NOTE : These angles, shown at
____
 removal, will be used as a
 datum. They will let you
 compare the APPU and the
 FPPU angles after the
 installation of the
 actuator (Ref. TASK 27-84-48-400-001).

 6.
 Push the line key < RETURN
 frequently until the CFDS menu
 page is shown.

 7.
 De-energize the aircraft
 electrical circuits (Ref. TASK
 24-41-00-862-002).

 Subtask 27-84-48-865-051
 D. Open, safety and tag this(these) circuit breaker(s):
 -------------------------------------------------------------------------------
PANEL DESIGNATION  IDENT. LOCATION
 -------------------------------------------------------------------------------

R 49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1  5CV B06
R 121VU FLIGHT CONTROLS/SLT/CTL/SYS2  7CV R21 Subtask 27-84-48-010-050

 E. Get Access
 (1)
 Put an adjustable access platform below the applicable torque shaft.

 (2)
 Remove the applicable torque shaft (1):

 (a) (Ref. TASK 27-84-45-000-005)
 -
FOR 6013CM remove the torque shaft FIN 6012CM

 -
FOR 6063CM remove the torque shaft FIN 6062CM.

 (b) (Ref. TASK 27-84-45-000-007)
 -
FOR 6015CM remove the torque shaft FIN 6016CM

 -
FOR 6065CM remove the torque shaft FIN 6066CM.

 (3)
 Remove the applicable torque shaft (3) (Ref. TASK 27-84-45-000-006):

 -
FOR 6013CM
 remove the torque shaft FIN 6014CM

 -
FOR 6015CM
 remove the torque shaft FIN 6014CM

 -
FOR 6063CM
 remove the torque shaft FIN 6064CM

 -
FOR 6065CM
 remove the torque shaft FIN 6064CM.

 (4)
 Make sure that a LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT (98D27504030001) is installed (Ref. TASK 27-50-00-400-003) as follows: - on the torque shaft inboard of the removed component - on the torque shaft ouboard of the removed component.

 4. Procedure
_________
 **ON A/C 001-049, 051-061, 101-105, 151-152, 201-204,
 (Ref. Fig. 401/TASK 27-84-48-991-001)
R **ON A/C 062-099, 106-149, 153-199, 205-299, 301-399, 401-499,
 (Ref. Fig. 401A/TASK 27-84-48-991-001-A)R **ON A/C ALL

 Subtask 27-84-48-020-050
 A. Removal of the Type A Actuator
 (1)
 Hold the actuator (2) and remove the bolts (4) and the washers (5). Remove the actuator (2).

 (2)
 If you remove the two actuators (2) from the slat, install a TOOL-ALIGNMENT AND LOCKING (SLAT TRACKS 2 AND 3) (98D27804006000) in each pinion after each actuator (2) is removed. This will prevent movement of the slat.

 TASK 27-84-48-400-001
 Installation of the Type A Actuators 6013CM(6063CM)/6015CM(6065CM)
 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. 09-019  USA AMS 3267/3
 LOW ADHESION CORROSION INHIBITING SEALANT
 (Ref. 20-31-00)

 Material No. 11-026  GB DEF-STAN 68-148/1
 SOLVENT GENERAL PURPOSE (Ref. 20-31-00)

 -------------------------------------------------------------------------------
　
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