(2.00 to 26.00 lbf.ft)
B. Consumable Materials
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 04-018
Material No. 04-024 GENERAL PURPOSE ASSEMBLY PASTE (Ref. 20-31-00)AIB AIMS 09-06-001
SYNTHETIC GREASE FOR FLAP & SLAT MECHANISM
Material No. 11-026 Material No. 19-003 (Ref. 20-31-00)GB DEF-STAN 68-148/1 SOLVENT GENERAL PURPOSE (Ref. 20-31-00)USA AMS 3819
FOR FIN 6261CM LINT-FREE COTTON CLOTH (Ref. 20-31-00)
Material No. 09-018 USA AMS 3267/3 CORROSION INHIBITING LOW ADHESION SEALANT
Material No. 09-019 (Ref. 20-31-00)USA AMS 3267/3 LOW ADHESION CORROSION INHIBITING SEALANT
Material No. 15-007 (Ref. 20-31-00)AIB TN 10138 TYPE II GRADE 1
CORROSION PREVENTIVE TEMPORARY PROTECTIVE COMPOUND
(Ref. 20-31-00)
C. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
20-28-00-912-004 24-41-00-861-002 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)-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 27-50-00-866-008 27-54-00-710-001 27-54-45-000-005 27-60-00-866-002 31-32-00-860-006 Removal of the Lock-Torque Shaft - Flaps and Slats (98D27504030001)Extension of the Flaps on the GroundOperational Test of the Flap SystemRemoval of the Torque Shaft 6210CM(6260CM)Extension-Retraction of the Spoilers for MaintenanceProcedure to Get Access to the SYSTEM REPORT/TEST F/CTL Page
R 1EFF : ALL 1 27-54-49Page 464 1 1 May 01/04 1 1 1CES 1 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
27-54-49-000-002 Removal of the Flap Track 2 Actuator 6211CM(6261CM) (for corrective action)
**ON A/C 001-049, 051-061, 101-105, 201-203,
27-54-49-991-002 Fig. 404
R **ON A/C 062-099, 106-149, 151-199, 204-299, 301-399, 401-499,
27-54-49-991-002-A Fig. 404A FOR FIN 6261CM 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)-27-54-45-400-005 Installation of the Torque Shaft 6210CM(6260CM)
**ON A/C ALL
3. Job Set-up
__________
**ON A/C 001-049, 051-061, 101-105, 201-203,
(Ref. Fig. 404/TASK 27-54-49-991-002)
R **ON A/C 062-099, 106-149, 151-199, 204-299, 301-399, 401-499,
(Ref. Fig. 404A/TASK 27-54-49-991-002-A) **ON A/C ALL
Subtask 27-54-49-941-069
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 flight controls.
Subtask 27-54-49-860-056
B. Aircraft Maintenance Configuration
**ON A/C 001-049, 051-061, 101-105, 201-203,
(Ref. Fig. 404/TASK 27-54-49-991-002) R **ON A/C 062-099, 106-149, 151-199, 204-299, 301-399, 401-499,
(Ref. Fig. 404A/TASK 27-54-49-991-002-A)
**ON A/C ALL
(1)
Make sure that the flaps are fully extended (Ref. TASK 27-50-00-866-008).
(2)
Make sure that the LOCKING TOOL - FLAP/SLAT CONTROL LEVER is on the flap/slat control lever in the cockpit.
(3)
Make sure that the No. 1 spoiler has been extended (Ref. TASK 27-60-00-866-002).
(4)
Make sure that the COLLAR-SAFETY, SPOILER is on the piston rod of the servo-control.
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