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2013-08-06: We are adopting a new airworthiness directive (AD) for Bell Model 430 helicopters, which requires replacing certain components of the air data system. This AD was prompted by the discovery of incorrect indicated airspeed when the helicopter was tested to the cold temperature limits (-40 degrees centigrade) required for Category A operations. The actions of this AD are intended to correct the published Vne and to correct the indicated airspeed.
93-02-12: 93-02-12 BEECH AIRCRAFT CORPORATION: Amendment 39-8495. Docket 92-NM-183-AD. Applicability: Model 400A airplanes; serial numbers RK-2 through RK-29, inclusive, RK-31, and RK-32; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the loss of standby power and the possibility of an electrical fire, accomplish the following: (a) Within 100 hours time-in-service after the effective date of this AD, inspect the left-hand interstage turbine temperature (LH ITT) circuit breaker wiring, in accordance with Beechcraft Service Bulletin No. 2458 (ATA Code 39-10), dated August 1992. Prior to further flight, correct any discrepancies found, in accordance with the service bulletin. (b) 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, Wichita Aircraft Certification Office (ACO), FAA, Small 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, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (c) 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. (d) The inspection shall be done in accordance with Beechcraft Service Bulletin No. 2458 (ATA Code 39-10), dated August 1992. (NOTE: The issue date of Beechcraft Service Bulletin No. 2458 is indicated only on "page 1 of 5"; no other page is dated.) 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 Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085.Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on March 26, 1993.
74-25-05: 74-25-05 SIKORSKY: Amendment 39-2030. Applies to S-61L, S-61N, S-61NM and S- 61R helicopters certificated in all categories including Military Type CH-3C helicopters equipped with S6115-20501 series, S6115-20601 series, S6117-20101 series, and S6188-15001 series main rotor blades except for blades with serial numbers subsequent to 61M-6350-6105 and blades which have had all main rotor blade pockets replaced by Sikorsky Aircraft after October 30, 1972. Compliance required within 5 hours time in service after the effective date of this AD. The maximum never exceed speed is hereby reduced to 110 knots. Install placards as close as practicable to the airspeed indicators reading as follows: "Never exceed speed 110 knots." This supersedes telegram dated October 8, 1974 and supersedes the maximum never exceed speed established by Airworthiness Directive 74-20-7, Amendment 39-1989. This amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated November 6, 1974.
2025-06-08: The FAA is adopting a new airworthiness directive (AD) for all Deutsche Aircraft GmbH (Type Certificate previously held by 328 Support Services GmbH; AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 and Model 328-300 airplanes. This AD was prompted by a report of a nose landing gear (NLG) uplock bracket assembly cracking. This AD requires an inspection of the affected part and applicable on-condition actions, 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.
2013-07-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-700, -700C, -800, and -900ER series airplanes, Model 747-400F series airplanes, and Model 767-200 and -300 series airplanes. This AD was prompted by reports indicating that certain crew oxygen mask stowage box units were possibly delivered with a burr in the inlet fitting. The burr might break loose during test or operation, and might pose an ignition source or cause an inlet valve to jam. This final rule adds a step to identify and label certain crew oxygen mask stowage box units that have already been inspected and reworked by the supplier, and allows operators to install new or serviceable crew oxygen mask stowage box units, and requires a general visual inspection for affected serial numbers of the crew oxygen mask stowage box units, and replacement or re-identification as necessary. We are issuing this AD to prevent an ignition source, which could result in an oxygen-fed fire; or an inlet valve jam in a crew oxygen mask stowage box unit, which could result in restricted flow of oxygen.
2000-05-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400A and 400T series airplanes, that requires a one-time inspection to detect incorrect wiring of the engine fire extinguisher bottle squibs, and corrective action, if necessary. It also requires a modification to the wiring and the addition of wire harness and bottle labeling for future reference. This amendment is prompted by reports of incorrect wiring of the engine fire extinguisher bottle squibs. The actions specified by this AD are intended to prevent failure of the engine fire extinguisher bottle to discharge, or discharge of the wrong engine fire extinguisher bottle.
91-26-09: 91-26-09 McDONNELL DOUGLAS: Amendment 39-8122. Docket No. 91-NM-136-AD. Supersedes AD 91-02-13, Amendment 39-6867. \n\n\tApplicability: Model DC-9-10, -20, -30, -40, and -50 series airplanes and C-9 (Military) series airplanes, operating in a passenger or passenger/cargo configuration, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tNOTE: The requirements of this AD become applicable at the time an airplane in an all-cargo configuration is converted to a passenger or passenger/cargo configuration. \n\n\tTo prevent failure of the tailcone release system, accomplish the following: \n\n\t(a)\tWithin 60 days after February 11, 1991 (the effective date of AD 91-02-13, Amendment 39-6867), unless previously accomplished within the last 60 days, inspect the interior and exterior tailcone release handles for cracks, in accordance with the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin A53-242, dated December20, 1990, or Alert Service Bulletin A53-243, Revision 1, dated February 8, 1991; and accomplish a tailcone release system functional test in accordance with the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin A53-243, dated January 10, 1991, or Revision 1, dated February 8, 1991. \n\n\t\t(1)\tCracked or broken tailcone release handles must be replaced prior to further flight. \n\n\t\t(2)\tDiscrepancies in the operation of the tailcone release system found as a result of the functional test must be repaired prior to further flight. \n\n\t(b)\tRepeat the inspection of the interior and exterior tailcone release handles and conduct the functional test required by paragraph (a) of this AD at intervals not to exceed 3,000 flight hours or 15 months, whichever occurs first. \n\n\t(c)\tWithin 30 days after discovery, report any cracked or broken tailcone release handles or any discrepancies found during the accomplishment of the inspection and functional tests required by paragraph (a) of this AD to the Manager, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California 90806-2425. 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 1990 (Pub. L 96-511) and have been assigned OMB Control Number 2120-0056. \n\n\t(d)\tWithin 90 days after the effective date of this AD, replace or modify the internal and external tailcone release system cable and handle assemblies, in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin 53-245, Revision 1, dated June 12, 1991. Accomplishment of such replacement or modification constitutes terminating action for the repetitive inspections of the interior and exterior tailcone release handles for cracks, as required by paragraph (b) of this AD. However, the repetitive functional tests of the tailcone release system required by paragraph(b) of this AD must continue to be accomplished. \n\n\tNOTE: The following portions of the continuing repetitive functional tests and inspections of the tailcone release system are not necessary to accomplish once the replacement/modification of the cable and handle assembly is completed: Those procedures specified in paragraphs H. and L., and the second paragraph of the Notes of paragraphs F. and J., of the Accomplishment Instructions of McDonnell Douglas Alert Service Bulletin A53-243, dated January 10, 1991, Revision 1, dated February 8, 1991, and all of McDonnell Douglas Alert Service Bulletin A53-242, dated December 20, 1990. \n\n\t(e)\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, Los Angeles 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, Los Angeles ACO. \n\n\t(f)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\t(g)\tThe inspection requirements of this AD shall be accomplished in accordance with McDonnell Douglas Alert Service Bulletin A53-242, dated December 20, 1990, or McDonnell Douglas Alert Service Bulletin A53-243, Revision 1, dated February 8, 1991. The functional test requirements of this AD shall be accomplished in accordance with McDonnell Douglas Alert Service Bulletin A53-243, dated January 10, 1991, or McDonnell Douglas Alert Service Bulletin A53-243, Revision 1, dated February 8, 1991. The replacement and modification requirements shall be accomplished in accordance with McDonnell Douglas Service Bulletin 53-245, Revision 1, dated June 12, 1991. 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 McDonnell Douglas Corporation, Post Office Box 1771, Long Beach, California 90801, ATTN: Business unit Manager, Technical Publications, Technical Administration Support, C1-L5B(45-60). Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\t(h)\tAirworthiness Directive 91-26-09, supersedes AD 91-02-13, Amendment 39-6867. \n\n\t(i)\tThis amendment (39-8122, AD 91-26-09) becomes effective on February 17, 1992.
89-25-01: 89-25-01 SIKORSKY AIRCRAFT: Amendment 39-6401. Docket No. 89-ASW-33. Applicability: Model S-58 series helicopters equipped with reciprocating engines, certificated in any category except restricted. Compliance: Required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. To prevent or reduce the hazards of an in-flight fire which could result in loss of the helicopter, accomplish the following: (a) Inspect the helicopter for the installation of an approved engine compartment fire extinguishing system. (b) If an approved engine fire extinguishing system is installed, no further action is necessary. (c) If an approved engine fire extinguishing system is not installed, accomplish the following: (1) Prior to further flight, install a placard, decal, or markings, in full view of and legible to the pilot in daylight which states "Engine Fire Extinguishing System Not Installed." (2) Prior to further flight, revise the helicopter's FAA-approved Rotorcraft Flight Manual (RFM) Operating Limitations Section by attaching or placing in front of the RFM a durable card or paper which contains the following limitations: (i) "No passengers allowed, except required crew and passengers necessary to accomplish a work program when carried on the flights to and from the work site." (ii) "Prior to the first flight of the day, test and determine that the fire detector system is properly functioning in accordance with the normal procedure section of the RFM." NOTE: An engine fire detector system is part of the approved type design and is required by the certification basis. Installation and proper operation are necessary for a determination of airworthiness in accordance with FAR Section 91.29. (3) Prior to November 30, 1990, install an approved engine compartment fire extinguishing system in accordance with technical data approved by the Administrator. When the fire extinguishing system has been installed, the placard, etc., required by paragraph (c)(1) and the RFM limitations required by paragraph (c)(2) may be removed. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) An alternate method of compliance or adjustment of the compliance times, which provides an equivalent level of safety, may be used if approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts 01803. NOTE: An operator's request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Boston Aircraft Certification Office. This amendment (39-6401, AD 89-25-01) becomes effective on December 26, 1989.
2013-07-04: We are superseding an existing airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. That AD currently requires installing spacer assemblies at the attachment points of the YZ-latches of the cargo loading system (CLS) in the forward and aft cargo compartments, as applicable. This new AD also requires modifying the attachment points of fixed YZ-latches of the CLS lower deck cargo holds on those airplanes on which one or both lower deck cargo holds have not been modified, which terminates the existing requirements. This AD was prompted by results from tests that have shown that the attachment points of the YZ-latches of the cargo loading system (CLS) fail under maximum loads and reports that installation has been applied only on one of the lower deck cargo holds, instead of on both forward and aft cargo holds, and that some airplanes could have installed the affected YZ-latches through the instructions of the cargo conversion manual. We areissuing this AD to prevent failure of the attachment points of the YZ-latches, which could result in unrestrained cargo causing damage to the fire protection system, hydraulic system, electrical wiring, or other equipment located in the forward and aft cargo compartments. This damage could adversely affect the continued safe flight of the airplane.
75-06-03: 75-06-03 BELL: Amendment 39-2122 as amended by Amendment 39-2146 and 39-2350 is further amended by Amendment 39-2386. Applies to Bell Models 206A, 206B, 206A-1, and 206B-1 helicopters, certificated in all categories, equipped with pitch link assemblies, P/N 206- 010-330 or 206-010-342. Compliance required within 10 hours' time in service after March 12, 1975, unless already accomplished. To detect possible fatigue cracks in each main rotor pitch link assembly, upper and lower clevis, accomplish the following. a. Remove each main rotor blade pitch link assembly from the helicopter and measure the distance between the bolt holes. Remove the upper and lower clevis from each pitch link assembly in accordance with Bell Model 206A or 206B maintenance and overhaul instructions. b. Inspect the threaded shank of each clevis using fluorescent penetrant or an equivalent inspection method. c. Replace each clevis that has a cracked shank before further flight. d. Assemble the pitch link assemblies in accordance with the Model 206A or 206B maintenance and overhaul instructions and set the pitch link assembly to the appropriate length measured in paragraph (a) of this AD. e. Determine that each bearing, P/N 206-010-469-1, installed in the swashplate outer ring horns has a breakaway force that does not exceed 10 pounds when measured as specified in the Mailgram dated February 15, 1975, from Bell Helicopter Company to all 206A, 206B, and TH57A operators or as specified in an FAA approved equivalent procedure. f. Replace each swashplate outer ring horn bearing, P/N 206-010-469-1, that exceeds 10 pounds breakaway force measured in paragraph (e) of this AD, prior to further flight, in accordance with procedures specified in Section XIV of the Bell Model 206A or 206B maintenance and overhaul instructions dated November 1, 1972, or later revision, or as specified in an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. g. Install the pitch link assemblies in accordance with the Bell Model 206A or 206B maintenance and overhaul instructions. h. This AD does not apply to the main rotor pitch link assemblies, P/N 206-010- 355. The 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). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S. W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. Amendment 39-2122 became effective March 12, 1975. Amendment 39-2146 became effective March 19, 1975. Amendment 39-2350 became effective October 2, 1975. This amendment 39-2386 becomes effective October 20, 1975.