Results
2022-13-15: The FAA is adopting a new airworthiness directive (AD) for certain Williams International Co., L.L.C. (Williams) FJ44-2A, FJ44-2C, FJ44-3A, and FJ44-3A-24 model turbofan engines. This AD was prompted by a report of cracks in the high-pressure turbine (HPT) disk posts and failure of an HPT disk post, resulting in the contained fracture of an HPT disk post and blade. This AD requires removing the HPT disk, part number (P/N) 67093, from service before reaching defined cycle limits and replacing it with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
99-09-19: This amendment adopts a new airworthiness directive (AD) that is applicable to all Aerospatiale Model ATR42 and ATR72 series airplanes. This action requires revising the Airplane Flight Manual to provide the flightcrew with modified procedures and limitations for operating in severe icing conditions. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent the airplane from stalling due to prolonged exposure to severe icing conditions, which could result in reduced performance and controllability of the airplane.
2013-22-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-300 series airplanes and Model A340-200 and -300 series airplanes. This AD was prompted by reports of corrosion found on certain trimmable horizontal stabilizer actuators (THSA), affecting the ballscrew lower splines between the tie bar and the screw-jack. This AD requires repetitive detailed inspections for corrosion of certain THSAs, ballscrew integrity tests if necessary; and replacing any affected THSA with a serviceable or new and improved THSA, if necessary. We are issuing this AD to detect and correct corrosion of the THSAs, which could lead, in the case of ballscrew rupture, to the loss of transmission of THSA torque loads from the ballscrew to the tie-bar, prompting THSA blowback, and possibly resulting in loss of control of the airplane.
2013-20-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A340-211 -212, -213, -311, -312, -313, -541, and -642 airplanes. This AD requires revising the maintenance program to incorporate certain maintenance requirements and airworthiness limitations. This AD was prompted by a determination that existing maintenance requirements are not adequate to address the unsafe condition. We are issuing this AD to address the aging effects of aircraft systems. Such aging effects could change the characteristics of systems life-limited components leading to an increased potential for failure, which, in isolation or in combination with one or more other specific failures or events, could result in failure of certain life limited parts, which could reduce the structural integrity or the controllability of the airplane.
99-09-15: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models A36, B36TC, 58, 58A, C90A, B200, B300, and 1900D airplanes. This AD requires inspecting for interference or inadequate clearance between the flight control mechanism and any component located forward of the instrument panel. If interference or inadequate clearance is found, this AD requires securing all components so that they are clear of the flight control mechanism. This AD is the result of an incident where the electrical/avionics wires made contact with and restricted the control system of the affected airplanes. The actions specified by this AD are intended to prevent any components or wiring from interfering with the flight control mechanism caused by inadequate clearance, which could result in reduced or loss of aileron and/or elevator control. Comments for inclusion in the Rules Docket must be received on or before June 18, 1999.
99-09-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes, that requires modifications to the attachment installation of the forward lavatory. This amendment is prompted by a stress analysis report indicating that the forward lavatory could break free from the upper and/or lower attachments during an emergency landing. The actions specified by this AD are intended to prevent failure of the attachment installation of the forward lavatory during an emergency landing, which could result in injury to the crew and passengers.
91-13-01: 91-13-01 AIRBUS INDUSTRIE: Amendment 39-7032. Docket No. 90-NM-217-AD. Applicability: Model A310-200 series airplanes, Serial Numbers 162 through 357, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the fuselage, accomplish the following: A. Prior to the accumulation of 12,000 landings, or within 2,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 landings, perform a visual inspection of Frame 46 at the level of the frame reinforcement angle runout between Stringer 21 and Stringer 22 (left and right), in accordance with Airbus Industrie Service Bulletin A310-53-2054, Revision 2, dated May 22, 1990. If cracks are found, prior to further flight, repair in accordance with the service bulletin. B. Modification of the reinforcement angle runout by tapering the angle and reducing the thickness, in accordance with Airbus Industrie Service Bulletin A310-53-2019, Revision 2, dated May 22, 1990, constitutes terminating action for the repetitive inspections 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 documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, AvenueDidier 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 (39-7032, AD 91-13-01) becomes effective July 15, 1991.
2022-13-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports that passenger door stop screws were found with missing screw heads. This AD requires repetitive inspections of each passenger door stop screw for any missing screw heads and applicable corrective actions, 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.
99-09-08: This amendment adopts a new airworthiness directive (AD) that applies to all Avions Pierre Robin Model R2160 airplanes. This AD requires repetitively inspecting the aileron/flap common support bracket for cracks, loose rivets, or separation of the bracket from the skin, and reinforcing the bracket either immediately or at a certain time period depending on whether discrepancies are found during the inspections. Reinforcing the aileron/flap common support bracket terminates the repetitive inspection requirement. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to detect defects in the aileron/flap common support bracket (cracks, loose rivets, or separation of the bracket from the skin), which could result in reduced or loss of control of the airplane.
92-25-06: 92-25-06 BRITISH AEROSPACE: Amendment 39-8421. Docket No. 92-NM-156-AD. Applicability: All Model ATP airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent malfunctioning of the stall warning system, accomplish the following: (a) Within 6 months after the effective date of this AD, accomplish paragraphs (a)(1), (a)(2), and (a)(3) of this AD: (1) Install a new stall warning lift transducer, part number C74007-4, on the left- and right-hand wing leading edges, in accordance with British Aerospace Service Bulletin ATP-27-41-70031B, Revision 3, dated June 5, 1992. (2) Increase the wiring cable size for the stall warning heater and the stall warning lift transducer, in accordance with British Aerospace Service Bulletin ATP-24-38-10204A, Revision 2, dated August 14, 1991. (3) Move the cabin lighting from the essential to the non-essential circuit, in accordance with British AerospaceService Bulletin ATP-33-19-10238A, dated March 19, 1992. (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, ANM-113. (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 and modifications shall be done in accordance with the following British Aerospace service bulletins, which contain the specified effectivepages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page ATP-27-41-70031B, 1 3 June 5, 1992 Revision 3, June 5, 1992 2 2 May 11, 1992 3, 5, 7 Original October 7, 1991 4, 6 (These pages are not used) ATP-24-38-10204A, 1-13, 15, 17, 2 August 14, 1991 Revision 2, 19, 21, 23, 25, August 14, 1991 27, 29, 31, 33, 35, 37, 39, 41, 43, 45-46 Even Pages 14 to 44 (These pages are not used) ATP-33-19-10238A, 1-5, 7, 9, Original March 19, 1992 March 19, 1992 11, 13, 15, 17, 19, 21, 23, 25, 27 6, 8, 10, 12, (These pages are not used) 14, 16, 18, 20, 22, 24, 26 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 20041-0414. 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 January 12, 1993.
90-19-09: 90-19-09 GENERAL ELECTRIC COMPANY: Amendment 39-6715. Docket No. 90-ANE-21-AD. Applicability: General Electric Company (GE) CF6-50/-45 series turbofan engines installed in, but not limited to, Airbus A300, Boeing 747, and McDonnell Douglas DC-10-15 and DC-10-30 series aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent uncontained engine failure, emergency takeoff abort, and potentially significant aircraft damage, accomplish the following: (a) Remove from service, high pressure turbine (HPT) stage one disks, Part Numbers (P/N) 9264M57P01, 9264M57P02, 1322M88P04, 1322M88P05, 1322M88P07, 9283M31P02, 9283M55P04, and 9283M55P05, in accordance with the following schedule based upon disk cycles since new (CSN) on the effective date of this AD: (1) For disks which have been operated in CF6-50 series engines: (i) Remove within 100 cycles in service (CIS) after the effective date of this AD, disks with greater than or equal to 7,500CSN. (ii) Remove at the next engine shop visit, but no later than 1,000 CIS after the effective date of this AD or prior to accumulating 7,600 CSN, whichever occurs first, disks with greater than or equal to 6,000 CSN, but less than 7,500 CSN. (iii) Remove at the next engine shop visit after accumulating 5,500 CSN, but no later than 1,500 CIS after the effective date of this AD or prior to accumulating 7,000 CSN, whichever occurs first, disks with greater than or equal to 4,000 CSN, but less than 6,000 CSN. (iv) Remove prior to exceeding 5,500 CSN, disks with less than 4,000 CSN. (v) Thereafter, remove affected disks from service and replace with a serviceable disk prior to exceeding 5,500 CSN. NOTE: CF6-50 Series Service Bulletin 72-966, dated September 1, 1989, introduces a new HPT stage one disk, P/N 1473M65P02, which has an FAA approved time limit of 15,000 CSN. (2) For disks which have been exclusively operated in CF6-45 series engines: (i) Removewithin 100 CIS after the effective date of this AD, disks with greater than or equal to 8,000 CSN. (ii) Remove at the next engine shop visit, but no later than 1,500 CIS after the effective date of this AD or prior to accumulating 8,100 CSN, whichever occurs first, disks with greater than or equal to 6,000 CSN, but less than 8,000 CSN. (iii) Remove at the next engine shop visit after accumulating 6,000 CSN, but no later than 2,000 CIS after the effective date of this AD or prior to accumulating 7,500 CSN, whichever occurs first, disks with greater than or equal to 4,000 CSN, but less than 6,000 CSN. (iv) Remove prior to exceeding 6,000 CSN, disks with less than 4,000 CSN. (v) Thereafter, remove affected disks from service and replace with a serviceable disk prior to exceeding 6,000 CSN. (b) An engine shop visit for the purpose of this AD is defined as the induction of the engine into a shop for the performance of maintenance. (c) 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. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, Ohio 45246. These documents may be examined at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 NewEngland Executive Park, Room 311, Burlington, Massachusetts 01803. This amendment (39-6715, AD 90-19-09) becomes effective on October 1, 1990.
2013-20-51: We are adopting a new airworthiness directive (AD) for Agusta Model A109A, A109A II, A109C, A109E, A109K2, A109S, AW109SP, A119, and AW119 MKII helicopters. The emergency AD was sent previously to all known U.S. owners and operators of these helicopters. This AD requires, before further flight, inspecting certain Thomas coupling nuts on the tail rotor drive shaft line for a crack and replacing all the nuts if any nut is cracked. Also this AD requires replacing all affected Thomas coupling nuts within 10 hours time-in-service (TIS) or 30 days, whichever occurs first. This AD was prompted by two incidents of cracking on the nuts that connect the flexible disc coupling (Thomas coupling) with the splined adapter on the tail rotor drive shaft. We are issuing this AD to correct the unsafe condition on these helicopters.
2010-14-17: We are adopting a new airworthiness directive (AD) for certain Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and 747SP series airplanes. This AD requires repetitive detailed inspections of certain overwing intercostal webs, and related investigative and corrective actions if necessary. This AD results from reports of cracks in overwing intercostal webs. We are issuing this AD to detect and correct such cracking, which could grow and result in a severed intercostal. If an intercostal is severed, cracks could develop in the adjacent frame structure and skin, resulting in a rapid loss of cabin pressure.
99-09-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models C90A, B200, B200C, B200T, B200CT, 300, B300, B300C, and A200CT airplanes. This AD requires installing a filter element in the landing gear hand pump suction line. This AD is the result of reports of the potential for debris to enter the landing gear hand pump and interfere with its operation, which could prevent the nose landing gear from being extended manually. Two occurrences were reported of nose landing gear collapse after manual extension. The actions specified by this AD are intended to prevent the inability to extend the landing gear with the hand pump caused by debris entering the landing gear hand pump, which could result in passenger injury or damage to the airplane if manual operation of the landing gear failed.
87-17-07: 87-17-07 SHORT BROTHERS PLC: Amendment 39-5711. Applies to Model SD3-60 airplanes with Pratt and Whitney PT6A-65R and PT6A-65AR engines installed, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent an unsafe out-of-trim condition accomplish the following within 90 days after the effective date of this AD: A. For airplanes equipped with Pratt and Whitney PT6A-65R engines, remark the green band on the elevator trim control indicator in accordance with the Accomplishment Instructions of Shorts Service Bulletin No. SD360-27-10, Revision 1, dated May 1986. B. For airplanes equipped with Pratt and Whitney PT6A-65AR engines, remark the green band on the elevator trim control indicator and rerig the elevator tab in accordance with the Accomplishment Instructions of Shorts Service Bulletin No. SD360-27-11, Revision 1, dated March 1986. 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, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Shorts Aircraft, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective September 22, 1987.
99-09-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes and all 747-E4B (military) airplanes. This action requires repetitive inspections to detect cracking or fracture of the steel attachment fittings of the diagonal brace to the nacelle struts; and replacement of the attachment fittings with new steel fittings, if necessary. This amendment is prompted by a report indicating a fractured steel attachment fitting of a diagonal brace to the number 2 nacelle strut; such fracture has been attributed to fatigue cracking. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in failure of a nacelle strut diagonal brace load path and possible separation of the nacelle from the wing.
99-09-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires a one-time inspection to verify correct wire terminations of certain circuit breakers in the cockpit overhead switch panel; and correction of incorrect wire termination. This amendment also requires that operators submit a report of the inspection results to the FAA. This amendment is prompted by incidents in which the wiring of circuit breakers on the overhead switch panel lighting were found to be terminated improperly during production of the airplane, which bypassed the circuit breaker protection. The actions specified in this AD are intended to prevent smoke and possible fire in the overhead switch panel lighting circuitry due to an overload condition, as a result of lack of circuit breaker protection.
2022-11-13: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-700, -800, and -900ER series airplanes. This AD was prompted by reports of incorrectly installed fuselage skin fasteners. This AD requires a detailed inspection of a certain body station bulkhead, between certain stringers, for any incorrectly installed fastener common to fuselage skin, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2013-20-12: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of cracks and heat damage on pivot joint components found during main landing gear (MLG) overhaul. This AD requires, for certain airplanes, repetitive inspections of the MLG pivots, truck beam bushings, and inner cylinder bushings. For all airplanes, this AD requires a maintenance program revision, one-time inspections of the MLG truck beam, and related investigative and corrective actions (including configuration changes) if necessary; accomplishment of these actions terminates the repetitive inspections. We are issuing this AD to detect and correct heat damage and cracks in the pivot pin, truck beam lugs, and inner cylinder lugs, which could result in fracture of the pivot joint components and consequent MLG collapse.
99-09-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires relocating the support bracket and rerouting the electrical wiring in the aft storage compartment drop ceiling structure. This amendment is prompted by an incident in which a burning odor was detected, and the rear galley power repeatedly tripped off line during flight of an in-service airplane, due to the sense wiring of the galley load control unit (GLCU) chafing against the support bracket. The actions specified in this AD are intended to prevent chafing of the sense wire of the GLCU due to the location of the support bracket of the aft drop ceiling, which could result in electrical arcing, smoke, and possible fire in the aft drop ceiling area of the passenger compartments.
99-09-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires a one-time inspection of the wiring and wire bundles of the aft main avionics rack (MAR) to determine if the wires are damaged, or riding or chafing on structure, clamps, braces, standoffs, or clips, and to detect damaged or out of alignment rubber cushions inserts of the wiring clamps; and corrective actions, if necessary. This amendment is prompted by an incident in which the automatic and manual cargo door test in the cockpit was inoperative during dispatch of the airplane, due to the wiring of the MAR chafing against clamps as a result of the wire bundles being installed improperly during production of the airplane. The actions specified in this AD are intended to ensure that the wires that route from the main wire bundles to the MAR and associated brackets, clamps, braces, standoffs, and clips are installed properly. Improper installation of such wiring and structure could cause chafing of the wire/wire bundles, which could result in electrical arcing, smoke, and possible fire in the MAR.
97-11-09: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-215T series airplanes. This action requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits the positioning of the power levers below the flight idle stop during flight, and to add a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller ground beta range was used improperly during flight. The actions specified in this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
2013-19-20: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-10-10 and MD-10-10F airplanes. This AD was prompted by a report that the safe life limit on certain main landing gear (MLG) upper torque link bolts is reduced significantly due to those bolts being fabricated from bar stock with a machined head instead of from a forged blank with an upset head. This AD requires replacing certain MLG upper torque link bolts with new or serviceable parts. We are issuing this AD to prevent damage to the MLG and consequent damage to airplane structure, which could adversely affect the airplane's continued safe flight and landing.
75-21-04: 75-21-04 MORANE SAULNIER (SOCATA): Amendment 39-2382. Applies to MS880B airplanes serial numbers 1724, 1725, and 1805 through 1893 certificated in all categories. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible battery relay wiring overheat that could result in fire, install a one ampere fuse in the battery relay circuit in accordance with paragraph III ("Description") of Socata Service Bulletin No. 96 GR24.09 dated January, 1972, or an FAA-approved equivalent. This amendment becomes effective October 22, 1975.
99-08-21: This amendment adopts a new airworthiness directive (AD) that applies to any aircraft equipped with Puritan-Bennett Aero Systems Company (Puritan-Bennett) C351-2000 series passenger oxygen masks and portable oxygen masks. This AD requires inspecting the passenger and portable oxygen masks for tears around the face cushion adjacent to the inner mask housing, and replacing or repairing any torn passenger or portable oxygen mask. This AD is the result of reports received from three airplane manufacturers of defective oxygen masks. The actions specified by this AD are intended to prevent reduced oxygen consumption when passengers are required to use defective oxygen masks, which could result in passenger injury.