HOT AIR DUCT RUPTURE CONDITION - MAINTENANCE PRACTICES (CONDITIONAL INSPECTION)
1. Hot Air Duct Rupture Conditional Inspection
A. Examine any airplane structure which has been exposed to excessive heat to determine whether such overheating has weakened structure (Ref Nondestructive Test Manual).
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EXCESSIVE AILERON OR RUDDER TRIM CORRECTION WITH FLAPS EXTENDED -
MAINTENANCE PRACTICES (CONDITIONAL INSPECTION)
1. General
A. This procedure contains one task:
(1) Outboard Flap Carriage Spindle Fracture Inspection
B. Operators have reported that due to the fracture of the inboard spindle of the outboard flap, pilots have had to hold more than 2.5 units of wheel or an unspecified amount of rudder to keep the airplane level. With one spindle broken, the airplane is controllable. But with both spindles broken at the critical section (forward end of the spindle), continued safe flight and landing for the airplane may be precluded. For this reason, if the flight crew reports that during the flap operation they had to use 2.5 or more units of wheel and/or 1.0 or more units of rudder to keep the airplane level, both spindles must be inspected for fracture.
C. You must inspect the outboard flap carriage spindles for fractures if either of the conditions below are necessary to maintain level flight when the flaps are in transition or the flaps are in any extended position:
(1)
2.5 units or more of wheel
(2)
1.0 or more units of rudder.
D. This inspection is required prior to the next flight.
WARNING YOU MUST PERFORM THIS INSPECTION PRIOR TO THE NEXT FLIGHT. IF YOU DO NOT PERFORM THIS INSPECTION PRIOR TO THE NEXT FLIGHT, INJURY TO PERSONS CAN OCCUR.
2. Outboard Flap Carriage Spindle Fracture Inspection
A. General
(1)
You must do one of the two inspections below. The ultrasonic inspection is preferred and you should perform this inspection when the equipment is available. If ultrasonic inspection equipment is not available, you should perform the alternate manual inspection.
(2)
See AMM 27-51-81/401, Fig.\401 for carriage spindle removal and installation.
B. Prepare for Inspection
(1) Extend the flaps to detent 40.
C. Ultrasonic Inspection (Preferred)
(1) Perform an ultrasonic inspection on the carriages as shown in Boeing 737 NDT Manual, Part 4-57-50-02 to detect fractured carriage spindles.
NOTE: Perform this procedure at both the inboard and outboard carriage positions.
(a)
If a fracture is detected in one of the carriage spindles, do these steps: 1) Remove the outboard flap (AMM 27-51-72/401). 2) Remove and replace the fractured carriage (AMM 27-51-81/401). 3) Install the outboard flap (AMM 27-51-72/401).
(b)
If you do not find spindle fractures, do this step:
1) Do the Flight Controls Trim Correction - Trouble Shooting (AMM 27-09-71/101) for troubleshooting of unexpected aileron and/or rudder inputs.
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D. Manual Inspection (Alternate)
(1) Manually lift the main flap box at each end separately to detect any differential movement between the main flap box and the flap carriage.
NOTE: Any differential motion between the flap box and the carriage is an indication of a fracture of forward portion of the spindle. Use the opposite flap as a basis of comparison to detect any abnormal differential movement between the flap box and the carriage
(a)
If a fracture is detected in one of the carriage spindles, do these steps: 1) Remove the flap (AMM 27-51-72/401). 2) Remove and replace the fractured carriage (AMM 27-51-81/401). 3) Install the flap (AMM 27-51-72/401).
(b)
If you do not find spindle fractures, do this step:
1) Do the Flight Controls Trim Correction - Trouble Shooting (AMM 27-09-71/101) for troubleshooting of unexpected aileron and/or rudder inputs.
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BIRD/HAIL STRIKE CONDITION - MAINTENANCE PRACTICES (CONDITIONAL INSPECTION)
1. General
A. Examine the entire aircraft exterior especially wing leading edges, flaps and slats, engine inlets, and nacelles for impact damage when a bird strike is reported or suspected due to extreme possibility of multiple bird strikes. Aircraft configuration should be the same as when bird strike occurred, i.e., position of flaps, landing gear, etc. If flap position is unknown, examine trailing edge flaps and leading edge flaps and slats in fully extended position. Damage areas should be marked for thorough examination and/or action when the exterior examination of the total aircraft is complete. Refer to the Structural Repair Conditional Manual for repair of any impact damage.
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