2022-15-03: Turbine Engine Compressor Section

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by: a. Removing Airworthiness Directive 2021-14-06, Amendment 39-21633 (86 FR 36061, July 8, 2021); and b. Adding the following new airworthiness directive: 2022-15-03 Pratt & Whitney: Amendment 39-22122; Docket No. FAA-2022-0384; Project Identifier AD-2022-00027-E. (a) Effective Date This airworthiness directive (AD) is effective August 19, 2022. (b) Affected ADs This AD replaces AD 2021-14-06, Amendment 39-21633 (86 FR 36061, July 8, 2021). (c) Applicability This AD applies to Pratt & Whitney PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. (e) Unsafe Condition This AD was prompted by reports of in-flight shutdowns due to failure of the low-pressure compressor (LPC) rotor 1 (R1) and by subsequent findings of cracked LPC R1s during inspection. The FAA is issuing this AD to prevent failure of the LPC R1. The unsafe condition, if not addressed, could result in an uncontained release of the LPC R1, damage to the engine, damage to the airplane, and loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-3, PW1525G, and PW1525G-3 model turbofan engines with installed electronic engine control (EEC) full authority digital electronic control (FADEC) software earlier than EEC FADEC software version V2.11.10.4, before further flight, remove the EEC FADEC software and install EEC FADEC software version eligible for installation. (2) For PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines with installed EEC FADEC software earlier than EEC FADEC software version V9.5.6.7, before further flight, remove the EEC FADEC software and install EEC FADEC software version eligible for installation. (3) For the model turbofan engines identified in paragraphs (g)(1) and (g)(2) of this AD, before further flight, perform a one-time borescope inspection (BSI) of the LPC R1 for damage and cracks at the following LPC R1 locations: (i) The blade tip; (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. (4) Based on the results of the BSI required by paragraph (g)(3) of this AD, before further flight, remove and replace the LPC R1 if: (i) There is damage on an LPC R1 that exceeds serviceable limits; or (ii) Any crack in the LPC R1 exists. Note 1 to paragraph (g)(4): Guidance on determining the serviceable limits in paragraphs (g)(4) and (6) of this AD can be found in Pratt & Whitney (PW) Service Bulletin (SB) PW1000G-A-72-00-0125-00A-930A-D, Issue No. 004, dated October 13, 2021, and PW SB PW1000G-A-72-00-0075-00B-930A-D, Issue No. 004, dated July 21, 2021. (5) For PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-3, PW1525G, and PW1525G-3 model turbofan engines with EEC FADEC software version V2.11.10.4 or later installed, within 15 flight cycles after receipt of Onboard Maintenance Message fault code 7100F0029 or 7100F0030, perform a BSI of the LPC R1 for damage and cracks at the locations specified in paragraph (g)(3) of this AD if the fault code is displayed on the Active Failure Messages and meets the following criteria: (i) N1 Exceedance is above 95.2%; (ii) N1 Exceedance occurred above 29,100 feet; (iii) N1 Exceedance occurs for a duration of 40 seconds (15 seconds of cockpit display) or more during any flight; and (iv) Compressor intermediate case (CIC) assembly installed has part number (P/N) 5379926, P/N 5379940, P/N 5379946, or P/N 5379926-001. Note 2 to paragraph (g)(5): Guidance on determining the N1 Exceedance duration can be found in Section PW1000G-A-72-00-00-02A-0B5A-A of PW engine maintenance manual (EMM), Issue No. 016, dated January 15, 2021. Note 3 to paragraph (g)(5): Guidance on performing the BSI can be found in Section PW1000G-A-72-31-00-00A-312A-D of PW EMM, Issue No. 017, dated March 19, 2021. (6) Based on the results of the BSI required by paragraph (g)(5) of this AD, before further flight, remove and replace the LPC R1 if: (i) There is damage on an LPC R1 that exceeds serviceable limits; or (ii) Any crack in the LPC R1 exists. (7) For all affected model turbofan engines, at the next engine shop visit after the effective date of this AD, remove CIC assembly with P/N 5379926, P/N 5379940, P/N 5379946, or P/N 5379926-001 and replace with a CIC assembly eligible for installation. (8) For PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-3, PW1525G, and PW1525G-3 model turbofan engines with installed EEC FADEC software version V2.11.10.4, at the next engine shop visit after the effective date of this AD, remove the EEC FADEC software and install EEC FADEC software version eligible for installation. (9) For PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines with installed EEC FADEC software version V9.5.6.7, at the next engine shop visit after the effective date of this AD, remove the EEC FADEC software and install EEC FADEC software version eligible for installation. (h) Definitions (1) For the purpose of this AD, "EEC FADEC software version eligible for installation" is EEC FADEC software version V2.11.12.1 or later for PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-3, PW1525G, and PW1525G-3 model turbofan engines, and EEC FADEC software version V9.6.5.6 or later for PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines. (2) For the purpose of this AD, an "engine shop visit" is the induction of an engine into the shop for maintenance involving the separation of the LPC Flange 1 or separation of the LPC Flange 4, except for the following situations, which do not constitute an engine shop visit. (i) Separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance. (ii) Separation of engine flanges solely for the purpose of replacing the fan without subsequent maintenance. (3) For the purpose of this AD, a "CIC assembly eligible for installation" is any CIC assembly that does not have P/N 5379926, P/N 5379940, P/N 5379946, or P/N 5379926-001. (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)(1) of this AD and email 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 (1) For more information about this AD, contact Mark Taylor, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238-7229; email: Mark.Taylor@faa.gov . (2) For service information identified in this AD, contact Pratt & Whitney, 400 Main Street, East Hartford, CT 06118; phone: (800) 565-0140; email: help24@pw.utc.com; website: http://fleetcare.pw.utc.com. (3) You may view this referenced service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call (817) 222-5110. (k) Material Incorporated by Reference None. Issued on July 7, 2022. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2022-15131 Filed 7-14-22; 8:45 am]BILLING CODE 4910-13-P