AD 94-13-02 Airworthiness Directives; Boeing Model 757-200, -200PF, and - 200CB Series Airplanes Equipped with Rolls-Royce Model RB211-535E4/E4B Engines

Models named: 757-200, -200PF, -200CB series, RB211-535E4/E4B. Read the applicability below — it usually turns on serial or part numbers too.

Model 757-200, -200PF, and -200CB series airplanes equipped with Rolls-Royce Model RB211-535E4/E4B engines, certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To prevent deployment of a thrust reverser in flight and consequent reduced controllability of the airplane, accomplish the following: (a) For airplanes on which the sync-lock feature was not installed during production or as a modification in accordance with Boeing Service Bulletin 757-78-0032, Revision 2, dated May 12, 1994: Within 4,000 hours time-in-service after July 20, 1994 (the effective date of AD 94-13-02, amendment 39-8942); and thereafter at intervals not to exceed 4,000 hours time-in-service until the modification required by paragraph (b) of this AD is accomplished; accomplish paragraphs (a)(1) and (a)(2) of this AD to verify proper operation of the thrust reverser system. Prior to further flight, repair any discrepancy found, in accordance with the procedures described in the Boeing 757 Maintenance Manual. (1) Perform a ``Thrust Reverser-Auto Restow Test'' in accordance with the procedures described in Section 78-31-00 of the Boeing 757 Maintenance Manual. (2) Perform an ``Actuator Lock and Crossover Shaft Integrity Test'' in accordance with the procedures described in Section 78-31- 00 of the Boeing 757 Maintenance Manual. (b) For airplanes on which the sync-lock feature was not installed during production or as a modification in accordance with Boeing Service Bulletin 757-78-0032, Revision 2, dated May 12, 1994: Within 5 years after July 20, 1994, accomplish the requirements of either paragraph (b)(1) or (b)(2) of this AD. Accomplishment of either of these installations constitutes terminating action for the tests required by paragraph (a) of this AD. [[Page 46880]] (1) Install an additional thrust reverser system locking feature (sync-lock installation) in accordance with Boeing Service Bulletin 757-78-0032, Revision 2, dated May 12, 1994. Note 2: Revision 2 of Boeing Service Bulletin 757-78-0032 references Rolls-Royce Service Bulletins RB.211-78-9613 and RB.211- 78-9627 as additional sources of service information. The intent of paragraph (b)(1) of this AD is that the appropriate revision levels of the Rolls-Royce service bulletins to be used in conjunction with Boeing Service Bulletin 757-78-0032 are as follows: Rolls-Royce Service Bulletin RB.211-78-9613, dated December 3, 1992, or Revision 1, dated March 5, 1993, or Revision 2, dated October 1, 1993; and Rolls-Royce Service Bulletin RB.211-78-9627, dated December 3, 1992. (2) Install a revised thrust reverser sync-lock in accordance with Boeing Service Bulletin 757-78-0032, Revision 2, dated May 12, 1994, and Rolls-Royce Service Bulletin RB.211-78-9822, dated October 1, 1993. Note 3: Rolls-Royce Service Bulletin RB.211-78-9822 references Rolls-Royce Service Bulletin RB.211-78-9613 as an additional source of service information for airplanes equipped with Rolls-Royce RB211-535E4/E4B engines. Rolls-Royce Service Bulletin RB.211-78-9613 references Rolls-Royce Service Bulletin RB.211-78-9627 as an additional source of service information. The FAA's intent is that the appropriate revision levels to be used in conjunction with Rolls-Royce Service Bulletin RB.211-78-9822 are as follows: Rolls- Royce Service Bulletin RB.211-78-9613, Revision 2, dated October 1, 1993; and Rolls-Royce Service Bulletin RB.211-78-9627, dated December 3, 1992. (c) Within 4,000 hours time-in-service after accomplishing the modification required by paragraph (b) of this AD, or within 4,000 hours time-in-service after July 20, 1994, whichever occurs later; and thereafter at intervals not to exceed 4,000 hours time-in- service: Accomplish the ``Thrust Reverser Sync-Lock Integrity Test'' specified below to verify that the sync-locks have not failed in the ``unlocked'' state. Prior to further flight, repair any discrepancy found, in accordance with procedures described in the Boeing 757 Maintenance Manual. THRUST REVERSER SYNC-LOCK INTEGRITY TEST 1. General A. Use this procedure to test the integrity of the thrust reverser sync locks. The procedure must be performed on each engine. 2. Thrust Reverser Sync Lock Test A. Prepare for the thrust reverser sync lock test. (1) Open the AUTO SPEEDBRAKE circuit breaker on the overhead circuit breaker panel, P11. (2) Do steps 2.A.(2)(a) through 2.A.(2)(f) to supply power to the thrust reverser system: (a) Make sure the thrust levers are in the idle position. (b) Make sure the thrust reversers are retracted and locked. (c) Make sure these circuit breakers on the main power distribution panel, P6, are closed: (1) L ENG SYNC LOCK (2) R ENG SYNC LOCK-ALTN (d) Make sure these circuit breakers on the overhead circuit breaker panel, P11, are closed: (1) LANDING GEAR POS SYS 1 (2) T/R IND R (3) T/R CONT-ALTN-R (4) T/R IND L (5) T/R CONT L (6) R ENG SYNC LOCK (7) T/R CONT R (8) EICAS CMPTR LEFT (9) EICAS UPPER IND (10) EICAS CMPTR RIGHT (11) EICAS LOWER IND (12) EICAS DISPLAY SW (13) EICAS PILOTS DSP (14) AIR/GND SYS 1 (15) AIR/GND SYS 2 (16) LANDING GEAR POS SYS 2 (17) PROX SW TEST (e) Supply electrical power. (f) Supply pressure to the left (for the left engine) or right (for the right engine) hydraulic system. B. Do the thrust reverser sync lock test. (1) Use the SENSOR CHANNEL SELECT thumb switches to set the PSEU code for the auto-restow proximity sensor. (a) On PSEU (-17), The left engine code is 433. (b) On PSEU (-16), The left engine code is 105. (c) The right engine PSEU code is 099. Note: Step 2.B.(2) will cause the Hydraulic Isolation Valve (HIV) to open for approximately 5 seconds. Steps 2.B.(3) through 2.B.(5) must be done during this 5 second time. Steps 2.B.(2) through 2.B.(5) may be repeated if necessary. (2) Push the TARGET TEST switch on the PSEU and hold for one second. (3) Make sure the TARGET NEAR light on the PSEU comes on after approximately four seconds. (4) Make sure that the EICAS Advisory message L(R) REV ISLN VAL shows for approximately 3 seconds and then does not show. (5) Make sure the sync lock manual unlock lever on the right sleeve of the reverser does not extend. (6) Push and release the RESET switch on the PSEU. (7) Open the applicable circuit breaker(s): (a) For the left engine; L ENG SYNC LOCK (Panel P6) (b) For the right engine; R ENG SYNC LOCK (Panel P11) R ENG SYNC LOCK-ALTN (Panel P6) (8) Move the left (right) reverse thrust lever up and rearward to the reverse thrust position. (9) Make sure that the thrust reverser does not extend. (10) Move the left (right) reverse thrust lever to the forward and down position. C. Put the airplane back to its usual condition. (1) Remove hydraulic pressure. (2) Close the applicable circuit breaker(s). (a) For the left engine; L ENG SYNC LOCK (Panel P6) (b) For the right engine; R ENG SYNC LOCK (Panel P11) R ENG SYNC LOCK-ALTN (Panel P6) (3) Close the AUTO SPEEDBRAKE circuit breaker on the overhead circuit breaker panel, P11. (4) Remove electrical power. D. Repeat the thrust reverser sync lock test on the other engine. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. Note 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. (e) Special flight permits may be issued in accordance with Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The installation shall be done in accordance with Boeing Service Bulletin 757-78-0032, Revision 2, dated May 12, 1994, and/or Rolls-Royce Service Bulletin RB.211-78-9822, dated October 1, 1993. This incorporation by reference was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of July 20, 1994 (59 FR 31512, June 20, 1994). Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on September 18, 1998. Issued in Renton, Washington, on August 28, 1998. Vi L. Lipski, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-23742 Filed 9-2-98; 8:45 am] BILLING CODE 4910-13-M