Y12F is an aircraft with high-wing, single vertical fin, a retractable tricycle landing gear and 2 PT6A-65B turboprop engines of Pratt & Whitney. Each engine is fitted with a low-noise, 5-blades metallic propeller HC-B5MP-3D/M10876ANSK of HARTZELL.
It is a reliable, economic and comfort aircraft designed to the latest airworthiness regulations and by adopting advanced aeronautical technologies, which is with high safety, payload and maintainability. The aircraft has a glass cockpit and the instrument panel incorporates 4 multifunction displays, standby instruments, warning lights and signal panel etc.
The aircraft has 2 pilot seats, with a navigator seat as option. It can carry maximum 19 passengers for passenger transportation application or 3 standard LD3 containers for cargo transportation.
TYPE CERTIFICATE ISSUED BY CAAC
TYPE CERTIFICATE ISSUED BY FAA
TYPE CERTIFICATE ISSUED BY CAA
| Type | Y12F | |
| Engine | Manufacturer | Pratt & Whitney Canada |
| Type |
PT6A-135A |
|
| Takeoff/Max. continuous power (SHP) | 750 | |
| Operation limit power (SHP) | 620 | |
| Qty. (set) | 2 | |
| Propeller | Manufacturer | HARTZEL, USA |
| Type | HC-D4N-3N/D9511FK | |
| Qty. (set) | 2 | |
| Np limit (RPM) | 1900 | |
| Qty. of blade (pc) | 4 | |
Y12 series aircraft are equipped with engine air intake anti-icing system and propeller electric de-icing system.
| Overall length (m) | 16.47 |
| Overall Height (m) | 6.035 |
| Wing span (m) | 19.888 |
| Wheel base (m) | 5.75 |
| Tread (m) | 3.2 |
| Cabin length (m) | 7.1 |
| Cabin width (m) | 1.9 |
| Cabin height (m) | 1.84 |
|
Cabin door (height by width) (m) |
2.32 х 1.74 |
| Cabin capacity (LxWxH, m3) | 7.1 x 1.9 x 1.84 |
| Max. height fuselage (m) | 2.2 |
| Max. width fuselage (m) | 2.1 |
| Max. takeoff weight (kg) | 8400 |
| Max. landing weight (kg) | 8000 |
| Max. payload (kg) | 3000 |
| Fuel weight (kg) | 2500 |
| Max. passenger | 19 |
| Max. cruising speed (kmph) | 358 |
| Long-range cruise speed (kmph) | 390 |
|
Max. speed of level flight |
430 |
| Cruising altitude (m) | 3000 |
| Service ceiling OEI (m) | 4600 |
| Takeoff distance (m) | 720 |
| Landing distance (m) | 420 |
All structure in metal except;
Nose dome, front luggage compartment door, electronic equipment compartment door, pilot door, passenger door, cargo door, rear luggage compartment door and tail cover are in composite;
Empennage includes trapezium shape single vertical fin and horizontal stabilizers, in twin-beam box type structure;
Elevator, rudder and ailerons are composite molded parts.
2 PT6A-65B turboprop engines of P&W;
Recommended fuel: Jet A, Jet A-1, JP5 and RP-3 (Chinese);
Take-off power: 1000 SHP;
Max. continuous power: 1000 SHP;
Max. climb/cruise power: 1000 SHP;
Engine oil as required by SB 13001 of P&W.
Engine adaptive propeller HC-B5MP-3D/M10876ANSK of HARTZELL :
Low noise
5 metallic blades
Steel hub
Auto-feathering;
Propeller dia.: 2824 mm (111.2 in.);
Max. rotation speed: (100%NP) 1700 rpm.
Cockpitr
Cockpit located between frames 5 and 11 Pilot door on the LH
An emergency window on the RH
Pilot seats are adjustable forward and backward, up and down
Passenger cabin
Cabin size:
Length: 7.30m (24.0ft) Width: 1.90m (6.2ft)
Height: 1.80m (5.9ft) (aisle area)
Load-bearing capacity: 50kg/m2 (10667 PSI)
Avionics
The communication and navigation system mainly consists of:
HF communication system, audio control system (including beacon receiver), multi-function radio set, CVR, radio altimeter, color weather radar, transponder, collision avoidance system, GPS, terrain avoidance and warning system, emergency locator transmitter , etc.
Avionics, based on the advanced APEX system of HONEYWELL, eases working processes for pilots
Fuel system
Two independent fuel supply systems feed left and right engines respectively. Two integral fuel tanks are in the wings
with the max. usable fuel capacity of 2500 kg.
Each tank has two booster pumps (primary fuel pump and emergency fuel pump).
A fuel cut off valve is provided for each fuel supply pipeline.
A cross feed valve is fitted between the two fuel supply systems.
Each integral fuel tank is designed with two normal ventilation pipelines and one emergency ventilation pipeline.
Hydraulic system
Dual redundancy hydraulic systems are adopted (primary and emergency).
The primary hydraulic system supplies power for extending and retracting the landing gears, for nose steering and the anti-skid brake (optional);
The primary hydraulic system supplies power for extending and retracting the landing gears, for nose steering and the anti-skid brake (optional);
Hydraulic system operating pressure: 14MPa
Anti-icing and De-icing system
The system includes: Ice detection system;
Pneumatic de-icing system of wing and empennage (optional);
Electrical anti-icing devices for windshield wiper, windshield and propeller blades;
Engine air inlet inertia deflector
Ram air ventilation system is used for both cockpit and cabin to get fresh air. Adjustable air vent nozzle is available above each pilot seat and passenger seat.
PASSENGER/CARGO TRANSPORTATION MARITIME SURVEILLANCE AIR DROPPING / PARACHUTE JUMPING GEOLOGICAL EXPLORATION
AEROPHOTOGRAPH OFFSHORE PATROL RAIN MAKING TOURISM
AMBULANCE TRAINING VIP
Your request has been accepted.
Information with the application has been sent to you on the mail
In the near future our managers will contact you for details.
