Results
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.
2020-25-03R1: The FAA is removing Airworthiness Directive (AD) 2020-25-03, which applied to all Airbus SAS Model A318, A319, A320, and A321 series airplanes. AD 2020-25-03 required repetitive checks of the pressure gauges to determine the amount of pressure on the inflation reservoir of each emergency escape slide/raft, and applicable corrective actions. AD 2020-25-03 also provided optional terminating action for the repetitive checks. The FAA issued AD 2020-25-03 to address insufficient reservoir pressure in an emergency escape slide/raft, which would prevent the deployment of the emergency escape slide/raft during an emergency, possibly resulting in injury to the occupants. The FAA has determined that AD 2020-25-03 is no longer necessary because the unsafe condition no longer exists. Accordingly, AD 2020-25-03 is removed.
2022-26-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by reports of flight control (horizontal stabilizer, rudder, and elevator) decals degrading and peeling (damage), reports of operators painting over these decals, and reports that procedures to replace these decals were inaccurate, potentially causing incorrect positioning of replacement decals. This AD requires inspecting the left and right horizontal stabilizer decals for visibility and damage; and for certain airplanes, inspecting the rudder and left and right elevator decals for visibility and damage; and doing applicable corrective actions; 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.
2022-26-04: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a report of an oxygen-fed ground fire event potentially caused by electrical arcing from a faulty surround light wire on the third crew member's (observer) oxygen mask. This AD was also prompted by the determination that additional inspections and a bracket trim are needed to address the unsafe condition. This AD requires an inspection for discrepancies of the observer's oxygen mask stowage box and stowage compartment, oxygen hose connections and routing, and the associated electrical harness, and corrective actions if necessary; and modifying the oxygen mask flexible lamp harness, mounting plate, and compartment panel, including rerouting the electrical harness and applying protective sealant. This AD also requires an inspection for correct installation of the flexible lamp assembly; trimming and reidentifying a bracket; and for certain airplanes, an inspection for damage of the wire harness assembly; and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
2007-23-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-200, -300, and -300F series airplanes. This AD requires a one-time inspection of each fuel quantity indication system (FQIS) wire harness connector for corrosion of the shield-to-backshell connection, corrosion on the ground jumper, and damage to the ground jumper; a loop resistance test of each FQIS wire harness; and related investigative and corrective actions if necessary. This AD results from reports of corrosion of the out-tank wire harness of the spar connector backshell for the FQIS. We are issuing this AD to detect and correct corrosion of the out-tank wire harness, which could prevent correct grounding of the lightning shield and result in total loss of the electrical grounding between the lightning shield and the airplane structure. This condition, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2007-23-11: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777 airplanes. This AD requires repetitive measurements of the freeplay of certain joints of the trailing edge flap supports; repetitive lubrication of the support joints; and related investigative and corrective actions if necessary. This AD also provides for modifying certain components of the trailing edge flap supports, which extends the intervals for the repetitive measurements, and revising the maintenance practices of the maintenance planning data document. This AD results from reports of excessive wear of the pins, bushings, and bearings, and corrosion at the joints of the outboard trailing edge flap supports. We are issuing this AD to prevent wear and corrosion at the flap support joints, which could result in loss of the trailing edge flap and possible loss of control of the airplane.
2022-25-20: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-1B and GEnx-2B model turbofan engines. This AD was prompted by a manufacturer investigation that revealed that certain high-pressure turbine (HPT) stage 2 disks, forward seals, and stages 6-10 compressor rotor spools were manufactured from powder metal material suspected to contain iron inclusion. This AD requires replacement of the affected HPT stage 2 disks, forward seals, and stages 6-10 compressor rotor spools. The FAA is issuing this AD to address the unsafe condition on these products.
2022-25-15: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report indicating that a crack was found in one of the holes of the wing rear spar lower chord at the main landing gear (MLG) aft fitting at a certain wing buttock line (WBL). This AD requires repetitive open hole high frequency eddy current (HFEC) inspections or surface HFEC and ultrasonic (UT) inspections for cracking of the wing rear spar lower chord at the MLG aft fitting at a certain WBL, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
87-12-03: 87-12-03 BRITISH AEROSPACE: Amendment 39-5634. Applies to BAC Model 1-11 Series 200 and 400 airplanes, certificated in any category. Compliance is required within 90 days after the effective date of this AD. To prevent loss of pressurization as a result of conducting the procedures for electrical smoke or fire, accomplish the following, unless previously accomplished. A. Modify the Airplane Flight Manual and notify flight crews as follows. This may be accomplished by inserting a copy of this AD in the Airplane Flight Manual. 1. In Section 3, Page 12A, add: "In the event that the procedure for electrical smoke or fire has to be carried out when both pneumatic and both air conditioning systems are operative, the subsequent busbar switching actions will result in the loss of one air conditioning system. Therefore, reduce aircraft altitude to 25,000 feet or below, as soon as practicable." 2. In Section 3, Page 12A, add: "In the event that the procedure for electrical smoke or fire has to be carried out with either pneumatic or either air conditioning system inoperative, reduce aircraft altitude to 15,000 feet or below, as soon as practicable, and open the ram air valve." 3. In Section 4, Page 49, add: "Should a pneumatic or an air conditioning system fail above 25,000 feet, reduce aircraft altitude to 25,000 feet or below, as soon as practicable." B. The limitation defined in paragraph A.2., above, may be removed after BAe Modification 21-PM5930 to the electrical system is incorporated. C. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to British Aerospace, Inc., Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective July 6, 1987.
2007-23-07: We are adopting a new airworthiness directive (AD) for the products listed above. 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: This Airworthiness Directive (AD) results from one report of main landing gear wheel attaching nut partly unscrewed on a TBM 850 what has generated a loss of braking and which could lead to a wheel loss. The investigation revealed that this incident was due to a wheel axle machining issue, concerning a few production batches. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2022-25-21: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-1041 airplanes. This AD was prompted by a report of a loud noise and vibration in the belly fairing (BF) access panel above the wings. This AD requires a one-time detailed inspection of the BF access panels and, depending on findings, accomplishment of applicable corrective actions, 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.
2007-22-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) provided by the aviation authority for the United Kingdom to identify and correct an unsafe condition on an aviation product. The MCAI states the following: This action is necessary following the discovery of IP Compressor Rotor stage 2-3 interstage spacer cracking on an in- service Trent 700 engine. Stress analysis of the damaged rotor has shown a possible threat to the rotor integrity, the cracking therefore presents a potential unsafe condition. The cause of the cracking is currently under investigation. We are issuing this AD to detect cracks in the stage 2-3 interstage spacer of the intermediate pressure (IP) Compressor Rotor. Cracking of the stage 2-3 interstage spacer could result in an uncontained engine failure and damage to the airplane.
2022-26-03: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AW169 helicopters. This AD was prompted by a report of a protruding pushbutton screw (screw) on a cockpit door internal handle resulting in an interference with the collective stick travel. This AD requires inspecting each screw and depending on the results, modifying the cockpit door handle and reporting information, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits installing an affected door handle assembly unless certain actions are accomplished. The FAA is issuing this AD to address the unsafe condition on these products.
2007-21-18: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas airplanes, identified above. This AD requires a one-time inspection to determine the configuration of the airplane. This AD also requires repetitive inspections for cracking of the tee or angle doubler, and corrective actions if necessary. This AD results from a report indicating that numerous operators have found cracks on the tee. We are issuing this AD to detect and correct stress corrosion cracking of the tee or angle doubler installed on the flat aft pressure bulkhead. Cracking in this area could continue to progress and damage the adjacent structure, which could result in loss of structural integrity of the airplane.
2007-21-16: 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: [A] roll spoiler cable failure could result in an unacceptable amount of roll spoiler deflection, which could result in reduced controllability of the aircraft. * * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2022-24-13: The FAA is superseding Airworthiness Directive (AD) 2021-22- 04, which applied to all Airbus SAS Model A318-111, -112, -121, and - 122 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. AD 2021-22-04 required a one-time eddy current conductivity measurement of certain structural parts of the outer flaps to determine if the incorrect alloy was used, and replacement if necessary; and also required a one-time eddy current conductivity measurement of certain other structural parts of the outer flaps to determine if the parts were properly heat treated, and replacement if necessary. This AD was prompted by the issuance of an updated list of suspected parts, including those that may have been improperly heat treated. This AD continues to require the actions in AD 2021-22-04, and requires using an updated list of suspected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.