AD 2022-18-16

final rule
Data completeness: 70%

Airworthiness Directives; General Electric Company Turboshaft Engines

AD Number
2022-18-16
Status
final_rule
Effective Date
Product Category
engine
Docket
Docket No. FAA-2022-0690
FR Citation
87 FR 54130

Applicability

TypeManufacturerModelDetails
engine General Electric Company Airworthiness Directives; General Electric Company Turboshaft Engines

Unsafe Condition

The failure of the stage 1 turbine aft cooling plates, stage 2 turbine forward cooling plates, turbine interstage seals, and stage 4 turbine disks. The unsafe condition, if not addressed, could result in uncontained part release, damage to the engine, damage to the helicopter, and possible loss of control of the helicopter.

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Required Actions

Within 90 days after the effective date of this AD, revise the ALS of the existing GE CT7-8 Turboshaft EMM and the operator's existing approved maintenance or inspection program, as applicable, by incorporating the following reduced life limits: (i) For stage 1 turbine aft cooling plate, part number (P/N) 6064T09P02, change the life limit cycles from 6,600 cycles since new (CSN) to 4,900 CSN; (ii) For stage 2 turbine forward cooling plate, P/N 4106T80P01, change the life limit cycles from 8,000 CSN to 7,200 CSN; (iii) For turbine interstage seal, P/N 4111T86P03, change the life limit cycles from 29,200 CSN to 19,000 CSN; and (iv) For stage 4 turbine disk, P/N 6068T32P04, change the life limit cycles from 24,100 CSN to 12,100 CSN. After performing the actions required by paragraph (g)(1) of this AD, except as provided in paragraph (h) of this AD, no alternative life limits may be approved.

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Compliance Time

Within 90 days after the effective date of this AD

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Affected Aircraft

General Electric Company (GE) CT7-8A model turboshaft engines.

AI-generated summary from the source AD text. Verify against the official source before acting.

Source: Official FAA Source ↗

Retrieved: Apr 6, 2026

Rights: U.S. Government Public Domain

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