Results
2005-24-11: The FAA is superseding an existing airworthiness directive (AD) that applies to certain EMBRAER Model EMB-135 and Model EMB-145 series airplanes. The existing AD currently requires repetitive inspections of the spring cartridges of the elevator gust lock system to determine if the lock washer projection correctly fits the slots in the cartridge flange, and corrective action if necessary. The existing AD also provides for optional terminating action for the repetitive inspections for certain airplanes. This AD retains the requirements of the existing AD and adds a requirement for final terminating action for all affected airplanes. This AD results from reports of an improperly fitting lock washer causing the clevis of the spring cartridge in the electromechanical elevator gust lock system to become unscrewed. We are issuing this AD to prevent the unscrewing of the spring cartridge clevis from jamming the elevator, which could lead to reduced controllability of the airplane.
88-01-03: 88-01-03 BOEING: Amendment 39-5810. Applies to Model 757 series airplanes equipped with Rolls Royce RB 211-535C or -535E4 engines, specified in Boeing Alert Service Bulletin 757-71A0026, Revision 1, dated September 24, 1987, certificated in any category. Compliance required within one year after the effective date of this AD, unless previously accomplished. \n\n\tTo minimize the potential for total thrust loss in both engines due to a lightning strike, accomplish the following: \n\n\tA.\tModify engine electrical and electronic control unit wiring in accordance with Boeing Alert Service Bulletin 757-71A0026, Revision 1, dated September 24, 1987, or later FAA-approved revision. \n\n\tB.\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\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, 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 the Seattle Aircraft Certification Office, 9010 East Marginal Way south, Seattle, Washington. \n\n\tThis amendment becomes effective February 16, 1988.
2006-18-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A340-541 and -642 airplanes. This AD requires a one-time inspection of the anti-stall valve sleeve of the ram air turbine (RAT) for proper installation, determining the part number of the modification plate on the hydraulic pump of the RAT, and follow-on corrective actions if necessary. This AD results from reports of failure of the anti-stall valve on the hydraulic pump of the RAT during scheduled ground tests. We are issuing this AD to prevent failure of the RAT hydraulic pump to supply adequate pressure to activate the RAT, and consequent loss of the RAT as a source of hydraulic and electrical power in an emergency situation.
2021-06-09: The FAA is adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by a report indicating that a passenger door opened under residual cabin pressure during taxiing after landing, and following the display of the CAB PRESS CTL alert. This AD requires revising the existing airplane flight manual (AFM) to update the Cabin Pressurization Control Fault procedure, 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.
2006-18-08: The FAA is adopting a new airworthiness directive (AD) for certain aviation tires installed on various transport category airplanes. This AD requires a one-time inspection of the nosewheel tires to determine if they are within a designated serial number range, and replacement if necessary. This AD results from reports of tread separations and tread-area bulges on the nosewheel tires. We are issuing this AD to prevent tread separation from a nosewheel tire during takeoff or landing, which could result in compromised nosewheel steering or ingestion of separated tread by an engine, and consequent reduced controllability of the airplane on the runway or in the air.
2021-04-19: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Inc. (Bell) Model 205B helicopters. This AD was prompted by flight testing and fatigue analysis results. This AD requires reducing the life limit of certain tail rotor (T/R) blades and re- identifying them with a new part number (P/N). The FAA is issuing this AD to address the unsafe condition on these products.
2018-18-06: We are superseding Airworthiness Directive (AD) 2013-02-04 for all Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211- Trent 977B-84, and RB211-Trent 980-84 turbofan engines. AD 2013-02-04 required on-wing inspections of low-pressure turbine (LPT) disk seal fins and interstage seals when post-flight review indicates Engine Health Monitoring (EHM) vibratory maintenance-alert limits were exceeded in flight. This AD requires additional criteria for the inspection of the stage 2, 3, and 4 LPT disk seal fins and interstage seals and removes the requirement to inspect the stage 5 LPT disk seal fins and interstage seal. This AD was prompted by a Trent 900 engine experiencing increased low-pressure rotor vibration while in flight resulting in an in-flight shutdown (IFSD) and air turnback. We are issuing this AD to address the unsafe condition on these products.
2018-17-11: We are adopting a new airworthiness directive (AD) for certain Linstrandt T30 propane cylinders installed on hot air balloons. 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 welding defects on the propane cylinder that could result in leaking of liquid propane. We are issuing this AD to require actions to address the unsafe condition on these products.
88-22-10: 88-22-10 BOEING: Amendment 39-6055. Applies to Model 757 series airplanes, as listed in Boeing Service Bulletin 757-26-0016, dated May 5, 1988, certificated in any category. \n\n\tCompliance required within the next 15 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent depressurization due to loss of all bleed air inflow following crew action based on an erroneous duct leak indication, accomplish the following: \n\n\tA.\tModify the wing and body duct leak detection system in accordance with Boeing Service Bulletin 757-26-0016, dated May 5, 1988. \n\n\tB.\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\tC.\tSpecial 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 inspections required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Being Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at 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, 39-6055, becomes effective December 7, 1988.
2006-17-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2006-17-51, sent previously to all known U.S. owners and operators of Agusta S.p.A. (Agusta) Model AB139 helicopters by individual letters. This AD requires, before further flight and at specified intervals, certain visual inspections of each tailpipe assembly for a crack and for overheating. If you find areas of overheating, this AD also requires, before further flight, certain inspections for damage to the surrounding structure, outside of the cowling, and inside of each tailpipe assembly in certain areas. This AD also requires, before further flight, if you find a crack, replacing the tailpipe assembly with an airworthy tailpipe assembly. This AD is prompted by several reports of tailpipe assembly cracks. The actions specified by this AD are intended to prevent a fire due to the structure in the cowling area overheating, separation of a part of a tailpipe assembly, and subsequent loss of control of the helicopter.
2018-17-19: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, and A320 series airplanes, and Model A321- 111, -112, -131, -211, -212, -213, -231, -232, -251N, -253N, and -271N airplanes. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate the specified maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products. \n\n((Page 44461))
2018-17-18: We are superseding Airworthiness Directive (AD) 2015-02-17, which applied to all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes. AD 2015-02-17 required revising the electrical emergency configuration procedure in the Emergency Procedures section of the airplane flight manual (AFM) to include procedures for deploying the ram air turbine manually to provide sufficient hydraulic power and avoid constant speed motor/generator (CSM/G) shedding. Since we issued AD 2015-02-17, we have determined that replacement or modification of the two flight warning computers (FWCs) is necessary to address the identified unsafe condition. This AD requires the replacement or modifications of the two FWCs. This AD also removes airplanes from the applicability. We are issuing this AD to address the unsafe condition on these products.
2020-24-12: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by reports that certain central wing box (CWB) fasteners had rotated inside the fastener holes due to insufficient friction for the application. This AD requires replacement of the affected fasteners, 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.
87-04-10: 87-04-10 CASA: Amendment 39-5538. Applies to all CASA Model C-212 series airplanes when converted to a cargo configuration in accordance with CASA Service Bulletin 212- 25-35, dated October 23, 1985, or other modifications, certificated in any category. Compliance is required within 9 months after the effective date of this AD, or prior to conversion to a cargo configuration, whichever occurs later. In the cargo configuration, to preclude an undetected fire in the main cabin, accomplish the following, unless previously accomplished: A. Install a smoke detector system in accordance with CASA Service Bulletin 212- 26-06, dated October 23, 1985. B. 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. C. 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 modification 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 Construcciones Aeronauticas S.A., Getafe, Madrid, Spain. 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 March 9, 1987.
2006-18-03: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-145XR airplanes. This AD requires modification of the flap system interface wiring. This AD results from a finding that the aural and visual warnings, which should be activated when the flaps are set to 22 degrees during takeoff, were not enabled during the manufacture of certain Model EMB-145XR airplanes. We are issuing this AD to prevent overrunning the runway during takeoff.
2018-15-04: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF6-80A, CF6-80A1, CF6-80A2, CF6-80A3, CF6-80C2A1, CF6-80C2A2, CF6-80C2A3, CF6-80C2A5, CF6-80C2A5F, CF6- 80C2A8, CF6-80C2B1, CF6-80C2B1F, CF6-80C2B2, CF6-80C2B2F, CF6-80C2B4, CF6-80C2B4F, CF6-80C2B5F, CF6-80C2B6, CF6-80C2B6F, CF6-80C2B6FA, CF6- 80C2B7F, CF6-80C2D1F, CF6-80C2L1F, and CF6-80C2K1F turbofan engines. This AD was prompted by an uncontained failure of a high-pressure turbine (HPT) stage 2 disk that resulted in a fire. This AD requires ultrasonic inspection (UI) of HPT stage 1 and 2 disks. We are issuing this AD to address the unsafe condition on these products.
87-23-07 R1: 87-23-07 R1 SIKORSKY AIRCRAFT DIVISION: Amendment 39-5754 as amended by Amendment 39-6091. Applies to all Sikorsky Model S-76A/B helicopters, certificated in all categories, equipped with electrical door locking actuators installed in accordance with Sikorsky Drawing 76088-20016 using actuator P/N 22020256 in left and right passenger doors, except those helicopters which have installed a manual override kit, P/N 76070-20097. (Docket 87-ASW-30) Compliance is required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent the passenger door locks from jamming in the locked position due to a malfunctioning electrical door locking actuator, accomplish the following: (a) Remove electrical door locking actuators, P/N 22020256, in accordance with Sikorsky Alert Service Bulletin (ASB) No. 76-52-10A, dated August 27, 1987. NOTE: Some of the actuators may not be identified with this P/N 22020256; however, as an alternate means of identifying these actuators, a housing/casting, P/N 20220307, appears on these units identifying them as GM actuators P/N 22020256. (b) Upon request, with substantiating data, an alternate means of compliance which provides an equivalent level of safety or adjustment in the compliance time may be used when approved by the Manager, Boston Aircraft Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. These procedures shall be accomplished in accordance with Sikorsky ASB No. 76-52-10A, dated August 27, 1987. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a)(1) and 1 CFR Part 51. Copies may be obtained from Sikorsky Aircraft, 6900 Main Street, Stratford, Connecticut 06601-1381. Copies may be inspected at the Office of the Regional Counsel, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. This amendment revises Amendment 39-5754 (52 FR 43054; November 9, 1987), AD 87-23-07 which was effective on January 11, 1989. This amendment (39-6091, AD 87-23-07 R1) becomes effective on January 11, 1989.
89-12-03: 89-12-03 BRITISH AEROSPACE: Amendment 39-6228. Applicability: Model BAe 125-800A series airplanes, up to and including serial number 258147, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent damage to the engine fan blades, accomplish the following: A. Within 14 days after the effective date of this AD, inspect the left and right airflow angle sensor vanes for the trailing edge balance weight installation feature, in accordance with British Aerospace Service Bulletin 27-149, dated March 17, 1989. 1. If the inspection reveals an airflow angle sensor vane that does not have the balance weight feature installed, no further action is required. 2. If the inspection reveals an airflow angle sensor vane that has the balance weight feature installed, visually inspect the balance weight for security of its attachment in the trailing edge of the airflow angle sensor vane, in accordance with the service bulletin. a. If the balance weight is loose, damaged, or missing, replace it with a new airflow angle sensor vane prior to further flight, in accordance with the service bulletin. b. If the balance weight is secure and is not damaged, reinspect the balance weight for security, prior to each flight, until it is replaced with a new airflow angle sensor vane that does not have the trailing edge balance weight installation feature. B. 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. NOTE: 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, Standardization Branch, ANM-113. C. 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 requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This information may be examined at the FAA, Transport Airplane Directorate, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6228, AD 89-12-03) becomes effective on June 12, 1989.
89-18-04: 89-18-04 MCDONNELL DOUGLAS: Amendment 39-6295. (Docket No. 89-NM-16-AD) \n\n\tApplicability: McDonnell Douglas Model DC-9-80 (MD-80) series airplanes and Model MD-88 airplanes, as listed in McDonnell Douglas Service Bulletin 80-8, dated November 3, 1988, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent fire in the number 2 engine nacelle, accomplish the following: \n\n\tA.\tWithin 18 months after the effective date of this AD, relocate the number 2 engine starter shutoff valve pneumatic tube, in accordance with the accomplishment instructions in McDonnell Douglas MD-80 Service Bulletin 80-8, dated November 3, 1988. \n\n\tB.\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, Los Angeles 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, Los Angeles Aircraft Certification Office. \n\n\tC.\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\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-LOO (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 3229 East Spring Street, Long Beach, California. \n\n\tThis amendment (39-6295, AD 89-18-04) becomes effective on September 18, 1989.
2006-17-16: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires a one- time detailed inspection to detect corrosion on the wing rear spar lower girder, and related investigative and applicable corrective actions if necessary. This AD results from reports of corrosion of the wing rear spar lower girder between wing station (STA) 8700 and wing STA 9200. We are issuing this AD to detect and correct corrosion of the wing rear spar lower girder, which could result in reduced structural integrity of the wing rear spar.
2006-17-17: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-100, DHC-8-200, DHC-8-300, and DHC-8-400 series airplanes. This AD requires inspecting the left and right control column torque tube assemblies to determine the type of rivets installed and replacing incorrect or indeterminate type rivets with the correct type rivets. This AD results from a report that incorrect rivets having lower than required strength were installed on the control column torque tube during production. We are issuing this AD to prevent shear failure of control column torque tube rivets, which could cause unexpected decoupling of the elevators and large unwanted deflection of the free elevator, and consequent reduced controllability of the airplane.
2018-17-17: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-400 series airplanes. This AD was prompted by reports of arcing and smoke emanating from the windshields. This AD requires a revision to the maintenance or inspection program, as applicable, to include an inspection of the windshield moisture seal for signs of cracks, erosion, wear, and other deterioration; doing that inspection and repair if necessary; and re-torqueing the screws that fasten the windshield heater terminal lugs and applying sealant to the screw heads of the windshield heaters. We are issuing this AD to address the unsafe condition on these products.
2006-17-15: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-10-10 and DC-10-10F airplanes; and Model MD-10-10F airplanes. This AD requires replacing the clamp bases for the fuel vent pipe with improved clamp bases. This AD results from reports that the foil wrapping on existing plastic clamp bases has migrated out of position, which compromises the bonding of the fuel vent pipes to the airplane structure. We are issuing this AD to ensure that the fuel vent pipes are properly bonded to the airplane structure. Improper bonding could prevent electrical energy from a lightning strike from dissipating to the airplane structure, and create an ignition source, which could result in a fuel tank explosion.
87-25-03: 87-25-03 BRITISH AEROSPACE: Amendment 39-5779. Applies to British Aerospace Model 125-800A series airplanes, listed in British Aerospace (BAe) Service Bulletin 57-64-(3067), dated November 29, 1985, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent entrapment of water within the aileron tab accomplish the following: A. Within the next 100 landings or within one year after the effective date of this AD, whichever occurs sooner, modify the aileron tab and the inboard aileron hinge to provide drainage in accordance with BAe Service Bulletin 57-64-(3067), dated November 29, 1985. B. 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. C. 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 modification required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective January 13, 1988.
2006-17-08: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engines that were reassembled with certain previously used high pressure compressor (HPC) exit brush seal assembly parts and certain new or refurbished HPC exit diffuser air seal inner lands. This AD requires replacing the HPC exit inner and outer brush seal packs with new brush seal packs, or replacing the HPC exit brush seal assembly with a new HPC exit brush seal assembly. This AD results from a report of oil leaking into the high pressure turbine (HPT) interstage cavity and igniting, leading to an engine case penetration and engine in- flight shutdown. Although liberated engine parts did not penetrate the engine nacelle, we are issuing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers.