Results
2023-03-15: The FAA is superseding Airworthiness Directive (AD) 2021-07- 09, which applies to all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2021-07-09 required repetitively inspecting all trim air diffuser ducts or sidewall riser duct assemblies (collectively referred to as TADDs) for damage, including repetitive structural inspections of the center fuel tanks for damage, and performing applicable on-condition actions. Since the FAA issued AD 2021-07-09, the agency has determined that the existing requirements do not adequately address the unsafe condition. This AD continues to require repetitive inspections of the TADDs for damage, with revised compliance times, and repair if applicable. This AD also requires repetitive replacement of the TADDs and removes the structural inspections of the center fuel tanks. This AD also prohibits the installation of affected parts. This AD removes certain airplanes from the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
2023-04-20: The FAA is adopting a new airworthiness directive (AD) for all Cirrus Design Corporation (Cirrus) Model SF50 airplanes. This AD was prompted by reports of an accident and an incident due to uncommanded activation of the Cirrus Airframe Parachute System (CAPS) autopilot mode while in flight. This AD requires booting the avionics in configuration mode, inhibiting the CAPS autopilot, fabricating and installing information placards, revising the existing airplane flight manual (AFM) for your airplane, and revising the airworthiness limitations section (ALS) of the existing airplane maintenance manual (AMM) or Instructions for Continued Airworthiness (ICA) and your existing approved maintenance or inspection program, as applicable. For certain airplanes, this AD also requires modifying the wiring to remove the CAPS power timer functionality. The FAA is issuing this AD to address the unsafe condition on these products.
2007-25-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: * * * accidents which occurred to in-service aircraft caused by the violent opening of a passenger door, related to excessive residual pressurization in the cabin on ground. * * * * * This unsafe condition could result in injury to crew members opening the passenger door. We are issuing this AD to require actions to correct the unsafe condition on these products.
2023-03-17: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by an in-service inspection that found overhead storage compartment (OHSC) crash rods that were disconnected. This AD requires a one-time detailed inspection of the OHSC crash rods and, depending on findings, corrective actions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2003-19-14 R1: The FAA revises Airworthiness Directive (AD) 2003-19-14 which applies to all BURKHART GROB LUFT-UND RAUMFAHRT GmbH & CO KG (GROB) Models G103 TWIN ASTIR, G103 TWIN II, G103A TWIN II ACRO, and G103C TWIN III ACRO sailplanes. AD 2003-19-14 currently requires you to modify the airspeed indicators, install flight speed reduction and aerobatic maneuver restrictions placards (as applicable), and revise the flight and maintenance manual. This AD retains all the actions in AD 2003-19-14 for all Model G103 TWIN ASTIR sailplanes, removes Model G103 TWIN II from the applicability, and retains the aerobatic maneuver restriction for Model G103C TWIN III ACRO sailplanes. This AD also requires you to revise the modification to airspeed indicators, install a revised flight speed reduction placard, and revise the flight and maintenance manual for certain Models G103A TWIN II ACRO, and G103C TWIN III ACRO sailplanes. Simple Aerobatic maneuvers are also re-approved for Model G103A TWIN II ACRO sailplanes. An option for modifying the rear fuselage for Models G103A TWIN II ACRO and G103C TWIN III ACRO sailplanes that terminates the flight limitation restrictions for aerobatic maneuvers is also included in this AD.
2007-25-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During scheduled MRB (maintenance review board) mid-life X-ray inspections of Fokker 50 (F27 Mark 050) engine mount frames, severe internal corrosion of the tubes was discovered. In some locations, the depth of the corrosion spots appeared to be more than 50 percent of material thickness. * * * This condition, if not corrected, could ultimately lead to failure of the engine mounting frame in cases where multiple tubes are severely affected. * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2023-03-18: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by reports of cracks found in the tailcone upper firewall where the auxiliary power unit (APU) muffler electrical bonding strap is attached. This AD requires a detailed visual inspection of the tailcone upper firewall for defects, rework by replacement of the APU electrical bonding strap, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2007-24-11: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: GROB received isolated difficulty reports regarding cracks on welded parts of the flight control system of the type G102, model CLUB ASTIR III & IIIb, and STANDARD ASTIR III. The cracks progress slowly from the welding seams periphery, and may eventually result in rupture at a matured stage. We are issuing this AD to require actions to correct the unsafe condition on these products.
2023-03-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by a report that an interference was detected between the installed nut and the foot radius of a section of a certain frame (FR) on the right-hand side. This AD requires removing the affected fasteners and inspecting the affected area for damage, and applicable corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
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.
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.
2007-23-15: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: It has been found the occurrence of incorrect use of the self- locking nuts in bolts subject to rotational loads in bolted fittings of some assemblies of metallic components. Such event may result in disconnection of those fittings, which jeopardizes the structural integrity of the aircraft or its flight controls. Since this condition may occur in other airplanes of the same type and affects flight safety, a corrective action is required. Thus, sufficient reason exists to request compliance with this AD in the indicated time limit. We are issuing this AD to require actions to correct the unsafe condition on these products.