R
R
R
C. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
27-50-00-400-003 Installation of the Lock-Torque Shaft - Flaps and
 Slats (98D27504030001) 27-80-00-866-004 Extending the Slats on the Ground 27-80-00-866-005 Retracting the Slats on the Ground 27-84-00-710-001 Operational Test of the Slat System 27-84-44-000-003 Removal of the Steady Bearing FIN 6021CM(6071CM) 27-84-44-400-003 Installation of the Steady Bearing FIN 6021CM(6071CM) 27-84-45-991-001 Fig. 401 27-84-45-991-002 Fig. 402
 3. Job Set-up
__________
 (Ref. Fig. 401/TASK 27-84-45-991-001)
 Subtask 27-84-45-941-066
 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 27-84-45-860-059
 B. Aircraft Maintenance Configuration
 (1)
 Make sure that the slats are extended fully (Ref. TASK 27-80-00-866-004).

 (2)
 Make sure that the LOCKING TOOL - FLAP/SLAT CONTROL LEVER is on to the flap/slat control lever.

(3)
 Make sure that a LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed (Ref. TASK 27-50-00-400-003): - on the torque shaft inboard of the applicable component - on the torque shaft outboard of the applicable component.

 (4)
 Make sure that the access platform is in position below the applicable access panel 521AT(621AT).

 (5) Make sure that the applicable access panels 521AT(621AT) are removed.
 (6) Make sure that the applicable steady bearings have been removed (Ref. TASK 27-84-44-000-003).
 Subtask 27-84-45-865-081
 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
 -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 5CV B06 121VU FLIGHT CONTROLS/SLT/CTL/SYS2 7CV R21
 4. Procedure_________ 
R R (Ref. Fig. 402/TASK 27-84-45-991-002) 
Subtask 27-84-45-420-079 
R  A. Preparation for Installation 
R R  CAUTION : DO NOT APPLY MORE THAN ONE TYPE OF LUBRICANT._______ GREASE AND ASSEMBLY PASTE DO NOT MIX.
R R  (1) Clean the component interface and/or the adjacent area with MISCELLANEOUS (Material No. 19-003) made moist with CLEANING AGENTS (Material No. 11-026).
 (2) Do an inspection of the component interface and/or the adjacent area.
 (3) Make sure that the parts retained from the removed component are clean and in the correct condition. 
R  (4) Do one of the steps that follow: 
R R  CAUTION : DO NOT APPLY MORE THAN ONE TYPE OF LUBRICANT._______ GREASE AND ASSEMBLY PASTE DO NOT MIX. 
R R R R  (a) Apply a thin layer of COMMON GREASE (Material No. 04-022) to the torque shaft splines. - or

R R R (b) Apply a thin layer of COMMON GREASE (Material No. 04-018) to the torque shaft splines. 
Subtask 27-84-45-420-080 
R  B. Installation of the Torque Shaft 6022CM(6072CM)
 (1) Install the shaft (42) and attach it with the bolts (41) and the nuts (40).
 (2) TORQUE the nuts (40) to between 1.02 and 1.24 m.daN (90.26 and 109.73 lbf.in).
 (3) Apply a layer of STORAGE PRESERVATION (Material No. 15-007) to: - the nuts (40) - the bolts (41) - the flange of the shaft (42).
R R  (4) Install the applicable steady bearing (43) (Ref. TASK 27-84-44-400-003): - FOR 6022CM install the steady bearing 6021CM - FOR 6072CM install the steady bearing 6071CM.
R R R  (5) Make sure that: - you cannot see the spline engagement groove at the movable joint - the dimension A is a minimum of 6.5 mm (0.2559 in.) at the movable joint.
 Subtask 27-84-45-710-060
 C. Test
R R  (1) The an operational test of the slat power-transmission system (Ref. TASK 27-84-00-710-001) is contained in the installation of the steady bearing (Ref. TASK 27-84-44-000-003).

 5. Close-up
________ R (Ref. Fig. 401/TASK 27-84-45-991-001) Subtask 27-84-45-866-052
 A. Extend the Flaps
 (1) Make sure that the slats are extended fully (Ref. TASK 27-80-00-866-004).
 Subtask 27-84-45-865-082
 B. Open, safety and tag this(these) circuit breaker(s):
　
中國航空網 m.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8(7)