Results
2012-18-10 R1: We are revising an existing airworthiness directive (AD) for all GA200 (Pty) Ltd Models GA200 and GA200C 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 failure of the wing strut bolt through the main spar. We are issuing this AD to require actions to address the unsafe condition on these products.
2006-01-05: The FAA is adopting a new airworthiness directive (AD) for certain Honeywell International Inc., (formerly AlliedSignal, Inc., formerly Textron Lycoming, formerly Avco Lycoming) T53 turboshaft engines, installed on, but not limited to, Bell 204, Bell 205, Kaman K- 1200 series, Bell AH-1, and Bell UH-1 helicopters, certified under 14 CFR 21.25 or 14 CFR 21.27. This AD requires implementing reduced life limits for certain parts, using cycle counting methods, and using draw- down schedules to replace components that exceed the new limits. This AD results from the manufacturer informing us of test and analysis showing lower calculated service life limits for certain parts, than previously published. We are issuing this AD to prevent failure of certain compressor, gas producer, and power turbine rotating components, which could result in failure of the engine and possible damage to the helicopter.
73-12-04: 73-12-04 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1654. Applies to Viscount Model 810 Series Airplanes, which do not incorporate Modification G.1843. Compliance is required as indicated. To detect loose or sheared rivets on the airsteps hinged fairing operating link, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 475 hours' time in service prior to the effective date of this AD, and thereafter at intervals not to exceed 500 hours' time in service from the last inspection, inspect the 3/16 inch diameter rivets on the airsteps hinged fairing operating link for looseness and shearing. (b) If sheared or loose rivets are found during an inspection required by paragraph (a), before further flight, either - (1) Replace the sheared or loose rivets with serviceable rivets of the same type, that are approved for installation in the assembly, and continue to inspect inaccordance with paragraph (a); or (2) Incorporate Modification G.1843, dated September 22, 1961, or an FAA- approved equivalent. (c) The repetitive inspections required by this AD may be discontinued after Modification G.1843 is incorporated. This amendment becomes effective July 1, 1973.
2012-25-10: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-300 series airplanes and Model A340-200 and -300 series airplanes. This AD was prompted by reports that, during a flight test, several spoiler servo-controls (SSCs) did not remain locked in the retracted position (hydraulic locking function) after manual depressurization of the corresponding hydraulic circuit. Loss of that locking function--which is ensured by a blocking valve--was caused by an internal leak from a sheared seal on the blocking valve. This AD requires inspecting to determine if certain SSCs are installed, performing an operational test of any affected SSC, and replacing if necessary. We are issuing this AD to prevent loss of the hydraulic locking function during take-off and go-around phases, which, in combination with malfunction of one engine, could result in reduced controllability of the airplane.
2012-25-08: We are adopting a new airworthiness directive (AD) for certain serial numbers (S/Ns) of Rolls-Royce plc (RR) RB211-Trent 768-60, 772- 60, and 772B-60 turbofan engines. This AD requires initial and repetitive on-wing or in-shop inspections of the high pressure/ intermediate pressure (HP/IP) turbine bearing support oil feed tube outer heat shield. This AD also requires installation of a revised HP/ IP turbine bearing support structure as terminating action to the repetitive inspections of the HP/IP turbine bearing support oil feed tube outer heat shield. This AD was prompted by a report of high oil consumption due to an oil leak from the HP/IP turbine bearing support oil feed tube. We are issuing this AD to prevent failure of the HP turbine disc, uncontained engine failure, and damage to the airplane.
75-24-14: 75-24-14 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2440. Applies to Alouette Helicopters SE-3130, SE-313B, SA-315B, SE-3160, SA-316B, SA- 316C, SA-3180, SA-318B, SA-318C, and SA-319B equipped with main rotor hydraulic dampers P/N 3130S.13.60.000. Compliance is required as indicated, unless already accomplished. To prevent excessive vibration or ground resonance, accomplish the following: (a) Prior to October 30, 1975, modify and reidentify main rotor hydraulic dampers P/N 3130S.13.60.000 in accordance with subparagraphs 2B(1), 2B(2), and 2(c) of Lama Service Bulletin No. 65.20 dated July 4, 1975, for Model SA-315B and Alouette Service Bulletin No. 65.107 dated July 4, 1975, for the other designated models, or equivalents approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, New York, N.Y. 09667. (b) Prior to further flight, for Models SA-3160, SA-316B, SA-316C, andSA-319B, remove the placard required by AD 75-17-30, if installed, and install a temporary placard on the instrument panel, in full view of the pilot, reading as follows: "Maximum density altitude: 8200 feet". Temporary placard may be removed upon accomplishment of paragraph (a) of this AD. (Alouette Service Bulletin No. 01.39 also refers to paragraph (b) of this AD). This AD supersedes Amendment 39-2335 (40 FR 33010), AD 75-17-30. This amendment is effective upon publication in the FEDERAL REGISTER as to all persons except those persons to whom it was made immediately effective by telegram dated September 30, 1975, which contained this amendment.
2003-09-05: This amendment adopts a new airworthiness directive (AD) for Schweizer Aircraft Corporation (Schweizer) Model 269D helicopters. This action requires inspecting each aluminum horizontal stabilizer endplate (endplate) and the attach angles for cracks, fretting, and endplate bending. If fretting is found, as indicated by a powder residue adjacent to a rivet head, installing an inspection hole in the horizontal stabilizer and inspecting the internal structure is required. Replacing unairworthy parts is required before further flight. Finally, reporting any cracked or bent endplate, any cracked attach angles, or fretting to the FAA is required. This amendment is prompted by reports of loose endplates, and one report of an endplate separating from the helicopter during flight. The actions specified in this AD are intended to prevent loss of an endplate during flight, which could strike the tail rotor and result in loss of control of the helicopter.
2012-25-07: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GIV-X airplanes. This AD requires performing a modified system power-on self test (SPOST) of the flap/stabilizer electronic control unit (FSECU), and revising the airplane flight manual to incorporate these test procedures into the daily preflight check. This AD was prompted by [[Page 74580]] reports indicating that the FSECU does not detect failures of the brake feature within the horizontal stabilizer electric motor unit (HSEMU), or failures of drive solenoids for hydraulic valves within the flap hydraulic control module (FHCM) during the SPOST. We are issuing this AD to detect and correct such failures, which could result in runaway horizontal stabilizer pitch trim system and consequent loss of pitch control.
49-49-01: 49-49-01 LOCKHEED: Applies to All Model 49 Series Aircraft Equipped With Eclipse- Pioneer Model PB-10 Automatic Pilots. Compliance required prior to reconnection in aircraft. Prior to reconnection in the aircraft of the Eclipse-Pioneer Model PB-10 automatic pilot, it is necessary to modify the installation to include provisions designed to safeguard the aircraft in the event of malfunctioning of the autopilot. This modification has been determined to consist of the following interdependent changes: Modify the master direction indicator and wiring at the autopilot controller plug and amplifier to change the direction signal from the rudder channel to the aileron channel; install resistors in series with the variable phase of aileron, rudder and elevator servo motors to reduce servo forces; install aileron servo disconnect interlock switch and change wiring to this switch from the existing rudder servo disconnect interlock switch. An acceptable method of accomplishingthis modification is described in LAC Service Bulletin No. 49/SB-576. This supersedes AD 49-36-01.
2012-21-52: We are publishing a new airworthiness directive (AD) for Agusta Model AW139 helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting the pilot's and co-pilot's collective and cyclic control sticks for correctly installed attaching hardware. This AD is prompted by a report of an incorrectly installed pilot's collective stick, pilot's cyclic stick, and co-pilot's cyclic stick. These actions are intended to prevent detachment of the cyclic or collective control stick, and subsequent loss of control of the helicopter.