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47-25-06: 47-25-06 GLOBE: (Was Mandatory Note 10 of AD-766-5.) Applies to Models GC-1A and GC-1B Aircraft Serial Numbers 3 to 157 Inclusive, and Number 159. Compliance required prior to August 1, 1947. Remove the carburetor flexible air duct, P/N 11-440-3405 and metal air intake scoop, at point of attachment at rear right engine cylinder and outboard connection to the right exhaust heater shroud. Replace with flexible air duct, Globe P/N 11-440-3648, and elbow, Globe P/N 11- 440-3729. This is necessary to prevent collapsing of the air duct when the carburetor air heater is used. (Globe Customer Service Maintenance Bulletin No. 5 covers this same subject.)
2022-24-11: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by a report indicating that foreign object debris (FOD) could have been introduced during rework of certain engine fire shutoff switches (EFSSs). This AD requires determining the serial number of the left and right EFSS and replacing affected parts. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2001-09-17: This amendment supersedes an emergency airworthiness directive (AD) that was sent previously to all known U.S. owners and operators of CFMI CFM56-5C turbofan engines by individual letters. That action required within 10 days after receipt of that emergency AD, an initial inspection of the fuel manifold for wear or chafing; and an initial inspection of the CJ9L harness for correct installation, for clamp wear and to verify a minimum clearance between the CJ9L harness and the fuel manifold. That action also required repetitive inspections of the fuel manifold, clamps, and the CJ9L harness within every 500 hours time in service until new configuration clamps are installed on the harness. This amendment requires the same inspections, and adds inspection requirements for the manifold, clamps, and the CJ10L harness, and clamps on the other side of the engine. The actions specified in this AD are intended to prevent fuel leakage on the hot section or in the primary fire zone of the engine which may result in an engine fire and subsequent damage to the airplane.
2001-09-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-100, -100C, and -200 series airplanes, that, for certain airplanes, requires a one-time inspection of certain fuselage circumferential skin joints to determine the type of fasteners installed, and replacement of any aluminum fasteners with steel fasteners, if necessary; or modification of certain fuselage circumferential skin joints; as applicable. For certain other airplanes, this amendment also requires repetitive inspections to detect corrosion, sealant deterioration, cracking, or disbonding; repair, if necessary; and modification of certain fuselage circumferential skin joints. This amendment is prompted by reports of corrosion between the body skins and cold-bonded doublers at the fuselage circumferential skin joints. The actions specified by this AD are intended to prevent delamination of the cold-bonded doublers, which could result in corrosion of the body skins and doublers, and consequent reduced structural capability of the fuselage circumferential skin joints.
2016-13-13: We are adopting a new airworthiness directive (AD) for certain Beechcraft Corporation Model BAe.125 Series 1000A and 1000B airplanes and Model Hawker 1000 airplanes. This AD was prompted by reports of inadvertent stowage of the thrust reversers, which can result in high forward engine thrust even though the throttle is commanding reverse thrust. This AD requires installing kits that include relays, associated wiring, and a thrust reverser fail annunciator. We are issuing this AD to prevent inadvertent stowage of the thrust reversers, which could cause a runway overrun during a rejected takeoff or landing, and consequent structural failure and possible injury to occupants.
2010-22-04: We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires a detailed inspection for certain defects of the upper fasteners of the aft mount support fittings of the left and right engines, and corrective actions if necessary. This new AD requires repetitive replacement of the upper row of fasteners of the support fittings of the engine aft mount with new fasteners; and repetitive general visual inspections for defects of the lower row fasteners (Row B) of the support fittings of the left and right engine aft mounts, and replacement of all clearance fit fasteners in the lower row if necessary. This AD was prompted by reports of loose, cracked, or missing fasteners in the aft mount support fitting of the left and right engines. We are issuing this AD to prevent loose, cracked, or missing fasteners in the engine aft mount support fittings, which could lead to separation of the support fittings from the pylon, and could result in separation of the engine from the airplane.
73-21-03: 73-21-03 BELL: Amdt. 39-1732. Applies to Model 206A and 206B helicopters, serial numbers 4 through 1097, certificated in all categories, equipped with vertical fin support forgings, P/N's 206-031-417 and -418. Compliance required within the next 50 hours' time in service after the effective date of this A.D., unless already accomplished. To detect possible fatigue cracks in the vertical fin support forgings in the area of the fin attachment nut plates, accomplish the following: (a) Remove the vertical fin in accordance with paragraph 8-47, Section VIII of the 206A/B Maintenance and Overhaul Instructions. (b) Remove the paint in the area of the fin attachment nut plates (4 places). (c) Inspect for cracks, using a dye penetrant or equivalent inspection method. (d) If cracks are found in either support forging, the cracked forging must be removed and replaced prior to further flight. (e) If no cracks are found, inspect the four holes for thread marks. Any marks must be removed in accordance with Bell Helicopter Company Service Bulletin No. 206-01-73-5, Part I, paragraph 5, dated June 27, 1973, or later FAA approved revision. Apply a coating of zinc chromate primer or other suitable corrosion protection. (f) Reinstall the fin in accordance with paragraph 8-49, Section VIII of the 206A/B Maintenance and Overhaul Instructions. (g) This A.D. is not applicable if the vertical fin support forgings have been replaced in accordance with Bell Helicopter Company Service Bulletin No. 206-01-73-5, Part II dated June 27, 1973, or later FAA approved revision. 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 the Service Manager, Bell Helicopter Company, P.O. Box 482,Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective November 15, 1973.
2001-09-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310-324, A310-325, and A300 B4-622R series airplanes equipped with Pratt & Whitney PW4000 series engines. This action requires revising the Airplane Flight Manuals (AFM) for the Model A310 and Model A300-600 series airplanes. This action is necessary to prevent acceleration and climb performance less than that specified in the AFM, which could result in runway overruns or impact with obstacles or terrain. This action is intended to address the identified unsafe condition.
2016-14-03: We are adopting a new airworthiness directive (AD) for all Airbus Model A319, A320, and A321 series airplanes. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires reinforcing the forward pressure bulkhead at a certain stringer on both the left-hand and right-hand sides, and doing related investigative and corrective actions if necessary. We are issuing this AD to prevent fatigue cracking of the forward pressure bulkhead, which could result in reduced structural integrity of the airplane.
78-11-01: 78-11-01 BEECH: Amendment 39-3220 as amended by Amendment 39-3277 is further amended by Amendment 39-3413. Applies to E50, F50, G50, H50, J50, 65, A65, A65-8200, 65- 80, 65-A80, 65-A80-8800, 65-B80, 65-88 and 70 model airplanes certified in all categories except those modified in accordance with STCs SA444SW or SA587SW. COMPLIANCE: Required as indicated unless already accomplished. To reduce the possibility of powerplant fire occurrence and improve powerplant fire containment and detection capabilities, accomplish the following: A) Within the next 25 hours time-in-service after June 1, 1978, install in the existing Airplane Flight Manual, the temporary airplane Flight Manual Supplement included in this AD as Figure 1, or, Beech Aircraft Company Airplane Flight Manual Supplement P/N 50-590211-31 dated May 29, 1978 or subsequent revision. B) Within the next 100 hours time-in-service after June 1, 1978, except that this compliance time may be extended to 200 hourstime-in-service if the inspection of components forward of the firewall required by AD 77-25-01 is accomplished at intervals no greater than 50 hours time-in-service during this compliance time extension. 1) Replace existing flexible fuel, oil, hydraulic, and fuel or oil vapor carrying hose assemblies except engine breather and drain lines in the engine compartment with equivalent length and diameter hoses having strength and fire resistance qualities meeting FAA Technical Standard Order C53A, Type C or D or as specified below. Hose assemblies fabricated of Stratoflex Type 111 or 130 hose covered by fire-resistant sleeve, Stratoflex Type 2650 or 2607 or Aeroquip hose Type 303 covered with fire-resistant sleeve Type AE102 or 624 or hose specified in Beechcraft Service Instructions No. 0999 or later approved revisions, or an FAA- approved equivalent are acceptable except as noted below. (Pressure test the hose assemblies in accordance with industry practice.) On airplanes having serial numbers LC-157 through LC-335, LB-1 through LB-35, and LD-135 through LD-512, replace the main oil supply hose running from the firewall to the engine with a Stratoflex Part No. 156F001-16D0200 hose assembly or Aeroquip 620100-16-0200 hose assembly or an FAA-approved equivalent. On the Model 88 series airplanes, fabricate the hose from the engine hydraulic pump "oil out" to the firewall using high pressure type hose. Stratoflex Type 112 or Aeroquip Type 309 or FAA-approved equivalent is acceptable. Subject only these hoses to a proof pressure test of 7000 PSI and install applicable hose manufacturer's fire sleeves of types noted above. Stratoflex Type 111 or 130 hose or Aeroquip Type 303 hose with appropriate manufacturer's fire sleeve as noted above or hose specified in Beechcraft Service Instructions No. 0999 or later approved revisions, or an FAA-approved equivalent are acceptable for all other pressurization system hoses. Engine induction system hoses and vacuum system hoses are not included in the requirements of this AD. Use old hoses as a pattern when fabricating new hoses. Caution should be exercised to assure end fittings on new hoses are equivalent to old hose end fittings. Install hoses observing manufacturer's torque limits. The torque chart contained in Beechcraft Service Instructions No. 0999 or later approved revisions list acceptable limits. Apply paint or torque putty to fittings after tightening. 2) On airplanes having engines with Bendix fuel injection system, after changing all engine and installation fuel system hoses but prior to connecting the hose at the fuel injector nozzle located at the top of the induction housing, cap this hose at the nozzle end, select main tanks, turn main boost pumps ON, place mixture controls in rich position, and check all fuel carrying lines and fittings for leakage. Correct any leaks detected and recheck prior to installing hose on nozzle fittings. 3) On airplanes otherthan those specified in Paragraph B(2) above, after changing all installation fuel system hoses, with mixture control in "cut off", select main tanks, turn main boost pumps ON, and check all fuel carrying lines and fittings for leakage. Correct any leaks detected and recheck. 4) After determining that no fuel is trapped in the induction system, conduct the runup specified in Figure 1 and inspect all hoses and fittings for signs of fuel or oil leakage. C) On or before January 31, 1979 install continuous type fire detector systems in the engine compartment and wheel wells in accordance with Beech Service Kit 80-9010. NOTE: The compliance date for this paragraph was established on the basis of the most accelerated schedule the vendors of the detector components can meet and the estimated number of active airplanes of the affected models. The FAA recommends that every owner place an order for the necessary modification kit as early as possible. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Beechcraft Service Instructions No. 0999 or later approved revisions referenced herein covers the subject matter of this AD. Figure 1 TEMPORARY AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECH MODEL 50 SERIES, 65 SERIES A65 SERIES AND 70 AIRPLANES WITH RECIPROCATING ENGINES (AD 78-11-01 requires this supplement to remain in the below designated airplane flight manual until replaced by Beech Aircraft Company Flight Manual Supplement P/N 50-590211-31 dated May 29, 1978, or later approved revisions.) Model_____________ N____________ S/N ______________ In addition to the presently specified preflight procedures, prior to the first flight of each day accomplish the following. 1. Start both engines and operate at 1500 RPM. After the oil pressures stabilize, shut down the engines using the mixture control. 2. Open thecowl doors on both sides of the engines and check all engine compartment fluid hoses and fittings for indications of fluid (fuel or oil) leakage Check the wheel wells for these same conditions using a flashlight or supplemental light as necessary to provide adequate illumination of the area. 3. Correct any leak detected and secure cowl doors. Amendment 39-3220 became effective June 1, 1978. Amendment 39-3277 became effective August 17, 1978. This amendment 39-3413 becomes effective February 6, 1979.