AD 97-06-13 Airworthiness Directives; Rolls-Royce plc RB.211 Trent 800 Series Turbofan Engines

Rolls-Royce plc (R-R) RB.211 Trent 800 series turbofan engines, installed on but not limited to Boeing 777 series aircraft. Note 1: This airworthiness directive (AD) applies to each engine 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 engines 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 loss of oil, that could cause an engine fire, and inflight engine shutdowns and airplane diversions caused by oil loss and from bearing failures, accomplish the following: (a) Inspect angle drive upper shroud tubes as follows: (1) Within 50 CIS after the effective date of this AD, visually inspect and measure the frettage and fluorescent penetrant inspect [[Page 23341]] (FPI) for cracks the angle drive upper shroud tubes in accordance with R-R Service SB No. RB.211-72-C089, Revision 1, dated January 24, 1997. (2) Thereafter, at intervals not to exceed 50 CIS since last inspection, visually inspect and measure the frettage and FPI for cracks the angled drive upper shroud tubes, in accordance with R-R SB No. RB.211-72-C089, Revision 1, dated January 24, 1997. (3) Prior to further flight, remove from service angled drive upper shroud tubes that exhibit frettage measured in excess of 0.020 inches, or any cracks, and replace with serviceable parts. (4) Installation of an improved angled drive upper shroud tube with a lower splitter fairing with revised sealing in accordance with R-R SB No. RB.211-72-C114, dated February 6, 1997, constitutes terminating action to the inspection requirements of paragraphs (a)(1), (a)(2), and (a)(3) of this AD. (5) Prior to initiation of ETOPS, or prior to September 30, 1997, whichever occurs first, install an improved angled drive upper shroud tube with a lower splitter fairing with revised sealing in accordance with R-R SB No. RB.211-72-C114, dated February 6, 1997. (b) Inspect the intermediate gearbox housing (IGH) and external gearbox lower bevel box (LBB) housing as follows: (1) Within 5 CIS after the effective date of this AD, perform an initial visual inspection of the IGH and LBB housing for cracks, in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (2) Within 10 CIS after the effective date of this AD, perform an initial FPI of the IGH for cracks, in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (3) Thereafter, at intervals not to exceed 5 CIS since last visual inspection, visually inspect the IGH and LBB housing for cracks, and at intervals not to exceed 10 CIS since last FPI, FPI the IGH, in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (4) Within 10 CIS after the effective date of this AD, perform an FPI of the IGH for porosity in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (5) Within the next 5 CIS, remove from service IGHs that exhibit porosity levels in excess of the acceptable criteria listed in the SB and replace with serviceable parts. (6) Prior to further flight, remove from service cracked IGHs and LLB housings and replace with serviceable parts. (c) Inspect the master magnetic chip detector as follows: (1) Within 100 hours time in service (TIS) after the effective date of this AD, perform an initial inspection of the master magnetic chip detector in accordance with Mandatory SB No. RB.211- 79-C093, Revision 1, February 28, 1997. (2) Thereafter, at intervals not less than 60 hours TIS and not greater than 130 hours TIS since last inspection, perform repetitive inspections of the master magnetic chip detector in accordance with Mandatory SB No. RB.211-79-C093, Revision 1, dated February 28, 1997. (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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (e) 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 aircraft to a location where the inspection requirements of this AD can be accomplished. (f) The actions required by this AD shall be performed in accordance with the following R-R service documents: ---------------------------------------------------------------------------------------------------------------- Document No. Pages Revision Date ---------------------------------------------------------------------------------------------------------------- SB No. RB.211-72-C089.................... 1-3 1........................ Jan. 24, 1997. Total pages: 3. SB No. RB.211-72-C129.................... 1-3 2........................ Mar. 21, 1997. 4-6 1........................ Mar. 7, 1997. 7 2........................ Mar. 21, 1997. Total pages: 7. SB No. RB.211-72-C114.................... 1-48 Original................. Feb. 6, 1997. Supplement............................... 1-4 Original................. Feb. 6, 1997. Total pages: 52. SB No. RB.211-79-C093.................... 1,2 1........................ Feb. 28, 1997. Total pages: 2. ---------------------------------------------------------------------------------------------------------------- This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Rolls-Royce North America, Inc., 2001 South Tibbs Ave., Indianapolis, IN 46241; telephone (317) 230-3995, fax (317) 230-4743. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on May 15, 1997. Issued in Burlington, Massachusetts, on April 14, 1997. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 97-10469 Filed 4-29-97; 8:45 am] BILLING CODE 4910-13-U