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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.