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98-21-01: This amendment adopts a new airworthiness directive (AD) that is applicable to International Aero Engines AG (IAE) V2500-A1 series turbofan engines. This action requires a one-time ultrasonic inspection of fan blade roots for cracks, and, if necessary, replacement of cracked fan blades with serviceable parts. This amendment is prompted by a report of dovetail root cracks visually detected on three fan blades from one engine during a routine inspection. The actions specified in this AD are intended to prevent fan blade root cracks, which could result in fan blade root failures, an uncontained engine failure, and damage to the aircraft.
79-13-01: 79-13-01 BEECH: Amendment 39-3504. Applies to Models C50, D50, D50A, D50B, D50C, D50E, E50, F50, G50, H50, and J50 airplanes modified in accordance with STC SA76SW certified in all categories. Compliance is 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 25 hours time-in-service after the effective date of this Amendment, incorporate into the existing Airplane Flight Manual, the temporary Airplane Flight Manual Supplement Included in this AD as Figure 1 or Excalibur Aviation Flight Manual Supplement dated May 31, 1979, or later approved revision. b. Within 100 hours time-in-service after the effective date of this Amendment, accomplish items (1), (2), (3), and (4) below, except that this compliance time may be extended to 200 hours time-in-service if the inspection of components forward of the firewall required by AD 79-01-02 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 or 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 an FAA-approved equivalent are acceptable. (Pressure test the hose assemblies in accordance with industry practice.) 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 the manufacturer's torque limits. Apply paint or torque putty to fittings after tightening. (2) On airplanes having engines with the 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 other than those specified in paragraph b(2) above, after changing all installation fuel system hoses, with mixture control in "cut off" position, select main tanks, turn main boost pump 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 run-up specified in Figure 1 and inspect all hoses and fittings for signs of fuel or oil leakage. c. On or before October 19, 1979, install continuous type fire detector systems in the engine compartment and wheel wells in accordance with the Beech Service Kit No. 80-9010, or the Shadin Kit No. 2125-1, with revisions as covered by Excalibur Aviation Company Service Bulletin No. 79-01. d. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region. Beechcraft Service Instructions No. 0999, Shadin Report No. 2125, and Excalibur Aviation Company Service Bulletin 79-01 or later approved revisions referenced herein cover the subject matter of this AD. This amendment becomes effective July 5, 1979. FIGURE 1 TEMPORARY AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECH MODEL 50 SERIES AIRPLANES (AD 79-13-01 requires this supplement to remain in the airplane flight manual until replaced by Excalibur Aviation Company Flight Manual Supplement dated May 31, 1979, or later approved revisions.) Model N- S/N In addition to the presently specified preflight procedures, prior to 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 the cowl 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. 4. Record in Airplane Maintenance Records.
91-24-01: 91-24-01 GENERAL ELECTRIC COMPANY: Amendment 39-8086. Docket No. 91-ANE-43. Supersedes AD 90-24-12, Amendment 39-6808. Applicability: General Electric Company (GE) CF6-6 series turbofan engines installed on but not limited to McDonnell-Douglas DC-10 aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent rupture of the compressor rear frame (CRF) casing that could result in an engine shutdown, aircraft damage, and aborted takeoff, accomplish the following: (a) At the next scheduled open cowl check, but not later than 100 cycles in service (CIS) after the effective date of this AD, inspect the CRF outer case compressor discharge pressure (CDP) manifold port plug weld area for cracks in accordance with GE CF6-6 Service Bulletin (SB) 72-971, Revision 2, dated August 27, 1991. (b) Remove from service, prior to further flight, CRF casings which exceed the serviceable limits specified in Table 1 or Table 2, as applicable, of GE CF6-6 SB 72-971, Revision 2, dated August 27, 1991. (c) For engines with CRF casings inspected after December 11, 1990 (the effective date of AD 90-24-12), reinspect and remove from service CRF casings in accordance with the inspection intervals and crack limits specified in Table 1 of GE CF6-6 SB 72-971, dated October 2, 1990, until the first scheduled inspection after the effective date of this AD. (d) Thereafter, reinspect and remove from service CRF casings in accordance with the inspection intervals and crack limits specified in Table 1 or Table 2, as applicable, of GE CF6-6 SB 72-971, Revision 2, dated August 27, 1991. (e) At the next shop visit, but not later than 4,500 CIS after the effective date of this AD, perform a visual, fluorescent-penetrant, and radiographic inspection of the CRF, and rework the CRF in accordance with GE CF6-6 SB 72-977, dated March 15, 1991. (f) For the purpose of this AD, a shop visit is defined as the CRF exposed at the piece-part level. (g) Compliance with paragraph (e) of this AD eliminates the inspection requirements of paragraphs (a), (b), (c), and (d) of this AD and constitutes a terminating action to this AD. (h) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Engine Certification Office. (i) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (j) The reinspections and removal of CRF casings shall be done in accordance with General Electric CF6-6 Service Bulletin 72-971, dated October 2, 1990. This incorporation by reference was previously approved by the Director of the Federal Register at 55 FR 48591, (December 11, 1990) in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies of General Electric service bulletins may be obtained from General Electric Aircraft Engines, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. (k) The inspections and rework shall be done in accordance with the following General Electric Company documents: Document Number Page Number Issue/Rev Date GE CF6-6 SB 72-971 1-11 Revision 2 8/27/91 12 Original 10/2/90 Total: 12 pages GE CF6-6 SB 72-977 1-34 Original 3/15/91 Total: 34 pages This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies of General Electric service bulletins may be obtained from General Electric Aircraft Engines, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. (l) This amendment becomes effective on May 26, 1992.
2013-05-15: We are adopting a new airworthiness directive (AD) for Robinson Helicopter Company (Robinson) Model R44 and R44 II helicopters equipped with emergency floats. This AD requires replacing the inflation valve assembly. This AD was prompted by the failure of the emergency floats to deploy during a factory test because a needle was binding within the inflation valve assembly. The actions are intended to prevent the failure of the floats to inflate during an emergency landing.
98-21-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB 2000 series airplanes. This action requires repetitive functional tests (checks) to verify proper operation of the nose wheel steering system (NWSS) limitswitch, and replacement of the existing limitswitch with a new limitswitch, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent combined failure of the limitswitch and the feedback shaft in the NWSS servo unit, which could result in uncommanded nose wheel steering deflection and reduced controllability of the airplane on the ground during takeoff or landing.
80-12-05 R2: 80-12-05 R2 BRITISH AEROSPACE, INC. (formerly Hawker Siddeley Aviation, Ltd.): Amendment 39-3789 as amended by Amendment 39-4390 is further amended by Amendment 39- 4580. Applies to Models HS/DH/BH 125 airplanes, all series, certificated in all categories. Compliance is required as indicated. To detect and correct cracks in the bridge casting of the nose landing gear drag stay assembly and prevent possible nose landing gear collapse, accomplish the following: (a) Upon the accumulation of 2000 landings on the bridge casting or within the next 100 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 900 landings on the bridge casting from the last inspection or every two years, whichever occurs first, inspect and rework or replace as necessary the bridge casting P/N 25UN49A in accordance with Section 2A "Accomplishment Instructions" of British Aerospace Service Bulletin 32-184, Revision 2, dated October 20, 1980, or an FAA-approved equivalent. (b) Prior to the installation of modified bridge casting P/N 25UN49AD held as spares or in store, accomplish the inspection and rework specified in paragraph (a) of this AD. NOTE: British Aerospace Modification 252677 introduces a new production standard of bridge casting P/N 25UN49AD, which incorporates "radiusing," polishing, and special surface treatment of the bridge area. (c) For modified bridge castings, P/N 25UN49AD, continue to inspect in accordance with paragraph 2.A., "Accomplishment Instructions," of British Aerospace Service Bulletin 32- 184, Revision 3, dated June 24, 1982, or an FAA-approved equivalent. (d) For purposes of complying with this AD, for airplanes for which no records exist that indicate the number of landings the bridge casting has accumulated, the number of landings may be estimated by using the total airplane time in service in hours on a 1-to-1 ratio. (e) Upon request of the operator, an FAA maintenance inspector may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increased inspection interval requested for that operator. (f) Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 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). Amendment 39-3789 became effective June 16, 1980. Amendment 39-4390 became effective June 8, 1982. This Amendment 39-4580 becomes effective March 16, 1983.
2006-12-08: The FAA is adopting a new airworthiness directive (AD) for Goodrich evacuation systems approved under TSO-C69b and installed on certain Airbus Model A330-200 and -300 series airplanes, Model A340-200 and -300 series airplanes, and Model A340-541 and -642 airplanes. This AD requires inspecting to determine the part number of the pressure relief valves on the affected Goodrich evacuation systems, and corrective action if necessary. This AD results from a report indicating that, during maintenance testing, the pressure relief valves on the affected Goodrich evacuation systems did not seal when activated, which caused the pressure in the escape slide/raft to drop below the minimum allowable raft mode pressure. We are issuing this AD to prevent loss of pressure in the escape slides/rafts after an emergency evacuation, which could result in inadequate buoyancy to support the raft's passenger capacity during ditching, and increase the chance for injury to raft passengers.
2013-05-21: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC130 B4 helicopters with a cabin vibration damper installed. This AD requires installing a vibration damper casing assembly on both sides of the helicopter. This AD was prompted by a crack and failure of a cabin vibration damper blade. The actions of this AD are intended to modify the cabin vibration damper assembly to prevent contact with the flight controls in the event of a cabin vibration blade failure, jamming of a flight control, and subsequent loss of control of the helicopter.
98-20-37: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and -300 series airplanes, that requires the replacement of certain switches located in the cabin attendant's panel at doors 1 and 3 right with new, improved switches. This amendment is prompted by reports indicating that fires have occurred on some airplanes due to the internal failure of some of these switches. The actions specified by this AD are intended to prevent the installation and use of such switches that could short circuit when they fail, and consequently cause fire and smoke aboard the airplane.
91-18-10: 91-18-10 BOEING: Amendment 39-8013. Docket No. 90-NM-206-AD. \n\n\tApplicability: Model 767 series airplanes equipped with brake part numbers (P/N) identified in paragraph (a) of this AD, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the loss of main landing gear braking effectiveness, accomplish the following: \n\n\t(a)\tWithin 180 days after the effective date of this AD, incorporate the maximum brake wear limits, shown below, into the FAA-approved maintenance inspection program. \n\nBrake Mfr. \tBrake P/N\t Boeing P/N\t Max. Wear Limit \n\nBendix\t\n2607092-1\t\nS160T200-12\t\n2.15 inches \nBendix\t\n2607092-2\nS160T200-13\n2.15 inches \nBendix\t\n2607092-3\t\nS160T200-14\n2.15 inches \nBendix\t\n2607092-4\nS160T200-15\n2.15 inches \nBendix\t\n2608812-4\t\nS160T300-12\n2.56 inches \nBendix\t\n2608812-6\t\nS160T300-14\n2.90 inches \n\t\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tThis amendment (39-8013, AD 91-18-10) becomes effective on November 12, 1991.