Results
2012-24-01: We are adopting a new airworthiness directive (AD) for certain serial number (S/N) Rolls-Royce Deutschland Ltd & Co KG (RRD) TAY 620- 15 turbofan engines. This AD requires initial and repetitive general inspections and ultrasonic inspections (UI) of low-pressure compressor (LPC) fan blades for cracks. If any fan blade is found cracked, this AD requires replacement of the LPC fan blade set and the LPC fan disc. This AD was prompted by a report of an LPC fan blade separation. We are issuing this AD to detect cracks in the LPC fan blades, which could lead to uncontained failure of the LPC fan blades and LPC fan disc, and damage to the airplane.
47-10-40: 47-10-40 LUSCOMBE: (Was Mandatory Note 11 of AD-694-4.) Applies to Model 8 Series Aircraft Serial Numbers 1934 to 2200 Inclusive. Compliance required prior to May 1, 1947. Determine if the attachment of the rudder control arm to the torque tube has been reinforced by a steel strap that extends completely around the torque tube and is securely welded to both the fore and aft flanges of the rudder control arms and the torque tube. If the reinforcing steel strap is not properly located and welded to both flanges, a repair should be made. (Luscombe Service Bulletin No. 4-46 covers this same subject.)
2002-15-04: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc. and Textron Lycoming) T5313B, T5317 series and former military T53 series, turboshaft engines having certain serial number centrifugal compressor impellers, installed. This amendment requires for T53 series engines, a revised operating cycle count (prorate) for those compressor impellers if installed, and initial and repetitive inspections, with eventual compressor impeller replacement. In addition, this amendment requires the marking of those compressor impellers. This amendment is prompted by a report from the supplier that four centrifugal compressor impellers may have been inadvertently misidentified. The actions specified by this AD are intended to prevent premature failure of the impellers from being operated beyond their design service life, which could result in an uncontained engine failure, in-flight shutdown, or damage to the helicopter.
2021-18-14: The FAA is adopting a new airworthiness directive (AD) for all DG Flugzeugbau GmbH Models DG-808C and DG-1000T gliders. This AD was prompted by 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 identifies the unsafe condition as damaged fuel hoses due to environmental and fatigue deterioration. This AD requires inspecting the polyurethane (PU) fuel hoses, replacing the PU fuel hoses if there is damage, and establishing a life limit for the PU fuel hoses. The FAA is issuing this AD to address the unsafe condition on these products.
74-04-05: 74-04-05 CANADAIR: Amdt. 39-1788. Applies to all CL-44D4 and CL-44J airplanes with more than 20,000 hours' time in service. To detect cracks in the main landing gear uplock attachment fitting, P/N 44-10162 and -1, accomplish the following: 1. Within the next 100 hours' time in service after the effective date of this AD, unless accomplished within the last 400 hours' time in service, and at intervals thereafter not to exceed 500 hours' time in service, inspect the main landing gear uplock attachment fitting, P/N 44-10162 and -1 at the four corners of the lug for cracks using a dye penetrant inspection with a glass of at least 10-power or an approved equivalent inspection. 2. Cracked parts must be replaced before further flight, or repaired before further flight as specified in paragraphs 1(a) and (b) of the Inspection Procedure of Canadair's Service Information Circular 374-CL-44 or with an approved equivalent repair. 3. The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA maintenance inspector. 4. Equivalent inspections, parts or repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective February 20, 1974.
2003-09-07: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas transport category airplanes listed above, that requires a check of the slant pressure panels of the wheel wells of the left and right main landing gear (MLG) for water leakage, and repair of any leak found. This action is necessary to prevent the accumulation of water in the wheel wells of the MLG during flight, which could freeze on the lateral control mixer and control cables, resulting in restricted lateral control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
99-21-27: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-311 and -315 series airplanes, that currently requires replacement of the nitrogen cylinder assemblies that inflate the airplane s ditching dams with improved nitrogen cylinder assemblies. This amendment expands the applicability of the existing 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 failure of the ditching dams to inflate fully during an emergency water landing, which could result in water entering the airplane.
2012-23-03: We are adopting a new airworthiness directive (AD) for all Eurocopter France (Eurocopter) Model SA.315B Alouette III, SE.3160 Alouette III, SA.316B Alouette III, SA.316C Alouette III, SA.319B Alouette III, SA 3180-ALOUETTE ASTAZOU, SA 318B-ALOUETTE ASTAZOU, and SA 318 C-ALOUETTE ASTAZOU helicopters. This AD requires inspecting the cage of the free-wheel assembly for the correct alignment of the roller drive pocket recesses and replacing the free-wheel cage with an airworthy free-wheel cage if a defect exists. This AD was prompted by incorrect positioning of the roller drive pocket recesses on the tail rotor drive shaft free-wheel cage, which caused a pilot to experience a heavy jerk in the yaw control during in-flight autorotation training. The requirements of this AD are intended to prevent a loss of tail rotor drive and subsequent loss of control of the helicopter.
2002-09-09: This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc., Textron Lycoming, Avco Lycoming, and Lycoming) former military T53 series turboshaft engines. This amendment requires conducting a revised operating cycle count (prorate) and initial and repetitive inspections for cracks of centrifugal compressor impellers. This amendment is prompted by a report of a military surplus helicopter that experienced low-cycle fatigue failure of the centrifugal compressor impeller, resulting in an uncontained engine failure. The actions specified by this AD are intended to prevent centrifugal compressor impeller failure, which can result in an uncontained engine failure, in-flight engine shutdown, or damage to the helicopter.
75-12-01: 75-12-01 SIKORSKY AIRCRAFT: Amendment 39-2221. Applies to S-61L, S-61N, S- 61R and S-61NM helicopters certificated in all categories including Military type CH-3C, HH- 3C, CH-3E, and HH-3E helicopters equipped with the following main rotor blades: (1) S6115-20501 series, prior to and including S6115-20501-9 main rotor blade assemblies. (2) S6115-20601 series, prior to and including S6115-20601-044 main rotor blade assemblies. (3) S6117-20101 series, prior to and including S6117-20101-053 main rotor blade assemblies. (4) S6188-15001 series, prior to and including S6188-15001-044 main rotor blade assemblies. Compliance required as indicated. (a) Prior to the first flight of each day, inspect each main rotor blade in accordance with Section 2, paragraph C of Sikorsky Service Bulletin No. S61B15-18B or later FAA-approved revisions for possible free counterweights or loose material in the blade spar cavity. If any sound is evident, remove the blade from service immediately and notify Sikorsky Aircraft Product Support Department. (b) If any unusual one-per-rev vibration is noted, inspect each main rotor blade prior to further flight for a possible free counter-weight or loose material in the spar cavity in accordance with Section 2, paragraph C of Sikorsky Service Bulletin No. 61B15-18B or later FAA-approved revisions. If any sound is evident, remove the blade from service immediately and notify Sikorsky Aircraft Product Support Department. (c) Upon request of the operator, equivalent methods of compliance with the inspection requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, New England Region, if the request contains substantiating data to justify that equivalent method for that operator. This supersedes Amendment 39-1992 (39 F.R. 37356), AD 74-22-02 and Amendment 39-2031 (39 F.R. 41739), AD 74-25-07. This amendment becomes effective June 12, 1975.
2012-23-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports of failure of wire support clamps in the forward section of the aft pressure bulkhead. This AD requires a detailed inspection of the clamps on the power feeder cable of the auxiliary power unit (APU) to determine if certain clamps are installed, and related investigative and corrective actions if necessary. We are issuing this AD to prevent failure of the clamp, which could result in wire chafing and potential arcing and consequent fire in section 48 (a flammable fluid leakage zone) or heat damage to the APU power feeder cable, insulation blankets, or pressure bulkhead.
2012-22-17: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by reports of cracks in the inner chords at both left-side and right-side stations 859.5, 883.5, and 903.5. This AD requires repetitive inspections of the frame inner chord transition radius for cracks, and related investigative and corrective actions if necessary. We are issuing this AD to prevent large cracks in the frames and adjacent structure that can adversely affect the structural integrity of the airplane.
50-04-02: 50-04-02 SUPERIOR (Culver): Applies to All Model V, Serial V-3 Through V-357 and Model V2, Serial V2-503 Through V2-517 Not Previously Modified in Accordance With Superior Service Bulletin No. 18. Compliance required at the next 100-hour inspection but not later than February 1, 1951. The teeth of the final pinion, P/N 10528, in the gear reduction train of the landing gear retraction motor have inadequate strength to sustain the shock loads due to abrupt reversal of the landing gear retraction switch and to maladjusted limit switches. As stripping of these teeth makes the emergency extension system inoperative, gears 10528 and 10529 should be replaced with gears 11520 and 11521 which have stronger teeth and are obtainable from the Superior Aircraft Co., University Airport, 2501 North Hillside, Wichita 25, Kansas. (Superior Service Bulletin No. 18 dated November 19, 1947, covers this same subject.) This supersedes AD 48-05-02, and eliminates placard installation provisions.
2012-23-04: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 737-100 and -200 series airplanes. The existing AD currently requires various inspections for cracks in the outboard chord of the frame at body station (BS) 727 and in the outboard chord of stringer (S) 18A, and repair or replacement of cracked parts. This new AD adds airplanes to the applicability statement in the existing AD and adds inspections for cracks in the BS 727 frame outboard chords and the radius of the auxiliary chord, for certain airplanes. This new AD also removes the inspections of the outboard chord of S-18A required by the existing AD. This AD was prompted by several reports of fatigue cracking in the frame outboard chord at BS 727 and in the radius of the auxiliary chord on airplanes that were not affected by the existing AD. We are issuing this AD to detect and correct fatigue cracking of the outboard and auxiliary chords, which could result in reduced structural integrity of the outboard chord and consequent rapid decompression of the airplane.
99-20-08: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-11 series airplanes. This action prohibits installation of a certain In-flight Entertainment Network system. This amendment is prompted by the results of a special certification review of the in-flight entertainment system installed on a Model MD-11 series airplane that was involved in a recent accident. The actions specified in this AD are intended to prevent possible confusion as the flightcrew performs their duties in response to a smoke/fumes emergency, which could impair their ability to correctly identify the source of the smoke/fumes and subsequently affect the continued safe flight and landing of the airplane.
2001-12-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain General Electric Company (GE) CT58 series and former military T58 series turboshaft engines. This action requires the removal from service of certain fuel flow divider assemblies, and replacement with serviceable parts. This amendment is prompted by reports of large volumes of fuel leakage from end caps on fuel flow divider assemblies. The actions specified in this AD are intended to prevent fuel flow divider assembly fuel leakage, which could cause an engine fire, leading to an in-flight engine shutdown and forced landing.
2012-23-05: We are adopting a new airworthiness directive (AD) for all Eurocopter Deutschland GmbH (ECD) Model MBB-BK117 C-2 helicopters with certain Generator Control Units (GCU) installed. This AD requires replacing the GCUs. This AD was prompted by reports of internal short circuits in certain GCUs. These actions are intended to prevent a short circuit, which could result in a loss of electrical generating power, loss of systems required for continued safe flight and landing, and subsequent loss of control of the helicopter.
2012-22-08: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600 and A300 B4-600R, Model A300, and Model A310 series airplanes. This AD was prompted by reports of fatigue cracking in the crossbeams at the junction of the actuator beam of the lower deck cargo door. This AD requires repetitive inspections of the crossbeams of certain fuselage frames, and repair if necessary. We are issuing this AD to detect and correct cracking of the crossbeams at the junction of the actuator beam of the lower deck cargo door, which could result in failure to withstand ultimate load conditions, and consequent reduced structural integrity of the airplane.
75-05-04: 75-05-04 WHELEN ENGINEERING COMPANY INCORPORATED: Amendment 39-2098. Applies to aircraft incorporating Whelen Engineering Company Incorporated A427 strobe light flash tubes manufactured before November 1, 1974. Compliance required within the next 100 hours time in service unless already accomplished. (a) To preclude possible ignition of flammable fluids or vapors by arcing at the strobe light flash tube, install on the base of Whelen Engineering Company Incorporated A427 flash tubes a pressure sensitive vinyl label conforming to Whelen Engineering Company Incorporated Drawing A-30052, Revision 1, dated October 15, 1974, or latter FAA approved revision. Scotch Brand Type 33+ vinyl plastic electrical tape or equivalent tape approved by an FAA Maintenance/Avionics Inspector can be used in lieu of the vinyl label. If vinyl plastic electrical tape is used, it must be formed to cover the rivet at the rear of the flash tube without covering the identifying part number. If the flash tube incorporates a label, the new label or tape may be installed directly over the old label. Install the label or tape only when the label or tape and the flash tube are at a temperature above 50 degrees F. (b) The installation required by this AD constitutes preventive maintenance and may be performed by persons authorized to perform preventive maintenance under FAR 43. (c) Upon request with substantiating data submitted through an FAA Maintenance/Avionics Inspector, equivalent methods of compliance with this AD may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region. NOTE: For the requirements regarding the listing of compliance and method of compliance with this AD in the airplane's permanent maintenance record, see FAR 91.173. This amendment becomes effective thirty (30) days after publication in the Federal Register.
48-06-02: 48-06-02 COMMONWEALTH: Applies to Models 175, 180, 180F, 185, and 190F Aircraft. Compliance required by March 15, 1948. Inspect the jury struts for indication of excessive corrosion (inside) or cracks and if either is noted, replace the jury strut. Drill a 1/8-inch diameter hole at the lower rear edge of all jury struts to provide adequate drainage.
2012-22-09: We are adopting a new airworthiness directive (AD) for the Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires inspecting the tail rotor (T/R) pylon for a loose or missing fastener, a crack, damage, or corrosion and adding an internal doubler to the aft shear deck tunnel assembly. This AD was prompted by the discovery of cracks in T/R pylons. The actions are intended to detect a loose or missing fastener, a crack, damage, or corrosion on the T/R pylon and, if present, to repair the T/R pylon and install a doubler on the aft shear deck tunnel assembly or to replace the T/R pylon and install a doubler on the aft shear deck tunnel assembly. The actions are intended to prevent failure of the T/R pylon or other T/R components, which could lead to the loss of control of the helicopter.
73-07-05: 73-07-05 McKINNON: Amdt. 39-1614. Applies to Model G-21 Series 73-07-05 McKinn Airplanes. Compliance required as indicated. Applicable to torque tube assemblies, Gruman Part Numbers 12755-1, 12756-1, 12757-1, and 12758-1, and the support tubes, Part Numbers 12725-1 and -2. A. Applicable to those torque tube and support tube assemblies having less than 6000 hours' time in service, or less than 7 years' life since re-manufacture: To prevent hazards in flight associated with the failure of the elevator or rudder torque tubes, unless already accomplished within the last eleven (11) months, visually inspect the external condition of the tubes within one (1) month after the effective date of this AD, and at intervals thereafter not to exceed twelve (12) months from last inspection. Tubes which are cracked or show evidence of corrosion must either be repaired or replaced in accordance with FAR Part 43 and Advisory Circular 43.13-1 prior to further flight. B. Applicable to those torque tube and support tube assemblies having more than 6000 hours' time in service, or more than 7 years since re-manufacture. Within the next year, unless already accomplished: (1) Visually inspect the support tubes, Part Numbers 12725-1 and -2 for corrosion. If corrosion is found, repair or replace in accordance with FAR Part 43 and Advisory Circular 43.13-1 before further flight. (2) Remove all bolted bellcranks, arms, and pedals from the torque tubes. Using visual and dye penetrant methods, or an FAA-approved equivalent inspection, inspect the parts removed from the torque tubes for corrosion and cracking. Repair and replace in accordance with FAR Part 43 and AC 43.13-1. (3) Discard elevator torque tube, Part Number 12755-1; rudder torque tube, Part Number 12756-1 and the L.H. and R.H. rudder pedal torque tubes, Part Numbers 12757-1 and 12758-1. Install new manufactured parts or fabricate replacement tubes in accordance with FAR 43 and AC 43.13-1 from new manufacture stock 2024-T3 (material specifications WW-T-700/3 or equivalent) in conformance with the above drawings taking special care to corrosion-proof the interior as well as the exterior surfaces of the tubes. (4) Re-assemble and re-initiate the visual inspection program per (A) until reaching the rebuild threshold per (B). C. Aircraft with badly corroded but uncracked torque tubes may be flown in accordance with FAR 21.197 to a base where a repair or replacement can be performed. D. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the repetitive inspection intervals specified in this AD. This supersedes Amendment 39-1525 (31 F.R. 13697), AD 72-20-04. This Amendment becomes effective on publication.
2012-22-11: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron (BHT) Model 412, 412EP, and 412CF helicopters. This AD requires a repetitive inspection of the collective lever for a crack, and if there is a crack, before further flight, replacing the collective lever with an airworthy collective lever. This AD was prompted by a reported failure of a collective lever. The actions are intended to detect a crack in the collective lever, which could lead to failure of the collective lever and subsequent loss of control of the helicopter.
99-20-12: This amendment adopts a new airworthiness directive (AD), applicable to MD Helicopters, Inc. Model 369D, 369E, 369FF, 500N, and 600N helicopters, that requires replacing the oil cooler blower bracket (bracket). This amendment is prompted by three reports of cracked brackets. The actions specified by this AD are intended to prevent failure of a bracket, loss of cooling of engine oil and transmission oil, and a subsequent forced landing.
67-19-04: 67-19-04 MARTIN: Amdt. 39-432, Part 39, Federal Register June 15, 1967. Applies to Type 202, 202A and 404 Airplanes Incorporating Engine Mount, P/N's A10100, A10100-9, 2021C11039-9, A16647-81, 404-5000004, 404-5000004-59, 404-5000005, or 404-5000005-29. Compliance required as indicated. To detect cracks and corrosion in the engine mounts, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the last 100 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection; visually inspect the engine mount tubular members and welds for cracks, using a glass of at least 10-power, or use an FAA- approved equivalent inspection. If a crack is found comply with (c) before further flight. (b) Within the next 250 hours' time in service after the effective date of this AD, unless already accomplished within the last 750 hours' time in service, and thereafter at intervals not to exceed 1000 hours' time in service from the last inspection, or one (1) year whichever occurs first, inspect the engine mount tubular members and welds for external and internal cracks and corrosion, using both Magnaflux and X-ray or FAA-approved equivalent inspections. Remove paint and sandblast the engine mount prior to inspecting, or use an FAA-approved equivalent method. The sandblasting operation should be limited to the removal of any light rust or other superficial discolorations as necessary to give a clean surface to conduct Magnaflux inspection. If a crack is found comply with (c) before further flight. Engine mounts inspected within the last 750 hours' time in service using Magnaflux and X-ray, or FAA-approved equivalent inspections, but without sandblasting need not be reinspected before 1000 hours' of time in service from such inspection. (c) If a crack is found in the weld metal or in any tube between welds, and the crack is parallel to the tube axis, repair or replace the cracked part in accordance with the procedures outlined in the latest FAA-approved revision of the applicable Martin structural repair manual, or with an FAA-approved equivalent repair, or replace the cracked part with a part of the same part number that has been inspected in accordance with (b) and found free of cracks and corrosion, or with an FAA-approved equivalent part. If a crack is found in any tube wall, and the crack is transverse to the tube axis, replace the entire engine mount with a part of the same part number that has been inspected in accordance with (b) and found free of cracks and corrosion, or with an FAA-approved equivalent part. If a crack is found which is not identified above, approval for continued use of the engine mount must be obtained from the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Substantiating data must be submitted along with the request. (d) The repetitive inspection interval specified in paragraph (a) may be increased to 350 hours' time in service, and the repetitive inspection interval specified in paragraph (b) may be increased to 2500 hours' time in service or two (2) years, whichever occurs first, on aircraft whose engine mounts are treated internally at the next required inspection with hot linseed oil. The liquid shall be applied through holes drilled therein, or by immersing the part in a bath of the liquid, or FAA-approved equivalent method. All excess holes must be closed with cadmium- plated or zinc-plated self-tapping screws. (e) Equivalent inspections and repairs may be approved by an FAA maintenance inspector. Equivalent parts, Structural Repair Manual revisions, and internal treatment methods specified in paragraph (d), must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (f) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance timesspecified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This supersedes AD 66-12-01. This amendment effective June 20, 1967.