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2015-14-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes. This AD was prompted by fuel system reviews conducted by the manufacturer. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new limitations for fuel tank systems. We are issuing this AD to prevent potential ignition sources within the fuel system, which could result in a fuel tank explosion.
2000-11-17: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 helicopters and that currently requires initial and repetitive inspections of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar) for cracks or delaminations. This amendment requires the same actions required by the existing AD and corrects an incorrectly stated part number (P/N) in the existing AD. This amendment is prompted by a report of delamination of a Kevlar tie- bar. The actions specified by this AD are intended to detect cracks that could lead to delamination of the Kevlar tie-bar, loss of tail rotor control, and subsequent loss of control of the helicopter.
2000-11-10: This amendment supersedes an existing airworthiness directive (AD) applicable to certain Rolls-Royce plc (R-R) RB211 series turbofan engines. That AD currently requires the removal from service of intermediate pressure (IP) compressor stage 6-7 rotor shafts that exceed reduced cyclic life limits. This amendment requires further reduction of cyclic life limits and introduction of new reduced cyclic bands for rework. This action is prompted by additional stress analysis conducted following failure of an IP compressor stage 6 disk. The actions specified by this AD are intended to prevent an uncontained engine failure due to rupture of an IP compressor stage 6-7 rotor shaft.
91-02-10: 91-02-10 CFM INTERNATIONAL: Amendment 39-6839. Docket No. 89-ANE-39. Applicability: CFM International (CFMI) CFM56-3, -3B, -3C series turbofan engines, installed on, but not limited to, Boeing 737-300, 737-400 and 737-500 aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent engine power loss or flameout while operating in heavy precipitation, accomplish the following: (a) Install fan splitter fairing, fan stage 1 vane assembly, and new centering shroud, in accordance with the Accomplishment Instructions contained in CFMI CFM 56-3, -3B, -3C series Service Bulletin (SB) 72-450, Revision 1, dated May 30, 1989, within 30 days after the effective date of this AD. (b) Install the 12 door variable bypass valve (VBV) configuration in accordance with the Accomplishment Instructions contained in CFMI CFM 56-3, -3B, -3C series SB 72-462, Revision 1, dated May 30, 1989, within 30 days after the effective date of this AD. (c) Aircraft may beferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803. The installation procedures shall be done in accordance with the following CFM International documents: Document Page Number Revision Date CFMI CFM 56-3, 1-4, 6-26 Revision 1 5/30/89 -3B, -3C 5 Original 4/17/89 SB 72-450 CFMI CFM 56-3, 1-27, 29-33 Revision 1 5/30/89 -3B, -3C 28 Original 4/10/89 SB 72-462 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to CFM International, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. These documents may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, NW, Room 8301, Washington, DC 20591. This amendment (39-6839, AD 91-02-10) is effective on February 11, 1991.
2015-14-04: We are adopting a new airworthiness directive (AD) for Kaman Model K-1200 helicopters with certain main rotor blades (MRB) installed. This AD requires inspecting each MRB for a crack or damage. This AD was prompted by a report that a crack was found on an MRB during a tear-down inspection. The actions are intended to detect a crack in the MRB, which could lead to failure of the MRB and subsequent loss of control of the helicopter.
59-12-01: 59-12-01 FAIRCHILD: Applies to all F-27 Series aircraft equipped with the heater system. Compliance required by July 15, 1959, and every 100 hours thereafter until forthcoming permanent fix is incorporated. (1) An incident has been reported in which a loose "B" nut on the fuel line connection to the combustion heater fuel control unit caused fuel to leak out around the shroud. In order to preclude possibilities of leakage at the heater fuel system fittings, remove and retain shroud assemblies, P/N 27-774575-1, attached to tube assemblies, P/N's 27-683051-151 or -251 and 27-774512-11, connected to fuel control assembly, P/N 43C80. Also remove and retain shroud assembly, P/N 27-774575-1, attached to opposite end of tube assembly, P/N 27-774512-11, connected to heater assembly, P/N 49C65. (2) At locations where shrouds were removed, inspect and determine that fittings of tube assemblies are torqued to proper values and no evidenceof fuel leakage exists. Torque fittings of tube assembly, P/N 27-774512-11 to 135 in. lbs. min. - 150 in. lbs. max., and tube assembly P/N 27-683051-151 or -251 to 40 in. lbs. min. - 65 in. lbs. max. (3) Operate heater to determine that no evidence of fuel leakage exists at tube assembly connections to fuel control and heater assemblies and reinstall shroud assemblies. (Fairchild F-27 Service Bulletin No. 21-48 dated April 22, 1959, covers this same subject.)
2010-17-16: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, S-76B, and S-76C helicopters. This AD requires an initial and recurring inspections of the tail rotor vertical stabilizer aft spar assembly (aft spar assembly) for a crack, loose or working fasteners, and corrosion, and, if any are found, further inspections of the vertical stabilizer forward spar assembly (forward spar assembly). Repairing or replacing any unairworthy part before further flight is also required. This AD also requires a recurring track-and-balance of the tail rotor. Finally, this AD requires installing a vertical stabilizer modification kit, which is terminating action for the requirements of the AD. This AD is prompted by 26 reports of fatigue cracks in the aft spar assembly web and outer caps. The actions specified by this AD are intended to detect and correct an unbalanced or out-of-track tail rotor, which could lead to increased vibrations, a fatigue crack, loss of a portion of the vertical stabilizer and subsequent loss of control of the helicopter.
2000-11-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time review of the maintenance records to determine if tripping of the fuel boost pump circuit breakers has been recorded, repetitive inspections to detect fuel leakage from the fuel boost pump wiring conduits, and corrective actions, if necessary. This amendment also requires replacement of the three single wires inside the metal conduit of the fuel boost pumps with new wires protected by a polyamide sleeve, which terminates the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the fuel boost pump wiring from chafing, which could result in electrical arcing and a possible fuel tank ignition source.
2015-14-01: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by a report of loose bolts that are intended to secure the translating door crank assembly to the outside handle shaft. This AD requires a detailed inspection for loose bolts on the aft translating door crank assembly, and removal and reinstallation of the bolts. We are issuing this AD to prevent loose bolts from falling out. If both bolts become loose or fall out after the door is closed and locked, the door cannot be opened from inside or outside, which could impede evacuation in the event of an emergency.
89-09-01: 89-09-01 AIRBUS INDUSTRIE: Amendment 39-6192. Applicability: Model A300 series airplanes, on which Modification 1988 has been accomplished (Post Service Bulletin A300-54-022), and all Model A310 and A300-600 equipped with Walter Kidde or APCO fire extinguisher bottles, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the inability to actuate the fire extinguisher bottles, accomplish the following: A. Within 10 days after the effective date of this AD, inspect the engine fire extinguishers for an electrical bonding defect in accordance with Airbus All Operator Telex (AOT) 26/88/01. If defects are found, repair prior to further flight, in accordance with the AOT. B. Whenever the fire extinguishers bottles are replaced, perform the inspection required by paragraph A., above. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspection/modification required by this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division Avenue Didier Daurat, 31700 Blagnac, France. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6192, AD89-09-01) becomes effective on May 1, 1989.