- Effective
- August 19, 1969
- Model
- 206A
- Data sheet
- TCDSH2SW
- Registered aircraft
- 23 matched by model
- Product
- Aircraft · Rotorcraft
- Amendment
- 39-820
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. The FAA’s own copy is the authoritative one. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
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On this page
The airworthiness directive
69-17-02 BELL: Amdt. 39-820. Applies to Bell Model 206A helicopters, Serial Numbers 1 through 412, 415 through 421, 423 through 428, 430 through 435, and 438 having co-pilot controls installed.
Compliance required within 10 hours' time in service after the effective date of this AD, unless already accomplished.
To prevent a possible restriction of the cyclic control system, accomplish the following one-time inspection and lever assembly replacement, as necessary:
a. Remove the co-pilot's seat, P/N 206-031-141, to expose the cyclic control lever assembly.
b. Inspect the control bearings in each end of the lever assembly, P/N 206-001-339- 1, for proper staking, as specified in Items 2, 3 and 4 of Bell Helicopter Company Service Bulletin No. 206A-13, dated August 4, 1969, or by a method approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, FAA.
c. Remove and replace lever assemblies that have improper stakedcontrol bearings before further flight.
This amendment becomes effective on August 19, 1969.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 23
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1967 | 3 |
|---|---|
| 1968 | 4 |
| 1969 | 7 |
| 1970 | 2 |
| 1971 | 2 |
5 with no year recorded