Results
2005-04-02: The FAA is adopting a new airworthiness directive (AD) for all Dassault Model Falcon 10 series airplanes. This AD requires a temporary change to the airplane flight manual (AFM) to provide procedures to the flightcrew for touchdown using the main landing gear to avoid a three- point landing. This AD also requires repetitive inspections of the piston rod of the drag strut actuator of the nose landing gear (NLG) for cracks, which would terminate the AFM revision, and corrective actions if necessary. In addition, this AD provides for a terminating modification, which would end the repetitive inspections. This AD is prompted by reports of failure of the piston rod of the drag strut actuator of the NLG. The cause of such failure has been attributed to fatigue cracking caused by corrosion in the piston rod of the drag strut actuator. We are issuing this AD to prevent cracking and/or fracture of the piston rod of the drag strut actuator of the NLG, which could result in a gear-up landing, structural damage, and possible injury to passengers and crew.
2005-03-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires doing repetitive inspections for fractures and cracks of the links of the aileron power control unit (PCU); replacing any fractured/cracked link; and doing applicable related investigative and corrective actions, if necessary. This AD is prompted by reports indicating that the links of the aileron PCU have failed. We are issuing this AD to prevent failure of both links of the aileron PCU, which could result in reduced lateral control of the airplane.
2015-02-17: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes. This AD requires revising the electrical emergency configuration procedure in the Emergency Procedures section of the airplane flight manual (AFM) to include procedures for deploying the ram air turbine manually to provide sufficient hydraulic power and avoid constant speed motor/generator (CSM/G) shedding. This AD was prompted by an electrical load analysis that revealed that hydraulic power might not be sufficient to supply the CSM/G during slat/flap extension when only one engine is running. We are issuing this AD to prevent such a condition which, in conjunction with the loss of the main electrical system, could lead to the scenario where the flightcrew is not clearly warned that the electrical system has switched on the battery and thus has a limited duration that would allow a safe landing.
77-03-05: 77-03-05 BEECH: Amendment 39-2827. Applies to Models A23-19, 19A, M19A and B19 (Serial Numbers MB-1 through MB-536); Models 23, A23, A23A, B23 and C23 (Serial Numbers M-2 through M-1392); and Models A23-24 and A24 (Serial Numbers MA-1 through MA-368) airplanes certificated in all categories. Compliance: Required as indicated unless already accomplished. To prevent possible collapse during landing or in-flight separation of the main landing gear, accomplish the following in accordance with Beech Service Instructions No. 0465-202, Rev. I or later FAA approved Revisions: A. Within the next 150 hours' time in service after the effective date of this AD for those aircraft on 100 hour (FAR 91.169(b)) inspections, progressive (FAR 91.171) inspections or approved aircraft inspection program (FAR 135.60) or within eighteen (18) months after the effective date of this AD for those aircraft on annual (FAR 91.169(a)) inspections: 1. Remove left and right main landing gearhousing (male part) from wing strut adapter (female part). 2. Using dye penetrant procedures, inspect the main landing gear housings (male part), in the areas around the fore and aft retention bolt hole for cracks. 3. If no cracks are found as a result of the inspection required in paragraph A.2.: a. Reinstall the main gear housings in accordance with Beech Service Instruction 0465-202, Revision I or later FAA approved revisions. b. Do not install any bolt in the fore and aft retention bolt hole. 4. If cracks are found during inspection required in paragraph A.2. above, prior to further flight: a. Replace any cracked main gear housing with a new Beech Part No. 169-810011-25 housing assembly in accordance with Beech Service Instructions 0465-202, Revision I or later FAA approved revisions. b. Do not install any bolt in the fore and aft retention bolt hole. NOTE. Even through Beech Service Instruction 0465-202, Rev. I refers to P/N 169- 810011-21 housing, Beech will ship a P/N 169-810011-25 housing assembly. The P/N 169- 810011-25 assembly consists of two bushings installed in a P/N 169-810011-21 housing. B. Any equivalent means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective March 14, 1977.
90-04-02: 90-04-02 LOCKHEED AERONAUTICAL SYSTEMS COMPANY-GEORGIA: Amendment 39-6479, Docket No. 89-NM-281-AD. Applicability: Model 382G series airplanes, Serial Numbers 5022, 5025, 5027, and 5029, certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless previously accomplished. To prevent the loss of the ability to extinguish a fire, accomplish the following: A. Inspect all six wrenching surfaces (flats) on the hexagonal shaped part of the engine fire extinguisher system squibs to determine the part number and manufacturing date that is stamped on the wrenching surface, in accordance with Lockheed Alert Service Bulletin A382-26-7, dated November 4, 1989. Prior to further flight, remove all Whittaker Ordnance fire extinguisher squibs Part Number 4199-1 (Lockheed Part Number 695679-15) with manufacturing date 7/87, and install Whittaker Ordnance fire extinguisher squibs that do not have 7/87 stamped on the wrenching surfaces or other approved squibs. WARNING: Observe all applicable safety precautions during the inspection. The fire extinguisher squibs are similar to a pistol cartridge. The squibs contain an explosive charge which could cause injury or death if accidentally fired. Do not expose squibs to heat, or an electric current, or strike or drop squibs. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Small Airplane Directorate, Atlanta, Georgia. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Atlanta Aircraft Certification Office. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements ofthis AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Lockheed Aeronautical Systems Company, Field Service Office, 86 South Cobb Drive, Marietta, Georgia 30063. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia. This amendment (39-6479, AD 90-04-02) becomes effective on February 26, 1990.
2023-18-08: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model MYSTERE-FALCON 900, FALCON 900EX, FALCON 2000, and FALCON 2000EX airplanes. This AD was prompted by reports of the wing anti-icing (WAI) system leaking in the wing leading edge. This AD requires a one-time inspection of the WAI system, 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.
2005-04-04: The FAA is adopting a new airworthiness directive (AD) for all Saab Model SAAB SF340A and SAAB 340B series airplanes. This AD requires a one-time inspection to determine the part and serial numbers of certain engine vibration isolators (mounts) and the cure dates of certain molded assemblies incorporated in those engine mounts; and related corrective actions if necessary. This AD is prompted by a report that disbonding of the elastomer from the inner metal core and shim of certain engine vibration mounts has occurred within a few hundred hours of operation, causing heavy chafing of the engine support system and chafing of the fire sensor loop. We are issuing this AD to prevent reduced integrity of the fire-shielding capacity of the nacelle structure and a possible fire detector fault.
2023-18-07: The FAA is superseding Airworthiness Directive (AD) 2020-03- 19, which applied to certain Dassault Aviation Model MYSTERE-FALCON 20- C5, 20-D5, 20-E5, and 20-F5 airplanes. AD 2020-03-19 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD continues to require the actions in AD 2020-03-19 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. 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.
78-04-03: 78-04-03 MCDONNELL DOUGLAS: Amendment 39-3141. Applies to Model DC-9 Series airplanes, certificated in all categories, including Military Type C-9A, C-9B, and VC-9C, F/N's 1 through 862. \n\n\tCompliance required as indicated. \n\n\tTo prevent the aileron/spoiler mixer cam from disengaging from the cam roller, accomplish the following: \n\n\t(a)\tWithin the next 275 hours time in service after the effective date of this AD, unless already accomplished, inspect and re-shim if required as specified in Items 1 through 6 under Accomplishment Instructions in McDonnell Douglas DC-9 Alert Service Bulletin A27-189 dated October 7, 1977 or later FAA approved revision. \n\n\t(b)\tWithin the next 2000 hours time in service after the effective date of this AD, unless already accomplished, add washers as specified in Item 7 under Accomplishment Instructions in McDonnell Douglas DC-9 Alert Service Bulletin A27-189 dated October 7, 1977 or later FAA approved revision, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(c)\tSpecial Flight permits may be issued in accordance with FAR's 21.197 and 21.199 to authorize operation of an airplane to a base for the accomplishment of the inspections and modifications required by this AD. \n\n\tThis amendment becomes effective February 21, 1978.
2005-04-01: The FAA is adopting a new airworthiness directive (AD) for certain Boeing transport category airplanes. This AD requires repetitive tests of the overwing fuel fill ports for certain wing tanks; an electrical bonding resistance test between the bulkhead fittings of the engine fuel feed tube and the front spar inside the fuel tank of the wings; other specified actions; and applicable corrective actions if necessary. This AD is prompted by our determination that this AD is necessary to reduce the potential for ignition sources inside fuel tanks. We are issuing this AD to prevent arcing or sparking at the interface between the bulkhead fittings of the engine fuel feed tube and the front spar inside the fuel tank of the wings and between the overwing fuel fill ports and the airplane structure during a lightning strike. Such arcing or sparking could provide a possible ignition source for the fuel vapor inside the fuel tank and cause consequent fuel tank explosions.
2023-17-07: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model A119 and AW119 MKII helicopters. This AD was prompted by a report of an electrical failure of a starter-generator caused by a ruptured drive shaft. This AD requires visually inspecting the drive shaft of an affected starter-generator and depending on the results, performing a dye penetrant inspection. Depending on the results of the dye penetrant inspection, this AD requires replacing the starter-generator, 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.
2023-19-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 series; A330-200 Freighter series; A330-300 series; A330-800 series; A330-900 series; A340-200 series; and A340-300 series airplanes. This AD was prompted by reports of cracks found in the scroll housing assembly of Honeywell GTCP331-350 auxiliary power units (APUs). This AD requires replacing each affected APU or re- identifying certain APU scroll housing assemblies, and prohibits the installation of affected parts under certain conditions, 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.
2000-16-52: This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (AD) 2000-16-52 which was sent previously to all known U.S. owners and operators of Eurocopter France (ECF) Model AS350B3 helicopters by individual letters. This AD requires visually inspecting the heat shield attachment areas on the tail rotor drive shaft forward fairing (fairing) for a crack. This AD also requires, at specified time intervals, removing the fairing and inspecting the heat shield attachment areas on the fairing for a crack. If a crack is found, this AD requires replacing the fairing with an airworthy fairing. This amendment is prompted by an in-flight loss of the fairing heat shield due to cracking in the areas where the heat shield is attached to the fairing. The actions specified by this AD are intended to prevent an in-flight loss of the heat shield, impact with tail or main rotor blades, and subsequent loss of control of the helicopter.
91-20-04: 1-20-04 BOEING: Amendment 39-8038. Docket No. 91-NM-38-AD. \n\n\tApplicability: Boeing Model 737-300, -400, and -500 series airplanes, as listed in Boeing Service Bulletin 737-27-1161, dated November 1, 1990, certificated in any category. \n\n\tCompliance: Required within 36 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent uncommanded stabilizer movement in the static position, accomplish the following: \n\n\t(a)\tRemove the existing stabilizer trim jackscrew actuator and replace it with a stabilizer trim assembly that has been modified with the redesigned auxiliary brake assembly in accordance with Boeing Service Bulletin 737-27-1161, dated November 1, 1990. \n\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should beforwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\t(d)\tThe replacement requirements shall be done in accordance with Boeing Service Bulletin 737-27-1161, dated November 1, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. \n\n\tThis amendment (39-8038, AD 91-20-04) becomes effective on November 7, 1991.
2005-03-15: The FAA is adopting a new airworthiness directive (AD) for certain BAE Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This AD requires repetitive inspections to detect discrepancies of the fuselage skin and reinforcing plates along the wing to fuselage fairing access panels on the left- and right-hand sides of the airplane, and repair if necessary. This AD also provides for an optional terminating action for the repetitive inspections. This AD is prompted by a report of chafing on the wing to fuselage fairing panels. We are issuing this AD to prevent chafing of the fuselage skin and reinforcing plates, which could lead to reduced structural integrity of the airplane's fuselage.
2023-17-12: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd. & Co. KG (RRD) Model RB211 Trent 768-60, 772-60, and 772B-60 engines. This AD was prompted by reports of cracks on affected intermediate-pressure compressor (IPC) rotor shaft balance lands. This AD requires repetitive on-wing or in-shop borescope inspections (BSIs) of the affected IPC rotor shaft balance land for cracks and replacement of any IPC rotor shaft if necessary and prohibits the installation of an affected IPC rotor shaft on any engine, 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.
95-08-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that requires modification of the spoiler system. This amendment is prompted by reports of fatigue failures of the tee fittings of the spoiler bleed nipples. The actions specified by this AD are intended to ensure that the tee fittings do not fail, and subsequently lead to loss of the main system hydraulics.
2005-03-08: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350B, BA, B1, B2, B3, C, D, D1, and EC130 B4 helicopters that requires removing and modifying the fuel bleed lever. This amendment is prompted by some cases of loss of the fuel bleed lever in flight. If the tension of the control cable is too low, the cable may vibrate out of its notch, resulting in the fuel bleed lever separating from the hinge. The actions specified by this AD are intended to prevent a fuel bleed lever from separating and striking the tail rotor blade (blade), resulting in damage to or loss of a blade, and subsequent vibration and loss of control of the helicopter.
2023-17-10: The FAA is adopting a new airworthiness directive (AD) for certain Vulcanair S.p.A. Model V1.0 airplanes. 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 identifies the unsafe condition as corrosion on the lower fuselage truss. This AD requires a detailed visual inspection of the right-hand (RH) and left-hand (LH) lower rear attachments of the fuselage truss for corrosion, a tactile inspection of the lower rear attachments for missing sealant, and a general visual inspection of the lower fuselage truss welded pipes for corrosion and the related rivets for missing stems and, depending on findings, additional inspections and actions (including a tap test) and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
2023-17-04: The FAA is superseding Airworthiness Directive (AD) 2022-04-04 for certain Continental Aerospace Technologies, Inc. (Continental) Model C-125, C145, IO-360, IO-470, IO-550, O-300, O-470, TSIO-360, and TSIO-520 series engines and certain Continental Motors IO-520 series engines with a certain oil filter adapter installed. AD 2022-04-04 required replacing the oil filter adapter fiber gasket (fiber gasket) with an oil filter adapter copper gasket (copper gasket). This AD was prompted by reports of two accidents that were the result of power loss due to oil starvation. This AD requires replacing the fiber gasket with a copper gasket or a stainless steel embedded within polytetrafluoroethylene gasket (stainless steel PTFE gasket). This AD also revises the applicability to include Continental model engines equipped with an F&M Enterprises, Inc. (F&M) or a Stratus Tool Technologies, LLC (Stratus) oil filter adapter installed. The FAA is issuing this AD to address the unsafe condition on these products.
78-07-11: 78-07-11 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-3172. Applies to AW-650 Series 101 airplanes certificated in all categories. To detect corrosion in the wing joints which if left undetected could seriously affect the structural strength of the wing, accomplish the following: (a) Before further flight, except that the airplane may be flown in accordance with FAR 21.197 and 21.199 to a base where the work can be performed, dismantle the intermediate to center joints and inspect and rework as necessary in accordance with the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Limited Service Bulletin 57/55, dated September 1977, or an FAA-approved equivalent. For the purpose of complying with this AD the following Hawker Siddeley Aviation, Ltd., reports referenced in Service Bulletin 57/55 are applicable: HSA-MES-R-650-0001, Issue 2, December 1977. HSA-MES-R-650-0002, Issue 2, December 1977. HSA-MES-R-650-0003, Issue 3, January 1978. HSA-MES-R-650-0004, Issue 3, January 1978. HSA-MES-R-650-0005, Issue 2, December 1977. HSA-MES-R-650-0006, Issue 3, January 1978. This amendment becomes effective April 20, 1978.
2023-17-01: The FAA is adopting a new airworthiness directive (AD) for all ATR--GIE Avions de Transport R[eacute]gional Model ATR42 and ATR72 airplanes. This AD was prompted by a determination that some batches of nose landing gear (NLG) drag brace panels (DBP) having certain part numbers were affected by a quality deficiency that was not detected in production. This AD requires a measurement of the affected part and, depending on findings, accomplishment of applicable corrective actions, 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. The FAA is issuing this AD to address the unsafe condition on these products.
97-06-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757-200 series airplanes. This action requires inspections to detect cracking on the free edge of the tang, if necessary, and of the fastener holes in the lower spar chord; and various follow-on actions. This action also provides for optional terminating action for the requirements of this AD. This amendment is prompted by a report of fatigue cracking in the lower spar chord of two Model 757 series airplanes. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in reduced structural integrity of the engine strut.
2005-03-16: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Model DH.125, HS.125, and BH.125 series airplanes; BAe.125 series 800A (C-29A and U-125) and 800B airplanes; and Hawker 800 (including variant U-125A) and 800XP airplanes. This AD requires installing insulating blankets on the engine compartment firewall and the wire harness passing through the firewall fairlead. This AD is prompted by a report indicating that insulation on the wire harness passing through the firewall fairlead ignited on the fuselage side of the firewall. We are issuing this AD to prevent a fire in the engine compartment from causing possible ignition of outgassing wire insulation on the fuselage side of the firewall, which could lead to an uncontrollable fire in the fuselage.
2023-17-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, Model A330-300 series airplanes, Model A340-200 series airplanes, and Model A340-300 series airplanes. This AD was prompted by a report that certain overheat detection system (OHDS) sensing elements, produced before January 31, 2021, may not properly detect thermal bleed leak events due to a quality escape during the manufacturing process. This AD requires a one-time special detailed inspection (SDI) for discrepancies of each affected part installed at an affected position, and replacement of discrepant parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD would also prohibit the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.