Piper PA-34-200T I-CNTL

The Piper PA-34 Seneca is an American twin-engined light aircraft, produced by Piper Aircraft since 1971 and still in production in 2009. The Seneca is primarily used for personal and business flying. The Seneca was developed as a twin-engine version of the Piper Cherokee Six. The prototype was a Cherokee Six that had wing-mounted engines installed, retaining its nose engine. The prototype was flown as a tri-motor aircraft in the initial stages of the test-flying programme, that ended with the development of a beautiful twin engine called SENECA. Today Piper, after 5 versions is selling the last version SENECA V, that looks after the other versions, but has full glass cockpit avionics and much more horse power than the oldest brothers.

PA-34-200T Seneca II - Responding to complaints about the aircraft's handling qualities, Piper introduced the PA-34-200T Seneca II. The aircraft was certified on July 18, 1974 and introduced as a 1975 model. The new model incorporated changes to the aircraft's control surfaces, including enlarged and balanced ailerons, the addition of a rudder anti-servo tab, and a stabilator bobweight. The "T" in the new model designation reflected a change to turbocharged, six cylinder Continental TSIO-360E or EB engines for improved performance, particularly at higher altitudes.

The Seneca II retained the counter-rotating engine arrangement of the earlier Seneca I. The Seneca II also introduced optional "club seating" whereby the two center-row seats face rearwards and the two back seats face forward allowing more legroom in the passenger cabin. A total of 2,588 Seneca IIs were built. Gross weights are 4,570 lb (2,070 kg) for takeoff and 4,342 lb (1,969 kg) for landing, with all weight in excess of 4,000 lb (1,800 kg) required to be fuel.

I-CNTL is a Seneca II very well equipped and maintained. It is equipped with the Robertson STOL kit (Full wing length flaps with Spoilers & Elec. Flaps); this modification permits a better Take off and landing performance with the addition of a lower Vmca.
I-CNTL is used by CANTOR AIR ATO for the final part of the IR and CPL training.

Specifications (Reference: Data from Piper Seneca II Information Manual)

General characteristics
Crew: One
Capacity: Five passengers
Length: 28 ft 7.44 in (8.72 m)
Wingspan: 38 ft 10.87 in (11.86 m)
Height: 9 ft 10.8 in (3.02 m)
Wing area: 208.7 ft² (19.39 m²)
Airfoil: laminar flow NACA 652-415
Empty weight: 3212 lb (1457 kg)
Loaded weight: 4773 lb (2165 kg)
Useful load: 993 lb (450 kg)
Max takeoff weight: 4750 lb (2155 kg)
Powerplant: 2× Continental TSIO-360RB and LTSIO-360RB 6-cylinder, air-cooled, horizontally-opposed piston engine, 220 hp (164 kW) each

Performance
Never exceed speed: 204 knots (378 km/h, 235 mph)
Maximum speed: 204 knots (378 km/h, 235 mph) at 23,000 ft (7,000 m)
Cruise speed: 188 knots (348 km/h, 216 mph) econ cruise at 25,000 ft (7,600 m)
Stall speed: 61 knots (113 km/h, 70 mph) wheels and flaps down
Range: 870 nmi (1611 km, 1000 mi) max fuel, econ cruise at 18,000 ft (5,500 m), no reserves
Service ceiling: 25,000 ft (7,620 m)
Rate of climb: 1550 ft/min (7.87 m/s)
Wing loading: 21.2 lb/ft² (104 kg/m²)
Power/mass: 0.1 hp/lb (164 W/kg)

Equipment
GARMIN 340 Audio Panel
COM/NAV/GPS 1 Garmin GNS430
COM/NAV/GPS 2 Garmin GNS430
XPDR 1 Garmin GTX 330 Mode S
Collins DME
Bendix King ADF KR87
EFIS ASPEN 1000 PBN CERTIFIED
Autopilot Altimatica IIIC
Weather Radar Bendix
Copilot Instruments
Full Deice
4 places Intercom (active)
Long Range Tank (125 Gal. usable Fuel)