Results
2013-19-12: We are adopting a new airworthiness directive (AD) for GA 8 Airvan (Pty) Ltd Models GA8 and GA8-TC320 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the fuel system integral sump tank does not meet FAA regulations. We are issuing this AD to require actions to address the unsafe condition on these products.
99-07-14: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes, and Model MD-88 airplanes, that requires a one-time inspection to detect corrosion of the lug bores and the surface of the hinge plates of the vertical-to-horizontal stabilizer; and corrective actions, if necessary. This amendment is prompted by reports of corrosion of the lug bores and the surface of the hinge plates of the vertical-to-horizontal stabilizer, apparently due to the improper brushing of cadmium on the hinge plates during manufacture. The actions specified by this AD are intended to detect and correct corrosion of the lug bores and the surface of the hinge plates of the vertical-to-horizontal stabilizer, which could result in reduced structural integrity of the airplane.
92-18-01: 92-18-01 BRITISH AEROSPACE: Amendment 39-8345. Docket No. 92-NM-45-AD. Applicability: Model ATP series airplanes; serial numbers 2001 through 2045, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent engine rundown (flame out) due to ice ingestion, accomplish the following: (a) Within 90 days after the effective date of this AD, install bonding straps, Modification 35229A, at the oil cooler temperature controller in Module 3, the throttle stepper motor controller, and the engine de-ice timers, in accordance with British Aerospace Service Bulletin ATP-24-45-35229A, dated December 20, 1991. (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, 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. (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 installation shall be done in accordance with British Aerospace Service Bulletin ATP-24-45-35229A, dated December 20, 1991, which contains the following list of effective pages: Page Number Revision Level Date 1-7, 9, 11, 13, Original December 20, 1991 15, 17, 19 8, 10, 12, 14, (These pages are not used) 16, 18 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC. 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. (e) This amendment becomes effective on October 8, 1992.
2022-11-20: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by a large crack detected on the tail gearbox (TGB) fitting during a scheduled inspection and the determination that certain TGB fittings are required to be inspected by the use of a borescope. This AD requires a one-time borescope inspection of certain part-numbered TGB fittings, and depending on the inspection results, removing the affected part from service and replacing with an airworthy part, 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.
93-11-11: 93-11-11 AC, TEXTRON LYCOMING, AND RAJAY/ROTOMASTER: Amendment 39-8584. Docket 93-ANE-16. Supersedes Priority Letter AD 93-05-21, which superseded Priority Letter AD 92-20-07. Applicability: AC, Textron Lycoming, and Rajay/Rotomaster-modified high pressure diaphragm fuel pumps, overhauled by Aero Accessories Inc. (AAI) between June 18, 1991, and November 24, 1992; AC model 41234, having AAI serial numbers (S/Ns) 91F006 through 92E050 and 92E052 through 92K008; AC model 40296, having AAI S/Ns 92B002 through 92I155; AC model 41812, having AAI S/N 91L142; Textron Lycoming model LW15473, having AAI S/Ns 91K049 through 92I151; Rajay/Rotomaster-modified model R00253-501, having AAI S/Ns 92D136 through 92J016; Rajay/Rotomaster modified model R00253-502, having AAI S/Ns 92D120 through 92H075; and Rajay/Rotomaster-modified model 103586-01, having AAI S/N 92J024; installed on but not limited to Textron Lycoming IO-320, LIO-320, IO-360, LIO-360, O-540-L3C5D, IO-540, TIO-540, and LTIO-540 piston engines; installed on but not limited to piston engine powered aircraft manufactured by Beechcraft, Bellanca, Cessna, Mooney, Piper, and Rockwell Commander (Models 112 and 114) aircraft; and AC, Textron Lycoming, and Rajay/Rotomaster-modified low pressure diaphragm fuel pumps, overhauled by AAI between November 1, 1991, and August 20, 1992; AC model numbers 40174, 40295, 40595, 41270, 41271, 41272, 41452, 41617, 75246, 75247; Textron Lycoming model numbers LW14282, LW15399, LW15472, LW16335, LW16775, LW16947; and Rajay/Rotomaster-modified models 103396-01, RJ4033, and R00253-2; having AAI S/Ns 91K073 through 91K125, all S/Ns beginning with prefixes 91L, 92A, 92B, 92C, 92D, 92E, 92F, 92G, and 92H001 through 92H146; installed on but not limited to Textron Lycoming model O-235, O-290, O-320, O-360, LO-360, LTO-360, and O-540 piston engines; installed on but not limited to piston engine powered aircraft manufactured by Beechcraft, Bellanca, Cessna, Mooney, and Piper. Compliance: Required prior to further flight, unless accomplished previously. To prevent disruption of fuel flow to the engine, which can result in a loss of engine power, accomplish the following: (a) Remove from service affected low pressure diaphragm fuel pumps and replace with a serviceable pump. (b) For the purposes of paragraph (a) of this AD, a serviceable low pressure diaphragm fuel pump is either an AC, Textron Lycoming, or Rajay/Rotomaster-modified pump that has never been overhauled by AAI, or has an "S" stamped on the flange above the inlet port of the fuel pump to indicate previous compliance with priority letter AD 92-20-07. (c) No further action is required for all affected low pressure diaphragm fuel pumps that have complied previously with priority letter AD 92-20-07. NOTES: 1. The model number is located on the edge of the mounting flange. 2. The S/N is located on the "housing backbone" between the mounting flange and the round spring housing.3. For further information, see Aero Accessories, Inc. Mandatory Service Bulletin No. 001, dated August 21, 1992. Copies of this service bulletin may be obtained from Aero Accessories, Inc., 1240 Springwood Church Road, Gibsonville, NC 27249, telephone (919) 449-5054. (d) Remove from service affected high pressure diaphragm fuel pumps and replace with a serviceable pump. (e) For the purposes of paragraph (d) of this AD, a serviceable high pressure diaphragm fuel pump is either an AC, Textron Lycoming, or Rajay/Rotomaster-modified pump that has never been overhauled by AAI, or has an "S2" stamped on the flange above the inlet port of the fuel pump to indicate previous compliance with priority letter AD 93-05-21. (f) All affected high pressure diaphragm fuel pumps must be replaced, regardless of compliance with priority letter AD 92-20-07. NOTES: 1. The model number is located on the edge of the mounting flange. 2. The serial number is located on the "housingbackbone" between the mounting flange and the round spring housing. 3. For further information, see Aero Accessories, Inc. Mandatory Service Bulletin No. 002, dated February 25, 1993. Copies of this service bulletin may be obtained from Aero Accessories, Inc., 1240 Springwood Church Road, Gibsonville, NC 27249, telephone (919) 449-5054. (g) 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, Atlanta Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Atlanta Aircraft Certification Office. (h) This amendment supersedes priority letter AD 93-05-21, issued March 17, 1993. (i) This amendment becomes effective on June 21, 1993.
2010-14-11: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from 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 describes the unsafe condition as: Certain main landing gear components have experienced premature failure during certification testing. Revision has been made to the DHC-8-400 Maintenance Requirements Manual, Airworthiness Limitation Items, to incorporate the revised safe life limits for the main landing gear lock actuator assembly, retraction actuator assembly rod end and piston, and the upper bearing in the main landing gear shock strut assembly. Failure of these components could adversely affect the structural integrity of the main landing gear. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
99-07-15: This amendment adopts a new airworthiness directive (AD) that is applicable to Bell Helicopter Textron, Inc. (BHTI)-manufactured Model HH-1K, SW204, SW204HP, SW205, SW205A-1, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters. This action requires inspecting the tail rotor yoke (yoke) assembly historical records to determine if the affected yoke assembly has been involved in any incidents that may have induced a bending load. It further requires replacement of the yoke assembly with a yoke assembly that has been x-ray diffraction inspected or has zero hours time-in-service (TIS); installing and inspecting an airworthy flapping stop or trunnion assembly to detect excessive bending loads; and revising the applicable Rotorcraft Flight Manual. This amendment is prompted by in-flight failures of yokes installed on civilian and military helicopters of similar type design, including three reported accidents. The actions specified in this AD are intended to detect static or dynamic overload on the yoke due to external bending forces, which could result in failure of the yoke, loss of the tail rotor, and subsequent loss of control of the helicopter.
84-10-51 R1: 84-10-51 R1 BOEING VERTOL COMPANY: Amendment 39-5024 as amended by Amendment 39-5352. Applies to Model 234 series helicopters, certificated in any category, equipped with forward main rotor drive shaft P/N 114D1245-7. Compliance is required as indicated, unless already accomplished. To prevent possible hazards in flight associated with cracking of the forward main rotor drive shaft, accomplish the following: (a) Within 70 hours time in service after the effective date of this amendment or upon accumulation of 1,600 total hours time in service on the rotor shaft, whichever occurs later, and thereafter at intervals not to exceed 35 hours time in service from the last inspection, inspect the rotor drive shaft in accordance with paragraph 3, "Accomplishment Instructions," Boeing Vertol Service Bulletin No. 234-63-1009, dated June 29, 1984, or Revision 1 dated May 1, 1986, or an FAA-approved equivalent. (b) Remove from service forward main rotor drive shafts havinga crack and replace with a serviceable part prior to further flight. (c) An equivalent method of compliance with this AD may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (d) Upon submission of substantiating data by an owner through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, FAA New England Region, may adjust the compliance times specified in this AD. (e) 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 Boeing Vertol Company, Boeing Center, P.O. Box 16858, Philadelphia, Pennsylvania 19142. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas. Amendment 39-5024 (50 FR 15539) became effective April 22, 1985, as to all persons except those persons to whom it was made immediately effective by telegraphic AD No. T84-10- 51, issued May 3, 1984, which contained this amendment. This Amendment 39-5352 becomes effective July 24, 1986.
2013-19-01: We are adopting a new airworthiness directive (AD) for AgustaWestland S.p.A. (AgustaWestland) Model A119 and AW119 MKII helicopters to require inspecting the pilot and co-pilot doors to ensure that the windows are properly bonded within the doors. If the windows are not properly bonded, the AD requires applying bonding to the windows, the seals, and the window frames of the pilot and co-pilot doors. This AD was prompted by the loss of a pilot-door window during a test flight. The actions of this AD are intended to ensure the windows do not detach from the doors, potentially injuring persons on the ground and damaging the helicopter's tailboom and the tail rotor blades.
2013-18-02: We are 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 cracked and corroded nuts on an outboard flap support rib. This AD requires, for certain airplanes, repetitive inspections of the cap seal for damaged sealant on nuts common to certain outboard flap support ribs, and related investigative and corrective actions if necessary. For certain other airplanes, this AD also requires repetitive inspections of the cap seal for damaged sealant on nuts common to certain outboard flap support ribs, related investigative and corrective actions if necessary, and if necessary, a detailed inspection to determine the nut type installed in the outboard flap support rib and corrective actions. This AD also provides terminating action for the repetitive inspections under certain conditions. We are issuing this AD to detect and correct cracked and corroded nuts and bolts and the installation of incorrect nuts on certain outboard flap support ribs, which could lead to additional nut and bolt damage in the joint, result in loss of an outboard flap, and adversely affect continued safe flight and landing of the airplane.