Results
75-22-02: 75-22-02 AVCO LYCOMING: Amendment 39-2385. Applies to all Avco Lycoming T53 series engines. To prevent secondary failure of the N2 accessory drive shaft, as a result of binding of the torquemeter boost pump drive shaft, remove torquemeter boost pump, Part Number 1-300-221-01 or Part Number 1-300-221- 02, and replace with Part Number 1-300-221-03 or Part Number 1-300-221-04 within 200 hours time in service after the effective date of this AD. NOTE: Avco Lycoming Service Bulletin Number 0031 pertains to this subject. This amendment becomes effective October 29, 1975.
91-14-15: 91-14-15 HOFFMANN AIRCRAFT, LTD.: Amendment 39-7056. Docket No. 90-CE-51- AD. Applicability: Model H-36 Dimona motor gliders (serial numbers 3501 through 36143) that were supplied or equipped with a fuel tank made of glass fiber reinforced plastic (GFRP) or fiber reinforced plastic (FRP), certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To avoid engine shutdown caused by solid or rubber-like gelcoat fuel deposits, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) or within the next 6 calendar months, whichever occurs first, accomplish the following: (1) Statically ground the glider and the fuel system. (2) Empty the fuel tank through a drainer, ventilate the tank, and then remove the tank. (3) Remove the gasoline filter and inspect the filter and the fuel lines for solid or rubber-like deposits. Remove any solid or rubber-like deposits and thoroughly clean the filter. (4) Replace the GFRP or FRP fuel tank with an aluminum tank, Part Number 820.5.12 S3a, and reinstall the gasoline filter and reconnect the fuel lines. (5) Using pen and ink, correct the glider weight and balance data sheet as follows: (i) Decrease the empty weight by 2.2 pounds (1kg). (ii) Show a forward shift of 0.06 inches (1.5mm) of the empty weight center of gravity value. (6) Using pen and ink, change the Maintenance and Inspection checklist, page 36 of the maintenance manual, by adding the following notations: (i) "14. Check fuel lines and tank assembly for security and leaks." (ii) Enter the symbol "0" in columns marked "100 hours" and "500 hours". (b) If the aluminum tank required by paragraph (a)(4) of this AD has been ordered, but is not available, within the next 50 hours TIS or 6 calendar months after the effective date of this AD, whichever occurs first, and thereafter at intervals not toexceed 100 hours TIS or 12 calendar months, whichever occurs first, accomplish the following interim actions: (1) Statically ground the glider and the fuel system. (2) Empty the fuel tank through a drainer, ventilate the tank, and then remove the tank. (3) Remove the gasoline filter and inspect the filter and the fuel lines for solid or rubber-like deposits. Remove any solid or rubber-like deposits and thoroughly clean the filter. (4) Remove the finger filter and inspect it for solid or gelatinous deposits, remove any solid or gelatinous deposits, and thoroughly clean the filter. (5) Perform the following inspections on the inner side of the fuel tank: (i) Inspect for deposits through the filler hole with a mirror and light. (ii) Inspect for softened spots in the gelcoat with a wood spatula. (A) If no deposits or soft spots are found in the fuel tank as a result of these inspections, the glider may be operated until the fuel tank specified in paragraph (a)(4) of this AD becomes available. (B) If any deposits or soft spots are found in the tank as a result of these inspections, prior to further flight, replace the fuel tank in accordance with the instructions of paragraph (a) of this AD. (c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, 15 Rue de la Loi, B-1040 Brussels Belgium, c/o American Embassy APO, New York, New York 09667. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (d) Information that is related to this AD may be obtained from the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri. This amendment (39-7056, AD 91-14-15) becomes effective on August 12, 1991.
95-11-11 R1: This amendment clarifies information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas DC-10 and KC-10 series airplanes, that currently requires repetitive eddy current inspections to detect fatigue cracking of the pylon aft bulkhead flange, upper pylon box web, fitting radius, and adjacent tangent areas; and repair, if necessary. The actions specified in that AD are intended to prevent failure of the wing pylon aft bulkhead due to fatigue cracking, which could lead to separation of the engine and pylon from the airplane. This amendment clarifies the requirements of the current AD by specifying the type of initial and repetitive inspections that must be conducted. This amendment is prompted by communications received from affected operators that the current requirements of the AD are unclear.
2021-22-17: The FAA is adopting a new airworthiness directive (AD) for all Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. This AD was prompted by a report of cracking in certain components on left and right sides of the aft wing-to-body fairing (WTBF) structure near the tie-rod attachment at a certain fuselage station; this cracking likely resulted from excessive tie-rod preload. This AD requires inspecting the aft WTBF structure for any cracking or damage, adjusting the load on the two tie-rods at a certain fuselage station, and repair if necessary, as specified in two Transport Canada Civil Aviation (TCCA) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2009-21-08: We are adopting a new airworthiness directive (AD) for the products listed above. 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: Some cases of uncommanded steering action were observed, while the steering system was switched off. A leakage in the Steering Select/Bypass Valve, installed in the Steering Manifold, when closed, is suspected to have caused the uncommanded steering. If left uncorrected, this condition could lead to a potentially dangerous veer along the runway; in fact, according to the Aircraft Flight Manual limitations, the steering system must be in `off' position during landing and takeoff (in this case when airspeed is higher than 60 knots). We are issuing this AD to require actions to correct the unsafe condition on these products.
94-20-03: This amendment supersedes an existing airworthiness directive (AD) applicable to Bell Helicopter Textron, Inc. (BHTI) Model 206A, 206B, 206B-1, 206L, 206L-1, 206L-3, and 206L-4 helicopters, that currently requires an inspection of the main rotor hub trunnion (trunnion) for a mislocated master spline and replacement of any trunnion that has a mislocated master spline. This amendment is prompted by a report that certain main rotor hub trunnions (trunnions) were manufactured with a mislocated master spline. The actions specified by this AD are intended to identify and require replacement of any trunnion with a mislocated master spline to prevent pitch link misalignment, altered cyclic stick control position, loss of the main rotor system, and subsequent loss of control of the helicopter.
91-22-07: 91-22-07 MCDONNELL DOUGLAS: Amendment 39-8067. Docket No. 91-NM-88-AD. Supersedes AD 91-03-07, Amendment 39-6869. \n\n\tApplicability: Model DC-9-10, -20, -30, -40, and -50 series and C-9 (Military) series airplanes; fitted with left (LH) or right (RH) main landing gear (MLG) outboard door with a wing-mounted aluminum hinge half (Group I) or titanium hinge half (Group II); certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the loss of the LH or RH MLG outboard door, accomplish the following: \n\n\t(a)\tFor Group I airplanes: Within 30 days after February 11, 1991 (the effective date of Amendment 39-6869, AD 91-03-07), and thereafter at intervals not to exceed one year, accomplish the following in accordance with McDonnell Douglas Alert Service Bulletin A32-244, dated November 20, 1990, for both the LH and RH MLG outboard door assemblies: \n\n\t\t(1)\tInspect the MLG door for delamination; and \n\n\t\t(2)\tInspect the MLG door linkages and their attachments for corrosion, pitting, wear, and general conditions; and \n\n\t\t(3)\tInspect the MLG door hinge lobes on both the wing-mounted hinge half and door-mounted hinge half for cracks and corrosion; and \n\n\t\t(4)\tInspect the hinge halves on articulating doors for cracks and corrosion. \n\n\t(b)\tFor Group II airplanes: Within 50 days after the effective date of this AD, and thereafter at intervals not to exceed one year, accomplish the following in accordance with McDonnell Douglas Alert Service Bulletin A32-244, dated November 20, 1990, for both the LH and RH MLG outboard door assemblies: \n\n\t\t(1)\tInspect the MLG door for delamination; and \n\n\t\t(2)\tInspect the MLG door linkages and their attachments for corrosion, pitting, wear, and general conditions; and \n\n\t\t(3)\tInspect the MLG door hinge lobes on both the wing-mounted hinge half and door-mounted hinge half for cracks and corrosion; and \n\n\t\t(4)\tInspect the hinge halves on articulating doors for cracksand corrosion. \n\n\t(c)\tFor Group I and II airplanes: Within 18 months after the effective date of this AD, measure the aluminum hinge lobes, if bushed, for minimum wall thickness of .055 inch or greater, in accordance with McDonnell Douglas Alert Service Bulletin A32-244, dated November 20, 1990. \n\n\t(d)\tIf discrepancies are found as a result of the inspections required by paragraph (a), (b), or (c) of this AD, prior to further flight, repair in a manner approved by the Manager of the Los Angeles Aircraft Certification Office (ACO). \n\n\t(e)\tAn 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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. \n\n\t(f)\tSpecial flight permitsmay 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\t(g)\tThe inspection, replacement, and repair requirements shall be done in accordance with McDonnell Douglas Alert Service Bulletin A32-244, dated November 20, 1990. 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 McDonnell Douglas Corporation, P. O. Box 1771, Long Beach, California 90846-0001, Attention: Business Unit Manager, Technical Publications, C1-HDR (54-60). Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\tAirworthiness Directive 91-22-07 supersedes AD 91-03-07, Amendment 39-6869. \n\n\tThis amendment (39-8067, AD 91-22-07) becomes effective on December 3, 1991.
2021-24-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model EC130T2 helicopters. This AD was prompted by a report of degradation of the rear transmission shaft bearing support and the determination that all of the attachment rivets of the transmission shaft bearing support were sheared. This AD requires repetitive visual inspections of the rivets on the rear transmission shaft bearing support and of the local structure for cracking and missing, loose, or sheared rivets and accomplishment of applicable corrective actions, 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.
89-09-02: 89-09-02 DAVIS AIRCRAFT PRODUCTS CO., INC.: Amendment 39-6102. Applicability: Safety-belts which incorporate the black "Ultem" plastic latch-cover with the 90 degree type pull-release mechanism, as listed below: Affected Safety-Belt Part Numbers (P/N's) FDC-6400B-6 FDC-6400B-22 FDC-6400B-56 FDC-6400B-7-*** FDC-6400B-27-3 FDC-6400B-63-2 FDC-6400B-12 FDC-6400B-29 FDC-6400B-63-4 FDC-6400B-12B FDC-6400B-29-2 FDC-6400B-63-507 FDC-6400B-18-3 FDC-6400B-29B FDC-6400B-63-508 FDC-6400B-18-5 FDC-6400B-29B-2 FDC-6400B-64-*** FDC-6400B-18-21 FDC-6400B-30B FDC-6400B-71-*** FDC-6400B-18-23 FDC-6400B-31-** FDC-6400B-80B FDC-6400B-18-25 FDC-6400B-32 FDC-6400B-85 FDC-6400B-18-27 FDC-6400B-36-*** FDC-6400B-85-2 FDC-6400B-18-29 FDC-6400B-39 FDC-6400B-90 FDC-6400B-18-505 FDC-6400B-50-***-** FDC-6400B-90-3 FDC-6400B-19 FDC-6400B-51 FDC-6400B-90-7 FDC-6400B-20 FDC-6400B-54 FDC-6400B-**-***-**-** * Denotes numerical (arabic) digit. Compliance required within the next 100 flights, after the effective date of this AD, unless already accomplished. To prevent the possibility of the applicable safety-belts from becoming difficult to release or becoming completely jammed when actuated through 90 degrees, accomplish the following: (a) Inspect safety-belts to determine if they have any of the above P/N's inscribed on the FAA-TSO-C22f metallic tag. (b) Replace all safety-belts with the above P/N's with an approved safety-belt. NOTES: (1) Safety-belt assemblies that have been modified by Davis Aircraft Products Co., Inc., are marked with a -1 suffix number at the end of the Part Numbers (listed above) on the FAA-TSO-C22f metallic tag, and are approved. (2) Davis Aircraft Products Co., Inc. has issued (recall) Service Bulletin No. 1, dated January 29, 1988, indicating that the affected safety-belts may be returned to them for replacement at no charge for the rework and parts. (c) Upon request, anequivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (d) Upon submission of substantiating data, by an owner or operator, through an FAA Airworthiness Inspector, the Manager, New York Aircraft Certification Office, may adjust the compliance time specified by this AD. This amendment (39-6102, AD 89-09-02) becomes effective on May 24, 1989.
2009-23-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Two incidents have occurred due to the lack of visibility on the Primary Flight Display (PFD) of the Traffic Alert and Collision Avoidance System (TCAS) indications. * * * * * We are issuing this AD to prevent possible mid-air collisions due to lack of visibility of TCAS indications on the PFD. We are issuing this AD to require actions to correct the unsafe condition on these products.
60-10-05: 60-10-05 LOCKHEED: Amdt. 145 Part 507 Federal Register May 10, 1960. Applies to All Model 188 Aircraft. Compliance required as indicated. There have been reported instances of the main float closure port of the fuel tank vent valve remaining closed due to slight pressure in the tank. These pressures are considerably less than the 1.75 p.s.i. setting of the pressure relief poppet. There is also a possibility of sticking of the pressure relief poppet in the P/N 634056-1 tank vent valves. As a precautionary measure, underwing refueling must be accomplished with the overwing fuel caps removed until the following action has been taken. As soon as possible but no later than the next periodic inspection: (a) Drill a 1/8-inch hole in the suction relief flapper approximately halfway between the center of the flapper and the flapper seat. (b) Manually determine that the pressure relief poppet action is free. Upon accomplishment of above action normal underwing fueling procedures may be resumed. (Lockheed message to all Electra operators dated April 18, 1960, covers this same subject.) This airworthiness directive sent by telegram to all operators of 188 aircraft on April 19, 1960.
2021-21-05: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) GEnx-1B64, GEnx-1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx-1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/P1, GEnx-1B70C/ P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx-1B76A/P2, GEnx-2B67, GEnx-2B67/P, and GEnx-2B67B model turbofan engines. This AD was prompted by an in-service occurrence of loss of engine thrust control resulting in uncommanded high thrust. This AD requires revising the operator's existing FAA-approved minimum equipment list (MEL) by incorporating into the MEL the dispatch restrictions listed in this AD. This AD also requires initial and repetitive replacement of the electronic engine control (EEC) MN4 microprocessor. The FAA is issuing this AD to address the unsafe condition on these products.
78-17-08: 78-17-08 PRATT & WHITNEY AIRCRAFT: Amendment 39-3288. Applies to all Pratt & Whitney Aircraft JT9D-3, -3A, -7, -7A, -7AH, -7H, -7F, -7J, -20, and -20B turbofan engines containing fifteenth stage compressor disk, P/N 672915 or P/N 658615. Compliance required as indicated, unless already accomplished. To preclude failures of fifteenth stage compressor disks due to low cycle fatigue cracking, inspect disks in accordance with the procedures specified in Pratt & Whitney Aircraft Alert Service Bulletin 4908, dated August 7, 1978, or later revision approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region, as specified below: (a) For disks with 6500 or more cycles in service, on the effective date of this AD, inspect within the next 100 cycles in service. (b) For disks having less than 6500 cycles in service, on the effective date of this AD, inspect prior to reaching 6600 cycles. (c) Reinspect the disks in paragraphs (a) and (b) in accordance with the following schedule: 1. Disks inspected by the Rim Access Ultrasonic Inspection method must be reinspected within the next 600 cycles and every 600 cycles in service thereafter. 2. Disks inspected by the HPC Central Cavity Access or the Detail Access Eddy Current Inspection method must be reinspected within the next 1600 cycles and every 1600 cycles thereafter. If any crack indications are found, the disk must be removed from service prior to further flight. In no case shall the established life limit of the disk be exceeded. Upon request of the operator, an equivalent method of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, New England Region, may adjust the repetitive inspection interval specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. 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 & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the Federal Aviation Administration, New England Region 12 New England Executive Park, Burlington, Massachusetts, 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 the New England Region. This amendment becomes effective September 1, 1978.
91-10-04: 91-10-04 TEXTRON LYCOMING: Amendment 39-6981. Docket No. 91-ANE-10. Applicability: Textron Lycoming Model TIO-540-AE2A engines, with serial numbers up to but not including L9161-61A, except L9157-61A, installed in Piper Malibu Mirage aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent engine power loss, engine fire, and possible loss of aircraft, accomplish the following: (a) Remove and replace exhaust transition flange bolts, within the next 10 hours in service, after the effective date of this AD, in accordance with the following procedures: (1) Apply penetrating oil to existing exhaust transition flange bolts and remove the two bolts. (2) Install the following hardware in place of the removed bolts: LYCOMING PART NO. DESCRIPTION QUANTITY LW-31SS-1.19 Bolt 2 77611 Gasket 1 STD-2043 Nut 2 (3) Torque the bolts to 17 ft.-lbs. (Do not use lockwashers on the bolts.) It may be necessary to start thelock nut prior to torqueing. (4) Install the locknuts on the protruding threads of the bolts, and insure that the bolts do not loosen during installation. (5) Recheck torque on bolt heads to ensure proper torque is retained (17 ft.-lbs.) NOTE: Further information can be obtained from Textron Lycoming Service Bulletin No. 491A, dated February 21, 1990. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, New York Aircraft Certification Office, ANE-170, Engine and Propeller Directorate, Aircraft Certification Service, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Textron Lycoming/Subsidiary of Textron Inc., Williamsport, Pennsylvania 17701. These documents may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts. This amendment (39-6981, AD 91-10-04) becomes effective on May 21, 1991.
97-07-06: This amendment supersedes an existing priority letter airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. Model 412 helicopters, that currently requires a daily inspection of certain swashplate support assemblies. It also requires a reduction in VNE, and installation of appropriate airspeed indicator markings and a placard. This amendment requires the same actions required by the existing priority letter AD, but restricts the applicability to the Model 412 helicopters with a certain steel main rotor control swashplate support assembly (steel swashplate support assembly) installed. This amendment also allows the installation of an improved main rotor control swashplate assembly that terminates the requirements of this AD. This amendment is prompted by reported cracking and in-service failures of certain steel swashplate support assemblies. The actions specified by this AD are intended to prevent failure of the steel swashplate support assembly that could result in loss of main rotor control and subsequent loss of control of the helicopter.
2009-25-07: We are adopting a new airworthiness directive (AD) for the Eurocopter France (ECF) Model EC120B helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community. The MCAI AD states that operators have reported that latching push buttons on the Emergency Floatation Gear Lighting and Ancillary Control Unit (LACU) used to arm the emergency floatation gear are unreliable, and the `FLOAT ARM' pushbutton does not latch in the depressed (LACU armed) position. These actions are intended to prohibit flight over water if a functional test indicates that the emergency floatation gear cannot be armed, which would preclude deployment of the floats in an emergency water ditching that could result in helicopter damage and a fatality.
93-24-10: 93-24-10 LEARJET: Amendment 39-8759. Docket 93-NM-95-AD. Applicability: Model 55, 55B, and 55C airplanes; serial numbers 55-003 through 55-147, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the loss of both generators during flight, accomplish the following: (a) Within 100 hours time-in-service or 90 days after the effective date of this AD, whichever occurs later, modify the wiring inside the left- and right-hand generator interface boxes and between these two boxes, and perform an operational test of the DC power distribution system in accordance with Learjet Service Bulletin SB 55-24-4, dated May 3, 1993. (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, Wichita Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (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 and operational test shall be done in accordance with Learjet Service Bulletin SB 55-24-4, dated May 3, 1993. 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 Learjet Corporation, Customer Services, P.O. Box 7707, Wichita, Kansas 67277-7707. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on January 18, 1994.
2008-05-18 R1: We are adopting a new airworthiness directive (AD) for the products listed above that would revise an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *. * * * * * Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements. ThisAD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective November 23, 2009. On April 16, 2008 (73 FR 13071, March 12, 2008), the Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD. We must receive comments on this AD by December 21, 2009.
92-02-03: 92-02-03 BOEING: Amendment 39-8139. Docket No. 91-NM-259-AD. \n\n\tApplicability: Model 727 and 727-100 series airplanes; equipped with a main cargo deck door installed in accordance with Supplemental Type Certification (STC) SA1368SO; certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent an inadvertent in-flight opening of the main deck cargo door, accomplish the following: \n\n\t(a)\tWithin 30 days after the effective date of this AD and thereafter prior to takeoff, each time the cargo door is cycled, verify that all seven cargo door latch lockpins are operative. Inoperative latch lockpins must be repaired, prior to further flight, in accordance with an FAA- approved method. \n\n\t(b)\tAn 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, Atlanta Aircraft Certification Office (ACO), ACE-115A, FAA, Small AirplaneDirectorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Atlanta ACO, ACE-115A. \n\n\t(c)\tSpecial 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. \n\n\t(d)\tThis amendment (39-8139, AD 92-02-03) becomes effective on January 21, 1992.
2009-25-08: We are adopting a new airworthiness directive (AD) for the BHTC Model 407 and Model 427 helicopters. This AD results from mandatory continuing airworthiness information (MCAI) ADs issued by the aviation authority of Canada. The MCAI ADs state that some hydraulic pump driveshaft assemblies may have been delivered with a missing internal plug or fastening rivet. This condition, if not corrected, could result in a loss of hydraulic pressure and subsequent loss of control of the helicopter.
2009-22-14: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747-200C and 747-200F series airplanes. This AD requires installing larger moisture shrouds and additional drain lines in the electrical/electronic equipment center. This AD results from reports of water contamination in the electrical/electronic units in the main equipment center. We are issuing this AD to prevent water contamination in the electrical/electronic units in the main equipment center, which could result in an electrical short and potential loss of several functions essential for safe flight.
2000-23-03: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time general visual inspection for proper rigging of the liftdumper micro switches installed in the left- and right-hand sides of the pedestal; a functional check of the micro switches; and re-rigging the cam, if necessary. The actions specified by this AD are intended to detect and correct improper rigging of the liftdumper micro switches, which could result in inadvertent extension of the liftdumpers during takeoff roll. This action is intended to address the identified unsafe condition.
77-15-13: 77-15-13 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2983. Applies to Model DH-114 airplanes certificated in all categories. Compliance is required within the next 300 hours time in service after the effective date of this AD, unless already accomplished. To prevent the possible seizure of the main landing gear damper ram, and consequent damage to the aircraft upon landing, accomplish the following: (a) Modify the damper ram, P/N AC11164, in accordance with Part A of the section entitled "Accomplishment Instructions" of Dunlop Aviation Division Service Bulletin 32-824, dated April 5, 1973, or an FAA-approved equivalent. (b) Upon completion of the modification specified in paragraph (a) of this AD, reidentify the modified damper ram as P/N AC65528, Mod. 1. (Hawker Siddeley Aviation, Ltd., Series: Heron (114), TNS. U.15, Issue 2, dated April 30, 1973, refers to this same subject.) This amendment becomes effective August 24, 1977.
2021-22-19: The FAA is superseding Airworthiness Directive (AD) 2011-07-02 for all Pratt & Whitney (P&W) JT8D-209, JT8D-217, JT8D-217A, JT8D-217C, and JT8D-219 model turbofan engines. AD 2011-07-02 required initial and repetitive torque inspections of the 3rd-stage and 4th-stage low- pressure turbine (LPT) blades. AD 2011-07-02 also required replacement of the LPT blade if wear limits are exceeded, replacement of the LPT- to-exhaust case bolts and nuts, and installation of crushable sleeve spacers on the bolts. This AD was prompted by a report of an MD-82 airplane, equipped with a JT8D-217C model turbofan engine, experiencing an engine surge that resulted in the fracture of the LPT blade and uncontained release of the LPT blade. This AD retains certain requirements of AD 2011-07-02, while revising the inspection thresholds and replacement intervals for the 3rd-stage and 4th-stage LPT blades. The FAA is issuing this AD to address the unsafe condition on these products.
91-18-01: 91-18-01 AIRBUS INDUSTRIE: Amendment 39-8004. Docket No. 91-NM-135-AD. Applicability: Model A300 B2-1C, B2K-3C, and B2-203 series airplanes, on which Modification Number 7811H1110 (described in Airbus Industrie Service Bulletin A300-57-165, dated May 21, 1990) has not been accomplished, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the wings, accomplish the following: (a) Prior to the accumulation of 11,000 landings, or within the next 25 landings after the effective date of this AD, whichever occurs later, perform a high frequency eddy current inspection of the vertical web of the front spar of both wings between ribs 10 and 11 to detect cracks, in accordance with Airbus Industrie All-Operators Telex (AOT) 57-03, Issue 2, dated June 13, 1991. Repeat this inspection at intervals not to exceed 25 landings thereafter, in accordance with AOT 57-04, dated June 21, 1991.(b) If cracks are found as a result of the initial or repetitive inspections, repair prior to further flight, in accordance with Airbus Industrie All-Operators Telex 57-03, Issue 2, dated June 13, 1991. (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) 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. (e) The inspection and repair requirements shall be done in accordance with Airbus Industrie All-Operators Telex (AOT) 57-03, Issue 2, dated June 13, 1991, and AOT 57-04, dated June 21, 1991. 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-8004, AD 91-18-01) becomes effective on September 3, 1991.