(2)
Open the access doors 811 and 824.
EFF : ALL
53-12-13Page 401
4. Procedure
_________
Subtask 53-12-13-020-050
A. Removal of the FWD Avionics-Compartment Floor-Panels
(Ref. Fig. 401/TASK 53-12-13-991-001)
(1)
Find one of the ends of the synthetic fiber cord (5) at one of the floor panel joints.
(2)
Pull the cord (5) up to remove the sealant from between the floor panels (4).
(3)
Remove the screws (1).
(4)
Remove the stiffener (2).
(5)
Remove the screws (3).
(6) Remove the panels (4). Subtask 53-12-13-020-051
B. Removal of the AFT Avionics-Compartment Floor-Panels
(Ref. Fig. 402/TASK 53-12-13-991-002)
(1)
Remove the screws (28) and the washers (29).
(2)
Remove the sheet metal assembly (30).
(3)
Remove the screws (25) and the washers (26).
(4)
Remove the track (27).
(5)
Remove the screws (22) and the washers (23).
(6)
Remove the fitting (24).
(7)
Find one of the ends of the synthetic fiber cord at one of the floor panel joints.
(8)
Pull the cord up to remove the sealant from between the floor panels.
(9)
Remove the screws (11).
(10) Remove the panel (12).
EFF : ALL
53-12-13Page 402
FWD Avionics-Compartment Floor-Panels
Figure 401/TASK 53-12-13-991-001
EFF : ALL 53-12-13 Page 403
Feb 01/98
CES
AFT Avionics-Compartment Floor-Panels
Figure 402/TASK 53-12-13-991-002
EFF : ALL 53-12-13 Page 404
Feb 01/98
CES
(11)
Remove the screws (19) and the washers (18).
(12)
Remove the panels (20) and (21).
(13)
Remove the screws (13).
(14)
Remove the panels (14), (15), (16) and (17).
EFF : ALL
53-12-13Page 405
TASK 53-12-13-400-001
Installation of the avionics compartment floor panels
1. Reason for the Job
__________________
Self Explanatory
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific lint-free cloth
No specific non metallic scraper R No specific Torque Wrench : range 0.00 to 1.20 m.daN R (0.00 to 9.00 lbf.ft)
B. Consumable Materials
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 05-002 USA MIL-P-8116 PUTTY, ZINC CHROMATE GENERAL PURPOSE (Ref. 20-31-00)
Material No. 09-018 USA AMS 3267/3
CORROSION INHIBITING LOW ADHESION SEALANT
(Ref. 20-31-00)
Material No. 11-003 USA ASTM D 740 METHYL-ETHYL-KETONE (Ref. 20-31-00) Material No. 11-021 ADHESIVE REMOVER CARBON STRUCTURE (Ref. 20-31-00)
Material No. 19-002 USA MIL-T-713
SYNTHETIC FIBRE CORD (NYLON) 2.5MM DIA.
(Ref. 20-31-00)
EFF : ALL
53-12-13Page 406
C. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R 52-41-00-410-002 Close the Avionics Compartment Doors after Access 53-12-00-300-001 Repair of the Damaged Area of the Adhesive Tape 53-12-13-991-001 Fig. 401 53-12-13-991-002 Fig. 402
3. Job Set-up
__________
Subtask 53-12-13-869-050
A. Aircraft Maintenance Configuration
(1)
Make sure that the access platform is in position in zone 121/122 and
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM FUSELAGE 機身1(96)
