The P92-JS and P92 ECHO Super are two-seater side
by side, single strut braced, high wing aircraft. The plane's
outstanding performance and flying qualities together with low
operating cost, easy piloting and maintenance, make these
aircraft an excellent solution for flying school and training
activity, and also for many other missions, such as touring,
property inspection, surveillance patrols, etc.
Long experience in this field has allowed Tecnam to create a
simple and light structure, easy to inspect and repair, by using
many original design solutions, manufacturing methods and
tooling.
The wing structure consists of a single spar metal torsion box
with an easily detachable leading edge of conventional metal
structure.
An integral fuel tank is located in the leading edge section
of each half wing, distant from the cabin.
The leading edge tapering
near the wing root improves visibility, also in a steep turn.
A rear window completes the 360-degree vision.
The cabin, which features extra large doors, is 45" wide. This,
combined with all surrounding windows, makes the aeroplane seem
very roomy. A large luggage area is placed behind the seats.
The dual control
sticks come up forward, between pilot's leg, in the conventional
manner.
The dual rudder pedals, of conventional type, also control the
nose wheel steering.
The all-moving tailplane provides remarkable longitudinal
hands-off stability and control with a minimum drag and weight
penalty.
A wide control trim-tab also accomplishes the anti-tab function.
The fin has a cantilever
structure of light alloy, except for a glass fibre tip. Fin and
rudder have ribbed light alloy skins.
A push-button switch, on the stick grip, controls the pitch
trim. The position indicator is on the instrument panel.
The wide slotted flaps, electrically activated, allow stall
speeds under 38 kts.
With flaps deployed, a steep approach is possible: a very short
flare and roll out will result.
The ailerons are very effective, allowing an aggressive roll
rate.
The flaps and aileron are made of light alloy structure.
The wide
instrument panel is designed to accommodate standard and
optional instrument configuration up to full IFR.
The fast opening cowling allow complete and easy access to the
engine and equipment.
The engine is set low and the cowling slopes down from the
windshield, so forward visibility is excellent.
The engine is connected to the airframe through a Cr-Mo
steel-tube engine mount and by vibration isolating suspension.
The firewall is soundproofed.
One 73 kW (100hp) Rotax 912S
four cylinder four-stroke liquid/air cooled engine, integrated
reduction gear (1:2.415) driving two-blade wooden propeller
(Hoffman HO17GHM-174 177C) is installed.
Independent fuel valves are located on each side of the cockpit.
The gascolator is installed in the engine bay. A back-up
electrical pump engages if the mechanical fuel pump
malfunctions.
Engine is equipped with a 21A 14V generator, 18 Ah battery. All
the circuits are breaker protected.
The steel leaf
main gear legs provide excellent shock absorption, are trouble
free and require no maintenance.
The levered suspension nose gear with rubber shock absorber has
been designed to resist high impact loading in basic training
use.
Wheel and hydraulic disc brakes are of standard aircraft type
(5.00x5)
The brake lever control is located forward between the seats. An
hydraulic valve provides the parking brake control.
specifications
powerplant
propeller
length
height
wing span
wing area
seats
empty weight
useful load
gross weight
fuel capacity
range |
Rotax 912S
Hoffman HO17GHM-174 177C
6,4 m
2,5 m
8,7 m
12 msq
2
281 Kg
x
450 Kg
70 Lt.
800 Km |
performance
takeoff
distance, ground roll
rate of climb
max speed
cruise speed
landing distance, ground roll
service ceiling |
140 m
5,9 m/s
235 Km/h
210 Km/h
100 m
x |
limiting and recommended speeds
design
manoeuvring speed (Va)
never exceed speed (Vne)
stall, power off (Vsl)
landing approach speed |
x
270 Km/h
63 Km/h
x |
All specifications are based on
manufacturer's calculations
|
