 ONLY) 170 70 (POST S.B. A320 004-25-74)

70 (PRE S.B. A320 004-25-74)

SLIDE ASSEMBLY IPL FIGURE 3 (SHEET 2 OF 2)

25-60-56

Page 10088 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM

AIRLINE PART NO.

NOMENCLATURE 1234567

UNITS EFF. PER CODE ASSY.

3 R

-1 D31910-101

Slide Assembly without Re-Entry tape (NP) (See IPL Figure 1 for NHA) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Supsd by Item 1B) (Pre S.B. A320 004-25-64 and Amendment #4) (Supsd by Item 1F)

A

RF

R

-1A D31910-103

B

RF

R

1B D31910-105

Slide Assembly with Re-Entry tape (NP) (See IPL Figure 1 for NHA) (Pre S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Supsd by Item 1C) (Pre S.B. A320 004-25-64 and Amendment #4) (Supsd by Item 1G) Slide Assembly without Re-Entry tape (NP) (See IPL Figure 1 for NHA) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Supsds Item 1) (Pre S.B. A320 004-25-64 and Amendment #4) (Supsd by Item 1D) (Pre S.B. A320 004-25-72) (Supsd by Item 1K)

C

RF

- Item Not Illustrated

25-60-56

Page 10089 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM

R

3 1C D31910-107

R

-1D D31910-109

R

-1E D31910-111

AIRLINE PART NO.

NOMENCLATURE 1234567

Slide Assembly with Re-Entry tape (NP) (See IPL Figure 1 for NHA) (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) (Supsds Item 1A) (Pre S.B. A320 004-25-64 and Amendment #4) (Supsd by Item 1E) (Pre S.B. A320 004-25-72) (Supsd by Item 1L) Slide Assembly with LED slide lighting and without Re-Entry tape (NP) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-64 and Amendment #4) (Supsds Item 1B) (Pre S.B. A320 004-25-72) (Supsd by Item 1H) Slide Assembly with LED slide lighting and Re-Entry tape (NP) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-64 and Amendment #4) (Supsds Item 1C) (Pre S.B. A320 004-25-72) (Supsd by Item 1J)

UNITS EFF. PER CODE ASSY. D

RF

E

RF

F

RF

- Item Not Illustrated

25-60-56

Page 10090 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM

R

3 -1F D31910-113

R

-1G D31910-115

R

1H D31910-121

R

1J D31910-123

AIRLINE PART NO.

NOMENCLATURE 1234567

Slide Assembly with LED lights and without Re-Entry tape (NP, Field Configuration part number only) (Post S.B. A320 004-25-64 and Amendment #4) (Supsds Item 1) Slide Assembly with LED lights and Re-Entry tape (NP, Field Configuration part number only) (Post S.B. A320 004-25-64 and Amendment #4) (Supsds Item 1A) Slide Assembly with LED lights and without Re-Entry tape (NP) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-72) (Supsds Item 1D) (Supsd by Item 1M) (Pre S.B. A320 004-25-97) Slide Assembly with LED lights and Re-Entry tape (NP) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-72) (Supsds Item 1E) (Supsd by Item 1N) (Pre S.B. A320 004-25-97)

UNITS EFF. PER CODE ASSY. G

RF

H

RF

J

RF

K

RF

- Item Not Illustrated

25-60-56

Page 10091 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM

R

3 -1K D31910-117

R

-1L D31910-119

R

1M D31910-125

R

1N D31910-127

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

Slide Assembly without Re-Entry tape (NP, Field Configuration part number only) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-72) (Supsds Item 1B) (Pre S.B. A320 004-25-97) (Supsd by Item 1U) Slide Assembly with ReEntry tape (NP, Field Configuration part number only) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-72) (Supsds Item 1C) (Pre S.B. A320 004-25-97) (Supsd by Item 1V) Slide Assembly with thermobond construction, LED lights and without Re-Entry tape (NP) (See IPL Figure 1 for NHA) (Supsds Item 1H) (Supsd by Item 1P) (Pre S.B. A320 004-25-97) Slide Assembly with thermobond construction, LED lights, and Re-Entry tape (NP) (See IPL Figure 1 for NHA) (Supsds Item 1J) (Supsd by item 1Q) (Pre S.B. A320 004-25-97)

L

RF

M

RF

N

RF

P

RF

- Item Not Illustrated

25-60-56

Page 10092 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM

R

3 1P D31910-129

R

1Q D31910-131

R

-1R D31910-221

R

-1T D31910-223

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

Slide Assembly with thermobond construction, LED lights, a wrapper, and without Re-Entry tape (See IPL Figure 1 for NHA) (Supsds Item 1M) (Post S.B. A320 004-25-97) Slide Assembly with thermobond construction, LED lights, a wrapper, and Re-Entry tape (See IPL Figure 1 for NHA) (Supsds Item 1N) (Post S.B. A320 004-25-97) Slide Assembly with LED lights, a wrapper, and without Re-Entry tape (NP, Field Configuration part number only) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-97) Slide Assembly with LED lights, a wrapper, and Re-Entry tape (NP, Field Configuration part number only) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-97)

Q

RF

R

RF

T

RF

U

RF

- Item Not Illustrated

25-60-56

Page 10093 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM

R

3 -1U D31910-217

R

-1V D31910-219

-10 -15 -20 -30 -40 -50

D37091-101 60461-101 9166L5 2525 B16045-1 A3-06-0746-101

50A D39011-101

50B 65349-3

AIRLINE PART NO.

NOMENCLATURE 1234567

Slide Assembly without Re-Entry tape (NP, Field Configuration part number only) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-97) (Supsds Item 1K) Slide Assembly with Re-Entry tape (NP, Field Configuration part number only) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-97) (Supsds Item 1L) Deleted Deleted Deleted Deleted Deleted .Lamp Harness Assembly (V55827) (Supsd by Item 50A) .Lamp Harness Assembly (P2-01-0035-001; V55827) (Supsds Item 50) (Pre S.B A320 004-25-64 and Amendment #4) .LED Harness Assembly (Post S.B. A320 004-25-64 and Amendment #4)

UNITS EFF. PER CODE ASSY. V

RF

W

RF

2

A-D

2

E-U

1

- Item Not Illustrated

25-60-56

Page 10094 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 3 50C 65349-1

-60 70 -80 -80A -90 -100 -110 120

B19958-101 C19988-101 C19347-111 C19347-104 C19347-107 C19347-121 B19882-1 D31202-111

-130 MILF218401BP

-140 MILF218401BP

-150 B30299-511

-160 60157-101 -160A 60157-103

AIRLINE PART NO.

NOMENCLATURE 1234567

UNITS EFF. PER CODE ASSY.

.LED Harness Assembly E-U (Post S.B. A320 004-25-64 and Amendment #4) Deleted .Knife Sheath Assembly Deleted Deleted Deleted Deleted Deleted .Re-Entry Strap B,D,F, (Post Optional S.B. A320 H,M,K, 004-25-57) P,R, U-W .Fastener, Pile, 1 x 9 In. B,D,F, (25.4 x 228.6 mm) Black, H,M,K, Class 1 (Post Optional S.B. P,R, A320 004-25-57) U-W .Fastener, Pile, 1 x 2 In. B,D,F, (25.4 x 50.8 mm) Black, H,M,K, Class 1 (Post Optional S.B. P,R, A320 004-25-57) U-W .Snap Patch Assembly B,D,F, (Post Optional S.B. H,M,K, A320 004-25-57) P,R, U-W .Reservoir Sling (Pre S.B. 004-25-07) .Reservoir Sling (Post S.B. 004-25-07)

1

1

1

1

6

4

1 1

- Item Not Illustrated

25-60-56

Page 10095 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 3 170 64328-101

180 62699-101

190 65424-101

200 65424-103

210 65424-105

220 65424-107

230 65475-101

240 65489-101

250 65476-101

260 65477-101

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

.Restraint with Color Code (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) .Restraint, Tracking (Post S.B. 004-25-51, FAA AD 2001-15-06, and DGAC AD 2000-359-152(B)) .Guide, Wire (Post S.B. A320 004-25-64 and Amendment #4) .Guide, Wire (Post S.B. A320 004-25-64 and Amendment #4) .Guide, Wire (Post S.B. A320 004-25-64 and Amendment #4) .Guide, Wire (Post S.B. A320 004-25-64 and Amendment #4) .Patch, Mounting (Post S.B. A320 004-25-64 and Amendment #4) .Patch, Mounting 90° (Post S.B. A320 004-25-64 and Amendment #4) .Patch, ECM Mounting (Post S.B. A320 004-25-64 and Amendment #4) .Patch, Mounting Runway (Post S.B. A320 004-25-64 and Amendment #4)

C-W

1

C-W

1

E-W

1

E-W

1

E-W

1

E-W

1

E-W

6

E-W

8

E-W

2

E-W

1

- Item Not Illustrated

25-60-56

Page 10096 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 3 270 65488-101

280 B31238-105 290 70223-101

AIRLINE PART NO.

NOMENCLATURE 1234567

UNITS EFF. PER CODE ASSY.

.Patch, Mounting Runway E-W (Post S.B. A320 004-25-64 and Amendment #4) .Retainer, Hose G-W (Post S.B. A320 004-25-72) .Wrapper Q,R, (Post S.B. A320 004-25-97) T-W

25-60-56

1

1 1

Page 10097 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

This page intentionally left blank.

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COMPONENT MAINTENANCE MANUAL D31516 D31517

PRE S.B. A320 004-25-61 400, 410

57 56

25, 25A, 25B

55 56 57

400, 410

420 POST S.B. A320 004-25-61 425 415

430 (4 PLACES) 425

435 (4 PLACES)

PACKBOARD ASSEMBLY IPL FIGURE 4 (SHEET 1 OF 3)

25-60-56

Page 10099 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

270

265 280 330 265 265 290A

290A

360 (2 PLACES) 370A (4 PLACES)

300A

320, 320A 310 380 340, 340A 350, 350A 340, 340B 345

PACKBOARD ASSEMBLY IPL FIGURE 4 (SHEET 2 OF 3)

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Page 10100 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

380

250 180 110

100 170

130

200

160

240

60 80

190 120 220 210

230A

140

PACKBOARD ASSEMBLY IPL FIGURE 4 (SHEET 3 OF 3)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

4 R

-1 E15366-101

R

-1A E15366-301

R

-5 62366-101

Packboard Assembly, Forward Door (with the Velcro method of decorative cover attachment - Pre S.B. 004-25-30) (with the Dual Lock Fastener method of decorative cover attachment - Post S.B. 004-25-30) (See IPL Figure 1 for NHA) (Incorporated large diameter lock pin holes Post S.B. 004-25-4; Air Cruisers S/N C0023 and Subs; Aerazur S/N A5043 and Subs) (Supsd by Item 5) (Pre S.B. A320 004-25-61) Packboard Assembly, Forward Door (with the Latch method of decorative cover attachment) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-61) Packboard Assembly, Forward Door (with the Dual Lock Fastener method of decorative cover attachment) (See IPL Figure 1 for NHA) (Post S.B. 004-25-30) (Supsds Item 1) (NP) (Pre S.B. A320 004-25-61) (Pre S.B. A320 004-25-75 and Amendment #5)

A

RF

E

RF

C

RF

- Item Not Illustrated

25-60-56

Page 10102 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

R

PART NUMBER

4 -5A 62366-103

-5B 62366-105

R

-10 E15367-101

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

Packboard Assembly, Forward Door (with the Dual Lock Fastener method of decorative cover attachment) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-75 and Amendment #5) (Pre Amendment #7) (Supsd by Item 5B) Packboard Assembly, Forward Door (See IPL Figure 1 for NHA) (Post Amendment #7) (Supsds Item 5A) Packboard Assembly, Aft Door (with the Velcro method of decorative cover attachment - Pre S.B. 004-25-30) (with the Dual Lock Fastener method of decorative cover attachment - Post S.B. 004-25-30) (See IPL Figure 1 for NHA) (Incorporated large diameter lock pin holes post S.B. 004-25-4; Air Cruisers S/N C0023 and Subs; Aerazur S/N A5043 and Subs) (Supsd by Item 15) (Pre S.B. A320 004-25-61)

G

RF

J

RF

B

RF

- Item Not Illustrated

25-60-56

Page 10103 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

R

4 -10A E15367-301

R

-15 62370-101

R

-15A 62370-103

-15B 62370-105

-20 60142-101

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

Packboard Assembly, Aft Door (with the Latch method of decorative cover attachment) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-61) Packboard Assembly, Aft Door (with the Dual Lock Fastener method of decorative cover attachment (NP) (See IPL Figure 1 for NHA) (Post S.B. 004-25-30) (Supsds Item 10) (Pre S.B. A320 004-25-61) (Pre S.B. A320 004-25-78 and Amendment #5) Packboard Assembly, Aft Door (with the Latch method of decorative cover attachment) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-78 and Amendment #5) (Pre Amendment #6) (Supsd by Item 15B) Packboard Assembly, Aft Door (See IPL Figure 1 for NHA) (Post Amendment #6) (Supsds Item 15A) .Packboard Sub-Assembly, Forward Door (Supsd by Item 25) (NP)

F

RF

D

RF

H

RF

K

RF

A,E

1

- Item Not Illustrated

25-60-56

Page 10104 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

4 25 62377-101

25A 62377-103 25B 62377-105 -30 60143-101

-35 62378-101

-35A 62378-103 -35B 62378-105 -37 PPPT60-1 -39 P29-1

-39A P295-1

-39B M12397-1

.Packboard Sub-Assembly, Forward Door (Supsds Item 20) (NP) .Packboard Sub-Assembly, Forward Door (NP) .Packboard Sub-Assembly, Forward Door (NP) .Packboard Sub-Assembly, Aft Door (NP) (Supsd by Item 35) .Packboard Sub-Assembly, Aft Door (NP) (Supsds Item 30) .Packboard Sub-Assembly, Aft Door (NP) .Packboard Sub-Assembly, Aft Door (NP) ..Tape, Green (True P/N is PPP-T-60-1) ..Tape, Black Fire Retardant (V99742) (True P/N is P-29-1) (Supsd by Item 39B) ..Tape, Black Fire Retardant (V99742) (Alternative to Item 39) (True P/N is P-295-1) (Supsd by Item 39B) ..Tape, Black Fire Retardant (Supsds Items 39 and 39A) (Reference S.I.L. 25-252)

C

1

G

1

J

1

B,F

1

D

1

H

1

K

1

D

A/R

D

A/R

D

A/R

D

A/R

- Item Not Illustrated

25-60-56

Page 10105 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

4 -40 MILF218401BP

-50 MILF218401BP

R

55 SJ3551

R

56 SJ3551

R

57 SJ3551

60 C16870-1 -70 80 -90 -92 R

AIRLINE PART NO.

..Velcro Pile, Black, 1 In. x 8.875 In. (25.4 x 225.4 mm) Long (Pre S.B. 004-25-30) ..Velcro Pile, Black, 1 In. x 1.875 In. (25.4 x 47.6 mm) Long (Pre S.B. 004-25-30) ..Dual Lock Fastener, 9 In. (228.6 mm) Long (V76381) (Post S.B. 004-25-30) ..Dual Lock Fastener, 2 In. (50.8 mm) Long (V76381) (Post S.B. 004-25-30) ..Dual Lock Fastener, 2.25 In. (57.2 mm) Long (V76381) (Post S.B. 004- 25-30) ..Side Bracket L. H. (NP)

C15457-1 C16870-2 C15457-2 C15494-101

..Side Bracket L. H. (NP) ..Side Bracket R. H. (NP) ..Side Bracket R. H. (NP) ..Chock Assembly, Cylinder

-92A C15494-105

..Chock Assembly, Cylinder ATTACHING PARTS ..Rivet, Solid

-93 MS20426A4-8 -94 NAS1169DD6

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

..Washer, Dimpled (True P/N is NAS1169-DD6)

A,B

1

A,B

4

A,B,C, D

1

A,B,C, D

2

A,B,C, D

2

A,C

1

B,D A,C B,D B,D,F, H K

1 1 1 1 1

B,D,F, H

6

B,D,F, H

6

- Item Not Illustrated

25-60-56

Page 10106 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

4 -94A MS24693A29

-94B MS21083D06

-95 E15429-101 -95A E15425-101 -95B 64211-101 -95C 64212-101 -95D 64211-103 -95E -95F 100 110

70869-1 70847-1 C16866-1 B15452-1

120 PL9 130 MS171534

140 D15467-1 -150 D15445-1 160 B15449-1 170 MS171496

AIRLINE PART NO.

NOMENCLATURE 1234567

..Screw, Flt. Hd., Csk., .138-32 (True P/N is MS24693-A29) ..Nut, Self Locking, Hex, .138-32 *** ..Tray, Packboard (NP) ..Tray, Packboard (NP) ..Tray, Packboard (NP) (Supsd by Item 95D) ..Tray, Packboard (NP) ..Tray, Packboard (NP) (Supsds Item 95B) ..Tray, Packboard (NP) ..Tray, Packboard (NP) .Bottom Housing .Pawl ATTACHING PARTS .Shoulder Screw, #8-32 UNC (V3J371) .Spring Pin, 0.125 Dia. x 1.000 Long *** ..Shaft Release (NP) ..Shaft Release (NP) ..Slotted Cap ATTACHING PARTS ..Spring Pin, 0.094 Dia. x 0.500 Long

UNITS EFF. PER CODE ASSY. K

6

K

6

A,E B,F C,G

1 1 1

D,H C,G

1 1

J K

1 1 1 1 4 1

A-C E-G

1 1 1

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

4 180 B16865-1 190 C15451-1 200 MS171532 210 MS51957-13 220 MS35338-135 -230 MS24693C51 230A MS24693C52 240 MS21083C08 250 B15450-1 -260 B15463-1 265 62351-1 270 D31880-101 280 ABA45 -290 B15497-1 290A B15497-3 -300 MS25281F2 300A MS25281R3

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

..Bushing (NP) ..Pin Shield ..Spring Pin, 0.125 Dia. x 0.875 Long ..Screw, Pan Head, #4-40 x 0.250 Long ..Lock Washer, #4 Deleted ..Screw, Flat Head (NP) (True P/N is MS24693-C52) ..Nut, Hex (NP) *** ..Spacer (NP) ..Attachment Strip (Supsd by Item 265) ..Attachment Strip (Supsds Item 260) ..Upper Lacing Cover ATTACHING PARTS ..Rivet (V3J371) *** ..Foam Pad (Pre S.B. 004-25-13) ..Rubber Pad (Post S.B. 004-25-13) .Clamp (Supsd by Item 300A) .Clamp (Supsds Item 300)

6 2 12 12 12 4 4 2 3 3 1 12 2 2 1 1

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

AIRLINE PART NO.

NOMENCLATURE 1234567

UNITS EFF. PER CODE ASSY.

4 310 MS51958-64 320 AN960C10L 320A NAS1149C0332R 330 F22NKM02 340 340A 340B 345 350 350A 360

MS3215-4031 MS16624-4025 MS16624-4031 70837-1 B16954-1 70838-1 60327-1

-370 MS20470A4-4 370A MS20470AD4-5

380 63433-101 -382 62753-101 -382A 62753-103 -382B 70841-101

ATTACHING PARTS .Screw, #10-32 x 0.625 .Washer .Washer (ALT to Item 320) .Nut (V3J371) *** ...Ring, Retaining ...Ring, Retaining ..Ring, Retaining ...Spacer ...Pin, Mounting ...Pin, Mounting ..Strap, Wear Bar

1 1 1 1 A-H J,K J,K J,K A-H J,K

ATTACHING PARTS ..Rivet (Supsd by Item 370A) ..Rivet (Supsds Item 370) *** .Release Mechanism, C,G,J Forward ..Support Bracket Assembly A,C,E ..Support Bracket Assembly G ..Support Bracket Assembly J

4 2 2 2 2 2 4

8 8

1 1 1 1

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

4 -384 62754-1

-384A 62754-2

-384B 66825-1

-384C 66825-2

-384D 70839-1 -384E 70839-2 -390 -392 -392A -394

63434-101 D16955-101 D16955-102 D16961-1

-394A D16961-2

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

...Bracket, Step, L.H. (NP) (Pre S.B. A320 004-25-75 and Amendment #5) ...Bracket, Step, R.H. (NP) (Pre S.B. A320 004-25-75 and Amendment #5) ...Bracket, Step, L.H. (Post S.B. A320 004-25-75 and Amendment #5) (Pre Amendment #7) ...Bracket, Step, R.H. (Post S.B. A320 004-25-75 and Amendment #5) (Pre Amendment #7) ...Bracket, Step, L.H. (Post Amendment #7) ...Bracket, Step, R.H. (Post Amendment #7) .Release Mechanism, Aft Deleted Deleted ..Bracket, Lower Mounting, L.H. (NP) (Pre S.B. A320 004-25-78 and Amendment #5) ..Bracket, Lower Mounting, R.H. (NP) (Pre S.B. A320 004-25-78 and Amendment #5)

A,C,E

1

A,C,E, G

1

A,C,E, G

1

A,C,E

1

J

1

J

1

D,H,K

1

B,D,F

1

B,D,F

1

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. ITEM

PART NUMBER

4 -394B 66826-1

-394C 66826-2

-394D 70840-1 -394E 70840-2

400 B15475-1 410 MS20426AD4-6 415 65460-1 420 65460-2

425 65032-1 430 MS24693C7

435 MS21083C04

AIRLINE PART NO.

NOMENCLATURE 1234567

UNITS EFF. PER CODE ASSY.

..Bracket, Lower Mounting, B,D,F, L.H. (Post S.B. A320 004H 25-78 and Amendment #5) ..Bracket, Lower Mounting, B,D,F, R.H. (Post S.B. A320 004H 25-78 and Amendment #5) ..Bracket, Lower Mounting, K L.H. (Post Amendment #6) ..Bracket, Lower Mounting, K R.H. (Post Amendment #6) *** .Plate, Clip (Prior to System S/N 7582) .Rivet (Prior to System S/N 7582) .Latch, Female Left E,F (Post S.B. A320 004-25-61) .Latch, Female Right E,F (Post S.B. A320 004-25-61) ATTACHING PARTS .Shim E,F (Post S.B. A320 004-25-61) .Screw, Flat Csk. E,F (Post S.B. A320 004-25-61) (True P/N is MS24693-C7) .Nut, Self Locking E,F (Post S.B. A320 004-25-61)

1

1

1 1

2 4 1 1

2 4

4

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

300A (2 PLACES)

300A (2 PLACES)

260B

260A

1A, 1B

290 (4 PLACES)

FORWARD PACKBOARD ASSEMBLY, LATCH CONFIGURATION IPL FIGURE 4A (SHEET 1 OF 2)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

240

270 270A (2 PLACES)

310 (8 PLACES)

20

50, 50A, 50B 190A

180 200

60 150 (12 PLACES)

10

190A

100A, 100B

180

140 (2 PLACES)

190A

70

30, 30A

180 210

80A, 80B

40

170A (6 PLACES) 140 (2 PLACES)

160 (6 PLACES)

230 90A, 90B

75 77 (TYPICAL 4 PLACES)

110, 110A 145

210 230

110, 110B 130, 130A

FORWARD PACKBOARD ASSEMBLY, LATCH CONFIGURATION IPL FIGURE 4A (SHEET 2 OF 2)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 4A -1 62366-301

1A 62366-303

1B 62366-305

10 MS25281R3 20 F22NKM02 30 AN960C10L 30A NAS1149C0332R 40 MS51958-64 50 62377-301

AIRLINE PART NO.

NOMENCLATURE 1234567

Packboard, Forward, Latch Configuration (NP) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-61) (Pre S.B. A320 004-25-75 and Amendment #5) Packboard, Forward, Latch Configuration (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-75 and Amendment #5) (Pre Amendment #7) (Supsd by Item 1B) Packboard, Forward, Latch Configuration (See IPL Figure 1 for NHA) (Post Amendment #7) (Supsds Item 1A) .Clamp, Loop ATTACHING PARTS .Nut (V3J371) .Washer .Washer (ALT to Item 30) .Screw *** .Packboard Sub-Assembly, Forward (NP)

UNITS EFF. PER CODE ASSY. A

RF

B

RF

C

RF

1 1 1 1 1 A

1

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 4A 50A 62377-303 50B 62377-305 60 B15473-1 70 63433-101 75 66623-101 77 PL9

-80 62753-101

80A 62753-103

80B 70841-101 -90 62754-1

90A 66825-1

90B 70839-1

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

.Packboard Sub-Assembly, Forward (NP) .Packboard Sub-Assembly, Forward (NP) ..Plate, Back-Up ..Release Assembly ...Pawl Assembly ATTACHING PARTS ...Screw (#8-32 UNC) (V3J371) *** ...Bracket Support Assembly (Pre S.B. A320 004-25-75 and Amendment #5) ...Bracket Support Assembly (Post S.B. A320 004-25-75 and Amendment #5) (Pre Amendment #7) ...Bracket Support Assembly (Post Amendment #7) ....Bracket, Step L.H. (NP) (Pre S.B. A320 004-25-75 and Amendment #5) ....Bracket, Step L.H. (Post S.B. A320 004-25-75 and Amendment #5) (Pre Amendment #7) ....Bracket, Step, L.H. (Post Amendment #7)

B

1

C

1 4 1 1 4

A

1

B

1

C

1

A

1

B

1

C

1

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 4A -100 62754-2

100A 66825-2

100B 70839-2 110 110A 110B -120 130 130A 140

MS3215-4031 MS16624-4025 MS166624-4031 60300-1 B16954-1 70838-1 MS24693C23

145 70837-1 150 MS20470AD4-8 160 NAS1169DD8

-170 MS20426B5-6 170A MS20426B5-7

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

....Bracket, Step R.H. (NP) (Pre S.B. A320 004-25-75 and Amendment #5) ....Bracket, Step R.H. (Post S.B. A320 004-25-75 and Amendment #5) (Pre Amendment #7) ....Bracket, Step. R.H. (Post Amendment #7) ....Ring, Retaining ....Ring, Retaining ....Ring, Retaining ....Support, Rear ....Pin, Mounting ....Pin, Mounting ....Screw, Csk. (True P/N is MS24693-C23) ....Spacer ATTACHING PARTS ...Rivet ...Washer, Dimpled (True P/N is NAS1169-DD8) ...Rivet (Supsd by Item 170A) ...Rivet (Supsds Item 170)

A

1

B

1

C

1

A,B C C

4 2 2 1 2 2 4

A,B C

C

2 12 6

6 6

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 4A 180 NAS1169DD6

-190 MS20426AD4-8

190A MS20426AD4-9

200 B15468-1 210 60327-1 -220 MS20470A4-4 230 MS20470AD4-5

240 D31880-101 -250 65460-1 -260 65460-2 260A 66094-1 260B 66094-2 270 62351-1 270A 62351-3

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

...Washer, Dimpled (True P/N is NAS1169-DD6) ...Rivet (Pre S.B. A320 004-25-75 and Amendment #5) ...Rivet (Post S.B. A320 004-25-75 and Amendment #5) *** ..Bar, Wear ..Strap, Wear Bar ATTACHING PARTS ..Rivet (Supsd by Item 230) ..Rivet (Supsds Item 220) *** ..Cover, Upper Lacing ..Latch, Female Left (Supsd by Item 260A) ..Latch, Female Right (Supsd by Item 260B) ..Latch, Female Left (Supsds Item 250) ..Latch, Female Right (Supsds Item 260) ..Strip, Attachment ..Strip, Attachment

4

A

4

B

4

2 4 8 8

1 1 1 1 1 1 2

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 4A -280 65032-1 290 MS21083C04 -300 MS24693C6

300A MS24693C5

310 ABA45 -320 64211-301 -320A 64211-303 -320B 70869-3

AIRLINE PART NO.

NOMENCLATURE 1234567

Deleted ATTACHING PARTS ..Nut, Self Locking ..Screw, Flat Csk. (Supsd by Item 300A) (True P/N is MS24693-C6) ..Screw, Flat Csk. (Supsds Item 300) (True P/N is MS24693-C5) ..Rivet (V3J371) *** ..Tray, Packboard (NP) (Supsd by Item 320A) ..Tray, Packboard (NP) (Supsds Item 320) ..Tray, Packboard (NP)

UNITS EFF. PER CODE ASSY.

4 4

4

8 A,B

1

A,B

1

C

1

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

270A (2 PLACES)

270A (2 PLACES)

230B

230A

1A, 1B

260 (4 PLACES)

AFT PACKBOARD ASSEMBLY, LATCH CONFIGURATION IPL FIGURE 4B (SHEET 1 OF 2)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

210 250 250A (2 PLACES)

50, 50A, 50B

60

280 (8 PLACES)

20

180

160, 160A

150A (6 PLACES)

10

140 (6 PLACES) 30, 30A 40 120B, 120C

70

170 200A (4 PLACES)

170

75 77 (TYPICAL 4 PLACES) 100, 100A 115

130B, 130C 100, 100B 110, 110A

200A (4 PLACES)

AFT PACKBOARD ASSEMBLY, LATCH CONFIGURATION IPL FIGURE 4B (SHEET 2 OF 2)

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 4B -1 62370-301

1A 62370-303

1B 62370-305

10 MS25281R3 20 F22NKM02 30 AN960C10L 30A NAS1149C0332R 40 MS51958-64 50 62378-301 50A 62378-303

AIRLINE PART NO.

NOMENCLATURE 1234567

Packboard, Aft, Latch Configuration (NP) (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-61) (Pre S.B. A320 004-25-78 and Amendment #5) Packboard, Aft, Latch Configuration (See IPL Figure 1 for NHA) (Post S.B. A320 004-25-78 and Amendment #5) (Pre Amendment #6) Packboard, Aft, Latch Configuration (See IPL Figure 1 for NHA) Post Amendment #6) .Clamp, Loop ATTACHING PARTS .Nut (V3J371) .Washer .Washer (ALT to Item 30) .Screw *** .Packboard Sub-Assembly, Aft (NP) .Packboard Sub-Assembly, Aft (NP)

UNITS EFF. PER CODE ASSY. A

RF

B

RF

C

RF

1 1 1 1 1 A

1

B

1

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 4B 50B 62378-305 -52 PPPT60-1 -54 P29-1

-54A P295-1

-54B M12397-1

60 B15473-1 70 63434-101 75 66623-101 77 PL9

-80 D16955-101 -90 D16955-102 100 MS3215-4031 100A MS16624-4025 100B MS16624-4031 - Item Not Illustrated

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

.Packboard Sub-Assembly, Aft (NP) ..Tape, Green (True P/N is PPP-T-60-1) ..Tape, Black, Fire Retardant (V99742) (True P/N is P-29-1) (Supsd by Item 54B) ..Tape, Black, Fire Retardant (V99742) (Alternative to Item 54) (True P/N is P-295-1) (Supsd by Item 54B) ..Tape, Black, Fire Retardant (Supsds Items 54 and 54A) (Reference S.I.L. 25-252) ..Plate, Back-Up ..Release Assembly ...Pawl Assembly ATTACHING PARTS ...Screw (#8-32 UNC) (V3J371) *** ..Bracket, Lower Mounting, LH (Supsd by Item 120B) ..Bracket, Lower Mounting, RH (Supsd by Item 130B) ...Ring, Retaining ...Ring, Retaining ...Ring, Retaining

25-60-56

C

1 A/R A/R

A/R

A/R

4 1 1 4

A,B

1

A,B

1

A,B C C

4 2 2

Page 10124 04 Dec 2018

COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 4B 110 110A 115 -120 -120A

B16954-1 70838-1 70837-1 B16961-1 D16961-1

120B 66826-1

120C 70840-1 -130 B16961-2 -130A D16961-2

130B 66826-2

130C 70840-2

140 NAS1169DD8

-150 MS20426B5-6

AIRLINE PART NO.

UNITS EFF. PER CODE ASSY.

NOMENCLATURE 1234567

...Pin, Mounting ...Pin, Mounting ...Spacer Deleted ...Bracket, Lower Mounting (NP) (Pre S.B. A320 00425-78 and Amendment #5) ...Bracket, Lower Mounting (Post S.B. A320 004-25-78 and Amendment #5) (Supsds Item 80) (Pre Amendment #6) ...Bracket, Lower Mounting, L.H. (Post Amendment #6) Deleted ...Bracket, Lower Mounting (NP) (Pre S.B. A320 00425-78 and Amendment #5) ...Bracket, Lower Mounting (Post S.B. A320 004-25-78 and Amendment #5) (Supsds Item 90) (Pre Amendment #6) ...Bracket, Lower Mounting, R.H. (Post Amendment #6) ATTACHING PARTS ..Washer, Dimpled (True P/N is NAS1169-DD8) ..Rivet (Supsd by Item 150A)

A,B C C

2 2 2

A

1

A,B

1

C

1

A

1

A,B

1

C

1

6

6

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM 4B 150A MS20426B5-7 R R

160 MS20470AD4-11 160A MS20470AD4-8 170 60327-1 180 B15468-1 -190 MS20470A4-4 -200 MS20470A4-5 200A MS20470AD4-5

210 D31880-101 -220 65460-1 -230 65460-2 230A 66094-1 230B 66094-2 -240 65032-1 250 62351-1 250A 62351-3

AIRLINE PART NO.

NOMENCLATURE 1234567

..Rivet (Supsds Item 150) ..Rivet ..Rivet *** ..Strap, Wear Bar ..Bar, Wear ATTACHING PARTS ..Rivet (Supsd by Item 200A) ..Rivet (Supsd by Item 200A) ..Rivet (Supsds Items 190 and 200) *** ..Cover, Upper Lacing ..Latch, Female Left (Supsd by Item 230A) ..Latch, Female Right (Supsd by Item 230B) ..Latch, Female Left (Supsds Item 220) ..Latch, Female Right (Supsds Item 230) Deleted ..Strip, Attachment ..Strip, Attachment

UNITS EFF. PER CODE ASSY. 6 A,B C

12 12 4 2 4 4 8

1 1 1 1 1

1 2

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FIG. PART NUMBER ITEM

AIRLINE PART NO.

NOMENCLATURE 1234567

UNITS EFF. PER CODE ASSY.

4B 260 MS21083C04 -270 MS24693C6

270A MS24693C5

280 ABA45 -284 C15494-101 -284A C15494-105 -286 MS20426A4-8 -287 MS24693A29

-288 NAS1169DD6

-289 MS21083D06 -290 64212-301 -290A 70847-3

ATTACHING PARTS ..Nut ..Screw, Flat Csk. (Supsd by Item 270A) (True P/N is MS24693-C6) ..Screw, Flat Csk. (Supsds Item 270) (True P/N is MS24693-C5) ..Rivet (V3J371) *** ..Chock Assembly, Cylinder ..Chock Assembly, Cylinder ATTACHING PARTS ..Rivet, Solid ..Screw, Flt. Hd., Csk., .138-32 (True P/N is MS24693-A29) ..Washer, Dimpled (True P/N is NAS1169-DD6) ..Nut, Self Locking, .138-32 *** ..Tray, Packboard (NP) ..Tray, Packboard (NP)

4 4

4

8 A,B C

1 1

A,B C

6 6

A,B

6

C

6

A,B C

1 1

- Item Not Illustrated

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COMPONENT MAINTENANCE MANUAL D31516 D31517

FOLDING PROCEDURE APPENDICES

APPENDIX

EVACUATION SLIDE

FOLDING PROCEDURE

Appendix-1

D31516-Series (Forward Door)

P-11895

D31517-Series (Aft Door)

25-60-56

APPX-1, 11 Dec 2015 APPX-2, Blank