Results
2013-25-02: We are superseding Airworthiness Directive (AD) 2000-11-06 for certain The Boeing Company Model 767 airplanes. AD 2000-11-06 required repetitive inspections to detect discrepancies of the wiring and surrounding Teflon sleeves of the fuel tank boost pumps and override/ jettison pumps; replacement of the sleeves with new sleeves, for certain airplanes; and repair or replacement of the wiring and sleeves with new parts, as necessary. This new AD requires reducing the initial compliance time and repetitive inspection interval in AD 2000-11-06; mandates a terminating action for the repetitive inspections to eliminate wire damage; removes certain airplanes from the applicability; and requires revising the maintenance program to incorporate changes to the airworthiness limitations section. This AD was prompted by fleet information indicating that the repetitive inspection interval in AD 2000-11-06 is too long, because excessive chafing of the sleeving continues to occur much earlierthan expected between scheduled inspections. We are issuing this AD to detect and correct chafing of the fuel pump wire insulation and consequent exposure of the electrical conductor, which could result in electrical arcing between the wires and conduit and consequent fire or explosion of the fuel tank.
2014-08-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of two in-service occurrences on Model 737-400 airplanes of total loss of boost pump pressure of the fuel feed system, followed by loss of fuel system suction feed capability on one engine, and in-flight shutdown of the engine. This AD requires revising the maintenance program to incorporate a revision to the Airworthiness Limitations section of the maintenance planning data document. We are issuing this AD to detect and correct failure of the engine fuel suction feed capability of the fuel system, which could result in dual engine flameout, inability to restart the engines, and consequent forced landing of the airplane.
99-19-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Sabreliner Model NA-265-40, NA-265-60, NA-70, and NA-265-80 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
91-13-05: 91-13-05 BRITISH AEROSPACE: Amendment 39-7036. Docket No. 90-NM-286-AD. Applicability: Model ATP series airplanes; equipped with Lucas starter motors, Part Numbers C5114-04, C5114-05, C5114-07, and C5114-08; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of engine oil and damage to the engine, accomplish the following: A. Within 30 days after the effective date of this AD, and thereafter at intervals not to exceed 250 hours time-in-service, perform a detailed visual inspection of the securing nuts and locking tab washers used to secure the motor section to the clutch housing, in accordance with British Aerospace Service Bulletin ATP-80-3, dated September 10, 1990. If any parts are damaged or loose, prior to further flight, repair in accordance with the service bulletin. NOTE: The British Aerospace Service Bulletin references Lucas Service Bulletins C5114-80-8 and C5114-80-9 for additional information. B. Within 150 days after the effective date of this AD, replace existing studs 80220185, tab washers SP42C, and nuts A24CP, with new bolts N137210-14 and washers AS12943, and lock new bolts with tie wire, in accordance with British Aerospace Service Bulletin ATP-80-4, dated November 23, 1990. This modification constitutes terminating action for the repetitive inspections required by paragraph A. of this AD. NOTE: The British Aerospace Service Bulletin references Lucas Service Bulletin C5114-80-A9 for additional information. C. An alternative method 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, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. Specialflight 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 the appropriate service documents 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. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7036, AD 91-13-05) becomes effective on July 15, 1991.
67-26-01: 67-26-01 BRITISH AIRCRAFT: Amdt. 39-482 Part 39, Federal Register September 15, 1967. Applies to Model BAC 1-11 200 Series Airplanes. Compliance required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. To prevent unwanted rudder actuation as a result of yaw-damper control valve drift when electrically deenergized, comply with either paragraph (a), (b), or (c). (a) Install a placard as near as practicable to the yaw-damper control switch, reading as follows: "Yaw Damper must be operating at the time of takeoff and at all times during flight." In the event of failure of the yaw damper during flight, the flight may continue only to the next scheduled stop. Repair yaw damper or comply with paragraph (b) before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. (b) Positively deactivate the yaw damper in accordance with British Aircraft Corporation Instruction SS316 or an FAA-approved equivalent, and install placard to indicate that the yaw damper is deactivated (c) Adjust and modify the yaw-damper control as follows: (1) Adjust the yaw-damper actuator Boulton Paul Part No. P185-45-10 to provide one degree bias between the torque motor and the rotary hydraulic control valve of the unit in accordance with BAC 1-11 Service Bulletin 27-PM 3291, or later ARB-approved issue, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (2) Modify the Elliotts Company torque motor type 130/6P to incorporate Boulton Paul Modification Nos. P185/11 or P185/15, in accordance with BAC 1-11 Service Bulletin No. 27-PM 3191 or later ARB-approved issue or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (3) Apply sealant, Midlands Silicones LTD, cold-cure silastromer K9160, or an FAA-approved equivalent, to the inside surfaces of the torque motor mounting access plates on final assembly and plug the 5/32 inch diameter dowel access hole, if present in the mounting, with a suitable aluminum alloy plug, in accordance with BAC 1-11 Service Bulletin No. 27-PM 3193 or later ARB-approved issue, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa and Middle East Region. (d) When the adjustments and modifications set forth in paragraph (c) are accomplished, any placards installed in accordance with paragraphs (a) and (b) may be removed. This amendment effective December 5, 1967.
60-03-03: 60-03-03 FAIRCHILD: Amdt. 94 Part 507 Federal Register January 29, 1960. Applies to Models F-27, F-27A, and F-27B, Serial Numbers 1 to 64 inclusive. Compliance required by February 15, 1960. As a result of investigation of loose rivets in the rudder and elevator tension regulator assembly, P/N 0501101-0 or 0501101-1, the following must be accomplished: Replace "cherry" rivets attaching the elevator bellcrank to tension regulator assembly with bolts, P/N 27-720003-9. Assemblies already modified by replacing the "Cherry" rivets with AN 470DD rivets are acceptable. However, further use of AN 470DD rivets in this assembly is prohibited due to the difficulty of installing these rivets without seriously damaging the bellcrank. If AN 470DD rivets are replaced or removed, they shall be replaced with bolts, P/N 27-720003-9. (Fairchild Service Bulletin No. 27-16, revised September 8, 1959, covers this subject.)
2014-09-05: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. This AD requires repetitive inspections of certain sidestay upper cardan pins of the main landing gear (MLG), and associated nuts and retainer assemblies, and pin replacement if necessary. This AD also provides for an optional measurement of the cardan pin clearance dimensions (gap check) and corrective actions if necessary, which would terminate the repetitive inspections. This AD was prompted by a report of a sidestay upper cardan pin of the MLG migrating out of position. We are issuing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing gear collapse and consequent damage to the airplane and injury to occupants.
99-19-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-7 and DHC-8 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
76-12-03: 76-12-03 PRATT & WHITNEY: Amendment 39-2634. Applies to all Pratt and Whitney JT9D Turbofan Engines containing turbine exhaust cases, part numbers 701877, 728301 thru 728309, 731370 thru 731373, 731377, 731565, 738438, 739431, 746128, 746272 thru 746274, 749510, 752872 thru 752876, 754763, 756838 and 761943. Compliance required once each day the engine is operated. In order to preclude failure of the sixth stage turbine disk resulting from an oil fire in the No. 4 bearing area, visually inspect the engine tailpipe/exhaust case area, to determine if there is oil leakage from the No. 4 bearing area. If oil leakage is found in the No. 4 bearing compartment area, either of the following corrective actions must be taken prior to further flight: 1. Inspect the No. 4 bearing oil pressure and scavenge tubes. Replace cracked or blocked tubes with new or serviceable parts. 2. Drill a drain hole in the turbine exhaust case inner flow path wall in accordance with Prattand Whitney Alert Service Bulletin 4552 dated March 29, 1976, or later FAA approved revision. 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 Pratt and Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, 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 New England Region. This amendment becomes effective June 22, 1976.
2014-08-10: We are superseding airworthiness directive (AD) 2013-14-08 for all Austro Engine GmbH model E4 engines. AD 2013-14-08 required removing from service certain part number (P/N) waste gate controllers. This AD requires removing certain additional P/N waste gate controllers from service. This AD was prompted by several reports of power loss events due to fracture of the waste gate controller lever. We are issuing this AD to prevent failure of the waste gate controller lever, which could lead to damage to one or more engines, loss of thrust control, and damage to the airplane.
77-10-14: 77-10-14 CANADAIR: Amendment 39-2908. Applies to Canadair CL-215-1A10 Airplanes, Serial Numbers 1001 through 1040 and 1046 certificated in all categories that have not been altered in accordance with Canadair Service Information Circular No. 136-CL-215. Compliance required prior to U.S. Airworthiness certification. Inspect and alter main landing gear actuator attachment fitting P/N 215-34014-1 and -2 in accordance with Canadair Service Information Circular No. 136-CL-215, page 2 of 3 dated June 11, 1976, or an approved equivalent. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment becomes effective May 26, 1977.
99-19-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab SAAB SF340A, SAAB 340B, and SAAB 2000 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
88-02-02: 88-02-02 GLASER-DIRKS FLUGZEUGBAU GmbH: Amendment 39-5814. Applies to Model DG-400 motor gliders, work numbers 4-1 thru 4-188, certificated in any category. Compliance is required as indicated unless already accomplished. To prevent damage to the drive pinion gears on the spindle motor that operates the engine extension/retraction mechanism, which could result in the inability to obtain power in flight, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD accomplish the following in accordance with the procedures specified in Glaser-Dirks Technical Note TN 826/18; dated March 10, 1987: (1) Replace pages in the aircraft handbook Flight and Maintenance Manuals in accordance with Procedure 1. (2) Check the engine extension time in accordance with Procedures 2 and 3. If this extension time exceeds 13 seconds: Within 25 hours time in service after the effective date of this AD, or 90 days, whichever comes first, replace the gas strut with Type 10-02-250-600/1200-N in accordance with Procedure 3 (procedures described on Page 41 of the Maintenance Manual). If extension time is 13 seconds or less, proceed to paragraph (b). NOTE: Replacement of pages in the aircraft handbook Flight and Maintenance Manuals and the check of the engine extension time may be accomplished by the pilot. (b) Within 25 hours time in service after the effective date of this AD, or 90 days, whichever comes first, modify the spindle drive in accordance with Procedure 4 of Glaser-Dirks Technical Note TN 826/18 (detailed procedures are described in Glaser-Dirks Service Instruction 1/10/86 dated March 10, 1987). This action must be accomplished regardless of whether the gas strut requires replacement. (c) Aircraft may be ferried in accordance with FAR Section 21.197 and Section 21.199 to a base where the AD can be accomplished. (d) Upon request, an equivalent means of compliance with the requirementsof this AD may be approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, and Middle East Office, Federal Aviation Administration, c/o American Embassy, 15 Rue de la Loi B-1040, Brussels, Belgium; telephone 513.38.30 ext. 2710, or the Manager, New York Aircraft Certification Office, Federal Aviation Administration, New England Region, 181 S. Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791-6690. (e) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. Glaser-Dirks Technical Note TN 826/18, and Service Instruction 1/10/86, each dated March 10, 1987, identified and described in this document, are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who havenot already received these documents from the manufacturer may obtain copies upon request to Glaser-Dirks Flugzeugbau GmbH, Im Schollongarton 19-20, D-7520 Bruchsal 4, Federal Republic of Germany. These documents may also be examined at the Office of the Regional Counsel, Rules Docket No. 87-ANE-33, Room 311, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment becomes effective on January 22, 1988.
2022-18-04: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-1B model turbofan engines. This AD was prompted by several reports of fuel leaks caused by high cycle fatigue (HCF) cracks found at the braze joints on fuel manifolds, and the subsequent manufacturer redesign of the high-pressure turbine (HPT) fuel hose variable stator vane (VSV) manifold, VSV fuel hose manifold, low-pressure turbine (LPT) fuel hose variable bleed valve (VBV) manifold, and VBV fuel hose manifold. This AD requires removal and replacement of the fuel hydraulic lines. The FAA is issuing this AD to address the unsafe condition on these products.
2014-08-08: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracking found in the skin at the lower aft corner of the forward entry doorway on airplanes that do not have an airstair door cutout. This AD requires repetitive inspections for cracking in the lower corners of the forward entry doorway on airplanes that do not have an airstair door cutout, and repair if necessary. We are issuing this AD to detect and correct cracking in the lower corners of the forward entry doorway, which could lead to crack progression and consequent rapid decompression of the airplane.
89-23-15: 89-23-15 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6384. Docket No. 89-NM-80-AD. Applicability: Model DHC-8-100 series airplanes, Serial Numbers 1 through 91, certificated in any category. Compliance: Required within the next 400 hours time-in-service after the effective date of this AD, unless previously accomplished. To prevent unwanted propeller feathering due to inadvertent activation of the alternate feather switches, accomplish the following: A. Modify the alternate feather system, in accordance with the Accomplishment Instructions of Boeing of Canada, Ltd., de Havilland Division, Service Bulletin No. 8-61-10, Revision A, dated August 5, 1988. 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, New York Aircraft Certification Office, FAA, New England 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, New York Aircraft Certification Office. 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 the appropriate service documents from the manufacturer may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or New York Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. This amendment (39-6384, AD 89-23-15) becomes effective on December 11, 1989.
99-19-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes and Model F27 Mark 050 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
82-18-09: 82-18-09 AIRCRAFT TANK SERVICE, INC.: Amendment 39-4449. Applies to Lockheed Model 1329 series airplanes, Avions Marcel Dassault Model Fan Jet Falcon series airplanes, and British Aerospace (Aircraft Group) Model DH-125 series airplanes which have been modified in accordance with STC SA2603WE, SA3221WE, SA3324WE, SA1851WE, or SA3382WE, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent possible engine fuel starvation, accomplish the following: A. Within the next 30 calendar days after the effective date of this AD, or before the accumulation of two years calendar time since the installation of tygothane tubing, whichever occurs later, inspect to determine the condition of the tygothane components in accordance with the appropriate service bulletin listed in the table below. 1. If there is cracking or brittleness, discontinue use of the single point refueling system and within 90 calendar days after the inspection, remove tygothane tubing systems components and replace with like serviceable components in accordance with Part III of the appropriate service bulletin. The appropriate service bulletin for each type airplane is shown below. Model STC No. Aircraft Tank Service, Inc. Service Bulletin Fan Jet Falcon SA1851WE A28-01 Rev. 1 dated January 21, 1982 DH-125 SA3382WE A28-02 Rev. 1 dated February 5, 1982 1329 SA2603WE A28-04 Rev. 1 dated January 29, 1982, or A28-05 Rev. 1 dated February 5, 1982 (see Service Bulletin effectivity) 1329 SA3221WE A28-05 Rev. 1 dated February 5, 1982 1329 SA3324WE A28-05 Rev. 1 dated February 5, 1982 2. If there is no cracking or brittleness but a chocolate brown color noted, continue operation and repeat inspection at six months from initial inspection and replace tygothane components per appropriate service bulletin within one year from initial inspection. 3. If the tygothane components are light colored, continue toinspect in accordance with paragraph A. of this AD at intervals not to exceed six months until such time as the tygothane components are replaced in accordance with Part III of the appropriate service bulletin. B. After the effective date of this AD, if difficulty in pressure refueling or spillage out of the vent line is encountered, inspect per paragraph A. of this AD, and: 1. If the tygothane tubing has started to break up and there is evidence of tygothane particles in the tank which could cause fuel system contamination, replace the tygothane tubing prior to next flight per Part III of the appropriate Service Bulletin. 2. If cracking or embrittlement is found without evidence of loose particles, discontinue use of the single point fueling system and replace the tygothane tubing within 90 days after the inspection in accordance with Part III of the appropriate Service Bulletin. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 tooperate aircraft to a base for the accomplishment of inspections or modifications required by this AD. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, FAA Northwest Mountain Region, Hawthorne, California. 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 proposal who have not already received these documents from the manufacturer may obtain copies upon request to Aircraft Tank Service, Inc., Product Support Engineering, P.O. Box 1307, Sun Valley, California 91352. These documents may also be examined at FAA Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168; or Western Aircraft Certification Field Office, 15000 Aviation Boulevard, Hawthorne, California 90261. This amendment becomes effective October 4, 1982.
2014-07-09: We are adopting a new airworthiness directive (AD) for British Aerospace Regional Aircraft Jetstream Series 3101 and Jetstream Model 3201 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as inadequate instructions for inspection for corrosion on the rudder upper hinge bracket and certain internal wing and drainage paths. We are issuing this AD to require actions to address the unsafe condition on these products.
99-19-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Fairchild Model F-27 and FH-227 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
99-24-04: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that requires a one-time visual inspection to determine whether self-aligning nuts are installed at certain locations of the aft pressure bulkhead tee; and corrective actions, if necessary. This amendment is prompted by reports of failures of certain Hi-Lok pin fasteners of the aft pressure bulkhead tee due to installation of non-self-aligning nuts. The actions specified by this AD are intended to prevent failure of certain Hi-Lok pin fasteners and subsequent gouging of the aft pressure bulkhead tee, which could result in fatigue cracking and reduced structural integrity of the airplane.
99-23-24: This amendment adopts a new airworthiness directive (AD), applicable to certain instrument landing system (ILS) navigation receivers manufactured by AlliedSignal. This action requires replacement of certain resistors in the ILS navigation receiver with higher ohm resistors and replacement of the nameplate on the receiver with a new nameplate. This amendment is prompted by reports of ILS navigation receivers incorrectly indicating signals from the glideslope ground station during final approach. The actions specified in this AD are intended to ensure the ILS receiver provides the flight crew with accurate glideslope data. Inaccurate glideslope data could result in an approach off the glideslope, and, consequently, a landing short of the runway or a runway overrun.
2014-08-04: We are superseding Airworthiness Directive (AD) 2012-03-04 for certain Airbus Model A310 series airplanes. AD 2012-03-04 required for certain airplanes, modifying the wire routing and installing additional protective sleeves. This new AD continues to require the actions in AD 2012-03-04, and requires additional work for certain airplanes. This AD was prompted by reports of new interferences of newly routed wire bundle 2S. We are issuing this AD to prevent short circuits leading to arcing, and possible fuel tank explosion.
99-24-03: This amendment supersedes two existing airworthiness directives (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently require inspections in the lower center cargo compartment at frame 1681 to verify that a certain bracket and a certain open face nylon clamp were installed to a specific wire bundle support and to detect damage of the subject wire bundle; and corrective actions, if necessary. This amendment requires a similar inspection and corrective actions required by the existing AD's and removes certain airplanes from the applicability of the existing AD's. This amendment also adds a requirement to install a wire assembly support bracket, clamp, and spacer, or revise the wire assembly support bracket and clamp installation; as applicable. This amendment is prompted by an incident in which the insulation blanket in the lower center cargo compartment was found to be burnt due to a missing wiring harness support bracket/clamp on a wirebundle. The actions specified by this AD are intended to prevent sparks, smoke, and possible fire in the lower center cargo compartment.
87-23-02: 87-23-02 AEROSPATIALE: Amendment 39-5761. Applies to Model ATR-42-300 series airplanes fitted with SOCEA flight attendants' seats, Part Numbers 2510132 and 2510137, certificated in any category. Compliance is required within 30 days after the effective date of this AD, unless already accomplished. To prevent collapse of the seat pan of the flight attendant's seats, accomplish the following: A. Modify seats in accordance with Aerospatiale Service Bulletin No. ATR42-25- 0003, Revision 2, dated November 5, 1986, or SOCEA Service Bulletin No. 25-73, dated June 1, 1986. 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 modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. 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 December 16, 1987.