-
remove the nut (11), the bolts (14), the spacers (12) and remove
the control cable (10).
FOR 2805GM
-
remove the nuts (11), the bolts (14) and remove the control cable (10).
1EFF : ALL 1 32-12-16Page 406 1 1 Feb 01/98 1 1 1CES 1 TASK 32-12-16-400-001
Installation of the Control Cable 2804GM (2805GM)
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.
WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.
WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU
_______
START A TASK ON OR NEAR:
-
THE FLIGHT CONTROLS
-
THE FLIGHT CONTROL SURFACES
-
THE LANDING GEAR AND THE RELATED DOORS
-COMPONENTS THAT MOVE.
1. Reason for the Job
__________________
Self Explanatory
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
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) 98DNSA20208040 1 RIGGING PIN
1EFF : ALL 1 32-12-16Page 407 1 1 May 01/05 1 1 1CES 1 1EFF : ALL 1 32-12-16Page 408 1 1 May 01/05 1 1 1CES 1 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
B. Consumable Materials
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
No specific Material No. 05-002 corrosion-resistant steel lockwire 0.8 mm (0.032 in.) dia.USA MIL-P-8116 PUTTY, ZINC CHROMATE GENERAL PURPOSE (Ref. 20-31-00)
C. Expendable Parts
-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN -------------------------------------------------------------------------------
5 cotter pin FOR FIN 2804GM 18 cotter pin FOR FIN 2805GM 18 cotter pin 32-31-03 50A-15032-12-16 01A-01032-12-16 02A-010
D. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
R R R R 24-41-00-862-002 29-10-00-864-001 29-23-00-860-001 29-23-00-860-002 32-00-00-860-001 32-00-00-860-002 32-12-00-010-001 32-12-00-410-001 32-12-00-710-002 32-31-35-400-001 De-energize the Aircraft Electrical Circuits Supplied from the External PowerDepressurize the Green Hydraulic SystemDisconnection of the Isolation Coupling of the Power Transfer Unit (PTU)Connection of the Isolation Coupling of the Power Transfer Unit (PTU) Flight Configuration Precautions with Electrical Power Ground Configuration after Flight Configuration with Electrical PowerOpen the Main Gear Doors for AccessClose the Main Gear Doors after AccessOperational Test of the Main Landing Gear (MLG) Doors Ground-Opening-MechanismInstallation of the MLG Door Actuating-Cylinder 2523GM (2522GM)
51-75-13-916-002 Repair to a layer of Corrosion Preventive Compound 32-12-16-991-001 Fig. 401 32-12-16-991-002 Fig. 402
3. Job Set-up
__________
Subtask 32-12-16-860-050
A. Aircraft Maintenance Configuration
(1) Make sure that the aircraft is in the same configuration as for the removal task.
R (2) Make sure that the PTU isolation coupling is disconnected (Ref. TASK 29-23-00-860-001).
(3)
Make sure that the aircraft electrical circuits are de-energized (Ref. TASK 24-41-00-862-002) or the
(4)
Make sure that the Green hydraulic system is depressurized (Ref. TASK 29-10-00-864-001).
(5)
Make sure that the RIGGING PIN is installed through the actuating lever and into the bypass valve 2517GM (2518GM). flight configuration precautions were obeyed (Ref. TASK 32-00-00-860-001).
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