Results
2007-02-22: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A310 airplanes. This AD requires doing repetitive inspections for any missing, damaged, or incorrectly installed wiper rings in the splined couplings of the flap transmission shafts; inspections for any missing, damaged, or incorrectly installed rubber gaiters and straps on the sliding bearing/plunging joints of the flap transmission; and corrective action if necessary. This AD results from reviews in which the manufacturer determined that the splined couplings and sliding bearings of the flap transmission system could be affected by corrosion and wear. We are issuing this AD to detect and correct damaged, missing, or incorrectly installed components of the flap transmission system, which could result in reduced functional integrity of the flap transmission system and consequent reduced control of the airplane.
2014-06-51: We are publishing a new airworthiness directive (AD) for Airbus Helicopters Model MBB-BK 117 A-3, MBB-BK 117 A-4, MBB-BK 117 B- 1, and MBB-BK 117 C-2 helicopters with a certain Metro Aviation, Inc. (Metro), vapor-cycle air conditioning kit pulley (pulley) installed, which was sent previously to all known U.S. owners and operators of these helicopters. This AD supersedes AD 2013-12-06, which required inspecting the pulley for looseness and properly installed lockwire and re-installing the pulley. Since we issued AD 2013-12-06, we received a report of a possible design and manufacturing deficiency in some pulleys wherein they did not have sufficient thread depth, allowing the pulley to detach from the rotor brake disc. This AD requires inspecting each pulley attaching bolt hole to determine if there is sufficient depth of the threads and either removing the pulley if the depth is insufficient or installing dual locking tabs under each pulley attaching bolt if the depth is sufficient. These actions are intended to prevent the pulley from detaching, resulting in damage to the tail rotor (T/R) driveshaft, and subsequent loss of control of the helicopter.
70-07-05: 70-07-05 BRITTEN-NORMAN, LTD: Amdt. 39-965. Applies to Models BN-2 and BN-2A airplanes. To prevent possible engine fires due to accumulation of fuel in the rear of the carburetor air box and hot air ducting, within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, install drain holes in each carburetor air box and in each engine cowling in accordance with Britten-Norman Service Bulletin No. BN-2/SB.28, dated February 12, 1970, or later ARB-approved issue, or an FAA-approved equivalent. This amendment becomes effective March 31, 1970.
2006-12-16: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 airplanes. This AD requires certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 airplanes. This AD results from a report that, during structural testing of the cockpit door, the lower hinge block rotated and caused the mating hinge pin to disengage, and caused excessive door deflection. We are issuing this AD to prevent failure of a door attachment, which could result in uncontrolled release of the cockpit door under certain fuselage decompression conditions, and possible damage to the airplane structure.
2018-07-20: We are superseding Airworthiness Directive (AD) 2014-03-07, which applied to certain The Boeing Company Model MD-11 and MD-11F airplanes. AD 2014-03-07 required inspecting certain locations of the wire bundles of the center upper auxiliary fuel tank for damage, and corrective action if necessary. AD 2014-03-07 also required installing nonmetallic barrier/shield sleeving, new clamps, new attaching hardware, and a new extruded channel. This AD adds certain inspections and expands the applicability. This AD was prompted by the determination that it is necessary to require an inspection of the wire bundles for damage at certain center upper auxiliary fuel tank locations on certain airplanes. We are issuing this AD to address the unsafe condition on these products.
2014-13-18: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-102, -103, and -106 airplanes; and DHC-8- 200 and DHC-8-300 series airplanes. This AD was prompted by a report of a beta warning horn (BWH) system failing to activate when the beta mode was triggered. This AD requires modifying the BWH microswitch installation. We are issuing this AD to prevent the inadvertent activation of ground beta mode during flight, which could lead to engine overspeed, engine damage or failure, and consequent reduced controllability of the airplane.
2008-23-05: 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: Investigations performed following a report about a fuel leakage in a Stemme S10-V powered-sailplane revealed that some fuel lines fabricated between March 2008 and May 2008, after the introduction of a new pressing tool, present a manufacturing defect which could lead to the puncture of the fuel lines. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
75-17-19: 75-17-19 SIAI-MARCHETTI: Amendment 39-2321. Applies to SIAI Marchetti F.260 airplanes, Serial Numbers 101 thru 125; 2-26 thru 2-57; 2-59 thru 2-61; 3-76 thru 3-81 and 502, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent possible failure of the landing gear, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection, until replaced in accordance with paragraph (b) or (c) of this AD, inspect the landing gear actuator brackets, P/N 260-05-1413 and -14, or P/N 260-05-14-25 and -26, installed on Bulkhead No. 5, for cracks in accordance with paragraph (a) of SIAI Marchetti Service Bulletin No. 260B13, dated March 10, 1975, or an FAA-approved equivalent. (b) If cracks are found during an inspection required by paragraph (a) of this AD, before further flight, replace the brackets with new brackets, P/N 260-05-201-03, in accordance with paragraph (b) of SIAI Marchetti Service Bulletin No. 260B13, dated March 10, 1975, or an FAA-approved equivalent. (c) If no cracks are found during an inspection required by paragraph (a) of this AD, within the next 500 hours' time in service after the effective date of this AD, replace the brackets with new brackets, P/N 260-05-201-03, in accordance with paragraph 9b) of SIAI Marchetti Service Bulletin No. 260B13, dated March 10, 1975, or an FAA-approved equivalent. This amendment becomes effective August 19, 1975.
2013-22-23 R1: We are rescinding Airworthiness Directive (AD) 2013-22-23 for AERMACCHI S.p.A. Models F.260, F.260B, F.260C, F.260D, F.260E, F.260F, S.208, and S.208A airplanes equipped with a Lycoming O-540, IO-540, or AEIO-540 (depending on the airplane model) wide cylinder flange engine with a front crankcase mounted propeller governor. AD 2013-22-23 resulted 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. We issued the AD to detect and [[Page 39960]] correct improper position of the set screw, which could lead to complete loss of engine oil pressure and result in emergency landing. Since we issued AD 2013-22-23, we have determined the unsafe condition does not exist specific to the airplane design features.
2006-09-10: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) Model SA-365 N1, AS-365 N2, N3, SA 366 G1, and EC-155B and B1 helicopters. This action requires a one-time inspection for end play in the pitch control rod assembly double bearing (bearing) using the tail rotor (T/R) hub control plate, and before further flight, replacing the bearing if end play is present. This amendment is prompted by one incident in which a pilot lost T/R pitch control of a helicopter while landing. The actions specified in this AD are intended to detect damage to the bearing, resulting in end play and prevent loss of T/R pitch control and subsequent loss of control of the helicopter.