Results
2012-17-11: We are adopting a new airworthiness directive (AD) for all BAE SYSTEMS (Operations) Limited Model 4101 airplanes. This AD was prompted by reports that the fire extinguisher in the toilet vanity unit needs to be mounted vertically rather than horizontally. This AD requires inspecting to determine if a certain fire extinguisher bottle is installed, and repositioning the affected fire extinguisher bottle to the vertical position. We are issuing this AD to detect and correct the orientation of the fire extinguisher bottle in the toilet vanity unit to the vertical position, which if not corrected, could result in a toilet waste bin fire spreading, and consequent damage to the airplane and injury to its occupants.
74-04-04: 74-04-04 CANADAIR: Amendment 39-1787. Applies to all CL-44D4 and CL-44J airplanes which have experienced more than 7,000 landings. To detect cracks in the lugs of the rear spar attachment lower fitting, P/N 44-10149, of the main landing gear actuator, accomplish the following: 1. Within the next 100 landings after the effective date of this AD, unless accomplished within the last 900 landings, and at intervals thereafter not to exceed 1,000 landings, inspect the lower lugs of the main landing gear actuator rear spar attachment fitting, P/N 44-10149, for cracks using a dye penetrant method with a glass of at least 10-power or an approved equivalent inspection. 2. If cracks are found, reduce the inspection intervals as noted in the instructions of paragraphs i, ii, iii of the Inspection Data of Canadair Service Information Circular No. 371-CL- 44. 3. The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data, submitted through an FAA maintenance inspector. 4. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 5. 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 Canadair Limited, Attention: Mr. C. Bloom, P.O. Box 6078, Montreal, Canada. These documents may also be examined at the Engineering and Manufacturing Branch, FAA, Eastern Region, J.F.K. International Airport, Jamaica, New York 11430, 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 at the Eastern Region. This amendment is effective February 18, 1974.
99-11-08: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Aircraft Engines (GE) CF34 series turbofan engines, that requires installation of a main fuel control (MFC) that incorporates a flange vent groove and installation of an MFC with improved overspeed protection. This amendment is prompted by reports of rapid uncommanded engine acceleration events. The actions specified by this AD are intended to prevent uncommanded engine accelerations, which could result in an engine overspeed, uncontained engine failure, and damage to the airplane.
2012-17-07: We are adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Models DA 42, DA 42 NG, and DA 42 M-NG airplanes. 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 excessive voids in the adhesive joint between the center wing spars and the [[Page 54801]] upper center wing skins. This condition could cause the wing to fail, which could result in loss of control of the airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
98-09-24: This amendment adopts a new airworthiness directive (AD) that applies to certain Diamond Aircraft Industries (Diamond) Models H-36 "Dimona" ; and HK 36 R "Super Dimona" sailplanes. This AD requires: inspecting the elevator rib area for damage on certain Models H-36 " Dimona" and HK 36 R "Super Dimona" sailplanes, and either immediately or eventually replacing the elevator ribs depending on the results of the inspection; replacing the M6 screws that attach the wheel axle to steel support with M8 screws on certain Models HK 36 R "Super Dimona" sailplanes; and inspecting the shoulder harness fittings for improper bonding on certain Diamond Model H-36 "Dimona" sailplanes, and repairing any harness with an improper bond. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Austria. The actions specified by this AD are intended to prevent failure of either the shoulder harness fittings, elevator rib, or the wheel axle to steel support attachment, which could result in passenger injury caused by an inadequate restraint system; reduced sailplane controllability caused by structural damage to the elevator; and/or reduced sailplane controllability during takeoff, landing, and ground operations caused by the installation of incorrect wheel axle screws.
96-05-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires modification of a certain galley; repetitive inspections to detect damage and to determine the clearance of generator wires in the auxiliary power unit (APU); and repair or replacement of the damaged wires. This amendment is prompted by reports indicating that, during an unscheduled removal of a galley from the production line, the insulation of one of the generator wires of the APU was found damaged due to inadequate clearance with the adjacent structure. The actions specified by this AD are intended to prevent such damage, which could result in a short in the electrical wiring of the APU and, thus, pose a potential fire hazard.
2012-17-03: We are adopting a new airworthiness directive (AD) for certain Eurocopter France Model AS350 helicopters. This AD requires installing protection sleeves over certain forward (pitch) servo-control hydraulic hoses. This AD was prompted by an in-flight fire caused by the ignition of hydraulic fluid leaking from a damaged forward servo-control hydraulic hose. This AD's actions are intended to prevent the forward servo-control hydraulic hoses from becoming damaged and leaking hydraulic fluid that could ignite in flight, which could result in loss of main rotor (M/R) control, power loss, structural damage, propagation of fire, and subsequent loss of control of the helicopter.
58-23-03: 58-23-03 MOONEY: Applies to Model M-20 Aircraft Serial Numbers 1002 Through 1051. Compliance required as soon as practicable but not later than December 15, 1958. Several failures of the aileron counterbalance buttweld at the aileron spar have occurred. The affected airplanes do not have a 3/8 inch O.D. x 0.028 inch x 3 inch steel reinforcing brace installed. It must be determined whether this brace has been incorporated. If not, the following inspection and repair must be accomplished: 1. Remove the paint from the subject welded joint and inspect for cracks. 2. Reweld the joint if cracks are present. 3. Install the 3/8 inch O.D. x 0.028 inch x 3 inch 4130 steel tubular brace (trimmed to fit). (Mooney Aircraft, Inc. Service Letter 20-7 Revision B covers this same subject.)
86-14-07: 86-14-07 SIKORSKY AIRCRAFT: Amendment 39-5432. Applies to all Model S-76A helicopters certificated in any category and model S-76B helicopters, serial numbers 760262, 760269, 760299, 760303, and 760310 through 760319, certificated in any category. Compliance is required as indicated, unless already accomplished. To prevent operation with a failed pilot's yaw control rod assembly, P/N 76400-00034-041, accomplish the following: (a) Prior to further flight, inspect the push rod assembly in accordance with Section E, paragraph 1, of Sikorsky Alert Service Bulletin (ASB) No. 76-ASB-76-67-22A, dated July 7, 1986, or an FAA-approved equivalent. If no dent, crack, distortion, or bowing is detected in the rod, install a placard legible to the pilot and in full view of the pilot stating "single pilot operation prohibited." This placard is to remain until the inspection required by paragraph (b) below is accomplished. (b) Within the next 25 hours' time in service afterthe effective date of this AD, inspect the push rod assembly for condition of heat treat in accordance with Section E, paragraph 2, of Sikorsky ASB No. 76-ASB-76-67-22A, dated July 7, 1986, or an FAA-approved equivalent. (c) If as a result of the inspection of paragraph (a), a dent, crack, distortion, or bowing is detected or if as a result of the inspection of paragraph (b) above, the heat treat (hardness) is incorrect, replace the rod assembly with a new or serviceable component that complies with this AD prior to further flight. (d) Aircraft may be ferried in accordance with the provision of FAR Sections 21.197 and 21.199 to a base where the requirements of the AD can be accomplished. (e) Upon request, an alternate method of compliance which provides an equivalent level of safety with the requirements of this AD may be approved by the Manager, Boston Aircraft Certification Office, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7118. Sikorsky Aircraft ASB No. 76-ASB-76-67-22A identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Sikorsky Aircraft, Division of United Technologies, North Main Street, Stratford, Connecticut 06601. This document also may be examined at the Rules Docket, Office of the Regional Counsel, Federal Aviation Administration, Southwest Region, 4400 Blue Mound Road, Fort worth, Texas, 76106. This amendment becomes effective October 20, 1986, as to all persons except those to whom it was made immediately effective by individual priority letter AD No. 86-14-07 issued July 9, 1986, which contained this amendment.
99-11-06: This amendment adopts a new airworthiness directive (AD) that applies to all Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires inspecting both (left and right wing configurations) environmental control system bleed tubes for damage, leakage, and a correct gap between the tube and wing lower panel crossing area, inspecting the wiring and surrounding structures for damage, and correcting any discrepancies found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent thermal expansion from causing leakage of an environmental control system bleed tube because of improper installation, which could result in deterioration of the electrical wiring and the surrounding structure.