Results
2021-13-17: The FAA is superseding Airworthiness Directive (AD) 2017-17- 01, which applied to certain Airbus Helicopters Model AS332L2 and EC225LP helicopters. AD 2017-17-01 required repetitive inspections of the main rotor blade (MRB) attachment pins. This AD continues to require the repetitive inspections of the MRB attachment pins, and also requires repetitive measurement of the attachment pin chamfer at certain intervals after corrosion removal, as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is incorporated by reference. This AD was prompted by the FAA's determination that it is necessary to measure the attachment pin chamfer after corrosion removal, that replacement of an attachment pin after four corrosion removals is no longer necessary, and that all Airbus Helicopters Model AS332L2 and EC225LP helicopters are affected by the unsafe condition. The FAA is issuing this AD to address the unsafe condition on these products.
2000-11-29: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050, 100, 200, 300, 400, 500, 600, and 700 series airplanes, and Model F28 Mark 0070, 0100, 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time functional test to verify correct installation of the shoulder harnesses of the pilot's and copilot's seats and, if necessary, replacement of the shoulder harness assembly with a new or serviceable shoulder harness assembly. 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 failure of the shoulder harness, which could result in injury to the flight crew during extremely turbulent flight conditions or during emergency landing or stopping conditions.
2018-21-08: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, -500 series airplanes. This AD was prompted by the results of a fleet survey that revealed cracking in the bulkhead frame web at a certain body station. This AD requires repetitive inspections of the bulkhead frame web at a certain station, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
2018-20-15: We are superseding Airworthiness Directive (AD) 2015-09-07, which applied to all The Boeing Company Model 787 airplanes. AD 2015- 09-07 required a repetitive maintenance task for electrical power deactivation. This AD requires installing new software for the generator control unit (GCU). This AD also removes certain airplanes from the applicability. This AD was prompted by the determination that a Model 787 airplane that has been powered continuously for 248 days can lose all alternating current (AC) electrical power due to the GCUs simultaneously going into failsafe mode. We are issuing this AD to address the unsafe condition on these products.
2000-12-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain CFM International (CFMI) CFM56 series turbofan engines, that requires revisions to the Airworthiness Limitations Section of applicable Engine Shop Manuals (ESMs). These revisions incorporate required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment requires the addition of CFM56 engine models to the applicability section of the AD, and the introduction of additional inspections. This amendment is prompted by additional focused inspection procedures that have been developed by the manufacturer. The actions specified by this AD are intended to prevent critical life- limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
98-26-10: This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Mystere-Falcon 20 series airplanes, Fan Jet Falcon series airplanes, and Fan Jet Falcon Series D, E, and F series airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flight crew with certain emergency procedures associated with an engine fire, or a rear compartment fire or overheat conditions. 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 fire from spreading throughout the airplane due to an engine fire, or with a rear compartment fire or overheat conditions.
89-18-07 R1: 89-18-07 R1 RAYTHEON AIRCRAFT COMPANY (Formerly Beech, Raytheon Corporate Jets, British Aerospace, Hawker Siddeley, et al.): Amendment 39-10878. Docket 97-NM-305-AD. Revises AD 89-18-07, Amendment 39-6297. Applicability: Model BAe.125, DH.125, BH.125, and HS.125 series airplanes; up to and including series 700; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. NOTE 2: Raytheon (Beech) Model DH.125-400B, BH.125-400B and -600B, HS.125-600B and -700B, and BAe 125-800B series airplanes are similar in design to the airplanes that are subject to the requirements of this AD, and, therefore, also may be subject to the unsafe condition addressed by this AD. However, as of the effective date of this AD, those models are not type certificated for operation in the United States. Airworthiness authorities of countries in which those models are approved for operation should consider adopting corrective action, applicable to these models, that is similar to the corrective action required by this AD. Compliance: Required as indicated, unless accomplished previously. To prevent control surface interference and jamming of flight controls, accomplish the following: (a) Within 3 years since the date of airplane manufacture, or within 60 days afterSeptember 21, 1989 (the effective date of AD 89-18-07, amendment 39-6297), whichever occurs later, accomplish the following: (1) Inspect the elevator mass balance weight side plate assembly and balance weight spigot for corrosion, in accordance with British Aerospace Service Bulletin 27-142, Revision 2, dated June 10, 1987, or Revision 3, dated November 13, 1989. Any corrosion detected during this inspection must be repaired prior to further flight, in accordance with the service bulletin. (2) Apply corrosion protection treatment and install Monel rivets, part number MS9318- 052, or British Standard Specification SP88-304 rivets, in the elevator balance weight structure, in accordance with British Aerospace Service Bulletin 27-142, Revision 2, dated June 10, 1987, or Revision 3, dated November 13, 1989. (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 3: 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 sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The actions shall be done in accordance with British Aerospace Service Bulletin 27-142, Revision 2, dated June 10, 1987, or British Aerospace Service Bulletin 27-142, Revision 3, dated November 13, 1989, which contains the following list of effective pages: Page Number Revision Level Shown on Page DateShown on Page 1 3 November 13, 1989 2 Original May 15, 1987 3 2 June 10, 1987 4 1 May 21, 1987 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 Raytheon Aircraft Company, Manager Service Engineering, Hawker Customer Support Department, P.O. Box 85, Wichita, Kansas 67201-0085. 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 December 18, 1998.
2021-14-14: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AW119 MKII helicopters. This AD was prompted by reports of detected smoke and burning smell during flight, caused by chafing of electrical wiring. This AD requires an inspection of the instrument panel electrical wiring, corrective actions if necessary, a modification of the wiring installation, and, for certain helicopters, an additional modification of the wiring installation, 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.
2021-12-14: The FAA is superseding Airworthiness Directive (AD) 2020-08- 11, which applied to all Yabora Industria Aeronautica Model ERJ 190- \n\n((Page 36208)) \n\n300 and ERJ 190-400 airplanes. AD 2020-08-11 required revising the existing airplane flight manual (AFM) procedures associated with messages of smoke in the electronic bays presented on the respective engine indication and crew alerting system (EICAS). This AD continues to require revising the existing AFM procedures, and adds requirements for a terminating modification of the electrical wiring of the mid- electronic bay and backup smoke detectors; as specified in an Agencia Nacional de Aviacao Civil (ANAC) AD, which is incorporated by reference. This AD was prompted by a failure propagation test, which revealed that under certain conditions, the smoke detection system of the electrical bays erroneously indicated the presence of smoke via the respective EICAS messages. The FAA is issuing this AD to address the unsafe conditionon these products.
2018-20-18: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-400 series airplanes. This AD was prompted by a report of uncommanded deployment of the ground spoilers when the power levers were advanced for takeoff, which was caused by faulty switches in the power lever module. This AD requires revising the maintenance or inspection program, as applicable. We are issuing this AD to address the unsafe condition on these products.
2006-24-06: 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 ripped pressure lines between Airbox-Carburetor-Differential fuel pressure sensor. We are issuing this AD to require actions that are intended to address the unsafe condition described in the MCAI.
2018-21-01: We are superseding Airworthiness Directive (AD) 2017-20-06 for certain Honeywell International Inc. (Honeywell) AS907-1-1A turbofan engines. AD 2017-20-06 required a one-time inspection of the second stage low-pressure turbine (LPT2) blades and, if the blades fail the inspection, the replacement of the blades with a part eligible for installation. This AD continues to require a one-time inspection of the LPT2 blades and, if the blades fail the inspection, the replacement of the blades with a part eligible for installation. This AD was prompted by the need to clarify the Applicability and Compliance sections of AD 2017-20-06. We are issuing this AD to address the unsafe condition on these products.
2000-11-23: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes, that requires an inspection to detect damage of the electrical bonding leads in specified locations of the fuel tanks, and replacement of any damaged electrical bonding leads with serviceable electrical bonding leads. For certain airplanes, this amendment also requires modifying the fuel pipe couplings in specified locations of the fuel tank. 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 electrical arcing/discharge in the fuel tank due to damaged electrical bonding leads or inadequate electrical bonding of the fuel pipe couplings, which could result in fuel ignition and consequent uncontained rupture of the fuel tank.
2000-11-24: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires repetitive inspections to detect discrepancies of the downlock support assembly and attachment of the nose landing gear (NLG), and of the bulkhead and adjacent structure in the NLG bay; and corrective action, if necessary. 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 detect and correct damage of the NLG downlock support, which could result in collapse of the NLG and consequent injury to passengers or flightcrew.
98-18-18: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires modification of the attach points of the uplock system of the nose landing gear (NLG). 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 wear of the attach points of the uplock system of the NLG; such wear could result in damage to the adjacent emergency hydraulic system, or jamming of the uplock system and consequent inability to extend and retract the NLG.
2006-24-04: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 767 airplanes. This AD requires repetitive detailed and high frequency eddy current (HFEC) inspections of the station (STA) 1809.5 bulkhead for cracking and corrective actions if necessary. This AD results from fatigue cracks found in the forward outer chord and horizontal inner chord at STA 1809.5. We are issuing this AD to detect and correct cracking in the bulkhead structure at STA 1809.5, which could result in failure of the bulkhead structure for carrying the flight loads of the horizontal stabilizer, and consequent loss of controllability of the airplane.
2006-24-05: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747 airplanes. This AD requires repetitive inspections for any cracking of the fuselage skin in section 41 of the airplane, and related investigative and corrective actions if necessary. This AD results from a report of fatigue cracks found in the skin in section 41 of the fuselage, on an in-service Model 747 airplane. We are issuing this AD to detect and correct fatigue cracks at the fastener rows of the fuselage skin in section 41, which could join together and cause a loss of structural integrity and rapid decompression of the airplane.
2021-14-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A319-151N, A319-153N, A319-171N, A320-251N, A320-252N, A320-253N, A320-271N, A320-272N, A320-273N, A321-251N, A321-251NX, A321-252N, A321-252NX, A321-253N, A321-253NX, A321-271N, A321-271NX, A321-272N and A321-272NX airplanes. This AD was prompted by reports of an increasing number of operational disruptions due to airspeed discrepancies. This AD requires revising the existing airplane flight manual (AFM) to include a procedure to reinforce the airspeed check during the take-off phase and provide instructions to abort take-off in certain cases, 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.
86-17-10: 86-17-10 BELL HELICOPTER TEXTRON, INC.: Letter issued August 21, 1986. Applies to all Bell Helicopter Models 205 and 205A-1 helicopters, which have retrofit kit, P/N 212-704-129-101, installed (reference Bell Service Instructions (S.I.)) 212-68, May 29, 1981, certified in any category. Compliance required as indicated unless already accomplished. To prevent failure of the tail rotor control, accomplish the following: (a) Within 25 hours' time in service after receipt of this AD, visually inspect the T/R hub assembly P/N 212-011-701-3, in accordance with Part I of Bell Helicopter Textron, Inc. (BHTI), Alert Service Bulletin (ASB) 205-86-24, Revision "A," dated July 23, 1986. (1) If the (P/N) 212-011-716-1 T/R trunnion housing is cracked or there is axial play in the T/R trunnion, or if there are excess balance washers, comply with Part II of the Alert Service Bulletin before further flight. (2) Repeat this inspection every 25 hours' time in service untilparagraph (b) of this AD is accomplished. (b) Remove the 212-011-701-1 T/R hub and blade assembly and inspect the trunnion bearing housing, P/N 212-011-716-1, as detailed in Part II of BHTI ASB 205-86-24, Revision "A," dated July 23, 1986, within 150 hours' time in service or within 60 days after the issue date of this AD, whichever occurs first. Replace any housing having an end web thickness of .059 inch or less with a serviceable part. An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region. This airworthiness directive becomes effective upon receipt.
2018-20-24: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by significant changes made to the airworthiness limitations (AWL) related to fuel tank ignition prevention and the nitrogen generation system. This AD requires revision of the maintenance or inspection program, as applicable, to include the latest revision of the AWLs. We are issuing this AD to address the unsafe condition on these products.
2006-23-17: The FAA is superseding an existing airworthiness directive (AD) for Turbomeca Turmo IV A and IV C series turboshaft engines. That AD currently requires borescope and eddy current inspections or ultrasonic inspections of centrifugal compressor intake wheel blades for cracks and evidence of corrosion pitting, and replacement with serviceable parts. This AD requires the same actions, but would require borescope inspections at more frequent intervals for certain engines. This AD results from Turbomeca's review of the engines' service experience that determined more frequent borescope inspections are required on engines not modified to the TU 191, TU 197, or TU 224 standard. We are issuing this AD to prevent centrifugal compressor intake wheel blade cracks, which can result in engine in-flight power loss, engine shutdown, or forced landing.
86-16-01: 86-16-01 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-5364. Applies to Models N22B and N24A (all serial numbers) airplanes certificated in any category, unless Service Bulletin (S/B) No. NMD-27-34 (Mod N642) has been accomplished. Compliance: Required within 100 hours time-in-service after the effective date of this AD or one calendar year after the effective date of this AD, whichever occurs first, unless already accomplished. To prevent jamming of the rudder pedals accomplish the following: (a) Modify the airplane sidewall structure and rudder pedals in accordance with Paragraph 2. "Accomplishment Instructions" of GAF S/B No. NMD-27-34 dated October 21, 1985. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. (c) An equivalent method of compliance with this AD if used, must be approved by the Manager, Western Aircraft Certification Office, ANM-170W, Northwest Mountain Region, FAA, Post Office Box 92007, Worldway Postal Center, Los Angeles, California 90009-2007. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Government Aircraft Factories, 226 Lormier Street, Fisherman's Bend, Port Melbourne, Victoria, Australia 3207, or FAA, Office of Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106 or the Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California 90009-2007. This amendment becomes effective August 28, 1986.
87-03-12: 87-03-12 DEHAVILLAND: Amendment 39-5549. Applies to DHC-6 Models 1, 100, 200, and 300 airplanes certificated in any category, when fitted with side folding cabin utility seats. Compliance: Required as indicated, unless already accomplished. To prevent disengagement of the utility seat forward legs from the floor mounting rail, accomplish the following: (a) Within 50 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished within the last 25 hours TIS, and at subsequent intervals not to exceed 50 hours TIS thereafter, attempt to move the lower end of each forward leg sideways into the open part of the keyhole slot using as much force as can be exerted by hand. If the leg can be removed from the keyhole slot, remove the seat from service until Modification No. 6/1828 is incorporated in accordance with the ACCOMPLISHMENT INSTRUCTIONS of DeHavilland Service Bulletin (S/B) No. 6/447, Revision C, dated May 16, 1986. (b) Repeat thecheck in paragraph (a) of this AD each time the seats are moved from stowed to deployed position. (c) The check required by paragraph (b) of this AD may be accomplished by a flightcrew member, certificated under FAR 61 or FAR 63 rules, briefed on the procedure. (d) When Modification No. 6/1828 is incorporated in accordance with the ACCOMPLISHMENT INSTRUCTIONS of DeHavilland S/B No. 6/447, Revision C, on each seat, subsequent checks required by this AD are no longer required on that seat. (e) An equivalent means of compliance may be used when approved by the Manager, New York Aircraft Certification Office, Federal Aviation Administration, ANE-170, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This AD supersedes AD 84-07-07, Amendment 39-4841. This amendment becomes effective on February 13, 1987.
88-26-51: 88-26-51 PRATT & WHITNEY CANADA: Amendment 39-6275. Final Rule of previously issued telegraphic AD. Applicability: Pratt & Whitney Canada (PWC) PW115/118/118A turboprop engines prior to Serial Number (S/N) PCE 115033, and PW120/120A/121 turboprop engines prior to S/N PCE 120174. Compliance: Required as indicated, unless already accomplished. To prevent an uncontained engine failure resulting from low cycle fatigue failure of certain high pressure turbine (HPT) components, accomplish the following: (a) Determine upon receipt of this AD the cyclic life accumulated on the HPT front cover, HPT rear cover, and HPT disk, in accordance with PWC Service Bulletin (SB) 20002, Revision 4, dated November 21, 1988, paragraph 2.D.(1), as follows: (1) For engines which have not incorporated PWC SB 20133, dated September 14, 1987, calculate the total cyclic life accumulated using a flight count factor (FCF) of 1.5 in accordance with the formula found in PWC SB 20002, Revision 4, paragraph 2.D.(1). (2) For engines which have incorporated PWC SB 20133, dated September 14, 1987, calculate the total cyclic life accumulated prior to the incorporation of PWC SB 20133 using an FCF of 1.5, plus the total cycles accumulated after the incorporation of PWC SB 20133 using an FCF of 1.0, in accordance with the note in PWC SB 20002, Revision 4, paragraph 2.D.(1). (b) Remove from service and replace with a serviceable part within 25 cycles in service (CIS) from the receipt of this AD, those HPT front covers, HPT rear covers, or HPT disks which have accumulated 14,975 CIS or greater upon receipt of this AD, as calculated in accordance with paragraph (a)(1) or (a)(2) of this AD. (c) Remove from service and replace with a serviceable part at or prior to accumulating 15,000 CIS, those HPT front covers, HPT rear covers, or HPT disks which have accumulated less than 14,975 CIS upon receipt of this AD, as calculated in accordance with paragraph (a)(1) or(a)(2) of this AD. (d) 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. (e) 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 adjustment to the compliance times specified in this AD, may be approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. The determination of the cyclic life accumulated on the HPT front cover, HPT rear cover, and HPT disk shall be accomplished in accordance with PWC SB 20002, Revision 4, dated November 21, 1988. 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 Pratt& Whitney Canada, 1000 Marie-Victorin, Longueuil, Quebec, Canada J4G 1A1. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, Room 8301, Washington, D.C. 20591. This amendment (39-6275, AD 88-26-51) becomes effective on September 22, 1989, as to all persons except those persons to whom it was made immediately effective by TAD T88-26-51, issued December 28, 1988, which contained this amendment.
2006-23-16: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD requires modifying the nose landing gear. This AD results from reports of loss of the nose wheel assembly. We are issuing this AD to prevent the nose wheel nut from loosening, and consequently, the nose wheel assembly detaching from the airplane; and to prevent the nose wheel clamping loads from applying to the machined radius at the root of the stub axle, which could result in damage to the nose landing gear.