Results
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.
96-07-14: 96-07-14 CONSTRUCCIONES AERONAUTICAS, S.A. (CASA): Amendment 39-9564. Docket 92-NM-75-AD. Applicability: All Model C-212-CB, -CC, -CD, -CE, and -CF series airplanes, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the airplane, accomplish the following: (a) For Model C-212-CB series airplanes: Prior to the accumulation of 16,500 total landings, or within 6 months after the effective date of this AD, whichever occurs later, replace the horizontal stabilizer-to-fuselage attach fittings, part numbers 212-31101.05 and 212-31102.05, with part numbers 212-31122.03 and 212-31123.05, respectively, in accordance with the CASA C-212 Aircraft Maintenance Manual, Chapter 5, Section 5-20, task number 55.15. NOTE 2: Replacement of the attach fittings on Model C-212-CB series airplanes may be accomplished by replacing part numbers 212-31101.05 and 212-31102.05 with part numbers 212- 31123.30 and 212-31122.29, respectively. (b) For all airplanes: Incorporate a revision into the FAA-approved maintenance inspection program that provides for inspection of the Principal Structural Elements (PSE) defined in CASA SupplementalInspection Document (SID) C-212-PV-01-SID, dated June 1, 1987 (hereinafter referred to as the "Document"), at the later of the times specified in paragraphs (b)(1) and (b)(2) of this AD. NOTE 3: Certain thresholds and intervals for inspections of the wing flap control system required by AD 89-02-08 R1, amendment 39-6280, are more restrictive than those specified in the Document. Where differences exist, the thresholds and intervals specified in AD 89-02-08 R1 prevail. (1) Prior to the accumulation of 20,000 total landings or 20,000 total hours time-in- service, whichever occurs first. Or (2) Within 9 months after the effective date of this AD. (c) Any cracked structure detected during the inspections required by paragraph (b) of this AD must be repaired or replaced, prior to further flight, in accordance with the instructions in the Document, or in accordance with other data meeting the certification basis of the airplane that is approved by the FAA or by theDirecci n General de Aviaci n Civil (DGAC). (d) Within 10 days after accomplishing each inspection required by paragraph (b) of this AD, report the results (positive or negative) of each inspection required by paragraph (b) of this AD to CASA in accordance with the Document. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (g) The maintenance program revision shall be done in accordance with CASA Supplemental Inspection Document (SID) C-212-PV-01-SID, dated June 1, 1987. (NOTE: The date of Volumes 2 and 3 of the SID is indicated only on the title page of the volume.) 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 Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at theOffice of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on May 15, 1996.
99-23-18: This amendment adopts a new airworthiness directive (AD) applicable to Bell Helicopter Textron Canada (BHTC) Model 407 helicopters. This action requires, before further flight, revising the life limits for certain parts and replacing each part that has exceeded its life limit. The AD also requires revising the applicable component history cards or equivalent records and the Airworthiness Limitations Schedule of the BHTC Model 407 maintenance manual to reflect these new life limits. This amendment is prompted by an engineering evaluation of additional flight test data, which resulted in redefining the service life for certain parts and revising the Airworthiness Limitations Schedule. The actions specified in this AD are intended to prevent a fatigue failure of certain parts that may have exceeded revised life limits and subsequent loss of control of the helicopter.
91-26-05 R1: 91-26-05 R1 BOEING: Amendment 39-8887. Docket 93-NM-64-AD. Revises AD 91-26-05, Amendment 39-8116. \n\n\tApplicability: Model 747-400 series airplanes, excluding airplanes having production line numbers 816, 839, and 961 and subsequent; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tNOTE 1: Paragraph (a) of this AD restates the requirements of paragraph (a) of AD 91-26-05, amendment 39-8116. As allowed by the phrase, "unless accomplished previously," if the requirements of AD 91-26-05 have been accomplished previously, paragraph (a) of this revised AD does not require the insertion of the Airplane Flight Manual (AFM) limitation to be repeated. \n\n\tTo prevent loss of all very high frequency (VHF) radio voice communication transmission capability, accomplish the following: \n\n\t(a)\tWithin 14 days after December 30, 1991 (the effective date of AD 91-26-05, amendment 39-8116): Add the following statement to the Limitations Section of the FAA- approved AFM. This may be accomplished by placing a copy of this AD in the AFM. \n\n\n\t"ELECTRONIC SYSTEMS \n\t\tVHF RADIO VOICE COMMUNICATIONS \n\n\t\tRight VHF radio (VHF R) communication system must be operational for dispatch." \n\n\t(b)\tReplacement of the currently-installed audio management unit (AMU) of the VHF radio communication system having Boeing part numbers S220U000-101, -102, or -104, (Hughes-Avicom part numbers 1167014-140, -141, or -142), with a modified AMU having Boeing part number S220U000-105 (Hughes part number 1167014-143), in accordance with Boeing Service Bulletin 747-23-2321, dated May 20, 1993, constitutes terminating action for the requirements of this AD. Following accomplishment of this replacement, the AFM limitation required by paragraph (a) of this AD may be removed. \n\n\t(c)\tAs of the effective date of this AD, no AMU having Boeing part numbers S220U000-101, -102, or -104, (Hughes-Avicom part numbers 1167014-140, -141, or -142), shall be installed on any airplane, unless the requirements of paragraph (a) of this AD have been accomplished. \n\n\t(d)\tAn alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. \n\n\tNOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(e)\tSpecial flight permits may be issued in accordance with sections 21.197 and 21.199 Federal Aviation Regulations (14 CFR sections 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. \n\n\t(f)\tThis amendment becomes effective on May 20, 1994.
2004-19-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes, that currently requires revising the airplane flight manual and eventual disconnection of the precooler differential pressure switches. This amendment expands the applicability of the existing AD. This amendment also requires a one-time inspection of those additional airplanes to ensure the disconnection and insulation of the electrical connectors of certain precooler differential pressure switches located in the left and right pylons; and disconnection and insulation of the connectors, if necessary. The actions specified by this AD are intended to prevent incorrect operation of the precooler differential pressure switches, which could result in inappropriate automatic shutoff of the engine bleed valve, and consequent inability to restart a failed engine using cross-bleed from the other engine or possible failure of the anti-ice system.This action is also necessary to ensure that the flightcrew is advised of the procedures necessary to restart an engine in flight using the auxiliary power unit. This action is intended to address the identified unsafe condition.
95-15-05: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A airplanes, that requires modification of the elevator control system of the flight controls. This amendment is prompted by reports of low frequency constant amplitude oscillations of the elevator control system and non-centering of the pitch control upon autopilot disconnect. The actions specified by this AD are intended to prevent uncommanded descent upon autopilot disconnect and reduced controllability of the airplane due to low frequency constant amplitude oscillations.
2022-13-18: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-700, 737-800, 747-400, 747-8, 767- 400ER, and 777-200 airplanes. This AD was prompted by a report that there is the potential for electrical current to pass through low pressure (LP) oxygen flex-hoses in the gaseous passenger oxygen system. This AD requires replacing each conductive oxygen flex-hose installed on LP gaseous passenger oxygen systems with a serviceable non- conductive oxygen flex-hose. This AD also prohibits installation of a conductive oxygen flex-hose on LP gaseous passenger oxygen systems. The FAA is issuing this AD to address the unsafe condition on these products.
2022-15-06: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This AD was prompted by high electrical resistance within the gust suppression sensor (GSS) transorb modules due to corrosion on the transorb module threads. This AD requires disconnecting the connectors and capping and stowing the wires that had been attached to the affected transorb modules. The FAA is issuing this AD to address the unsafe condition on these products.
92-20-04: 92-20-04 CANADAIR, LTD.: Amendment 39-8378. Docket No. 91-NM-248-AD. Supersedes AD 91-17-02, Amendment 39-8000. Applicability: Model CL-600-2A12 (CL-601) and CL-600-2B16 (CL-601-3A) series airplanes equipped with a tail cone fuel tank, installed in accordance with the Original Issue, Revision 1, or Revision 2 of Canadair Service Bulletin 601-0262, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the presence of fuel vapors in the aft equipment bay, which could result in an in-flight fire in the event of a lightning strike or other ignition source in the area, accomplish the following: (a) Within 5 days after August 28, 1991 (the effective date of AD 91-17-02, Amendment 39-8000), or prior to refuelling of the tail cone fuel tank, whichever occurs later, perform a visual inspection of the unshrouded portion of the sensing line in the aft equipment bay to detect any damage or deformation, in accordance with Canadair Alert Wire TA601-0381-003, dated June 11, 1991. Thereafter, repeat the inspection prior to each refuelling. If damage or deformation of the sensing line is found as a result of the visual inspection, accomplish either subparagraph (a)(1) or (a)(2) of this AD, in accordance with the alert wire: (1) Prior to further flight, drain the tail cone fuel tank, and continue flight operations with no fuel in the tail cone fuel tank; or (2) Prior to further flight, drain the tail cone fuel tank, replace the level control valve sensing line, and continue flight operations with fuel in the tail cone fuel tank. (b) After each refuelling of the tail cone fuel tank, inspect for any signs of leakage from the fuel sensing line in the aft equipment bay and at the fuel shroud drain, in accordance with Canadair Alert Wire TA601-0381-003, dated June 11, 1991. If leakage is found, prior to further flight, either drain the tail cone fuel tank, or replace the tail cone fuel tanklevel control valve sensing line, in accordance with the alert wire. (c) Within 6 months after the effective date of this AD, modify the sensing line; perform functional tests of the refuel/defuel line, tail tank fuel shroud, and tail tank sensing line; and perform an electrical bonding and resistance test on all fuel lines installed during this modification; in accordance with Canadair Alert Service Bulletin A601-0381, Revision 2, dated January 27, 1992. (d) Modification of the sensing line, as required by paragraph (c) of this AD, constitutes terminating action for the repetitive inspections required by paragraphs (a) and (b) of this AD. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (f) 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. (g) The modification and test shall be done in accordance with Canadair Alert Service Bulletin A601-0381, Revision 2, dated January 27, 1992. 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. The inspection shall be done in accordance with Canadair Alert Wire TA601-0381-003, dated June 11, 1991. This incorporation by reference was approved previously by the Director of the Federal Register as of August 28, 1991 (56 FR 38337, August 13, 1991). Copies may be obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station A, Montreal, Quebec H3C 3G9, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on November 17, 1992.