Results
2006-14-07: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 737 series airplanes. That AD currently requires inspection of the elevator tab inboard hinge support structure to detect fatigue cracking and corrective action if necessary. That AD also provides an optional terminating action. This new AD adds airplanes to the applicability and requires new repetitive inspections. For airplanes having elevators with laminated rear spars, this new AD requires repetitive inspections for interlaminar corrosion, delamination, or disbonding in the rear spar, repetitive inspections for cracking in the spar web, and repair including related investigative/corrective actions if necessary. For airplanes having elevators with solid rear spars, this new AD requires repetitive inspections for cracking in the spar web and repair including related investigative/corrective actions if necessary. This AD results from reports of cracks in the elevator rear spar web at the tab hinge bracket locations. We are issuing this AD to detect and correct cracking, corrosion, interlaminar corrosion, delamination, and disbonding in the elevator rear spar, which may reduce elevator stiffness and lead to in-flight vibration. In-flight vibration may lead to elevator and horizontal stabilizer damage and reduced controllability of the airplane.
2006-14-09: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300, and A340-200 and -300 series airplanes. This AD requires modifying certain rotary actuator assemblies for the leading edge slat. This AD results from a leak found at the seal of the torque limiter output shaft of the Type A rotary actuator of leading edge slat No. 1. We are issuing this AD to prevent a decrease in the torque limiter function, which could result in degradation and damage to the attachment bolts of the leading edge slat, loss of the slat, and consequent reduced control of the airplane.
2018-15-02: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This AD requires inspecting the tail rotor (TR) pitch rod. This AD is prompted by a report of several cases of damaged TR pitch rod ball joints. The actions of this AD are intended to correct an unsafe condition on these helicopters.
67-27-03: 67-27-03 BRITISH AIRCRAFT: Amendment 39-762. Applies to Model BAC 1-11 200 and 400 Series airplanes. Compliance required as indicated. To prevent fatigue failures of the flap carriage links P/N AB09 A943 and post modification PM 2245 flap carriage links P/N AB09 A3657, accomplish the following: (a) For airplanes equipped with carriage links P/N AB09 A943, within the next 500 landings after January 15, 1967, or before the accumulation of the number of landings specified in Column 2 or Column 3, as applicable, for the respective flap numbers specified in Column 1, whichever occurs later, and thereafter at intervals not to exceed the number of landings specified for that flap number and series of airplane, replace carriage links P/N AB09 A943 with new links of the same part number; or replace with carriage links P/N AB09 A3657. If carriage links P/N AB09 A3657 are used as replacements, they must be replaced in accordance with the requirements of paragraph (b). (Column 1) (Column 2) (Column 3) Flap No. Number of Landings Number of Landings (link location) 200 Series Airplanes 400 Series Airplanes 1 3,000 2,000 2 10,000 8,000 3 24,000 16,000 (b) For airplanes equipped with carriage links P/N AB09 A3657, within the next 300 landings after the effective date of this AD or before the accumulation of the number of landings specified in Column 2 or Column 3, as applicable, for the respective flap number specified in Column 1, whichever occurs later, and thereafter at intervals not to exceed the number of landings specified for that flap number and series of airplane, replace carriage links P/N AB09 A3657 with new links of the same part number, or replace with carriage links P/N AB09 A943. If carriage links P/N AB09 A943 are used as replacements, they must be replaced in accordance with the requirements of paragraph (a). (Column 1) (Column 2) (Column 3) Flap No. Number of Landings Number of Landings (link location)200 Series Airplanes 400 Series Airplanes 1 4,000 3,000 2 12,000 10,000 3 32,000 24,000
51-11-04: 51-11-04 TEMCO: Applies to Models GC-1A and GC-1B and Includes All Serial Numbers. Compliance required as indicated. A. At each 100-hour or annual inspection, all bushings in all landing gear pivot points should be inspected for wear that would allow fore and aft travel of the main landing gear. The total fore and aft travel of the wheels, measured at the center of the axle, due to the cumulative slack in the worn bushing, should not be more than 3/8-inch. This check should be made with the hydraulic pressure relieved on the system and with the landing gear in two positions: (1) Unlocked and in an intermediate position near to, but not in, the full down position; and (2) With the landing gear just entering the wheelwell. If the total fore and aft travel of the wheel of either landing gear is more than 3/8-inch in either position, the landing gear assembly must be repaired as necessary to reduce this travel to less than 3/8-inch. B. At the next 100-hour or annualinspection, whichever occurs first, unless already accomplished, install spacer emergency landing gear pull down system to prevent inadvertent unthreading of drive screw. (TEMCO Service Bulletin No. 28 covered this same subject.) C. At each 100-hour or annual inspection, the emergency extension system should be inspected for proper adjustment in accordance with paragraphs 8, 9 and 12 of TEMCO Service Bulletin No. 28.
2006-13-17: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200 series airplanes. This AD requires a one- time deactivation of the auxiliary fuel system, repetitive venting and draining of the auxiliary fuel tank sumps, and revising the Limitations section of the airplane flight manual to limit the maximum cargo weight. This AD results from a re-evaluation of the floor structure and cargo barriers conducted by the STC holder. We are issuing this AD to prevent structural overload of the auxiliary fuel tank support structure, which could cause the floor beams to fail, damaging the primary flight controls and the auxiliary power unit fuel lines that pass through the floor beams, resulting in loss of control of the airplane. We are also issuing this AD to prevent structural overload of the cargo barriers, which could cause the barriers to fail, allowing the cargo to shift, resulting in damage to the auxiliary fuel tanks, residual fuel leakage, and consequent increased risk of a fire.
2021-01-02: The FAA is adopting a new airworthiness directive (AD) for M7 Aerospace LLC Models SA26-AT and SA26-T airplanes. This AD was prompted by reports of the airplane power lever linkage detaching from the TPE331 engine propeller pitch control (PPC) shaft. This AD requires repetitively inspecting the PPC for proper torque and making any necessary corrections until the replacement of the PPC assembly and the installation of a secondary retention feature (safety wire) are done. The FAA is issuing this AD to address the unsafe condition on these products.
2006-14-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 F4-600R series airplanes and Model A300 C4- 605R Variant F airplanes. This AD requires modifying certain structure in the fuselage zone at the lavatory venturi installation in the nose section, and performing a related investigative action and corrective action if necessary. This AD results from an analysis that revealed that airplanes equipped with Airbus Modification 08909 had a concentration of loads higher than expected in the fuselage zone (high stress) at the lavatory venturi installation in the nose section, which could be the origin of cracks that developed in the fuselage skin and propagated from the edge of the air vent hole. We are issuing this AD to prevent fatigue cracking of the fuselage skin, which could result in loss of the structural integrity of the fuselage and consequent rapid depressurization of the airplane.
2006-14-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes, and Model A340-541 and A340-642 airplanes. This AD requires inspecting to determine if certain emergency escape slides/slide rafts (referred to as slide/rafts) are installed in certain crew/passenger doors; and, if so, performing a one-time inspection to determine if the electrical harnesses of the slide/rafts are properly routed, and rerouting the harnesses if necessary. This AD results from report that a slide/raft failed to deploy properly during a deployment test. We are issuing this AD to detect and correct improper routing of the electrical harnesses of certain slide/rafts, which could prevent proper deployment of the slide/rafts and delay evacuation of passengers and flightcrew during an emergency.
2018-13-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-300 and -300F series airplanes. This AD was prompted by reports of fatigue cracking in the lower outboard wing skin at the farthest outboard fastener of the inboard segment of a certain stringer. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of the lower outboard wing skin at the inboard segment of a certain stringer, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2018-14-06: We are superseding Airworthiness Directive (AD) (AD) 2017-07- 10 for certain American Champion Aircraft Corp. (ACAC) Model 8KCAB airplanes. AD 2017-07-10 required fabrication and installation of a placard to prohibit aerobatic flight, inspection of the aileron hinge rib and support, and a reporting requirement of the inspection results to the FAA. This AD requires repetitive inspections of the aileron hinge support, installation of the aileron hinge support reinforcement kit, and incorporation of revised pages into the service manual. This AD was prompted by a report of a cracked hinge support and cracked hinge ribs, which resulted in partial loss of control with the aileron binding against the cove. We are issuing this AD to address the unsafe condition on these products.
95-19-04 R1 RES: This amendment rescinds an existing Airworthiness Directive (AD), applicable to certain Learjet Model 35, 35A, 36, 36A, 55, 55B, and 55C airplanes. That AD currently requires installation of a placard on the instrument panel in the cockpit to advise the flightcrew that the Omega navigation system may be inoperative at certain engine speeds. That AD also provides for an optional installation of certain band reject filters, which eliminates the need for the placard. The requirements of that AD were intended to prevent excessive deviation from the intended flight path due to loss of navigation signals, which could result in a potentially low-fuel condition or a traffic conflict. Since the issuance of that AD, use of the Omega navigation system has been permanently discontinued; therefore, the original unsafe condition no longer exists.
68-21-06: 68-21-06 SIKORSKY: Amendment 39-671. Applies to S-61A, S-61L, S-61N Type Helicopters. (a) Within the next ten hours time in service after the effective date of this Airworthiness Directive unless already accomplished, deactivate the automatic flight control system (AFCS) by disconnecting the power sources to the AFCS system and the channel monitor panel as follows: (1) Pull circuit breakers for electric power to the channel monitor panel and the AFCS system and safety the circuitbreaker buttons in the tripped position. (2) Disconnect electrical connectors at the aux. servos and secure to wire bundle. Electrically ground all three pins on each plug on the aux. servos. (b) For Models S-61L and S-61N, the AFCS may be reactivated when Sikorsky Service Bulletin No. 61B55-10A, dated October 4, 1968, or later FAA approved revision, or equivalent alteration approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) For Model S-61A, the AFCS maybe reactivated when an alteration approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region is incorporated. This amendment is effective October 24, 1968, and supersedes the telegram dated September 17, 1968 on this subject.
2020-26-14: The FAA is superseding Airworthiness Directive (AD) 75-16-20, which applied to all Mitsubishi Heavy Industries, Ltd., Model MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B-26, MU-2B-30, MU-2B-35, and MU-2B-36 airplanes. AD 75-16-20 required repetitive inspections of the propeller pitch control (PPC) lever for security and proper rigging. This AD requires \n\n((Page 85507)) \n\nmodification and repetitive inspections of the PPC lever linkage. The FAA is issuing this AD to address the unsafe condition on these products.
2006-13-13: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737 airplanes. This AD requires revising the airplane flight manual to advise the flightcrew of improved procedures for pre- flight setup of the cabin pressurization system, as well as improved procedures for interpreting and responding to the cabin altitude/ configuration warning horn. This AD results from reports that airplanes have failed to pressurize, and that the flightcrews failed to react properly to the cabin altitude warning horn. We are issuing this AD to prevent failure of the airplane to pressurize and subsequent failure of the flightcrew to recognize and react to a valid cabin altitude warning horn, which could result in incapacitation of the flightcrew due to hypoxia (lack of oxygen in body) and consequent loss of airplane control.
2006-13-15: We are adopting a new airworthiness directive (AD) for all Mitsubishi Heavy Industries MU-2B series airplanes. This AD requires you to do the following: Remove and visually inspect the wing attach barrel nuts, bolts, and retainers for cracks, corrosion, and fractures; replace any cracked, corroded, or fractured parts; inspect reusable wing attach barrel nuts and bolts for deformation and irregularities in the threads; check the minimum breakaway torque of reused wing attach barrel nuts; replace any deformed or irregular parts; and install new or reusable parts and torque to the correct value. This AD results from a recent safety evaluation that used a data-driven approach to evaluate the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type designairplanes. We are issuing this AD to detect and correct cracks, corrosion, fractures, and incorrect torque values in the wing attach barrel nuts, which could result in failure of the wing barrel nuts and/or associated wing attachment hardware. This failure could lead to in-flight separation of the outer wing from the center wing section and result in loss of controlled flight.
2018-14-08: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200LR series airplanes. This AD requires revising certain documents to provide revised operating limitations. For certain airplanes, modification of the water and fuel scavenge systems in the fuel tanks, electrical changes in the main equipment center, and installation of new electrical load management system (ELMS2) software is an acceptable alternative to the documents revision. This AD was prompted by reports of unreliable performance of the water and fuel scavenge systems. We are issuing this AD to address the unsafe condition on these products.
2006-13-16: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 727 airplanes. This AD requires repetitive measurements of the freeplay of the left and right outboard aileron balance tabs and of the upper and lower rudder tabs, and related investigative/corrective actions if necessary. This AD also requires repetitive lubrication of the hinge bearings and rod end bearings of the outboard aileron balance tabs. This AD results from reports of freeplay-induced vibration of the outboard aileron balance tabs and rudder tabs. We are issuing this AD to prevent excessive vibration of the airframe during flight, which could result in divergent flutter and loss of control of the airplane.
69-22-01: 69-22-01 BRITISH AIRCRAFT CORPORATION: Amdt. 39-863. Applies to BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated unless already accomplished. To prevent a malfunction of the ventral stairway door, accomplish the following: (a) Inspect ventral stairway starboard hinge bolt (M.M. 52-10) for signs of looseness or insecurity within the next 100 hours' time in service after the effective date of this AD unless already accomplished within the last 550 hours' time in service and thereafter at intervals not to exceed 650 hours from the last inspection. (b) If during the inspection required by paragraph (a), the starboard hinge bolt (M.M. 52-10) is found to be insecure or to have rotated loose, secure the hinge bolt before further flight in accordance with BAC 1-11 Alert Service Bulletin 52-A-PM 3701, dated March 24, 1969, or later ARB-approved issue, or FAA-approved equivalent. (c) The repetitive inspection required by paragraph (a) may be discontinued after the hinge bolt has been secured in accordance with paragraph (b). This amendment becomes effective November 17, 1969.
2020-26-09: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report of cracks found in fastener holes at a certain station of the center wing box. This AD requires repetitive external surface high frequency eddy current (HFEC) inspections and repetitive external surface ultrasonic inspections; or repetitive internal detailed inspections; of a certain station of the center wing box for any cracking, and repair if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2020-25-06: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report that corrosion was found on the shock strut cylinders during unscheduled maintenance of the nose landing gear (NLG). This AD requires a modification of the NLG shock strut cylinder. The FAA is issuing this AD to address the unsafe condition on these products.
70-10-01: 70-10-01 BEECH: Amdt. 39-986 as amended by Amendment 39-1222. Applies to all 99 Series Airplanes (Serial Numbers U-1 through U-114). Compliance: Required as indicated, unless already accomplished. To prevent a fire hazard, accomplish the following: Within the next 50 hours' time in service after the effective date of the AD, modify the printed circuit boards in the edge lighted instrument panels in accordance with either Beechcraft Service Instruction No. 0203-351 or any other method approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region. Amendment 39-986 became effective May 12, 1970. This Amendment 39-1222 becomes effective June 3, 1971.
2006-13-14: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters. This action requires initial and repetitive inspections of each tail rotor counterweight bellcrank (bellcrank) with a specified part number and serial number. If external damage, a crack, roughness, or looseness between the bearing set and bellcrank is found or if bearing set axial play exceeds 0.015 inch, this action requires replacing the bellcrank with an airworthy bellcrank with two prefix letters in the serial number. This amendment is prompted by reports of failure and subsequent loss of a weighted portion of the bellcrank and reports of certain replacement bellcranks having design flaws. The actions specified in this AD are intended to prevent bellcrank failure, loss of a weighted portion of the bellcrank, and subsequent loss of control of the helicopter.
2000-06-05: This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France Model SA330F, SA330G, SA330J, AS332C, AS332L, AS332L1, and AS332L2 helicopters. This action requires replacing certain tail rotor blades before further flight after April 30, 2000. This amendment is prompted by loss of control of a helicopter due to a lightning strike on a tail rotor blade. This condition, if not corrected, could result in loss of a tail rotor blade and subsequent loss of control of the helicopter
2009-18-06: 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: During operation in icing conditions, an asymmetric configuration of the de-icing boots was detected, occurring during the inflation and deflation check of the de-icing system. This was found to be due to an unexpected failure mode in the pneumatic and de-icing system's control electronic logic. This condition, if not corrected, could affect the de-icing capabilities of the boots installed on the wing and horizontal stabilizers, potentially leading to loss of control of the aircraft. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.