(2.00 to 26.00 lbf.ft) 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
-------------------------------------------------------------------------------
27-50-00-000-003 Removal of the Lock-Torque Shaft - Flaps and Slats (98D27504030001) 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
27-84-45-991-001 Fig. 401
R 27-84-45-991-002 Fig. 402
3. Job Set-up
__________
(Ref. Fig. 401/TASK 27-84-45-991-001)
Subtask 27-84-45-941-064
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 27-84-45-860-057
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.
R (3) 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 applicable components - on the torque shaft, outboard of the applicable components.
(4) Make sure that the adjustable access platform is in position below the applicable access panel.
R R R R R R R R R (5) Make sure that the applicable access panel has been removed: - FOR 6016CM panel 521EB - FOR 6020CM panel 521EB - FOR 6026CM panel 522AB - FOR 6030CM panel 522CB - FOR 6066CM panel 621EB - FOR 6070CM panel 621EB - FOR 6076CM panel 622AB - FOR 6080CM panel 622CB.
Subtask 27-84-45-865-076
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 121VU FLIGHT CONTROLS/SLT/CTL/SYS2 5CV 7CV B06R21
4. Procedure_________
R R (Ref. Fig. 402/TASK 27-84-45-991-002)
Subtask 27-84-45-420-076
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 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.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM FLIGHT CONTROLS 飞行操纵8(2)
