Results
46-23-06: 46-23-06 NOORDUYN: (Was Mandatory Note 2 of AD-2-578-1.) Applies Only to Army UC-64, -64A, and -64B Airplanes Equipped With Fuel-Burning Cabin Heaters. Required at next periodic inspection. The surface combustion fuel burning heater must be made inoperative by disconnecting and plugging the fuel line as near the engine as practicable unless the following modifications are accomplished: (a) At fire resistant bulkhead must be installed between the heater and the belly fuel tank. A firewall having the fire-resistant qualities specified in CAR 3.624 will be acceptable. (b) A fuel shutoff valve, controllable from the pilots' compartment must be installed in the fuel line between the engine and the heater. (c) Shrouds must be installed on the heater exhaust and drain lines to isolate the lines from the airframe.
2013-19-24: We are superseding Airworthiness Directive (AD) 2003-08-51 for MD Helicopters, Inc. (MDHI), Model 369A, 369D, 369E, 369H, 369HE, 369HM, 369HS, 369F and 369FF helicopters with certain MDHI or Helicopter Technology Company (HTC) tail rotor blades installed. AD 2003-08-51 required reducing the retirement life of each tail rotor blade (blade), performing a one-time visual inspection of each blade's pitch horn (pitch horn) for a crack or corrosion, and replacing any cracked blade or any blade that has exceeded its retirement life with an [[Page 65181]] airworthy blade. AD 2003-08-51 also required reporting information to the FAA within 24 hours following the one-time inspection. Since we issued AD 2003-08-51, an accident in England prompted an investigation that showed corrosion on the blade's pitch horn that had not been detected under the paint. This new AD retains some of the requirements of AD 2003-08-51 and also requires paint removal for all pitch horn inspections, inspecting for pitting and the shot peen surface's condition in addition to cracks and corrosion, and adds certain part- numbered blades to the applicability. These actions are intended to prevent a pitch horn from cracking, leading to vibration, loss of tail rotor pitch control, and subsequent loss of tail rotor and helicopter control.
75-07-04: 75-07-04 GRUMMAN AMERICAN: Amendment 39-2135. Pursuant to the authority of the Federal Aviation Act of 1958 delegated to me by the Administrator, the following Airworthiness Directive is issued applicable to operators of Grumman American AA-1, AA-1A, AA-1B, AA-5 and AA-5B airplanes delivered prior to February 18, 1975 and certified in all categories. The directive requires an inspection prior to further flight, unless already accomplished, and is effective immediately upon receipt of the Airworthiness Directive because there may be missing welds in the rudder control bar assemblies P/N 601031-501 located inside the forward portion of the fuselage. Before further flight, unless already accomplished, inspect Grumman American Model AA-1, AA-1A, AA-1B, AA-5 and AA-5B airplanes certified in all categories for missing welds in the rudder control bar assemblies P/N 601031-501. 1. Inspect the rudder pedal posts and rudder cable attaching arm inserted through the rudder torque tube bar for missing welds. At each intersection, there should be a minimum of two (2) 90 degree circumferential welds located both top and bottom (fore and aft) at the intersection of each tube. 2. If inspection reveals that there are no missing welds, no further action is required and the aircraft may be approved for return to service. 3. If inspection reveals missing welds, replace rudder control bar assembly P/N 601031-501 with a new part of the same part number. 4. If parts are unavailable, repair may be accomplished by contacting the local FAA Maintenance Inspector concerning a repair procedure which must be approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. 5. A special flight permit per FAR 21.197 may be issued after accomplishment of Paragraph 1 to allow repairs in accordance with this Airworthiness Directive. This amendment is effective upon publication in the Federal Register and was effective prior to further flightfor all recipients of the air mail letters dated March 6, 1975 which contained this amendment.
2013-20-04: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that certain special washers used in the bearing installation of the retraction jack anchorage fitting in the main landing gear (MLG) were incorrectly manufactured. This AD requires an inspection of the left-hand (LH) and right-hand (RH) bearing assemblies of the MLG retraction jack anchorage fitting to verify that the special washer is seated correctly, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct installation of incorrectly manufactured special washers, which could lead to a local stress concentration resulting in possible reduction of the fatigue life of the jack fitting, and consequent reduction of the structural integrity of the affected MLG.
2013-22-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by reports of airspeed mismatch between the pilot and co-pilot's airspeed indicators, which occurred during or after heavy rain. This AD requires, for certain airplanes, inspecting for drain bottles having certain part numbers, and replacing affected drain bottles. This AD requires, for certain other airplanes, replacing drain bottles. We are issuing this AD to prevent pitot static tubing from becoming blocked by water, which if not corrected, could lead to erroneous airspeed and altitude indications, and consequent loss of control of the airplane.
2013-22-08: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes. This AD was prompted by a report of a cracked pick-up bracket of the forward outboard pylon of the number 1 engine due to stress corrosion. This AD requires repetitive inspections and, depending on findings, repair of the pylon pick-up brackets. We are issuing this AD to detect and correct cracking of the pick-up bracket, which could result in the engine pylon separating from the wing, with consequent damage to the airplane and reduced controllability.
75-16-16: 75-16-16 ISRAEL AIRCRAFT INDUSTRIES, LTD: Amendment 39-2290. Applies to Israel Aircraft Industries Jet Commander Models 1121, 1121A and 1121B, and Westwind Model 1123 airplanes certificated in all categories having autopilot vertical reference component Collins P/N 332D-11/522-3985-001 or Collins P/N 332D-11A/792-6694-001 or both, installed in an unpressurized area. Compliance is required as indicated unless already accomplished. To prevent loss of attitude information and improper operation of the autopilot, accomplish the following: (a) Before further IFR or night flight, install a placard on the instrument panel in full view of the pilot to read, "Cross Check Attitude Indicators with Third Attitude Indicator to Detect Unflagged Failures". (b) Within the next 100 hours' time in service, after the effective date of this AD, modify the vertical reference (Collins P/N 332D-11/522-3985-001, or Collins P/N 332D-11A/ 792-6694-001), in accordance with Collins ServiceBulletin No. 9, dated May 1, l974, or an FAA-approved equivalent. (c) The placard required by paragraph (a) of this AD may be removed when the modification required by paragraph (b) has been accomplished. This amendment becomes effective August 12, 1975.
2000-22-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain International Aero Engines AG (IAE) V2500-A5 and -D5 series turbofan engines, identified by serial number. This amendment requires the removal of engines assembled with an improper High Pressure Turbine (HPT) module configuration from service prior to accumulating 5,100 or 7,600 cycles in the improper configuration, or at the next shop visit, depending on the type of improper HPT configuration, and restoration to type design. This amendment is prompted by reports of engines that do not conform to the engine type design, which could cause a Low Cycle Fatigue (LCF) life reduction of the HPT stage 1 disk. The actions specified by this AD are intended to restore engines to type design configuration and to prevent possible LCF failure of the HPT stage 1 disk, which could result in an uncontained engine failure and damage to the airplane.
2013-20-11: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that oxygen generators installed on a certain batch of passenger emergency oxygen container assemblies might become detached by extreme pulling of the mask tube at the end of the oxygen supply causing a high temperature oxygen generator and mask to fall down. This AD requires modifying the passenger emergency oxygen container assembly. We are issuing this AD to prevent a high temperature oxygen generator and mask from falling down and possibly resulting in an ignition source in the passenger compartment, injury to passengers, and reduced availability of supplemental oxygen.
74-18-01: 74-18-01 MCDONNELL DOUGLAS: Amendment 39-1927 as amended by Amendment 39-2533. Applies to all Douglas Aircraft Company DC-10-10/-30/-40 Series airplanes which incorporate Douglas DC-10 Service Bulletin 21-68 or Service Change 1545 when inertial navigation systems are installed. \n\n\tCompliance required as indicated, unless previously accomplished. \n\n\tWithin 300 additional hours time in service after the effective date of this AD, either \n\n\t(1)\tIncorporate in the FAA-approved Airplane Flight Manual, Documents MDC-J1010, MDC-J1030, MDC-J5830, MDC-J1040, and Appendix X of MDC-J1010, the following revision in Section I, Limitations, under the existing heading 'Cabin Pressurization': \n\n\t'For the inertial platform configured airplanes, temporary installation of wiring per Douglas Drawing WBP 9502 must be accomplished for planned unpressurized flight'; or \n\n\t(2)\tIncorporate other airplane flight manual revisions, and/or equipment modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tAmendment 39-1927 became effective August 26, 1974. \n\n\tThis amendment 39-2533 becomes effective March 8, 1976.