Results
2003-13-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Iniziative Industriali Italiane S.p.A. (3I) Models Sky Arrow 650 TC and 650 TCN airplanes. This AD requires you to modify the nose gear support bulkhead (STA600). This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent failure of the nose gear support bulkhead (STA600). Such failure could lead to loss of control of the airplane during landing or take-off.
2018-07-11: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by interference between certain passenger service unit (PSU) panels, when in the deployed/open position, and the nearby emergency exit door cover. We are issuing this AD to address the unsafe condition on these products.
2013-22-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes; and Model DHC-8-200, -300, and -400 series airplanes. This AD was prompted by reports of excessive wear found in the clevis (bolt) hole where the rod assembly attaches to the rudder/brake pedal bellcrank, due to prolonged fretting. This AD requires measuring the bellcrank clevis holes, inspecting for cracking of the bellcrank, and re-working the clevis holes with steel bushings, or replacing the bellcrank. We are issuing this AD to detect and correct a worn or cracked clevis hole, which could cause failure of the bellcrank on one side, with subsequent asymmetric braking and consequent runway excursion.
97-15-09: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 757 and 767 series airplanes. This action requires repetitive inspections to detect damage and to verify proper configuration of the battery ground terminations of the auxiliary power unit (APU) at the battery and connected structure; and removal, replacement, and repair of the battery ground termination, if necessary. This amendment is prompted by reports of smoke or fire coming from the APU due to battery grounds that were not installed/maintained properly. The actions specified in this AD are intended to detect and correct such APU battery grounds, which could result in heat damage and consequent smoke/fire on the airplane.
2003-13-02: This amendment adopts a new airworthiness directive (AD), applicable to all Model A321-131 series airplanes, equipped with International Aero Engines (IAE) V25()()-A5 series engines. This action requires revising the Limitations section of the airplane flight manual to incorporate new procedures to follow in the event of an oil filter clog message. This action is necessary to require the flightcrew to follow the procedures necessary to prevent smoke caused by an oil filter clog from entering the cabin during flight. This action is intended to address the identified unsafe condition.
2021-10-28: The FAA is adopting a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition \n\n((Page 30764)) \n\non an aviation product. The MCAI identifies the unsafe condition as the need to revise certain airworthiness limitations and certification maintenance instructions. The FAA is issuing this AD to address the unsafe condition on these products.
2000-02-16: This amendment adopts a new airworthiness directive (AD) that applies to all Short Brothers and Harland Ltd. (Shorts) Models SC-7 Series 2 and SC-7 Series 3 airplanes. This AD requires you to repetitively inspect the wing attachment bushes in the fuselage front and rear spar frames for migration (gaps), and replace the bushes if a gap exists that is of a certain length or more. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and correct migration of the wing attachment bushes in the fuselage front and rear spar frames, which could result in structural damage to the wing spar/fuselage fitting with possible loss of control of the airplane.
2003-12-12: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires either revising the Airplane Flight Manual (AFM) to require a maximum operating altitude of 25,000 feet; or modifying the flight attendant's seat or reworking the oxygen bottle kit, as applicable, and revising the AFM to require a maximum operating altitude of 30,000 feet. This action is necessary to prevent the unavailability of supplemental oxygen to the flight attendant in the event of cabin decompression, which could result in loss of consciousness of the flight attendant. This action is intended to address the identified unsafe condition.
2013-20-05: We are adopting a new airworthiness directive (AD) for certain Bell Model 407 helicopters. This AD requires installing a placard beneath the NR/NP dual tachometer and revising the limitations section of the rotorcraft flight manual (RFM). This AD was prompted by several incidents of third stage engine turbine wheel failures, which were caused by excessive vibrations at certain engine speeds during steady- state operations. These actions are intended to alert pilots to avoid certain engine speeds during steady-state operations, prevent failure of the third stage engine turbine, engine power loss, and subsequent loss of control of the helicopter.
2013-20-03: We are adopting a new airworthiness directive (AD) for certain Bell Model 430 helicopters. This AD requires installing a placard on the instrument panel and revising the limitations section of the rotorcraft flight manual (RFM). This AD was prompted by several incidents of third stage engine turbine wheel failures, which were caused by excessive vibrations at certain engine speeds during steady- state operations. These actions are intended to alert pilots to avoid certain engine speeds during steady-state operations, prevent failure of the third stage engine turbine, engine power loss, and subsequent loss of control of the helicopter.
2000-23-19: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that currently requires inspections to detect damage or cracking of the forward and aft attachment lugs of the flap fittings at wing station (WS) 123.38; an inspection to verify that the sizes of the holes of the flap fittings are within specified limits and to ensure that the swaged bushings are not loose; and modification of the flap fittings. This amendment requires repetitive accomplishment of the inspections using improved inspection methods; a one-time visual and repetitive general visual and detailed visual inspections; new repetitive non-destructive test (NDT) inspections; and corrective and follow-on actions, as necessary. This amendment also provides for terminating action for all repetitive inspections and revises the applicability of the existing AD. The actions specified by this AD are intended to prevent high bearingstress on the bushings of the flap fittings, which could result in wear on the bushings, cracking of the flap fittings, and breakage of the lugs; these conditions could result in jamming of the flaps and consequent reduced controllability of the airplane.
46-23-06: 46-23-06 NOORDUYN: (Was Mandatory Note 2 of AD-2-578-1.) Applies Only to Army UC-64, -64A, and -64B Airplanes Equipped With Fuel-Burning Cabin Heaters. Required at next periodic inspection. The surface combustion fuel burning heater must be made inoperative by disconnecting and plugging the fuel line as near the engine as practicable unless the following modifications are accomplished: (a) At fire resistant bulkhead must be installed between the heater and the belly fuel tank. A firewall having the fire-resistant qualities specified in CAR 3.624 will be acceptable. (b) A fuel shutoff valve, controllable from the pilots' compartment must be installed in the fuel line between the engine and the heater. (c) Shrouds must be installed on the heater exhaust and drain lines to isolate the lines from the airframe.
2013-19-24: We are superseding Airworthiness Directive (AD) 2003-08-51 for MD Helicopters, Inc. (MDHI), Model 369A, 369D, 369E, 369H, 369HE, 369HM, 369HS, 369F and 369FF helicopters with certain MDHI or Helicopter Technology Company (HTC) tail rotor blades installed. AD 2003-08-51 required reducing the retirement life of each tail rotor blade (blade), performing a one-time visual inspection of each blade's pitch horn (pitch horn) for a crack or corrosion, and replacing any cracked blade or any blade that has exceeded its retirement life with an [[Page 65181]] airworthy blade. AD 2003-08-51 also required reporting information to the FAA within 24 hours following the one-time inspection. Since we issued AD 2003-08-51, an accident in England prompted an investigation that showed corrosion on the blade's pitch horn that had not been detected under the paint. This new AD retains some of the requirements of AD 2003-08-51 and also requires paint removal for all pitch horn inspections, inspecting for pitting and the shot peen surface's condition in addition to cracks and corrosion, and adds certain part- numbered blades to the applicability. These actions are intended to prevent a pitch horn from cracking, leading to vibration, loss of tail rotor pitch control, and subsequent loss of tail rotor and helicopter control.
75-07-04: 75-07-04 GRUMMAN AMERICAN: Amendment 39-2135. Pursuant to the authority of the Federal Aviation Act of 1958 delegated to me by the Administrator, the following Airworthiness Directive is issued applicable to operators of Grumman American AA-1, AA-1A, AA-1B, AA-5 and AA-5B airplanes delivered prior to February 18, 1975 and certified in all categories. The directive requires an inspection prior to further flight, unless already accomplished, and is effective immediately upon receipt of the Airworthiness Directive because there may be missing welds in the rudder control bar assemblies P/N 601031-501 located inside the forward portion of the fuselage. Before further flight, unless already accomplished, inspect Grumman American Model AA-1, AA-1A, AA-1B, AA-5 and AA-5B airplanes certified in all categories for missing welds in the rudder control bar assemblies P/N 601031-501. 1. Inspect the rudder pedal posts and rudder cable attaching arm inserted through the rudder torque tube bar for missing welds. At each intersection, there should be a minimum of two (2) 90 degree circumferential welds located both top and bottom (fore and aft) at the intersection of each tube. 2. If inspection reveals that there are no missing welds, no further action is required and the aircraft may be approved for return to service. 3. If inspection reveals missing welds, replace rudder control bar assembly P/N 601031-501 with a new part of the same part number. 4. If parts are unavailable, repair may be accomplished by contacting the local FAA Maintenance Inspector concerning a repair procedure which must be approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. 5. A special flight permit per FAR 21.197 may be issued after accomplishment of Paragraph 1 to allow repairs in accordance with this Airworthiness Directive. This amendment is effective upon publication in the Federal Register and was effective prior to further flightfor all recipients of the air mail letters dated March 6, 1975 which contained this amendment.
2013-20-04: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that certain special washers used in the bearing installation of the retraction jack anchorage fitting in the main landing gear (MLG) were incorrectly manufactured. This AD requires an inspection of the left-hand (LH) and right-hand (RH) bearing assemblies of the MLG retraction jack anchorage fitting to verify that the special washer is seated correctly, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct installation of incorrectly manufactured special washers, which could lead to a local stress concentration resulting in possible reduction of the fatigue life of the jack fitting, and consequent reduction of the structural integrity of the affected MLG.
2013-22-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by reports of airspeed mismatch between the pilot and co-pilot's airspeed indicators, which occurred during or after heavy rain. This AD requires, for certain airplanes, inspecting for drain bottles having certain part numbers, and replacing affected drain bottles. This AD requires, for certain other airplanes, replacing drain bottles. We are issuing this AD to prevent pitot static tubing from becoming blocked by water, which if not corrected, could lead to erroneous airspeed and altitude indications, and consequent loss of control of the airplane.
2013-22-08: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes. This AD was prompted by a report of a cracked pick-up bracket of the forward outboard pylon of the number 1 engine due to stress corrosion. This AD requires repetitive inspections and, depending on findings, repair of the pylon pick-up brackets. We are issuing this AD to detect and correct cracking of the pick-up bracket, which could result in the engine pylon separating from the wing, with consequent damage to the airplane and reduced controllability.
75-16-16: 75-16-16 ISRAEL AIRCRAFT INDUSTRIES, LTD: Amendment 39-2290. Applies to Israel Aircraft Industries Jet Commander Models 1121, 1121A and 1121B, and Westwind Model 1123 airplanes certificated in all categories having autopilot vertical reference component Collins P/N 332D-11/522-3985-001 or Collins P/N 332D-11A/792-6694-001 or both, installed in an unpressurized area. Compliance is required as indicated unless already accomplished. To prevent loss of attitude information and improper operation of the autopilot, accomplish the following: (a) Before further IFR or night flight, install a placard on the instrument panel in full view of the pilot to read, "Cross Check Attitude Indicators with Third Attitude Indicator to Detect Unflagged Failures". (b) Within the next 100 hours' time in service, after the effective date of this AD, modify the vertical reference (Collins P/N 332D-11/522-3985-001, or Collins P/N 332D-11A/ 792-6694-001), in accordance with Collins ServiceBulletin No. 9, dated May 1, l974, or an FAA-approved equivalent. (c) The placard required by paragraph (a) of this AD may be removed when the modification required by paragraph (b) has been accomplished. This amendment becomes effective August 12, 1975.
2000-22-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain International Aero Engines AG (IAE) V2500-A5 and -D5 series turbofan engines, identified by serial number. This amendment requires the removal of engines assembled with an improper High Pressure Turbine (HPT) module configuration from service prior to accumulating 5,100 or 7,600 cycles in the improper configuration, or at the next shop visit, depending on the type of improper HPT configuration, and restoration to type design. This amendment is prompted by reports of engines that do not conform to the engine type design, which could cause a Low Cycle Fatigue (LCF) life reduction of the HPT stage 1 disk. The actions specified by this AD are intended to restore engines to type design configuration and to prevent possible LCF failure of the HPT stage 1 disk, which could result in an uncontained engine failure and damage to the airplane.
2013-20-11: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that oxygen generators installed on a certain batch of passenger emergency oxygen container assemblies might become detached by extreme pulling of the mask tube at the end of the oxygen supply causing a high temperature oxygen generator and mask to fall down. This AD requires modifying the passenger emergency oxygen container assembly. We are issuing this AD to prevent a high temperature oxygen generator and mask from falling down and possibly resulting in an ignition source in the passenger compartment, injury to passengers, and reduced availability of supplemental oxygen.
74-18-01: 74-18-01 MCDONNELL DOUGLAS: Amendment 39-1927 as amended by Amendment 39-2533. Applies to all Douglas Aircraft Company DC-10-10/-30/-40 Series airplanes which incorporate Douglas DC-10 Service Bulletin 21-68 or Service Change 1545 when inertial navigation systems are installed. \n\n\tCompliance required as indicated, unless previously accomplished. \n\n\tWithin 300 additional hours time in service after the effective date of this AD, either \n\n\t(1)\tIncorporate in the FAA-approved Airplane Flight Manual, Documents MDC-J1010, MDC-J1030, MDC-J5830, MDC-J1040, and Appendix X of MDC-J1010, the following revision in Section I, Limitations, under the existing heading 'Cabin Pressurization': \n\n\t'For the inertial platform configured airplanes, temporary installation of wiring per Douglas Drawing WBP 9502 must be accomplished for planned unpressurized flight'; or \n\n\t(2)\tIncorporate other airplane flight manual revisions, and/or equipment modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tAmendment 39-1927 became effective August 26, 1974. \n\n\tThis amendment 39-2533 becomes effective March 8, 1976.
52-04-01: 52-04-01: MARTIN: Applies to All Models 202 Aircraft. Compliance required not later than May 1, 1952. Provide adequate drain for throttling valve vent in the cabin heater fuel supply line.
2025-06-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. This AD was prompted by a design review that discovered software protection logic for potential large leaks from the engine bleed duct inside the engine core compartments was partially impaired. This AD requires revising the existing airplane flight manual (AFM) to incorporate the procedures for the flightcrew to manually isolate the opposite functional engine in the event of an engine bleed duct large leak condition, as specified in a Transport Canada AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2013-20-14: We are adopting a new airworthiness directive (AD) for certain the Boeing Company Model 747-400 and -400F series airplanes. This AD was prompted by a report of cracks on airplanes prior to line number 1308 in the forward and aft inner chords of the station (STA) 2598 bulkhead, and the bulkhead upper and lower webs. This AD requires, as applicable, repetitive high frequency eddy current (HFEC) and low frequency eddy current (LFEC) inspections for cracks in the splice fitting, support frame, forward and aft inner chords, floor support, bulkhead upper web on the upper left and right side of the bulkhead, and the bulkhead lower web on the lower left side of the bulkhead and repair if necessary; and repetitive post-repair inspections and repair if necessary. We are issuing this AD to detect and correct cracks in the splice fitting, support frame, floor support, forward and aft inner chords, and the bulkhead upper and lower webs of the STA 2598 bulkhead, which could adversely affectthe structural integrity of the airplane.
75-04-09: 75-04-09 MOONEY: Amendment 39-2091 as amendment by Amendment 39-2127. Applies to Models M20C, M20E, and M20F airplanes manufactured after October 1974 with the following serial numbers on which the landing gear actuator, P/N LA11C2110, manufactured by International Telephone and Telegraph Corporation, is installed: Model M20C: 20-0037, 0038, 0039, 0040, 0041, 0042, 0043, 0044, 0045, and 0046; Model M20E: 21-0050, 0051, 0052, 0053, 0054, 0055, 0056, 0057, 0058, 0059, and 0060; Model M20F: 22-0065, 0066, 0067, 0068, 0069, 0070, 0071, 0072, 0073, 0074, 0075, 0076, 0077, and 0078. Compliance is required prior to further flight except that airplanes may be flown to a facility for actuator replacement after fixing the landing gear in the extended position in accordance with instructions included in Mooney Aircraft Corporation Service Bulletin M20-191, dated January 28, 1975, or later FAA approved revision, or an FAA approved equivalent procedure. To prevent further failures, replace the International Telephone and Telegraph Corporation P/N LA11C2110 landing gear actuator with a Mooney Aircraft Corporation P/N 950227-501 landing gear actuator in accordance with Mooney Aircraft Corporation Service Bulletin M20-191, dated January 28, 1975, or later FAA approved revision, or by an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. Amendment 39-2091 became effective on February 20, 1975. This amendment 39-2127 becomes effective on March 20, 1975.