Results
2018-02-04: We are adopting a new airworthiness directive (AD) for certain Aerospace Welding Minneapolis, Inc. mufflers, part numbers A1754001-23 and A1754001-25, installed on airplanes. This AD was prompted by occurrences of cracks or broken welds in the connecting weld of the muffler body to muffler cuff that may allow carbon monoxide exhaust fumes into the cockpit heating system. This AD requires an inspection of the muffler for leaking to identify cracks and replacement of the muffler. We are issuing this AD to address the unsafe condition on these products.
2018-01-07: We are adopting a new airworthiness directive (AD) for all Airbus 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) airplanes. This AD was prompted by a revision of certain airworthiness limitation item (ALI) documents, which require more restrictive maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2007-09-09: 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. The MCAI describes the unsafe condition as un-damped extension of the main landing gear (MLG), potentially leading to loss of side stay integrity and then MLG collapse. We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-24-02: 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 aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: The manufacturer has advised of receiving a report of looseness of the drive arm of the mechanical elevator trim tab, found during an annual inspection. This kind of damage is likely caused by penetrated humidity over the years. If left uncorrected, this condition could lead to the separation of the drive arm which could result in flutter of the elevator and possible loss of control of the aircraft. We are issuing this AD to require actions to correct the unsafe condition on these products.
2000-26-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737, 747, 757, and 767 series airplanes, that requires rework of certain duct assemblies of the environmental control system (ECS) or replacement of the duct assemblies with new or reworked duct assemblies. This action is necessary to prevent potential ignition of fiberglass insulation material installed on the outside of the ECS ducts, which could propagate a small fire and lead to a larger fire. This action is intended to address the identified unsafe condition.
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.