- Effective
- April 20, 1968
- Models
- DH.125 Series 1A, DH.125 Series 1A-522, DH.125 Series 3A
- Data sheet
- TCDSA3EU
- Product
- Aircraft · Large airplane
- Amendment
- 39-566
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 |
|---|---|---|---|
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On this page
The airworthiness directive
68-06-03 HAWKER SIDDELEY: Amdt. 39-566. Applies to Model DH. 125 airplanes, Series 1A, 1A/522 and 3A.
Compliance required as indicated.
To prevent a fully asymmetric flap condition in the lift dump position, within the next 150 hours' time in service after the effective date of this AD, replace the flap center hinge bolt, P/Ns 25CF71, 25CF1837, 25CF2387 and 25CF2357, with a self-retaining bolt, P/N 3110-7681, in accordance with Hawker Siddeley Service Bulletin 27-49-(1894) Revision 2, dated November 27, 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 becomes effective April 20, 1968.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.