R 1EFF : 104-105, 301-399, 1 27-54-49Page 433 1 1 May 01/05 1 1 1CES 1 **ON A/C ALL
TASK 27-54-49-400-001
Installation of the Flap Track 1 Actuator 6205CM(6255CM)
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
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GEAR.
CAUTION : BE CAREFUL WHEN YOU DO MAINTENANCE TASKS ON THE WING TRAILING EDGE:
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-
DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE RACEWAYS.
-
DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE INSTALLATIONS.
-MAKE SURE THAT THE ELECTRICAL CABLES ARE INSTALLED CORRECTLY. INCORRECT INSTALLATION CAN CAUSE DAMAGE.
1. Reason for the Job
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Self Explanatory
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
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REFERENCE QTY DESIGNATION
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No specific access platform
No specific safety barriers
No specific warning notice
R No specific Torque Wrench : range 0.00 to 1.20 m.daN
R (0.00 to 9.00 lbf.ft) No specific Torque Wrench : range 0.20 to 3.60 m.daN
(2.00 to 26.00 lbf.ft) FOR FIN 6255CM No specific 4mm (0.1574 in.) dia. rod B. Consumable Materials
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 04-018
GENERAL PURPOSE ASSEMBLY PASTE (Ref. 20-31-00)
Material No. 04-024 AIB AIMS 09-06-001
SYNTHETIC GREASE FOR FLAP & SLAT MECHANISM
(Ref. 20-31-00)
Material No. 11-026 GB DEF-STAN 68-148/1
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. 16-021 F ASNB70720
FLEXIBLE POLYURETHANE (Ref. 20-31-00)
Material No. 19-003 USA AMS 3819
LINT-FREE COTTON CLOTH (Ref. 20-31-00)
C. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
20-28-00-869-002 Table of the Maximum Permitted Resistance Values
20-28-00-912-004 Electrical Bonding of Components With Conductive Bolts and Screws and Bonding Straps in the Fuselage and in the Wings (this does not include the tanks)-
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External Power 27-50-00-000-003 Removal of the Lock-Torque Shaft - Flaps and Slats (98D27504030001) 27-50-00-866-008 Extension of the Flaps on the Ground
R 27-50-00-866-009 Retraction of the Flaps on the Ground 27-54-00-710-001 Operational Test of the Flap System 27-54-45-000-002 Removal of the Torque Shaft 6204CM(6254CM) 27-54-45-000-003 Removal of the Torque Shaft 6206CM(6256CM) 31-32-00-860-006 Procedure to Get Access to the SYSTEM REPORT/TEST
F/CTL Page
32-12-00-010-001 Open the Main Gear Doors for Access
32-12-00-410-001 Close the Main Gear Doors after Access
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REFERENCE DESIGNATION
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57-51-37-000-002 Removal of the Access Panels 573AB(673AB), 573BB(673BB), 573CB(673CB) 57-51-37-400-002 Installation of the Access Panels 573AB(673AB), 573BB(673BB), 573CB(673CB) 27-54-49-000-001 Removal of the Flap Track 1 Actuator 6205CM(6255CM) (for corrective action)
**ON A/C 001-049, 051-061, 101-103, 201-203,
27-54-49-991-001 Fig. 402
R **ON A/C 062-099, 106-149, 151-199, 204-299, 401-499,
27-54-49-991-001-B Fig. 402A
**ON A/C 104-105,
27-54-49-991-001-A Fig. 402B
**ON A/C 301-399,
27-54-49-991-001-C Fig. 402C
FOR FIN 6205CM
27-54-45-400-002 Installation of the Torque Shaft 6204CM(6254CM)
27-54-45-400-003 Installation of the Torque Shaft 6206CM(6256CM)
FOR FIN 6255CM
27-54-45-400-002 Installation of the Torque Shaft 6204CM(6254CM)
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