- Effective
- May 3, 1965
- Published
- April 2, 1965
- 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
- Amendment
- 39-52
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 | d733f147…7072e62 | FAA DRS (API key needed) |
On this page
The airworthiness directive
65-08-01 HAWKER SIDDELEY: Amdt. 39-52 Part 39 Federal Register April 2, 1965. Applies to de Havilland Model 114 "Heron" Aircraft.
Compliance required as indicated.
To prevent further cases of overheating of electric cables in the cockpit and fuselage nose area, accomplish the following:
Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, dismantle, clean, inspect, replace and modify as required, the main ground (earth) assembly in the forward fuselage in accordance with Hawker Siddeley Technical News Sheet Heron (114) No. N.4, Issue 1, dated July 20, 1964.
(Hawker Siddeley Aviation, de Havilland Division, Technical News Sheet Heron (114) No. N.4, Issue 1, dated July 20, 1964, covers this same subject.)
This directive effective May 3, 1965.
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.