Airworthiness Directive · Amendment 39-16954 · General Electric Company (GE) Turbofan Engines
General Electric Company (GE) Turbofan Engines
This AD is applicable to all GE CF6-80C2 model turbofan engines, including engines marked on the engine data plate as CF6-80C2B7F1.
We are adopting a new airworthiness directive (AD) for all GE CF6-80C2 model turbofan engines, including engines marked on the engine data plate as CF6-80C2B7F1. This AD was prompted by a report of a supplier shipping a batch of nonconforming No. 3 bearing packings that had incorrect cooling holes and by subsequent reports of nonconforming No. 3 bearing packings being installed on engines in service. This AD requires a one-time inspection of the No. 3 bearing packing for an incorrect cooling hole size and, if it is found nonconforming, removing the packing and removing certain engine rotating life-limited parts (LLPs), if they were operated with unacceptable rotor bore cooling flow for a specified number of cycles. We are issuing this AD to prevent an uncontained failure of the high-pressure compressor (HPC) rotor or the low-pressure turbine (LPT) rotor, or both, which could cause damage to the airplane.
(1) Perform a one-time inspection of the No. 3 bearing packing. Use paragraphs 3.A.(1) through 3.A.(1)(b) of the Accomplishment Instructions of GE Service Bulletin (SB) No. CF6-80C2 S/B 72-1405, Revision 01, dated December 16, 2011, to do your inspection. Inspect as follows:
(i) Before 5,500 engine cycles-in-service (CIS) since the last engine shop visit where the fan was removed from the core, or within 500 CIS from the effective date of this AD, whichever occurs later; or
(ii) At the next shop visit, if the engine passes an optional borescope inspection (BSI) within 500 CIS from the effective date of this AD.
(2) Remove the packing from service before further flight if the wrong packing part number (P/N) is found on the engine during the inspection of paragraph (f)(1) of this AD.
The optional BSI identified in paragraph (f)(1)(ii) of this AD must determine an “ACCEPTABLE FLOW” packing is installed. Use paragraph 3.A, excluding subparagraphs 3.A.(4)(a) 6 through 3.A.(4)(a) 9 and 3.A.(4)(b) 5, of the Accomplishment Instructions of GE SB CF6-80C2 S/B 72-1427, dated December 16, 2011, to do your BSI.
Remove the following rotating parts from service, if they were operated for 5,500 CIS or more with a packing determined to be an “UNACCEPTABLE FLOW” packing using paragraph 3.A.(1)(c) of the Accomplishment Instructions of GE SB CF6-80C2 S/B 72-1405, Revision 01, dated December 16, 2011:
(1) HPC rotor stage 10-through-14 spool, any P/N,
(2) HPC rotor stage 11-through-14 spool, any P/N,
(3) LPT rotor stage 3 disk, P/N 9373M53P05, and
(4) LPT rotor stage 4 disk, P/N 9373M54P03.
After the effective date of this AD, do not install or reinstall in any engine any rotating part that has been removed from service in accordance with paragraph (h) of this AD.
For the purposes of this AD, an engine shop visit is the induction of an engine into the shop after the effective date of this AD, where the separation of a major engine flange occurs; except the following maintenance actions, or any combination, are not considered engine shop visits:
(1) Induction of an engine into a shop solely for removal of the compressor top or bottom case for airfoil maintenance or variable stator vane bushing replacement.
(2) Induction of an engine into a shop solely for replacement of the turbine rear frame.
(3) Induction of an engine into a shop solely for replacement of the accessory gearbox or transfer gearbox, or both.
(4) Induction of an engine into a shop solely for core vibration trim balance procedure that requires separation of a major engine flange.
An inspection of the No. 3 bearing packing performed before the effective date of this AD using GE SB CF6-80C2 S/B 72-1405 satisfies the requirements of paragraph (f)(1) of this AD.
