Airworthiness directives › 2022-03-16
AD 2022-03-16 Airworthiness Directives; General Electric Company Turbofan Engines
Applicability*9
This AD applies to General Electric Company (GE) GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx-1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx-1B76A/P2, GEnx-2B67, GEnx-2B67B, and GEnx-2B67/P model turbofan engines with a compressor discharge pressure (CDP) bolted joint assembled or reassembled with the 11C4525P01 torque fixture or assembled with the 11C4629P01 torque wrench.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) At the next engine shop visit after the effective date of this AD, perform an inspection of the CDP bolted joint for fractured or missing material using the Accomplishment Instructions, paragraph 3.A.(2) of GE GEnx-1B Service Bulletin (SB) 72-0495 R00, dated May 11, 2021 (GEnx-1B SB 72-0495) (for GEnx-1B models) or Accomplishment Instructions, paragraph 3.A.(2) of GE GEnx-2B SB 72-0433 R00, dated May 11, 2021, (GEnx-2B SB 72-0433) (for GEnx-2B models). (2) Repeat the inspection required by paragraph (g)(1) of this AD at every engine shop visit. (3) If a fractured or missing bolt or nut is found during any inspection required by paragraph (g)(1) or (2) of this AD, before further flight, perform piece part inspections of the stages 6-10 compressor rotor spool, CDP seal, and high-pressure turbine rotor stage 1 disk in accordance with the Instructions for Continued Airworthiness.
Unsafe condition
This AD was prompted by a report from the manufacturer of two findings of sheared CDP bolts during engine shop visits. The FAA is issuing this AD to prevent fracture of the CDP bolt. The unsafe condition, if not addressed, could result in damage to the engine and damage to the airplane.
Affected ADs
None.
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