Results
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.
76-05-09: 76-05-09 AER PEGASO (AEROMERE & AVIONAUTICA RIO): Amendment 39-2544. Applies to M100S gliders, certificated in all categories. Compliance is required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent separation of lower rudder hinge pin from the rudder hinge bracket and the consequent loss of rudder control, accomplish the following: Replace the lower rudder hinge pin with a new pin made of SAE 1024 steel and inspect the new pin's weld for cracks, using the dye penetrant method, in accordance with the steps (1) through (9) of the Description section of Ingg. A. & P. Morrelli (Aer Pegaso) Technical Bulletin No. 11/M100S, dated March 16, 1971, or an FAA- approved equivalent. This amendment becomes effective March 25, 1976.
2012-16-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -200 freighter series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires modification of the control circuit for the fuel pumps for the center fuel tanks for certain airplanes, and center and rear fuel tanks for certain other airplanes. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
99-09-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 and Mark 0100 series airplanes, that currently requires a one-time inspection for heat damage of the fuselage skin and stubwing structure; either repetitive tests of certain seals or repair of heat damage, as necessary; and eventual replacement of corrujoint seals with new, improved seals. This amendment adds a requirement for repetitive inspections for heat damage of the subject area, and provides for a new optional terminating action for the repetitive inspections. This action 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 leakage of hot air from the corrujoint seals of certain valves in the stubwings, and subsequent heat damage of the fuselage skin and stubwing structure, which could result in reduced structural integrity of theairplane. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 8, 1999. The incorporation by reference of certain other publications as listed in the regulations, was approved previously by the Director of the Federal Register as of May 14, 1998 (63 FR 17318, April 9, 1998).
75-24-11: 75-24-11 BEECH: Amendment 39-2437. Applies to all civilly certificated Models A45 (Military T-34A, B-45) and D45 (Military T-34B) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent failure of the P/N 45-524504 and 45-524505 rudder-aileron bungee interconnect cable assembly and the P/N 45-524697 or P/N 45-524028 bellcrank assembly, accomplish the following: A) On Model A45 (Military T-34A, B-45) airplanes not incorporating P/N MS- 20219-2 pulleys (1.75 inch O.D.) per Beech Kit 45-325 and Beech P/N 105740B-ZF-0105 bronze bushings per Beech Drawing 45-000060, Rev. C, or later revision, within 50 hours' time in service after the effective date of this AD, or within 100 hours' time in service after the last inspection per AD 62-27-01, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, accomplish Paragraphs 1(a) and 1(b). B) On Models A45 (Military T-34A, B-45) and D45 (Military T-34B) airplanes incorporating P/N MS-20219-2 pulleys (1.75 inch O.D.) per Beech Kit 45-325 and Beech P/N 105740B-ZF-0105 bronze bushings per Beech Drawing 45-000060, Rev. C, or later revision, within 50 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 300 hours' time in service from the last inspection, accomplish Paragraphs 1(a) and 1(b). 1. (a) Disconnect the turn buckles P/N 45-524504 and 45-524505 rudder-aileron bungee interconnect cable assemblies, visually inspect the cables and replace frayed, internally broken or excessively worn cables. (b) Disconnect the two AN 161-8RS forks that attach to the P/N 45- 524697 or P/N 45-524028 bellcrank assembly and visually inspect the 3/16-inch diameter holes in the bellcrank for elongation or cracks. If elongation exceeds 0.02 inches or if cracks are found, replace the bellcrank. If no elongation or cracks are found, lubricate the holes in the bellcrank prior to reinstallation of theAN 161-8RS forks. 2. The airplane may be flown in accordance with FAR 21.197 to a location where parts replacement can be accomplished. 3. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Beechcraft Service Bulletin No. 32 on Model A45 (Military T-34A, B-45) airplanes covers the cable inspection. This AD supersedes AD 62-27-01. This amendment becomes effective November 28, 1975.
2012-16-10: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by chafing on high pressure fuel lines due to improper installation of an expandable pin on the lower cowl assembly. This AD requires installing spring clips and repositioning the lanyard attachment points at the forward end and the forward firefloor of the lower cowl. We are issuing this AD to prevent chafing of the high pressure fuel lines, which if not corrected, could cause fuel leakage in a fire zone.