2019-19-11: Turbine Engine Compressor Section

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2019-19-11 Pratt & Whitney: Amendment 39-19747; Docket No. FAA-2019- 0771; Product Identifier 2019-NE-27-AD. (a) Effective Date This AD is effective September 26, 2019. (b) Affected ADs None. (c) Applicability This AD applies to Pratt & Whitney Models PW1519G, PW1521G, PW1521GA, PW1524G, PW1525G, PW1521G-3, PW1524G-3, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A turbofan engines that have accumulated fewer than 300 flight cycles. (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. (e) Unsafe Condition This AD was prompted by two recent in-flight shutdowns on PW PW1524G-3 model turbofan engines, due to failure of the low-pressure compressor (LPC) rotor 1 (R1). The FAA is issuing this AD to prevent failure of the LPC R1. The unsafe condition, if not addressed, could result in uncontained release of the LPC R1, damage to the engine, damage to the airplane, and loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within 50 flight cycles from the effective date of this AD, and thereafter at intervals not to exceed 50 flight cycles until the engine accumulates 300 flight cycles, borescope inspect each LPC inlet guide vane (IGV) stem for proper alignment. (2) Within 50 flight cycles from the effective date of this AD, and thereafter at intervals not to exceed 50 flight cycles until the engine accumulates 300 flight cycles, borescope inspect the LPC R1 for damage and cracks at the following locations: (i) The blades tips; (ii) the leading edge; (iii) the leading edge fillet to rotor platform radius; and (iv) the airfoil convex side root fillet to rotor platform radius. (3) As the result of the inspections required by paragraphs (g)(1) and (2) of this AD, before further flight, remove and replace the LPC if: (i) An IGV is misaligned; or (ii) there is damage on an LPC R1 that exceeds serviceable limits; or (iii) there is any crack in the LPC R1. Note 1 to paragraph (g): Guidance on determining serviceable limits can be found in PW Service Bulletin (SB) PW1000G-A-72-00- 0125-00A-930A-D, Issue No. 001, dated September 23, 2019, and PW SB PW1000G-A-72-00-0075-00B-930A-D, Issue No. 001, dated September 23, 2019. (h) Definition For the purpose of this AD, a misaligned IGV is an IGV that is rotated about its radial axis at a different angle than the remainder of the IGVs in the circumferential set. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j) of this AD. You may email your request to: ANE-AD-AMOC@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (j) Related Information For more information about this AD, contact Kevin M. Clark, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7088; fax: 781-238-7199; email: kevin.m.clark@faa.gov. (k) Material Incorporated by Reference None.