-
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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