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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.