Results
99-19-26: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 and A300-600 series airplanes, that currently requires inspections to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, and repair, if necessary. This amendment establishes repetitive inspection intervals for certain inspections required by the existing AD. This amendment also adds a requirement to modify Gear Rib 5 of the MLG attachment fittings, which constitutes terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking of the MLG attachment fittings, which could result in reduced structural integrity of the airplane.
2000-25-09: This amendment supersedes an existing airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters that currently requires inspecting the exhaust ejector locking system, clamp, and dampers for each engine. The existing AD also requires verifying the torque of the metallic clamps and installing safety wire on the metallic clamps; inspecting and modifying the ejector saddles and the locking metallic clamps; and inspecting the metallic clamps, locking mechanisms, and dampers. This amendment requires modifying the engine exhaust ejectors. This amendment is prompted by the development of a kit to modify the engine exhaust ejectors to provide terminating action from the requirements of the current AD. The actions specified by this AD are intended to prevent loss of the metallic clamp or the engine exhaust ejector, damage to the main or tail rotor system and subsequent loss of control of the helicopter.
2007-06-52: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2007-06-52 that was sent previously to all known U.S. owners and operators of Boeing Model 737- 800 series airplanes by individual notices. This AD requires inspecting spoilers to determine spoiler position after every landing and after any rejected takeoff maneuvers. For airplanes on which any spoiler is found in the up position with the speedbrake handle in the down position, this AD requires replacement of the flight spoiler actuator with a flight spoiler actuator having a certain part number. This AD also requires an operational test of the speedbrake control system after any maintenance actions that operate the spoiler system and replacement of the flight spoiler actuator if necessary. This AD also provides for optional terminating action for those requirements. In addition, this AD requires you to report to the manufacturer any spoiler panel that is found in the up positionwith the speedbrake handle in the down position. This AD results from a report of seven flight spoiler actuator jams on Model 737-800 Short Field Performance airplanes. We are issuing this AD to detect and correct any spoiler panel that is found in the up position with the speedbrake handle in the down position, which could result in a spoiler actuator hardover, and could cause the spoiler surface to jam in the fully extended position. Two or more hardover failures of the spoiler surfaces in the up direction on the same wing, if undetected prior to takeoff, can cause significant roll and consequent loss of control of the airplane.
2019-08-08: We are superseding Airworthiness Directive (AD) 2010-14-05, which applied to certain Bombardier, Inc., Model CL-600-1A11 (600), CL- 600-2A12 (601), and CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. AD 2010-14-05 required inspection for the part numbers of the system and brake accumulators, and repetitive replacement of affected accumulators. This AD adds requirements for relocating the accumulators and revising the existing maintenance or inspection program to incorporate new or more restrictive airworthiness limitations. This AD also adds optional terminating action for certain airplanes. This AD was prompted by reports of on-ground hydraulic accumulator screw cap or end cap failure that resulted in the loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. We are issuing this AD to address the unsafe condition on these products.
77-15-06: 77-15-06 MORANE SAULNIER (SOCATA): Amendment 39-2975. Applies to Model MS 892A150, MS 892E150, MS 893A, MS 893E, RALLYE 150T and RALLYE 150ST airplanes, certificated in all categories. Compliance is required as indicated. To prevent failure of engine mounts, accomplish the following: (a) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 50 hours time in service from the last inspection, visually inspect the engine mounts for cracks using dye penetrant in accordance with paragraphs 111-1-1 and 111-1-2 of SOCATA Service Bulletin No. 98/2, dated April 1976, or an FAA-approved equivalent. (b) If one or more cracks are detected as a result of any inspection required by paragraph (a) of this AD, repair as necessary in accordance with paragraph 111-1-3 of SOCATA Service Bulletin No. 98/2, dated April 1976, or an FAA-approved equivalent. (c) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, on airplanes with right angle engine mount brackets, modify the brackets in accordance with paragraph 111-2 of SOCATA Service Bulletin No. 98/2, dated April 1976, or an FAA-approved equivalent. This amendment becomes effective August 22, 1977.
2007-09-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as Several recent inspections have revealed that some spar wooden centre blocks have shown cracks. Investigation revealed that cracks are generated by the wood drying. Actions specified in this AD are intended to detect and correct any defects on the central wing spar block. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2000-26-11: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters. This action requires replacing certain tail rotor blades with airworthy tail rotor blades. This amendment is prompted by a tail rotor blade (blade) failure that caused a high vibration level in the helicopter. Investigation revealed that the failure was due to a change in the manufacturing process for an identified production lot of blades. This condition, if not corrected, could result in a failure of a blade and subsequent loss of control of the helicopter.
2000-25-53: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-25-53, which was sent previously to all known U.S. owners and operators of Airbus Model A330 series airplanes by individual notices. This AD requires either repetitive detailed visual inspections or repetitive borescopic inspections to detect cracking or other damage of the barrel nuts of the engine aft mount; and replacement of any cracked nut and its associated bolt with a new nut and bolt, or replacement of all 4 nuts and their associated bolts if two or more nuts on the same engine mount are found cracked. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct cracking of the aft engine mount nut, which could result in reduced structural integrity of the engine-to-pylon aft mount assembly, or, in the case of multiple cracked nuts, possible loss of an engine.
2013-25-08: We are superseding airworthiness directive (AD) 2009-24-09 for all Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2009-24-09 required a repetitive inspection program on certain check valves in the hydraulic systems that includes, among other things, inspections for lock wire presence and integrity, traces of seepage or black deposits, proper torque, alignment of the check valve and manifold, installing new lock wire, and corrective actions if needed. This new AD expands the applicability, reduces the compliance time, changes torque values of the check valve tightening, and requires a repetitive inspection program for certain check valves in the [[Page 78695]] hydraulic systems on airplanes that have had a certain modification embodied during production or in-service. This AD was prompted by multiple reports of hydraulic line check valves loosening. We are issuing this AD to detect and correct such check valve loosening, which could result in hydraulic leaks, possibly leading to the loss of all three hydraulic systems and consequent loss of control of the airplane.
2007-09-01: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Model 182 series airplanes that are equipped with Air Plains Services Corporation Supplemental Type Certificate (STC) SA00152WI. This AD requires you to disconnect or remove the electrical cable between the forward ground power relay and the starter relay, install a placard, inspect the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump for chafing, and replace the fuel line if chafing is found. This AD results from a report of an in-flight and post-landing engine compartment fire. We are issuing this AD to detect and correct interference between the ground power electrical cable, the fuel strainer cable, and the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump. This condition could lead to a fire in the engine compartment.