A320飞机维护手册 AMM FLIGHT CONTROLS 飞行操纵4(156)_航空信息_民用航空_通用航空

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R THE GAS CAN GO THROUGH THE SKIN AND MAKE BUBBLES IN THE
R BLOOD. THIS CONDITION CAN KILL YOU.
R WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER_______
R SPECIAL MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.
R OBEY THE MANUFACTURERS INSTRUCTIONS.
R PUT ON PROTECTIVE CLOTHING.
R DO NOT GET THEM IN YOUR MOUTH.
R DO NOT SMOKE.
R DO NOT BREATHE THE GAS.
R THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN
R IRRITANT.
R GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.
R 1_ Use a clean lint-free cotton cloth MISCELLANEOUS (Material No.
R 19-003) and the cleaning agent CLEANING AGENTS (Material No.
R 11-026) to clean the parts that follow:
R - The nuts (22)
R - The bolts (23)
R - The flange of the universal joint (21)
R - The flange of the torque shaft (20).
R 2_ Dry the parts with compressed air.
R 3_ Make sure that the parts retained from the removed component
R are clean and in the correct condition.
R 4_ Clean the component interface and/or the adjacent area.
R 5_ Lubricate the torque splines as follows:
R CAUTION : DO NOT APPLY MORE THAN ONE TYPE OF LUBRICANT._______
R GREASE AND ASSEMBLY PASTE DO NOT MIX.
R - Apply a thin layer of the COMMON GREASE (Material No. 04-
R 018) to the splines of the torque shaft (20).
R Or:

R - Apply a thin layer of the COMMON GREASE (Material No. 04-
R 022) to the splines of the torque shaft (20).
R 6_ Apply a layer of the STORAGE PRESERVATION (Material No. 15-
R 007) to the parts that follow:
R - The nuts (22)
R - The bolts (23)
R - The flange of the universal joint (21)
R - The flange of the torque shaft (20).
R (d) Installation of the torque shaft 6222CM (6272CM)
R 1_ Put the universal joint (21) in the installation position.
R Make sure that the flange aligns with the torque shaft (20).
R 2_ Install the bolts (23) and the nuts (22). Tighten the nuts
R (22) with your hand.
R 3_ TORQUE the nuts (22) to between 1.02 and 1.24 m.daN (90.26 and
R 109.73 lbf.in).
R (e) Install the PIN RIGGING FLAPS (2).
R 1_ Make sure that you can remove/install the rigging pin (2)
R easily.
R 2_ If you cannot remove/install the rigging pin (2) easily do the
R adjustment procedure again.
R (f) Make sure that:
R - You cannot see the spline engagement groove at the movable
R joint
R - The dimension "A" is a minimum of 6.5 mm (0.2559 in.) at the
R movable joint.
R (g) Remove the LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT
R (Ref. TASK 27-50-00-000-003)

R Subtask 27-54-00-865-083
R E. Make sure that this(these) circuit breaker(s) is(are) closed:
R -------------------------------------------------------------------------------
R PANEL DESIGNATION IDENT. LOCATION
R -------------------------------------------------------------------------------
R 49VU AUTO FLT/FAC1/28VDC 5CC1 B04
R 49VU AUTO FLT/FAC1/26VAC 14CC1 B03
R 121VU AUTO FLT/RUDDER/TRIM/IND 15CC M20
R 121VU AUTO FLT/FAC2/28VDC 5CC2 M19
R 121VU AUTO FLT/FAC2/26VAC 14CC2 M18
R Subtask 27-54-00-740-050
R F. Do a Check of the Position Pick-Off Units (PPUs) on the Centralized Fault
R Display-System (CFDS)
R (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-
R 002).
R (2) Get access to the SYSTEM REPORT/TEST (F/CTL) page on the Multipurpose
R Control Display-Unit (MCDU) (Ref. TASK 31-32-00-860-006).
R (3) Do a check of the flap PPU angles (deg) at the slat/flap control
R lever position FULL on the MCDU as follows:
R -------------------------------------------------------------------------------
R ACTION RESULT
R -------------------------------------------------------------------------------