Results
2013-22-11: We are superseding Airworthiness Directive (AD) 2009-10-06 for certain The Boeing Company Model 747-400 and -400D series airplanes. AD 2009-10-06 required repetitive inspections to detect cracks in the floor panel attachment fastener holes of the Section 41 upper deck floor beam upper chords, and corrective actions if necessary; and repetitive post-repair and post-modification inspections, and corrective actions if necessary. This new AD adds repetitive inspections of Section 44 upper deck floor beam upper chords, and corrective actions if necessary; repetitive post-repair and post- modification inspections, and corrective actions if necessary; and replacement of the upper deck floor beam upper chords. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain upper chords of the upper deck floor beam are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam, which could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane.
75-21-02: 75-21-02 MESSERSCHMITT-BOLKOW-BLOHM: Amendment 39-2380. Applies to Models BO-209 airplanes, S/N's 101 thru 201, and 301, certificated in all categories. Compliance is required as indicated. To prevent possible failure of the fuselage carry-through member of the wing, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, visually inspect the rear side of the beam web of fuselage frame No. 2 for cracks, in accordance with paragraph C.1. of Messerschmitt-Bolkow-Blohm (MBB) Service Bulletin No. 209-20-1 7/74 dated 7/74, or an FAA-approved equivalent. (b) If the inspection required by paragraph (a) of this AD reveals cracks, before further flight, repair and reinforce fuselage frame No. 2 in accordance with MBB Instruction No. MBB 209-1/74, undated, or an FAA-approved equivalent. (c) If the inspection required by paragraph (a) of this AD reveals no cracks, within the next 50 hours' time in service after the effective date of this AD, unless already accomplished, reinforce fuselage frame No. 2 in accordance with MBB Instruction No. MBB 209-1/74, undated, or an FAA-approved equivalent. This amendment becomes effective October 16, 1975.
73-11-01: 73-11-01 HUGHES: Amendment 39-1641. Applies to Hughes Model 269C Helicopters, certificated in all categories, incorporating idler pulley bearings, P/N 269A5050-62. Compliance required as indicated: To prevent possible failure of idler pulley bearings, accomplish the following: (A) For all helicopters, serial numbers 0004 through 0092 listed in Hughes Service Information Notice No. N-90.1, dated September 7, 1971, which, as of the effective date of this AD, have idler pulley bearings, P/N 269A5050-62 installed, (1) but have not previously had the replacement and inspection of the bearings accomplished as described in said Notice; perform the replacement and inspection described in said Notice, or later FAA-approved revisions, within the next 50 hours time in service on helicopters having 150 or more hours time in service on the bearings on the effective date of this AD, or at the first 200 hour periodic inspection on helicopters having less than 150 hours time inservice on the bearings on the effective date of this AD. Repeat the installation and inspection, per (C), below. (2) and have previously had the replacement and inspection of the bearings accomplished as described in said Notice as of the effective date of this AD, perform the replacement and inspection instructions in said Notice, or later FAA-approved revisions, before the accumulation of 600 hours total time in service on the bearings, or within 50 hours additional time in service after the effective date of this AD, whichever occurs later. Repeat the installation and inspection, per (C), below. (B) For all helicopters, other than those listed in (A) above, which as of the effective date of this AD, have idler pulley bearings P/N 269A5050-62 installed, with less than 600 hours total time in service, replace the bearings with new P/N 269A5050-62 bearings within 50 hours additional time in service after the effective date of this AD, or before the accumulation of 600 hours total time in service, whichever occurs later, in accordance with the replacement and inspection instructions in Hughes Service Information Notice No. N-90.1, or later FAA-approved revisions. All helicopters with bearings with 600 hours or more total time in service as of the effective date of this AD, replace the bearings with new P/N 269A5050-62 bearings within 50 hours time in service after the effective date of this AD, in accordance with the replacement and inspection instructions in Notice No. N-90.1, or later FAA-approved revisions. Repeat the installation and inspection per (C), below. (C) Thereafter, replace the idler pulley bearings, at or before the accumulation of 600 hours total time in service on the bearing, in accordance with the instructions provided in Hughes Service Information Notice No. N-90.1 dated September 7, 1971, or later FAA-approved revisions. (D) Mutilate and discard old bearings per Part II, Hughes Service Information Notice No. N-90.1, dated September 7, 1971, or later FAA-approved revisions. NOTE: Special caution should be exercised in performing the TIR runout and end play checks of Part III of the Notice. (E) Equivalent replacement and inspection procedures of idler pulley bearing may be approved by the Chief, Aircraft Engineering Division, FAA, Western Region. This amendment becomes effective May 21, 1973.
2018-07-14: We are adopting a new airworthiness directive (AD) for certain Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as insufficient engagement of the couplings with the flex drive of the rudder trim drive system. We are issuing this AD to require actions to address the unsafe condition on these products.
2013-22-14: We are adopting a new airworthiness directive (AD) for any DG Flugzeugbau GmbH Model DG-1000T glider equipped with a Solo Kleinmotoren Model 2350 C engine. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as engine shaft failure and consequent propeller detachment. We are issuing this AD to require actions to address the unsafe condition on these products.
2000-23-34: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-300, -400, and -500 series airplanes, that requires replacement of the existing autothrottle computer with a new, improved autothrottle computer. This amendment is prompted by reports of asymmetric thrust conditions during flight caused by irregular autothrottle operation in which the thrust levers slowly move apart causing the airplane to bank excessively and go into a roll. The actions specified by this AD are intended to prevent such conditions, which could result in loss of control of the airplane.
2003-13-05: This amendment adopts a new airworthiness directive (AD) that applies to all Iniziative Industriali Italiane S.p.A. (3I) Models Sky Arrow 650 TC and 650 TCN airplanes. This AD requires you to repetitively inspect the engine mount for cracks and modify or replace the engine mount if cracks are found. 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 detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane.
2013-21-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 727 airplanes. This AD was prompted by certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires, for certain airplanes, a modification of the web of the horizontal stabilizer center section rear spar. For the other airplanes, this AD requires an inspection for cracks in the web, and repair or modification as applicable. We are issuing this AD to prevent cracking at the upper fastener holes in the riveted web in the horizontal stabilizer center section rear spar, which could result in failure of the spar forging and lead to horizontal stabilizer separation and loss of control of the airplane.
72-03-04: 72-03-04 CESSNA: Amdt. 39-1388. Applies to Model 421B (S/Ns 421B0001 through 421B0149) airplanes. Compliance: Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To prevent blockage of the crankcase vent line by ice with subsequent engine failure due to loss of engine oil, accomplish the following modifications in accordance with Cessna Service Letter ME72-2, dated January 28, 1972, or any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region: A) Install a protective insulation sleeve over the crankcase vent line and scarf the vent line outlet to face aft. B) Install propeller shaft seal retainer on each engine. This amendment becomes effective February 4, 1972.
2013-20-02: We are adopting a new airworthiness directive (AD) for Bell Model 230 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.
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.