Results
2017-18-09: 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, CN- 235-300, and C-295 airplanes. This AD was prompted by reports of excessive play between bushings and their respective fitting housings at certain elevator fittings. This AD requires a one-time detailed inspection and repetitive eddy current inspections of the elevator hinge fitting and bracket assembly, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-18-06: We are superseding Airworthiness Directive (AD) 2012-05-03, which applied to certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2012-05-03 required modifying the fluid drain path in the leading edge area of the wing. This AD requires additional work to seal those drainage holes in the wing access panels. This AD was prompted by a design review following a ground fire \n\n((Page 41327)) \n\nincident and reports of flammable fluid leaks from the wing leading edge area onto the engine exhaust area. We are issuing this AD to address the unsafe condition on these products.
2010-24-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: As a result of a change in the low-cycle fatigue lifing methodology for the IMI 834 material, the recommended service life of certain PW305A and PW305B Impellers has been reduced, as published in the Airworthiness Limitations (AWL) section of Engine Maintenance Manual (EMM). The in-service life of impellers P/N 30B2185, 30B2486 and 30B2858-01 has been reduced from 12,000 to 7,000 cycles; and of P/N 30B4565-01 from 8,500 to 7,000 cycles. We are issuing this AD to prevent failure of the impeller, which could result in an uncontained event and possible damage to the airplane.
2002-01-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that currently requires an in-situ one-time detailed visual inspection of Draeger Type I oxygen containers, located in the passenger service units, and Draeger Type II oxygen containers, located in the utility areas, for the presence of foam pads. That action also currently requires the installation of a new foam pad, if necessary; and other actions to ensure proper operation of the masks. This amendment retains those requirements and expands the applicability of the existing AD to include additional airplanes that were inadvertently excluded from that AD. The actions specified in this AD are intended to prevent failure of the oxygen containers to deliver oxygen to the passengers in the event of a rapid decompression or cabin depressurization. This action is intended to address the identified unsafe condition.
75-26-03: 75-26-03 BELL: Amendment 39-2451. Applies to Bell Models 204B, 205A-1, and 212 helicopters certificated in all categories. Compliance required within 100 hours' time in service after the effective date of this AD unless already accomplished and, thereafter, at intervals not to exceed 300 hours' time in service from the last inspection. To deter unauthorized access to the emergency exit operating handle and to improve identification of the emergency exit handle and the main sliding door handle, accomplish the following: (a) Inspect the helicopter main passenger doors and the four emergency exits for proper and legible placards and for proper exit handle covers, both inside and outside the helicopter, in accordance with the figures in Bell Helicopter Company Service Bulletins noted in paragraph (c). (b) If proper and legible placards and proper exit handle covers are not installed, install the placards and handle covers as specified in Bell Helicopter Company Service Bulletins noted in paragraph (c). (c) The following Bell Helicopter Company service bulletins, or later approved revisions thereto, apply to the noted helicopter models. (1) Bell Helicopter Company Service Bulletin No. 204-75-2 dated September 16, 1975, for Model 204B. (2) Bell Helicopter Company Service Bulletin No. 205-75-6, Revision A, dated August 22, 1975, for Model 205A-1. (3) Bell Helicopter Company Service Bulletin No. 212-75-7, Revision A, dated August 22, 1975, for Model 212. (d) Equivalent means of compliance with this AD may be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Federal Aviation Administration, Southwest Region, Fort Worth, Texas. (e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Federal Aviation Administration, 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 that operator. (f) 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, P. O. Box 482, Fort Worth, Texas 76101. 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, 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 Office ofRegional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas. This amendment becomes effective January 19, 1976.
2017-17-19: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD- \n\n((Page 41161)) \n\n81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes. This AD was prompted by reports of cracking of various structures in the bulkhead. This AD requires an inspection for cracking in these structures, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2002-01-05: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes that are equipped with certain main landing gear (MLG) radius rods. This AD requires you to inspect the MLG radius rod cylinders for the required conductivity or hardness standard. This AD also requires you to replace any MLG radius rod cylinder that does not meet this standard. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of the MLG due to incorrectly heat treated MLG radius rod cylinders. Such failure during takeoff, landing, or taxi operations, could lead to loss of airplane control.
78-05-01: 78-05-01 SIKORSKY AIRCRAFT: Amendment 39-3146. Applies to all Model S-58T series helicopters. Compliance required prior to May 25, 1978. To preclude possible fuel starvation of the PT6T-3 and PT6T-6 engines resulting from oil-to-fuel heater contamination, relocate the impending fuel bypass sensor lines on both engine power sections in accordance with the instructions set forth in Part II, Paragraph A, of Sikorsky Service Bulletin No. 58B30-12C, dated January 12, 1976. This amendment becomes effective March 31, 1978.
2002-01-07: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters that requires changes to the electrical power distribution system. This amendment is prompted by design deficiencies in the electrical systems. The actions specified by this AD are intended to prevent failure of both generators, loss of primary electrical power, and subsequent loss of control of the helicopter.
74-12-06: 74-12-06 LOCKHEED: Amendment 39-1867 as amended by Amendment 39-2512 is further amended by Amendment 39-3361. Applies to all Model 382 series airplanes, Serial Numbers 3946 and 4101 through 4541 certificated in all categories. Compliance as indicated. a) For airplanes with 5000 or more hours total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours time in service, and thereafter at intervals not to exceed 1000 hours time in service from the last inspection. b) For airplanes with less than 5000 hours total time in service on the effective date of the AD comply with paragraph (c) before the accumulation of 5050 hours total time in service, and thereafter at intervals not to exceed 1000 hours time in service from the last inspection. c) Inspect outer wing lower forward beam cap, web, and skin for cracks in the area extending from outer wing stations 144 to 165 and 195 to 214, both left and right in accordance with Lockheed Hercules Airfreighter Inspection Procedures, SMP 515-A, Card SP-75, revised October 15, 1978, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. d) Repair of the beam cap shall be in accordance with Lockheed Service Bulletin A382-169, Revision 7, and repair of the beam web in accordance with SMP 583, Lockheed Hercules Structural Repair Manual, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. e) Before the accumulation of 30,000 flight hours, preventive modification shall be installed in accordance with Lockheed Service Bulletin 382-152, Revision 2, and Alert Service Bulletin A382-169, Revision 7, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. f) Recurring inspections shall be performed in accordance with the following: 1) Recurring inspections for unmodified airplanes will be in accordance with paragraphs (a), (b), and (c) of this amendment. 2) Recurring inspections for airplanes with preventive modifications shall be in accordance with Lockheed Airfreighter Inspection Procedures, SMP 515-A, Card SP-75, revised October 15, 1978, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, and a detailed visual inspection of the front beam lower cap and adjacent structure including modifications across the entire length of the outer wing dry bays from outer wing stations 144 to 214 at each "C" check. 3) In addition to the recurring inspections of paragraphs (f)(1) and (f)(2), recurring inspections for airplanes with repairs shall be a detailed visual inspection of the front beam lower cap and adjacent structure, including repairs, across the entire length of the outer wing dry bays from outer wing stations 144 to 214 at each "C" check. g) Upon request of the operator, an FAA Maintenance Inspector, subjectto prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, may adjust the repetitive inspection intervals specified in this amendment to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. h) Airplanes may be flown to a base for performance of the inspections required by this amendment in accordance with Federal Aviation Regulations 21.197 and 21.199. i) Report inspection findings to Chief, Engineering and Manufacturing Branch, FAA, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. Lockheed-Georgia Alert Service Bulletin A382-169, dated May 30, 1974, covers this same subject. Amendment 39-1867 became effective May 30, 1974. Amendment 39-2512 became effective February 13, 1976. This amendment 39-3361 becomes effective December 8, 1978.
2023-03-03: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by a report of a damaged tail rotor duplex bearing (TRDB). This AD requires repetitively inspecting certain TRDBs and depending on the results, replacing the TRDB or tail rotor actuator (TRA), or as an option, replacing the sliding control assembly. This AD also requires replacing an affected TRDB with a serviceable TRDB at a specified threshold and prohibits the installation of certain TRDBs or sliding control assemblies on any helicopter, 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.
2017-17-13: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by reports of low clearance in the aft equipment bay between auxiliary power unit (APU) generator power cables and a hydraulic line, which can cause damage to wire insulation. This AD requires an inspection of the APU generator power cables and the adjacent hydraulic line for damage, and repair, if necessary; and modification of the APU generator power cable installation. We are issuing this AD to address the unsafe condition on these products.
2002-01-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Israel Aircraft Industries, Ltd., Model Galaxy airplanes. This action requires disabling the baggage compartment heating blanket system. This action is necessary to prevent a short circuit between the baggage compartment heating blankets and the electrical connectors, which could result in fire and smoke in the baggage compartment. This action is intended to address the identified unsafe condition.
2004-08-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a magnetic inspection of the sliding members of the main landing gear (MLG) for cracking, and replacement of the sliding members with serviceable parts, if necessary. This action is necessary to prevent fatigue cracking of the sliding member, which could result in possible separation of the MLG from the airplane and consequent reduced controllability of the airplane upon landing and possible injury to passengers. This action is intended to address the identified unsafe condition.
2017-16-12: We are superseding Airworthiness Directive (AD) 2013-19-09 and AD 2014-25-51, which applied to all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013-19-09 required replacing Angle of Attack (AOA) sensor conic plates with AOA sensor flat plates. AD 2014-25-51 required revising the airplane flight manual (AFM) to advise the flightcrew of emergency procedures for abnormal Alpha Protection (Alpha Prot). This new AD requires replacing certain AOA sensors; and doing a detailed inspection and a functional heating test for discrepancies on certain AOA sensors, and replacing the affected AOA sensors. This AD was prompted by a report indicating that a Model A321 airplane encountered a blockage of two AOA probes during climb, leading to activation of the Alpha Prot while the Mach number increased. We are issuing this AD to address the unsafe condition on these products.
2025-11-03: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx- 1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx- 1B76A/P2, and GEnx-2B67/P engines. This AD was prompted by a manufacturer's investigation that revealed certain high-pressure turbine (HPT) stage 1 and HPT stage 2 disks were manufactured from powder metal material suspected to contain iron inclusion. This AD requires replacement of affected HPT stage 1 and HPT stage 2 disks with parts eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2002-01-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, that requires initial and repetitive inspections of the elevator tab assembly to find any damage or discrepancy; and corrective actions, if necessary. The actions specified by this AD are intended to prevent excessive in-flight vibrations of the elevator tab, which could lead to loss of the elevator tab and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
49-34-01: 49-34-01 CONVAIR: Applies to All Model 240 Airplanes Incorporating Activated Reversing Propellers. Compliance required as soon as possible but in any event not later than August 29, 1949. Two cases have been experienced in which inadvertent reversal of the propellers occurred in flight during approach for landing. To minimize the possibility of inadvertent reversal, an item shall be added to the "before landing" cockpit checklist requiring that the reverse throttle stop override handles be checked to assure that they are in the retracted "in" position.
2025-11-01: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. This AD was prompted by a report of cracking found in new locations at a certain body station (STA) during frame segment replacement repairs, including in the web at the K-hole between certain stringers, in the outer chord above the lower hinge intercostal, and in the inner chord and web between certain stringers. This AD requires an inspection or records check for the presence of approved or local repairs, repetitive eddy current inspections for cracking, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2023-02-17: The FAA is adopting a new airworthiness directive (AD) for all Textron Aviation Inc. (type certificate previously held by Cessna Aircraft Company) (Textron) Model 210N, 210R, P210N, P210R, T210N, T210R, 177, 177A, 177B, 177RG, and F177RG airplanes. This AD was prompted by the in-flight break-up of a Model T210M airplane in Australia, due to fatigue cracking that initiated at a corrosion pit, and subsequent corrosion reports on other Model 210- and 177-series airplanes. This AD requires visual and eddy current inspections of the carry-thru spar lower cap for corrosion, cracking, and damage; corrective action if necessary; application of a protective coating and corrosion inhibiting compound (CIC); and reporting the inspection results to the FAA. The FAA is issuing this AD to address the unsafe condition on these products.
2017-17-10: We are superseding Airworthiness Directive (AD) 2015-23-12, which applied to all ATR-GIE Avions de Transport R gional Model ATR42 and ATR72 airplanes. AD 2015-23-12 required identifying the serial number and part number of the main landing gear (MLG) rear hinge pins, and replacing pins or the MLG if necessary. This AD retains the requirements of AD 2015-23-12, requires replacing certain additional MLG hinge pins, and reduces certain compliance times. This AD was prompted by a new occurrence of a cracked MLG rear hinge pin. We are issuing this AD to address the unsafe condition on these products.
2001-26-25: This amendment adopts a new airworthiness directive (AD) that applies to all Grob-Werke Gmbh & Co KG (Grob) Models G102 Club Astir III, G102 Club Astir IIIb, and G102 Standard Astir III sailplanes. This AD requires you to apply a red mark and install a placard on the airspeed indicator to restrict the Vne airspeed. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent elevator flutter, which could cause structural damage. Such damage could result in loss of control of the sailplane.
75-13-06: 75-13-06 BRITISH AIRCRAFT CORPORATION: Amendment 39-2236. Applies to Viscount Model 700 Series airplanes certificated in all categories. Compliance required as indicated. To prevent the possible in-flight fatigue failure of the horizontal stabilizer, accomplish the following: (a) For horizontal stabilizer rear spars with more than 25,000 landings on the effective date of this AD, comply with paragraphs (c) and (d) of this AD within the next 10 landings or 50 hours time in service, whichever occurs first, unless already accomplished. (b) For all horizontal stabilizer rear spars not covered in paragraph (a) of this AD, comply with paragraphs (c) and (d) of this AD before the accumulation of 20,000 total landings or the lesser of 100 landings or 300 hours time in service after the effective date of this AD, whichever occurs later, unless already accomplished. (c) Inspect the rear spar of the left and right horizontal stabilizer for cracks and corrosion, and repairor replace as necessary, in accordance with CAA-approved British Aircraft Corporation (BAC) Alert Preliminary Technical Leaflet (PTL) No. 298, Issue 1, dated August 16, 1974, or an FAA-approved equivalent. (d) Accomplish BAC Modification Leaflet D.3268 or D.3269, or an FAA-approved equivalent of either, as provided in BAC PTL NO. 298, Issue 1. (e) Spar booms on which the corrosion damage exceeds the limits set forth in BAC PTL No. 298, Issue 1, may not be returned to service unless the repair of such damage is approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region of the FAA. (f) The service life limitation of the rear spar assembly of a spar boom modified in accordance with BAC Modification Leaflet D.3268, or an FAA-approved equivalent, is 2000 landings after modification or 30,000 total pre-modification and post-modification landings, whichever occurs first. (g) The service life limitation of the rear spar assembly of a spar boom modified in accordance with BAC Modification Leaflet D.3269, or an FAA-approved equivalent, is 30,000 total pre-modification and post- modification landings. (h) For the purpose of this AD, the number of landings may be determined by actual count, or, subject to the acceptance of the assigned FAA maintenance inspector, by dividing the horizontal stabilizer spar total time in service by an average flight time determined from the airplane log book to be representative for that airplane. Operators who have not kept records of landings or time in service for individual horizontal stabilizers must substitute total number of airplane landings or time in service in place thereof. This amendment becomes effective June 6, 1975.
2002-01-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Turbomeca S.A. Arrius 1A turboshaft engines. This action requires replacement of the 10 main fuel injectors in Arrius 1A engines with new or overhauled injectors. This amendment is prompted by routine inspections conducted in the repair workshop demonstrating that some main fuel injectors were partially or totally blocked. The actions specified in this AD are intended to prevent blocked main fuel injectors that could lead to engine flameout during engine deceleration or that could prevent the engine from obtaining the 2 1/2 minute one engine inoperative (OEI) power.
2025-11-05: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by reports of multiple supplier notices of escapement (NOEs) indicating that seat track splice fittings were possibly manufactured with an incorrect titanium alloy material. This AD requires an inspection of seat track splice fittings to determine the material and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.