AD 80-12-07 R2
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Fokker Services | F27 Mark 050 | Airworthiness Directives; FOKKER Model F-27 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 100 | Airworthiness Directives; FOKKER Model F-27 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 200 | Airworthiness Directives; FOKKER Model F-27 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 300 | Airworthiness Directives; FOKKER Model F-27 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 400 | Airworthiness Directives; FOKKER Model F-27 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 500 | Airworthiness Directives; FOKKER Model F-27 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 600 | Airworthiness Directives; FOKKER Model F-27 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 700 | Airworthiness Directives; FOKKER Model F-27 Series Airplanes |
Unsafe Condition
Jamming of the nose landing gear in the retracted position due to leakage of the shock absorber; partial loss of electrical power capacity in flight due to inadequate attachment of bus bars on panels 1, 2, and 3; failure of the nose gear steering system due to trapped air in the steering motor; loss of electrical DC generator power in flight as a consequence of inadequate grounding of generator master switches; loss of electrical DC generator power in flight as a consequence of inadequate grounding of generator master switches; asymmetric extension of wing flaps due to certain failures of the mechanical drive system; failure of the engine mount due to use of improper material when manufactured; cable slippage from drum of aileron control due to inadequate flange on aileron cable drum; possible disconnection of an aileron control rod from the differential sector due to failure of the control rod bearing; unwanted opening of the large cargo door in flight due to wear and distortion; instability of the DC generator control system due to interaction with the static inverters; loosening of the aileron stops due to improper design; possible failure of the pneumatic system due to cracking of isolating valve bodies P/N ACM 16724 or ACM 26573; possible fatigue cracks and loose rivets in the upper surface of the RH horizontal stabilizer torsion box; loss of the main instrument panel fluorescent lighting system due to short circuiting.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect, rectify as appropriate, install improved components, modify systems, or comply with specific service bulletins as outlined in each item (e.g., Service Bulletin No. 27-109, 55-53, etc.).
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next 1,000 hours time-in-service after August 7, 1980 for item (53); within the next 10,000 flights for other items unless specified otherwise.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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