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55-02-02: 55-02-02 LYCOMING: Applies to Model O-320 Engines Below Serial Number 612 Installed in Aircraft Equipped With Fixed Pitch Propellers. Compliance required as soon as possible but not later than February 28, 1955. Several immediate forced landings have occurred with aircraft equipped with the above engine and propeller combinations due to rapid loss of engine oil from the engine accessory drive adapter gasket location. To preclude this possibility, all such engines should be inspected to insure that the proper gasket is installed under the lower accessory drive adapter cover. For engines with fixed pitch propellers, Lycoming P/N 69551, gasket must be installed at this location. (Lycoming Service Bulletin No. 176 covers this same subject.)
2006-19-11: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to require actions to correct the unsafe condition on these products.
67-22-08: 67-22-08 ROLLS-ROYCE: Amdt. No. 39-451, Part 39, Federal Register July 26, 1967. Applies to Spey Model 506-14 Engines. Compliance required as indicated, unless already accomplished. To prevent failure of the C.A.S.C. 105 and 125 Lucas fuel flow controls installed on Spey Model 506-14 engines due to wear of the splines on the input drive assembly, accomplish the following: (a) For fuel flow controls with 700 or more hours' total time in service on the effective date of this AD and that have not been overhauled, comply with paragraph (e) within the next 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection. (b) For fuel flow controls with less than 700 hours' total time in service on the effective date of this AD and that have not been overhauled, comply with paragraph (e) before the accumulation of 800 hours' total time in service, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection. (c) For fuel flow controls that have been overhauled and that on the effective date of this AD, have 700 or more hours' time in service since overhaul, comply with paragraph (e) within the next 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection. (d) For fuel flow controls that have been overhauled and that on the effective date of this AD have less than 700 hours' time in service since overhaul, comply with paragraph (e) before the accumulation of 800 hours' time in service since overhaul, and thereafter at intervals not to exceed 800 hours' time in service from the last inspection. (e) Inspect the input drive assembly, in accordance with Rolls-Royce Service Bulletin Number SP 73- A109 dated February 2, 1967, or later ARB-approved issue, or FAA-approved equivalent. If wear is found, incorporate Rolls-Royce Modification 3258, or an FAA-approved equivalent, before further flight. (f) The repetitive inspection required by paragraphs (a) through (d) may be discontinued upon incorporation of Modification 3258, or an FAA-approved equivalent. This amendment effective August 25, 1967.
2021-09-09: The FAA is adopting a new airworthiness directive (AD) for certain Uninsured United Parachute Technologies, LLC (UPT) parachutes. This AD results from reserve pin covers (RPCs) catching on the parachute container flaps and preventing the reserve parachute from deploying. This AD requires modifying the RPC before the next parachute jump and replacing the RPC at the next reserve parachute packing. The FAA is issuing this AD to address the unsafe condition on these products.
2021-07-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC 155B and EC155B1 helicopters. This AD was prompted by a report of mechanical deformation of the protective cover of the ''SHEAR'' control pushbutton on the copilot collective stick. This AD requires replacement of the protective cover of the ''SHEAR'' control pushbutton on the pilot and copilot collective sticks and re- identification of the pilot and copilot collective sticks, 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.
2018-19-01: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365N1, and SA-366G1 helicopters. This AD requires repetitive inspections of the aft fuselage outer skin. This AD was prompted by several reports of aft fuselage outer skin disbonding. The actions of this AD are intended to address an unsafe condition on these products.
89-08-08: 89-08-08 BOEING: Amendment 39-6191. \n\n\tApplicability: Model 737-100 and 737-200 series airplanes, certificated in any category, which presently do not use nose gear compression logic to enable thrust reversers. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo ensure timely deployment of reverse thrust when landing under adverse weather and runway conditions, accomplish the following: \n\n\tA.\tWithin 18 months from the effective date of this AD, install an FAA-approved modification to the Air/Ground Sensing System which causes the thrust reverser logic to be enabled by nose gear strut compression in addition to the present logic of the right main gear oleo compression. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. \n\n\tThis amendment (39-6191, AD 89-08-08) becomes effective on May 10, 1989.
2006-19-08: The FAA is adopting a new airworthiness directive (AD) for certain Stemme GmbH & Co. KG Model STEMME S10-VT sailplanes. This AD requires you to do a one-time inspection of all exhaust bends (each cylinder 1 to 4) in the area of the curvature bend near the cylinder flange, replace any damaged exhaust pipes found, and recondition the heat protection wrapping. This AD results from deformations and cracks found at an exhaust bend during maintenance work. We are issuing this AD to detect and correct cracks in the exhaust pipes. Damaged exhaust pipes could cause exhaust gases to expand into the engine compartment and/or carbon monoxide (CO) to leak into the cockpit section.
2018-17-15: We are superseding Airworthiness Directive (AD) 2018-02-14 for certain Honeywell International Inc. (Honeywell) TPE331 turboprop and TSE331 turboshaft engines. AD 2018-02-14 required inspection of the affected combustion chamber case assembly, replacement of those assemblies found cracked, and removal of affected assemblies on certain TPE331 and TSE331 engines. This AD retains the inspection and replacement requirements in AD 2018-02-04; revises the Applicability to add the TPE331-12 engine model and the related inspection action, correct references to certain engine models; and revises compliance to allow certain weld repair procedures. This AD was prompted by comments to revise the applicability and required actions of AD 2018-02-14 to include the TPE331-12B engine model, correct certain TPE engine model typographical errors, and to allow certain weld repair procedures. We are issuing this AD to address the unsafe condition on these products.
2000-10-07: This amendment adopts a new airworthiness directive (AD) that applies to Eurocopter Model EC 135 helicopters. This AD requires replacing a certain oil cooler fan splined drive shaft (shaft) with a different airworthy shaft and re-identifying the part numbers on the oil cooler fans. This amendment is prompted by two incidents in which the shaft broke. The actions specified by this AD are intended to prevent failure of the shaft, loss of oil cooling, and a subsequent engine shutdown during flight.