Results
2022-21-14: The FAA is superseding Airworthiness Directive (AD) 2017-10- 17, which applied to certain Airbus SAS Model A330-200; A330-200 Freighter; and A330-300 series airplanes. AD 2017-10-17 required revising the existing maintenance or inspection program, as applicable, to incorporate new fuel airworthiness limitations. This AD was prompted by a determination that new or more restrictive fuel airworthiness limitations and tasks are necessary. This AD continues to require the actions in AD 2017-10-17 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive fuel airworthiness limitations and tasks, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also expands the applicability to include additional airplane models. The FAA is issuing this AD to address the unsafe condition on these products.
2022-21-07: The FAA is adopting a new airworthiness directive (AD) for all Deutsche Aircraft GmbH (Type Certificate Previously Held by 328 Support Services GmbH; AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 and -300 airplanes. This AD was prompted by a safety analysis that lithium batteries installed in the personal electronic devices (PED) are a potential risk of an in-flight fire in the flight deck stowage boxes. This AD requires installing a placard and stowing the fire gloves on the left-hand (LH) flap door of the flight deck step; and installing the placards on the LH and right-hand (RH) flight deck stowage boxes. This AD also requires revising the operator's existing airplane flight manual (AFM) to include emergency procedures, 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.
2006-06-03: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Model 500, 501, 550, S550, 551, and 560 airplanes. This AD requires revising the airplane flight manual (AFM) to prohibit use of the wing fuel boost pumps for defueling under certain conditions; installing a placard; doing other specified investigative and corrective actions as necessary; and modifying the boost pumps. This AD also requires the subsequent removal of the AFM revision and placard. This AD results from a report of a chafed electrical wiring harness, which was arcing inside the fuel tank. We are issuing this AD to prevent potential fuel vapor ignition in a fuel tank, which could result in explosion and loss of the airplane.
98-21-30: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes and all Model A310 and A300-600 series airplanes, that requires repetitive inspections for wear damage of the aft attachment fittings of the articulated seats and dummy tracks in the passenger compartment; and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct wear damage of the aft attachment fittings of the articulated seats and dummy tracks. Such wear damage could cause the floor panels to sag and result in failure of flight control systems and consequent reduced controllability of the airplane.
76-15-05: 76-15-05 CANADAIR: Amendment 39-2676 as amended by Amendment 39-3181. Applies to all CL-44D4 and CL-44J airplanes, certificated in all categories. Compliance required as indicated unless already accomplished. Affects the nose landing gear retraction actuator lever attachment bolts. (a) On airplanes with nose landing gear retraction actuator lever attachment bolts, P/N 44-85279, installed: (1) Within the next 250 landings after the effective date of this AD, accomplish the following: (i) Replace bolts with unused vacuum cadmium plated Voi-Shan bolts, P/N V.S.2738, or equivalent bolts. Voi-Shan bolts are identified by part number impression on the bolt head. (ii) Install V.S.2738 bolts in accordance with paragraph 4.1(e) through 4.1(h) of Canadair Service Information Circular No. 387-CL44, Issue 2, (SIC) or an equivalent installation. (b) On airplanes with V.S.2738 bolts installed: (1) Within the next 25 landings after the effective date of this airworthiness directive, accomplish the following: (i) Inspect V.S.2738 bolts in accordance with paragraph 4.1(a) through 4.1(c) of the SIC, or an equivalent inspection, for cracks, corrosion, pitting, or rework by chrome plating. (ii) Replace bolts showing signs of any of the above defects, before further flight, with unused V.S.2738 bolts, and install in accordance with paragraph 4.1(c) thru 4.1(h) of the SIC or approved equivalent procedure. (2) Vacuum cadmium plated V.S.2738 bolts, found free from defects, may be reinstalled provided: (i) Within the next 500 hours in service or 125 landings, whichever occurs first, after reinstallation and thereafter, at intervals not to exceed 500 hours in service or 125 landings from the last inspection, the bolts are inspected for cracks by magnetic particle inspection or eddy current inspection or an equivalent procedure. (ii) Reinstalled bolts that have attained 5000 hours in service or 1250 landings, must be replaced with unused V.S.2738 bolts or equivalent bolts, and installed in accordance with paragraph 4.1(c) thru 4.1(h) of the SIC or approved equivalent procedure. (iii) The repetitive inspection required by paragraph (b)(2)(i) may be discontinued when the used bolts are replaced with unused vacuum cadmium plated V.S.2738 bolts or equivalent bolts and installed in accordance with paragraph 4.1(c) thru 4.1(h) of the SIC, or approved equivalent procedure. (c) Unused vacuum cadmium plated Voi-Shan bolts, installed in accordance with paragraph (a)(1)(ii), must be replaced with unused bolts of the same type and installed in the same manner, at or before 13,500 hours in service or eight years, whichever occurs first. If bolts are removed prior to the aforementioned life limits, they must be inspected and installed in accordance with paragraph (b)(1)(i) and (ii). (d) Equivalent inspections, installations, bolts, and service information circular revisions, must be approved by theChief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance time specified in this AD. Amendment 39-2676 was effective July 28, 1976. This amendment 39-3181 is effective April 17, 1978.
2015-18-03: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. TPE331-5, -5A, -5AB, -5B, -10, -10R, -10U, -10UF, -10UG, -10UGR, and -10UR model turboprop engines. This AD was prompted by engine propeller shaft coupling failures, leading to unexpected propeller pitch changes causing increased aerodynamic and asymmetric drag on the airplanes using these engines. This AD requires removing certain part number (P/N) engine propeller shaft couplings from service. This AD also requires inserting a copy of certain airplane operating procedures into applicable flight manuals. We are issuing this AD to prevent loss of airplane control, leading to an accident.
2009-09-03R1: We are revising an existing 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: Since issuance of AD 2007-0109, Turbom ca has released modification TU166 which consists in inserting HP blade dampers between the HP disc and the HP blade platform. Introduction of these dampers has demonstrated to limit axial displacement of the HP blade relative to the disk in case of blade lock rupture or opening, therefore eliminating the need for inspection and replacement. We are issuing this AD to prevent an uncommanded in-flight engine shutdown which could result in an emergency autorotation landing or an accident.
89-22-09: 89-22-09 CASA: Amendment 39-6363. Docket No. 89-NM-111-AD. Applicability: Model C-212 series airplanes equipped with a passenger entry step installed under Supplemental Type Certificate (STC) SA906GL, certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless previously accomplished. To prevent delay in opening the passenger door in the event of an emergency evacuation, accomplish the following: A. Remove the step, handrails, door latch modifications, and associated hardware installed in accordance with Fischer Brothers Aviation, Inc., Installation Instructions for FBD-206, Revision F, dated June 5, 1985. B. Restore the door handle to the original CASA configuration. C. 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, Chicago Aircraft Certification Office, ACE-115C, FAA, Central 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, Chicago Aircraft Certification Office, ACE-115C. 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. The applicable service information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Chicago Aircraft Certification Office, 2300 East Devon Avenue, Des Plaines, Illinois. This amendment (39-6363, AD 89-22-09) becomes effective November 20, 1989.
2000-16-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Saab Model SAAB 340B and SAAB 2000 series airplanes, that currently requires various inspections of fluorescent lamps and lampholders in the cabin area for discrepancies; corrections, if necessary; and reinspection of the lamps to ensure correct installation after replacement or reinstallation of the lamps. This amendment requires replacement of the electronic light ballasts with improved ballasts, which terminates the reinspections, and expands the applicability of the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent electrical arcing between the fluorescent tube pins and the lampholders, which could burn the surrounding area and lead to smoke and fumes in the passenger compartment or lavatory area.
93-14-13: 93-14-13 TEXTRON LYCOMING: Amendment 39-8637. Docket 91-ANE-55. Applicability: Textron Lycoming ALF502R and ALF502L turbofan engines installed on but not limited to British Aerospace BAe-146 and Canadair Challenger CL600 aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent third stage turbine disk failure, which could result in engine shutdown, accomplish the following: (a) For ALF502R series engines with installed third stage turbine rotor shaft assemblies, Part Number (P/N) 2-143-040-12, P/N 2-143-040-15, or P/N 2-143-040-16, rework the third stage turbine disk blade slots and mark the third stage turbine assembly with a new part number in accordance with the Accomplishment Instructions of Textron Lycoming Service Bulletin (SB) No. ALF502R 72-270, dated March 31, 1992, or replace with a serviceable part as follows: (1) For third stage turbine disks with 15,000 or more cycles in service (CIS) on the effective date of this AD, within 1,000 CIS after the effective date of this AD. (2) For third stage turbine disks with 10,000 or more CIS but less than 15,000 CIS on the effective date of this AD, within 1,000 CIS, after the effective date of this AD, or at the next shop visit, whichever occurs later, but prior to accumulating 16,000 CIS since new. (3) For third stage turbine disks with less than 10,000 CIS on the effective date of this AD, at the next blade removal, but prior to accumulating 13,000 CIS since new. (4) For third stage turbine disks not reworked in accordance with the requirements of this AD and installed on Textron ALF-502R engines as replacement disks when complying with this paragraph, accomplish the requirements of this paragraph as to that replacement disk. (b) For ALF502L series engines with installed third stage turbine rotor shaft assemblies, Part Number (P/N) 2-143-040-10, P/N 2-143-040-11, P/N 2-143-040-12, P/N 2-143-040-15, or P/N 2-143-040-16, rework the third stage turbine disk blade slots and mark the third stage turbine assembly with a new part number in accordance with the Accomplishment Instructions of Textron Lycoming SB ALF502L 72-270, dated April 30, 1993, or replace with a serviceable part as follows: (1) For third stage turbine disks with 15,000 or more CIS on the effective date of this AD, within 1,000 CIS after the effective date of this AD. (2) For third stage turbine disks with 10,000 or more CIS but less than 15,000 CIS on the effective date of this AD, within 1,000 CIS after the effective date of this AD or at the next shop visit, whichever occurs later, but prior to accumulating 16,000 CIS since new. (3) For third stage turbine disks with less than 10,000 CIS on the effective date of this AD, at the next blade removal, but prior to accumulating 13,000 CIS since new. (4) For third stage turbine disks not reworked in accordance with the requirements of this AD and installed on Textron Lycoming ALF-502L engines as replacement disks when complying with this paragraph, accomplish the requirements of this paragraph as to that replacement disk. (c) For the purpose of this AD, a shop visit is defined as the induction of an engine into a shop for maintenance. (d) 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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (e) 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. (f) The rework and reidentification shall be done in accordance with the following Textron Lycoming service bulletins: Document No. Pages Revision Date ALF502R 72-270 1-4 1 March 31, 1992 5 Original June 28, 1991 6-7 1 March 31, 1992 8-10 Original June 28, 1991 Total pages: 10 ALF502L 72-270 1-13 Original April 30, 1993 Total pages: 13 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 Textron Lycoming, 550 Main Street, Stratford, Connecticut 06497. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (g) This amendment becomes effective on October 4, 1993.