Results
59-11-04: 59-11-04 VICKERS: Applies to All Viscount 745D Aircraft Which Do Not Embody Modification D.2783. Compliance required as indicated. Service experience has shown that a gap of less than 0.25 inch between the end of No. 3 flap and the aileron may, under certain flight conditions, produce a condition where the flap could foul or contact the inboard end of the aileron (port and starboard wings). As soon as possible but not later than June 15, 1959, inspect for adequate clearance between the outboard end of the No. 3 flap at the No. 4 flap beam unit and the inboard end of the aileron on both the right and left sides. Where the gap is found to be less than 0.25 inch, the outboard end of the No. 3 flap must be modified to provide proper clearance. The British Air Registration Board considers this mandatory. (Vickers-Armstrong PTL No. 208 and Modification Bulletin No. D.2783 cover the same subject.)
2006-09-06 R1: The FAA is revising an existing airworthiness directive (AD) that applies to certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747-400, 747-400D, and 747SR series airplanes. That AD currently requires repetitive inspections to detect cracking of certain lower lobe fuselage frames, and repair if necessary. This new AD specifies appropriate service information for certain corrective actions. This AD results from reports indicating that fatigue cracks were found in lower lobe frames on the left side of the fuselage. We are issuing this AD to detect and correct fatigue cracking of certain lower lobe fuselage frames, which could lead to fatigue cracks in the fuselage skin, and consequent rapid decompression of the airplane. \n\n\nDATES: The effective date of this AD is June 7, 2006. \n\n\tOn June 7, 2006 (71 FR 25926, May 3, 2006), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2408, Revision 1, dated April 4, 2002. \n\n\tOn May 5, 1999 (64 FR 15298, March 31, 1999), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2408, dated April 25, 1996.
2018-20-14: We are adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R(eacute)gional Model ATR42-500 airplanes. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new and/or more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2018-20-21: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (CL-604 Variants) airplanes. This AD was prompted by reports of floodlight lamps found burned and the corresponding circuit breaker tripped as a result of fluid entering the cockpit floodlight fixtures. This AD requires installation of new gasket seals on floodlight fixtures. We are issuing this AD to address the unsafe condition on these products.
99-26-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires replacement of the rudder trim switch in the flight compartment with a new switch having a longer shaft; modification of wiring in panel 408VU; and replacement of the rudder trim control knob with an improved new knob. 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 inadvertent and uncommanded rudder trim activation, which could result in yaw and roll excursions and consequent reduced controllability of the airplane.
2006-24-07: The FAA is adopting a new airworthiness directive (AD) for certain Hartzell Propeller Inc. HC, BHC, and PHC series propellers; and McCauley Propeller Systems controllable propellers serviced by Oxford Aviation Services Limited, doing business as CSE Aviation, in the United Kingdom between September 1998 and October 2003. This AD requires inspecting the propeller blades and other critical propeller parts for wear and mechanical damage. This AD results from findings that CSE Aviation failed to perform some specific inspections and repairs. We are issuing this AD to detect unsafe conditions that could result in a propeller blade separating from the hub and loss of control of the airplane.
2006-23-09: The FAA adopts a new airworthiness directive (AD) for all Air Tractor, Inc. (Air Tractor) Model AT-602 airplanes. This AD requires you to repetitively inspect (using the eddy current method) the wing center splice joint two outboard fastener holes on both of the wing main spar lower caps for fatigue cracking; repair or replace any wing main spar lower cap where fatigue cracking is found; and report any fatigue cracking found. This AD results from fatigue cracking at the wing center splice joint outboard fastener hole in one of the wing main spar lower caps. We are issuing this AD to detect and correct cracks in the wing main spar lower cap, which could result in failure of the spar cap and lead to wing separation and loss of control of the airplane.
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.