Airworthiness Directive · Amendment 39-22184 · Turbine section
International Aero Engines, LLC Turbofan Engines
Superseded. A later AD replaced this one: AD 2024-05-11. Comply with the one in force.
This AD applies to International Aero Engines, LLC PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G1-JM, PW1127GA-JM, PW1127G-JM, PW1129G-JM, PW1130G-JM, PW1133GA-JM, and PW1133G-JM model turbofan engines with an installed:
(1) High-pressure turbine (HPT) 1st-stage disk, part numbers (P/Ns) 30G4201, 30G6201, or 30G7301; and
(2) HPT 2nd-stage disk, P/Ns 30G3902, 30G5502, or 30G6602.
The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. That AD applies to certain International Aero Engines, LLC (IAE LLC) PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G1-JM, PW1127GA-JM, PW1127G-JM, PW1129G-JM, PW1130G- JM, PW1133GA-JM, and PW1133G-JM model turbofan engines. The table numbers of the service information referenced in paragraphs (g)(2) and (3) are incorrect. This document corrects those errors. In all other respects, the original document remains the same.
(1) For affected engines that have not incorporated Pratt & Whitney (PW) Service Bulletin (SB) PW1000G-C-72-00-0112-00A-930A-D, at the next engine shop visit after the effective date of this AD, perform the following:
(i) Ultrasonic inspection (USI) of the HPT 1st-stage disk using the Accomplishment Instructions, paragraph 9.A. or B., as applicable, of PW SB PW1000G-C-72-00-0188-00A-930A-D, Issue No: 002, dated July 8, 2022 (PW SB PW1000G-C-72-00-0188-00A-930A-D); and
(ii) USI of the HPT 2nd-stage disk using the Accomplishment Instructions, paragraph 9.C. or D., as applicable, of PW SB PW1000G-C-72-00-0188-00A-930A-D.
(2) For affected engines that have incorporated PW SB PW1000G-C-72-00-0112-00A-930A-D, with an installed HPT 1st-stage disk having a serial number (S/N) identified in the Accomplishment Instructions, Table 3., of PW SB PW1000G-C-72-00-0188-00A-930A-D, at the next engine shop visit after the effective date of this AD, perform a USI of the HPT 1st-stage disk using the Accomplishment Instructions, paragraph 9.A. or B., as applicable, of PW SB PW1000G-C-72-00-0188-00A-930A-D.
(3) For affected engines that have incorporated PW SB PW1000G-C-72-00-0112-00A-930A-D, with an installed HPT 2nd-stage disk having an S/N identified in the Accomplishment Instructions, Table 4., of PW SB PW1000G-C-72-00-0188-00A-930A-D, at the next engine shop visit after the effective date of this AD, perform a USI of the HPT 2nd-stage disk using the Accomplishment Instructions, paragraph 9.C. or D., of PW SB PW1000G-C-72-00-0188-00A-930A-D.
(4) Based on the results of the USIs required by paragraphs (g)(1) through (3) of this AD, if any HPT 1st-stage disk or HPT 2nd-stage disk does not pass the USI, as specified in the Accomplishment Instructions, paragraphs 9.A. through D., of PW SB PW1000G-C-72-00-0188-00A-930A-D, as applicable, before further flight, remove the HPT 1st-stage disk or HPT 2nd-stage disk from service and replace with a part eligible for installation.
(5) For affected engines that have incorporated PW SB PW1000G-C-72-00-0112-00A-930A-D and do not require an inspection per paragraph (g)(2) or (3) of this AD, no further action is required.
(1) For the purpose of this AD, a “part eligible for installation” is:
(i) Any HPT 1st-stage disk that has passed the USI required by paragraphs (g)(1)(i) or (g)(2) of this AD.
(ii) Any HPT 2nd-stage disk that has passed the USI required by paragraphs (g)(1)(ii) or (g)(3) of this AD.
(iii) Any HPT 1st-stage disk that has incorporated PW SB PW1000G-C-72-00-0112-00A-930A-D and does not require an inspection per paragraph (g)(2) of this AD.
(iv) Any HPT 2nd-stage disk that has incorporated PW SB PW1000G-C-72-00-0112-00A-930A-D and does not require an inspection per paragraph (g)(3) of this AD.
(v) Any HPT 1st-stage disk or HPT 2nd-stage disk with a certificate of conformance that shows “PW1000G-C-72-00-0188-00A-930A-D,” “1 CODE 45S,” or identified by part marking “21CC332” or “SB 72-0188.”
(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 “M” flange. Separation of the “M” flange solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit.
