Results
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.
2023-01-10: The FAA is adopting a new airworthiness directive (AD) for certain GE Aviation Czech s.r.o. (GEAC) M601E-11, M601E-11A, M601E- 11AS, M601E-11S, and M601F model turboprop engines. This AD was prompted by the exclusion of life limits for certain compressor cases and compressor drums from the airworthiness limitations section (ALS) of the engine maintenance manual (EMM). This AD was also prompted by certain compressor cases that, following rework, were improperly re- identified and the engine logbook entries were not completed. This AD requires recalculation of the consumed life for the affected compressor cases and compressor drums and, depending on the results of the recalculation, removal and replacement of the affected compressor case or compressor drum with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2007-23-18: The FAA is superseding an existing airworthiness directive (AD) that applies to all Boeing Model 747-100B SUD, 747-300, 747-400, and 747-400D series airplanes; and Model 747-200B series airplanes having a stretched upper deck. The existing AD currently requires repetitively inspecting for cracking or discrepancies of the fasteners in the tension ties, shear webs, and frames at body stations 1120 through 1220, and performing related investigative and corrective actions if necessary. This new AD reduces the repetitive interval for certain inspections. This AD results from new reports of multiple severed adjacent tension ties, in addition to the previous reports of cracked and severed tension ties, broken fasteners, and cracks in the frame, shear web, and shear ties adjacent to tension ties for the upper deck. We are issuing this AD to detect and correct cracking of the tension ties, shear webs, and frames of the upper deck, which could result in rapid decompression and reduced structural integrity of the airplane. \n\n\nDATES: This AD becomes effective November 28, 2007. \n\n\tOn April 26, 2006 (71 FR 14367, March 22, 2006), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747- 53A2507, dated April 21, 2005. \n\tWe must receive any comments on this AD by January 22, 2008.
2007-19-53: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2007-19-53, which was sent previously to all known U.S. owners and operators of the specified Bell Helicopter Textron, Inc. (BHTI) model helicopters by individual letters. This AD requires replacing each affected tail rotor blade (blade) with an airworthy blade with a serial number not listed in the applicability of this AD. This AD is prompted by three incidents in which blade tip weights were slung from the blades during flight causing significant vibration. The actions specified by this AD are intended to prevent loss of a blade tip weight, loss of a blade, and subsequent loss of control of the helicopter.
2023-01-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, - 114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, - 211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report of a nose landing gear (NLG) sliding tube rupture that led to a NLG collapse. This AD requires inspection of certain NLG and main landing gear (MLG) sliding tubes and applicable corrective actions and eventual replacement of all affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). This AD also prohibits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2023-01-04: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This AD was prompted by an occurrence reported where during an inspection of a tail rotor head (TRH) pitch change spider, excessive play and excessive wear were detected, due to an unwanted rotating motion. This AD requires for helicopters with certain part- numbered TRH spider pitch change units installed, inspecting for correct installation of the spider pitch change nut (nut); marking a 2 to 5 mm wide black paint index mark and repetitively inspecting the alignment of the marking; and additional inspections and corrective actions if necessary. This AD also allows an affected part to be installed on a helicopter if certain requirements of this AD are met. The FAA is issuing this AD to address the unsafe condition on these products.