- Effective
- July 30, 1966
- Models
- F-27, F-27A, F-27B, F-27F, F-27G, F-27J
- Data sheet
- TCDS7A1
- Registered aircraft
- 1 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-252
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
66-16-04 FAIRCHILD: Amdt. 39-252 Part 39 Federal Register June 30, 1966. Applies to Models F-27, F-27A, F-27B, F-27F, F-27G, and F-27J Airplanes, Serial Numbers 1 through 122, Equipped with Center Hinge Wing Flap Asymmetry Switches, P/N 658-001.
Compliance required within the next 300 hours' time in service after the effective date of this AD unless already accomplished.
To prevent failure of the flap asymmetry switch to continuously detect an asymmetric condition as the asymmetry increases above the 3 degree setting, accomplish the following:
(a) Rewire asymmetry system in accordance with Fairchild-Hiller Service Bulletin No. 27-43, dated December 23, 1965, or later FAA-approved revision, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
(b) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the compliance time specified in this AD if the request contains substantiating data to justify the increase for that operator.
This directive effective July 30, 1966.
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.