Results
2003-03-21: This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney Canada (PWC) PW500 series turbofan engines. This action requires a one-time visual inspection and re-marking, or in lieu of inspection, replacement of certain part numbers (P/N's) of the flexible fuel tube located between the fuel/oil heat exchanger and the integral fuel control unit-fuel pump. This amendment is prompted by reports of fuel found dripping from engine nacelles caused by leaking flexible fuel tubes. The actions specified in this AD are intended to prevent a fire in the engine nacelle.
99-10-16: This amendment adopts a new airworthiness directive (AD), applicable to all Mitsubishi Model YS-11 series airplanes, that requires repetitive inspections to detect fatigue cracking in the manhole doublers of the lower wing panels; and repair, if necessary. This amendment also requires eventual modification of screw holes in the manhole doublers of the lower wing panels, which constitutes terminating action for the repetitive inspections required by this AD. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fatigue cracking in the manhole doublers of the lower wing panels, which could result in failure of the wing structure.
99-10-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and 747-SP series airplanes and military type E-4B airplanes, that requires repetitive inspections to detect cracking of the wing front spar web, and repair of cracked structure. This amendment also provides for optional terminating action for the repetitive inspection requirements. This amendment is prompted by reports indicating that fatigue cracks were found on the aft surface of the wing front spar web. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in a fuel leak, and consequent increased risk of a fire.
99-10-15: This amendment adopts a new airworthiness directive (AD) that is applicable to AS332L2 helicopters. This action requires inspecting each main rotor head drag damper (damper) for a tear, crack, or bonding separation in the elastomer and, if necessary, replacing the damper with an airworthy damper. This amendment is prompted by a report of increased helicopter vibration in flight that was traced to the delamination of the elastomer on a damper. This condition, if not corrected, could result in failure of a damper and subsequent loss of control of the helicopter.
84-01-52 R1: 84-01-52 R1 WESTLAND HELICOPTERS LIMITED: Amendment 39-4845. Applies to Westland Model 30 Series 100 helicopters certificated in all categories. Compliance is required as indicated (unless already accomplished). To prevent failure of the tail rotor gearbox input pitch control lever and subsequent loss of control in flight accomplish the following: (a) Prior to further flight comply with the requirements of Westland Service Bulletins W30-67-26, Revision 3, and W30-65-14 or subsequent FAA approved revisions or FAA approved equivalent. (b) Remove from service all tail rotor gearbox input pitch control levers P/N WK 3068-0037-101 with 200 hours time in service and replace with a serviceable part. (c) An equivalent method of compliance with this AD may be used when approved by the Manager, Brussels Aircraft Certification Office, c/o United States Embassy, Brussels, Belgium. This amendment becomes effective April 16, 1984, as to all persons except those persons to whom it was made immediately effective by priority letter AD T84-01-52, issued December 30, 1983, which contained this amendment.
2000-24-03 R1: The FAA is revising an existing airworthiness directive (AD) that applies to all AvCraft Dornier Model 328-100 airplanes. That AD currently requires revising the airplane flight manual (AFM) to provide the flightcrew with additional information regarding procedures to ensure complete pressurization of the hydraulic lines for the flaps. The existing AD also requires, for certain airplanes, modifying of the flap actuators of the flight controls. We issued that AD to prevent an uncommanded retraction of the flaps during takeoff, which could result in an aborted takeoff and consequent potential for runway overrun. This new AD allows the removal of the AFM revisions after modifying the flap actuators of the flight controls. This AD results from the determination that the AFM revisions are not necessary after modifying the flap actuators of the flight controls. We are issuing this AD to prevent an uncommanded retraction of the flaps during takeoff, which could result in an aborted takeoff and consequent potential for runway overrun.
2019-24-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by an investigation that identified the cargo lining gutter assembly would be unable to drain a certain quantity of water in case of leakage or rupture of certain water pipes. This AD requires modification of the cargo lining gutter assemblies, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2009-15-18: 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 found one occurrence of a fuel booster pump circuit br[e]aker opening during an engine maintenance servicing. An inspection inside the fuel tank revealed the fuel booster pump[']s electrical harness chafing against its body, causing the loss of the electrical wiring protection and resulting in a short circuit. Further in-tank inspections have showed other fuel booster pump electrical harnesses chafing either with the pump body and/or with adjacent fuel lines, causing damage to the harness protective layers and resulting * * * [in a] possible ignition source inside the fuel tank. * * * * * We are issuing this AD to require actions to correct theunsafe condition on these products.
99-10-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Avions Pierre Robin Model R2160 airplanes. This AD requires inspecting to assure that the fuel filler cap has a 2.5 millimeter (mm) diameter hole drilled through it or that a vinyl piping is connected to the filler neck inside the cabin. If neither of these items exists, this AD requires replacing the fuel filler cap with a fuel filler cap that has a 2.5 mm diameter hole drilled through it. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect and correct the installation of improperly designed fuel venting system parts, which could result in an inadequate fuel supply to the engine with loss of engine power.
72-26-01: 72-26-01 BEECH: Amdt. 39-1576. Applies to 99 series (Serial Numbers U-1 thru U-148) airplanes. Compliance: Required as indicated, unless already accomplished. To reduce the possibility that baggage or cargo in the nose compartment might become a hazard by shifting, accomplish either Paragraph A or Paragraph B within 200 hours' time in service after the effective date of this AD: A) Install an additional latch on the nose compartment door as provided in Beech Kit No. 99-4019S or any FAA-approved equivalent, or B) Install a baggage/cargo restraint system in accordance with data approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective December 21, 1972.