AD 97-11-06 Airworthiness Directives; Pratt & Whitney PW4164 and PW4168 Series Turbofan Engines

Pratt & Whitney (PW) PW4164 and PW4168 series turbofan engines, installed on but not limited to Airbus Industrie A330 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 (e) 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 fan blade failure and separation at the root section, which could result in high N1 rotor imbalance, and liberation of the fan containment system, which can hazard the aircraft, accomplish the following: (a) Perform visual inspections of fan blades, Part Number (P/N) 55A221, for surface damage and cracks, and lubricate the fan blade shrouds, in accordance with the Accomplishment Instructions of PW SB No. PW4G-100-72-69, dated August 6, 1996, as follows: (1) At the next ``A'' check inspection, not to exceed 500 hours time in service (TIS) after the effective date of this AD, whichever occurs first, perform the initial inspection of the fan blades and lubricate the fan blade shrouds. (2) Thereafter, at each ``A'' check inspection, but not to exceed 500 hours TIS since last inspection and lubrication, whichever occurs first, inspect the fan blades and lubricate the fan blade shrouds. (3) Prior to further flight, remove from service fan blades that do not meet the return to service criteria stated in the SB, and replace with serviceable parts. (b) Perform an ultrasonic inspection (UI) of the fan blade root attachment area of fan blades, P/N 55A221, for cracks and perform a radius dimension inspection in accordance with Attachments 1 and 2 of PW SB No. PW4G-100-72-81, dated December 18, 1996, as follows: (1) Prior to accumulating 2,500 total part cycles (TPC), or within 250 part cycles after the effective date of this AD, whichever occurs later. (2) Prior to further flight, remove from service fan blades that do not meet the return to service criteria stated in the SB, and replace with serviceable parts. (c) Following a bird strike, prior to further flight remove from service undamaged fan blades immediately adjacent on both sides to any fan blades exhibiting bird ingestion damage in addition to the damaged fan blades, in accordance with Airbus A330 Aircraft Maintenance Manual, Section 72-00-00, Subtask 72-00-00-210-093, Paragraph (A)(1), dated October 1, 1996, and replace with serviceable parts. (d) Install a new or a modified fan blade assembly, in accordance with the requirements of PW SB No. PW4G-100-72-92, dated April 24, 1997, prior to December 31, 1998. Installation of a new of modified fan blade assembly, in accordance with PW SB No. PW4G-100- 72-92, dated April 24, 1997, constitutes terminating action to the inspection requirements of paragraphs (a), (b), and (c) of this AD. (e) 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. Operators shall submit their requests 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. (f) Special flight permits may be issued in accordance with Secs. 21.197 and 21.199 of the [[Page 28628]] Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (g) The actions required by this AD shall be done in accordance with the following PW SBs: ------------------------------------------------------------------------ Document No. Pages Date ------------------------------------------------------------------------ PW4G-100-72-69..................... 1-10 Aug. 6, 1996. Total pages: 10. PW4G-100-72-81..................... 1-8 Dec. 18, 1996. NDIP-883........................... 1-27 Dec. 11, 1996. NDIP-893........................... 1-9 Dec. 11, 1996. Total pages: 44. PW4G-100-72-92..................... 1-24 Apr. 24, 1997. Total pages: 24. ------------------------------------------------------------------------ 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 Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-6600, fax (860) 565- 4503. 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. (h) This amendment becomes effective on June 11, 1997. Issued in Burlington, Massachusetts, on May 15, 1997. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 97-13464 Filed 5-22-97; 9:57 am] BILLING CODE 4910-13-U