Results
58-23-03: 58-23-03 MOONEY: Applies to Model M-20 Aircraft Serial Numbers 1002 Through 1051. Compliance required as soon as practicable but not later than December 15, 1958. Several failures of the aileron counterbalance buttweld at the aileron spar have occurred. The affected airplanes do not have a 3/8 inch O.D. x 0.028 inch x 3 inch steel reinforcing brace installed. It must be determined whether this brace has been incorporated. If not, the following inspection and repair must be accomplished: 1. Remove the paint from the subject welded joint and inspect for cracks. 2. Reweld the joint if cracks are present. 3. Install the 3/8 inch O.D. x 0.028 inch x 3 inch 4130 steel tubular brace (trimmed to fit). (Mooney Aircraft, Inc. Service Letter 20-7 Revision B covers this same subject.)
86-14-07: 86-14-07 SIKORSKY AIRCRAFT: Amendment 39-5432. Applies to all Model S-76A helicopters certificated in any category and model S-76B helicopters, serial numbers 760262, 760269, 760299, 760303, and 760310 through 760319, certificated in any category. Compliance is required as indicated, unless already accomplished. To prevent operation with a failed pilot's yaw control rod assembly, P/N 76400-00034-041, accomplish the following: (a) Prior to further flight, inspect the push rod assembly in accordance with Section E, paragraph 1, of Sikorsky Alert Service Bulletin (ASB) No. 76-ASB-76-67-22A, dated July 7, 1986, or an FAA-approved equivalent. If no dent, crack, distortion, or bowing is detected in the rod, install a placard legible to the pilot and in full view of the pilot stating "single pilot operation prohibited." This placard is to remain until the inspection required by paragraph (b) below is accomplished. (b) Within the next 25 hours' time in service afterthe effective date of this AD, inspect the push rod assembly for condition of heat treat in accordance with Section E, paragraph 2, of Sikorsky ASB No. 76-ASB-76-67-22A, dated July 7, 1986, or an FAA-approved equivalent. (c) If as a result of the inspection of paragraph (a), a dent, crack, distortion, or bowing is detected or if as a result of the inspection of paragraph (b) above, the heat treat (hardness) is incorrect, replace the rod assembly with a new or serviceable component that complies with this AD prior to further flight. (d) Aircraft may be ferried in accordance with the provision of FAR Sections 21.197 and 21.199 to a base where the requirements of the AD can be accomplished. (e) Upon request, an alternate method of compliance which provides an equivalent level of safety with the requirements of this AD may be approved by the Manager, Boston Aircraft Certification Office, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7118. Sikorsky Aircraft ASB No. 76-ASB-76-67-22A identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Sikorsky Aircraft, Division of United Technologies, North Main Street, Stratford, Connecticut 06601. This document also may be examined at the Rules Docket, Office of the Regional Counsel, Federal Aviation Administration, Southwest Region, 4400 Blue Mound Road, Fort worth, Texas, 76106. This amendment becomes effective October 20, 1986, as to all persons except those to whom it was made immediately effective by individual priority letter AD No. 86-14-07 issued July 9, 1986, which contained this amendment.
99-11-06: This amendment adopts a new airworthiness directive (AD) that applies to all Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires inspecting both (left and right wing configurations) environmental control system bleed tubes for damage, leakage, and a correct gap between the tube and wing lower panel crossing area, inspecting the wiring and surrounding structures for damage, and correcting any discrepancies 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 prevent thermal expansion from causing leakage of an environmental control system bleed tube because of improper installation, which could result in deterioration of the electrical wiring and the surrounding structure.
2012-17-02: We are adopting a new airworthiness directive (AD) for all Eurocopter France (EC) Model SA-365N, SA-365N1, SA-366G1, AS-365N2, AS 365 N3, EC 155B, and EC155B1 helicopters. This AD was prompted by the discovery of a cracked main rotor mast nut. This condition, if not corrected, could lead to complete failure of the mast nut, resulting in failure of the rotor mast and loss of control of the helicopter. This AD will require replacing the main rotor mast nut with an airworthy main rotor mast nut to prevent this scenario.
2012-17-01: We are adopting a new airworthiness directive (AD) for Goodyear Aviation Tires, part number 299K63-1 (Brazilian made new tires only), installed on various transport category airplanes, including but not limited to Bombardier, Inc. Model CL-600-2B19 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 tire tread separations and tread-area bulges on the main landing gear tires due to low adhesion in the tread shoulder area. The unsafe condition is specific to Brazilian produced new tires, size H29x9.0-15, only; retread tires are not affected by this AD. This condition, if not detected and corrected, could cause the main landing gear tires to fail during takeoff or landing. The failure may cause damage to the airplane structure, flaps, engine, and wheel well and result in reduced controllability of the airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
71-20-04: 71-20-04 CHAMPION: Amendment 39-1299. Applies to Model 7ECA (Serial Numbers 145, 151, 182, 190, 194, 199, 207, 211, 212, 226, 228, 229, 233, 242, 250, 253, 269, 270, 276, 281 thru 284, 287, 289, 292, 296, 298 thru 303, 306, 308, 316, 317, 321, 325, 328, 335, 344, 353, 354 thru 357, 365, 381, 387, 388, 403, 411, 416, 417, 421, 423, 439, 442, 447, 448, 450, 452, 463, 464, 470, 497, 501, 504, 515, 518, 531, 532, 543, 546, 552, 557, 560, 564, 569), Model 7GCAA (Serial Numbers 6, 8, 15, 44, 88, 91, 104, 106, 111, 112, 114, 125, 128, 141 thru 144, 150, 152, 154, 156 thru 167, 169, 172), Model 7GCBC (Serial Numbers 4, 7, 10, 14, 15, 16, 36, 45, 79, 83, 84, 86 thru 90, 92 thru 95), and Model 7KCAB (Serial Numbers 3, 16 thru 22, 24 thru 37, 39 thru 45, 47, 48, 50, 51, 53, 54, 55, 57, 58, 61, 62 and 64) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent structural failure of the lower longerons, accomplish the following: A) Within the next50 hours' time in service after the effective date of this AD, visually inspect the lower fuselage longerons in accordance with Champion Service Letter No. 96, dated August 1, 1969, to determine its method of fabrication. B) If the lower fuselage longerons, inspected in accordance with Paragraph A, do not meet the radius criteria specified in Champion Service Letter No. 96, dated August 1, 1969, prior to return to service, install Champion Service Kit 233, or any equivalent modification approved by the Chief, Engineering & Manufacturing Branch, FAA, Central Region. NOTE: Champion Aircraft Corporation is now Bellanca Aircraft Corporation. This amendment becomes effective September 30, 1971.
2012-16-14: We are adopting a new airworthiness directive (AD) for all Honeywell International Inc. TFE731-20R, -20AR, -20BR, -40, -40AR, - 40R, -50R, and -60 turbofan engines. This AD was prompted by a report of a quality escape of about 8,000 2nd stage low-pressure turbine (LPT2) rotor blades, manufactured by Honeywell Chihuahua Manufacturing Operation since 2009. This AD requires removing and inspecting certain LPT2 rotor blades. We are issuing this AD to correct an unsafe condition caused by these blades installed on these engines.
99-10-11: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney JT8D-200 series turbofan engines, that currently requires periodic inspection of fan blades for locked rotors and foreign object damage (FOD), unlocking of shrouds if necessary, lubrication of fan blade shrouds, and dimensional restoration of the fan blade leading edge. In addition, that AD requires installation of improved design fan blades as terminating action for the inspections. This AD will reduce the lubrication interval, and require removal of rotors that experience repeat lockups within 225 cycles in service. This supersedure is prompted by reports of twenty-five fan blade failures to date. The actions specified by the AD are intended to prevent fan blade failure, which can result in damage to the aircraft.
2012-15-08: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76A helicopters to require modifying the electric rotor brake (ERB) and inserting changes into the ``Normal Procedures'' and ``Emergency Procedures'' sections of the Rotorcraft Flight Manual (RFM). This AD was prompted by a fire in the main gearbox area as a result of a hot electric rotor brake (ERB). The actions are intended to prevent overheating of the ERB, ignition of the ERB hydraulic fluid, a fire in the main gearbox area, and subsequent loss of control of the helicopter.
99-06-17: This action confirms the effective date of Airworthiness Directive (AD) 99-06-17, which applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. AD 99-06-17 requires installing a support bracket and a cut-out relay for the second generator control unit. AD 99-06-17 also requires making all the wiring additions and adjustments necessary for the above-referenced installations. This AD was the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified in this AD are intended to prevent damage to electrical components because incorrectly connected cables or broken or damaged wires cause excessive voltages to the second generator, which could result in loss of electrical power during any phase of flight.