AD 98-17-10 Airworthiness Directives; Pratt & Whitney Canada PW530A Series Turbofan Engines

Makes named: cessna. Models named: 550 Bravo. Read the applicability below — it usually turns on serial or part numbers too.

Pratt & Whitney Canada (PWC) PW530A series turbofan engines, with serial numbers (S/Ns) PCE-DA0001 through PCE- DA0059, and S/Ns PCE-DA0061 through PCE-DA0064 (S/N PCE-DA0060 is not affected, as it was shipped with the increased type design clearance). These engines are installed on but not limited to Cessna Citation Model 550 Bravo 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 inflight engine shutdown due to rubbing of the second stage stator vanes on the compressor rotor, accomplish the following: (a) In the event of an engine surge, make a record of the engine which surged and the date and approximate time of the event in the aircraft maintenance records. For this purpose, an engine surge is defined as unstable engine operation which is accompanied by unusual sounds which could be described as bangs, pops, growls, or rumbles and which may also be accompanied by increased engine vibration levels. [[Page 53562]] (b) If an engine surge event is experienced, prior to the next flight, inspect that engine for evidence of rubbing of the second stage stator vanes on the compressor rotor in accordance with PWC Service Bulletin (SB) No. PW500-72-30063, Revision 2, dated July 10, 1998. (c) If evidence of rubbing is discovered, prior to further flight, remove from service the engine that experienced rubbing and replace with a serviceable engine. (d) Within 200 hours time in service (TIS) after the effective date of this AD, or prior to December 31, 1998, whichever occurs first, rework all affected engines identified by S/N in the applicability of this AD to increase the clearance between the second stage stator vanes and the compressor rotor, in accordance with PWC SB No. PW500-72-30044, Revision 2, dated July 10, 1998. Completion of this rework constitutes terminating action to the inspection requirements 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 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) The requirements of this AD shall be done in accordance with the following PWC SBs: ---------------------------------------------------------------------------------------------------------------- Document No. Pages Revision Date ---------------------------------------------------------------------------------------------------------------- PW500-72-30063.................................. 1-5 2 July 10, 1998. Total pages: 5. PW500-72-30044.................................. 1-6 2 July 10, 1998. Total pages: 6. ---------------------------------------------------------------------------------------------------------------- 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 Canada, Inc., 1000 Marie-Victorin, Longueuil, Quebec, Canada J4G 1A1; Attn: Supervisor, Publications Customer Service (01CA4); telephone (514) 647-2705, fax (514) 647-2702. Copies may be inspected at the FAA, New England Region, Office of the Regional 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 October 21, 1998, to all persons except those persons to whom it was made immediately effective by priority letter AD 98-17-10, issued August 7, 1998, which contained the requirements of this amendment. Issued in Burlington, Massachusetts, on September 28, 1998. Diane Romanosky, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 98-26528 Filed 10-5-98; 8:45 am] BILLING CODE 4910-13-P