Results
2008-03-10: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 525, 525A, and 525B airplanes. This AD requires you to inspect the lower wing skin structure, forward wing spar, lower fuselage skin, fairings, and the external fairing frames for corrosion; repair any damage found; apply a corrosion inhibitive sealant to the fuselage fairings before reinstalling; and disable the cockpit mounted pilot relief tube. This AD results from leaking of the cockpit mounted pilot relief tube, which caused corrosion of the airplane structure. We are issuing this AD to detect and correct any damage from corrosion of the airplane structure. Corrosion of the airplane structure could cause structural degradation and lead to structural failure of the airplane with consequent loss of control.
2020-19-04: The FAA is adopting a new airworthiness directive (AD) for Leonardo S.p.a. (Leonardo) Model AB139 and AW139 helicopters. This AD requires removing certain main gearbox (MGB) input modules from service. This AD was prompted by the discovery that a batch of duplex bearings, which are installed on the MGB input modules, are defective. The actions of this AD are intended to address an unsafe condition on these products.
94-17-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections of the inboard and outboard strut chords, stiffeners, and web to detect cracks and loose fasteners; repair of the chords, stiffeners, or web, if necessary; and replacement of any loose fastener. This amendment is prompted by reports of fatigue cracks and loose fasteners found in the forward lower spar web of the inboard strut on Model 747 series airplanes equipped with Pratt & Whitney JT9D-3 and JT9D-7 series engines. The actions specified by this AD are intended to prevent separation of the strut from the wing of the airplane due to fatigue cracking.
2008-03-05: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747- 200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes; and Model 767-200 and -300 series airplanes; equipped with certain Goodrich evacuation systems. For certain airplanes, this AD requires replacing the evacuation system shear-pin restraints with new ones. For certain other airplanes, this AD requires an inspection for manufacturing lot numbers; and a general visual inspection of the shear-pin restraints for discrepancies, and corrective actions if necessary. This AD results from several reports of corroded shear-pin restraints that prevented Goodrich evacuation systems from deploying properly. We are issuing this AD to prevent failure of an evacuation system, which could impede an emergency evacuation and increase the chance of injury to passengers and flightcrew during the evacuation.
2001-13-22: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A military), and -40 series airplanes; and Model MD-10-10F and MD-10-30F series airplanes, that currently requires, among other actions, performing repetitive ultrasonic inspections of the attaching bolts on the inboard and outboard support on the inboard and outboard flap assembly to detect failed bolts, or verifying the torque of the attaching bolts on the inboard support on the outboard flap; and follow-on actions. This amendment, among other actions, adds a requirement to verify the torque of the attaching bolts on the outboard support on the inboard and outboard flaps, and allows repetitive torque verifications. This amendment is prompted by a review that revealed inadvertent omission of a requirement. The actions specified by this AD are intended to prevent in-flight loss of inboard and outboard flap assemblies due to failure ofH-11 attaching bolts, which could result in reduced controllability of the airplane.
2001-13-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires a one-time inspection to find wire chafing of the left and right engine fuel shutoff valve wire bundles at Power Plant Station 278 on each engine strut, and repair if necessary. This amendment also requires replacement of three wire support brackets with improved wire support brackets. This amendment is prompted by reports that such wire support brackets failed due to fatigue, which subsequently caused the fuel shutoff valve wire to chafe and to experience a short circuit. The actions specified by this AD are intended to prevent such conditions, which could result in either the possible ignition of fuel vapors in a flammable leakage zone or in the inability to stop the flow of fuel in the event of an engine fire.
94-16-04: This amendment adopts a new airworthiness directive (AD), applicable to Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH55A series helicopters, that requires a one-time visual inspection to detect missing or damaged tail rotor pedal bulkhead gussets (gussets), loose or missing gusset rivets, and initial installation of missing gussets or replacement of damaged gussets and rivets, if necessary. This amendment is prompted by reports of missing or damaged tail rotor pedal bulkhead gussets and loose or missing gusset rivets. The actions specified by this AD are intended to prevent failure of the tail rotor pedal support structure that could result in loss of tail rotor control and subsequent loss of control of the helicopter.
2008-03-09: The FAA is adopting a new airworthiness directive (AD) for CFM International, S.A. CFM56-7B series turbofan engines. This AD requires revising the Airworthiness Limitations Section (ALS) in the Engine Shop Manual (ESM) and the air carrier's approved continuous airworthiness maintenance program (CAMP) to add mandatory inspections of certain low pressure turbine rear frames (TRFs) to the ALS or CAMP. This AD results from a refined lifing analysis by the engine manufacturer that shows the need to identify an initial threshold for inspecting certain TRFs. We are issuing this AD to prevent failure of the TRF from low-cycle fatigue cracks. Failure of the TRF could result in engine separation from the airplane, which could lead to loss of control of the airplane.
2001-13-18: This document supersedes Airworthiness Directive (AD) 99-12-02, which currently requires flight and operating limitations on Raytheon Aircraft Corporation (Raytheon) Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) airplanes. AD 99-12-02 resulted from a report of an in-flight separation of the right wing on a Raytheon Beech Model A45 (T-34A) airplane. The AD was issued as an interim action until the development of FAA-approved inspection procedures. Raytheon has developed procedures to inspect the wing spar assemblies of the above-referenced airplanes. This AD requires repetitive inspections of the wing spar assembly for cracks with replacement of any wing spar assembly found cracked (unless the spar assembly has a crack indication in the filler strip where the direction of the crack is toward the outside edge of the filler strip). This AD also includes a reporting requirement of the results of the initial inspection and maintains the flight and operating restrictions required by AD 99-12-02 until accomplishment of the initial inspection. The actions specified by this AD are intended to prevent wing spar failure caused by fatigue cracks in the wing spar assemblies and ensure the operational safety of the above-referenced airplanes.
2020-06-16: The FAA is superseding Airworthiness Directive (AD) AD 2017- 03-02 for certain Rolls-Royce, Deutschland Ltd. & Co. KG RB211 Trent 768-60, 772-60, and 772B-60 model turbofan engines. AD 2017-03-02 required initial and repetitive ultrasonic inspections (UIs) of the affected low-pressure (LP) compressor blades. This \n\n((Page 17739)) \n\nAD requires initial and repetitive UIs of the affected LP compressor blades and, depending on the results of the UIs, their replacement with a part eligible for installation. This AD was prompted by LP compressor blade partial airfoil release events. The FAA is issuing this AD to address the unsafe condition on these products.