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74-25-03: 74-25-03 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 2027 as amended by Amendment 39-2043. Applies to Grumman American G-1159 airplanes certificated in all categories. Compliance required immediately after the effective date of this AD. To preclude the actuation of the Flight Power Shut-off valve in flight, accomplish the following: Make and install a placard reading "DO NOT PULL IN FLIGHT" on the Flight Power Shut-off handle. Incorporate Grumman American Aircraft Service Change No. 186. Upon compliance with this service change, remove the placard. Amendment 39-2027 became effective immediately. This amendment 39-2043 becomes effective immediately.
70-07-06: 70-07-06 HAWKER SIDDELEY: Amdt. 39-963. Applies to Models DH-104 "Dove" and DH-114 "Heron" airplanes. Within the next 25 hours' time in service after the effective date of this AD, accomplish the following: (a) Conduct an x-ray inspection of the two tailplane rear spar to rear fuselage bulkhead support struts for internal corrosion. (b) If corrosion is found during the inspection required by paragraph (a), before further flight replace each strut found corroded with a serviceable strut of the same part number. (c) Within 30 days after completing the inspection required by paragraph (a), report the results of the inspection, negative or positive, to the Chief, Engineering and Manufacturing Branch, Aeronautical Center, AC-210, Federal Aviation Administration, Oklahoma City, Oklahoma 73125. (Reporting approved by Bureau of Budget under BOB No. 04-RO 174). This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by the telegram dated 4 March, 1970, which contained this amendment.
2006-15-04: The FAA is superseding two existing airworthiness directives (AD) that apply to certain Airbus Model A300 B2, A300 B4, and A300-600 series airplanes. One AD currently requires an inspection for cracks of the lower outboard flange of gantry No. 4 in the main landing gear (MLG) bay area, and repair if necessary. The other AD currently requires, among other actions, repetitive inspections of the gantry lower flanges, and repair if necessary. This new AD requires new repetitive inspections for cracks in the lower flange of certain gantries, and repair if necessary, which ends the existing inspection requirements. This new AD also provides for optional terminating actions for the new repetitive inspections. This AD results from a report of a large fatigue crack along the outboard flange of beam No. 4 and a subsequent determination that existing inspections are inadequate. We are issuing this AD to detect and correct fatigue cracks in the lower flanges of gantries 1 through 5 inclusive in the MLG bay area, which could result in reduced structural integrity of the fuselage, and consequent rapid decompression of the airplane. DATES: This AD becomes effective August 24, 2006. The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300-53-0379, Revision 01, excluding Appendix 01, dated October 4, 2005; and Airbus Service Bulletin A300-53-6152, Revision 01, excluding Appendix 01, dated October 4, 2005; listed in the AD as of August 24, 2006. On October 19, 2004 (69 FR 55329, September 14, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300-53-6128, excluding Appendix 01, dated March 5, 2001. On January 22, 2004 (69 FR 867, January 7, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A300-53A0371, Revision 01, dated September 10, 2003; and Airbus All Operators Telex A300-53A6145, Revision 01, dated September 10, 2003. On July 30, 1998 (63 FR 34589, June 25, 1998), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex (AOT) 53-11, dated October 13, 1997.
47-10-28: 47-10-28 LOCKHEED: (Was Mandatory Note 31 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088. Compliance required prior to July 1, 1947. Enlarge holes in elevator cable seals in aft pressure bulkhead to 0.19 + 0.031-inch diameter. (LAC Service Bulletin 49/SB-208 covers this same subject.)
69-07-02: 69-07-02 PILATUS: Amdt. 39-743. Applies to Model PC-6 Airplanes Serial Nos. 1 through 701, 2001 through 2018, 2023, 2025 through 2029, 2040 and 2041. Compliance required as indicated unless already accomplished. To prevent structural damages to the aileron mass balance unit P/N 6106.11, due to internal corrosion, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 10 hours' time in service from the last inspection, inspect the external surface of the mass balance support arms for evidence of corrosion (indicated by blistering of paint or slight discoloration). (b) If evidence of corrosion is detected during the inspection prescribed in paragraph (a), before further flight, replace the aileron mass balance unit P/N 6106.11 with a modified aileron mass balance unit P/N 6106.11 (which is identified by a 1/2-inch diameter yellow colored marking), or with a new aileronmass balance unit P/N 111.45.08.001, in accordance with Pilatus Service Bulletin No. 89, dated November 1968 or later Swiss Federal Air Office approved revision or an FAA approved equivalent. (c) The repetitive inspections required by paragraph (a) may be discontinued after the modified or new aileron mass balance unit has been installed. This amendment becomes effective April 1, 1969.
2006-14-08: The FAA adopts a new airworthiness directive (AD) for some Mitsubishi Heavy Industries (MHI) MU-2B series airplanes. This AD requires you to verify that the current flight idle blade angles are set at 12 degrees. If not already set at that angle, set the flight idle blade angles to 12 degrees. This AD results from a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. We are issuing this AD to prevent incorrect flight idle blade angle settings. This unsafe condition, if not corrected, could lead to an asymmetric thrust situation in certain flight conditions, which could result in airplane controllability problems.
72-09-03: 72-09-03 BEECH: Amdt. 39-1440. Applies to Model 99 Series (Serial Numbers U-1 through U-145) Airplanes. Compliance: Required as indicated, unless already accomplished. To assure security of control wheel adapters, accomplish the following: A) Within 25 hours' time in service after the effective date of this AD, remove all paint from Beech P/N 50-524590-3 control wheel adapters and dye penetrant inspect said adapters in accordance with FAA Advisory Circular 43.13-1. Repeat the inspection at 100 hour intervals thereafter. If a crack is found during any of the inspections required by this AD, prior to further flight, replace with Beech P/N 99-524036-33 control wheel adapters, except that the aircraft may be flown in accordance with FAR 21.197 to a location where the replacement may be performed. B) When the old Beech P/N 50-524590-3 control wheel adapters are replaced by the new Beech P/N 99-524036-33 control wheel adapters the inspections called for herein areno longer required. C) Equivalent methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Beechcraft Service Instruction No. 0380-155, Rev. 1, pertains to this subject. This amendment becomes effective May 2, 1972.
48-18-02: 48-18-02 SIKORSKY: Applies to Model S-51 Series Helicopters Serial Numbers SS-51- 01 Through SS-5157. Compliance required at first main gearbox overhaul but in any event not later than the next 400 hours of operation. To prevent cracks caused by stress concentration at the corners of the internal splines on the bevel drive gear (Sikorsky P/N S-535360), a 1/32-inch radius relief should be formed at the lower end of each spline. The procedure for accomplishing this modification is given in Sikorsky Aircraft Information Circular No. 40 and No. 40 Revision "A".
97-19-09: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214ST helicopters, that requires creation of a component history card or equivalent record using a Retirement Index Number (RIN) system; establishes a system for tracking increases to the accumulated RIN; and establishes a maximum accumulated RIN for the pillow block bearing bolts (bearing bolts). This amendment is prompted by fatigue analyses and tests that show certain bearing bolts fail sooner than originally anticipated because of the unanticipated high number of takeoffs and external load lifts utilizing high-power settings in addition to the time-in-service (TIS) accrued under other operating conditions. The actions specified by this AD are intended to prevent fatigue failure of the bearing bolts, which could result in failure of the main rotor system and subsequent loss of control of the helicopter.
98-05-13: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A310 and A300-600 series airplanes, that requires a one-time visual inspection to determine the accuracy of the outer placards of the static ports. This amendment also requires a one-time inspection to detect crossed connections of the air data static system and the static probe heating system, and correction of any discrepancies. 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 erroneous display of altitude information to the flight crew, and consequent reduced operational safety during all phases of flight.