Results
2023-02-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B2K-3C, B2-203, B4-2C, and B4-203 airplanes. This AD was prompted by a determination that internal system pollution can occur, most likely due to corroded unions in the pressurization lines, with an associated risk of contamination of the check valves. This AD requires repetitive inspections (functional checks) of the pressurization of the hydraulic system reservoirs, and corrective actions if necessary, 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.
2001-23-17: This amendment adopts a new airworthiness directive (AD) that applies to certain GARMIN International (GARMIN) GNS 430 units that are installed on aircraft. This AD requires you to modify the unit to incorporate circuitry changes to the GNS 430 unit's deviation and flag outputs. This AD is the result of reports of inaccurate course deviations caused by external electrical noise to the GNS 430 unit's course deviation indicator (CDI). The actions specified by this AD are intended to prevent such external noise from causing inaccurate course deviation displays in the GNS 430 unit's CDI or horizontal situation indicator (HSI). Such displays could result in the pilot making flight decisions that put the aircraft in unsafe flight conditions.
2001-24-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers Model SD3 series airplanes, that requires repetitive tests (checks) of the engine power lever to ensure that the fuel control unit (FCU) lever is contacting the maximum stop, adjustment of the FCU rigging, if necessary, and an engine ground run for correct gas generator rotational speed. This AD also requires a static reduced power check on each engine to ensure correct operation of the reserve takeoff power (RTOP) system; and follow-on actions, if necessary. This action is necessary to prevent failure of the engines to reach adequate RTOP boost during takeoff, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2017-11-05: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) AE 3007C and 3007C1 turbofan engines. This AD was prompted by analysis and by cracks found in the high- pressure turbine (HPT) wheel during an inspection. This AD requires replacement of the affected HPT wheels at new, lower life limits. We are issuing this AD to correct the unsafe condition on these products.
2001-24-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 707-100, -100B, -300, and -E3A (military airplanes); 727-100 and -200; 737-200, -200C, -300, -400, and -500; 747SP and 747SR; 747-100B, -200B, -200C, -200F, -300, -400, and -400D; 757-200 and -200PF; and 767-200 and -300 series airplanes. This AD requires inspection of the attachment of the shoulder restraint harness to the mounting bracket on certain observer and attendant seats to determine if a C-clip is used in the attachment, and corrective action, if necessary. This action is necessary to prevent detachment of the shoulder restraint harness of the attendant or observer seat from its mounting bracket during service, which could result in injury to the occupant of the seat. This action is intended to address the identified unsafe condition.
2001-24-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires a one-time detailed visual inspection of certain wire bundles located in the aft section of the strut forward fairing panel of both engine struts to detect chafing damage, and repair or replacement of wiring, if necessary. This amendment also requires replacement of wires repaired by splicing and damaged wires that require splicing, and replacement of the support brackets of the existing wire bundles with new brackets and clamps, which would terminate the existing requirements. The actions specified by this AD are intended to prevent the potential for dual wire faults from grounded, separated, or shorted wires; which could result in inadvertent takeoff thrust overboost, in-flight loss of thrust, or engine shutdown.
2017-11-15: We are adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80C2L1F turbofan engines. This AD was prompted by a reduction in the life limit of the affected engines which is the result of a revised operating profile. This AD requires replacement of the high-pressure turbine (HPT) spacer/impeller, part number (P/N) 1539M12P02, at a newer, lower life limit. We are issuing this AD to correct the unsafe condition on these products.
97-21-12: 97-21-12 CONSTRUCCIONES AERONAUTICAS, S.A. CASA: Amendment 39-10165. Docket 96-NM-126-AD. Applicability: Model CN-235 series airplanes, as listed in CASA Service Bulletin SB-235-53-20, Revision 2, dated June 9, 1994 (for non-military airplanes); and Service Bulletin SB-235-53-20M, Revision 1, dated November 27, 1995 (for military airplanes); certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed bythis AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue cracking in the area of the center wing-to-fuselage attachment fitting, which consequently could reduce the structural integrity of this area, accomplish the following: (a) For non-military airplanes: Prior to the accumulation of 17,000 total landings, accomplish the actions specified in paragraphs (a)(1), (a)(2), and (a)(3) of this AD: (1) Remove all parts and other items in the area of the center wing-to-fuselage attachment fitting, in accordance with Paragraph 2.B. ("Removal") of the Accomplishment Instructions of CASA Service Bulletin SB-235-53-20, Revision 2, dated June 9, 1994. (2) After all parts and other items have been removed in accordance with paragraph (a)(1) of this AD, conduct a visual inspection, using a magnifier of at least 10x magnitude, to detect fatigue cracking in this area (ref: Figure 1, Sheet 1, of the service bulletin). If any cracking is detected, prior to further flight and prior to installing the reinforcing plate in accordance with paragraph (a)(3) of this AD, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (3) Install a reinforcing plate having CASA part number (P/N) 35-25010-0101 in the attachment area of the center wing-to-fuselage attachment fitting, in accordance with the service bulletin. (b) For military airplanes: Prior to the accumulation of 15,000 total landings, accomplish the actions specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD: (1) Remove all parts and other items in the area of the center wing-to-fuselage attachment fitting, in accordance with Paragraph 2.B. ("Removal") of the Accomplishment Instructions of CASA Service Bulletin SB-235-53-20M, Revision 1, dated November 27, 1995.(2) After all parts and other items have been removed in accordance with paragraph (b)(1) of this AD, conduct a visual inspection, using a magnifier of at least 10x magnitude, to detect fatigue cracking in this area (ref: Figure 1, Sheet 1, of the service bulletin). If any cracking is detected, prior to further flight and prior to installing the reinforcing plate in accordance with paragraph (b)(3) of this AD, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA. (3) Install a reinforcing plate having CASA part number (P/N) 35-25010-0101 in the attachment area of the center wing-to-fuselage attachment fitting, in accordance with the service bulletin. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector,who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (e) Certain actions shall be done in accordance CASA Service Bulletin SB-235-53-20M, Revision 1, dated November 27, 1995 (for military airplanes); and CASA Service Bulletin SB-235-53-20, Revision 2, dated June 9, 1994 (for non-military airplanes), which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1 1 April 13, 1994 2 2 June 9, 1994 3-11 Original July 29, 1993 This incorporation byreference 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 Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. NOTE 3: The subject of this AD is addressed in Spanish airworthiness directive 03/94, dated August 1994. (f) This amendment becomes effective on November 24, 1997.
93-01-21: 93-01-21 AIRBUS INDUSTRIE: Amendment 39-8475. Docket 92-NM-244-AD. Applicability: Model A320 series airplanes on which Modification 22561 has not been installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the smoke detection system to provide warning of a fire in the lavatory, accomplish the following: (a) Within 450 hours time-in-service after the effective date of this AD, perform a close visual inspection to detect damage or blockage of the flexible hoses that connect the smoke detector to the air extraction duct in each lavatory, and to detect contamination of the hoses, air extraction ducting, hose/duct connection, or inlet grid, in accordance with Airbus Industrie All Operator Telex (AOT) 26-07, dated October 6, 1992. (1) If any damaged hose is found as a result of the inspection required by paragraph (a) of this AD, prior to further flight, repair or replace the damaged hose, in accordance with the AOT. If any damaged hose is repaired, that hose must then be replaced with a new hose within 400 hours time-in-service following the repair. (2) If any blocked hose or contaminated hose, air extraction ducting, hose/duct connection, or inlet grid is found as a result of the inspection required by paragraph (a) of this AD, prior to further flight, clean the blocked or contaminated part, in accordance with the AOT. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained fromthe Standardization Branch. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspection, repair, and replacement shall be done in accordance with Airbus Industrie All Operators Telex (AOT) 26-07, dated October 6, 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on February 10, 1993.
2025-11-07: The FAA is superseding Airworthiness Directive (AD) 2024-19-11 for all Robinson Helicopter Company Model R44 and R44 II helicopters. AD 2024-19-11 required visually inspecting a certain flex plate assembly (flex plate) and certain clutch shaft forward yokes (yokes), including each flex plate bolt, and depending on the results, taking corrective actions. AD 2024-19-11 also required removing certain yokes from service within a specified threshold, or as an alternative, performing in-depth inspections. Since the FAA issued AD 2024-19-11, it has been determined that clarifications regarding the alternative inspections are necessary. This AD requires the actions of AD 2024-19- 11 and clarifies that the alternative inspections are repetitive and adds a particular paint remover option to use when performing those alternative inspections. The FAA is issuing this AD to address the unsafe condition on these products.