Results
2021-11-11: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200 Freighter series airplanes. This AD was prompted by a report indicating occurrences of broken brackets of the support structure of the halon fire extinguishing bottle 4005WX; investigation showed that fatigue cracks initiated in the attachment brackets at the cross beams due to dynamic loading, and in some cases propagated in the struts. This AD requires replacing the support brackets of the 4005WX fire extinguisher bottle with reinforced support brackets, and replacing the strut assembly at the affected location, 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.
46-46-02: 46-46-02\tNORTH AMERICAN: Was Mandatory Note 6 of AD-2-575-3.) Applies to Army BC-1A, AT-6, -6A, -6B, -6C; Navy SNJ-2, -3, -4 Aircraft.\n \n\tTo be accomplished prior to January 1, 1947. \n\n\tInspect all airplanes having Vest Two-Place Chum Seats installed prior to October 9, 1946, to determine that an elevator rear stop is installed on the horizontal stabilizer rear spar directly in front of the elevator horn and that the modification incorporates revised self-aligning rudder balance brackets, rudder balance cable, rudder pedal adjustment bar and reinforcement plates on forward side of firewall at the balance pulley bracket attachment points in accordance with Vest Installation Instructions dated October 9, 1946.
2004-05-06: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, DC-10-10F, DC- 10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F airplanes; and Model MD-11 and MD-11F airplanes. This amendment requires replacement of the left and right number one passenger door bolted lower seal-to-retainer and girt bar view window assemblies with new, double-flush riveted assemblies. This action is necessary to prevent the number one passenger door slide from inflating before it has cleared the slide cover, which could result in the slide being unusable during an emergency evacuation and consequent injury to passengers or airplane crewmembers. This action is intended to address the identified unsafe condition.
2010-26-54: We are adopting a new airworthiness directive (AD) for the products listed above. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires obtaining written approval from the Manager, Wichita Aircraft Certification Office (ACO), to operate the airplane. This written approval must clearly state that operation is approved per Emergency AD 2010-26-54. This AD was prompted by a Cessna Model LC41-550FG airplane that suffered a significant structural failure in the wing during a production acceptance flight test. We are issuing this AD to prevent catastrophic failure of the wing due to disbonding of the wing skin from the wing spar.
2021-10-21: The FAA is superseding Airworthiness Directive (AD) 2019-07-07 for various Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK117 and Model BO-105 helicopters. AD 2019-07-07 required removing certain part numbered swashplate bellows (bellows) from service, cleaning and inspecting certain parts, and depending on the inspection results removing certain parts from service, applying torque, and repetitively inspecting the swashplate assembly (swashplate). This AD retains certain requirements of AD 2019-07-07, expands the installation prohibition, adds additional inspections, and updates the applicable service information. The FAA is issuing this AD to address an unsafe condition on these products.
2004-05-02: The FAA adopts a new airworthiness directive (AD) for all AeroSpace Technologies of Australia Pty Ltd. (ASTA) Models N22B, N22S, and N24A airplanes. This AD requires you to repetitively inspect wing fittings for fatigue defects, replace or correct defective wing fittings, and replace the stub wing front spar assembly and wing fitting when fatigue life limits are reached. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. We are issuing this AD to detect and correct defects in the wing strut upper end fittings, wing strut lower end fittings, stub wing strut pick up fittings, and the stub wing front spar assembly. These defects could result in failure of the fittings or spar assembly and lead to reduced structural capability or reduced controllability of the airplane.
67-14-05: 67-14-05 BRITISH AIRCRAFT: Amdt. 39-398 Part 39 Federal Register April 14, 1967. Applies to Model BAC 1-11 200 Series Airplanes. Compliance required as indicated. To prevent fatigue failure of the nose landing gear steering jack cylinder gland nut, accomplish the following: (a) Replace aluminum alloy gland nuts P/N AB44-229 having less than 4,900 hours' time in service on the effective date of this AD with unused aluminum alloy gland nuts of the same part number or with steel gland nuts P/N AB44-1793, before the accumulation of 5,000 hours' time in service. (b) Replace aluminum alloy gland nuts P/N AB44-229 having 4,900 or more hours' time in service on the effective date of this AD with unused aluminum alloy gland nuts having the same part number or with steel gland nuts P/N AB44-1793, within the next 100 hours' time in service. (c) Aluminum alloy gland nuts P/N AB44-229 installed as replacement parts in complying with either (a) or (b) must be replaced before the accumulation of 5,000 hours' time in service. (British Aircraft Corporation (BAC) One-Eleven Alert Service Bulletin 32-A-PM 2496 pertains to this subject.) This directive effective May 14, 1967.
2004-05-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-31 and DC-9-32 airplanes, that requires replacement of certain power relays, and subsequent repetitive cleaning, inspecting, repairing, and testing of certain replaced power relays. This action is necessary to prevent internal arcing of the left and right generator power relays, auxiliary power relays, and external power relays, and consequent smoke and/or fire in the cockpit and cabin. This action is intended to address the identified unsafe condition.
2011-01-06: We are superseding an existing airworthiness directive (AD) that applies to 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: During High Time Equipment (HTE) reviews conducted within the scope of the A310 aircraft Design Service Goal (DSG) extension work, Airbus discovered that the splined couplings and the sliding bearings of the flap transmission system could be affected by corrosion and wear, especially when their protective components such as wiper rings and rubber gaiters could become defective. This condition, if not detected and corrected, could degrade the functional integrity of the flap transmission system. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-10-29: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. This AD was prompted by a determination that the cabin swift broadband antenna doubler installation does not meet widespread fatigue damage (WFD) requirements. This AD requires a one- time special detailed inspection of certain fastener holes, replacement of the cabin swift broadband antenna doubler, and repair if necessary, 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.
2004-03-33: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes; Model A300 B4-600, A300 B4-600R, and A300 F4-600R series airplanes (collectively called A300-600); Model A310 series airplanes; Model A319, A320, and A321 series airplanes; Model A330-301, -321, -322, -341, and -342 airplanes; and Model A340 series airplanes. This AD requires, among other actions, replacement of certain pitot probes with certain new pitot probes. The actions specified by this AD are intended to prevent loss or fluctuation of indicated airspeed, which could result in misleading information being provided to the flightcrew. This action is intended to address the identified unsafe condition.
72-17-03: 72-17-03 MCDONNELL DOUGLAS: Amdt. 39-1502. Applies to Model DC-8 Series Airplanes, Fuselage Numbers 1 through 551, inclusive, which correspond to the factory serial numbers listed in Douglas Service Bulletin No. 27-247, dated 21 January 1972, or later FAA-approved revisions; and Model DC-9 Series Airplanes, Fuselage Numbers 1 - 19, 21 - 32, 35 - 546, 548 - 638 and 640 which correspond to the factory serial numbers listed in Douglas Service Bulletin No. 27-148, dated 21 January 1972, or later FAA-approved revisions. \n\n\tCompliance required within the next 90 days after the effective date of this AD unless already accomplished. \n\n\tTo detect defective rudder pedal arm casting perform a one-time-only inspection in accordance with: \n\n\t(1)\tFor Model DC-8 airplanes; per Service Bulletin 27-247, dated 21 January 1972, or later FAA-approved revisions or other FAA-approved equivalent inspection, or \n\n\t(2)\tFor Model DC-9 airplanes; per Service Bulletin 27-148, dated 21 January 1972, or later FAA-approved revisions, or other FAA-approved equivalent inspection. \n\n\tReplace any casting that exceeds the defect limits specified in paragraph 2(h) of the Service Bulletins. \n\n\tThis amendment becomes effective on September 16, 1972.
2021-10-15: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH Model MBB-BK 117 C-2 and Model MBB- BK 117 D-2 helicopters. This AD was prompted by a determination that a life limit for the adapter forward (FWD) of the outboard load system, repetitive inspections of other components of that system, and for certain helicopters, a modification of the outboard load system, are necessary to address the unsafe condition. This AD requires a modification of the outboard load system for certain helicopters, repetitive inspections of the outboard load system and its components for any defect (including cracking, damage, corrosion, and incorrect installation) and applicable corrective actions, and implementation of a new life limit for the FWD adapter, as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is \n\n((Page 28477)) \n\nincorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2021-11-06: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by the loss of a windshield in flight, and the consequent rapid depressurization of the flight deck, which caused damage to flight deck items and systems and subsequent thermal shock and overheat, damage to windshield structural plies, and impaired structural integrity of the windshield. This AD requires repetitive inspections and electrical test measurements (EMTs) of affected windshields, and corrective actions if necessary, 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.
69-26-03: 69-26-03 ALLISON: Amdt. 39-895. Applies to Model 250-C18 Series Engines. Compliance: Unless already accomplished, accomplish the following: (1) At next overhaul but no later than 750 hours' time in service since last overhaul or since new if never overhauled, modify the engine in accordance with Allison Commercial Engine Bulletins numbered 250CEB-57, - 58, -59, -61, -62, -63, -65, -66, -67, -68, -69, -70, -72, -73, -74, -75, -76, -77, -78, -79, -80, -81, -85, -86 and -89, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, except as specified in (2) below. (2) At next overhaul but no later than 1125 hours' time in service since last overhaul or since new if never overhauled, modify the power and accessories gear box in accordance with applicable portions of Allison Commercial Engine Bulletins specified in (1) above, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Central Region.(3) All engines must be modified in accordance with (1) and (2) above on or before October 1, 1971. This amendment becomes effective December 25, 1969.
2021-10-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH Model BO-105A, BO-105C, BO- 105S, and BO-105LS A-3 helicopters. This AD was prompted by the FAA's determination that aging of the elastomeric material in a tension torsion strap (TT-strap) could affect the structural characteristics of the TT-strap. This AD requires replacement of certain TT-straps with serviceable parts and implementation of a new storage life limit for TT-straps, as specified in a European Aviation Safety Agency (now 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.
2004-05-01: The FAA adopts a new airworthiness directive (AD) for certain Bombardier Inc. (formerly deHavilland Inc.) Model Otter DHC-3 airplanes that have turbine engines installed per one of three supplemental type certificates (STC). This AD prohibits you from operating any affected airplane with these engine and propeller configurations unless a new STC for an elevator servo-tab with a redundant control linkage is installed. This AD is the result of reports of the control rod to the elevator servo-tab system detaching from the elevator servo-tab, which caused the elevator servo-tab to flutter on airplanes with a turbine engine installed. We are issuing this AD to prevent a single failure of the elevator servo-tab system, which could cause severe tab flutter. This failure could lead to possible loss of control of the airplane.
86-25-07 R1: We are rescinding an existing airworthiness directive (AD) for the products listed above. The existing AD resulted 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: Since issuance of that AD, we have determined that the AD is not applicable because the Model LS6 is not type certificated in the United States. During flights at speeds between 250 to 270 km/h (135 to 145 kts) aileron flutter occurred resulting in damage of control stick attachment.
70-01-06: 70-01-06 HUGHES: Amdt. 39-921. Applies to Model 269A, 269A-1, 269A-2 and 269B helicopters certificated in all categories with P/N 269A7506 lateral pitch mixer idler bellcrank assembly installed. To insure continued airworthiness of Hughes Model 269A, 269A-1, 269A-2 and 269B helicopters, with P/N 269A7506 lateral pitch mixer idler bellcrank assembly installed, accomplish the following: (a) For helicopters equipped with P/N 269A7506 bellcrank assembly having less than 875 hours time in service on the effective date of this AD, remove from service P/N 269A7506 lateral pitch mixer idler bellcrank assembly prior to the accumulation of 900 hours time in service, and mark it permanently and conspicuously to prevent its inadvertent return to service. Replace it with a serviceable P/N 269A7506 or P/N 269A7508 lateral pitch mixer idler bellcrank assembly. (b) For helicopters equipped with P/N 269A7506 bellcrank assembly having 875 or more hours' time in service on the effective date of this AD, remove from service P/N 269A7506 lateral pitch mixer idler bellcrank assembly prior to the accumulation of 25 additional hours time in service, and mark it permanently and conspicuously to prevent its inadvertent return to service. Replace it with a serviceable P/N 269A7506 or P/N 269A7508 lateral pitch mixer idler bellcrank assembly. This amendment becomes effective January 17, 1970.
2001-13-18 R1: The FAA is revising Airworthiness Directive (AD) 2001-13-18, which applies to Raytheon Aircraft Corporation (Raytheon) Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) airplanes. AD 2001-13-18 currently requires you to repetitively inspect the wing spar assembly for cracks and replace any wing spar assembly found cracked (unless the spar assembly has a crack indication in the filler strip where the direction of the crack is toward the outside edge of the filler strip). AD 2001-13-18 also requires you to report the results of the initial inspection and maintain the flight and operating restrictions required by AD 99-12-02 until the initial inspection is done. We approved alternative methods of compliance (AMOCs) to AD 2001-13-18. We have since determined that those AMOCs do not address all critical areas in the wing spar assemblies and should no longer be valid. We are issuing this revision to AD 2001-13-18 for the purpose of eliminating the AMOCs to AD 2001-13-18. The actions of this AD are intended to prevent wing spar failure caused by fatigue cracks in the wing spar assemblies and ensure the operational safety of the above-referenced airplanes.
2010-26-12: 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: A manufacturing quality non-conformity has been identified that resulted in the under-crimping of ring tags on a batch of In-tank Fuel Harnesses. The affected ring tags are used to join individual electrical wires in the Wing Tank harness installations to in-tank equipment on QT [Tank Quantity] circuit. The failure of a one or more ring tag crimp connections may result in the disconnection of the electrical wire with a possibility that the loose wire ends can contact the tank structure. When combined with a loss of equipment surface protection this constitutes a potential source of ignition in a fuel tank and consequent danger of fire or explosion. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2021-10-03: The FAA is superseding Airworthiness Directive (AD) 2019-03-12 for certain Airbus Helicopters Model EC225LP helicopters. AD 2019-03-12 required repetitively inspecting, cleaning, and lubricating each life raft inflation cylinder percussion system bellcrank (bellcrank). This new AD continues to require the actions specified in AD 2019-03-12, and requires replacing any affected bellcrank with a serviceable bellcrank, which terminates the repetitive actions. This AD was prompted by reports of jammed bellcranks in the life raft jettison inflation cylinder percussion system. The actions of this AD are intended to address an unsafe condition on these products.
2004-04-09: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) JT15D-1, -1A, and -1B turbofan engines with certain impellers part number (P/N) 3020365. This AD requires a one-time borescope inspection of the rear face of certain impellers for evidence of a machined groove or step, and repair or replacement of the impeller if a groove or step is found. This AD results from three reports of uncontained failure of the impeller. We are issuing this AD to prevent uncontained failure of the impeller and possible damage to the airplane.
2010-26-09: This amendment supersedes an existing emergency airworthiness directive (EAD) for the specified Sikorsky model helicopters. The EAD requires inspecting the LITEF Attitude Heading and Reference System (AHRS) unit of the navigation system to determine if it is at a Mod Status "18.'' If either AHRS unit is at Mod Status "18,'' the EAD requires installing placards on the instrument panel to prohibit single pilot instrument flight rule (IFR) and single pilot night flight and reducing airspeeds to 120 knots indicated airspeed (KIAS) if both autopilots uncouple during instrument meteorological conditions (IMC) or night flight. The EAD also requires inserting minimum crew and airspeed limitations into the Limitations section of the applicable Rotorcraft Flight Manual (RFM) to limit the minimum flight crew to 2 pilots for night flight and IFR flight and to reduce airspeed to 120 KIAS if both autopilots uncouple during IMC or night flight. This amendment contains the same requirements but draws the appropriate distinctions between IFR and IMC as used in the intended operating limitations. Also, unlike the EAD, this AD states the airspeed must be reduced to 120 KIAS if both autopilots uncouple during IMC or night flight. Further, we are removing the limitation contained in the Active Temporary Revisions relating to pilots keeping their hands and feet near the flight controls. This AD was prompted by the need to supersede the EAD to state the distinction between IFR and IMC as used in the operating limitations and to reduce the airspeed to 120 KIAS if both autopilots uncouple during IMC or night flight. The actions specified by this AD are intended to implement operating limitations based on an anomaly in the AHRS related to the 26 volt AC inverter that could result in a decoupling of both autopilots and to prevent loss of control of the helicopter during IMC and during night flight.
97-11-05: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Textron Lycoming) ALF502 and LF507 series turbofan engines, that requires initial and repetitive on-wing eddy current or in-shop fluorescent penetrant inspections of fuel manifold assemblies for cracks, and replacement, if necessary, with serviceable parts. In addition, this AD presents an optional terminating action to the repetitive inspections by replacing the fuel manifold assembly with an assembly of a new, improved design. This amendment is prompted by reports of cracking of the fuel manifold assembly at the No. 5 scallop location. The actions specified by this AD are intended to prevent cracking of the fuel manifold assembly, which could result in an engine fire.