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Military


PC-21 NextGen Trainer

CountrySwitzerland
BuilderPilatus Aircraft Ltd
StatusIn Production
Training Roles Basic Flying Training
Advanced Flying Training
Full Mission Management Training
Embedded Simulation and Emulation
Orders as of Jan 2017
  1. 8 x PC-21 - Swiss Air Force
  2. 19 x PC-21 - Republic of Singapore Air Force
  3. 25 x PC-21 - UAE Air Force & Air Defence
  4. 55 x PC-21 - Royal Saudi Air Force
  5. 24 x PC-21 - Qatar Emiri Air Force
  6. 49 x PC-21 - Australian Defence Force
  7. 10 x PC-21 - Royal Jordanian Air Force
  8. 17 x PC-21 - French Armée de l'Air
  9. 2 x PC-21 - Qinetiq Empire Test Pilots’ School (ETPS)
WING SPAN 9.108 m 29 ft 11 in.
HORIZONTAL TAIL SPAN 4.000 m 13 ft 1 in.
FUSELAGE LENGTH 11.232 m 36 ft 11 in.
FUSELAGE WIDTH 1.002 m 3 ft 3 in.
PROPELLER DIAMETER 2.388 m 94 in.
WING PROJECTED AREA 15.221 m2 168.848 ft2
ASPECT RATIO 5.120
MEAN AERODYNAMIC CHORD 1.783 m
WEIGHTSACROBATIC WITH STORES*
MAX. RAMP WEIGHT 3,120 kg / 6,878 lb 4,270 kg/ 9,414 lb
MAX. TAKE-OFF WEIGHT 3,100 kg / 6,834 lb 4,250 kg / 9,370 lb
MAX. LANDING WEIGHT 3,100 kg / 6,834 lb 4,038 kg / 8,902 lb
MAX. ZERO FUEL WEIGHT 2,750 kg 6,063 lb
MAX. WEIGHT OF STORES 1,150 kg 2,535 lb
CENTRE OF GRAVITY RANGE ACROBATIC CATEGORY 20% - 28% MAC
WITH STORES* 20% - 28% MAC
SPEEDS Equivalent air speeds (EAS) at
max. operating weights in acrobatic configuration:
MAX. OPERATING SPEED (VMO) 370 kt
MAX. OPERATING MACH NO. (MMO) 0.72 M
MANOEUVRING SPEED (VO) AILERONS 370 kt
MANOEUVRING SPEED (VO) RUDDER, ELEVATOR 220 kt
MAX. SPEED WITH FLAPS AND/OR LANDING GEAR EXTENDED (VFT,VFL,VLE) 180 kt
STALLING SPEED (IDLE POWER) AT MTOW (3,100 KG)
WITH: FLAPS TAKE-OFF, GEAR DOWN (VS1) 86 kt
WITH:FLAPS LAND, GEAR DOWN (VS0) 81 kt
ALTITUDE
MAX. OPERATING ALTITUDE 25,000 ft
SERVICE CEILING 38,000 ft
OPERATING TEMPERATURE MIN. – 55° C
(– 40° C OIL TEMPERATURE FOR ENGINE STARTING)
MAX. + 50° C
LOAD FACTOR
ACROBATIC WITH STORES*
WITH LANDING GEAR UP AND LOCKED OR DOWN AND LOCKED:
MAX. POSITIVE + 8.0 g + 5.0 g
MAX. NEGATIVE – 4.0 g – 2.5 g
WITH FLAPS EXTENDED IN TAKE-OFF OR LAND POSITION:
MAX. POSITIVE + 4.0 g + 4.0 g
MAX. NEGATIVE 0 g 0 g
TAKE-OFF AND LANDING
TAKE-OFF GROUND ROLL, SEA LEVEL 490 m 1,608 ft
TAKE-OFF DISTANCE TO CLEAR 15 m (50 ft) OBSTACLE, SEA LEVEL 725 m 2,380 ft
LANDING GROUND ROLL, SEA LEVEL 600 m 1,969 ft
LANDING DISTANCE TO CLEAR 15 m (50 ft) OBSTACLE, SEA LEVEL 900 m 2,953 ft
MAX. RATE OF CLIMB AT MAX. POWER AVAILABLE:
SEA LEVEL 4,250 ft/min
10,000 ft 3,325 ft/min
20,000 ft 2,125 ft/min
TIME TO CLIMB:
10,000 ft 2 min 35 s
20,000 ft 6 min 20 s
CRUISE
MAX. HORIZONTAL SPEED, BASED ON MAX. POWER AVAILABLE:
SEA LEVEL 323 KTAS
10,000 ft 337 KTAS
20,000 ft 334 KTAS
HORIZONTAL SPEED AT NORMAL CRUISE POWER:
SEA LEVEL 308 KTAS
10,000 ft 310 KTAS
20,000 ft 306 KTAS
SUSTAINED LOAD FACTOR AT A TYPICAL WEIGHT OF 2,700 KG WITH HALF FUEL:
SEA LEVEL 3.7 g
10,000 ft 3.0 g
20,000 ft 2.1 g
ROLL RATE MAX. STEADY ROLL RATE IN ACROBATIC CONFIGURATION 200°/s AT 10,000 ft, AT ALL SPEEDS ABOVE 250 KEAS.
The performance figures above are valid for the following conditions:
  • international standard atmosphere (ISA)
  • calm wind
  • typical aircraft weight of 2,950 kg unless otherwise specified
  • propeller speed 2,000 rpm
  • airframe in new condition, standard antenna installation
  • environmental control system on





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