Results
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.
2016-12-05: We are superseding Airworthiness Directive (AD) 2014-15-04 for certain Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. AD 2014- 15-04 required deactivating the potable water system, or alternatively filling and activating the potable water system. This new AD requires inspecting the in-line heater for correct brazing and corrective action if needed, and installing a shrinkable tube on the water line and a spray shield on the in-line heater. This AD was prompted by a report of rudder pedal restriction which was the result of water leakage at the inlet tubing of an in-line heater in the lower part of the forward fuselage. This AD was also prompted by the development of a modification that would address the unsafe condition. We are issuing this AD to prevent rudder pedal restriction due to the pitch control mechanism becoming frozen as the result of water spray, which could prevent disconnection of the pitch control mechanism and normal pitch control, and consequently resultin reduced controllability of the airplane.
92-18-09: 92-18-09 BRITISH AEROSPACE: Amendment 39-8353. Docket No. 92-NM-97-AD. Applicability: Model BAe 125-800A series airplanes; post-mod 259404B (Turbomach auxiliary power unit) and post-mod 258706 (Garrett auxiliary power unit); certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a short circuit, arcing, and an electrical fire, accomplish the following: (a) Within 120 days after the effective date of this AD, modify the auxiliary power unit wiring, in accordance with British Aerospace Service Bulletin 49-37-25A253A&B, dated October 28, 1991. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send itto the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with British Aerospace Service Bulletin 49-37-25A253A&B, dated October 28, 1991. (NOTE: The issue date of that service bulletin is indicated only on "page 1 of 10"; no other page of the document is dated.) This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on November 17, 1992.
49-11-01: 49-11-01 NAVION: Applies to Airplanes Equipped With Carter Fuel Pumps Continental P/N 530509 (Carter M687-S and M688-S) or Continental P/N 50375. To be accomplished as soon as possible but not later than April 15, 1949. Due to Carter fuel pump lower diaphragm failures, caused by diaphragm deterioration due to excessive pump temperatures when pumps are run dry, the two Carter pumps should be connected in series to insure that fuel will be continuously flowing both pumps and that the pumps will not overheat. It is therefore required that all parallel Carter pump fuel systems be converted to the series pump arrangement, or, as an alternative, that either an approved Ryan fuel system incorporating an Adel electric booster pump or an equivalent approved fuel system be installed. Ryan Navion Field Service Bulletin No. 7 also covers this subject and describes means for connecting the fuel pumps in series. In addition, the daily inspections for looseness of the pump lower bowl, which are specified in section II of Ryan's Bulletin No. 7, should be continued. This supersedes AD 48-40-01.
2003-25-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-622R and A300 F4-622R airplanes, and Model A310-324 and -325 series airplanes, that are equipped with Pratt & Whitney PW4000 series engines. This AD requires replacement of the existing flexible hose assembly that connects the oil pressure transmitter to the main oil circuit, with a new improved tube assembly. This action is necessary to prevent failure of the oil pressure indicator and low-oil-pressure warning in the event of an engine fire, which could result in an unannounced shutdown of the engine. This action is intended to address the identified unsafe condition.
76-15-03: 76-15-03 BELL: Amendment 39-2675. Applies to Bell Models 206A, 206B, 206A-1, and 206B-1 helicopters, equipped with main rotor blade tension-torsion straps, P/N 206-010-105-3, certificated in all categories. Compliance required as indicated. To detect straps with inadequate torsional resistance or stiffness and to remove certain straps possibly made from certain spools of wire from further service, comply with the following. (a) Within the next 25 hours' time in service after the effective date of this AD, accomplish the following, unless previously accomplished: (1) Determine the serial number of each strap and remove from service straps having serial numbers 15432 through 15472 in accordance with the pertinent model maintenance manual or an FAA approved equivalent. (2) Conduct the inspections noted in paragraph II of Bell Helicopter Company Service Bulletin No. 206-76-4, Revision A dated May 11, 1976, or a later approved revision and remove those strapswith unacceptable rotation (inadequate torsional resistance) before further flight. (b) Prior to installing replacement straps or replacement hub assemblies, determine that paragraphs (a)(1) and (a)(2) of this AD have been accomplished. Install replacement straps in accordance with the pertinent model maintenance manual or an FAA approved equivalent. (c) The 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). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective July 29, 1976.