Results
2008-10-03: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron (Bell) model helicopters. This action requires certain checks and inspections of each tail rotor blade assembly (T/R blade) at specified intervals and repairing or replacing, as applicable, any unairworthy T/R blade. This amendment is prompted by three failures of a T/R blade occurring during flight and a recent incident of a cracked T/R blade discovered during a scheduled visual inspection. The actions specified in this AD are intended to detect damage to a T/R blade that could lead to cracking of a T/R blade and subsequent loss of control of the helicopter.
79-18-06: 79-18-06 BENDIX: Amendment 39-3546 as amended by Amendment 39-3606. Applies to Bendix D-2000 and D-2200 series magnetos installed on 4, 6, or 8 cylinder reciprocating engines. To preclude the loss of ignition, accomplish the following within the next ten hours after the effective date of this AD unless previously accomplished. (a) Housing Distortion For any of the following magnetos, accomplish Detailed Instructions, Part I of Bendix Service Bulletin No. 605 by means of any one of Methods, I, II or III and Information Parts I-C and I-D or FAA approved equivalent procedures. (1) Red nameplate magnetos, Serial Numbers below 25001. (2) Blue nameplate magnetos, Serial Numbers below 901001. (3) Dual Ignition Systems with broken torque seals or no torque seals on four middle cover screws. (4) Duel Ignition Systems not having the letter "K" stamped on the magneto nameplate following the serial number and without a caution decal on the magneto cover. (b) Coil Securing Kit For the following magnetos, accomplish Detailed Instructions of Part II of Bendix Service Bulletin No. 605 or FAA approved equivalent procedures. (1) Red nameplate magnetos, Serial Numbers below Serial Number 17815 not having the letter, "C", stamped approximately in the center of the magneto nameplate bottom line. (2) Blue nameplate magnetos, Serial Numbers below 806001 not having the letter, "C", stamped approximately in the center of the magneto nameplate bottom line. (Bendix Service Bulletin No. 584B incorporated by reference in Service Bulletin No. 605.) (c) Identification After accomplishing the instructions of the Airworthiness Directive, metal stamp the letter, "K", after the magneto serial number on the magneto nameplate, the letter, "C", approximately centered on the magneto nameplate bottom line, and make an engine log book entry of compliance including magneto serial number. Equivalent inspections and procedures must be approved by the Chief of the Engineering and Manufacturing Branch, AEA-210, Federal Aviation Administration, (FAA) Eastern Region. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this Airworthiness Directive can be accomplished. Upon request, with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-3546 was effective September 17, 1979. This Amendment 39-3606 is effective upon publication in the Federal Register.
2008-09-13: We are adopting a new airworthiness directive (AD) for all Boeing Model 737-300, -400, and -500 series airplanes. This AD requires revising the FAA-approved maintenance inspection program to include inspections that will give no less than the required damage tolerance rating for each structural significant item (SSI), doing repetitive inspections to detect cracks of all SSIs, and repairing cracked structure. This AD results from a report of incidents involving fatigue cracking in transport category airplanes that are approaching or have exceeded their design service objective. We are issuing this AD to maintain the continued structural integrity of the entire fleet of Model 737-300, -400, and -500 series airplanes.
63-13-01: 63-13-01 BOEING: Amdt. 579 Part 507 Federal Register June 21, 1963. Applies to All Model 75 Series Aircraft Equipped With Pratt & Whitney R-985 or Wright R-975 Series Engines and Western Propeller Repair Model W2-1 Propellers, Including Those Certificated in the Restricted Category. Compliance required as indicated. As a result of several propeller blade failures the following inspections are required: Within 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 225 hours' time in service, and thereafter at intervals not to exceed 250 hours' time in service from the last inspection, remove propeller blades from hub, clean surface as necessary and inspect by dye penetrant or equivalent method for evidence of cracks within the hub area and for at least 6 inches of shank portion of the blade outside of the hub. If no cracks are found blades may be returned to service. Any blades showing evidence of cracks are not eligible for repair and shall not be used again in certificated aircraft. The repetitive inspections required on Pratt and Whitney R-985 engines in this AD are no longer necessary when the engine crankshaft flyweight and flyweight liners have been reworked or replaced at each overhaul period as detailed in AD 65-07-02. This directive effective June 21, 1963. Revised October 13, 1965.
2008-09-05: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747 airplanes. This AD requires inspecting the trunnion fork assembly of the wing landing gears to determine the part number and serial number and to determine the category of the trunnion fork assemblies. For certain airplanes, this AD also requires, if necessary, various inspections to detect discrepancies of the trunnion fork assemblies, related investigative/corrective actions, and a terminating action. This AD results from a report of a fractured trunnion fork assembly. We are issuing this AD to prevent a fractured trunnion fork assembly, which could result in the collapse of a wing landing gear on the ground and possible damage to hydraulic equipment and the aileron and spoiler cables. Such damage could result in reduced controllability of the airplane.
80-02-08: 80-02-08 VARGA AIRCRAFT CORPORATION (Morrisey): Amendment 39-3664. Applies to Varga Model 2150 and 2150A series airplanes certificated in all categories. Compliance required within the next ten (10) hours' time in service from the effective date of this AD, unless already accomplished. To prevent jamming of the rudder cables on the rudder balance weight attach bolts, accomplish the following: \n\n\t(a)\tRemove the two bolts attaching the rudder balance weight to the static balance arm and reinstall these bolts head downward, as shown in Figure 1 of this AD. \n\n\n\n\n\t(b)\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective January 21, 1980.
2008-08-20: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Wing anti ice telescopic tubes (P/N [part number] 5035-400 and 5035-500) ball joints were originally designed with high temperature polymer (Kynel\TM\) sealing rings. Temperature induced cracking of these rings associated with long term wear has been encountered in a small number of cases. This degradation may lead to binding of the ball joint and high swiveling forces which may result in improper operation of the leading edge slats and also in failure of the ball joint mounting bracket with possible friction on the aileron control rod, which could lead, if combined with a failure of the aileron emergency actuator, to an aileron jamming. The unsafe condition is a jammed aileron, which results in reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-06-22: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) Model EC 130 B4 helicopters, with certain twist grip assemblies installed, that requires inspecting the pilot and co-pilot collective levers for proper bonding between the twist grip drive tubes and the control pinions and if debonding is present, replacing the collective levers before further flight. This amendment is prompted by one incident in which the engine remained at idle speed although the twist grip had been turned to the flight position. The actions specified by this AD are intended to detect debonding between the twist grip drive tubes and the control pinions on the pilot and co-pilot collective levers to prevent loss of cockpit throttle control of the engine, and subsequent loss of control of the helicopter.
82-24-04: 82-24-04 MCDONNELL DOUGLAS: Amendment 39-4500. Applies to McDonnell Douglas Model DC-9-30, -50, and -80 series airplanes including C-9B airplanes, with manufacturer's serial numbers 48002 through 48020, 48024 through 48059, 48062, 48063, 48066 through 48074, 48079, 48080, 48083, 48086, 48087, 48092 through 48151, 48154 through 48159, 49100, 49101, 49112, 49113, and 49116 through 49119. \n\n\tCompliance required within 30 days from the effective date of this AD, unless already accomplished. \n\n\tTo assure proper functioning of the horizontal stabilizer leading edge de-icing system, accomplish the following: \n\n\tA.\tAccomplish the inspection, and if necessary, take the corrective action specified in the Accomplishment Instructions of McDonnell Douglas DC-9 Alert Service Bulletin A30-50, dated October 5, 1982, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAffected DC-9 airplanes may be operated after 30 days following the effective date of this AD, and prior to the accomplishment of Paragraph (A), above, under the following conditions: \n\n\t\t1)\tThey are not operated into known icing conditions; and \n\n\t\t2)\tA placard is installed in full view of the pilots which reads: "Flight into known icing conditions is prohibited." \n\n\tC.\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial 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. \n\n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168, or Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California 90808. \n\n\tThis amendment becomes effective November 23, 1982.
2008-08-02: We are adopting a new airworthiness directive (AD) for all Boeing Model 727 airplanes. This AD requires repetitive inspections for cracking or corrosion of the threaded end of the lower segment of the main landing gear (MLG) side strut, and corrective actions if necessary. This AD also requires prior or concurrent inspection for cracking or corrosion of the threads and thread relief area of the lower segment, corrective action if necessary, and re-assembly using corrosion inhibiting compound. This AD results from reports of the threads cracking on the MLG side strut lower segment. We are issuing this AD to \nprevent a fractured side strut, which could result in collapse of the MLG.