- Effective
- December 11, 1967
- Models
- DH.125 Series 1A, DH.125 Series 1A-522
- Data sheet
- TCDSA3EU
- Product
- Aircraft · Large airplane
- Amendment
- 39-511
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 January 21, 2026.
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 | 0f93ca6a…43d2d26 | FAA DRS (API key needed) |
On this page
The airworthiness directive
67-30-04 HAWKER SIDDELEY: Amdt. 39-511 Part 39 Federal Register November 10, 1967. Applies to Model DH-125 Series 1A and 1A-522 Airplanes, Serial Numbers 25013 through 25104.
Compliance required within the next 500 hours' time in service after the effective date of this AD, unless already accomplished.
To preclude the possibility of engine mount beam failure, modify the engine mount beam by removing the foam filler, reinforcing the lower flanges at the outboard ends with bar inserts and installing aluminum guard plates, in accordance with Hawker Siddeley Service Bulletin 53- 22-(1723). Revisions 1, dated April 10, 1967, or later ARB-approved revision or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region.
This amendment effective December 11, 1967.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.