AD 84-14-51 R1

84-14-51 R1 BOEING: Amendment 39-5149. Applies to Model 757 airplanes listed in Boeing Service Bulletin 757-32-0033 dated September 7, 1984, certificated in any category, on which incorporation of Boeing Service Bulletin 757-32-0033, dated September 7, 1984, or later FAA- approved revision, has not been accomplished. Compliance is required as indicated below, after the effective date of this airworthiness directive (AD). To assure landing gear extension following a jam of the landing gear handle in the up position, accomplish the following, unless already accomplished:

A. Within 24 hours:

1. Incorporate the following information into the FAA-approved airplane flight manual and the flight operations manual as an emergency procedure and provide to flight crews:

GEAR LEVER WILL NOT MOVE FROM UP POSITION AIRSPEED......................................................................... MAINTAIN 200-220 KTS UNTIL GEAR EXTENDED FLAP LEVER..................................................................... ................1 PTU CONT CIRCUIT BREAKER (D31).................................... PULL LEFT AUTOPILOT (IF ENGAGED)............................................DISCONNECT LEFT ELECTRIC AND ENGINE HYDRAULIC PUMP SWITCHES................................OFF ALTERNATE GEAR EXTENSION SWITCH..........................PUSH If, after 60 seconds, any gear down (green) lights not illuminated: FLAP LEVER..................................................................... 5/1 Select flaps 5 then 1. Repeat until all gear down (green) lights illuminate. - Use flaps 20 and VREF 20 for landing. - L thrust reverser and nose wheel steering inoperative GROUND PROXIMITY FLAPS OVERRIDE SWITCH........ OVRD ALTERNATE FLAPS SELECTOR.............................................SET Position to agree with flap lever. ALTERNATE FLAPS SWITCHES (Leading and Trailing Edge)........................................ ALTN ALTERNATE FLAPS SELECTOR.............................................SET Extend or Retract Flaps as required.

CAUTION: DO NOT REPRESSURIZE LEFT HYDRAULIC SYSTEM OR RESET PTU CONT CIRCUIT BREAKER INFLIGHT OR ON THE GROUND, AS GEAR WILL RETRACT.

NOTE: Compliance with this directive may be effected by including a copy of telegraphic AD T84-14-51, issued June 29, 1984, in the airplane flight manual and operating manual.

2. Further revenue flight following landing gear jam is prohibited until repairs are made.

3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.

4. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD.

B. Prior to September 1, 1986:

1. Modify the landing gear selector valve assembly, Boeing P/N 60B00216-7, in accordance with Boeing Service Bulletin 757-32-0033, dated September 7, 1984, or later FAA- approved revision.

2. Following modification of the selector valve, the special emergency procedure implemented by paragraph A., above, may be removed.

All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.

The telegraphic AD issued June 29, 1984, became effective upon receipt. This amendment becomes effective November 12, 1985.