Posts Tagged ‘Agusta AW139’

AD on Fuselage for Agusta AB139 and AW139 Helicopters

Thursday, March 6th, 2014

The FAA is adopting a new airworthiness directive 2014-03-01 (AD) for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters with a certain wire strike protection system (WSPS) top cable cutter assembly installed. This AD requires reworking or replacing the top cable cutter assembly to increase clearance between the WSPS and the main rotor (M/R) blades and requires that the reworked or replaced part be marked at the end of the part number to reflect the field modification. This AD was prompted by a report of in-flight contact between the top cable-cutter assembly and two M/R blades. The actions of this AD are intended to prevent damage to the M/R blades and subsequent loss of helicopter control. DATES: This AD is effective April 7, 2014. pdf icon 2014-03-01.pdf

AD to deactivate Ice Protection on Agusta helicopters

Tuesday, October 1st, 2013

The FAA is adopting a new airworthiness directive 2013-15-01 (AD) for Agusta Model AB139 and AW139 helicopters. This AD requires deactivating the Full Icing Protection System (FIPS) and installing a placard next to the FIPS controller stating that flight into known icing is prohibited. This AD is prompted by a report of a fire in the aft avionics bay and the baggage compartment resulting from an Auto Transformer Rectifier Unit internal circuit overload. These actions are intended to prevent a fire, structural damage, and subsequent loss of control of the helicopter. DATES: This AD becomes effective October 16, 2013. pdf icon 2013-15-01.pdf

Emergency AD on Tail Rotor for Agusta AW139

Sunday, August 28th, 2011

This Emergency Airworthiness Directive (AD) 2011-18-52 is prompted by a fatal accident involving an Agusta Model AW139 helicopter, which may have been caused by cracks in a tail rotor (T/R) blade. This condition, if not detected and corrected, could result in failure of a T/R blade, and subsequent loss of control of the helicopter.

Within 5 hours time-in-service (TIS), establish a life limit of 600 hours TIS or 1,500 takeoff and landing cycles (cycles), whichever occurs first, on the affected T/R blades and update the helicopter’s historical records. If a T/R blade’s total number of cycles is unknown, determine the T/R blade cycles by multiplying the T/R blade’s hours TIS by 4.

For a T/R blade that, on the effective date of this AD, has already exceeded 600 hours TIS or 1,500 cycles, within 5 hours TIS replace the T/R blade with an airworthy T/R blade.

Within 25 hours TIS, and thereafter at intervals not to exceed 25 hours TIS, visually inspect the T/R blade for a crack or damage that exceeds the limits of the applicable maintenance manual. Inspect the T/R blade using a mirror, magnifying glass (5X or greater), and light source; or borescope.

If there is a crack, or if there is damage that exceeds the limits of the applicable maintenance manual, before further flight, replace the T/R blade with an airworthy T/R blade.

pdf icon2011-18-52_emergency.pdf