Results
2010-08-05: We are adopting a new airworthiness directive (AD) for the products listed above. 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: It was noticed in production that in the area between frame (FR) C53.9 and FR C55 RH [right-hand], the distance between the route 9R of the In-Flight Entertainment system and the wire harness for the Lower Deck-Mobile Crew Rest system provisions is too small. This limited distance may cause chafing between the affected electrical harness 6581VB and the harness 5495VB or 6938VB. This condition, if not corrected, could lead to the short circuit of wires dedicated to oxygen, which, in case of emergency, could result in a large number of passenger oxygen masks not being supplied with oxygen, possibly causing personal injuries. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
95-15-09: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAC 1-11-200 and -400 series airplanes, that requires various inspections to detect discrepancies of fuselage frames at certain stations, and correction of discrepancies; and rework to limit the maximum differential operating pressure of the fuselage. This amendment will also require eventual modification of fuselage frames at certain stations, which will terminate the repetitive inspection requirements. This amendment is prompted by reports of fatigue cracking in certain fuselage frames in the vicinity of the passenger door at floor level due to fatigue-related stress. The actions specified by this AD are intended to detect and prevent such fatigue-related cracking, which could result in reduced structural integrity of the fuselage pressure vessel and possible decompression of the pressurized cabin.
95-19-15: This amendment adopts a new airworthiness directive (AD) that applies to American General Aircraft Corporation (American General) Models AA-5, AA-5A, AA-5B, and AG-5B airplanes. This action requires inspecting the wing attach shoulder bolts for fretting, scoring, wear, or enlarged or elongated mounting holes (known as damage from hereon), and replacing any damaged parts and repairing any damaged areas; and inspecting the wing spar at the center spar clearance gap for excessive clearance, and shimming the spar if excessive clearance is found. The actions specified by this AD are intended to prevent wing attach shoulder bolt failure, which, if not detected and corrected, could lead to structural damage to the wing/fuselage to the point of failure.
2021-04-05: The FAA is superseding Airworthiness Directive (AD) 2019-23- 15, which applied to certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. AD 2019-23-15 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
66-28-01: 66-28-01 AERO COMMANDER (MEYERS): Amdt. 39-305 Part 39 Federal Register November 9, 1966. Applies to Model 200 Series Airplanes. Compliance required as indicated. To prevent takeoff with excessive elevator trim set, accomplish the following: (a) Before each flight after the effective date of this AD until the elevator trim system has been modified in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region, check operation of elevator trim control for freedom of movement, and check cockpit indicator for accuracy by setting the elevator trim to neutral position as indicated on cockpit indicator, and visually checking elevator trim surface for zero deflection. (b) If trim control is not free and unbinding, or if elevator trim surface is deflected when cockpit indicator indicates neutral trim, repair before further flight in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (c) Before further flight after the effective date of this AD, until the elevator trim system has been modified in accordance with (a), attach the following placard to the instrument panel in full view of the pilot: "Before each flight ensure that elevator trim control is free and unbinding and that elevator trim surface is not defected when cockpit indicator indicates neutral trim." (d) The checks required by this AD may be performed by the pilot. This directive effective November 19, 1966.
2004-02-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-V series airplanes. This action requires a one-time inspection of the landing gear selector dump valve (LGSDV) to determine the serial number (S/N). For any part with an affected S/N, or for any part for which the S/N cannot be determined, this action requires replacing the LGSDV with a cleaned part having an S/N within the affected range; or replacing the LGSDV with a new or serviceable part that has an S/N outside the affected range. This action is necessary to prevent uncommanded unlocking of the landing gear, which could result in collapse of the landing gear. This action is intended to address the identified unsafe condition.
95-11-02: This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes and Model KC-10A (military) airplanes and certain Model MD-11 series airplanes, that currently requires inspections to detect defects in the upper and lower lock links on the nose landing gear (NLG), and rework or replacement of any defective link with a serviceable link. The actions specified by that AD are intended to prevent collapse of the NLG. This amendment requires accomplishment of a certain inspection that constitutes terminating action for the currently required inspections.
2021-01-07: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-700 series airplanes. This AD requires repetitive testing to verify correct operation of the smoke clearance mode of the equipment cooling system and low pressure environmental control system, and corrective actions if necessary. This AD also requires installing new relays and changing the wiring to the environmental control system, among other actions. This AD was prompted by a determination that a repetitive test is needed to assess the components on airplanes equipped with a certain air distribution system configuration. The FAA is issuing this AD to address the unsafe condition on these products.
70-15-04: 70-15-04 HANDLEY PAGE: Amdt. 39-1031 as amended by Amendment 39-1317 is further amended by Amendment 39-1556. Applies to all HP-137 Mark I airplanes having Turbomeca Astazou XIV series engines installed. To reduce the possibility of inflight failure of the first stage engine turbine disc and subsequent rupture of fuel and hydraulic lines, accomplish the following: (a) Before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the modification can be performed, modify the fuel and hydraulic systems by relocating the fuel and hydraulic shutoff valves from the engine nacelles to a location on the front spar inboard of the nacelle in accordance with a modification approved by the engineering and manufacturing branch of the nearest FAA regional office. (b) For first stage turbine discs, P/N 0.261.25.013.0, installed on engines that do not incorporate Turbomeca Mods. TU-123, TU-124, and TU-126, before the accumulation of 400hours total disc time in service or 1,000 cycles, whichever occurs sooner, remove the first stage turbine disc from service and replace it with a new disc of the same part number. (c) For first stage turbine discs, P/N 0.261.25.013.0 installed with less than 100 hours' time in service since new on engines that incorporate Turbomeca Mods. TU-123, TU-124, and TU-126, installed in accordance with Turbomeca Service Instructions No. 0123, dated August 27, 1970, No. 0124, dated September 16, 1970, and No. 0127, dated September 16, 1970, respectively, or FAA-approved equivalents, before the accumulation of 750 hours total disc time in service or 2,000 cycles, whichever occurs sooner, remove the first stage turbine disc from service and replace it with a disc of the same part number, which has less than 100 hours' time in service since new. (d) For the purpose of complying with this AD, a cycle constitutes: (1) Any takeoff and landing operation; (2) Any touch and go landing operation; (3) Any other operation where reduction of power is followed by application of takeoff power. Amendment 39-1031 became effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by the telegram dated May 15, 1970, which contained this amendment. Amendment 39-1317 became effective October 5, 1971. This Amendment 39-1556 becomes effective November 13, 1972.
95-19-10: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 767 series airplanes. This action requires operators to perform visual inspections of the outer cylinder aft trunnion on the main landing gear to determine if the fillet seal is cracked or missing. This action also requires operators to inspect for evidence of corrosion in this location. Finally, this action prescribes the procedures that operators must follow if corrosion is found. This amendment is prompted by several reports of fractures of the outer cylinder aft trunnion due to stress corrosion cracking. The actions specified in this AD are intended to ensure that corrosion is not present in this location, thereby preventing future failures due to stress corrosion cracking.