Results
2004-19-04: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-22B, RB211-524, and RB211-535 series turbofan engines. This AD requires revising the Time Limits Manual for RR RB211-22B, RB211-524, and RB211-535 series turbofan engines. These revisions include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD results from the need to require enhanced inspection of selected critical life-limited parts of RB211-22B, RB211-524, and RB211-535 series turbofan engines. We are issuing this AD to prevent failure of critical life-limited rotating engine parts, which could result in an uncontained engine failure and damage to the airplane.
96-13-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 series airplanes, that requires replacement of junction fittings of the horizontal stabilizer with improved fittings. For certain airplanes, this amendment also requires replacement of the drive-fitting bushings and bolts of the horizontal stabilizer with improved bushings and bolts. This amendment is prompted by reports of stress corrosion cracking in a junction fitting lug of the horizontal stabilizer. The actions specified by this AD are intended to prevent such cracking, which could result in failure of a lug and uncommanded movement of the horizontal stabilizer. This condition, if not corrected, could result in reduced controllability of the airplane.
91-07-04: 91-07-04 BOEING: Amendment 39-6933. Docket No. 90-NM-116-AD. \n\n\tApplicability: Model 737 series airplanes, line numbers 001 through 519, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent rapid decompression of the airplane, accomplish the following: \n\n\tA.\tWithin the next 3,000 cycles after the effective date of this AD, unless previously accomplished within the last 3,000 cycles, and thereafter at intervals not to exceed 6,000 cycles, perform an ultrasonic inspection for delamination of the window belt skin doubler from the fuselage skin, in accordance with Boeing Service Bulletin 737-53-1078, Revision 1, dated September 25, 1986, or Revision 2, dated April 19, 1990. \n\n\tB.\tIf delamination is found as a result of the inspections required by paragraph A. of this AD, prior to further flight, conduct a high frequency eddy current (HFEC) inspection for cracks of the skin around the countersunk fasteners in thearea of delamination and common to the window forging, in accordance with Boeing Model 737 Non-destructive Test (NDT) Manual Document D6-37239, Part 6, Subject 53-30-05, and repeat thereafter at intervals not to exceed 6,000 cycles. \n\n\tC.\tIf cracks are detected as a result of the inspection required by paragraph B. of this AD, prior to further flight, repair cracking and delamination in accordance with Boeing Service Bulletin 737-53-1078, Revision 1, dated September 25, 1986, or Revision 2, dated April 19, 1990. Further HFEC inspections for cracks under the repairs are not required. \n\n\tD.\tIf delamination is found as a result of the inspection required by paragraph A. of this AD, perform the terminating modification in accordance with Boeing Service Bulletin 737- 53-1078, Revision 1, dated September 25, 1986, or Revision 2, dated April 19, 1990, prior to the accumulation of 40,000 cycles or within the next 24 months, whichever occurs later, after discovery of the delamination. Accomplishment of this modification constitutes terminating action for the inspections required by paragraphs A. and B. of this AD. \n\n\tE.\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 be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\tF.\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\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tAirworthiness Directive 91-07-04 supersedes AD 89-15-05, Amendment 39-6264. \n\n\tThis amendment (39-6933, AD 91-07-04) becomes effective on April 15, 1991.
2022-18-01: The FAA is superseding Airworthiness Directive (AD) 2017-10- 24, which applied to certain Airbus SAS Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330- 300 series airplanes; AD 2018-23-14, which applied to certain Airbus SAS Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, and Model A330-300 series airplanes; and AD 2021-05-12, which applied to certain Airbus SAS Model A330-200 Freighter series airplanes. AD 2017-10-24, AD 2018-23-14, and AD 2021-05-12 require revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD revises the applicability by adding airplanes. This AD continues to require the actions in AD 2018-23-14 and AD 2021-05-12, and 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. The FAA is issuing this AD to address the unsafe condition on these products.
2022-17-13: The FAA is adopting a new airworthiness directive (AD) for certain Piaggio Aero Industries S.p.A. (Piaggio) Model P-180 airplanes. This AD is 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 identifies the unsafe condition as altimetry system errors in the air data computers (ADCs) and stand-by instrument systems. This AD requires amending the existing airplane flight manual (AFM), installing improved ADCs and a detachable configuration module (DCM), and revising the existing instructions for continued airworthiness. The FAA is issuing this AD to address the unsafe condition on these products.
90-14-09: 90-14-09 SHORT BROTHERS: Amendment 39-6649. Docket No. 90-NM-128-AD. Applicability: Model SD3-60 series airplanes, Serial Numbers SH3601 through SH3642, inclusive, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the wings, accomplish the following: A. Upon the accumulation of 9,600 hours time-in-service or within 30 days after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 600 hours time-in-service, perform the following inspections: 1. For airplanes with Serial Numbers SH360l through SH3635, inclusive: Perform a visual inspection of the left and right outerwing/strut attachment fittings in accordance with Short Brothers Service Bulletin SD360-57-12, dated June 8, 1990. 2. For airplanes with Serial Numbers SH3601 through SH3642, inclusive: Perform a visual inspection of the left and right stub wing/strut attachment fittings in accordance with Short Brothers Service Bulletin SD360-57-12, dated June 8, 1990. B. If cracks are found, prior to further flight, repair or replace with serviceable part in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. C. 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. 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. All persons affectedby this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Short Brothers, PLC, Service Representative, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6649, AD 90-14-09) becomes effective on July 23, 1990.
91-07-12: 91-07-12 BRITISH AEROSPACE: Amendment 39-6950. Docket No. 90-NM-273-AD. Applicability: All Model DH/BH/HS 125 series airplanes, post-modification 255640, certificated in any category. Compliance is required as indicated, unless previously accomplished. To ensure proper operation of the main landing gear (MLG) door, accomplish the following: A. Prior to the accumulation of 6,000 landings on the right and left MLG door aluminum forward hinge fittings, or within the next 400 landings after December 4, 1990 (the effective date of Amendment 39-6786, AD 90-23-01), whichever occurs later, and thereafter at intervals not to exceed 6,000 landings, replace the aluminum forward hinge fittings in accordance with British Aerospace Service Bulletin 32-218, dated July 28, 1988. B. Replacement of an aluminum hinge fitting with a new stainless steel hinge fitting, in accordance with British Aerospace Service Bulletin 32-220-3176A, B, and C, dated September 2, 1988, terminates the requirements for the replacement of the hinge fittings required by paragraph A. of this AD. C. An 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. 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. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 91-07-12 supersedes AD 90-23-01, Amendment 39-6786. This amendment (39-6950, AD 91-07-12) becomes effective on April 29, 1991.
2004-20-02: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 707 and 720 series airplanes, that requires an inspection of the main landing gear (MLG) lock support fitting and the wing fillet flap support link for damage, and corrective action, if necessary; and replacement of the bolts and bushings at the joint between the MLG lock support fitting and the wing fillet flap support link. This action is necessary to prevent stress corrosion cracking of the bolts and wearing of the joint between the lock support fitting and the support link, which could lead to failure of the joint and could cause the collapse of the MLG. This action is intended to address the identified unsafe condition.
2013-12-05: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model MBB-BK 117 C-2 helicopters. This AD requires determining if a certain serial-numbered bevel gear is installed in the tailrotor intermediate gear box (IGB). If such a bevel gear is installed in the IGB, this AD requires recording the bevel gear's reduced life limit in the Airworthiness Limitations section of the maintenance manual and on the component history card or equivalent IGB record. If the bevel gear's life limit has been reached or exceeded, this AD requires, before further flight, replacing the bevel gear with an airworthy bevel gear. This AD is prompted by the discovery that the tooth foot fillets in certain bevel gears fall below the minimum dimensions required in the design documents to ensure safe functioning of the bevel gear until it reaches its approved life limit. This AD's actions are intended to prevent failure of a bevel gear before it reaches its currentlyapproved life limit, failure of the IGB, and subsequent loss of helicopter control.
96-25-15: This amendment adopts a new airworthiness directive (AD), applicable to certain transport category airplanes equipped with certain Honeywell Standard Windshear Detection System (WSS). It requires a revision to the airplane flight manual to alert the flightcrew of the potential for significant delays in the WSS detecting windshear when the flaps of the airplane are in transition. This amendment also requires replacement of the currently-installed line replaceable unit (LRU) with a modified LRU having new software that eliminates delays in the WSS. This amendment is prompted by a report of an accident during which an airplane encountered severe windshear during a missed approach. The actions specified by this AD are intended to prevent significant delays in the WSS detecting hazardous windshear, which could lead to the loss of flight path control.
2022-18-16: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) CT7-8A model turboshaft engines. This AD was prompted by the manufacturer revising the airworthiness limitations section (ALS) of the existing engine maintenance manual (EMM) to incorporate reduced life limits for certain stage 1 turbine aft cooling plates, stage 2 turbine forward cooling plates, turbine interstage seals, and stage 4 turbine disks. This AD requires revising the ALS of the existing EMM and the operator's existing approved maintenance or inspection program, as applicable, to incorporate reduced life limits for these parts. The FAA is issuing this AD to address the unsafe condition on these products.
91-06-18: 91-06-18 AIRBUS INDUSTRIE: Amendment 39-6940. Docket No. 90-NM-225-AD. Applicability: All Model A310-200 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks in the wing rear spar and prevent reduced structural integrity of the wings, accomplish the following: A. Prior to the accumulation of 12,000 landings, or within 1,000 landings after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) rototest inspection of the wing rear spar at certain bolt holes where the main landing gear (MLG) forward pick-up fittings are attached to the rear spar, in accordance with Airbus Industrie Service Bulletin A310-57-2046, dated March 5, 1990. 1. If no cracks are found at the first inspection and no cold working of the holes concerned is carried out, repeat the HFEC rototest inspection at intervals not to exceed 4,500 landings. 2. If no cracksare found at the first inspection and a spar life extension by cold working of the holes concerned is carried out in accordance with the paragraph 2.3.(1)(b) of the Accomplishment Instructions of the above service bulletin or Airbus Industrie Service Bulletin A310-57-2049, dated April 10, 1990; repeat the HFEC rototest inspection within the next 18,000 landings, and thereafter at intervals not to exceed 12,000 landings. B. If cracks are found, repair prior to further flight, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Repeat the HFEC rototest inspection at an interval approved by the Manager, Standardization Branch, ANM-113. C. 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 theManager, 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. 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. 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 (39-6940, AD 91-06-18) becomes effective on April 22, 1991.
96-21-13: This amendment adopts a new airworthiness directive (AD) that is applicable to LITEF GmbH Attitude and Heading Reference System (AHRS) Unit Model LCR-92, LCR-92S, and LCR-92H installed on but not limited to Sikorsky Aircraft Model S-76 helicopters, McDonnell Douglas Helicopter Systems Model MD-900 helicopters, Bell Helicopter Textron, Inc. Model 412 helicopters, and Pilatus Model PC-12 airplanes. This action requires either installing a placard adjacent to each primary attitude indicator which states that flight is limited to Visual Flight Rules (VFR) operations only, or modifying and inspecting the AHRS wiring cables, requiring a repetitive inspection of the cable shielding, and inserting a statement into the aircraft flight manual. This amendment is prompted by a field report and verified by laboratory tests that shows there is an unusual AHRS reaction to certain radio frequency signals. The actions specified by this AD are intended to prevent reliance on or to correct the cause of misleading roll and pitch information produced by the AHRS when encountering certain radio frequency signals.
2004-20-03: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-8-101, -102, -103, -106, -201, - 202, -301, -311, and -315 airplanes. This amendment requires a detailed inspection of the wing leading edge de-icer boots to determine if they comply with certain patch limits in the critical zone; and corrective action, if necessary. This action is necessary to prevent reduced aerodynamic smoothness of the wing leading edge de-icer boots and possible reduced stall margin, which could result in a significant increase in stall speeds, leading to a possible stall prior to activation of the stall warning. This action is intended to address the identified unsafe condition.
76-12-01: 76-12-01 BELL: Amendment 39-2636. Applies to Bell Models 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, and 47H-1 helicopters certificated in all categories. Compliance required within 300 hours' time in service after the effective date of this AD unless already accomplished. To prevent possible fatigue failure of tail rotor hub bolt, Part Numbers 47-641-052-3 or - 5, accomplish the following: (a) Remove and disassemble the tail rotor hub and blade assembly. (b) Remove the metal grease seal from each tail rotor blade grip and install the seal, Part Number 47-641-042-3, in each blade grip to clear the head of the hub bolt. (c) Remove the hub assembly bolts, Part Numbers 47-641-052-3 or -5, from the tail rotor hub assembly. Install hub bolts, Part Number 47-641-194-1, in the tail rotor hub as specified in paragraph 6-16.e., Section IV, Models 47D-1, 47G, and 47G-2 Maintenance and Overhaul Instruction Manual, as revised August 15, 1961, or as specified by equivalent FAAapproved procedures. (d) Assemble and track and balance the tail rotor hub and blade assembly as specified in the pertinent Model Maintenance and Overhaul Instruction Manual or as specified in FAA approved equivalent procedures. (e) Compliance with Bell Helicopter Company Service Bulletin No. 47-76-1 dated January 5, 1976, or later approved revision fulfills compliance with this AD. This amendment becomes effective July 14, 1976.
2022-17-12: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) LEAP-1A model turbofan engines. This AD was prompted by reports of two in-flight shutdowns (IFSDs) and subsequent investigation by the manufacturer that revealed cracks in the high-pressure turbine (HPT) rotor stage 1 blades. This AD requires initial and repetitive borescope inspections (BSIs) of the HPT rotor stage 1 blades. Depending on the results of the BSIs, this AD requires either additional BSIs at reduced intervals or replacement of the HPT rotor stage 1 blades. This AD also requires sending the inspection results to CFM if any unserviceable finding is found. The FAA is issuing this AD to address the unsafe condition on these products.
78-08-04: 78-08-04 BOEING: Amendment 39-3187. Applies to Model 747 series airplanes certificated in all categories and equipped with pressurization system outflow valve assemblies, Boeing P/N 60B00025-3, -11, -12, and -17 (Hamilton Standard P/N 719201-2, -3, -4, -5, -6, -7, - 8, and -9). Compliance required as indicated. To prevent rapid loss of pressurization in flight accomplish the following: \n\n\tA.\tWithin 350 hours time in service after the effective date of this airworthiness directive, unless already accomplished, and thereafter at intervals not to exceed 900 hours time in service until modified in accordance with part B of this airworthiness directive, inspect forward and aft gates of each outflow valve assembly in accordance with the instructions contained in Boeing Service Bulletin No. 747-21-2139, Revision 1 dated April 7, 1978, or later FAA approved revisions, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. Gates found with delamination or cracks in the hinge-to-gate bonds must be removed and replaced with a part free of delamination or cracks. Removed gates may be forwarded to Hamilton Standard for further evaluation or modified in accordance with part B of this airworthiness directive, as applicable, prior to being returned to service. \n\tB.\tWithin 4000 hours time in service after the effective date of this airworthiness directive, modify the outflow valve assemblies in accordance with the instructions contained in Hamilton Standard Service Bulletin H.S. Code 747 AC-114, Revision 1 dated March 15, 1978, or later FAA approved revision, or by an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tC.\tUpon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the inspection compliance time and/or modification compliance time specified in this airworthiness directive to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\n\tAD 77-25-06, Amendment 39-3098 (42 FR 63637) is hereby superseded. \n\tThis amendment becomes effective May 10, 1978.
2004-19-08: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 800 series turbofan engines. This AD requires revising the Time Limits Manual for RR RB211 Trent 800 series turbofan engines. These revisions include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD results from the need to require enhanced inspection of selected critical life-limited parts of RB211 Trent 800 series turbofan engines. We are issuing this AD to prevent failure of critical life- limited rotating engine parts, which could result in an uncontained engine failure and damage to the airplane.
2013-12-06: We are adopting a new airworthiness directive (AD) for Eurocopter Model MBB-BK117 A-3, MBB-BK117 A-4, MBB-BK117 B-1, and MBB- BK117 C-2 helicopters with a Metro Aviation (Metro) vapor-cycle air conditioning kit installed in accordance with Supplemental Type Certificate (STC) No. SH3880SW. This AD requires repetitively inspecting the air conditioning drive pulley (pulley) for looseness and properly installed lockwire, and also requires reinstalling the pulley. This AD is prompted by two reports of the pulley detaching from the rotor brake disc on the tail rotor (T/R) driveshaft. These actions are intended to prevent separation of the pulley, damage to the T/R driveshaft, and subsequent loss of control of the helicopter.
2022-16-07: The FAA is superseding Airworthiness Directive (AD) 2016-26-05 and AD 2019-21-02, which applied to certain Airbus SAS Model A330-200, A330-200 Freighter, and A330-300 series airplanes. AD 2016-26-05 and AD 2019-21-02 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary, and that new airplanes have been added to the applicability. This AD continues to require the actions in AD 2019-21-02, and also 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) The FAA is issuing this AD to address the unsafe condition on these products.
2022-16-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a dual-engine automatic shutdown on landing. This AD requires revising the existing airplane flight manual (AFM) to incorporate a new normal procedure and revised non-normal procedures, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
92-12-01: 92-12-01 AIRBUS INDUSTRIE: Amendment 39-8261. Docket No. 91-NM-264-AD. Supersedes AD 88-22-08, Amendment 39-6049. Applicability: Airbus Industrie Model A300 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the installation of incorrectly sized bolts, which could lead to loss of tension in the aft attachment of the flap beams, accomplish the following: (a) Within 350 landings after December 1, 1988 (the effective date of AD 88-22-08, Amendment 39-6049), perform a detailed visual inspection of flap beam numbers 2, 3, 4, 5, and 6 aft attachment on both wings to detect damage. Repeat this inspection within 700 landings after December 1, 1988. If damaged parts are found, replace in accordance with Airbus Industrie Service Bulletin A300-57-150, Revision 1, dated September 18, 1987, or in accordance with Airbus Industrie Service Bulletin A300-57-145, Revision 3, dated February 10, 1988.(b) For airplanes on which Modification 3553 has not been accomplished: Within 700 landings after December 1, 1988 (the effective date of AD 88-22-08, Amendment 39-6049), replace the bolts on flap beam number 2 with 3/8-inch diameter bolts in accordance with Airbus Industrie Service Bulletin A300-57-145, Revision 3, dated February 10, 1988. (c) For airplanes on which Modification 3553 has been accomplished: Within 1,000 landings after December 1, 1988 (the effective date of AD 88-22-08, Amendment 39-6049), replace the bolts on flap beam number 2 with 7/16-inch diameter bolts in accordance with Airbus Industrie Service Bulletin A300-57-145, Revision 3, dated February 10, 1988. (d) For all airplanes: Within 1,000 landings after the effective date of this AD, replace the bolts on flap beam numbers 3, 4, 5, and 6 with 3/8-inch diameter bolts, in accordance with Airbus Service Bulletin A300-57-145, Revision 3, dated February 10, 1988. (e) Replacement of the flap beam bolts in accordance with Airbus Service Bulletin A300-57-145, Revision 3, dated February 10, 1988, constitutes terminating action for the inspections required by paragraph (a) of this AD. (f) An 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Standardization Branch, ANM-113. (g) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (h) The inspectionsand modifications shall be done in accordance with Airbus Industrie Service Bulletin A300-57-150, Revision 1, dated September 18, 1987; or in accordance with Airbus Industrie Service Bulletin A300-57-145, Revision 3, dated February 10, 1988, as applicable. These service bulletins contain the following list of effective pages: Service Bulletin Page Number Revision Level Date A300-57-150 1-2, 4-9, 1 September 18, 1987 Revision 1 3, 10-12 Original July 10, 1987 A300-57-145 1-3, 6-18 3 February 10, 1988 Revision 3 4-5 2 November 13, 1987 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street NW., 7th Floor, Suite 700, Washington, DC. (i) This amendment becomes effective on September 28, 1992.
2004-19-09: This amendment supersedes an existing emergency airworthiness directive (AD) for the Robinson Helicopter Company (Robinson) Model R22, R22 Alpha, R22 Beta, and R22 Mariner helicopters, that currently requires track-and-balancing certain main rotor blades (blades), replacing blades, and determining the age of each blade and revising the component history card or equivalent maintenance record. This amendment requires the same actions, but changes the applicability and adds clarifying language. It also prohibits the issuance of special flight permits, which the existing AD allows. This amendment is prompted by the need to clarify the existing AD language. The actions specified by this AD are intended to prevent a fatigue crack, blade failure, and subsequent loss of control of the helicopter.
99-24-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200 and -300 series airplanes. This action requires a one-time visual inspection to determine the part number and serial number of the lower drag strut of the nose landing gear (NLG); and corrective actions, if necessary. This amendment is prompted by reports of a fracture of the lower drag strut of the NLG, which was caused by a thin wall thickness condition that occurred during the manufacturing process. The actions specified in this AD are intended to prevent a fracture of the lower drag strut, which could result in collapse of the NLG.
2022-13-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by reports of burned Boeing Material Specification (BMS) 8-39 urethane foam, which is a material with fire-retardant properties that deteriorate with age. This AD requires replacing certain BMS 8-39 foam pads with Nomex felt in certain areas, removing certain BMS 8-39 foam pads in a certain area (which includes a general visual inspection to find BMS 8-39 foam pads), and inspecting the corner seals to determine if the corner seals were replaced, and replacing affected corner seals. This AD also prohibits the installation of BMS 8-39 urethane foam seal in certain locations. The FAA is issuing this AD to address the unsafe condition on these products.