AD 95-10-13 Airworthiness Directives; Boeing Model 757 Series Airplanes Equipped With Rolls Royce Engines

Models named: 757 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 757 series airplanes equipped with Rolls Royce engines; as listed in Boeing Alert Service Bulletin 757- 54A0030, Revision 1, dated December 20, 1993; 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 use the authority provided in paragraph (h) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Required as indicated, unless accomplished previously. To prevent fuel or hydraulic fluid leakage into the interior of the engine strut, which could cause a fire, accomplish the following: (a) For Group 2 Airplanes: Within 60 days after February 28, 1994 (the effective date of AD 94-04-04, amendment 39-8822), perform an inspection using a magnet to determine whether the forward support bracket for the hydraulic tubing on the upper spar web of each engine strut is manufactured from 17-7PH steel, in accordance with Boeing Alert [[Page 25985]] Service Bulletin 757-54A0030, Revision 1, dated December 20, 1993. If any forward support bracket is manufactured from 17-7PH steel, no further action is required by this AD for that forward bracket. Note 2: The brackets positioned after the forward bracket should be manufactured from 17-7PH steel, as shown below: ------------------------------------------------------------------------ (Power plant Bracket Part No. station No.) ------------------------------------------------------------------------ First Bracket............................ 312N5817-13...... PPS 102 (or equivalent).. Second Bracket........................... 312N5817-19...... PPS 120 (or equivalent).. Third Bracket............................ 312N5817-23...... PPS 129 (or equivalent).. Fourth Bracket........................... 312N5817-25...... PPS 145 (or equivalent).. ------------------------------------------------------------------------ (b) For Groups 1 and 2 Airplanes: Within 60 days after February 28, 1994 (the effective date of AD 94-04-04, amendment 39-8822) (for Group 1 airplanes), and prior to further flight following the inspection required by paragraph (a) of this AD (for Group 2 airplanes), perform an initial visual inspection to detect fatigue- related cracks or breakage on the hydraulic tubing support brackets not manufactured of 17-7PH steel on the upper spar web of each engine strut, in accordance with Boeing Alert Service Bulletin 757- 54A0030, Revision 1, dated December 20, 1993. If any discrepancy is detected, prior to further flight, accomplish the following in accordance with the alert service bulletin: (1) For any support bracket that is completely broken: Perform a further visual inspection to detect worn areas or other damage of the upper spar web, the fuel lines, and the hydraulic lines; and prior to further flight, accomplish paragraphs (b)(1)(i), (b)(1)(ii), (b)(1)(iii), and (b)(1)(iv) of this AD in accordance with the alert service bulletin: (i) Repair any damaged upper spar web. (ii) Repair or replace any damaged fuel line with new or serviceable parts, as necessary. (iii) Replace any damaged hydraulic line with new or serviceable parts. (iv) Remove any broken support bracket; and, except as provided by paragraph (c) of this AD, replace it with a new nickel alloy 625 bracket. (2) For any support bracket that is cracked, but not completely broken: Perform a further visual inspection to detect damage of the hydraulic pressure line only; and prior to further flight, accomplish paragraphs (b)(2)(i) and (b)(2)(ii) of this AD in accordance with the alert service bulletin: (i) Replace any damaged hydraulic pressure line with new or serviceable parts, as necessary. (ii) Remove any cracked support bracket; and, except as provided by paragraph (c) of this AD, replace it with a new nickel alloy 625 bracket. (c) For any airplane having a support bracket that is removed during accomplishment of paragraph (b)(1)(iv) or (b)(2)(ii) of this AD: The following number of flights are permitted prior to replacement of any removed support bracket with a new nickel alloy 625 bracket (in accordance with Boeing Alert Service Bulletin 757- 54A0030, Revision 1, dated December 20, 1993), provided that, prior to further flight, the cracked or broken brackets are removed completely, damaged spar webs are repaired, and fuel lines and hydraulic lines are repaired or replaced, in accordance with paragraph (b) of this AD: ---------------------------------------------------------------------------------------------------------------- Part No. (power plant station Bracket No.) Flights permitted ---------------------------------------------------------------------------------------------------------------- First Bracket Removed.............................. 312N5817-55 (PPS 102)............ No Flights. Second Bracket Removed............................. 312N5817-69 (PPS 120)............ Ten Flights. Third Bracket Removed.............................. 312N5817-73 (PPS 129)............ Ten Flights. Fourth Bracket Removed............................. 312N5817-75 (PPS 145)............ Three Flights. Second and Third Brackets Removed.................. ................................. One Flight. Multiple Brackets, other than Second and Third..... ................................. No Flights. ---------------------------------------------------------------------------------------------------------------- (d) For any airplane having a support bracket that is manufactured from 2024-T42 aluminum alloy or 301 stainless steel: Repeat the initial inspection required by paragraph (b) of this AD thereafter at intervals not to exceed 2,000 flight hours, in accordance with the procedures described in Boeing Alert Service Bulletin 757-54A0030, Revision 1, dated December 20, 1993. (e) For any airplane having a support bracket that is manufactured from 2219 aluminum: Repeat the initial inspection required by paragraph (b) of this AD thereafter at intervals not to exceed 1,000 flight hours, in accordance with the procedures described in Boeing Alert Service Bulletin 757-54A0030, Revision 1, dated December 20, 1993. (f) Within 18 months after the effective date of this AD: Replace all support brackets manufactured from 2219 aluminum, 2024- T42 aluminum alloy, or 301 stainless steel, with either new 17-7PH steel brackets or new nickel alloy 625 support brackets for the hydraulic tubing on the upper spar web of the engine struts at all locations, in accordance with Boeing Alert Service Bulletin 757- 54A0030, Revision 1, dated December 20, 1993. Accomplishment of this modification constitutes terminating action for the requirements of this AD. (g) As of February 28, 1994 (the effective date of AD 94-04-04, amendment 39-8822), no person shall install any hydraulic tubing support bracket on the upper spar web of the engine struts that is manufactured from 2219 aluminum, 2024-T42 aluminum alloy, or 301 stainless steel on any airplane. (h) 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 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. (i) Special flight permits may be issued in accordance with sections 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. (j) The inspections, repair, replacement, and removal shall be done in accordance with Boeing Alert Service Bulletin 757-54A0030, Revision 1, dated December 20, 1993. The incorporation by reference of this document 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 February 28, 1994 (59 FR 65420). 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. (k) This amendment becomes effective on June 15, 1995. Issued in Renton, Washington, on May 9, 1995. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 95-11906 Filed 5-15-95; 8:45 am] BILLING CODE 4910-13-U