Results
2016-06-06: We are adopting a new airworthiness directive (AD) for certain Quest Aircraft Design, LLC Model KODIAK 100 airplanes. This AD was prompted by a report of limited control yoke movement of the elevator control system due to cushion edging jammed in the elevator control anti-rotation guide slot. This AD requires repetitively inspecting the elevator control system cushion edging for proper condition; replacing the cushion edging; and at a specified time terminating the repetitive inspections by installing wear pads on the elevator bearing assemblies. We are issuing this AD to correct the unsafe condition on these products.
2000-26-10: This amendment adopts a new airworthiness directive (AD), applicable to all BAe Systems (Operations) Limited Model ATP airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of a revision to the airworthiness limitations of the British Aerospace ATP Aircraft Maintenance Manual, which specifies new inspections and compliance times for inspection and replacement action. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
53-17-01: 53-17-01 MOONEY: Applies to All Model M-18 Series Aircraft. Compliance required by October 15, 1953. To prevent possible fouling of controls and the control stick by foreign objects install canvas boot P/N 22-7 around control stick and secure to floor boards. These boots are available from Mooney Aircraft, Inc., Box 72, Kerrville, Texas. (Mooney Service Bulletin No. 11 covers this same subject.)
2016-06-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by reports of cracking at certain fastener locations in the window corners of the window belt area. This AD requires repetitive high frequency eddy current (HFEC) inspections for fatigue cracking in certain fastener locations in the window corners of the window belt area, and related investigative and corrective actions if necessary. This AD also provides an optional preventive modification that terminates the inspections at the modified location. We are issuing this AD to detect and correct fatigue cracking around fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of structural integrity of the airplane.
2016-05-13: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) PT6A-60AG, -65AG, -67AF, and -67AG turboprop engines. This AD requires removing Woodward fuel control units (FCUs) and installing an FCU that is eligible for installation. This AD was prompted by incidents of corrosion and perforation of the two-ply Cu-Be bellows in Woodward FCUs. We are issuing this AD to prevent failure of the Woodward FCU and engine, in-flight shutdown, and loss of control of the airplane.
2000-26-08: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of a revision to the airworthiness limitations of the British Aerospace J41 Aircraft Maintenance Manual. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
78-06-02: 78-06-02 MCCAULEY PROPELLERS: Amendment 39-3159 as amended by Amendment 39-3233. Applies to the following three bladed full feathering constant speed Model 3FF32C501 propellers installed on but not limited to the Cessna Model 421C and 404 aircraft: Affected Propeller Serial Numbers 769303 769304 769571 769572 769573 769574 769575 769576 769577 769578 769579 769580 769581 769582 769583 769584 769585 769586 769587 769588 769589 769590 770176 770177 770178 770179 770601 770602 770603 770604 770605 770606 770607 770643 770644 770645 770646 770647 770648 770649 770650 770651 770652 770653 770654 771239 771291 771318 771319 771320 771321 771322 771323 771324 771325 771326 771327 771328 771329 771330 771331 771332 771333 771334 771335 771491 771492 771493 771495 771496 771497 771498 771499 771500 771534 771535 771536 771537 771538 771539 771540 771734 771735 771736 771737 771738 771739 771740 771741 771742 771743 771744 771745 771746 771747 771748 771839 771840 771841 771843 771848 772212 772213 772335 772336 772337 772338 772339 772340 772341 772342 772343 772344 772345 772346 772347 772348 772349 772396 772397 772398 772399 772400 772401 772429 772430 772432 772433 772434 772435 772436 772437 772438 772439 772440 772952 772953 772958 772959 772960 772961 772994 772995 772996 772997 772998 772999 773000 773047 773048 773049 773050 773051 773052 773053 773054 773055 773056 773057 773058 773059 773060 773061 773062 773066 773184 773185 773186 773187 773188 773189 773190 773191 773348 773349 773350 773351 773352 773353 773356 773358 773359 773360 773361 773573 773574 773575 773896 773897 773898 773899 773903 773966 773969 773970 773971 773973 773974 774113 774116 774122 774124 774175 774178 774180 774181 NOTE: Serialnumbers are stamped on the side of the propeller hub. These propellers are equipped with Model 90UMB-0 blades. Compliance required before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a Federal Aviation Administration Certificate Propeller Repair Station. To prevent possible blade pitch control failures, accomplish the following: (a) Replace blade actuating pin screws, P/N A-1635-104 (cadmium plated), with new screws, P/N A-1635-108 (black oxide) in accordance with McCauley Service Bulletin No. 131 dated January 20, 1978, and Service Manual No. 751201 or later Federal Aviation Administration approved revisions. (b) Replacement of the above parts must be accomplished by a Federal Aviation Administration Certificated Propeller Repair Station, since it is considered a major repair. (c) When the affected propellers are approved for return to service, compliance with this airworthiness directive shall be noted in the Aircraft's Records. The manufacturer's specifications and procedures identified in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer, may obtain copies upon request to McCauley Accessory Division, Cessna Aircraft Company, Box 7, Roosevelt Station, Dayton, Ohio 45417. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this airworthiness directive which includes incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and the Great Lakes Region. Amendment 39-3101 became effective March 22, 1978. This amendment 39-3233 becomes effective on June 7, 1978.
2000-26-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires deactivation of the map light assemblies; or modification and reidentification of the insulation blankets adjacent to certain map light assemblies, if applicable, a general visual inspection to detect damage of the Captain, First Officer, and Right Observer map light assemblies, and follow-on actions. This amendment is prompted by the FAA's determination that certain airplanes equipped with reading light assemblies in the crew rest area are subject to the identified unsafe condition. For certain airplanes, this amendment requires deactivation of the reading light assemblies, or an inspection to detect damage of the reading light assemblies, and follow-on or corrective actions, as applicable. The actions specified in this AD are intended to detect any broken light bulb housing, which could expose the power contactor. An exposed power contactor could cause the Captain, First Officer, or Right Observer map light or reading light in the crew rest area to short or overheat, which could result in smoke or fire in the cockpit.
2000-25-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires inspections to detect cracking of the front spar web of the wing, and corrective action, if necessary. The actions specified by this AD are necessary to detect and correct fatigue cracking of the front spar web, which could result in fuel leaking onto an engine and a consequent fire. This action is intended to address the identified unsafe condition.
93-09-03: 93-09-03 DASSAULT AVIATION: Amendment 39-8570. Docket 92-NM-242-AD. Applicability: Model Mystere-Falcon 900 series airplanes; serial numbers 1 through 9, inclusive; and 11 through 20, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the windshield support structure and potential loss of the windshield, accomplish the following: (a) For airplane serial number 1: Prior to the accumulation of 3,750 total landings, or within 6 months after the effective date of this AD, whichever occurs later, modify the windshield support structure-to-aft window frame attachment at frame 4 on the right-hand and left-hand sides, in accordance with Dassault Aviation F900-91 Service Bulletin F900-53-12 and Appendix 1 to that service bulletin, both dated July 8, 1992. (b) For airplanes having serial numbers 2 through 9, inclusive, and 11 through 20, inclusive: Modify the windshield support structure-to-aft window frame attachment at frame 4 on the right-hand and left-hand sides, in accordance with Dassault Aviation F900-91 Service Bulletin F900-53-12 and Appendix 1 to that service bulletin, both dated July 8, 1992; and at the later of the times specified in paragraphs (b)(1) and (b)(2) of this AD. (1) Prior to the accumulation of 3,750 total landings, or within 6 years since date of manufacture, whichever occurs first. (2) Within 6 months after the effective date of this AD. (c) 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) 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. (e) The modification shall be done in accordance with Dassault Aviation F900-91 Service Bulletin F900-53-12, dated July 8, 1992 and Appendix 1 to that service bulletin F900-53-12, both dated July 8, 1992. (NOTE: Appendix 1 contains pages 101 through 106.) 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 Falcon Jet Corporation, Customer Support Department, Teterboro Airport, Teterboro, New Jersey 07608. 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., suite 700, Washington, DC. (f) This amendment becomes effective on June 9, 1993.