Results
47-21-21: 47-21-21 REPUBLIC: (Was Service Note 1 of AD-769-2.) Applies to Model RC-3 Aircraft Serial Numbers 5 to 236, Inclusive. Inspection required immediately and periodically as noted below. Inspect two slots at upper end of each tip float strut (P/N 17W23001) very carefully for cracks. Slots are located inside of wing contour, therefore, struts must be removed from wing at upper attachment for proper inspection. If any cracks are present, strut shall be replaced prior to further operation. All struts without relief holes at ends of slots as recommended by manufacturer shall be inspected for cracks at 50-hour intervals. (Republic Seabee Service Bulletin No. 12 covers this same subject.)
47-06-10: 47-06-10 CESSNA: (Was Mandatory Note 6 of AD-768-4.) Applies to 120 and 140 Aircraft Serial Numbers Up to and Including 9669. Compliance required prior to April 1, 1947. Install carry-through bar between the ends of the aileron control chain that is installed at the top of the control "T" to make a continuous loop at this chain installation so that both control wheels operate positively in the same direction. This is necessary to prevent possible locking of aileron system at full throw. (Cessna Service Letter No. 17 dated September 19, 1946, covers this same subject.)
2003-01-01: This amendment supersedes Airworthiness Directive (AD) 2000- 26-16, which applies to certain Raytheon Aircraft Company (Raytheon) Beech Models A36, B36TC, and 58 airplanes. AD 2000-26-16 requires you to inspect for missing rivets on the right hand side of the fuselage and, if necessary, install rivets. AD 2000-26-16 resulted from Raytheon identifying several instances of missing rivets on these airplanes. AD 2000-26-16 incorporated an incorrect listing of serial numbers for the affected model airplanes and omitted certain airplane models from the applicability section of AD 2000-26-16. This AD retains the actions required in AD 2000-26-16 and corrects the applicability section. The actions specified by this AD are intended to detect and correct missing rivets in the right hand fuselage panel assembly in the area above the right wing and below the cabin door threshold. These rivets must be present for the fuselage to carry the ultimate load and prevent critical structural failure with loss of airplane control. DATES: This AD becomes effective on February 27, 2003. The Director of the Federal Register previously approved the incorporation by reference of Raytheon Mandatory Service Bulletin SB 53-3341, Rev. 1, Revised May, 2000, as of February 16, 2001 (66 FR 1253, January 8, 2001). The Director of the Federal Register approved the incorporation by reference of Raytheon Mandatory Service Bulletin SB 53-3341, Rev. 2, Revised October, 2002, as of February 27, 2003.
2015-22-51: We are publishing a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109A and A109AII helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires checking and inspecting each main rotor blade (blade) for a crack and replacing any cracked blade before further flight. This AD is prompted by abnormal vibrations leading to a precautionary landing and a post-flight inspection finding of a crack in a blade. These actions are intended to detect a crack in a blade and prevent failure of a blade and subsequent loss of control of the helicopter.
48-08-02: 48-08-02 AERONCA, CHAMPION AND SILVAIRE: Applies to all Aeronca 11 Series, Champion (Aeronca) 7 Series, and Silvaire (Luscombe) 8 Series Aircraft Equipped with Cleveland Model 6:00 DMB Wheels, Assembly No. C-38500. Compliance required after initial 500 hours of operation and each 100 hours of operation thereafter. Remove the tires and inspect the wheel flanges for fatigue cracks. The wheel should be replaced if cracks are found.
2016-02-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, and - 115 airplanes; Model A320-214 [[Page 4170]] airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. This AD was prompted by reports of cracked cadmium-plated lock nuts that attach the hinge to the fan cowl door. This AD requires inspecting to determine the serial number of each engine fan cowl door, inspecting for cracking of the hinge lock nuts of any affected door, and replacing the lock nuts if necessary. We are issuing this AD to detect and correct cracking of the hinge lock nuts, which could result in separation of the hinge from the fan cowl door, in-flight loss of the door, and consequent damage to the airplane.
2024-25-08: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 767-200, -300, and -300F airplanes. This AD was prompted by a report of a main landing gear (MLG) collapse event following maintenance where a grinder was operating outside of its input parameters, resulting in possible heat damage to the outer cylinder of the MLG. This AD requires replacing affected outer cylinders. The FAA is issuing this AD to address the unsafe condition on these products.
2024-25-07: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx- 1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx- 1B76A/P2, GEnx-2B67, GEnx-2B67B, and GEnx-2B67/P engines. This AD was prompted by a manufacturer evaluation that determined a lower life limit may be necessary for certain stages 6-10 compressor rotor spools than allowed by the engine shop manual (ESM). This AD requires a one- time inspection of the stages 6-10 spools for previously accomplished blend repairs, a one-time inspection of the blend repairs on the stages 6-10 spools for compliance with the updated allowable limits, and replacement if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2021-10-12: The FAA is superseding Airworthiness Directive (AD) 2020-09- 14, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2020-09-14 required revising the existing airplane flight manual (AFM) to define a liquid-prohibited zone on the flight deck and provide procedures following liquid spillage on the center pedestal. AD 2020-09-14 also required installing a removable integrated control panel (ICP) cover on the flight deck and further revising the AFM to include instructions for ICP cover use. This AD requires installing a new, water-resistant ICP, which allows removing the ICP protective cover and the AFM revisions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by development of a new, water-resistant ICP. The FAA is issuing this AD to address the unsafe condition on these products.
94-01-10 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain Boeing Model 757-200 and -200PF series airplanes, that currently requires inspections, adjustments, and functional checks of the engine thrust reverser system; and modification of the engine thrust reverser directional control valve. The existing AD also requires installation of an additional thrust reverser locking feature and periodic functional tests of the locking feature following installation. That AD was prompted by results of a safety review of the thrust reverser system on these airplanes. The actions specified by that AD are intended to prevent deployment of a thrust reverser in flight and subsequent reduced controllability of the airplane. This action reduces the applicability of the existing AD. \n\nDATES: Effective September 18, 2003.\n\n\tThe incorporation by reference of certain publications, as listed in the regulations, was approved by the Director of the Federal Register asof March 3, 1994 (59 FR 4558, February 1, 1994). The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of September 16, 1991 (56 FR 46725, September 16, 1991). (The document numbers of these certain publications were\ncited erroneously in the September 16, 1991, issue of the Federal Register, as listed in the regulations.)
47-41-06: 47-41-06 BELL: (Was Mandatory Note 18 of AD-1H-2.) Applies to All Models of 47B Series, Through Serial Number 71. Compliance required prior to next periodic inspection. The butt plate screws of the main rotor blade should be staked in accordance with Bell Service Bulletin 47C50 dated July 22, 1947, to prevent them from working loose in service.
94-14-10: 94-14-10 CURTISS-WRIGHT: Amendment 39-9471. Docket 94-ANE-36. Applicability: Curtiss-Wright R1820 series reciprocating engines, installed on the following U.S. registered aircraft: N313WB, N7044L, N815SH, and N83AW. NOTE: This airworthiness directive (AD) applies to each engine 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 engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (c) to request approval from the Federal Aviation Administration (FAA). This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configurationon the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any engine from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent detonation due to low octane, which can result in severe engine damage and subsequent failure, accomplish the following: (a) For engines that are certified to operate on only 91 or higher octane aviation gasoline (avgas) within the next 2 hours time in service (TIS) after the effective date of this airworthiness directive (AD) perform an engine teardown and analytical inspection, and replace with serviceable parts as necessary in accordance with the applicable overhaul manuals. (b) For engines that are certified to operate on 80 octane avgas, within the next 2 hours TIS after the effective date of this AD conduct a differential compression test on all cylinders in accordance with the applicable maintenance manuals, and examinethe oil filter by cutting the oil filter apart and spreading the filter paper out to look for metal particles. If metal particles are present, or if one or more cylinders shows unacceptable compression as specified in the applicable maintenance manuals, perform an engine teardown and analytical inspection, and replace with serviceable parts as necessary in accordance with the applicable overhaul manuals. NOTE: Additional guidance for conducting differential compression tests is contained in paragraph 692 of Advisory Circular (AC) No. 43.13-1A, dated 1988. (c) 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, Engine and Propeller Standards Staff. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Engine and Propeller Standards Staff. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine and Propeller Standards Staff. (d) 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 aircraft to a location where the requirements of this AD can be accomplished. (e) This amendment becomes effective February 13, 1996, to all persons except those persons to whom it was made immediately effective by priority letter AD 94-14-10, issued June 23, 1994, which contained the requirements of this amendment.
2016-01-11: We are superseding Airworthiness Directive (AD) 98-18-26, for certain Airbus Model A320 series airplanes. AD 98-18-26 required repetitive inspections to detect fatigue cracking of the front spar vertical stringers on the wings; and repair, if necessary. This new AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame 36, a rototest inspection for cracking of the fastener holes of the front spar vertical stringers on frame 36, and repair if necessary. This AD was prompted by reports that indicate new repetitive inspections having new thresholds and intervals are needed and that additional work is needed to accomplish the inspections on airplanes on which a previous modification has been accomplished. We are issuing this AD to detect and correct fatigue cracking of the front spar vertical stringers on the wings, which could result in the reduced structural integrity of the airframe.
48-50-01: 48-50-01 FRANKLIN: Applies to All Bellanca 14-13, 14-13-2 and Universal (Stinson) 108, 108-1 Aircraft Equipped With Franklin Model 6A4-150-B3 and B31 Engines With Serial Numbers 11000 to 14000 Inclusive. Compliance required after each 25 hours of operation. To prevent possible cylinder base flange failure, visual inspection for cracks just above the base flange should be made every 25 hours of operation on the early type cylinders until replaced by the later type cylinders. Early type cylinders have a flat section which extends 3/8 inch to 7/8 inch from the outer edge of the base flange. On later type cylinders the flat section has been practically eliminated by extending the ribbed section close to the edge of the flange. It is urgently recommended that early type cylinders be replaced at the earliest opportunity. (Franklin Service Bulletin No. 69 covers this same subject and offers special discounts effective through January 1949, for cylinder replacements). This supersedes AD 48-47-02.
2024-25-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-200, and CN-235-300 airplanes. This AD was prompted by a torn bulkhead seal found jamming the nose landing gear (NLG) emergency cable pulley. Due to the similarity of design, the main landing gear (MLG) emergency cable pulley could be exposed to the same failure mode. This AD requires repetitive inspections and corrective actions for damage of affected bulkhead seals and retainer rings, and repetitive replacement of affected parts, 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.
2024-25-03: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GVII-G500 and GVII-G600 airplanes. This AD was prompted by a report of cracking in the electrical grounding receptacles located on the left and right wings. This AD requires inspecting the electrical grounding receptacles for cracks and corrosion, performing applicable on-condition actions, and sealing over the grounding receptacles on the top of the wings to permanently disable the receptacle. The FAA is issuing this AD to address the unsafe condition on these products.
2009-02-10: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from 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 describes the unsafe condition as: Several reports have been received about roll control problems due to frozen moisture on the aileron pulleys that are located in the LH [left-hand] and RH [right-hand] Main Landing Gear (MLG) wheel bays on the centre wing rear spar, under the wing to fuselage fairings. Investigation revealed that improper sealing of the aerodynamic seals of the Wing-to-Fuselage Fairings can cause rain-or washwater and de-icing fluids to leak onto the affected aileron pulleys. Exposure of the aileron pulleys to the leaked moisture in freezing condition can result in restricted aileron control movement (partly jammed) and/or higher control forces. This condition,if not corrected, could lead to partial loss of control of the aircraft. * * ** * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective April 2, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 2, 2009. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of April 3, 2008 (73 FR 10650, February 28, 2008).
2016-01-14: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (AHD) (previously Eurocopter Deutschland GmbH) Model MBB-BK 117 A-1, A-3, A-4, B-1, B-2, C-1, and C-2 helicopters. This AD requires an initial and recurring inspection of the N2 control arm and, depending on the outcome of the inspection, repairing or replacing the N2 control arm. This AD was prompted by a report of a heavily corroded and broken N2 control arm. The actions of this AD are intended to detect corrosion, a crack, or a scratch in the N2 control arm, which could lead to failure of the N2 control arm, a drop in rotor speed, and subsequent loss of control of the helicopter.
98-12-22: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron Canada (BHTC) Model 407 helicopters that requires shimming the tail rotor drive system bearing supports (bearing supports). This amendment is prompted by reports of cracked bearing hangar support arms in the area of the fillet radius. The actions specified by this AD are intended to prevent failure of the bearing supports, which could result in excessive tail rotor drive system vibration, loss of tail rotor drive, and subsequent loss of control of the helicopter.
2002-26-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2C10 (Regional Jet Series 700 & 701) series airplanes. This action requires revising the airplane flight manual (AFM) to advise the flightcrew to limit use of the auxiliary power unit (APU) to ground operation only, except for those in-flight emergencies described in the AFM when use of the APU is specified. This action also provides for optional terminating action for the requirements of this AD. This action is necessary to prevent fuel from being sprayed throughout the APU compartment and drawn out of the APU exhaust duct due to a cracked APU fuel nozzle, which could result in a fire or explosion in the APU compartment during flight. This action is intended to address the identified unsafe condition.
47-33-03: 47-33-03 BEECH: (Was Mandatory Note 5 of AD-757-2 and Mandatory Note 4 of AD- 582-2.) Applies to AT-11 and C18S Aircraft. \n\n\tTo be accomplished prior to certification or, if certificated, on next periodic inspection but not later than November 1, 1947. \n\n\tIn order to provide better tail cone drainage, add two drain holes in the tail cone and two 1/4-inch drain holes in the fuselage bulkhead No. 15 as shown in Figure 2. \n\n\n\n\n\t(Beech Service Bulletin No. C18-7 covers this same subject.)
2024-25-02: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) Model LEAP-1B engines. This AD was prompted by a report of a quality escape involving certain high- pressure compressor (HPC) stage 2 seals manufactured without detailed finish machining, which could result in deeper rubs and mechanical damage to the seal teeth of the stage 3-4 compressor rotor blisk (stage 3-4 blisk) of the mating compressor rotor during initial operation. This AD requires a visual inspection of the HPC stage 2 seal, a visual inspection of the forward arm seal teeth of the stage 3-4 blisk, an eddy current inspection (ECI) of the forward arm seal teeth of the stage 3-4 blisk, and replacement of the HPC stage 2 seal and the stage 3-4 blisk, if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2016-01-12: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of fluid entry and accumulation in the aft equipment bay. This AD requires modifying the aft equipment bay. We are issuing this AD to prevent excessive quantities of flammable fluid accumulation in the aft equipment bay. Flammable fluid entry and accumulation in the aft equipment bay, in excessive quantities, could exceed safe levels maintained by the drainage and ventilation system.
98-04-31: This amendment adopts a new airworthiness directive (AD), applicable to all Fairchild Model F27 and FH227 series airplanes, that requires revising the Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2002-24-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-24-51 that was sent previously to all known U.S. owners and operators of the airplane models described previously by individual notices. This AD requires revising the Airplane Flight Manual to require the flightcrew to maintain certain minimum fuel levels in the center fuel tanks and, for certain airplanes, to prohibit the use of the horizontal stabilizer fuel tank and the certain center auxiliary fuel tanks. This action is prompted by reports indicating that two fuel tank pumps showed evidence of extreme localized overheating of parts in the priming and vapor pump section of the fuel pump; such overheating provides an ignition source in the fuel tank during dry running of the pump, which could result in fire/explosion of the fuel tank. The actions specified by this AD are intended to require the flightcrew to maintain certain minimum fuel levels in the center fuel tanks and, for certain airplanes and, for certain airplanes to prohibit the use of the horizontal stabilizer fuel tank and certain center auxiliary fuel tanks.