Results
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.
98-08-29: This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Model ASK 21 sailplanes. This AD requires removing certain pages from the sailplane flight manual and replacing these pages with new pages having different information regarding spin and stall recovery. This action is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent operators from using inaccurate stall and spin recovery information provided in the sailplane flight manual (SFM), which could result in the inability to recover from a spin or stall during flight.
2017-11-10: We are adopting a new airworthiness directive (AD) for all Lycoming TIO-540-AJ1A reciprocating engines. This AD requires initial and repetitive inspections of engine exhaust system weld joints and torque checking the exhaust pipe flange mounting nuts. This AD was prompted by several reports of engine exhaust leaks. We are [[Page 26983]] issuing this AD to correct the unsafe condition on these products.
2017-10-25: We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) model Spey 506-14A, Spey 555- 15, Spey 555-15H, Spey 555-15N, and Spey 555-15P turbofan engines. This AD requires reducing the maximum approved life limits for certain high- pressure compressor (HPC) stage 12 rotor disks. We are issuing this AD to correct the unsafe condition on these products.
98-08-24: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection to determine if all corners of the forward lower cargo doorjamb have been previously modified. This amendment also requires low frequency eddy current inspections to detect cracks of the fuselage skin and doubler at all corners of the forward lower cargo doorjamb, various follow-on repetitive inspections, and modification, if necessary. This amendment is prompted by fatigue cracks found in the fuselage skin and doubler at the corners of the forward lower cargo doorjamb. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.