-
THE LANDING GEAR AND THE RELATED DOORS
-COMPONENTS THAT MOVE.
(3)
Put the access platform in position below Zone 312.
(4)
Put the access platform in position below Zone 314.
(5)
Open the access doors 312AR and 314AR.
(6)
Remove the THS aprons (Ref. TASK 55-15-11-000-001).
(7) Remove the THS fairings (Ref. TASK 53-55-13-000-001). Subtask 53-53-11-864-050
B. Depressurize the Blue, Green and Yellow hydraulic systems (Ref. TASK 29-10-00-864-001), (Ref. TASK 29-10-00-864-002) and (Ref. TASK 29-10-00-864-003).
EFF : ALL
53-53-11Page 411
Subtask 53-53-11-865-053
C. Open, safety and tag this(these) circuit breaker(s):
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------
R R R R 49VU FLIGHT CONTROLS/ELAC1/NORM/SPLY 49VU FLIGHT CONTROLS/FCDC1/SPLY 49VU FLIGHT CONTROLS/THS/ACTR/MOT2 49VU FLIGHT CONTROLS/SEC1/NORM/SPLY 105VU FLIGHT CONTROLS/ELAC2/STBY SPLY 105VU FLT CTL/ELAC1/STBY SPLY 105VU FLT CTL/SEC1/STBY SPLY 121VU FLIGHT CONTROLS/FCDC2/SPLY 121VU FLIGHT CONTROLS/SEC3/SPLY 121VU FLIGHT CONTROLS/SEC2/SPLY 121VU FLIGHT CONTROLS/THS ACTR/MOT3 121VU FLIGHT CONTROLS/THS ACTR/MOT1 121VU FLIGHT CONTROLS/ELAC2/NORM/SPLY 15CE1 20CE1 19CE2 21CE1 16CE2 16CE1 22CE 20CE2 21CE3 21CE2 19CE3 19CE1 15CE2 B11B10B09B08 A02 A01 B01 Q20Q19Q18Q17Q16R20
4. Procedure_________
(Ref. Fig. 402/TASK 53-53-11-991-002)
Subtask 53-53-11-020-051
A. Removal:
(1) Remove the nuts (9), the washers (7) and the screws (6).
(2) Remove the bonding straps (8) and (10).
(3) Remove and discard the cotter pins (4).
(4) Remove the nuts (3) and the washers (2).
(5) Identify each support strut (5).
(6) Remove the bolts (1).
(7) Remove the support struts (5).
EFF : ALL
53-53-11Page 412
Diagonal Support Struts
Figure 402/TASK 53-53-11-991-002
EFF : ALL 53-53-11 Page 413
Feb 01/98
CES
TASK 53-53-11-400-002
Installation of the Diagonal Support Struts at STA3655/FR77
NOTE : The installation for one support strut is given. The procedure is the
____
same for the other support struts.
1. Reason for the Job
__________________
Self Explanatory
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------
No specific warning notice
No specific Torque Wrench : range 0.20 to 3.60 m.daN
(2.00 to 26.00 lbf.ft) No specific Torque Wrench : range 2.00 to 20.00 m.daN
(15.00 to 150.00 lbf.ft)
B. Consumable Materials
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
No specific corrosion-resistant steel lockwire 0.8 mm (0.032 in) dia.
R Material No. 04-004 USA MIL-PRF-23827 TYPE I SYNTH.ESTER BASED GREASE HIGH PRESSURE (Ref. 20-31-00) Material No. 15-007 AIB TN 10138 TYPE II GRADE 1 CORROSION PREVENTIVE TEMPORARY PROTECTIVE COMPOUND (Ref. 20-31-00)
C. Expendable Parts
-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------
cotter pins 53-53-04 02 -060
EFF : ALL
53-53-11Page 414
D. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
20-28-00-912-004 Electrical Bonding of Components With Conductive Bolts and Screws and Bonding Straps in the Fuselage
R and in the Wings (this does not include the tanks)-29-10-00-864-001 Depressurize the Green Hydraulic System 29-10-00-864-002 Depressurize the Yellow Hydraulic System 29-10-00-864-003 Depressurize the Blue Hydraulic System 51-75-13-916-002 Repair to a layer of Corrosion Preventive Compound 53-55-13-400-001 Installation of the Fairings at the THS Fittings. 55-15-11-400-001 Installation of the Apron 333AT/333AB/343AT/343AB 53-53-11-991-002 Fig. 402
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM FUSELAGE 机身3(122)
