- Effective
- August 5, 1968
- Models
- DH.125 Series 1A, DH.125 Series 1A-522, DH.125 Series 1A/R-522, DH.125 Series 1A/S-522, DH.125 Series 3A, DH.125 Series 3A/R, DH.125 Series 3A/RA, DH.125 Series 400A
- Data sheet
- TCDSA3EU
- Registered aircraft
- 2 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-626
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
68-16-01 HAWKER SIDDELEY: Amendment 39-626. Applies to all Series of Model DH- 125 airplanes.
Compliance required as indicated, unless already accomplished.
To prevent engine flameouts during icing conditions, within the next 15 hours' time in service after the effective date of this AD, or before further flight into known or predicted icing conditions, whichever occurs first, install a placard on the flight instrument panel in clear view of the pilot reading as follows:
"TURN ENGINE RELIGHT SWITCH ON WHEN OPERATING ENGINE ANTI- ICING SYSTEM."
This supersedes Amendment 39-549 (33 F.R. 2504), AD 68-03-02.
This amendment becomes effective August 5, 1968.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 2
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.