Results
2004-15-15: The FAA supersedes Airworthiness Directive (AD) 2002-19-10, which applies to certain Air Tractor, Inc. (Air Tractor) Models AT-402, AT-402A, AT-402B, AT-602, AT-802, and AT-802A airplanes. AD 2002-19-10 currently requires you to repetitively inspect the upper longeron and upper diagonal tube on the left hand side of the aft fuselage structure for cracks and contact the manufacturer for a repair scheme if cracks are found. This AD is the result of reports of the same cracks recently found on AT-500 series airplanes. The manufacturer has also issued new and revised service information that incorporates a modification to terminate the repetitive inspection requirements. Consequently, this AD retains the inspection actions required in AD 2002-19-10, adds certain AT-500 series airplanes to the applicability section, changes the compliance times, and incorporates new and revised manufacturer service information that contains a terminating action for the repetitive inspection requirement. We are issuing this AD to detect and correct cracks in the upper aft longeron, which could cause the fuselage to fail. Such failure could result in loss of control of the airplane.
2022-07-08: The FAA is superseding Airworthiness Directive (AD) 2016-17- 12, which applied to all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2016- 17-12 required inspecting certain trimmable horizontal stabilizer actuators (THSAs) to determine the number of total flight cycles the THSA has accumulated, and replacing the THSA if necessary. Since the FAA issued AD 2016-17-12, the FAA has determined that a more restrictive airworthiness limitations is necessary for carbon friction disks on the no-back brake (NBB) of the THSA. This AD continues to require the inspections of the THSAs and replacement if necessary. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2022-07-06: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8F and 747-8 series airplanes. This AD was prompted by a report of unusual flight instrument and engine indication and crew alerting system (EICAS) behavior. This AD requires inspecting the left, center, and right electronic flight instrument system (EFIS)/EICAS interface unit (EIU) for certain serial numbers and replacement if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
73-12-07: 73-12-07 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1655. Applies to Viscount Model 744, 745D, and 810 Series airplanes. Compliance is required as indicated. To prevent failures of the nacelle structure tubes and end fittings on high time engine nacelle structures due to fatigue and corrosion, accomplish the following: (a) For airplanes which have not been inspected in accordance with paragraph (h) of AD 66-12-3 prior to the effective date of this AD, - (1) Within the next 500 landings or 12 calendar months, whichever occurs sooner, after the effective date of this AD, and thereafter at intervals not to exceed 7,500 landings form the last inspection, comply with paragraph (e); and (2) Within the next 500 landings after the effective date of this AD or before the accumulation of 19,000 total landings, whichever occurs later, and thereafter at intervals not to exceed 7,500 landings from the last inspection, comply with paragraph (d). (b) For airplanes which haveaccumulated 5,500 or more landings since compliance with paragraph (h) of AD 66-12-3, within the next 2,000 landings after the effective date of this AD, or before the accumulation of 19,000 total landings, whichever occurs later, and thereafter at intervals not to exceed 7,500 landings from the last inspection, comply with paragraphs (d) and (e). (c) For airplanes which have accumulated less than 5,500 landings since compliance with paragraph (h) of AD 66-12-3 on the effective date of this AD, within the next 7,500 landings after compliance with paragraph (h) of AD 66-12-3 or, before the accumulation of 19,000 total landings , whichever occurs later, and thereafter at intervals not to exceed 7,500 landings from the last inspection, comply with paragraphs (d) and (e). (d) Inspect the engine nacelle structure tubes and end fittings for cracks at the positions specified for the applicable technique in figures 1 and 2 of British Aircraft Corporation (BAC) Ltd., Preliminary Technical Leaflet (PTL) No. 258, Issue 4 (700 Series), dated August 31, 1971, or No. 122, Issue 4 (800/810 Series), dated August 31, 1971, using dye penetrant, radiographic, and ultrasonic resonance methods in accordance with Techniques 1, 3, and 4, respectively, of the applicable PTL or an FAA-approved equivalent. (e) Inspect the engine nacelle structure tubes for internal corrosion at the positions specified for Technique 2 in figures 1 and 2 of BAC Ltd. PTL No. 258, Issue 4 (700 Series), dated August 31, 1971, or No. 122, Issue 4 (800/810 Series), dated August 31, 1971, using the radiographic method in accordance with Technique 2 of the applicable PTL or an FAA-approved equivalent. (f) If, during an inspection required by paragraph (a), (b), or (c), any end fittings are found cracked, or any tubes are found cracked or corroded beyond the limits specified in the applicable PTL, before further flight replace the affected parts with serviceable parts of the same part number. Thissupersedes Amendment 39-231 (31 F.R. 6790), AD 66-12-3. This Amendment becomes effective July 5, 1973.
2022-07-14: The FAA is adopting a new airworthiness directive (AD) for certain Viking Air Limited (type certificate previously held by Bombardier Inc. and de Havilland, Inc.) Model DHC-6-400 airplanes. This AD was prompted by 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 corrosion of the fuel system components located in the fuel gallery due to inadequate corrosion protection. This AD requires repetitively inspecting the fuel gallery for corrosion, rectifying any deficiencies, and accomplishing modifications to the fuel gallery system. The FAA is issuing this AD to address the unsafe condition on these products.
2022-06-15: The FAA is adopting a new airworthiness directive (AD) for all De Havilland Aircraft of Canada Limited Model DHC-8-401 and -402 airplanes. This AD was prompted by reports of bleed air leaks in the wing box area and failure of the leak detection shroud. This AD requires removing and inspecting the affected V-band coupling and check valve seals, doing corrective actions if necessary, and replacing the coupling and seals with a redesigned assembly. The FAA is issuing this AD to address the unsafe condition on these products.
2004-15-20: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and -145 series airplanes, that requires replacing the electrical harness for the tail boom strobe light with a new, improved harness that has a built-in metallic overbraid, and performing an operational test following the replacement. This action is necessary to ensure that there is sufficient lightning bonding at the electrical harness for the tail boom strobe light, and to prevent the simultaneous failure of multiple avionics systems in the event of a lightning strike, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
72-16-09: 72-16-09 HUGHES: Amendment 39-1497. Applies to Hughes Model 369A and 369H Series Helicopters certificated in all categories. Compliance required as indicated. To prevent possible failure of the input gearshaft assembly, accomplish the following: (a) For those helicopters incorporating tail rotor input gearshaft assemblies (see NOTE for P/N's) which have accumulated 2,000 hours' or more time in service on the effective date of this AD, accomplish (c) and (d), below, unless already accomplished, prior to further flight. (b) For those helicopters incorporating tail rotor input gearshaft assemblies (see NOTE for P/N's) which have accumulated 1,800 hours' or more time in service on the effective date of this AD, accomplish (c) and (d), below, within 100 additional time in service, unless already accomplished. If the additional time in service would result in a total time in service in excess of 2000 hours, the 100 hours' compliance time shall be reduced by that amount necessary to prevent any tail rotor input gearshaft assemblies from being operated beyond 2000 hours before accomplishment of this AD. (c) Revise the helicopter logbook, as applicable, to record both the input and the output gearshaft assemblies incorporated in the 369A5406 tail rotor gear set, per the instructions of Part I of Hughes Service Information Notice No. HN-53, dated July 24, 1972, or later FAA approved revisions. (d) Retire and replace the 369A5425 and 369A5425-3 input gearshaft assemblies (input part of 369A5406 gearset), per the instructions of Part II of Hughes Service Information Notice No. HN-53, dated July 24, 1972, or later FAA approved revisions. Owners and operators may exercise the options specified in Part II of the Notice. NOTE: The part number assemblies and finite life are: TAIL ROTOR INPUT FINITE GEARSHAFT ASSEMBLY LIFE P/N 369A5406 (input only) 1,800 hours P/N 369A5425, -3 1,800 hours P/N 369A5425-5 27,600 hoursNOTE: The P/N 369A5406 tail rotor gearset is comprised of an input gearshaft assembly and a pinion output gearshaft assembly. The finite life of all existing pinion output gearshaft assemblies remains unchanged at 2,940 hours. This amendment becomes effective August 8, 1972.
2022-07-10: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that certain overheat detection system (OHDS) sensing elements may not properly detect thermal bleed leak events due to a quality escape during the manufacturing process. This AD requires revising the operator's existing FAA-approved minimum equipment list (MEL) to include dispatch restrictions as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts. This AD also allows operators to inspect affected parts for discrepancies, and do applicable replacements, in order to terminate the revision of the operator's existing MEL required by this AD. The FAA is issuing this AD to address the unsafe condition on these products.
2004-15-11: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires cleaning the auxiliary system unit (ASU) board and modifying the wiring and wiring harness. If a temporary modification is done, the AD requires inserting a placard regarding on-ground operation of the emergency landing gear pump (pump). Also, this AD revises the Limitations section of the Rotorcraft Flight Manual (RFM) to limit the operation of the pump. Permanently modifying the wiring and wiring harness and removing the placard and limitations from the RFM is terminating action for the requirements of this AD. This amendment is prompted by the report of an emergency landing with the landing gear retracted. The landing gear failed to extend in normal and emergency extension modes following failure of the ASU board 10 Alpha 2. The actions specified by this AD are intended to prevent an electrical short circuit, failure of landing gear to extend, and a landing gear-up emergency landing.