@airbus: Component Maintenance Manual With Illustrated Part List

@AIRBUS
AIRBUS S.A.S.
Customer Services
Technical Data Support and Services
31707 Blagnac Cedex
FRANCE
FAPE3
COMPONENT MAINTENANCE MANUAL

WITH
ILLUSTRATED PART LIST
FWD CARGO COMPARTMENT DOOR
PN : D5237300000600
D5237300001000
D5237300001200
D5237300001400
Issue: Nov 01/04 52-31-19 Rev: Jul 01/12

@AIRBUS
D5237300000600
HIGHLIGHTS
Revision No. 8 - Jul 01/12
LOCATIONS CHG DESCRIPTIONS OF CHANGE

CODE
HIGHLIGHTS
Page 1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
LIST OF EFFECTIVE CONTENT
Revision No. 8 - Jul 01/12
CONTENT CHG LAST REVISION

CODE DATE
INTRODUCTION
TASK 52-31-19-871-801-A01 Jul 01/12
DESCRIPTION AND OPERATION

TASK 52-31-19-870-802-A01 Jul 01/12
TASK 52-31-19-870-803-A01 Jul 01/12
FIGURE 52-31-19-991-001-A01 Jul 01/12
FIGURE 52-31-19-991-002-A01 Jul 01/12
FIGURE 52-31-19-991-003-A01 Jul 01/12
TASK 52-31-19-870-804-A01 Jul 01/12
FIGURE 52-31-19-991-004-A01 Jul 01/12
FIGURE 52-31-19-991-005-A01 Jul 01/12
TESTING AND FAULT ISOLATION

TASK 52-31-19-700-801-A01 Jul 01/12
Subtask 52-31-19-750-001-A01 Jul 01/12
FIGURE 52-31-19-991-006-A01 Jul 01/12
TASK 52-31-19-700-802-A01 Jul 01/12
Subtask 52-31-19-750-002-A01 Jul 01/12
TASK 52-31-19-810-803-A01 Jul 01/12
Subtask 52-31-19-810-003-A01 Jul 01/12
TASK 52-31-19-700-804-A01 Jul 01/12
Subtask 52-31-19-750-004-A01 Jul 01/12
FIGURE 52-31-19-991-007-A01 Jul 01/12
SCHEMATIC AND WIRING DIAGRAMS

TASK 52-31-19-878-805-A01 Jul 01/12
FIGURE 52-31-19-991-008-A01 Jul 01/12
L.E.C.
Page 1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

CODE DATE
DISASSEMBLY
TASK 52-31-19-000-801-A01 Jul 01/12
Subtask 52-31-19-000-001-A01 Jul 01/12
TASK 52-31-19-000-802-A01 Jul 01/12
Subtask 52-31-19-000-002-A01 Jul 01/12
TASK 52-31-19-000-803-A01 Jul 01/12
Subtask 52-31-19-000-003-A01 Jul 01/12
TASK 52-31-19-000-804-A01 Jul 01/12
Subtask 52-31-19-000-004-A01 Jul 01/12
TASK 52-31-19-000-805-A01 Jul 01/12
Subtask 52-31-19-000-005-A01 Jul 01/12
TASK 52-31-19-000-806-A01 Jul 01/12
Subtask 52-31-19-000-006-A01 Jul 01/12
TASK 52-31-19-000-807-A01 Jul 01/12
Subtask 52-31-19-000-007-A01 Jul 01/12
TASK 52-31-19-000-808-A01 Jul 01/12
Subtask 52-31-19-010-002-A01 Jul 01/12
Subtask 52-31-19-000-008-A01 Jul 01/12
TASK 52-31-19-000-809-A01 Jul 01/12
Subtask 52-31-19-000-009-A01 Jul 01/12
TASK 52-31-19-000-810-A01 Jul 01/12
Subtask 52-31-19-000-010-A01 Jul 01/12
TASK 52-31-19-000-811-A01 Jul 01/12
Subtask 52-31-19-000-011-A01 Jul 01/12
TASK 52-31-19-000-812-A01 Jul 01/12
Subtask 52-31-19-000-012-A01 Jul 01/12
TASK 52-31-19-000-813-A01 Jul 01/12
Subtask 52-31-19-010-003-A01 Jul 01/12
Subtask 52-31-19-000-013-A01 Jul 01/12
L.E.C.
Page 2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

CODE DATE
TASK 52-31-19-000-814-A01 Jul 01/12
Subtask 52-31-19-000-014-A01 Jul 01/12
TASK 52-31-19-000-815-A01 Jul 01/12
Subtask 52-31-19-010-004-A01 Jul 01/12
Subtask 52-31-19-010-001-A01 Jul 01/12
TASK 52-31-19-000-816-A01 Jul 01/12
Subtask 52-31-19-000-015-A01 Jul 01/12
TASK 52-31-19-000-817-A01 Jul 01/12
Subtask 52-31-19-000-016-A01 Jul 01/12
TASK 52-31-19-000-818-A01 Jul 01/12
Subtask 52-31-19-000-017-A01 Jul 01/12
CLEANING
TASK 52-31-19-100-801-A01 Jul 01/12
Subtask 52-31-19-100-001-A01 Jul 01/12
Subtask 52-31-19-100-002-A01 Jul 01/12
Subtask 52-31-19-100-003-A01 Jul 01/12
Subtask 52-31-19-100-004-A01 Jul 01/12
INSPECTION/CHECK
TASK 52-31-19-210-801-A01 Jul 01/12
Subtask 52-31-19-210-001-A01 Jul 01/12
TASK 52-31-19-210-802-A01 Jul 01/12
Subtask 52-31-19-210-002-A01 Jul 01/12
TASK 52-31-19-210-803-A01 Jul 01/12
Subtask 52-31-19-210-003-A01 Jul 01/12
TASK 52-31-19-210-804-A01 Jul 01/12
Subtask 52-31-19-210-004-A01 Jul 01/12
TASK 52-31-19-210-805-A01 Jul 01/12
Subtask 52-31-19-210-005-A01 Jul 01/12
L.E.C.
Page 3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

CODE DATE
TASK 52-31-19-210-806-A01 Jul 01/12
Subtask 52-31-19-210-006-A01 Jul 01/12
TASK 52-31-19-210-807-A01 Jul 01/12
Subtask 52-31-19-210-007-A01 Jul 01/12
TASK 52-31-19-210-808-A01 Jul 01/12
Subtask 52-31-19-210-008-A01 Jul 01/12
FIGURE 52-31-19-991-010-A01 Jul 01/12
TASK 52-31-19-210-809-A01 Jul 01/12
Subtask 52-31-19-210-009-A01 Jul 01/12
TASK 52-31-19-220-801-A01 Jul 01/12
Subtask 52-31-19-220-001-A01 Jul 01/12
Subtask 52-31-19-220-002-A01 Jul 01/12
FIGURE 52-31-19-991-011-A01 Jul 01/12
REPAIR
TASK 52-31-19-300-801-A01 Jul 01/12
Subtask 52-31-19-300-004-A01 Jul 01/12
TASK 52-31-19-300-802-A01 Jul 01/12
Subtask 52-31-19-300-002-A01 Jul 01/12
FIGURE 52-31-19-991-012-A01 Jul 01/12
FIGURE 52-31-19-991-013-A01 Jul 01/12
FIGURE 52-31-19-991-014-A01 Jul 01/12
TASK 52-31-19-300-803-A01 Jul 01/12
Subtask 52-31-19-300-003-A01 Jul 01/12
ASSEMBLY
TASK 52-31-19-400-801-A01 Jul 01/12
Subtask 52-31-19-410-001-A01 Jul 01/12
TASK 52-31-19-400-802-A01 Jul 01/12
Subtask 52-31-19-410-002-A01 Jul 01/12
L.E.C.
Page 4
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

CODE DATE
TASK 52-31-19-400-803-A01 Jul 01/12
Subtask 52-31-19-410-003-A01 Jul 01/12
TASK 52-31-19-400-804-A01 Jul 01/12
Subtask 52-31-19-440-001-A01 Jul 01/12
TASK 52-31-19-400-805-A01 Jul 01/12
Subtask 52-31-19-420-001-A01 Jul 01/12
TASK 52-31-19-400-806-A01 Jul 01/12
Subtask 52-31-19-420-002-A01 Jul 01/12
TASK 52-31-19-400-807-A01 Jul 01/12
Subtask 52-31-19-440-002-A01 Jul 01/12
TASK 52-31-19-400-808-A01 Jul 01/12
Subtask 52-31-19-400-001-A01 Jul 01/12
TASK 52-31-19-400-809-A01 Jul 01/12
Subtask 52-31-19-400-002-A01 Jul 01/12
TASK 52-31-19-400-810-A01 Jul 01/12
Subtask 52-31-19-420-003-A01 Jul 01/12
TASK 52-31-19-400-811-A01 Jul 01/12
Subtask 52-31-19-400-003-A01 Jul 01/12
TASK 52-31-19-400-812-A01 Jul 01/12
Subtask 52-31-19-400-004-A01 Jul 01/12
TASK 52-31-19-400-813-A01 Jul 01/12
Subtask 52-31-19-400-005-A01 Jul 01/12
TASK 52-31-19-400-814-A01 Jul 01/12
Subtask 52-31-19-410-004-A01 Jul 01/12
TASK 52-31-19-400-815-A01 Jul 01/12
Subtask 52-31-19-400-006-A01 Jul 01/12
TASK 52-31-19-400-816-A01 Jul 01/12
Subtask 52-31-19-410-005-A01 Jul 01/12
TASK 52-31-19-400-817-A01 Jul 01/12
L.E.C.
Page 5
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

CODE DATE
Subtask 52-31-19-410-006-A01 Jul 01/12
TASK 52-31-19-400-818-A01 Jul 01/12
Subtask 52-31-19-410-007-A01 Jul 01/12
TASK 52-31-19-800-801-A01 Jul 01/12
Subtask 52-31-19-820-008-A01 Jul 01/12
Subtask 52-31-19-820-001-A01 Jul 01/12
FIGURE 52-31-19-991-015-A01 Jul 01/12
FIGURE 52-31-19-991-016-A01 Jul 01/12
TASK 52-31-19-800-802-A01 Jul 01/12
Subtask 52-31-19-820-009-A01 Jul 01/12
Subtask 52-31-19-820-002-A01 Jul 01/12
FIGURE 52-31-19-991-017-A01 Jul 01/12
TASK 52-31-19-800-803-A01 Jul 01/12
Subtask 52-31-19-820-010-A01 Jul 01/12
Subtask 52-31-19-820-003-A01 Jul 01/12
FIGURE 52-31-19-991-018-A01 Jul 01/12
TASK 52-31-19-800-804-A01 Jul 01/12
Subtask 52-31-19-820-011-A01 Jul 01/12
Subtask 52-31-19-820-004-A01 Jul 01/12
FIGURE 52-31-19-991-019-A01 Jul 01/12
TASK 52-31-19-800-805-A01 Jul 01/12
Subtask 52-31-19-820-012-A01 Jul 01/12
Subtask 52-31-19-820-005-A01 Jul 01/12
FIGURE 52-31-19-991-020-A01 Jul 01/12
TASK 52-31-19-800-806-A01 Jul 01/12
Subtask 52-31-19-820-013-A01 Jul 01/12
Subtask 52-31-19-820-006-A01 Jul 01/12
FIGURE 52-31-19-991-021-A01 Jul 01/12
TASK 52-31-19-800-807-A01 Jul 01/12
L.E.C.
Page 6
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

CODE DATE
Subtask 52-31-19-820-014-A01 Jul 01/12
Subtask 52-31-19-820-007-A01 Jul 01/12
FIGURE 52-31-19-991-022-A01 Jul 01/12
FITS AND CLEARANCES

TASK 52-31-19-820-806-A01 Jul 01/12
TASK 52-31-19-820-807-A01 Jul 01/12
FIGURE 52-31-19-991-023-A01 Jul 01/12
FIGURE 52-31-19-991-024-A01 Jul 01/12
FIGURE 52-31-19-991-025-A01 Jul 01/12
FIGURE 52-31-19-991-026-A01 Jul 01/12
FIGURE 52-31-19-991-027-A01 Jul 01/12
FIGURE 52-31-19-991-028-A01 Jul 01/12
FIGURE 52-31-19-991-029-A01 Jul 01/12
SPECIAL TOOLS,FIXTURES,EQUIPMENT AND CONSUMABLES

TASK 52-31-19-940-808-A01 Jul 01/12
FIGURE 52-31-19-991-030-A01 Jul 01/12
STORAGE INCLUDING TRANSPORTATION

TASK 52-31-19-550-801-A01 Jul 01/12
Subtask 52-31-19-620-001-A01 Jul 01/12
Subtask 52-31-19-530-001-A01 Jul 01/12
Subtask 52-31-19-550-004-A01 Jul 01/12
Subtask 52-31-19-550-002-A01 Jul 01/12
Subtask 52-31-19-550-003-A01 Jul 01/12
ILLUSTRATED PARTS LIST

IPL Introduction
TASK 52-31-19-872-801-A01 Jul 01/12
VENDOR LIST Jul 01/12
Figure 01
L.E.C.
Page 7
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

CODE DATE
FIGURE 52-31-19-991-801-001 Nov 01/08
Parts List Jul 01/12
Figure 02
FIGURE 52-31-19-991-802-001 Nov 01/08
Figure 03
FIGURE 52-31-19-991-803-001 Nov 01/08
Figure 04
FIGURE 52-31-19-991-804-001 Nov 01/08
Parts List Nov 01/08
Figure 05
FIGURE 52-31-19-991-805-001 Nov 01/08
Figure 08
FIGURE 52-31-19-991-808-001 Nov 01/08
Figure 09
FIGURE 52-31-19-991-809-001 Nov 01/08
Figure 13
FIGURE 52-31-19-991-813-001 Nov 01/08
Figure 20
FIGURE 52-31-19-991-820-001 Nov 01/08
Figure 21
FIGURE 52-31-19-991-821-001 Nov 01/08
L.E.C.
Page 8
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

CODE DATE
Figure 30
FIGURE 52-31-19-991-830-001 Nov 01/08
Figure 31
FIGURE 52-31-19-991-831-001 Nov 01/08
Figure 32
FIGURE 52-31-19-991-832-001 Nov 01/08
Figure 33
FIGURE 52-31-19-991-833-001 Nov 01/08
Figure 34
FIGURE 52-31-19-991-834-001 Nov 01/08
Figure 40
FIGURE 52-31-19-991-840-001 Nov 01/08
Figure 41
FIGURE 52-31-19-991-841-001 Nov 01/08
Figure 44
FIGURE 52-31-19-991-844-001 Nov 01/08
Figure 50
FIGURE 52-31-19-991-850-001 Nov 01/08
Figure 60
FIGURE 52-31-19-991-860-001 Nov 01/08
L.E.C.
Page 9
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

CODE DATE
Figure 62
FIGURE 52-31-19-991-862-001 Nov 01/08
Figure 63
FIGURE 52-31-19-991-863-001 Nov 01/08
Figure 90
FIGURE 52-31-19-991-890-001 Nov 01/08
Figure 91
FIGURE 52-31-19-991-891-001 Nov 01/08
Figure 96
FIGURE 52-31-19-991-896-001 Nov 01/08
Figure 97
FIGURE 52-31-19-991-897-001 Nov 01/08
L.E.C.
Page 10
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
TABLE OF CONTENTS
INTRODUCTION
52-31-19-871-801-A01 Introduction

52-31-19-870-802-A01 General
52-31-19-870-803-A01 Description
52-31-19-870-804-A01 Operation

52-31-19-700-801-A01 Test of the Proximity Sensors 5MJ and 28WV
52-31-19-700-802-A01 Test of the Electrical Circuit
52-31-19-810-803-A01 Fault Isolation
52-31-19-700-804-A01 Test of the Electrical Resistance

52-31-19-878-805-A01 Schematics and Wiring Diagram
DISASSEMBLY
52-31-19-000-801-A01 Removal of the Insulation and the Door Seal
52-31-19-000-802-A01 Removal and Disassembly of the Access Cover Assemblies
52-31-19-000-803-A01 Removal of the Plugs, the Adjusting Screws and the Protective
Plugs
52-31-19-000-804-A01 Removal of the Hand Lever Mechanism
52-31-19-000-805-A01 Disassembly of the Hand Lever Assembly
52-31-19-000-806-A01 Removal and Disassembly of the Drift Pin Rods
52-31-19-000-807-A01 Removal and Disassembly of the Cover Beam 4
52-31-19-000-808-A01 Removal and Disassembly of the Sequence Shaft Assembly
52-31-19-000-809-A01 Removal of the Vent Door Assembly Mechanism
52-31-19-000-810-A01 Removal and Disassembly of the Vent Door Assembly
52-31-19-000-811-A01 Removal of the Latching Mechanism Assemblies
52-31-19-000-812-A01 Disassembly of the Latching Hook Assemblies
52-31-19-000-813-A01 Removal and Disassembly of the Latching Shaft Assembly
52-31-19-000-814-A01 Removal and Disassembly of the Interlock Mechanism
52-31-19-000-815-A01 Removal of the Locking Shaft Assembly
52-31-19-000-816-A01 Removal of the Cargo Door Drainage
52-31-19-000-817-A01 Removal of the Door Proximity Sensors
52-31-19-000-818-A01 Removal of the Hinge Assemblies
T.O.C.
Page 1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
CLEANING
52-31-19-100-801-A01 Cleaning
INSPECTION/CHECK
52-31-19-210-801-A01 Check of the Door Structure
52-31-19-210-802-A01 Structure Components
52-31-19-210-803-A01 Check of the Door Seal
52-31-19-210-804-A01 Check of the Door Mechanism
52-31-19-210-805-A01 Check of the Locking Mechanism
52-31-19-210-806-A01 Check of the Protective Treatment
52-31-19-210-807-A01 Check of the Electrical Equipment
52-31-19-210-808-A01 Check of the Springs
52-31-19-210-809-A01 Check of the Placard
52-31-19-220-801-A01 Visual Examination
REPAIR
52-31-19-300-801-A01 Reworking or Machining
52-31-19-300-802-A01 Repair of the Cargo Door Seal
52-31-19-300-803-A01 Replacement of Parts
ASSEMBLY
52-31-19-400-801-A01 Installation of the Insulation and the Door Seal
52-31-19-400-802-A01 Assembly and Installation of the Access Cover Assemblies
52-31-19-400-803-A01 Installation of the Plugs and the Protective Plugs
52-31-19-400-804-A01 Assembly of the Hand Lever Assembly
52-31-19-400-805-A01 Installation of the Hand Lever Mechanism
52-31-19-400-806-A01 Installation of the Latching Mechanism Assemblies
52-31-19-400-807-A01 Assembly of the Latching Hook Assemblies
52-31-19-400-808-A01 Assembly and Installation of the Latching Shaft Assembly
52-31-19-400-809-A01 Assembly and Installation of the Interlock Mechanism
52-31-19-400-810-A01 Installation of the Locking Shaft Assembly
52-31-19-400-811-A01 Assembly and Installation of the Sequence Shaft Assembly
52-31-19-400-812-A01 Assembly and Installation of the Cover Beam 4
52-31-19-400-813-A01 Assembly and Installation of the Drift Pin Rods
52-31-19-400-814-A01 Installation of the Vent Door Assembly Mechanism
52-31-19-400-815-A01 Assembly and Installation of the Vent Door Assembly
52-31-19-400-816-A01 Installation of the Door Proximity Sensors
52-31-19-400-817-A01 Installation of the Cargo Door Drainage
T.O.C.
Page 2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
52-31-19-400-818-A01 Installation of the Hinge Assemblies

52-31-19-800-801-A01 Adjustment of the Hand Lever Assembly
52-31-19-800-802-A01 Adjustment of the Latching Mechanism
52-31-19-800-803-A01 Adjustment of the Locking Mechanism
52-31-19-800-804-A01 Adjustment of the Drift Pin Mechanism
52-31-19-800-805-A01 Adjustment of the Interlock Mechanism
52-31-19-800-806-A01 Adjustment of the Skin Offset of the Vent Door Assembly
52-31-19-800-807-A01 Adjustment of the Proximity Sensors
FITS AND CLEARANCES

52-31-19-820-806-A01 Fits and Clearances - General
52-31-19-820-807-A01 Fits and Clearances - Tables

52-31-19-940-808-A01 Special Tool

52-31-19-550-801-A01 Storage

52-31-19-872-801-A01 Introduction Illustrated Parts List (IPL)
VENDOR LIST
DETAILED PARTS LIST
T.O.C.
Page 3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
LIST OF SERVICE BULLETINS
SB No REV No MOD No INCORP. TITLE

DATE
*** NO SB ***
SBL
Page 1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
INTRODUCTION
**For PN’s ALL
TASK 52-31-19-871-801-A01
Introduction
1. General
A. This manual is written to the iSpec 2200 and in ASD Simplified Technical English (STE). The
international SI units of measurement are used in this manual, with imperial units shown in
parentheses.
B. The manual contains data about maintenance on the component in a workshop. It does not
contain data about maintenance on the component when it is installed in the aircraft.
C. Only approved persons with the necessary skills are permitted to do the maintenance procedures
in this manual.
D. Maintenance Task Oriented Support System (MTOSS) task and subtask identification is used in
this manual. The maintenance tasks and other data have special MTOSS numbers for Electronic
Data Processing (EDP). The user of the manual can ignore the MTOSS numbers.
E. This manual contains:
- Technical data for the component
- Maintenance and repair procedures about the component
- An Illustrated Parts List (IPL) with data for the component parts. Parts are identified in all
sections of the manual by the IPL-Figure and item number.
F. We verified the DISASSEMBLY, TESTING and ASSEMBLY procedures by simulation.
2. How to use the Manual
A. Make sure that the manual contains the information applicable to your component.
B. If you need to identify a part or find a part number, use the search function.
C. You must use the instructions in this manual for all the component maintenance. Read all the
applicable WARNINGS and CAUTIONS before you do the work on the component.
3. List of Abbreviations
ACM Abbreviated Component Maintenance Manual
AEB Airline Engineering Bulletin
AF Across Flats
ASD Aero Space and Defence Industries Association of Europe
ATA Air Transport Association of America
ATLAS Abbreviated Test Language for All Systems
CMM Component Maintenance Manual
CMS Component Maintenance Sheet
INTRO
Page 1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
FIN Functional Item Number

IPC Illustrated Parts Catalog
IPL Illustrated Parts List
ID Inside Diameter
MFG Manufacturing
MFR Manufacturer
MOD Modification
MTOSS Maintenance Task Oriented Support System
NTF Non Textile Floor
OD Outside Diameter
PA Poly-Amide
PARA Paragraph
PC Poly-Carbonate
PMS Process and Materials Specification
PN Part Number
PU Poly-Urethane
PV Poly-Venyl-Fluorite
SB Service Bulletin
SERNO Serial Number
STE Simplified Technical English
TBD To Be Determined
List of Abbreviations
TABLE 1
INTRO
Page 2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-870-802-A01
General
1. The FWD Cargo Compartment Door (referred to as cargo door) is installed on the lower right hand
side of the aircraft. Hinge assemblies at the top end attach the cargo door to the fuselage. The
locking and the unlocking operation of the cargo door is carried out mechanically with a hand lever.
2. For the data of the proximity sensors refer to CMMV 32-10-03 of the supplier ELDEC.
3. Technical Data (approx.):
Width: 355 mm (14.0 in )
Height: 2035 mm (52.2 in )
Length: 1321 mm (80.1 in )
Weight: 86 kg (189.6 Ib.)
Technical Data
TABLE 1
Page 1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-870-803-A01
Description
1. Door Structure
NOTE : Refer to FIGURE 52-31-19-991-001-A and FIGURE 52-31-19-991-002-A.

A. The cargo door structure has:
- the frames and beams,
- the vertical and horizontal edge members,
- the inner and outer skin,
- the door seal,
- the fire protection lining.
B. The cargo door structure is made of aluminium sheet metal and machined parts. Rivets attach
the parts together to form a torsion resistant structure. Sealant on the mating surfaces of the
parts prevents corrosion and makes them pressure tight.
C. The attachment fittings for the hydraulic actuators on the inner side of the cargo door are part
of the upper ends of the FR25A and FR26A.
D. The outer skin has a cut-out for the vent door. The inner side of the vent door has a cover.
E. An access panel for the door mechanism is installed on the lower side of the cargo door
structure. Indication windows allow the visual checking of the locked/unlocked (green/red)
position of the safety cams of the locking shaft.
F. At the upper edge member and beam No. 1, replaceable hinge assemblies with bronze bushings,
are installed to fit the cargo door to the fuselage.
G. Three blanking plugs, made from plastic, are installed in the hoist fittings on the outer side of
the cargo door.
H. Four adjustable screws are installed on the lower part of the cargo door. The adjustable screws
stop the movement of the cargo door when it is in the closed position and in line with the
aircraft fuselage.
J. The door seal is made of fabric reinforced silicon rubber. Retainers attach the door seal to the
edge members of the cargo door.
K. A drainage hose and a drainage valve are installed in the cargo door structure to drain the
condensed water.
L. The fire protection lining assembly with integral insulation is made of prepreg. The insulation is
made of PE-foam material lined with self-adhesive. The fire protection lining assembly is
attached to the inner skin of the cargo door with quick release fasteners.
Page 2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
2. Door Mechanism (Refer to FIGURE 52-31-19-991-001-A and FIGURE 52-31-19-991-002-A)

A. The door mechanism is installed in the lower part of the cargo door and has:
- the handle mechanism,
- the latching mechanism,
- the interlock mechanism,
- the locking mechanism,
- the vent door mechanism,
- the target mechanism,
- the drift pin mechanism,
(1) Handle Mechanism
(a) The handle mechanism is installed in the lower part of the cargo door and has a flap
assembly, a door handle assembly and a lever mechanism.
(b) The handle mechanism operates
- the locking mechanism with the vent door,
- the latching mechanism,
- the drift pin mechanism,
- the actuator system interlock and
- the door warning system.
(c) In the closed and locked position the hand lever is kept in a recess and is then in line
with the outer contour of the cargo door. A catch holds it in position. A spring-
loaded flap operates the catch.
(2) Latching Mechanism
(a) The Latching mechanism is installed in the lower part of the cargo door. The latching
shaft operates all the latching hooks through shaft levers, spring units, bellcranks and
links.
(b) In the latching position, four over-center linking locks hold the latching hooks. There
is a stop to guarantee dead center at each latching hook between the latching hook
and the bellcrank.
(c) Safety cams, installed at the locking shaft, lock the latching hooks.
(3) Interlock Mechanism
(a) The interlock mechanism is installed in the center of the lower part of the door. It
has a spring loaded strut, a connection rod, an interlock lever, a stop bolt and a roller
lever.
(b) The interlock mechanism locks and unlocks the latching shaft.
(4) Locking Mechanism
(a) The locking mechanism is installed parallel to the latching mechanism in the lower
part of the cargo door. The locking mechanism is operated with the hand lever by a
rod connection at one end of the locking shaft.
Page 3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Locking cams, painted with red and green markings, are installed on the locking shaft
to keep the latching hooks in the LOCKED position.
(5) Vent Door Mechanism
(a) You operate the vent door with rods and levers.
(b) It is linked with a rod to the drift pin mechanism.
(c) The vent door prevents a cabin and cargo compartment pressure to an unsafe level.
The other task of the vent door is to act as a visual locking indicator. When the vent
door is closed, all latching hooks must be in the latched position and the drift pins
must be in the extended position.
(6) Target Mechanism
(a) The target mechanism of the door warning system is installed at the sequence shaft
which is part of the vent door mechanism.
(7) Drift Pin Mechanism
(a) The drift pin mechanism, installed in the middle of the cargo door, makes sure that
no contour offset exists between the aircraft fuselage and the cargo door when the
cargo door is installed at the aircraft, closed and Locked.
(b) The drift pin mechanism includes the control rods with the related bellcranks, the
drift pin lever on the locking shaft and the drift pins.
(c) Control rods transmit the movement of the locking shaft to retract or extend the drift
pins.
3. Door Warning and Control System
NOTE : Refer to FIGURE 52-31-19-991-003-A and TASK 52-31-19-878-805-A01.

A. A cable harness for the transmission of the data of the door mode is installed in the door
structure.
B. Two proximity sensors are installed in the cargo door.
(1) The proximity sensor 28WV is installed adjacent to the door handle (Door Warning
System).
(2) The proximity sensor 5MJ is installed on the frame near the target lever on the latching
shaft (Door Control System).
NOTE : For data of the proximity sensors refer to CMMV 32-10-03.

C. The target mechanism with the target lever for the proximity sensor 30WV, which is a part of
the aircraft fuselage, is installed on the frame. A rod assembly connects the target lever to the
locking shaft.
D. A direct visual locking indicator system is installed in the cargo door as shown in FIGURE
52-31-19-991-002-A. It has the four integrated windows and related green/red markings on the
locking cams of the locking shaft.
Page 4
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
E. In addition the open vent door is an indication for an UNLOCKED position of the locking shaft.
4. Electrical Equipment Installation
NOTE : Refer to FIGURE 52-31-19-991-003-A and TASK 52-31-19-878-805-A01.

A cable harness for transmission of data of the door condition (LOCKED/UNLOCKED) to the
ECAM is installed in the door structure (Refer to FIGURE 52-31-19-991-003-A). For the wiring
diagram refer to TASK 52-31-19-878-805-A01.
Page 5
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
UPPER EDGE
MEMBER
HINGE
ASSEMBLIES
A
ATTACHMENT
FITTINGS
FIRE PROTECTION
LINING ASSEMBLY
COVER
VENT DOOR
DRIFT PIN
MECHANISM
DRAINAGE
DRIFT PIN VALVE
B
B
COVER BEAM 4
B
B A
EDGE
B MEMBER EXAMPLE
EXAMPLE
RETAINER
ADJUSTING
SCREW INNER SKIN
DOOR
SEAL
SELF ADHESIVE
INSULATION MAT
FIRE PROTECTION
LINING ASSEMBLY
QUICK RELEASE
FASTENER
F_CM_523119_1_0010101_01_00
FWD Cargo Compartment Door

FIGURE-52-31-19-991-001-A01
Page 6
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A
A
PLUG INSTALLATION
FOR HOISTING
VENT
DOOR BLANKING
PLUG
A
DOOR
HANDLE TARGET
MECHANISM
LATCHING
SHAFT
LOCKING
SHAFT LATCHING
HOOK
LATCHING/LOCKING
B INTERLOCK
MECHANISM
MECHANISM
FLAP
B
ACCESS
PANEL
INDICATION
WINDOW
F_CM_523119_1_0020101_01_00

FIGURE-52-31-19-991-002-A01
Page 7
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
CONNECTOR
1856VC−A
7526VT
7522VP
7532VP
PROXIMITY
SWITCH
28WV
PROXIMITY
SWITCH
5MJ
F_CM_523119_1_0030101_01_00
Electrical Equipment Installation

FIGURE-52-31-19-991-003-A01
Page 8
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-870-804-A01
Operation
1. Refer to FIGURE 52-31-19-991-004-A and FIGURE 52-31-19-991-005-A.
2. When you push the flap of the handle mechanism into the cargo door, the flap mechanism unlocks
the door handle.
3. When you pull out the door handle (65 deg.), the locking shaft with the cams turns (red marks are
visible through the indication windows) in the direction UNLOCKED. The blockage of all the latching
hooks is released. At one end of the locking mechanism a cam on the sequence shaft moves in the
direction UNLOCKED. The blockage of the latching shaft releases, the vent door opens and the drift
pins retract.
4. When you pull up the door handle from LATCHED to the UNLATCHED position (126 deg. = fully
open):
- the latching shaft turns,
- the over-center linking latches break,
- the four latching hooks move through shaft levers, bellcranks and links to the unlatched position.
5. When you press and move the lever of the interlock mechanism, the blockage of the latching shaft
releases.
6. When you move the door handle down from the fully open position (UNLATCHED) to the
LATCHED position (65 deg.)
- the latching shaft turns to the latched position,
- the shaft levers, bellcranks and links move the hook operating linkage to the over-center position,
- all the latching hooks are engaged.
7. When you push the door handle of the handle mechanism 65 deg. down (until the door handle is
smooth with outer contour of the cargo door), the locking shaft and the cams turn in the direction
LOCKED (the green marks are visible through the indication windows).
Page 9
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
UPPER EDGE
MEMBER
HINGE
ASSEMBLIES
A
ATTACHMENT
FITTINGS
FIRE PROTECTION
LINING ASSEMBLY
COVER
VENT DOOR
DRIFT PIN
MECHANISM
DRAINAGE
DRIFT PIN VALVE
B
B
COVER BEAM 4
B
B A
EDGE
B MEMBER EXAMPLE
EXAMPLE
RETAINER
ADJUSTING
SCREW INNER SKIN
DOOR
SEAL
SELF ADHESIVE
INSULATION MAT
FIRE PROTECTION
LINING ASSEMBLY
QUICK RELEASE
FASTENER
F_CM_523119_1_0040101_01_00

FIGURE-52-31-19-991-004-A01
Page 10
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A
A
PLUG INSTALLATION
FOR HOISTING
VENT
DOOR BLANKING
PLUG
A
DOOR
HANDLE TARGET
MECHANISM
LATCHING
SHAFT
LOCKING
SHAFT LATCHING
HOOK
LATCHING/LOCKING
B INTERLOCK
MECHANISM
MECHANISM
FLAP
B
ACCESS
PANEL
INDICATION
WINDOW
F_CM_523119_1_0050101_01_00

FIGURE-52-31-19-991-005-A01
Page 11
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-700-801-A01
Test of the Proximity Sensors 5MJ and 28WV
1. General
A. The test of the cargo door is limited to the electrical system.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
REFERENCE DESIGNATION
355M03210000 Check Doors Tool
355M03213000 Cable Loom
355M03214000 Extension Cable Loom
Fixtures, Tools, Test and Support Equipment
TABLE 1
B.Referenced Information
TASK 52-31-19-000-802-A01 Removal and Disassembly of the Access Cover Assemblies
TASK 52-31-19-400-802-A01 Assembly and Installation of the Access Cover Assemblies
TASK 52-31-19-878-805-A01 Schematics and Wiring Diagram
FIGURE 52-31-19-991-006-A FIGURE 52-31-19-991-006-A-Electrical Equipment Installation
Referenced Information
TABLE 2
3. Procedure
Subtask 52-31-19-750-001-A01
A. Test of the Proximity Sensors 5MJ and 28WV
NOTE : See IPL_FIGURE_03, IPL_FIGURE_09 and IPL_FIGURE_62.
NOTE : See FIGURE 52-31-19-991-006-A and TASK 52-31-19-878-805-A01.

(1) Make sure that the access cover assembly 03-010 is removed, see DISASSEMBLY TASK
52-31-19-000-802-A01.
Page 1001
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(2) Prepare the 355M03210000 Check Doors Tool for the test as follows::
NOTE : See the AEROSPATIALE Ground Equipment Manual (GEM) for the details and
the function of the 355M03210000 Check Doors Tool.
(a) On the PROXIMITY DETECTOR ADJUSTMENT section put the switch S6 in the
ON position. The three red LEDs (DS22, DS23, DS24) stay off.
(b) Press the LIGHT TEST pushbutton S5. The three red LEDs (DS22, DS23, DS24)
come on.
(c) Release the LIGHT TEST pushbutton S5. The three red LEDs (DS22, DS23, DS24)
go off.
(d) Put the switch S6 in the OFF position.
(3) Prepare the test as follows:
(a) Disconnect the plug connectors from the proximity sensor 2SWV and 5MJ 62-010.
(b) Install the connector P4 of the 355M03213000 Cable Loom at the connector P9 of
the 355M03214000 Extension Cable Loom
(c) Connect the connector P1 of the 355M03213000 Cable Loom to the connector J1 of
the doors check tool.
(d) Connect the connector P10 of the 355M03214000 Extension Cable Loom to the
proximity sensor 28WV or 5MJ 62-010 for test.
(4) Do the test for the proximity sensor 28WV 62-010 as follows:
(a) Put the switch S6 in the ON position.
(b) If the red SENSOR LED NC (DS24) comes on and shows a malfunction of the
proximity sensor 28WV, replace it.
ACTION RESULT
(1) Move the hand lever 09-010 to the The red LED (DS23) comes on and shows that the
LOCKED position. TARGET is NEAR.
(2) Push the handle flap 09-100 in and pull the The red illuminated LED (DS23) for TARGET
hand lever 09-010 out of its recess. NEAR goes off. The LED (DS22) comes on and
shows that the TARGET is FAR.
(3) Move the hand lever 09-010 back in the The red illuminated LED (DS22) goes off and the
LOCKED position. red LED (DS23) comes on and shows that the
TARGET is NEAR.
Action Result Table
TABLE 3
(c) Move the switch S6 to OFF position.

(d) Disconnect the connector P10 from the proximity sensor 28WV.
Page 1002
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(e) Connect the plug connector to the proximity sensor 28WV.

(5) Do the test for the proximity sensor 5MJ 62-010 as follows:
(a) Move the switch S6 to the ON position.
(b) If the red SENSOR LED NC (DS24) comes on and shows a malfunction of the
proximity sensor 5MJ, replace it.
ACTION RESULT
(1) Put the hand lever 09-010 in the LOCKED The red LED (DS22) comes on and shows that the
position. TARGET is FAR.
(2) Push the handle flap 09-100 in and pull theThe red illuminated LED (DS22) for the TARGET
hand lever 09-010 out of its recess. FAR stays on, until the handle is in fully open
position. Then the red illuminated LED (DS22)
goes off.
(3) Move the hand lever 09-010 back to the The red illuminated LED (DS23) goes off and the
LOCKED position. red LED (DS22) comes on and shows that the
TARGET is FAR.
Action Result Table
TABLE 4
(c) Move the switch S6 to the OFF position.

(d) Disconnect the connector P10 from the proximity sensor 5MJ.
(e) Connect the plug connector to the proximity sensor 5MJ.
(6) Disconnect the connector P1 from the connector J1 of the doors check tool.
(7) Disconnect the connector P9 from the connector P4 of the cable looms.
(8) Install the access cover assembly 03-010, see ASSEMBLY TASK 52-31-19-400-802-A01.
Page 1003
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
CONNECTOR
1856VC−A
7526VT
7522VP
7532VP
PROXIMITY
SWITCH
28WV
PROXIMITY
SWITCH
5MJ
F_CM_523119_1_0060101_01_00
Electrical Equipment Installation

FIGURE-52-31-19-991-006-A01
Page 1004
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-700-802-A01
Test of the Electrical Circuit
1. General
continuity tester
TABLE 1
B.
TASK 52-31-19-878-805-A01 Schematics and Wiring Diagram
TABLE 2
3. Procedure
Subtask 52-31-19-750-002-A01
A. Test of the Electrical Circuit
NOTE : See IPL_FIGURE_62.
NOTE : For this test you must use a continuity tester. If you find a failure, you must check all
connections for correct assembly, see TASK 52-31-19-878-805-A01.
NOTE : If there is no indication on the continuity tester, do the continuity test again for 5
times. If there is no indication on the continuity tester, replace the complete wire
harness.
(1) Action Result Table
ACTION RESULT
(1) Remove the connectors from the proximity
sensors 5MJ and 28WV 62-010.
(2) Make a connection between the contacts
1-2 and 13-14 of the connector 1856VC-A.
Page 1005
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
ACTION RESULT
(3) Connect a continuity tester to the contacts Indication comes on the continuity tester.
A-B of the connectors for the proximity
sensor 5MJ and 28WV.
(4) Install the connectors on the proximity
sensors 5MJ and 28WV 62-010.
Action Result Table
TABLE 3
Page 1006
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-810-803-A01
Fault Isolation
1. General
A. The fault isolation is limited to the door mechanism.
A. Consumable Materials
04-004 Synthetic Ester Based Grease High Pressure
Consumable Materials
TABLE 1
B. Referenced Information
TASK 52-31-19-000-804-A01 Removal of the Hand Lever Mechanism
TASK 52-31-19-400-805-A01 Installation of the Hand Lever Mechanism
TASK 52-31-19-800-801-A01 Adjustment of the Hand Lever Assembly
TASK 52-31-19-000-811-A01 Removal of the Latching Mechanism Assemblies
TASK 52-31-19-400-806-A01 Installation of the Latching Mechanism Assemblies
TASK 52-31-19-800-802-A01 Adjustment of the Latching Mechanism
TASK 52-31-19-000-815-A01 Removal of the Locking Shaft Assembly
TASK 52-31-19-400-810-A01 Installation of the Locking Shaft Assembly
TASK 52-31-19-800-803-A01 Adjustment of the Locking Mechanism
TASK 52-31-19-000-805-A01 Disassembly of the Hand Lever Assembly
TASK 52-31-19-400-804-A01 Assembly of the Hand Lever Assembly
TASK 52-31-19-000-813-A01 Removal and Disassembly of the Latching Shaft Assembly
TASK 52-31-19-400-808-A01 Assembly and Installation of the Latching Shaft Assembly
TASK 52-31-19-000-814-A01 Removal and Disassembly of the Interlock Mechanism
TASK 52-31-19-400-809-A01 Assembly and Installation of the Interlock Mechanism
TABLE 2
Page 1007
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
3. Procedure
Subtask 52-31-19-810-003-A01
A. Fault Isolation
NOTE : See IPL_FIGURE_08, IPL_FIGURE_09, IPL_FIGURE_13, IPL_FIGURE_33,

IPL_FIGURE_34 and IPL_FIGURE_44.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 04-004 SYNTHETIC ESTER
BASED GREASE HIGH PRESSURE. OBEY THE MATERIAL
MANUFACTURER’S INSTRUCTIONS.
(1) Fault Isolation
FAULT POSSIBLE CAUSE CORRECTION
(1) You cannot move the hand (a) Parts of the hand lever Examine the hand lever
lever assembly 08-010 to mechanism are damaged or mechanism and replace the
the OPEN or CLOSED adjustment is not correct. damaged parts, see
positions. DISASSEMBLY TASK
52-31-19-000-804-A01 and
ASSEMBLY TASK
52-31-19-400-805-A01 and
adjust, see ASSEMBLY TASK
52-31-19-800-801-A01.
(b) Parts of the latching shaft are Examine the latching
damaged or adjustment of the mechanism and replace the
latching mechanism is not damaged parts, see
correct. DISASSEMBLY TASK
52-31-19-000-811-A01 and
ASSEMBLY TASK
52-31-19-400-806-A01 and
52-31-19-800-802-A01.
(c) Parts of the locking shaft are Examine the locking mechanism
damaged or adjustment of the and replace the damaged parts,
locking mechanism is not see DISASSEMBLY TASK
correct. 52-31-19-000-815-A01 and
ASSEMBLY TASK
52-31-19-400-810-A01 and
52-31-19-800-803-A01.
Page 1008
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

(2) You can move the hand (a) Damaged surfaces on the Replace the damaged parts, see
lever assembly 08-010 to sequence cams 09-020, the DISASSEMBLY TASK
the OPEN and CLOSED universal joint lock 08-240 and 52-31-19-000-805-A01, TASK
position only with high the universal joint assembly 52-31-19-000-804-A01 and
force. 08-450, adjustment incorrect. ASSEMBLY TASK
52-31-19-400-804-A01, TASK
52-31-19-400-805-A01, and
adjust ASSEMBLY TASK
52-31-19-800-801-A01.
(b) The sliding surfaces of the
sequence cams 09-020, the
universal joint lock 08-240 and
the universal joint asseembly
08-450 are not lubricated.
(c) No grease between the sliding Apply Material No. 04-004
surfaces of the shaft 08-250 and Synthetic Ester Based Grease
the sequence cams 09-020. High Pressure to the lubrication
fitting 08-280 of the shaft
08-250.
(d) The actuating unit 08-040 is Replace the actuating unit
damaged and has a leak. 08-040, see DISASSEMBLY
TASK 52-31-19-000-804-A01
and ASSEMBLY TASK
52-31-19-400-805-A01.
(e) The control rod 08-160 is too Adjust the control rod 08-160,
long or too short. see ASSEMBLY TASK
52-31-19-800-803-A01.
(f) The control rod 08-540 is too Adjust the control rod 08-540,
long or too short. see ASSEMBLY TASK
52-31-19-800-802-A01.
(3) The handle mechanism has (a) The thickness of the washers Remove the hand lever
axial play and an axial gap. 08-260, 08-270 must be assembly 08-010 and install new
increased. washers 08-260, 08-270, see
DISASSEMBLY TASK
52-31-19-000-804-A01 and
ASSEMBLY TASK
52-31-19-400-805-A01.
(4) You cannot lock the hand (a) The bearing bolt 09-140 is Replace the bearing bolt
lever assembly 08-010 with broken. 09-140, see DISASSEMBLY
the handle flap 09-100 in TASK 52-31-19-000-805-A01
the CLOSED position. and ASSEMBLY TASK
52-31-19-400-804-A01.
Page 1009
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

(5) The handle flap 09-100 is (a) The force of the spring 09-110 The spring 09-110 is weak or
not flush with the contour cannot hold the handle flap broken. Replace the spring
of the hand lever assembly 09-100 in position. 09-110, see DISASSEMBLY
08-010. TASK 52-31-19-000-805-A01
and ASSEMBLY TASK
52-31-19-400-804-A01.
(6) The latching shaft does (a) Foreign objects between the Remove the latching shaft, see
not move easily. sliding surfaces of the bearing TASK 52-31-19-000-813-A01
bushes and the latching shaft. and ASSEMBLY TASK
52-31-19-400-808-A01.
Examine the latching shaft and
the bearing bushes, replace the
damaged parts.
(b) Not sufficient lubrication Apply Material No. 04-004
between the bearing bushes and Synthetic Ester Based Grease
the latching shaft. High Pressure to the sliding
surfaces of the bearing bushes
and the latching shaft.
(7) The locking shaft does not (a) Foreign objects between the Remove the locking shaft, see
move easily. sliding surfaces of the bearing DISASSEMBLY TASK
bushes and the locking shaft. 52-31-19-000-815-A01 and
ASSEMBLY TASK
52-31-19-400-810-A01.
Examine the locking shaft and
the bearing bushes, replace the
damaged parts.
(b) Not sufficient lubrication Apply Material No. 04-004
between the bearing bushes and Synthetic Ester Based Grease
the locking shaft. High Pressure to the sliding
and the locking shaft.
(8) The drift pin mechanism (a) Not sufficient lubrication Apply Material No. 04-004
does not move easily. between the bearing bushes and Synthetic Ester Based Grease
the drift pins 13-010. High Pressure to the sliding
and the drift pins 13-010.
Page 1010
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

(8) The interlock mechanism (a) The compression spring 44-040 Install a new compression
moves too easily. is broken or has lost its spring spring 44-040, see
force. DISASSEMBLY TASK
52-31-19-000-814-A01 and
ASSEMBLY TASK
52-31-19-400-809-A01.
(10) Hard movement of the (a) Not sufficient lubrication of the Apply Material No.04-004
latching mechanism. latching mechanism. Synthetic Ester Based Grease
High Pressure to the lubrication
fittings 33-030, 34-030 and
33-200, 34-200 of the latching
mechanism.
Fault Isolation
TABLE 3
Page 1011
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-700-804-A01
Test of the Electrical Resistance
1. General
ohmmeter
TABLE 1
B.
TASK 52-31-19-300-801-A01 Reworking or Machining
FIGURE 52-31-19-991-007-A FIGURE 52-31-19-991-007-A-Test of the Electrical Resistance
TABLE 2
3. Procedure
Subtask 52-31-19-750-004-A01
A. Test of the Electrical Resistance
NOTE : Remove the surface protection to get sufficient contact. See REPAIR TASK
52-31-19-300-801-A01 for the repair of the protective treatment.
(1) Test of the Electrical Resistance
ACTION RESULT
(1) Connect the ohmmeter near the bonding The resistance must not be more than 10 mω.
lead attachment point on the structure and
the cargo door structure which has a bare
metal point, see FIGURE 52-31-19-991-007-
A.
Electrical Resistance Test
TABLE 3
Page 1012
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
BONDING LEAD ATTACHMENT POINT ATTACHMENT ITEM
2 2
1 10.0m
2 REMOVE THE SURFACE PROTECTION 1

TO GET SUFFICIENT CONTACT.
REFER TO REPAIR FOR THE REPAIR
OF THE PROTECTIVE TREATMENT.
F_CM_523119_1_0070101_01_00
Test of the Electrical Resistance

FIGURE-52-31-19-991-007-A01
Page 1013
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-878-805-A01
Schematics and Wiring Diagram
1. Schematics and Wiring Diagram
NOTE : See FIGURE 52-31-19-991-008-A.
Page 2001
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
2
B A A
R
13 A
3154−5864−CF24
3154−5863−CF24 F B B
B
14 G C
7522VP
28WV−A
1
B A A
R
1 A 5235−1023−CF24
5235−1025−CF24 F B B
B
2 G C
7526VT 7532VP
5MJ−A
1856VC−A
FWD CARGO COMPARTMENT DOOR
F_CM_523119_1_0080101_01_00
Wiring Diagram
FIGURE-52-31-19-991-008-A01
Page 2002
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
DISASSEMBLY
**For PN’s ALL
TASK 52-31-19-000-801-A01
Removal of the Insulation and the Door Seal
1. General
A. Temporarily attach the bolts, washers, nuts and screws loosely to their attachment lugs. This
will keep them together for the subsequent installation procedure.
B. Do the INSPECTION/CHECK and TESTING AND FAULT ISOLATION procedure to find the
cause of a malfunction or to make sure that the component is in correct condition. Use only the
procedures that are necessary to get access to and to disassemble an unserviceable item.
A. Referenced Information
TASK 52-31-19-210-803-A01 Check of the Door Seals
TASK 52-31-19-300-802-A01 Repair of the Cargo Door Seal
TASK 52-31-19-220-801-A01 Visual Examination
TASK 52-31-19-300-803-A01 Replacement of Parts
TABLE 1
3. Procedure
CAUTION : MAKE SURE THAT THE COMPONENT IS CLEAN BEFORE YOU DISASSEMBLE
IT. THIS IS TO PREVENT CONTAMINATION OF INTERNAL PARTS.
Subtask 52-31-19-000-001-A01
A. Removal of the Insulation and the Door Seal

(1) Remove the fire protection lining assembly 02-010 as follows:
(a) Disconnect the stud assemblies 02-020 or 02-030 and remove the fire protection lining
assembly 02-010 from the door structure.
NOTE : It is only necessary to replace the cling strips 02-080 and the catch strips
02-090 if they are damaged.
NOTE : It is only necessary to replace the protective strip 02-070 if it is damaged.
Page 3001
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
NOTE : It is only necessary to replace the bushings 02-110 if they are not in the
limits, see CHECK TASK 52-31-19-220-801-A01 and REPAIR TASK
52-31-19-300-803-A01.
(2) Remove the door seal 02-100.
NOTE : It is only necessary to replace the door seal 02-100 if it is damaged, see CHECK
TASK 52-31-19-210-803-A01 and REPAIR TASK 52-31-19-300-802-A01.
Page 3002
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-802-A01
Removal and Disassembly of the Access Cover Assemblies
1. General
C. Remove only those parts of the insulation that you must remove to get access to the
component.
-
NOTE : For the removal of the insulation linings, see DISASSEMBLY TASK
52-31-19-000-801-A01.
TASK 52-31-19-000-801-A01 Removal of the Insulation and the Door Seal
TASK 52-31-19-000-806-A01 Removal and Disassembly of the Drift Pin Rods
TABLE 1
3. Procedure
Subtask 52-31-19-000-002-A01
A. Removal and Disassembly of the Access Cover Assemblies
Page 3003
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(1) Remove the access cover assembly 03-010 as follows:

(a) Disconnect the studs 03-070, 03-100, 03-110 and remove the access cover assembly
03-010 from the cargo door.
NOTE : It is only necessary to replace the stud assemblies 03-070, 03-100, 03-110 if
they are damaged.
NOTE : It is only necessary to replace the riveted receptacles 03-200 if they are
damaged, see TASK 52-31-19-300-803-A01.
(2) Remove the access cover 03-120 as follows:
NOTE : It is only necessary to remove the access cover 03-120 if a replacement of the
drift pin parts is necessary, see TASK 52-31-19-000-806-A01.
(a) Remove the screws 03-130 and remove the access cover 03-120.
(3) Remove the access cover assembly 03-140 as follows:
(a) Remove the screws 03-170, 03-190, the washers 03-180 and remove the access cover
assembly 03-140. Record the position and number of screws 03-190 for the assembly
procedure.
NOTE : It is only necessary to replace the self-adhesive sealing section 03-160 from
the access cover 03-150 if it is damaged.
(4) Remove the sight glasses 03-040 as follows:
NOTE : It is only necessary to replace the sight glasses 03-040 if they are damaged, see
CHECK TASK 52-31-19-220-801-A01.
(a) Remove the nuts 03-060, the screws 03-050 and remove the sheets 03-030 and the
sight glasses 03-040.
Page 3004
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-803-A01
Removal of the Plugs, the Adjusting Screws and the Protective Plugs
1. General
component.
-
52-31-19-000-801-A01.
A.Referenced Information
TABLE 1
3. Procedure
Subtask 52-31-19-000-003-A01
A. Removal of the Plugs, the Adjusting Screws and the Protective Plugs
NOTE : See IPL_FIGURE_01 and IPL_FIGURE_04.

(1) Remove the plugs 01-090.
NOTE : It is only necessary to replace the inserts 01-040 from the cargo door structure if
they are damaged, see REPAIR TASK 52-31-19-300-803-A01.
Page 3005
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(2) Remove the adjusting screws 01-100.
NOTE : It is only necessary to replace the adjusting screws 01-100 from the cargo door
structure if they are damaged.
NOTE : It is only necessary to replace the inserts 01-130 from the cargo door structure if
they are damaged, see REPAIR TASK 52-31-19-300-803-A01.
(3) Remove the protective plugs 04-020, 04-030 from the cargo door structure.
Page 3006
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-804-A01
Removal of the Hand Lever Mechanism
1. General
component.
-
52-31-19-000-801-A01.
TASK 52-31-19-210-805-A01 Check of the Locking Mechanism
TASK 52-31-19-210-804-A01 Check of the Door Mechanism
TABLE 1
3. Procedure
Subtask 52-31-19-000-004-A01
A. Removal of the Hand Lever Mechanism

(1) Set the hand lever assembly 08-010 to the UNLOCKED position.
Page 3007
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(2) Install a locally manufactured bush and a nut (e.g. NAS 509-4) on the spring bolt 08-400
and turn the nut until the compression spring 08-410 is fully compressed.
NOTE : The locally manufactured bush must be made of aluminum or bronze and have
the dimensions that follow:
- Length: 12.0 mm (0.4724 in)
- Inner Diameter: 7.5 mm (0.2953 in)
- Outer Diameter: 13.0 mm (0.5118 in)
(3) Disconnect the control rods 08-160, 08-540 as follows:
(a) Remove and discard the cotter pin 08-170 from the nut 08-180.
(b) Remove the nut 08-180, the washer 08-190, the bolt 08-200 and the washer 08-210
and disconnect the control rod 08-160 from the lever 08-090.
(c) Remove and discard the cotter pin 08-480 from the nut 08-490.
(d) Remove the nut 08-490, the washer 08-500, the bolt 08-520 and the washer 08-510
and disconnect the control rod 08-540 from the universal joint assembly 08-450.
(4) Remove the shaft 08-250 and the hand lever assembly 08-010 as follows:
(a) Remove the bolts 08-140 and the lock washer 08-150.
(b) Remove the shaft 08-250 and the spacer washers 08-260, 08-270 and remove the
hand lever assembly 08-010 from the cargo door. Measure and record the thickness of
the spacer washers 08-260, 08-270.
NOTE : It is only necessary to replace the lubrication fitting 08-280 on the shaft
08-250 if it is damaged, see CHECK TASK 52-31-19-220-801-A01 and
REPAIR TASK 52-31-19-300-803-A01.
(5) Remove and disassemble the lever assembly 08-020 as follows:
(a) Remove the nuts 08-110, the bolts 08-130 and the washers 08-120 from the bracket
08-030 and the door structure.
(b) Remove the nut 08-110, the washer 08-220 and the bolt 08-230 from the lever
08-090.
WARNING : THE LEVER ASSEMBLY IS INSTALLED WITH LOAD, REMOVE IT

CAREFULLY.
(c) Remove the lever assembly 08-020 from the shaft 08-250.
(d) Remove and discard the cotter pins 08-060 from the locating pins 08-050.
Page 3008
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(e) Remove the washers 08-070, the locating pins 08-050 and the washers 08-080 and
disconnect the actuating unit 08-040 from the lever 08-090 and the bracket 08-030.
NOTE : It is only necessary to replace the bonded-in bearing 08-100 on the lever
08-090 if it is worn, see CHECK TASK 52-31-19-220-801-A01 and REPAIR
TASK 52-31-19-300-803-A01.
(6) Remove the compression spring 08-410 as follows:
(a) Remove the nut 08-110, the washer 08-120 and the bolt 08-390.
WARNING : THE COMPRESSION SPRING IS INSTALLED WITH LOAD. REMOVE IT

CAREFULLY.
(b) Carefully remove the nut (e.g. NAS 509-4) and the bush from the spring bolt 08-400
and release the tension of the compression spring 08-410.
(c) Remove the compression spring 08-410 from the spring bolt 08-400.
NOTE : It is only necessary to replace the spring bolt 08-400 if it is not in the limits,
see CHECK TASK 52-31-19-210-805-A01.
(7) Remove the shaft 08-290 as follows:
(a) Remove the nut 08-110, the washer 08-220 and the bolt 08-230 from the universal
joint lock 08-240.
(b) Carefully remove the shaft 08-290 from the door structure and remove the universal
joint lock 08-240, the roller lever assembly 08-300 and the universal joint assembly
08-450.
NOTE : It is only necessary to replace the bonded-in bearing 08-530 on the universal
joint latch 08-460 if it is worn, see CHECK TASK 52-31-19-220-801-A01
and REPAIR TASK 52-31-19-300-803-A01.
NOTE : It is only necessary to replace the pressed-in bushes 08-470 on the universal
joint latch 08-460 if they are not in the limits, see CHECK TASK
52-31-19-210-804-A01 and REPAIR TASK 52-31-19-300-803-A01.
(d) Remove the nut 08-340, the washer 08-350 and the bolt 08-370 and remove the roller
08-330 from the roller lever 08-310.
NOTE : It is only necessary to replace the pressed-in bushes 08-320 on the roller
lever 08-310 if they are not in the limits, see CHECK TASK
(8) Remove the control rods 08-160, 08-540 as follows:
(a) Record the position of the control rods 08-160, 08-540.
Page 3009
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Remove and discard the cotter pins 08-170 from the fork-end connection of the
control rods 08-160, 08-540.
(c) Remove the nuts 08-180, the washers 08-190, the bolts 08-200 and the washers
08-210 from the fork-end connection of the control rods 08-160, 08-540.
(d) Disconnect the fork-end of the control rod 08-160 from the locking shaft.
(e) Disconnect the fork-end of the control rod 08-540 from the latching shaft.
(f) Measure and record the length of the control rods 08-160, 08-540 between the center
of the rod ends.
(9) Remove the catching hook 08-430 as follows:
(a) Remove the bolts 08-440, the washers 08-120 and remove the catching hook 08-430
and the sheet 08-420. Measure and record the thickness of the sheet 08-420.
Page 3010
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-805-A01
Disassembly of the Hand Lever Assembly
1. General
component.
-
52-31-19-000-801-A01.
TABLE 1
3. Procedure
Subtask 52-31-19-000-005-A01
A. Disassembly of the Hand Lever Assembly

(1) Remove the retaining rings 09-050, the washers 09-060, the bolts 09-040, the rollers 09-080
and remove the stop 09-030.
NOTE : It is only necessary to replace the bonded-in bushes 09-070 if they are not in the
52-31-19-300-803-A01.
Page 3011
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(2) Remove the bolts 09-190, the washers 09-150 and remove the sequence cams 09-020.
NOTE : It is only necessary to replace the bonded-in insert 09-090 and the inserts 09-200
if they are damaged, see REPAIR TASK 52-31-19-300-803-A01.
(3) Remove and discard the cotter pins 09-120 from the two ends of the bearing bolts 09-140
and 09-160.
(4) Remove the washers 09-130 and remove the bearing bolt 09-140.
WARNING : THE SPRING IS INSTALLED WITH LOAD.

(5) Remove the washers 09-150 and the bearing bolt 09-160 and collect the spring sleeve
09-170, the spring 09-110 and the handle flap 09-100.
NOTE : It is only necessary to replace the bonded-in bushes 09-180 if they are not in the
52-31-19-300-803-A01.
NOTE : It is only necessary to replace the bonded sliding layer 09-210 from the handle
flap 09-100 if it is damaged.
Page 3012
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-806-A01
Removal and Disassembly of the Drift Pin Rods
1. General
component.
-
52-31-19-000-801-A01.
TABLE 1
3. Procedure
Subtask 52-31-19-000-006-A01
A. Removal and Disassembly of the Drift Pin Rods

(1) Remove the fixed rod 20-180 as follows:
(a) Remove and discard the cotter pin 20-090.
(b) Remove the nut 20-100, the washer 20-080, the bolt 20-220 and the washer 20-230.
(c) Remove the rod 20-180 from the link lever assembly 13-230.
Page 3013
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(2) Remove the rod 40-010 as follows:

(b) Remove the nut 40-050, the washer 40-040, the bolt 40-020 and the washer 40-030.
(c) Remove the rod 40-010 from the link lever 13-130.
(3) Remove the rods 13-080, 13-270 as follows:
(a) Remove and discard the cotter pins 13-070, 13-360.
(b) Remove the nuts 13-050, 13-350, the washers 13-060, 13-340, the bolts 13-020,
13-310 and the washers 13-320.
(c) Remove the rods 13-080, 13-270 and the washers 13-030, 13-330.
NOTE : Do not disassemble the rods 13-080, 13-270.

(4) Remove the drift pins 13-010 from the door structure.
(5) Remove the rod 13-180 as follows:
(a) Remove and discard the cotter pins 13-360.
(b) Remove the nuts 13-350, the washers 13-340, the bolts 13-310 and the washers
13-320.
(c) Remove the rod 13-180 from the bellcrank assemblies 13-090, 13-190.
(6) Remove the bellcrank assembly 13-090 as follows:
(a) Remove the nuts 13-300, the sleeves 13-290 and the taper pins 13-280.
(b) Remove the link lever 13-130 from the beam 3-shaft 13-160.
NOTE : It is only necessary to replace the bonded-in bearing 13-150 on the lever
TASK 52-31-19-300-803-A01.
(c) Support the link lever assembly 13-100 and remove the beam 3-shaft 13-160 and the
link lever 13-130 from the cargo door structure.
NOTE : It is only necessary to replace the bonded-in bearings 13-120 on the link
lever 13-110 if they are worn, see CHECK TASK 52-31-19-220-801-A01
and REPAIR TASK 52-31-19-300-803-A01.
(7) Remove the belllcrank assembly 13-190 as follows:
Page 3014
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Support the link lever assemblies 13-200, 13-230 and remove the beam 3-shaft
13-260, the link lever assemblies 13-200, 13-230 and the bush 13-170 from the cargo
door structure.
NOTE : It is only necessary to replace the bonded-in bearings 13-220, 13-250 on the
link levers 13-210, 13-240 if they are worn, see CHECK TASK
Page 3015
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-807-A01
Removal and Disassembly of the Cover Beam 4
1. General
component.
-
52-31-19-000-801-A01.
TABLE 1
3. Procedure
Subtask 52-31-19-000-007-A01
A. Removal and Disassembly of the Cover Beam 4

(b) Remove the nuts 40-050, the washers 40-040, the bolts 40-020 and the washers
40-030.
Page 3016
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(c) Remove the rod 40-010 and disconnect the rod 40-150 from the lever assembly
41-220.
NOTE : Do not disassemble the rod 40-010.

(2) Remove and disassemble the cover beam 4 assembly 40-070 as follows:
(a) Remove the bolts 40-240, the washers 40-250 and remove the cover beam 4 assembly
40-070 from the door structure.
(b) Remove and discard the cotter pin 40-160.
(c) Remove the nut 40-170, the washer 40-180, the bolt 40-190 and the washer 40-200.
(d) Remove the rod 40-150 from the beam 4 lever 40-120.
(e) Remove the nuts 40-220, the sleeves 40-230 and the taper pins 40-210.
(f) Remove the beam 4 shaft 40-100, the spacer sleeve 40-110 and the beam 4 levers
40-120 from the cover beam 4 40-080.
NOTE : It is only necessary to replace the bonded-in bearings 40-140 on the beam 4
levers 40-120 if they are worn, see CHECK TASK 52-31-19-220-801-A01
and REPAIR TASK 52-31-19-300-803-A01.
NOTE : It is only necessary to replace the pressed-in bushes 40-090 on the cover
beam 4 40-080 if they are not in the limits, see CHECK TASK
Page 3017
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-808-A01
Removal and Disassembly of the Sequence Shaft Assembly
1. General
component.
-
52-31-19-000-801-A01.
TASK 52-31-19-000-807-A01 Removal and Disassembly of the Cover Beam 4
TABLE 1
3. Job Setup
Subtask 52-31-19-010-002-A01
A. Preliminary Procedures
(1) Make sure that the cover beam 4 assembly is disconnected from the sequence shaft
assembly, see DISASSEMBLY TASK 52-31-19-000-807-A01.
Page 3018
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
4. Procedure
Subtask 52-31-19-000-008-A01
A. Removal and Disassembly of the Sequence Shaft Assembly
NOTE : Identify and record the position of the serrated lever assembly 41-220 and the serrated
lever 41-360 on the sequence shaft assembly 41-200.
(1) Remove the connecting rod assembly 41-440 as follows:
(b) Remove the nuts 41-380, the washers 41-390, the bolts 41-410, the washers 41-400
and the connecting rod assembly 41-440.
NOTE : It is only necessary to replace the bonded-in bearings 41-460 on the

connecting rod 41-450 if they are worn, see CHECK TASK
(2) Remove and disassemble the link assembly 41-010 as follows:
(a) Remove the link assembly 41-010 as follows:
1 Remove and discard the cotter pins 41-110, 41-350.
2 Remove the nuts 41-100, 41-340, the washers 41-090, 41-290, the bolts 41-080,
41-320, the link assembly 41-010, the sleeves 41-070, 41-330 and the bush
41-270.
(b) Disassemble the link assembly 41-010 as follows:
1 Release the tab washers 41-040.
2 Loosen the nuts 41-030, 41-050.
3 Remove the forks 41-020, 41-060 from the rod 41-120.
4 Remove the tab washers 41-040 and the nuts 41-030, 41-050 from the rod
41-120.
5 Discard the tab washers 41-040.
(3) Remove the lever assembly 41-130 as follows:
(b) Remove the nut 41-380, the washer 41-390 and the lever assembly 41-130 from the
fitting support 41-170.
NOTE : It is only necessary to replace the pressed-in bushes 41-150, 41-160 on the
lever 41-140 if they are not in the limits, see CHECK TASK
Page 3019
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
NOTE : It is only necessary to replace the riveted fitting support 41-170 on the
cargo door structure if it is damaged, see REPAIR TASK 52-31-19-300-803-
A01.
(4) Remove the sequence shaft assembly 41-200 as follows:
(a) Remove the nuts 41-300, the washers 41-290 and the rivet pins 41-280.
(b) Remove the nut 41-300 and the rivet pin 41-310.
(c) Release the lockwasher 41-430.
(d) Remove the screw 41-420 and the lockwasher 41-430.
(e) Discard the lockwasher 41-430.
(f) Remove the serrated lever 41-360, the link lever 41-260, the serrated lever assembly
41-220, the sequence shaft 41-210 and the locking cam 41-250 from the cargo door
structure. Record the position of the serrated lever 41-360, the link lever 41-260, the
serrated lever assembly 41-220 and the locking cam 41-250 for the assembly
procedure.
NOTE : It is only necessary to replace the bonded-in bearing 41-240 on the serrated
lever 41-230 if it is worn, see CHECK TASK 52-31-19-220-801-A01 and
REPAIR TASK 52-31-19-300-803-A01.
Page 3020
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-809-A01
Removal of the Vent Door Assembly Mechanism
1. General
component.
-
52-31-19-000-801-A01.
TABLE 1
3. Procedure
Subtask 52-31-19-000-009-A01
A. Removal of the Vent Door Assembly Mechanism

(1) Remove the cover 20-010 as follows:
(a) Remove the nuts 20-020, the washers 20-030, the screws 20-040, the spacers 20-050
and the cover 20-010 from the cargo door structure.
Page 3021
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Remove the nuts 20-100, the bolts 20-070, 20-220, the washers 20-080, 20-230 and
the bush 20-110.
(c) Remove the rods 20-120, 20-180 from the vent door assembly 20-060 and the
bellcrank assembly 20-130.
NOTE : Do not disassemble the rods 20-120, 20-180

(3) Remove the bellcrank assembly 20-130 as follows:
(b) Support the link lever assemblies 20-140 and remove the beam 3 shaft 20-170 and the
link lever assemblies 20-140 from the cargo door structure.
NOTE : It is only necessary to replace the bonded-in bearings 20-160 on the link
levers 20-150 if they are worn, see CHECK TASK 52-31-19-220-801-A01
and REPAIR TASK 52-31-19-300-803-A01.
Page 3022
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-810-A01
Removal and Disassembly of the Vent Door Assembly
1. General
component.
-
52-31-19-000-801-A01.
TABLE 1
3. Procedure
Subtask 52-31-19-000-010-A01
A. Removal and Disassembly of the Vent Door Assembly

(1) Remove the vent door assembly 21-110 as follows:
(b) Remove the nuts 21-020 and the washers 21-030.
WARNING : THE SPRINGS ARE INSTALLED WITH LOAD.
Page 3023
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(c) Remove the sleeves 21-070.

(d) Remove the bolts 21-080, the washers 21-030 and the sleeve 21-100.
(e) Remove the washers 21-040, 21-050 and record the number of washers 21-040,
21-050 used.
(f) Remove the springs 21-060, 21-090.
(g) Remove the vent door assembly 21-110 from the cargo door.
(2) Disassemble the vent door assembly 21-110 as follows:
NOTE : It is only necessary to replace the pressure-relief flap seal 21-180 on the vent
door 21-210 if it is damaged, see REPAIR TASK 52-31-19-300-803-A01.
NOTE : It is only necessary to replace the riveted retainers 21-190, 21-200 on the vent
door 21-210 if they are damaged, see REPAIR TASK 52-31-19-300-803-A01.
NOTE : It is only necessary to replace the pressed-in bushes 21-240, 21-250, 21-260,
21-330, 21-340, 21-410, 21-420 on the actuator arms 21-230, 21-320 and the
bracket 21-400 if they are damaged, see CHECK TASK 52-31-19-220-801-A01
and REPAIR TASK 52-31-19-300-803-A01.
(a) Remove the bracket assembly 21-390 as follows:
1 Remove the nuts 21-140, the washers 21-130, the screws 21-150 and the bracket
assembly21-390 from the vent door 21-210.
(b) Remove and discard the cotter pins 21-170.
(c) Remove the washers 21-130 and the spring bolts 21-160 from the actuator arm
assemblies 21-220, 21-310.
(d) Remove and disassemble the actuator arm assemblies 21-220, 21-310 as follows:
1 Remove the nuts 21-140, the washers 21-130, the screws 21-120, 21-150 and the
actuator arm assemblies 21-220, 21-310 from the vent door 21-210.
2 Release the tab washers 21-280, 21-360 and loosen the nuts 21-290, 21-370.
3 Remove the bolts 21-270, 21-350 with the tab washers 21-280, 21-360 and the
nuts 21-290, 21-370 from the actuator arms 21-230, 21-320.
NOTE : It is only necessary to replace the inserts 21-300, 21-380 on the

actuator arms 21-230, 21-320 if they are damaged, see TASK
52-31-19-300-803-A01.
4 Remove the tab washers 21-280, 21-360 and the nuts 21-290, 21-370 from the
bolts 21-270, 21-350.
5 Discard the tab washers 21-280, 21-360.
Page 3024
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-811-A01
Removal of the Latching Mechanism Assemblies
1. General
component.
-
52-31-19-000-801-A01.
TABLE 1
3. Procedure
Subtask 52-31-19-000-011-A01
A. Removal of the Latching Mechanism Assemblies
NOTE : Do the steps that follow for each of the four latching mechanism assemblies 30-020,
30-030.
(1) Remove and discard the cotter pin 30-270 from the nut 30-280.
(2) Remove the nuts 30-280, the bolt 30-230, 30-290, the washers 30-240 and the bushes
30-250, 30-260.
Page 3025
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(4) Remove the nut 30-060, the bolt 30-080, the washer 30-070, 30-090 and the sleeve 30-120.
(5) Remove the nut 30-150, the bolt 30-130 and the washers 30-140.
(7) Remove the nut 30-190, the bolt 30-160, the washers 30-170 and the sleeve 30-210.
(8) Remove the latching mechanism assemblies 30-020, 30-030 from the cargo door.
(9) Remove the shouldered bushings 30-100, 30-110.
Page 3026
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-812-A01
Disassembly of the Latching Hook Assemblies
1. General
component.
-
52-31-19-000-801-A01.
TABLE 1
3. Procedure
Subtask 52-31-19-000-012-A01
A. Disassembly of the Latching Hook Assemblies
NOTE : Do the steps that follow for each of the four latching hook assemblies.
(1) Remove and discard the cotter pins 33-140, 34-140 from the nuts 33-120, 34-120.
(2) Remove the nuts 33-120, 34-120, the bolts 33-080, 34-080, 33-150, 34-150 and the washers
33-090, 34-090, 33-130, 34-130.
Page 3027
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(3) Disconnect the connecting link 33-070, 34-070 from the bellcrank assembly 33-160, 34-160
and from the latching hook assembly 33-010, 34-010.
(4) Remove the bushes 33-100, 34-100, 33-110, 34-110 from the connecting Link 33-070,
34-070.
(5) Remove the sleeves 33-060, 34-060 from the latching hook assembly 33-010, 34-010 and
from the bellcrank assembly 33-160, 34-160.
34-050 on the latching hook 33-020, 34-020 if they are not in the limits, see
CHECK TASK 52-31-19-210-804-A01 and REPAIR TASK 52-31-19-300-803-
A01,
34-190 on the bellcrank 33-170, 34-170 if they are not in the limits, see CHECK
TASK 52-31-19-210-804-A01 and REPAIR TASK 52-31-19-300-803-A01.
NOTE : It is only necessary to replace the lubrication fitting 33-030, 34-030 on the
latching hook 33-020, 34-020 if it is damaged, see CHECK TASK
NOTE : It is only necessary to replace the lubrication fitting 33-200, 34-200 on the
bellcrank 33-170, 34-170 if it is damaged, see CHECK TASK 52-31-19-220-801-
A01 and REPAIR TASK 52-31-19-300-803-A01.
(6) Remove and discard the cotter pin 33-140, 34-140 from the nut 33-250, 34-250.
(7) Remove the nut 33-250, 34-250, the bolt 33-210, 34-210, the washers 33-220, 34-220 and
the bush 33-240, 34-240 and remove the connecting rod 33-260, 34-260 from the bellcrank
33-170, 34-170.
NOTE : It is only necessary to replace the pressed-in bush 33-230, 34-230 on the
bellcrank 33-170, 34-170 if it is not in the limits, see CHECK TASK
NOTE : Do not disassemble the connecting rod 33-260, 34-260.
Page 3028
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-813-A01
Removal and Disassembly of the Latching Shaft Assembly
1. General
TASK 52-31-19-000-812-A01 Disassembly of the Latching Hook Assemblies
TABLE 1
3. Job Setup
CAUTION : IT IS NOT PERMITTED TO REPAIR OR REPLACE COMPONENTS THAT ARE

ASSEMBLED WITH TAPER PIN(S). IF YOU FIND A DEFECTIVE COMPONENT
THAT IS ASSEMBLED WITH TAPER PIN(S), YOU MUST REPLACE THE
ASSEMBLY.
Subtask 52-31-19-010-003-A01
(1) Remove only those parts of the insulation that you must remove to get access to the
component, see DISASSEMBLY TASK 52-31-19-000-801-A01.
(2) Make sure that the hand lever mechanism is disconnected, see DISASSEMBLY TASK
52-31-19-000-804-A01.
(3) Make sure that the latching hook assemblies are disconnected, see DISASSEMBLY TASK
52-31-19-000-812-A01.
Page 3029
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
4. Procedure
Subtask 52-31-19-000-013-A01
A. Removal and Disassembly of the Latching Shaft Assembly

(1) Remove the nuts 32-130, the sleeves 32-120 and the taper pins 32-100, 32-110.
(2) Remove the latching shaft 32-020, the shaft levers 32-030, 32-040, the switch lever 32-060,
the hinged lever assembly 32-070 and the stop cam 32-050. Record the position of the
shaft levers 32-030, 32-040.
NOTE : It is only necessary to replace the bonded-in bearing 32-090 on the hinged lever
TASK 52-31-19-300-803-A01.
Page 3030
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-814-A01
Removal and Disassembly of the Interlock Mechanism
1. General
component.
-
52-31-19-000-801-A01.
TABLE 1
3. Procedure
Subtask 52-31-19-000-014-A01
A. Removal and Disassembly of the Interlock Mechanism
NOTE : See IPL_FIGURE_44..

(1) Remove the interlock mechanism 44-090 as follows:
WARNING : THE COMPRESSION SPRING IS INSTALLED WITH LOAD. REMOVE IT

CAREFULLY.
(a) Compress the compression spring 44-040 and the spring sleeve assembly 44-010 to
decrease its length.
Page 3031
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Remove and discard the cotter pins 44-060 from the pins 44-050.
(d) Remove the nut 44-290, the bolt 44-260 and the washers 44-300.
(e) Remove the bushes 44-230, 44-270 and remove the interlock mechanism 44-090 from
the cargo door structure.
(f) Remove and discard the cotter pin 44-060 from the nut 44-240.
(g) Remove the nut 44-240, the bolt 44-250 and the washers 44-070, 44-220.
(h) Remove the pin 44-050 and the washer 44-070.
(i) Remove the washer 44-070, the pin 44-050 and the spacers 44-080 and remove the
spring sleeve assembly 44-010 and the compression spring 44-040.
NOTE : It is only necessary to replace the pressed-in bushing 44-030 on the spring
sleeve 44-020 if it is not in the limits, see CHECK TASK 52-31-19-210-804-
A01 and REPAIR TASK 52-31-19-300-803-A01.
(2) Disassemble the interlock mechanism 44-090 as follows:
(a) Remove the retaining ring 44-160 and the pin 44-110.
(b) Remove the retaining rings 44-160, the pins 44-110 and remove the connecting rod
44-150 from the levers 44-100, 44-170.
(c) Remove the adjusting screw 44-180, the nut 44-190 and the locking plate 44-200 from
the lever 44-170.
(d) Remove the retaining ring 44-120, the pin 44-130 and the roller 44-140 from the lever
44-100.
Page 3032
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-815-A01
Removal of the Locking Shaft Assembly
1. General
TASK 52-31-19-000-809-A01 Removal of the Vent Door Assembly Mechanism
TASK 52-31-19-000-807-A01 Removal and Disassembly of the Cover Beam 4
TABLE 1
3. Job Setup
CAUTION : IT IS NOT PERMITTED TO REPAIR OR REPLACE COMPONENTS THAT ARE

ASSEMBLED WITH TAPER PIN(S). IF YOU FIND A DEFECTIVE COMPONENT
THAT IS ASSEMBLED WITH TAPER PIN(S), YOU MUST REPLACE THE
ASSEMBLY.
Subtask 52-31-19-010-004-A01
(1) Remove only those parts of the insulation that you must remove to get access to the
component, see DISASSEMBLY TASK 52-31-19-000-801-A01.
(2) Make sure that the hand lever assembly is disconnected, see TASK 52-31-19-000-804-A01.
(3) Make sure that the vent door mechanism is disconnected, see TASK 52-31-19-000-809-
A01.
Page 3033
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(4) Make sure that the drift pin mechanism is disconnected, see TASK 52-31-19-000-807-A01.
4. Procedure
Subtask 52-31-19-010-001-A01
A. Removal of the Locking Shaft Assembly

(1) Remove the nuts 31-090, the washers 31-100, the sleeves 31-110, the taper pins 31-080
and the rivet pins 31-120.
(2) Discard the nuts 31-090 and the rivet pins 31-120.
(3) Remove the locking shaft 31-020 with the lever 31-060, the hinged lever assembly 31-030
and the locking cams 31-070. Record the position of the locking cams 31-070.
NOTE : It is only necessary to replace the bonded-in bearing 31-050 on the hinged lever
TASK 52-31-19-300-803-A01.
Page 3034
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-816-A01
Removal of the Cargo Door Drainage
1. General
component.
-
52-31-19-000-801-A01.
TABLE 1
3. Procedure
Subtask 52-31-19-000-015-A01
A. Removal of the Cargo Door Drainage

(1) Remove the hose 50-010 as follows:
(a) Cut and discard the cable ties 50-090.
(b) Remove the nut 50-130, the bolt 50-110, the washers 50-120 and remove the mount
50-100 from the door structure.
(c) Remove the hose 50-010 from the cargo door structure.
Page 3035
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(2) Remove the basic valve 50-030 and the tube 50-080 as follows:
(a) Remove the nuts 50-060, the screws 50-040 and the washers 50-050.
(b) Remove the flange 50-070 with the tube 50-080 and the valve retainer50-020 with the
basic valve 50-030.
Page 3036
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-817-A01
Removal of the Door Proximity Sensors
1. General
component.
-
52-31-19-000-801-A01.
TABLE 1
3. Procedure
Subtask 52-31-19-000-016-A01
A. Removal of the Door Proximity Sensors

(1) Disconnect the electrical harness from the proximity sensors 62-010.
(2) Install blanking caps on the electrical connectors.
(3) Remove the proximity sensor 28WV 62-010, Detail C, as follows:
(a) Remove the nuts 62-060, the washers 62-050, the screws 62-040 and remove the
proximity sensor 62-010 from the door structure.
Page 3037
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(4) Remove the proximity sensor 5MJ 62-010, Detail B, as follows:

(a) Remove the screws 62-040 and remove the proximity sensor 62-010 from the door
structure.
(5) Remove the targets 62-020 as follows:
(a) Remove the nuts 62-060, the washers 62-050, the screws 62-040, 62-030 and remove
the targets 62-020 from the door mechanism.
Page 3038
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-000-818-A01
Removal of the Hinge Assemblies
1. General
component.
-
52-31-19-000-801-A01.
TABLE 1
3. Procedure
Subtask 52-31-19-000-017-A01
A. Removal of the Hinge Assemblies

(1) Remove the end fittings 90-010, 91-090 as follows:
(a) Remove the nuts 90-120, 91-120, the washers 90-140, 91-140, the screws 90-100,
91-100, 90-130, 91-130, the washers 90-110, 91-110 and remove the end fittings
90-010, 91-090 and the shims 90-020, 91-080. Record the position and number of the
shims 90-020, 91-080.
Page 3039
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(2) Remove the hinge assemblies 90-030, 90-060, 91-010, 91-050.
NOTE : It is only necessary to replace the hinge assemblies 90-030, 90-060, 91-010,
91-050 on the door structure if they are damaged, see REPAIR TASK
52-31-19-300-803-A01. If you must remove a defective hinge assembly, measure
and identify the position and the thickness of the hinge shims.
NOTE : It is only necessary to replace the bushes 90-050, 90-080, 90-090, 91-030,
91-040, 91-070 on the hinges 90-040, 90-070, 91-020, 91-060 if they are not in
the limits, see CHECK TASK 52-31-19-210-804-A01 and REPAIR TASK
52-31-19-300-803-A01.
Page 3040
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
CLEANING
**For PN’s ALL
TASK 52-31-19-100-801-A01
Cleaning
1. General
- Not applicable
11-001 Detergent
19-003 Lint-Free Cotton Cloth
11-003 Methyl-Ethyl-Ketone
talcum powder
11-010 Isopropyl Alcohol
11-019 Cabin Window Cleaner
TABLE 1
B. Fixtures, Tools, Test and Support Equipment

vacuum cleaner
TABLE 2
3. Procedure
Subtask 52-31-19-100-001-A01
A. Clean the Painted Component Parts as follows:
(1) Remove the loose dirt with a vacuum cleaner or a soft brush.
CAUTION : USE ONLY THE SPECIFIED CLEANING AGENT (MATERIAL NO. 11-001).
(2) Remove the old sealant and the remaining dirt with a nonmetallic scraper.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 11-001 DETERGENT. OBEY
THE MATERIAL MANUFACTURER’S INSTRUCTIONS.
Page 4001
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(3) Clean the painted component parts with Material No. 11-001 Detergent.
(a) Use a soft brush or clean Material No. 19-003 Lint-Free Cotton Cloth.
(4) Make sure that the drain valves and holes are clean and not clogged.
(5) Dry the component parts with clean, dry Material No. 19-003 Lint-Free Cotton Cloth or
with a hot-air blower.
Subtask 52-31-19-100-002-A01
B. Clean the Component Parts that are not painted as follows:
(2) Remove the remaining dirt with a nonmetallic scraper.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 11-003 METHYL-ETHYL-

KETONE. OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS.
(3) Clean the component parts that are not painted with Material No.11-003 Methyl-Ethyl-
Ketone.
(4) Dry the clean parts with clean, dry Material No. 19-003 Lint-Free Cotton Cloth.
(5) Clean all bushes and bearings with clean, dry Material No. 19-003 Lint-Free Cotton Cloth.
(6) Clean the door seal, the vent door seal and the CFRP parts with a weak soap solution.
(7) Dry the clean seals and the CFRP parts with clean, dry Material No. 19-003 Lint-Free
Cotton Cloth.
(8) Apply talcum powder to the door seal and the vent door seal.
Subtask 52-31-19-100-003-A01
C. Clean the Electrical Components as follows:
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 11-010 ISOPROPYL

ALCOHOL. OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS.
(2) Clean the electrical wiring with Material No. 11-010 Isopropyl Alcohol.

ALCOHOL. OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS.
(3) Clean the electrical connectors with Material No. 11-010 Isopropyl Alcohol,
(4) Dry the parts with clean, dry Material No. 19-003 Lint-Free Cotton Cloth or a hot-air
blower.
Page 4002
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
Subtask 52-31-19-100-004-A01
D. Clean the Sight Glasses as follows:
CAUTION : DO NOT RUB THE SURFACE WITH DRY CLOTH.

(1) Clean the sight glasses with a weak soap solution.
(2) Dry the sight glasses with clean, dry Material No.19-003 Lint-Free Cotton Cloth.
(3) If more cleaning is required, clean the sight glasses with Material No. 11-019 Cabin
Window Cleanerand dry them with clean, dry Material No. 19-003 Lint-Free Cotton Cloth.
Page 4003
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
INSPECTION/CHECK
**For PN’s ALL
TASK 52-31-19-210-801-A01
Check of the Door Structure
1. General
A. The check is a visual inspection of the door structure.
B. Do an approved nondestructive test if you think there is a crack which is not clearly visible.
2. Procedure
CAUTION : THE LIMITS OF ALLOWABLE DAMAGE ARE ALWAYS RELATED TO THE

NOMINAL MATERIAL THICKNESS OF THE COMPONENT PARTS.
Subtask 52-31-19-210-001-A01
A. Check of the Door Structure
(1) Do a check of the door structure for damage.
(a) For the Allowable Damage Limits (ADL) and the repair procedure, see the Structural
Repair Manual (SRM).
Page 5001
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-210-802-A01
Structure Components
1. General
A. The check is a visual inspection of the component parts.
C. For the replacement of the permanently attached parts, see REPAIR.
TASK 52-31-19-000-818-A01 Removal of the Hinge Assemblies
TASK 52-31-19-400-818-A01 Installation of the Hinge Assemblies
TABLE 1
3. Procedure
Subtask 52-31-19-210-002-A01
A. Structure Components
NOTE : See TABLE 2 for the appropriate procedures for parts specified as structure
component.
Structure Component IPL Figure-Item Disassembly Assembly
End Fitting 90-010 TASK 52-31-19-000-818- TASK 52-31-19-400-818-
Hinge 90-040 A01 A01
Hinge 90-070
End Fitting 91-090 TASK 52-31-19-000-818- TASK 52-31-19-400-818-
Hinge 91-020 A01 A01
Hinge 91-060
Structure Components
TABLE 2
(1) Do a check of the structure components for cracks, deformation and corrosion.
(a) Cracks, deformation and corrosion are not permitted.
Page 5002
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) See DISASSEMBLY, ASSEMBLY for the replacement of the structure components
which have cracks, deformation and corrosion.
(2) Do a check of the structure components for scratches and marks.
(a) Scratches and marks are permitted up to a depth of 0.25 mm (0.01 in).
(b) See REPAIR TASK 52-31-19-300-801-A01 for the removal of scratches or marks
which are in the limits.
(c) See DISASSEMBLY, ASSEMBLY for the replacement of the structure components
which have scratches or marks that are not in the limits.
Page 5003
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-210-803-A01
Check of the Door Seal
1. General
A. The check is a visual inspection of the door seal.
2. Procedure

Subtask 52-31-19-210-003-A01
A. Check of the Door Seal

(1) Do a check of the door seal for hardening, cracks, oil contamination and porosity.
(a) No hardening, cracks, oil contamination or porosity are permitted.
(b) See DISASSEMBLY and ASSEMBLY for the replacement of the door seals which
have cracks, porosity, oil contamination or are hardened.
Page 5004
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-210-804-A01
Check of the Door Mechanism
1. General
A. The check is a visual inspection of the door mechanism.
TASK 52-31-19-820-807-A01 Fits and Clearances - Tables
TABLE 1
3. Procedure

Subtask 52-31-19-210-004-A01
A. Door Mechanism
(1) Examine all the component parts of the door mechanism for wear.
(a) See FITS AND CLEARANCES TASK 52-31-19-820-807-A01 for the wear limits.
(b) See DISASSEMBLY, ASSEMBLY or REPAIR for the replacement of component parts
which have wear that is not in the limits.
Page 5005
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-210-805-A01
Check of the Locking Mechanism
1. General
A. The check is a visual inspection of the door locking mechanism.
TASK 52-31-19-820-807-A01 Fits and Clearances - Tables
TABLE 1
3. Procedure

Subtask 52-31-19-210-005-A01
A. Check of the Locking Mechanism

(1) Do a check for cracks.
(a) Cracks are not permitted.
(b) See DISASSEMBLY and ASSEMBLY for the replacement of the parts which have
cracks.
(2) Do a check for scratches, marks and corrosion.
(a) Scratches, marks and corrosion are permitted up to a maximum depth of 0.3 mm
(0.012 in).
(b) See REPAIR TASK 52-31-19-300-801-A01 for the removal of the scratches, marks
and corrosion which are in the limits.
(c) See DISASSEMBLY and ASSEMBLY for the replacement of the parts which have
scratches, marks and corrosion that are not in the limits.
(3) Do a check for deformation.
(a) Deformation is not permitted.
Page 5006
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
deformation.
(4) Do a check for wear.
(a) Make sure that the outer diameter of the spring bolt 08-400 is more than or equal to
6.25 mm (0.2461 in).
(b) Replace the parts which have dimensions that are not in the limits, see FITS AND
CLEARANCES TASK 52-31-19-820-807-A01.
(c) See DISASSEMBLY and ASSEMBLY for the replacement of the parts which are not
in the limits.
(5) Check for other damage.
(a) Other damage is not permitted.
other damage.
Page 5007
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-210-806-A01
Check of the Protective Treatment
1. General
A. The check is a visual inspection of the protective treatment.
TABLE 1
3. Procedure
Subtask 52-31-19-210-006-A01
A. Check of the Protective Treatment
(1) Examine the structure components and the door mechanism for damaged protective
treatment.
(a) See REPAIR TASK 52-31-19-300-801-A01 for the repair of the protective treatment.
Page 5008
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-210-807-A01
Check of the Electrical Equipment
1. General
A. The check is a visual inspection of the electrical equipment parts.
TASK 52-31-19-100-801-A01 Cleaning
TABLE 1
3. Procedure

Subtask 52-31-19-210-007-A01
A. Check of the Electrical Equipment
(1) Examine the electrical harness and connections for loose and damaged attachments, chafe
marks, spots of arcing, contamination and other damage.
(a) Chafe marks, spots of arcing, contamination, loose and damaged attachments or other
damage are not permitted.
(b) See CLEANING TASK 52-31-19-100-801-A01 for the removal of contamination.
(c) Tighten the loose attachments and connections.
(d) Replace the attachments and connections which have damage.
(e) Replace the parts of the electrical harness which have chafe marks, spots of arcing
and other damage.
(2) Examine the electrical components for loose attachment, contamination and other damage.
(a) Damage is not permitted.
(b) Tighten the loose attachments.
(c) See CLEANING TASK 52-31-19-100-801-A01 for the removal of contamination.
(d) See DISASSEMBLY and ASSEMBLY for the replacement of the electrical
components.
Page 5009
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-210-808-A01
Check of the Springs
1. General
A. The check is a visual inspection and a test of the spring data.
FIGURE 52-31-19-991-010-A FIGURE 52-31-19-991-010-A-Check of the Torsion Springs
TABLE 1
3. Procedure

Subtask 52-31-19-210-008-A01
A. Check of the Springs
(1) Do a check for damage.
(a) Damage is not permitted.
(b) See DISASSEMBLY and ASSEMBLY for the replacement of the springs which have
damage.
(2) Do a check of the spring data.
(a) Do a check of the compression and tension springs, see TABLE 2.
IPL FIG. - ITEM FREE LENGTH mm (in) TEST LENGTH mm (in) LOAD daN (lbf)
08-410 61.0 (2.402) 45.2 (1.780) 25.90-31.14
(50.43-66.76)
44-040 98.0 (3.858) 78.0 (3.071) 7.08-13.10 (13.65-18.18)
Spring Dimensions (Compression and Tension Springs)
TABLE 2
Page 5010
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Do a check of torsion springs, see TABLE 3 and FIGURE 52-31-19-991-010-A.

IPL FIG. - Pos. Angle Bending Bending
ITEM Moment Moment
daNm lbf. in
A 09-110 A1 68.9 deg. 0.018 - 0.022 1.60 - 1.94
A2 127.9 deg. 0.032 - 0.040 2.84 - 3.54
B 21-060, 21-090 B1 20.52 deg. 0.074 - 0.087 6.55 - 7.70
B2 76.95 deg. 0.276 - 0.326 24.43 - 28.85
Test Data of the Torsion Springs
TABLE 3
(c) See DISASSEMBLY and ASSEMBLY for the replacement of the springs which have
test data that are not in the limits.
Page 5011
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A1
A2
B1
B2
F_CM_523119_1_0100101_01_01
Check of the Torsion Springs

FIGURE-52-31-19-991-010-A01
Page 5012
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-210-809-A01
Check of the Placard
1. General
A. The check is a visual inspection of the placard.
TABLE 1
3. Procedure

Subtask 52-31-19-210-009-A01
A. Bonded Identification Plate

(1) Examine the identification plate 01-080 for readability and attachment.
(a) Loose or damaged identification plates are not permitted.
(b) See TASK 52-31-19-300-803-A01 for the replacement of the damaged identification
plates.
Page 5013
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-220-801-A01
Visual Examination
1. General
A. The check is a visual inspection of component parts.
15-005 Corrosion Preventive Temporary Protective Compound
TABLE 1
B.Referenced Information
FIGURE 52-31-19-991-011-A FIGURE 52-31-19-991-011-A-Visual Examination of the Surface
Protection and Locking Indication
TABLE 2
3. Procedure

Subtask 52-31-19-220-001-A01
A. Visual Examination
NOTE : See IPL_FIGURE_01, IPL_FIGURE_03, IPL_FIGURE_08, IPL_FIGURE_09,

IPL_FIGURE_33, IPL_FIGURE_34 and IPL_FIGURE_50.
(1) Examine all screws, bolts, nuts and tapered pins for general condition, wear and other
damage.
(2) Examine all bearings for correct movement without play.
(3) Examine all bushes for wear, scratches, corrosion and correct installation.
(4) Examine all bonding leads for damage and corrosion.
(5) Examine all nut plates for damaged threads, correct attachment and corrosion.
Page 5014
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(6) Examine the hoist fitting inserts 01-040 for defective threads and corrosion.
(7) Examine the insulation for contamination and correct attachment.
(8) Make sure that the hose 50-010, the water drain valve 50-030 and holes are clean and not
blocked.
(9) Examine the red painted areas of the hand lever assembly 08-010, the handle flap 09-100
and the inside of the vent door frame for damage.
(10) Examine the lubrication fittings 08-280, 33-030, 33-200, 34-030, 34-200 for damage.
(11) Examine the red and green marks on the locking cams 31-070 for damage, see FIGURE
52-31-19-991-011-A.
(12) Examine the sight glasses 03-040 installed to the access cover for damage.
Subtask 52-31-19-220-002-A01
B. Check of the Surface Protection on the Door Structure
(1) Do a check of the surface protection of the door structure for damage.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 15-005 CORROSION

PREVENTIVE TEMPORARY PROTECTIVE COMPOUND. OBEY THE
MATERIAL MANUFACTURER’S INSTRUCTIONS.
(a) Make sure that all inner surfaces of the cargo door have a protection of Material
No.15-005 Corrosion Preventive Temporary Protective Compound, see FIGURE
52-31-19-991-011-A.

(b) Make sure that the outer surface, shown in FIGURE 52-31-19-991-011-A, has a
protection of Material No. 15-007 Corrosion Preventive Temporary Protective
Compound.
Page 5015
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
CARGO DOOR
SEAL
FR57A
CARGO DOOR
INSULATION
CORROSION PREVENTIVE CORROSION PREVENTIVE

(MAT. NO. 15−005) (MAT. NO. 15−007)
CARGO DOOR
STRUCTURE
CARGO DOOR SURFACE PROTECTION
LOCKING SHAFT
(REFER TO THE IPL−FIGURE 31)
83
AREA OF THE RED MARK
43
AREA OF THE GREEN MARK
LOCKING CAM, ITEM 70

(REFER TO THE IPL−FIGURE 31)
TYPICAL DIRECT VISUAL LOCKING INDICATION

F_CM_523119_1_0110101_01_01
Visual Examination of the Surface Protection and Locking Indication

FIGURE-52-31-19-991-011-A01
Page 5016
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
REPAIR
**For PN’s ALL
TASK 52-31-19-300-801-A01
Reworking or Machining
1. General
A. See CHECK for the limits.
B. See the Structural Repair Manual (SRM) for the door structure.
11-001 Detergent
16-020 Wash Primer
16-001 Anti Corrosion Primer (Polyurethane)
16-002 Polyurethane Topcoat Grey (for Internal Applic.)
13-002 Chemical Conversion Coating Yellow Aluminum
15-004 Corrosion Preventive Compound
abrasive cloth
TABLE 1

buffing wheel
TABLE 2
Page 6001
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
3. Procedure
WARNING : BE CAREFUL WHEN YOU USE SOLVENTS/CLEANING AGENTS, SEALANTS AND

OTHER MATERIALS. OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS
AND THE LOCAL REGULATIONS. MAKE SURE THAT THERE IS A GOOD FLOW
OF AIR THROUGH THE WORK AREA. DO NOT BREATHE THE FUMES. DO NOT
SMOKE. DO NOT USE THESE MATERIALS NEAR A FLAME, SPARKS OR
SOURCES OF HEAT. USE PROTECTIVE CLOTHING, GOGGLES AND GLOVES. IF
YOU GET ONE OF THESE MATERIALS ON YOUR SKIN OR IN YOUR EYES,
FLUSH IT AWAY WITH A FLOW OF CLEAN WATER. IF YOU GET ONE OF
THESE MATERIALS IN YOUR MOUTH, GET IMMEDIATE MEDICAL AID. IN
GENERAL, THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN
IRRITANTS.
CAUTION : USE ONLY THE SPECIFIED MATERIALS. MATERIALS WHICH ARE NOT
SPECIFIED, CAN CAUSE DAMAGE.
CAUTION : AFTER THE REMOVAL OF THE DAMAGE THE COMPONENTS PARTS MUST BE
IN THE LIMITS. REFER TO CHECK FOR THE LIMITS.
Subtask 52-31-19-300-004-A01
A. Reworking or Machining
CAUTION : THE WIDTH OF THE GROOVE AFTER THE REPAIR MUST NOT BE MORE
THAN 6 MM (0.24 IN.).
(1) Repair of Scratches and Marks
(a) Remove the necessary material from the scratch or the mark to make a shallow
groove.
NOTE : Do not remove more material than necessary and keep the width to 6.0 mm
(0.24 in).
(b) Make the groove smooth with abrasive cloth.
(c) Burnish the surface with your hands or with a buffing wheel.
(d) Repair the damaged paintwork as specified in .
(2) Repair of Corrosion Damage
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 11-001 DETERGENT.

OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS.
(a) Clean the corroded and the adjacent areas and remove the grease with Material
No.11-001 Detergent.
Page 6002
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Dry the wet areas with clean, dry Material No. 19-003 Lint-Free Cotton Cloth.
NOTE : Before you start to repair the corrosion damage, approved persons must
make an analysis of the level of the corrosion damage.
(c) Remove the surface protection from the corroded area with an abrasive cloth.
(d) Remove the corroded material.
1 Apply masking material around the corroded area.
2 Remove the corrosion with a synthetic sponge and/or an abrasive cloth.
3 Feather the material to the adjacent area, so that the transition to the work
area is smooth and without stress concentrations.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 11-003 METHYL-

ETHYL-KETONE. OBEY THE MATERIAL MANUFACTURER’S
INSTRUCTIONS.
4 Clean the work area with Material No. 11-003 Methyl-Ethyl-Ketone.
5 Let the work area dry.
(e) Use a magnifying glass to make sure that all corroded material is removed and that
there are no cracks.
NOTE : It is important that all corroded material is removed before you continue
the work. The smallest corroded area can cause new extended corrosion
damage.
NOTE : If you find a defect, you must do an approved nondestructive test.

(f) Repair the damaged paintwork as specified in .
(g) Remove the masking material.
(3) Repair of the Protective Treatment
(a) Repair of Damaged Paintwork
1 Remove the damaged paintwork with an abrasive cloth.
2 Remove the paint dust.

INSTRUCTIONS.
3 Clean the work area with Material No. 11-003 Methyl-Ethyl-Ketone.
NOTE : Do not touch the cleaned area.

4 Let the work area dry.
Page 6003
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 16-020 WASH

PRIMER. OBEY THE MATERIAL MANUFACTURER’S
INSTRUCTIONS.
5 Apply Material No. 16-020 Wash Primer to the metal surface.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 16-020 WASH

PRIMER. OBEY THE MATERIAL MANUFACTURER’S
INSTRUCTIONS.
6 Let Material No. 16-020 Wash Primer dry.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 16-001 ANTI

CORROSION PRIMER (POLYURETHANE). OBEY THE MATERIAL
7 Apply Material No. 16-001 Anti Corrosion Primer (Polyurethane).
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 16-001 ANTI

CORROSION PRIMER (POLYURETHANE). OBEY THE MATERIAL
8 Let Material No. 16-001 Anti Corrosion Primer (Polyurethane) dry.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 16-002

POLYURETHANE TOPCOAT GREY (FOR INTERNAL APPLIC.).
9 Apply Material No. 16-002 Polyurethane Topcoat Grey (for Internal Applic.).
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 16-002

POLYURETHANE TOPCOAT GREY (FOR INTERNAL APPLIC.).
10 Let Material No. 16-002 Polyurethane Topcoat Grey (for Internal Applic.) dry.
(b) Repair of Anodized Surfaces

INSTRUCTIONS.
1 Clean the area with Material No. 11-003 Methyl-Ethyl-Ketone.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 13-002 CHEMICAL

CONVERSION COATING YELLOW ALUMINUM. OBEY THE
Page 6004
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
CAUTION : MAKE SURE THAT THE COATING MATERIAL NO. 13-002 -

CHEMICAL CONVERSION COATING YELLOW ALUMINUM DOES
NOT GO INTO GAPS OR BELOW FASTENERS WHERE YOU
CANNOT MAKE IT NEUTRAL. COATING WHICH YOU DO NOT
MAKE NEUTRAL CAUSES NEW CORROSION.
2 Apply Material No. 13-002 Chemical Conversion Coating Yellow Aluminum to
the prepared area and let it work for 3 minutes.
3 Make the area neutral with clean water.
4 Dry the repaired area with warm air up to a maximum temperature of 60 deg. C
(140 deg. F).
(c) Repair of Corrosion Preventive

PREVENTIVE COMPOUND. OBEY THE MATERIAL
1 Apply Material No. 15-004 Corrosion Preventive Compound to the components.
NOTE : Make sure that the existing drain holes are not blocked.
Page 6005
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-300-802-A01
Repair of the Cargo Door Seal
1. General
A. Refer to CHECK for the limits.
11-016 Safety Solvent
08-004 Adhesive Sealant
05-024 Fabric
05-023 Polyterepthalate
abrasive cloth
very fine abrasive cloth
very fine abrasive cloth
abrasive cloth
TABLE 1

wooden bonding block
TABLE 2
C.Referenced Information
FIGURE 52-31-19-991-012-A FIGURE 52-31-19-991-012-A-Door Seal Repair
FIGURE 52-31-19-991-013-A FIGURE 52-31-19-991-013-A-Door Seal Repair
FIGURE 52-31-19-991-014-A FIGURE 52-31-19-991-014-A-Bonding Block
TABLE 3
Page 6006
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
3. Procedure

IRRITANTS.
Subtask 52-31-19-300-002-A01
A. Repair of the Cargo Door Seal
CAUTION : MAKE SURE THAT THE SEAL IS TAGGED ”TO BE SUBJECTED TO A

FUSELAGE PRESSURIZATION CHECK” AFTER THE INSTALLATION OF THE
DOOR.
(1) Remove the cargo door seal 02-100 from the seal retainer.
(2) Repair the chafe marks and cuts with a length less than or equal to 25.4 mm (1.0 in) that
are not in the contact area, see FIGURE 52-31-19-991-012-A as follows:
(a) Drill a stop hole of 2.0 mm (0.08 in) dia. at each end of the cut.
(b) Apply pressure to the seal to open the cut.
(c) Make the face of the cut rough with an abrasive cloth.
(d) Carefully remove the first layer of the reinforced tissue from the door seal on a
distance of 10.0 mm (0.4 in) around the cut.
(e) Prepare the surface of the repair area with a very fine abrasive cloth .
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 11-016 SAFETY

SOLVENT. OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS.
(f) Clean the repair area with Material No. 11-016 Safety Solvent.
(g) Dry the cleaned area with Material No. 19-003 Lint-Free Cotton Cloth .
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 08-004 ADHESIVE

SEALANT. OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS.
Page 6007
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(h) Apply a thin layer of Material No.08-004 Adhesive Sealant to the faces of the cut.
(i) Press the faces of the cut together and let them cure.
(j) Cut a piece of Material No.05-024 Fabric to the size of the repair area.

(k) Apply a thin layer of Material No.08-004 Adhesive Sealant to the repair area and fill
the stop holes.
(l) Install the prepared replacement tissue on the repair area so that it is as smooth as
the seal surface.
(m) Cover the repair area with a layer of Material No.05-023 Polyterepthalate and install
the seal in the wooden bonding block , see FIGURE 52-31-19-991-014-A.
(n) Compress the seal for 24 hours in the wooden bonding block with a clamp.
(o) Remove the bonding block and the special material from the repair area of the seal.
(p) Polish the repair area with very fine abrasive cloth to get a smooth surface of the seal.
(3) Repair the chafe marks and cuts with a length more than 25.4 mm (1.0 in) or in the
contact area by replacement of a section, see FIGURE 52-31-19-991-013-A as follows:
NOTE : The repair area must be at a minimum of 50.0 mm (1.97 in) from the inflation
holes.
(a) Remove the damaged section of the seal.
(b) In straight and curved sections, cut the replacement section of the seal to the same
length as the removed section.
NOTE : Make sure that the quantity of the inflation holes are the same as in the
removed section.
(c) Carefully remove the first layer of the tissue reinforcement from the ends of the seal
and the replacement sections over a length of 25.4 mm (1.0 in).
(d) Make the surfaces of the repair areas rough with an abrasive cloth.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 11-016 SAFETY

SOLVENT. OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS.
(e) Clean the surface with Material No. 11-016 Safety Solvent.
(f) Dry the cleaned area with Material No. 19-003 Lint-Free Cotton Cloth .

(g) Apply a thin coat of the bonding and Material No. 08-004 Adhesive Sealant to the
ends of the seals and the replacement sections.
Page 6008
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(h) Press and hold the ends of the replacement section and the seal together and them
cure.
(i) Cut a piece of Material No. 05-024 Fabric to the size of the repair areas.

(j) Apply a thin layer of Material No. 08-004 Adhesive Sealant to the contact surface of
the replacement tissue and the repair areas.
(k) Install the replacement Material No. 05-024 Fabric on the repair areas.
(l) Cover the repair area with a layer of Material No. 05-023 Polyterepthalate and install
the seal in the wooden bonding block, see FIGURE 52-31-19-991-014-A.
(m) Compress the seal during a period of 24 hours in the wooden bonding block with a
clamp.
(n) Remove the bonding block and Material No.05-023 Polyterepthalate from the repair
area of the seal.
(o) Prepare the repair area with very fine abrasive cloth to get a smooth surface of the
seal.
Page 6009
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A 1
C B
"V"
"X"
B
SECTION
B−B
CONTACT AREA
90
"W"
"X"
REPLACEMENT
"V" = DIA STOP HOLE 2.0mm (0.08 in.) TISSUE
"W" = MAX LENGTH OF CUT 25.4mm (1.0 in.)
"X" = MIN REPAIR AREA AROUND CUT 10mm (0.4 in.)
1 AREA IN WHICH THE FIRST LAYER
OF REINFORCEMENT TISSUE IS REMOVED.
F_CM_523119_1_0120101_01_00
Door Seal Repair

FIGURE-52-31-19-991-012-A01
Page 6010
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
"S"
"T"
"U"
"U"
C
"Y"
A
"Y"
SECTION
C−C
EXISTING REPLACEMENT B
DOOR SEAL SECTION
C REPLACEMENT
SECTION
B
EXISTING
DOOR SEAL LAYER OF TISSUE
REPLACEMENT TISSUE SECTION REPLACEMENT
B−B
"S" = MIN DISTANCE OF 50mm (1.97 in.) 1
FROM INFLATION HOLE
"T" = MIN REPAIR LENGTH OF 200mm (7.87 in.)
"U" = MIN REPAIR LENGTH OF 200mm (7.87 in.)
FOR RADII
"Y" = MIN ABRADED LENGTH OF
REPAIR AREA 25.4mm (1.0 in.)
1 AREA IN WHICH THE FIRST LAYER
OF REINFORCEMENT TISSUE IS REMOVED SEAM
F_CM_523119_1_0130101_01_00
Door Seal Repair

FIGURE-52-31-19-991-013-A01
Page 6011
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
19.4mm
(0.76 in.)
R 1.0mm
(R 0.04 in.)
UPPER
HALF
(0.55 in.)
(0.63 in.)
14.0mm
16.0mm
LOWER
R 1.5mm HALF
(R 0.06 in.)
NOTE: THE BONDING BLOCK CAN BE MANUFACTURED FROM HARDWOOD.

USE THE DIMENSIONS AS DETAILED. LENGTH AS REQUIRED.
F_CM_523119_1_0140101_01_00
Bonding Block
FIGURE-52-31-19-991-014-A01
Page 6012
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-300-803-A01
Replacement of Parts
1. General
A. See CHECK and FITS AND CLEARANCES for the limits.
09-013 Corrosion Inhibiting Brush Consistency
09-016 Corrosion Inhibiting Fillet Consistency
16-021 Flexible Polyurethane
08-029 Adhesive
08-007 Sealant, High Temperature
08-001 General Purpose Adhesive Honeycomb Filler
07-023 Protective Coating, Transparent
05-002 Putty, Zinc Chromate General Purpose
08-050 Adhesive
cloth
TABLE 1

warm air furnace
TABLE 2
C. Referenced Information
TASK 52-31-19-940-808-A01 Special Tool
PMS 01-05-05
PMS 01-05-27
PMS 01-05-04
PMS 01-05-45
Page 6013
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
PMS 01-02-41
TABLE 3
3. Procedure

IRRITANTS.
WARNING : USE HEAT-INSULATED GLOVES WHEN YOU DO WORK WITH HOT PARTS.
HOT PARTS CAN CAUSE INJURY IF YOU TOUCH THEM WITHOUT SUFFICIENT
PROTECTION. IF AN INJURY OCCURS, HOLD IT IN COLD WATER FOR 10
MINUTES AND GET IMMEDIATE MEDICAL AID.
Subtask 52-31-19-300-003-A01
A. Replacement of Parts
(1) Replacement of the Pressed-in Bushes
NOTE : The component parts with the pressed-in bushes are given in TABLE 4.
NOTE : If you find a damaged bush in one hinge assembly, you must replace all bushes in
the hinge assembly. Use the local manufactured special tool (see TASK
52-31-19-940-808-A01) for the replacement of the bushes in the hinge
assemblies.
CAUTION : DO NOT DAMAGE THE EDGES OF THE COMPONENT BORE.

(a) Remove the bush from the component part with an applicable press-tool.

Page 6014
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Remove the grease and clean the component bore with Material No. 11-003 Methyl-
Ethyl-Ketone.
(c) Let the component bore dry.
(d) Visually examine the component bore for damage.
IPL FIG. - ITEM COMPONENT PART REPLACEMENT PART
NAME NAME
- Door Structure Bushing
02-110
08-3108 Roller Lever Shouldered Bushing
08-320
08-460 Universal Joint Latch Bushing
08-470
21-230 Actuator Arm Bushing
21-240 Shouldered Bushing
21-260
21-320 Actuator Arm Bushing
21-340
21-400 Bracket Bushing
21-420
33-020, 34-020 Latching Hook Shouldered Bushing
33-040, 34-040 Shouldered Bushing
33-050, 34-050
33-170, 34-170 Bellcrank Shouldered Bushing
33-230, 34-230
40-080 Cover Beam 4 Shouldered Bushing
40-090
41-140 Lever Shouldered Bushing
41-150 Bushing
41-160
44-020 Spring Sleeve Bushing
44-030
90-040 Outer Hinge Bushing
90-050
90-070 Inner Hinge Bushing
90-090
Page 6015
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

NAME NAME
91-020 Mid Hinge Bushing
91-040
91-060 Outer Hinge Bushing
91-070
Pressed-in Bushes
TABLE 4

INHIBITING BRUSH CONSISTENCY. OBEY THE MATERIAL
(e) Install the new bush, see PMS 01-05-05.
NOTE : You must install the bush with Material No.09-013 Corrosion Inhibiting
Brush Consistency.
(f) Check the installed bush for correct and satisfactory installation.


(g) Carefully remove Material No. 09-013 Corrosion Inhibiting Brush Consistency from the
surfaces of the component part and the bush with a cloth soaked in Material No.
11-003 Methyl-Ethyl-Ketone.

INHIBITING FILLET CONSISTENCY. OBEY THE MATERIAL
(h) Apply Material No. 09-016 Corrosion Inhibiting Fillet Consistency to the joint between
the component bore and the bush.

(i) Let Material No. 09-016 Corrosion Inhibiting Fillet Consistency dry.
Page 6016
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 16-021 FLEXIBLE

POLYURETHANE. OBEY THE MATERIAL MANUFACTURER’S
INSTRUCTIONS.

(j) Apply Material No. 16-021 Flexible Polyurethane to Material No. 09-016 Corrosion
Inhibiting Fillet Consistency.

INSTRUCTIONS.
(k) Let Material No. 16-021 Flexible Polyurethane dry.
(2) Replacement of the Bonded-in Bushes
NOTE : The component parts with the bonded-in bushes are given in the TABLE 5.
NAME NAME
09-030 Stop Shouldered Bushing
09-070
09-100 Handle Flap Shouldered Bushing
09-180
Bonded-in Bushes
TABLE 5
(a) Heat the component part to a maximum temperature of 120 deg. C (248 deg. F) to
soften the bond of the bush.
(b) Press out the bush with a suitable tool.

WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 08-029 ADHESIVE.

CAUTION : DO NOT TOUCH THE BONDING SURFACES. CONTAMINATION CAN

CAUSE AN UNSATISFACTORY BOND.
Page 6017
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(c) Clean the component bore and the new bush with Material No.11-003 Methyl-Ethyl-
Ketone.
NOTE : You must use a nonmetallic scraper to remove the unwanted bonding and
Material No.08-029 Adhesive.
(d) Dry the component bore and the bush with a dry, clean Material No.19-003 Lint-Free
Cotton Cloth .

(e) Install the new bush, see PMS 01-05-27.
NOTE : You must install the bush with the bonding and Material No. 08-029
Adhesive.

INSTRUCTIONS.
(f) Apply Material No. 16-021 Flexible Polyurethane to the gap between the bush and
the component part.
(3) Replacement of the Bonded-in Bearings
NOTE : The component parts with the bonded-in bearings are given in the TABLE 6.
NAME NAME
08-090 Lever Bearing
08-100
08-460 Universal Joint Latch Bearing
08-530
13-110 Bellcrank Bearing
13-120
13-150
13-220
13-250
20-150 Link Lever Bearing
20-160
31-040 Hinged Lever Bearing
31-050
32-080 Hinged Lever Bearing
32-090
Page 6018
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

NAME NAME
40-130 Beam 4 Lever Bearing
40-140
41-230 Serrated Lever Bearing
41-240
41-450 Connecting Rod Bearing
41-460
Bonded-in Bearings
TABLE 6
CAUTION : TAKE CARE NOT TO DAMAGE THE EDGES OF THE BORE.

(a) Remove the bearing from the component with an applicable tool.


CAUTION : HANDLING OF SURFACE AFTER DEGREASING WILL IMPAIR

BONDING.
(b) Clean the component bore with Material No.11-003 Methyl-Ethyl-Ketone.
NOTE : Use a wooden scraper or a plastic scraper to remove the old bonding and
Material No. 08-029 Adhesive.

(c) Clean the outer ring of the new bearing with Material No. 11-003 Methyl-Ethyl-
Ketone.
(d) Dry the parts in a warm air furnace. Alternatively, you can use hot air at a
temperature of 30 to 40 deg. C (86 to 104 deg. F) and a relative humidity of 50 %
for approx. 30 minutes.

(e) Install the bearing in the component, see PMS 01-05-27.
NOTE : You must install the bearing with the bonding and Material No. 08-029
Adhesive.
Page 6019
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

(f) When the bearing is installed, apply a small quantity of the bonding and Material No.
08-029 Adhesive to the gap between the bearing and the component.
(g) Examine the bond and make sure that the bearing is correctly installed.

(h) Remove the unwanted bonding and Material No.08-029 Adhesive from the bearing
and the component with dry, clean Material No. 19-003 Lint-Free Cotton Cloth.
(i) Keep the parts at a room temperature for at least 30 minutes and let the part cure as
it is specified in PMS 01-05-27.
NOTE : Keep the component in such a position that the bond can cure.
(j) Do not put a load on the bonded bearing until it has cured for 24 hours at room
temperature.


(k) Carefully remove the unwanted bonding and Material No. 08-029 Adhesive with clean
Material No. 19-003 Lint-Free Cotton Cloth soaked with Material No. 11-003 Methyl-
Ethyl-Ketone.

(l) Apply Material No. 09-016 Corrosion Inhibiting Fillet Consistency to the joint between
the component bore and the bearing.

(m) Let Material No. 09-016 Corrosion Inhibiting Fillet Consistency dry.

INSTRUCTIONS.
Page 6020
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

(n) Apply Material No. 16-021 Flexible Polyurethane to Material No.09-016 Corrosion

INSTRUCTIONS.
(o) Let Material No. 16-021 Flexible Polyurethane dry.
(4) Replacement of Riveted Parts
(a) Replace the riveted parts, refer to the standard riveting procedure.
(5) Replacement of the Receptacles
NOTE : The component parts with the riveted nuts are given in the TABLE 7.
NAME NAME
- Door Structure Receptacle
03-200
Riveted Nut
TABLE 7
(a) Remove the rivets and the damaged receptacle from the component part.
(b) Install the new receptacle, refer to the standard riveting procedure.
(6) Replacement of Threaded Inserts
NOTE : The component parts with the threaded inserts are given in the TABLE 8.
NAME NAME
- Door Structure Insert
01-130
09-020 Sequence Cam Insert
09-200
Threaded Inserts
TABLE 8
(a) Replace the threaded inserts, see PMS 01-05-04.
Page 6021
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(7) Replacement of the HELI-COIL Threaded Inserts
NOTE : The component parts with the HELI-COIL threaded inserts are given in the
TABLE 9.
NAME NAME
01-030 Door Structure Assembly Insert
01-040
21-230 Actuator Arm Insert
21-300
21-320 Actuator Arm Insert
21-380
HELI-COIL Threaded Inserts
TABLE 9
(a) Carefully remove the fractured inserts.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 05-002 PUTTY, ZINC
CHROMATE GENERAL PURPOSE. OBEY THE MATERIAL
(b) Install the new HELI-COIL threaded inserts, see PMS 01-05-45.
NOTE : Do the replacement with a HELI-COIL tool set.
NOTE : Use Material No. 05-002 Putty, Zinc Chromate General Purpose for the
installation of the HELI-COIL threaded inserts 21-300, 21-380.
(8) Replacement of the Lubrication Fittings
NOTE : The component parts with the lubrication fittings are given in the TABLE 10.
NAME NAME
08-250 Shaft Lubrication Fitting
08-280
33-020, 34-020 Latching Hook Lubrication Fitting
33-030, 34-030
33-170, 34-170 Bellcrank Lubrication Fitting
33-200, 34-200
Lubrication Fittings
TABLE 10
(a) Remove the damaged or worn lubrication fitting from the component.
Page 6022
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

(b) Clean the component bore and remove the grease with Material No.11-003 Methyl-
Ethyl-Ketone.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 08-007 SEALANT, HIGH
TEMPERATURE. OBEY THE MATERIAL MANUFACTURER’S
INSTRUCTIONS.
(c) Apply Material No. 08-007 Sealant, High Temperature to the thread of the lubrication
fitting.
(d) Install the lubrication fitting in the component and tighten.
(9) Replacement of the Bonded-in Insert
NOTE : The component part with the bonded-in insert is given in TABLE 11.
NAME NAME
09-010 Hand Lever Insert
09-090
Bonded-in Insert
TABLE 11
(a) Remove the damaged insert from the component part with an applicable tool.


CAUTION : DO NOT TOUCH THE BONDING SURFACES. CONTAMINATION CAN

CAUSE AN UNSATISFACTORY BOND.
(b) Clean the component bore and the new insert with Material No. 11-003 Methyl-Ethyl-
Ketone.
NOTE : You must use a nonmetallic scraper to remove the remaining bonding and
Material No. 08-050 Adhesive.
(c) Dry the component bore and the bush with dry, clean Material No. 19-003 Lint-Free
Cotton Cloth .

Page 6023
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(d) Install the insert, see PMS 01-05-27.
NOTE : You must install the insert with bonding and Material No. 08-050 Adhesive.

INSTRUCTIONS.
(e) Apply Material No. 16-021 Flexible Polyurethane to the gap between the insert and
the component part.
(10) Replacement of Identification Plates
NOTE : The component part with the bonded identification plate is given in TABLE 12.
NAME NAME
- Forward Cargo Compartment Identification Plate
01-080 Door
Bonded Identification Plate
TABLE 12
(a) Record the data of the old door identification plate.

(b) Write the data of the old identification plate on the new door identification plate.
(c) Remove the damaged or loose identification plate with a nonmetallic scraper.

(d) The Material No.11-003 Methyl-Ethyl-Ketone is dangerous.

(e) Clean the bonding area with Material No.11-003 Methyl-Ethyl-Ketone.
(f) Do not touch the bonding surfaces.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 08-001 GENERAL

PURPOSE ADHESIVE HONEYCOMB FILLER. OBEY THE MATERIAL
(g) Apply Material No.08-001 General Purpose Adhesive Honeycomb Filler to the bonding
surface, refer to the manufacturer’s instruction.
(h) Align and install the identification plate on the bonding surface.
(i) Remove the unwanted bonding material from the edges of the identification plate.
Page 6024
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 07-023 PROTECTIVE

COATING, TRANSPARENT. OBEY THE MATERIAL MANUFACTURER’S
INSTRUCTIONS.
(j) Apply Material No. 07-023 Protective Coating, Transparent to the edges of the
identification plate, see PMS 01-02-41.
Page 6025
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
ASSEMBLY
**For PN’s ALL
TASK 52-31-19-400-801-A01
Installation of the Insulation and the Door Seal
1. General
A. Make sure that you torque all threaded fasteners to the standard values unless the procedure
gives you a different value.
-
NOTE : For the standard torque values, see PMS 01-05-66.

TABLE 1
TASK 52-31-19-300-802-A01 Repair of the Cargo Door Seal
PMS 01-05-66
TABLE 2
3. Procedure

IRRITANTS.
Page 7001
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
Subtask 52-31-19-410-001-A01
A. Installation of the Insulation and the Door Seal

(1) Install the insulation as follows:
NOTE : Before you install the insulation, make sure that Material No.15-005 Corrosion
Preventive Temporary Protective Compound is applied on the inner surfaces of
(a) Install the insulation at the cargo door and connect the insulation with the stud
assemblies 02-020, 02-030.
(2) Install the door seal 02-100 as follows:
WARNING : IF THE DOOR SEAL IS NOT INSTALLED IN THE CORRECT POSITION;

THE CABIN PRESSURE CAN DECREASE. THIS CAN RESULT IN A
DISRUPTION OF THE FLIGHT.
(a) If you have removed the door seal 02-100 during the DISASSEMBLY TASK
52-31-19-000-801-A01 or REPAIR TASK 52-31-19-300-802-A01 procedure, install it
correctly in its retainer on the cargo door structure.
Page 7002
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-802-A01
Assembly and Installation of the Access Cover Assemblies
1. General
A. Install all bolted parts with sealant and apply putty to the shafts of all screws and bolts before
you install them.

Use Material No. 09-013 Corrosion Inhibiting Brush Consistency and Material No. 05-002 Putty,
Zinc Chromate General Purpose.
B. Make sure that you torque all threaded fasteners to the standard values unless the procedure
-

C. Apply protective treatment to the fasteners after they are installed and the final adjustment is
done, see REPAIR.
D. Clean the screws and bolts.

Use Material No. 19-003 Lint-Free Cotton Cloth and Material No. 11-003 Methyl-Ethyl-Ketone.
09-018 Corrosion Inhibitinglow Adhesion Sealant
11-010 Isopropyl Alcohol
adhesive compound (Material No. 08-616)
TABLE 1
Page 7003
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
TASK 52-31-19-000-802-A01 Removal and Disassembly of the Access Cover Assemblies
PMS 01-05-66
PMS 01-02-36
PMS 01-05-47
TABLE 2
3. Procedure

IRRITANTS.
Subtask 52-31-19-410-002-A01
A. Assembly and Installation of the Access Cover Assemblies

(1) Assemble the access cover assembly 03-010 as follows:
(a) If you have removed a damaged sight glass 03-040 during the DISASSEMBLY TASK
52-31-19-000-802-A01 procedure, proceed as follows:

1 Apply Material No. 09-013 Corrosion Inhibiting Brush Consistency at the mating
surfaces of the sheet 03-030 and the sight glass 03-040, see PMS 01-02-36.
Page 7004
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

2 Apply Material No. 09-013 Corrosion Inhibiting Brush Consistency on the shaft
of the screws 03-050, see PMS 01-05-47.
3 Install the screws 03-050, the sight glass 03-040, the sheet 03-030 and the nuts
03-060 on the access cover 03-020.

4 Apply Material No. 09-016 Corrosion Inhibiting Fillet Consistency on the gap
between the sheet 03-030, the sight glass 03-040 and the access cover 03-020.

5 Let Material No. 09-016 Corrosion Inhibiting Fillet Consistency dry.
(2) Install the access cover assembly 03-010 as follows:
(a) Put the access cover assembly 03-010 in position on the cargo door structure and
install the studs 03-070, 03-100 or 03-110 with the washers 03-080 and the tab
washers 03-090.
(3) Put the access cover assembly 03-140 in position on the cargo door structure and install
the washers 03-180 and the screws 03-170, 03-190. Install the screws 03-190 as recorded
during the DISASSEMBLY procedure.
(a) If you have removed the self adhesive sealing 03-160 during the DISASSEMBLY
procedure, do as follows:

ALCOHOL. OBEY THE MATERIAL MANUFACTURER’S
INSTRUCTIONS.
1 Clean the installation surface for the self adhesive sealing 03-160 on the access
cover 03-150 with Material No. 11-010 Isopropyl Alcohol.
2 Cut the sealing 03-160 to the length and remove the protection foil from the
sealing 03-160.
3 Install the sealing 03-160 on the cover 03-150 and glue the ends of the sealing
03-160 together with Material No. adhesive compound (Material No. 08-616).
Page 7005
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(4) Install the access cover 03-120 as follows:

INHIBITINGLOW ADHESION SEALANT. OBEY THE MATERIAL
(a) Apply Material No. 09-018 Corrosion Inhibitinglow Adhesion Sealant on the
installation surface of the access cover 03-120.

(b) Apply Material No. 09-013 Corrosion Inhibiting Brush Consistency on the shaft of the
screws 03-130.
(c) Install the access cover 03-120 on the cargo door with the screws 03-130.
Page 7006
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-803-A01
Installation of the Plugs and the Protective Plugs
1. General
you install them.

-

done, see REPAIR.

TABLE 1
Page 7007
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
PMS 01-05-66
TABLE 2
3. Procedure

IRRITANTS.
Subtask 52-31-19-410-003-A01
A. Installation of the Plugs and the Protective Plugs

(1) Install the plugs 01-090 as follows:
(a) Attach a tag that tells people to install the plugs 01-090 flush with the cargo door
skin after the final installation of the cargo door on the aircraft.
(2) Install the protective plugs 04-020, 04-030 as follows:
(a) Install the protective plugs 04-020, 04-030 in the cargo door.

(b) Apply Material No. 09-016 Corrosion Inhibiting Fillet Consistency to the space
between the plugs 04-020, 04-030 and the cargo door.
Page 7008
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-804-A01
Assembly of the Hand Lever Assembly
1. General
A. Apply grease to all the cleaned component parts that turn or move before you install them. But
do not put grease on the PTFE bushes.
Use grease Material No. 04-004 Synthetic Ester Based Grease High Pressure.
B. Install all bolted parts with sealant and apply putty to the shafts of all screws and bolts before
you install them.

C. Make sure that you torque all threaded fasteners to the standard values unless the procedure
-

D. Apply protective treatment to the fasteners after they are installed and the final adjustment is
done, see REPAIR.
E. Clean the screws and bolts.

Page 7009
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

TABLE 1
PMS 01-05-66
TABLE 2
3. Procedure

IRRITANTS.
Subtask 52-31-19-440-001-A01
A. Assembly of the Hand Lever Assembly

(1) Install the bearing bolt 09-140 and the washers 09-130 at the handle flap 09-100.
(2) Safety the bearing bolt 09-140 with the cotter pins 09-120.
WARNING : YOU MUST INSTALL THE SPRING WITH LOAD.

(3) Install the spring 09-110, the spring sleeve 09-170, the handle flap 09-100, the bearing bolt
09-160 and the washers 09-150 in the hand lever 09-010.
Page 7010
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(4) Safety the bearing bolt 09-160 with the cotter pins 09-120.
(5) Install the sequence cams 09-020 with the bolts 09-190 and the washers 09-150 on the
hand lever 09-010.
(6) Tighten the bolts 09-190.
(7) Apply Material No. 04-004 Synthetic Ester Based Grease High Pressure to the shafts of the
bolts 09-040.
(8) Install the stop 09-030, the rollers 09-080, the bolts 09-040 and the washers 09-060.
(9) Safety the bolts 09-040 with the retaining rings 09-050.
Page 7011
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-805-A01
Installation of the Hand Lever Mechanism
1. General
you install them.

-

done, see REPAIR.

F. Make sure that all drain holes, flanges, hoses and manifolds are clean and free from obstruction.
Page 7012
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
04-017 Silicone Grease
09-018 Corrosion Inhibitinglow Adhesion Sealant
TABLE 1
PMS 01-05-66
TABLE 2
3. Procedure

IRRITANTS.
Subtask 52-31-19-420-001-A01
A. Installation of the Hand Lever Mechanism

(1) Install the catching hook 08-430 as follows:
(a) Install the sheet 08-420 as recorded during the DISASSEMBLY procedure.
(b) Install the catching hook 08-430 with the washers 08-120 and the bolts 08-440 at the
cargo door.
(c) Tighten the bolts 08-440.
Page 7013
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(d) Adjust the catching hook 08-430, see TASK 52-31-19-800-801-A01.

(2) Install the control rods 08-160, 08-540 as follows:
(a) Connect the fork-end of the control rod 08-540 to the latching shaft.
(b) Install the washer 08-210, the bolt 08-200, the washer 08-190 and the nut 08-180 on
the control rod 08-540. Tighten the nut 08-180.
(c) Connect the fork-end of the control rod 08-160 to the locking shaft.
(d) Install the washer 08-210, the bolt 08-200, the washer 08-190 and the nut 08-180 on
the control rod 08-160. Tighten the nut 08-180.
(e) Safety the nuts 08-180 with new cotter pins 08-170.
(3) Assemble the roller lever assembly 08-300 as follows:
(a) Install the roller 08-330 with the bolt 08-370, the washer 08-350 and the nut 08-340
on the roller lever 08-310.
(b) Make sure that the roller 08-330 turns freely.
(c) Safety the nut 08-340 with a new cotter pin 08-360.
(4) Install the shaft 08-290 as follows:
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 04-004 SYNTHETIC

ESTER BASED GREASE HIGH PRESSURE. OBEY THE MATERIAL
(a) Apply Material No. 04-004 Synthetic Ester Based Grease High Pressure to the mating
surfaces of the shaft 08-290 and the bushes 08-320, 08-470.
(b) Install the shaft 08-290 in the door structure as follows:
1 During the installation of the shaft 08-290, install the universal joint assembly
08-450, the roller lever assembly 08-300 and the universal joint lock 08-240 on
the shaft 08-290.
NOTE : Make sure that the attachment holes are aligned.

(c) Install the bolt 08-230, the washer 08-220 and the nut 08-110 on the universal joint
lock 08-240.
(d) Tighten the nut 08-110.
(5) Install the compression spring 08-410 as follows:
WARNING : YOU MUST INSTALL THE COMPRESSION SPRING WITH LOAD.

(a) Install the compression spring 08-410 on the spring bolt 08-400.
(b) Install the spring bolt 08-400 with the compression spring 08-410 at the hole in the
cargo door structure.
(c) Push the spring bolt 08-400 down against the compression spring 08-410.
Page 7014
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(d) Install a locally manufactured bush and a mounting nut (e.g. NAS 509-4) on the
thread of the spring bolt 08-400 to compensate the load of the compression spring
08-410 for easy installation.
(e) Connect the spring bolt 08-400 with the bolt 08-390, the washer 08-120 and the nut
08-110 on the roller lever assembly 08-300.
(f) Tighten the nut 08-110.
(6) Assemble and install the lever assembly 08-020 as follows:
(a) Assemble the lever assembly 08-020 as follows:
1 Put the actuating unit 08-040 in position on the bracket 08-030 and the lever
08-090.
2 Install the washers 08-080, the locating pins 08-050 and the washers 08-070.
3 Safety the locating pins 08-050 with new cotter pins 08-060.
(b) Install the lever assembly 08-020 as follows:

INHIBITINGLOW ADHESION SEALANT. OBEY THE MATERIAL
1 Apply Material No. 09-018 Corrosion Inhibitinglow Adhesion Sealant to the
mating surface of the bracket 08-030.
WARNING : YOU MUST INSTALL THE LEVER ASSEMBLY WITH LOAD.

2 Put the lever 08-090 in position on the shaft 08-290 and the bracket 08-030 on
3 Make sure that the attachment holes in the lever 08-090 and in the shaft 08-290
are aligned.
4 Attach the bracket 08-030 with the washers 08-120, the bolts 08-130, the
washers 08-120 and nuts 08-110 on the cargo door structure.
5 Install the bolt 08-230, the washer 08-220 and the nut 08-110 at the lever
08-090 and the shaft 08-290.
(c) Remove the locally manufactured bush and the mounting nut from the spring bolt
08-400.
(d) Connect the control rod 08-540 with the washer 08-510, the bolt 08-520, the washer
08-500 and the nut 08-490 on the universal joint latch 08-460.
(e) Tighten the nut 08-490 and safety with a new cotter pin 08-480.
(f) Connect the control rod 08-160 with the washer 08-210, the bolt 08-200, the washer
08-190 and the nut 08-180 on the lever 08-090.
(g) Tighten the nut 08-180 and safety with a new cotter pin 08-170.
Page 7015
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(7) Install the hand lever assembly 08-010.
WARNING : BE CAREFUL WHEN YOU USE MATERIAL NO. 04-017 SILICONE

GREASE. OBEY THE MATERIAL MANUFACTURER’S INSTRUCTIONS.
(a) Apply Material No.04-017 Silicone Grease to the hand lever contact surfaces of the
hand lever 08-010, the roller lever assembly 08-300 and the universal joint assembly
08-450.
(b) Install the shaft 08-250, the spacer washers 08-260, 08-270, as recorded during the
disassembly procedure, and the hand lever assembly 08-010 on the cargo door.
(c) Measure and if necessary adjust the clearance ”A” between the hand lever assembly
08-010 and the door structure, see TASK 52-31-19-800-801-A01.
(d) Put the lock washer 08-150 in position on the shaft 08-250.
(e) Install the bolts 08-140 and tighten.
(f) Make sure that the hand lever assembly 08-010 is flush with the cargo door skin.
NOTE : If the hand lever assembly 08-010 is not flush with the cargo door skin, see
TASK 52-31-19-800-801-A01.
Page 7016
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-806-A01
Installation of the Latching Mechanism Assemblies
1. General
you install them.

-

done, see REPAIR.

TASK 52-31-19-800-802-A01 Adjustment of the Latching Mechanism
TASK 52-31-19-800-807-A01 Adjustment of the Proximity Sensors
Page 7017
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
PMS 01-05-66
TABLE 1
3. Procedure

IRRITANTS.
Subtask 52-31-19-420-002-A01
A. Installation of the Latching Mechanism Assemblies

(1) Install the shouldered bushings 30-100, 30-110.
(2) Install the sleeves 30-210, the latching mechanism assemblies 30-020, 30-030, the washers
30-170, the bolts 30-160, the washers 30-170 and the nuts 30-190 at the cargo door.
(3) Safety the nuts 30-190 with new cotter pins 30-180.
(4) Install the washers 30-140, the bolts 30-130, the washers 30-140 and the nuts 30-150.
(5) Install the sleeves 30-120, the washers 30-090, the bolts 30-080, the washers 30-070 and
the nuts 30-060.
(7) Install the bushes 30-250, 30-260, the washers 30-240, the bolts 30-230, 30-290, the
washers 30-240 and the nuts 30-280.
(9) Make sure that the upper dead center of the latching mechanism is correctly adjusted, see
TASK 52-31-19-800-802-A01.
Page 7018
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(10) Make sure that the proximity switch 5MJ is correctly adjusted, see TASK
52-31-19-800-807-A01.
(11) Make sure that the lower dead center of each latching mechanism is correctly adjusted, see
TASK 52-31-19-800-802-A01.
Page 7019
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-807-A01
Assembly of the Latching Hook Assemblies
1. General
you install them.

-

done, see REPAIR.

Page 7020
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

PMS 01-05-66
TABLE 1
3. Procedure

IRRITANTS.
Subtask 52-31-19-440-002-A01
A. Assembly of the Latching Hook Assemblies

(1) Assemble the bellcrank assemblies 33-160 or 34-160 and the connecting link 33-070 or
34-070 as follows:
(a) Put the sleeves 33-060 or 34-060 in position on the bellcrank assemblies 33-160 or
34-160.
(b) Put the bushes 33-100, 33-110 or 34-100, 34-110 in position on the upper fork-end of
the connecting link 33-070 or 34-070.
(c) Put the bellcrank assemblies 33-160 or 34-160 in position on the connecting link
33-070 or 34-070.
(d) Install the washers 33-090 or 34-090, the bolts 33-150 or 34-150, the washers 33-130
or 34-130 and the nuts33-120 or 34-120.
(e) Safety the nuts 33-120 or 34-120 with new cotter pins 33-140 or 34-140.
Page 7021
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(2) Connect the connecting rod 33-260 or 34-260 as follows:

(a) Install the bush 33-230 or 34-230 on the bellcrank assemblies 33-160 or 34-160.
(b) Install the bush 33-240 or 34-240 and move the eye-end of the connecting rods
33-260 or 34-260 on the fork-end of the bellcrank assemblies 33-160 or 34-160.
(c) Install the washers 33-220 or 34-220, the bolts 33-210 or 34-210, the washers 33-220
or 34-220 and the nuts 33-250 or 34-250.
(d) Tighten the nuts 33-250 or 34-250.
(e) Safety the nuts 33-250 or 34-250 with new cotter pins 33-140 or 34-140.
(3) Install the latching hook assemblies 33-010 or 34-010.
(a) Install the sleeves 33-060 or 34-060 at the latching hook assemblies 33-010 or 34-010.
(b) Install the bushes 33-100, 33-110 or 34-100, 34-110 on the fork-end of the connecting
link 33-070 or 34-070.
(c) Install the latching hook assemblies 33-010 or 34-010, the washers 33-090 or 34-090,
the bolts 33-080 or 34-080, the washers 33-130 or 34-130 and the nuts 33-120 or
34-120.
(d) Safety the nuts 33-120 or 34-120 with new cotter pins 33-140 or 34-140.
Page 7022
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-808-A01
Assembly and Installation of the Latching Shaft Assembly
1. General
you install them.

-

done, see REPAIR.

PMS 01-05-66
TABLE 1
Page 7023
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
3. Procedure

IRRITANTS.
Subtask 52-31-19-400-001-A01
A. Assembly and Installation of the Latching Shaft Assembly

(1) Put the switch lever 32-060, the hinged lever assembly 32-070, the stop cam 32-050 and
the shaft levers 32-030, 32-040 in position and install the latching shaft 32-020. Install the
shaft levers 32-030, 32-040 as recorded during the disassembly procedure.
(2) Install the taper pins 32-100, 32-110, the sleeves 32-120 and the nuts 32-130.
(3) Connect the latching mechanism (see TASK 52-31-19-400-806-A01) and the hand lever
mechanism (see TASK 52-31-19-400-805-A01) on the latching shaft assembly 32-010.
Page 7024
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-809-A01
Assembly and Installation of the Interlock Mechanism
1. General
you install them.

-

done, see REPAIR.

TASK 52-31-19-800-805-A01 Adjustment of the Interlock Mechanism
Page 7025
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
PMS 01-05-66
TABLE 1
3. Procedure

IRRITANTS.
Subtask 52-31-19-400-002-A01
A. Assembly and Installation of the Interlock Mechanism

(1) Assemble the interlock mechanism 44-090 as follows:
(a) Install the roller 44-140 and the pin 44-130 on the lever 44-100.
(b) Safety the pin 44-130 with the retaining ring 44-120.
(c) Install the adjusting screw 44-180 with the nut 44-190 and the lock plate 44-200 on
the lever 44-170. Do not safety the nut 44-190 with the lock plate 44-200 at this
time. Attach a tag that tells people that the nut 44-190 must be safetied with the
lock plate 44-200 during the final adjustment of the cargo door on the aircraft.
(d) Install the levers 44-100, 44-170 with the pins 44-110 on the connecting rod 44-150.
(e) Safety the pins 44-110 with the retaining rings 44-160.
(f) Install the bolt 44-210 with the pin 44-110 on the lever 44-170.
(g) Safety the pin 44-110 with the retaining ring 44-160.
(2) Install the interlock mechanism 44-090 as follows:
(a) Install the pin 44-050 and the washer 44-070.
Page 7026
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Safety the pin 44-050 with a new cotter pin 44-060.
(c) Install the bushing 44-270 and the interlock mechanism 44-090 on the cargo door
structure as follows:
1 Install the washer 44-300, the bolt 44-260, the washer 44-300 and the nut
44-290.
2 Safety the nut 44-290 with a new cotter pin 44-280.
(d) Install the bushing 44-230 on the interlock mechanism 44-090 as follows:
44-240.
2 Safety the nut 44-240 with a new cotter pin 44-060.
(e) Install the spring sleeve assembly 44-010 with the compression spring 44-040 on the
bolt 44-210.
WARNING : YOU MUST INSTALL THE COMPRESSION SPRING WITH LOAD.

(f) Compress the compression spring 44-040 and the spring sleeve assembly 44-010 to
decrease its length.
(g) Install the pin 44-050 and the spacers 44-080 on the spring sleeve assembly 44-010
and on the cargo door structure.
(h) Install the washer 44-070 and safety the pin 44-050 with a new cotter pin 44-060.
(3) Adjust the interlock mechanism 44-090, see TASK 52-31-19-800-805-A01.
Page 7027
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-810-A01
Installation of the Locking Shaft Assembly
1. General
you install them.

-

done, see REPAIR.

TASK 52-31-19-800-803-A01 Adjustment of the Locking Mechanism
TASK 52-31-19-400-814-A01 Installation of the Vent Door Assembly Mechanism
TASK 52-31-19-400-813-A01 Assembly and Installation of the Drift Pin Rods
PMS 01-05-66
TABLE 1
Page 7028
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
3. Procedure

IRRITANTS.
Subtask 52-31-19-420-003-A01
A. Installation of the Locking Shaft Assembly

(1) Put the hinged lever assembly 31-030 and the locking cams 31-070 in position as recorded
during the disassembly procedure.
(2) Put the lever 31-060 in position and install the locking shaft 31-010.
(3) Install the rivet pins 31-120, the taper pins 31-080, the sleeves 31-110, the washers 31-100
and the nuts 31-090.
(4) Connect the locking shaft assembly 31-010 to the assemblies that follow:
- the hand lever mechanism, see TASK 52-31-19-400-805-A01,
- the vent door mechanism, see TASK 52-31-19-400-814-A01,
- and the drift pin mechanism, see TASK 52-31-19-400-813-A01.
(5) Adjust the locking shaft assembly, see TASK 52-31-19-800-803-A01.
Page 7029
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-811-A01
Assembly and Installation of the Sequence Shaft Assembly
1. General
you install them.

-

done, see REPAIR.

Page 7030
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

TABLE 1
PMS 01-05-66
TABLE 2
3. Procedure

IRRITANTS.
Subtask 52-31-19-400-003-A01
A. Assembly and Installation of the Sequence Shaft Assembly

(1) Install the sequence shaft assembly 41-200 as follows:
(a) Put the locking cam 41-250 in position.
(b) Install the sequence shaft 41-210 at the cargo door structure and the locking cam
41-250 as recorded during the disassembly procedure.
(c) Install the rivet pins 41-280, the washers 41-290 and the nuts 41-300.
Page 7031
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(d) Tighten the nuts 41-300.

(e) Install the serrated lever assembly 41-220 and the link lever 41-260 on the sequence
shaft 41-210. Install the serrated lever assembly 41-220 and the link lever 41-260 as
recorded during the disassembly procedure.
(f) Install the rivet pin 41-310, the washer 41-290 and the nut 41-300.
(g) Tighten the nut 41-300.
(h) Install the serrated lever 41-360 on the sequence shaft 41-210. Install the serrated
lever 41-360 as recorded during the disassembly procedure.
NOTE : Make sure that the center punches on the serrated lever 41-360 and on the
sequence shaft 41-210 align.
(i) Install a new lockwasher 41-430 and the screw 41-420.
(j) Tighten the screw 41-420 and safety with a new lockwasher 41-430.
(2) Install the lever assembly 41-130 as follows:

(a) Apply Material No. 04-004 Synthetic Ester Based Grease High Pressure to the inner
diameter of the bushes 41-150.
(b) Install the lever assembly 41-130 on the support fitting 41-170.
(c) Install the washer 41-390 and the nut 41-380 on the support fitting 41-170.
(d) Tighten the nut 41-380 and safety with a new cotter pin 41-370.
(3) Assemble and install the link assembly 41-010 as follows:
(a) Assemble the link assembly 41-010 as follows:
1 Install the tab washers 41-040 and the nuts 41-030, 41-050 on the rod 41-120.
2 Install the forks 41-020, 41-060 on the rod 41-120.
NOTE : Make sure that you can see the thread of the rod 41-120 through the
inspection hole of the forks 41-020, 41-060.
3 Adjust the link assembly 41-010 to the length recorded during the disassembly
procedure.
NOTE : Attach a tag which tells persons to safety the nuts 41-030, 41-050
with the tab washers 41-040 after the final adjustment of the cargo
door.
Page 7032
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Install the link assembly 41-010 as follows:

1 Apply Material No. 04-004 Synthetic Ester Based Grease High Pressure to the
sleeves 41-070, 41-330 and the bushes 41-160, 41-270.
2 Install the link assembly 41-010, the bolts 41-080, 41-320, the washers 41-090,
41-290 and the nuts 41-100, 41-340.
3 Tighten the nuts 41-100, 41-340 and safety with new cotter pins 41-110, 41-350.
(4) Install the connecting rod assembly 41-440 as follows:
(a) Put the connecting rod assembly 41-440 in position on the serrated lever 41-360 and
the lever 31-060.
(b) Install the washers 41-400, the bolts 41-410), the washers 41-390 and the nuts
41-380.
(c) Tighten the nuts 41-380 and safety with new cotter pins 41-370.
Page 7033
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-812-A01
Assembly and Installation of the Cover Beam 4
1. General
you install them.

-

done, see REPAIR.

Page 7034
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

TABLE 1
PMS 01-05-66
TABLE 2
3. Procedure

IRRITANTS.
Subtask 52-31-19-400-004-A01
A. Assembly and Installation of the Cover Beam 4

(1) Pre-assemble the cover assembly 40-070 on the bench as follows:

(a) Apply Material No. 04-004 Synthetic Ester Based Grease High Pressure to the sliding
surfaces of the beam-4 shaft 40-100 and the bushes 40-090.
Page 7035
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Assemble the cover assembly 40-070 as follows:

1 Put the beam-4 levers 40-120 and the spacer sleeve 40-110 in position and
install the beam-4 shaft 40-100 on the cover 40-080.
2 Install the taper pins 40-210, the sleeves 40-230 and the nuts 40-220.
3 Put the fixed rod 40-150 in position and install with the washer 40-200, the bolt
40-190, the washer 40-180 and the nut 40-170.
4 Safety the nut 40-170 with the cotter pin 40-160.
(2) Install the cover assembly 40-070 at beam 4 as follows:
(a) Put the pre-assembled cover assembly 40-070 in position on the cargo door structure.
(b) Install the washers 40-250 and the bolts 40-240.
(c) Connect the fixed rod 40-150 to the serrated lever assembly 41-220 with the washer
40-030, the bolt 40-020, the washer 40-040 and the nut 40-050.
(d) Tighten the nut 40-050 and safety with the cotter pin 40-060.
Page 7036
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-813-A01
Assembly and Installation of the Drift Pin Rods
1. General
you install them.

-

done, see REPAIR.

Page 7037
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

PMS 01-05-66
TABLE 1
3. Procedure

IRRITANTS.
Subtask 52-31-19-400-005-A01
A. Assembly and Installation of the Drift Pin Rods

(1) Do a pre-assembly on the bench as follows:
(a) Pre-assemble the adjustable rod 13-180 and the bellcrank assemblies 13-090 and
13-190 on the bench as follows:
1 Connect the adjustable rod 13-180 on the bellcrank assemblies 13-090 and
13-190.
2 Install the washers 13-320, the bolts 13-310, the washers 13-340 and the nuts
13-350.
3 Tighten the nuts 13-350 and safety with new cotter pins 13-360.
(b) Pre-assemble the rod 13-270 and the link lever assembly 13-230 on the bench as
follows:
1 Connect the rod 13-270 on the link lever assembly 13-230.
Page 7038
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
2 Install the washers 13-330, 13-320, the bolt 13-310, the washer 13-340 and the
nut 13-350.
3 Tighten the nut 13-350 and safety with a new cotter pin 13-360.
(c) Pre-assemble the fixed rod 40-010 with the link lever 13-130 as follows:
1 Connect the fixed rod 40-010 with the link lever 13-130.
40-050.
(d) Pre-assemble the fixed rod 20-180 with the bellcrank assembly 20-130 as follows:
1 Connect the fixed rod 20-180 with the bellcrank assembly 20-130.
20-100.
(2) Install the fixed rod 13-080, the rod 13-270 with the assembled link lever assembly 13-230
and the drift pins 13-010 as follows:
(a) Install the drift pins 13-010 in the cargo door structure.
NOTE : Make sure that the flattened side of the drift pin 13-010 points to the outer
side of the cargo door.
(b) Put the fixed rod 13-080, the rod 13-270 with the assembled link lever assembly
13-230 and with the bushes 13-040 and the washers 13-030 in position at the drift pin
13-010.
(c) Install the bolts 13-020, the washers 13-060 and the nuts 13-050.
(d) Tighten the nuts 13-050 and safety with new cotter pins 13-070.
(3) Install the rod 13-180 with the assembled bellcrank assemblies 13-090 and 13-190 as
follows:
(a) Put the rod 13-180 with the assembled bellcrank assemblies 13-090 and 13-190 and
the link lever assembly 13-230 in position and install the beam-3 shafts 13-160,
13-260 on the cargo door structure.
(b) Install the taper pins 13-280, the sleeves 13-290 and the nuts 13-300.
(c) Connect the bellcrank assy 13-090 to the fixed rod 13-080 with the washer 13-330,
13-320, the bolt 13-310, the washer 13-340 and the nut 13-350.
(d) Tighten the nut 13-350 and safety with a new cotter pin 13-360.
(4) Install the fixed rod 40-010 as follows:
(a) Put the fixed rod 40-010 with the assembled link lever 13-130 in position.
(b) At beam 3, install the taper pin 13-280, the sleeve 13-290 and the nut 13-300.
Page 7039
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(c) At beam 4, install the washer 40-030, the bolt 40-020, the washer 40-040 and the nut
40-050.
(d) Safety the nut 40-050 with a new cotter pin 40-060.
(5) Install the pre-assembled rod 20-180 as follows:
(a) Install the rod 20-180 on the link lever assembly 13-230.
(b) Install the washer 20-230, the bolt 20-220, the washer 20-080 and the nut 20-100.
(c) Tighten the nut 20-100 and safety with a new cotter pin 20-090.
Page 7040
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-814-A01
Installation of the Vent Door Assembly Mechanism
1. General
you install them.

-

done, see REPAIR.

Page 7041
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

PMS 01-05-66
TABLE 1
3. Procedure

IRRITANTS.
Subtask 52-31-19-410-004-A01
A. Installation of the Vent Door Assembly Mechanism

(1) Do a pre-assembly on the bench as follows:
(a) Pre-assemble the adjustable rod 20-120 and the link lever assembly 20-140 on the
bench as follows:
1 Connect the adjustable rod 20-120 on the link lever assembly 20-140.
20-100.
(2) Install the adjustable rod 20-120 and the fixed rod 20-180 as follows:
(a) Put the link lever assemblies 20-140 in position and install the beam 3 shaft 20-170.
(b) Install the taper pins 20-190, the sleeves 20-200 and the nuts 20-210.
Page 7042
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(3) Install the rod 20-120 on the vent door 20-060 as follows:
(a) Install the bushing 20-110, the rod 20-120, the washers 20-080, the bolt 20-070, the
washer 20-080 and the nut 20-100.
(b) Tighten the nut 20-100 and safety with a new cotter pin 20-090.
(4) Install the cover 20-010 as follows:
(a) Install the cover 20-010, the spacers 20-050, the screws 20-040, the washers 20-030
and the nuts 20-020.
(b) Tighten the nuts 20-020.
Page 7043
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-815-A01
Assembly and Installation of the Vent Door Assembly
1. General
you install them.

-

done, see REPAIR.

09-005 Corrosion Inhibitive Interfay Sealant
Page 7044
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
TABLE 1
PMS 01-05-66
TABLE 2
3. Procedure

IRRITANTS.
Subtask 52-31-19-400-006-A01
A. Assembly and Installation of the Vent Door Assembly

(1) Install the actuator arm assembly 21-310 as follows:
(a) Install the screws 21-120, the actuator arm assembly 21-310, the washers 21-130 and
the nuts 21-140.

INHIBITIVE INTERFAY SEALANT. OBEY THE MATERIAL
Page 7045
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(c) Apply Material No. 09-005 Corrosion Inhibitive Interfay Sealant to the nuts 21-140.
(2) Install the bracket assembly 21-390 as follows:
(a) Install the screws 21-150, the bracket assembly 21-390, the washers 21-130 and the
nuts 21-140.

(3) Install the actuator arm assembly 21-220 as follows:
(a) Install the screws 21-150, the actuator arm assembly 21-220, the washers 21-130 and
the nuts 21-140.

(4) Install the spring bolts 21-160 as follows:
(a) Install the spring bolts 21-160 and the washers 21-130.
(b) Safety the spring bolts 21-160 with new cotter pins 21-170.
(5) Install the bolts 21-270, 21-350 as follows:
(a) Install the nuts 21-290, 21-370 on the bolts 21-270, 21-350.
(b) Install the bolts 21-270, 21-350 with the nuts 21-290, 21-370 and the tab washers
21-280, 21-360 on the actuator arm assemblies 21-220, 21-310. Attach a tag which
tells persons that the nuts 21-290, 21-370 must be safetied with the tab washers
21-280, 21-360 after the final adjustment of the vent door assembly 21-110.
(6) Install the vent door 21-210 as follows:.

(a) Apply Material No. 04-004 Synthetic Ester Based Grease High Pressure to the mating
surfaces of the sleeves 21-070, 21-100, the bushings 21-240, 21-250, 21-330 and the
shafts of the bolts 21-080.
WARNING : YOU MUST INSTALL THE SPRINGS WITH LOAD.
Page 7046
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Put the vent door assembly 21-110 with the washers 21-030, the springs 21-060,
21-090, the sleeves 21-070, 21-100 and the bolts 21-080 in position on the cargo door
structure.
(c) Install the washers 21-030, 21-040, 21-050 and the nuts 21-020.
(d) Tighten the nuts 21-020 and safety with new cotter pins 21-010.
(e) Install the adjustable rod 20-120 at the vent door mechanism, see TASK
52-31-19-400-814-A01.
Page 7047
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-816-A01
Installation of the Door Proximity Sensors
1. General
you install them.

-

done, see REPAIR.

TASK 52-31-19-800-807-A01 Adjustment of the Proximity Sensors
PMS 01-05-66
TABLE 1
Page 7048
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
3. Procedure

IRRITANTS.
Subtask 52-31-19-410-005-A01
A. Installation of the Door Proximity Sensors
NOTE : See IPL_FIGURE_09, IPL_FIGURE_32, IPL_FIGURE_41 and IPL_FIGURE_62.

(1) Install the targets 62-020 as follows:
(a) Install the targets 62-020, the screws 62-030, 62-040, the washers 62-050 and the
nuts 62-060 on the items that follow:
1 the lever assembly 41-130 of the sequence shaft assembly.
2 the hand lever 09-010.
3 the switch lever 32-060 of the latching shaft assembly.
(2) Install the proximity sensor 5MJ 62-010 as follows:
(a) Remove the blanking caps from the electrical connectors.
(b) Install the proximity sensor 5MJ 62-010 and the screws 62-040 on the cargo door
structure.
(c) Adjust the proximity sensor 5MJ 62-010, see TASK 52-31-19-800-807-A01.
(3) Install the proximity sensor 28WV 62-010 as follows:
(a) Remove the blanking caps from the electrical connectors.
(b) Install the proximity sensor 28WV 62-010, the screws 62-040, the washers 62-050 and
the nuts 62-060 on the cargo door structure.
(c) Adjust the proximity sensor 28WV 62-010, see TASK 52-31-19-800-807-A01.
Page 7049
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-817-A01
Installation of the Cargo Door Drainage
1. General
you install them.

-

done, see REPAIR.

E. Make sure that all drain holes, flanges, hoses and manifolds are clean and free from obstruction.
09-005 Corrosion Inhibitive Interfay Sealant
TABLE 1
Page 7050
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
PMS 01-05-66
TABLE 2
3. Procedure

IRRITANTS.
Subtask 52-31-19-410-006-A01
A. Installation of the Cargo Door Drainage

(1) Install the tube 50-080 as follows:

(a) Apply Material No. 09-005 Corrosion Inhibitive Interfay Sealant to the mating surfaces
of the retainer 50-020 and the flange 50-070.
(b) Install the retainer 50-020, the basic valve 50-030 and the tube 50-080 with the flange
50-070.
(c) Install the washers 50-050, the screws 50-040 and the nuts 50-060.
(2) Install the hose 50-010 as follows:
(a) Install the mount 50-100 with the washer 50-120, the bolt 50-110, the washer 50-120
and the nut 50-130 on the cargo door structure.
Page 7051
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(b) Move the lower end of the hose 50-010 through the holes in the cargo door structure.
(c) Install the hose 50-010 on the tube 50-080.
(d) Fasten the hose 50-010 on the tube 50-080 and on the mount 50-100 with the cable
ties 50-090.
NOTE : Make sure that the cable ties 50-090 do not compress the diameter of the
hose 50-010.
Page 7052
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-400-818-A01
Installation of the Hinge Assemblies
1. General
you install them.

-

done, see REPAIR.

16-021 Flexible Polyurethane
TABLE 1
Page 7053
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
PMS 01-05-66
TABLE 2
3. Procedure

IRRITANTS.
Subtask 52-31-19-410-007-A01
A. Installation of the Hinge Assemblies

(1) Install the end fittings 90-010, 91-090 as follows:

(a) Apply Material No. 09-013 Corrosion Inhibiting Brush Consistency to the mating
surfaces of the shims 90-020, 91-080.
(b) Install the shims 90-020, 91-080, the fittings 90-010, 91-090, the screws 90-100,
91-100, 90-130, 91-130, the washers 90-110, 91-110, 90-140, 91-140 and the nuts
90-120, 91-120.
NOTE : Make sure that the shims 90-020, 91-080 have the same thickness as
recorded during the disassembly procedure.
Page 7054
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

(c) Apply Material No. 09-016 Corrosion Inhibiting Fillet Consistency to the space
between the door structure, the hinge assemblies 90-030, 91-050 and the fittings
90-010, 91-090.

(d) Let Material No. 09-016 Corrosion Inhibiting Fillet Consistency dry.

INSTRUCTIONS.

(e) Apply Material No. 16-021 Flexible Polyurethane to Material No. 09-016 Corrosion

INSTRUCTIONS.
(f) Let Material No. 16-021 Flexible Polyurethane dry.
(2) Install the hinge assemblies 90-030, 90-060, 91-010, 91-050.
NOTE : For the replacement of the hinge assemblies 90-030, 90-060, 91-010, 91-050, see
REPAIR TASK 52-31-19-300-803-A01.
Page 7055
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-800-801-A01
Adjustment of the Hand Lever Assembly
1. General
-

PMS 01-05-66
FIGURE 52-31-19-991-016-A FIGURE 52-31-19-991-016-A-Adjustment of the Hand Lever Assembly
FIGURE 52-31-19-991-015-A FIGURE 52-31-19-991-015-A-Adjustment of the Hand Lever Assembly
TABLE 1
3. Job Setup
Subtask 52-31-19-820-008-A01
(1) Make sure that the hand lever assembly is installed, see ASSEMBLY TASK
52-31-19-400-804-A01.
(2) Make sure that the hand lever mechanism is installed, see ASSEMBLY TASK
52-31-19-400-805-A01.
4. Procedure
Subtask 52-31-19-820-001-A01
A. Adjustment of the Hand Lever Assembly
NOTE : See IPL_FIGURE_08 , IPL_FIGURE_09.

(1) Set the hand lever assembly 08-010 to the LOCKED position.
Page 7056
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(2) Adjust the clearance ”A” as follows, see FIGURE 52-31-19-991-016-A:

(a) Measure the clearances ”A” between the hand lever assembly 08-010 and the door
structure.
(b) The clearances ”A” must have the same dimensions and must be between 1.0 and 3.0
mm (0.0393 and 0.1181 in).
(c) If the clearances ”A” are not in the limits, change the position and/or the quantity of
the spacer washers 08-260, 08-270 until the adjustment is correct.
(3) Adjust the handle offset between the hand lever assembly 08-010 and the installed access
cover assembly 03-010 as follows:
(a) Measure the handle offset at the given measuring points, see FIGURE
52-31-19-991-015-A.
(b) If the handle offset is not in the limits, loosen the nut 08-110, see FIGURE
52-31-19-991-016-A.
(c) Adjust the handle offset with the bolt 08-380.
(d) Tighten the nut 08-110.
(4) Adjust the catching hook 08-430 as follows:
(a) Make sure that the bearing bolt 09-160 does not touch the catching hook 08-430, see
FIGURE 52-31-19-991-016-A.
(b) Make sure that the handle offset between the hand lever assembly 08-010 and the
cargo door skin is as given on FIGURE 52-31-19-991-015-A.
(c) If the handle offset is not correct, remove the bolts 08-440, the washers 08-120, the
catching hook 08-430 and the shim 08-420.
(d) Do the adjustment with the shim 08-420.
(e) Install the shim 08-420, the catching hook 08-430, the washers 08-120 and the bolts
08-440.
(f) Tighten the bolts 08-440.
Page 7057
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A MEASURING
POINT "1"
MEASURING MEASURING
POINT "6" POINT "2"
A
MEASURING MEASURING
POINT "5" POINT "3"
MEASURING
POINT "4"
MEASURING
HANDLE OFFSET
POINT
"1" +0.8 TO −1.0mm (+0.0315 TO −0.0394 in.)
"2" +0.2 TO −1.0mm (+0.0079 TO −0.0394 in.)
"3" 0.0 TO −1.0mm
(0.0000 TO −0.0394 in.)
"4" 0.0 TO −1.0mm
(0.0000 TO −0.0394 in.)
"5" 0.0 TO −1.0mm
(0.0000 TO −0.0394 in.)
"6" +0.2 TO −1.0mm (+0.0079 TO −0.0394 in.)
F_CM_523119_1_0150101_01_00

FIGURE-52-31-19-991-015-A01
Page 7058
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
CARGO DOOR SKIN

B C
ADJUSTMENT OF
HANDLE LEVER ASSY CLEARANCE "A"
(8−10)
C "A"= 1.0 TO 3.0mm
(0.0393 TO 0.1181 in.)
SPACER WASHER
"A"= 1.0 TO 3.0mm (8−260, 270)
(0.0393 TO 0.1181 in.)
E
ADJUSTMENT OF
HANDLE OFFSET
FOR THE MEASURE
POINTS 3, 4 AND 5
HANDLE
D OFFSET
HANDLE LEVER ASSY

(8−10)
BEARING
BOLT
(9−160)
SHIM
(8−420) D
CATCHING
HOOK ADJUSTMENT OF
WASHER (8−430) HANDLE OFFSET
(8−120) FOR THE MEASURE
BOLT POINTS 1, 2 AND 6
(8−440)
HANDLE LEVER ASSY

(8−10)
HANDLE LEVER ASSY BEAM4

(8−10)
HANDLE
OFFSET NUT
(8−110)
ACCESS BOLT
COVER (8−380)
F_CM_523119_1_0160101_01_01

FIGURE-52-31-19-991-016-A01
Page 7059
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-800-802-A01
Adjustment of the Latching Mechanism
1. General
-

lockwire
TABLE 1

98D52307525200 Rigging Pin
98D52307525000 Adjustment Tool - Cargo Doors
TABLE 2
TASK 52-31-19-400-807-A01 Assembly of the Latching Hook Assemblies
PMS 01-05-66
FIGURE 52-31-19-991-017-A FIGURE 52-31-19-991-017-A-Adjustment of the Latching Mechanism
TABLE 3
Page 7060
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
3. Job Setup
Subtask 52-31-19-820-009-A01
(1) Make sure that the latching mechanism assemblies are installed, see ASSEMBLY TASK
52-31-19-400-806-A01.
(2) Make sure that the latching hook assemblies are installed, see ASSEMBLY TASK
52-31-19-400-807-A01.
(3) Make sure that the latching shaft assembly is installed, see ASSEMBLY TASK
52-31-19-400-808-A01.
4. Procedure
Subtask 52-31-19-820-002-A01
A. Adjustment of the Latching Mechanism
WARNING : USE GOGGLES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME
YOU CUT LOCKWIRE DURING THE TASK, REMOVE AND DISCARD IT (THE
UNWANTED LOCKWIRE) IMMEDIATELY. LOOSE LOCKWIRE CAN CUT
YOU OR MAKE YOU BLIND.
NOTE : See IPL_FIGURE_08, IPL_FIGURE_30, IPL_FIGURE_33 and IPL_FIGURE_34.

(1) Set the latching mechanism assemblies 30-020, 30-030 to the LOCKED position.
(2) Make sure that the hand lever assembly 08-010 is flush with the door structure during the
adjustment procedure, see ASSEMBLY TASK 52-31-19-800-801-A01.
(3) Install the 98D52307525200 Rigging Pin (1) of the 98D52307525000 Adjustment Tool -
Cargo Doors through the rigging holes of the cargo door structure and in the bolt 30-230,
see FIGURE 52-31-19-991-017-A.
(4) If you cannot install the 98D52307525200 Rigging Pin (1) of the 98D52307525000
Adjustment Tool - Cargo Doors easily in the bolt 30-230, adjust the length of the control
rod 08-540 as follows:
(a) If necessary, cut and remove the lockwire from the safety devices.
(b) Loosen the two jam nuts.
(c) Turn the turnbuckle until you can install the 98D52307525200 Rigging Pin (1), of the
98D52307525000 Adjustment Tool - Cargo Doors, easily in the bolt 30-230.
(d) Tighten the jam nuts and safety them with lockwire on the safety devices.
(5) Adjust the length of the four connecting rods 33-260, 34-260 as follows to make sure that
the lower over-centering is correct, see FIGURE 52-31-19-991-017-A:
(a) If necessary, cut and remove the lockwire from the safety devices.
Page 7061
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

(c) Turn the turnbuckle until the back section of the bellcrank assembly 33-160 touches
the bolt 30-130.
(d) Turn the turnbuckle 10 deg. back until you can move the rod easily.
(e) Make sure that you can install the 98D52307523100 Rigging Pin (2) of the
98D52307525000 Adjustment Tool - Cargo Doors through the cargo door structure
and in the bolt 33-150.
(f) If you cannot, turn the turnbuckle until you can install the 98D52307523100 Rigging
Pin (2) of the 98D52307525000 Adjustment Tool - Cargo Doors easily.
(g) Tighten the jam nuts and safety them with lockwire at the safety devices.
(h) Make sure that you can turn the connecting rods 33-260, 34-260.
(i) Remove the 98D52307525200 Rigging Pin and 98D52307523100 Rigging Pin (1, 2) of
the 98D52307525000 Adjustment Tool - Cargo Doors.
Page 7062
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A
EXAMPLE
LATCHING UNIT
JAM NUT
SAFETY
DEVICE
CONTROL ROD
TURNBUCKLE (8−540)
SAFETY
DEVICE
JAM NUT
LATCHING SHAFT
BOLT
(30−230, 290)
1 RIGGING PIN (1) JAM NUT
SAFETY DEVICE
TURNBUCKLE CONNECTION ROD
(33, 34−260)
JAM NUT
SAFETY DEVICE
BOLT
(30−130) BELLCRANK ASSY
(33, 34−160)
LOCKING SHAFT
BOLT
(33, 34−150)
RIGGING PIN (2)
1 THE RIGGING PIN (1)

IS ON FWD DOOR AT FR26A
F_CM_523119_1_0170101_01_00
Adjustment of the Latching Mechanism

FIGURE-52-31-19-991-017-A01
Page 7063
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-800-803-A01
Adjustment of the Locking Mechanism
1. General
-

lockwire
TABLE 1
TASK 52-31-19-400-810-A01 Installation of the Locking Shaft Assembly
PMS 01-05-66
FIGURE 52-31-19-991-018-A FIGURE 52-31-19-991-018-A-Adjustment of the Locking Mechanism
TABLE 2
3. Job Setup
Subtask 52-31-19-820-010-A01
(1) Make sure that the hand lever mechanism is installed, see TASK 52-31-19-400-805-A01.
(2) Make sure that the latching mechanism assemblies are installed, see TASK
52-31-19-400-806-A01.
(3) Make sure that the locking shaft assembly is installed, see TASK 52-31-19-400-810-A01.
Page 7064
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
4. Procedure
Subtask 52-31-19-820-003-A01
A. Adjustment of the Locking Mechanism
NOTE : See IPL_FIGURE_08, IPL_FIGURE_30, IPL_FIGURE_31, IPL_FIGURE_33 and

IPL_FIGURE_34.
(1) Move the hand lever assembly 08-010 away from the cargo door structure up to a 65
degree position.
NOTE : Make sure that the latching mechanism assemblies 30-020, 30-030 remain in the
latched position.
(2) Measure the clearance ”C” between the locking cam 31-070 and the latching hook 33-020,
34-020, see FIGURE 52-31-19-991-018-A. The dimension of clearance ”C” must be
between 2.0 and 3.2 mm (0.0787 and 0.1260 in).
(3) If the dimension of clearance ”C” is not in the limits, adjust the control rod 08-160 as
follows, see FIGURE 52-31-19-991-018-A:
(a) Cut, remove and discard the lockwire from the safety devices.
(c) Turn the turnbuckle until the dimension is correct.
(d) Tighten the jam nuts and safety them with lockwire to the safety devices.
Page 7065
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
JAM NUT
LOCKING
DEVICE
TURNBUCKLE
LATCHING
SHAFT
A
CONTROL ROD
(8−160)
B
EXAMPLE
LOCKING CAM
(31−70) LOCKING
SHAFT
TURNBUCKLE
LOCKING
DEVICE JAM NUT
MIN 2.0 TO 3.2mm

(MIN 0.0787 TO 0.1260 in.)
LATCHING HOOK
B
(33, 34−20)
LATCHING MECHANISM ASSY
(30−20, 30)
F_CM_523119_1_0180101_01_00
Adjustment of the Locking Mechanism

FIGURE-52-31-19-991-018-A01
Page 7066
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-800-804-A01
Adjustment of the Drift Pin Mechanism
1. General
-

lockwire
TABLE 1

98D52307525000 Adjustment Tool - Cargo Doors
TABLE 2
TASK 52-31-19-400-813-A01 Assembly and Installation of the Drift Pin Rods
TASK 52-31-19-400-811-A01 Assembly and Installation of the Sequence Shaft Assembly
PMS 01-05-66
FIGURE 52-31-19-991-019-A FIGURE 52-31-19-991-019-A-Adjustment of the Drift Pin Mechanism
TABLE 3
Page 7067
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
3. Job Setup
Subtask 52-31-19-820-011-A01
(1) Make sure that the drift pin rods are installed, see TASK 52-31-19-400-813-A01.
(2) Make sure that the sequence shaft assembly is installed, see TASK 52-31-19-400-811-A01.
(3) Make sure that the vent door assembly mechanism is installed, see TASK
52-31-19-400-814-A01.
4. Procedure
Subtask 52-31-19-820-004-A01
A. Adjustment of the Drift Pin Mechanism

(1) Make sure that the hand lever assembly is in the LOCKED position and in the recess of the
(2) Install the 98D52308309000 Rigging Pin (3) of the 98D52307525000 Adjustment Tool -
Cargo Doors through the cargo door structure and the link levers 13-130, 13-230, see
FIGURE 52-31-19-991-019-A, Sheet 2.
NOTE : This position will give the dimensions that follow:

- 1.5 mm (0.0591 in) above dead center measured at the link lever assembly
13-230 and
- 1.5 mm (0.0591 in) above dead center measured at the link lever assembly
13-130.
(3) (3) If you cannot install the 98D52308309000 Rigging Pin (3) of the 98D52307525000
Adjustment Tool - Cargo Doors into the link levers 13-130, 13-230, adjust the length of the
rod 40-010 and the rod 13-180 as follows:
(c) Turn the turnbuckle until you can install the98D52308309000 Rigging Pin (3) of the
98D52307525000 Adjustment Tool - Cargo Doors in the link levers 13-130, 13-230.
(d) Tighten the jam nuts and safety them with lockwire on the safety devices.
Page 7068
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(e) Remove the (98D52308309000 Rigging Pin (3) of the 98D52307525000 Adjustment
Tool - Cargo Doors from the link levers 13-130, 13-230.
(4) Measure the distance ”Y” between the end of the extended drift pins 13-010 and the edge
members of the cargo door.
NOTE : Make sure that the distance ”Y” is between 32.5 and 35.5 mm (1.2795 to 1.3976
in).
(5) Move the hand lever assembly to the UNLOCKED position.
(6) Make sure that the retracted drift pins 13-010 are behind the skin edge of the cargo door,
see FIGURE 52-31-19-991-019-A, Sheet 1, Section E-E.
Page 7069
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A B
DETAIL B MIRROR
IMAGE OF DETAIL A
D
B
C
E
DRIFT PIN
A (13−10)
SECTION
E−E
EXTENDED
"Y"= 32.5 TO 35.5mm
Y
(1.2795 TO 1.3976 in.)
IN RETRACTED CONDITION
THE DRIFT PIN MUST BE
BEHIND THE SKIN EDGE
SKIN EDGE
5.0mm (0.1969 in.)
F_CM_523119_1_0190101_01_00

(Sheet 1 of 2)
FIGURE-52-31-19-991-019-A01
Page 7070
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
C
F
ROD
(13−180)
LINK LEVER
(13−130)
ABOVE DEAD CENTER
1.5mm (0.0591 in.)
0N EXTENDED DRIFT PIN
(13−10)
RIGGING PIN (3) D

ROD
(40−10)
LINK LEVER
(13−230)
RIGGING PIN (3)

F
ABOVE DEAD CENTER
TYPICAL 1.5mm (0.0591 in.) ON
EXTENDED DRIFT
PIN (13−10)
JAM NUT
ADJUSTABLE SAFETY
ROD (40−10) DEVICE
(13−180)
TURNBUCKLE
F_CM_523119_1_0190102_01_00

(Sheet 2 of 2)
FIGURE-52-31-19-991-019-A01
Page 7071
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-800-805-A01
Adjustment of the Interlock Mechanism
1. General
-

PMS 01-05-66
FIGURE 52-31-19-991-020-A FIGURE 52-31-19-991-020-A-Adjustment of the Interlock Mechanism
TABLE 1
3. Job Setup
Subtask 52-31-19-820-012-A01
(1) Make sure that the hand lever assembly and the hand lever mechanism are installed, see
TASK 52-31-19-400-804-A01 and TASK 52-31-19-400-805-A01.
(2) Make sure that the latching shaft assembly is installed, see ASSEMBLY TASK
52-31-19-400-808-A01.
(3) Make sure that the interlock mechanism is installed, see ASSEMBLY TASK
52-31-19-400-809-A01.
4. Procedure
Subtask 52-31-19-820-005-A01
A. Adjustment of the Interlock Mechanism
Page 7072
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(1) Make sure that the hand lever assembly is in the UNLOCKED position.
(2) Measure the clearance ”Z” between the adjusting screw 44-180 and the stop cam 32-050 of
the latching shaft assembly 32-010, see FIGURE 52-31-19-991-020-A.
NOTE : The clearance ”Z” must be between 1.0 and 1.4 mm (0.0394 and 0.0551 in).
(3) If the clearance ”Z” is not in the limits, adjust the clearance ”Z” as follows:
(a) Bend and release the locking plate 44-200.
(b) Loosen the nut 44-190 and remove the adjusting screw 44-180 from the lever 44-170.
(c) Install a new locking plate 44-200 with the adjusting screw 44-180 and the nut 44-190
on the lever 44-170.
(d) Adjust the adjusting screw 44-180 until the clearance ”Z” is correct.
(e) Tighten the nut 44-190 and safety it with the new locking plate 44-200.
Page 7073
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A
LATCHING SHAFT
(32−20)
STOP CAM
(32−50)
A
1.0 TO 1.4mm
B (0.0394 TO 0.0551 in.)
ADJUSTING SCREW
(44−180)
ADJUSTING SCREW
(44−180)
NUT
(44−190)
LOCK PLATE
(44−200)
LEVER
(44−170)
F_CM_523119_1_0200101_01_00
Adjustment of the Interlock Mechanism

FIGURE-52-31-19-991-020-A01
Page 7074
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-800-806-A01
Adjustment of the Skin Offset of the Vent Door Assembly
1. General
-

lockwire
TABLE 1
TASK 52-31-19-400-815-A01 Assembly and Installation of the Vent Door Assembly
PMS 01-05-66
FIGURE 52-31-19-991-021-A FIGURE 52-31-19-991-021-A-Adjustment of the Vent Door Assembly
TABLE 2
3. Job Setup
Subtask 52-31-19-820-013-A01
(1) Make sure that the vent door assembly is installed, see ASSEMBLY TASK
52-31-19-400-815-A01.
(2) Make sure that the vent door assembly mechanism is installed, see ASSEMBLY TASK
52-31-19-400-814-A01.
Page 7075
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
4. Procedure
Subtask 52-31-19-820-006-A01
A. Adjustment of the Skin Offset of the Vent Door Assembly
NOTE : See IPL_FIGURE_20, IPL_FIGURE_21 and FIGURE 52-31-19-991-021-A.

(1) Make sure that the hand lever assembly is in the LOCKED position and in the recess of the
(2) Measure the skin offset ”A” between the external contour of the vent door assembly
20-060 and the cargo door skin, see FIGURE 52-31-19-991-021-A.
NOTE : Make sure that the skin offset ”A” is between 0.5 and 1.5 mm (0.0197 and
0.0591 in).
(3) If the skin offset is not correct, adjust the length of the actuating rod 20-120 as follows:
(b) Loosen the jam nuts to release the turnbuckle.
(c) Turn the turnbuckle until the skin offset is correctly adjusted.
(d) Tighten the jam nuts and safety them with lockwire at the safety devices.
(4) Measure the clearance ”B” between the screws 21-270, 21-350 and the stops on the vent
door frame.
NOTE : Make sure that the clearance ”B” is between 0.2 and 0.6 mm (0.0079 and
0.0236 in).
(5) If the clearance ”B” is not correct, adjust the clearance as follows:
(a) Pull the hand lever assembly out of the recess until it is in a 65 degree position to
open the vent door assembly 20-060.
(b) Bend the tab washers 21-280, 21-360 to release the nuts 21-290, 21-370.
(c) Loosen the nuts 21-290, 21-370 to release the screws 21-270, 21-350.
(d) Remove the screws 21-270, 21-350 with the nuts 21-290, 21-370 and tab washers
21-280, 21-360 from the actuator arms 21-230, 21-320.
(e) Discard the tab washers 21-280, 21-360.
Page 7076
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(f) Install the screws 21-270, 21-350 with the nuts 21-290, 21-370 and new tab washers
21-280, 21-360 on the actuator arms 21-230, 21-320.
NOTE : Make sure that the tab washers 21-280, 21-360 are correctly installed on
the actuator arms 21-230, 21-320.
(g) Close the vent door assembly 20-060 as follows:
1 Push the roller lever 44-100 of the interlock mechanism to the outer side of the
cargo door to release the latching shaft.
2 Move the hand lever assembly down to the LOCKED position and push it into
the recess of the cargo door structure.
(h) Adjust the screws 21-270, 21-350 until the clearance ”B” is between 0.2 and 0.6 mm
(0.0079 and 0.0236 in).
(i) Tighten the nuts 21-290, 21-370 and safety them with the tab washers 21-280,
21-360.
Page 7077
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
ACTUATOR ARM
(21−320)
TAB WASHER
(21−360)
NUT
(21−370) JAM NUT
JAM NUT
SCREW
(21−350) SAFETY
DEVICE
B TURNBUCKLE
SAFETY
ACTUATOR ARM DEVICE
(21−220) ACTUATING ROD
(20−120)
TAB WASHER
(21−280)
NUT B
(21−290)
CLEARANCE CHECK OF VENT DOOR STOP
AND SKIN OFFSET CHECK
SCREW
(21−270) "B" = 0.2 TO 0.6mm
(0.0079 TO 0.0236 in.) VENT DOOR ASSY
(21−110)
SCREW
(21−270, 350)
STOP VENT DOOR CONTOUR

"A" = 0.5 TO 1.5mm
CARGO DOOR CONTOUR (0.0197 TO 0.0591 in.)
F_CM_523119_1_0210101_01_00
Adjustment of the Vent Door Assembly

FIGURE-52-31-19-991-021-A01
Page 7078
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-800-807-A01
Adjustment of the Proximity Sensors
1. General
-

TASK 52-31-19-400-816-A01 Installation of the Door Proximity Sensors
PMS 01-05-66
FIGURE 52-31-19-991-022-A FIGURE 52-31-19-991-022-A-Adjustment of the Proximity Sensors
TABLE 1
3. Job Setup
Subtask 52-31-19-820-014-A01
(1) Make sure that the proximity sensors are installed, see TASK 52-31-19-400-816-A01.
(2) Make sure that the latching shaft assembly is installed, see TASK 52-31-19-400-808-A01.
(3) Make sure that the interlock mechanism is installed, see TASK 52-31-19-400-809-A01.
4. Procedure
Subtask 52-31-19-820-007-A01
A. Adjustment of the Proximity Sensors
NOTE : See IPL_FIGURE_32 , IPL_FIGURE_44 and IPL_FIGURE_62.

(1) Make sure that the hand lever assembly is in the UNLOCKED position.
Page 7079
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(2) Adjust the proximity sensor 5MJ 62-010 installed near the latching shaft as follows, see
FIGURE 52-31-19-991-022-A, Detail B:
(a) Move the hand lever assembly until you get a clearance between 1.0 and 1.4 mm
(0.0394 and 0.0551 in) between the adjusting screw 44-180 and the stop cam 32-050.
(b) Measure the clearance between the target 62-020 and the proximity sensor 5MJ
62-010 installed on the cargo door structure.
NOTE : Make sure that the clearance is between 1.60 and 2.00 mm (0.0630 and
0.0787 in).
(c) If the clearance is not correct, adjust the position of the target 62-020 until you get
the correct clearance.
(d) If the adjusting screw 44-180 touches the stop cam 32-050, adjust the clearance
between the proximity sensor 5MJ 62-010 and the target 62-020 to a maximum of 3.0
mm (0.1811 in).
(3) Adjust the proximity sensor 28WV 62-010 installed near the hand lever assembly as follows,
see FIGURE 52-31-19-991-022-A, Detail A:
(a) Make sure that the hand lever assembly is in the LOCKED position.
(b) Measure the clearance between the proximity sensor 28WV 62-010 and the target
62-020 installed on the hand lever assembly.
NOTE : Make sure that the clearance is between 1.60 and 2.00 mm (0.0630 and
0.0787 in).
(c) If the clearance is not correct, adjust the position of the target 62-020 until you get
the correct clearance.
Page 7080
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A
1.60 TO 2.00mm
(0.0630 TO 0.0787 in.)
B
A HAND LEVER ASSY PROXIMITY SENSOR
28WV
TARGET (62−10)
(62−20)
B
PROXIMITY SENSOR
5MJ
(62−10)
1.60 TO 2.00mm
(0.0630 TO 0.0787 in.)
TARGET
(62−20)
STOP CAM
1.0 TO 1.4mm
(32−50)
(0.0394 TO 0.0551 in.)
ADJUSTING SCREW
(44−180)
F_CM_523119_1_0220101_01_00
Adjustment of the Proximity Sensors

FIGURE-52-31-19-991-022-A01
Page 7081
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
FITS AND CLEARANCES
**For PN’s ALL
TASK 52-31-19-820-806-A01
Fits and Clearances - General
1. General
A. How to use the Fits and Clearances Table (See TABLE 1)
(1) A NOTE above the table gives the reference to the related CMM figure.
(2) Column 1 gives the location number (LOC NO.) of the part.
(3) Column 2 gives links to the IPL figure item numbers of the mating parts.
(4) Column 3 gives the dimensions and the assembly clearances of the original manufacturer
(MFR) limits.
(5) Column 4 gives the dimension limits and the maximum allowable clearance of the in-
service wear limits.
NOTE : It is necessary to replace the parts which are not in the limits (See
DISASSEMBLY, REPAIR and ASSEMBLY).
B. Sample of Fits and Clearances
NOTE : See FIGURE XXX

1 2 3 4
MFR LIMITS IN-SERVICE WEAR LIMITS
MATING MAX
IPL ASSEMBLY DIMENSION ALLOWABLE
LOC FIGURE DIMENSION CLEARANCE LIMITS CLEARANCES
NO. AND millimeters millimeters millimeters millimeters
ITEM NO. (inches) (inches) (inches) (inches)
MIN MAX MIN MAX MIN MAX
Sample
TABLE 1
Page 8001
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-820-807-A01
Fits and Clearances - Tables
1. Fits and Clearances
NOTE : Refer to FIGURE 52-31-19-991-023-A.

MATING MAX
B1 OD 8-250 15.976 15.994 15.951
(0.6342) (0.6350) 0.006 0.042 (0.6279) 0.092
B2 ID 9-20 16.000 16.018 (0.0002) (0.0017) 16.043 (0.0036)
(0.6352) (0.6359) (0.6396)
C1 OD 8-290 19.972 19.993 19.941
(0.7863) (0.7871) 0.007 0.049 (0.7851) 0.111
C2 ID 8-290 20.000 20.021 (0.0003) (0.0019) 20.052 (0.0044)
(0.7874) (0.7882) (0.7894)
C1 OD 8-290 19.972 19.993 19.941
(0.7863) (0.7871) 0.007 0.049 (0.7851) 0.111
C3 ID 8-470 20.000 20.021 (0.0003 (0.0019) 20.052 (0.0044)
(0.7874) (0.7882) (0.7894)
Fits and Clearances
TABLE 1
Page 8002
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

MATING MAX
D1 OD 30-210 13.976 13.994 13.941
(0.5502) (0.5155) 0.006 0.042 (0.5489) 0.102
D2 ID 33,34 14.000 14.018 (0.0002) (0.0017) 14.043 (0.0040)
-180 (0.5512) (0.5519) (0.5529)
E1 OD 30-120 22.959 22.980 22.928
(0.8685) (0.8693) 0.020 0.062 (0.9027) 0.124
E2 ID 33,34 23.000 23.021 (0.0009) (0.0024) 23.052 (0.0049)
-40 (0.9055) (0.9063) (0.9076)
F1 OD 33,34 12.994 12.983 12.967
-60 (0.5116) (0.5094) 0.017 0.024 (0.5105) 0.076
F2 ID 33,34 13.000 13.018 (0.0007) (0.0009) 13.043 (0.0030)
-190 (0.5118) (0.5125) (0.5135)
G1 OD 33,34 12.994 12.983 12.967
-60 (0.4761) (0.4757) 0.017 0.024 (0.5105) 0.076
G2 ID 33,34 13.000 13.018 (0.0007) (0.0009) 13.043 (0.0030)
-50 (0.5118) (0.5125) (0.5135)
Fits and Clearances
TABLE 2

MATING MAX
B1 OD 32-20 31.850 31.875 31.813
(1.2539) (1.2549) 0.125 0.175 (1.2525) 0.249
B2 ID FRAME 32.000 32.025 (0.0049) (0.0069) 32.062 (0.0098)
BUSHES (1.2598) (1.2608) (1.2623)
Page 8003
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

MATING MAX
B1 OD 31-20 23.859 23.880 23.828
(0.9383) (0.9402) 0.120 0.162 (0.9381) 0.193
B2 ID FRAME 24.000 24.021 (0.0047) (0.0064) 24.052 (0.0076)
BUSHES (0.9449) (0.9457) (0.9469)
Fits and Clearances
TABLE 3

MATING MAX
C1 OD FUSELG 10.857 10.900 10.400
HINGE (0.4274) (0.4291) (0.4094)
BOLT
0.300 0.860 1.100
C2 ID 90- 11.200 11.243
(0.0118) (0.0339)
11.500
(0.0433)
50,80,90 (0.4409) (0.4426) (0.4528)
91-
30,40,70
Fits and Clearances
TABLE 4
Page 8004
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

MATING MAX
A1 OD 40-100 19.980 19.993 19.960
(0.7866) (0.7871) 0.0070 0.041 (0.7858) 0.092
A2 ID 40-90 20.000 20.021 (0.0003) (0.0016) 20.052 (0.0036)
(0.7874) (0.7882) (0.7894)
B1 OD 41-210 23.859 23.880 23.828
(0.9393) (0.9402) 0.200 0.0620 (0.9381) 0.124
B2 ID FRAME 23.900 23.921 (0.0008) (0.0024) 23.952 (0.0049)
BUSH (0.9409) (0.9418) (0.9430)
B3 OD 41-330 7.972 7.987 7.951
(0.3139) (0.3144) 0.0130 0.0430 (0.3130) 0.085
B4 ID 41-270 8.000 8.015 (0.0005) (0.0017) 8.036 (0.0033)
(0.3150) (0.3156) (0.3164)
C1 OD 41-70 7.972 7.987 7.951
(0.3139) (0.3144) 0.0130 0.0430 (0.3130) 0.085
C2 ID 41-160 8.000 8.015 (0.0005) (0.0017) 8.036 (0.0033)
(0.3150) (0.3156) (0.3164)
C3 OD 41-170 9.972 9.987 9.951
(0.3926) (0.3932) 0.013 0.043 (0.3918) 0.085
C4 ID 41-150 10.000 10.015 (0.0005) (0.0017) 10.036 (0.0033)
(0.3937) (0.3943) (0.3951)
Fits and Clearances
TABLE 5
Page 8005
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

MATING MAX
A1 OD 40-100 19.980 19.993 19.960
(0.7866) (0.7871) 0.007 0.041 (0.7858) 0.092
A2 ID 40-90 20.000 20.021 (0.0003) (0.0016) 20.052 (0.0036)
(0.7874) (0.7882) (0.7894)
B1 OD 13-160 19.980 19.993 19.960
(0.7866) (0.7871) 0.007 0.041 (0.7858) 0.092
B2 ID BRACKET 20.000 20.021 (0.0003) (0.0016) 20.052 (0.0036)
BUSH (0.7874) (0.7882) (0.7894)
C1 OD 13-260 19.980 19.993 19.960
(0.7866) (0.7871) 0.007 0.041 (0.7858) 0.092
C2 ID BRACKET 20.000 20.021 (0.0003) (0.0016) 20.052 (0.0036)
BUSH (0.7874) (0.7882) (0.7894)
D1 OD 13-10 24.959 24.980 24.928
(0.9826) (0.9835) 0.020 0.062 (0.9814) 0.124
D2 ID BRACKET 25.000 25.021 (0.0008) (0.0024) 25.052 (0.0049)
BUSH (0.9843) (0.9851) (0.9863)
Fits and Clearances
TABLE 6

MATING MAX
A1 OD 44-110 6.336 6.345 6.323
(0.2495) (0.2498) 0.005 0.050 (0.2489) 0.087
A2 ID 44-210 6.350 6.386 (0.0002) (0.0020) 6.410 (0.0034)
A3 44-170 (0.2500) (0.2514) (0.2524)
Page 8006
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

MATING MAX
A4 OD 44-50 6.248 6.299 6.200
(0.2460) (0.2480) 0.051 0.138 (0.2441) 0.240
A5 ID 44-30 6.350 6.386 (0.0020) (0.0054) 6.440 (0.0094)
(0.2500) (0.2514) (0.2535)
A6 OD 44-210 7.978 7.987 7.965
(0.3141) (0.3145) 0.013 0.058 (0.3136) 0.125
A7 ID 44-20 8.000 8.036 (0.0005) (0.0023) 8.090 (0.0049)
(0.3150) (0.3164) (0.3185)
B1 OD 44-270 11.983 11.994 11.967
(0.4718) (0.4722) 0.006 0.035 (0.4711) 0.076
B2 ID 44-170 12.000 12.018 (0.0002) (0.0014) 12.043 (0.0030)
(0.4724) (0.4731) (0.4741)
B3 OD 44-110 6.336 6.345 6.323
(0.2495) (0.2498) 0.005 0.050 (0.2489) 0.117
B4 ID 44-170 6.350 6.386 (0.0002) (0.0020) 6.440 (0.0046)
B5 44-100 (0.2500) (0.2514) (0.2535)
B7 OD 44-50 7.986 7.995 7.965
(0.3144) (0.3148) 0.005 0.029 (0.3136) 0.071
B8 ID 44-100 8.000 8.015 (0.0002) (0.0011) 8.036 (0.0028)
(0.3150) (0.3156) (0.3164)
B9 OD 44-130 4.788 4.796 4.788
(0.1885) (0.1888) 0.204 0.287 (0.1881) 0.402
B10 ID 44-140 5.000 5.075 (0.0080) (0.0113) 5.180 (0.0158)
(0.1969) (0.1998) (0.2039)
Fits and Clearances
TABLE 7
Page 8007
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A
A
B
C
B
SECTION
B2 B−B
B2
B1
SECTION
C−C
C1
C2 C3
F_CM_523119_1_0230101_01_00
Hand Lever Mechanism

FIGURE-52-31-19-991-023-A01
Page 8008
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A B
BOLT OF SECTION E−E
INSTALLED
IN OPPOSITE
DIRECTION
A
D
B
B
B F2 C
G2
E
SECTION D
F−F
G−G F1
G1
SECTION
E−E
C F
G
F
SECTION
E1 E2 D1 D2
D−D G
F_CM_523119_1_0240101_01_00
Latching Hook Assembly

FIGURE-52-31-19-991-024-A01
Page 8009
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A B
B
SECTION
A−A
A1 A2 A2
SECTION
B−B
B1 B2 B2
F_CM_523119_1_0250101_01_00
Latching and Latching Shaft

FIGURE-52-31-19-991-025-A01
Page 8010
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A
B
B
A
D
D
B
C
SECTION D2
C
D1
D−D
SECTION C2
C−C C1
F_CM_523119_1_0260101_01_00
Door Hinge
FIGURE-52-31-19-991-026-A01
Page 8011
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A B SECTION
A−A
A2
A A2
C
B C
A1
SECTION
B1 B2
B−B B2 B1
B3
B4
SECTION
C−C
C3 C4
C4
C1
C2
F_CM_523119_1_0270101_01_00
Vent Door Mechanism

FIGURE-52-31-19-991-027-A01
Page 8012
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
D
D
A
A C SECTION
A−A
B C
D
A1
D A2
A2
SECTION
B B−B
B2
SECTION
C−C B1
C2 B2
C1
C2
D1 D2 D2 SECTION D2 D2 D1
D−D
F_CM_523119_1_0280101_01_00
Drift Pin Mechanism

FIGURE-52-31-19-991-028-A01
Page 8013
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
A B
SECTION
A2 A1 A6
A−A A7 A4 A5
A3
SECTION
B1 B2 B3 B6
B−B B3 B7 B9 B10
B4 B5 B8
F_CM_523119_1_0290101_01_00
Interlock Mechanism
FIGURE-52-31-19-991-029-A01
Page 8014
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-940-808-A01
Special Tool
1. Tool Set for the Replacement of the Bushes of the Hinge Assemblies (See FIGURE 52-31-19-991-030-
A
2. For the Special Tool, see TABLE 1.
SUPPLIERS CODE
PART No. DESCRIPTION OR NAME AND WHERE USED TID
ADDRESS
355M03210000 Check Doors Tool TASK
52-31-19-700-801-
A01
355M03213000 Cable Loom TASK
52-31-19-700-801-
A01
355M03214000 Extension Cable Loom TASK
52-31-19-700-801-
A01
98D52307523100 Rigging Pin FAPE3 TASK
52-31-19-800-802-
A01
98D52307525000 Adjustment Tool - Cargo FAPE3 TASK
Doors 52-31-19-800-802-
A01 TASK
52-31-19-800-804-
A01
52-31-19-800-802-
A01
52-31-19-800-804-
A01
Special Tools, Fixtures and Equipment
TABLE 1
Page 9001
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
BOLT NUT 1 BUSH BOLT NUT 2 BUSH
REMOVAL OF THE BUSHES INSTALLATION OF THE BUSHES
THREAD
M8x1 DIA "X" DIA "Y"
SECTION
A
A−A
"AF" = 6.0mm
(0.236 in.) A 3.0mm
(0.12 in.)
40.0mm
15.0mm
(1.57 in.)
(0.59 in.)
25.0mm
(0.98 in.)
65.0mm
(2.56 in.)
110.0mm
(4.33 in.)
NUT 1 NUT 2
THREAD "AF" = 17.0mm THREAD "AF" = 17.0mm
M8x1 (0.67 in.) M8x1 (0.67 in.)
5.0mm
15.0mm
(0.20 in.) DIA "Z"
(0.60 in.)
15.0mm
(0.60 in.)
INNER DIA OF BUSHES BOLT−DIA "X" BOLT−DIA "Y" NUT 2−DIA "Z"
11.200 TO 11.243mm 11.0 TO 11.1mm 13.0 TO 13.1mm 13.0 TO 13.1mm
(0.4409 TO 0.4426 in.) (0.397 TO 0.437 in.) (0.476 TO 0.516 in.) (0.476 TO 0.516 in.)
F_CM_523119_1_0300101_01_00
Tool Set for the Replacement of the Bushes of the Hinge Assemblies
FIGURE-52-31-19-991-030-A01
Page 9002
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
**For PN’s ALL
TASK 52-31-19-550-801-A01
Storage
1. Reason for the Job
-
NOTE : Self Explanatory

TASK 52-31-19-870-802-A01 General
TABLE 1
3. Procedure
Subtask 52-31-19-620-001-A01
A. Preservation
(1) Make sure that you do the preservation procedure before you put the in its packing. The
preservation procedure is given in the MIL-P-116 and/or MIL-P-25690A Specification.
Subtask 52-31-19-530-001-A01
B. Packing
(1) Put the component in its initial container. Use the initial material for the protection of the
component.
(2) If the initial container is not available:
(a) Refer to DESCRIPTION AND OPERATION TASK 52-31-19-870-802-A01 for the
dimensions and weight of the component.
(b) Refer to ATA Specification 300. Use only approved materials for the protection of the
component.
Subtask 52-31-19-550-004-A01
C. Identification Label
(1) Put the identification labels on the component and on the outside of the container. Make
sure that you can read the labels easily.
Page 15001
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(2) The identification label must have all the related data of the component.
(3) The component is not approved for installation if there is no identification label attached to
it.
Subtask 52-31-19-550-002-A01
D. Storage
CAUTION : DO NOT KEEP THE CONTAINER NEAR FLUIDS THAT CAN CAUSE
CORROSION OR DAMAGE AND DO NOT KEEP IT NEAR SOURCES THAT
MAKE OZONE OR HEAT.
CAUTION : MAKE SURE THAT THERE IS NOT TOO MUCH WEIGHT ON THE
CONTAINER IF YOU USE THE STACK STORAGE METHOD. TOO MUCH
WEIGHT ON THE CONTAINER CAN CAUSE DAMAGE TO THE
COMPONENT.
(1) Keep the container in a clean, dry room with a good supply of air.
CAUTION : DO NOT KEEP THE COMPONENTS WITH RUBBER PARTS AT MORE

THAN + 20 DEG.C (+ 68 DEG.F).
(2) If components do not have rubber parts, keep the temperature of the room to between +18
and +28 deg. C (+64 and +82 deg. F). We recommend +18 deg. C (+64 deg. F).
(3) Keep the relative humidity to between 25 and 65 %.
(4) Put the containers where you can clearly read the identification label.
Subtask 52-31-19-550-003-A01
E. Condition Check and Functional Test
(1) Examine the condition and function of the component at specified times.
Page 15002
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
Page 1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
INTRODUCTION
**For PN’s ALL
TASK 52-31-19-872-801-A01
Introduction Illustrated Parts List (IPL)
1. General
A. The procedure recommended for finding a part number, or details of a part are in paragraph 2
of this introduction.
B. The IPL contains:
- illustrations that show an exploded view of the parts,
- the related detailed Parts Lists.
C. The IPL is used to identify, to get, keep and issue replacement aircraft parts and units.
D. AIRBUS S.A.S. has no responsibility for parts and/or units deleted or revised as a result if
airline initiated modifications are included.
E. Part numbers shown in this document are written to Air Transport Association of America
(ATA) Specification ISPEC 2200.
F. Illustrations are applicable to more than one customer.
G. In the Detailed Parts List, each figure has its own page numbering system that starts at zero.
2. How to use the IPL
A. To find a Part Number (P/N) in a Figure or Illustration you can either:
- Enter the PN in the SEARCH tool within the AirN@v / Workshop. This will show you the
Figure or Figures where this appears. Click on your chosen Fig/Item number to go open the
Figure.
- Or refer to the Alph/Numeric Parts List and find the PN. In the Fig/Item column it will
show you all the figures where this PN exists, and the Item number. Click one of these to
open the Figure.
3. Plan of the IPL
A. Indenture System of the Detailed Parts List
(1) The indenture system shows how parts and assemblies relate to their next higher
assemblies (NHA) as follows:
1234567
Assembly
Attaching parts for assembly
.Detail parts for assembly
.Sub-assembly
..Detailed parts for sub-assembly
..Sub-sub-assembly
IPL INTRO
Page 1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
...Detailed parts for sub-sub-assembly.

B. AIRBUS Part -- Numbering System
(1) The example that follows shows the identification of a part/assembly:
Basic Part Number L 57 4 6 0200 000 00
DRAWING NUMBER PARTS LIST DATA
AIRBUS Part -- Numbering System
TABLE 1
(1) L Aircraft A = AIRBUS A310/A300/A300-600 Aircraft

D = AIRBUS A320 Aircraft
F = AIRBUS A340 Aircraft
L = AIRBUS A380 Aircraft
NOTE: Initial aircraft type the part assembly was first used
on.
(2) 57 ATA Chapter Design and Manufacturing requirements of the above
breakdown will not always be the same as those in the
ATA Specification and the IPL.
(3) 4 ATA Section Changes with the ATA Chapter.
(4) 6 Drawing Responsibility The Engineering Department that is responsible for the
Design.
(5) 0200 Drawing Number The Drawing number.
(6) 000 Part or Assembly Part/assembly number.
(7) 00 Technical Specification Manufacturing or spares requirements suffix.
AIRBUS Part -- Numbering System
TABLE 2
C. Suffixes
SUFFIXES DEFINITION REMARKS
00 and 40 to 49 Production Part to drawing
The same as the Production Part.
01 to 39 Production Part not to drawing
50 Spare Part to drawing Spare part is not the same as the
51 to 59 Spare Part not to drawing Production Part
60 to 89 Spare Part not to drawing and not Number for Product Support
storable Breakout, but not for Production
99 Spare Part to drawing and not
storable
90 to 94 Specific Part for Repair Kits
IPL INTRO
Page 2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
SUFFIXES DEFINITION REMARKS

95 to 98 Specific Part for Service Bulletin Kits
Suffixes
TABLE 3
D. D. Detailed composition for an IPL

Column 1 Column 2 Column 3 Column 4 Column 5
FIG-ITEM PART NUMBER 1234567 NOMENTLATURE USAGE UNIT
FROM TO PER
ASSY
1 -- 1A L5217605100000 ARM ASSY-SUPPORT EFF//NHA RF
1 -- 2A L5217605100100 ARM ASSY-SUPPORT EFF//NHA RF
10A L5217605100100 .SUPPORT ASSY (LH) ) (V2D671) 1
SEE 52-10-50-02 FOR DET
20A L5217605500300 .SUPPORT ASSY (RH) (V2D671) 1
SEE 52-10-50-02 FOR DET
*** L5217605501100 .SUPPORT ASSY (V2D671) SPARE
30A L5217609020000 .SHEET-BONDING (V2D671) 2
40A ABS0114T3-1 .BOLT V2D671) 18
50A NAS1149C0363R .WASHER (V80205) 21
60A L9247100502400 .STRAP-BONDING (V2D671) 3
90A L5217608620000 .BRACKET-DOOR (V2D671) 1
100A ABS0114T5-25 .BOLT (V2D671) 1
110A L5217608720000 .WASHER-TOOTHED (V2D671) 2
120A NAS1149C0532R .WASHER (V80205) 1
130A NAS1291C5M .NUT (V80205) 1
OPT TO H42-5 (V15653)
OPT TO PLH55M (VF0224)
OPT TO VN300D054
(V92215)
140A L5217605600000 .BRACKET ASSY (V2D671) 2
*** L5217605600200 .BRACKET ASSY (V2D671) SPARE
145A L5217605620000 ..BRACKET (V2D671) EFF/NHA 1
IPL INTRO
Page 3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
Column 1 Column 2 Column 3 Column 4 Column 5

USED WITH L5217605600000
*** L5217605620200 ..BRACKET (V2D671) SPARE
150A MS21209F4-15 ..INSERT (V96906) EFF/NHA 1
USED WITH L5217605600000
160A L5217607600000 .BUMPER ASSY (LH) (V2D671) 1
170A L5217607600100 .BUMPER ASSY (RH) (V2D671) 1
180A L5217607800000 ..BRACKET ASSY (LH) (V2D671) 1
190A L5217607800100 ..BRACKET ASSY (RH) (V2D671) 1
200A L5217607820000 ...BRACKET (LH) (V2D671) 1
210A L5217607820100 ...BRACKET (RH) (V2D671) 1
220A D5237111620400 ...BUSHING-SHOULDERED (V2D671) 1
230A L5217608000000 ..STOP ASSY (V2D671) 1
240A L5217608120000 ...STOP (V2D671) 1
250A L5217608220000 ...SUPPORT (V2D671) 1
260A ABS0114T5-15 ..BOLT (V2D671) 1
270A NAS1291C5M ..NUT (V80205) 1
OPT TO H42-5 (V15653)
OPT TO PLH55M (VF0224)
OPT TO VN300D054
(V92215)
Detailed composition for an IPL
TABLE 4
(1) Help for the IPL-Page example

Column 1 Figure Number The figure number refers to its
related illustration. Modifications and
system variants can cause a different
figure. It will be added with a
sequential alpha-suffix, e.g. modified
versions of Figure 1 would be Figure
1A then Figure 1B and so on.
Non-Illustrated Parts The dash before an item number
shows it is not illustrated.
Item Number Initially, only every tenth number is
used for item numbers so that other
items can be added later.
IPL INTRO
Page 4
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
Column 2 AIRBUS Part AIRBUS manufactured parts e. g.

L5217605600000
Standard Part A standard part such as AN, MS,
NAS ...., is not given a supplier code.
Column 3 See XX-XX-XX-XX for DET or NHA Identifies correctly:
- the location of the full breakdown
of a sub-assembly in the IPL
- the location of the NHA of the item
in the IPL.
Usage From To In the Usage From To field the
statement ”EFF//NHA” related to
an NHA. At the same time in the
Nomenclature Field under the
description of the Part A Statement
”Used With ***” will state the NHA
PNR.
Symmetrical Parts LH or RH identifies the left hand or
right hand position of the part. If a
part is only on one assembly, (LH
side) or (RH side) follows its name.
VENDOR CODE A supplier code is given to the parts
manufactured by firms other then
AIRBUS.
Non-Procurable Item (NP) Identifies an item that is not
supplied.
Column 4 Usage From To In the Usage From To field the
statement ”EFF//NHA” related to
an NHA. At the same time in the
Nomenclature Field under the
description of the Part A Statement
”Used With ***” will state the NHA
PNR.
Column 5 Quantity The number in the Units Per Assy
column shows the quantity of parts
used for each NHA or installation.
AR = as required
RF = reference (quantity shown in
the NHA figure).
Help for the IPL-Page example
TABLE 5
IPL INTRO
Page 5
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
E. Other Notes
(1) ORDER OVRLGTH MPN XXXXXXXXXX
- Identifies a part number with more than fifteen characters that cannot fit in the part
number column.
(2) SB XX-XXX
- Identifies the Service Bulletin (SB) which adds to or changes the Detailed Parts List.
When the SB number shown in the name column is related to an AIRWORTHINESS
DIRECTIVE (AD), the letters AD and its number are shown in parenthesis. Also they
will follow the SB number, for example: PRE SB XX XXX (AD XXXX), POST SB XX
XXX (AD XXXX), ADDED by SB XX XXX (AD XXXX), DELETED BY SB XX XXX
(AD XXX), etc.
(3) SEL FROM
- Identifies a group of alternative parts from which you can take the necessary ones.
(4) OVERSIZE/UNDERSIZE
- Identifies a part as oversize or undersize.
(5) OPT TO
- Identifies an optional part that is fully interchangeable with the initial part.
(6) ALT FROM PN XXXXXXXXXX
- Identifies an alternate part number (this is a part that is fully interchangeable with the
initial part after it has had a change(s)).
(7) BUY PN XXXXXXXXXX
- Identifies the replacement part for the part in the part number column.
(8) LM = LOCAL MANUFACTURE
- Identifies the part number of the basic material (e.g. for seals, hinge strips, extrusion
etc...) from which the part in the part number column is manufactured.
- Identifies the unit of measurement followed by the dimensions or quantity.
(9) SEE CMM OR ACMM
- Refer to the Component Maintenance Manual or Abbreviated Component Maintenance
Manual for the part listed in the Detailed Parts List.
(10) MADE FROM JXXXX, MADE BY VXXXXX, MM XXX
- Identifies a part that is made from bulk material e.g. seals extrusions etc. and, if
necessary, the unit of measurement and quantity.
(11) USED ON MPN
- Identifies the NHA for a part in the part number column. This is used when the NHA
is not clear from the Usage Code (almost the same assemblies with details that are not
the same but have a single breakdown).
IPL INTRO
Page 6
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
(12) VENDOR CODE

(a) These codes agree with the current issue of the Manufacturers Cataloging Handbook
H4/HB:
- Federal Supply Code for Manufacturing (FSCM) or Commercial and Government
Entity (CAGE) code (United States and Canada only).
- NATO Supply Code for Manufacturers (NSCM) codes (does not include United
States and Canada)
(b) The letter ’V’ comes before the vendors code. For suppliers with no official code,
AIRBUS has given a provisional code. These codes are identified in the supplier table
by the information ”DUMMY CODE”.
NOTE : Suppliers who manufacture parts for which AIRBUS S.A.S. has an exclusive
sale right are not given a vendor code.
- AIRBUS standard parts (Prefix DAN, NSA etc...) are given the supplier code of
the seller of the parts. If there is more than one seller, a dummy supplier code
VT0000 is assigned to the related P/N. In this case, the additional cross-
reference table gives, for each P/N the various supplier codes and their own P/N
if applicable.
NOTE : All relevant Supplier Codes are shown in the ’Vendors Name and Code
List’, which is a part of the IPL INTRO.
IPL INTRO
Page 7
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
VENDOR LIST
CODE NAME AND ADDRESS

V01673 AIRDROME PARTS CO/3251 AIRPORT WAY/ 1867/CA 90801/LONG BEACH/USA
V04348 LAWRENCE ENGINEERING AND SUPPLY INC/500 SO; FLOWER ST, POB
30/CA-91503/BURBANK/USA
V04795 HONEYWELL INTERNATIONAL INC/DIV HARDWARE PRODUCT GROUP/875W
ELLIOT RD SUITE 106/AZ-85284/TEMPE/USA
V06329 ASC INTERNATIONAL INCORPORATED/1227 CORPORATE DR
WEST/TX-76005/ARLINGTON/USA
V06383 PANDUIT CORP/17301 RIDGELAND/IL 60477-3048/TINLEY PARK/USA
V06725 AIR INDUSTRIES CORP/12570 KNOTT ST/CA 92641-3932/GARDEN GROVE/USA
V08748 ELDEC CORPORATION/16700 13TH AVE WEST/WA 98046/LYNNWOOD/USA
V10630 ANILLO INDUSTRIES INC/2090 N GLASSELL/CA 92667/ORANGE/USA
V11815 TEXTRON INC/PO BOX 1224 E WARNER AVE/CA 92707-0157/USA
V13899 HYDRO FITTING MFG CORP/733 E EDNA PLACE/PO BOX 1558/CA
91722-3246/COVINA/USA
V14283 AMPHENOL AEROSPACE/7077 CONSOLIDATED WAY/CA 92121/SAN DIEGO/USA
V15653 KAYNAR TECHNOLOGIES INC/KAYNAR DIV/800 S STATE COLLEGE BLVD/CA
92631/FULLERTON/USA
V1ER65 3-V FASTENERS/1651 B.MARKET STREET/CA-91720/CORONA/USA
V1V757 WESCO AIRCRAFT HARDWARE CORP/27727 AVE
SCOTT/91355/VALENCIA,CA/USA
V27238 BRISTOL INDUSTRIES/630 EAST LAMBERT ROAD/CA 92821-4119/USA
V29372 ALCOA GLOBAL FASTENERS INC/DBA ALCOA FASTENING SYSTEMS DIV TRIDAIR
PRODUCTS/3000 W LOMITA BLVD/CA 90505-5103/TORRANCE/USA
V2N935 M & M AEROSPACE HARDWARE INC/10000 NW 15TH TERR/33172-2754/MIAMI,
FL/USA
V32664 AEROMETALS INC/11362 MONIER PARK PL BLDG 3B/CA 95742/RANCHO
CORDOVA/USA
V42C51 MIDI PYRENNES PLASTIQUES/Z I ESCALQUENS/31320/CASTANET/FR
V49367 AMPHENOL CORP/AMPHENOL AEROSPACE,PYLE-NATIONAL CONNECTORS/40-60
DELAWARE AVE/13838/SIDNEY,NY/USA
V52828 REPUBLIC FASTENER MFG CORP/1300 RANCHO CONEJO BLVD/CA
91320-1405/NEWBURY PARK/USA
V56563 ALATEC PRODUCTS INC/21123 NORDHOFF ST/2344/CA
91311-2344/CHATSWORTH/USA
IPL INTRO
Page 8
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

V56878 SPS TECHNOLOGIES INC/AEROSPACE AND INDUSTRIAL PRODUCTS
DIV/HIGHLAND AVENUE/PA 19046-2299/JENKINTOWN/USA
V57336 STEWARD INDUSTRIES INC/5210 14TH AVENUE NW/WA
98107-3729/SEATTLE/USA
V57983 GREER INDUSTRIES INC/2659 GRAVEL STREET/ 14249/TX 76117-0249/FORT
WORTH/USA
V59730 THOMAS AND BETTS CORP/HWY 218 S/IA 52240/IOWA CITY/USA
V60119 THE MONADNOCK COMPANY/18301 E.ARENTH AVE/CA-91749/CITY OF
INDUSTRY/USA
V60516 WEST COAST AEROSPACE INC/220 WEST E
STREET/CA-90744/WILMINGTON/USA
V60996 AERO FASTENER INC/507 300 UNION ST/01085/WESTFIELD,MA/USA
V69289 ORKAL INDUSTRIES LLC/333 WESTBURY AVE/11514/CARLE PLACE,NY/USA
V6D833 D AND D BEAN CO/701 SEVENTH ST/80631/GREELEY,CO/USA
V70347 AMERICAN AVIATION/180 VARICK STREET/NY-10014/NEW YORK/USA
V71286 FAIRCHILD CORP/CAMLOC PRODUCTS DIV FAIRCHILD FASTENER GROUP/3012
W LOMITA BLVD/CA 90505/TORRANCE/USA
V72962 HARVARD INDUSTRIES INC/PO BOX 3 WERNER WAY SUITE 210/NJ 08833/USA
V73197 HI-SHEAR CORP/PO BOX 2600 SKYPARK DR/CA 90505/USA
V75237 KAYNAR TECHNOLOGIES INC/MICRODOT DIV/190 W CROWTHER AVE/CA
92670/PLACENTIA/USA
V80205 NATIONAL AEROSPACE STANDARDS/(STANDARDISATION OFFICE.REFER TO
OPT VENDORS)/1725 DE SALES N W/WA-20036/WASHINGTON/USA
V80539 SPS TECHNOLOGIES INC AEROSPACE INDUSTRIAL PROD/2701 S HARBOR BLVD/
1259/CA 92702-1259/SANTA ANA/USA
V81343 SOCIETY OF AUTOMOTIVE ENGINEERS INC/(STANDARDISATION OFFICE.REFER
TO OPT VENDORS)/400 COMMONWEALTH DR/PA
15096-0001/WARRENDALE/USA
V81349 MILITARY SPECIFICATIONS/(STANDARDISATION OFFICE.REFER TO OPT
VENDORS)
V81482 SIMMONDS PRECISION PRODUCTS INC/CO-OPERATIVE INDUSTRIES DIV/100
OAKDALE RD/NJ 07930/CHESTER/USA
V83324 REXNORD INC ROSAN DIV/3130 W HARWARD STREET/ 25225/CA 92799/SANTA
ANA/USA
V84114 AMERICAN STEEL CO/103 PARK AVENUE/PA-16117/ELLWOOD CITY/USA
IPL INTRO
Page 9
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

V88044 AERONAUTICAL STANDARDS GROUP,DEPT OF NAVY AND
AIR/FORCE(STANDARDISATION OFFICE.REFER TO OPT
VENDORS)/MA-89536/SILVER SPRINGS/USA
V8K160 UNIREX INC/9310 EAST 37TH SREET NORTH/KS-67226/WICHITA/USA
V8Z507 CALIFORNIA SCREW PRODUCTS CORP/14957 GWENCHRIS
AVENUE/CA-90723/PARAMOUNT/USA
V91345 MILLER DIAL CORP/4400 N TEMPLE CITY BLVD/CA 91734/EL MONTE/USA
V92215 FAIRCHILD FASTENERSS INC/PO BOX 3000 W LOMITA BLVD/CA 90505-5103/USA
V92595 AUTOMATIC SCREW MACHINE/709 2ND AVENUE S.E/AL-35602/DECATURE/USA
V94931 BENDIX INTERNATIONAL/1633 BROADWAY/NY-10019/NEW YORK/USA
V952D1 SOURIAU-CLUSES/Z.I. DES GRANDS PRES/74301/CLUSES CEDEX/F
V96906 MILITARY STANDARDS PROMULGATED/(STANDARDISATION OFFICE.REFER TO
OPT VENDORS)/1321 FOURTEENTH STREET,N.W/WA-20005/WASHINGTON
D.C/USA
V97464 INDUSTRIAL RETAINING RING CO/57 CORDIER ST/NJ-07111/IRVINGTON, NJ/USA
V97928 DEUTSCH FASTENER CORP/3969 PARAMOUNT BLVD/CA
90712-4193/LAKEWOOD/USA
VB0014 ADB NV/585 LEUVENSESTEENWEG/1930/ZAVENTEN/BEL
VB0128 SONACA SA PARC INDUSTRIEL/5 ROUTE NATIONALE/6200/GOSSELIES/BEL
VB1395 TECHNICAL AIRBORNE COMPONENTS SA/PARC INDUSTRIEL DES HAUTS-SARTS
5 AVE/4040/HERSTAL/BEL
VC0258 BINDER GOTTLIEB GMBH UND CO BANDWEBEREI/BAHNHOF STRASSE
19/POSTFACH 20/71088/HOLZGERLINGEN/GER
VC0259 PANDUIT GMBH/STEINMUEHL STRASSE 14/61352/BAD HOMBURG/GER
VC3471 GLENAIR ELECTRIC GMBH/HOLZWEG 32A/POSTFACH
4147/61440/OBERURSEL/GER
VC3753 WULFMEYER RUDOLF AIRCRAFT INTERIOR GMBH & CO. KG/FRANKENRING
15/170263/LANGENHAGEN/GER
VC4293 ALCOA FASTENING SYSTEMS/FAIRCHILD FASTENERS EUR.-VSD GMBH/STEVEN
3/101320/31135/HILDESHEIM/GER
VC4344 FROELICH GMBH/FRIEDRICH-EBERT-STR.209/37520/OSTERODE/D
VC4863 SCHWARZ/IM UNTEREN RIED 7/75382/ALTHENGSTETT/D
VC5543 INTERTURBINE AVIATION LOGISTIC GMBH/KISDORFER WEG
36-38/24568/KALTENKIRCHEN/D
VC5729 HONEYWELL HPG/LADEMANNBOGEN 128/22339/HAMBURG,/D
IPL INTRO
Page 10
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

VC7009 DUDEINS AEROSPACE GMBH/HOEKERWEG 270/40231/DUESSELDORF/GER
VC7100 ICORE INTERNATIONAL GMBH/FRIEDBERGER STRASSE 2/61350/BAD
HOMBURG/GER
VC7239 NMB MINEBA GMBH/SIEMENSTRASSE 30/63225/LANGEN/GER
VC7839 ROSWITHA WILDE TRADING/HOEHERWEG 270/40231/DUESSELDORF/D
VD0680 FAIRCHILD FATENERS EUROPE/CAMLOC GMBH/INDUSTRIES STRASSE
6/POSTFACH 180/65779/KELKHEIM/GER
VD1283 HUCK INTERNATIONAL GMBH/AN DER UNTEREN SOESE
26/37520/OSTERODE/GER
VD8090 SEEGER ORBIS GMBH/WIESBADENER STRASSE 243-247/POSTFACH
1460/61462/KOENIGSTEIN/GER
VD8286 DIN DEUTSCHES INSTITUT FUER NORMUNG E V/(STANDARDISATION OFFICE
REFER TO OPT VENDORS)/KAMEKE STRASSE 2-8/50672/KOELN/GER
VD8485 STABILUS GMBH/WALLERSHEIMER WEG 100/POSTFACH
2029/56070/KOBLENZ/GER
VD8518 DEUTSCHE AEROSPACE AIRBUS GMBH/KREETSLAG 10/POSTFACH
950109/21129/HAMBURG/GER
VD8527 HELLERMANN PAUL GMBH/SIEMENS STRASSE 5/25421/PINNEBERG/GER
VDM498 SFS INTEC GMBH/AIRCRAFT COMPONENTS/FERDINAND-PORSCHE-STR
1/75382/ALTHENGSTETT/GER
VF0095 ATELIERS DE LA HAUTE-GARONNE ETS AURIOL/ZI DE
FLOURENS/31130/BALMA/FR
VF0188 BLANC AERO INDUSTRIES/193,RUE DEN BERCY,TOUR GAMMA A/75582/PARIS
CEDEX.12/FR
VF0215 ESPA.SA/2 R DE BALZAC/75008/PARIS/FR
VF0222 SKF AEROSPACE FRANCE/1 AVENUE MARC SEGUIN/BP 29/26241/ST VALLIER
CEDEX/FR
VF0224 SIMMONDS SA/9 RUE DES CRESSONNIERES/72110/ST COSME EN VAIRAIS/FR
VF0225 SOURIAU/9 RUE DE LA PORTE DE BUC/78000/VERSAILLES/FR
VF0236 BLANC AERO INDUSTRIES/18-20 RUE SAINT-HILAIRE/95310/ST QUEN
L’AUMONE/FR
VF0347 3M FRANCE/BD DE L’OISE/95006/CERGY PONTOISE CEDEX/FR
VF0355 CAILLAU SARL/28 RUE ERNEST RENAN/BP 82/92134/ISSY LES MOULINEAUX
CEDEX/FR
VF0394 AIR-LB STE SA/240 RUE GABRIEL PERI/92700/ COLOMBES/FR
IPL INTRO
Page 11
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

VF0434 D M G DECOLLETAGE GENERAL MODERNE/1 RUE GERBIER/75011/ PARIS/FR
VF0564 PLASTIC OMNIUM SA/3 RUE DU PARC/92305/ LEVALLOIS-PERRET/FR
VF0582 SUPERFLEXIT SA/58 BOULEVARD GALLIENI/92130/ ISSY LES MOULINEAUX/FR
VF1983 DEUTSCH CIE SA/17 RUE LAVOISIER................................./117/27091/EVREUX
CEDEX 9/FR
VF2094 S N E P SA/ZI DE SURVAURE/84/42602/MONTBRISSON CEDEX/FR
VF2693 LEGRAND SA/128 AVENUE DE LATTRE DE TASSIGNY/87000/LIMOGES/FR
VF3132 ITT COMPOSANTS ET INSTRUMENTS DIV CONN CANNON/157 RUE DES
BLAINS/92220/ BAGNEUX/FR
VF3341 HELLERMANNTYTON CABLE MANAGEMENT PRODUCTS/MINIPARC DU MANET/2
R DES HETRES/78190/TRAPPES/FR
VF4240 HUBER ET CIE / ETS/ SA/19,RUE DE MALAKOFF/92320/CHATILLON/FR
VF4250 CONNECTRAL SA/29 RUE DES BAS ROGERS/92150/ SURESNES/FR
VF5442 EADS NORMALISATION STANDARD ASN/REFER TO OPT VENDORS/37
BOULEVARD DE MONTMORENCY/75781/PARIS/FR
VF6101 AERAZUR /DIV EQUIPEMENTS AERONAUTIQUES SA/2 R MAURICE
MALLET/92137/ISSY LES MOULINEAUX CEDEX/FR
VF6162 AMPHENOL SOCAPEX/948 PROMENADE DE L’ARVE/74311/THYEZ CEDEX/FR
VF6167 HUCK FRANCE SA/US PAR VIGNY/95450/CLOS D’ASSEVILLE/FR
VF7395 DECOUPAGE INDUSTRIEL DE PRECISION SARL/ZI DE
FERRIERES/45210/FERRIERES EN GATINAIS/FR
VF7411 MECAERO SA/BLVD DU GRAND CASTAING/31120/PORTET SUR GARONNE/FR
VF7756 NORMAERO SARL/270 RUE DE L’ABBAYE/82000/MONTAUBAN/FR
VF8421 OXYGRAVURE/518 AV DE JOUQUES/13685/AUBAGNE/FR
VF8612 MATRIX SC FRANCE/29 CHS JULES CESAR/95300/CERGY PONTOISE CEDEX/FR
VF8982 SA G.ESTEVE/8 RUE CLAUDE GONIN ZI DE MONTAUDRAN/31400/ TOULOUSE/FR
VF9211 L,HOTELLIER/4 RUE HENRI POINCARE/92167/ANTONY CEDEX/FR
VFAPE3 AIRBUS SAS (FOR ORDERING REFER TO SUPPLIER CODE)/1 ROND-POINT
MAURICE BELLONTE/31707/BLAGNAC/FRA
VH1822 STORK FOKKER AESP BV/INDUSTRIEWEG 4/1/3351 LB/PAPENDRECHT/NL
VH2776 AIR PARTS INTERNATIONAL BV/KALKOVENWEG 12/255/2401/LK ALPHEN AD
RIJN/NL
VH6173 HI-SHEAR CORP/EUROPEAN OFFICE/OOST/SCHIPHOL/HOL
IPL INTRO
Page 12
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

VI9005 A E C M A/(STANDARDISATION OFFICE.REFER TO OPT VENDORS)/88 BLVD
MALESHERBES/75008/PARIS/FR
VK0316 ITT CANNON UK/JAYS CLOSE VIABLES INDUSTRIAL ESTATE/RG22
4BW/BASINGSTOKE HANTS/GB
VK0653 DOWTY ELECTRONIC COMPONENTS LTD/KINGSDITCH LANE/GL51
9PG/CHELTENHAM GL0S/UK
VK0654 MESSIER DOWTY LTD/CHELTENHAM ROAD EAST CHURCHDOWN/GL2
9QH/GLOUCESTER/GB
VK0685 ICORE INTERNATIONAL LTD/LEIGH ROAD SLOUGH TRADING ESTATE/SL1
4BB/SLOUGH BERKS/GB
VK0720 HELLERMANN TYTON/1 ROBESON WAY/ALTRINCHAM ROAD/M22
4TY/WYTHENSHAWE MANCHESTER/UK
VK1010 TYCO ELECTRONICS UK LTD/FARADAY ROAD/SN3
5HH/DORCAN,SWINDON,WILTSHIRE/UK
VK1678 FAIRCHILD FASTENERS UK LTD/UNIT 6/22 BARDON INDUSTRIAL ESTATE/LE67
1TE/BARDON HILL, COALVILLE/UK
VK4130 WILD MANUFACTURING GROUP LTD/FLOODGATE STREET/B5
5SJ/BIRMINGHAM/GB
VK4975 LENTERN /AIRCRAFT/ LTD/MAIN ROAD/SS5 4JJ/HAWKWELL HOCKLEY
ESSEX/UK
VK5269 SKF (U.K) LTD AEROSPACE DIVISION/108 STRODE ROAD/BS21 6QQ/CLEVEDON
AVON/UK
VK5673 S P S TECHNOLOGIES LTD/T J BROOKS DIVISION/191 BARKBY ROAD TROON
INDUST0IAL ESTATE/LE4 9HX/LEICESTER/GB
VK6405 MICRODOT AEROSPACE LTD/BLACKTHORN ROAD/SL3 0AG/COLNEBROOK
SLOUGH BERKS/UK
VK7766 BRITISH STANDARDS INSTITUTION/(STANDARDISATION OFFICE.REFER TO OPT
VENDORS)/2 PARK STREET/W1A 2BS/LONDON/GB
VK8753 LINREAD NORTHBRIDGE/AIRCRAFT PRODUCT DIVISION/CROSSGATE ROAD
PARK FARM INDUSTRIAL ESTATE/28/B98 7TD/REDDITCH WORCS/UK
VR1120 SATAIR/AMAGER LANDEVEJ 147A/KASTRUP,2770/DK
VS0352 NIPPON MINIATURE BEARING COMPANY LTD/00389/TOKYO/JAP
VS5540 ULTRA PRECISION SA/MONTHEY/CH
VU1653 SOCIETY OF BRITISH AEROSPACE COMPANIES LTD/(STANDARDISATION
OFFICE.REFER TO OPT VENDORS)/29 KING STREET/SW1Y 6RD/LONDON/GB
VU1901 BESTOBELL AVIATION /PART MEGGITT AEROSPACE//127/135 FARNHAM
ROAD/SL1 4UY/SLOUGH BERKS/UK
IPL INTRO
Page 13
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

VU7388 SMITHS AEROSPACE ACTUATION SYSTEMS/(FORMERLY DOWTY AEROSPACE
HYDRAULICS)/ARLE COURT/GL51 0TP/CHELTENHAM GLOUCESTER/GB
IPL INTRO
Page 14
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
DETAILED PARTS LIST
Page 10001
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
C
70
10
130
120
110
100 B
60
B
C
A
A
C
80
30 40
20
90
50
F_PL_523119_01_0_01_00
DOOR ASSY-CARGO COMPARTMENT,FWD

Figure 01 / FIGURE-52-31-19-950-801-01
Page 10001-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
FIG-ITEM PART NUMBER NOMENCLATURE USAGE UNIT

1234567 FROM PER
TO ASSY
01 - 001A D5237300000600 DOOR ASSY-CARGO COMPARTMENT,FWD VFAPE3 RF
01 - 001B D5237300001000 DOOR ASSY-CARGO COMPARTMENT,FWD VFAPE3 RF
01 - 001C D5237300001200 DOOR ASSY-CARGO COMPARTMENT,FWD VFAPE3 RF
01 - 001D D5237300001400 DOOR ASSY-CARGO COMPARTMENT,FWD VFAPE3 RF
01 010A D2587114000060 . PROTECTION INSTL-FIRE VFAPE3 001
used on 001A
SEE 52-31-19-020 FOR DET
01 010B D2587114000260 . PROTECTION INSTL-FIRE VFAPE3 001
used on 001B
SEE 52-31-19-020 FOR DET
01 010C D2587114000261 . PROTECTION INSTL-FIRE VFAPE3 001
used on 001C, 001D
SEE 52-31-19-020 FOR DET
01 020A D5237300200061 . COVER-ACCESS VFAPE3 001
used on 001A, 001B, 001C, 001D
SEE 52-31-19-030 FOR DET
01 030A D5237300500060 . STRUCTURE ASSY-DOOR VFAPE3 001
used on 001A, 001B, 001C, 001D
SEE 52-31-19-040 FOR DET
01 040A MS21209F1215P . INSERT V96906 003
Optional Vendor Code 04795, 06329, 2N935, 60996,
8K160, C4293, C5543, K6405
used on 001A, 001B, 001C, 001D
01 050A D5237306000060 . MECHANISM ASSY-DOOR VFAPE3 001
used on 001A, 001B, 001C, 001D
SEE 52-31-19-050 FOR DET
01 060A D5237300000660 . HOUSING-VALVE VFAPE3 001
used on 001A, 001B, 001C, 001D
SEE 52-31-19-500 FOR DET
01 070A D9209031102060 . ELECTRIC SYSTEM VFAPE3 001
used on 001A
SEE 52-31-19-600 FOR DET
01 070B D9209031102061 . ELECTRIC SYSTEM VFAPE3 001
used on 001B
SEE 52-31-19-600 FOR DET
01 080A NSA9117-63 . PLATE-IDENTIFICATION VF5442 001
Optional Vendor Code FAPE3
used on 001A, 001B, 001C, 001D
01 090A D5237121720000 . PLUG VFAPE3 003
OPT TO ABS0411PF1210 FAPE3
used on 001A, 001B, 001C, 001D
- ITEM NOT ILLUSTRATED
Page 10001-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
01 100A D5237113420000 . SCREW-ADJUSTING VFAPE3 004
used on 001A, 001B, 001C, 001D
01 110A NAS509-5C . NUT V80205 004
Optional Vendor Code 92595
used on 001A, 001B, 001C, 001D
01 120A SP112G . WASHER-TAB VK7766 004
OPT TO 5310999480982 K4975
Optional Vendor Code 04795, 2N935, C5543, F7395,
K4130
used on 001A, 001B, 001C, 001D
01 130A NSA5054-5 . INSERT VF5442 004
OPT TO K8000-5 K6405
OPT TO SR314L0036 83324
Optional Vendor Code 04795, 2N935, C5543, K6405
used on 001A, 001B, 001C, 001D
Page 10001-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
A 1
F
B
F 80
G
80 70
C D
60 20 C
10 D
30
G 50
40
B
E
A E 1
E 100
C
90
F
D
110
NOTE:
1 TYPICAL INSTALLATION 110
F_PL_523119_02_0_01_00
PROTECTION INSTL-FIRE
Figure 02 / FIGURE-52-31-19-950-802-01
Page 10002-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
02 - 001A D2587114000060 PROTECTION INSTL-FIRE VFAPE3 RF
used on 010A (523119010)
SEE 52-31-19-010 FOR NHA
02 - 001B D2587114000260 PROTECTION INSTL-FIRE VFAPE3 RF
used on 010B (523119010)
SEE 52-31-19-010 FOR NHA
02 - 001C D2587114000261 PROTECTION INSTL-FIRE VFAPE3 RF
used on 010C (523119010)
SEE 52-31-19-010 FOR NHA
02 010A D2587114100000 . LINING ASSY-FIRE PROTECTION VFAPE3 001
used on 001A
SIL 25-135 ((FAR 25-856))
02 010B D2587114100200 . LINING ASSY-FIRE PROTECTION VFAPE3 001
used on 001B, 001C
02 020A NSA55131-007 .. STUD VF5442 013
OPT TO 2700-7S K1678
OPT TO J710-7N F9211
Optional Vendor Code 04795, 2N935, C5543
used on 010A, 010B
02 030A NSA55131-005 .. STUD VF5442 001
OPT TO 2700-5S K1678
OPT TO J710-5N F9211
used on 010A, 010B
02 040A NAS1149C0532R .. WASHER V80205 014
Optional Vendor Code 04795, 2N935, 60996, 8K160,
C5543
used on 010A, 010B
02 050A D2587115820200 .. SPACER VFAPE3 014
used on 010A, 010B
02 060A NSA55144-001 .. WASHER-LOCK VF5442 014
OPT TO 1127722 60119
OPT TO 2600SW K1678
Optional Vendor Code 04795, 2N935, 71286, C5543,
D0680
used on 010A, 010B
02 070A NSA939510AN .. STRIP-PROTECTIVE VF5442 AR
USE AS REQUIRED, REQUIRED LENGTH 60 MM
OPT TO G51NA F3341
Optional Vendor Code C5543, F3341
used on 010A, 010B
Page 10002-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
02 080A DAN98S1B .. STRIP-CLING VFAPE3 AR
ABS1133D020 FAPE3
OPT TO 6TBD501284 C0258
Optional Vendor Code C0258, C3753, C5543
used on 010A
02 080B ABS1133D020 .. TAPE VFAPE3 AR
OPT TO APLIX840AP55L20 C3753
Optional Vendor Code C3753, C5543
used on 010B
02 090A DAN98S1A . STRIP-CATCH VFAPE3 AR
ABS1133C020 FAPE3
OPT TO 6TBD501282 C0258
Optional Vendor Code C0258, C3753, C5543
used on 001A
02 090B ABS1133C020 . TAPE VFAPE3 AR
OPT TO APLIX840AP55H20 C3753
used on 001B, 001C
02 100A D5237300120000 . SEAL-DOOR VFAPE3 001
used on 001A, 001B
02 100B D5237300120200 . SEAL-DOOR VFAPE3 001
used on 001A, 001B, 001C
02 110A D5237112720000 . BUSHING VFAPE3 004
used on 001A, 001B, 001C
Page 10002-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
120
A
B
10
20
A F
130
D
D
A G
B F
D
D
C
D
D D
D C
E C 50
D
C 40
F
E 30
C
E
F 60
G 170
180
D TO F
D
70
190 E
100
F
110 200
150 90 210
140
80
160
F_PL_523119_03_0_01_00
COVER-ACCESS
Figure 03 / FIGURE-52-31-19-950-803-01
Page 10003-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
03 - 001A D5237300200061 COVER-ACCESS VFAPE3 RF
used on 020A (523119010)
SEE 52-31-19-010 FOR NHA
03 010A D5237300200000 . COVER ASSY-ACCESS VFAPE3 001
used on 001A
03 020A D5237300220000 .. COVER-ACCESS VFAPE3 001
used on 010A
03 030A D5237124220000 .. SHEET VFAPE3 004
used on 010A
03 040A D5237124120200 .. GLASS-SIGHT VFAPE3 004
used on 010A
03 050A NAS1102-06-6 .. SCREW V80205 008
K8753
used on 010A
03 060A MS21042L06 .. NUT V96906 008
OPT TO AS8600B U1653
OPT TO H14L06 15653
OPT TO RH30A06 52828
OPT TO RM52LH3324-62 72962
OPT TO T98S632 11815
OPT TO VN300A62 92215
8K160, C5543
used on 010A
03 070A ABS0691-020 .. STUD VFAPE3 010
OPT TO 1604S41-020BP D0680
OPT TO DV691-020 C4863
used on 010A
03 080A ABS0604-4 .. WASHER VFAPE3 017
OPT TO CA21077-4 D0680
OPT TO EN6094-16 I9005
OPT TO SS604-4 C4863
OPT TO W6094-16 DM498
used on 010A
03 090A ABS0692-01 .. WASHER-TAB VFAPE3 017
OPT TO 1604W50-1BP D0680
OPT TO H200S C4863
used on 010A
Page 10003-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
03 100A ABS0691-015 .. STUD VFAPE3 003
OPT TO 1604S41-015BP D0680
OPT TO DV691-015 C4863
used on 010A
03 110A ABS0691-010 .. STUD VFAPE3 004
OPT TO 1604S41-010BP D0680
OPT TO DV691-010 C4863
used on 010A
03 120A D5237288000200 . COVER-ACCESS VFAPE3 002
used on 001A
03 130A NAS1102E08-8 . SCREW V80205 004
Optional Vendor Code F0188, K8753
used on 001A
03 140A D5237173600200 . COVER ASSY-ACCESS VFAPE3 001
used on 001A
03 150A D5237173620200 .. COVER-ACCESS VFAPE3 001
used on 140A
03 160A D5347504521600 .. SECTION-SEALING VFAPE3 002
used on 140A
03 170A NAS1100E3-8 . SCREW V80205 018
Optional Vendor Code 1ER65, 8Z507, F0188, F7411,
K8753
used on 001A
03 180A NAS1149C0332R . WASHER V80205 018
Optional Vendor Code 04795, 60996, 8K160, C5543,
C5729
used on 001A
03 190A NAS1102E3-7 . SCREW V80205 002
K8753
used on 001A
03 200A ABS0368-01 . RECEPTACLE VFAPE3 017
OPT TO 1604R02-1 71286
OPT TO HN368-01 C4863
Optional Vendor Code 04795, 2N935, C5543, D0680
used on 001A
03 210A DIN65399-2400BF . RIVET VD8286 034
EN6101AD3 I9005
used on 001A
Page 10003-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
10
B 20
30
20 30
30
F_PL_523119_04_0_01_00
STRUCTURE ASSY-DOOR
Figure 04 / FIGURE-52-31-19-950-804-01
Page 10004-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
04 - 001A D5237300500060 STRUCTURE ASSY-DOOR VFAPE3 RF
used on 030A (523119010)
SEE 52-31-19-010 FOR NHA
04 010A D5237300500061 . HINGE INSTL VFAPE3 001
used on 001A
SEE 52-31-19-900 FOR DET
04 020A D5237127620000 . PLUG-PROTECTIVE VFAPE3 002
used on 001A
04 030A D5237127620200 . PLUG-PROTECTIVE VFAPE3 003
used on 001A
04 - 040A D5237300500063 . BUSHING INSTL-DOOR STRUCTURE VFAPE3 001
used on 001A
SEE 52-31-19-960 FOR DET
Page 10004-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
30
20
60
10
50 40
F_PL_523119_05_0_01_00
MECHANISM ASSY-DOOR
Figure 05 / FIGURE-52-31-19-950-805-01
Page 10005-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
05 - 001A D5237306000060 MECHANISM ASSY-DOOR VFAPE3 RF
used on 050A (523119010)
SEE 52-31-19-010 FOR NHA
05 010A D5237306000061 . LEVER ASSY-HAND VFAPE3 001
used on 001A
SEE 52-31-19-080 FOR DET
05 - 013A D5237306000069 . LEVER ASSY-HAND VFAPE3 001
used on 001A
SEE 52-31-19-080 FOR DET
05 - 015A D5237306000070 . LEVER ASSY-HAND VFAPE3 001
used on 001A
SEE 52-31-19-080 FOR DET
05 020A D5237306000062 . ROD AND PIN-DRIFT VFAPE3 001
used on 001A
SEE 52-31-19-130 FOR DET
05 - 023A D5237306000071 . ROD AND PIN-DRIFT VFAPE3 001
used on 001A
SEE 52-31-19-130 FOR DET
05 - 025A D5237306000072 . ROD AND PIN-DRIFT VFAPE3 001
used on 001A
SEE 52-31-19-130 FOR DET
05 030A D5237306000063 . DOOR ASSY-VENT VFAPE3 001
used on 001A
SEE 52-31-19-200 FOR DET
05 - 033A D5237306000073 . DOOR ASSY-VENT VFAPE3 001
used on 001A
SEE 52-31-19-200 FOR DET
05 - 035A D5237306000074 . DOOR ASSY-VENT VFAPE3 001
used on 001A
SEE 52-31-19-200 FOR DET
05 040A D5237306000064 . MECHANISM ASSY-LOCKING VFAPE3 001
used on 001A
SEE 52-31-19-300 FOR DET
05 050A D5237306000065 . MECHANISM-INTERLOCK VFAPE3 001
used on 001A
SEE 52-31-19-440 FOR DET
05 060A D5237306000066 . SHAFT-SEQUENCE VFAPE3 001
used on 001A
SEE 52-31-19-400 FOR DET
05 - 063A D5237306000075 . SHAFT-SEQUENCE VFAPE3 001
used on 001A
SEE 52-31-19-400 FOR DET
Page 10005-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
05 - 065A D5237306000076 . SHAFT-SEQUENCE VFAPE3 001
used on 001A
SEE 52-31-19-400 FOR DET
Page 10005-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
120
30 130
60
A 70 110
120
280
20 80 60
140 50 70
250 80
40
A 150
80
260 50
290 80
230 60
450 70
90
260 270 460 470
300 470 60
340 100
350 70
360 110
330 220
270 510 200
240 520
310 210
230 170
320 180
190
110 530
370 120
320 480
490 540 160
500
110
220 390
430
420
400
170 200
180 210
190
120 200
440 210
410
10 380
170
180
110 190
220
F_PL_523119_08_0_01_00
LEVER ASSY-HAND
Figure 08 / FIGURE-52-31-19-950-808-01
Page 10008-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
08 - 001A D5237306000061 LEVER ASSY-HAND VFAPE3 RF
used on 010A (523119050)
SEE 52-31-19-050 FOR NHA
08 - 001B D5237306000069 LEVER ASSY-HAND VFAPE3 RF
used on 013A (523119050)
SEE 52-31-19-050 FOR NHA
08 - 001C D5237306000070 LEVER ASSY-HAND VFAPE3 RF
used on 015A (523119050)
SEE 52-31-19-050 FOR NHA
08 010A D5237177000000 . LEVER ASSY-HAND VFAPE3 001
used on 001A, 001B, 001C
SEE 52-31-19-090 FOR DET
08 020A D5237178000000 . LEVER ASSY VFAPE3 001
used on 001A, 001B, 001C
08 030A D5237177620000 .. BRACKET VFAPE3 001
used on 020A
08 040A ASNA2151-08 .. ACTUATING UNIT VF5442 001
OPT TO 192953 D8485
used on 020A
08 050A F5237136720200 .. PIN-LOCATING VFAPE3 002
used on 020A
08 060A MS24665-86 .. PIN-COTTER V96906 004
84114, 8K160, C5543
used on 020A
08 070A NAS1149C0463R .. WASHER V80205 004
C5543
used on 020A
08 080A NAS1149C0432R .. WASHER V80205 004
C5543
used on 020A
08 090A D5237179620000 .. LEVER VFAPE3 001
used on 020A
08 100A MS14102-4K .. BEARING V96906 001
Optional Vendor Code 04795, 2N935, C5543, C7239,
K5269, S0352
used on 020A
08 110A NAS1291C3M . NUT V80205 007
OPT TO H42-3 15653
Page 10008-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
F0224
used on 001A, 001B, 001C
08 120A NAS1149C0332R . WASHER V80205 009
C5729
used on 001A, 001B, 001C
08 130A NSA5031-3-5 . BOLT VF5442 003
Optional Vendor Code 04795, 2N935, C5543, D1283,
F0188, F6167, F7411, K5673, K8753
used on 001A, 001B, 001C
08 140A NSA5031-3-2 . BOLT VF5442 002
ABS0114T3-2 FAPE3
F0188, F6167, F7411, K5673, K8753
used on 001A, 001B, 001C
08 150A D5237179820000 . WASHER-LOCK VFAPE3 001
used on 001A, 001B, 001C
08 160A D5237176820000 . ROD ASSY VFAPE3 001
OPT TO B322104-003 F0222
OPT TO R24359 B1395
used on 001A
08 160B R24359 . ROD ASSY VB1395 001
OPT TO D5237176820000 FAPE3
used on 001B
08 160C B322104-003 . ROD ASSY VF0222 001
OPT TO D5237176820000 FAPE3
used on 001C
08 170A MS24665-151 . PIN-COTTER V96906 003
84114, 8K160, C5543
used on 001A, 001B, 001C
08 180A NSA5059E4 . NUT VF5442 003
OPT TO 73783CM8-428 56878
F0188
used on 001A, 001B, 001C
08 190A NAS1149C0463R . WASHER V80205 003
C5543
used on 001A, 001B, 001C
Page 10008-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
08 200A NSA5031-4D11 . BOLT VF5442 003
F0188, F6167, F7411, K5673, K8753
used on 001A, 001B, 001C
08 210A NAS1149C0432R . WASHER V80205 003
C5543
used on 001A, 001B, 001C
08 220A NAS1149C0363R . WASHER V80205 003
70347, 8K160, C5543
used on 001A, 001B, 001C
08 230A NSA5031-3-17 . BOLT VF5442 002
F0188, F6167, F7411, K5673, K8753
used on 001A, 001B, 001C
08 240A D5237179120000 . LOCK-UNIVERSAL JOINT VFAPE3 001
used on 001A, 001B, 001C
08 250A D5237179720200 . SHAFT VFAPE3 001
used on 001A, 001B, 001C
08 260A D5237179922000 . WASHER-SPACER VFAPE3 002
used on 001A, 001B, 001C
THICKNESS 3.8 MM, THICKNESS 0.149 INCHES
used on 001A, 001B, 001C
08 280A MS15001-1 . FITTING-LUBRICATION V96906 001
AS15001-1 81343
8K160, C5543
used on 001A, 001B, 001C
08 290A D5237179520000 . SHAFT VFAPE3 001
used on 001A, 001B, 001C
08 300A D5237178500200 . LEVER ASSY-ROLLER VFAPE3 001
used on 001A, 001B, 001C
08 310A D5237178420000 .. LEVER-ROLLER VFAPE3 001
used on 300A
08 320A D5237178320000 .. BUSHING-SHOULDERED VFAPE3 002
used on 300A
08 330A D5237178620000 .. ROLLER VFAPE3 001
used on 300A
Page 10008-3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
08 340A NSA5059E3 .. NUT VF5442 001
OPT TO 73783CM8-328 56878
F2094
used on 300A
08 350A NAS1149C0332R .. WASHER V80205 001
C5729
used on 300A
08 360A MS24665-88 .. PIN-COTTER V96906 001
84114, 8K160, C5543
used on 300A
08 370A NSA5042C04-150 .. BOLT VF5442 001
Optional Vendor Code 04795, C5543, F0095, F0188,
F7411, K4975, K5673, K8753
used on 300A
08 380A NAS428C3A7 . BOLT V80205 001
OPT TO D5237164820000 FAPE3
used on 001A, 001B, 001C
08 390A NSA5042C04-185 . BOLT VF5442 001
Optional Vendor Code 04795, C5543, F0095, F0188,
F7411, K4975, K5673, K8753
used on 001A, 001B, 001C
08 400A D5237178920000 . BOLT-SPRING VFAPE3 001
used on 001A, 001B, 001C
08 410A D5237178820000 . SPRING-COMPRESSION VFAPE3 001
used on 001A, 001B, 001C
08 420A A5217236820000 . SHEET VFAPE3 001
used on 001A, 001B, 001C
08 430A D5237176320000 . HOOK-CATCHING VFAPE3 001
used on 001A, 001B, 001C
08 440A NAS6703-4 . BOLT V80205 002
60996, 8K160, C5543, K8753
used on 001A, 001B, 001C
08 450A D5237179000200 . JOINT ASSY-UNIVERSAL VFAPE3 001
used on 001A
08 450B D5237179000200 . JOINT ASSY-UNIVERSAL VFAPE3 001
used on 001B
Page 10008-4
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
08 450C D5237179000200 . JOINT ASSY-UNIVERSAL VFAPE3 001
used on 001C
08 460A D5237179220000 .. LATCH-UNIVERSAL JOINT VFAPE3 001
used on 450A, 450B, 450C
used on 450A, 450B, 450C
08 480A MS24665-153 .. PIN-COTTER V96906 001
84114, 8K160, C5543
used on 450A, 450B, 450C
08 490A NSA5059C4 .. NUT VF5442 001
OPT TO TE9925-4 72962
OPT TO THCR54 F0224
Optional Vendor Code 04795, 2N935, C5543, F0188
used on 450A, 450B, 450C
08 500A NAS1149C0463R .. WASHER V80205 001
C5543
used on 450A, 450B, 450C
08 510A NAS1149C0432R .. WASHER V80205 001
C5543
used on 450A, 450B, 450C
08 520A NSA5031-4D11 .. BOLT VF5442 001
F0188, F6167, F7411, K5673, K8753
used on 450A, 450B, 450C
08 530A MS14102-4K .. BEARING V96906 001
K5269, S0352
used on 450A, 450B, 450C
08 540A D5237176720200 .. ROD ASSY VFAPE3 001
OPT TO B322104-012 F0222
OPT TO R24358 B1395
used on 450A
08 540B R24358 .. ROD ASSY VB1395 001
OPT TO D5237176720000 FAPE3
OPT TO D5237176720200 FAPE3
OPT TO D5237176720400 FAPE3
used on 450B
08 540C B322104-012 .. ROD ASSY VF0222 001
OPT TO D5237176720200 FAPE3
Page 10008-5
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 450C
Page 10008-6
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
200 200
20
20
150
190
50
60
150 70
190
80
30
70
40
50 40
60
150
70
80 120 110
10 70
120 170
90
120
160
180
120
130
180
140
180
150
130
180
180
210
100
F_PL_523119_09_0_01_00
LEVER ASSY-HAND
Figure 09 / FIGURE-52-31-19-950-809-01
Page 10009-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
09 - 001A D5237177000000 LEVER ASSY-HAND VFAPE3 RF
used on 010A (523119080)
SEE 52-31-19-080 FOR NHA
09 010A D5237177120000 . LEVER-HAND VFAPE3 001
used on 001A
09 020A D5237178220000 . CAM-SEQUENCE VFAPE3 002
used on 001A
09 030A D5237178120000 . STOP VFAPE3 001
used on 001A
09 040A D5237177820200 . BOLT VFAPE3 002
used on 001A
09 050A NSA5321-6 . RING-RETAINING VF5442 002
OPT TO ST6 D8090
used on 001A
09 060A D5237152220000 . WASHER VFAPE3 002
used on 001A
09 070A D5237153220000 . BUSHING-SHOULDERED VFAPE3 004
used on 001A
09 080A D5237177920200 . ROLLER VFAPE3 002
used on 001A
09 090A D5227246920000 . INSERT VFAPE3 001
used on 001A
09 100A D5237177220000 . FLAP-HANDLE VFAPE3 001
used on 001A
09 110A D5237177320000 . SPRING VFAPE3 001
used on 001A
09 120A MS24665-153 . PIN-COTTER V96906 004
84114, 8K160, C5543
used on 001A
09 130A NAS1149C0363R . WASHER V80205 002
70347, 8K160, C5543
used on 001A
09 140A D5237177520200 . BOLT-BEARING VFAPE3 001
used on 001A
09 150A NAS1149C0332R . WASHER V80205 008
C5729
used on 001A
Page 10009-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
09 160A D5237177520000 . BOLT-BEARING VFAPE3 001
used on 001A
09 170A D5237180420000 . SLEEVE-SPRING VFAPE3 001
used on 001A
09 180A D5237136720000 . BUSHING VFAPE3 006
used on 001A
09 190A NSA5031-3-3 . BOLT VF5442 006
F0188, F6167, F7411, K5673, K8753
used on 001A
09 200A NSA5054-3 . INSERT VF5442 006
OPT TO K8000-3 K6405
OPT TO M45932-1-9AL 81349
used on 001A
09 210A D5237110220600 . LAYER-SLIDING VFAPE3 001
used on 001A
Page 10009-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
A 20
10
50
60 40
70
310
340 320
350
360
30
270
340 310
350 320
360
180 300
300 330
310
340 320 290
290
350
360
170
220
190 200
210 280
280
250 240
90 260 230
100 300
50 110 130
60 40 120 290 150
70 300 140
290
340
10 20 350
360 160
330
310 280
320
280
30
80
F_PL_523119_13_0_01_00
ROD AND PIN-DRIFT

Figure 13 / FIGURE-52-31-19-950-813-01
Page 10013-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
13 - 001A D5237306000062 ROD AND PIN-DRIFT VFAPE3 RF
used on 020A (523119050)
SEE 52-31-19-050 FOR NHA
13 - 001B D5237306000071 ROD AND PIN-DRIFT VFAPE3 RF
used on 023A (523119050)
SEE 52-31-19-050 FOR NHA
13 - 001C D5237306000072 ROD AND PIN-DRIFT VFAPE3 RF
used on 025A (523119050)
SEE 52-31-19-050 FOR NHA
13 010A D5237157120200 . PIN-DRIFT VFAPE3 002
used on 001A, 001B, 001C
13 020A NAS1303-11D . BOLT V80205 002
NAS6603D11 80205
Optional Vendor Code F0188, F7411, K8753
used on 001A, 001B, 001C
13 030A D5237156420000 . WASHER VFAPE3 002
used on 001A, 001B, 001C
13 040A D5237151620000 . BUSHING VFAPE3 002
used on 001A, 001B, 001C
13 050A NSA5059E3 . NUT VF5442 002
OPT TO 73783CM8-328 56878
F2094
used on 001A, 001B, 001C
13 060A NAS1149C0332R . WASHER V80205 002
C5729
used on 001A, 001B, 001C
13 070A MS24665-88 . PIN-COTTER V96906 002
84114, 8K160, C5543
used on 001A, 001B, 001C
13 080A D5237332220000 . ROD-FIXED VFAPE3 001
used on 001A
13 080B R25257 . ROD ASSY VB1395 001
used on 001B
13 080C B318217-022 . ROD ASSY VF0222 001
used on 001C
13 090A D5237186100000 . BELLCRANK ASSY VFAPE3 001
used on 001A, 001B, 001C
Page 10013-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
13 100A D5237331700000 .. LEVER ASSY-LINK VFAPE3 001
used on 090A
13 110A D5237331720000 ... LEVER-LINK VFAPE3 001
used on 100A
13 120A MS14102-4K ... BEARING V96906 002
K5269, S0352
used on 100A
13 130A D5237331600200 .. LEVER-LINK VFAPE3 001
used on 090A
used on 130A
13 150A MS14102-4K ... BEARING V96906 001
K5269, S0352
used on 130A
13 160A D5237103220200 .. SHAFT-BEAM 3 VFAPE3 001
used on 090A
13 170A D5237331520200 . BUSH VFAPE3 001
used on 001A, 001B, 001C
13 180A D5237332320000 . ROD-ADJUSTABLE VFAPE3 001
used on 001A
13 180B R25258 . ROD ASSY VB1395 001
used on 001B
13 180C B318217-023 . ROD ASSY VF0222 001
used on 001C
used on 001A, 001B, 001C
used on 190A
used on 200A
13 220A MS14102-4K ... BEARING V96906 001
K5269, S0352
used on 200A
used on 190A
used on 230A
Page 10013-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
13 250A MS14102-4K ... BEARING V96906 002
K5269, S0352
used on 230A
used on 190A
13 270A D5237305720000 . ROD VFAPE3 001
used on 001A
13 270B R25259 . ROD ASSY VB1395 001
used on 001B, 001C
13 280A AN386-2-8A . PIN-TAPER V88044 004
used on 001A, 001B, 001C
13 290A D5237180220000 . SLEEVE VFAPE3 004
used on 001A, 001B, 001C
13 300A NAS1291C3M . NUT V80205 004
OPT TO H42-3 15653
F0224
used on 001A, 001B, 001C
13 310A NSA5031-4D11 . BOLT VF5442 004
F0188, F6167, F7411, K5673, K8753
used on 001A, 001B, 001C
13 320A NAS1149C0432R . WASHER V80205 004
C5543
used on 001A, 001B, 001C
13 330A NAS1149C0632R . WASHER V80205 002
56563, 60996, 70347, 8K160, C5543
used on 001A, 001B, 001C
13 340A NAS1149C0463R . WASHER V80205 004
C5543
used on 001A, 001B, 001C
13 350A NSA5059E4 . NUT VF5442 004
OPT TO 73783CM8-428 56878
F0188
used on 001A, 001B, 001C
Page 10013-3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
13 360A MS24665-151 . PIN-COTTER V96906 004
84114, 8K160, C5543
used on 001A, 001B, 001C
Page 10013-4
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
A
B
10
60
A
140 70
190 80
150 160
220
230
110
80
120 90
100
200
190 210 80
170 90
150 200
130 140 210 100
160
220
230
80
90 180
100 B
220
230 40
80
90
100
20
30
50
F_PL_523119_20_0_01_00
DOOR ASSY-VENT
Figure 20 / FIGURE-52-31-19-950-820-01
Page 10020-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
20 - 001A D5237306000063 DOOR ASSY-VENT VFAPE3 RF
used on 030A (523119050)
SEE 52-31-19-050 FOR NHA
20 - 001B D5237306000073 DOOR ASSY-VENT VFAPE3 RF
used on 033A (523119050)
SEE 52-31-19-050 FOR NHA
20 - 001C D5237306000074 DOOR ASSY-VENT VFAPE3 RF
used on 035A (523119050)
SEE 52-31-19-050 FOR NHA
20 010A D5237166120200 . COVER VFAPE3 001
used on 001A, 001B, 001C
20 020A NAS1291C3M . NUT V80205 004
OPT TO H42-3 15653
F0224
used on 001A, 001B, 001C
20 030A NAS1149C0332R . WASHER V80205 004
C5729
used on 001A, 001B, 001C
20 040A NAS1100E3-8 . SCREW V80205 004
Optional Vendor Code 1ER65, 8Z507, F0188, F7411,
K8753
used on 001A, 001B, 001C
20 050A D2587115820000 . SPACER VFAPE3 004
used on 001A, 001B, 001C
used on 001A, 001B, 001C
SEE 52-31-19-210 FOR DET
20 070A NSA5031-4D16 . BOLT VF5442 001
F0188, F6167, F7411, K5673, K8753
used on 001A, 001B, 001C
20 080A NAS1149C0463R . WASHER V80205 005
C5543
used on 001A, 001B, 001C
20 090A MS24665-151 . PIN-COTTER V96906 004
84114, 8K160, C5543
used on 001A, 001B, 001C
Page 10020-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
20 100A NSA5059E4 . NUT VF5442 004
OPT TO 73783CM8-428 56878
F0188
used on 001A, 001B, 001C
20 110A D5237141420000 . BUSHING VFAPE3 001
used on 001A, 001B, 001C
20 120A D5237333120000 . ROD-ADJUSTABLE VFAPE3 001
used on 001A
20 120B R25261 . ROD ASSY VB1395 001
used on 001B
20 120C B318217-031 . ROD ASSY VF0222 001
used on 001C
used on 001A, 001B, 001C
used on 130A
used on 140A
20 160A MS14102-4K ... BEARING V96906 001
K5269, S0352
used on 140A
used on 130A
used on 001A
20 180B R25260 . ROD ASSY VB1395 001
used on 001B
20 180C B318217-030 . ROD ASSY VF0222 001
used on 001C
20 190A AN386-2-8A . PIN-TAPER V88044 002
used on 001A, 001B, 001C
20 200A D5237180220000 . SLEEVE VFAPE3 002
used on 001A, 001B, 001C
20 210A NAS1291C3M . NUT V80205 002
OPT TO H42-3 15653
F0224
used on 001A, 001B, 001C
Page 10020-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
20 220A NSA5031-4D11 . BOLT VF5442 003
F0188, F6167, F7411, K5673, K8753
used on 001A, 001B, 001C
20 230A NAS1149C0432R . WASHER V80205 003
C5543
used on 001A, 001B, 001C
Page 10020-3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
120 210 200
180
190
150
350
370 360
380
130
30 170
80
340
100 130
140
150 330
320
310
340
390
330 400
160
70
130
140 270
90
10 10 290 280
20 20 420 300
30 30
160
40 410
50
260
60
230
110 70 220
130
30 140
40
50 260
240
250 30 130
80 170
F_PL_523119_21_0_01_00
DOOR ASSY-VENT
Figure 21 / FIGURE-52-31-19-950-821-01
Page 10021-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
21 - 001A D5237335000061 DOOR ASSY-VENT VFAPE3 RF
used on 060A (523119200)
SEE 52-31-19-200 FOR NHA
21 010A MS24665-300 . PIN-COTTER V96906 002
84114, 8K160, C5543
used on 001A
21 020A NSA5059E6 . NUT VF5442 002
OPT TO 73783CM8-624 56878
F0188
used on 001A
21 030A NAS1149C0632R . WASHER V80205 AR
USE AS REQUIRED, USAGE RANGE FROM 3 TO 6
56563, 60996, 70347, 8K160, C5543
used on 001A
56563, 60996, 70347, 8K160, C5543
used on 001A
60996, 70347, 8K160, C5543
used on 001A
21 060A D5237166620100 . SPRING VFAPE3 001
used on 001A
21 070A D5237166320200 . SLEEVE VFAPE3 002
used on 001A
21 080A NSA5031-6D38 . BOLT VF5442 002
Optional Vendor Code 04795, C5543, D1283, F0188,
F6167, F7411, K5673, K8753
used on 001A
21 090A D5237166620000 . SPRING VFAPE3 001
used on 001A
21 100A D5237166320400 . SLEEVE VFAPE3 001
used on 001A
used on 001A
Page 10021-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
21 120A NSA5030-4-26 .. SCREW VF5442 002
ASNA2001V4-26 F5442
F0188, F6167, F7411, K5673, K8753
used on 110A
21 130A NAS1149C0463R .. WASHER V80205 010
C5543
used on 110A
21 140A NAS1291C4M .. NUT V80205 006
OPT TO 180003-5 60119
OPT TO PLH504M F0224
used on 110A
21 150A NSA5030-4-27 .. SCREW VF5442 004
ASNA2001V4-27 F5442
F0188, F6167, F7411, K5673, K8753
used on 110A
21 160A D5237165220200 .. BOLT-SPRING VFAPE3 002
used on 110A
21 170A MS24665-86 .. PIN-COTTER V96906 002
84114, 8K160, C5543
used on 110A
21 180A D5237163920200 .. SEAL-PRESSURE RELIEF FLAP VFAPE3 001
used on 110A
21 190A D5237163820600 .. RETAINER VFAPE3 001
used on 110A
21 200A D5237163820700 .. RETAINER VFAPE3 001
used on 110A
21 210A D5237334920000 .. DOOR-VENT VFAPE3 001
used on 110A
21 220A D5237334600000 .. ARM ASSY-ACTUATOR VFAPE3 001
used on 110A
21 230A D5237334720000 ... ARM-ACTUATOR VFAPE3 001
used on 220A
21 240A D5237165620200 ... BUSHING VFAPE3 001
used on 220A
21 250A D5237165420200 ... BUSHING-SHOULDERED VFAPE3 001
used on 220A
Page 10021-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 220A
21 270A NAS428C3A7 ... BOLT V80205 001
OPT TO D5237164820000 FAPE3
used on 220A
21 280A SP108D ... WASHER-TAB VK7766 001
used on 220A
21 290A MS35650-304 ... NUT V96906 001
Optional Vendor Code 04795, 06329, 1V757, 2N935,
57983, 69289, C5543
used on 220A
21 300A MS21209F1-20 ... INSERT V96906 001
8K160, C4293, C5543, K6405
used on 220A
21 310A D5237334800000 .. ARM ASSY-ACTUATOR VFAPE3 001
used on 110A
21 320A D5237334720000 ... ARM-ACTUATOR VFAPE3 001
used on 310A
21 330A D5237165620200 ... BUSHING VFAPE3 002
used on 310A
used on 310A
21 350A NAS428C3A7 ... BOLT V80205 001
OPT TO D5237164820000 FAPE3
used on 310A
21 360A SP108D ... WASHER-TAB VK7766 001
used on 310A
21 370A MS35650-304 ... NUT V96906 001
Optional Vendor Code 04795, 06329, 1V757, 2N935,
57983, 69289, C5543
used on 310A
21 380A MS21209F1-20 ... INSERT V96906 001
8K160, C4293, C5543, K6405
used on 310A
21 390A D5237334400000 .. BRACKET ASSY VFAPE3 001
used on 110A
Page 10021-3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
21 400A D5237334320000 ... BRACKET VFAPE3 001
used on 390A
21 410A D5237164320000 ... BUSHING VFAPE3 001
used on 390A
used on 390A
Page 10021-4
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
40
10
D
A TO D
A
B
170
180
C 190
240
270
280 140
260 150
200
C 230
ABD 290 210
240 220 B
250
220 B 110
160
80 D
120
170
90 D
130 ABC 90
140
100
50
20 ACD 60 ABC
50 30 B 70
60 D
70
80 ABC
F_PL_523119_30_0_01_00
MECHANISM ASSY-LOCKING
Figure 30 / FIGURE-52-31-19-950-830-01
Page 10030-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
30 - 001A D5237306000064 MECHANISM ASSY-LOCKING VFAPE3 RF
used on 040A (523119050)
SEE 52-31-19-050 FOR NHA
30 010A D5237306000067 . SHAFT ASSY-LOCKING VFAPE3 001
used on 001A
SEE 52-31-19-310 FOR DET
30 020A D5237149000000 . LATCHING MECHANISM ASSY VFAPE3 003
used on 001A
SEE 52-31-19-330 FOR DET
30 030A D5237149000200 . LATCHING MECHANISM ASSY VFAPE3 001
used on 001A
SEE 52-31-19-340 FOR DET
used on 001A
SEE 52-31-19-320 FOR DET
30 050A MS24665-370 . PIN-COTTER V96906 004
84114, 8K160, C5543
used on 001A
30 060A NSA5059E10 . NUT VF5442 004
OPT TO 73783CM8-1018 56878
used on 001A
30 070A NAS1149C1032R . WASHER V80205 004
C5543
used on 001A
30 080A D5237144120000 . BOLT VFAPE3 004
used on 001A
30 090A D5237140120000 . WASHER VFAPE3 004
used on 001A
used on 001A
used on 001A
30 120A D5237144220200 . SLEEVE VFAPE3 004
used on 001A
30 130A NAS6705U42 . BOLT V80205 004
F7411, K8753
used on 001A
Page 10030-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
30 140A NAS1149C0532R . WASHER V80205 008
C5543
used on 001A
30 150A NAS1291C5M . NUT V80205 004
OPT TO H42-5 15653
OPT TO PLH55M F0224
OPT TO VN300D054 92215
F0224
used on 001A
30 160A NSA5031-7D42 . BOLT VF5442 004
Optional Vendor Code 04795, C5543, D1283, F0188,
F6167, F7411, K5673, K8753
used on 001A
30 170A NAS1149C0763R . WASHER V80205 008
C5543
used on 001A
30 180A MS24665-300 . PIN-COTTER V96906 004
84114, 8K160, C5543
used on 001A
30 190A NSA5059E7 . NUT VF5442 004
OPT TO 73783CM8-720 56878
used on 001A
used on 001A
30 210A D5237144420400 . SLEEVE VFAPE3 004
used on 001A
30 220A D5237140120400 . WASHER VFAPE3 002
used on 001A
30 230A D5237144520200 . BOLT VFAPE3 001
used on 001A
30 240A NAS1149C0432R . WASHER V80205 008
C5543
used on 001A
30 250A D5237141320400 . BUSHING VFAPE3 004
used on 001A
30 260A D5237141420000 . BUSHING VFAPE3 004
used on 001A
Page 10030-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
30 270A MS24665-151 . PIN-COTTER V96906 004
84114, 8K160, C5543
used on 001A
30 280A NSA5059E4 . NUT VF5442 004
OPT TO 73783CM8-428 56878
F0188
used on 001A
30 290A NSA5031-4D16 . BOLT VF5442 003
F0188, F6167, F7411, K5673, K8753
used on 001A
Page 10030-3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
A
70
90
100
70
90
100 120
120
80
80
10
120 20
90
120 90 100
100
50 110
110
110
90
100
40 70
30 110 90
100
60
80
80
70
90
100
120
120
120
120
F_PL_523119_31_0_01_00
SHAFT ASSY-LOCKING
Figure 31 / FIGURE-52-31-19-950-831-01
Page 10031-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
31 - 001A D5237306000067 SHAFT ASSY-LOCKING VFAPE3 RF
used on 010A (523119300)
SEE 52-31-19-300 FOR NHA
used on 001A
31 020A D5237305220000 .. SHAFT-LOCKING VFAPE3 001
used on 010A
31 030A D5237150300000 .. LEVER ASSY-HINGED VFAPE3 001
used on 010A
31 040A D5237150320000 ... LEVER-HINGED VFAPE3 001
used on 030A
31 050A MS14102-4K ... BEARING V96906 001
K5269, S0352
used on 030A
31 060A D5237176920000 .. LEVER VFAPE3 001
used on 010A
31 070A D5237151221000 .. CAM-LOCKING VFAPE3 004
used on 010A
31 080A AN386-1-10A . PIN-TAPER V88044 004
F0434
used on 001A
31 090A NAS1291C3M . NUT V80205 012
OPT TO H42-3 15653
F0224
used on 001A
31 100A NAS1149C0332R . WASHER V80205 012
C5729
used on 001A
31 110A D5237167320000 . SLEEVE VFAPE3 004
used on 001A
31 120A DAN15-6-18 . PIN-RIVET VD8518 008
OPT TO HL20PB6-18 73197
used on 001A
Page 10031-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
A
A
130 120 70
80
90
130
120
100
100
40
100 50
120
120 100
130
100
130
100
60
120
130
10
100 20
40
120 110
130
120 30
130
100 120
130
120 100
130
100
40
120
130
120
130
100
120
130
F_PL_523119_32_0_01_00
SHAFT ASSY-LOCKING
Figure 32 / FIGURE-52-31-19-950-832-01
Page 10032-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
32 - 001A D5237306000068 SHAFT ASSY-LOCKING VFAPE3 RF
used on 040A (523119300)
SEE 52-31-19-300 FOR NHA
32 010A D5237305400200 . SHAFT ASSY-LATCHING VFAPE3 001
used on 001A
32 020A D5237305520000 .. SHAFT-LATCHING VFAPE3 001
used on 010A
32 030A D5237150620200 .. LEVER-SHAFT VFAPE3 001
used on 010A
32 040A D5237150620000 .. LEVER-SHAFT VFAPE3 003
used on 010A
32 050A D5237141920200 .. CAM-STOP VFAPE3 001
used on 010A
32 060A D5237143220200 .. LEVER-SWITCH VFAPE3 001
used on 010A
32 070A D5237150500000 .. LEVER ASSY-HINGED VFAPE3 001
used on 010A
32 080A D5237150520000 ... LEVER-HINGED VFAPE3 001
used on 070A
32 090A MS14102-4K ... BEARING V96906 001
K5269, S0352
used on 070A
32 100A AN386-2-13A . PIN-TAPER V88044 011
F0434
used on 001A
32 110A AN386-2-12A . PIN-TAPER V88044 001
F0434
used on 001A
32 120A D5237180220000 . SLEEVE VFAPE3 012
used on 001A
32 130A NAS1291C3M . NUT V80205 012
OPT TO H42-3 15653
F0224
used on 001A
Page 10032-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
A
A 100
110
120
130
140
110
100
120
130
140
90
150
70
260
160
90
170 60
80
190
180
60
50
140
220
250
240
210 230
220
190 40
200
50
20
30
10
F_PL_523119_33_0_01_00

Figure 33 / FIGURE-52-31-19-950-833-01
Page 10033-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
33 - 001A D5237149000000 LATCHING MECHANISM ASSY VFAPE3 RF
used on 020A (523119300)
SEE 52-31-19-300 FOR NHA
33 010A D5237143500000 . HOOK ASSY-LATCHING VFAPE3 001
used on 001A
33 020A D5237143620000 .. HOOK-LATCHING VFAPE3 001
used on 010A
33 030A MS15001-1 .. FITTING-LUBRICATION V96906 001
AS15001-1 81343
8K160, C5543
used on 010A
used on 010A
used on 010A
33 060A D5237140320200 . SLEEVE VFAPE3 002
used on 001A
33 070A D5237185320000 . LINK-CONNECTING VFAPE3 001
used on 001A
33 080A D5237140420200 . BOLT VFAPE3 001
used on 001A
33 090A NAS1149C0732R . WASHER V80205 002
C5543
used on 001A
used on 001A
used on 001A
33 120A NSA5059C5 . NUT VF5442 002
OPT TO TE9925-5 72962
OPT TO THCR55 F0224
used on 001A
33 130A NAS1149C0532R . WASHER V80205 002
C5543
used on 001A
33 140A MS24665-153 . PIN-COTTER V96906 003
84114, 8K160, C5543
Page 10033-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 001A
33 150A D5237140420000 . BOLT VFAPE3 001
used on 001A
used on 001A
33 170A D5237185520000 .. BELLCRANK VFAPE3 001
used on 160A
33 180A D5237142320200 .. BUSHING VFAPE3 001
used on 160A
used on 160A
AS15001-1 81343
8K160, C5543
used on 160A
33 210A NSA5031-4D16 . BOLT VF5442 001
F0188, F6167, F7411, K5673, K8753
used on 001A
33 220A NAS1149C0432R . WASHER V80205 002
C5543
used on 001A
33 230A D5237141320400 . BUSHING VFAPE3 001
used on 001A
33 240A D5237141420000 . BUSHING VFAPE3 001
used on 001A
33 250A NSA5059C4 . NUT VF5442 001
OPT TO TE9925-4 72962
OPT TO THCR54 F0224
used on 001A
33 260A D5237180120000 . ROD-CONNECTING VFAPE3 001
OPT TO B322104-013 F0222
OPT TO R24225 B1395
used on 001A
Page 10033-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
A
100
A 110
150
90
100
110
80
90
120
130 70
140
260
160 120
130
170 140
60
190
180
60
50
140
220
250
240
210 230
220 190
40
200
50
20
30
10
F_PL_523119_34_0_01_00

Figure 34 / FIGURE-52-31-19-950-834-01
Page 10034-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
34 - 001A D5237149000200 LATCHING MECHANISM ASSY VFAPE3 RF
used on 030A (523119300)
SEE 52-31-19-300 FOR NHA
34 010A D5237143500000 . HOOK ASSY-LATCHING VFAPE3 001
used on 001A
34 020A D5237143620000 .. HOOK-LATCHING VFAPE3 001
used on 010A
AS15001-1 81343
8K160, C5543
used on 010A
used on 010A
used on 010A
34 060A D5237140320200 . SLEEVE VFAPE3 002
used on 001A
34 070A D5237185320000 . LINK-CONNECTING VFAPE3 001
used on 001A
34 080A D5237140420200 . BOLT VFAPE3 001
used on 001A
34 090A NAS1149C0732R . WASHER V80205 002
C5543
used on 001A
used on 001A
used on 001A
34 120A NSA5059C5 . NUT VF5442 002
OPT TO TE9925-5 72962
OPT TO THCR55 F0224
used on 001A
34 130A NAS1149C0532R . WASHER V80205 002
C5543
used on 001A
34 140A MS24665-153 . PIN-COTTER V96906 003
84114, 8K160, C5543
Page 10034-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 001A
34 150A D5237140420000 . BOLT VFAPE3 001
used on 001A
used on 001A
34 170A D5237185520000 .. BELLCRANK VFAPE3 001
used on 160A
34 180A D5237142320200 .. BUSHING VFAPE3 001
used on 160A
used on 160A
AS15001-1 81343
8K160, C5543
used on 160A
34 210A NSA5031-4D16 . BOLT VF5442 001
F0188, F6167, F7411, K5673, K8753
used on 001A
34 220A NAS1149C0432R . WASHER V80205 002
C5543
used on 001A
34 230A D5237141320400 . BUSHING VFAPE3 001
used on 001A
34 240A D5237141420000 . BUSHING VFAPE3 001
used on 001A
34 250A NSA5059C4 . NUT VF5442 001
OPT TO TE9925-4 72962
OPT TO THCR54 F0224
used on 001A
34 260A D5237180120000 . ROD-CONNECTING VFAPE3 001
OPT TO B322104-013 F0222
OPT TO R24225 B1395
used on 001A
Page 10034-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
20
30
40
50
60
A
10
20
30
40
A 50
60
210
140
120
130
240 110
250 90
70
80 230
220
90
220
230
100
130 120
140
160
170
190 180 210
200
150
20
30
40
50
60
F_PL_523119_40_0_01_00
SHAFT-SEQUENCE
Figure 40 / FIGURE-52-31-19-950-840-01
Page 10040-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
40 - 001A D5237306000066 SHAFT-SEQUENCE VFAPE3 RF
used on 060A (523119050)
SEE 52-31-19-050 FOR NHA
40 - 001B D5237306000075 SHAFT-SEQUENCE VFAPE3 RF
used on 063A (523119050)
SEE 52-31-19-050 FOR NHA
40 - 001C D5237306000076 SHAFT-SEQUENCE VFAPE3 RF
used on 065A (523119050)
SEE 52-31-19-050 FOR NHA
used on 001A
40 010B R25256 . ROD ASSY VB1395 001
used on 001B
40 010C B318217-021 . ROD ASSY VF0222 001
used on 001C
40 020A NSA5031-4D11 . BOLT VF5442 003
F0188, F6167, F7411, K5673, K8753
used on 001A, 001B, 001C
40 030A NAS1149C0432R . WASHER V80205 003
C5543
used on 001A, 001B, 001C
40 040A NAS1149C0463R . WASHER V80205 003
C5543
used on 001A, 001B, 001C
40 050A NSA5059E4 . NUT VF5442 003
OPT TO 73783CM8-428 56878
F0188
used on 001A, 001B, 001C
40 060A MS24665-151 . PIN-COTTER V96906 003
84114, 8K160, C5543
used on 001A, 001B, 001C
40 070A D5237186000000 . COVER BEAM 4 ASSY VFAPE3 001
used on 001A, 001B, 001C
40 080A D5237185700000 .. COVER BEAM 4 VFAPE3 001
used on 070A
Page 10040-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 080A
used on 070A
40 110A D5237162820000 .. SLEEVE-SPACER VFAPE3 001
used on 070A
40 120A D5237162700000 .. LEVER-BEAM 4 VFAPE3 002
used on 070A
40 130A D5237162720000 ... LEVER VFAPE3 001
used on 120A
40 140A MS14102-4K ... BEARING V96906 001
K5269, S0352
used on 120A
40 150A D5237332020200 .. ROD-FIXED VFAPE3 001
OPT TO R26229 B1395
used on 070A
40 160A MS24665-151 .. PIN-COTTER V96906 001
84114, 8K160, C5543
used on 070A
40 170A NSA5059E4 .. NUT VF5442 001
OPT TO 73783CM8-428 56878
F0188
used on 070A
40 180A NAS1149C0463R .. WASHER V80205 001
C5543
used on 070A
40 190A NSA5031-4D11 .. BOLT VF5442 001
F0188, F6167, F7411, K5673, K8753
used on 070A
40 200A NAS1149C0432R .. WASHER V80205 001
C5543
used on 070A
40 210A AN386-2-8A .. PIN-TAPER V88044 002
used on 070A
40 220A NAS1291C3M .. NUT V80205 002
OPT TO H42-3 15653
Page 10040-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
F0224
used on 070A
40 230A D5237180220000 .. SLEEVE VFAPE3 002
used on 070A
40 240A NSA5031-3-3 . BOLT VF5442 004
F0188, F6167, F7411, K5673, K8753
used on 001A, 001B, 001C
40 250A NAS1149C0332R . WASHER V80205 004
C5729
used on 001A, 001B, 001C
40 - 260A D52373060000CTD . SHAFT ASSY-SEQUENCE VFAPE3 001
used on 001A, 001B, 001C
SEE 52-31-19-410 FOR DET
Page 10040-3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
420 400
360 410
430
200
290 210
300
250
460
440
370
380 450
310 220
390
230
280
260 280
270
330 290
300 460
240
290
340 180
350 170
30
320 40 130
20
150 400
140 410
190
370 150
380
10 390 370
120 380
390
70
160
40
50
60
90
100
110
80
F_PL_523119_41_0_01_00
SHAFT ASSY-SEQUENCE
Figure 41 / FIGURE-52-31-19-950-841-01
Page 10041-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
41 - 001A D52373060000CTD SHAFT ASSY-SEQUENCE VFAPE3 RF
used on 260A (523119400)
SEE 52-31-19-400 FOR NHA
41 010A D5237330600000 . LINK ASSY VFAPE3 001
used on 001A
41 020A D5237153120200 .. FORK VFAPE3 001
used on 010A
41 030A NAS509L3C .. NUT V80205 001
Optional Vendor Code 01673, 04795, 06329, 2N935,
60996, 8K160, 92595, C5543
used on 010A
41 040A SP108D .. WASHER-TAB VK7766 002
used on 010A
41 050A NAS509-3C .. NUT V80205 001
60996, 8K160, 92595, C5543
used on 010A
41 060A D5237152620200 .. FORK VFAPE3 001
used on 010A
41 070A D5237153420200 .. SLEEVE VFAPE3 001
used on 010A
41 080A NSA5031-3D7 .. BOLT VF5442 001
F0188, F6167, F7411, K5673, K8753
used on 010A
41 090A NAS1149C0332R .. WASHER V80205 001
C5729
used on 010A
41 100A NSA5059E3 .. NUT VF5442 001
OPT TO 73783CM8-328 56878
F2094
used on 010A
41 110A MS24665-88 .. PIN-COTTER V96906 001
84114, 8K160, C5543
used on 010A
41 120A D5237152820000 .. ROD VFAPE3 001
used on 010A
Page 10041-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
41 130A D5237336800000 .. LEVER ASSY VFAPE3 001
used on 010A
41 140A D5237330720000 ... LEVER VFAPE3 001
used on 130A
used on 130A
41 160A D5237153320000 ... BUSHING VFAPE3 001
used on 130A
41 170A D5237111920200 . SUPPORT-FITTING VFAPE3 001
used on 001A
41 180A DAN5-5-5 . PIN-RIVET VD8518 002
OPT TO ABS0250A5-5 FAPE3
OPT TO F0N2-1196-5-5 56878
OPT TO HL10VDF5-5 92215
Optional Vendor Code 04795, 2N935, 56878, 73197,
C5543, D1283, F0188, K5673
used on 001A
41 190A NSA5075-5 . COLLAR VF5442 002
OPT TO DAN11-5 D8518
OPT TO F0N2-1181-5 H1822
OPT TO HL70AA5 92215
C5543, R1120
used on 001A
41 200A D5237186400000 . SHAFT ASSY-SEQUENCE VFAPE3 001
used on 001A
41 210A D5237186520000 .. SHAFT-SEQUENCE VFAPE3 001
used on 200A
41 220A D5237186700000 .. LEVER ASSY-SERRATED VFAPE3 001
used on 200A
41 230A D5237186720000 ... LEVER-SERRATED VFAPE3 001
used on 220A
41 240A MS14102-4K ... BEARING V96906 001
K5269, S0352
used on 220A
41 250A D5237151220800 .. CAM-LOCKING VFAPE3 001
used on 200A
41 260A D5237186820000 .. LEVER-LINK VFAPE3 001
used on 200A
41 270A D5237153320000 .. BUSHING VFAPE3 001
used on 200A
Page 10041-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
41 280A DAN15-6-18 . PIN-RIVET VD8518 002
OPT TO HL20PB6-18 73197
used on 001A
41 290A NAS1149C0332R . WASHER V80205 004
C5729
used on 001A
41 300A NAS1291C3M . NUT V80205 003
OPT TO H42-3 15653
F0224
used on 001A
41 310A DAN15-6-16 . PIN-RIVET VD8518 001
OPT TO HL20PB6-16 92215
C5543, D1283, F0188, K5673
used on 001A
41 320A NSA5031-3D7 . BOLT VF5442 001
F0188, F6167, F7411, K5673, K8753
used on 001A
41 330A D5237153420200 . SLEEVE VFAPE3 001
used on 001A
41 340A NSA5059E3 . NUT VF5442 001
OPT TO 73783CM8-328 56878
F2094
used on 001A
41 350A MS24665-88 . PIN-COTTER V96906 001
84114, 8K160, C5543
used on 001A
41 360A D5237186620000 . LEVER-SERRATED VFAPE3 001
used on 001A
41 370A MS24665-151 . PIN-COTTER V96906 003
84114, 8K160, C5543
used on 001A
41 380A NSA5059E4 . NUT VF5442 003
OPT TO 73783CM8-428 56878
F0188
Page 10041-3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 001A
41 390A NAS1149C0463R . WASHER V80205 003
C5543
used on 001A
41 400A NAS1149C0432R . WASHER V80205 002
C5543
used on 001A
41 410A NSA5031-4D11 . BOLT VF5442 002
F0188, F6167, F7411, K5673, K8753
used on 001A
41 420A A5227148120200 . SCREW VFAPE3 001
used on 001A
41 430A NSA5355-4CA . WASHER-LOCK VF5442 001
F7395, F7756
used on 001A
41 440A D5237180300200 . ROD ASSY-CONNECTING VFAPE3 001
used on 001A
41 450A D5237180320200 .. ROD-CONNECTING VFAPE3 001
used on 440A
41 460A MS14102-4K .. BEARING V96906 002
K5269, S0352
used on 440A
Page 10041-4
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
A
60 280
70 290
300
50
A 270 60
260 70 60
300 70
240
110
160
210
50
220
250
40
180
190
200 80
30
20
170 10
80
110 230
160 90
100
110
160
150 130
120 140
F_PL_523119_44_0_01_00
MECHANISM-INTERLOCK
Figure 44 / FIGURE-52-31-19-950-844-01
Page 10044-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
44 - 001A D5237306000065 MECHANISM-INTERLOCK VFAPE3 RF
used on 050A (523119050)
SEE 52-31-19-050 FOR NHA
44 010A D5237145500000 . SLEEVE ASSY-SPRING VFAPE3 001
used on 001A
44 020A D5237145620000 .. SLEEVE-SPRING VFAPE3 001
used on 010A
44 030A D5237145820400 .. BUSHING VFAPE3 001
used on 010A
44 040A D5237148220000 . SPRING-COMPRESSION VFAPE3 001
used on 001A
44 050A MS20392-3T49 . PIN V96906 002
Optional Vendor Code 04795, 06329, 2N935, 6D833,
70347, C5543, F0188, H2776
used on 001A
44 060A MS24665-151 . PIN-COTTER V96906 003
84114, 8K160, C5543
used on 001A
44 070A NAS1149C0463R . WASHER V80205 003
C5543
used on 001A
used on 001A
44 090A D5237145000400 . MECHANISM-INTERLOCK VFAPE3 001
used on 001A
44 100A D5237147620200 .. LEVER VFAPE3 001
used on 090A
44 110A D5237148320400 .. PIN VFAPE3 003
used on 090A
44 120A MS16624-5018-1 .. RING-RETAINING V96906 001
C5543
used on 090A
44 130A D5237147820000 .. PIN VFAPE3 001
used on 090A
44 140A D5237147720000 .. ROLLER VFAPE3 001
used on 090A
44 150A D5237179420000 .. ROD-CONNECTING VFAPE3 001
used on 090A
Page 10044-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
44 160A NSA5321-6 .. RING-RETAINING VF5442 003
OPT TO ST6 D8090
used on 090A
44 170A D5237146620400 .. LEVER VFAPE3 001
used on 090A
44 180A D5237113420600 .. SCREW-ADJUSTING VFAPE3 001
used on 090A
44 190A NAS509-5C .. NUT V80205 001
used on 090A
44 200A A5217026320200 .. PLATE-LOCKING VFAPE3 001
used on 090A
44 210A D5237146120200 .. BOLT VFAPE3 001
used on 090A
44 220A NAS1149C0432R . WASHER V80205 001
C5543
used on 001A
44 230A D5237145821000 . BUSHING VFAPE3 001
used on 001A
44 240A NSA5059E4 . NUT VF5442 001
OPT TO 73783CM8-428 56878
F0188
used on 001A
44 250A NAS1304-23D . BOLT V80205 001
NAS6604D23 80205
used on 001A
44 260A NAS1306-22D . BOLT V80205 001
NAS6606D22 80205
C5543, F0188, K8753
used on 001A
44 270A D5237145821200 . BUSHING VFAPE3 001
used on 001A
44 280A MS24665-300 . PIN-COTTER V96906 001
84114, 8K160, C5543
used on 001A
Page 10044-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
44 290A NSA5059E6 . NUT VF5442 001
OPT TO 73783CM8-624 56878
F0188
used on 001A
44 300A NAS1149C0663R . WASHER V80205 002
60996, 70347, 8K160, C5543
used on 001A
Page 10044-3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
40 A
50
20
30
80
70
110
120
50
60
120
130
90
90
100
10
F_PL_523119_50_0_01_00
HOUSING-VALVE
Figure 50 / FIGURE-52-31-19-950-850-01
Page 10050-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
50 - 001A D5237300000660 HOUSING-VALVE VFAPE3 RF
used on 060A (523119010)
SEE 52-31-19-010 FOR NHA
50 010A DAN79-07 . HOSE VFAPE3 001
REQUIRED LENGTH 400 MM
Optional Vendor Code C5543, U1901
used on 001A
50 020A ABS0341-1-01 . RETAINER-VALVE VFAPE3 001
OPT TO 140N2021-1H 57336
used on 001A
50 030A ABS0341-2-02 . VALVE VFAPE3 001
OPT TO 140N2022S1 57336
used on 001A
50 040A NAS1100E08-12 . SCREW V80205 002
used on 001A
50 050A NAS1149CN832R . WASHER V80205 004
OPT TO 7283A04-230 B0014
C5543
used on 001A
50 060A NAS1291C08M . NUT V80205 002
OPT TO 180003-08 60119
OPT TO FN1014M832 56878
OPT TO H42L08 K6405
OPT TO RMLH3858-82 72962
OPT TO T99C832M 11815
OPT TO VN300D82 92215
Optional Vendor Code 04795, 06329, 60996, 8K160,
C5543, C5729, H2776
used on 001A
50 070A D5237183120000 . FLANGE VFAPE3 001
used on 001A
50 080A D5237183020000 . TUBE VFAPE3 001
used on 001A
Page 10050-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
50 090A NSA935401-04 . TIE-CABLE VF5442 002
OPT TO 32015 F2693
OPT TO 32254 F2693
OPT TO PLT1-5I30 06383
OPT TO SST1-5I30 06383
OPT TO T30RHS D8527
used on 001A
50 100A NSA935504-01 . BRACKET VF5442 001
OPT TO 00326110059 F0394
Optional Vendor Code 04795, 2N935, 42C51, C5543
used on 001A
50 110A NAS1303-3 . BOLT V80205 001
NAS6603-3 80205
used on 001A
50 120A NAS1149C0332R . WASHER V80205 002
C5729
used on 001A
50 130A NAS1291C3M . NUT V80205 001
OPT TO H42-3 15653
F0224
used on 001A
Page 10050-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
20
A B
A
280
50 290
10 250
C 260
240
270
B 350
320
270
70
C 290
330 310 300

330
350
340 G
350 340
340 D 350
350
350
E
F 350
200
90
360 150
370
160
F G D
170
90
120
E 80
130 F
180 G
120
190
F_PL_523119_60_0_01_00
ELECTRIC SYSTEM
Figure 60 / FIGURE-52-31-19-950-860-01
Page 10060-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
60 - 001A D9209031102060 ELECTRIC SYSTEM VFAPE3 RF
used on 070A (523119010)
SEE 52-31-19-010 FOR NHA
60 - 001B D9209031102061 ELECTRIC SYSTEM VFAPE3 RF
POST SB 33-1058
used on 070B (523119010)
SEE 52-31-19-010 FOR NHA
60 010A D9299741100200 . HARNESS-CABLE,4611VB VFAPE3 001
used on 001A
60 010B D9299741100400 . HARNESS-CABLE,4611VB VFAPE3 001
used on 001B
60 020A EN2997SE61624AN .. CONNECTOR-PLUG VI9005 001
EN2997SE61624CN I9005
OPT TO 6TBD100550 14283
OPT TO 85333ES16-24PNL F0225
OPT TO 9836SE16-24PNL F1983
OPT TO E0442SE16-24PNA F5442
used on 010A, 010B
60 - 030A EN3155-018M2018 .. CONTACT VI9005 024
OPT TO 006-0044-20A F1983
OPT TO 050-0001-2018 14283
OPT TO 330-7587-000 F3132
OPT TO 8522-2349A F0225
OPT TO B6320 S5540
used on 010A, 010B
60 - 040A E0616BB2000 .. PLUG VF5442 020
OPT TO 8522-389A F0225
OPT TO NSA938153BB2000 F5442
OPT TO SB2034 F0225
used on 010A, 010B
60 - 045A NSA935401-03 .. TIE-CABLE VF5442 008
OPT TO 32012 F2693
OPT TO 32251 F2693
OPT TO PLT1M30 06383
OPT TO SST1M30 06383
OPT TO T18RHS D8527
D8527
Page 10060-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 010A, 010B
60 050A E0115A12-16-3 .. ELBOW VF5442 001
OPT TO T9312-12 K0685
used on 010A, 010B
60 - 060A DAN79-05 .. HOSE VFAPE3 AR
USE AS REQUIRED
used on 010A, 010B
60 - 065A NSA935805-12 .. ELECTRICAL CONDUIT VF5442 AR
USE AS REQUIRED
OPT TO C10000-0-0-24 81482
OPT TO GC100-12 F0564
OPT TO SF001-00-00-12 F6101
Optional Vendor Code C5543
used on 010A, 010B
60 070A D9299741000200 . HARNESS-CABLE,4610VB VFAPE3 001
used on 001A
60 070B D9299741000400 . HARNESS-CABLE,4610VB VFAPE3 001
used on 001B
60 080A EN3646A6083ADN .. CONNECTOR-PLUG VI9005 001
OPT TO 6TBD101465 F0225
OPT TO 6TBD101466 F1983
OPT TO 7TBD101554 F1983
OPT TO 7TBD102262 F0225
OPT TO E0052R8B3ASNE F5442
used on 070A, 070B
60 090A ABS0638A08 .. BACKSHELL-CONNECTOR VFAPE3 003
OPT TO GK5430 C3471
used on 070A, 070B
60 - 100A EN3155-019F2018 .. CONTACT-SOCKET VI9005 006
OPT TO 006-0055-20A F1983
OPT TO 031-7741-000 F3132
OPT TO 050-1001-2018 14283
OPT TO 8520-292 F0225
OPT TO B6321 S5540
used on 070A, 070B
Page 10060-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
60 - 110A E0616BB2000 .. PLUG VF5442 034
OPT TO 8522-389A F0225
OPT TO NSA938153BB2000 F5442
OPT TO SB2034 F0225
used on 070A, 070B
60 120A ABS0638B08 .. BACKSHELL-CONNECTOR VFAPE3 003
OPT TO GK5440 C3471
used on 070A, 070B
60 130A E0073-8-3AT .. SEAL-PRESSURE VF5442 001
OPT TO DTP07-8-3AK F1983
OPT TO PVW77-8-98-57 K0316
used on 070A, 070B
60 - 140A NSA934701BU2000 .. PLUG-BLIND VF5442 002
OPT TO DF90-006-20 F1983
Optional Vendor Code D8518
used on 070A, 070B
60 150A A5217240234400 .. WASHER-SPECIAL VFAPE3 002
used on 070A, 070B
60 160A D9249550120000 .. PLATE-MOUNTING VFAPE3 002
used on 070A, 070B
60 170A D9249550220000 .. WASHER VFAPE3 002
used on 070A, 070B
60 180A E0073-8-3AT .. SEAL-PRESSURE VF5442 001
OPT TO DTP07-8-3AK F1983
OPT TO PVW77-8-98-57 K0316
used on 070A, 070B
60 190A EN3646A6083ADN .. CONNECTOR-PLUG VI9005 001
OPT TO 6TBD101465 F0225
OPT TO 6TBD101466 F1983
OPT TO 7TBD101554 F1983
OPT TO 7TBD102262 F0225
OPT TO E0052R8B3ASNE F5442
used on 070A, 070B
60 200A D9269000400200 .. BLOCK-TERMINAL VFAPE3 001
used on 070A, 070B
SEE 52-31-19-630 FOR DET
Page 10060-3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
60 - 210A EN3155-016M2018 .. CONTACT VI9005 004
OPT TO 00110421002 F0394
OPT TO 123-0001-20 F1983
OPT TO NSA937910EA2000 F5442
OPT TO SB2029 F0225
F0394, F1983, F3132
used on 070A, 070B
60 - 220A NSA935401-03 .. TIE-CABLE VF5442 024
OPT TO 32012 F2693
OPT TO 32251 F2693
OPT TO T18RHS D8527
D8527
used on 070A, 070B
60 - 230A NSA935805-04 .. ELECTRICAL CONDUIT VF5442 AR
USE AS REQUIRED
OPT TO C10000-0-0-08 81482
OPT TO GC100-04 F0564
OPT TO SC001-0-0-04 K0685
OPT TO SF001-00-00-04 F6101
Optional Vendor Code C5543
used on 070A, 070B
60 240A NSA935807-12 . CLAMP VF5442 001
OPT TO 50011-12 F6101
F0355
used on 001A, 001B
60 250A NSA5527-03-03 . SPACER VF5442 001
used on 001A, 001B
60 260A NAS1096-2-29 . SCREW V80205 001
NAS1801-08-29 80205
K8753
used on 001A, 001B
60 270A NAS1149DN816K . WASHER V80205 003
56563, 60996, 70347, 8K160, C5543
Page 10060-4
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 001A, 001B
60 280A NSA935808-01 . WASHER VF5442 001
OPT TO 3732-109 C7100
OPT TO 50012-1-31 F6101
OPT TO 715120001 F0355
used on 001A, 001B
60 290A MS21042L08 . NUT V96906 003
OPT TO AS8600C K4975
OPT TO BH21042L08 27238
OPT TO EH14L08 15653
OPT TO H14L08 15653
OPT TO RH30A08 52828
OPT TO RM52LH3324-82 72962
OPT TO T98S832 11815
OPT TO VN300A82 92215
75237, 8K160, C5543
used on 001A, 001B
60 300A NSA5527-03-01 . SPACER VF5442 002
Optional Vendor Code F8982
used on 001A, 001B
60 310A NAS1096-2-14 . SCREW V80205 002
NAS1801-08-14 80205
K8753
used on 001A, 001B
60 320A NSA935513-07 . MOUNT VF5442 001
OPT TO TY5K7HS D8527
used on 001A, 001B
60 330A NSA935513-05 . MOUNT VF5442 011
used on 001A, 001B
60 340A NSA935513-01 . MOUNT-CABLE VF5442 005
OPT TO TY5K1HSNAT K0720
used on 001A, 001B
Page 10060-5
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
60 350A NSA931025-03A . LABEL VF5442 007
OPT TO ABS0724-006-020 FAPE3
F0347, F4240, F8421
used on 001A, 001B
60 360A NAS1096-2-8 . SCREW V80205 004
NAS1801-08-8 80205
K8753
used on 001A, 001B
60 370A NAS1149CN832R . WASHER V80205 004
OPT TO 7283A04-230 B0014
C5543
used on 001A, 001B
60 - 380A D9239125401260 . SENSOR-DOOR VFAPE3 001
used on 001A, 001B
SEE 52-31-19-620 FOR DET
60 - 390A NSA935401-03 . TIE-CABLE VF5442 025
OPT TO 32012 F2693
OPT TO 32251 F2693
OPT TO T18RHS D8527
D8527
used on 001A, 001B
Page 10060-6
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
B
C A
20
C 50
60
50
60
10 40
40
B
50
60
10
20 30
30
40
50 20
60
F_PL_523119_62_0_01_00
SENSOR-DOOR
Figure 62 / FIGURE-52-31-19-950-862-01
Page 10062-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
62 - 001A D9239125401260 SENSOR-DOOR VFAPE3 RF
used on 380A (523119600)
SEE 52-31-19-600 FOR NHA
62 010A 8-933-01 . SENSOR-PROXIMITY V08748 002
OPT TO 201655069 K0654
OPT TO ABS0121-40 FAPE3
OPT TO H10468642SC U7388
used on 001A
62 020A 8-368-04 . SENSOR-PROXIMITY V08748 003
OPT TO 666000078 K0654
OPT TO ABS0121-11 FAPE3
used on 001A
62 030A NAS1096-3-8 . SCREW V80205 004
NAS1801-3-8 80205
F7411, K8753
used on 001A
62 040A NAS1096-3-7 . SCREW V80205 006
NAS1801-3-7 80205
Optional Vendor Code F0188, K8753
used on 001A
62 050A NAS1149C0332R . WASHER V80205 008
C5729
used on 001A
62 060A NAS1291C3M . NUT V80205 008
OPT TO H42-3 15653
F0224
used on 001A
Page 10062-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
20
40
30
20
10
F_PL_523119_63_0_01_00
BLOCK-TERMINAL
Figure 63 / FIGURE-52-31-19-950-863-01
Page 10063-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
63 - 001A D9269000400200 BLOCK-TERMINAL VFAPE3 RF
used on 200A (523119600)
SEE 52-31-19-600 FOR NHA
63 010A NSA937901RB0100 . RAIL VF5442 001
F1983
used on 001A
63 020A NSA937901S . CLAMP-END VF5442 002
OPT TO 00110201060 F0394
OPT TO 020-0020-00 F1983
used on 001A
63 030A NSA937901M20-01 . MODULE VF5442 002
OPT TO 001115-201-02 F0394
OPT TO 00111520103 F0394
OPT TO 208-2B01 F4250
OPT TO 8559E2001 F0225
OPT TO FMJ11E20-01K F1983
used on 001A
63 040A NSA937901M20-09 . MODULE VF5442 002
OPT TO 001115-209-02 F0394
OPT TO 00111520903 F0394
OPT TO 208-2B09 F4250
OPT TO 8559E2009 F0225
OPT TO FMJ11E20-09K F1983
used on 001A
Page 10063-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
30
50 40 150
C A 220
180
230
150
A 150 210
200
B
220
160
170 150
C 100
110
170
160 190 160
170 170
120
140
130 170
190
10 B 90
80
20
120 60
140
240
70 230 200
100
110
120
140
170
190 130
170
190
120
140
120
140
F_PL_523119_90_0_01_00
HINGE INSTL
Figure 90 / FIGURE-52-31-19-950-890-01
Page 10090-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
90 - 001A D5237300500061 HINGE INSTL VFAPE3 RF
used on 010A (523119040)
SEE 52-31-19-040 FOR NHA
90 010A D5237114720500 . FITTING-END VFAPE3 001
used on 001A
90 020A D5237120220600 . SHIM VFAPE3 001
used on 001A
90 030A D5237114001500 . HINGE ASSY VFAPE3 001
used on 001A
90 040A D5237114120900 .. HINGE-OUTER VFAPE3 001
used on 030A
90 050A D5237113820600 .. BUSHING VFAPE3 005
used on 030A
used on 001A
90 070A D5237303320100 .. HINGE-INNER VFAPE3 001
used on 060A
90 080A D5237113820600 .. BUSHING VFAPE3 008
used on 060A
used on 060A
90 100A NSA5030-3-9 . SCREW VF5442 011
ASNA2001V3-9 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
90 110A NAS1149C0363R . WASHER V80205 011
70347, 8K160, C5543
used on 001A
90 120A NAS1291C3M . NUT V80205 032
OPT TO H42-3 15653
F0224
used on 001A
90 130A NSA5030-3-8 . SCREW VF5442 011
ASNA2001V3-8 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
USE AS REQUIRED
Page 10090-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
C5729
used on 001A
90 150A NSA5030-4-9 . SCREW VF5442 007
ASNA2001V4-9 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
90 160A NAS1149C0432R . WASHER V80205 011
C5543
used on 001A
90 170A NAS1291C4M . NUT V80205 023
OPT TO 180003-5 60119
used on 001A
90 180A NSA5030-4-11 . SCREW VF5442 001
ASNA2001V4-11 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
90 190A NAS1149C0463R . WASHER V80205 012
C5543
used on 001A
90 200A NSA5030-4-12 . SCREW VF5442 008
ASNA2001V4-12 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
90 210A NSA5030-4-10 . SCREW VF5442 001
ASNA2001V4-10 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
90 220A NSA5030-4-8 . SCREW VF5442 002
ASNA2001V4-8 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
90 230A NAS1154-11 . SCREW V80205 004
Page 10090-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 001A
90 240A NSA5030-3-7 . SCREW VF5442 010
ASNA2001V3-7 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
90 - 250A D52373005000CTD . STRUCTURE-DOOR VFAPE3 001
used on 001A
SEE 52-31-19-910 FOR DET
Page 10090-3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
40
A
240
150
A 180
210
B
C
100
110
120
140 30
10
160
170 130
20
160
170
120
140
100
50 B
C 110 120
140
70 60
150
230
200
220
130
220 150 150
120 180
140 150
210
90
80
160
170
120
140 170
190
160
170
170 160
190 170
F_PL_523119_91_0_01_00
STRUCTURE-DOOR
Figure 91 / FIGURE-52-31-19-950-891-01
Page 10091-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
91 - 001A D52373005000CTD STRUCTURE-DOOR VFAPE3 RF
used on 250A (523119900)
SEE 52-31-19-900 FOR NHA
used on 001A
91 020A D5237303320000 .. HINGE-MID VFAPE3 001
used on 010A
91 030A D5237113820600 .. BUSHING VFAPE3 008
used on 010A
used on 010A
used on 001A
91 060A D5237114120800 .. HINGE-OUTER VFAPE3 001
used on 050A
91 070A D5237113820600 .. BUSHING VFAPE3 005
used on 050A
91 080A D5237120220600 . SHIM VFAPE3 001
used on 001A
91 090A D5237114720400 . FITTING-END VFAPE3 001
used on 001A
91 100A NSA5030-3-9 . SCREW VF5442 011
ASNA2001V3-9 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
91 110A NAS1149C0363R . WASHER V80205 011
70347, 8K160, C5543
used on 001A
91 120A NAS1291C3M . NUT V80205 032
OPT TO H42-3 15653
F0224
used on 001A
91 130A NSA5030-3-8 . SCREW VF5442 011
ASNA2001V3-8 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
USE AS REQUIRED
Page 10091-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
C5729
used on 001A
91 150A NSA5030-4-9 . SCREW VF5442 009
ASNA2001V4-9 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
91 160A NAS1149C0432R . WASHER V80205 017
C5543
used on 001A
91 170A NAS1291C4M . NUT V80205 023
OPT TO 180003-5 60119
used on 001A
91 180A NSA5030-4-11 . SCREW VF5442 003
ASNA2001V4-11 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
91 190A NAS1149C0463R . WASHER V80205 006
C5543
used on 001A
91 200A NSA5030-4-12 . SCREW VF5442 004
ASNA2001V4-12 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
91 210A NSA5030-4-10 . SCREW VF5442 003
ASNA2001V4-10 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
91 220A NSA5030-4-8 . SCREW VF5442 002
ASNA2001V4-8 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
91 230A NAS1154-11 . SCREW V80205 002
Page 10091-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 001A
91 240A NSA5030-3-7 . SCREW VF5442 010
ASNA2001V3-7 F5442
F0188, F6167, F7411, K5673, K8753
used on 001A
Page 10091-3
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
C A B
40 A
120 B
80 A 60 A
140 B
B
A
70 A 20 A
150 B 100 B
30 A
110 B
A 40 A
50
B 120B
130
20 A
100 B
D
190
C
170
F_PL_523119_96_0_01_00
BUSHING INSTL-DOOR STRUCTURE

Figure 96 / FIGURE-52-31-19-950-896-01
Page 10096-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
96 - 001A D5237300500063 BUSHING INSTL-DOOR STRUCTURE VFAPE3 RF
used on 040A (523119040)
SEE 52-31-19-040 FOR NHA
96 - 010A D5237302000260 . FRAME ASSY (NP) 001
used on 001A
96 020A D5237112920200 .. BUSHING VFAPE3 002
used on 001A
used on 001A
used on 001A
96 050A D5237112820200 .. BUSHING VFAPE3 001
used on 001A
used on 001A
used on 001A
96 080A D5237183220000 .. SPACER VFAPE3 002
used on 001A
96 - 090A D5237302100260 . FRAME ASSY (NP) 001
used on 001A
96 100A D5237112920200 .. BUSHING VFAPE3 002
used on 001A
used on 001A
used on 001A
96 130A D5237112820200 .. BUSHING VFAPE3 001
used on 001A
used on 001A
used on 001A
96 - 160A D5237304600060 . BEAM-4 (NP) 001
used on 001A
96 170A NSA5054-3 .. INSERT VF5442 004
OPT TO K8000-3 K6405
OPT TO M45932-1-9AL 81349
used on 001A
96 - 180A D5237182500061 . BEAM ASSY-3,FWD (NP) 001
used on 001A
Page 10096-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 001A
96 - 200A D5237300500064 . BUSHING INSTL-DOOR STRUCTURE VFAPE3 001
used on 001A
SEE 52-31-19-970 FOR DET
Page 10096-2
52-31-19 Jul 01/12
@AIRBUS
D5237300000600
A B 150 B
40 A
110 B
60 A
130 B
D
C E
F
70 A 20 A
140 B 90 B
B 30 A
A 100 B
50 A 40 A
120 B 110 B
210
20 A C
F 90 B 260
200
170
190
E 280 D
230
240
F_PL_523119_97_0_01_00
BUSHING INSTL-DOOR STRUCTURE

Figure 97 / FIGURE-52-31-19-950-897-01
Page 10097-0
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
97 - 001A D5237300500064 BUSHING INSTL-DOOR STRUCTURE VFAPE3 RF
used on 200A (523119960)
SEE 52-31-19-960 FOR NHA
97 - 010A D5237302200260 . FRAME ASSY (NP) 001
used on 001A
97 020A D5237112920200 .. BUSHING VFAPE3 002
used on 001A
used on 001A
used on 001A
97 050A D5237112820200 .. BUSHING VFAPE3 001
used on 001A
used on 001A
used on 001A
97 - 080A D5237302300260 . FRAME ASSY (NP) 001
used on 001A
97 090A D5237112920200 .. BUSHING VFAPE3 002
used on 001A
used on 001A
used on 001A
97 120A D5237112820200 .. BUSHING VFAPE3 001
used on 001A
used on 001A
used on 001A
97 150A D5237179320000 .. BUSHING VFAPE3 001
used on 001A
97 - 160A D5237174700060 . SEGMENT-FRAME,FWD VFAPE3 001
used on 001A
used on 160A
97 - 180A D5237174800060 . SEGMENT-FRAME,AFT VFAPE3 001
used on 001A
used on 180A
Page 10097-1
52-31-19 Jul 01/12
@AIRBUS
D5237300000600

1234567 FROM PER
TO ASSY
used on 180A
97 210A NSA5054-3 .. INSERT VF5442 002
OPT TO K8000-3 K6405
OPT TO M45932-1-9AL 81349
used on 180A
97 - 220A D5237174200260 . BEAM ASSY-4 VFAPE3 001
used on 001A
97 230A D5237178720000 .. BUSH-GUIDE VFAPE3 001
used on 220A
97 240A NSA5054-3 .. INSERT VF5442 001
OPT TO K8000-3 K6405
OPT TO M45932-1-9AL 81349
used on 220A
97 - 250A D5237182600060 . BEAM ASSY-3,MID VFAPE3 001
used on 001A
used on 250A
97 - 270A D5237182400060 . BEAM ASSY-2A VFAPE3 001
used on 001A
used on 270A
Page 10097-2
52-31-19 Jul 01/12

@airbus: Component Maintenance Manual With Illustrated Part List

Uploaded by

Copyright:

Available Formats

@airbus: Component Maintenance Manual With Illustrated Part List

Uploaded by

Document Information

Original Description:

Original Title

Copyright

Available Formats

Share this document

Share or Embed Document

Sharing Options

Did you find this document useful?

Is this content inappropriate?

Copyright:

Available Formats

@airbus: Component Maintenance Manual With Illustrated Part List

Uploaded by

Copyright:

Available Formats

@AIRBUS

COMPONENT MAINTENANCE MANUAL

FWD CARGO COMPARTMENT DOOR

Issue: Nov 01/04 52-31-19 Rev: Jul 01/12

Revision No. 8 - Jul 01/12

LOCATIONS CHG DESCRIPTIONS OF CHANGE

LIST OF EFFECTIVE CONTENT

Revision No. 8 - Jul 01/12

CONTENT CHG LAST REVISION

DESCRIPTION AND OPERATION

TESTING AND FAULT ISOLATION

SCHEMATIC AND WIRING DIAGRAMS

CONTENT CHG LAST REVISION

CONTENT CHG LAST REVISION

CONTENT CHG LAST REVISION

CONTENT CHG LAST REVISION

CONTENT CHG LAST REVISION

CONTENT CHG LAST REVISION

FITS AND CLEARANCES

SPECIAL TOOLS,FIXTURES,EQUIPMENT AND CONSUMABLES

STORAGE INCLUDING TRANSPORTATION

ILLUSTRATED PARTS LIST

CONTENT CHG LAST REVISION

CONTENT CHG LAST REVISION

CONTENT CHG LAST REVISION

DESCRIPTION AND OPERATION

TESTING AND FAULT ISOLATION

SCHEMATIC AND WIRING DIAGRAMS

52-31-19-400-818-A01 Installation of the Hinge Assemblies

FITS AND CLEARANCES

SPECIAL TOOLS,FIXTURES,EQUIPMENT AND CONSUMABLES

STORAGE INCLUDING TRANSPORTATION

ILLUSTRATED PARTS LIST

LIST OF SERVICE BULLETINS

SB No REV No MOD No INCORP. TITLE

**For PN’s ALL

FIN Functional Item Number

DESCRIPTION AND OPERATION

**For PN’s ALL

**For PN’s ALL

NOTE : Refer to FIGURE 52-31-19-991-001-A and FIGURE 52-31-19-991-002-A.

2. Door Mechanism (Refer to FIGURE 52-31-19-991-001-A and FIGURE 52-31-19-991-002-A)

NOTE : Refer to FIGURE 52-31-19-991-003-A and TASK 52-31-19-878-805-A01.

NOTE : For data of the proximity sensors refer to CMMV 32-10-03.

NOTE : Refer to FIGURE 52-31-19-991-003-A and TASK 52-31-19-878-805-A01.

**For PN’s ALL

FWD Cargo Compartment Door

**For PN’s ALL

FWD Cargo Compartment Door

**For PN’s ALL

Electrical Equipment Installation

**For PN’s ALL

**For PN’s ALL

FWD Cargo Compartment Door

**For PN’s ALL

FWD Cargo Compartment Door

TESTING AND FAULT ISOLATION

**For PN’s ALL