Results
76-24-04: 76-24-04 MORANE SAULNIER (SOCATA): Amendment 39-2780. Applies to Models MS 892A-150, MS 892E-150, and MS 893A airplanes, all serial numbers, and Model MS 893E airplanes, serial numbers 12674 and below, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect rocker oil return pipe wear and prevent possible engine failure, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, inspect the rocker oil return pipes for wear in accordance with Socata Service Bulletin No. 124, GR 79-09, dated January 1976, or an FAA-approved equivalent. (b) If, during the inspection required by paragraph (a) of this AD, rocker oil return pipe wear is found to exceed 10% of pipe wall thickness, before further flight, replace the part with a new part of the same part number. (c) Within the next 25 hours time in service after the effective date of this AD, rework the cylinder cooling deflector spring in accordance with Socata Service Bulletin No. 124, GR 79-09, dated January 1976, or an FAA-approved equivalent. This amendment becomes effective on December 14, 1976.
2007-06-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: * * * * ** * * updates [to the airplane maintenance manual (AMM), engine service manual (ESM), and quick engine change kit instruction manual (QECKIM)] have inadvertently introduced torque value errors for the bolts that attach the forward engine mount to the engine. * * * * * * * * Application of the incorrect torque to the forward engine mount bolts during maintenance could result in failure of the forward engine mount and possible separation of the engine from the airplane and damage to the wing or loss of control of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2007-06-02: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A318-100 and A319-100 series airplanes, Model A320-111 airplanes, and Model A320-200, A321-100, and A321-200 series airplanes. That AD currently requires repetitive inspections of the upper and lower attachments of the trimmable horizontal stabilizer actuator (THSA) to measure for proper clearance and to detect cracks, damage, and metallic particles. The existing AD also requires corrective actions, if necessary, and reports of inspection findings. This new AD shortens the repetitive interval for inspecting the upper THSA attachment. This AD results from new test results on the secondary load path, which indicated the need to shorten the repetitive interval for inspecting the upper THSA attachment. We are issuing this AD to detect and correct failure of the THSA's primary load path, which could result in latent (undetected) loading and eventual failure of the THSA's secondary load path and consequent uncontrolled movement of the horizontal stabilizer and loss of control of the airplane. DATES: This AD becomes effective April 19, 2007. The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-27-1164, Revision 04, including Appendix 01, dated July 17, 2006, as of April 19, 2007. On May 5, 2006 (71 FR 16203, March 31, 2006), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-27-1164, Revision 03, including Appendix 01, dated August 24, 2005.
93-10-04: 93-10-04 GULFSTREAM AEROSPACE CORPORATION: Amendment 39-8582. Docket 92-NM-222-AD. Supersedes AD 89-05-05, Amendment 39-6198. Applicability: All Model G1159 (G-II), G1159A (G-III), G1159B (G-IIB), and G-IV series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fire bottles being discharged into the wrong nacelle, accomplish the following: (a) Within 3 days or 10 hours time-in-service after May 8, 1989 (the effective date of AD 89-05-05, Amendment 39-6198), whichever occurs later, perform an inspection to determine proper configuration of electrical power leads to the engine fire extinguishing system, in accordance with the following Gulfstream Alert Customer Bulletins, dated February 2, 1989: G-II Bulletin No. 20 (for Model G1159/G1159B series airplanes); G-III Bulletin No. 4 (for Model G1159A series airplanes); or G-IV Bulletin No. 5 (for Model G-IV series airplanes); as applicable. If the configuration is not correct, prior to further flight, correct the installation in accordance with the applicable alert customer bulletin. (b) Immediately following any maintenance performed on the engine fire extinguishing system, perform the inspection procedures required by paragraph (a) of this AD in accordance with the applicable alert customer bulletin to ensure that the system is functioning properly. (c) Within 2 years after the effective date of this AD, modify the electrical leads and plumbing connections to the fire extinguishers in accordance with the following Gulfstream Aircraft Service Changes: Gulfstream II/IIB Change No. 401, dated December 6, 1991 (for Model G1159/G1159B series airplanes); Gulfstream III Change No. 195, dated December 6, 1991 (for Model G1159A series airplanes); or Gulfstream Change No. 146, dated September 5, 1991 (for Model G-IV series airplanes); as applicable. Accomplishment of this modification constitutes terminating action for theinspection procedures required by paragraph (b) of this AD. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (e) 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. (f) The inspections shall be done in accordance with Gulfstream G-II Alert Customer Bulletin No. 20, dated February 2, 1989 (for Model G1159/G1159B series airplanes); Gulfstream G-III AlertCustomer Bulletin No. 4, dated February 2, 1989 (for Model G1159A series airplanes); or Gulfstream G-IV Alert Customer Bulletin No. 5, dated February 2, 1989 (for Model G-IV series airplanes); as applicable. The modification shall be done in accordance with Gulfstream II/IIB Aircraft Service Change No. 401, dated December 6, 1991 (for Model G1159/G1159B series airplanes); Gulfstream III Aircraft Service Change No. 195, dated December 6, 1991 (for Model G1159A series airplanes); or Gulfstream IV Aircraft Service Change No. 146, dated September 5, 1991 (for Model G-IV series airplanes); as applicable. 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 may be obtained from Gulfstream Aerospace Corporation, Technical Operations Department, P.O. Box 2206, Savannah, Georgia 31402-9980. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington;or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, Suite 210C, 1669 Phoenix Parkway, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on July 1, 1993.
95-21-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires a visual inspection to detect damage to the flexible fuel drain line of the auxiliary power unit (APU), and replacement of the drain line, if necessary. This amendment also requires installation of two additional clamps to secure the flexible fuel drain line to the fuel supply line of the APU. This amendment is prompted by reports of electrical arcing between the flexible fuel drain line and the APU starter motor. The actions specified by this AD are intended to prevent such electrical arcing, which could result in a fire in the APU.
2007-05-12: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330 airplanes and Model A340-200 and -300 series airplanes. This AD requires inspecting to determine the part number of certain S4- and MZ-type spoiler servo controls (SSCs). For certain other airplanes, this AD requires inspecting to determine the part number of all SSCs. This AD also requires replacing any affected SSC with a new SSC. This AD results from a new load duty cycle defined by the manufacturer. Additional fatigue tests and calculations done on this basis indicated that the spoiler valve manifold of the S4-type SSCs, and, on certain airplanes, the maintenance cover of the MZ-type SSCs, may crack during its service life due to pressure impulse fatigue. We are issuing this AD to prevent fatigue cracking of certain SSCs, which could result in hydraulic leakage and consequent loss of SSC function and loss of the associated hydraulic system. These conditions could affect all three hydraulicsystems, which could result in reduced controllability of the airplane.
95-23-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires inspections to detect cracking, corrosion, and freeplay in the spherical washers located in certain assemblies where the aft flap track attaches to the wing trailing edge, and replacement of the washers, if necessary. This amendment is prompted by reports indicating that these washers can break under load. The actions specified in this AD are intended to prevent breakage of these washers, which could result in structural damage to the attachment assembly and eventually lead to separation of the flap from the airplane.
2007-05-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Following Safety Alert No. SA-006, issued by the National Transportation Safety Board (NTSB) on aircraft icing, it was impossible to demonstrate that the aircraft can safely takeoff when contaminated by frost, ice, snow, or slush, and fly into icing conditions. We are issuing this AD to require actions to correct the unsafe condition on these products.
47-12-01: 47-12-01 DOUGLAS: (Was Mandatory Note 14 of AD-762-7.) Applies to All C-54 and R5D Series Airplanes, and the Following DC-4 Airplanes: 42904 to 42943, Inclusive; 42948 to 42952, Inclusive; 42982 to 42996, Inclusive; 43065 to 43069, Inclusive; 43071; 43072; and 43102. DC-4 Production Airplanes Nos. 43070, 43090, and Subsequent Except 43102, as Noted Above, Will be Modified Prior to Delivery. \n\n\tTo be accomplished not later than January 1, 1948. \n\n\tIf the clear-view panel in the windshield is opened in flight when the landing gear and flaps are extended, exhaust fumes enter the cabin. This causes considerable discomfort to passengers and may create a hazard which would affect the safe operation of the airplane. In order to prevent the exhaust fumes from entering the cabin under these conditions, all openings around the control cables and flap buss system at the side of the fuselage must be sealed and additional means for exhausting main cabin and cockpit ventilating air provided, unless tests made by the operator of the individual airplane show no unsatisfactory condition of carbon monoxide entering cabin with open windows when landing gear down and flaps extended. \n\n\t(Douglas Service Bulletin No. DC-4, No. 32, covers this same subject.)
2007-04-24: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires repetitive inspections of the bolts that attach the exhaust nozzle to the aft engine flange to determine if any bolts are missing or fractured, and replacement of the existing bolts with new, improved bolts. This AD results from reports of the engine exhaust nozzle and fairing departing from the airplane in flight due to missing attachment bolts. We are issuing this AD to detect and correct missing or fractured attachment bolts, which could lead to the loss of an engine exhaust nozzle during flight and consequent structural damage to the airplane and hazard to people or property on the ground. Damage to the airplane could cause the airplane to yaw and result in reduced controllability of the airplane.