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2018-14-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by reports that additional areas of Boeing Material Specification (BMS) 8-39 flexible urethane foam were found during a routine inspection. This AD requires an inspection for foam insulation on the dripshield above the overhead panel support structure and replacement if necessary. For certain airplanes, this AD also requires replacement of foam insulation on the overhead panel support structure. We are issuing this AD to address the unsafe condition on these products. \n\n((Page 31651))
47-49-11: 47-49-11 LOCKHEED: (Was Service Note 11 of AD-763-3.) Applies to Models 49, 649, and 749 Serials as Noted. At periods not to exceed 50 hours of operation, inspect the following fuel system elements to determine that they are tight and will not permit leakage or other hazardous conditions: (a) Fuel dump valve shaft gland nuts (Serials up to and including 2075). (b) Valves on drain lines from outboard portion of inboard fuel tanks, fuel system crossfeed lines, and cabin heater fuel lines (Serials 2047 to 2088, inclusive, and 2501 to 2503, inclusive). If safety wiring of these items is provided, the required inspections may be discontinued. (Lockheed Service Bulletin 49/SB-215 covers part (a), and Lockheed Service Instruction 49/SI-10A covers part (b).)
48-12-02: 48-12-02 DOUGLAS: Applies to All C54-DC Serial and the Following DC-4 Airplanes: 42904 Through 42943, 42948 Through 42952, 42982 Through 42996, 43065 Through 43068, 43071, 43072, 43093, 43094, and 43102. \n\n\tTo be accomplished not later than the date established in accordance with the provisions of Special Civil Air Regulation Serial Number SR-329, or any subsequent regulation affecting this compliance date. \n\n\tAs a result of investigation of heater fires, the following changes are to be accomplished in the nose and cabin heater installation: \n\n\t1.\tInstall steel firewall at Station 260 (cabin forward bulkhead) from ceiling level to top of bulkhead to provide isolation between heater compartment and the space between cabin ceiling and top of fuselage. Also, replace present wood panels under heaters with metal panels. \n\n\t(Douglas Service Bulletin DC-4 No. 47 covers this same subject.) \n\n\t2.\t(a)\tInstall all heater control components in airtight steel containers. \n\t\t(b)\tReplace present heater fuel supply pumps with a single electric driven pump attached to No. 2 main fuel tank. \n\n\t\t(c)\tProvide shrouds around all heater fuel line fittings in fuselage. \t \n\n\t\t(d)\tInstall a fire detector and extinguisher system for the nose heater and cabin heaters. \n\n\t(Douglas Service Bulletins DC-4 Nos. 64 and 64 addendum cover this same subject.) \n\n\tIn some cases, operators have obtained approval from FAA Regional Offices for systems which differ in arrangement and detail from the above provisions. Designs which have been separately approved in this manner are considered to meet the intent of this Note. \n\n\tThis supersedes AD 46-39-02.
2005-19-19: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-300, -400, -500, -600, -700, -700C, -800 and - 900 series airplanes. This AD requires installing an updated version of the operational program software (OPS) and certain other software in the flight management computers (FMCs); and doing configuration checks to ensure that certain software is properly installed and doing other specified actions. This AD also requires reinstalling software, if necessary. This AD results from one operator reporting FMC map shifts on several Model 737-400 series airplanes with dual FMCs, using OPS version U10.4A. We are issuing this AD to prevent the FMC from displaying the incorrect actual navigation performance value to the flightcrew, which could prevent adequate alerting of a potential navigation error. This condition could result in a near miss with other airplanes or terrain, or collision if other warning systems also fail.
65-04-01: 65-04-01 BELL: Amdt. 39-36 Part 39 Federal Register February 17, 1965. Applies to Model 47 Series Helicopters Equipped With Transmissions Serial Numbers B12-885 through B12-969. Compliance required within 25 hours' time in service after the effective date of this AD, unless previously accomplished in accordance with Bell Helicopter Company Service Bulletin No. 141SB. Some of the P/N 47-620-535-1 outer races installed in the freewheeling clutch of transmissions listed herein may not have been tempered properly. To eliminate the possibility of excessive wear of these races and subsequent malfunction of the freewheeling clutch, conduct a hardness test on these races as described by Bell Service Bulletin No. 141SB. If the hardness does not fall within the limits prescribed by the bulletin, replace the outer race with one which is within the limits before further flight. This directive effective February 17, 1965.
2018-12-03: We are superseding Airworthiness Directive (AD) 2013-11-09 for all Safran Helicopter Engines, S.A., Arrius 2B1 and 2F turboshaft engines. AD 2013-11-09 required the repetitive replacement of the fuel injector manifolds and privilege injector, or only the privilege injector. This AD retains the repetitive hardware replacement requirements of AD 2013-11-09, but only allows replacement pipe injector preferred assembly, part number (P/N) 0 319 73 044 0, on the Arrius 2F engines. This AD was prompted by reports of engine flameouts as a result of reduced fuel flow due to the presence of coking. We are issuing this AD to address the unsafe condition on these products.
65-03-01: 65-03-01 BEECH: Amdt. 39-26 Part 39 Federal Register January 28, 1965 is amended by Amendment 39-1263. Applies to Models AT-11, C18S, D18S, E18S and C-45 series airplanes which have been modified in accordance with one or more of Airline Training, Inc. Supplemental Type Certificates Nos. SA4-113, SA-119, SA4-128, SA2-280, SA2-383, SA2-523, SA2-820, SA2-1016 and SA2-1246. Compliance required as indicated. Freezing of moisture in the continuous (piano) hinges which attach the stabilizer-to- elevator gap seal strips causes the spring loaded strips to stick in a deflected position. The deflected strips act as aerodynamic spoilers which cause serious longitudinal control difficulties. In order to preclude this condition, accomplish the following: Within 25 hours' time in service after the effective date of this AD, and thereafter at intervals not exceeding 50 hours' time in service, or 60 days, whichever occurs first, accomplish the following or equivalent approved by Engineering and Manufacturing Branch, FAA Southern Region. (a) Apply a good coverage of Federal Specification VV-L-800 oil to the top and bottom sides of both upper and lower stabilizer-to-elevator gap seal strip piano-type hinges. An acceptable alternate lubricant is a mixture of MIL-G-81322 (MIL-G-25760) or MIL-G-23827 (MIL-G-7118) grease and methyl ethyl ketone or aliphatic naphtha (Varsol), to a consistency suitable for application with a squirt-type oil can or an equivalent material approved by Engineering and Manufacturing Branch, FAA Southern Region. (b) While the mixture is being applied, deflect the seal strips several times to assure maximum penetration of the fluid into the hinge pin and hinge mating areas. Amendment 39-26 was effective February 8, 1965. Amendment 39-1263 becomes effective upon publication in the Federal Register.
47-21-05: 47-21-05 NAVION: (Was Mandatory Note 4 of AD-782-3.) Applies to Serial Numbers NAV-4-11 Through 21 and 44 Through 47. To be accomplished not later than August 1, 1947. Replace the original propeller control with one that incorporates a positive friction lock in accordance with NAA Kit Drawing 145-89011. (NAA Field Service Bulletin No. 5 covers this change.)
47-32-05: 47-32-05 BELL: (Was Mandatory Note 5 of AD-1H-1.) Applies to Model 47B. Compliance required before next flight. Remove the main rotor mast spinner assembly from all Model 47B helicopters, in order that the possibility of its jamming the mast control tubes, in the event it becomes loose during flight, is eliminated. (Bell Service Bulletin 47C38 dated May 15, 1947, also covers this same subject.)
49-26-01: 49-26-01 BEECH: Applies to All Models 35 and A35 Airplanes Equipped With an Automatic Reel Trailing Antenna. Compliance required by January 1, 1950. Because of reported cases of jamming of the controls due to the rear antenna guide rail being knocked loose by the movable pulley assembly (P/N 1X007) when the antenna wire was broken or came loose in flight, the following should be accomplished: (1) Tack a plywood block to the wood antenna strip in the aft section of the fuselage, with 3/4 inch No. 18 flathead nails. The rear end of the block should be at least 1 1/4 inches forward of the centerline of the aft pulley. (2) Stretch a rubber bumper ring over the block. (Beech Service Bulletin Model 35 No. 13 and Model A-35 No. 4 dated March 15, 1949, covers this same subject.)