Results
2023-09-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by a report that certain environmental control system (ECS) pre-cooler clamp assemblies may not conform to specifications. This AD requires an inspection of the pre-cooler clamps and replacement of non- conforming pre-cooler clamps. The FAA is issuing this AD to address the unsafe condition on these products.
2002-08-11: This amendment supersedes an existing airworthiness directive (AD), that is applicable to certain Pratt & Whitney JT9D series turbofan engines. That AD currently requires revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional critical life-limited parts for enhanced inspection. This amendment is prompted by an FAA study of in-service events involving uncontained failures of critical rotating engine parts. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
80-01-08: 80-01-08 PIPER: Amendment 39-3653. Applies to Models PA-31T serial numbers 31T-7920001 thru 7920068, 7920070 thru 7920080; and PA-31T1 serial numbers 31T-7904001 thru 7904044. Compliance required within the next 25 hours of operation as indicated unless already accomplished. To preclude the necessity of inflight engine shutdown due to oil loss caused by leakage of the oil cooler inlet hose assembly, accomplish the following on each engine: Remove engine cowlings and remove oil cooler inlet hose, P/N 80026-05. Cap engine outlet immediately upon removal of hose. Remove the band clamp from the 90-degree fitting end of the fire sleeve and pull fire sleeve back as far as possible to inspect steel braiding for kinking. If kinking is found, replace hose. (Note: Kinking will usually be noticed on the steel braiding between the midpoint of the hose and the 90-degree fitting end.) If no evidence of kinking is found and with band clamp still removed, pressure test hose to 500 psi using dry nitrogen with hose submerged in water. (Note: A suitable pressure test arrangement is to cap both ends of the hose with appropriate AN hardware items, one of which has been drilled and fitted with a Schrader valve.) If leakage is observed, replace hose with a new oil inlet hose, P/N 80026-05. If test indicates no leakage, install new band clamp on fire sleeve. Reinstall tested hose or new hose as required per above instructions. Reinstall support clamp, maintaining the maximum possible bend ratios to prevent kinking of hose, check engine oil supply, and replenish if necessary. Run engine; insure that no oil leaks exist, and reinstall cowling. Equivalent methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration (FAA), Eastern Region. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this Airworthiness Directive can be accomplished. Piper Telex F.L.31-22A dated August 17, 1979, and Emergency Airworthiness Directive dated August 13, 1979, pertain to this subject. This amendment is effective January 14, 1980, and was effective upon receipt by all addressees of an airmail letter, dated August 13, 1979, on this same matter.
80-09-04: 80-09-04 PIPER AIRCRAFT CORPORATION: Amendment 39-3749. Applies to Model PA-34-200, serial numbers 34-E4, 34-7250001 through 34-7450220, Model PA-34-200T, serial numbers 34-7570001 through 34-7770441, airplanes certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent elongation or cracking of fitting holes and wearing of attaching nuts and bolts of the vertical fin attachment fittings and stabilator attachment and stabilator hinge assembly, accomplish the following within 25 hours time in service after the effective date of this AD: a. Inspect, replace parts and modify, as necessary, the vertical fin attachment fittings and stabilator attachment and stabilator hinge assembly in accordance with Piper Aircraft Corporation Service Bulletin No. 579, dated November 14, 1977, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. b. Make appropriate maintenancerecord entry. This amendment becomes effective April 24, 1980.
79-26-05: 79-26-05 AIRCRAFT METAL PRODUCTS CORPORATION: Amendment 39-3645. Applies to all general aviation airplanes with Aircraft Metal Products oil and fuel system hoses P/N 762506 installed. The subject hose is known to be installed on, but not limited to, certain Piper Model PA-28 and PA-32 aircraft. To prevent possible fire or explosion in the engine compartment or engine failure due to loss of engine oil, accomplish the following within 10 hours time in service from the effective date of this AD: (a) Inspect hoses for fluid leakage, excessive abrasion or excessive length. Replace hose if fluid leakage, excessive abrasion or excessive length exists. (b) Loosen each coupling fitting and notice if hose moves in direction of fitting, indicating a pre-existing hose twist. Replace the hose if there is evidence of a pre-existing hose twist. (c) Retighten each coupling fitting, gripping the collar just behind the fitting with pliers with just enough force to keep the hose from turning with the retightened fitting. If the hose turns with the retightened fitting, loosen the coupling fitting and repeat the retightening procedure. (d) Inspect the hose installation for adequate separation between metal hose and other parts of the airplane. If there is contact between metal parts, then complete insulation must be provided using AN742 cushion clamps and/or KOROSEAL lacing or equivalent. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. (f) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective January 3, 1980.
2023-09-11: The FAA is superseding Airworthiness Directive (AD) 2019-24- 13, which applied to certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-24-13 required repetitive high-frequency eddy current (HFEC) inspections for cracking of a stiffener of a certain lateral window frame, and applicable related investigative and corrective actions. This AD was prompted by a determination that certain inspection times need to be revised. This AD retains the requirements of AD 2019-24-13, with amended compliance times, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-09-12: The FAA is adopting a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Model PC-12, PC-12/45, PC-12/ 47, and PC-12/47E airplanes. This AD is prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as insufficient grounding of the vapor cycle cooling system (VCCS) compressor/condenser. This AD requires inspecting the power return and chassis grounding cable attachment points at frame 37, including the attachment parts, and depending on the inspection results, corrective action. This AD also requires modifying the installation of the VCCS compressor/condenser power return cables and installing an additional isolated VCCS chassis ground cable. The FAA is issuing this AD to address the unsafe condition on these products.
2002-08-16: This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters. That AD currently requires replacing each affected unairworthy main rotor head torsion tie bar (tie bar) with an airworthy tie bar and revising the limitations section of the maintenance manual by adding a life limit for certain tie bars. This amendment requires additional revisions to the limitations section of the maintenance manual by further reducing the life limit for certain tie bars. This amendment is prompted by an accident involving an ECF Model SA341G helicopter due to the failure of a tie bar. The actions specified by this AD are intended to prevent failure of a tie bar, loss of a main rotor blade, and subsequent loss of control of the helicopter.
2011-02-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitively inspecting the cockpit heated windshields for damage and replacing damaged windshields. This AD was prompted by reports from the windshield manufacturer of inner glass ply fracture. We are issuing this AD to detect and correct damage to the cockpit heated windshield, which could result in failure of the windshield with consequent rapid cabin decompression and loss of control of the airplane.
86-16-09: 86-16-09 BRITISH AEROSPACE VISCOUNT: Amendment 39-5377. Applies to Vickers Viscount Model 800 series airplanes, certificated in any category. Compliance is required as indicated, unless previously accomplished. To prevent nose landing gear collapse as a result of a faulty hydraulic cut out valve, accomplish the following: A. Within the next 1,000 hours time-in-service or nine months after the effective date of this AD, whichever occurs first, modify the cut out valve, Part Number AIR 41916, in accordance with Automotive Products Modification Standard SA 3490, dated December 16, 1959 (reference BAe Technical News Sheet No. 232, Issue 1, dated August 5, 1985). B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 tooperate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive, who have not already received the appropriate service document from the manufacturer, may obtain copies upon request to British Aerospace, Inc., Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective September 8, 1986.