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84-20-08: 84-20-08 GULFSTREAM AEROSPACE CORPORATION: Amendment 39-4927. Applies to Model G-159 airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To detect and prevent corrosion or failure of the forward and aft engine mount assemblies, Vickers Drawing Number 81037, Sheet 29, and Gulfstream Aerospace Drawing Numbers 159W10432-1 (L/H) and 159W10432-3 (R/H), respectively, accomplish the following unless already accomplished: (a) Within 200 hours time in service or four months after the effective date of this AD, whichever is sooner, inspect the forward and aft engine mounts, L/H and R/H, in accordance with Gulfstream I Customer Bulletin (CB) Number 241C, dated July 10, 1984, or in an equivalent manner approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. (b) If corrosion is indicated: (1) Replace corroded tubes in accordance with Customer Bulletin 241C before further flight, then revert to the inspections required under Category A, as stated in paragraph (d), below; or (2) If continued flight is desired, ascertain the remaining wall thickness of the corroded tubes and categorize in accordance with Customer Bulletin No. 241C, and perform the operations for each category as indicated by paragraph (d), below. (c) If corrosion is not indicated, perform the operations described in paragraph (d), below, for Category A. (d) Category A - Reinspect as in paragraph (a) of this AD for corrosion at intervals not exceeding six years from last inspection. Category B - Treat the tubes within 50 hours time in service in accordance with Addendum 1 or 4 of Customer Bulletin 241C and reinspect for corrosion as in paragraph (a) of this AD at annual intervals for at least two years after treatment. If there are no changes in the thickness measurements, reinspect at intervals not exceeding two years. Categories C and D - Replace corroded tubes in accordancewith Customer Bulletin 241C within 150 hours time in service or three months, whichever is sooner; then revert to the inspections required under Category A. Category E - Replace corroded tubes in accordance with Customer Bulletin 241C before further flight; then revert to inspections required under Category A. (e) To prevent failure of Category B Gulfstream "Grumman mounts," replace the mounts prior to the accumulation of 7500 landings or within the next 25 landings, whichever occurs later within the following time period, in accordance with Gulfstream Aerospace Corporation Gulfstream I Customer Bulletin No. 241C, dated July 10, 1984, or equivalent manner approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region: (1) For airplanes that have accumulated 7500 landings prior to the effective date of this AD, within the next 25 landings after the effective date of this AD; (2) For airplanes with less than 7500 landings on the effective date of this AD, within the next 25 landings after the accumulation of 7500 landings. (f) To qualify for service beyond 7500 landings, Category A Gulfstream "Grumman mounts" must accomplish paragraph (g), below, within the following period: (1) For airplanes that have accumulated 7500 landings prior to the effective date of this amendment, within the next 30 days or within 12 months of the last successful mount inspection in accordance with Gulfstream Aerospace Corporation Gulfstream I Customer Bulletin 289, Amendment 1, dated 26 May 1977, whichever occurs later, or (2) For airplanes with less than 7500 landings on the effective date of this amendment, no later than the next 30 days after the accumulation of 7500 landings. (g) Perform the ultrasonic and visual inspections in accordance with Gulfstream Aerospace Corporation Gulfstream I Inspection Schedule, Section V, Special Inspections, Engine Mounts, dated July 31, 1984, or in an equivalent manner approved by theManager, Atlanta Aircraft Certification Office, FAA, Central Region. If the inspections indicate negligible or no corrosion and no cracks, then the Grumman mount initially qualifies for the 20,000 landing life limit in accordance with Gulfstream Aerospace Corporation Gulfstream I Inspection Schedule, Section IV, Life Limited Components, dated July 31, 1984, and is no longer required to comply with the inspection requirements of paragraph (a) of this AD. Throughout this extended life limit, the inspections must be repeated at intervals not to exceed 12 months to maintain qualification for the 20,000 landing life limit. If, during such inspection, any mount subassemblies are found to have negligible or no internal corrosion and no cracks, those subassemblies may continue to be used if a detailed record of each life limited subassembly usage is maintained by the operator. If any inspection indicates the presence of unacceptable internal corrosion, replace the affected mount subassembly within the next 25 landings or 30 days, whichever occurs first. If a mount crack is found by any inspection, notify Gulfstream Aerospace Corporation, Technical Services Department, for dispositon before further flight. All life limited subassemblies that are not replaced during the repetitive inspections must be replaced by the end of the 20,000 landing life limit established by Gulfstream Aerospace Corporation Gulfstream I Inspection Schedule dated July 31, 1984. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Gulfstream Aerospace Corporation, P.O. Box 2206, Savannah, Georgia 31402. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington. This supersedes Airworthiness Directive 74-03-01, Amendment 39-3667 (38 FR 23962). This amendment becomes effective January 22, 1985.
2021-26-27: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a report indicating that during production, the manual opening and closing of the over-wing emergency exit door (OWEED) prior to the installation of the OWEED interior panel could have resulted in damaged insulation blankets below the left and right OWEEDs. This AD requires a one-time inspection for damage of the insulation blankets below the left and right OWEEDs, and replacement if necessary, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
96-17-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. This action requires the installation of a mechanical flight idle stop on the control quadrant of the flight compartment. This action also requires a revision of the Airplane Flight Manual to ensure the use of certain operating procedures after the mechanical flight idle stop is installed. Additionally, this action provides an optional terminating action for the requirements of this AD. This amendment is prompted by a report indicating that the means of protection against the selection of the "beta" range of propeller operation during flight has been reduced on certain modified control quadrants. Additionally, there have been reports indicating that power levers on the control quadrant have been moved aft of the flight idle position during flight due to improper usage of the mechanical beta stop. The actions specified in this AD areintended to prevent such movement of the power lever(s) during flight, which could result in propeller overspeed, engine damage, and loss of power to one or both engines.
90-13-11: 90-13-11 S.N. CENTRAIR: Amendment 39-6630. Docket No. 90-CE-12-AD. Applicability: Model 201B (Serial Numbers 201026 thru 201077) gliders certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To assure that the airbrake is properly functioning, accomplish the following: (a) Visually inspect the rear cockpit airbrake handle for any distortion or cracks per the instructions in S.N. Centrair Service Bulletin (SB) No. 201-07, dated February 14, 1990. (b) Determine that the airbrake handle lower arm has a minimum adequate thickness of 1.5 mm or cannot be inserted into the thickness gauge provided by Centrair per S.N. Centrair SB No. 201-07, dated February 14, 1990. (c) Prior to further flight, replace any distorted, cracked, or undersized parts with serviceable parts in accordance with the applicable manufacturers Maintenance Manual. (d) An alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, 1000 Brussels, Belgium; Telephone 513.38.30 extension 2710/2711. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. All persons affected by this directive may obtain copies of the document referred to herein upon request to S.N. Centrair Aerodrome FFN 44 36300 La Blanc, France; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6630, AD 90-13-11) becomes effective on July 17, 1990.
2011-12-03: We are adopting a new airworthiness directive (AD) for the Sikorsky Model S-92A helicopters. This AD requires a nondestructive inspection (NDI), eddy current or fluorescent penetrant inspection (FPI), of each main gearbox (MGB) upper housing assembly rib on the left, right, and forward MGB mounting foot at specified intervals based on the MGB upper housing assembly hours time-in-service (TIS). If there is a crack, this AD requires replacing the MGB upper housing assembly with an airworthy MGB upper housing assembly. This AD is prompted by a report of a crack found on the MGB upper housing assembly left mounting foot forward rib that cannot be detected visually. We are issuing this AD to prevent loss of the MGB and subsequent loss of control of the helicopter.
76-12-02: 76-12-02 BELL: Amendment 39-2638. Applies to Bell Models 47B, 47B-3, 47D, 47D-1, 47E, 47G, 47G-2, and 47H-1 helicopters certificated in all categories. Compliance required as indicated. To prevent possible fatigue failure of the tail rotor yoke, Part Number 47-641-057-9, remove and replace tail rotor yokes having Serial Numbers SR29-50501 through SR29-50507, SR-29-50509 through SR29-50528, SR29-50530 through SR29-50533, SR29-50535 through SR29-50537, SR29-50539 through SR29-50544, and SR29-50546 through SR29-50554, as specified below. (a) Replace those yokes with 390 or more hours' total time in service on the effective date of this AD, within 10 hours' time in service. (b) Replace those yokes with less than 390 hours' total time in service on the effective date of this AD, prior to accumulating 400 hours' total time in service. (c) Compliance with Bell Helicopter Company Service Bulletin Number 47-05-73-1, Revision A, dated November 18, 1975, fulfills compliance with this AD. (d) The requirements of this AD do not affect other Model 47 series helicopter tail rotor yokes. This amendment becomes effective July 14, 1976.
96-17-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that requires inspections to detect cracking of the support fittings of the Krueger flap actuator and, if necessary, replacement of existing fittings with new steel fittings and modification of the aft attachment of the actuator. This amendment is prompted by reports of cracking due to fatigue and stress corrosion of the support fittings of the Krueger flap actuator. The actions specified by this AD are intended to prevent such cracking, which could result in fracturing of the actuator attach lugs, separation of the actuator from the support fitting, severing of the hydraulic lines, and resultant loss of hydraulic fluids. These conditions, if not corrected, could result in possible failure of one or more hydraulic systems, and subsequent reduced controllability of the airplane.
2010-24-13: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires adding two new indicator lights on a certain panel to inform the captain and first officer of a low pressure condition in the left and right override/jettison pumps of the center wing tanks. This AD also requires replacing the left and right override/jettison switches on the M154 fuel control module on the P4 panel with improved switches and doing the associated wiring changes. This AD also requires, for certain airplanes, installation of a mounting bracket for the new indicator lights. This AD also requires a revision to the maintenance program to incorporate airworthiness limitation No. 28-AWL-22. This AD also requires a revision to the airplane flight manual to advise the flightcrew what to do in the event that the pump low pressure light on the flight engineer's panel does not illuminate when the pump is selected off. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent uncommanded operation of the override/jettison pumps of the center wing tanks, and failure to manually shut off the override/ jettison pumps at the correct time, either of which could lead to an ignition source inside the center wing tank. This condition, in combination with flammable fuel vapors, could result in a center fuel tank explosion and consequent loss of the airplane.
2011-08-51: We are adopting a new airworthiness directive (AD) for the products listed above. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires repetitive external eddy current inspections of the lap joints at stringers S-4R and S-4L, along the entire length from body station (BS) 360 to BS 908. If a crack indication is found, the AD requires either confirming the crack by doing internal eddy current inspections, or repairing the crack. As an alternative to the external eddy current inspections, the AD provides for internal eddy current and detailed inspections for cracks in the lower skin at the lower row of fasteners at stringers S-4L and S-4R. This AD was prompted by a report indicating that a Model 737-300 series airplane experienced a rapid decompression when the lap joint at stringer S-4L between BS 664 and BS 727 cracked and opened up due to cracking in the lower skin at the lower row of fasteners. We are issuing thisAD to detect and correct such cracking, which could result in an uncontrolled decompression of the airplane.
96-16-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 727-100 and -200 series airplanes. This action requires an inspection to detect discrepancies of internal wires and electrical components of the control box of the main deck cargo door; modification of the wiring and components of the control box of the main deck cargo door; and a revision of the Airplane Flight Manual to impose an operational limitation of the motor pump power relay and pump motor. This amendment is prompted by results of an engineering review of the wiring diagram of the main deck cargo door installations, which revealed potential failures of the control box and hydraulic pump assembly installed in accordance with the STC. The actions specified in this AD are intended to prevent such failures, which could result in an inadvertent opening of the main deck cargo door during flight, with resultant major structural damage and possible reduced controllabilityof the airplane.