Miloch
March 30th 20, 03:27 PM
https://en.wikipedia.org/wiki/Harbin_Y-12
The Harbin Y-12 is a high wing twin-engine turboprop utility aircraft built by
Harbin Aircraft Industry Group (HAIG).
The Y-12 started as a development of the Harbin Y-11 airframe called Y-11T in
1980. The design featured numerous improvements including a redesigned wing with
a new low drag section, a larger fuselage and bonded rather than riveted
construction.
The first prototype, followed by about 30 production Y-12 (I) aircraft before a
revised version was produced. This was designated the Y-12 (II), which featured
more powerful engines and removal of leading edge slats, first flying on 16
August 1984 and receiving Chinese certification in December of the following
year. The power plants are two Pratt & Whitney Canada PT6A-27 turboprops with
Hartzell propellers. The Y-12 has a maximum takeoff weight of 5,700 kg (12,600
lb) with seating for 17 passengers and two crew. The aircraft is operated as a
light commuter and transport aircraft.
The latest development is Y-12F, which is almost a new design with many
improvements: new wings, new landing gears, new fuselage, with more powerful
engines from Pratt & Whitney Canada and extended payload and range. The Y-12F
made its maiden flight on December 29, 2010, received the CAAC type
certification on December 10, 2015, and the FAA type certification on February
22, 2016. In 2015 Kenmore Air announced that they would begin development of
floats for the Y-12 for FAA certification. The Y-12 completed the FAA
evaluation flight tests for its automatic flight control system on June 30,
2018, with its performance meeting the requirements, said AVIC Harbin Aircraft
Industry Company Ltd (AVIC HAFEI).
Role
Twin-engine turboprop utility aircraft
National origin
China
Manufacturer
Harbin Aircraft Industry Group
First flight
14 July 1982
Status
Active, In production
Primary user
People's Liberation Army Air Force
Produced
1985 - present
Unit cost
US$3 million (1998)
Developed from
Harbin Y-11
Specifications (Y-12 (II))
General characteristics
Crew: 2
Capacity: 17 pax / 1,700 kg (3,748 lb) max payload
Length: 14.86 m (48 ft 9 in)
Wingspan: 17.235 m (56 ft 7 in)
Height: 5.575 m (18 ft 3 in)
Wing area: 34.27 m2 (368.9 sq ft)
Airfoil: LS(1)-0417
Empty weight: 2,840 kg (6,261 lb)
Max takeoff weight: 5,300 kg (11,684 lb)
Fuel capacity: 1,616 l (427 US gal; 355 imp gal) / 1,230 kg (2,712 lb) max
usable fuel weight
Powerplant: 2 × Pratt & Whitney Canada PT6A-27 turboprop engines, 462 kW (620
hp) each
Propellers: 3-bladed Hartzell HC-B3TN-3B/T10173B-3, 2.49 m (8 ft 2 in) diameter
constant-speed fully-feathering reversible-pitch propellers (4 and 5 bladed
propellers used on some models)
Performance
Maximum speed: 328 km/h (204 mph, 177 kn) VMO (maximum operating speed) at 3,000
m (9,843 ft)
Cruise speed: 292 km/h (181 mph, 158 kn) (max) at 3,000 m (9,843 ft)
250 km/h (160 mph; 130 kn) (economical) at 3,000 m (9,843 ft)Range: 1,340 km
(830 mi, 720 nmi) at econ cruise, 45 min reserves at 3,000 m (9,843 ft)
Endurance: 5 hours 12 minutes at econ cruise
Service ceiling: 7,000 m (23,000 ft)
3,000 m (9,843 ft) on one engineRate of climb: 8.1 m/s (1,590 ft/min)
1.4 m/s (4.6 ft/s) on one engineWing loading: 145.9 kg/m2 (29.9 lb/sq ft)
Power/mass: 0.106 kW/kg (0.064 hp/lb)
Take-off run: 370 m (1,214 ft)
Take-off run to 15 m (49 ft): 490 m (1,608 ft)
Landing run: 340 m (1,115 ft)
Landing run from 15 m (49 ft): 630 m (2,067 ft)
*
The Harbin Y-12 is a high wing twin-engine turboprop utility aircraft built by
Harbin Aircraft Industry Group (HAIG).
The Y-12 started as a development of the Harbin Y-11 airframe called Y-11T in
1980. The design featured numerous improvements including a redesigned wing with
a new low drag section, a larger fuselage and bonded rather than riveted
construction.
The first prototype, followed by about 30 production Y-12 (I) aircraft before a
revised version was produced. This was designated the Y-12 (II), which featured
more powerful engines and removal of leading edge slats, first flying on 16
August 1984 and receiving Chinese certification in December of the following
year. The power plants are two Pratt & Whitney Canada PT6A-27 turboprops with
Hartzell propellers. The Y-12 has a maximum takeoff weight of 5,700 kg (12,600
lb) with seating for 17 passengers and two crew. The aircraft is operated as a
light commuter and transport aircraft.
The latest development is Y-12F, which is almost a new design with many
improvements: new wings, new landing gears, new fuselage, with more powerful
engines from Pratt & Whitney Canada and extended payload and range. The Y-12F
made its maiden flight on December 29, 2010, received the CAAC type
certification on December 10, 2015, and the FAA type certification on February
22, 2016. In 2015 Kenmore Air announced that they would begin development of
floats for the Y-12 for FAA certification. The Y-12 completed the FAA
evaluation flight tests for its automatic flight control system on June 30,
2018, with its performance meeting the requirements, said AVIC Harbin Aircraft
Industry Company Ltd (AVIC HAFEI).
Role
Twin-engine turboprop utility aircraft
National origin
China
Manufacturer
Harbin Aircraft Industry Group
First flight
14 July 1982
Status
Active, In production
Primary user
People's Liberation Army Air Force
Produced
1985 - present
Unit cost
US$3 million (1998)
Developed from
Harbin Y-11
Specifications (Y-12 (II))
General characteristics
Crew: 2
Capacity: 17 pax / 1,700 kg (3,748 lb) max payload
Length: 14.86 m (48 ft 9 in)
Wingspan: 17.235 m (56 ft 7 in)
Height: 5.575 m (18 ft 3 in)
Wing area: 34.27 m2 (368.9 sq ft)
Airfoil: LS(1)-0417
Empty weight: 2,840 kg (6,261 lb)
Max takeoff weight: 5,300 kg (11,684 lb)
Fuel capacity: 1,616 l (427 US gal; 355 imp gal) / 1,230 kg (2,712 lb) max
usable fuel weight
Powerplant: 2 × Pratt & Whitney Canada PT6A-27 turboprop engines, 462 kW (620
hp) each
Propellers: 3-bladed Hartzell HC-B3TN-3B/T10173B-3, 2.49 m (8 ft 2 in) diameter
constant-speed fully-feathering reversible-pitch propellers (4 and 5 bladed
propellers used on some models)
Performance
Maximum speed: 328 km/h (204 mph, 177 kn) VMO (maximum operating speed) at 3,000
m (9,843 ft)
Cruise speed: 292 km/h (181 mph, 158 kn) (max) at 3,000 m (9,843 ft)
250 km/h (160 mph; 130 kn) (economical) at 3,000 m (9,843 ft)Range: 1,340 km
(830 mi, 720 nmi) at econ cruise, 45 min reserves at 3,000 m (9,843 ft)
Endurance: 5 hours 12 minutes at econ cruise
Service ceiling: 7,000 m (23,000 ft)
3,000 m (9,843 ft) on one engineRate of climb: 8.1 m/s (1,590 ft/min)
1.4 m/s (4.6 ft/s) on one engineWing loading: 145.9 kg/m2 (29.9 lb/sq ft)
Power/mass: 0.106 kW/kg (0.064 hp/lb)
Take-off run: 370 m (1,214 ft)
Take-off run to 15 m (49 ft): 490 m (1,608 ft)
Landing run: 340 m (1,115 ft)
Landing run from 15 m (49 ft): 630 m (2,067 ft)
*