-
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
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊(cè) AMM FUSELAGE 機(jī)身3(122)