Results
98-09-23: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Lockheed Model L-1011 series airplanes, that currently requires various modifications and corrective actions to prevent a potential fire hazard caused by heat damage to the flex fuel feed line from an undetected gearbox fire. In lieu of the various modifications and corrective actions, that AD also provides for an optional terminating action (i.e., installation of a vent air tube in the gear compartment and thickened gearbox housings) for another existing AD. For airplanes on which that optional terminating action has been accomplished, this amendment requires accomplishment of the various modifications and corrective actions. This amendment is prompted by a report indicating that, due to bearing failure, an in-flight fire occurred on an airplane on which a thickened gearbox housing was installed. The actions specified by this AD are intended to detect and correct bearing failure, which could lead to a fire in the gearbox.
98-09-12: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes (formerly known as Beech Aircraft Corporation Model 1900D airplanes). This AD requires inspecting and repairing the radio switching panel relay printed circuit board (PCB) and the nose avionics wire harnesses, and replacing the existing A017 component PCB with a new A017 component PCB that has internal overcurrent protection fuses. Several reported incidents of lost use of the pilot/co-pilot intercom system, VHF communication system, and public address system while in flight prompted this action. The actions specified by this AD are intended to prevent the loss of the pilot and co-pilot intercom, VHF communications, and passenger address system, which could result in loss of all communication during critical phases of flight.
98-09-17: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-200F and -200C series airplanes. This action requires repetitive inspections or a one-time inspection to detect cracking of certain areas of the upper deck floor beams; and corrective actions, if necessary. This amendment is prompted by reports indicating that fatigue cracks were found in the upper chord and web of upper deck floor beams. The actions specified in this AD are intended to prevent such fatigue cracking and the resultant failure of such floor beams. Failure of the floor beam could result in damage to critical flight control cables and wire bundles that pass through the floor beam, and consequent reduced controllability of the airplane; failure of the floor beam also could result in the failure of the adjacent fuselage frames and skin, and consequent rapid decompression of the airplane.
2005-20-29: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747- 300, 747SP, and 747SR series airplanes. This AD requires repetitive inspections to detect cracks in various areas of the upper deck floor beams, and repair if necessary. This AD results from fatigue testing that revealed severed upper chords of the upper deck floor beams due to fatigue cracking. We are issuing this AD to detect and correct cracking in the upper chords of the upper deck floor beams. Undetected cracking could result in large deflection or deformation of the upper deck floor beams, resulting in damage to wire bundles and control cables for the flight control system, and reduced controllability of the airplane. Multiple adjacent severed floor beams could result in rapid decompression of the airplane. \n\nDATES: This AD becomes effective November 16, 2005. \n\n\tThe Director of the Federal Register approved the incorporation by reference ofBoeing Service Bulletin 747-53A2349, Revision 2, dated April 3, 2003; and Boeing Alert Service Bulletin 747-53A2452, dated April 3, 2003; as of November 16, 2005. \n\n\tOn June 27, 2002 (67 FR 36081, May 23, 2002), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2349, Revision 1, dated October 12, 2000. \n\n\tOn June 11, 1993 (58 FR 27927, May 12, 1993), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 747-53-2349, dated June 27, 1991.
60-06-03: 60-06-03 BRANTLY: Amdt. 112 Part 507 Federal Register March 10, 1960. Applies to all Brantly B-2 helicopters Serial Numbers 1 through 29 with tail rotor guard upper fitting, P/N B2-416-2 installed. Compliance required within the next 10 hours' time in service and at each 10 hours' time in service thereafter. A fatigue crack has been found around the forward end of the weld joining the tail rotor guard to the sheet metal bracket at the upper tail rotor gear box. To preclude the possibility of the tail rotor loss because of entanglement with the tail rotor guard, the following shall be accomplished: (a) Remove paint in the area of the weld joining the upper guard fitting P/N B2-416- 2 and the tail rotor guard P/N B2-416-3 and inspect the weld area for cracks using a dye penetrant method or equivalent. (b) If a crack is found the defective parts must be replaced or repaired prior to further flight. The fitting may be repaired by stop drilling the crack and adding a reinforcing plate of 0.035 inch by 1 inch by 1 inch SAE 4130 steel over the crack, welding all four edges to P/N B2- 416-2. The reinforcing plate may be located under the head of the screw attaching the guard fitting to the tail rotor gear box, provided the plate is drilled for this screw and extends completely under the screw head. (c) When an improved upper fitting as specified in Brantly Service Bulletin No. 1 is incorporated, the provisions of this directive no longer apply.
2002-09-04: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 205A, 205A-1, 205B, 212, 412, 412EP, and 412CF helicopters, that requires inspecting each affected tail rotor blade forward tip weight retention block (tip block) and the aft tip closure (tip closure) for adhesive bond voids, and removing any tail rotor blade with an excessive void from service. This AD also requires modifying certain tail rotor blades by installing shear pins and tip closure rivets. This amendment is prompted by five occurrences of missing tip blocks or tip closures resulting in minor to substantial damage. The actions specified by this AD are intended to prevent loss of a tip block or tip closure, loss of a tail rotor blade, and subsequent loss of control of the helicopter.
98-05-06: This action confirms the effective date of Airworthiness Directive (AD) 98-05-06, which applies to Pilatus Aircraft Ltd. (Pilatus) Model PC-12 airplanes. AD 98-05-06 requires inspecting the elevator for incorrect rivet lengths and installing new rivets if incorrect rivet lengths are found. This AD also requires inspecting the elevator to assure that an excessive gap (more than .004 inches or .1 millimeters (mm)) does not exist in the rivet shanks, and installing a shim between the rib and skin to fill any excessive gap. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified in this AD are intended to prevent fatigue damage to the elevator, which could result in structural failure and eventual loss of control of the airplane.
60-23-02: 60-23-02 CURTISS-WRIGHT: Amdt. 217 Part 507 Federal Register November 4, 1960. Applies to all C-46 Series aircraft. Compliance required as indicated. As a result of recent inspections of C-46 aircraft, unapproved inspection openings approximately 3 inches by 5 inches have been found in the wing rear spar web at the inboard flap actuator. (a) Prior to further flight visually inspect rear face of rear spar web at flap actuators by extending flap. (b) Cargo aircraft found to have unapproved openings in the rear spar web must have an approved repair accomplished within not more than 25 flight hours. Pending accomplishment of an approved repair the inspection in paragraph (a) must be accomplished after each landing and further flight not authorized if cracks or other damage are found. (c) Passenger aircraft found to have unapproved openings in the rear spar web must have an approved repair accomplished before next flight with passengers. Special flight permits maybe obtained for the purpose of permitting aircraft to be ferried to a base where repairs can be made. This airworthiness directive sent by telegram to all known air carrier operators of Curtiss- Wright C-46 Series aircraft on October 21, 1960. Effective on date of publication in the Federal Register to all persons not receiving telegram of October 21, 1960.
2002-09-06: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and MD-88 airplanes. This AD requires an inspection to verify proper installation of the support clamp of the alternating current (AC) power relay feeder cables at the aft inboard side of the electrical power center, and corrective actions, if necessary. This action is necessary to prevent the AC power relay feeder cables from chafing against the aft inboard side of the electrical power center due to improper installation, which could result in electrical arcing and damage to adjacent structures, and consequent smoke and/or fire in the electrical power center area. This action is intended to address the identified unsafe condition.
64-05-05: 64-05-05 PRATT & WHITNEY: Amdt. 691 Part 507 Federal Register February 27, 1964. Applies to All JT3C-7, JT3C-12, and JT3D Series Turbofan Engines, and JT4A Series Turbojet Engines. Compliance required as indicated. To preclude severe engine damage as the result of the engine fuel control throttle valve packing leakage, accomplish the following on all Hamilton Standard JFC25 engine fuel controls incorporating aluminum throttle valve assemblies. (a) For throttle valve assemblies previously overhaul by the procedure described in (d) or engine fuel controls Serial Numbers 34550 and up, overhaul in accordance with (d) at every engine fuel control overhaul. (b) For throttle valve assemblies previously overhauled with low burnish finish or unknown burnish finish packings P/N's 562026-28 and -29 and with the following new aluminum parts: throttle valve piston, throttle valve rod and throttle valve lower cylinder, overhaul in accordance with (d) as follows: (1) Overhaul throttle valve assemblies with 2,500 or more hours' time in service since last throttle valve assemblies overhaul or since new, within the next 100 hours' time in service after the effective date of this AD and at every engine fuel control overhaul thereafter. (2) Overhaul throttle valve assemblies with less than 2,500 hours' time in service since last throttle valve assembly overhaul or since new, prior to the accumulation of 2,600 hours' time in service since last throttle valve assembly overhaul or since new and at every engine fuel control overhaul thereafter. (c) For throttle valve assemblies previously overhauled with low burnish, unknown burnish finish or high burnish finish packings, P/N's 562026-28 and -29 and any of the following used aluminum parts: throttle valve piston, throttle valve rod and throttle valve lower cylinder, overhaul in accordance with (d) as follows: (1) Overhaul throttle valve assemblies with 1,100 or more hours' time in service since last throttle valve assemblies overhaul, within the next 100 hours' time in service after the effective date of this AD and every engine fuel control overhaul thereafter. (2) Overhaul throttle valve assemblies with less than 1,100 hours' time in service since last throttle valve assembly overhaul prior to the accumulation of 1,200 hours' time in service since last throttle valve assembly overhaul and at every engine fuel control overhaul thereafter. (d) Replace the packings P/N's 562026-28 and -29 with new high burnish finish packings, P/N's 562026-28 and -29. In addition, replace the aluminum throttle valve piston, throttle valve rod, and throttle valve lower cylinder with a new aluminum throttle valve piston, throttle valve rod, and throttle valve lower cylinder. Conduct a complete fuel control calibration after incorporation of the new parts. (e) Upon the request of the operator an FAA maintenance inspector, subject to prior approval of the Chief, Engineering andManufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Pratt & Whitney Aircraft telegraphic messages dated August 5 and 27, and October 30, 1963, to all JT3C-7, JT3C-12, JT3D Series, and JT4A Series operators cover this same subject.) This directive effective February 27, 1964.