Results
77-14-12: 77-14-12 BRITISH AIRCRAFT CORPORATION: Amendment 39-2967. Applies to Model BAC 1-11, 200 and 400 series airplanes, certificated in all categories. Compliance is required within the next 500 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible leaks in the ring main ducts of the passenger oxygen system, accomplish the following: (a) Gain access to and conduct a one-time inspection of the passenger oxygen ring main ducts in accordance with paragraph 2.1.1. of the "Accomplishment Instructions" of British Aircraft Corporation Alert Service Bulletin 35-A-PM 5124, Issue No. 1, dated February 12, 1973, or an FAA-approved equivalent. (b) If during the inspection required by paragraph (a) of this AD, chafing of any of the oxygen ducts is found or the clearance with adjacent structure is less than 0.050 inches, comply with the applicable provisions specified in paragraph 2.1.2, 2.1.3, 2.1.4, or 2.1.5 of BAC Alert Service Bulletin 35-A-PM 5124, dated February 12, 1973, or an FAA-approved equivalent. (c) If, as a result of any of the actions required by paragraph (b) of this AD, the use of the passenger oxygen system is restricted, install an FAA-approved placard in full view of the pilot which defines the restriction and states that flight operations must be limited to those allowed by the applicable operating rules for the particular airplane. This amendment becomes effective August 15, 1977.
2016-24-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by reports of cracked and corroded barrel nuts found at the mid-spar location of the horizontal-stabilizer-to-vertical-stabilizer attachment joint. This AD requires repetitive detailed [[Page 88624]] inspections of each barrel nut and cradle, a check of the bolt torque of the preload indicating (PLI) washers, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
2016-24-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes, Model DHC- 8-200 series airplanes, and Model DHC-8-300 series airplanes. This AD was prompted by several occurrences of loss of airspeed data on both pilot and co-pilot air speed indicators due to the accumulation of ice on the pitot probes caused by inoperative pitot probe heaters. This AD requires replacing the existing circuit breakers in the pitot heater system. We are issuing this AD to address the unsafe condition on these products.
2010-12-05: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Following in-flight test deployments on CL-600-2B19 aircraft, several Air-Driven generators (ADGs) failed to come online. Investigation revealed that, as a result of a wiring anomaly that had not been detected during ADG manufacture, a short circuit was possible between certain internal wires and their metallic over- braided shields, which could result in the ADG not providing power when deployed. * * * The unsafe condition is failure of the ADG, which could lead to loss of several functions essential for safe flight. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective July 12, 2010. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of April 30, 2009 (74 FR 13094, March 26, 2009).
2016-19-16: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 707-300, 707-300B, and 707-300C series airplanes; and certain Model 727C, 727-100C, and 727-200F series airplanes. This AD was prompted by a report indicating that a cam latch on the main cargo door (MCD) broke during flight. This AD requires various inspections and related investigative and corrective actions, if necessary. We are issuing this AD to address the unsafe condition on these products.
2005-18-03: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) PW2000 series turbofan engines. That AD currently requires revisions to the engine manufacturer's time limits section (TLS) to include enhanced inspection of selected critical life- limited parts at each piece-part opportunity. This AD requires modifying the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. This AD results from an FAA study of in-service events involving uncontained failures of critical rotating engine parts that indicates the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result inan uncontained engine failure and damage to the airplane.
80-20-01: 80-20-01 BOEING: Amendment 39-3927. Applies to those Model 747 series airplanes listed under Groups I and II in Boeing Service Bulletin 747-53-2114, Revision 3, dated September 3, 1980, or later FAA approved revisions. Prior to January 31, 1981, unless already accomplished: \n\n\tA.\tModify stringers 18 and 19, left and right side, between fuselage stations 2360 and 2412, in accordance with Boeing Service Bulletin 747-53-2114, Revision 3, dated September 3, 1980, or later FAA approved revisions; or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region.\n \n\tB.\tUpon request of the operator, an FAA Principal Maintenance Inspector, subject to prior approval by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the compliance times if the request contains substantiating data to justify the increase for that operator. \n\n\tC.\tAircraft may be ferried to a base for maintenance in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations.\n\n \tThe 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). \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective October 7, 1980.
2016-24-05: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by heavy corrosion found on the wing rear spar lower girder. This AD requires inspections of the affected areas, modification of the wing trailing edge lower skin panels, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
61-10-02: 61-10-02 CONVAIR: Amdt. 283 Part 507 Federal Register May 11, 1961. Applies to All Model 22 (880) Aircraft. Compliance required as indicated. Two cases of failure of the forward engine mount support fitting P/N 22-02593-1, have been reported. Failure of this part permits the engine to rotate with the forward end coming to rest on the bottom of the engine pod structure. (a) Unless P/N 22-02593-3 or an FAA approved equivalent has already been installed, within the next 250 hours' time in service and at intervals of 250 hours' time in service thereafter, remove and inspect by means of dye penetrant or magnetic particle inspection, or equivalent, P/N 22-02593-1 for cracks and/or material defects. If cracks and/or material defects are found, the part must be replaced prior to further flight. (b) When P/N 22-02593-1 has been replaced with P/N 22-02593-3 or FAA approved equivalent, the inspection required above may be discontinued. (Convair Service Bulletin No. A71-2 covers this same subject.) This directive effective May 11, 1961.
81-15-07: 81-15-07 KAWASAKI HEAVY INDUSTRIES, LTD. (KHI): Amendment 39-4164. Applies to Models KV107-II and KV107-IIA helicopters equipped with main rotor tension-torsion strap assemblies, P/N 107R2003-1, certificated in all categories (Airworthiness Docket No. 81-ASW-11). Compliance required as indicated. To prevent fatigue failure of the main rotor tension-torsion strap assemblies, remove from service tension-torsion strap assemblies, P/N 107R2003-1, on or before the accumulation of 27,800 hours' time in service and replace with a serviceable part that has less than 27,800 hours' total time in service. This amendment becomes effective August 25, 1981.