Results
2014-10-01: We are superseding airworthiness directive (AD) 2008-24-11 for Vulcanair S.p.A. Model P68 airplanes. This AD results from 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 describes the unsafe condition as cracking and/or corrosion of the wing spar. We are issuing this AD to require actions to address the unsafe condition on these products.
2021-11-18: The FAA is superseding Airworthiness Directive (AD) 2019-03- 10, which applied to all Airbus SAS Model A300 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 2019-03-10 required repetitive detailed visual inspections of the main landing gear (MLG) leg components and replacement of the MLG leg if cracked components are found. This AD continues to require the actions required by AD 2019-03-10. For certain airplanes, this AD also requires modification of the MLG hinge arm by installing improved MLG hinge arm/barrel pins; an out-of-roundness check of removed pins; repetitive inspections of any affected pins and the associated connecting rod bushes, and replacement of the MLG leg if cracked components are found; and installation of an improved spacer; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference.This AD was prompted by reports of cracks in MLG leg components and a determination that additional actions (including inspections, modifications, and checks) are needed to address the unsafe condition. The FAA is issuing this AD to address the unsafe condition on these products.
2014-09-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of bearing damage at certain trailing edge (TE) flap support rib assemblies. This AD requires inspecting certain TE flap support rib assemblies to determine if the bearings have a roller retention feature, and performing corrective actions if necessary; and inspecting for bearing damage of each pair of removed bearings, and performing related investigative and corrective actions if necessary. We are issuing this AD to detect and correct damage to the TE flap support bearings, which could ultimately result in loss of controllability of the airplane.
2014-09-04: We are superseding Airworthiness Directive (AD) 2009-21-08 R1 for Piaggio Aero Industries S.p.A Model P-180 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cases of un-commanded operation of switched off nose-wheel steering system caused by internal leakage of a steering select/bypass valve. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-08-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2003-08-51, which was sent previously to all known U.S. owners and operators of the specified model MD Helicopters, Inc. helicopters by individual letters. This AD requires reducing the retirement life of certain tail rotor blades, performing a one-time visual inspection of each tail rotor blade pitch horn (pitch horn) for a crack or corrosion, and replacing unairworthy tail rotor blades with airworthy tail rotor blades. This AD also requires revising the Airworthiness Limitations section of the helicopter maintenance manual to reflect the reduced retirement life, and reporting information to the FAA within 24 hours following the one- time inspection. The actions specified by this AD are intended to prevent a pitch horn from separating from the tail rotor blade, leading to an unbalanced condition, vibration, loss of tail rotor pitch control, and loss of directional control of thehelicopter.
2014-09-01: We are adopting a new airworthiness directive (AD) for Agusta Model A109C, A109E, A109K2, and A119 helicopters. This AD requires a recurring visual inspection of the tail rotor (T/R) blade retaining bolts (bolts) for a crack, corrosion, damage, or missing cadmium plating in the central part of the bolt and, depending on findings, a liquid penetrant inspection. This AD also requires replacing a cracked or damaged bolt. This AD was prompted by two reported incidents of cracked bolts. The actions of this AD are intended to detect an unairworthy bolt and prevent failure of a bolt, release of a T/R blade, and subsequent loss of control of the helicopter.
2014-09-03: We are superseding Airworthiness Directive (AD) 99-07-11 for SOCATA Model TBM 700 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracks on the outboard hinge fittings. We are issuing this AD to require actions to address the unsafe condition on these products.
94-12-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect fatigue-related skin cracks and corrosion of the skin lap joints in the fuselage upper lobe, and repair, if necessary. This amendment also requires modification of certain lap joints and inspections of modified lap joints. This amendment is prompted by a structural review of Model 747 series airplanes. The actions specified by this AD are intended to prevent rapid decompression of the airplane and the inability to carry fail-safe loads, due to the problems associated with fatigue cracking and corrosion.
51-11-02: 51-11-02 CESSNA: Applies to All Models 190 and 195 Aircraft Serial Numbers 7004 to 7474 and 7476 to 7479, Inclusive. Compliance required not later than June 1, 1951, and upon each 100 hours of operation thereafter until reinforcing doublers are installed at outboard hinge fittings. Inspect for fatigue cracks in the elevator spar webs at the outboard hinges. This may be accomplished by loosening the two attaching bolts as necessary to facilitate inspection for cracks at the bolt holes. Cracks extending less than 3/4 inch beyond the hinge fitting should be stop- drilled and reinforcing doublers, Cessna P/N 10008-11-2 and -3, should be installed on the forward side of the spar. If any cracks are longer than 3/4 inch, the spar should be replaced and the reinforcing doublers added. (Cessna Service Letter No. 10 dated November 18, 1949, covers this same subject.)
2021-11-19: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) (Bell) Model 505 helicopters. This AD was prompted by the discovery of a gap between the transmission restraint assembly aft attachment hardware lower washer and mating airframe truss assembly (truss assembly) clevis lower lug. This AD requires inspecting the transmission restraint aft attachment hardware installation for a gap and corrective action depending on the inspection results. The FAA is issuing this AD to address the unsafe condition on these products.