Comparable aircraft:

1. ATP / Jetstream 61

Dimensions, External

Wing span 15.85 m (52 ft 0 in)Wing chord: at root 2.19 m (7 ft 2½ in)    at tip 0.80 m (2 ft 7¼ in)Wing aspect ratio 9.95

Length overall14.37 m (47 ft 1½

in)

Length of fuselage13.40 m (43 ft 11½

in)Height overall 5.38 m (17 ft 8 in)Fuselage: Max diameter

1.98 m (6 ft 6 in)

Tailplane span 6.60 m (21 ft 8 in)Wheel track 5.94 m (19 ft 6 in)Wheelbase 4.60 m (15 ft 1 in)Propeller diameter 2.69 m (8 ft 10 in)Passenger door: Height

1.42 m (4 ft 8 in)

    Width 0.86 m (2 ft 10 in)Emergency exit: Height

0.91 m (3 ft 0 in)

    Width 0.56 m (1 ft 10 in)

Dimensions, Internal

Cabin, excl flight deck: Length 7.39 m (24 ft 3 in)    Max width 1.85 m (6 ft 1 in)    Max height 1.80 m (5 ft 11 in)    Floor area 8.35 m2 (90 sq ft)    Volume (trimmed aircraft) 16.99 m3 (600 cu ft)Baggage compartment volume:    Airliner 2.13-2.74 m3 (75.2-96.7 cu ft)    Corporate 1.34-1.48 m3 (47.2-52.2 cu ft)Baggage pod (optional) 1.39 m3 (49 cu ft)

Areas

Wings, gross 25.20 m2 (271.3 sq ft)

Ailerons, aft of hinge line (total) 1.52 m2 (16.4 sq ft)Trailing-edge flaps (total) 3.25 m2 (35.0 sq ft)Vertical tail surfaces (total) 7.72 m2 (83.1 sq ft)Horizontal tail surfaces (total) 7.80 m2 (84.0 sq ft)

Weights and Loadings

Operating weight empty 4,488 kg (9,894 lb)Baggage pod weight 59 kg (130 lb)Max fuel 1,372 kg (3,024 lb)Max payload 1,805 kg (3,980 lb)Max capacity of baggage pod 197 kg (435 lb)Max T-O weight: standard 6,950 kg (15,322 lb)    US domestic 6,900 kg (15,212 lb)Max ramp weight 7,000 kg (15,432 lb)Max landing weight 6,600 kg (14,550 lb)Max zero-fuel weight 6,300 kg (13,889 lb)Max wing loading 275.8 kg/m2 (56.5 lb/sq ft)Max power loading 4.96 kg/kW (8.15 lb/shp)

Performance(at max T-O weight except where stated)

Max cruising speed at max cruise power at 4,570 m (15,000 ft)

263 kt (488 km/h; 303 mph)

Econ cruising speed at 7,620 m (25,000 ft)

230 kt (426 km/h; 264 mph)

Stalling speed, flaps down 86 kt (159 km/h; 99 mph)Max rate of climb at S/L 635 m (2,080 ft)/minRate of climb at S/L, one engine out 119 m (390 ft)/minCertificated ceiling 7,620 m (25,000 ft)Service ceiling, one engine out 3,660 m (12,000 ft)Min ground turning radius about nosewheel

6.50 m (21 ft 4 in)

T-O field length: BCAR Section D 1,440 m (4,724 ft)T-O to 15 m (50 ft): SFAR 41C 975 m (3,200 ft)

Landing field length, at max landing weight:

    BCAR Section D 1,235 m (4,052 ft)    SFAR 41C/FAR 135 1,165 m (3,820 ft)

Accelerate/stop distance:    SFAR 41C 1,362 m (4,470 ft)Range see individual model listings

Height (m): 5.38Length (m): 14.37Max Level Speed (kts): 263Max Rate Climb (m/min): 635Max T-O Weight (kg): 6950

Max Wing Load (kg/m2): 275.8

Service Ceiling (m): 3660Wing Span (m): 15.85

Range:

Airliner: Designed to carry 18/19 passengers. Able to operate up to 680 n miles (1,260 km; 783 miles) stage length, without refuelling, with 18 passengers, baggage and full IFR reserves.        Corporate: Executive version, designed for 8 to 10 passengers, and able to carry nine passengers and baggage for 1,050 n miles (1,945 km; 1,208 miles) with full IFR reserves. Typical interior has six fully reclining and swivelling chairs, a three-place divan, galley for hot and cold meal service, cocktail cabinet, wardrobe and washroom/toilet.        Executive shuttle: Intended for the large company, shuttling its personnel between factories, or for the business charter market. With typical layout for 12 passengers, this version has a range of 1,050 n miles (1,945 km; 1,208 miles) with full IFR reserves.        Special role: Intended for various specialist applications such as military communications, casualty evacuation, multi-engine training, cargo operations, airfield calibration, resources survey and protection. A patrol version designated Jetstream

Design FeaturesCantilever low-wing monoplane. Wing section NACA 63A418 at root. NACA 63A412 at tip. Dihedral 7º from roots. Incidence 2º at root, 0º at tip. Sweepback 0º 34' at quarter-chord. Cantilever tail unit with fixed-incidence tailplane.

Flying ControlsManually operated alloy Frise ailerons. Hydraulically operated aluminium alloy double-slotted flaps. No slats or leading-edge flaps. Trim tab in each aileron. The tail unit has manually operated control surfaces. Trim tabs in rudder and each elevator.

StructureAluminium alloy fail-safe structure of front, main and rear spars with chordwise

ribs. Wing skins chemically etched and reinforced with bonded spanwise stringers. The fuselage is a conventional aluminium alloy semi-monocoque fail-safe structure with chemically milled skin panels. Nose and tail sections unpressurised. The tail unit is a cantilever two-spar aluminium alloy structure.

Power PlantTwo 701 kW (940 shp) Garret TPE331-10UG turboprops, each driving a Dowty Rotol four-blade variable-pitch and reversible-pitch fully-feathering metal propeller. Fuel in integral tank in each wing, total capacity 1,718 litres (454 US gallons; 378 Imp gallons). Refuelling point on top of each outer wing. Water methanol injection optional.

2. Do 328JET / 328-300

Crew 2Passengers 33

Propulsion 2 Turbofan EnginesEngine Model Pratt & Whitney Canada PW306BEngine Power (each) 26,9 kN 6047 lbf

Speed 737 km/h398 kts  458 mph

Service Ceiling 10.668 m 35.000 ftRate of climb 1125 m/min 3690 ft/min

Range 1.667 km900 NM1.036 mi.

Empty Weight 9.420 kg 20.768 lbsmax. Takeoff Weight 15.660 kg 34.524 lbsmax. Landing Weight 14.390 kg 31.724 lbs

Wing Span 20,98 m 68,8 ftWing Area 40,0 m² 431 ft²Length 21,28 m 69,8 ftHeight 7,24 m 23,8 ft

First Flight 20.01.1998Production Status out of productionTotal Production 211

ICAO Code J328FAA TCDS A55NM

EASA TCDS A.096

Data for (Version) Dornier 328-300Variants Dornier Envoy 3

3. Do 328 / 328-100

Crew 2Passengers 33

Propulsion 2 Turboprop EnginesEngine Model Pratt & Whitney Canada PW119BEngine Power (each) 1625 kW 2179 shp

Speed 620 km/h335 kts  386 mph

Service Ceiling 9.449 m 31.000 ftRate of climb 628 m/min 2060 ft/min

Range 1.852 km1.000 NM1.151 mi.

Empty Weight 8.810 kg 19.423 lbsmax. Takeoff Weight 13.990 kg 30.843 lbsmax. Landing Weight 13.230 kg 29.167 lbs

Wing Span 20,98 m 68,8 ftWing Area 40,0 m² 431 ft²Length 21,28 m 69,8 ftHeight 7,24 m 23,8 ft

First Flight 09.12.1991Production Status out of productionTotal Production 107

ICAO Code D328FAA TCDS A45NMEASA TCDS A.096

Data for (Version) Dornier Do 328-120Variants 328-110, 328-120, 328-130

Aircraft related to project

LET L-410 TURBOLET

TypeTwin-turboprop general purpose light transport aircraft.

Design FeaturesCantilever high-wing monoplane. Wing section NACA 63A418 at root, NACA 63A412 at tip. Dihedral 1º 45'. Incidence 2º at root, 0º 30' at tip. No sweepback at front spar. Vertical tail surfaces swept back 35º. One-piece tailplane, with 7º dihedral from roots, mounted part-way up fin.

Power PlantTwo 544 kW (730 ehp) Walter M 601 B turboprop engines, each driving an Avia V 508 B three-blade reversible-pitch fully feathering metal propeller. At higher ambient temperatures, engine power can be increased to 590 kW (790 ehp) for short periods

by water injection into compressor. De-icing for propeller blades (electrical) and water lower intakes; anti-icing flaps inside each nacelle. Eight bag-type fuel tanks in wings, total capacity 1,290 litres (341 US gallons; 284 Imp gallons). Total oil capacity (including oil in cooler) 22 litres (5.75 US gallons; 4.8 Imp gallons). Water tank capacity (for injection into compressor) 11 litres (2.8 US gallons; 2.4 Imp gallons).

Dimensions, External

Wing span 19.478 m (63 ft 10¾ in)Wing chord at root 2.534 m (8 ft 3¾ in)Length overall 14.467 m (47 ft 5½ in)Fuselage: Max width 2.08 m (6 ft 10 in)    Max depth 2.10 m (6 ft 10¾ in)Height overall 5.829 m (19 ft 1½ in)Tailplane span 6.736 m (22 ft 1¼ in)Wheel track 3.65 m (11 ft 11½ in)Wheelbase 3.666 m (12 ft 0¼ in)Propeller diameter 2.50 m (8 ft 2½ in)Distance between propeller centres 4.816 m (15 ft 9½ in)Passenger/cargo door (port, aft):    Height 1.46 m (4 ft 9½ in)    Width overall 1.25 m (4 ft 1 in)    Width (passenger door only) 0.80 m (2 ft 7½ in)    Height to sill 0.79 m (2 ft 7 in)Emergency exit door (stbd, fwd):    Height 0.97 m (3 ft 2¼ in)    Width 0.66 m (2 ft 2 in)

Areas

Wings, gross 35.18 m2 (378.67 sq ft)Ailerons (total) 2.89 m2 (31.11 sq ft)Automatic bank control flaps (total) 0.49 m2 (5.27 sq ft)Trailing-edge flaps (total) 5.92 m2 (63.72 sq ft)Spoilers (total) 0.87 m2 (9.36 sq ft)Fin 4.49 m2 (48.33 sq ft)Rudder, incl tab 2.7 m2 (29.1 sq ft)Tailplane 6.53 m2 (70.29 sq ft)Elevators, incl tabs 3.03 m2 (32.61 sq ft)

Weights and Loadings

Basic empty weight 3,800 kg (8,377 lb)Max fuel 1,000 kg (2,205 lb)Max payload 1,310 kg (2,888 lb)

Max T-O weight 5,800 kg (12,787 lb)Max landing weight 5,500 kg (12,125 lb)Max zero-fuel weight 5,270 kg (11,618 lb)

Performance(at max T-O weight, ISA, except where indicated)

Max operating speed 194 kt (360 km/h; 224 mph) EASMax cruising speed at 3,000 m (10,000 ft) 197 kt (365 km/h; 227 mph) TASEcon cruising speed at 3,000 m (10,000 ft) 162 kt (300 km/h; 186 mph) TASStalling speed:    flaps up 75 kt (139 km/h; 86.4 mph) EAS    flaps down, at max landing weight

63 kt (117 km/h; 72.7 mph) EASMax rate of climb at S/L 468 m (1,535 ft)/minRate of climb at S/L, one engine out 90 m (295 ft)/minMax operating altitude 6,000 m (19,700 ft)Service ceiling, one engine out 2,850 m (9,350 ft)T-O run 400 m (1,312 ft)T-O to 10.5 m (35 ft) 520 m (1,706 ft)Landing from 9 m (30 ft) at max landing weight

810 m (2,657 ft)

Landing run at max landing weight 328 m (1,000 ft)Range at 3,000 m (9,850 ft) with max fuel and 850 kg (1,874 lb) payload, 30 min reserves

561 n miles (1,040 km; 646 miles)

Range with max payload and 505 kg (1,113 lb) fuel, 30 min reserves

248 n miles (460 km; 285 miles)

Height (m): 5.829

Length (m): 14.467

Max Level Speed (kts): 194

Max Range (nm): 561

Max Rate Climb (m/min): 468

Max T-O Weight (kg): 5800

Service Ceiling (m): 6000

T-O Run (m): 400

Landing Run (m): 328

Wing Span (m): 19.478