-
FOR 6029CM
remove the torque shaft FIN 6030CM
-
FOR 6077CM
remove the torque shaft FIN 6076CM
-
FOR 6079CM remove the torque shaft FIN 6080CM.
(b) (Ref. TASK 27-84-45-000-012)
-
FOR 6035CM
remove the torque shaft FIN 6034CM
-
FOR 6085CM remove the torque shaft FIN 6084CM.
1EFF : ALL 1 27-84-49Page 407 1 1 Nov 01/01R 1 1 1CES 1
(c) (Ref. TASK 27-84-45-000-006)
-
FOR 6039CM remove the torque shaft FIN 6040CM
-
FOR 6089CM remove the torque shaft FIN 6090CM.
(d) (Ref. TASK 27-84-45-000-013)
-
FOR 6045CM remove the torque shaft FIN 6046CM
-
FOR 6095CM remove the torque shaft FIN 6096CM.
(4) Make sure that a LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT (98D27504030001) (Ref. TASK 27-50-00-400-003) is installed as follows: - on the torque shaft inboard of the removed component - on the torque shaft outboard of the removed components.
4. Procedure
_________
**ON A/C 001-049, 051-061, 101-105, 151-152, 201-204,
(Ref. Fig. 401/TASK 27-84-49-991-001)
R **ON A/C 062-099, 106-149, 153-199, 205-299, 301-399, 401-499,
(Ref. Fig. 401A/TASK 27-84-49-991-001-A)
**ON A/C ALL
Subtask 27-84-49-020-050
A. Removal of the Type B Actuators
(1)
Hold the actuator (7) and remove the bolts (9) and the washers (8). Remove the actuator (7).
(2)
If you remove both actuators from a slat, install a TOOL-ALIGNMENT AND LOCKING (SLAT TRACKS 5 TO 12) (98D27804007000) in each pinnion after each actuator (7) is removed or the slat will extend.
TASK 27-84-49-400-001
Installation of the Type B Actuators 6027CM(6077CM)/6029CM(6079CM)/6035CM
(6085CM)/6039CM(6089CM)/6045CM(6095CM)
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
_______
GEAR.
1. Reason for the Job
__________________
R R Self Explanatory
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific safety barriers
No specific warning notice(s)
98D27804012000 1 GAGE-RIGGING
B. Consumable Materials
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 04-018
GENERAL PURPOSE ASSEMBLY PASTE (Ref. 20-31-00)
Material No. 05-063 USA MIL-A-907E
NEVERSEEZ NICKEL SPECIAL GRADE (Ref. 20-31-00)
Material No. 09-018 USA AMS 3267/3
CORROSION INHIBITING LOW ADHESION SEALANT
(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)
-------------------------------------------------------------------------------
REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 19-003 USA AMS 3819 LINT-FREE COTTON CLOTH (Ref. 20-31-00)
C. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
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
27-50-00-400-003 Installation of the Lock-Torque Shaft - Flaps and
Slats (98D27504030001)
27-80-00-866-005 Retracting the Slats on the Ground
27-84-00-710-001 Operational Test of the Slat System
27-84-45-000-006 Removal of the Torque Shafts
6014CM(6064CM)/6028CM(6078CM)/6036CM(6086CM)/
6038CM(6088CM)/6040CM(6090CM)/6042CM(6092CM)/6044CM(6
094CM)
27-84-45-000-007 Removal of the Torque Shafts
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本文链接地址：A320飞机维护手册 AMM FLIGHT CONTROLS 飞行操纵8(24)
