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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 27-84-45-000-006 27-84-45-000-011 27-84-45-400-006 27-84-45-400-007 27-84-45-400-012 27-84-48-000-001 27-84-49-000-002 27-84-49-400-002 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 Shafts 6014CM(6064CM)/6028CM(6078CM)/6036CM(6086CM)/ 6038CM(6088CM)/6040CM(6090CM)/6042CM(6092CM)/6044CM(6 094CM)Removal of the Torque Shaft 6032CM(6082CM)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 Shaft 6032CM(6082CM)Removal of the Type A Actuators 6013CM(6063CM)/6015CM(6065CM)Removal of the Type B Actuators 6033CM(6083CM)/6037CM(6087CM)/6041CM (6091CM)Installation of the Type B Actuators 6033CM(6083CM)/6037CM(6087CM)/ 6041CM(6091CM)Procedure to Get Access to the SYSTEM REPORT/TEST F/CTL Page
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**ON A/C 001-049, 051-061, 101-105, 151-152, 201-204,
27-84-49-991-001 Fig. 401 R **ON A/C 062-099, 106-149, 153-199, 205-299, 301-399, 401-499,
27-84-49-991-001-A Fig. 401A
FOR FIN 6083CM
27-84-45-000-012 Removal of the Torque Shaft 6034CM(6084CM)
**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 27-84-49-991-001) 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 27-84-49-941-055
A. Safety Precautions
(1)
Make sure that the safety barriers are in position.
(2)
Make sure that the warning notice(s) are in the cockpit to tell persons not to operate the slat controls.
Subtask 27-84-49-860-053
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 adjustable access platform is below the applicable torque shaft.
(4)
Make sure that the applicable torque shaft (3) is removed:
(a) (Ref. TASK 27-84-45-000-006)
-
FOR 6037CM
the torque shaft 6036CM
-
FOR 6041CM
the torque shaft 6040CM
-
FOR 6087CM
the torque shaft 6086CM
-
FOR 6091CM
the torque shaft 6090CM.
(b) (Ref. TASK 27-84-45-000-011)
-
FOR 6033CM
the torque shaft 6032CM
-
FOR 6083CM the torque shafts 6082CM and 6086CM.
(5)
Make sure that the applicable torque shaft (1) is removed:
(a) (Ref. TASK 27-84-45-000-012)
-
FOR 6033CM
the torque shaft 6034CM
-
FOR 6083CM
the torque shaft 6032CM
(b) (Ref. TASK 27-84-45-000-006)
-
FOR 6037CM
the torque shaft 6090CM
-
FOR 6041CM
the torque shaft 6042CM
-
FOR 6087CM
the torque shaft 6032CM
-
FOR 6091CM
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the torque shaft 6082CM.
(6)
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.
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