# AD 69-11-04: Control Pedal Force

- Type: Airworthiness directive
- Status: Current
- Products: Bell Helicopter Textron Canada 206A
- Effective: May 28, 1969
- Superseded by: Nothing supersedes this AD
- Product type: Aircraft, Rotorcraft
- Amendment: 39-778
- Registered aircraft: 23 may be affected, by airframe or engine model (OpenAirDocs)
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/3191D46FBBECB5C586256E0100547260.0001
- DRS record last changed: May 30, 2024
- Page: https://openairdocs.org/ad/69-11-04

## The airworthiness directive

69-11-04 BELL: Amdt. 39-778. Applies to Model 206A helicopters.

Compliance required as indicated.

To balance directional control pedal forces at cruise flight, to prevent pedal creep and to eliminate a possible interference between the pilots' feet and protruding head screws in the instrument console, accomplish the following:

a. Install and adjust the spring, P/N 206-001-721, and friction clamp, P/N 206-001- 710, within 50 hours' time in service after the effective date of this AD, unless already accomplished, in accordance with the instructions in Bell Helicopter Company Service Bulletin No. 206A-5, Reissue dated May 23, 1969, or later FAA-approved revision or in accordance with instructions approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, FAA.

b. Inspect and adjust, if necessary, the spring, P/N 206-001-721, and friction clamp, P/N 206-001-710, within 50 hours' time in service after the effective date of this AD, unless accomplished within the last 50 hours' time in service, in accordance with Item 4 on Page 2 of Bell Helicopter Company Service Bulletin No. 206A-5, Reissue dated May 23, 1969, or later FAA-approved revision, or in accordance with instructions approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, FAA.

c. Replace the three protruding head screws on the right and left side of the instrument panel console that are adjacent to the pilots' pedals and install equivalent flat head screws within 50 hours' time in service after the effective date of this AD, unless already accomplished, in accordance with the instructions in Bell Helicopter Company Service Letter No. 206A-120, dated May 16, 1969, or later FAA-approved revision or in accordance with an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, FAA.

(Bell Helicopter Company Model 206A Maintenance and Overhaul Instructions Interim Revisions No. 206A-69-20 and No. 206A-69-21 dated May 15, 1969, and No. 206A-69-22 dated May 23, 1969, pertain to this subject.)

This amendment becomes effective May 28, 1969. Revised June 14, 1969.

## Affected data sheets (1) (OpenAirDocs)

The type certificate data sheets whose models the AD names.

- [TCDS H2SW](https://openairdocs.org/tcds/H2SW): Bell Textron Canada Limited; names 1 of 12 models: 206A

## 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: 23 (23 by airframe model, 0 by engine model)
- Makers: Bell 23

Models with the most aircraft:

- [Bell 206A](https://openairdocs.org/model/bell-206a): 23 aircraft (airframe model)

All 1 models: https://openairdocs.org/ad/69-11-04/models.md
Every aircraft: https://openairdocs.org/ad/69-11-04/aircraft.md

Its text cites no advisory circulars or STCs.

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