Results
2007-24-13: The FAA is adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation (Cirrus) Model SR22 airplanes. This AD requires you to install a drain hole in the left and right outboard wing tips. This AD results from reports of pilots' inability to move the aileron control without using excessive force when flying in freezing conditions. Moisture from a prior rain shower entered through a gap at the interface of the left and right outboard wing tips and wing structure. The moisture traveled along the aft wing shear web, accumulated below the aileron control pulley, and froze at an altitude with an outside air temperature below freezing. When this moisture is exposed to freezing conditions, operation of the aileron control pulley is impaired. We are issuing this AD to prevent moisture from accumulating along the wing shear web where it may freeze in certain conditions. This condition could result in operational failure of the aileron control pulley, which could lead to loss of control.
2007-24-09: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. That AD currently requires initial and repetitive on- wing or in-shop inspections of the high pressure/intermediate pressure (HP/IP) turbine bearing oil feed tube heat shield. This AD requires the same actions but introduces a terminating action to the repetitive inspections. This AD results from RR introducing a revised HP/IP turbine bearing support structure as terminating action to the repetitive inspections of the HP/IP turbine bearing oil feed tube heat shield. We are issuing this AD to prevent an uncontained failure of the HP turbine disc and damage to the airplane. DATES: Effective December 14, 2007. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of December 19, 2006 (71 FR 66229, November 14, 2006). The Director of the FederalRegister approved the incorporation by reference of certain publications listed in the regulations as of December 14, 2007. We must receive any comments on this AD by January 28, 2008.
2023-03-12: The FAA is superseding Airworthiness Directive (AD) 2004-04- 09, which applied to certain Pratt & Whitney Canada Corp. (P&WC) JT15D- 1, JT15D-1A, and JT15D-1B model turbofan engines. AD 2004-04-09 required a one-time borescope inspection (BSI) of the rear face of certain impellers for evidence of a machined groove or step, and repair or replacement of the impeller if a groove or step is found. Since the FAA issued AD 2004-04-09, the FAA was notified of an uncontained failure of an impeller installed on a P&WC JT15D-1A engine during takeoff and subsequent investigation by the manufacturer that discovered machining marks on the impeller. This AD was prompted by three prior reports of uncontained failure of the impeller, and one additional recent report of an in-service uncontained failure event. This AD requires borescope fluorescent penetrant inspection (FPI) of the rear face of certain impellers for evidence of machining witness lines and, depending on the results of the inspection, replacement of the impeller, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-04-08: The FAA is adopting a new airworthiness directive (AD) for certain Continental Aerospace Technologies, Inc. (Continental) GTSIO- 520-C, -D, -H, -K, -L, -M, -N, and -S; IO-360-A, -AB, -AF, -C, -CB, -D, -DB, -E, -ES, -G, -GB, -H, -HB, -J, -JB, -K, and -KB; IO-470-D, -E, -G, -H, -J, -K, -L, -M, -N, -P, -R, -S, -T, -U, -V, and -VO; IO-520-A, -B, -BA, -BB, -C, -CB, -D, -E, -F, -J, -K, -L, -M, and -MB; IO-550-A, -B, - C, -D, -E, -F, -G, -L, -N, -P, and -R; LTSIO-360-E, -EB, -KB, and -RB; LTSIO-520-AE; O-470-A, -B, -E, -G, -H, -J, -K, -L, -M, -N, -R, -S, -T, and -U; TSIO-360-A, -AB, -B, -BB, -C, -CB, -D, -DB, -E, -EB, -G, -GB, - H, -HB, -JB, -KB, -LB, -MB, -RB, and -SB; TSIO-520-A, -AE, -AF, -B, - BB, -BE, -C, -CE, -D, -DB, -E, -EB, -G, -H, -J, -JB, -K, -KB, -L, -LB, -M, -NB, -P, -R, -T, -UB, -VB, and -WB; TSIO-550-A, -B, -C, -E, -G, -K, and -N; TSIOF-550-K; and TSIOL-550-A, -B, and -C model reciprocating engines. This AD was prompted by a report of a quality escape involving improper installation of counterweight retaining rings in the engine crankshaft counterweight groove during manufacture. This AD requires inspection of the crankshaft assembly for proper installation of the counterweight retaining rings in the counterweight groove, and corrective actions if improper installation is found. The FAA is issuing this AD to address the unsafe condition on these products.
2023-02-14: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of potential foreign object debris (FOD) contamination of the thermal relief valve (TRV). This AD requires replacement of affected auxiliary power unit (APU) low-pressure (LP) shut-off valves (SOVs), an inspection to detect fuel leaks of affected engine LP SOVs and APU isolation shut-off valves (ISOVs), and applicable corrective actions, and prohibits installation of affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2023-03-02: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) PT6E-67XP model turboprop engines with serial number HP0194 and earlier. This AD is prompted by multiple reports of engines failing to achieve required power (torque) during high power applications due to internal leaks in the bleed-off valves (BOVs). This AD requires replacement of the compressor BOV assembly, replacement of the BOV orifice feed air tube assembly, and installation of a redesigned P3 probe snorkel, as specified in a Transport Canada AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2007-24-05: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce Corporation (RRC) AE 3007A and AE 3007C series turbofan engines. That AD currently prohibits any flight following a ground engine start where the engine oil temperature is below 32 [deg]F (0 [deg]C), unless certain preflight operational procedures are followed. This AD also requires those actions and would also require a terminating action. This AD results from design improvements to components in the accessory gearbox air turbine starter mounting pad. We are issuing this AD to prevent an in-flight engine shutdown due to loss of engine oil from the engine accessory gearbox starter pad shaft seal drain and possible loss of the airplane.
89-09-03: 89-09-03 BOEING: Amendment 39-6184. \n\tApplicability: Model 737 airplanes, line numbers 001 through 291, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent decompression of the airplane, accomplish the following:\n\n\tA.\tIn accordance with the schedule set forth in paragraph B. of this AD: \n\n\t\t1.\tAccomplish the terminating repair at all lap joints between BS 259 and BS 1016, which includes replacing all upper row fasteners with standard protruding head solid fasteners and assuring the tearstraps are functional 2 bays above and 1 bay below each lap joint, by the use of mechanical fasteners where disbonding of the tearstraps has occurred, in accordance with Boeing Alert Service Bulletin 737-53A1039, Revision 4, dated April 14, 1988. \n\n\t\t2.\tAccomplish the preventative modification as described in Boeing Service Bulletin 737-53-1089, Revision 1, dated October 13, 1988, along S-17, using standard protruding head solid fasteners and assure the tearstraps are functional 1 bay above and below S-17, by the use of mechanical fasteners where disbonding of the tearstraps has occurred, in accordance with the Structural Repair Manual. \n\n\tB.\tAirplanes are to be modified as required by paragraph A., above, in accordance with the following times after the effective date of this AD: \n\n\t\t1.\tFor fuselage structure between BS 360 and BS 1016: \n\n\n\nNumber of landings on effective date of this AD\nModify within the next: \n70,000 or more\n6 months \n60,000 - 69,999\n12 months \n50,000 - 59,999\n18 months \n40,000 - 49,999\n24 months \nless than 40,000\t\n36 months \n\t\t\t\t\n\n\t\t2.\tFor fuselage structure between BS 259 and BS 360, accomplish the modifications prior to a. or b., below, whichever occurs later: \n\n\t\t\ta.\tthe accumulation of 80,000 flight cycles or 4 years after the effective date of this AD, whichever occurs first; or \n\n\t\t\tb.\tone year after the effective date of this AD. \n\n\tC.\tFor airplanes on which the procedure described in paragraph A.1., above, has been accomplished in accordance with Part IV, A.2, of Boeing Alert Service Bulletin 737-53A1039, Revision 4, dated April 14, 1988, within 15 months after accomplishment, or within 6 months after the effective date of this AD, whichever occurs later, perform an external visual inspection of the skin for corrosion and delamination at all lap joints in accordance with that service bulletin. If corrosion is found, prior to further flight, perform a low frequency eddy current inspection of the entire length of the affected panel to determine material loss. If cracks are found, prior to further flight, perform a high frequency eddy current inspection of the entire length of the affected skin panel for cracks in accordance with the service bulletin. Repair cracks, corrosion, and delamination, prior to further flight (except as permitted by paragraph D., below), in accordance with the service bulletin. Inspections are to continue at intervals not to exceed 15 months. \n\n\tD.\tIf corrosion found as a result of the external inspection does not exceed 10 percent of the skin thickness, reinspect for corrosion in accordance with paragraph C., above, at intervals not to exceed 2,250 cycles or 6 months, whichever occurs first, until a repair is accomplished. If such corrosion exceeds 10 percent of skin thickness or if cracking is found, repair prior to further flight, in accordance with Boeing Alert Service Bulletin 737-53A1039, Revision 4, dated April 14, 1988. Following such repair, resume inspections in accordance with paragraph C., above. \n\n\tE.\tAccomplishment of the requirements of this AD constitutes terminating action for the requirements of AD 88-22-11, Amendment 39-6059, and is equivalent to the terminating modification therein. Any alternate means of compliance issued for that amendment are considered approved for this amendment. \n\n\tF.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tG.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\t\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6184, AD 89-09-03) becomes effective on May 19, 1989.
2007-24-07: The FAA is adopting a new airworthiness directive (AD) for a GE CF6-80C2B1 turbofan engine, serial number (SN) 690203, with fan disk, part number (P/N) 1703M78P11, SN RPMDA662, installed. This AD requires stripping of thermal spray coating, inspection of dovetail slots, and reapplication of thermal spray coating on certain stage 1 fan disks. This AD results from a report that a repair shop did not meet the process requirements when applying copper-nickel-indium (Cu- Ni-In) thermal coating to certain stage 1 fan disks. We are issuing this AD to prevent possible uncontained release of multiple fan blades, resulting in damage to the airplane.
2023-02-01: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by an investigation that indicated that one of the springs in the pitch trim switch of the horizontal stabilizer had failed. The failure of the spring could result in the airplane pitching nose down when actually commanded nose up. This AD requires a verification of the serial numbers of certain pitch trim switches, and replacement of the affected pitch trim switches with new ones in the pilot and co-pilot control wheels. This AD would also prohibit the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.