- Effective
- September 7, 1964
- Published
- August 7, 1964
- Models
- D.H.114 Heron Series 2A, D.H.114 Heron Series 2DA, D.H.114 Heron Series 2X
- Data sheet
- TCDSA-816
- Registered aircraft
- 1 matched by model
- Product
- Aircraft · Small/large airplane
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 | 19 KB | aebd87be…509dc3f | FAA DRS (API key needed) |
On this page
The airworthiness directive
64-19-02 DEHAVILLAND: Amdt. 786 Part 507 Federal Register August 7, 1964. Applies to Model 114 Heron Aircraft.
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/Ns CM2A and CM2B, and make the crack test specified in T.N.S. Heron (114) No. CF10 issued February 24, 1964.
(b) Replace cracked parts before further flight. (Hawker Siddeley Aviation, deHavilland Division T.N.S. Heron (114) No. CF10 covers this same subject.)
This directive effective September 7, 1964.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 1
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.