2021-26-04: 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 2019-18-08, Amendment 39-19735 (84 FR 49944, September 24, 2019); and b. Adding the following new airworthiness directive: 2021-26-04 Engine Alliance: Amendment 39-21862; Docket No. FAA-2021-1069; Project Identifier AD-2021-00308-E. (a) Effective Date This airworthiness directive (AD) is effective January 12, 2022. (b) Affected ADs This AD replaces AD 2019-18-08, Amendment 39-19735 (84 FR 49944, September 24, 2019). (c) Applicability This AD applies to all Engine Alliance (EA) GP7270 and GP7277 model turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. (e) Unsafe Condition This AD was prompted by an uncontained failure of the engine fan hub. The FAA is issuing this AD to detect defects, damage, and cracks that could result in an uncontained failure of the engine fan hub assembly. The unsafe condition, if not addressed, could result in uncontained failure of the engine fan hub assembly, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For EA GP7270 and GP7277 model turbofan engines with engine fan hub assembly part numbers (P/Ns) 5760221, 5760321, or 5760001, within 1,700 cycles since new, within 150 flight cycles (FCs) after October 9, 2019 (the effective date of AD 2019-18-08), within 330 FCs since an eddy current inspection (ECI) was performed using the Accomplishment Instructions of EA Turbojet Engines Alert Service Bulletin (ASB) EAGP7-A72-389, Revision No. 6, dated November 21, 2019, or earlier versions of that ASB, or before further flight, whichever occurs later: (i) For engine fan hub assemblies at the low-pressure compressor (LPC) module assembly level, perform an ECI of the engine fan hub blade slot bottom and blade slot front edge, and perform an ultrasonic test (UT) inspection of the fan hub rim area, using the Accomplishment Instructions, Part A-For Fan Hubs at LPC Module Assembly Level, paragraphs 1.B., 1.C., and 1.E., of EA Turbojet Engine ASB EAGP7-A72-389, Revision No. 7, dated October 8, 2021 (EAGP7-A72-389, Revision No. 7). (ii) For engine fan hub assemblies at the piece part level, perform an ECI of the engine fan hub blade slot bottom and blade slot front edge, and perform a UT inspection of the fan hub rim area, using the Accomplishment Instructions, Part B-For Fan Hubs at Piece Part Level, paragraphs 1.B., 1.C., and 1.E., of EAGP7-A72-389, Revision No. 7. (iii) For engine fan hub assemblies installed in an engine (on-wing or off-wing), perform an ECI of the engine fan hub blade slot bottom and blade slot front edge, and perform a UT inspection of the fan hub rim area, using the Accomplishment Instructions, Part C-For Fan Hubs Installed in an Engine, paragraphs 3.B., 3.C., and 3.E., of EAGP7-A72-389, Revision No. 7. (2) Thereafter, at intervals not exceeding 290 FCs since the previous ECI and UT inspection, repeat the ECI of the engine fan hub blade slot bottom, ECI of the blade slot front edge, and UT inspection of the fan hub rim area required by paragraphs (g)(1)(i) through (iii) of this AD. (3) If, during any ECI or UT inspection required by paragraphs (g)(1) through (g)(2) of this AD, a rejectable indication is found, before further flight, remove the engine fan hub assembly from service and replace with a part that is eligible for installation. (4) For all GP7270 and GP7277 model turbofan engines, after the effective date of this AD: (i) At the next disassembly of the engine fan hub blade lock assembly, visually inspect the fan hub fan blade lock groove area (also known as the fan hub lock ring contact area) for damage. (ii) At the next reassembly of the engine fan hub blade lock assembly, visually inspect the following areas of the engine fan hub for damage: (A) The fan hub scallop areas; (B) The fan hub bore area behind the balance flange; (C) The fan hub fan blade lock retention hooks; (D) The fan hub rim face; and (E) The clinch nut holes. (iii) After any reassembly of the fan hub blade lock assembly, before further flight, perform an independent inspection for damage of the areas of the engine fan hub identified in paragraph (g)(4)(ii) of this AD. (iv) Thereafter, repeat the inspections required by paragraphs (g)(4)(i) through (iii) of this AD at each disassembly and reassembly of the engine fan hub blade lock assembly, as applicable. (v) As an optional terminating action to the inspection and independent inspection requirements of paragraphs (g)(4)(i) through (iv) of this AD, insert the requirements for the visual inspections and independent inspections required by paragraphs (g)(4)(i) through (iv) as Required Inspection Items in the existing approved continuous airworthiness maintenance program for the airplane. (vi) If damage is found that exceeds serviceable limits during the inspections required by paragraphs (g)(4)(i) through (iv) of this AD, before further flight, remove the engine fan hub assembly from service and replace it with a part eligible for installation. (5) For GP7270 and GP7277 model turbofan engines with engine serial numbers P550101 through P550706, inclusive, within 200 FCs from August 1, 2020 or before further flight, whichever occurs later, remove the engine fan hub blade lock assembly, P/N 5700451, and replace it with a part eligible for installation. Note 1 to paragraph (g)(5): EA Turbojet Engines ASB EAGP7-A72-418, Revision No. 1, dated January 11, 2019, contains guidance on replacement of the engine fan hub blade lock assembly. (h) Credit for Previous Actions You may take credit for the ECI inspections required by paragraph (g)(1)(i) through (iii) of this AD if you performed the ECI inspections before the effective date of this AD using EA ASB EAGP7-A72-389, Revision No. 6, dated November 21, 2019, or an earlier version. (i) Definitions (1) For the purpose of this AD, a "part eligible for installation," when referring to replacement of the engine fan hub assembly, is a part that has passed the inspections required by paragraph (g)(1) of this AD. (2) For the purpose of this AD, a "part eligible for installation," when referring to replacement of the engine fan hub blade lock assembly, is: (i) A part that is not P/N 5700451, or (ii) An engine fan hub blade lock assembly that has been modified in accordance with EA ASB EAGP7-A72-418, Revision No. 1, dated January 11, 2019, or EA ASB EAGP7-A72-418, Revision No. 0, dated December 7, 2018. (3) For the purpose of this AD, an "independent inspection" is a second visual inspection performed by an individual qualified to perform inspections who was not involved in the original inspection of the engine fan hub assembly following disassembly and reassembly of the engine fan hub blade lock assembly. (j) 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 (k) of this AD. Information may be emailed to: [email protected]. (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. (k) Related Information For more information about this AD, contact Stephen Elwin, Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: (781) 238-7236; fax: (781) 238-7199; email: [email protected]. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Engine Alliance (EA) Turbojet Engines Alert Service Bulletin EAGP7-A72-389, Revision No. 7, dated October 8, 2021. (ii) [Reserved] (3) For EA service information identified in this AD, contact Engine Alliance, 411 Silver Lane, East Hartford, CT, 06118; phone: (800) 565-0140; email: [email protected]; website: www.engineallianceportal.com. (4) You may view this 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued on December 8, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021-27981 Filed 12-27-21; 8:45 am]BILLING CODE 4910-13-P