# AD 69-23-02: Stage 2 Compressor Rotor Disc Shafts

- Type: Airworthiness directive
- Status: Historical
- Products: General Electric CT58-100-2, CT58-110-1, CT58-110-2, CT58-140-1 and CT58-140-2
- Effective: October 15, 1970
- Superseded by: [AD 2001-18-06](https://openairdocs.org/ad/2001-18-06)
- Product type: Engine
- Amendment: 39-1086
- Registered aircraft: 53 may be affected, by airframe or engine model (OpenAirDocs)
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/7740382CCBF9C89286256E4B005E73A2.0001
- DRS record last changed: August 7, 2025
- Page: https://openairdocs.org/ad/69-23-02

## The airworthiness directive

69-23-02 GENERAL ELECTRIC: Amdt. 39-870 as amended by Amendment 39-1086. Applies to models CT58-100-1, CT58-100-2, CT58-110-1, CT58-110-2, CT58-140-1, CT58-140-2, T58-GE-1 and T58-GE-5 turboshaft engines.

Compliance required as indicated.

To ensure adequate life limit margin for stage 2 compressor rotor disc shafts the life limits on these parts have been reduced below the figures currently approved.

Unless already accomplished, remove from service stage 2 compressor rotor disc shafts prior to reaching the revised life limit or in accordance with the removal schedule given below for those parts which are close to or exceed the limit on the effective date of this AD.

Part Numbers

Previous Life Limits

Revised Life Limits

Removal Schedule Above 2,400 hrs. 5,800 Cycles

Hrs. Cycles Hrs. Cycles

Remove within* 37E500153P101 2,500 8,000 2,500 6,000 100 Hrs. 200 Cycles 37E500213P101 2,500 8,000 2,500 6,000 100 Hrs 200 Cycles37E500213P103 2,500 8,000 2,500 6,000 100 Hrs. 200 Cycles

Above 2,950 Hrs. 5,900 Cycles Remove within* 5008T79P01 10,000 40,000 3,000 6,000 50 Hrs. 100 Cycles 37E500153P101M 10,000 40,000 3,000 6,000 50 Hrs. 100 Cycles

Above 5,150 Hrs. 8,400 Cycles Remove within* 5005T34P01 5,000 10,000 5,200 8,500 50 Hrs. 100 Cycles 5005T34P03 5,000 10,000 5,200 8,500 50 Hrs. 100 Cycles 5008T79P02 5,000 10,000 5,200 8,500 50 Hrs. 100 Cycles

*Time in service or cycles, whichever occurs first after the effective date of this AD.

For the purposes of this AD a cycle is considered as any engine operating sequence involving engine start, at least one acceleration to a power required for takeoff and shutdown.

Amendment 39-870 effective November 15, 1969.

This amendment 39-1086 is effective October 15, 1970.

## Affected data sheets (1) (OpenAirDocs)

The type certificate data sheets whose models the AD names.

- [TCDS 1E3](https://openairdocs.org/tcds/1E3): General Electric Company; names 5 of 5 models: CT58-100-2, CT58-140-2, CT58-140-1, CT58-110-1, CT58-110-2

## Registered aircraft it may apply to (OpenAirDocs)

Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment.

- Aircraft: 53 (0 by airframe model, 53 by engine model)
- Makers: Sikorsky 42, Boeing-Vertol 5, Columbia Helicopters 2, Boeing V-Columbia Helicopters 1, Carson Helicopters / Sikorsky 1, Kawasaki Vertol 1, Vertol 1

Models with the most aircraft:

- [GE CT58-140-2](https://openairdocs.org/engine/ge-ct58-140-2): 33 aircraft (engine model)
- [GE CT58-140-1](https://openairdocs.org/engine/ge-ct58-140-1): 20 aircraft (engine model)

All 2 models: https://openairdocs.org/ad/69-23-02/models.md
Every aircraft: https://openairdocs.org/ad/69-23-02/aircraft.md

## Related documents

- [AD 2001-18-06](https://openairdocs.org/ad/2001-18-06) (historical): Engine Life-limited Rotating Parts · General Electric CT58-100-2, CT58-110-1, CT58-110-2 and 2 more. Effective Oct 18, 2001. Supersedes this AD

Its text cites no advisory circulars or STCs.

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