Results
2023-21-04: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. (Embraer) Model EMB-505 airplanes. This AD was prompted by occurrences of an uncommanded change in the setting of the barometric pressure in both primary flight displays (PFDs). This AD requires installing a new version of the airplane avionics system software, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-20-10: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by a report that some of the multi-function spoiler (MFS) anti-rotation plates failed in-service due to a thin wall design. This AD requires replacing the MFS anti-rotation plates, inspecting the MFS anti-rotation plates for cracking and hinge bolts for evidence of rotation, accomplishing applicable corrective actions, and performing a functional test of the MFS control surfaces. The FAA is issuing this AD to address the unsafe condition on these products.
2000-20-19: This amendment supersedes an existing airworthiness directive (AD) for Eurocopter France Model AS-350B, BA, B1, B2, C, D, and D1, and AS-355E, F, F1, and F2 helicopters. That AD currently requires inspections of the main rotor head components, the main gearbox (MGB) suspension bars, and the ground resonance prevention system components. This amendment requires those same inspections, but would also apply to Model AS-350B3 and AS-355N helicopters. This amendment is prompted by the inadvertent omission of those model helicopters from the previous AD. The actions specified by this AD are intended to prevent ground resonance due to reduced structural stiffness, which could lead to failure of a main rotor head or MGB suspension component and subsequent loss of control of the helicopter.
90-21-14: 90-21-14 AIRBUS INDUSTRIE: Amendment 39-6771. Docket No. 90-NM-94-AD. Applicability: Model A320 series airplanes, which have not incorporated Modification 21892, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To prevent failure of the ram air turbine (RAT) to deploy on command due to a malfunction of the extension jack, accomplish the following: A. Remove ejection jack, Part Number (P/N) 114160003, and replace it with a new or modified ejection jack, P/N 114160004 or 114160005, in accordance with Airbus Industrie Service Bulletin A320-29-1030, dated February 15, 1990. 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. 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 of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6771, AD 90-21-14) becomes effective on November 19, 1990.
2023-20-12: The FAA is superseding Airworthiness Directive (AD) 2022-18- 09, which applied to certain Airbus SAS Model A319-111, -112, -113, - 114, -115, -131, -132, and -133; A320-211, -212, -214, -216, -231, - 232, -233, -251N, and -271N; and A321-111, -112, -131, -211, -212, - 213, -231, -232, -251N, and -253N airplanes. AD 2022-18-09 continued to require the actions in AD 2019-26-01 and AD 2021-23-15, and added airplanes to the applicability. Since the FAA issued AD 2022-18-09, it was determined that additional airplanes and galleys are subject to the unsafe condition, and a compliance time for certain airplanes should be extended. This AD continues to require the actions in AD 2022-18-09 and requires expanding the applicability, obtaining and following additional instructions for certain modified airplanes, and extending the compliance time for certain airplanes, 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.
2000-20-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires modification of the nacelle strut and wing structure. This amendment is prompted by reports indicating that the actual operational loads applied to the nacelle are higher than the analytical loads that were used during the initial design. Such an increase in loading can lead to fatigue cracking in primary strut structure prior to an airplane reaching its design service objective. The actions specified by this AD are intended to prevent fatigue cracking in primary strut structure and consequent reduced structural integrity of the strut.
2000-20-16: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 757-200 series airplanes. This action requires repetitive inspections of the cargo loader system in the forward and aft cargo compartments to detect discrepancies, and corrective actions, if necessary. This action is necessary to detect and correct such discrepancies, which could result in reduced structural integrity of the fuselage and consequent cabin depressurization.
81-12-02: 81-12-02 LOCKHEED: Amendment 39-4127. Applies to Model 382 series airplanes, Serial Numbers 3946 and 4101 through 4871 except 4834, 4839, 4850, and 4853, certificated in all categories. Compliance required during the next "B" or "C" inspection/check, whichever occurs first after the effective date of this AD, unless already accomplished. To prevent possible failure of the longerons, accomplish the following: a. Inspect the center fuselage upper longeron splice bolts, immediately aft of fuselage station 597.00, along buttock line 20.00, on each side of the airplane, for correct installation, and determine the condition category of the airplane in accordance with Lockheed-Georgia Company Service Bulletin No. A382-53-29, Revision 1, dated April 24, 1981, or later FAA approved revision. b. If an out-of-tolerance condition is found to exist, accomplish one of the following: 1. Based on the condition category, placard the airplane in accordance with Lockheed-GeorgiaCompany Service Bulletin No. A382-53-29, Revision 1, dated April 24, 1981, or later FAA approved revision, and incorporate Airplane Flight Manual (AFM) Supplement No. 382-11, dated February 18, 1981. The AFM Supplement may be obtained from the Lockheed- Georgia Company, Marietta, Georgia 30063. If repairs are accomplished in accordance with b.2., placards and AFM Supplement may be discarded. 2. Repair the airplane in accordance with Lockheed-Georgia Company Service Bulletin No. A382-53-29, Revision 1, dated April 24, 1981, or later FAA approved revision, or an alternate method of compliance, approved by the Chief, Engineering and Manufacturing Branch, Southern Region. c. An alternate method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Southern Region. d. 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 of this AD. This amendment becomes effective June 5, 1981.
2015-02-11: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-300, A340-200, and A340-300 series airplanes. This AD was prompted by a report of substantial inner skin disbonding damage found on a rudder. This AD requires performing an inspection for damage of certain rudders, and repair if necessary. We are issuing this AD to detect and correct damage of the rudder, which could result in reduced structural integrity of the rudder.
2000-19-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes powered by Rolls-Royce RB211 series engines. This action requires modification of the nacelle strut and wing structure. This action is necessary to prevent fatigue cracking in primary strut structure and consequent reduced structural integrity of the strut. This action is intended to address the identified unsafe condition.
79-03-05: 79-03-05 BRITTEN-NORMAN (Bembridge) LTD: Amendment 39-3412. Applies to Model BN-2A Mk III Trislander series airplanes, certificated in all categories. Compliance is required, as indicated, unless already accomplished. To prevent structural failure of the main landing gear: (a) Within the next 10 hours time in service after the effective date of this AD, inspect the shock absorber mounting flange, P/N NB-40-C-075, at attachment point to the lower extremity of the main landing gear leg extension tube, P/N NB-40-D-337, for sheared or loose rivets and general structural integrity in accordance with paragraph "ACTION" of Britten- Norman Service Bulletin BN-2/SB.118 (Service Bulletin), dated July 25, 1978, or an FAA- approved equivalent. (b) If, during any inspection required by this AD, sheared or loose rivets or indications of movement of the mounting flange within the extension tube are found, before further flight, accomplish the appropriate rectification and modification in accordance with paragraph "Rectification/Modification" (Mod. NB/M/1007) of the Service Bulletin, or an FAA- approved equivalent. (c) If, during the inspection required by paragraph (a) of this AD, no sheared or loose rivets or indications of movement of the mounting flange within the extension tube are found, the airplane may be returned to service and thereafter, prior to the accumulation of 200 hours time in service after the completion of the inspection required by paragraph (a) of this AD, accomplish the rectification and modification required by paragraph (b) of this AD. (d) If, prior to the accomplishment of the rectification and modification required by this AD, the landing gear is abused, e.g., the aircraft experiences hard or rough landings, a blown tire, sharp turns pivoting about a braked wheel, or taxiing over rough or soft surfaces, before further flight, inspect the shock absorber mounting flange, P/N NB-40-C-075, at attachment point to the lower extremity of the main landing gear extension tube, P/N NB-40-D-337, for sheared or loose rivets and general structural integrity in accordance with paragraph "ACTION" of the Service Bulletin, or an FAA-approved equivalent. (e) Within the next 10 hours time in service after the effective date of this AD, fabricate and install in the cockpit near the limitation placard a temporary placard, which must remain in place until the rectification and modification required by this AD are accomplished, which states: CAUTION 1. Avoid sharp turns pivoting about a braked wheel. 2. Avoid taxiing over rough or soft surfaces. 3. Record any abuse of the landing gear, e.g., hard or rough landings, blown tire, sharp turns pivoting about a braked wheel, taxiing over rough or soft surfaces, in the aircraft maintenance log book or other appropriate maintenance record and have inspected in accordance with AD 79-03-05 prior to next flight. 4. These limitations must be observed until the modification required by AD 79-03- 05 is incorporated. (f) Before installation on aircraft, incorporate Britten-Norman Mod. NB/M/1007 or an FAA-approved equivalent on main landing gear extension tube assemblies held as spares which do not already incorporate that modification. This amendment becomes effective February 27, 1979.
77-14-08: 77-14-08 BEECH: Amendment 39-2960. Applies to Models 60 (Serial Number P-3 thru P-126 except P-123), A60 (Serial Numbers P-123, P-127 thru P-246), and B60 (Serial Numbers P-247 thru P-346) airplanes certified in all categories. Compliance: Required as indicated, unless already accomplished. To prevent collection of water in the bottom of the fuselage, subsequent freezing of the water and resulting restriction of elevator control, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: A. Locate and drill five (5) .250 inch diameter drain holes and install five (5) Beech P/N 50-420082-3 drain seals in the bottom of the fuselage in accordance with Beechcraft Service Instructions No. 0741-103, Rev. I, or later approved revisions. B. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective August 18, 1977.
2023-20-02: The FAA is superseding Airworthiness Directive (AD) 2022-18- 12, which applied to all Airbus SAS Model A330-841 and -941 airplanes. AD 2022-18-12 required installing serviceable engine electronic control (EEC) software or EEC units having the serviceable software, limiting certain parts installation configurations, and prior or concurrent modification of EEC software. This AD was prompted by a determination that engine crystal icing protection could be (temporarily) lost if an erroneous total pressure value is provided by the airplane system, which is addressed through EEC software. This AD continues to require certain actions in AD 2022-18-12 and requires adding new limitations for intermixing of certain EEC software standards and a new operational limitation for engines with certain EEC software installed, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of certain engines under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2023-19-08: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a manufacturing quality escape concerning the installation of the Halon metering device on certain cargo fire extinguisher containers. This AD requires the inspection of cargo fire extinguisher container serial numbers and the replacement of the affected containers. This AD would also limit the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
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.