TYPE OF AIRCRAFT

Minimum 34.5 t (76,000 lb) 35.4 t (78,000 lb) 37.23 t (82,100 lb) 47.5 t (105,000 lb)
Weight[87]

Speed Cruise: Mach 0.78 (447 kn; 829 km/h),[118] MMO: Mach 0.82 (470 kn; 871 km/h)[118]

Range[d] 5,741 km 6,945 km 6,112 km 5,926 km
(3,100 nmi) (3,750 nmi)[c] (3,300 nmi)[c] (3,200 nmi)[c]

Takeoff (MTOW, 1,780 m 1,850 m 2,100 m
SL, ISA) (5,840 ft)[119] (6,070 ft)[120] (6,900 ft)[121]

Landing (MLW, 1,230 m 1,360 m 1,500 m
SL, ISA) (4,040 ft)[119] (4,460 ft)[120] (4,900 ft)[121]

Ceiling 39,100–41,000 ft (11,900–12,500 m)[87]

CFM International CFM56-5B, 68.3 in (1.73 m) fan

Engines (×2)

PW6000A, IAE V2500-A5, 63.5 in (1.61 m) fan
56.5 in (1.44 m)

fan

Thrust (×2) 96–106 kN 98–120 kN (22,000–27,000 lbf) 133–147 kN
(22,000– (30,000–33,000 lbf)

24,000 lbf)

ICAO code[122] A318 A319 A320 A321

AIRBUS A300

Specifications

model A300B4-200[62] A300-600R[63] A300-600F[64]

Cockpit crew Three Two

281/309Y @ 34/31 247 (46F + 201Y)/285Y 540 m³, 43
AYY ULD
Main deck in) @ 34 in 9 AMJ/LD7 + 16

max 345 max 345 (3-3-3 Y) AYY

Lower deck 20 LD3 + bulk 22 LD3 + bulk / 158 m³

Length 53.61 m (175.9 ft) 54.08 m (177.4 ft)

Height 16.72 m (54.9 ft) 16.66 m (54.7 ft)

Wing 44.84 m (147.1 ft) span, 260 m2 (2,800 sq ft) area[65] 7.7 aspect ratio

Width 5.287 m (17.35 ft) cabin, 5.64 m (18.5 ft) Fuselage, usually 2-4-2Y

Pressurized volume 542 m³ / 19 140 cu 860 m³ / 30 370 cu ft
ft

MTOW 165,000 kg 171,700 kg (378,534 lb) 170,500 kg
(363,763 lb) (375,888 lb)

Max payload 37,495 kg 41,374 kg (91,214 lb) 48,293 kg
(82,662 lb) (106,468 lb)

Fuel capacity 48,470 kg 53,505 kg (117,958 lb)
(106,858 lb)

OEW 88,505 kg 88,626 kg (195,387 lb) 81,707 kg
(195,120 lb) (180,133 lb)

Engines CF6-50C2 or JT9D- CF6-80C2 or PW4158
59A

Takeoff thrust 230 kN 249–270 kN (56,000–61,000 lbf)[67]
(52,000 lbf)[66]

Takeoff (MTOW, SL, 2,300 m (7,500 ft) 2,400 m (7,900 ft)
ISA)

Speed Mach 0.78 (450 kn; 833 km/h) FL350 cruise, MMO Mach 0.82[67]

Range 5,375 km / 7,500 km / 4,050 nmi[67]
2,900 nmi

ATR 42

ATR family booklet[57]

ATR 42-300 ATR 42-400 ATR 42-500/600

Flight crew 2

Seating 48

Length 22.67 m (74 ft 5 in)

Wingspan 24.57 m (80 ft 7 in)

Height 7.59 m (24 ft 11 in)

Wing area 54.5 m2 (587 sq ft)

Aspect ratio 11.08

Empty weight 10,285 kg - 22,680 lb 11,050 kg - 24,361 lb 11,550 kg - 25,463 lb

MTOW 16,900 kg - 37,257 lb 18,200 kg - 40,123 lb 18,600 kg - 41,005 lb

Max payload 5255 kg - 11579 lb 5550 kg - 12235 lb 5450 kg - 12015 lb

Fuel capacity 4,500 kg - 9,921 lb

Engines (×2) PW120, -320: PW121 PW121A PW127E/M

Power 1,800 hp (1,300 kW) 1,980 hp (1,480 kW) 2,160 hp (1,610 kW)
-320: 1,900 hp (1,400 kW)

Cruise speed 270 kn - 500 km/h 261 kn - 484 km/h 300 kn - 556 km/h

48 pax range 459 nmi (850 km) 794 nmi (1,470 km) 716 nmi (1,326 km)

ATR 72

General characteristics

 Crew: 2
 Capacity: 70 seats at 30 inch pitch standard, 2-2 abreast (68 to 78 seats[78])
 Length: 27.17 m (89 ft 2 in)
 Wingspan: 27.05 m (88 ft 9 in)
 Width: 2.57 m (8 ft 5 in) (cabin, maximum)
 Height: 7.65 m (25 ft 1 in)
 Wing area: 61.0 m2 (657 sq ft)
 Aspect ratio: 12
 Empty weight: 13,311 kg (29,346 lb) Typical in-service: 13,500 kg (29,762 lb)
 Max takeoff weight: 23,000 kg (50,706 lb)
 Fuel capacity: 5,000 kg (11,000 lb)
 Max payload: 7,500 kg (16,500 lb)
 Powerplant: 2 × Pratt & Whitney Canada PW127M , 1,846 kW (2,475 shp) each
 Propellers: 6-bladed Hamilton Standard 568F, 3.93 m (12 ft 11 in) diameter

Performance

 Cruise speed: 510 km/h (320 mph, 280 kn) TAS
 Range: 1,528 km (949 mi, 825 nmi) typical in-service OEW, 70 PAX@95kg

 Service ceiling: 7,600 m (25,000 ft) [79]
 Rate of climb: 6.88 m/s (1,355 ft/min)
 Fuel consumption: 1.49 kg/km (5.3 lb/mi)
 Takeoff: 1,367 m (4,485 ft) [MTOW]

AVIAT PITTS S-2C

Pitts S-2C SPECS

Engine Lycoming AEIO-540, 260 HP
Propeller The Claw by Hartzell® 76: Composite Constant Speed
Length
Height 17 feet 9 inches
Wing Span 6 feet 5 inches
Wing Area
Wing Loading 20 feet
Power Loading 127.5 square feet
Seats 13.3 lb/sqft (normal)/12.7 lb/sqft (aerobatic)
Cabin Length 6.59 lb/hp (normal)/6.25 lb/hp (aerobatic)
Cabin Width
Cabin Height 2 tandem
Empty Weight 6 feet 11 inches

28 inches
47 inches
1,155 pounds

Maximum Gross Weight 1700 pounds

Useful Load 545 lb (normal)/470 lb (aerobatic)
Payload w/Full Fuel 371 pounds
Fuel Capacity w/5 Gallon Wing Tank
29 U.S. gallons (28 gallons usable)

PERFORMANCE

Pitts S-2C +6 G/-5 G
554 feet
Aerobatic Flight Load Limits 860 feet
Takeoff Distance Ground Roll 17 kt
Takeoff Distance Over 50 ft Obstacle
Max Demonstrated Crosswind Component 2,900 fpm
Rate of Climb, Sea Level, Minimum Weight 169 kt
Maximum Level Speed, Sea Level
Cruise Speed w/30 min rsv. at 75% Power 150 KTAS/1.6 hours
Range w/30 min rsv. at 75% Power 284 st. miles
Fuel Consumption at 75% Power
Best Economy 84 pph/14 gph
Landing Distance over 50 ft Obstacle 6,000 feet
Landing Distance, Ground Roll 1,200 feet
VY (Best Rate of Climb) 750 Feet
VA (Design Maneuvering) KIAS 82
VNO (Max Structural Cruising) KIAS 134
VNE (Never Exceed) KIAS 134
VSI (Stall, Clean) KIAS 185
KIAS 56

BRITISH AEROSPACE 146

BAe 146/Avro RJ[92]

Variant -100/RJ70 -200/RJ85 -300/RJ100

Crew 70–82 2 97–112
Seats 85–100

Cabin width 3.42 m (11.2 ft)

Length 26.19 m (85.9 ft) 28.55 m (93.7 ft) 31 m (102 ft)

Height 8.61 m (28.2 ft)

Wing 26.34 m (86.4 ft) span, 77.3 m2 (832 sq ft) area, 8.98 AR

MTOW 38,101 kg (84,000 lb) 42,184 kg (93,000 lb) 44,225 kg (97,500 lb)

OEW 23,820 kg (52,510 lb) 24,600 kg (54,230 lb) 25,640 kg (56,530 lb)

Max. Payload 8,612 kg (18,990 lb) 11,233 kg (24,760 lb) 11,781 kg (25,970 lb)

Fuelcapacity 11,728 L (3,098 US gal), option : 12,901 L (3,408 US gal)[93]

Engines (4×) BAe 146 : Lycoming ALF 502R-5, Avro RJ : Honeywell LF 507-1F

Thrust (×4) 6,990 lbf (31.1 kN)

Speed Mach 0.739 (426 kn; 789 km/h) Max, Mach 0.7 (404 kn; 747 km/h) cruise

Ceiling 35,000 ft (11,000 m)

Range 82 pax: 3,870 km 100 pax: 3,650 km 100 pax: 3,340 km
(2,090 nmi) (1,970 nmi) (1,800 nmi)

Takeoff (SL, 1,195 m (3,921 ft) 1,390 m (4,560 ft) 1,535 m (5,036 ft)
ISA)

Landing (SL, 1,180 m (3,870 ft) 1,190 m (3,900 ft) 1,270 m (4,170 ft)
ISA)

Fuel 425 kn: 2,468 kg 423 kn: 2,483 kg 429 kn: 2,517 kg
consumption (5,441 lb)/h (5,474 lb)/h (5,549 lb)/h

(FL 310)[93] 361 kn: 1,594 kg 361 kn: 1,672 kg 377 kn: 1,724 kg
(3,514 lb)/h (3,686 lb)/h (3,801 lb)/h

BEECHCRAFT 1900

General characteristics

 Crew: 1 (2 for airline operations)
 Capacity: 19 passengers and 6,356 lb (2,882 kg) useful load
 Length: 57 ft 8 in (17.62 m)
 Wingspan: 57 ft 9 in (17.64 m)
 Height: 15 ft 5 in (4.72 m)
 Empty weight: 10,434 lb (4,732 kg)
 Gross weight: 17,227 lb (7,814 kg)
 Max takeoff weight: 17,120 lb (7,764 kg)
 Fuel capacity: 4,458 lb (2,022 kg)
 Fuel type: Jet A recommended, others usable
 Powerplant: 2 × Pratt & Whitney Canada PT6A-67D turboprops, 1,279 shp (955 kW)

each

Performance

 Cruise speed: 280 kn (322 mph, 518 km/h) at 20,000 ft (6,100 m)
 Range: 382 nmi (439 mi, 707 km) with 19 passenger payload
 Ferry range: 1,245 nmi (1,432 mi, 2,306 km)
 Service ceiling: 25,000 ft (7,620 m)
 Rate of climb: 2,615 ft/min (13.28 m/s)

BEECHCRAFT KING AIR B200gt

Variant 250[96] 350i[97] 350ER[98]

Crew 1–2

Capacity 10 11

Length 43 ft 10 in / 13.36 m 46 ft 8 in / 14.22 m

Span 57 ft 11 in / 17.65 m

Height 14 ft 10 in / 4.52 m 14 ft 4 in / 4.37 m

Cabin L × W × H 16'8" × 4'6" × 4'9" 19'6" × 4'6" × 4'9"
5.08 × 1.37 × 1.45 m 5.94 × 1.37 × 1.45 m

MTOW 12,500 lb / 5,670 kg 15,000 lb / 6,804 kg 16,500 lb / 7,484 kg

OEW[a] 8,830 lb / 4,005 kg 9,955 lb / 4,516 kg 9,455 lb / 4,289 kg[b]

Useful load 3,760 lb / 1,706 kg 5,145 lb / 2,334 kg 7,145 lb / 3,241 kg

Engine type (2×) PWC PT6A-52 PWC PT6A-60A

Power or Thrust 850 shp / 625 kW 1,050 shp / 783 kW

Maximum Cruise 310 kt / 574 km/h 312 kt / 578 km/h 303 kt / 561 km/h

Ferry Range 1,720 nm / 3,185 km 1,806 nm / 3,345 km 2,670 nm / 4,945 km

Takeoff 2,111 ft / 643 m[c] 350i: 3,300 ft / 1,006 m 4,057 ft / 1,237 m[8]

Ceiling 35,000 ft / 10,668 m

BOMBARDIER CHALLENGER 300

Variant Challenger 300[10] Challenger 350[14]
Crew
Capacity two
Length
Span eight to nine nine (standard)
Height
Wing Area 68.63 ft / 20.92 m

63.84 ft / 19.46 m 69 ft 0 in / 21.0 m

20.33 ft / 6.20 m 20 ft 0 in / 6.1 m

523 ft2 / 48.5 m2

Aspect ratio 7.81 9.09

MTOW 38,850 lb / 17,622 kg 40,600 lb / 18,416 kg

OEW 23,500 lb / 10,659 kg 24,800 lb / 11,249 kg

Fuel capacity 14,150 lb / 6,418 kg

Maximum payload 3,500 lb / 1,588 kg 3,400 lb / 1,542 kg

Wing loading 74.3 lb/ft2/ 363.3 kg/m2 77.6 lb/ft2 / 379.7 kg/m2

Turbofans (2×) Honeywell HTF7000 Honeywell HTF7350

Thrust[a] 6,826 lbf / 30.4 kN 7,323 lbf / 33 kN

Maximum speed Mach 0.82 / 470 kn / 870 km/h Mach 0.83 / 477 kn / 882 km/h

Cruise speed Mach 0.80 / 459 kn / 850 km/h

Range[b] 3,100 nmi / 5,741 km 3,200 nmi / 5,926 km

Ceiling 45,000 ft / 13,716 m

Takeoff[c] 4,810 ft / 1,466 m 4,835 ft / 1,474 m

Landing[d] 2,600 ft / 792 m 2,710 ft / 826 m

BOEING 747

Specifications

Model 747SP[280] 747-100[280] 747- 747- 747-400[281] 747-8[282]
200B[280] 300[280]

Cockpit Three Two
crew

Typical 276 (25F 366 (32F 74J 260Y) 400 (34F 416 (23F 78J 467 (24F
seats 57J 194Y) 76J 315Y) 87J 356Y)

290Y)

Exit 400 440/550 550/660 495/605
limit[283][a]

Cargo 3,900 cu ft 6,190 cu ft (175 m3), 30×LD1 5,655 ft³ (160.1 m³) 6,345 cu ft
(110 m3) (179.7 m3)

Length 184 ft 9 in 231 ft 10 in (70.66 m) 250 ft 2 in
(56.3 m) (76.25 m)

Cabin 239.5 in (608 cm)[281]
width

Wingspa 195 ft 8 in (59.6 m) 211 ft 5 in (64.4 m) 224 ft 7 in
n (68.4 m)

Wing 5,500 ft² (511 m2) 5,650 sq ft 5,960 sq ft
area (525 m )2 [284] (554 m )2 [285]

Wing 37.5°[286][287][288]
sweep

Aspect 7 7.9 8.5
ratio

Tail 65 ft 5 in 63 ft 5 in (19.3 m) 63 ft 8 in (19.4 m) 63 ft 6 in
height (19.9 m) (19.4 m)

MTOW 700,000 lb 735,000 lb 833,000 lb (377.8 t) 910,000 lb (412.8 t) 987,000 lb
(317.5 t) (333.4 t) (447.7 t)

OEW 337,100 lb 379,500 lb 375,100 l 384,000 l 412,300 lb (187.0 t) 485,300 lb
(152.9 t) (172.1 t) b b (174 t) (220.1 t)

(170.1 t)

Fuel 50,359 US 48,445 US 53,985 US gal 63,705 US gal 63,034 US
capacity gal gal 204.36 m3 241.15 m3 gal

190.63 m3 183.38 m3 238.61 m3

Turbofan Pratt & Whitney JT9D-7 or Rolls-Royce RB211- PW4000 / CF6 / RB GEnx-2B67
×4 524 or GE CF6 211

Thrust ×4 46,300– 43,500– 46,300– 46,300– 62,100–63,300 lbf 66,500 lbf
276–282 kN 296 kN
56,900 lbf 51,600 lbf 54,750 lbf 56,900 lbf
206– 193– 206.0– 206–

253 kN 230 kN 243.5 kN 253 kN

MMo[283] Mach 0.92 Mach 0.9

Cruise econ. 907 km/h (490 kt), max. Mach 0.855 (504 kn; 933 km/h)
939 km/h (507kt)[289][290]

5,830 nmi 4,620 nmi 6,560 nmi 6,330 nmi 7,670 nmi 7,730 nmi
10,800 km[b] 8,560 km[c] 14,200 km[e]
Range 12,150 k 11,720 k 14,320 km[f][

m[c] m[d] 291]

Takeoff 9,250 ft 10,650 ft 10,900 ft 10,900 ft 10,700 ft (3,260 m) 10,200 ft
(2,820 m) (3,250 m) (3,300 m) (3,300 m) (3,100 m)

BOEING777

Boeing 777 specifications

Variants Initial[186] Long-range[146]

Model 777-200/200ER 777-300 777-300ER 777-
200LR/777F

Crew Two (cockpit)

3-class seats[173] 305 368 365 301
(24F/54J/227Y) (30F/84J/254Y) (22F/70J/273 (16F/58J/227Y)

Y) [a]

2-class seats[177] 313 396 317

Exit limit[191] 440 550 440 [b]

Length 209 ft 1 in / 242 ft 4 in / 73.86 m 209 ft 1 in /
63.73 m 63.73 m

Wingspan 199 ft 11 in / 60.93 m, 31.6° Wing 212 ft 7 in / 64.80 m, 31.6°
sweep[286] Wing sweep[286]

Wing area 4,605 sq ft (427.8 m2),[286] 8.68 AR 4,702 sq ft (436.8 m2),[287] 9.04
AR

Tail height[177] 60 ft 9 in / 18.5 60 ft 8 in / 18.5 m 61 ft 1 in / 18.6 m
m

Fuselage width 20 ft 4 in / 6.20 m

Cabin width 231 in / 5.86 m,[288] Seats: 18.5 in / 47 cm at 9 abreast, 17 in / 43 cm at
10 abreast

Cargo volume[177] 5,330 ft³ / 150.9 7,120 ft³ / 201.6 m³[c] 5,330 ft³ /
m³ 150.9 m³ [d]

MTOW 545,000 lb / 660,000 lb / 775,000 lb / 766,000 lb /
247,200 kg 299,370 kg 351,533 kg 347,452 kg

200ER: 777F:
656,000 lb / 766,800 lb /
297,550 kg 347,815 kg

OEW 299,550 lb / 353,800 lb / 370,000 lb / 320,000 lb /
135,850 kg 160,530 kg 167,829 kg 145,150 kg
300ERSF:
200ER: 336,000 lb 777F:
304,500 lb / (152 t)[289] 318,300 lb /
138,100 kg 144,379 kg

Fuel capacity 31,000 US gal / 117,340 L / 47,890 US gal / 181,283 L /
207,700 lb / 94,240 kg 320,863 lb / 145,538 kg

200ER/300: 45,220 US gal /
171,171 L / 302,270 lb / 137,460 kg

Ceiling[191] 43,100 ft (13,100 m)

Speed Max. Mach 0.87–Mach 0.89 (499–511 kn; 924–945 km/h),[191] Cruise
Mach 0.84 (482 kn; 892 km/h)

Range[177] 5,240 nmi / 6,030 nmi / 7,370 nmi / 8,555 nmi /
9,700 km[e][173] 11,165 km[g][173] 13,649 km[h] 15,843 km[i]
200ER: 7,065 300ERSF: 777F: 4,970
nmi / 13,080 km[f] 4,650 nmi nmi / 9,200 km[j]
(8,610 km)[289]

Takeoff[k] 8,000 ft 10,600 ft 10,000 ft 9,200 ft
(2,440 m) (3,230 m) (3,050 m) (2,800 m)
200ER:11,100 ft 777F: 9,300 ft
(3,380 m) (2,830 m)

Engine 2× PW4000 / Tr 2× PW4000 / Tr 2× GE90- 2× GE90-
115B[290] 110B/-115B[290]
ent 800 / GE90 ent 800[191]

Max thrust 2× 77,200 lbf 2× 98,000 lbf 2× 2× 110,000–
(343 kN) (440 kN) 115,300 lbf
200ER: 2× 115,300 lbf
93,700 lbf (513 kN) 489–513 kN
(417 kN)

ICAOdesignation[ B772 B773 B77W B77L

170]

BRITISH AEROSPACE ATP

General characteristics

 Crew: 2
 Capacity: 64 passengers + 2 flight attendants
 Length: 26.00 m (85 ft 4 in)
 Wingspan: 30.63 m (100 ft 6 in)
 Height: 7.14 m (23 ft 5 in)
 Wing area: 78.3 m2 (843 sq ft) [6]
 Empty weight: 13,595 kg (29,972 lb)
 Max takeoff weight: 22,930 kg (50,552 lb)
 Fuel capacity: 6,364 L (1,400 imp gal; 1,681 US gal)
 Powerplant: 2 × Pratt & Whitney Canada PW126 turboprops, 1,978 kW (2,653 shp)

each
 Propellers: 6-bladed BAe/Hamilton Standard, 4.19 m (13 ft 9 in) diameter

Performance

 Cruise speed: 496 km/h (308 mph, 268 kn) at 4,575 m (15,010 ft)
 Range: 1,825 km (1,134 mi, 985 nmi) with 64 passengers
 Ferry range: 4,070 km (2,530 mi, 2,200 nmi)
 Service ceiling: 7,600 m (25,000 ft) (max operating altitude)[7]

BEECHCRAFT PREMIER I

General characteristics

 Crew: 1
 Capacity: 6 / 7
 Length: 46 ft 0 in (14.02 m)
 Wingspan: 44 ft 6 in (13.56 m)
 Height: 15 ft 4 in (4.67 m)
 Wing area: 246 sq ft (22.9 m2) [15]
 Aspect ratio: 8.03
 Empty weight: 8,600 lb (3,901 kg) Basic Operating
 Max takeoff weight: 12,500 lb (5,670 kg)
 Fuel capacity: 3,670 lb / 1,665 kg
 Max Payload: 1,400 lb / 635 kg
 Cabin Length × Width × Height: 13 ft 6 in × 5 ft 6 in × 5 ft 5 in (4.11 × 1.68 × 1.65 m)
 Hold: 76.9 cu. ft / 2.2 cu. m
 Powerplant: 2 × Williams FJ44-2A Turbofan, 2,300 lbf (10.23 kN) thrust each

Performance

 Maximum speed: 523 mph (841 km/h, 454 kn) max cruise
 Range: 950 mi (1,530 km, 830 nmi) Max Payload
 Ferry range: 1,710 mi (2,750 km, 1,480 nmi)

 Service ceiling: 41,000 ft (12,500 m)
 Wing loading: 50.6 lb/sq ft (247 kg/m2)
 Fuel consumption: 1.67[4] lb/mi (0.47 kg/km)
 Thrust/weight: 0.37
 Take-off (MTOW): 3,792 ft / 1,156 m
 Landing (MLW): 3,177 ft / 968 m

BRITTEN-NORMAN BN-2 ISLANDER

General characteristics

 Crew: 1
 Capacity: 10 passengers / 2,048 lb (929 kg) maximum payload
 Length: 35 ft 7 3⁄4 in (10.865 m)
 Wingspan: 49 ft 0 in (14.94 m)
 Height: 13 ft 8 3⁄4 in (4.185 m)
 Wing area: 325.0 sq ft (30.19 m2)
 Aspect ratio: 7.4:1
 Airfoil: NACA 23012
 Empty weight: 4,114 lb (1,866 kg) equipped (without avionics)
 Max takeoff weight:6,600 lb (2,994 kg)
 Fuel capacity:137 imp gal (165 US gal; 620 L)
 Powerplant: 2 × Lycoming O-540-E4C56-cylinder air-cooled horizontally-opposed

piston engines, 260 hp (190 kW) each

 Propellers: 2-bladed Hartzell HC-C2YK-2B constant speed propellers, 6 ft 6 in (1.98 m)
diameter

Performance

 Maximum speed: 148 kn (170 mph, 274 km/h) at sea level
 Cruise speed: 130 kn (150 mph, 240 km/h) at 12,000 ft (3,700 m) (59% power)
 Stall speed: 40 kn (46 mph, 74 km/h) (flaps down)
 Never exceed speed: 183 kn (211 mph, 339 km/h)
 Range: 755 nmi (869 mi, 1,398 km) at 130 kn (150 mph; 241 km/h) and 12,000 ft

(3,700 m) (59% power, standard fuel)
 Service ceiling: 11,300 ft (3,400 m)
 Rate of climb: 860 ft/min (4.4 m/s) at sea level
 Take-off run to 50 ft (15 m): 1,218 ft (370 m) (at sea level)
 Landing run from 50 ft (15 m): 980 ft (300 m) (at sea level)

BOMBARDIER CRJ1000 SERIES

CRJ Series Brochure[97]

Variant CRJ700 CRJ900 CRJ1000

Cockpit crew 2
Cabin crew 2–3

Seating 66 to 78 76 to 90 97 to 104
capacity

Cargo capacity 547 cu ft / 15.5 m3 594 cu ft / 16.8 m3 683 cu ft / 19.4 m3
5,375 lb / 2,438 kg 6,075 lb / 2,756 kg 7,180 lb / 3,257 kg

Length 106 ft 1 in / 32.3 m 118 ft 11 in / 36.2 m 128 ft 5 in / 39.1 m

Height 24 ft 10 in / 7.6 m 24 ft 7 in / 7.5 m 24 ft 6 in / 7.5 m

Wingspan 76 ft 3 in / 23.2 m 81 ft 7 in / 24.9 m 85 ft 11 in / 26.2 m

Wing area 760 sq ft / 70.6 m2 765 sq ft / 71.1 m2 833 sq ft / 77.4 m2

Fuselage 8 ft 10 in / 2.7 m maximum diameter

Cabin 100.5 in / 2.55 m width × 74.4 in / 1.89 m height

MTOW 75,000 lb / 34,019 kg (ER) 84,500 lb / 38,330 kg 91,800 lb / 41,640 kg
(LR) (ER)

Operating 44,245 lb (20,069 kg) 48,160 lb (21,845 kg) 51,120 lb (23,188 kg)
empty

Max. payload 18,055 lb / 8,190 kg 22,590 lb / 10,247 kg 26,380 lb / 11,966 kg
(LR)

Max. fuel 19,595 lb / 8,888 kg[98][99] 19,450 lb / 8,822 kg[100]

Engines (2×) GE CF34-8C5B1 GE CF34-8C5 GE CF34-8C5A1

Thrust (2×)[a] 13,790 lbf / 61.3 kN 14,510 lbf / 64.5 kN

Max. speed 0.825 Mach (473 kn, 0.82 Mach (470 kn, 871 km/h)
876 km/h)

Service ceiling 41,000 ft / 12,479 m[59]

Cruise Mach 0.78 (447 kn, 829 km/h)

Range[b] 1,378 NM / 2,553 km (ER) 1,553 NM / 2,876 km 1,622 NM / 3,004 km
(LR) (ER)

Takeoff[c] 5,265 ft / 1,605 m (ER) 6,360 ft / 1,939 m (LR) 6,955 ft / 2,120 m (ER)

Landing[d] 5,040 ft / 1,536 m 5,355 ft / 1,632 m 5,740 ft / 1,750 m

CASA C-212 AVIOCAR

General characteristics

 Crew: 2
 Capacity: 26 passengers / 25 paratroops / 2,820 kg (6,217 lb) military payload /

2,700 kg (5,952 lb) cargo payload
 Length: 16.15 m (53 ft 0 in)
 Wingspan: 20.28 m (66 ft 6 in)
 Height: 6.6 m (21 ft 8 in)
 Wing area: 41 m2(440 sq ft)
 Aspect ratio: 10
 Airfoil: NACA 653-218[53]
 Empty weight: 3,780 kg (8,333 lb)
 Max takeoff weight: 8,000 kg (17,637 lb) military
7,700 kg (16,976 lb) standard

 Max Landing weight: 7,450 kg (16,424 lb)
 Fuel capacity: 2,040 l (540 US gal; 450 imp gal) / 1,600 kg (3,527 lb) internal
and

1,000 l (260 US gal; 220 imp gal) auxiliary fuel tanks in the cabin
or

2x 750 l (200 US gal; 160 imp gal) auxiliary fuel tanks in the cabin
and/or

2x 500 l (130 US gal; 110 imp gal) underwing auxiliary fuel tanks

 Powerplant: 2 × Garrett AiResearch TPE331-10R-513Cturboprop engines,
671 kW (900 hp) each

 Propellers: 4-bladed Dowty Rotol R-334/4-82-F/13, 2.74 m (9 ft 0 in) diameter
constant-speed fully-feathering reversible-pitch propellers

Performance

 Maximum speed: 370 km/h (230 mph, 200 kn) VMO (maximum operating speed)
at MTOW

 Cruise speed: 354 km/h (220 mph, 191 kn) (max cruise) at 3,050 m (10,007 ft)
 Economical cruise speed: 300 km/h (190 mph; 160 kn) at 3,050 m (10,007 ft)
 Stall speed: 145 km/h (90 mph, 78 kn) in take-off configuration
 Range: 835 km (519 mi, 451 nmi) with full military payload
 Ferry range: 2,680 km (1,670 mi, 1,450 nmi) with maximum fuel and 1,192 kg

(2,628 lb) payload
 Service ceiling: 7,925 m (26,001 ft)
3,380 m (11,089 ft) on one engine

 Rate of climb: 8.283 m/s (1,630.5 ft/min)
 Take-off distance to 15 m (49 ft): 610 m (2,001 ft) (MIL-7700C)
 Landing distance from 15 m (49 ft): 462 m (1,516 ft) (MIL-7700C)
 Landing run: 285 m (935 ft) (MIL-7700C)

CESSNA 150

General characteristics

 Crew: one
 Capacity: one passenger (plus two children not exceeding 120 lb (54 kg) on optional

bench seat in baggage space)
 Length: 23 ft 11 in (7.29 m)
 Wingspan: 33 ft 2 in (10.11 m)
 Height: 8 ft 6 in (2.59 m)
 Wing area: 160 sq ft (15 m2)
 Aspect ratio: 6.7:1
 Airfoil: NACA 2412
 Empty weight: 1,122 lb (509 kg)
 Max takeoff weight: 1,600 lb (726 kg)
 Fuel capacity: 22.5 US gal (18.7 imp gal; 85 L) usable internal fuel
 Powerplant: 1 × Continental O-200-A air-cooled horizontally-opposed engine, 100 hp

(75 kW)
 Propellers: 2-bladed McCauley metal fixed-pitch propeller, 5 ft 9 in (1.75 m) diameter

Performance

 Maximum speed: 109 kn (125 mph, 202 km/h) at sea level
 Cruise speed: 82 kn (94 mph, 152 km/h) at 10,000 ft (3,050 m) (econ cruise)
 Stall speed: 42 kn (48 mph, 78 km/h) (flaps down, power off)
 Never exceed speed: 140 kn (160 mph, 260 km/h)
 Range: 420 nmi (480 mi, 780 km) (econ cruise, standard fuel)
 Service ceiling: 14,000 ft (4,300 m)
 Rate of climb: 670 ft/min (3.4 m/s)
 Take-off run to 50 ft (15 m): 1,385 ft (422 m)
 Landing run from 50 ft (15 m): 1,075 ft (328 m)

CESSNA 152

General characteristics

 Crew: one
 Capacity: one passenger (plus two children not exceeding 120 lb (54 kg) on optional

baggage compartment bench seat)
 Length: 24 ft 1 in (7.34 m)
 Wingspan: 33 ft 4 in (10.16 m)
 Height: 8 ft 6 in (2.59 m)
 Wing area: 160 sq ft (15 m2)
 Empty weight: 1,081 lb (490 kg)
 Gross weight: 1,670 lb (757 kg)
 Powerplant: 1 × Lycoming O-235-L2C flat-4 engine, 110 hp (82 kW)
 Propellers: 2-bladed fixed pitch, 69-inch (180 cm) McCauley or 72-

inch Sensenich propeller

Performance

 Maximum speed: 126 mph (203 km/h, 109 kn)
 Cruise speed: 123 mph (198 km/h, 107 kn)
 Stall speed: 49 mph (79 km/h, 43 kn) (power off, flaps down)
 Range: 477 mi (768 km, 415 nmi)
 Ferry range: 795 mi (1,279 km, 691 nmi) with long-range tanks
 Service ceiling: 14,700 ft (4,500 m)
 Rate of climb: 715 ft/min (3.63 m/s)

CESSNA 172

General characteristics

 Crew: one
 Capacity: three passengers
 Length: 27 ft 2 in (8.28 m)
 Wingspan: 36 ft 1 in (11.00 m)
 Height: 8 ft 11 in (2.72 m)
 Wing area: 174 sq ft (16.2 m2)
 Aspect ratio: 7.32
 Airfoil: modified NACA 2412
 Empty weight: 1,691 lb (767 kg)
 Gross weight: 2,450 lb (1,111 kg)
 Fuel capacity: 56 US gallons (212 litres)
 Powerplant: 1 × Lycoming IO-360-L2A four cylinder, horizontally opposed aircraft

engine, 160 hp (120 kW)
 Propellers: 2-bladed metal, fixed pitch

Performance

 Cruise speed: 122 kn (140 mph, 226 km/h)
 Stall speed: 47 kn (54 mph, 87 km/h) (power off, flaps down)[92]
 Never exceed speed: 163 kn (188 mph, 302 km/h) (IAS)[11]
 Range: 696 nmi (801 mi, 1,289 km) with 45 minute reserve, 55% power, at 12,000 ft
 Service ceiling: 13,500 ft (4,100 m)
 Rate of climb: 721 ft/min (3.66 m/s)
 Wing loading: 14.1 lb/sq ft (68.6 kg/m2)

CESSNA 208 CARAVAN

General characteristics

 Crew: one or two
 Capacity: nine passengers or 13 with FAR Part 23 waiver
 Length: 37 ft 7 in (11.46 m)
 Wingspan: 52 ft 1 in (15.87 m)
 Height: 14 ft 11 in (4.53 m)
 Wing area: 279 sq ft (25.96 m2)
 Aspect ratio: 9.702
 Airfoil: wing root: NACA 23017.424, wing tip: NACA 23012[39]
 Empty weight: 4,730 lb (2,145 kg)
 Gross weight: 8,000 lb (3,629 kg)

Maximum landing weight : 7,800 lb (3,538 kg)
 Fuel capacity: 2,224 lb (1,009 kg/332 gal/1,257 l)
 Cabin height: 54 in (1.37 m)
 Cabin width: 64 in (1.63 m)
 Powerplant: 1 × Pratt & Whitney Canada PT6A-114A turboprop, 675 shp (503 kW)
 Propellers: 3-bladed McCauley Constant speed, full feathering, reversible pitch

Performance

 Cruise speed: 186 kn (214 mph, 344 km/h) true air speed
 Stall speed: 61 kn (70 mph, 113 km/h) calibrated air speed
 Range: 1,070 nmi (1,232 mi, 1,982 km)

 Service ceiling: 25,000 ft (7,600 m)
 Rate of climb: 1,234 ft/min (6.27 m/s)
 Wing loading: 28.674 lb/sq ft (139.792 kg/m2)

CESSNA 402

General characteristics

 Crew: Two pilots
 Capacity: Six passengers
 Length: 36 ft 4 1⁄2 in (11.087 m)
 Wingspan: 44 ft 1 1⁄2 in (13.449 m)
 Height: 11 ft 5 1⁄2 in (3.493 m)
 Wing area: 225.8 sq ft (20.98 m2)
 Airfoil: NACA 23018 (root) NACA 23015 (tip)
 Empty weight: 4,077 lb (1,849 kg)
 Max takeoff weight: 6,850 lb (3,107 kg)
 Fuel capacity: 206 US gal (172 imp gal; 780 L) usable fuel
 Powerplant: 2 × Continental TSIO-520-VB air-cooled turbocharged flat-sixengines,

325 hp (242 kW) each
 Propellers: 3-bladed McCauley 0850334-34 constant speed propeller

Performance

 Maximum speed: 231 kn (266 mph, 428 km/h) at 16,000 ft (4,900 m)
 Cruise speed: 142 kn (163 mph, 263 km/h) at 10,000 ft (3,000 m) (econ cruise)
 Stall speed: 68 kn (78 mph, 126 km/h) (flaps down, power off) (CAS)
 Never exceed speed: 231 kn (266 mph, 428 km/h) (CAS)
 Range: 1,273 nmi (1,465 mi, 2,358 km) at 10,000 ft (3,000 m), econ cruise
 Service ceiling: 26,900 ft (8,200 m)
 Rate of climb: 1,450 ft/min (7.4 m/s)
 Takeoff distance to 50 ft (15m): 2,195 ft (669 m)
 Landing distance from 50 ft (15m): 2,485 ft (757 m)

CESSNA 185 SKYWAGON

General characteristics

 Crew: one
 Capacity: five passengers
 Length: 25 ft 9 in (7.85 m)
 Wingspan: 35 ft 10 in (10.92 m)
 Height: 7 ft 9 in (2.36 m)
 Wing area: 174 sq ft (16.2 m2)
 Empty weight: 1,748 lb (793 kg)
 Gross weight: 3,350 lb (1,520 kg)
 Powerplant: 1 × Continental IO-520-D , 300 hp (220 kW)
 Propellers: 2-bladed constant speed, 6 ft 10 in (2.08 m) diameter

Performance

 Maximum speed: 155 kn (178 mph, 287 km/h)
 Cruise speed: 145 kn (167 mph, 269 km/h)
 Stall speed: 49 kn (56 mph, 91 km/h)

 Range: 720 nmi (830 mi, 1,330 km)
 Service ceiling: 17,150 ft (5,230 m)
 Rate of climb: 1,010 ft/min (5.1 m/s)
 Wing loading: 19.3 lb/sq ft (94 kg/m2)

Specification for differing configurations[edit]

Landplane Floatplane Amphibian

Length 27 ft 0 in (8.23 m) 27 ft 6 in (8.38 m)

Height 12 ft 2 in (3.71 m) 12 ft 8 in (3.86 m)

Empty weight 1,745 lb (792 kg) 1,910 lb (866 kg) 2,165 lb (982 kg)

MTOW 3,320 lb (1,506 kg) 3,265 lb (1,481 kg) on land
3,100 lb (1,406 kg) on water

Max. speed 136 knots (252 km/h) 141 knots (261 km/h) 135 knots (251 km/h)

Range 516 nm (957 km) 503 nm (933 km) 482 nm (893 km)

Service ceiling 16,400 ft (5,000 m) 15,300 ft (4,700 m)

Rate of climb 960 ft/min (293 m/min) 970 ft/min (296 m/min)

Wing loading 19.1 lb/ft2(93.3 kg/m2) 18.8 lb/ft2(91.8 kg/m2)

CESSNA 206

General characteristics

 Crew: one
 Capacity: five passengers
 Length: 28 ft 3 in (8.61 m)
 Wingspan: 36 ft 0 in (10.97 m)
 Height: 9 ft 3 1⁄2 in (2.832 m)
 Wing area: 175.5 sq ft (16.30 m2)
 Empty weight: 2,176 lb (987 kg)
 Max takeoff weight: 3,600 lb (1,633 kg)
 Powerplant: 1 × Lycoming IO-540-AC1A naturally aspirated air-cooled flat-six engine,

300 hp (220 kW)
 Propellers: 3-bladed McCauley metal constant-speed propeller

Performance

 Maximum speed: 174 mph (280 km/h, 151 kn) at sea level
 Cruise speed: 163 mph (262 km/h, 142 kn) at 6,200 ft (1,900 m) (75% power)
 Stall speed: 63 mph (101 km/h, 55 kn) (flaps down)
 Range: 840 mi (1,350 km, 730 nmi) at 6,500 ft (2,000 m) (max fuel, 45 min reserves)
 Service ceiling: 15,700 ft (4,800 m)
 Rate of climb: 988 ft/min (5.02 m/s)


DORNIER 328

General characteristics

 Crew: 3 (2 Pilots, one Flight Attendant)
 Capacity: 30 to 33 (14 in First Class Config) / 4,890 kg (10,781 lb) payload
 Length: 21.23 m (69 ft 8 in)
 Wingspan: 20.98 m (68 ft 10 in)
 Height: 7.05 m (23 ft 2 in)
 Wing area: 40 m2 (430 sq ft)
 Airfoil: Do A-5 [54]
 Empty weight: 9,100 kg (20,062 lb)
 Max takeoff weight: 13,990 kg (30,843 lb)
 Powerplant: 2 × Pratt & Whitney Canada PW119B turboprop engines, 1,625 kW (2,179 hp)

each

Performance

 Cruise speed: 620 km/h (390 mph, 330 kn)
 Range: 1,852 km (1,151 mi, 1,000 nmi)
 Service ceiling: 9,492 m (31,142 ft)

DE HAVILLAND CANADA DHC-6 TWIN OTHER

Series 100[84] 300[84] 400[85]

Cockpit crew 1–2

Seating 20 19

Length 49 ft 6 in (15.09m) 51 ft 9 in (15.77 m)

Height 19 ft 6 in / 5.94 m

Wing 65 ft 0 in (19.81 m) span, 420 sq ft (39 m2) area (10.05 AR)

Empty weight 5,850l lb / 2,653 kg 7,415 lb / 3,363 kg 7,100 lb / 3,221 kg (no
accommodation)

MTOW 10,500 lb / 4763 kg 12,500 lb / 5,670 kg[a]

payload 975 kg (2150 lb) over 1135 kg (2500 lb) over 4,061 lb / 1,842 kg over
1344 km (727nmi) 1297 km (700 nm) 100 nmi (185 km)

860 kg (1900 lb) over 3,031 lb / 1,375 kg over
1705 km (920 nm)[b] 400 nmi (741 km)

Fuel capacity 378 US gal /
1466 L,[b]2,590 lb /

1,175 kg

Turboprops P&WC PT6A-20 PT6A-27 PT6A-34
(×2)

Unit Power 431 kW / 578shp 460 kW / 620shp 559 kW (750 hp)

Max. Cruise 297 km/h / 160kn 338 km/h / 182kn 337 km/h (182 kn) (FL100)

Takeoff to 1,200 ft / 366 m
50 ft

Landing from 1,050 ft / 320 m
50 ft

Stall Speed 65 mph

Ferry Range 771 nmi / 1,427 km 799 nmi / 1480 km[c]

Endurance 6.94 h[c]

Ceiling 25,000 ft / 7,620 m

Climb rate 1,600 ft/min (8.1 m/s)

FL100 fuel 468.2 lb (212.4 kg)/hour
burn 0.311 nmi/lb (1.27 km/kg)
146 kn

(270 km/h)

Power/mass 0.11 hp/lb (0.18 kW/kg) 0.1 hp/lb (0.16 kW/kg) 0.12 hp/lb (0.20 kW/kg)

DE HAVILLAND CANADA DASH 8

Specifications[edit]

Model Q200[90] Q300[91] Q400[92]
2 2-3
Cockpit crew
1-2
Cabin crew 1

Passengers, typical 37 50@30–33"[93] 82@30"

Max capacity[94] 40 56 90@28"

Length 73 ft / 22.25 m 84 ft 3 in / 25.70 m 107 ft 9 in / 32.8 m

Height 24 ft 7 in / 7.49 m 27 ft 5 in / 8.4 m

Wingspan 85 ft / 25.89 m 90 ft / 27.4 m 93 ft 3 in / 28.4 m

Wing area 585 ft² / 54.40 m2 605 ft² / 56.20 m2 689 ft² / 64 m2

Aspect ratio 12.32 13.36 12.6

Width Fuselage 8 ft 10 in / 2.69 m, cabin 8 ft 3 in / 2.52 m

Cabin length 30 ft 1 in / 9.16 m 41 ft 6 in / 12.60 m 61 ft 8 in / 18.80 m

Max takeoff 36,300 lb / 43,000 lb / 19,505 kg 67,200 lb / 30,481 kg
16,466 kg

Operating empty 23,098 lb / 26,000 lb / 11,793 kg 39284 lb / 17819 kg [95]
10,477 kg

Max payload 8,921 lb / 4,647 kg 13,500 lb / 6,124 kg 18,716 lb / 8,489 kg

Max fuel 835 U.S. gal / 3,160 L 1,724 U.S. gal / 6,526
L[96]

Engines 2 × PW123C/D 2 × PW123/B/E 2 × PW150

Unit power 2,150 hp 2,380–2,500 hp (1,770– 5,071 shp / 3,781 kW
(1,600 kW) 1,860 kW)

High speed cruise 289 kn / 535 km/h 287 kn / 532 km/h 300–360 kn / 556–
667 km/h

Ceiling 25,000 ft / 7,620 m 27,000 ft / 8229 m

Range 1,125 nmi / 924 nmi / 1,711 km 1,100 nmi / 2,040 km
2,084 km

Takeoff (MTOW, SL, 3,280 ft / 1,000 m 3,870 ft / 1,180 m 4,675 ft / 1,425 m
ISA)

Landing (MLW, SL) 2,560 ft / 780 m 3,415 ft / 1,040 m 4,230 ft / 1,289 m

DORNIER D0 28

General characteristics

 Crew: 1 or 2
 Capacity: 12 or 13 passengers
 Length: 11.41 m (37 ft 5 in)
 Wingspan: 15.55 m (51 ft 0 in)
 Height: 3.90 m (12 ft 10 in)
 Wing area: 29.00 m2 (312.2 sq ft)
 Aspect ratio: 8.3:1

 Airfoil: NACA 23018 (modified)
 Empty weight: 2,304 kg (5,079 lb)
 Max takeoff weight: 4,015 kg (8,852 lb)
 Fuel capacity: 893 L (236 US gal; 196 imp gal)
 Powerplant: 2 × Lycoming IGSO-540-A1E air-cooled flat-six engines, 280 kW (380 hp)

each
 Propellers: 3-bladed Hartzell constant-speed propellers

Performance

 Maximum speed: 325 km/h (202 mph, 175 kn) at 3,000 m (10,000 ft)
 Cruise speed: 241 km/h (150 mph, 130 kn) at 10,000 ft (3,000 m) (econ cruise, 50%

power)
 Stall speed: 104 km/h (65 mph, 56 kn) (power off, flaps down)
 Minimum control speed: 65 km/h (40 mph, 35 kn) (power on, flaps down)
 Range: 2,950 km (1,830 mi, 1,590 nmi) (with max fuel)
 Service ceiling: 7,680 m (25,200 ft)
 Rate of climb: 5.3 m/s (1,050 ft/min)



EMBRAER LEGACY 600

Embraer Legacy Brochures

Variant Legacy 600[12] Legacy 650[13]

Crew 2
Passengers 13 / 14
Baggage Capacity 286 cu ft / 8.1 m3

Length 26.33 m / 86 ft 5 in

Wingspan 21.17 m / 68 ft 11 in
Height
6.76 m / 22 ft 2 in
MTOW[14]
BOW[14] 49,604 lb (22,500 kg) 53,572 lb (24,300 kg)
Max Fuel[14]
Max. Payload 30,081 lb (13,645 kg) 31,217 lb (14,160 kg)
Engines
18,170 lb (8,242 kg) 20,600 lb (9,344 kg)
Thrust
5,193 lb / 2,356 kg 4,939 lb / 2,240 kg
Ceiling
Range [a] Rolls-Royce AE 3007A1E Rolls-Royce AE 3007A2

Cruise 7,953 lbf (35.38 kN), 9,020 lbf (40.1 kN),
Maximum Speed ISA+22ºC ISA+15ºC
Takeof (MTOW, SL, ISA)
Landing (Typical LW, SL, 41,000 ft / 12,497 m

ISA) 3,400 nmi / 6,297 km 3,900 nmi / 7,223 km
Avionics
Mach 0.78 (829 km/h; 515 mph)

Mach 0.80 (850 km/h; 528 mph)

5,614 ft / 1,711 m 5,741 ft / 1,750 m

2,685 ft / 818 m 2,842 ft / 866 m

Honeywell Primus Elite

EMBRAER ERJ FAMILY

Variant ERJ135LR[41][42] ERJ140LR[43][44] ERJ145XR[45][46]

Crew 3 (2 pilots + flight attendant)

Seating 37 44 50

Length 26.33 m (86 ft 5 in) 28.45 m (93 ft 4 in) 29.87 m (98 ft 0 in)

Wing span 20.04 m (65 ft 9 in)

Wing 51.18 m2 (550.9 sq ft) area, aspect ratio 7.9, supercritical airfoil[47]

Height 6.76 m (22 ft 2 in)

MTOW 20,000 kg (44,092 lb) 21,100 kg (46,517 lb) 24,100 kg (53,131 lb)

BOW 11,501 kg / 25,355 lb 11,808 kg / 26,032 lb 12,591 kg / 27,758 lb

Max payload 4,499 kg (9,918 lb) 5,292 kg (11,666 lb) 5,909 kg (13,027 lb)

Fuel capacity LR: 4,499 kg (9,919 lb), XR: 5,973 kg (13,168 lb)

Engines (2x) AE 3007-A1/3 AE 3007-A1/3 AE 3007-A1E

Takeoff Thrust A1/3 : 33.71 kN / 7580 lbf; A1E: 39.67 kN / 8917 lbf[48]

Maximum cruise Mach 0.78 (450 kn; 833 km/h) / 145XR: Mach 0.8 (461 kn; 854 km/h)

Service ceiling 37,000 ft / 11,278m[a]

Range 1,750 nmi (3,240 km) 1,650 nmi (3,060 km) 2,000 nmi (3,700 km)

EMBRAER PHENOM 300

General characteristics

 Crew: 1 or 2 pilots
 Capacity: 6 passengers (standard configuration) + 1 in cockpit; maximum of 10

incl.[30] 1 in cockpit and 1 on belted toilet)
 Length: 15.9 m (52 ft 2 in)
 Wingspan: 16.2 m (53 ft 2 in)
 Height: 5 m (16 ft 5 in)
 Max takeoff weight: 8,150 kg (17,968 lb)
 Fuel capacity: 2,428kg[6]
 Pressurization: 9.4 psi (0.65 bar)[31]
 Cabin height: 4.9 ft (1.49 m)[6]
 Cabin width: 5.1 ft (1.55 m)[32]
 Cabin length: 5.23 m (17.2 ft)[6]
 Powerplant: 2 × PW535E1[8] turbofans, 15.471 kN (3,478 lbf) thrust each

Performance

 Maximum speed: 834 km/h (518 mph, 450 kn)
 Range: 3,723 km (2,313 mi, 2,010 nmi) with IFR reserves, 5 occupants
 Service ceiling: 13,716 m (45,000 ft)
 Wing loading: 286 kg/m2 (59 lb/sq ft)
 Fuel burn: 346 kg/h at 364 kt, 456 kg/h at 431 kt (at FL410)[6]
 Take-off distance: 978 m (3,209 ft) MTOW, SL, ISA[29]
 Landing distance: 674 m (2,212 ft) 4 occupants at 200 lb each, NBAA IFR reserves, SL,

ISA

FOKKER F27 FRIENDSHIP

General characteristics

 Crew: 2 or 3
 Capacity: 48-56 passengers
 Length: 25.06 m (82 ft 3 in)
 Wingspan: 29 m (95 ft 2 in)
 Height: 8.72 m (28 ft 7 in)
 Wing area: 70 m2(750 sq ft)
 Empty weight:11,204 kg (24,701 lb)
 Max takeoff weight:19,773 kg (43,592 lb)
 Powerplant: 2 × Rolls-Royce Dart Mk.532-7two-stage centrifugal compressor turboprop,

1,678 kW (2,250 hp) each

Performance

 Cruise speed: 460 km/h (290 mph, 250 kn)
 Range: 2,600 km (1,600 mi, 1,400 nmi)
 Rate of climb: 7.37 m/s (1,451 ft/min)

GIPPSAERO GA8 AIRVAN

General characteristics

 Crew: 1
 Capacity: Seven passengers
 Length: 8.95 m (29 ft 4 in)
 Wingspan: 12.28 m (40 ft 3 in)
 Height: 3.89 m (12 ft 9 in)
 Wing area: 19.32 m2(208.0 sq ft)
 Aspect ratio: 7.9:1
 Empty weight: 997 kg (2,198 lb)
 Max takeoff weight:1,814 kg (3,999 lb)
 Fuel capacity: 340 L (74.8 Imp Gallons)
 Powerplant: 1 × Textron Lycoming IO-540-K1A5 air-cooled flat-six, 220 kW (300 hp)
 Propellers: 2-bladed Hartzell F8475R constant speed propeller

Performance

 Maximum speed: 241 km/h (150 mph, 130 kn) at 1,525 m (5,000 ft)
 Cruise speed: 222 km/h (138 mph, 120 kn) at 3,050 m (10,000 ft)
 Stall speed: 97 km/h (60 mph, 52 kn) (flaps down)
 Range: 1,352 km (840 mi, 730 nmi)
 Endurance: Six hours
 Service ceiling: 6,100 m (20,000 ft)

 Rate of climb: 4.00 m/s (788 ft/min)

STODDARD-HAMILTON GLASAIR II

General characteristics

 Crew: one
 Capacity: one passenger
 Length: 20.8 ft (6.3 m)
 Wingspan: 23.3 ft (7.1 m)
 Wing area: 81.3 sq ft (7.55 m2)
 Airfoil: NASA GA(W)-2
 Empty weight: 1,400 lb (635 kg)
 Gross weight: 2,100 lb (953 kg)
 Fuel capacity: 70 U.S. gallons (260 L; 58 imp gal)
 Powerplant: 1 × Lycoming O-360 four cylinder, air-cooled, four stroke aircraft engine,

180 hp (130 kW)
 Propellers: 2-bladed constant speed propeller

Performance

 Cruise speed: 221 mph (356 km/h, 192 kn)
 Stall speed: 73 mph (117 km/h, 63 kn)