Results
2010-03-06: 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: Several events of uncoupling of the low-pressure (LP) fuel pump impeller and the high-pressure (HP) fuel pump shaft have been reported on Arriel 2 engines which do not incorporate Modification TU 147. In most cases the "low fuel pressure switch'' enlightened, the pilot activated the aircraft booster pump in accordance with the Flight Manual Instructions and landed safely with no other incident. One case, on a single-engine helicopter, led to a sudden engine power loss. The uncoupling of the LP fuel pump impeller and the HP fuel pump shaft may lead to a limitation of engine power or, at worst, an uncommanded in-flight shutdown. On a single-engine helicopter,the result may be an emergency autorotation landing. We are issuing this AD to prevent a forced autorotation landing or an accident.
2000-26-17: This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes that are equipped with a certain windshield configuration. This AD requires you to incorporate pilot's operating handbook (POH) information that prohibits the operation of the windshield heating system in the "LIGHT" mode, and requires you to modify the windshield deicing system wiring and circuit breakers. You can remove the POH information after accomplishing the modification. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent loss of electrical power to the windshield deicing system due to operation in the "LIGHT" mode, which could result in icing of the windshield and loss of control of the airplane.
2007-11-06: The FAA is superseding an existing airworthiness directive (AD) for Turbomeca Arrius 2F turboshaft engines. That AD currently requires removing from service certain serial number (SN) fuel control units (FCUs) or replacing the constant delta pressure (delta P) diaphragm in those FCUs. This AD requires replacing all FCUs not incorporating modification Tf 55 with FCUs that incorporate modification Tf 55. This AD results from the European Aviation Safety Agency (EASA) and Turbomeca expanding the applicability to the full population of FCUs installed on Arrius 2F turboshaft engines. FCUs not incorporating modification Tf 55 are susceptible to having an improperly assembled constant delta P diaphragm. We are issuing this AD to prevent an uncommanded engine in-flight shutdown on a single-engine helicopter, resulting in a forced autorotation landing or an accident.
2000-26-09: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of new revisions to the Dornier 328 Airworthiness Limitations Document. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
74-24-02: 74-24-02 SWEARINGEN: Amendment 39-2012 as amended by Amendment 39-2529. Applies to Models SA226-T, SA226-AT, and SA226-TC airplane. Compliance required as indicated. To detect cracks and provide for repair and reinforcement of the horizontal stabilizer rear spar at the outboard elevator hinge bracket attachment accomplish the following inspection and modifications: (a) After September 2, 1974, conduct the following inspection for the Model SA226-TC before the next flight unless already accomplished and for the Models SA226-T and SA226-AT within the next 10 hours time in service unless already accomplished. Inspect horizontal stabilizer rear spar in the vicinity of the left and right outboard elevator hinge bracket attachment for spanwise cracking above and below the hinge bracket in the bend radii of the spar flanges in accordance with paragraphs II.A.1. through 4. of Swearingen Service Bulletins A27-40-3067, revised October 9, 1974, for the Model SA226-T and A27-40-2064-4067, revised October 9, 1974, for the Models SA226-TC and SA226-AT or later FAA approved revisions. (b) If cracks are found, before further flight, repair horizontal stabilizer rear spar in accordance with: (1) Paragraph II.B. of Swearingen Service Bulletin A27-40-3067, revised October 9, 1974 or later FAA approved revision for the Model SA226-T, or (2) Paragraph II.B. of Swearingen Service Bulletin A27-40-2064-4067 revised October 9, 1974 or later FAA approved revision for the Models SA226-TC and SA226-AT. (c) If no cracks are found, accomplish the following: (1) Continue the inspections specified in (a) for the Model SA226-T at intervals not to exceed 200 hours time in service after the effective date of this AD. These periodic inspections may be discontinued after installation of the spar reinforcement specified in paragraph II.C. of Swearingen Service Bulletin A27-40-3067 revised October 9, 1974 or later FAA approved revision. (2) Within 50 hours timein service after the effective date of this AD, unless already accomplished for the Models SA226-TC and SA226-AT, install the spar reinforcement specified in paragraph II.C. of Swearingen Service Bulletin A27-40-2064-4067 revised October 9, 1974, or later FAA approved revisions. (3) After the rework specified in (c)(2), continue the inspections specified in (a) for the Models SA226-TC and SA226-AT at intervals not to exceed 500 hours' time in service from the date of rework or from the effective date of this AD if the rework was accomplished before the effective date. (d) Alternate methods of spar repair and reinforcement must be approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA. Amendment 39-2012 superseded Amendment 39-1950, AD 74-18-14, and became effective November 18, 1974. This amendment 39-2529 becomes effective March 8, 1976.
2018-02-05: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-28-140, PA-28-150, PA-28-151, PA-28-160, PA-28-161, PA-28-180, PA-28-181, [[Page 3065]] PA-28-236, PA-28-201T, PA-28R-180, PA-28R-200, PA-28R-201, PA-28R-201T, PA-28RT-201, and PA-28RT-201T airplanes. This AD requires inspecting the fuel tank selector cover to verify the left and right fuel tank selector placards are located at the proper positions and replacing those that are improperly located with new placards. This AD was prompted by a quality control issue at the manufacturer that resulted in the installation of the fuel tank selector covers with the left and right fuel tank selector placards improperly located. We are issuing this AD to address the unsafe condition on these products.
89-18-06: 89-18-06 AMERICAN CHAMPION AIRCRAFT (BELLANCA, CHAMPION): Amendment 39-6306. Applicability: Models 7ECA, 7GCAA, 7GCBC, 7KCAB, 8GCBC, and 8KCAB (all serial numbers) airplanes certificated in any category, when equipped with front folding seats. Compliance: Required as indicated in the body of the AD, unless already accomplished. To prevent failure of the seat back which could result in loss of control of the airplane, accomplish the following: (a) Within the next 25 hours time-in-service after the effective date of this AD and, thereafter at intervals not to exceed 25 hours time-in-service from the last inspection until the actions specified in paragraph (b) below are accomplished, accomplish the following: (1) Magnetic particle or dye penetrant inspect the left and right sides of the welded lower seat frame side-tube/side-brace junction and seatback hinges for evidence of cracks. If any cracks are found, prior to further flight repair, in accordancewith the recommended procedures in Advisory Circular (AC) 43.13-1A, the crack or replace the cracked part with a serviceable part. (2) Fabricate and install on the instrument panel in clear view of the pilot a placard with letters of minimum 0.2 inches in height which reads as follows: "Warning: Do not pull or push on upper seat back." (b) Within the next 150 hours time-in-service after the effective date of this AD, replace the front folding seat frame with an exchange unit in accordance with American Champion Aircraft Service Letter No. 401, dated June 14, 1989. The repetitive inspections and the placard specified in paragraph (a) above are no longer required after the actions specified in this paragraph have been accomplished. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Chicago Aircraft Certification Office,ACE-115C, 2300 East Devon Avenue, Des Plaines, Illinois 60018. All persons affected by this directive may obtain copies of the documents referred to herein upon request to American Champion Aircraft, P.O. Box 37, Rochester, Wisconsin 53167, or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6306, AD 89-18-06) becomes effective on September 21, 1989.
98-24-01: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires repetitive detailed visual inspections to detect cracking or other damage of certain diaphragm support structures of the forward equipment compartment; and repair, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct failure of the two diaphragms that support the upper structure of the forward equipment compartment, which could accelerate fatigue damage in adjacent structure and result in reduced structural integrity of the airframe.
2019-08-04: We are superseding Airworthiness Directive (AD) 2012-25-02, which applied to certain Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2012-25-02 required revising the airworthiness limitations section (AWL) of the instructions for continued airworthiness (ICA) of the maintenance requirements manual (MRM) by incorporating new procedures for repetitive inspections for cracking of the rear pressure bulkhead (RPB). AD 2012-25-02 also required revising the maintenance or inspection program to incorporate a revised task. This AD also mandates modification of the RPB and adds repetitive inspections for cracking of the RPB web, which terminates certain actions in this AD. This AD was prompted by additional in- service crack findings, which resulted in the development of a structural modification to the RPB. We are issuing this AD to address the unsafe condition on these products.
2007-10-11: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-145LR, -145XR, and -145MP airplanes; and Model EMB-135BJ and -135LR airplanes. This AD requires replacing the electrical bonding clamps inside the fuel tanks and adjacent areas. This AD results from a report of the failure of a fitting clamp of an electrical bonding cable for the fuel tubing. We are issuing this AD to prevent loss of bonding protection in the interior of the fuel tanks or adjacent areas, and a consequent potential source of ignition in a fuel tank and possible fire or explosion.