Results
2004-22-11: This amendment supersedes an existing airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model EC135 P1, P2, T1, and T2 helicopters. That AD currently requires adding the AD or a statement to the Rotorcraft Flight Manual (RFM) informing the pilot to reduce power and land as soon as practicable if a thump-like sound followed by an unusual vibration occurs during flight. That AD also requires visually inspecting the main rotor drive torque strut assembly (strut) for a crack or a break, recording the inspections in the historical or equivalent record, re-marking and relocating the strut, as appropriate, and replacing any unairworthy strut with an airworthy strut. Also, that AD establishes life limits for certain struts and revises the life limit for other struts. This amendment requires the same actions as the existing AD except that it changes the visual inspection from a one-time inspection to daily inspections; reduces the life limit for aluminum struts;and eliminates the once-only transfer and remarking of certain struts. This amendment is prompted by an incident in which a pilot felt an in-flight increase in vibration and subsequent discovery of a failed strut. The actions specified by this AD are intended to prevent failure of a strut and subsequent loss of control of the helicopter.
98-19-15 R1: This amendment revises Airworthiness Directive (AD) 98-19-15, which currently requires incorporating information into the Limitations Section of the airplane flight manual (AFM) that imposes a speed restriction and a minimum pilot requirement for Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes equipped with Barber-Colman pitch trim actuators, part number (P/N) 27-19008-001/-004 or P/N 27-19008-002/-005. Since AD 98-19-15 became effective, improved design pitch trim actuators have been developed that, when installed, will eliminate the speed restriction and minimum pilot requirements of the current AD. This AD requires incorporating these installations as a method of complying with the current AD. The actions specified by this AD are intended to lessen the possibility of airplane pitch up caused by mechanical failure of the pitch trim actuator, which could result in a pitch upset and structural failure of the airplane.
2022-24-12: The FAA is superseding Airworthiness Directive (AD) 2020-23-05 for certain Airbus Helicopters Model EC225LP helicopters. AD 2020-23-05 required inspecting the control rod attachment yokes (yokes) of certain main rotor (M/R) rotating swashplates (swashplates), establishing a life limit, performing a one-time inspection of stripped yokes, and applicable corrective actions. Since the FAA issued AD 2020-23-05, the FAA has determined that certain swashplates are not susceptible to the unsafe condition, repetitive inspections for certain swashplates are necessary, and the criteria for when to perform a dye penetrant inspection needed to be revised. This AD retains some of the requirements of AD 2020-23-05 and also requires compliance with a revised life limit; performing a repetitive visual inspection of the yokes on certain swashplates; and depending on the inspection results, removing the affected swashplates from service, performing a dye penetrant inspection of the yoke, and additional corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
90-01-08: 90-01-08 MCDONNELL DOUGLAS HELICOPTER COMPANY (MDHC): Amendment 39-6456. Docket No. 89-ASW-10. Applicability: Model 369 series helicopters (including Models YOH-6A and OH-6A) certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent possible failure of the engine-to-transmission driveshaft coupling, which could result in loss of control of the helicopter, accomplish the following: (a) Within the next 25 hours' time in service or within 120 days after the effective date of the AD, whichever occurs first, inspect the couplings, MDHC Part Number (P/N) 369H5660, to determine serial numbers. (b) Replace any couplings, P/N 369H5660, which have serial numbers in the range from 5200 through 5309, with airworthy parts. (c) Record compliance with paragraph (a) of this AD in the AD compliance record and in the maintenance record of the helicopter log book. This record must include the serial numbers of any deficient couplings found during compliance with this AD. NOTE: MDHC Service Information Notices HN-216, DN-157, EN-47, FN-35, dated April 5, 1989, pertain to this subject. (d) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the requirements of this AD may be accomplished. (e) An alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety, may be used if approved by the Manager, Los Angeles Aircraft Certification Office, ANM-100L, FAA, 3229 East Spring Street, Long Beach, California 90806-2425. NOTE: Unairworthy couplings removed from service and in spares inventory should be marked unairworthy. Unairworthy couplings should be purged from spares inventory in accordance with MDHC SIN HN-216, DN-157, EN-47, FN-35, dated April 5, 1989. This amendment (39-6456, AD 90-01-08) becomes effective on February 5, 1990.
2022-23-07: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 series airplanes. This AD was prompted by a finding that when the autopilot is engaged, the architecture of the autopilot system does not automatically disconnect the autopilot in response to pilot application of a pitch input or when the electric pitch trim switch on either pilot control wheel is operated. This AD requires modifying the autopilot engagement circuit. The FAA is issuing this AD to address the unsafe condition on these products.
91-23-08: 91-23-08 MITSUBISHI HEAVY INDUSTRIES: Amendment 39-8077. Docket No. 91-CE-33-AD. Applicability: Models MU-2B-10, MU-2B-15, and MU-2B-20 airplanes (serial numbers (S/N) 008 through 211), Model MU-2B-30 airplanes (S/N 502 through 542), and Model MU-2B-36 airplanes (S/N 501), certificated in any category. Compliance: Required within the next 200 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent interference between the rudder and the rudder trim tab that could result in loss of control of the airplane, accomplish the following: (a) Modify the rudder trim tab in accordance with the instructions in Mitsubishi Heavy Industries Service Bulletin No. 211, dated November 20, 1990. (b) 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. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3229 E. Spring Street, Long Beach, California 90806-2425. The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles Aircraft Certification Office. (d) The modification required by this AD shall be done in accordance with Mitsubishi Heavy Industries Service Bulletin No. 211, dated November 20, 1990. 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 Mitsubishi Heavy Industries, Nagoya Aerospace Systems, 10, Oyecho, Minato-Ku, Nagoya, Japan. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. (e) This amendment (39-8077, AD 91-23-08) becomes effective on December 18, 1991.
2022-23-02: The FAA is superseding Airworthiness Directive (AD) 99-23-18, AD 2005-03-07, AD 2013-12-07, and AD 2014-04-07, which applied to certain Bell Helicopter Textron Canada (now Bell Textron Canada Limited) Model 407 helicopters. AD 99-23-18 required revising the life limits for certain parts, replacing each part that had exceeded its life limit, and revising the Airworthiness Limitation Section (ALS) of the existing maintenance manual. AD 2005-03-07 required establishing a maximum accumulated Retirement Index Number (RIN) count for certain crosstube assemblies and revising the ALS of the existing maintenance manual. AD 2013-12-07 required inspecting the tailboom assembly for a crack, loose rivet, or other damage and depending on the inspection results, replacing certain parts. AD 2014-04-07 required preflight checking, repetitively inspecting for a crack in certain tailbooms, modifying and re-identifying certain tailbooms, installing an improved horizontal stabilizer assembly, and revising the ALS of the existing maintenance manual. Since the FAA issued those ADs, a report was received of a crack on the tailboom lower skin due to fatigue damage and new and more restrictive airworthiness limitations have been issued. This AD was prompted by a report of a crack on the tailboom lower skin due to fatigue damage and the issuance of new and more restrictive airworthiness limitations. This AD requires incorporating into existing maintenance records requirements (airworthiness limitations) as specified in the ALS service information. The FAA is issuing this AD to address the unsafe condition on these products.
2022-23-04: 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 the flightcrew and passenger oxygen system's refill and capillary lines may have been contaminated by sealant and cotton fibers. This AD requires an inspection to determine the serial numbers of the oxygen cylinders installed and replacement of each affected oxygen cylinder and regulator assembly (OCRA). The FAA is issuing this AD to address the unsafe condition on these products.
78-13-01: 78-13-01 SHORT BROTHERS LIMITED: Amendment 39-3243. Applies to Model SD3-30 airplanes, S/N's 3003 through 3015, certificated in all categories. Compliance is required as indicated unless already accomplished. To prevent possible collapse of the main landing gear, prior to the accumulation of 50 landings after the effective date of this AD, install a one way restrictor valve, Menasco P/N 17516-1 or 17517-1, and associated hardware in the main landing gear retraction/extension system (R/H and L/H) in accordance with section 2, "Accomplishment Instructions" and figures 1, 2, and 3, of Short Brothers Limited Service Bulletin SD3-32-41, dated March 23, 1978, or an FAA approved equivalent. This amendment becomes effective July 5, 1978.
99-27-16: This amendment adopts a new airworthiness directive (AD), applicable to CFE Company Model CFE738-1-1B turbofan engines. This AD requires, on certain engines identified by serial numbers: a one-time visual inspection of Stage 2 high pressure turbine (HPT) aft cooling plates for nicks, dents, and scratches, and if present, dimensional inspection of indentation depth; repair, if indentation is within acceptable limits, and, if necessary, replacement with serviceable parts. This AD also requires inspection for raised metal on the Stage 2 HPT rotor disk post aft surface that mates with the Stage 2 HPT aft cooling plate, and removal of the raised metal, if present. This amendment is prompted by reports of Stage 2 HPT aft cooling plates that were dented during the assembly of the cooling plate to the Stage 2 disk due to raised metal on the stage 2 HPT disk post aft mating surface. The actions specified by this AD are intended to prevent aft HPT cooling plate failure, which couldresult in an uncontained engine failure and damage to the airplane.
2022-20-14: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Inc., Model 204B, 205A, 205A-1, 205B, 210, 212, 412, 412CF, and 412EP helicopters and various restricted category helicopters. This AD was prompted by reports of cracks found on the main transmission support case. This AD requires repetitive inspections of the main transmission housing assembly for cracks, pitting, and corrosion and depending on the results, corrective action. The FAA is issuing this AD to address the unsafe condition on these products.
2005-13-08: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes. This AD requires the overhaul of certain auxiliary components installed on the main landing gear (MLG) and nose landing gear (NLG). This AD is prompted by manufacturer determination that overhaul limits need to be imposed for certain auxiliary components of the MLG and NLG. Components that exceed the established overhaul limits could fail due to fatigue, wear, and age. We are issuing this AD to prevent failure of the MLG or NLG, and consequent damage to the airplane and injury to flightcrew and passengers.
99-27-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires repetitive inspections of the control quadrant for loose screws, and replacement of the control quadrant with a modified part, which constitutes terminating action for the repetitive inspections. 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 the power levers from binding due to the backing out of screws that secure the solenoid bracket within the flight idle stop assembly, which could result in the malfunction of the flight idle stop mechanism and the override function, and the inability to move the power levers aft of flight idle.
99-27-12: This amendment supersedes an existing airworthiness directive (AD), applicable to Agusta Model A109A and A109A II helicopters, that currently requires, before further flight, inspecting any tail rotor blade (blade) with 400 or more hours time-in-service (TIS) for a crack and replacing any cracked blade before further flight. This amendment contains the same requirements as the current AD but corrects the paragraph that requires "replacing any cracked blade with an unairworthy blade." This amendment is prompted by the need to correct the requirement to mandate "replacing any cracked blade with an airworthy blade." The actions specified by this AD are intended to prevent fatigue failure of the blade, loss of the tail rotor, and subsequent loss of control of the helicopter.
2022-24-08: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 505 helicopters. This AD was prompted by the discovery of a potential fouling condition between the rotating swashplate outer ring and the non-rotating collective lever. This AD requires inspecting the collective control system rigging and depending on the results, rigging the collective and cyclic control systems, as specified in a Transport Canada emergency AD, which is incorporated by reference. This AD also requires reporting certain information. The FAA is issuing this AD to address the unsafe condition on these products.
91-12-14: 91-12-14 DORNIER: Amendment 39-7025; Docket No. 91-CE-04-AD. Applicability: Models Dornier 228-100, Dornier 228-101, Dornier 228-200, Dornier 228-201, and Dornier 228-202 airplanes (serial numbers 7000 through 7036, and 8000 through 8050), certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent complete loss of alternating current (AC) electrical power, accomplish the following: (a) Modify the electrical AC power supply system in accordance with the instructions in Dornier Service Bulletin No. SB-228-171, dated July 20, 1990. (b) 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. (c) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, Europe, Africa, Middle East office, FAA, c/o American Embassy, 1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (d) The modification required by this AD shall be done in accordance with Dornier Service Bulletin No. SB-228-171, dated July 20, 1990. 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 upon request to Dornier Luftfahrt GmbH, P.O. Box 3, D-8031 Wessling, Germany. This information may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, DC. This amendment (39-7025, AD 91-12-14) becomes effective onJuly 19, 1991.
99-27-01: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 series turbofan engines, that requires inspection of the 3rd stage and 4th stage low pressure turbine (LPT) blades for shroud notch wear and replacement of the blade if wear limits are exceeded. This amendment is prompted by a report of an uncontained blade failure. The actions specified by this AD are intended to prevent an uncontained blade failure that could result in damage to the airplane.
2004-22-13: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (Bell) model helicopters that requires a one-time inspection of the adjustable stop screws of the magnetic brake assembly; repairing, as appropriate, certain mechanical damage to the cyclic and collective flight control magnetic brake arm assembly (arm assembly), if necessary; and installing the stop screw with the proper adhesive, adjusting the arm assembly travel and applying slippage marks. This amendment is prompted by reports that the magnetic brake adjustable screws have backed out, which limited travel of the arm assembly. The actions specified by this AD are intended to detect loose adjustable stop screws, that could result in limiting the travel of the cyclic and collective arm assembly, and subsequent loss of control of the helicopter.
2022-22-07: The FAA is adopting a new airworthiness directive (AD) for certain Piaggio Aviation S.p.A. (type certificate previously held by Piaggio Aero Industries S.p.A.) (Piaggio) Model P-180 airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as corrosion in the bottom fuselage area of the cabin compartment due to inner and outer sides of fuselage skin panels of certain airplanes treated with the less effective primer. This AD requires repetitively inspecting the fuselage skin panels, visually inspecting the entire fuselage inner side skin if necessary, and taking any necessary corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
90-10-06: 90-10-06 SAAB-SCANIA: Amendment 39-6595. Docket No. 90-NM-64-AD. Applicability: Model SAAB 340B series airplanes, Serial Numbers 161 through 197, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent oscillations (flutter) of the rudder, accomplish the following: A. Within 10 flight hours time-in-service, accomplish the following: 1. Install a placard in the cockpit stating: "Air Speed Restricted to 220 KIAS", and 2. Incorporate the following into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM): Restrict the maximum operating speed to 220 KIAS in accordance with Section 2. under "Short Term Actions" of SAAB 340 Service Newsletter, SN-9002, Revision 1, dated February 19, 1990. This may be accomplished by inserting a copy of this AD in the AFM. B. Within 90 days after the effective date of this AD, install new rudder and rudder trim tab balance weights in accordance with SAAB-Scania Service Bulletin SAAB 340-55-026, dated March 16, 1990. Upon installation of these balance weights, the placard and flight manual limitation required by paragraph A., above, may be removed. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either 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 information from the manufacturer may obtaincopies upon request to SAAB-Scania AB, SAAB Aircraft Product Support, S-581.88, Linkoping, Sweden. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6595, AD 90-10-06) becomes effective on May 24, 1990.
96-12-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, that requires measurements of the thickness of the inner skin of the longitudinal lap joint from the inside of the fuselage at certain stringers. This amendment also requires inspections to detect stress corrosion cracking in the subject area, and repair, if necessary. This amendment is prompted by reports of stress corrosion cracking found in the skin at the longitudinal lap joint at certain stringers of the fuselage, which was caused by the increased stress level in the subject area when it was reworked beyond certain limits. The actions specified by this AD are intended to prevent such stress corrosion cracking which, if not detected and corrected in a timely manner, could result in rapid depressurization of the airplane.
2004-22-03: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-135 and -145 series airplanes. This AD requires measuring the fillet radius dimension of the trunnion fitting webs of the wings; and reworking the fillet radius of the trunnion fitting web in order to increase the radius, doing related investigative actions, and doing applicable corrective action, if necessary. This AD is prompted by a report indicating that trunnion fittings of the wings have been manufactured with a web fillet radius smaller than the minimum required by the design data, which may induce the occurrence of fatigue cracks at the root of the trunnion fillet radius and adjacent structures (e.g., spar and ribs). We are issuing this AD to detect and correct fatigue cracking of the wing trunnion fittings or adjacent structure, which could result in failure of the main landing gear, consequent damage to surrounding structure, and possible loss of control of the airplane during landing.
99-27-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires repetitive inspections of the connections between certain ribs and stringers of the wing skins to detect loose or missing rivets or gaps, and corrective actions, if necessary. This action also requires eventual modification of the rib-stringer connection, which terminates the repetitive inspections. 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 fatigue cracking in the skin and stringers, which could result in reduced structural integrity of the wings.
2022-20-04: The FAA is superseding airworthiness directive (AD) 2021-26- 08, which applied to certain Bell Textron Canada Limited Model 206, 206A, 206A-1, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 helicopters. AD 2021-26-08 required removing certain nuts from service; installing newly designed nuts; applying a specific torque, and a torque stripe to each newly installed nut; after the installation of each newly designed nut, inspecting the torque; and depending on the inspection results, either applying a torque stripe, or performing further inspections and removing certain parts from service. AD 2021- 26-08 also prohibited installing any affected nut on any tail rotor drive shaft (TRDS) disc pack (Thomas) coupling. Since the FAA issued AD 2021-26-08, the FAA determined certain torque values and part numbers (P/Ns) need to be revised. This AD was prompted by reports of cracked or missing nuts installed on the TRDS Thomas couplings and the need to revise certain torque values and P/Ns in AD 2021-26-08. This AD requires removing certain nuts from service; installing newly designed nuts; applying torque and a torque stripe; and additional corrective actions if necessary. This AD also prohibits installing any affected nut on any TRDS Thomas coupling, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
95-25-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech Model 400, 400A, and 400T (military T-1A) airplanes, that requires modification of the standby instrument lighting system. This amendment is prompted by a report that, due to the design of the standby instrument lighting system, the lighting for the standby instruments dimmed to an unacceptable level when the main electrical power was turned off. The actions specified by this AD are intended to ensure that the standby instrument lighting system adequately illuminates the standby instrument, if normal electrical power is lost or is turned off as a result of fire or smoke in the cockpit.