Results
69-17-01: 69-17-01 MCDONNELL DOUGLAS DC-9 and BOEING 737: Amdt. 39-819. Applies to DC-9 airplanes equipped with AiResearch Model GTCP85-98D Auxiliary Power Unit (APU) Serial Numbers listed in AiResearch Telegraphic Bulletin No. 49A1761 dated July 1, 1969, or later FAA approved revision, and to Boeing 737 airplanes equipped with AiResearch Model GTCP85-129 APU serial numbers listed in AiResearch Telegraphic Bulletin No. 49A1760 dated July 1, 1969, or later FAA approved revision. \n\n\tCompliance required as indicated unless already accomplished. \n\n\tBecause of possible failure of the second stage impeller blades, the auxiliary power unit shall not be used as an alternate electric power source in place of a main engine driven generator until deficient impellers have been replaced. Pending replacement of the auxiliary power unit impeller, accomplishment of the following is required. \n\n\t1.\tWithin 10 hours time in service after the effective date of this Airworthiness Directive, install a placard in full view of the pilot to read: \n\n\tBoth main engine driven generators must be operative for takeoff. Only during in-flight emergency may the auxiliary power unit be used as an alternate electric power source. \n\n\t2.\tThis placard may be removed when the APU is replaced with an APU having satisfactory impeller blades, or when the APU is modified to incorporate an impeller with satisfactory impeller blades in accordance with the above AiResearch Telegraphic Service Bulletins. \n\n\tNOTE: Compliance with the inspection and speed reduction adjustments in these bulletins is optional. \n\n\tThis amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated July 3, 1969.
2016-13-06: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by reports of ruptured horizontal stabilizer de-icing boots. This AD requires a revision of the applicable airplane flight manual (AFM), repetitive inspections of the horizontal stabilizer de-icing boots, and applicable corrective actions. We are issuing this AD to detect and correct damage of the de- icing boot; such damage could lead to a ruptured boot, severe vibrations, and possible reduced control of the airplane.
83-08-06: 83-08-06 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-4636. Applies to Lockheed Model L-1011-385-3 series airplanes, certificated in all categories. Compliance is required as indicated, unless previously accomplished. To minimize the potential for a total loss of the Active Control System (ACS) inflight, accomplish the following by June 30, 1983: A. Modify the aircraft wiring in accordance with Part 2, Accomplishment Instructions, in Lockheed-California Company L-1011 Service Bulletin 093-22-147 dated August 17, 1982, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Alternative means of compliance providing an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, 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 in order to comply with the requirements of this AD. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This amendment becomes effective June 2, 1983.
82-26-01: 82-26-01 BOEING: Amendment 39-4514. Applies to all Boeing Model 747 Series airplanes equipped with a dual channel autopilot with a Monitor and Logic (M & L) Unit, Boeing Part Number 60B00013-452, -453, -454, and on, listed in Boeing Service Bulletin 747-22-2130, Fail- Passive Autopilot Stabilizer Trim Bias and Automatic Disconnect Modification. \n\n\tCompliance required as indicated. To prevent no-flare automatic landings with excessive sink rates, accomplish the requirements of paragraph A and either paragraph B or C below within 180 days after the effective date of this AD: \n\n\tA.\tIncorporate the following limitations as appropriate in "Section 1 - Certification Limitations" of the Airplane Flight Manual: \n\n\t\t1.\tOn airplanes equipped with an operating Autoland Bias Control System, incorporate the following limitation: "Autopilot - Autopilot use below 50 feet AGL is prohibited except when Boeing Service Bulletin 747-22-2127 FAIL PASSIVE AUTOPILOT FLARE COMMAND WIRING MODIFICATION or FAA approved production equivalent is installed and one of the following conditions is met: \n\n\t\t\t(a)\tAt flaps 25 - the ground speed on final approach is less than 187 kts.\n \n\t\t\t(b)\tAt flaps 30 - the ground speed on final approach is less than 173 kts." \n\n\t\t2.\tOn all other airplanes incorporate the following limitation: "Autopilot - Autopilot use below 50 feet AGL is prohibited except when Boeing Service Bulletin 747-22- 2127 FAIL PASSIVE AUTOPILOT FLARE COMMAND WIRING MODIFICATION or FAA approved production equivalent is installed and one of the following conditions is met: \n\n\t\t\t(a)\tAt flaps 25 - the ground speed on final approach is less than 180 kts. \n\n\t\t\t(b)\tAt flaps 30 - the ground speed on final approach is less than 163 kts." \n\n\tB.\tInstall a placard on the autopilot flight director mode select panel which reads: "DO NOT USE AUTOPILOT BELOW 50 FT. AGL." \n\n\tC.\tAccomplish Boeing Service Bulletin 747-22-2127, FAIL PASSIVE AUTOPILOT FLARE COMMAND WIRING MODIFICATION or FAA approved production equivalent. Install a placard on the autopilot flight director mode select panel which reads: "DO NOT USE AUTOPILOT BELOW 50 FT AGL EXCEPT PER FLIGHT MANUAL LIMITATIONS." \n\n\tD.\tAccomplishment of Boeing Service Bulletin 747-22-2130 provides terminating action and allows removal of the placard and flight manual limitations required by paragraphs A, B, and C above. \n\n\tE.\tAlternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tF.\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 inspections and/or modifications required by this AD. \n\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\n\tThis amendment becomes effective January 17, 1983.
2016-13-02: We are superseding Airworthiness Directive (AD) 2016-09-04 for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2016-09-04 required replacement of incorrectly calibrated angle of attack (AOA) transducers. This new AD requires the same actions as AD 2016-09-04. This new AD was prompted by a report of a typographical error in the regulatory text of AD 2016-09-04. We are issuing this AD detect and replace incorrectly calibrated AOA transducers; incorrect calibration of the transducers could result in late activation of the stick pusher.
72-10-03: 72-10-03 HAWKER SIDDELEY: Amendment 39-1443. Applies to DeHavilland Model D.H. 104 Series 7A, 7AXC, 8A, 8AXC airplanes modified per STC SA1747WE certificated in all categories. (Also known as "Carstedt Jet Liner C-600"). Compliance required prior to further flight after the effective date of this AD as indicated, unless already accomplished. To prevent fatigue failure of a wing main spar lower attach fitting or of a wing center section lower spar boom, accomplish the following: (a) Replace each wing lower spar attach fitting P/N CPD 2004 installed under STC SA1747WE at or before 1800 hours' time in service, and at intervals thereafter not to exceed 1800 hours' time in service, with a new attach fitting (Strato Engineering Co., Inc. Part No. CPD 2004). (b) Replace the wing center section lower spar boom at or before 1800 hours' time in service, and at intervals thereafter not to exceed 1800 hours' time in service, in accordance with DeHavilland Aircraft Company drawing number 4-Z-13775, or another replacement modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) If aircraft are further modified in accordance with STC SA2438WE, or an alternate acceptable modification approved by the Chief, Aircraft Engineering Division, Western Region, replacement of the parts as specified in (a) and (b) above, may be discontinued. This amendment becomes effective June 7, 1972.
2024-19-16: The FAA is adopting a new airworthiness directive (AD) for all Deutsche Aircraft GmbH Model 328-100 and 328-300 airplanes. This AD was prompted by reports of a broken attachment eyebolt in a Collins Aerospace JB6 Commuter Class passenger seat. This AD requires a one- time detailed inspection of each affected part, and applicable corrective actions, and limits the installation of affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2024-19-05: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. (Safran) (type certificate previously held by Turbomeca, S.A.) Model Makila 1A, Makila 1A1, and Makila 1A2 engines. This AD is prompted by a determination that the accumulated service life of certain critical parts was underestimated. This AD requires determining the recalculated service life of certain critical parts, replacing if necessary, and also specifies conditions for installing the parts, 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.
2004-01-10: This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland (Eurocopter) Model MBB-BK-117 A-1, A-3, A-4, B-1, B-2, and C-1 helicopters with a certain tail rotor (TR) transmission or intermediate (INT) gearbox installed. This action requires inspecting the magnetic plug of the TR transmission and INT gearbox for metal particles before the first flight of each day. Replacing an unairworthy TR transmission, INT gearbox, or bearings with airworthy parts is also required within 30 days after the effective date of this AD. This amendment is prompted by a report of production-related cracks on the cage of bearings installed in certain TR transmissions and INT gearboxes. This condition, if not corrected, could result in cracking and separation of the bearing cage, failure of a bearing, failure of the TR transmission or INT gearbox, and subsequent loss of control of the helicopter.
2024-19-09: The FAA is superseding Airworthiness Directive (AD) 2016-08-08 for all SOCATA (type certificate now held by DAHER) Model MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150ST, Rallye 150T, Rallye 235C, and Rallye 235E airplanes. AD 2016-08-08 required doing repetitive detailed visual inspections of the intersection between the axle radius and the nose landing gear (NLG) fork area for chafing; doing repetitive dye penetrant inspections on the NLG wheel axle for cracks, distortion, and nicks or wear; doing corrective actions if necessary; and replacing the NLG wheel axle attachment screws with new screws. This AD is prompted by the introduction of a new inspection method and a new design for the affected NLG wheel axle that provides terminating action for the repetitive inspections, as specified in updated service information published by the manufacturer. This AD requires preparing, inspecting, replacing, reconditioning the NLG wheel axle, and prohibiting affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2003-26-14: The FAA adopts a new airworthiness directive (AD) for certain Kidde Aerospace P/N 898052 hand-held halon fire extinguishers that are utilized on aircraft. This AD requires you to remove the affected fire extinguishers from service and would prevent you from using them in the future. This AD is the result of information that shows that the discharge time of the affected fire extinguishers exceeds the maximum allowable discharge time. The problem is due to incomplete crimping of the siphon tube. We are issuing this AD to remove from service fire extinguishers that had this incomplete crimping of the siphon tube. If not removed from service, these fire extinguishers could function at diminished levels and compromise the level of safety in an emergency situation.
2003-26-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires identification of the valves installed on the engine struts as hydraulic supply (fire) shutoff valves for the engine-driven pump, corrective action if necessary, and eventual replacement of discrepant valves with serviceable parts. This action is necessary to prevent leakage of hydraulic (flammable) fluid into an engine fire, which could result in an uncontrolled fire. This action is intended to address the identified unsafe condition.
2016-13-01: We are superseding Airworthiness Directive (AD) 2016-08-05 for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) 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. AD 2016-08-05 required replacement of affected angle of attack (AOA) transducers. This new AD requires the same actions as AD 2016-08-05. This new AD was prompted by a report of a typographical error in the regulatory text of AD 2016-08-05. We are issuing this AD to detect and replace incorrectly calibrated AOA transducers; incorrect calibration of the transducers could result in late activation of the stick pusher.
47-49-09: 47-49-09 LOCKHEED: (Was Service Note 9 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088 and to Models 649 and 749 Serials 2501 Through 2513, Inclusive. At each engine change period, inspect the wing attaching pins at Station 80 to determine whether any of these pins are working upward through the fittings. If any pin has worked up until only the lower chamfered portion protrudes, replace the Station 80 cover strip with a new 0.064 24ST alclad strip. When this strip has been replaced the periodic inspection of that joint may be discontinued. (LAC Service Bulletin 49/SB-151 covers this same subject.)
2003-26-05: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-8C1 series and CF34-8C5 series turbofan engines, with certain serial number (SN) master variable geometry (VG) actuators installed. This AD requires initial and repetitive reviews of the airplane Maintenance Data Computer (MDC) for master VG actuator fault messages, and if the MDC is inoperative, reviews of the Engine Indication and Crew Alerting System (EICAS) for fault messages. This AD also requires replacement of actuators reported faulty by the Full Authority Digital Engine Control (FADEC). This AD results from nine reports of master VG actuator electrical signal faults, one report of which was a dual-channel fault, resulting in the FADEC commanding the engine power to idle. We are issuing this AD to prevent VG master actuator dual-channel electrical signal faults: Which will cause an uncommanded reduction of thrust to idle with a subsequent loss of the ability to advance thrust above idle; and Could result in a multi-engine loss of thrust if dual-channel faults occur on more than one engine simultaneously.
74-25-10: 74-25-10 BELL: Amendment 39-2039. Applies to Model 206A and 206B helicopters certificated in all categories and equipped with Rotor Brake Kit, P/N 206-706-032-1. Compliance required within the next ten hours' time in service after the effective date of this airworthiness directive unless already accomplished. To prevent failure of the rotor brake disc which could cause serious damage to critical components of the helicopter, accomplish the following: a. Remove the engine to transmission driveshaft and aft coupling. (Refer to Section VI of the Maintenance and Overhaul Manual.) b. Remove the Rotor Brake Disc Assembly P/N 4000071 or 4000071-1, attachment bolts and gasket from the coupling and discard. c. Reinstall the coupling and driveshaft as described in the Maintenance and Overhaul Manual. d. Disable the brake by removing the P/N 156F538-4S-0061 hose assembly between the rotor brake and firewall and capping the AN833-4C elbows with AN929-4J caps or equivalent. e. Bell Service Bulletin No. 206-50-74-1, Revision A, dated October 29, 1974 or later FAA/DER Approved Revision, includes equivalent instructions for these procedures and lists alternate FAA approved rotor brake configurations. f. Equivalent methods of compliance with this Airworthiness Directive must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. This amendment becomes effective December 16, 1974.
2016-12-07: We are superseding airworthiness directive (AD) 2010-11-10 for all Turbomeca S.A. Astazou XIV B and XIV H turboshaft engines. AD 2010- 11-10 requires inspection of certain third stage turbine wheels and removal of any damaged wheel. This AD requires expanding the population and frequency of repetitive inspections. This AD was prompted by a report of a third stage turbine wheel crack detected during engine overhaul. We are issuing this AD to prevent uncontained failure of the third stage turbine wheel, which could result in damage to the engine and damage to the helicopter.
2024-19-13: The FAA is superseding Airworthiness Directive (AD) 2023-04-06 and AD 2024-04-07, which applied to certain Airbus SAS Model A318, A319, A320 and A321 series airplanes. AD 2023-04-06 and AD 2024-04-07 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2023-04-06 and AD 2024-04-07 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; as specified in the 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.
91-03-16: 91-03-16 BOEING: Amendment 39-6875. Docket No. 90-NM-175-AD. \n\n\tApplicability: Model 747-400 series airplanes, as listed in Boeing Alert Service Bulletin 747-25A2862, Revision 1, dated December 13, 1990, certificated in any category. \n\n\tCompliance: Required within the next 9 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent smoking material from dropping behind the sidewall lining at the second observers station, accomplish the following: \n\n\tA.\tInstall a housing on the outboard side of the second observer's ashtray in accordance with Boeing Alert Service Bulletin 747-25A2862, Revision 1, dated December 13, 1990. \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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, SeattleACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6875, AD 91-03-16) becomes effective on March 4, 1991.
2016-11-19: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and all Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports of chafing of the feeder cable at the pylon- wing junction due to vibration; one report revealed that the cable loom plastic support bracket of the G-route was broken due to vibration; and another report revealed wire chafing due to clamp damage. This AD requires modifying the cable loom support bracket of the G-route of the inboard pylons at the pylon-wing junction. We are issuing this AD to prevent chafing of the wiring in the pylon-wing area, which could result in an electrical short circuit near a flammable fluid vapor zone, and consequent fire or fuel tank explosion.
77-12-05: 77-12-05 CHAMPION SPARK PLUG COMPANY: Amendment 39-2923 as amended by Amendment 39-3208. Applies to Part Numbers CH48108 and CH48109 oil filters as installed in aircraft certified in all categories, identified by the following manufacturing date codes, 1A7E and 2A7C for the Part Number CH48108 filters, and 1A7G and 1A7I for the Part Number CH48109 oil filters, except for those affected filters which are identified with the symbol "Insp OK 5G7A" stamped adjacent to the manufacturing date code. The manufacturing date code is located on the outside of the filter housing adjacent to the filter installation instructions. Champion Spark Plug Company Aviation Sales Bulletin No. 77-13 also pertains to this subject. Compliance required before further flight, unless already accomplished, except that the airplane may be flown in accordance with FAR 21.197 to a base where the removal can be performed. To preclude possible oil filter malfunction resulting from internal bypass valve failure, remove all applicable filters from service. Amendment 39-2923 became effective June 24, 1977. This amendment 39-3208 becomes effective May 12, 1978.
2003-26-02: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A319-113 and -114 series airplanes; and Model A320-111, -211, and -212 series airplanes; that requires either a review of airplane maintenance or delivery records, or one-time inspection of the hydraulic actuators located in the pivot doors of both thrust reversers to identify the part number, and eventual replacement of certain actuators with modified or new actuators. This action is necessary to prevent jamming of a thrust reverser door during operation, or inadvertent deployment of a thrust reverser door in-flight, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2001-21-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Company) TPE331-8, -10N, and -12B turboprop engines with certain electronic engine controls (EEC's) installed. This AD requires revising the Emergency and Normal Procedures section of the applicable Airplane Flight Manual (AFM) until the existing EEC's are replaced. This amendment is prompted by a report of an engine experiencing an uncommanded full power increase during an approach while both engine power levers were at the flight idle gate. The actions specified in this AD are intended to minimize exposure to flight and ground operations that could lead to the loss of control of the airplane due to asymmetric thrust and an uncommanded torque increase.
2024-19-06: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-8 and Model 737-9 airplanes. This AD was prompted by a Boeing review of the standby power system control unit (SPCU) design where a single point of failure exists internal to the SPCU. This AD requires installing four diodes and changing wire bundles in the P5 panel, as well as performing installation and power tests and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2003-26-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319, A320, and A321 series airplanes equipped with certain Litton air data inertial reference units (ADIRU). This AD requires modifying the shelf (floor panel) above ADIRU 3, and, for certain airplanes, modifying the polycarbonate guard that covers the ADIRUs, and the ladder located in the avionics compartment, as applicable. This action is necessary to prevent failure of ADIRU 3 during flight, which could result in loss of one source of critical attitude and airspeed data and reduce the ability of the flightcrew to control the airplane. This action is intended to address the identified unsafe condition.