Results
99-20-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes, that requires modification of the 90VU electronics rack umbrellas, the 91VU upper shelf assembly, the cockpit drain circuit, and the electrical wire routing above the 90VU electronics rack. 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 damage to computer electrical connectors due to ingress of water into the avionics bay, which could result in malfunctioning of the avionics computers.
2006-07-16: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires replacing all domed anchor nuts at all attachment locations of the upper fuel access panels of the center wing in the wet bay location with new nuts. This AD results from reported cases of corroded dome anchor nuts at the attachment locations of the upper surface of the fuel access panel of the center wing. We are issuing this AD to prevent corrosion or perforation of domed anchor nuts, which could result in arcing and ignition of fuel vapor in the center wing fuel tank during a lightning strike and consequent explosion of the fuel tank.
99-19-35: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace BAe Model ATP airplanes, that requires repetitive tests for the serviceability of the nose landing gear compensator; 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 prevent a nose wheel shimmy, which could lead to the collapse of the nose landing gear during landing.
51-07-01: 51-07-01 NAVION: Applies to All Models Having Serial Numbers 1789 Through 2019; 2021 Through 2026; 2028 Through 2142; 2144 Through 2169; 2171 Through 2177; and 2180. To be accomplished as indicated below. It has been found that on some of these airplanes throttle housing slippage has occurred at the point where the cable housing is swaged to the ferrule at the instrument panel end. This slippage can result in erratic throttle operation. An inspection of these controls for evidence of housing slippage must be made not later than March 5, 1951. Any control showing evidence of slippage shall be replaced immediately. It has been found that housing slippage may be caused by the inner shaft in the control head striking the end of the housing when the throttle is moved to the full open position. To prevent such occurrence, a special stop nut must be installed on the throttle shaft in place of the existing jam nut. This special nut, which will prevent the inner shaft from striking the end of the housing, is being furnished by the Ryan Co. and must be installed by July 15, 1951. (Ryan Field Service Bulletin No. 9, dated September 1, 1950, covers this same subject.)
98-14-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes. This action requires repetitive inspections to detect cracks in the forward canted frames between fuselage frames 47a and 48 from stringer (STGR) 41 to STGR 43; and temporary repair, or replacement of the forward canted frame with a new frame, if necessary. 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 detect and correct cracking in the forward canted frames, which could result in failure of the forward canted frame, and consequent reduced structural integrity of the airplane.
2006-07-10: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 727 airplanes. That AD currently requires repetitive visual inspections for cracking of the forward entry doorway forward frame and repair if necessary. That AD also provides an optional modification that constitutes terminating action. This new AD requires adding new post-repair and post- modification inspections for previously repaired or modified airplanes, mandating the optional modification, and adding airplanes to the applicability of the AD. This AD results from reports of cracking of the forward entry doorway forward frame of airplanes previously modified. We are issuing this AD to prevent the loss of the structural integrity of the forward entry doorway due to cracking of the frame at Body Station 303.9, and consequent cracking of the fuselage skin and rapid decompression of the airplane.
2003-03-18: This amendment adopts a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C, and 1900D airplanes. This AD requires you to perform control column sweep and stop bolt inspections to verify full elevator travel to the primary up and down stops and that the stop bolt length is not excessive, re-rig the elevator control system if the airplane does not pass the control column sweep and stop inspections, and do a more detailed inspection at a later time if the airplane does pass the inspection. This AD also requires you to report the results of certain inspections. This AD is the result of recent ground testing and a review of the rigging procedures of a Raytheon Beech Model 1900D airplane, which reveals that the elevator control system could be mis-rigged to restrict elevator travel if current maintenance procedures are not properly followed. In these instances, it may appear to the crew that they have full elevator control column movement. However, the elevator may not have full travel. Such restricted travel may remain undetected until the airplane is operated in a loading condition that requires full elevator authority to control the pitch. The actions specified by this AD are intended to detect and correct any mis-rigged elevator control system, which could lead to insufficient elevator control authority and loss of control of the airplane.
2002-04-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 series airplanes and A320-200 series airplanes, that requires repetitive inspections to detect loose or missing rivets in specified areas of the door frames of the overwing emergency exits and corrective action, if necessary. This AD also requires measurement of the grip length of all rivets in the specified areas and corrective action, if necessary, which terminates the repetitive inspections. This amendment is prompted by mandatory continuing airworthiness information from a foreign airworthiness authority. The actions specified by this AD are intended to detect and correct loose or missing rivets or discrepant rivets, which could lead to reduced structural integrity of the overwing emergency exit door frames. This action is intended to address the identified unsafe condition.
2006-07-12: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires a one-time inspection for scribe lines and cracks in the fuselage skin at certain lap joints, butt joints, external repair doublers, and other areas; and related investigative/ corrective actions if necessary. This AD results from reports of fuselage skin cracks adjacent to the skin lap joints on airplanes that had scribe lines. Scribe line damage can also occur at many other locations, including butt joints, external doublers, door scuff plates, the wing-to-body fairing, and areas of the fuselage where decals have been applied or removed. We are issuing this AD to prevent rapid decompression of the airplane due to fatigue cracks resulting from scribe lines on pressurized fuselage structure.
68-03-04: 68-03-04 VICKERS: Amendment 39-551. Applies to Viscount Models 744, 745D, and 810 Series airplanes. Compliance required as indicated, unless already accomplished To detect cracking of the upper and lower torsion link hinge pins of the nose landing gear, accomplish the following: (a) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with less than 4,000 landings on the effective date of this AD, before the accumulation of 5,000 landings, and thereafter at intervals not to exceed 1,000 landings from the last inspection until the accumulation of 10,000 landings and thereafter at intervals not to exceed 500 landings from the last inspection, comply with paragraph (d). (b) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with 4,000 or more landings but less than 9,000 landings on the effective date of this AD, within the next 1,000 landings after the effective date of this AD and thereafter at intervals not to exceed 1,000 landings from the last inspection until the accumulation of 10,000 landings and thereafter at intervals not to exceed 500 landings, comply with paragraph (d). (c) For airplanes with pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins with 9,000 or more landings on the effective date of this AD, within the next 500 landings or before the accumulation of 10,000 landings, whichever occurs later, and thereafter at intervals not to exceed 500 landings from the last inspection, comply with paragraph (d). (d) Remove pre Modification D.3045 (700 Series) and FG.1861 (800 Series) hinge pins and inspect for cracks using Magnaflux examination or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, in accordance with British Aircraft Corporation (BAC) Preliminary Technical Leaflets (PTLs) No. 233, Issue 3 (700 Series) and No. 99, Issue 3 (800 Series), or later ARB-approved issued, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (e) If cracked hinge pins are found during the inspections required by paragraphs (a), (b) and (c), before further flight, replace the pins with serviceable pins of the same part number and comply with the inspection requirements of paragraph (a), or replace the pins with Modification D.3045 (700 Series) and FG.1861 (800 Series) pins. (f) The repetitive inspections required by paragraphs (a), (b) and (c) may be discontinued on those hinge pins replaced by Modification D.3045 (700 Series) and FG.1861 (800 Series) pins. (g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. This amendment becomes effective March 7, 1968.
98-05-11: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-215-6B11 (CL-215T) series airplanes. This action requires either replacement of the switching valve-to-rear inlet case sealing air tube assembly with a tube assembly that includes an integral fire detector (intercompressor case [ICC] fire detector loop), and modification of the nacelle fire detection system; or modification of the No. 5 bearing air system. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect internal engine fire within the ICC; or to prevent air/oil from leaking into the ICC, which could result in such fire.
2020-07-11: The FAA is adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R(eacute)gional Model ATR42 airplanes and Model ATR72 airplanes. This AD was prompted by reports of interference and chafing between a propeller brake hydraulic pipe and an electrical wire bundle bracket screw installed in the underwing box of the right-hand (RH) engine nacelle. This AD requires modification of the electrical wiring routing in the engine nacelles, a one-time detailed visual inspection (DVI) of the propeller brake hydraulic pipe and electrical wire bundle bracket screw head in the underwing box of the RH engine nacelle and, depending on findings, accomplishment of applicable corrective actions, 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. \n\n((Page 20397))
2020-06-12: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332L2 and EC225LP helicopters. This AD requires determining the accumulated hours time-in-service (TIS) of certain part-numbered main gearbox (MGB) suspension bar attachment bolts and fittings, applying a life limit add-on factor, and inspecting the torque of certain MGB suspension bar attachment nuts. This AD was prompted by a report of torque loss on an MGB suspension bar bolt. The actions of this AD are intended to address an unsafe condition on these products.
99-16-05: This amendment adopts a new airworthiness directive (AD), applicable to Saab Model SAAB 2000 series airplanes, that requires repetitive inspections for excessive wear of the aileron control cables, cable guides, and cable pulleys located at the rear wing spars; and corrective actions, if necessary. This amendment also requires repetitive replacement of the control cables and cable guides with new or serviceable components. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness. The actions specified by this AD are intended to detect and correct excessive wear on the aileron control cables, cable guides, and cable pulleys located at the rear wing spars, which could result in broken aileron control cables and consequent reduced controllability of the airplane.
99-02-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models B300 and B300C airplanes (commonly referred to as Beech Models B300 and B300C airplanes). This AD requires modifying the elevator trim tab actuators by incorporating a new elevator trim tab actuator assembly kit, replacing the elevator trim tab pushrod assembly, or modifying the elevator spar opening, whichever is applicable. Reports from operators of ice forming on the elevator trim tab actuators and jamming the trim tab control prompted this action. The actions specified by this AD are intended to prevent jamming of the elevator trim tab actuator caused by ice formations, which could result in loss of control of the airplane.
2006-07-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318-100 and A319-100 series airplanes; Model A320-111 airplanes; and Model A320-200, A321-100, and A321-200 series airplanes. This AD requires repetitive detailed inspections of the trimmable horizontal stabilizer actuator (THSA) attachments for proper clearances, and any crack, damage, or metallic particles; related corrective actions if necessary; and a report of the inspection results to the manufacturer. This AD results from a report that during lab testing to verify the performance of the THSA's secondary load path with a simulated failure of the THSA's primary load path, the secondary load path's nut did not jam (as it was supposed to do). We are issuing this AD to ensure the integrity of the THSA's primary load path, which if failed, could result in latent (undetected) loading and eventual failure of the THSA's secondary load path and consequent uncontrolled movement of the horizontal stabilizer and loss of control of the airplane.
99-19-41: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires modification of the insulation pads in the lower side of the fuselage at the wing aft area. 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 loose insulation from interfering with an aileron control cable, which could result in reduced aileron control.
99-08-08: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires repetitive lubrication of the engine control push-pull cables, and installation of heating tubes on the control cables in the cockpit area and in the left-hand and right-hand engine balconies, which terminates the repetitive lubrication requirement. 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 ice from building up on the engine control push-pull cables, which could result in friction or jamming of the engine controls, and consequent reduced controllability of the airplane.
99-04-02: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model C-212 series airplanes, that requires repetitive visual inspections for damage or "electrical spark marks" on the cover plates for the fuel pumps, and corrective actions, if necessary. This AD also requires modification of the fuel pump installation by incorporating a non-conductive film on the cover plate, which constitutes terminating action for this AD. 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 shorting between the fuel pump electrical connections and the fuel pump cover plate, which could result in the ignition of fuel vapor and consequent fuel tank explosion/fire.
2006-07-11: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas airplanes identified above. This AD requires a one- time inspection of the aft attach fitting assembly of the spoiler link to determine the part number, and further investigative action and replacement of the assembly with a new or serviceable assembly, if necessary. This AD results from a determination that the holes of certain aft attach fitting assemblies of the spoiler link were not cold-worked during production. We are issuing this AD to prevent fatigue cracking of the aft attach fitting of the spoiler link and consequent failure of the fitting. Failure of the fitting could result in an asymmetrical lift condition and consequent reduced controllability of the airplane.
99-19-30: This amendment adopts a new airworthiness directive (AD) applicable to Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, B, and C helicopters. This action requires conducting a visual inspection to detect disbonding of the attachment angle between the tail gearbox forward fairing (fairing) and the pylon and replacing or repairing the attachment angles as necessary. This amendment is prompted by incidents, two in flight and eight on the ground, of fairing bonding failures. The actions specified in this AD are intended to prevent separation of the fairing, damage to the tail rotor blades, and subsequent loss of control of the helicopter.
98-06-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Aviation Model Mystere Falcon 900 series airplanes, that requires replacement of the water heater control relays with improved relays having high-power contactors; the addition of a testing and monitoring circuit for each contactor; and installation of improved electrical bonding of the potable water 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 overheating of the water heaters for the galley or the washbasin, which could result in damage to the water heater and nearby electrical wiring, and consequent smoke in the cabin.
2020-05-26: The FAA is adopting a new airworthiness directive (AD) for certain \n\n((Page 17481)) \n\nThe Boeing Company Model 787-8 airplanes. This AD was prompted by a report of failure of a wing strut leak test due to a missing bolt on the firewall. This AD requires a one-time leak test of the strut upper spar areas for the left and right wing struts, and corrective action if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
99-19-29: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires repetitive inspections of certain H-11 tension bolts at each side-of-body kick-load fitting and on the lower splice plate (both located on the wing rear spar) to detect damaged or broken bolts; and follow-on actions, if necessary. This amendment also requires eventual replacement of the existing bolts with new, improved bolts, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report that an operator found two broken H-11 tension bolts on the side-of-body kick-load fitting on one airplane. The actions specified by this AD are intended to prevent cracking of the bolts due to stress corrosion, which could result in reduced structural integrity of the wing-to-body joint structure.
87-04-09: 87-04-09 HELIO: Amendment 39-5533. Applies to Models H-700 and H-800 airplanes (all serial numbers) certificated in any category. Compliance: Required as indicated, unless already accomplished. To assure airworthiness of the composite main landing gear legs, accomplish the following: (a) Within the next 100 hours TIS after the effective date of this AD and each 100 hours TIS thereafter, remove landing gear fairings, if installed, and visually inspect the edges of the composite main landing gear legs for evidence of delamination. Delamination is evidenced by longitudinal splitting between the fiberglass plies. This could occur anywhere along the span of the landing gear leg. If any delamination is found, prior to further flight, install FAA-approved right and left metallic landing gear legs. NOTE: On the effective date of this AD, the only known FAA-approved replacement landing gear is per STC SA2171CE. (b) If, in between the inspections required in paragraph (a) above, it is observed that the wings do not appear level, or one side of the airplane appears to be drooping, prior to further flight, conduct the inspections and replacement, If necessary, required in paragraph (a) of this AD. (c) The inspection required in paragraphs (a) and (b) are no longer required when FAA-approved metallic landing gear legs have been installed. (d) Ferry permits issued in accordance with FAR 21.197 and equivalent methods of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Federal Aviation Administration, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on March 9, 1987.