Results
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.
2014-13-05: We are superseding Airworthiness Directive (AD) 2007-10-16 for all British Aerospace Regional Aircraft Jetstream Model 3201 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 the need to incorporate revisions to the Airworthiness Limitations section of the Instructions for Continued Airworthiness. We are issuing this AD to require actions to address the unsafe condition on these products.
2014-11-05: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corp. (P&WC) turboprop engines. This AD requires installing a reinforcement liner to the power turbine (PT) containment ring and, for certain PT containment rings, adding scallops. This AD was prompted by in-service events involving the perforation of engine cases as a result of the liberation of PT blades and the fracture/ displacement of the PT containment ring. We are issuing this AD to prevent uncontained engine failure and damage to the airplane.
2005-23-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness of the Canadair Regional Jet Maintenance Requirements Manual by incorporating new procedures for repetitive detailed and special detailed inspections for cracking of the aft pressure bulkhead. This AD results from a fatigue test, which revealed cracking of the aft pressure bulkhead; subsequent in-service reports show that fatigue cracking has been found on other airplanes. We are issuing this AD to detect and correct cracking in the aft pressure bulkhead, which could result in reduced structural integrity and rapid decompression of the airplane.
2014-12-02: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. This AD was prompted by a determination that new center of gravity (CG) limits are applicable during takeoff with certain conditions. This AD requires revising the airplane flight manual (AFM) to include procedures to advise the flightcrew of the new CG limits. We are issuing this AD to prevent an erratic takeoff path and consequent reduced controllability of the airplane.
2014-10-02: We are superseding airworthiness directive (AD) 2006-11-19 for Dornier Luftfahrt GmbH Model Dornier 228-100, 228-101, 228-200, 228- 201, 228-202, and 228-212 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 chafed or damaged wiring on the flight deck overhead panels (5VE and 6VE). We are issuing this AD to require actions to address the unsafe condition on these products.
70-03-06: 70-03-06 BRITTEN-NORMAN, LTD: Amdt. 39-934. Applies to Britten-Norman Models BN-2 and BN-2A airplanes. Compliance is required as indicated. To prevent failure of the rudder bar assembly due to failure of the silver solder joint attaching the bronze bushing to the inboard end of the rudder bar beams, accomplish the following: (a) Within the next 20 hours' time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 20 hours' time in service since the last inspection, visually inspect the silver solder joint attaching the bronze bushing to the inboard end of each rudder bar beam (P/N NB-45-3-071) for failure in accordance with Britten-Norman Service Bulletin No. BN-2/SB.20, Issue 2, dated 17 November 1969, or an FAA-approved equivalent. (b) If during the inspections required by paragraph (a), a rudder bar beam is found that has failed - (1) Rework the failed rudder bar beam by removing the bronze bushingand welding in a steel bushing in accordance with Britten-Norman Service Bulletin No. BN-2/SB.20, Issue 2, dated 17 November 1969, or an FAA-approved equivalent; or (2) Replace the failed rudder bar beam with a serviceable beam which has had incorporated Britten-Norman Modification NB/M/341, Part A (left hand assembly), or NB/M/341, Part B (right hand assembly). (c) The repetitive inspections required by paragraph (a) may be discontinued on each rudder bar beam which has been reworked or replaced in accordance with paragraph (b). This amendment becomes effective February 5, 1970.