Results
2000-16-13: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires you to inspect the nose wheel steering system to assure that the free play between the steering handle or knob and the nose wheels is within acceptable limits, and requires you to adjust the free play as necessary. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent the inability to steer the airplane because of excessive free play in the steering linkage. This excessive free play could then result in loss of control of the airplane during take-off, landing, or taxi operations.
98-16-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires revising the Airplane Flight Manual (AFM) to require use of the electrical fuel pump for take-off and landing and performance of an operational check of the electrical fuel pump following landing. This amendment also requires replacement of the jet booster pumps with new or modified jet booster pumps, which terminates the requirement for the AFM revision. 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 failure of the jet booster pumps, which could result in reduced engine thrust during take-off or landing, and consequent increased risk of impact with terrain.
77-16-04: 77-16-04 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2996 applies to de Havilland Model DH-104 "Dove" airplanes, all series, certificated in all categories. Compliance is required as indicated. To prevent possible fatigue failure of the wing structure, accomplish the following: (a) Irrespective of the incorporation of Hawker Siddeley Aviation, Ltd., (HSA) Modification 539, for wings which have not had HSA Modification 780 incorporated, within the next 25 hours time in service after the effective date of this AD or prior to accumulation of 3400 hours total time in service on the wing lower spar boom, whichever occurs later, at intervals not to exceed 3400 hours time in service, on the boom, replace it with a serviceable boom of the same part number or an FAA-approved equivalent. (b) For wings which incorporate HSA Modification 780, replace the wing lower spar boom with a serviceable boom of the same part number or an FAA-approved equivalent - (1) For Series1A, 2A, 5A, 5BA, 6A airplanes, prior to the accumulation of 20,000 hours total time in service on the wing lower spar boom including the time in service prior to incorporation of the modification; and (2) For Series 7A and 8A airplanes, prior to the accumulation of 16,000 hours total time in service on the boom including the time in service prior to incorporation of the modification. (c) For airplanes which do not incorporate HSA Modification 538 in the area of the fuselage center section, or have Modification 538 incorporated but not the associated HSA Modification 686, within the next 25 hours time in service after the effective date of this AD or prior to the accumulation of 1800 hours total time in service on the fuselage center section lower spar boom whichever occurs later, and thereafter, at intervals not to exceed 1800 hours time in service on the boom, replace the fuselage center section lower spar boom with a serviceable boom of the same part number or an FAA-approved equivalent. (d) For airplanes which incorporate HSA Modification 538 in the area of the fuselage center section, provided the associated HSA Modification 686 has been incorporated within 3600 hours time in service on the fuselage center section lower spar boom since incorporating Modification 538, within the next 25 hours time in service on the boom after the effective date of this AD or prior to the accumulation of 6700 hours total time in service on the fuselage center section lower spar boom, including time in service prior to incorporation of the modification, whichever occurs later, and thereafter at intervals not to exceed 6700 hours time in service, replace the fuselage center section lower spar boom with a serviceable boom of the same part number or an FAA-approved equivalent. NOTE: For airplanes which incorporate HSA Modification 779 in the area of the fuselage center section, no mandatory retirement time is imposed on the fuselage center section lower spar boom. (e) Upon the request of an operator, the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East region may adjust a replacement interval specified in paragraphs (a), (c), or (d) of this AD, if the request contains substantiating data to indicate that the average operating spectrum of the particular airplane is less severe than the operating spectrum upon which the specified replacement times are based and that the adjustment requested is justified. Forward request to FAA, Chief, Aircraft Certification Staff, c/o American Embassy, APO New York, N.Y. 09667. NOTE: Appendix 1 of HSA Technical New Sheet (TNS) No. 119, Issue 10, dated July 19, 1971, contains information with respect to data needed to determine an average operating spectrum. (f) Unless already accomplished, on airplanes converted to series 7AXC or 8AXC in accordance with HSA TNS No. 181, Issue 3, dated November 21, 1966, replace the wings prior to the accumulation of one fifth the total hourstime in service at conversion plus 16,000 hours time in service as determined in accordance with the instructions in paragraph 7 of HSA TNS No. 181, Issue 3, dated November 21, 1966, or an FAA-approved equivalent. (g) Operators who have not kept records of time in service on any component to which a provision of this AD applies shall substitute airplane hours time in service in lieu thereof. This amendment supersedes Amendment 289 to Part 507 of the Regulations of the Administrator (26 FR 4395), AD 61-11-03, as amended by Amendment 585 (28 FR 7394) and Amendment 662 (28 FR 14238). This amendment becomes effective August 31, 1977.
2022-22-02: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, and EC155B1 helicopters. This AD was prompted by reports of the cockpit doors failing to open after ditching with inflated floats on certain helicopters equipped with an emergency flotation system (EFS). This AD requires revising the existing Rotorcraft Flight Manual (RFM) for your helicopter, installing placards, and depending on your model helicopter, modification of the jettisoning system, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2010-20-07: The FAA is adopting a new airworthiness directive (AD) for all International Aero Engines AG (IAE) V2500-A1, V2525-D5 and V2528-D5 turbofan engines and certain serial numbers (S/Ns) of IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan engines. For certain S/Ns of V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 series turbofan engines, this AD requires initial and repetitive on-wing ultrasonic inspections of the high-pressure compressor (HPC) stage 3 to 8 drum for cracks. As mandatory terminating action to the repetitive inspections, this AD requires removal from service of the fully silver plated nuts attaching the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum, removal of silver residue from the HPC stage 3 to 8 drum, and fluorescent penetrant inspection (FPI) of the stage 3 to 8 drum within a specified time. For all other engines, this AD requires removal from service of the fully silver plated nuts attaching the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum, removal of silver residue from the HPC stage 3 to 8 drum, and FPI of the HPC stage 3 to 8 drum at the next drum piece-part exposure. This AD results from reports of 39 HPC stage 3 to 8 drums found cracked since March 2009. We are issuing this AD to prevent uncontained failure of the HPC stage 3 to 8 drum, which could result in damage to the airplane.
2000-16-03: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-7-100, and DHC-8-100, -200, and -300 series airplanes, that requires a one-time inspection of maintenance records to determine the method used during the most recent weight and balance check of the airplane and, if necessary, accomplishment of a weight and balance check. 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 unusual handling characteristics and consequent reduced controllability during ground operations due to incorrect methods of weighing and balancing the airplane.
2022-21-14: The FAA is superseding Airworthiness Directive (AD) 2017-10- 17, which applied to certain Airbus SAS Model A330-200; A330-200 Freighter; and A330-300 series airplanes. AD 2017-10-17 required revising the existing maintenance or inspection program, as applicable, to incorporate new fuel airworthiness limitations. This AD was prompted by a determination that new or more restrictive fuel airworthiness limitations and tasks are necessary. This AD continues to require the actions in AD 2017-10-17 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive fuel airworthiness limitations and tasks, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also expands the applicability to include additional airplane models. The FAA is issuing this AD to address the unsafe condition on these products.
2022-21-07: The FAA is adopting a new airworthiness directive (AD) for all Deutsche Aircraft GmbH (Type Certificate Previously Held by 328 Support Services GmbH; AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 and -300 airplanes. This AD was prompted by a safety analysis that lithium batteries installed in the personal electronic devices (PED) are a potential risk of an in-flight fire in the flight deck stowage boxes. This AD requires installing a placard and stowing the fire gloves on the left-hand (LH) flap door of the flight deck step; and installing the placards on the LH and right-hand (RH) flight deck stowage boxes. This AD also requires revising the operator's existing airplane flight manual (AFM) to include emergency procedures, 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.
2006-06-03: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Model 500, 501, 550, S550, 551, and 560 airplanes. This AD requires revising the airplane flight manual (AFM) to prohibit use of the wing fuel boost pumps for defueling under certain conditions; installing a placard; doing other specified investigative and corrective actions as necessary; and modifying the boost pumps. This AD also requires the subsequent removal of the AFM revision and placard. This AD results from a report of a chafed electrical wiring harness, which was arcing inside the fuel tank. We are issuing this AD to prevent potential fuel vapor ignition in a fuel tank, which could result in explosion and loss of the airplane.
98-21-30: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes and all Model A310 and A300-600 series airplanes, that requires repetitive inspections for wear damage of the aft attachment fittings of the articulated seats and dummy tracks in the passenger compartment; and repair, if necessary. 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 detect and correct wear damage of the aft attachment fittings of the articulated seats and dummy tracks. Such wear damage could cause the floor panels to sag and result in failure of flight control systems and consequent reduced controllability of the airplane.