Results
2016-07-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of cracking of the aft fixed fairing (AFF) of the pylons due to fatigue damage of the structure. This AD requires repetitive inspections for damage and cracking of the AFF of the pylons, and repair if necessary. We are issuing this AD to detect and correct damage and cracking of the AFF of the pylons, which could result in detachment of a pylon and consequent reduced structural integrity of the airplane.
2024-22-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model Airbus A350-941 and -1041 airplanes. This AD was prompted by a determination that the lower attachment studs on the aft galley complex may be installed incorrectly due to a missing instruction in the maintenance procedure task. This AD requires a one- time inspection of the lower attachment studs on the aft galley complex, 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.
47-10-05: 47-10-05 LOCKHEED: (Was Mandatory Note 6 of AD-763-3.) Applies Only to Model 49 Serial Numbers 2021 to 2088, Inclusive. Compliance required prior to March 15, 1947. Inspect landing gear selector valve (Bendix P/N 403875-0-1) installed in forward cargo compartment. Those valves bearing Serial Numbers 1 through 120 and identified by letter "R: following the serial number have been reworked to incorporate a new type poppet. All unreworked valves should be replaced with reworked valves. (LAC Service Instruction 049/SI-34 covers this same subject.)
51-10-06: 51-10-06 CURTISS-WRIGHT Applies to all model C-46 Series aircraft. Compliance required at next periodic inspection, not to exceed 100 hours, and each 200 hours or nearest regular inspection period thereafter. Inspect all aileron, rudder and elevator hinge fittings and adjacent structure for cracks, loose rivets, worn bolts and condition of bearings. If defects are found, the part should be replaced by an undamaged part or repaired. This supersedes AD 50-14-1.
73-12-05: 73-12-05 FAIRCHILD: Amendment 39-1656 as amended by Amendment 39-2078 is further amended by Amendment 39-3543. Applies to all Fairchild F-27 and FH-227 Type Aircraft Certificated in all categories. Compliance required as indicated: 1. As to the vertical stabilizer attachment fitting assemblies for both front and rear spars, P/N's 27-233000-11, -12, -31, -32, -41 and -42 which have accumulated 2500 hours or more in service. a. Within the next 30 days, unless accomplished within the last 11 months, inspect all surfaces of the lugs of the fittings for cracks using an ultrasonic method in accordance with paragraph 2, Accomplishment Instructions, Part I, of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or an approved equivalent inspection. Inspect other areas of the fittings for cracks using a dye penetrant and a 10-power glass or an approved equivalent inspection. b. Within the next 60 days, unless accomplished within the last 10 months, inspect the fittings around the flanges and inner cavity for corrosion in accordance with paragraph 2, Accomplishment Instructions, Part II, of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or in accordance with an approved equivalent procedure. c. The inspection specified in "a" above shall be repeated at intervals not to exceed 12 calendar months or 2500 hours in service from the last inspection, whichever occurs first. d. The inspection specified in "b" above shall be repeated at intervals not to exceed 12 calendar months from the last inspection. 2. Cracked parts shall be replaced and corroded parts shall be replaced or repaired prior to further flight. a. Parts replacement shall be in accordance with paragraph 2 of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, and they shall be the same part number or approved equivalent parts. b. Parts repair shall be in accordancewith paragraph 2 and Figures 2 and 3 of Fairchild Service Bulletins F-27-55-20 and FH-227-55-11, reissued June 15, 1979, or an approved equivalent repair. 3. The aircraft may be flown in accordance with FAR 21.197 to a base where the inspection or repairs can be performed. 4. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection interval specified in this AD. Equivalent inspections, parts or repair must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Amendment 39-1656 was effective June 14, 1973. Amendment 39-2078 was effective January 28, 1975. This Amendment 39-3543 is effective August 29, 1979.
2016-07-08: We are adopting a new airworthiness directive (AD) for a certain The Boeing Company Model DC-9-83 (MD-83) airplane. This AD requires installing fuel level float and pressure switch in-line fuses, and doing applicable wiring changes, on the left, right, and center wing forward spars, forward auxiliary fuel tank, and aft auxiliary fuel tank. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
66-16-02: 66-16-02 BRITISH AIRCRAFT CORPORATION: Amdt. 39-254 Federal Register July 1, 1966. Applies to Model BAC 1-11 200 Series Airplanes. Compliance required before the accumulation of 3,000 hours' time in service for airplanes with less than 2,900 hours' time in service on the effective date of this AD and within the next 100 hours' time in service after the effective date of this AD for airplanes with 2,900 or more hours' time in service on the effective date of this AD unless already accomplished. To prevent chafing of the fuselage frame forward flange by the aft end of the headliner, rework the headliner, P/N AB77 A1605, and inspect the flange of fuselage frame, P/N AB29 A501, and rework as necessary in accordance with British Aircraft Corporation (BAC) One- Eleven Alert Service Bulletin 53-A-PM 2107, dated February 1, 1966, or later ARB-approved issue. This directive effective July 31, 1966.
73-16-05: 73-16-05 PRATT & WHITNEY: Amdt. 39-1698. Applies to all Pratt and Whitney Aircraft JT9D turbofan engines containing fourth and fifth stage turbine discs, P/N 646304, 694804, 618305, and 705905. Compliance required as indicated. To prevent possible failure of fourth and fifth stage turbine discs, the life limits on these parts have been reduced below the figures currently approved. Unless already accomplished, remove from service fourth and fifth stage turbine discs prior to reaching the revised life limit listed below or within the next 25 cycles in service after the effective date of this airworthiness directive whichever comes later. Disc Part Number Previous Life Limit Cycles Revised Life Limit Cycles 646304 8000 4000 694804 8000 4000 618305 8000 4000 705905 8000 4000 (Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance time). NOTE: (Pratt and Whitney Service Bulletin No. 3785 pertains to this subject). This amendment becomes effective August 15, 1973.
2016-07-04: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report that, during the assembly process, several gaps between the two parts of the girt bar fittings for the aft passenger doors were found to exceed tolerances. This AD requires an inspection of the gap between the two parts of the girt bar fittings on left-hand (LH) and right-hand (RH) aft passenger doors, and corrective actions if necessary. We are issuing this AD to detect and correct incorrect gaps between the girt bar fittings. Detachment of a girt bar could lead to the separation of the slide or slide-raft from the fuselage, making the emergency exit inoperative, which could impede an emergency evacuation.
71-16-01: 71-16-01 de HAVILLAND AIRCRAFT of CANADA LTD: Amdt. 39-1250. Applies to de Havilland Type DHC-6 Aircraft, Serial Numbers 1 through 299, inclusive. Compliance required, unless already accomplished, within 30 days after the effective date of this AD for aircraft which have been in service for 12 months or more from the date of first flight. For aircraft which have been in service less than 12 months, compliance required within 30 days after the accumulation of 12 months' service. To preclude the possibility of engine flameout due to fuel starvation in the event of separation of the flapper valve seal in fuel cells No. 4 and No. 5, replace No. 4 and No. 5 flapper valve assemblies, P/N C6PF1026-3, with new like parts and repeat replacement thereafter at 12- month intervals until such time as DHC modifications 6/1406 is incorporated in accordance with instructions contained in DHC Service Bulletin No. 6/269, dated February 19, 1971, or an equivalent modification approved bythe Chief, Engineering & Manufacturing Branch, Federal Aviation Administration, Eastern Region. This amendment is effective August 3, 1971.
2003-11-24: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-100 series airplanes. This action requires installation of retainers instead of washers in the upper and lower torsion bars of the rudder tab. This action is necessary to prevent a spring tab torsion bar from slipping through its retaining adapters, which could result in a loose spring tab; the loss of both tension springs could allow the spring tab to flutter and result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
48-13-01: 48-13-01 BEECH: Applies to All D18S, D18C Airplanes Equipped With Pilot's Reclining Seats and Having the Generator Control Box Mounted on Bulkhead No. 5. To be accomplished not later than July 1, 1948. To prevent a short circuit between the hot terminal of the generator control box and bulkhead No. 5, rivet a 0.016 phenolic sheet 13/4 x 3 inches between the bulkhead web and the first horizontal angle immediately above the generator control box. The sheet should extend downward from the angle to the web cutout and provide positive insulation between the web and the hot post of the generator control box. If a phenolic strip has previously been installed at this point, an additional strip will not be necessary. (Beech Service Letter No. D18-23 covers this same subject.)
2003-16-18: The FAA is adopting a new airworthiness directive (AD) that applies to Rolls-Royce plc (RR) RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with intermediate pressure (IP) turbine discs, part numbers (P/Ns) FK21117 and FK33083 installed. This AD requires removal from service of these IP turbine discs based on newly established reduced turbine disc life limits. This AD is prompted by reports of two IP turbine blade release incidents as a result of dust caps separating from the blades and subsequent improved modeling analysis. We are issuing this AD to prevent uncontained IP turbine disc failure and damage to the airplane.
71-06-05: 71-06-05 ROLLS-ROYCE: Amdt. 39-1172. Applies to Rolls-Royce Dart engine models 506, 510, 511, 511-7E, 514, and 514-7 installed on, but not necessarily limited to British Aircraft Corporation Viscount 744 and 745D; Fairchild F-27 and F-27B; and Fokker F-27 airplanes. Compliance is required as indicated, unless already accomplished. (a) For all engines installed on airplanes having an average daily utilization rate of more than three hours flight time per day, comply with paragraph (c) within the next 4,000 hours' time in service after the effective date of this AD, or at the next engine overhaul, whichever occurs first. (b) For all engines installed on airplanes having an average daily utilization rate of three hours flight time or less per day, comply with paragraph (c) within the next 2,000 hours' time in service after the effective date of this AD, or at the next engine overhaul, whichever occurs first. (c) Replace Rolls-Royce turbine disc retaining bolt P/N RK 33044 with P/N RK 43376 in accordance with Rolls-Royce Dart Aero Engine Service Bulletin Number Da 72-347, Revision 2, dated July 24, 1970, or later ARB-approved revision, or an FAA-approved equivalent. (d) For the purpose of complying with this AD, the average daily utilization rate shall be determined on the basis of the average daily utilization rate for the 12-month period immediately preceding the effective date of this AD. This amendment becomes effective April 12, 1971.
2003-16-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes, and Airbus Model A310 series airplanes. This AD requires replacement of Honeywell inertial reference units (IRU) with new or modified Honeywell IRUs. For certain airplanes, this proposal also would require replacement of Litton IRUs, mode selector units (MSU), and an inertial sensor display unit (ISDU) with new Honeywell IRUs, MSUs, and a new ISDU. This action is necessary to prevent loss of positioning data and a display of incorrect attitude data, which could compromise the ability of the flightcrew to maintain the safe flight and landing of the airplane. This action is intended to address the identified unsafe condition.
2003-11-23: The FAA is adopting a new airworthiness directive (AD) for certain IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan engines. This AD requires initial and repetitive inspections of the master magnetic chip detector (MCD) or the No. 1, 2, 3 bearing chamber MCD. This AD is prompted by reports of No. 3 bearing failures that resulted in in-flight engine shutdowns (IFSDs) and significant smoke in the cockpit and cabin. The actions specified in this AD are intended to prevent failure of the No. 3 bearing, which could result in IFSDs and smoke in the cockpit and cabin.
2024-24-02: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. (Safran) Model ARRIUS 2F engines. This AD was prompted by a report of an uncommanded in-flight shut-down (IFSD) of a Safran Model ARRIUS 2F engine, followed by an investigation that revealed the IFSD was due to a missing lubricating and balancing groove on one of the bearings of the fuel control unit (FCU) fuel pump related to a non-conforming manufacturing process. This AD requires removal of the affected fuel pump from service and replacement with a serviceable part, 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.
2016-07-11: We are adopting a new airworthiness directive (AD) for all Weatherly Aircraft Company Models 201, 201A, 201B, 201C, 620, 620A, 620B, 620B-TG, and 620TP airplanes. This AD requires visually inspecting the center and outer wing front spar lower hinge fittings for cracks and corrosion [[Page 18462]] and taking all necessary corrective actions. This AD also requires sending the inspection results to the FAA. This AD was prompted by a report of cracks found on the center wing front spar lower hinge fitting. We are issuing this AD to correct the unsafe condition on these products.
70-10-06: 70-10-06 CESSNA: Amendment 39-990 as amended by Amendment 39-1008. Applies to Models 172I (Serial Numbers 17256513 through 17257161) and 172K (Serial Numbers 17256493, and 17257162 through 17259043) Airplanes. Compliance: Required as indicated, unless already accomplished. To prevent the loss of engine oil caused by failure of the metal oil pressure instrument line, accomplish the following: Within 50 hours' time in service from June 1, 1970, but by no later than June 30, 1970, replace the metal oil pressure instrument line between the engine and the firewall with a flexible hose assembly in accordance with the instructions contained in Cessna Service Letter No. SE70-10, dated May 5, 1970, or Cessna Service Letter No. SE70-10, Supplement No. 1, dated June 9, 1970, or any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-990 effective May 19, 1970. This amendment becomes effective upon publication in the FEDERAL REGISTER.
2008-26-06: The FAA is superseding emergency airworthiness directive (AD) 2008-19-51 that we sent previously to all known U.S. owners and operators of RRC AE 3007A series turbofan engines. That AD requires performing initial and repetitive eddy current inspections (ECIs) on the high-pressure turbine (HPT) stage 2 wheel for cracks. This AD continues to require those same inspections, but revises the compliance schedule for the initial inspection and specifies the affected HPT stage 2 wheels by part number (P/N). This AD results from reports of cracked HPT stage 2 wheels. We are issuing this AD to detect cracks in the HPT stage 2 wheel, which could result in a possible uncontained failure of the HPT stage 2 wheel and damage to the airplane.
2016-07-06: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This AD was prompted by reports of cracking of the main fitting of the nose landing gear (NLG) and a determination that a new safe-life limitation for affected NLG main fittings has not been mandated. This AD requires replacing affected NLG main fittings that have exceeded the safe-life limitation with a new or serviceable fitting. We are issuing this AD to prevent collapse of the NLG, which if not corrected, could lead to degradation of direction control on the ground or an un-commanded turn to the left, and a consequent loss of control of the airplane on the ground, possibly resulting in damage to the airplane and injury to occupants.
54-25-02: 54-25-02 WRIGHT: Applies to All Models 975C18CB1, 972TC18DA1, and 972TC18DA2 Engines. Compliance required as indicated. I. Compliance required by November 1, 1955. To alleviate front intermediate cam drive gear failures and associated possible engine overspeeding, the following intermediate cam drive gears must be removed from the front cam drive gear train: P/N's 138608, 138608 N, 171385, 171238, or 171387. These gears may still be used in the rear cam drive configuration. Intermediate cam drive gears incorporating increased tooth width and thick hubs must be used in the front cam drive configuration. The following gears comply with this requirement: P/N's 171347, 171348, or 171994. II. Compliance required at next and each subsequent overhaul. To insure proper assembly of cam drive gear configurations, the following assembly instructions must be followed and applicable measurements recorded on engine build up sheets: TC18DA Overhaul Manual:Section V. Instruction 17. Section VIII. Instruction No. 2 plus referenced Table of Limits fits including Reference No. 238. (Wright Aeronautical Division Service Bulletins Numbers C18C-83 and TC18-92 cover these same subjects.)
2024-19-15: The FAA is superseding Airworthiness Directive (AD) 2023-13- 11, which applied to certain AVOX Systems Inc. (formerly Scott Aviation) oxygen cylinder and valve assemblies, and oxygen valve assemblies, installed on but not limited to various transport airplanes. AD 2023-13-11 required inspecting the oxygen valve assemblies, and oxygen cylinder and valve assemblies, to determine the serial number of the valve, cylinder, and entire assembly; inspecting certain assemblies and parts for correct spacing of the gap between the bottom of the packing retainer and top of the valve body on the assemblies, and replacing assemblies having unacceptable gaps. AD 2023- 13-11 also limited the installation of affected parts and required reporting inspection results and returning certain assemblies to the manufacturer. This AD was prompted by the determination that additional assemblies and parts are subject to the unsafe condition. This AD requires the actions specified in AD 2023-13-11 and expands the list of affected assemblies and parts. The FAA is issuing this AD to address the unsafe condition on these products.
2016-07-02: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. (Honeywell) TFE731-4, -4R, -5AR, -5BR, and -5R turbofan engines. This AD was prompted by a report of certain interstage turbine transition (ITT) ducts failing to meet containment capability requirements. This AD requires replacing certain ITT ducts. We are issuing this AD to prevent failure of the ITT duct, which could lead to an uncontained part release, damage to the engine, and damage to the airplane.
2024-18-06: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by reports that the pivot door pressure seals on the thrust reverser fixed structure were found disbonded or missing on several airplanes. This AD requires inspecting the pivot door pressure seals and accomplishing applicable corrective actions. This AD also requires a functional test of the thrust reversers. The FAA is issuing this AD to address the unsafe condition on these products.