(2)
 Make sure that the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) is on the flap/slat control lever on panel 114VU.

 Subtask 27-84-45-865-097
 C. Open, safety and tag this(these) circuit breaker(s):
 -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 5CV B06 121VU FLIGHT CONTROLS/SLT/CTL/SYS2 7CV R21
 Subtask 27-84-45-010-060
 D. Get Access
 (1)
 Remove the access panels 191BB, 192FB (Ref. TASK 53-35-13-000-002).

 (2)
 Install the LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT (98D27504030001) (Ref. TASK 27-50-00-400-003): - on a torque shaft, indoard of the applicable component - on a torque shaft, outboard of the applicable component.

 1EFF : ALL 1 27-84-45Page 421 1 1 Feb 01/00R 1 1 1CES 1

 (3) Remove the applicable steady bearing (15) (Ref. TASK 27-84-44-000-001):
 -
FOR 6008CM
 remove the steady bearing FIN 6007CM

 -
FOR 6058CM
 remove the steady bearing FIN 6057CM.

 4. Procedure
_________
 (Ref. Fig. 401/TASK 27-84-45-991-001, 402/TASK 27-84-45-991-002)
 Subtask 27-84-45-020-052
 A. Removal of the Torque Shafts FIN 6008CM(6058CM)
 (1) Remove the retaining ring (18), the pin (12) and then the universal joint (13).
 1EFF : ALL 1 27-84-45Page 422 1 1 Feb 01/00R 1 1 1CES 1

 TASK 27-84-45-400-004
 Installation of the Torque Shaft 6008CM(6058CM)
 WARNING : MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING
_______
 NOTICES ARE IN POSITION.

 WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
_______
 GEAR.

 1. Reason for the Job
__________________
 Self Explanatory
 2. Job Set-up Information
______________________
 A. Fixtures, Tools, Test and Support Equipment
 -------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific safety barriers
 No specific warning notice
 No specific Torque Wrench : range 0.20 to 3.60 m.daN

 (2.00 to 26.00 lbf.ft) FOR FIN 6058CM 98D27504030001 2 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT
 B. Consumable Materials
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 04-018
 GENERAL PURPOSE ASSEMBLY PASTE (Ref. 20-31-00)

 Material No. 04-022  USA MIL-PRF-81322 GRADE 2
 SYNTHE.HYDROCARBON GREASE HIGH PRESSURE
 (Ref. 20-31-00)

 Material No. 11-026 GB DEF-STAN 68-148/1 R SOLVENT GENERAL PURPOSE (Ref. 20-31-00)
 Material No. 15-007  AIB TN 10138 TYPE II GRADE 1 CORROSION PREVENTIVE TEMPORARY PROTECTIVE COMPOUND (Ref. 20-31-00)
 Material No. 19-003  USA AMS 3819
 LINT-FREE COTTON CLOTH (Ref. 20-31-00)

 C. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
27-50-00-400-003 Installation of the Lock-Torque Shaft - Flaps and
 Slats (98D27504030001) 27-80-00-866-005 Retracting the Slats on the Ground 27-84-44-000-001 Removal of the Steady Bearing FIN 6007CM(6057CM) 27-84-44-400-001 Installation of the Steady Bearing FIN 6007CM(6057CM) 53-35-13-000-002 Removal of the Quick-Release Access Panels from the
 Belly Fairing Structure 53-35-13-400-002 Installation of the Quick-Release Access Panels on the Belly Fairing Structure 27-84-45-991-001 Fig. 401
R  27-84-45-991-002 Fig. 402 FOR FIN 6058CM 27-50-00-000-003 Removal of the Lock-Torque Shaft - Flaps and Slats
 (98D27504030001)
 3. Job Set-up
__________
 (Ref. Fig. 401/TASK 27-84-45-991-001)
 Subtask 27-84-45-941-060
 A. Safety Precautions
 (1)
 Make sure that the safety barriers are in position.

 (2)
 Make sure that the warning notice is in position to tell persons not to operate the slat controls.

 Subtask 27-84-45-860-053
 B. Aircraft Maintenance Configuration
 (1)
 Make sure that the slats are retracted fully (Ref. TASK 27-80-00-866-005).
　
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 FLIGHT CONTROLS 飛行操縱7(132)