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92-16-07: 92-16-07 CESSNA: Amendment 39-8316. Docket No. 92-CE-16-AD. Applicability: Model 441 airplanes (serial numbers 441-0001 through 441-0362), certificated in any category. Compliance: Required initially upon the accumulation of 3,000 hours time-in-service (TIS) or within the next 200 hours TIS after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 2,000 hours TIS, unless already accomplished. To prevent loss of horizontal stabilizer front spar structural support caused by cracks in the fuselage bulkhead, accomplish the following: (a) Gain access to and dye penetrant inspect the horizontal stabilizer forward attach bulkhead at Fuselage Station (FS) 387.22 in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Attachment to Service Bulletin CQB91-1R1, dated June 21, 1991. (b) If cracks are found as a result of the inspection required by paragraph (a) of this AD, prior to further flight, replace thehorizontal stabilizer forward attach bulkhead at FS 387.22 and install Service Kit SK441-103A in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Kit SK441-103A, dated June 21, 1991. (c) The installation of Service Kit SK441-103A in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Kit SK441-103A, dated June 21, 1991, is considered terminating action for the repetitive inspection requirements of this AD. Although not required, this installation may be accomplished at any time after the initial inspection. (d) 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. (e) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita,Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (f) The inspections and possible installation required by this AD shall be done in accordance with Cessna Attachment to Service Bulletin CQB91-1R1, and Cessna Service Kit SK441-103A, both dated June 21, 1991. 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 the Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (g) This amendment becomes effective on August 30, 1992.
2012-07-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A340-500 and -600 series airplanes. This AD requires repetitive inspections of the forward and aft attachment fittings and of the swan neck for cracks, and replacing the attachment fittings and the swan neck with serviceable ones if necessary. This AD was prompted by reports of cracks on the forward attachment fittings of the left and right sides of the forward hinge of the nose landing gear (NLG) aft door. We are issuing this AD to detect and correct cracks of the forward attachment fittings and the swan neck, which could lead to the in-flight detachment of the NLG aft door and result in injury to persons on the ground or damage to the airplane.
97-23-05: This amendment adopts a new airworthiness directive (AD) that applies to all Avions Pierre Robin Model R3000 airplanes. This AD requires replacing the attachment bolt between the pitch control cables and control column lever with a bolt of improved design. This AD is the result of mandatory continued airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to prevent the pitch control cables on the control column from becoming jammed due to failure of the attachment bolt, which could result in a reduction in the directional controllability of the airplane.
97-23-04: This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires replacing the fuel tank vent valves with modified fuel tank vent valves. This AD is the result of mandatory continued airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent the fuel tank inward vent valve from freezing, which, if followed by a cold soak at altitude, could result in wing airfoil distortion and structural damage with consequent degradation of the airplane's handling qualities.
92-07-14: 92-07-14 AIR TRACTOR INC: Amendment 39-8210. Docket No. 91-CE-55-AD. Applicability: Models AT-300, AT-301, and AT-302 airplanes (serial numbers (S/N) 300-0001 through 301-0688); Model AT-400 airplanes (S/N 400-0244 through 400-0415; and Model AT-400A airplanes (all S/N), certificated in any category. Compliance: Required within the next 90 calendar days after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 12 calendar months. To prevent failure of the wing structure that could result in loss of control of the airplane, accomplish the following: (a) Remove the inspection plates on the lower side of the wing leading edge skin, and visually inspect the upper and lower aluminum spar caps from the centerline to outboard end for corrosion using a flashlight and mirror. (1) If corrosion is found that is equal to or less than the criteria in Air Tractor Inc. Service Letter No. 90, dated May 6, 1991, prior tofurther flight, repair in accordance with the instructions in Air Tractor Inc. Service Letter No. 90, dated May 6, 1991. (2) If corrosion is found that is more than the criteria in Air Tractor Inc. Service Letter No. 90, dated May 6, 1991, prior to further flight, replace the wing spar cap in accordance with the applicable maintenance manual. (b) 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. (c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas 76193. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Certification Office. (d) The inspections and possible repair required by this AD shall be done in accordance with Air Tractor Inc. Service Letter No. 90, dated May 6, 1991. 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 Air Tractor Inc., P.O. Box 485, Olney, Texas 76374-0150. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. (e) This amendment becomes effective on May 8, 1992.
2012-06-21: We are adopting a new airworthiness directive (AD) for all DASSAULT AVIATION Model MYSTERE-FALCON 900 airplanes. This AD was prompted by multiple reports of fuel leakage from a defective fuel high-level sensor located in the wing front spar. This AD requires inspecting to determine fuel quantity sensors part numbers and replacing of certain fuel quantity sensors with new fuel quantity sensors. We are issuing this AD to prevent internal fuel leakage with significant fuel vapors, which could result in a fire hazard.
97-23-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 727-100 series airplanes. This action requires a revision to the Airplane Flight Manual (AFM) to prohibit stabilized operation between 60 and 75 percent N1 speed during ground operations in reverse or forward thrust. This amendment is prompted by a report that, during preparation for takeoff, a transport category airplane equipped with Rolls-Royce Tay 650-15 engines sustained an engine fan blade failure, followed by an engine fire. The actions specified in this AD are intended to prevent uncontained failure of engine fan blades due to high cycle fatigue cracking, which could result in loss of thrust from the affected engine and secondary damage to the airplane and/or fire.
97-22-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes (formerly referred to as Beech Models 1900, 1900C, and 1900D airplanes). This AD requires fabricating and installing a placard that restricts the use of the forward and aft vent blower assemblies to only the "OFF" or "HIGH" position. This AD also requires incorporating a modification that would replace the bearings on the vent blower assemblies with improved design bearings, and provide thermal protection for the vent blowers, as applicable. Incorporating the modification will eliminate the need for the placard. The AD results from reports of vent blower assembly bearings seizing and locking the blower motor on several of the affected airplanes. The actions specified by this AD are intended to prevent the vent blower assembly bearings from seizing, which could result in smoke emanating from the insulating material covering the electrical wiring and entering the airplane cabin.
2012-06-17: We are adopting a new airworthiness directive (AD) for certain [[Page 16918]] Rolls-Royce Deutschland (RRD) Models Tay 611-8 and Tay 611-8C turbofan engines. This AD requires replacement of the high-pressure (HP) turbine spanner retaining nut. This AD was prompted by the discovery that certain HP turbine spanner retaining nuts were improperly heat treated after application of silver plating. We are issuing this AD to prevent failure of the HP turbine stage 2 disc, uncontained engine failure, and damage to the airplane.
2012-06-05: 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 the inability to open the airstair door while on the ground, because the airstair door seal did not deflate, which prevented the airstair door from opening. This AD requires changing the wiring that controls the pneumatic shut-off valve. We are issuing this AD to prevent the airstair door seal from not deflating, which could result in the airstair door not opening and could impede evacuation in the event of an emergency.