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88-24-51: 88-24-51 BOEING CANADA, DE HAVILLAND DIVISION: Amendment 39-6107. Final copy of telegraphic airworthiness directive, issued December 9, 1988. Applicability: Model DHC-8-100 series airplanes, Serial Numbers 1 through 126, certificated in any category. Compliance: Required within the next 50 hours time-in-service, unless previously accomplished. To preclude the possibility of deformation or jamming of the elevator control system, accomplish the following: A. Remove inspection panels 121 BL and 121 BR or the floor panel in flight compartment aft of center console, and inspect the elevator control quadrant levers, Item 160/Part Numbers 82710146-101 (left side) and 82710146-102 (right side), for correct installation. Ensure that the curved portion of each lever points forward. B. If both left and right levers curve forward, no further action is necessary and the inspection panels may be reinstalled. C. If either lever curves rearward, inspect the associated push rod for evidence of bending or binding. Replace, prior to further flight, any incorrectly installed levers and damaged push rods with new or serviceable units, as applicable. D. 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, New York Aircraft Certification Office, FAA, New England 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, New York Aircraft Certification Office. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer, may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. Amendment 39-6107 was effective earlier to all recipients of Telegraphic AD T88-24-51, issued December 9, 1988. This amendment (39-6107, AD 88-24-51) becomes effective January 27, 1989.
2016-13-16: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of a manufacturing oversight, in which a supplier omitted the required protective finish on certain bushings installed in the rear spar upper chord on horizontal stabilizers, which could lead to galvanic corrosion and consequent cracking of the rear spar upper chord. This AD requires an inspection or records check to determine if affected horizontal stabilizers are installed, related investigative actions, and for affected horizontal stabilizers, repetitive inspections for any crack of the horizontal stabilizer rear spar upper chord, and corrective action if necessary. We are issuing this AD to detect and correct cracking of the rear spar upper chord, which can result in the failure of the upper chord and consequent departure of the horizontal stabilizer from the airplane, which can lead to loss of control of the airplane.
2016-14-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by reports of water leakage from the potable water system due to improperly installed waterline couplings, and water leaking into the electronics equipment (EE) bays from above the floor in the main cabin, resulting in water on the equipment in the EE bays. This AD requires replacing the potable waterline couplings above the forward and aft EE bays with new, improved couplings. This AD also requires sealing the main cabin floor areas above the aft EE bay, installing drip shields and foam blocks, and rerouting the wire bundles near the drip shields above the equipment in the aft EE bay. We are issuing this AD to prevent a water leak from an improperly installed potable water system coupling, or main cabin water source, which could cause the equipment in the EE bays to become wet, resulting in an electrical short and potential loss of system functions essential for safe flight.
2001-09-15: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-200 and -300 series airplanes, that currently requires repetitive inspections to detect cracking in the radii on the support angles on the lower jamb (latch lug fittings) of the main deck cargo door, and replacement of cracked parts. This amendment adds a requirement for installation of redesigned lower jamb latch support angles in the main cargo door surround structure, which would terminate the repetitive inspections. This amendment is prompted by the development of a modification that will provide better protection of the subject area against effects of structural fatigue. The actions specified by this AD are intended to prevent in-flight separation of the main deck cargo door from the airplane due to fatigue cracking on the support angles on the lower door jamb.
47-25-06: 47-25-06 GLOBE: (Was Mandatory Note 10 of AD-766-5.) Applies to Models GC-1A and GC-1B Aircraft Serial Numbers 3 to 157 Inclusive, and Number 159. Compliance required prior to August 1, 1947. Remove the carburetor flexible air duct, P/N 11-440-3405 and metal air intake scoop, at point of attachment at rear right engine cylinder and outboard connection to the right exhaust heater shroud. Replace with flexible air duct, Globe P/N 11-440-3648, and elbow, Globe P/N 11- 440-3729. This is necessary to prevent collapsing of the air duct when the carburetor air heater is used. (Globe Customer Service Maintenance Bulletin No. 5 covers this same subject.)
2022-24-11: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by a report indicating that foreign object debris (FOD) could have been introduced during rework of certain engine fire shutoff switches (EFSSs). This AD requires determining the serial number of the left and right EFSS and replacing affected parts. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2001-09-17: This amendment supersedes an emergency airworthiness directive (AD) that was sent previously to all known U.S. owners and operators of CFMI CFM56-5C turbofan engines by individual letters. That action required within 10 days after receipt of that emergency AD, an initial inspection of the fuel manifold for wear or chafing; and an initial inspection of the CJ9L harness for correct installation, for clamp wear and to verify a minimum clearance between the CJ9L harness and the fuel manifold. That action also required repetitive inspections of the fuel manifold, clamps, and the CJ9L harness within every 500 hours time in service until new configuration clamps are installed on the harness. This amendment requires the same inspections, and adds inspection requirements for the manifold, clamps, and the CJ10L harness, and clamps on the other side of the engine. The actions specified in this AD are intended to prevent fuel leakage on the hot section or in the primary fire zone of the engine which may result in an engine fire and subsequent damage to the airplane.
2001-09-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-100, -100C, and -200 series airplanes, that, for certain airplanes, requires a one-time inspection of certain fuselage circumferential skin joints to determine the type of fasteners installed, and replacement of any aluminum fasteners with steel fasteners, if necessary; or modification of certain fuselage circumferential skin joints; as applicable. For certain other airplanes, this amendment also requires repetitive inspections to detect corrosion, sealant deterioration, cracking, or disbonding; repair, if necessary; and modification of certain fuselage circumferential skin joints. This amendment is prompted by reports of corrosion between the body skins and cold-bonded doublers at the fuselage circumferential skin joints. The actions specified by this AD are intended to prevent delamination of the cold-bonded doublers, which could result in corrosion of the body skins and doublers, and consequent reduced structural capability of the fuselage circumferential skin joints.
2016-13-13: We are adopting a new airworthiness directive (AD) for certain Beechcraft Corporation Model BAe.125 Series 1000A and 1000B airplanes and Model Hawker 1000 airplanes. This AD was prompted by reports of inadvertent stowage of the thrust reversers, which can result in high forward engine thrust even though the throttle is commanding reverse thrust. This AD requires installing kits that include relays, associated wiring, and a thrust reverser fail annunciator. We are issuing this AD to prevent inadvertent stowage of the thrust reversers, which could cause a runway overrun during a rejected takeoff or landing, and consequent structural failure and possible injury to occupants.
2010-22-04: We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires a detailed inspection for certain defects of the upper fasteners of the aft mount support fittings of the left and right engines, and corrective actions if necessary. This new AD requires repetitive replacement of the upper row of fasteners of the support fittings of the engine aft mount with new fasteners; and repetitive general visual inspections for defects of the lower row fasteners (Row B) of the support fittings of the left and right engine aft mounts, and replacement of all clearance fit fasteners in the lower row if necessary. This AD was prompted by reports of loose, cracked, or missing fasteners in the aft mount support fitting of the left and right engines. We are issuing this AD to prevent loose, cracked, or missing fasteners in the engine aft mount support fittings, which could lead to separation of the support fittings from the pylon, and could result in separation of the engine from the airplane.