(2.00 to 26.00 lbf.ft) FOR FIN 6082CM 98D27504030001 2 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT
B. Consumable Materials
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. 04-018
GENERAL PURPOSE ASSEMBLY PASTE (Ref. 20-31-00)
Material No. 04-022 USA MIL-PRF-81322 GRADE 2
SYNTHE.HYDROCARBON GREASE HIGH PRESSURE
(Ref. 20-31-00)
Material No. 11-026 GB DEF-STAN 68-148/1 R 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)
Material No. 19-003 USA AMS 3819
LINT-FREE COTTON CLOTH (Ref. 20-31-00)
C. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
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 27-84-44-000-006 Removal of the Steady Bearing FIN 6031CM(6081CM) 27-84-44-400-004 Installation of the Steady Bearing FIN 6023CM(6073CM) 27-84-44-400-006 Installation of the Steady Bearing FIN 6031CM(6081CM) 27-84-45-991-001 Fig. 401
R 27-84-45-991-002 Fig. 402 FOR FIN 6082CM 27-50-00-000-003 Removal of the Lock-Torque Shaft - Flaps and Slats
(98D27504030001)
3. Job Set-up
__________
(Ref. Fig. 401/TASK 27-84-45-991-001)
Subtask 27-84-45-941-068
A. Safety Precautions
(1)
Make sure that the safety barriers are in position.
(2)
Make sure that the warning notice is in position to tell persons not to operate the slat controls.
Subtask 27-84-45-860-061
B. Aircraft Maintenance Configuration
(1)
Make sure that the access platform is in position below the applicable access panel 522FB(622FB).
(2)
Make sure that the applicable access panel 522FB(622FB) is removed.
(3)
Make sure that the applicable steady bearing has been removed (Ref. TASK 27-84-44-000-006).
(4)
Make sure that the slats are retracted fully (Ref. TASK 27-80-00-866-005).
(5) Make sure that the TOOL-ZERO LOCKING, FLAP SLAT CTL LEVER is installed on the flap/slat control lever on panel 114VU.
(6) Make sure that a LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed (Ref. TASK 27-50-00-400-003): - on the torque shaft, inboard of the removed component - on the torque shaft, outboard of the removed component.
Subtask 27-84-45-865-088
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
4. Procedure_________
R R (Ref. Fig. 402/TASK 27-84-45-991-002)
Subtask 27-84-45-420-083
R A. Preparation for Installation
R R CAUTION : DO NOT APPLY MORE THAN ONE TYPE OF LUBRICANT._______ GREASE AND ASSEMBLY PASTE DO NOT MIX.
R R (1) Clean the component interface and/or the adjacent area with a MISCELLANEOUS (Material No. 19-003) made moist with CLEANING AGENTS (Material No. 11-026).
(2) Do an inspection of the component interface and/or the adjacent area.
(3) Make sure that the parts retained from the removed component are clean and in the correct condition.
R (4) Do one of the steps that follow:
R R CAUTION : DO NOT APPLY MORE THAN ONE TYPE OF LUBRICANT._______ GREASE AND ASSEMBLY PASTE DO NOT MIX.
R R R R (a) Apply a thin layer of COMMON GREASE (Material No. 04-022) to the torque shaft splines. - or
R R R (b) Apply a thin layer of COMMON GREASE (Material No. 04-018) to the torque shaft splines.
Subtask 27-84-45-420-084
R B. Installation of the Torque Shaft 6032CM(6082CM)
R (1) Put the retaining ring (18) in position over the shaft (14).
(2) Install the universal joint (13) and attach it with the pin (12) and the retaining ring (18).
(3) Install the shaft (14) and attach it with the bolts (17) and the nuts (16).
(4) TORQUE the nuts (16) to between 1.02 and 1.24 m.daN (90.26 and 109.73 lbf.in).
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