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REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 15-007  AIB TN 10138 TYPE II GRADE 1 CORROSION PREVENTIVE TEMPORARY PROTECTIVE COMPOUND (Ref. 20-31-00)
 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 27-80-00-866-005 27-84-00-710-001 27-84-45-000-005 27-84-45-000-006 27-84-45-000-007 27-84-45-400-006 27-84-45-400-007 27-84-45-400-008 27-84-48-000-001 27-84-48-400-001 31-32-00-860-006  Installation of the Lock-Torque Shaft - Flaps and Slats (98D27504030001)Retracting the Slats on the GroundOperational Test of the Slat SystemRemoval of the Torque Shaft 6012CM(6062CM)Removal of the Torque Shafts 6014CM(6064CM)/6028CM(6078CM)/6036CM(6086CM)/ 6038CM(6088CM)/6040CM(6090CM)/6042CM(6092CM)/6044CM(6 094CM)Removal of the Torque Shafts 6016CM(6066CM)/6020CM(6070CM)/6026CM(6076CM)/ 6030CM(6080CM)Installation of the Torque Shaft 6012CM(6062CM)Installation of the Torque Shafts 6014CM(6064CM)/6028CM(6078CM)/6036CM (6086CM)/6038CM(6088CM)/6040CM(6090CM)/6042CM(6092CM) /6044CM(6094CM)Installation of the Torque Shafts 6016CM(6066CM)/6020CM(6070CM)/6026CM (6076CM)/6030CM(6080CM)Removal of the Type A Actuators 6013CM(6063CM)/6015CM(6065CM)Installation of the Type A Actuators 6013CM(6063CM)/6015CM(6065CM)Procedure to Get Access to the SYSTEM REPORT/TEST F/CTL Page

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REFERENCE DESIGNATION
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**ON A/C 001-049, 051-061, 101-105, 151-152, 201-204,
 27-84-48-991-001 Fig. 401 R **ON A/C 062-099, 106-149, 153-199, 205-299, 301-399, 401-499,
 27-84-48-991-001-A Fig. 401A
 **ON A/C ALL
 3. Job Set-up
__________
 **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)
 **ON A/C ALL

 Subtask 27-84-48-941-052
 A. Safety Precautions
 (1)
 Make sure that the safety barriers are in position.

 (2)
 Make sure that the warning notice(s) is in the cockpit to tell persons not to operate the slat controls.

 

 Subtask 27-84-48-860-050
 B. Aircraft Maintenance Configuration
 (1)
 Make sure that the slats are retracted fully (Ref. TASK 27-80-00-866-005).

 (2)
 Make sure that the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER is installed on the flap/slat control lever on panel 114VU.

 (3)
 Make sure that the applicable torque shaft (1) has been removed:

 (a) (Ref. TASK 27-84-45-000-005)
 FOR 6013CM

 -
the torque shaft 6012CM
 FOR 6063CM

 -
the torque shaft 6062CM.

 (b) (Ref. TASK 27-84-45-000-007)
 FOR 6015CM

 -
the torque shaft 6016CM
 FOR 6065CM

 -
the torque shaft 6066CM.

 

 (4)
 Make sure that the applicable torque shaft (3) (Ref. TASK 27-84-45-000-006) has been removed: FOR 6013CM

 -
the torque shaft 6014CM
 FOR 6015CM

 -
the torque shaft 6014CM
 FOR 6063CM

 -
the torque shaft 6064CM
 FOR 6065CM

 -
the torque shaft 6064CM.

 

 (5)
 If the two actuators (2) have been removed from the slat, make sure that the TOOL-ALIGNMENT AND LOCKING (SLAT TRACKS 2 AND 3) is installed in each pinion.

 (6)
 Make sure that a LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed (Ref. TASK 27-50-00-400-003) as follows: - on the torque shaft inboard of the removed component - on the torque shaft outboard of the removed component.

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 Subtask 27-84-48-865-050
 C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
 -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 5CV B06 121VU FLIGHT CONTROLS/SLT/CTL/SYS2 7CV R21
　
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