Results
2001-01-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 10 and Model Mystere-Falcon 50 series airplanes. For certain airplanes, this amendment requires modification of the aircraft wiring to illuminate the "T/O CONFIG" red warning light on the cockpit warning panel. For certain other airplanes, this amendment requires installation of a "NO TAKEOFF" red light on each pilot's instrument panel; modification of the associated aircraft wiring to activate the lights whenever the aircraft is not in the proper configuration for takeoff; and a revision to the Airplane Flight Manual to check that the "NO TAKEOFF" lights are out prior to takeoff. 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 takeoff with the parking brake engaged, which could result in an extended takeoff roll or a rejected takeoff, and consequent runway overrun.
2007-11-19: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Installation of G-load monitoring units on some Zlin Z 42 series airplanes has revealed that certain aircraft during aerobatic manoeuvres exceeded the limit loads initially defined for the certification. As a consequence to restore the safety margins on aircraft operated in Utility ("U'') category; this Airworthiness Directive (AD) mandates a modification of the Airplane Flight Manual (AFM) so as to limit the permissible manoeuvres in "U'' category flights. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
68-07-04: 68-07-04 PIPER AIRCRAFT: Amdt. 39-576 as amended by Amendment 39-1324 is further amended by Amendment 39-1426. Applies to Piper PA-23-250 airplanes Serial Nos. 27- 2505 and up having engine mount part number 31215. Compliance required as indicated. a. With airplanes having engine mount date stamped prior to 26 May 1965, within the next 50 hours in service after the effective date of this AD unless already accomplished within the last 50 hours in service and thereafter at intervals not to exceed 100 hours in service from the last inspection visually inspect the mount for cracks in the following areas: (i) The lower forward lateral tube (ii) The three-tube horizontal diagonal truss in and around the three welded junctures with the lower forward lateral fore and aft tube, and (iii) The lower left horizontal fore and aft tube. b. With airplanes having engine mounts date stamped 26 May 1965 and after, and having 1000 or more hours in service, within the next 50 hours in service after the effective date of this AD, unless already accomplished within the last 50 hours in service, and thereafter at intervals not to exceed 100 hours in service from the last inspection visually inspect the engine mount tubes forward of the firewall for cracks. c. If cracks are found accomplish either of the following, (i) Replace the engine mount prior to further flight with a new mount part number 31215. After installation of new mount continue repetitive inspection of this mount after 1000 hours as described in paragraph b. (ii) Repair the engine mount prior to further flight in accordance with FAR 43. Conduct a magnetic particle, or equivalent method, inspection of the entire mount for cracks prior to approval of the repaired engine mount. Continue visual inspections of the mount within 100 hours in service and thereafter not to exceed 100 hours in service from the last inspection. NOTE: On engine mounts date-stamped prior to 26 May 1965, a pictorial description of the affected areas can be found in Piper Service Letter No. 462. The engine mount is date- stamped on either of the two diamond-shaped gusset plates located near the upper firewall attachment points. Amendment 39-576 was effective April 11, 1968. Amendment 39-1324 was effective November 2, 1971. This Amendment 39-1426 is effective April 11, 1972.
2007-11-14: 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: It has been found that both fuel level control units (LCU) and their associated harnesses throughout the aircraft does not comply with the requirements of proper segregation, in order to preclude a possible ignition source in the vicinity of the fuel tanks, as required by SFAR (Special Federal Aviation Regulation) 88 regulations. We are issuing this AD to require actions to correct the unsafe condition on these products.
2007-11-16: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model MD-11 and MD-11F airplanes. This AD requires installing bracket assemblies and jumper wires in the center main wheel well to improve the bonding path between the structure (wall) of the lower auxiliary fuel tank and its internal fuel pumps; measuring the electrical resistance between the fuel pump housings and the fuel tank structure; and doing corrective actions if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to detect and correct an inadequate bond between the internal fuel pump housings and the structure of the lower auxiliary fuel tank. This condition, if not corrected, could fail to meet fault current requirements and result in a potential ignition source that, in combination with flammable fuel vapors, could cause a fuel tank explosion and consequent loss of the airplane.
2018-03-06: We are superseding Airworthiness Directive (AD) 2015-02-18, which applied to all Airbus Model A330-201, -202, -203, -301, -302, and -303 airplanes. AD 2015-02-18 required a one-time ultrasonic inspection for fractures of all aft mount-pylon bolts of each engine. This new AD was prompted by the failure of a bolt on the aft engine mount upper beam, which was found to be caused by inappropriate in-production upper beam installation. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. We are issuing this AD to address the unsafe condition on these products.
2001-01-08: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires inspection for cracking of the mounting brackets of the hydraulic hand pump at the frame attachment flanges, replacement of any cracked bracket with a new bracket, replacement of all bolts and nuts with new bolts and nuts, and installation of a particular `D' packer. The actions specified by this AD are intended to prevent failure of these brackets, which could result in inability to extend the landing gear in an emergency situation where the main hydraulic system is lost. This action is intended to address the identified unsafe condition.
63-26-03: 63-26-03 PIPER: Amdt. 663 Part 507 Federal Register December 24, 1963 as amended by Amendment 39-1240. Applies to Piper Models PA-23 and PA-23-160 Aircraft, Serial Numbers 23-1 through 23-1267, inclusive. Compliance required as indicated: (a) Within the next 50 hours in service after the effective date of this AD, unless already accomplished within the last 50 hours in service, and thereafter at intervals not to exceed 100 hours in service from the last inspection, visually inspect for cracks each of the castings listed herein. When any casting is replaced by the respective forging listed herein, the repetitive inspections of this paragraph and paragraph (b) are no longer required for that forging. NAME CASTING PART NO. FORGING Elevator Torque Tube Bracket 17033-00 and 17033-01 19407-00 Front Stabilizer Attachment 17049-00 and 19253-00 19409-02 Rudder Torque Tube Horn 17060-00 19405-00 Elevator Torque Tube Horn 17066-00 19404-00 RudderTorque Tube Bracket 17062-00 19408-00 Fin Attachment Bracket 17072-00 19406-00 or 19406-02 (b) For airplanes having 1,000 or more hours in service, remove the subject castings from the aircraft, clean thoroughly removing all paint, and perform a dye penetrant inspection for cracks, within the next 100 hours in service after the effective date of this AD, unless already accomplished within the last 400 hours in service, and thereafter at intervals not to exceed 500 hours in service from the last inspection. Prior to reinstallation of castings without cracks, clean thoroughly, and apply zinc chromate primer. (c) Replace cracked castings before further flight with a replacement forged or cast part. (d) Inspection and reassembly shall be accomplished in accordance with Piper Service Bulletin No. 155B, dated October 28, 1963, or FAA-approved equivalent. NOTE: For paragraph (a), it is necessary to remove the tail cone, covers, and fairings to gain access to most of the parts to be inspected. However, parts need not be disassembled and/or removed from the aircraft to accomplish this inspection. All of the forged parts listed herein have integral raised digit forging numbers. Therefore, the absence of raised digits will serve to identify the part as a casting. AD 63-26-03 Amendment 663 supersedes AD 57-13-09. Amendment 663 was effective December 24, 1963. Revised on April 26, 1966 and December 16, 1966. This Amendment 39-1240 is effective July 13, 1971.
2007-11-10: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires a detailed inspection for wear of the attachment holes of the control levers of the braking system and applicable corrective actions. This AD results from a report that, after landing, the flightcrew of a Model F.28 Mark 0100 airplane noted that an extreme difference in pedal angle was required to achieve equal braking action. We are issuing this AD to prevent failure of one or more brake control levers, which could result in uncommanded braking and loss of control of the airplane during takeoff, landing, or taxiing.
2007-11-01: This amendment adopts a new airworthiness directive (AD) for Robinson Helicopter Company (Robinson) Model R44 and R44 II helicopters that have a certain seat belt buckle (buckle) assembly installed, that requires removing the buckle assembly and the buckle assembly spacer, and replacing them with airworthy parts. This amendment is prompted by an accident in which a seat belt failed, and also by reports of cracking in the buckle assembly stainless support strap (support strap). The actions specified by this AD are intended to prevent cracking in the support strap and failure of a seat belt.