- Effective
- February 27, 1966
- Published
- January 28, 1968
- Models
- D.H. 104 Dove Series 1A, D.H. 104 Dove Series 2A, D.H. 104 Dove Series 5A, D.H. 104 Dove Series 5BA, D.H. 104 Dove Series 6A, D.H. 104 Dove Series 6BA and 4 more
- Data sheet
- TCDSA-807
- Registered aircraft
- 3 matched by model
- Product
- Aircraft · Small airplane
- Amendment
- 39-185
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.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| FAA DRS HTML | 20 KB | 00894917…380ef95 | FAA DRS (API key needed) |
On this page
The airworthiness directive
66-05-02 HAWKER SIDDELEY: Amdt. 39-185, Part 39, Federal Register January 28, 1968. Applies to de Havilland Model 104 Dove Series Airplanes.
Compliance required within 150 hours' time in service after the effective date of this AD.
As a result of cracking of eye ends used in the rudder and elevator trim tab connecting rod assemblies, accomplish the following unless already accomplished.
(a) Remove eye ends, P/N's CM.2A and CM.2B, and inspect for cracks visually or by use of other FAA-approved methods.
(b) Replace cracked parts with uncracked parts of the same part number before further flight.
(Hawker Siddeley Aviation, de Havilland Division T.N.S. Dove (104) Series CT (104) No. 187 or later ARB-approved issues cover this same subject).
This directive effective February 27, 1966.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 3
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.