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93-04-03: 93-04-03 GENERAL DYNAMICS: Amendment 39-8505. Docket 92-NM-202-AD. Applicability: Model 340, 440, and C-131B through C-131H (military) series airplanes, all serial numbers, certificated in any category, including those modified for turbo-propeller power. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the stabilizer attach fittings, and potential subsequent loss of a horizontal or vertical stabilizer, accomplish the following: (a) Within 12 months or 1,500 flight hours after the effective date of this AD, whichever occurs first, accomplish paragraphs (a)(1) and (a)(2) of this AD: (1) Inspect both horizontal stabilizers and vertical stabilizer attach fittings in accordance with General Dynamics, Convair Division, Service Bulletin 640(340D) S.B. No. 55-6, Paragraph 2.A, Accomplishment Instructions, Part 1, dated September 1, 1992. If the attach fittings are not within the tolerance limitations specified in the Convair 440 Structural Repair Manual, prior to further flight, bush the fittings in accordance with the repair manual. (2) Perform a hardness test of the horizontal and vertical stabilizer taper pins and split sleeve bushings in accordance with normal maintenance procedures. The equivalent strength values for the pins and bushings based on the hardness test must be between 160-180 ksi. Taper pins and split sleeve bushing received directly from Convair and bearing the Convair mark are excluded from this requirement. NOTE: The Convair mark is an etched mark: CV SD It is located on a flat side near the top of the taper pin, and on the top of the bushing. (i) If the pins or bushings have a lower strength value than 160 ksi, if they are worn into the parent metal, if they show signs of corrosion, or if they have been ground and replated, prior to further flight, remove the discrepant part(s) and replace it with a new FAA-approved part(s). Reworked parts are not acceptable for use as replacement parts. (ii) Prior to installing any FAA-approved new taper pin or split sleeve bushing on the airplane, perform a hardness test on the part(s) and ensure that the equivalent strength value is between 160 and 180 ksi. Parts having a strength value lower than 160 ksi shall not be installed. Taper pins and split sleeve bushing received directly from Convair and bearing the Convair mark are excluded from this requirement. (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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport 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, Los Angeles ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles 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 inspection shall be done in accordance with General Dynamics, Convair Division, Service Bulletin 640(340D) S.B. No. 55-6, dated September 1, 1992. 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 General Dynamics, Convair Division, Lindberg Field Plant, P.O. Box 85377, San Diego, California 92138, Attention: L.J. Hayes. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on April 19, 1993.
99-27-14: This document corrects a typographical error that appeared in airworthiness directive (AD) 99-27-14 that was published in the Federal Register on January 6, 2000 (65 FR 697). The typographical error resulted in a reference to an incorrect AD number. This AD is applicable to all Airbus Model A340-211, -212, -213, -311, -312, and -313 series airplanes. This AD requires repetitive operational tests to ensure proper operation of the actuator of the secondary locks of the thrust reversers, and corrective actions, if necessary.
92-12-02: 92-12-02 ISRAEL AIRCRAFT INDUSTRIES (IAI), LTD.: Amendment 39-8262. Docket No. 91-NM-272-AD. Supersedes AD 90-10-04, Amendment 39-6589. Applicability: Israel Aircraft Industries (IAI), Ltd., Model 1123, 1124, and 1124A Westwind series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced controllability of the airplane, accomplish the following: (a) Within 20 hours time-in-service after May 18, 1990 (the effective date of AD 90-10-04, Amendment 39-6589), and thereafter at intervals not to exceed 150 hours time-in-service, perform a detailed visual inspection to detect evidence of corrosion, such as pits, and/or blisters under the paint, on the lower exterior surface of the aileron torque transfer tubes, in accordance with Astra Service Bulletin 1123-27-026 (for Model 1123 Westwind series airplanes), Revision 1, dated April 25, 1990; or Astra Service Bulletin 1124-27-100 (for Models 1124 and 1124A Westwind series airplanes), Revision 1, dated April 25, 1990. (b) If corrosion or cracks are found as a result of the inspections required by paragraph (a) of this AD, prior to further flight, remove and replace the aileron control rod assemblies with improved assemblies, P/N 513506-503 RD or RE, in accordance with Astra Service Bulletin 1123-27-026 (for Model 1123 Westwind series airplanes), Revision 1, dated April 25, 1990, or Revision 2, dated April 24, 1991; or Astra Service Bulletin 1124-27-100 (for Models 1124 and 1124A Westwind series airplanes), Revision 1, dated April 25, 1990, or Revision 2, dated April 24, 1991. (c) Within 150 hours time-in-service after the effective date of this AD, or within 6 months after the effective date of this AD, whichever occurs first, replace the left and right aileron rod assemblies with improved rod assemblies, P/N 513506-503 RD or RE, in accordance with Astra Service Bulletin 1123-27-026 (for Model 1123 Westwind series airplanes), Revision 2, dated April 24, 1991; or Astra Service Bulletin 1124-27-100 (for Models 1124 and 1124A Westwind series airplanes), Revision 2, dated April 24, 1991. (d) Replacement of the left and right aileron rod assemblies with improved rod assemblies, P/N 513506-503 RD or RE, in accordance with Astra Service Bulletin 1123-27-026 (for Model 1123 Westwind series airplanes), Revision 2, dated April 24, 1991; or Astra Service Bulletin 1124-27-100 (for Models 1124 and 1124A Westwind series airplanes), Revision 2, dated April 24, 1991; constitutes terminating action for the requirements of this AD. (e) 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Standardization Branch, ANM-113. (f) 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. (g) The inspections and replacement shall be done in accordance with Astra Service Bulletin 1123-27-026 (for Model 1123 Westwind series airplanes), Revision 1, dated April 25, 1990, or Revision 2, dated April 24, 1991; or Astra Service Bulletin 1124-27-100 (for Models 1124 and 1124A Westwind series airplanes), Revision 1, dated April 25, 1990, or Revision 2, dated April 24, 1991; as applicable. 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 Astra Jet Corporation, Technical Publications, 77 McCullough Drive, Suite 11, New Castle, Delaware 19720. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (h) This amendment becomes effective on July 31, 1992.
80-22-55 R4: 80-22-55 R4 SIKORSKY AIRCRAFT: Amendment 39-4018 as amended by Amendment 39-4043 is further amended by Amendment 39-4336. Applies to S-76A series helicopters certificated in all categories. To prevent operation with cracked or separated main rotor damper piston rods accomplish the following: 1. Within 25 hours time in service, after the effective date of this AD, and thereafter at intervals not to exceed 30 hours time in service, conduct dye penetrant inspections for cracks in the piston rods of P/N 76106-08000-042 and -043 main rotor dampers with more than 400 hours time in service or that have had a damper spherical bearing replaced. Accomplish these inspections in accordance with specification MIL-I-6866, Type II, Method C, and with at least a 3-power magnifying glass. Protect piston seals and rod end bearings from cleaning and inspection fluids. If a crack is found, replace the piston rod prior to further flight with a serviceable piston rod. 2. On sphericalbearings of P/N 76106-08000-042 and -043 main rotor dampers with more than 100 hours time in service: Within the next 25 hours time in service, after the effective date of this AD, and thereafter at intervals not to exceed 15 hours time in service, conduct a bearing wear inspection of the spherical bearings of P/N 76106-08000-042 and -043 main rotor dampers in accordance with Item 88 of Temporary Revision 5-27 (reference Paragraph 9 of Temporary Revision 5-23) of Sikorsky S-76 Maintenance Manual No. SA4047-76-2. When a damper spherical bearing fails to meet the wear criteria of this inspection, conduct a dye penetrant inspection in accordance with the specification in paragraph 1 of the damper piston rod for cracks. If a crack is found, replace the piston rod prior to further flight with a serviceable piston rod. Note: Mandatory requirements for wear inspections of the spherical bearings of P/N 76106-08000-044 dampers are contained in Airworthiness Limitations Section, Chapter 4, Sikorsky S-76A Maintenance Manual, 5A 4047-76-2-1. 3. Other methods of compliance with this directive must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England-Region, 12 New England Executive Park, Burlington, Massachusetts 01803. NOTE: The following revisions to the Sikorsky S-76 Maintenance Manual No. 5A 4047-76-2 pertain to the subject matter of this directive. a. Item 28 of Temporary Revision No. 5-21, dated January 28, 1981. b. Item 88 of Temporary Revision No. 5-27, dated January 28, 1981 (reference Paragraph 9 of Temporary Revision 5-23). c. Temporary Revision No. 5-31, dated January 28, 1981. 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 Sikorsky Aircraft, Division of United Technologies Corporation, Stratford, Connecticut 06602. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.in., Washington, D.C. A historical file on this AD is maintained by the FAA at its Headquarters in Washington, D.C., and at the FAA, New England Region Headquarters, Burlington, Massachusetts. Amendment 39-4018 became effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated October 24, 1980, and air mail letter dated November 21, 1980. Amendment 39-4043 became effective February 15, 1981. This amendment 39-4336 becomes effective March 10, 1982.
2014-21-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-10-10, DC-10-10F, DC-10-30, DC-10-30F (KC- 10A and KDC-10), DC-10-40, MD-10-10F, and MD-10-30F airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the forward cargo compartment frames are subject to widespread fatigue damage (WFD). This AD requires an inspection of the attachment holes at the forward cargo compartment frames and the cargo liner for cracking, and repair if necessary. This AD would also require installing new oversized fasteners in the forward cargo compartment frames. We are issuing this AD to prevent fatigue cracking of the forward cargo compartment frames, which could result in loss of the fail-safe structural integrity of the airplane.
2014-21-04: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This AD was prompted by reports of cracks emanating from the aft-most barrel nut holes of the left and right upper rear spar caps of the horizontal stabilizer. This AD requires repetitive high frequency eddy current (ETHF) inspections for cracks in the areas around the two aft-most barrel nut holes of the upper rear spar caps, and corrective actions if necessary; and repetitive ETHF inspections for cracks in the areas around the two aft- most barrel nut holes of any repaired or replaced upper rear spar cap, and corrective actions if necessary. We are issuing this AD to detect and correct cracks in the horizontal stabilizer, which could propagate until an upper rear spar cap severs, and result in failure of the horizontal stabilizer upper center or aft skin panel and adversely affect the structural integrityof the airplane.
2014-15-02 R1: We are adopting a new airworthiness directive (AD) for Fiberglas-Technik Rudolf Lindner GmbH & Co. KG (type certificates formerly held by GROB-WERKE GMBH & CO KG and BURKHART GROB LUFT- UND RAUMFAHRT GmbH & CO KG) Models G102 STANDARD ASTIR III, G102 CLUB ASTIR III, G102 CLUB ASTIR IIIb, G103 TWIN II, G103A TWIN II ACRO, G103C TWIN III ACRO, and G 103 C Twin III SL gliders. This AD revises AD 2014-15- 02, which required inspection of the rudder control unit for installation of plastic cable pulleys and replacement of plastic cable pulleys with aluminum cable pulleys. This AD retains the actions of AD 2014-15-02 but clarifies the suffixes of serial numbers (S/Ns) in paragraph (c) Applicability. This AD was prompted by reports of plastic control cable pulleys developing cracks due to aging, which could lead to breaking of the pulley and potentially jamming the rudder control unit, possibly resulting in loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
2000-04-16: This amendment adopts a new airworthiness directive (AD) that applies to all Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Models ASH 25M and ASH 26E sailplanes. This AD requires that you accomplish the following: - check to see if the sailplane has a muffler marked with an X on the front plate; - accomplish pre-flight checks on the carbon reinforced plastic fairing for signs of overheat traces and/or perform boroscope inspections, depending on the number of sailplane hours accumulated; and - replace the muffler with an improved design muffler either at a certain time period or immediately if discrepancies are found during any inspection. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent excessive radiation from causing the carbon fiber shroud on the engine muffler to delaminate. The carbon fiber shroud serves the same function as a firewall and delamination could cause a fire to spread throughout the sailplane.
2000-04-21: This amendment adopts a new airworthiness directive (AD), applicable to MD Helicopters Inc. (MDHI) Model MD600N helicopters, that requires inspecting each internal fuel hose connection to verify proper installation. This amendment is prompted by the discovery that certain fuel hose connections between the fuel cells and the engine can be incorrectly installed. The actions specified by this AD are intended to prevent fuel starvation of the engine while the fuel gage indicates fuel remaining in the tank, engine flameout, and a subsequent forced landing.
2022-19-09: 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 reports of in-service findings of corrosion on the flange of the main landing gear (MLG) lower spindle pin. This AD requires repetitive inspections of the left and right MLG lower spindle pins to detect corrosion, and applicable repair or replacement if necessary, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.