Results
2013-14-04: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. This AD was prompted by fatigue load analysis that determined that the inspection interval for certain pylon bolts must be reduced. This AD requires a torque check of forward engine mount bolts, and replacement if necessary. We are issuing this AD to detect and correct loose or broken bolts, which could lead to engine detachment in-flight, and damage to the airplane.
2013-21-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8F and 747-8 series airplanes. This AD requires a detailed inspection of the power control actuator (PCA) installation to determine if a bushing is installed, a general visual inspection between the horizontal stabilizer rear spar and the elevator front spar and between certain stabilizer stations for defects and damage, and corrective actions if necessary. This AD was prompted by a report of unusual noise coming from the left inboard elevator during a functional check of the ram air turbine system, and a determination that a bushing was not installed. We are issuing this AD to detect and correct non-installation of bushings. If the \n\n((Page 63856)) \n\nbushings are not present, the stiffness of the load path will be decreased, which will cause wear of adjacent parts and increased freeplay of the elevator surfaces. Freeplay that exceeds acceptable limits could result in divergent flutter for certain maneuvers, which could lead to loss of controllability of the airplane.
2004-23-03: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 700 series turbofan engines. This AD requires initial and repetitive borescope inspections of the high pressure-and-intermediate pressure (HP-IP) turbine internal and external oil vent tubes for coking and carbon buildup, and cleaning or replacing the vent tubes if necessary. This AD results from a report of a RB211 Trent 700 series engine experiencing a disk shaft separation, overspeed of the IP turbine rotor, and multiple blade release of IP turbine blades. Preliminary findings suggest these events resulted from an internal oil fire in the HP-IP turbine oil vent tubes due to coking and carbon buildup. This fire led to a second fire in the internal air cavity below the IP turbine disk drive shaft. We are issuing this AD to prevent internal oil fires due to coking and carbon buildup, that could cause uncontained engine failure and damage to the airplane.
2013-19-17: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-535E4-B-37 series turbofan engines. This AD requires removal of affected parts using a drawdown plan. This AD was prompted by recalculating the lives of certain rotating life limited parts (LLPs) operated to certain flight profiles. We are issuing this AD to prevent the failure of rotating LLPs, which could result in uncontained failure of the engine and damage to the airplane.
90-12-11 R1: 90-12-11 R1 BOEING: Amendment 39-6626 as revised by Amendment 39-6683. Docket No. 90-NM-86-AD. \n\n\tApplicability: Model 727, 737, and 757 series airplanes, equipped with escape slide release cables, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo ensure proper escape slide release from the escape slide compartment, accomplish the following: \n\n\tA.\tWithin 45 days after the effective date of this AD, unless previously inspected within the last three months, perform a visual inspection of each escape slide release cable, if installed. Replace frayed (one or more broken strands) or broken cables prior to further flight.\n \n\tB.\tRepeat the inspection for frayed or broken release cables required by paragraph A. of this AD, at intervals not to exceed 12 months. \n\n\tC.\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 will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\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\tThis AD revises AD 90-12-11, Amendment 39-6626. \n\n\tThe effective date for the requirements of this amendment remains June 25, 1990, as specified in Amendment 39-6626, AD 90-12-11. \n\tThis amendment (39-6683, AD 90-12-11 R1) is effective on July 31, 1990.
2004-22-14: The FAA is adopting a new airworthiness directive (AD) for certain Saab Model SAAB SF340A and SAAB 340B series airplanes. This AD requires an inspection of the elevator and aileron trim-tab fittings, and related investigative/corrective actions if necessary. This AD is prompted by reports of improperly installed rivets in the retainers that hold the elevator trim-tab bearings. We are issuing this AD to prevent the elevator and aileron trim-tab bearings from coming loose, which could result in excessive play in the elevator and aileron trim systems, and reduced controllability of the airplane.
2022-25-22: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports indicating that protective caps were found on engine fire extinguishing pipes in the engine core zone (Zone 2) after airplane delivery. This AD requires a one-time inspection of the engine fire extinguishing pipes for the presence of protective caps and removal of any protective caps found, 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.
77-15-14: 77-15-14 MORANE SAULNIER (SOCATA): Amendment 39-2985. Applies to Model MS 760 (Paris 1) and MS 760A (Paris 1A) airplanes, all serial numbers, certificated in all categories, that are equipped with ERAM wheels, P/N 3760-A. Compliance is required within the next 50 hours time in service after the effective date of this AD, unless already accomplished within the preceding 50 hours time in service, and thereafter, at intervals not to exceed 100 hours time in service from the last inspection. To detect cracks in the landing gear wheels and prevent possible wheel failure, accomplish the following: (a) Visually inspect, using a dye penetrant procedure, each ERAM wheel, P/N 3760-A, in accordance with paragraph 2 of ERAM Service Bulletin No. 32-01, dated December 1970, as revised October 1973, or an FAA-approved equivalent. (b) If, during an inspection required by this AD, a wheel is found to have more than one crack per stud or any crack exceeding 14 mm in length, replacethat wheel with a serviceable wheel of the same part number or an FAA-approved equivalent. This amendment becomes effective August 29, 1977.
2000-01-09: This amendment adopts a new airworthiness directive (AD) that is applicable to GE Aircraft Engines (GEAE) CJ610 series turbojet and CF700 series turbofan engines. This action requires removal of certain unapproved parts before further flight. This amendment is prompted by findings that life-limited parts, with forged and inaccurate records, have been introduced into the field and might be installed on the affected engines. The actions specified in this AD are intended to prevent the use of unapproved parts. This condition, if not corrected, could lead to an uncontained engine failure and damage to the airplane.
2004-22-21: The FAA adopts a new airworthiness directive (AD) for all GROB-WERKE (GROB) Model G120A airplanes. This AD requires you to repetitively inspect visually the area between the vertical stabilizer main spar and the nearby vertical stabilizer skin for any disbonding/ crack; repair any disbonding/crack found; and calculate weight and balance after any repair. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct any disbonding/crack in the area between the vertical stabilizer main spar and nearby stabilizer skin, which could result in possible structural failure. This failure could lead to difficulty in airplane flight control.
2000-01-04: This amendment adopts a new airworthiness directive (AD), applicable to all Saab Model SAAB 2000 series airplanes, that requires a one time general visual inspection to verify the proper orientation of the aft exterior light; and corrective actions, if necessary. This amendment 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 improper illumination of the ground under the service door due to incorrect installation of the aft exterior light, which could result in injury to the passengers or crew members during an emergency evacuation.
2022-25-04: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 and 747-8 series airplanes. This AD was prompted by reports of three opened door 5 right ceiling stowage boxes that fell freely and injured a flight attendant in each event. This AD requires replacing certain snubbers of the door 5 ceiling stowage boxes on certain airplanes, and replacing certain snubbers and changing the location of the snubber attachments on certain other airplanes. This AD also requires an operation check of the stowage boxes or snubber, as applicable, and applicable on- condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
90-19-02: 90-19-02 McDONNELL DOUGLAS HELICOPTER COMPANY (MDHC): Amendment 39-6716. Docket No. 89-ASW-44. Applicability: All Model 369 series helicopters, certified in all categories, that are equipped with a cargo hook. Compliance: Required as indicated, unless already accomplished. To prevent an overrunning clutch assembly failure, which may result in the loss of engine power to the main rotor, accomplish the following: (a) Within the next 300 hours' time in service after the effective date of this AD or at the next annual inspection, whichever occurs first, accomplish the following: (1) Remove overrunning clutch assembly, part number (P/N) 369A5350- BSC, -601, or -603, if installed. (2) Install the overrunning clutch subassembly, P/N 369A5350-41, in the clutch assembly, P/N 369A5350-BSC, -601, or -603, whichever is installed, or replace clutch assemblies with P/N 369A5350-605. NOTE: Clutch subassembly, P/N 369A5350-31, can be converted to P/N 369A5350-41, in accordance with MDHC Service Information Notice (SIN) No. DN-164, EN-54, and FN-44, dated October 27, 1989. Clutch assemblies, P/N 369A5350-BSC, -601, or -603, can be reidentified as a -605 clutch assembly after installation of clutch subassembly, P/N 369A5350-41. (b) Inspect the overrunning clutch assembly, P/N 369A5350-605 or P/N 369A5350- BSC, -601, or -603 with P/N 369A5350-41 subassembly, at intervals not to exceed 300 hours' time in service or at annual inspections, whichever occurs first, for condition of the race inner clutch, P/N 369A5353-3, the race outer clutch, P/N 369A5352, and the sprag assembly, P/N 369D25351. (c) Replace sprag assemblies, P/N 369D25351 and P/N 369A5364, with an airworthy part on or before attaining 1,800 hours' total time in service. NOTE: The Manufacturer's Handbook of Maintenance Instruction and the Component Overhaul Manual pertain to the removal, identification, and installation of these assemblies. (d) Special flightpermits may be issued in accordance with FAR Sections 21.197 and 21.199 to operate helicopters to a base for the accomplishment of inspections required by this AD. (e) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, ANM-100L, FAA, Northwest Mountain Region, 3229 East Spring Street, Long Beach, California 90806-2425. (f) For the purpose of establishing the "time in service" specified in this AD, either the clutch total time with hook attached may be used, or a separate and permanent log of external load operating time (take-off to landing on a flight which involves external load operations) may be used; this log must meet the requirements of FAR Section 91.173. Airworthiness Directive 90-19-02 supersedes AD 81-07-10, Amendment 39-4077, as revised by Amendment 39-4266. This amendment (39-6716, AD 90-19-02) becomes effective on October 5, 1990.
2000-01-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires a measurement of the extension of the piston in the retract actuator of the main landing gear (MLG); and corrective action, if necessary. This amendment also requires repetitive replacement of the retract actuator with a repaired retract actuator, or repetitive replacement of the piston in the retract actuator with a new piston. This amendment 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 fatigue failure of the piston in the retract actuator of the MLG, and reduced structural integrity of the MLG.
2004-22-16: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Model GV and GV-SP series airplanes. This AD requires a one-time general visual inspection for contact or insufficient clearance between the crew oxygen bottle/supports and any wiring harness, and related investigative and corrective actions if necessary. This AD also requires, for certain airplanes, adjusting the wiring harness to obtain a minimum clearance between the crew oxygen bottle and wiring, and applying Teflon sheeting, as applicable; and for certain other airplanes, reworking certain wiring bundles. This AD is prompted by reports of insufficient clearance between certain wiring harnesses and the crew oxygen bottle on several in-production and in- service airplanes. We are issuing this AD to prevent chafing of the electrical wires of the wiring harness against the crew oxygen bottle, which could result in electrical shorting and possible fire in the underfloor structure of the airplane.
2022-24-10: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) airplanes, Model CL-600-2C11 (Regional Jet Series 550) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600- 2D24 (Regional Jet Series 900) airplanes, and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report that the pressure switch gauge assembly for the cargo bay fire extinguisher container has the potential to display an incorrect pressure under certain environmental conditions. This AD requires replacing affected high rate of discharge (HRD) and low rate of discharge (LRD) pressure switch gauge assemblies for the cargo bay fire extinguisher container. The FAA is issuing this AD to address the unsafe condition on these products.
2004-22-09: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes. This AD requires a one-time high-frequency eddy current inspection for cracking of the attachment lugs of the aileron spring tab balance unit, and corrective actions if necessary. This AD is prompted by a report indicating that, during heavy turbulence, a pilot needed to apply aileron trim to maintain level flight because cracking of the upper inboard attachment lug of the aileron spring tab balance unit, probably due to corrosion, had caused permanent deflection of the spring tab and consequent aileron damage. We are issuing this AD to prevent diminished control of the airplane in turbulence or total loss of roll control for the affected wing.
76-15-06: 76-15-06 BOEING: Amendment 39-2678. Applies to all Model 727 series airplanes, categorized as Group I and II in Boeing Service Bulletin No. 727-55-A65, or later FAA approved revisions, and certificated in all categories. Compliance required as indicated unless it can be shown that this AD is not applicable per paragraph B. \n\n\tTo prevent possible stabilizer flutter from mismatch of the elevator balance panel aft hinges in bays 2 and 5, accomplish the following: \n\tA.\tUnless already accomplished, within the next 300 flight hours from the effective date of this AD, inspect the elevator balance panel aft hinges in elevator bays 2 and 5 (left and right) for compatibility in accordance with Boeing Service Bulletin No. 727-55-A65, or later FAA approved revisions, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. If an aluminum hinge is installed in bay 2 and an aluminum-bronze hinge is installed in bay 5, replace in accordance with the service bulletin and physically rebalance in accordance with the Boeing 727 Structural Repair Manual prior to the next flight. \n\tB.\tIf it can be shown through an operator's records or airplane's maintenance records that the elevator balance panel aft hinges are not of the combination of aluminum in bay number 2 and aluminum-bronze in bay number 5, the AD is not applicable. \n\tC.\tAirplanes requiring action prior to the next flight per paragraph A may be flown to the nearest maintenance base in accordance with FAR 21.197 and 21.199. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98108. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective August 9, 1976.
2022-24-14: The FAA is superseding Airworthiness Directive (AD) 2020-12- 11, which applied to all Airbus SAS Model A319-111, -112, -113, -114, - 115, -151N, and -153N airplanes; Model A320-251N, -252N, -253N, -271N, -272N, and -273N airplanes; and Model A321-251N, -251NX, -252N, -252NX, -253N, -253NX, -271N, -271NX, -272N, and -272NX airplanes. AD 2020-12- 11 required revising the existing airplane flight manual (AFM) to limit the use of speed brakes in certain airplane configurations, as specified in a European Union Aviation Safety Agency (EASA) AD. This AD was prompted by a non-stabilized approach followed by an automatic go- around that led to an airplane pitch-up attitude and resulted in an auto-pilot disconnection. This AD continues to require the actions in AD 2020-12-11 and also requires, for certain airplanes, installing updated FG 3G standard software for the FMGC, and prohibits the installation of affected FG standards, as specified in an EASA AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2022-24-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A300 F4-600R series airplanes. This AD was prompted by a determination that the forward cargo door compartment between certain frame forks is susceptible to widespread fatigue damage (WFD). This AD completes certain mandated programs to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires modifying the forward cargo compartment between certain frame forks, 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.
2022-24-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report that damage (including delamination of the work deck, and corroded and cracked retainer blocks) was found during inspection of certain galleys. This AD requires repetitive inspections of certain galleys for corrosion of trolley retainer aluminum blocks and delamination of the upper panel of the trolley compartment, and applicable corrective action, 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 under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2004-22-11: This amendment supersedes an existing airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model EC135 P1, P2, T1, and T2 helicopters. That AD currently requires adding the AD or a statement to the Rotorcraft Flight Manual (RFM) informing the pilot to reduce power and land as soon as practicable if a thump-like sound followed by an unusual vibration occurs during flight. That AD also requires visually inspecting the main rotor drive torque strut assembly (strut) for a crack or a break, recording the inspections in the historical or equivalent record, re-marking and relocating the strut, as appropriate, and replacing any unairworthy strut with an airworthy strut. Also, that AD establishes life limits for certain struts and revises the life limit for other struts. This amendment requires the same actions as the existing AD except that it changes the visual inspection from a one-time inspection to daily inspections; reduces the life limit for aluminum struts;and eliminates the once-only transfer and remarking of certain struts. This amendment is prompted by an incident in which a pilot felt an in-flight increase in vibration and subsequent discovery of a failed strut. The actions specified by this AD are intended to prevent failure of a strut and subsequent loss of control of the helicopter.
98-19-15 R1: This amendment revises Airworthiness Directive (AD) 98-19-15, which currently requires incorporating information into the Limitations Section of the airplane flight manual (AFM) that imposes a speed restriction and a minimum pilot requirement for Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes equipped with Barber-Colman pitch trim actuators, part number (P/N) 27-19008-001/-004 or P/N 27-19008-002/-005. Since AD 98-19-15 became effective, improved design pitch trim actuators have been developed that, when installed, will eliminate the speed restriction and minimum pilot requirements of the current AD. This AD requires incorporating these installations as a method of complying with the current AD. The actions specified by this AD are intended to lessen the possibility of airplane pitch up caused by mechanical failure of the pitch trim actuator, which could result in a pitch upset and structural failure of the airplane.
2022-24-12: The FAA is superseding Airworthiness Directive (AD) 2020-23-05 for certain Airbus Helicopters Model EC225LP helicopters. AD 2020-23-05 required inspecting the control rod attachment yokes (yokes) of certain main rotor (M/R) rotating swashplates (swashplates), establishing a life limit, performing a one-time inspection of stripped yokes, and applicable corrective actions. Since the FAA issued AD 2020-23-05, the FAA has determined that certain swashplates are not susceptible to the unsafe condition, repetitive inspections for certain swashplates are necessary, and the criteria for when to perform a dye penetrant inspection needed to be revised. This AD retains some of the requirements of AD 2020-23-05 and also requires compliance with a revised life limit; performing a repetitive visual inspection of the yokes on certain swashplates; and depending on the inspection results, removing the affected swashplates from service, performing a dye penetrant inspection of the yoke, and additional corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
90-01-08: 90-01-08 MCDONNELL DOUGLAS HELICOPTER COMPANY (MDHC): Amendment 39-6456. Docket No. 89-ASW-10. Applicability: Model 369 series helicopters (including Models YOH-6A and OH-6A) certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent possible failure of the engine-to-transmission driveshaft coupling, which could result in loss of control of the helicopter, accomplish the following: (a) Within the next 25 hours' time in service or within 120 days after the effective date of the AD, whichever occurs first, inspect the couplings, MDHC Part Number (P/N) 369H5660, to determine serial numbers. (b) Replace any couplings, P/N 369H5660, which have serial numbers in the range from 5200 through 5309, with airworthy parts. (c) Record compliance with paragraph (a) of this AD in the AD compliance record and in the maintenance record of the helicopter log book. This record must include the serial numbers of any deficient couplings found during compliance with this AD. NOTE: MDHC Service Information Notices HN-216, DN-157, EN-47, FN-35, dated April 5, 1989, pertain to this subject. (d) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the requirements of this AD may be accomplished. (e) An alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety, may be used if approved by the Manager, Los Angeles Aircraft Certification Office, ANM-100L, FAA, 3229 East Spring Street, Long Beach, California 90806-2425. NOTE: Unairworthy couplings removed from service and in spares inventory should be marked unairworthy. Unairworthy couplings should be purged from spares inventory in accordance with MDHC SIN HN-216, DN-157, EN-47, FN-35, dated April 5, 1989. This amendment (39-6456, AD 90-01-08) becomes effective on February 5, 1990.