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Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: \n\nPART 39-AIRWORTHINESS DIRECTIVES \n\n1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n§ 39.13 (Amended) \n\n2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2019-19-11, Amendment 39-19747 (84 FR 50719, September 26, 2019) and adding the following new AD: \n\n\n\n\n\nFAA Aviation Safety AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html \n\n2019-21-11 Pratt & Whitney: Amendment 39-19777; Docket No. FAA-2019-0843; Product Identifier 2019-NE-27-AD. \n\n(a) Effective Date \n\n\n\tThis AD is effective October 29, 2019. \n\n(b) Affected ADs \n\n\n\tThis AD replaces AD 2019-19-11, Amendment 39-19747 (84 FR 50719, September 26, 2019). \n\n(c) Applicability \n\n\n\tThisAD applies to Pratt & Whitney Model PW1519G, PW1521G, PW1521GA, PW1524G, PW1525G, PW1521G-3, PW1524G-3, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines that have accumulated fewer than 300 flight cycles since new (CSN) or that have accumulated fewer than 300 flight cycles since installation of v2.11.7 or v2.11.8 electronic engine control (EEC) software. \n\n(d) Subject \n\n\n\tJoint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. \n\n(e) Unsafe Condition \n\n\n\tThis AD was prompted by a recent in-flight shutdown due to failure of the low-pressure compressor (LPC) rotor 1 (R1) and by findings of cracked LPC R1s during inspections. 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. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) Required Actions \n\n\n\t(1) Except for those engines identified in paragraph (g)(2) of this AD, borescope inspect the LPC R1 for damage and cracks at the locations in paragraph (g)(1)(iv) of this AD as follows: \n\t(i) For engines that have accumulated fewer than 300 flight cycles since new (CSN), inspect within 50 flight cycles from September 26, 2019 (the effective date of AD 2019-19-11). \n\t(ii) For engines that have accumulated fewer than 300 flight cycles since installation of v2.11.7 or v2.11.8 electronic engine control (EEC) software, inspect within 50 flight cycles from the effective date of this AD. \n\t(iii) Thereafter, at intervals not to exceed 50 flight cycles until the engine accumulates 300 flight CSN or accumulates 300 flight cycles since the installation of v2.11.7 or v2.11.8 EEC software, whichever occurs later, repeat this borescope inspection for damage and cracks at the locations in paragraph (g)(1)(iv) of this AD.(iv) Perform the borescope inspection required by paragraphs (g)(1)(i) through (iii) of this AD at the following locations: \n\t(A) the blades tips; \n\t(B) the leading edge; \n\t(C) the leading edge fillet to rotor platform radius; and \n\t(D) the airfoil convex side root fillet to rotor platform radius. \n\t(2) For all affected PW model turbofan engines installed as a "zero time spare," except for PW1519G, PW1521GA and PW1919G model turbofan engines, within 15 flight cycles from the effective date of this AD, and thereafter at intervals not to exceed 15 flight cycles until the engine accumulates 300 flight CSN, perform the borescope inspections required by paragraph (g)(1) of this AD. \n\t(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: \n\t(i) there is damage on an LPC R1 that exceeds serviceable limits; or \n\t(ii) there is any crack in the LPC R1. \n\n\n\tNote 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. 002, dated October 22, 2019, and PW SB PW1000G-A-72-00-0075-00B-930A-D, Issue No. 003, dated October 22, 2019. \n\n(h) Definition \n\n\n\tFor the purpose of this AD, a "zero time spare" is an engine that had zero flight hours time-in-service when it was installed on an airplane after the airplane had entered service. \n\n(i) Alternative Methods of Compliance (AMOCs) \n\n\n\t(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. \n\t(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. \n\n(j) Related Information \n\n\n\tFor 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. \n\n(k) Material Incorporated by Reference \n\n\n\tNone. \n\n\n\tIssued in Burlington, Massachusetts, on October 25, 2019. Karen M. Grant, Acting Manager, Engine & Propeller Standards Branch, Aircraft Certification Service. 8
