Results
2004-22-16: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Model GV and GV-SP series airplanes. This AD requires a one-time general visual inspection for contact or insufficient clearance between the crew oxygen bottle/supports and any wiring harness, and related investigative and corrective actions if necessary. This AD also requires, for certain airplanes, adjusting the wiring harness to obtain a minimum clearance between the crew oxygen bottle and wiring, and applying Teflon sheeting, as applicable; and for certain other airplanes, reworking certain wiring bundles. This AD is prompted by reports of insufficient clearance between certain wiring harnesses and the crew oxygen bottle on several in-production and in- service airplanes. We are issuing this AD to prevent chafing of the electrical wires of the wiring harness against the crew oxygen bottle, which could result in electrical shorting and possible fire in the underfloor structure of the airplane.
2022-24-10: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) airplanes, Model CL-600-2C11 (Regional Jet Series 550) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600- 2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report that the pressure switch gauge assembly for the cargo bay fire extinguisher container has the potential to display an incorrect pressure under certain environmental conditions. This AD requires replacing affected high rate of discharge (HRD) and low rate of discharge (LRD) pressure switch gauge assemblies for the cargo bay fire extinguisher container. The FAA is issuing this AD to address the unsafe condition on these products.
2004-22-09: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes. This AD requires a one-time high-frequency eddy current inspection for cracking of the attachment lugs of the aileron spring tab balance unit, and corrective actions if necessary. This AD is prompted by a report indicating that, during heavy turbulence, a pilot needed to apply aileron trim to maintain level flight because cracking of the upper inboard attachment lug of the aileron spring tab balance unit, probably due to corrosion, had caused permanent deflection of the spring tab and consequent aileron damage. We are issuing this AD to prevent diminished control of the airplane in turbulence or total loss of roll control for the affected wing.
76-15-06: 76-15-06 BOEING: Amendment 39-2678. Applies to all Model 727 series airplanes, categorized as Group I and II in Boeing Service Bulletin No. 727-55-A65, or later FAA approved revisions, and certificated in all categories. Compliance required as indicated unless it can be shown that this AD is not applicable per paragraph B. \n\n\tTo prevent possible stabilizer flutter from mismatch of the elevator balance panel aft hinges in bays 2 and 5, accomplish the following: \n\tA.\tUnless already accomplished, within the next 300 flight hours from the effective date of this AD, inspect the elevator balance panel aft hinges in elevator bays 2 and 5 (left and right) for compatibility in accordance with Boeing Service Bulletin No. 727-55-A65, or later FAA approved revisions, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. If an aluminum hinge is installed in bay 2 and an aluminum-bronze hinge is installed in bay 5, replace in accordance with the service bulletin and physically rebalance in accordance with the Boeing 727 Structural Repair Manual prior to the next flight. \n\tB.\tIf it can be shown through an operator's records or airplane's maintenance records that the elevator balance panel aft hinges are not of the combination of aluminum in bay number 2 and aluminum-bronze in bay number 5, the AD is not applicable. \n\tC.\tAirplanes requiring action prior to the next flight per paragraph A may be flown to the nearest maintenance base in accordance with FAR 21.197 and 21.199. \n\tThe 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). \n\tAll persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98108. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective August 9, 1976.
2022-24-14: The FAA is superseding Airworthiness Directive (AD) 2020-12- 11, which applied to all Airbus SAS Model A319-111, -112, -113, -114, - 115, -151N, and -153N airplanes; Model A320-251N, -252N, -253N, -271N, -272N, and -273N airplanes; and Model A321-251N, -251NX, -252N, -252NX, -253N, -253NX, -271N, -271NX, -272N, and -272NX airplanes. AD 2020-12- 11 required revising the existing airplane flight manual (AFM) to limit the use of speed brakes in certain airplane configurations, as specified in a European Union Aviation Safety Agency (EASA) AD. This AD was prompted by a non-stabilized approach followed by an automatic go- around that led to an airplane pitch-up attitude and resulted in an auto-pilot disconnection. This AD continues to require the actions in AD 2020-12-11 and also requires, for certain airplanes, installing updated FG 3G standard software for the FMGC, and prohibits the installation of affected FG standards, as specified in an EASA AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2022-24-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A300 F4-600R series airplanes. This AD was prompted by a determination that the forward cargo door compartment between certain frame forks is susceptible to widespread fatigue damage (WFD). This AD completes certain mandated programs to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires modifying the forward cargo compartment between certain frame forks, 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.
2022-24-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report that damage (including delamination of the work deck, and corroded and cracked retainer blocks) was found during inspection of certain galleys. This AD requires repetitive inspections of certain galleys for corrosion of trolley retainer aluminum blocks and delamination of the upper panel of the trolley compartment, and applicable corrective action, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
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.