- Effective
- January 3, 1970
- Models
- D.H. 104 Dove Series 1A, D.H. 104 Dove Series 2A, D.H. 104 Dove Series 5A, D.H. 104 Dove Series 5BA, D.H. 104 Dove Series 6A, D.H. 104 Dove Series 6BA and 4 more
- Data sheet
- TCDSA-807
- Registered aircraft
- 3 matched by model
- Product
- Aircraft · Small airplane
- Amendment
- 39-887
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.
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On this page
The airworthiness directive
69-25-06 HAWKER SIDDELEY AVIATION, LTD: Amdt. 39-887. Applies to Model DH-104 Dove Airplanes which have aileron lever P/N 4 WA.315 installed.
Compliance is required as indicated unless already accomplished.
To prevent fatigue failure of the aileron lever, accomplish the following:
(a) Visually inspect the aileron lever, P/N 4 WA.315 for cracks at the lugs for the attachment of the connecting rod and in the counterbored portion which receives the mass balance arm within the next 50 hours' time in service after the effective date of this AD unless already accomplished within the last 50 hours' time in service, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. If evidence of cracks is found, verify using dye penetrant or other FAA-approved equivalent inspection methods.
(b) If cracks are found during the inspection required by paragraph (a), before further flight, install a new forged aileron lever, P/N 4 WA.491 in accordance with Hawker Siddeley Aviation, Ltd. Dove Modification No. 967, or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region.
(c) If no cracks are found during the inspections required by paragraph (a), within the next 1,000 hours' time in service after the effective date of this AD, install a new forged aileron lever P/N 4 WA.491 in accordance with Hawker Siddeley Aviation, Ltd. Dove Modification No. 967, or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region.
(d) The inspection required in paragraph (a) may be discontinued after the new aileron lever, P/N 4 WA.491 or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region is installed.
(Hawker Siddeley Aviation, Ltd. Technical News Sheet CT (104) No. 151, Issue 4, dated 14 July 1969 covers this subject.)
This supersedes Amendment 454, Part 507 (27 F.R. 5793) AD 62-14-02. This amendment becomes effective January 3, 1970.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 3
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.