C. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
27-84-00-710-001 Operational Test of the Slat System
27-84-45-400-008 Installation of the Torque Shafts 6016CM(6066CM)/6020CM(6070CM)/6026CM (6076CM)/6030CM(6080CM)
FOR FIN 6071CM 27-50-00-400-003 Installation of the Lock-Torque Shaft - Flaps and Slats (98D27504030001)
3. Job Set-up
__________
Subtask 27-84-44-941-064
A. Safety Precautions
(1)
Make sure that the safety barriers are in position.
(2)
Make sure that the warning notice is in the cockpit to tell persons not to operate the slat controls.
Subtask 27-84-44-860-052
B. Aircraft Maintenance Configuration
(1)
Make sure that the access platform is in position below the applicable torque shaft.
(2)
Make sure that the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER (98D27803500001) is on the slat/flap control lever.
(3)
Make sure that the applicable torque shaft (26) is removed (Ref. TASK 27-84-45-400-008): FOR 6021CM
-
remove the torque shaft FIN 6020CM
FOR 6071CM
-
remove the torque shaft FIN 6070CM.
(4)
Make sure that the applicable access panel(s) have been removed: FOR 6021CM
-
remove 521GB
FOR 6071CM
-
remove 621GB.
(5)
Make sure that a LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT
is installed (Ref. TASK 27-50-00-400-003) as follows: - on the torque shaft inboard of the removed component - on the torque shaft outboard of the removed component.
Subtask 27-84-44-865-052
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
_________
Subtask 27-84-44-420-061
A. Preparation for Installation
WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL
_______ MATERIALS ONLY WITH A GOOD SUPPLY OF AIR. OBEY THE MANUFACTURERS INSTRUCTIONS. PUT ON PROTECTIVE CLOTHING. DO NOT GET THEM IN YOUR MOUTH. DO NOT SMOKE. DO NOT BREATHE THE GAS. THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT. GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.
(1)
Use a MISCELLANEOUS (Material No. 19-003) with CLEANING AGENTS (Material No. 11-004) to clean the component interface and/or the adjacent area.
(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.
(4)
Apply a layer of SEALANTS (Material No. 09-018) or SEALANTS (Material No. 09-019) to:
-
the mating faces of the steady bearing (22) and the nose rib (23)
-
the shanks of the bolts (21).
Subtask 27-84-44-420-062
B. Installation of the Steady Bearing FIN 6021CM (6071CM)
(1)
Attach the steady bearing (22) to the torque shaft (25) and the nose rib (23) with the bolts (21) and the nuts (24).
(2)
Apply a layer of STORAGE PRESERVATION (Material No. 15-007) to:
-
the bolts (21)
-
the nuts (24)
-
the flange of the steady bearing (22).
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 FLIGHT CONTROLS 飞行操纵7(119)
