Results
2017-20-03: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a review showing that inadequate clearance may exist between certain electrical wiring and nearby structures. This AD requires an inspection of certain electrical wiring bundles and feeders, modifications, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2002-01-22: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3 series airplanes, that requires a one-time inspection of the installation of the bearing housings of the elevator torque shaft assembly, and corrective action if necessary. This action is necessary to prevent failure of the elevator torque shaft, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
78-13-03: 78-13-03 BURKHART GROB: Amendment 39-3244. Applies to Model G102 Astir CS gliders, Serial numbers, 1001 to 1234 and 1300 to 1315, certificated in all categories. Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To reduce the possibility of elevator control failure due to possible loss of an elevator control pivot bolt, modify the elevator control assembly by installing a mechanical stop to the elevator control pivot (bearing) bolt, part no. 4205.06, in accordance with Burkhart Grob Technical Information TM102-4 dated August 16, 1976, or an equivalent, approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. This amendment becomes effective July 5, 1978.
2017-19-05: We are adopting a new airworthiness directive (AD) for certain Siemens S.A.S. smoke detectors installed on various transport category airplanes. This AD requires inspection and replacement of the affected smoke detectors. This AD was prompted by a report that the affected smoke detectors failed an acceptance test. We are issuing this AD to correct the unsafe condition on these products.
2017-20-05: We are superseding Airworthiness Directive (AD) 2011-01-15, which applied to certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. AD 2011-01-15 required repetitive inspections for cracking of the fuselage skin of the crown skin panel along the chem-milled step at certain stringers, and repair if necessary. This AD adds repetitive inspections for cracking in additional areas, and repair if necessary; removes airplanes from the applicability; adds an optional skin panel replacement, which terminates all inspections; adds an optional preventive modification, which terminates certain inspections; and reduces the compliance time for certain inspections. This AD was prompted by reports of the initiation of new fatigue cracking in the fuselage skin of the crown skin panel along locally thinned channels adjacent to the chem-milled steps. We are issuing this AD to address the unsafe condition on these products.
2017-20-08: We are superseding Airworthiness Directive (AD) 2009-17-01, which applied to certain Gulfstream Model G-IV, GIV-X, GV-SP airplanes and Model GV airplanes. AD 2009-17-01 required an inspection for sealant applied to the exterior of the auxiliary power unit (APU) enclosure (firewall), and a revision of the airplane flight manual (AFM), as applicable. This AD requires revising the AFM and revising the applicability to include additional airplanes. This AD was prompted by a report indicating that the type design sealant applied to the APU enclosure failed certain tests. We are issuing this AD to address the unsafe condition on these products.
2002-01-28: This amendment adopts a new airworthiness directive (AD) that is applicable to Dowty Aerospace Propellers Type R334/4-82-F/13 with propeller hub assemblies, part number (P/N) 660709201. This action requires a one-time ultrasonic inspection of the propeller hub for cracks. This amendment is prompted by a report of an in-flight loss of a propeller. The actions specified in this AD are intended to prevent propeller hub failure due to cracks in the hub, which could result in loss of control of the airplane.
78-17-01: 78-17-01 MOONEY AIRCRAFT CORPORATION: Amendment 39-3279. Applies to Model M20C, Serial Number 20-1186 through 20-1258, M20F, Serial Number 22-1306 through 22-1486, and M20J, Serial Number 24-0001 through 24-0454 airplanes, with Pacific Communications, Inc., Aircraft Products Division, Model Alert 50, Part No. 01070-5 emergency locator transmitter system installed. Compliance is required as indicated. To assure that the emergency locator transmitter will radiate a proper signal when activated during emergency conditions, accomplish the following: 1. Rework the aircraft skin in accordance with Mooney Aircraft Corporation Service Bulletin M20-213 dated July 21, 1978, within ten hours operating time but no later than 30 days from the effective date of this AD. 2. Upon completion of the Mooney Service Bulletin No. 20-213 instructions, measure the resistance between the antenna and the aircraft skin using an appropriate meter and assure that a reading of 9,000 to 13,000 ohms isobtained. Determine that the ELT transmits properly by testing it in accordance with FAA Advisory Circular No's. 91-44 or 20-81. 3. 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 Mooney Aircraft Corporation, P. O. Box 72, Kerrville, Texas 78028. These documents may also be examined at Southwest Regional Office, Regional Counsel, Building 3B, Room 100, 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 Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective August 21, 1978.
2017-19-25: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes; and Model C-295 airplanes. This AD was prompted by reports of leakage of motorized cross-feed fuel valves. This AD requires repetitive inspections and operational checks of the affected fuel valves, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-19-23: We are superseding Airworthiness Directive (AD) 2015-15-10, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2015-15-10 required repetitive inspections of the trimmable horizontal stabilizer actuator (THSA) for damage, and replacement if necessary; and replacement of the THSA after reaching a certain life limit. This AD requires repetitive detailed inspections of certain THSAs, and related investigative and corrective actions if necessary. This AD was prompted by the establishment of an additional life limit for the THSA, based on flight cycles. In addition, the THSA manufacturer has issued service information which, when accomplished, increases the life limit of the THSA. We are issuing this AD to address the unsafe condition on these products.
2004-08-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes; Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes. This AD requires various modifications and repetitive inspections of the throttle control system, and follow-on actions if necessary. This action is necessary to prevent hard points in the throttle control system that could lead to jamming of the throttle control cable. Such jamming could result in an asymmetric thrust condition and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
98-06-32: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332C, L, and L1 helicopters. This action requires greasing and inspecting main rotor blade horn eye bolts (eye bolts), and replacing certain eye bolt bearings (bearings) with airworthy bearings. This amendment is prompted by one report of abnormally high amplitude inflight vibrations due to failure of a bearing. The actions specified in this AD are intended to prevent failure of a bearing, due to premature wear caused by an improper axial pre-load, which could result in loss of main rotor blade pitch control and subsequent loss of control of the helicopter.
2023-03-11: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report of smoke in the flightdeck and loss of the right- hand (RH) primary display unit (PDU) and the secondary flight display (SFD). This AD requires inspecting the two electrical power feeders for damage (deterioration), measuring the clearance between the two electrical power feeders and the forward lavatory bulkhead, 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.
76-21-05: 76-21-05 BELL: Amendment 39-2749. Applies to Bell Model 47K helicopters certificated in all categories. Compliance required as indicated. A report has been received of fatigue cracking of the tubular spar of the synchronized elevator at the rollpin hole. To preclude possible separation of the elevator from the helicopter, accomplish the following: (a) Within 25 hours' time in service after the effective date of this AD: (1) Remove the elevators from the tail boom in accordance with the Bell Maintenance Manual. (2) Clean the area around the Rollpin hole and remove any zinc chromate putty from any plugged hole in the tubular spar at B.L. 7.0 for both right and left elevators. (3) Inspect for cracks in the tubular spar of both elevators at the Rollpin hole at B.L. 7.0 using a 5-power or higher magnifying glass. (4) Inspect the inboard rib for cracks using a 5-power or higher magnifying glass. (b) If cracks are found in the tubular spar, modify the elevator with Bell Helicopter Kit No. 47-3746-1 or 47-3746-2, "Improved Design Synchronized Elevator," or FAA engineering approved equivalent prior to further flight. (c) If no cracks are found in the tubular spar, install clevis pin in accordance with subparagraphs (1) through (4) below or in accordance with item 2 of Bell Helicopter Company Service Bulletin No. 135SB dated July 27, 1961, or later approved revision, and reinspect in accordance with subparagraph (5). (1) Position coupling assembly P/N 47-267-483-1 on elevators and line drill through Rollpin holes with a "D" (0.2460-inch diameter) drill. Remove sharp edges from holes. Install MS 20392-3-49 clevis pins, AN 960-4162 washers, and AN 381-3-6 cotter pins. A finger tight slip fit of the clevis pins is desired, approximately 0.0005 inch loose. (2) Reinstall the elevator on the helicopter, shim as required to prevent preload or end play at bearings. (3) Check clearance between skin and end of clevis pins. Trim skin, if necessary, to obtain clearance. (4) Rerig elevator in accordance with the Bell Maintenance Manual. (5) Reinspect in accordance with (a)(1) through (a)(3) within each succeeding 50 hours' time in service until Bell Helicopter Kit No. 47-3746-1 or 47-3746-2, "Improved Design Synchronized Elevator," or FAA approved equivalent is installed. (d) If cracks are found in the inboard rib, repair the elevator as specified below, or modify with Bell Helicopter Kit No. 47-3746-1 or 47-3746-2, or FAA engineering approved equivalent prior to further flight. (1) Remove the inboard rib by drilling out the rivets and remove the Bell P/N 47-267-404-7 shoulder from the rib by drilling out the rivets. (2) Add a doubler of 0.032 thickness, or a new rib of 0.032 thickness, material aluminum alloy 2024-0, or a Bell rib P/N 47-267-453-7 (one required per elevator). (3) Rivet Bell P/N 47-267-404-1 shoulder to the old rib and new doubler or to the newrib. Use the rivet pattern in the shoulder with AN 470-AD3 or -4 rivets. (4) Install the rib assembly, using the rivet pattern in the elevator skin with MS 20600 AD4 or -5 rivets. (e) If no cracks are found in the inboard rib: (1) Reinstall the elevator on the helicopter in accordance with Bell Maintenance Manual. (2) Reinspect rib for cracks in accordance with (a)(4) within each succeeding 50 hours' time in service until Bell Helicopter Kit No. 47-3746-1 or 47-3746-2, "Improved Design Synchronized Elevator," or FAA engineering approved equivalent is installed. (f) Upon request of the operator, an FAA maintenance inspector subject to prior approval of the Chief, Engineering and Manufacturing Branch, Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. 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 Service Manager, Bell Helicopter Company, Box 482, Fort Worth, Texas 76101. These documents may also be examined at 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 Office of Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas. This amendment becomes effective November 26, 1976.
2023-03-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by a report that certain fasteners attaching the fuselage skin to a certain stringer may be missing. This AD requires inspecting for missing fasteners and damage, including cracking, of the affected area, and repair or installation of fasteners if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2002-01-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This action requires repetitive inspections of the lubrication passage and link assembly joint in the inboard and outboard flaps of the trailing edge for discrepancies, and corrective action, if necessary. This action is necessary to prevent failure of the bearings in the link assembly joint, which could result in separation of the outboard flap and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
46-46-03: 46-46-03 CESSNA: (Was Mandatory Note 10 of AD-722-5.) Applies to T-50 Aircraft. Inspection required not later than January 1, 1947. Inspect the aileron and flap hinge brackets for evidence of cracking where the bearing is staked into the hinge bracket. If cracks are found, the hinge bracket should be replaced.
2023-04-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a determination that longitudinal sealing tape in the forward and aft cargo compartments had migrated from its original position, which could affect the fire extinguishing system efficiency in the cargo compartments. This AD requires repetitive detailed inspection of the affected parts, and, depending on findings, accomplishment of applicable corrective action, 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.
2004-07-25: The FAA is superseding an existing airworthiness directive (AD) for Hartzell Propeller Inc. Model HC-B5MP-3C/M10876K propellers, installed on Short Brothers Model SD3-60 airplanes. That AD currently requires initial and repetitive removal, disassembly, inspection, and rework if necessary of Hartzell Propeller Inc. Model HC-B5MP-3C/M10876K propellers until blades are replaced with new design blades, no later than March 31, 1988. This ad requires installation of new design blades before further flight, on Hartzell Propeller Inc. Models HC-B5MP-3C/ M10876K propellers. This AD supersedure is prompted by a review of all currently effective ADs, which found that AD 87-16-02 was not published in the Federal Register to make it effective to all operators, as opposed to just the operators who received actual notice of the original AD. We are issuing this AD to prevent propeller blade separation near the hub, which could result in engine separation from the airplane.
2002-01-27: This amendment supersedes an existing airworthiness directive (AD), that is applicable to General Electric Company (GE) GE90-76B, -77B, -85B, -90B, and -92B model turbofan engines. That AD currently requires initial and repetitive eddy current inspections (ECI) for cracks in the high pressure compressor (HPC) stage 2-6 spool, and, if necessary, replacement with serviceable parts. That amendment was prompted by reports of cracks in the stage 3-4 and stage 4-5 interstage seal teeth and spacer arms. This amendment deletes reference to the GE90-92B engine model, deletes reference to HPC spool part number (P/N) 350-005-769-0 and directs the removal from service of affected part number spools by either engine cycles or calendar date, whichever occurs first. This amendment is prompted by the introduction of a new design HPC stage 2-6 spool and four additional HPC stage 2-6 spool P/N's that are terminating action for the repetitive inspection requirements for certain P/N spools. The actions specified by this AD are intended to prevent failure of the HPC stage 2-6 spool due to cracks, which could result in an uncontained engine failure and damage to the airplane.
90-22-08: 90-22-08 AIRBUS INDUSTRIE: Amendment 39-6781. Docket No. 90-NM-199-AD. Applicability: All Model A320-231 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks in the rear engine mount barrel nuts, and to prevent reduced structural integrity of the rear engine support structure, accomplish the following: A. Within 25 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 700 hours time-in-service, perform a visual inspection of the rear engine mount barrel nuts, in accordance with Airbus Industrie Operator Information Telex (AOT) ST/999.0085/90, dated April 3, 1990. If a nut is cracked, replace with a new nut, prior to further flight, in accordance with the Operator Information Telex. Following replacement of the nut, continue the visual inspections at intervals not to exceed 700 hours time-in-service in accordance with the AOT. NOTE: This Airbus Industrie telex references International Aero Engines (IAE) Service Bulletin No. V2500-NAC-71-0071, Revision 3, dated March 30, 1990, for additional information. B. On each day that flying occurs, perform a torque check of the rear engine mount bolts in accordance with Airbus Industrie Operator Information Telex (AOT) ST/999.0087/90, dated April 4, 1990. Any bolt which does not meet the appropriate torque limits specified in the AOT must be retorqued prior to further flight. NOTE: This Airbus Industrie telex references IAE Service Bulletin No. V2500-NAC-71- 0071, Revision 3, dated March 30, 1990, for additional information. 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 the Manager, 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 information from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6781, AD 90-22-08) becomes effective on November 5, 1990.
99-21-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310-300 and A300-600R series airplanes, that requires installation of a new cover assembly, associated new drain and vent pipework, and a new electrical harness on the trimmable horizontal stabilizer for the fuel tank water scavenge motive pump. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent fuel leakage from the seal of the water scavenge pumps, which, if not corrected, could result in leakage of fuel into fuselage areas not designed for fuel, and consequent potential for fuel to be in contact with a fuel ignition source.
2023-03-06: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by the determination that radio altimeters cannot be relied upon to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band), and a recent determination that this interference can result in unavailable or misleading radio altimeter information, adversely affecting the performance of the automatic flight control system (AFCS) and resulting in increased flightcrew workload during takeoff, approach, and landing below 400 feet above ground level (AGL). This AD requires revising the existing airplane flight manual (AFM) with new limitations to mitigate identified hazards due to 5G C-Band interference as identified by Notices to Air Missions (NOTAMs). The FAA is issuing this AD to address the unsafe condition on these products.
T83-25-51 R1: T83-25-51 R1 BOEING VERTOL COMPANY: Amendment 39-4828 and Telegram issued June 11, 1984. Applies to Boeing Vertol Model 234 series helicopters certificated in all categories. Compliance is required as indicated. To prevent possible hazards in flight associated with cracking of the main rotor head horizontal hinge pins, accomplish the following: (a) Within the next 25 hours time in service from the effective date of this AD or before the accumulation of 1,600 hours time in service, whichever comes later, retire main rotor head horizontal hinge pins P/N's 114R2196-2, 114R2197-1, and 114R2197-5 and replace with serviceable parts. (b) 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, Valley Stream, New York 11581. (c) In accordance with FAR 21.197 flight is permitted to a base where the requirements of this AD may be accomplished. (d) Within the next 50 hours time in service from the effective date of this AD revision or before the accumulation of 300 hours time in service, whichever comes later, retire main rotor head horizontal hinge pins that have serial numbers other than A-356 thru A-367, A- 380 thru A-403, A-440 and subsequent, and YZ-135 and subsequent, and replace with serviceable parts. Amendment 39-4828 became effective March 26, 1984, as to all persons except those persons to whom it was made immediately effective by telegraphic AD No. T83-25-51 issued December 9, 1983, which contained the amendment. This telegraphic revision becomes effective upon receipt.
68-11-02: 68-11-02 LOCKHEED: Amdt. 39-701. Applies to Lockheed Model 188A and 188C Series airplanes. Compliance required as indicated. To detect fatigue cracks in the upper planks at the fillet attachment holes, accomplish the following: (a) Within the next 400 hours' time in service after the effective date of this AD, unless already accomplished within the last 1000 hours' time in service, and thereafter at intervals not to exceed 1400 hours' time in service from the last inspection, inspect visually the upper wing planks in the vicinity of the fillet attachment holes on both sides of the four nacelles in accordance with Paragraphs (2)(B) of Lockheed Service Bulletin No. 88/SB-649A dated June 14, 1968, (or later FAA approved revision), or by a method approved by the Chief, Aircraft Engineering Division, FAA Western Region, and if cracks are found, repair before further flight in accordance with Section (2)(C) or (2)(D) of Lockheed Service Bulletin No. 88/SB-649A dated June 14,1968, (or later FAA approved revision,) or by a method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) The repetitive inspection required by (a) may be discontinued in the respective affected areas upon completion of the repairs described in Section 2.C. of Lockheed Service Bulletin No. 88/SB-649A, dated June 14, 1968, (or later FAA approved revision), or upon completion of the appropriate preventive repair installation described in Section I.C.I. or preventive reinforcement of Section I.C.II. of Lockheed Service Bulletin No. 88/SB-665, dated November 11, 1968, (or later FAA approved revision). (c) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. This Directive effective July 5, 1968. Revised August 20, 1968. Revised October 26, 1968. Revised January 4, 1969.