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2013-23-05: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 0070 and 0100 airplanes. This AD was prompted by a design review, which revealed that, under certain failure conditions, wiring in the main fuel tank could develop a short circuit that might cause a hot spot on the wiring conduit or puncture the wiring conduit wall. This AD requires installing fuses in the power supply wiring and/or return wiring for various components in the fuel system; and revising the airplane maintenance program by incorporating critical design configuration control limitations. We are issuing this AD to prevent an ignition source in the main fuel tank vapor space, which could result in a fuel tank explosion and consequent loss of the airplane.
72-21-02: 72-21-02 BRANTLY: Amdt. 39-1534 as amended by Amendment 39-1569. Applies to Model B-2, B-2A and B-2B Helicopters certificated in all categories. Compliance required as indicated, unless already accomplished: To prevent fatigue failure of the pylon outboard bearing shaft, Part Number 280-5 or 280- 6, replace these parts (three per helicopter) with serviceable parts having Part Number 280-6 within the next 10 hours time in service after the effective date of this AD, or upon the accumulation of 500 hours total time in service, whichever occurs later. The replacement pylon outboard bearing shafts must be torqued to 2500 plus or minus 100 inch-pounds and secured with an AN435-4-9 rivet or equivalent. This AD effectively revises the service life limits published in Type Certificate Data Sheet No. 2H2 for Part Numbers 280-5 and 280-6, which are a part of the hub and inboard blade assembly Part Number 305-1. Part Numbers 280-5 and 280-6 pylon outboard bearing shafts, willnow have a service life limit of 500 hours time in service. Type Certificate Holder, Mr. M. K. Hynes, 1241 Lake Horney Drive, Lakeland, Florida, 33801, may be contacted for information regarding installation tools, replacement parts, etc. Amendment 39-1534 became effective October 14, 1972, for all persons except those to whom it was made effective upon receipt of the air mail letter dated October 3, 1972, which contained this amendment. This Amendment 39-1569 becomes effective on December 8, 1972
2013-22-22: We are superseding airworthiness directive (AD) 2013-01-07 for all Turbomeca S.A. Arriel 2D turboshaft engines. AD 2013-01-07 required replacing the hydromechanical metering unit (HMU) at a reduced life. This AD maintains that requirement and also requires conducting inspections of the HMU. This AD was prompted by further cases of deterioration of HMU rotating components. We are issuing this AD to prevent an uncommanded in-flight shutdown of the engine and possible loss of the helicopter.
2013-23-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR series airplanes. This AD requires inspecting to determine the part number of the inboard actuator attach fittings of the outboard flap. For affected attach fittings, this AD requires doing a detailed inspection of the attach fittings for a cylindrical defect and replacing if necessary. As an option to the detailed inspection, this AD allows replacement of affected attach fittings. This AD was prompted by a report of the fracture of an inboard actuator attach fitting of the outboard flap. An inspection of the attach fitting revealed that it was incorrectly machined with a cylindrical profile instead of a conical profile, resulting in reduced wall thickness. We are issuing this AD to detect and correct defective inboard actuator attach fittings which, combined with loss of the outboard actuator load path, could result in uncontrolled retraction of the outboard flap, damage to flight control systems, and consequent reduced controllability of the airplane.
69-15-07: 69-15-07 BELL: Amendment 39-801. Applies to Bell Model 204B, 205A, and 205A-1 helicopters equipped with the Float Kit Installation, Part No. 204-706-053, or Part No. 205-706- 050. Compliance required as indicated. To prevent possible failure of the aft cross tube, Part No. 204-706-053-5, or Part No. 205-050-114-1, due to fatigue cracks, accomplish the following: (a) Remove and replace aft cross tubes with 900 or more hours' time in service on the effective date of this AD within the next 100 hours' time in service. (b) Remove and replace aft cross tubes with less than 900 hours' time in service on the effective date of this AD, prior to accumulating 1000 hours' time in service. (c) Remove and replace all subsequent replacement aft cross tubes prior to accumulating 1000 hours' time in service. (d) Operators not having kept time in service records on individual cross tubes should use float kit hours' time in service for the purpose of Paragraphs (a), (b), and (c) above. (Bell Helicopter Company Service Bulletin No. 204B-5, 205A-3, dated April 2, 1969, pertains to this subject.) This amendment becomes effective August 16, 1969.
2013-20-17: We are adopting a new airworthiness directive (AD) for ECD Model BO105C (C-2 and CB-2 Variants) and BO105S (CS-2 and CBS-2 Variants) helicopters with a certain third stage turbine wheel installed. This AD requires installing a placard on the instrument panel and revising the limitations section of the rotorcraft flight manual (RFM). This AD is prompted by several incidents of third stage engine turbine wheel failures, which were caused by excessive vibrations at certain engine speeds during steady-state operations. These actions are intended to alert pilots to avoid certain engine speeds during steady-state operations, prevent failure of the third stage engine turbine, engine power loss, and subsequent loss of control of the helicopter.
74-17-03: 74-17-03 DEHAVILLAND: Amendment 39-1914. Applies to Model DHC-2 (Mk I) Beaver Airplane. Compliance required within the next 110 hours in service after the last inspection pursuant to this directive and thereafter at intervals not to exceed 110 hours in service from a preceding inspection. To prevent carbon monoxide from entering the airplane cabin, accomplish the following: (a) For airplanes using the intensifier tube cabin heater system, remove the tube and perform a visual inspection on both the intensifier tube and the exhaust pipe for any holes, cracks, flaking or weld separations. (b) For airplanes using heater jackets, remove the jacket and perform the same inspection as in (a) above. Replace or repair parts found to have any holes, cracks flaking or weld separations. Make welding repairs in accordance with Advisory Circular AC 43.13-1 or an FAA approved equivalent. Upon submission of substantiation data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, Eastern Region, may adjust the repetitive inspection intervals specified in this AD. This Directive supersedes Airworthiness Directive 57-13-02. This amendment is effective August 12, 1974.
55-15-05: 55-15-05 DOUGLAS: Applies to All DC-7 Aircraft Below Fuselage No. 486 Equipped With Hamilton Standard Propellers. \n\n\tCompliance required by first scheduled engine change after November 1, 1955, but not later than November 1, 1956. \n\n\tTo increase the integrity of the propeller feathering system in the event of a powerplant fire, all existing propeller feathering lines located forward of the firewall in zone 2 must be replaced with lines and flexible hose assemblies which will meet current fireproof and fire resistant requirements. \n\n\t(a)\tInstall Aeroquip 304 protective sleeves on the propeller feathering line forward of the feathering pump, in accordance with Aeroquip Drawing 304005-10S-46. Resistoflex SSFR-3800-10 hose assembly and Aeroquip 309009-10S hose assembly are also considered acceptable for this application. \n\n\t(b)\tRemove the existing short 304 sleeves from the feathering pump supply line between the oil tank and feathering pump and install a fireproof cover, Douglas P/N 3500614-2. Aeroquip 601000 hose assembly equipped with Aeroquip 304 full-length protective sleeve, or Aeroquip 680-16S hose assembly equipped with Aeroquip 304 short sleeves covering the end fittings are also considered acceptable for this application. \n\n\t(Douglas Service Bulletin DC-7 No. 74 dated July 19, 1955, covers this same subject.)
67-30-03: 67-30-03 FAIRCHILD-HILLER: Amdt. 39-503 Part 39 Federal Register November 2, 1967. Applies to Type FH-227 Airplanes, and Type F-27A, F-27F, F-27G and F-27J Airplanes. Compliance required as indicated. To detect cracks in the rudder skin, stiffeners, and rear spar flange located between the ribs of the lower section of the rudder, accomplish the following: (a) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 150 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection, comply with (b). (b) Visually inspect for cracks the left and right rudder skins from Stations 10 to 71 between the middle and rear spars. By manual compression of the left and right rudder skins, inspect for indications of cracks in the rudder stiffeners at Stations 16, 28, 40, 52 and 64 between the middle and rear spars, and in the rear spar flanges at these stations, or use an FAA-approved equivalent inspection. If a skin crack or indications of a crack in the stiffeners or rear spar flanges are found, comply with (d). (c) Within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the last 300 hours' time in service, and thereafter at intervals not to exceed 400 hours' time in service from the last inspection, comply with (b) on FH-227 airplanes modified in accordance with Fairchild-Hiller Service Bulletin No. 27-4 (FH 227) dated December 27, 1966 or later FAA-approved revision, and on F-27 airplane modified in accordance with Fairchild-Hiller Service Bulletin No. 27-42 (F-27) dated December 27, 1966 or later FAA-approved revision, or an FAA-approved equivalent modification. If a skin crack or indications of a crack in the stiffeners or rear spar flanges are found, comply with (d). (d) Repair cracked parts in accordance with Part 43 of the Federal Aviation Regulations or replace them with an unused part of the same part number or an FAA-approved equivalent before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. (e) The repetitive inspection specified in (c) may be discontinued on FH-227 airplanes modified in accordance with Fairchild-Hiller Service Bulletin No. 27-11 (FH-227) Revision No. 1, dated September 7, 1967 or later FAA-approved revision, and on F-27 airplanes modified in accordance with Fairchild-Hiller Service Bulletin No. 27-54 (F-27) Revision No. 1, dated September 7, 1967 or later FAA-approved revision, or an FAA approved equivalent modification. (f) Equivalent inspections may be approved by an FAA maintenance inspector, Equivalent parts, Service Bulletin revisions, and modifications, must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (g) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This supersedes Amendment 39-390 (Part 39 F.R. April 8, 1967), AD 67-12-03. This amendment effective November 1, 1967.
2013-22-21: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (Bell), Model 206A, 206B, 206L, 206L-1, 206L- 3, 206L-4, and 407 helicopters with an Apical Industries, Inc. (Apical) emergency float kit installed under Supplemental Type Certificate (STC) Number SR01535LA. This AD was prompted by an incident in which the floats installed on a helicopter failed to deploy. This AD requires inspecting, labeling, and replacing the float inflation hoses. We are issuing this AD to prevent failure of the emergency floatation gear to deploy during an emergency event.