aircraft specs-1

3rd Year Design Project Comparable Aircraft

LET L-410 TURBOLET

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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) EAS

Max cruising speed at 3,000 m (10,000 ft) 197 kt (365 km/h; 227 mph) TAS

Econ cruising speed at 3,000 m (10,000 ft) 162 kt (300 km/h; 186 mph) TAS

Stalling 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) EAS

Max rate of climb at S/L 468 m (1,535 ft)/min

Rate of climb at S/L, one engine out 90 m (295 ft)/min

Max 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

Aerospatiale N-262 Fregate & Mohawk 298http://www.aero.pub.ro/wp-content/themes/aero.pub.ro/uploads/JANE_S_ALL_THE_WORLD_S_AIRCRAF/JANE_S_AIRCRAFT_UPGRADES/jau_0693.htm

TypeTwin-engined light transport aircraft.

Versions262 Series A: Preceded by Series B Standard early production version, with 805 kW (1,080 ehp Bastan) VIC turboprop engines. Received FAA Type Approval on 15 March 1965. First production Series A was airframe number 9 in production (F-WLHX), delivered to Lake Central Airlines on 17 August 1965. 262 Series B: Designation of first four production aircraft only, built for Air Inter. Same power plant as Series A. First Series B (F-BLHS, airframe number 4) flown for first time on 8 June 1964. Received SGAC certification on 16 July 1964. Entered service 24 July 1964. Frégate (formerly 262 Series C and D): Version for both civil and military use, with more powerful Bastan VII turboprop engines, having improved single-engine ceiling,



cruising speed and T-O performance at `hot-and-high' airfields. Power plant dispenses with water-methanol system of Series A and B and has higher initial TBO. A 262 (airframe number 36) began flying experimentally with Bastan VIIA engines in July 1968, and was also test-flown with different wingtips which bestow improved low-speed handling. The Frégate entered production in 1970, alongside the Series A, from the 64th aircraft for Series D, from the 74th aircraft for Series C. Certification granted 24 December 1970. 262 E: Converted 262As for navigation and flight engineer training. Aircraft also used for inshore surveillance.

Design FeaturesCantilever high-wing monoplane. Wing section NACA 23016 (modified) at root, NACA 23012 (modified) at tip. Dihedral 3º from root. Incidence 3º. No sweepback. Cantilever tail unit. Fixed incidence tailplane.

Flying ControlsSealed all-metal ailerons. Balance tab in starboard aileron. Electrically controlled hydraulically actuated all-metal three-position flaps in inner and outer sections on each trailing-edge. Tail unit control surfaces fabric-covered. One controllable tab and one balance tab in rudder and each elevator.

StructureThe wing is an all-metal two-spar fail-safe structure in conventional light alloys. The fuselage is a light-alloy fail-safe semi-monocoque structure built up from 39 circular main and secondary frames covered with skin panels arranged circumferentially in sets of four. The tail unit is a metal structure built as a separate unit and bolted to rear fuselage frame.

Landing GearRetractable tricycle type, designed and manufactured by ERAM, with single wheel on each unit. Electrohydraulic retraction, nosewheel forward, mainwheels rearward into fairings on sides of fuselage. ERAM oleo-pneumatic nitrogen-filled shock-absorbers. Mainwheels have Dunlop or Kléber-Colombes tyres size 12.50-16, pressure 4.00 bars (58 lb/sq in). Nosewheel has Goodyear Type 06 tyre, size 9.00-6, pressure 3.50 bars (51 lb/sq in). Goodyear hydraulic disc brakes, with anti-skid units. Self-centring nosewheel is fitted with shimmy damper and is steerable hydraulically.

Power Plant(Frégate)

Two 854 kW (1,145 ehp) Turbomeca Bastan VII turboprop engines, each driving a Ratier Forest FH 206-1 four-blade constant-speed fully feathering metal propeller. Six bag-type flexible fuel tanks between wing spars, forming two groups of three tanks with provision for cross-feed and having a total usable capacity of 2,000 litres (528 US gallons; 440 Imp gallons). Provision for two additional optional bag tanks in wing centre-section, each of 285 litres (75 US gallons; 62.5 Imp gallons) usable capacity, giving a maximum usable capacity of 2,570 litres (678 US gallons; 565 Imp gallons). Refuelling point above outer wing tank on each side. Pressure refuelling point at front of starboard side main landing gear fairing. No fuel dump system. Oil capacity 23 litres (6 US gallons; 5 Imp gallons). Electrical anti-icing of engine intakes, spinners and propellers, with additional anti-icing of intakes by engine bleed air.

AccommodationCrew of two on flight deck, with central jump-seat at rear for a third crew member if carried. Standard airline version has seating for 26 passengers at 810 mm (32 in) pitch; maximum seating for 29 at 710 mm (28 in) pitch, in three-abreast rows, with two seats on starboard side of aisle and single seat on port side. Movable forward bulkhead, to cater for variable mixed cargo (in front)/passenger (at rear) layouts. Bulkhead can be located in two intermediate positions, to provide 20 or 14 seats at 810 mm (32 in) pitch in rear of cabin, with 9.7 m3 (342 cu ft) or 13.2 m3 (467 cu ft) of cargo space respectively in front part of cabin. Galley, toilet and (on 26-seat version) separate coat space at rear of cabin. For quick-change passenger/cargo operation, foldaway seats can be installed which, when folded, give an available width for cargo of 1.68 m (5 ft 6 in) throughout entire cabin length. Alternative layouts include a six-person executive suite forward with 10 passengers aft; ambulance version with accommodation for 12 stretchers and two medical attendants; or aerial survey version with wide range of cameras and survey equipment and fully equipped darkroom. Military versions can be fitted out to carry 18 paratroops or 29 troops, or as 22-seat utility transports. Naval versions (Series A) can be equipped for target towing, artillery and missile observation, radar calibration or crew training duties. Standard transport versions have two-section passenger door at rear on port side, the lower half of which has built-in airstairs, and a large cargo door at front on the port side. Emergency exits at front of cabin on each side, at rear on starboard side and on port side of flight deck. Standard baggage compartments between flight deck and cabin on each side. All accommodation is pressurised, soundproofed and air conditioned. Windscreen has electrical anti-icing.

SystemsSEMCA air conditioning system using bleed air from engine. Maximum pressure differential 0.29 bars (4.20 lb/sq in). Auxiliary ventilation via ram air inlet at front of port main landing gear fairing. Hydraulic system, operated by two engine-driven pumps at pressure of 207 bars (3,000 lb/sq in), actuates landing gear, nosewheel steering, flaps, brakes and gust locks. Electrically driven (27 V DC) back-up pump and 100 bars (1,450 lb/sq in) surge accumulator. Hand pump for emergency operation of flaps, landing gear and gust locks. Kléber-Colombes (Goodrich licence) pneumatic de-icing boots on wing outer leading-edges and tail unit leading-edges. Two 24/27 V 40 Ah Ni/Cd batteries, in rear fuselage, and two 9 kVA engine-driven starter/generators provide 28 V DC electrical supply for engine starting, feathering pumps and rotary inverters. External 28 V DC power receptacle. AC system includes two engine-driven 12 kVA three-phase alternators providing 115/200 V 400 Hz power for engine anti-icing, windscreen heating and anti-icing, and heating for galley. Two single-phase 750 VA rotary inverters provide continuous 115 V 400 Hz AC supply for flight deck instruments. System also includes four 115/26 V 400 Hz auto-transformers. Optional APU, in port landing gear fairing, provides power for electrical services, engine starting and cabin air conditioning.

EquipmentStandard equipment includes two Collins 618 M 1 VHF, two Collins 51 RV 1 VOR/ILS, Collins 51 Z 4 marker beacon receiver, Collins DF 203 ADF, Collins 331 A6A course indicator, SFIM A 213 flight recorder, Sperry C 14 gyrocompass, two Allen RMI, one Bendix OMI, interphone and public address systems. Emergency equipment includes oxygen masks and cylinders, fire extinguishers, liferafts and emergency radio. Optional equipment includes HF radio, autopilot, second gyro compass, second ADF, weather radar, ATC transponder, radio altimeter and DME; and choice of flight director/recorder, VHF, VOR/ILS and marker beacon receiver.

Dimensions, External(Frégate)

Wing span 22.60 m (74 ft 1¾ in)

Wing chord: at root 3.10 m (10 ft 2 in)

at tip 1.80 m (5 ft 10¾ in)

Wing aspect ratio 9.10

Length overall 19.28 m (63 ft 3 in)

Height overall 6.21 m (20 ft 4½ in)

Fuselage: Max diameter 2.45 m (8 ft 0½ in)

Tailplane span 8.80 m (28 ft 10½ in)

Wheel track 3.13 m (10 ft 3 in)

Wheelbase 7.23 m (23 ft 9 in)

Propeller diameter 3.20 m (10 ft 6 in)

Distance between propeller centres 5.91 m (19 ft 4¾ in)

Passenger door (rear, port): Height 1.66 m (5 ft 5¼ in)


Height to sill 1.08 m (3 ft 6½ in)

Cargo door (fwd, port): Height 1.53 m (5 ft 0¼ in)

Width 1.28 m (4 ft 2½ in)

Height to sill 1.08 m (3 ft 6½ in)

Emergency exit doors (fwd, port and stbd):



Emergency exit door (aft, stbd):



Dimensions, Internal

Cabin, incl baggage space and toilet:

Length 10.61 m (34 ft 10 in)

Max width 2.15 m (7 ft 1 in)

Width at floor 1.66 m (5 ft 5¼ in)

Max height 1.80 m (5 ft 10¾ in)

Floor area 17.0 m2 (183 sq ft)

Volume 32.5 m3 (1,146 cu ft)

Baggage hold: port 1.9 m3 (67 cu ft)

stbd 2.6 m3 (92 cu ft)

Areas(Frégate)

Wings, gross 55.79 m2 (601 sq ft)



Fin 10.1 m2 (108.7 sq ft)

Rudder, incl tabs 3.75 m2 (40.4 sq ft)


Elevators, incl tabs 4.54 m2 (48.8 sq ft)

Weights and Loadings(Frégate)

Basic weight empty 6,200 kg (13,668 lb)

Manufacturer's weight empty, equipped 6,959 kg (15,342 lb)

Basic operating weight 7,225 kg (15,928 lb)



Max ramp weight 10,850 kg (23,920 lb)



Max wing loading 193 kg/m2 (39.5 lb/sq ft)

Max power loading 6.32 kg/kW (10.2 lb/ehp)

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

Max level speed 225 kt (418 km/h; 260 mph)

Max and econ cruising speed 220 kt (408 km/h; 254 mph)

Normal operating limit speed 214 kt (397 km/h; 247 mph)

Max speed: with landing gear extended 154 kt (285 km/h; 177 mph)

with 15º flap 143 kt (265 km/h; 165 mph)

with 35º flap 127 kt (235 km/h; 146 mph)

Final approach speed 90 kt (167 km/h; 104 mph)

Stalling speed: flaps up, at max landing weight 86 kt (159 km/h; 99 mph)

wheels and flaps down, at max landing weight

74 kt (136 km/h; 85 mph)


Service ceiling 8,690 m (28,500 ft)

Service ceiling, one engine out, at AUW of 9,525 kg (21,000 lb)

4,920 m (15,000 ft)

Min ground turning radius 8.0 m (26 ft 3 in)

Runway LCN at max weight 8

T-O run 570 m (1,870 ft)

T-O to 10.7 m (35 ft) 1,070 m (3,510 ft)

Landing from 15 m (50 ft) 530 m (1,740 ft)

Range: with max fuel, no reserves 1,295 n miles (2,400 km; 1,490 miles)

with max fuel, FAA reserves 985 n miles (1,825 km; 1,135 miles)

with 26 passengers and baggage, no reserves 780 n miles (1,450 km; 900 miles)

with 26 passengers and baggage, FAA reserves

550 n miles (1,020 km; 633 miles)

UPDATED Aerospatiale (Nord) 262 Frégate twin-engined light transport aircraft (Aerospatiale)(1998)Aerospatiale (Nord) 262 Frégate twin-engined light transport aircraft of the French Air Force (Aerospatiale)(1996)

Height (m): 6.21

Length (m): 19.28


Max Range (nm): 1295



Max Wing Load (kg/m2): 193


T-O Run (m): 570


ATR 42

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Regional Airliner

The ATR 42 is a twin-engined turboprop-powered regional airliner with a capacity of maximum 50 passengers produced by the French/Italian manufacturer ATR, Avions de Transport Regional, a joint-venture of EADS and Alenia Aeronautica.

Crew 2Passengers 46 - 50 Propulsion 2 Turboprop EnginesEngine Model Pratt & Whitney Canada PW120Engine Power (each) 1529 kW 2050 shp

Speed 491 km/h265 kts 305 mph

Service Ceiling 7.620 m 25.000 ft

Range 1.150 km621 NM715 mi.

Empty Weight 10.285 kg 22.675 lbsmax. Takeoff Weight 16.700 kg 36.817 lbs Wing Span 24,57 m 80,6 ftWing Area 54,5 m² 587 ft²Length 22,67 m 74,4 ftHeight 7,59 m 24,9 ft First Flight 16.08.1984Production Status in production FAA TCDS A53EUEASA TCDS A.084Data for (Version) ATR 42-300

Variants 42-300, 42-320, 42-400, 42-500, 42-600

RemarksCurrent version is the ATR 42-500.

ATP / Jetstream 61


TypeLight commuter executive transport.

ProgrammeDevelopment of this current version of the Jetstream was launched by British Aerospace on 5 December 1978. A development aircraft (G-JSSD), converted from a Jetstream 1 built by Handley Page, flew for the first time on 28 March 1980. Full production go-ahead was given in January 1982, and the first production Jetstream 31 (G-TALL) made its first flight on 18 March 1982. On 29 June 1982, the Jetstream 31 was certified to BCAR Section D in the UK. US certification under SFAR 41C followed on 30 November 1982. German (LBA) certification was gained in July 1983, Australian (DOA) certification in February 1984, Swedish (BCA) in December 1984, Dutch (RLD) in January 1985 and Canadian (TC) in May 1987. First deliveries, to customers in Germany and the UK, took place in December 1982, and the 200th delivery was made on 3 October 1988.

VersionsAirliner: 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 31EZ was developed for operation in exclusive economic zones (for example, offshore patrol and surveillance), with underbelly 360º scan radar, increased fuel, observation windows and searchlight. Two aircraft, specially equipped with Tornado IDS avionics, were delivered to the Royal Saudi Air Force in November 1987 for navigator training. Jetstream Super 31: Announced at 1987 Paris Air Show; certified in FAA's 19-seat commuter category (formulated under FAR Pt 23-24) 30 September 1988; also certified by CAA 6 September 1988 under International Public Transport Category of BCAR section D; also certified in Canada February 1989, Australia 1990, Switzerland April 1990 and Japan April 1991. Jetstream 32: Alternative designation for the Jetstream Super 31. Jetstream T. Mk 1: Royal Air Force crew trainer aircraft powered by two Turboméca Astazou engines. Jetstream T. Mk 2: Royal Navy crew trainer aircraft powered by two Turboméca Astazou engines. Jetstream T. Mk 3: Training version, in service with the Royal Navy. Eyebrow windows above flight deck windscreen to improve all-round view. Interior fitted with two observer training consoles with radar indicator, TANS computer and Doppler. Racal ASR 360 search radar mounted under the fuselage. Four ordered in April 1984, for operation by No. 750 Naval Air Squadron based at Culdrose, Cornwall, for helicopter observer training. All delivered by October 1986.

UpgradesBAe Asset Management-Jets: Developed the Jetstream 32EP programme to enhance the payload and runway performance of the Jetstream 32 (also known as Jetstream Super 31). Jetstream: Developed programme to extend the Jetstream 31 to 45,000 cycles. BAe has also indicated that if the economics became viable the aircraft could be extended to 67,000 cycles.

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.

Landing GearRetractable tricycle type, with nosewheel steering (±45º). Hydraulic retraction, mainwheels

inward into wings, twin nosewheels forward. British Aerospace oleo-pneumatic shock-absorbers in all units. Dunlop wheels and tyres; mainwheel tyre size 28 × 9.00-12, pressure 3.93 bars (57 lb/sq in); nosewheel tyres size 6.00-6, pressure 2.34 bars (34 lb/sq in). Anti-skid units.

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.

AccommodationTwo seats side by side on flight deck, with provision for dual controls, though aircraft can be approved (subject to local regulations) for single pilot operation. Main cabin can be furnished in commuter layout for up to 19 passengers at 76/79 cm (30/31 in) pitch, or with executive interior for 8/10 passengers, but optional layouts are available, including a QC (Quick Change) option enabling an operator to change from an 18-seat layout to 12-seat executive configuration in around 1 hour 15 minutes. Downward-opening passenger door, with integral airstairs, at rear of cabin on port side. Emergency exit over wing on starboard side. Baggage compartment in rear of cabin, aft of main door. Entire accommodation pressurised, heated, ventilated and air conditioned. Toilet standard; galley and bar optional. Jetstream completion is by Field Aircraft at East Midlands Airport, Castle Donington, UK.

SystemsAir conditioning system with cabin pressurisation at maximum differential of 0.38 bars (5.5 lb/sq in), providing a 2,440 m (8,000 ft) cabin altitude at 7,620 m (25,000 ft). Single hydraulic system, pressure 138 bars (2,000 lb/sq in), with two engine-driven pumps, each capable of supplying 20.7 litres (5.46 US gallons; 4.55 Imp gallons)/min. One pump is capable of supplying all hydraulic systems. Combined air/oil reservoir, pressurised to 1.24 bars (18 lb/sq in), for main and emergency supply, for actuation of flaps, landing gear, brakes and nosewheel steering. APU optional. Goodrich rubber de-icing system for leading-edges.


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)



Length of fuselage 13.40 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)




Passenger door: Height 1.42 m (4 ft 8 in)


Emergency exit: Height 0.91 m (3 ft 0 in)



Cabin, excl flight deck: Length 7.39 m (24 ft 3 in)


Max height 1.80 m (5 ft 11 in)


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


Ailerons, aft of hinge line (total) 1.52 m2 (16.4 sq ft)


Vertical tail surfaces (total) 7.72 m2 (83.1 sq ft)

Horizontal tail surfaces (total) 7.80 m2 (84.0 sq ft)


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 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 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)



Certificated ceiling 7,620 m (25,000 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

VERIFIED Jetstream 31 T. Mk 3 training aircraft of the Royal Navy(1995)Jetstream 41 following role conversion into multirole maritime patrol aircraft (FR Aviation)(1999)BAe Jetstream T. Mk 1 crew trainer in service with the Royal Air Force (Paul Tompkins)(1997)BAe Jetstream Super 31 twin-turboprop commuter/executive light transport (Jane's/Mike Keep)(1998)

Height (m): 5.38

Length (m): 14.37




Max Wing Load (kg/m2): 275.8





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Do 328JET / 328-300

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Regional Airliner

The Dornier 328JET / Do 328-300 is a twin-engined regional jet airliner with a capacity of maximum 33 passengers produced by the German manufacturer Fairchild-Dornier.

Crew 2Passengers 33 Propulsion 2 Turbofan EnginesEngine Model Pratt & Whitney Canada PW306BEngine Power (each) 26,9 kN 6047 lbf


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 ft

Height 7,24 m 23,8 ft First Flight 20.01.1998Production Status out of productionTotal Production 211 ICAO Code J328FAA TCDS A55NMEASA TCDS A.096 Data for (Version) Dornier 328-300Variants Dornier Envoy 3

RemarksThe 328JET is a development of the turboprop powered Dornier 328-100.

Do 328 / 328-100

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Regional Airliner

The Dornier 328 / 328-100 is a twin-engined regional airliner with a capacity of maximum 33 passengers produced by the German manufacturer Dornier GmbH, later Fairchild-Dornier.

Crew 2Passengers 33 Propulsion 2 Turboprop EnginesEngine Model Pratt & Whitney Canada PW119BEngine Power (each) 1625 kW 2179 shp


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

Saab 340

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Saab 340B Variant

Crew 2Passengers 35 Propulsion 2 Turboprop EnginesEngine Model General Electric CT7-9BEngine Power (each) 1394 kW 1869 shp



Range 1.685 km910 NM1.047 mi.

Empty Weight 8.035 kg 17.714 lbsmax. Takeoff Weight 13.063 kg 28.799 lbs Wing Span 21,44 m 70,3 ftWing Area 41,8 m² 450 ft²Length 19,73 m 64,7 ftHeight 6,87 m 22,5 ft First Flight 25.01.1983Production Status out of productionTotal Production 459 EASA TCDS A.068 Data for (Version) Saab 340B

RemarksDeveloped together with Fairchild

SAAB 340A Variant


TypeTwin-turboprop regional transport aircraft.

ProgrammeFirst details of the 340, then called Saab-Fairchild 340, were announced January 1980 and the go-ahead on joint design, development, manufacture and marketing was given in September 1980. Saab took complete control of the programme in November 1985 and Fairchild continued as a subcontractor until 1987, when the designation was changed to Saab 340. The first prototype (SE-ISF) made the first flight on 25 January 1983. The fourth (first production) 340A (SE-E04) flew 5 March 1984. The USA and 10 European nations took part in the joint certification process to FAR/JAR 25, resulting in Swedish certification May 1984 and virtually simultaneous certification by the other countries in June. The 340A first went into service, with Crossair, in June 1984 and the first in the USA entered service in August that year. The first corporate 340A was delivered in November 1985. From mid-1985, engine power was increased from 1,215 kW (1,630 shp) to 1,294 kW (1,735 shp) and propeller diameter was increased. Earlier aircraft were retrofitted. An improved cabin with new lining and larger overhead bins, plus improved fittings, was introduced in mid-1988. It was designed and fitted by Metair Aircraft of the UK, meeting the FAA fire resistance standards that became mandatory August 1990. The 340B hot-and-high version was announced late 1987 and replaced the 340A on the production line from c/n 160. It was certificated on 3 July 1989 and the first aircraft was delivered to Crossair in September 1989. By 1 February 1991, firm orders for the 340A and B totalled 354, of which more than half were for US customers and the rest for Europe, Australia, Southeast Asia and South America. The 200th 340 was handed over 14 August 1990, and a total of 229 340As and 340Bs had been delivered by 31 March 1991. The Saab board of directors decided to terminate the programme by mid-1999.

UpgradesUltra Electronics: Installation of Active Noise Control (ANC) systems as retrofit programme. See separate entry in UK section.

Design FeaturesCantilever low-wing monoplane. Basic wing section NASA MS(1)-0313 with thickness/chord ratios of 16 and 12 per cent at root and tip respectively. Dihedral 7º from roots. Incidence 2º at root. Sweepback 3º 36' at quarter-chord. The tail unit is a cantilever structure, with sweptback vertical and non-swept horizontal surfaces, the latter having marked dihedral.

Flying ControlsHydraulically actuated single-slotted trailing-edge flaps with aluminium alloy spars, honeycomb panels faced with aluminium sheet, and leading/trailing-edges of Kevlar. Ailerons have Kevlar skins and glass fibre leading-edges. Electrically operated geared/trim tab in each aileron. Geared trim tab in each elevator; spring trim tab in rudder.

StructureTapered two-spar wings embodying fail-safe principles. Stringers and skins of 2024/7075

aluminium alloy. Wingroot/fuselage fairings of Kevlar sandwich. The fuselage is a conventional fail-safe/safe-life semi-monocoque pressurised metal structure, of circular cross-section. Built in three portions: nose (including flight deck), passenger compartment, and tail section (incorporating baggage compartment). All doors of aluminium honeycomb. Nosecone of Kevlar; cabin floor of carbonfibre sandwich. Fin integral with fuselage. Construction similar to that of wings, with tailplane and fin of aluminium honeycomb. Rudder and elevators have Kevlar skins and glass fibre leading-edges.

Landing GearRetractable tricycle type, of AP Precision Hydraulics design and manufacture, with twin Goodyear wheels and oleo-pneumatic shock-absorber on each unit. Hydraulic actuation. All units retract forward, main units into engine nacelles. Mainwheel doors of Kevlar sandwich. Hydraulically steerable nose unit (60º to both left and right), with shimmy damper. Mainwheel tyres size 24 × 7.7-10, pressure 6.89 bars (100 lb/sq in); nosewheel tyres size 18 × 6.0-6, pressure 3.79 bars (55 lb/sq in). Independent Goodyear carbon hydraulic disc brakes on main units, with anti-skid control.

Power PlantTwo General Electric CT7-5A2 turboprops, each rated at 1,294 kW (1,735 shp). Dowty Rotol four-blade slow-turning constant-speed propellers with full autofeathering and reverse pitch capability, each with spinner and glass fibre/polyurethane foam/carbonfibre moulded blades. Fuel in each tank in each outer wing; total capacity 3,220 litres (850.5 US gallons; 708 Imp gallons). Single-point pressure refuelling inlet in starboard outer wing panel. Overwing gravity refuelling point in each wing.

AccommodationTwo pilots and provision for observer on flight deck; attendant's seat (forward, port) in passenger cabin. Main cabin accommodates up to 35 passengers, in 11 rows of three, with aisle, and rearward-facing seat(s) on starboard side at front. One or both rearward-facing seats can be replaced by an optional galley module and/or baggage/wardrobe module. Seat pitch 76 cm (30 in). Standard provision for galley, wardrobe or storage module on port side at front of cabin, regardless of installations on starboard side. Toilet at front or rear of cabin. In former case, QC operation (conversion from passenger to freight interior or vice versa) is possible. Also available is a VIP to airliner convertible, as well as a fixed-installation combi with 19 passengers and 1,500 kg (3,307 lb) of cargo. Passenger door (plug type) at front of cabin on port side, with separate airstair. Type II emergency exit opposite this on starboard side and Type III over wing on each side. Overhead crew escape hatch in flight deck roof. Baggage space under each passenger seat; overhead storage bins. Main baggage/cargo compartment aft of passenger cabin, with large plug type door on port side. Entire accommodation pressurised, including baggage compartment.

SystemsHamilton Standard environmental control system (maximum pressure differential 0.48 bar; 7.0 lb/sq in) maintains a S/L cabin environment up to an altitude of 3,660 m (12,000 ft) and a 1,525 m (5,000 ft) environment up to the maximum cruising altitude of 7,620 m (25,000 ft). Single, on-demand hydraulic system, operating between 138 and 207 bars (2,000-3,000 lb/sq in), for actuation of landing gear, wheel and propeller braking, nosewheel steering and wing flaps. System is powered by single 28 V DC electric motor driven pump, rated delivery 9.5 litres (2.5 US gallons; 2.1 Imp gallons)/min. Self-pressurising main reservoir with 5.08 litres (0.18 cu ft) capacity, operating at pressure of 1.79-2.69 bars (26-39 lb/sq in). Hydraulic back-

up via four accumulators and pilot-operated handpump, working via an emergency reservoir of 2.5 litres (0.09 cu ft) capacity. Electrical power supplied by two 28 V 400 A DC engine-driven starter/generators, each connected to a separate busbar. Variable frequency 115/200 V for heating circuits provided by two 26 kVA AC generators; single-phase 115 V and 26 V AC at 400 Hz for avionics provided by static inverters. Two 40 Ah Ni/Cd batteries for ground power and engine starting; standby 5 Ah lead-acid battery for emergency use. External power receptacle. Pneumatic boot de-icing of wing and tail unit leading-edges, using engine bleed air. Flight deck windows have electric anti-icing and electrically driven windscreen wipers. Electric anti-icing is provided also for engine air intakes, propellers and pitot heads. Demisting by means of air conditioning system. Plug-in connections for oxygen masks. Kidde engine fire detection system. Duncan/Garrett GTCP 36-150W APU kit certificated for installation as optional extra, to provide standby and emergency electrical power, main engine starting assistance, ground preheating and precooling and other power support functions. Pneumatic boot de-icing of wing leading-edges. Pneumatic boot de-icing of fin and tailplane leading-edges.

AvionicsStandard avionics include all equipment required for FAR 121 operations. Aircraft is equipped with AlliedSignal Gold Crown III or Collins Pro Line II com/nav radios and a Collins integrated digital Flight Guidance and Autopilot System (FGAS) consisting of attitude and heading reference units, electronic (CRT) flight display units, fail-passive autopilot/flight director system, colour weather radar, air data system with servo instruments, and radio altimeter. Lucas Aerospace electroluminescent flight deck instrument panel array. Dowty Aerospace microprocessor-based flight deck central warning system. Rosemount pitot static tubes, total temperature sensors and stall warning system. Provision for additional avionics to customer's requirements.



Wing chord: at root 2.837 m (9 ft 3¾ in)

at tip 1.0645 m (3 ft 5{5/6}in)





Tailplane span 8.67 m (28 ft 5¼ in)



Propeller diameter: initially 3.20 m (10 ft 6 in)

current 3.35 m (11 ft 0 in)

Propeller ground clearance 0.58 m (1 ft 11 in)

Distance between propeller centres 6.71 m (22 ft 0 in)




Cargo door: Height 1.30 m (4 ft 3 in)



Emergency exit (fwd, stbd): Height 1.32 m (4 ft 4 in)


Emergency exits (overwing, each):

Height 0.91 m (3 ft 0 in)


Dimensions, Internal: Cabin, excl flight deck, incl toilet and galley:

Length 10.39 m (34 ft 1 in)


Width at floor 1.70 m (5 ft 7 in)


Volume 33.5 m3 (1,183.0 cu ft)

Baggage/cargo compartment volume 6.8 m3 (240.0 cu ft)

Areas




Fin (incl dorsal fin) 10.53 m2 (113.38 sq ft)

Rudder (incl tab) 2.76 m2 (29.71 sq ft)


Elevators (total, incl tabs) 3.29 m2 (35.40 sq ft)


Typical operating weight empty 7,899 kg (17,415 lb)

Max payload (weight limited) 3,668 kg (8,087 lb)

Max fuel load 2,581 kg (5,690 lb)







Performance(at MTOW, ISA, except where indicated)

Max operating speed (VMO) 250 kt (463 km/h; 288 mph)

Max operating Mach number (MMO) 0.5

Max cruising speed:

at 4,575 m (15,000 ft) 272 kt (504 km/h; 313 mph)

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

250 kt (463 km/h; 288 mph)

Stalling speed: flaps up 104 kt (193 km/h; 120 mph)

T-O flap 93 kt (173 km/h; 107 mph)

approach flap 87 kt (162 km/h; 101 mph)

landing flap 82 kt (152 km/h; 95 mph)



Service ceiling: standard 7,620 m (25,000 ft)

Service ceiling, one engine out (net) 3,960 m (13,000 ft)

FAR Pt 25 required T-O field length:

at S/L 1,212 m (3,975 ft)

at S/L, ISA + 15ºC 1,295 m (4,250 ft)

at 1,525 m (5,000 ft) 1,509 m (4,950 ft)

at 1,525 m (5,000 ft), ISA + 15ºC 1,935 m (6,350 ft)

FAR Pt 25 required landing field length (at MLW):

at S/L 1,180 m (3,870 ft)

at 1,525 m (5,000 ft) 1,335 m (4,380 ft)

Min ground turning radius 15.85 m (52 ft 0 in)

Runway LCN: flexible pavement 8

rigid pavement 10

Range with 35 passengers and baggage, reserves for 45 min hold at 1,525 m (5,000 ft) and 100 n mile (185 km; 115 mile) diversion: at max cruising speed

570 n miles (1,056 km; 656 miles)

at long-range cruising speed 630 n miles (1,167 km; 725 miles)

Range with 30 passengers, reserves as above:

at max cruising speed 845 n miles (1,566 km; 973 miles)

at long-range cruising speed 940 n miles (1,742 km; 1,082 miles)

Operational Noise Levels(FAR Pt 36, and ICAO 16)

T-O (with cutback) 85.7 EPNdB

Sideline 87.6 EPNdB

Approach 89.6 EPNdB

UPDATED Saab 340A twin-turboprop regional transport aircraft(1999)

Height (m): 6.86

Length (m): 19.72


Max Range (nm): 570






EMB 120 Brasilia

http://www.flugzeuginfo.net/acdata_php/acdata_emb120_en.php

Regional Airliner

The EMBRAER EMB 120 Brasilia is a twin-engined regional airliner with a capacity of max. 30 passengers produced by the Brazilian manufacturer Embraer (Empresa Brasileira de Aeronautica, S.A.).

Crew 2

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Passengers 30 Propulsion 2 Turboprop EnginesEngine Model Pratt & Whitney Canada PW118Engine Power (each)

1342 kW 1800 shp



Range 1.750 km945 NM1.087 mi.

Empty Weight 7.070 kg 15.587 lbsmax. Takeoff Weight

11.500 kg 25.353 lbs

Wing Span 19,78 m 64,9 ftWing Area 39,4 m² 424 ft²Length 20,00 m 65,6 ftHeight 6,35 m 20,8 ft First Flight 27.07.1983Production Status out of productionProduction Range 1985 - 2007Total Production 352 ICAO Code E120 Data for (Version) EMBRAER EMB-120 Brasilia

VariantsEMB 120ER, EMB 120FC, EMB 120QC, EMB 120RT, VC-97

DHC-8 Dash 8

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http://www.flugzeuginfo.net/acdata_php/acdata_dhc8_en.php

Regional Airliner

The de Havilland Canada DHC-8 (Dash 8) is a family of regional airliner produced by the Canadian manufacturer de Havilland Aircraft of Canada Ltd., today Bombardier Aerospace.

Crew 2Passengers 39 (78) Propulsion 2 Turboprop EnginesEngine Model

Pratt & Whitney Canada PW120A (PW150A)

Engine Power (each)

1491 (3415) kW 2000 (4580) shp

Speed 496 (669) km/h 268 (361) kts308 (415) mph

Service Ceiling

7.620 m 25.000 ft

Range 1.520 (2.626) km821 (1.418) NM945 (1.632) mi.

Empty Weight

9.979 (17.186) kg 22.000 (37.888) lbs

max. Takeoff Weight

15.650 (29.257) kg 34.502 (64.500) lbs

max. Landing Weight

15.650 (28.009) kg 34.502 (61.750) lbs

Wing Span 25,91 (28,42) m 85,0 (93,2) ftWing Area 54,0 (63,1) m² 581 (679) ft²Length 22,25 (32,84) m 73,0 (107,7) ftHeight 7,49 (8,34) m 24,6 (27,4) ft First Flight 20.06.1983 (31.01.1998)

Production Status

in production

Developed from

de Havilland Canada DHC-7

ICAO Code DH8A, DH8B, DH8C, DH8DIATA Code DH8, DH1, DH2, DH3, DH4FAA TCDS A13NMEASA TCDS A.191other TCDS TC Canada A-142 Data for (Version)

DHC-8 Dash 8 Serie 100 (Q400 DHC-8-402)

Variants

DHC-8-101, DHC-8-102, DHC-8-103, DHC-8-106, DHC-8M-100, CC-142, CT-142, E-9A, DHC-8-201, DHC-8-202, Q200, DHC-8-301, DHC-8-311, DHC-8-314, DHC-8-315, Q300, DHC-8-400, DHC-8-401, DH

RemarksThe DHC-8 is a development of the de Havilland Canada DHC-7 (Dash 7). The current production model is the Bombardier Q400 NextGen.The DHC-8 (Dash 8) Series 100 was the first production version for 39 passengers, powered by PW120A or PW121 engines with 1491 kW (2000 shp).The DHC-8 (Dash 8) Series 200, later Bombardier Q200 is a more powerful version of the Series 100, powered by PW123/PW123A/PW123B engines with 1600 kW (2150 shp).The DHC-8 (Dash 8) Series 300, later Q300 is a stretched version (+ 3,43 m / 11 ft) for 56 passengers, powered by PW123/PW123B/PW123E engines with 1600 kW (2150 shp).The DHC-8 (Dash 8) Series 400, later Q400 is a further stretched version (+6,83m /22ft 5in compared to the Series 300) for 78 passengers, powered by PW150A engines.

Il-14

Airliner / Transport Aircraft

The Ilyushin Il-14 is a twin-engined short-range airliner for max. 36 passengers and transport aircraft developed by the Soviet design bureau Ilyushin OKB.

Crew 4Passengers 24-36 Propulsion 2 Radial EnginesEngine Model Schwetsow / Shvetsov ASh-82TEngine Power (each) 1398 kW 1875 hp



Range 1.306 km705 NM811 mi.

Empty Weight 12.700 kg 28.000 lbsmax. Takeoff Weight 18.000 kg 39.683 lbs Wing Span 31,70 m 104,0 ftWing Area 99,7 m² 1073 ft²Length 22,30 m 73,2 ftHeight 7,90 m 25,9 ft First Flight 1952Production Status out of productionTotal Production ca. 3600 ICAO Code IL14NATO Code Crate Data for (Version) Iljuschin / Ilyushin Il-14M

RemarksThe Il-14 is a development of the Ilyushin Il-12. The Il-14 was also license-built by VEB Flugzeugwerke Dresden in the German Democratic Republic and by Avia in Czechoslovakia as the Avia 14. Standard seating on the Il-14 was 18 to 26 passengers. The stretched variant Il-14M has a capacity of max. 36 passengers.

Jetstream 31/32





TypeLight commuter executive transport.

ProgrammeDevelopment of this current version of the Jetstream was launched by British Aerospace on 5 December 1978. A development aircraft (G-JSSD), converted from a Jetstream 1 built by Handley Page, flew for the first time on 28 March 1980. Full production go-ahead was given in January 1982, and the first production Jetstream 31 (G-TALL) made its first flight on 18 March 1982. On 29 June 1982, the Jetstream 31 was certified to BCAR Section D in the UK. US certification under SFAR 41C followed on 30 November 1982. German (LBA) certification was gained in July 1983, Australian (DOA) certification in February 1984, Swedish (BCA) in December 1984, Dutch (RLD) in January 1985 and Canadian (TC) in May 1987. First deliveries, to customers in Germany and the UK, took place in December 1982, and the 200th delivery was made on 3 October 1988.

VersionsAirliner: 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 31EZ was developed for operation in exclusive economic zones (for example, offshore patrol and surveillance), with underbelly 360º scan radar, increased fuel, observation windows and searchlight. Two aircraft, specially equipped with Tornado IDS avionics, were delivered to the Royal Saudi Air Force in November 1987 for navigator training. Jetstream Super 31: Announced at 1987 Paris Air Show; certified in FAA's 19-seat commuter category (formulated under FAR Pt 23-24) 30 September 1988; also certified by CAA 6 September 1988 under International Public Transport Category of BCAR section D; also certified in Canada February 1989, Australia 1990, Switzerland April 1990 and Japan

April 1991. Jetstream 32: Alternative designation for the Jetstream Super 31. Jetstream T. Mk 1: Royal Air Force crew trainer aircraft powered by two Turboméca Astazou engines. Jetstream T. Mk 2: Royal Navy crew trainer aircraft powered by two Turboméca Astazou engines. Jetstream T. Mk 3: Training version, in service with the Royal Navy. Eyebrow windows above flight deck windscreen to improve all-round view. Interior fitted with two observer training consoles with radar indicator, TANS computer and Doppler. Racal ASR 360 search radar mounted under the fuselage. Four ordered in April 1984, for operation by No. 750 Naval Air Squadron based at Culdrose, Cornwall, for helicopter observer training. All delivered by October 1986.

UpgradesBAe Asset Management-Jets: Developed the Jetstream 32EP programme to enhance the payload and runway performance of the Jetstream 32 (also known as Jetstream Super 31). Jetstream: Developed programme to extend the Jetstream 31 to 45,000 cycles. BAe has also indicated that if the economics became viable the aircraft could be extended to 67,000 cycles.

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.

Landing GearRetractable tricycle type, with nosewheel steering (±45º). Hydraulic retraction, mainwheels inward into wings, twin nosewheels forward. British Aerospace oleo-pneumatic shock-absorbers in all units. Dunlop wheels and tyres; mainwheel tyre size 28 × 9.00-12, pressure 3.93 bars (57 lb/sq in); nosewheel tyres size 6.00-6, pressure 2.34 bars (34 lb/sq in). Anti-skid units.

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.

AccommodationTwo seats side by side on flight deck, with provision for dual controls, though aircraft can be approved (subject to local regulations) for single pilot operation. Main cabin can be furnished in commuter layout for up to 19 passengers at 76/79 cm (30/31 in) pitch, or with executive interior for 8/10 passengers, but optional layouts are available, including a QC (Quick Change) option enabling an operator to change from an 18-seat layout to 12-seat executive configuration in around 1 hour 15 minutes. Downward-opening passenger door, with integral airstairs, at rear of cabin on port side. Emergency exit over wing on starboard side. Baggage compartment in rear of cabin, aft of main door. Entire accommodation pressurised, heated, ventilated and air conditioned. Toilet standard; galley and bar optional. Jetstream completion is by Field Aircraft at East Midlands Airport, Castle Donington, UK.

SystemsAir conditioning system with cabin pressurisation at maximum differential of 0.38 bars (5.5 lb/sq in), providing a 2,440 m (8,000 ft) cabin altitude at 7,620 m (25,000 ft). Single hydraulic system, pressure 138 bars (2,000 lb/sq in), with two engine-driven pumps, each capable of supplying 20.7 litres (5.46 US gallons; 4.55 Imp gallons)/min. One pump is capable of supplying all hydraulic systems. Combined air/oil reservoir, pressurised to 1.24 bars (18 lb/sq in), for main and emergency supply, for actuation of flaps, landing gear, brakes and nosewheel steering. APU optional. Goodrich rubber de-icing system for leading-edges.



Wing chord: at root 2.19 m (7 ft 2½ in)

at tip 0.80 m (2 ft 7¼ in)



Length of fuselage 13.40 m (43 ft 11½ in)



Tailplane span 6.60 m (21 ft 8 in)






Emergency exit: Height 0.91 m (3 ft 0 in)



Cabin, excl flight deck: Length 7.39 m (24 ft 3 in)




Volume (trimmed aircraft) 16.99 m3 (600 cu ft)


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


Ailerons, aft of hinge line (total) 1.52 m2 (16.4 sq ft)


Vertical tail surfaces (total) 7.72 m2 (83.1 sq ft)

Horizontal tail surfaces (total) 7.80 m2 (84.0 sq ft)


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 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)






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)



Certificated ceiling 7,620 m (25,000 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

VERIFIED Jetstream 31 T. Mk 3 training aircraft of the Royal Navy(1995)Jetstream 41 following role conversion into multirole maritime patrol aircraft (FR Aviation)(1999)BAe Jetstream T. Mk 1 crew trainer in service with the Royal Air Force (Paul Tompkins)(1997)BAe Jetstream Super 31 twin-turboprop commuter/executive light transport (Jane's/Mike Keep)(1998)

Height (m): 5.38

Length (m): 14.37







Short 330








http://www.aero.pub.ro/wp-content/themes/aero.pub.ro/uploads/JANE_S_ALL_THE_WORLD_S_AIRCRAF/JANE_S_AIRCRAFT_UPGRADES/l2189.jpg%00%E5%A1%B9%EF%92%81%E1%B4%BB%E4%A1%BF%E2%B2%AF%E5%B6%82%E8%97%84%E6%8C%A7%00%00%EA%AE%A5

TypeTwin-turboprop transport.

ProgrammeOriginally known as SD3-30; first flight of first prototype (G-BSBH) 22 August 1974; CAA certification to full Transport Category 18 February 1976; US FAR Pt 25 and Pt 36 approval 18 June 1976; subsequent approvals from Canadian Department of Transport, German LBA and Australian Department of Transport. First order (three), by Command Airways of Poughkeepsie, New York, 14 August 1974; deliveries began June 1976; first entered service with Time Air, 24 August 1976. The following versions of the Shorts 330 were built: 97 Shorts 330s including two prototypes; 18 C-23A; six C-23B; four UTT and three Sherpas plus one prototype. The last Shorts 330 was built in 1989.

Versions330-200: Standard passenger version, as detailed. 330-UTT: Military utility tactical transport version. Described separately. Sherpa: Freighter version of 330, with ramp type full-width rear-loading door. Described separately. C-23A: Initial version developed for the US Air Force. Nine aircraft since transferred to the Army National Guard (ARNG). Described separately. C-23B: Version developed for the US Army National Guard. Distinguishable from C-23A by a row of 11 windows on both port and starboard fuselage. Described separately.

UpgradesField Aircraft Services of Calgary: Contract from the US Army to modify four ex-airline 330s to military standard for operations in Kwajalein area of Pacific. Shorts: Developed programme to extend the lives of the 330 to 57,600 cycles from 28,000 cycles.

OperatorsVersions of the Shorts 330 (specifically 330 UTT and C-23) are in service with the armed forces of: Dubai (1); Thailand (4) and USA (19).

Design FeaturesDerived from smaller STOL Skyvan, retaining latter's proven characteristics, including large square-section unpressurised cabin with low floor level, braced high-mounted wings, twin tail unit and safe-life concept and design philosophy for structural components; conforms with CAB Pt 298 (US); meets FAR Pt 36 noise requirements by substantial margin.

First 26 Shorts 330s powered by 875 kW (1,173 shp) PT6A-45As; next 40 given PT6A-45Bs; subsequent aircraft fitted with more powerful PT6A-45Rs; and higher equipment standard; optional Goodrich pneumatic boot de-icing on wing and tail leading-edges. NACA 63A series (modified) wing sections; thickness/chord ratio 18 per cent at root, 14 per cent on outer panels; dihedral 3º on outer panels.The following description applies to standard 330-200 passenger version:

Flying ControlsSingle-slotted ailerons with geared trim tabs; twin unshielded horn aerodynamic balance rudders; full-span elevator, aerodynamically balanced by setback hinges; geared trim tabs in elevator and starboard rudder (port rudder, trim only); single-slotted three-section flaps; fixed-incidence tailplane.

StructureAll-metal safe-life construction; wing centre-section (integral with top of centre-fuselage) tapered on leading- and trailing-edges, and is two-spar single-cell box with conventional skin and stringers; strut-braced wing outer panels are reinforced Skyvan constant-chord units, each with two-cell box and having smooth outer skin bonded to corrugated inner skin; fuselage in three main portions; nose portion (including flight deck, nosewheel bay and forward baggage compartment), centre (including main wing spar attachment frames and lower transverse beams carrying main landing gear and associated fairings), and rear portion (including aft baggage compartment and tail unit attachment frames); nose and rear fuselage of skin/stringer design, remainder smooth outer skin bonded to corrugated inner skin and stabilised by frames; two-spar twin-fin tail unit, with reinforced tailplane leading-edge.

Landing GearMenasco retractable tricycle type, with single wheel on each unit. Main units carried on short sponsons, into which the wheels retract hydraulically. Oleo-pneumatic shock-absorbers. Nosewheel is steerable ±50º. Mainwheel tyre size 34 × 10.75-16; nosewheel tyre size 9.6. Normal tyre pressures: main units 5.45 bars (79 lb/sq in), nose unit 3.79 bars (55 lb/sq in).

Power PlantTwo 893 kW (1,198 shp) Pratt & Whitney Canada PT6A-45R turboprops, each driving a Hartzell five-blade constant-speed fully feathering metal low-speed propeller. Fuel tanks in wing centre-section/fuselage fairing; total usable capacity increased from original 2,182 litres (576 US gallons; 480 Imp gallons) to 2,546 litres (672.5 US gallons; 560 Imp gallons) in January 1985 for Sherpa, C-23A/B and UTT only. Normal cross-feed provisions to allow for pump failure. Single pressure refuelling point in starboard landing gear fairing, backed by three gravity refuelling points in fuselage spine.

AccommodationCrew of two on flight deck, plus cabin attendant. Dual controls standard. Standard seating for 30 passengers, in 10 rows of three at 76 cm (30 in) pitch, with wide aisle. Seat rails fitted to facilitate changes in configuration. Galley, toilet and cabin attendant's seat at rear. Large overhead baggage lockers. Entire accommodation soundproofed and air conditioned. Baggage compartments in nose and to rear of cabin, each with external access and capable of holding a combined total of 500 kg (1,100 lb) of baggage. Passenger door is at rear of cabin on port side. Passenger version has two emergency exits on the starboard side, two on the port side (including passenger door) and one in the flight deck roof. Mixed traffic version has full access to these emergency exits. For mixed passenger/freight operation a partition divides

the cabin into a rear passenger area (typically for 18 persons) and a forward cargo compartment, the latter being loaded through a large port side door capable of admitting ATA `D' type containers. In all-cargo configuration the cabin can accommodate up to seven `D' type containers, with ample space around them for additional freight. Cabin floor is flat throughout its length, and is designed to support loadings of 181 kg (400 lb)/ft run at 610.3 kg/m2 (125 lb/sq ft). Locally reinforced areas of higher strength are also provided. Seat rails can be used as cargo lashing points. Freight loading is facilitated by the low-level cabin floor.

SystemsHamilton Standard air conditioning system, using engine bleed air. Hydraulic system of 207 bars (3,000 lb/sq in), supplied by engine-driven pumps, operates landing gear, nosewheel steering, flaps and brakes (at half pressure) and includes emergency accumulators. Air/oil reservoir pressurised to 1.72 bars (25 lb/sq in) at 20ºC. Main electrical system, for general services, is 28 V DC and is of the split busbar type with cross-coupling for essential services. Lucas 28 V DC starter/generator for engine starting and aircraft services, with separate 1.5 kW 200 V AC output for windscreen anti-icing and demisting. Special AC sources of 115 V and 26 V available at 400 Hz for certain instruments, avionics and fuel booster pumps. Anti-icing standard for engine intake ducts, inlet lips and propellers. Optional de-icing of wing and tailplane leading-edges.

AvionicsWide range of radio and navigation equipment available to customer's requirements. Typical standard avionics comprise duplicated VHF communications and navigation systems, two glide slope/marker beacon receivers, two ILS repeaters, two radio magnetic indicators, one ADF, one transponder, one DME, PA system and weather radar. Flight data recorder and voice recorder available as standard options.

EquipmentPassenger safety equipment standard.



Wing chord (standard mean) 1.85 m (6 ft 0¾ in)


Width of fuselage 2.24 m (7 ft 4 in)


Tailplane span 5.68 m (18 ft 7¾ in)

Wheel track 4.24 m (13 ft 10{7/8} in)



Propeller ground clearance 1.83 m (6 ft 0 in)

Cabin floor: Height above ground 0.94 m (3 ft 1 in)

Passenger door (port, rear): Height 1.57 m (5 ft 2 in)



Cargo door (port, fwd): Height 1.68 m (5 ft 6 in)




Cabin: Max length, incl toilet 9.47 m (31 ft 1 in)




Volume (all-cargo) 34.83 m3 (1,230 cu ft)


nose 1.27 m3 (45 cu ft)

rear of cabin 2.83 m3 (100 cu ft)

Cabin overhead lockers (total) 1.13 m3 (40 cu ft)

Areas


Ailerons (total, aft of hinges) 2.55 m2 (27.5 sq ft)


Fins (total) 8.65 m2 (93.1 sq ft)

Rudders (total, aft of hinges) 2.24 m2 (24.1 sq ft)

Tailplane (total) 7.77 m2 (83.6 sq ft)

Elevator (total, aft of hinges) 2.55 m2 (27.5 sq ft)


Weight empty, equipped (incl crew of three):

330-200 for 30 passengers 6,680 kg (14,727 lb)

Fuel 1,742 kg (3,840 lb)

Max payload for normal max T-O weight:

30 passengers and baggage 2,653 kg (5,850 lb)

cargo 3,400 kg (7,500 lb)





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

Max cruising speed at 3,050 m (10,000 ft), AUW of 9,525 kg (21,000 lb)

190 kt (352 km/h; 218 mph)

Econ cruising speed at 3,050 m (10,000 ft), AUW of 9,525 kg (21,000 lb)

160 kt (296 km/h; 184 mph)

Stalling speed, flaps and landing gear up 90 kt (167 km/h; 104 mph)

EAS

Stalling speed at max landing weight, flaps and landing gear down

73 kt (136 km/h; 85 mph) EAS


Service ceiling, one engine out, AUW of 9,072 kg (20,000 lb)

3,500 m (11,500 ft)

Min ground turning radius about nosewheel

7.77 m (25 ft 6 in)

T-O distance (FAR Pt 25 and BCAR Gp A):

ISA 1,042 m (3,420 ft)

ISA + 15ºC 1,295 m (4,250 ft)

Landing distance, AUW of 9,072 kg (20,000 lb):

BCAR 1,143 m (3,750 ft)

FAR 1,030 m (3,380 ft)

Runway LCN at max T-O weight 10.7

Range with max passenger payload, cruising at 3,050 m (10,000 ft), no reserves

473 n miles (876 km; 544

miles)

Range with max fuel, cruising at 3,050 m (10,000 ft), no reserves:

passenger version, 1,966 kg (4,335 lb) payload

915 n miles (1,695 km; 1,053 miles)

cargo version, 2,306 kg (5,085 lb) payload 758 n miles (1,403 km; 872 miles)

Operational Noise Levels(FAR Pt 36):

T-O 88.9 EPNdB

Sideline 84.7 EPNdB

Approach 92.9 EPNdB

UPDATED

Height (m): 4.95

Length (m): 17.69


Max Range (nm): 473





T-O Run (m): 1042

Landing Run (m): 1143


aircraft specs-1

Documents

ft range

ft landing run

ft stalling speed

ft econ cruising speed

max range nm

production series

max level speed kts

max rate climb mmin