Results
2016-10-11: We are superseding Airworthiness Directive (AD) 2015-03-06 for all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. AD 2015-03-06 required repetitive inspections of the left-hand (LH) and right-hand (RH) wing main landing gear (MLG) rib 6 aft bearing lugs (forward and aft) to detect any cracks on the two lugs, and replacement if necessary. This new AD requires reduction of certain compliance times. This AD was prompted by reports of additional cracking of the MLG rib 6 aft bearing lugs. We are issuing this AD to detect and correct cracking of the MLG rib 6 aft bearing lugs, which could result in collapse of the MLG upon landing.
75-23-01: 75-23-01 SCHEIBE FLUGZEUGBAU GmbH: Amendment 39-2412. Applies to SF 27A gliders, serial numbers 6001 to 6105 inclusive, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent failure of the welded area of the elevator actuating lever of the elevator driveshaft, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, inspect the welded area of the elevator actuating lever of the elevator drive shaft for cracks in accordance with No. 1 of the Action paragraph of Scheibe Flugzeugbau Technical Note No. 257- 1/74, translation dated 26 June, 1975, or an FAA-approved equivalent. (b) If cracks are found, before further flight, repair the weld and modify the elevator drive shaft by applying a new reinforcing plate in accordance with No. 2 of the Action paragraph of Scheibe Flugzeugbau Technical Note No. 257-1/74, translation dated 26 June 1975, or an FAA-approved equivalent. (c) If no cracks are found, within the next 100 hours' time in service after the effective date of this AD, modify the elevator drive shaft by applying a new reinforcing plate in accordance with No. 2 of the Action paragraph of Scheibe Flugzeugbau Technical Note No. 257- 1/74 translation dated June 26, 1975, or an FAA-approved equivalent. This amendment becomes effective November 14, 1975.
97-14-01: This amendment supersedes Airworthiness Directive (AD) 75-24-07 R1, which currently requires repetitively inspecting the left-hand (LH) rudder bar assembly for cracks and loose fasteners on certain Pilatus Britten-Norman Ltd. BN-2A and BN-2A Mk 111 series airplanes, and replacing any cracked part. The superseding action requires inspecting the LH rudder bar assembly and determining the wall thickness of the slider tube unit. This action also would require modifying the rudder bar assembly by replacing the LH slider tube with a new strengthened slider tube unit as terminating action for the repetitive inspections currently required by AD 75-24-07 R1. The development of a modification to the rudder bar assembly, which terminates the repetitive inspections required by AD 75-24-07 R1, prompted this AD. The actions specified by this AD are intended to prevent failure of the pilot s rudder bar assembly, which could result in loss of control of the airplane during landing operations.
2005-13-25: The FAA is adopting a new airworthiness directive (AD) for Turbomeca S.A. Arriel 2B turboshaft engines with Modification TU62A incorporated. This AD results from several reports of the hydromechanical unit (HMU) acceleration controller axle sticking. This AD requires initial and repetitive inspections, cleaning, lubrication, and checks for proper operation of the HMU acceleration controller axle. We are issuing this AD to prevent loss of control of engine fuel flow in manual control mode or mixed control mode, leading to engine overspeed and in-flight engine shutdown, or uncommanded in-flight engine shutdown.
2016-10-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes. This AD was prompted by a report of a pilot commanding an in-flight engine shut down in response to a low oil pressure warning indication. Further investigation revealed the mounting studs in the engine mounted alternating current (AC) generator mounting plate were pulled out of position and the threaded interface in the plate was corroded. This AD requires repetitive inspections for discrepancies on certain AC generator mounting adapters, and replacing discrepant adapters with serviceable ones. This AD also requires revising the maintenance program to incorporate a repetitive task specified in certain temporary revisions. We are issuing this AD to detect and correct corrosion in the AC generator mounting plate, which could result in a gap between the AC generator and the generator mounting plate, and cause loss of engine oiland consequent engine failure.
99-23-11: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 and Avro 146-RJ series airplanes, that requires repetitive inspections to detect signs of chafing to the fuel feed pipe, and repair or replacement of the fuel feed pipe with a serviceable part, if necessary; and ensuring that responder units, electrical connector backshells, and associated wiring are undamaged and are positioned correctly to provide maximum clearance with the fuel pipe. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent damage to the fuel feed pipe, which could result in fuel leaks and an increased potential for fire on the airplane.
2005-13-24: The FAA is adopting a new airworthiness directive (AD) for all AvCraft Dornier Model 328-100 airplanes. This AD requires modifying the electrical wiring of the fuel pumps; installing insulation at the hand flow control and shut-off valves, and other components of the environmental control system; and installing markings at fuel wiring harnesses. This AD also requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new inspections of the fuel tank system. This AD is prompted by the results of fuel system reviews conducted by the airplane manufacturer. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2001-18-08: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767-300 series airplanes modified by supplemental type certificate SA7019NM-D, that requires modification of the in-flight entertainment (IFE) system to install a switch to remove power from the IFE system, and revision of flight crew and cabin crew procedures. This action is necessary to ensure that the flight crew and cabin crew are able to remove electrical power from the IFE system when necessary and are advised of appropriate procedures for such action. Inability to remove power from the IFE system during a non-normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
74-17-01: 74-17-01 SARGENT INDUSTRIES, PICO DIVISION: Amendment 39-1913. Applies to Sargent Industries, Pico Division Regulator P/N 30001 incorporated in passenger evacuation slides and slide/rafts on aircraft certificated in all categories. \n\n\tNote: This regulator is installed in, but not limited to, Pico, Air Cruiser and International Inflatable slides on B-707, B-727, B-737, DC-6, DC-7, DC-8, DC-9, DC-10, and L-188 aircraft. \n\n\tCompliance required within two years after the effective date of this AD, unless already accomplished. \n\n\tTo prevent delayed actuation of regulator P/N 30001, modify the Sargent Industries, Pico Division regulator, P/N 30001, in accordance with Sargent Industries, Pico Division Service Bulletin 25-51, dated March 14, 1974, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective September 16, 1974.
74-17-05: 74-17-05 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 1920 as amended by amendment 39-2263 is further amended by Amendment 39-2359. Applies to Grumman Model G-1159 airplanes certificated in all categories. Compliance required within the next 10 hours' time in service after receipt of telegram dated July 17, 1974, unless already accomplished or noted otherwise. Any equivalent method of compliance with this AD must be approved by Chief, Engineering and Manufacturing Branch, FAA, Southern Region. Deactivate the ground spoilers by accomplishing the following: 1. Remove the electrical connector on the ground spoiler solenoid operated control valve P/N 1159 SCH 230-1. Cap and stow. Placard control valve "INOPERATIVE". 2. Pull and lock out ground spoiler circuit breaker (2 amp) (Pilot's Circuit Breaker Panel). 3. Disconnect the ground spoiler actuators from the solenoid actuated control valve by either of the following methods: 1st METHOD (A) Removehydraulic line P/N 1159H20014-770 GRSU-6 which connects the ground spoiler control valve to hydraulic flow divider P/N 1159 SCH 255-1. (B) Remove AN815-6 union from flow divider. Remove restrictor-filter P/N H962-041 from the control valve and install in open port of flow divider using P/N 1159H20011- 6 O-ring. Leave port open to atmosphere. Plug open port of control valve with P/N AN814-6DL plug and P/N 1159HZ0011-6 O-ring. Safety plug. (C) Plug both ends of line removed and place line and union in storage, OR 2nd METHOD (A) Disconnect restrictor-filter P/N H962-041 from the control valve. Leave restrictor-filter attached to the hydraulic line P/N 1159H20014-770 GRSU-6 and open to the atmosphere. Secure the hydraulic line and restrictor-filter. (B) Plug the control valve with P/N AN814-6D plug and P/N 1159H20011-6 O-ring. 4. Without hydraulic system pressure applied, check that the ground spoiler cylinders are locked. This may be accomplished byapplying an upward force of approximately 50 pounds to the trailing edge surface of the ground spoiler. There shall be no motion of the cylinder piston. If the piston extends, readjust the cylinder terminal end until a locked condition results. 5. Repeat item 4 with "Combined" hydraulic system pressure applied. 6. Install following placard adjacent to the Ground Spoiler Hydraulic Pressure Arming Switch with the words "GROUND SPOILERS INOPERATIVE". 7. To prevent the Speed Brake/Take-Off warning from sounding during landing incorporate Grumman Interim Aircraft Service Change (ASC) 181 "Speed Brake/Flap Warning - Ground Disable" by September 13, 1974. The "NO GRD SPOILER" light will be inoperative. 8. Follow the Airplane Flight manual procedures for selection of ground spoiler switch, "armed" for take-off, to prevent hydraulic system pressure fluctuations in the event of failure of the left engine during take-off. For flight operation with the ground spoilers inoperative, attention is directed to the following limitations in the AFM: Page 1-9, Anti-Skid Brakes. The airplane will not be dispatched with the anti- skid system inoperative. Page 1-10, Takeoff with 10 degree flaps. No takeoff will be made when using 10 degree flaps. Page 1-27, Note at bottom of page. Add 680 feet to the required field length or subtract 680 feet from the available field length in determining allowable weight. Landing field lengths in AFM are unchanged - See AFM Page 4-126. In order to reactivate the ground spoilers, Grumman ASC 180 - Flight Controls (ATA No. 27) "Reactivation of Ground Spoilers" or equivalent approved by Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region, must be complied with. Amendment 39-1920 was effective August 9, 1974, and was effective on receipt for all recipients of the telegrams dated July 17, 1974, and July 25, 1974, and the letter of July 29, 1974, which contained this amendment. Amendment 39-2263 became effective on July 18, 1975. This amendment 39-2359 becomes effective September 1, 1975.