Results
2012-02-04: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc RB211-Trent 500 series turbofan engines. This AD requires a one-time inspection of the fuel tubes and fuel tube clips for evidence of damage, wear, and fuel leakage. This AD was prompted by reports of wear found between the securing clips and the low-pressure (LP) fuel tube outer surface, which reduces the fuel tube wall thickness, leading to fracture of the fuel tube and consequent fuel leak. We are issuing this AD to prevent engine fuel leaks, which could result in risk to the airplane.
75-18-07: 75-18-07 BELL: Amendment 39-2346. Applies to Bell Models 206A, 206B, 206A-1, and 206B-1 helicopters certificated in all categories. Compliance required within 600 hours' time in service after the effective date of this AD, unless already accomplished. To prevent loss of attaching bolt torque for the main rotor blade hub pillow blocks, accomplish the following: (a) Remove the four nuts and bolts that attach the pillow block assemblies to the main rotor yoke and remove the washers, P/N 206-010-171-1, and bushings, P/N 206-010- 170-1. (b) Install four flanged bushings, P/N 206-011-128-1, into the pillow blocks with the flanges facing outboard. Secure the pillow blocks to the yoke with appropriate nuts and bolts, with a washer under each nut, and torque the nut and bolt 60 inch pounds, plus drag (tare) torque of the self-locking nut. (Note: Compliance with items 1, 2, and 3 of Bell Service Bulletin No. 206-75-3, dated May 1, 1975, or later FAA approved revision, will constitute compliance with the requirements of this AD.) This amendment becomes effective September 19, 1975.
73-18-02: 73-18-02 HAWKER SIDDELEY AVIATION, LTD.: Amendment 39-1706. Applies to Hawker Siddeley Model BH-125 and DH-125 airplanes equipped with overhauled oxygen cylinders. Compliance is required within the next 14 days after the effective date of this AD, except as provided in paragraph (c), and thereafter at each replacement of an oxygen cylinder with an overhauled oxygen cylinder. To prevent the possible burst failure of overhauled oxygen cylinders, P/N WKA 29396/GR14, WKA 29396/GR22, WKA 31393, and WKA 31394, due to the overhaul stamp impression being located on a critical area of the cylinder, accomplish the following: (a) Visually inspect the surface of the oxygen cylinder for evidence of stamp impressions indicating the date of the overhaul or letters designating the overhaul agency. (b) If stamp impressions are found during an inspection required by paragraph (a), on the cylinder shoulder, either (1) outboard of a radius of 3 inches from the cylinder center, or (2) inboard of a 3 inch radius and accompanied by local distortion in the hemispherical profile at the stamp impression, before further flight, replace the cylinder with a serviceable part of the same part number, or an FAA-approved equivalent. (c) If the oxygen system is to be recharged before accomplishment of the inspection provisions of this AD, the oxygen system charge must be limited to not more than 50 percent of normal full quantity, and a placard must be installed adjacent to the oxygen system charging point, stating, "System Contents Must Not Exceed 1/2 Full At Any Time." (d) The placard required by paragraph (c) may be removed when it is determined by an inspection in accordance with paragraph (a) that the oxygen cylinders have no stamp impressions on the cylinder shoulder, outboard of a radius of 3 inches from the cylinder center, and if there is a stamp impression inboard of a 3 inch radius, that there is no local distortion in the hemispherical profile at the stamp impression. This amendment becomes effective August 28, 1973.
2012-02-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, and -300 series airplanes. This AD was prompted by a report from the airplane manufacturer that airplanes were assembled with air distribution ducts in the environmental control system (ECS) wrapped with Boeing Material Specification (BMS) 8-39 or Aeronautical Materials Specifications (AMS) 3570 polyurethane foam insulation, a material with fire-retardant properties that deteriorate with age. This AD requires reworking certain air distribution ducts in the ECS. We are issuing this AD to prevent ignition of the BMS 8-39 or AMS 3570 polyurethane foam insulation on the duct assemblies of the ECS due to a potential electrical arc, which could start a small fire and lead to a larger fire that may spread throughout the airplane through the ECS.
75-22-19: 75-22-19 SIAI-MARCHETTI: Amendment 39-2388. Applies to F.260 and F.260B airplanes, Serial Numbers 101 thru 125, 2-26 thru 2-52 (except S/N 2-33, 2-47, 2-50, and 2-51), 3-76, 3-77, and 502, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent failure of the main landing gear, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, or before the accumulation of 300 hours total aircraft time in service, whichever occurs later, perform a magnetic particle inspection of the landing gear bellcrank pivot bolts, P/N 260-14-35- 1, in accordance with SIAI Marchetti Service Bulletin S.B. No. 260B7, dated August 27, 1971, or an FAA-approved equivalent. (b) If cracks are found, before further flight, comply with paragraph (d) of this AD. (c) If no cracks are found, comply with paragraph (d) of this AD within the next 100 hours' time in service after the inspection.(d) Where required by paragraph (b) or (c) of this AD, replace the pivot bolts P/N 260-14-35-1 and bushings P/N 260-14-17-3 with modified bolts P/N 260-14-35-3 and modified bushings P/N 260-14-17-5 in accordance with SIAI Marchetti Service Bulletin S.B. No. 260B8, dated September 18, 1971, or an FAA-approved equivalent. This amendment becomes effective October 27, 1975.
70-09-04: 70-09-04 MCDONNELL DOUGLAS: Amdt. 39-982. Applies to Douglas DC-9 series airplanes certificated in all categories as listed in Douglas Aircraft Company Service Bulletin No. 28-16, Revision 1, dated January 9, 1970, or later FAA approved revision. \n\n\tCompliance required within the next 800 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent a possible fuel interruption due to tire tread separation striking the fire-x-fuel shutoff valve cable system, accomplish the following. \n\n\tInstall a protective guard over the fire-x-fuel shutoff valve return idler pulley bracket located in the main landing gear wheel wells in accordance with the instructions of Douglas Aircraft Co. Service Bulletin No. 28-16, Revision 1, dated January 9, 1970, or later FAA approved revision or an equivalent installation approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective June 2, 1970.
2012-01-06: We are adopting a new airworthiness directive (AD) for certain Model 767-200 and 767-300 series airplanes. This AD was prompted by reports of water accumulation in the forward lower lobe of the forward cargo compartment. This AD requires installing cargo bulkhead supports, ceiling supports, a secondary dam support, drainage tubing, and ceiling panels to the forward lower lobe in the forward cargo compartment. We are issuing this AD to prevent water from accumulating in the forward lower lobe of the forward cargo compartment and entering the adjacent electronic equipment bay, which could result in an electrical short and the potential loss of several functions essential for safe flight.
71-10-01: 71-10-01 BELLANCA: Amendment 39-1205. Applies to Model 17-30 (Serial Numbers 30002 through 30216) Airplanes. Compliance: Required as indicated unless already accomplished. To prevent hazardous fuel leakage in these airplanes, accomplish the following: Within 50 hours time in service after the effective date of this AD, install an electric fuel pump seal chamber drain in accordance with instructions contained in Bellanca Service Letter No. 64, dated April 6, 1971, or any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective May 8, 1971.
74-24-06: 74-24-06 BOEING: Amendment 39-2018. Applies to Boeing Model 727-200 airplanes, listed in Boeing Service Bulletin 727-32-222 dated September 6, 1974, or later FAA approved revisions. \n\t(1)\tTo detect broken wires or a failed nose landing gear position indicator lock switch, perform an operational test of the nose landing gear position indication system per Boeing 727 Maintenance Manual, Chapter 32-61-71, within the next 300 hours time in service after the effective date of this AD, unless Service Bulletin 727-32-222 is already accomplished. \n\t(2)\tAs terminating action to prevent false "Down and Locked" nose landing gear position indication, within the next 1,000 hours time in service after the effective date of this AD, unless already accomplished, modify the wiring in accordance with Boeing Service Bulletin 727-32-222 dated September 6, 1974, or Boeing Service Bulletin 727-32-222, Revision 1, dated November 15, 1974, or later FAA approved revisions, or an equivalent modificationapproved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \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\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. The documents may be examined at FAA Northwest Region, 9010 East Marginal Way, Seattle, Washington 98108. \n\n\tThis amendment becomes effective November 26, 1974.
72-22-02: 72-22-02 RAZORBACK FABRICS, INC: Amdt. 39-1531 as amended Amendment 39-1541. Applies to airplanes having wings, tail, or control surfaces covered with fiberglass using the "razorback" method, certificated in all categories. This covering process has been approved by numerous Supplemental Type Certificates and FAA Forms 337 as complying with Advisory Circular 20-44, "Glass Fiber Fabric for Aircraft Covering." Compliance required within the next fifty hours' time in service after the effective date of this airworthiness directive, unless already accomplished. To determine if the fabric is attached with plastic coated glass rib stitch cord, inspect the interior of the wings, tail, or control surfaces through inspection openings or by cutting small holes in the fabric. The plastic coating on the rib stitch cord is black in color. a. If the fabric is attached with the plastic coated rib stitch cord, replace the stitching with MIL-C-5649 cord or FAA approved equivalent before fifty hours' time in service from the effective date of this Airworthiness Directive. b. If the fabric is attached with MIL-C-5649 cord, or FAA approved equivalent, no further action is required. c. All work required, including patching holes, may be accomplished in accordance with FAA Advisory Circular 43.13-1. Razorback Fabrics, Inc., Service Bulletin 1-1 dated 3/11/64 covers the same subject. (NOTE: Copies of Razorback Fabrics, Inc., Service Bulletin 1-1 may be obtained from the company at Manila, Arkansas 72442.) This supersedes Amendment 39-1531, 37 F.R. Amendment 39-1531 became effective October 16, 1972. This amendment 39-1541 becomes effective November 15, 1972.