Results
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.
47-32-15: 47-32-15 SIKORSKY: (Was Mandatory Note 1 of AD-2H-1.) Applies to Model S-51 Helicopters. Compliance required prior to next flight. Inspect the chain and sprockets of the control system for an accumulation of excessive grease and foreign matter. Excessive grease and any foreign matter adhering to the chain and sprockets should be removed prior to the next flight in order to prevent possible malfunctioning of the flight control system. The recommended procedure as contained in the Sikorsky Service Information Circular No. 17 dated June 2, 1947, should be followed at the first disassembly of these parts.
2003-17-03 R1: We are revising an existing airworthiness directive (AD) for certain Piaggio Aero Industries S.p.A. Model P-180 airplanes. That AD currently requires replacement of any firewall shutoff or crossfeed valve with a serial number in a certain range even if it has been previously modified. The way the applicability was written includes valves that should not be affected and are not included in the referenced service information. This AD requires [[Page 67765]] the same actions as the current AD, but only affects those firewall shutoff valves referenced in the referenced service information. We are issuing this AD to clarify the affected parts required to correct the unsafe condition on these products.