TYPE OF AIRCRAFT

 Il-114T: 76 m 3 (2.684 kaki kubik) kapasitas kargo
 Panjang: 26,877 m (88 ft 2 in)
 Lebar sayap: 30 m (98 ft 5 in)
 Tinggi: 8.32 m (27 ft 4 in)
 Area sayap: 81,9 m 2 (882 sq ft)
 Max berat lepas landas: 23.500 kg (£ 51.809)
 Kapasitas bahan bakar: 8.360 l (1.839 imp gal)
 Berguna beban: 6.500 kg (£ 14.330)
 Il-114T: 7.000 kg (£ 15.432)
 Powerplant: 2 × Klimov TV7-117 mesin turboprop, 1.900 kW (2.500 hp) masing-masing
 Il-114-100: 2 x Pratt & Whitney Canada PW127Н 1.972 kW (2.644 hp) masing-masing
 Il-114-300: 2 x Klimov TV7-117SM 1.980 kW (2.655 hp) masing-masing

 Kecepatan jelajah: 500 km / h (311 mph, 270 kn)
 Rentang: 1.000 km (621 mil, 540 nm) muatan maksimum
 Il-114-100: 1.400 km (870 mil)
 Il-114-300: 2.180 km (1.355 mil)
 Layanan langit-langit: 7.600 m (24.934 kaki)

FOKKER 50

 Crew: 2 flight crew
 Capacity: 46 seats at 34" pitch to 56 seats at 30" pitch,[32] 5,500 kg (12,125 lb) max

payload
 Length: 25.25 m (82 ft 10 in)
 Wingspan: 29 m (95 ft 2 in)
 Height: 8.32 m (27 ft 4 in)
 Wing area: 70 m2 (750 sq ft)
 Aspect ratio: 12.01
 Empty weight: 13,400 kg (29,542 lb)
 Max takeoff weight: 20,820 kg (45,900 lb)
 Fuel capacity: 4,120 kg (9,090 lb)

 Fuselage width: 2.70 m (8.86 ft)
 Cabin Width: 2.50 m (98.5 in)
 Powerplant: 2 × Pratt & Whitney Canada PW125B turboprop engines, 1,864kW

(2,500 hp) each
 Propellers: six-bladed Dowty Rotol composite propellers, 3.66 m (12 ft 0 in) diameter

Performance

 Maximum speed: 565 km/h (351 mph, 305 kn)
 Maximum speed: Mach 0.507
 Cruise speed: 500 km/h (310 mph, 270 kn)
 Range: 1,700 km (1,000 mi, 900 nmi)
 Service ceiling: 7,620 m (25,000 ft)
 Wing loading: 297.4 kg/m2 (60.9 lb/sq ft)
 Takeoff: 1,350 m (4,430 ft) - ISA, SL, MTOW
 Landing: 1,130 m (3,710 ft) - ISA, SL, MLW

d. WIDE BODY AIRLINERS
IIYUSHIN II-96

Country of Origin
Russia
Type
Long range widebody airliner
History
Despite resembling the larger Il-86, the Il-96-300 is essentially a new design, incorporating a number of
advanced technologies and new engines aimed at improving on the uncompetitive Il-86. Development of
Russia's second widebody airliner began in the mid 1980s, resulting in the Il-96's first flight on September
28 1988. Two other flying prototypes were built, as were two airframes to be used for static and ground
testing. Commonality in some areas with the Il-86 allowed a 1200 flight hour certification program,
resulting in Russian certification being awarded on December 29 1992. The Il-96-300 entered service with
Aeroflot Russian International Airlines the following year. The Il-96-300 is based on the older and larger Il-
86, but it features a number of new technologies previously the exclusive domain of modern western built
airliners. These include a triplex flybywire flight control system, a six screen EFIS flightdeck (however

three flightcrew are retained, and not two as on most modern western designs), some composite
construction (including the flaps and main deck floors), and winglets. The modern PS-90 turbofans are
designed to comply with ICAO Stage 3 noise limits (something the Il-86 cannot conform to) and the Il-86's
unique lower deck airstair design was deleted. Perhaps the Il-96-300's greatest claim to fame though is
that it forms the basis for the stretched and westernised (with Pratt & Whitney PW-2337s and Collins
digital avionics) Il-96M and Il-96T, described separately.
Powerplants
Four 160.0kN (35,970lb) Aviadvigatel (Soloviev) PS-90A turbofans.
Performance
Cruising speed 850 to 900km/h (460 to 485kt). Long range cruising speed M0.78, hi-speed cruising
M0.80, max speed M0.84. Range with max payload of 37,5 tonne (82,675lb) and reserves 9000km
(4850nm), with 30 tonne (66,140lb) payload 10,000km (5400nm), with 15 tonne (33,070lb) payload
12,000km (6500nm).
Weights
Operating empty 121,500kg (267,860lb), max takeoff 250,000kg (551,160lb), max landing 183,000kg
(403,450lb), max tankage 150,000liters (39,625gallon).
Dimensions
Wing span over winglets 60.11m (197ft 3in), length 55.35m (181ft 7in), height 17.55m (57ft 7in). Wing
area 391.6m2 (4215.0sq ft).
Capacity
Flightcrew of three, comprising two pilots and flight engineer. Basic single class seating for 300 at nine
abreast in two cabins. Three class arrangement seats 235 comprising 22 first class at six abreast and
102cm (40in) pitch, 40 business class at eight abreast and 90cm (35in) pitch, and 173 economy class at
nine abreast and 87cm (34in) pitch. Forward lower freight hold accommodates six LD3 containers or
pallets (9000kg/19,840lb), rear hold accommodates 10 LD3s or pallets (15,000kg/33,070lb).
Production
Approximately 15 Il-96-300s have been built, of which six are in service with Aeroflot and three with
Domodedovo Civil Aviation Enterprise and others in Russian government service (including one used as
a presidential transport)

side view

Data from Ilyushin Aviation Complex,[26] FAA Certification Document A54NM and Il-96-300
Pilot Manual

Variant Il-96-300 Il-96M Il-96T Il-96-400

Cockpit crew 3 2 2/3

Seats (3/2/1- 237/263/300 307/340/420 315/386/436
class)

Cargo capacity 25 t 776 m³ 196 m³

LD3 capacity 16 32

Length 55.3 m (181 ft 7 64.7 m (212 ft 3 63.9 m (209 ft 9 in)
in) in)

Wing 60.11 m (197 ft 3 in) span, 350 m² (3767.9 ft²), 30° sweep

Fuselage 6.08 m (19.94 ft) diameter, 5.70 m (18.70 ft) cabin width[27]

Height 15.7 m (57 ft 7 in)

OEW 120.4 t 132.4 t 116.4 t 122.3 t
(265,198 lb) (291,630 lb) (256,387 lb) (269,383 lb)

MTOW 250 t (551,000 lb) 270 t (595,000 lb) 270 t 265 t (583,700 lb)
(594,713 lb)
Max. payload
Fuel capacity 40 t (88,105 lb) 58 t (127,753 lb) 92 t (202,643 lb) 58 t (127,753 lb)
Engines (×4)
152,620 l (40,322 US gal)
Thrust (×4)
Aviadvigatel PS- PW2037 PW2337 or PS- PS-90A1[b]
Cruise 90A[a] 90A1
Range (max.
156.9 kN 170.1 kN 166.8 kN 170.7 kN
payload) (35,242 lbf) (38,250 lbf) (37,500 lbf) (38,326 lbf)
Takeoff run
0.78-0.84 Mach / 850-870 km/h / 459-469 kn TAS; 13,100 m (43,000 ft)
(MTOW) Ceiling
Landing run
11,500 km 12,800 km 5,000 km 10,000 km
(6,209 nmi) (6,907 nmi) (2,699 nmi) (5,400 nmi)

2,340 m (7,677 ft) 3,000 m (9,843 ft) 2,700 m 2,700 m (8,858 ft)
(8,858 ft)

860 m (2,821 ft) 1,800 m (5,906 ft) 1,650 m 1,650 m (5,511 ft)
(5,511 ft)

McDonnell Douglas DC-10

Country of Origin
United States of America
Type
Medium to long range widebody airliner
History
Designed in response to the same American Airlines requirement as the Lockheed TriStar, the
DC-10, despite a sometimes troubled past, was the more successful of the two widebody trijets.
Although originally conceived as a twinjet, the DC-10 gained a third engine at the base of its
vertical tail to meet an American Airlines requirement that the aircraft be capable of operating
from existing runways. The DC-10 subsequently was launched in February 1968 with orders
from American and United. First flight took place on August 29 1970. The first transcontinental
range DC-10-10s entered service with American in August 1971. By then work was already

underway on the intercontinental range DC-10-30 which introduced more powerful engines,
additional fuel tanks and a third main undercarriage unit. Most DC-10s built were 30s (including
convertible 30CFs and pure freight 30Fs), while the 40 is a Pratt & Whitney JT9D powered
variant ordered by Northwest and JAL. The United States Air Force ordered 60 CF6 powered
DC-10s as KC-10A Extender tanker transports. A number of major and catastrophic accidents
marred the DC-10's service record in the mid to late 1970s, but the various causes of these
accidents were overcome and the DC-10 continues to operate reliably. Production ceased in
1989. The Boeing MD-10 conversion for Federal Express involves fitting DC-10s (both current
freighters and "new" ex airliner freighter conversions) with a two crew Honeywell VIA 2000
EFIS flightdeck with six LCD screens. The instrument panel layout is identical to that in the
MD-11, and pilots can be qualified to fly the two interchangeably. First flight was on April 4
1999, while the first of 89 MD-10 conversions for FedEx was delivered on May 9 2000 (the
same day the conversion was certificated). Boeing is offering the MD-10 conversion to other
DC-10 operators.
Powerplants
DC-10-10 - Three 178kN (40,000lb) General Electric CF6-6D turbofans, or 182.4kN (41,000lb)
CF6-6D1s. DC-10-30 - Three 218kN (49,000lb) CF6-50As, 226.9kN (51,000lb) CF6-50Cs, or
233.5kN (52,500lb) CF6-50C1s or C2s, or 240.2kN (54,000lb) CF6-50C2Bs. DC-10-40 - Three
219.6kN (49,400lb) Pratt & Whitney JT9D-20s, or 235.8kN (53,000lb) JT9D-59As.
Performance
DC-10-30 - Max speed 982km/h (530kt), max cruising speed 908km/h (490kt). Range with max
fuel and no payload 12,055km (6505nm), range with max payload 7415km (4000nm). DC-10-40
- Speeds same. Range with max fuel and no payload 11,685km (6305nm), range with max
payload (& JT9D-59As) 7505km (4050nm).
Weights
DC-10-30 - Empty 121,198kg (267,197lb), max takeoff 263,085kg (580,000lb). DC-10-40 -
Empty 122,951kg (271,062lb), max takeoff 259,450kg (572,000lb).
Dimensions
Wing span 50.40m (165ft 5in), length 55.50m (182ft 1in), height 17.70m (58ft 1in). Wing area
367.7m2 (3958.0sq ft).
Capacity
Flightcrew of three. Max seating for 380 passengers at nine abreast and 81cm (32in) pitch.
Mixed class seating arrangements vary between 250 and 270. DC-10-30F - 23 pallets on main
deck.
Production
386 civil DC-10s and 60 military KC-10As built. By early 2003 180 remaining in airline service.
FedEx has ordered 89 MD-10 conversions.

Specifications

The schematic of the McDonnell Douglas DC-10-30 (side, top, front, cross-section)

DC-10 Airplane Characteristics[110]

Variant -10 -30 -40

Cockpit crew Three

Std. seating 270 (222Y 8-abreast @ 34" + 48J 6-abreast @ 38")

Max. seating 399Y (10-abreast @ 29–34" pitch) layout, FAA exit limit: 380[111]

Cargo 26 LD3 layout, main deck: 22 88×125″ or 30 88x108″ pallets

Length 182 ft 3.1 in / 55.55 m 181 ft 7.2 in / 55.35 m 182 ft 2.6 in / 55.54 m

Height 57 ft 6 in / 17.53 m 57 ft 7 in / 17.55 m

Wingspan 155 ft 4 in / 47.35 m 165 ft 4 in / 50.39 m

Wing area[112] 3,550 sq ft (330 m2) 3,647 sq ft (338.8 m2)

Width 19 ft 9 in (6.02 m) fuselage, 224 in (569 cm) interior

OEW(pax) 240,171 lb / 108,940 kg 266,191 lb / 120,742 kg 270,213 lb / 122,567 kg

MTOW 430,000 lb / 195,045 kg 555,000 lb / 251,744 kg

Max. payload 94,829 lb / 43,014 kg 101,809 lb / 46,180 kg 97,787 lb 44,356 kg

Fuel capacity 21,762 US gal / 82,376 L 36,652 US gal / 137,509 L

Engines ×3 GE CF6-6D GE CF6-50C PW JT9D-20 / -59A

Thrust ×3[112] 40,000 lbf / 177.92 kN 51,000 lbf / 226.85 kN 53,000 lbf / 235.74 kN

Cruise Mach 0.82 (473 kn; 876 km/h) typical, Mach 0.88 (507 kn; 940 km/h) MMo[111]

Range[a] 3,500 nmi (6,500 km) 5,200 nmi (9,600 km) 5,100 nmi (9,400 km)

Takeoff[b] 9,000 ft (2,700 m) 10,500 ft (3,200 m) 9,500 ft (2,900 m)

Ceiling 42,000 ft (12,800 m)[111]

AIRBUS A300

AIRBUS A340

AIRBUS A330

AIRBUS A350 XWB

Model A350-900 A350-1000

Kru kokpit Dua
Tempat duduk
Batas maksimum [194] 315 (48J + 267Y) 369 (54J + 315Y)
Panjang keseluruhan
440 480
Sayap
Rasio aspek 66,8 m / 219,2 kaki 73,79 m / 242,1 kaki
Area sayap
Rentang 64,75 m / 212,43 kaki, sapuan 31,9
Tinggi keseluruhan ° [126]

Badan pesawat 9.49 9.03

Lebar kabin 442 m 2 (4.760 kaki 464,3 m 2 (4.998 kaki
MTOW persegi) [127] persegi) [130]

Max. muatan 17,05 m / 55 kaki 11 17,08 m / 56 kaki 0
inci [157] inci [249]
Kapasitas bahan bakar [194]
Lebar 5,96 m / 19,7 kaki, tinggi 6,09 m / 19,98
kaki

5,61 m / 18 kaki 5 inci, [157] [249] kursi 9-sejajar:
18 inci / 46 cm [a]

280 t / 617.295 lb 316 t / 696.661 lb

53,3 t (118,000 lb) 68 t (150.000 lb)
45,9–56,4 t (101,300–

124,300 lb) [126]

140.795 L (37.194 US 158.791 L (41.948 US
gal) gal)

110.523 kg (243.662 124.651 kg (274.808
lb) [b] lb)

OEW 142,4 t (314.000 lb) 155 t (342.000 lb)
biasa 155 t (342.000 lb)

134,7–145,1 t (297.000– kering [251]
320.000 lb) [126]

MENGEONG 115,7 t (255.075 lb) [252] 129 t (284.000 lb) [98]

Kapasitas kargo 36 LD3 atau 11 palet 44 LD3 atau 14 palet

Kecepatan jelajah Mach 0,85 (488 kn; 903 km / j) Biasa, Mach 0,89
(513 kn; 950 km / jam) Maksimum [126]

Jarak 15.000 km / 8.100 16.100 km (8.700
nm [c] [157] [b] nmi) [c] [249]

Lepas landas(MTOW, SL, ISA) 2.600 m (8.500 kaki)

Mendarat (MLW, SL, ISA) 2.000 m (6.600 kaki)

Plafon layanan [194] 43.100 kaki (13.100 m) 41.450 kaki (12.630 m)

Mesin (2 ×) Rolls-Royce Trent XWB

Doronganmaksimum (2x) [194] 84.200 lbf / 374,5 kN 97.000 lbf / 431,5 kN

BOEING 747

BOEING 767

BOEING 777

BOEING 787 DREAMLINER



e. NARROW BODY AIRLINERS
DE HAVILLAND COMET

BOEING 707

Country of Origin
United States of America
Type
Medium to long range airliner and freighter
History
The 707's jet speed, long range, high seating capacity and operating economics revolutionised airliner
travel when it was introduced into service in 1958. The 707 also laid the foundations for Boeing's
dominance of the jet airliner market. Recognising the jet engine's potential for commercial aviation,
Boeing (at great financial risk) decided to develop a jet powered transport that could fulfil military tanker
transport roles but be easily adapted to become an airliner. The resulting prototype, known as the 367
Dash 80, flew for the first time on July 16 1954. Impressed, the US Air Force ordered a larger version,
with a wider fuselage (12 ft, vs 11 ft for the Dash 80) into production as the KC-135 tanker/transport
(more than 800 were built). At first, Boeing wanted to sell the same size aircraft to the airlines, but the
airlines insisted on an even larger airplane, which Douglas promised to build (this became the DC-8).
Boeing finally relented, designing the 707 as a longer aircraft with a slightly wider fuselage (12 ft 4 in).
The first production 707 (a 707-120 for Pan Am) flew on December 20 1957, and entered service later the
following year. Developments of the 707-120 include the similar 707-220, the shorter 138 for Qantas, and
the stretched 707-320, which flew in July 1959. The 707-120 and 320 were later reengined with JT3D
turbofans (in place of the original JT3 and JT4 turbojets) to become the 707-120B, and the 707-320B
respectively. The 707-320C was a convertible model, the 707-420 was powered by RollsRoyce Conways,
while the proposed CFM-56 powered 707-700 upgrade was flight tested in the late 1970s but never
entered production. Most civil 707s in service today have been converted to freighters, while a number
are used as corporate transports. Many air forces have bought 707s, new or converted second-hand
aircraft, for general transport, aerial refuelling, and electronic warfare. The E-3 Sentry is a dedicated
airborne warning and control system (AWACS) platform with a large rotodome above the fuselage. The E-
6 Mercury performs the TACAMO (Take Charge and Move Out) role with the US Navy, maintaining
communication with the ballistic missile submarines. The E-8 J-Stars (Joint Surveillance Target Attack
Radar System) performs the battlefield control role. Other military 707s received the designations C-137,
or C-18, but many others have no special military designation.
Powerplants
707-120B - Four 75.6kN (17,000lb) Pratt & Whitney JT3D-1 turbofans. 707-320B - Four 80kN (18,000lb)
JT3D-3s or four 84.4kN (19,000lb) JT3D-7s.
Performance
707-120B - Max speed 1010km/h (545kt), max cruising speed 1000km/h (540kt), economical cruising
speed 897km/h (484kt). Range with max payload 6820km (3680nm), range with max fuel 8485km
(4580nm). 707-320B - Max speed 1009km/h (545kt), max cruising speed 974km/h (525kt), long range
cruising speed 885km/h (478kt). Range with max passengers 6920km (3735nm), range with max fuel and
147 passengers 9265km (5000nm).
Weights
707-120B - Operating empty 55,589kg (122,533lb), max takeoff 116,575kg (257,000lb). 707-320B -
Empty 66,406kg (146,400lb), max takeoff 151,315kg (333,600lb).

Dimensions
707-120B - Wing span 39.90m (130ft 10in), length 44.07m (144ft 6in), height 12.94m (42ft 5in). Wing
area 226.3m2 (2433sq ft). 707-320B - Wing span 44.42m (145ft 9in), length 46.61m (152ft 11in), height
12.93m (42ft 5in). Wing area 283m2 (3050sq ft).
Capacity
Flightcrew of three or four. 707-120 max seating for 179, or 110 in two classes (44 first and 66 economy).
707-320B - Max seating for 219, or 189 single class at 81cm (32in) pitch, or 147 in two classes.
Convertible or freighter versions - 13 A type containers.
Production
Production of commercial 707s ended in 1978 after 878 had been built. Limited production of military
variants continued until 1990. Approximately 130 remain in commercial service.

Variant 707- 707-
707-120 707-120B 320 420 707-320B 707-320C

Cockpit crew[66] Three minimum: Pilot, Copilot, and Flight Engineer

1-Class/cargo:16– 174 @ 34" 189 @ 34" 194 @ 32"

18

2-class/cargo:16– 137 (32J @ 38" + 105Y @ 141 (18J + 123Y) 13 88×125"
18 34") pallets

Exit Limit[66] 189 219

Length:5 145 ft 1 in (44.22 m) 152 ft 11 in (46.61 m)

Fuselage width:19 148 in / 3.759 m

Wingspan:5 130 ft 10 in (39.88 m) 142 ft 5 in 145 ft 9 in (44.42 m)
(43.41 m)

Wing area[67] 2,433 sq ft / 226.3 m² 3,050 sq ft / 283 m²

Tail height:5 41 ft 8 in (12.70 m) 42 ft 2 in 42 ft 1 in 42 ft 0 in
(12.85 m) (12.83 m) (12.80 m)

MTOW:9 247,000 lb / 258,000 lb / 312,000 lb / 333,600 lb / 151.5 t

123.5 t 129 t 141.7 t

OEW:9 122,533 lb / 127,500 lb / 142,600 lb / 148,800 lb / 148,300 lb /

57.6 t[b] 58.4 t[c] 64.6 t[d] 67.5 t[d] 67.3 t[e]

Fuel capacity:9 17,330USgal / 65.59 m3 23,820USgal / 23,855 USgal / 90.29 m3

90.16 m3

P&W JT3C- P&W JT3D- JT4A- Conway-
Engines (x4):36 1 11/12 12 Pratt & Whitney JT3D-3/7
6

Thrust per 13,500 lbf 17,000 lbf 17,500 lbf 18,000 lbf (80 kN) -
engine:36–41 (78 kN) 19,000 lbf (85 kN)
(60 kN) (76 kN)

Cruise[67] 484-540 kn / 897- 478-525 kn / 885-974 km/h
Range:30–34 1000 km/h
3,750 nmi 5,000 nmi 2,900 nmi
Takeoff 3,000 nmi 3,600 nmi (6,940 km)[h] (9,300 km)[h] (5,400 km)[i]
Landing[j]:42–46 (5,600 km)[f] (6,700 km)[g]
10,700 ft 10,000 ft (3.0 km)
7,500 ft (2.3 km) (3.25 km)

6,500 ft (2.0 km) 7,200 ft 5,900 ft 6,200 ft
(2.2 km) (1.8 km) (1.9 km)

DOUGLAS DC-8

Country of Origin
United States of America
Type
Medium to long range airliner and freighter
History
The popular DC-8 was Douglas' first jet powered airliner, and the USA's second successful jet powered
transport behind the Boeing 707. Despite its strong hold on the world airliner market in the early 1950s,
and the appearance of the jet powered De Havilland Comet in 1949, Douglas moved cautiously into the
field of jet powered transports, a decision which was to cost it dearly in lost potential sales over the
following decades. Douglas announced it was developing the jet powered DC-8 airliner in June 1955, a
year after the first flight of the Boeing Model 367-80, the 707 predecessor. The first DC-8 flew on May 30

1958, five months before the 707 entered service with Pan Am. A concerted flight test program involving
nine aircraft led to certification being awarded on August 31 1959. Entry into commercial service with
launch customers United and Delta was on September 18 that year. Unfortunately for Douglas, the earlier
availability of the 707 meant that initial sales of the DC-8 were relatively slow. However, the emergence of
Douglas' design had already forced Boeing to widen the fuselage width of the 707, and unlike the Boeing
the DC-8 was offered in domestic and intercontinental versions from the start. Versions of the initial short
fuselage DC-8 were: the Series 10, the initial domestic version with 60.1kN (13,500lb) P&W JT3C-6
turbojets - 28 were built for Delta and United; the similar Series 20 but with more powerful 74.7kN
(16,800lb) JT4A-9 turbojets; the intercontinental Series 30 and Series 40, powered by JT4A-11s or Rolls-
Royce Conways respectively; and the Series 50, perhaps the definitive short fuselage model and a direct
competitor to the 707-320B/C, with 80.1kN (18,000lb) JT3D-3 turbofans. Convertible 50CF and pure
freight 50AF Jet Trader versions were also offered, while others were subsequently converted to
freighters. The short fuselage DC-8s were replaced in production by the substantially larger stretched DC-
8 Super Sixty series.
Powerplants
Series 50 - Four 80.1kN (18,000lb) Pratt & Whitney JT3D-3 turbofans.
Performance
Series 50 - Max cruising speed 933km/h (504kt). Range with max payload 9205km (4970nm), max range
11,260km (6078nm).
Weights
Series 50 - Operating empty 60,020kg (132,325lb), max takeoff 147,415kg (325,000lb).
Dimensions
Wing span 43.41m (142ft 5in), length 45.87m (150ft 6in), height 12.91m (42ft 4in). Wing area 257.6m2
(2773sq ft) on early aircraft, 266.5m2 (2868sq ft) on later aircraft.
Capacity
Flightcrew of three. Mixed class seating for 132, typical all economy seating for 144, or up to 179 in high
density single class layout. A number of aircraft are converted for VIP/executive use. Freighter versions
can carry approximately 15 tonnes (34,000lb) of cargo consisting of pallets or containers.
Production
295 Series 10, 20, 30, 40 and 50 DC-8s built between the late 1950s and 1968. Approximately 25 series
DC-8-50s were still in commercial service in 2002.

Variant -10/20/30 -40/43/50/55 -61/71 -63/73 -62/72

Passengers 177 -40/43: 177, - 259 189
50/55: 189

Max. cargo 1,390 cu ft (39 m3) 2,500 cu ft (71 m3) 1,615 cu ft
(45.7 m3)
Wingspan
142.4 ft (43.4 m) 148.4 ft (45.2 m)
Length
150.7 ft (45.9 m) 187.4 ft (57.1 m) 157.5 ft
Fuselage (48.0 m)
Max.
outside width: 147 in (373.4 cm), inside width: 138.25 in (351.2 cm)
Takeoff
-10: 315,000 lb 325,000 lb 355,000 lb 350,000 lb
273,000 lb (142.9 t) (147.4 t) (161.0 t) (158.8 t)

Weight (123.8 t) -55: 325,000 lb -F: 328,000 lb -72F:
(MTOW) 335,000 lb
-20: (147.4 t) (148.8 t) (152.0 t)

276,000 lb

(125.2 t)

30: 315,000 lb

(142.9 t)

-10: 46,103 lb 52,000 lb -61: 71,899 lb -63: 71,262 lb -62:
(20.9 t) (23.6 t) 51,745 lb
Max. -43: 41,691 lb (32.6 t) (32.3 t)
payload -20: 43,624 lb (18.9 t) (23.5 t)
(19.8 t) -71: 60,300 lb -73: 64,800 lb -72:

-30: 51,870 lb (27.4 t) (29.4 t) 41,800 lb
(23.5 t) (19.0 t)

Operating -10: -40/50: -61: -63: -62:
empty 119,797 lb 124,800 lb 152,101 lb 158,738 lb 143,255 lb
weight
(OEW) (54.3 t) (56.6 t) (69.0 t) (72.0 t) (65.0 t)
-20: -43: 136,509 lb -71: -73: -72:

123,876 lb (61.9 t) 163,700 lb 166,200 lb 153,200 lb
(56.2 t) -55: 138,266 lb (74.3 t) (75.4 t) (69.5 t)
-30:
(62.7 t)
126,330 lb
(57.3 t)

Max. fuel 23,393 US gal (88.6 m3), -10/20: 17,550 US gal 24,275 US gal (91.9 m3)
(66.4 m3)

-10: P&W -40/43: RCo.12 Super 61/62: P&W JT3D-3B, Super 63:
JT3C P&W JT3D-7
Engines[a] -50/55: P&W
-20/30: P&W Super 70: CFM56-2
JT4A JT3D-3B

Cruise Mach 0.82 (483 kn; 895 km/h)
speed

Range[b] -10: -40: 5,310 nmi -61: -63: -62:
3,760 nmi (9,830 km) 3,200 nmi 4,000 nmi 5,200 nmi
(6,960 km) (5,900 km) (7,400 km) (9,600 km)
-43: 4,200 nmi
-20: (7,800 km) -71: -73: -72:
4,050 nmi 3,500 nmi 4,500 nmi 5,300 nmi
(7,500 km) -50: 5,855 nmi (6,500 km) (8,300 km) (9,800 km)
(10,843 km)
-30: -55: 4,700 nmi
4,005 nmi (8,700 km)
(7,417 km)

Freighter -50/-55 -61/71 63/73 -62/72
versions
Volume -50: 9,310 cu ft 12,171 cu ft 12,830 cu ft 9,737 cu ft
(264 m3) (344.6 m3) (363 m3) (275.7 m3)
Payload
-55: 9,020 cu ft -62:
OEW (255 m3) 91,440 lb

Max PL -50: 88,022 lb -61: 88,494 lb -63: (41.5 t)
Range (39.9 t) (40.1 t) 119,670 lb -72:
McDonnell Douglas DC-9
-55: 92,770 lb -71: 81,300 lb (54.3 t) 90,800 lb
(42.1 t) (36.9 t) -73: (41.2 t)

111,800 lb -62:
(50.7 t) 138,560 lb

-50: 130,207 lb -61: -63: (62.8 t)
(59.1 t) 145,506 lb 141,330 lb -72:

-55: 131,230 lb (66.0 t) (64.1 t) 140,200 lb
(59.5 t) -71: -73: (63.6 t)

152,700 lb 149,200 lb -62:
(69.3 t) (67.7 t) 3,200 nmi
(5,900 km)
-55: 3,000 nmi -61/63: 2,300 nmi
(5,600 km) (4,300 km) -72:
3,900 nmi
-71/73: 2,900 nmi (7,200 km)
(5,400 km)

Country of Origin
United States of America
Type
Short range airliners
History
No other airliner in history has undergone more development than the prolific DC-9/MD-80/MD-90/717
series, which started life with the 70 seat DC-9-10 of the early sixties. Douglas developed the DC-9 as a
short range airliner complementing the much larger DC-8. Development was launched on April 8 1963,
with a launch order from Delta following soon after. The DC-9 was an all new design, featuring rear
fuselage mounted engines, a T-tail, moderately swept wings and seats for up to 90 passengers in a five
abreast fuselage. Construction of the prototype began in July 1963 and the first flight occurred on
February 25 1965. Certification and service entry was on November 23 and December 8 1965,
respectively. From the outset the DC-9 had been designed with stretched larger capacity developments in
mind. The first stretch resulted in the biggest selling DC-9, the 4.54m (14ft 11in) longer, 105 seat DC-9-
30, which entered service with Eastern on February 1 1967. Subsequent stretched versions are described
separately. Small numbers of developed versions of the DC-9-10 were also built. The DC-9-20 featured
the DC-9-10's fuselage with the 30's more powerful engines and longer span wings, giving better hot and
high performance. The DC-9-15 was basically a -10 but with more fuel and higher weights. Factory built
convertibles and pure freighters were also offered, while a number of DC-9-30s have been converted to
freighters, and/or are having Stage 3 hushkits fitted, further extending their useful service lives.
Powerplants
10 - Two 54.5kN (12,250lb) Pratt & Whitney JT8D-5 turbofans. 30 - Two 64.5kN (14,500lb) JT8D-9s, or
two 66.7kN (15,000lb) JT8D-11s, or two 71.2kN (16,000lb) JT8D-17s.
Performance
10 - Max cruising speed 903km/h (488kt), economical cruising speed 885km/h (478kt). Range with max
payload 1055km (570nm). 30 - Max cruising speed 907km/h (490kt), long range cruise 798km/h (430kt).
Range at high speed cruise with 64 passengers and reserves 2150km (1160nm), range at long range
cruise with 80 passengers and reserves 3095km (1670nm).
Weights
10 - Operating empty 22,635kg (49,900lb), max takeoff 41,140kg (90,700lb). 30 - Empty 25,940kg
(57,190lb), max takeoff 54,885kg (121,000lb).
Dimensions
10 - Wing span 27.25m (89ft 5in), length 31.82m (104ft 5in), height 8.38m (27ft 6in). Wing area 86.8m2
(934sq ft). 30 - Same except for length 36.37m (119ft 4in), wing span 28.47m (93ft 5in). Wing area
93.0m2 (1000.7sq ft).
Capacity

Flightcrew of two. 10 - Seating for 80 in a single class at five abreast and 86cm (34in) pitch. Max seating
for 90. 30 - Max seating for 115 in a single class, five abreast and 81cm (32in) pitch, standard single class
seating for 105. 30CF - can carry over eight cargo pallets.
Production
976 DC-9s of all models built including 137 -10s, 10 -20s and 662 -30s (including military C-9s). 97 DC-9-
10s, 4 DC-9-20s and 381 DC-9-30s in airline service at late 2002. 9 DC-9-10s and 3 DC-9-30s used as
corporate jets at late 2002.

DC-9 airplane characteristics[86]

Variant -15 -21 -32 -41 -51

Cockpit Two
crew[87]:66

1-class 90Y@31-32" 115Y@31-33" 125@31- 135@32-
seating:15–18 34" 33"

Exit 109 127 128 139
limit[87]:80

Cargo:4 600 ft³ / 17.0m³[a] 895 ft³ / 25.3m³[b] 1,019 ft³ / 1,174 ft³ /
28.9m³ 33.2m³

Length:5–9 104 ft 4.8in / 31.82m 119 ft 3.6in / 125 ft 7.2in 133 ft 7in /

36.36m / 38.28m 40.72m

Wingspan:10– 89 ft 4.8in / 93 ft 3.6in / 28.44m 93 ft 4.2in
27.25m / 28.45m
14

Height:10–14 27 ft 7in / 8.4m 27 ft 9in / 8.5m 28 ft 5in / 28 ft 9in /

8.7m 8.8m

Width 131.6in / 334.3 cm Fuselage,:23 122.4in / 311cm Cabin:24

Max. 90,700 lb / 98,000 lb / 108,000 lb / 114,000 lb 121,000 lb
takeoff:4 41,141 kg 45,359 kg 48,988 kg /
/ 51,710 kg 54,885 kg

Empty:4 49,162 lb / 52,644 lb / 56,855 lb / 61,335 lb / 64,675 lb /
22,300 kg[a] 23,879 kg 25,789 kg[b] 27,821 kg 29,336 kg

Fuel:4 24,743 lb / 11,223 kg 24,649 lb / 11,181 kg

Engine JT8D- -9/11 -- -15/17
(2×)[87] 1/5/7/9/11/15/17 1/5/7/9/11/15/17 9/11/15/17

Thrust -1/7: 14,000 lbf (62 kN), -5/-9: 12,250 lbf (54.5 kN), -11: 15,000 lbf
(2×)[87] (67 kN), -15: 15,500 lbf (69 kN), -17: 16,000 lbf (71 kN)

Ceiling[87]:67 35,000 ft (11,000 m)

MMo[87] Mach 0.84 (484 kn; 897 km/h)

Range:36–45 1,300 nmi 1,500 nmi 1,500 nmi 1,200 nmi 1,300 nmi
(2,400 km) (2,800 km) (2,800 km) (2,200 km) (2,400 km)

McDonnell Douglas MD-80

Variant MD-81/82/83/88 MD-87

Cockpitcrew Two

1-classseats[92] 155Y @32-33" (max 172) 130Y @31-33" (max 139)

2-class seats[92] 143: 12J @ 36" + 131Y@ 31-34" 117: 12J+105Y

Length 147 ft 10 in (45.06 m) 130 ft 5 in (39.75 m)

Wing 107 ft 8 in (32.82 m) span, 1,209 sq ft (112.3 m2) area, aspect ratio: 9.6

Tail height 29 ft 7 in (9.02 m) 30 ft 4 in (9.25 m)

Width 131.6 in / 334.3 cm fuselage, 122.5 in / 311.2 cm cabin

Cargo 1,253 cu ft (35.5 m3) 938 cu ft (26.6 m3)
-83/88: 1,013 cu ft (28.7 m3)

Empty weight 77,900–79,700 lb(35,300–36,200 kg) 73,300 lb (33,200 kg)

MTOW -81: 140,000 lb (63,500 kg) 140,000–149,500 lb (63,500–
-82: 149,500 lb (67,800 kg) 67,800 kg)
-83/88: 160,000 lb (72,600 kg)

Fuel capacity 5,850 US gal (22,100 L) -83/88: 7,000 US gal (26,000 L)

Engines(×2) Pratt & Whitney JT8D-200 series
Thrust(×2) 18,500–21,000 lbf (82–93 kN)

Long- Mach 0.76 (448 kn; 830 km/h)[93]
range Cruise

High-speed Mach 0.8 (472 kn; 873 km/h)[92]
cruise

Range[a] -81: 1,800 nmi(3,300 km) @ 137 pax 2,400–2,900 nmi (4,400–5,400 km)
Takeoff[b] -82: 2,050 nmi (3,800 km) @ 155 pax
-83/88: 2,550 nmi (4,720 km) @ 155

pax

7,200–8,000 ft (2,200–2,400 m) 7,500 ft (2,300 m)

McDonnell Douglass MD-90

Variant[15] MD-90-30 MD-90-30ER

Seating, 2–class 153-158: 12J@36" + 141/146Y@31-33"
Seating, 1–class 163-172Y@29-33"

Cargo 1,300 cu ft (36.8 m3) 1,177 cu ft (33.3 m3)

Length 152.6 ft (46.51 m)

Fuselage 131.6×142 in (334.3×360.7 cm) width × height[44]

Wingspan 107.8 ft (32.86 m)

Height 30.6 ft (9.33 m)

MTOW 156,000 lb(70,760 kg) 166,000 lb (75,296 kg)

Empty weight 88,200 lb (40,007 kg) 88,400 lb (40,098 kg)[a]

Max. payload 41,800 lb (18,960 kg) 43,600 lb (19,777 kg)

Fuel capacity 39,128 lb (17,748 kg)[b]

Turbofanengines (2×) IAE V2525-D5

Unit thrust 25,000 lbf (111.21 kN)[c]

VMO Mach 0.84 (506 kn; 937 km/h) at 27,240 ft (8,303 m)[45]

Cruise speed Mach 0.76 (438 kn; 812 km/h) at 34,777 ft (10,600 m)[46][47]

Ceiling 37,000 ft (11,278 m)[45]

Range, 153 pax 2,045 nmi(3,787 km) 2,237 nmi (4,143 km)[d]

Takeoff runway 7,000 ft (2,134 m) at 156,000 lb, ISA, SL[44]

BOEING 717

Country of Origin
United States of America
Type
Short to medium range airliner
History
The 100 seat 717 is the latest development of the popular DC-9/MD-80/MD-90 family and the only
Douglas airliner which Boeing (which merged with McDonnell Douglas in 1997) plans to retain in its
product line-up. It is designed for high cycle, short range regional airline operations. McDonnell Douglas
first announced the MD-95 at the Paris Airshow in June 1991. At the time MDC anticipated a formal
program launch by late 1991 and a first flight in July 1994. As it happened program launch was not until
October 1995 when US airline ValuJet (now AirTran Airlines) ordered 50 and optioned 50. In January
1998 Boeing (following the August 1997 Boeing/McDonnell Douglas merger) relaunched the aircraft as
the 717-200 (the second use of the Boeing designation "717", as this was previously allocated to the
military C-135/KC-135 family). First flight took place on September 2 1998, followed by a second
development 717 on October 26. Certification was awarded on September 1 1999 while the first delivery,
to AirTran, was on September 23 that year. Initially MDC studied powering the MD-95 with Pratt &
Whitney JT8D-218s or Rolls-Royce Tays. In February 1994 however MDC announced it had chosen the
new BMW Rolls-Royce (now just Rolls-Royce) BR715 over the JT8D-200 and an engine from the
proposed "Project Blue" teaming of General Electric, Snecma, MTU and P&W. Other 717-200 features
include a fuselage 1.45m (4ft 9in) longer than the DC-9-30's, a wing based on the DC-9-34's, an
advanced six LCD screen Honeywell EFIS flightdeck, and a cabin interior similar to that developed for the
MD-90. It is offered in standard 717-200BGW (Basic Gross Weight) and extended range 717-200HGW
(High Gross Weight) forms. In addition, 80 seat shortened 717-100 (formerly MD-95-20) and 120 seat
stretched 717-300 (formerly MD-95-50) models have been studied, as has a business jet variant.
Companies participating in 717 production include Alenia (fuselage), Korean Air (nose), AIDC of Taiwan
(empennage), ShinMaywa of Japan (engine pylons and horizontal stabilizers), Israel Aircraft Industries
(undercarriage), and Fischer of Austria (interior). Final assembly is at Boeing's Long Beach plant, in the
same building that the DC-9 and MD-80 were built in. Initial orders and operators are: AeBal, Airtran,
Bangkok Air, Bavaria International Leasing, Hawaiian Airlines, Impulse Airlines, Midwest Express Airlines,
Olympic Aviation, Pembroke Leasing, Qantas Link, Siam Reap Air, Trans World Airlines, and
Turkmenistan Airlines.
Powerplants
717-200BGW - Two 82.3kN (18,500lb) Rolls-Royce BR715-A1-30 turbofans. 717-200HGW - Same or
optionally 89.6kN (20,000lb) or 93.4kN (21,000lb) BR715s.
Performance
717-200BGW - Cruising speed 811km/h (438kt). Range with 106 passengers 2545km (1375nm). 717-
200HGW - Cruising speed same. Range with 106 passengers 3815km (2060nm).
Weights
717-200BGW - Operating empty 31,674kg (69,830lb), max takeoff 49,940kg (110,100lb) or 51,710kg
(114,000lb). 717-200HGW - Operating empty 32,110kg (70,790lb), max takeoff 54,885kg (121,000lb).
Dimensions
Wing span 28.44m (93ft 3in), length 37.80m (124ft 0in), height 8.87m (29ft 1in). Wing area 93.0m2
(1000.7sq ft).
Capacity
Flightcrew of two. Typical two class seating for 106 passengers at five abreast in main cabin. Single class
seating for 117.
Production
As of early 2003, 153 717s had been ordered, of which 111 had been delivered.

Variant Basic High Gross Weight

Cockpit crew[59]:66 Two

2-class seating:10 106 (8J+98Y @36–32 in, 91–81 cm)

1-class seating:11 117Y@32 in (81 cm)

Exit limit[59]:81 134

Cargo:7 935 ft³ / 26.5 m³ 730 ft³ / 20.7 m³

Length:8 124 ft 0 in / 37.8 m

Wingspan:8 93 ft 4 in / 28.4 m

Height:9 29 ft 8 in / 9.0 m

Width:13 Fuselage: 131.6 in / 334.2 cm, Cabin: 123.8 in / 314.5 cm

Max. takeoff:7 110,000 lb / 49,895 kg 121,000 lb / 54,884 kg

Empty weight:7 67,500 lb / 30,617 kg 68,500 lb / 31,071 kg

Max. payload[59]:66 26500 lb / 12021 kg 32000 lb / 14515 kg

Fuel weight:7 24,609 lb / 11,163 kg 29,500 lb / 13,382 kg

Fuel Capacity[60] 3,673 US Gal. / 13,903 L 4,403 US Gal. / 16,665 L

Turbofans (2×)[59]:65 Rolls-Royce BR715-A1-30 Rolls Royce BR715-C1-30

Thrust (2×)[59]:65 18,920 lbf (84.2 kN) 21,430 lbf (95.3 kN)

Ceiling[59]:67 37,000 ft (11,000 m) maximum

Cruise (34,200 ft)[12] Mach 0.77 (822 km/h; 444 kn)

Range[12] 1,430 nmi (2,648 km) 2,060 nmi (3,815 km)

BOEING 727

Country of Origin
United States of America
Type
Short to medium range narrowbody airliner
History
The 727-100 had been in service barely a year when Boeing began serious consideration of a stretched,
greater capacity development. This resulted in the 727-200, which Boeing announced it was developing
in August 1965. The 727-200 was essentially a minimum change development of the 100, the only major
change being the 6.10m (20ft) fuselage stretch, which increased maximum seating to 189 passengers.
The 727-200's stretch consisted of two 3.05m (10ft) plugs, one forward and one rear of the wing.
Otherwise the 727-100 and 200 shared common engines, fuel tank capacity and the same maximum
takeoff weight. The first flight of the 727-200 occurred on July 27 1967, with certification granted in late
November that year. The -200 was placed into service by launch customer Northeast Airlines (this airline
was later acquired by Delta) the following month, by which time total 727 orders for both models had
exceeded 500. The 727-200 helped broaden the sales appeal of the 727 considerably and snared
significant sales. However the 200 was restricted by its relatively short range, due to it having the same
fuel capacity as the 727-100, so Boeing developed the increased range Advanced 727-200. First flown in
March 1972 changes introduced on the Advanced model included increased fuel capacity, and thus
range, the option of more powerful engines, quieter engine nacelles and strengthened structure. The
Advanced remained the primary 727-200 production model until production ceased in 1984. The 727-200
remains popular with passengers and pilots but it does not meet Stage 3 noise requirements. To
overcome this a number of hushkit programs are on offer while Valsan converted 23 727s to its Stage 3

compliant Quiet 727 standard (before the company collapsed). This retrofit included installing JT8D-217s
on the outer pylons and acoustic treatment of the centre engine. Other 727s have been fitted with
winglets for improved performance.
Powerplants
Three 64.5kN (14,500lb) Pratt & Whitney JT8D-9 turbofans, or 67.2kN (15,000lb) JT8D-11s, or 68.9kN
(15,500lb) JT8D-15s or 71.1kN (16,000lb) JT8D-17s (Advanced only), or 77.3kN (17,400lb) JT8D-17Rs
(Advanced only).
Performance
Advanced 727-200 - Max speed 1017km/h (549kt), max cruising speed 953km/h (515kt), economical
cruising speed 865km/h (467kt). Range with max payload 3965km (2140nm), range with max fuel
4450km (2400nm).
Weights
Advanced 727-200 - Operating empty 45,360kg (100,000lb), max takeoff 95,030kg (209,500lb).
Dimensions
Wing span 32.92m (108ft 0in), length 46.69m (153ft 2in), height 10.36m (34ft 0in). Wing area 157.9m2
(1700sq ft).
Capacity
727-200 - Max seating for 189 at six abreast and 76cm (30in) pitch, typical two class seating for 14
premium class and 131 economy class passengers. 727-200F - Typical max payload comprises 11 2.23m
x 3.17m (7ft 4in x 10ft 5in) pallets.
Production
1831 727s of all models built when production ceased in 1984, including 1249 200s. Approx 940 727-
200s in commercial service at late 1998, with a further 15 as corporate transports.

Boeing 727 Characteristics[80]

Variant 727-100 727-200

Flight three: pilot, copilot, and flight engineer
crew[81]

Two-class 106: 16F@38", 90Y@34" 134: 20F@38",
seats 114Y@34"

One-class 125@34" 155@34"
seats

Exit limit[81] 131 189

Length 133ft2in / 40.59m 153ft2in / 46.68m

Height 34ft3in / 10.44m 34ft11in / 10.65m

Cabin width 140in / 3.56m

Wingspan 108 ft / 32.92m

Wing[40] 1,650 sq ft (153 m2), 32° sweep

MTOW 169,000 lb / 76,700 kg 172,000 lb / 78,100 kg
Adv. 209,500 lb /
95,100 kg

OEW 87,696 lb / 39,800 kg 97,650 lb / 44,330 kg
Adv. 100,700 lb /
45,720 kg

Fuel capacity 7,680gal / 29,069L 8,090USgal / 30,620L
Adv. 10,585USgal /

40,060L

Engines ×3 Pratt & Whitney JT8D- JT8D-7/9/11 (Adv.: -
1/7/9 9/15/17/17R)

Thrust ×3 14,000–14,500 lbf (62– 14,000–15,000 lbf (62–
64 kN) 67 kN)

Adv. 14,500–
17,400 lbf(64–77 kN)

Range[c] 2,250 nmi (4,170 km) 1,900 nmi (3,500 km)
Adv. 2,550 nmi
(4,720 km)

Take-off[d] 8,300 ft (2,500 m) 8,400 ft (2,600 m)
Adv. 10,100 ft (3,100 m)

MMO[81] Mach 0.9 (961 km/h; 519 kn)

Cruise 495 kn/ 917 km/h / 865–953 km/h / 467-
Mach 0.86[82] 515kt [83]

Ceiling[81] 42,000 ft (13,000 m)

BOEING 737

BOEING 757-200

Country of Origin
United States of America
Type
Medium range narrowbody airliner

History
After a slow sales start, the medium range single aisle 757 has become yet another sales success story
for Boeing. Boeing considered a number of proposals for a successor to the 727 tri-jet during the 1970s,
with many of these designs featuring the nose and T-tail of the earlier jet. It was not until later in that
decade however that Boeing settled on a more conventional design featuring the same cross section as
the 727 (not to mention the 737, 707 and 720) but with the fuselage considerably longer in length, an all
new wing, nose and flightdeck and fuel efficient high bypass turbofan engines. Boeing launched
development of the 757 in March 1979 following orders from British Airways and Eastern. Developed in
tandem with the larger widebody 767 the two types share a number of systems and technologies,
including a common early generation EFIS flightdeck. First flight was on February 19 1982 and the 757
entered service in January the following year. Subsequent versions to appear are the 757-200PF
Package Freighter, a pure freighter, and the 757-200M Combi (only one has been built). The standard
passenger aircraft is designated the 757-200, there being no -100. The stretched 757-300 is described
separately. Initial sales of the 757 were fairly slow, however orders picked up significantly in the mid to
late 1980s as traffic on routes previously served by smaller 727s and 737s grew to require the 757's extra
capacity. Today 757 sales comfortably exceed those of the 767, a position that was reversed until the late
1980s.
Powerplants
Two 166.4kN (37,400lb) RollsRoyce RB211-535C turbofans, or 178.8kN (40,200lb) RB211-535E4s, or
193.5kN (43,500lb) RB211-535E4-Bs, or 162.8kN (36,600lb) Pratt & Whitney PW2037s, or two 178.4kN
(40,100lb) PW2040s, or 189.5kN (42,600lb) PW2043s.
Performance
Max cruising speed 914km/h (493kt), economical cruising speed 850km/h (460kt). Range with P&W
engines and 186 passengers 5053km (2728nm), with RR engines 4758km (2569nm). Range at optional
max takeoff weight with P&W engines 7277km (3929nm), with RR engines 6888km (3719nm). 757-
200PF - Speeds same. Range with 22,680kg payload and P&W engines 7195km (3885nm), with RR
engines 6857km (3700nm).
Weights
Operating empty with P&W engines 57,840kg (127,520lb), with RB211s 57,975kg (127,810lb). Basic max
takeoff 99,790kg (220,000lb), medium range MTOW 108,860kg (240,000lb), extended range MTOW
115,665kg (255,000lb) or 115,895kg (255,550lb).
Dimensions
Wing span 38.05m (124ft 10in), length 47.32m (155ft 3in), height 13.56m (44ft 6in). Wing area 185.3m2
(1994sq ft).
Capacity
Flightcrew of two. 757-200 - Typical passenger arrangements vary from 178 two class (16 first & 162
economy), or 202 (12 first & 190 economy) or 208 (12 first and 196 economy) or 214 to 239 in all
economy class. 757-200PF - Maximum of 15 standard 2.24 x 2.74m (88 x 108in) freight pallets on main
deck.
Production
987 757-200s had been ordered by late 2002, of which over 983 had been delivered.

BOEING 757-300

Country of Origin
United States of America
Type
Medium range narrowbody airliner
History
The stretched, 240 seat Boeing 757-300 is the first significant development of the basic 757-200 and is
aimed primarily at the European vacation charter market. Although design work on the original 757 began
in the late 1970s and its entry into service was in 1983, it wasn't until over a decade later in the mid 1990s
that Boeing began to study a stretched development of its popular narrowbody twin. This new 757 stretch
was covered by the 757-300X designation until its launch at the Farnborough Airshow in England in
September 1996. The most obvious change over the 757-200 is the 300's 54.43m (178ft 7in) long
fuselage, which is 7.11m (23ft 4in) longer than the standard aircraft (and only fractionally shorter than the
767-300). This fuselage stretch allows a 20% increase in seating to 225 to 279 passengers, depending on
the interior configuration. Lower hold freight capacity is also increased by 40% over the 757-200 by virtue
of the longer fuselage. Another feature of the 757-300 is its new interior which is based on that developed
for the Next Generation 737 models. Features include a new sculptured ceiling, larger overhead bins,
indirect overhead lighting and vacuum toilets. The 757-300 shares the 200's cockpit, wing, tail and
powerplant options, although the 300 will feature strengthened structure and landing gear to cope with the
increased weights, new wheels, tyres and brakes and a tailskid. The 757-300 first flew on August 2 1998,
with certification in January 1999, and entry into service (with launch customer Condor - the charter arm
of German flag carrier Lufthansa) in March 1999. The -300's 27 month development program from final
configuration to planned first delivery is the fastest for any Boeing airliner (the 777-300 took 31 months for
example). Other early customers are Icelandair, Arkia, Northwest, American Trans Air, Continental, and
JMC Air.
Powerplants
Two 191.7kN (43,100lb) RollsRoyce RB-211-535E4-B turbofans, or 195.1kN (43,850lb) Pratt & Whitney
PW-2043s.
Performance
Cruising speed Mach 0.80. Range with 240 passengers 6055km (3270nm) with RB-211s, 6455km
(3485nm) with PW-2043s.
Weights
Operating empty with RB-211s 64,590kg (142,400lb), with PW-2043s 64,460kg (142,110lb), max takeoff
122,470kg (270,000lb).
Dimensions
Wing span 38.05m (124ft 10in), length 54.47m (178ft 7in), height 13.56m (44ft 6in). Wing area 185.3m2
(1994sq ft).
Capacity
Flightcrew of two. Typical two class arrangement seats 240 passengers, comprising 12 premium class at
91cm (36in) pitch and 228 economy class at 81cm (32in) pitch. Max seating for 289 passengers in a high
density configuration 71-74cm (28-29in) pitch.
Production

63 ordered by May 2002, of which 30 had been delivered.

TUPOLEV Tu-154

Country of Origin
Russia
Type
Medium range airliner
History
Tupolev's Tu-154 tri-jet remains the standard medium range airliner on domestic flights in Russia and
other states of the former Soviet Union and to a lesser extent in eastern Europe and Iran. The Tu-154
was developed to replace the turbojet powered Tupolev Tu-104, plus the An-10 and Il-18 turboprops.
Design criteria in replacing these three relatively diverse aircraft included the ability to operate from gravel
or packed earth airfields, to be able to fly at high altitudes above most Soviet Union air traffic, and good
field performance. To meet these aims the initial Tu-154 design featured three Kuznetsov (now KKBM)
NK-8 turbofans (which also powered the larger, longer range Il-62) giving a relatively good thrust to
weight ratio, triple bogie main undercarriage units which retract into wing pods and a rear engine T-tail
configuration. The Tu-154 first flew on October 4 1968. The first production example was delivered to
Aeroflot in early 1971, although regular commercial service did not begin until February 1972. Three
Kuznetsov powered variants of the Tu-154 were built, the initial Tu-154, the improved Tu-154A with more
powerful engines and a higher max takeoff weight, and the Tu-154B with a further increased max takeoff
weight. Tu-154S is a freighter version of the Tu-154B. Current production is of the Tu-154M, which first
flew in 1982. The major change introduced on the M was the far more economical, quieter and reliable
Soloviev (now Aviadvigatel) turbofans. Low rate production continues. Meanwhile the proposed Tu-154M-
2 with two PS-90A turbofans remains unbuilt.
Powerplants
Tu-154 - Three 93.2kN (20,950lb) Kuznetsov NK-82 turbofans. Tu-154M - Three 103.6kN (23,380lb)
Aviadvigatel (Soloviev) D-30KU-154-II turbofans.
Performance
Tu-154 - Max cruising speed 975km/h (527kt), economical cruising speed 900km/h (486kt), long range
cruising speed 850km/h (460kt). Range with max payload and reserves 3460km (1870nm), range with
max fuel and 13,650kg (31,100lb) payload 5280km (2850nm). Tu-154M - Max cruising speed 950km/h
(513kt). Range with max payload 3900km (2100nm), range with max fuel and 5450kg (12,015lb) payload
6600km (3563nm).
Weights
Tu-154 - Operating empty 43,500kg (95,900lb), max takeoff 90,000kg (198,415lb). Tu-154M - Basic
operating empty 55,300kg (121,915lb), max takeoff 100,000kg (220,460lb).
Dimensions

Wing span 37.55m (123ft 3in), length 47.90m (157ft 2in), height 11.40m (37ft 5in). Wing area 201.5m2
(2168.4sq ft).
Capacity
Flightcrew of three or four. Typical single class seating for 158 to 164 at six abreast, or 167 in a high
density layout for Tu-154; Tu-154M seats a maximum of 180 at six abreast and 75cm (29.5in) seat pitch.
Production
Approximately 900 Tu-154s of all models have been built, including approximately 325 Tu-154Ms. Approx
580 were in service in late 1998.

Measurement Tu-154B-2 Tu-154M

Cockpit crew 5(Tu-154B)-3(Tu-154M)[118]

Seating capacity 114–180

Length 48.0 m (157 ft 6 in)

Wingspan 37.55 m (123 ft 2 in)

Wing area 201.5 m2 (2,169 sq ft)

Height 11.4 m (37 ft 5 in)

Cabin width 3.58 m (11 ft 9 in)[119]

MTOW 98,000–100,000 kg 102,000–104,000 kg
216,000–220,000 lb 225,000–229,000 lb

Empty weight 50,700 kg (111,800 lb) 55,300 kg (121,900 lb)

Maximum speed 913 km/h (493 kn) (Mach 0.86)[120]

Range fully loaded 2,500 km (1,300 nmi) 5,280 km (2,850 nmi)

Range with max fuel 3,900 km (2,100 nmi) 6,600 km (3,600 nmi)

Service ceiling 12,100 m (39,700 ft)

Engine (x 3) Kuznetsov NK-8-2U Soloviev D-30KU-154

Max. thrust (x 3) 90 kN (20,000 lbf) each[121] 103 kN (23,000 lbf) each[121]

Max. fuel capacity 47,000 l (12,000 US gal) 49,700 l (13,100 US gal)

AIRBUS A220

Variant A220-100 (BD-500-1A10)[215] A220-300 (BD-500-1A11)[215]
Cockpit crew
Passengers 2 pilots

Seat pitch 100-120 (135 max)[216] 120-150 (160 max)[216]
Seat width
Cargo volume 28–36 in (71–91 cm) in Y/J 28–38 in (71–97 cm) in Y/J

Length 18.5 to 20 in (47 to 51 cm)
Wing
Height 23.7 m³ / 839 cu.ft 31.6 m³ / 1,118 cu.ft
Fuselage diameter
Cabin 35.00 m / 114' 9" 38.70 m / 127' 0"

35.10 m / 115' 1" span / 112.3 m2(1,209 sq ft) area (10.97 AR)

11.50 m / 38' 8"

3.7 m (12 ft 2 in)

3.28 m / 10' 9" width / 2.11 m (6 ft 11 in) height

Cabin length 23.7 m (78 ft)[217] 27.5 m (90 ft)[218]

MTOW[216] 63.10 t / 139,000 lb 69.90 t / 154,000 lb

Maximum payload 15.1 t (33,300 lb) 18.7 t (41,200 lb)

OEW 77,650 lb (35.22 t)[219] 81,750 lb (37.08 t)[220]

Fuel capacity[216] 21,805 L / 5,760 USgal 21,508 L / 5,681 USgal

Range[216] 6,297 km / 3,400 nmi 6,204 km / 3,350 nmi

Cruise speed Mach .82 (470 kn; 871 km/h) max, Mach .78 (447 kn; 829 km/h)
typical

Takeoff distance 4,800 ft / 1,463 m[217] 6,200 ft / 1,890 m[218]
(MTOW)

Landing distance (MLW) 4,550 ft / 1,387 m[217] 4,950 ft / 1,509 m[218]

Ceiling 41,000 ft / 12,497 m[215]

Engines 2× Pratt & Whitney PW1500G
Unit thrust
18,900–23,300 lbf / 84.1– 21,000–23,300 lbf / 93.4–
103.6 kN 103.6 kN

ICAO type BCS1[221] BCS3[221]

AIRBUS A320



EMBRAER E-jet

Varian E-170 E-175 E-190 E-195
(ERJ170-100) (ERJ170-200) (ERJ190-100) (ERJ190-200)

Awak dek Dua
penerbangan

Kapasitas 80 (1-kelas, 88 (1-kelas, 30") 114 (1-kelas, 122 (1-kelas,
penumpang 29"/30") 86 (1-kelas, 31") 29"/30") 30"/31")
78 (1-kelas, 32")
78 (1-kelas, 106 (1-kelas, 118 (1-kelas,
30"/31") 78 (2-kelas, 31") 31")
standard)
70 (1-kelas, 32") 98 (1-kelas, 32") 108 (1-kelas,
70 (2-kelas, [23] 94 (2-kelas, 32")
36"/32") standard)
106 (2-kelas,
[22] [24] standard)

[25]

Panjang 29,90 m 31,68 m (103 ft 36,24 m (118 ft 38,65 m
Bentang sayap (98 ft 1 in) (126 ft 10 in)
11 in) 11 in)

26,00 m (85 ft 4 in) 28,72 m (94 ft 3 in)

Tinggi 9.67 m 10.28 m
(32 ft 4 in) (34 ft 7 in)

Berat kosong 21140 kg 21810 kg 28080 kg 28970 kg
(46610 pon) (48080 pon) (61910 pon) (63870 pon)

Berat lepas landas 35990 kg 37500 kg 47790 kg 48790 kg
maksimum (79340 pon) (82700 pon) (105360 pon) (107560 pon)
(MTOW)
(STD) (STD) (STD) (STD)
37200 kg 38790 kg 50300 kg 50790 kg
(82000 pon) (85520 pon) (LR) (110900 pon) (111970 pon)
40370 kg
(LR) (89000 pon) (LR) (LR)
38600 kg 51800 kg 52290 kg
(85100 pon) (AR) (114200 pon) (115280 pon)

(AR) (AR) (AR)

Berat muatan 9100 kg 10080 kg 13080 kg 13650 kg
maksimum (20100 pon) (22220 pon) (28840 pon) (30090 pon)
(STD&LR) (STD&LR)

9840 kg 10360 kg
(21690 pon) (22840 pon)

(AR) (AR)

Lepas landas di 1.644 m 2.244 m 2.056 m 2.179 m
MTOW (5.394 ft) (7.362 ft) (6.745 ft) (7.149 ft)

Tenaga 2× GE CF34-8E 2× GE CF34-10E
62,3 kN (13.800 lbf) masing- 82,3 kN (18.500 lbf) masing-masing

masing 89 kN (20.000 lbf) APR masing-
63,2 kN (14.200 lbf) APR masing- masing

masing

Kecepatan 890 km/jam (481 kn, Mach 0.82)
maksimum

Jarak tempuh STD: 3.334 km STD: 3.334 km STD: 3.334 km STD: 2.593 km
(1.800 nmi) (1.800 nmi) (1.800 nmi) (1.400 nmi)
LR: 3.889 km LR: 3.889 km LR: 4.260 km LR: 3.334 km
(2.100 nmi) (2.100 nmi) (2.300 nmi) (1.800 nmi)

AR: 3.892 km AR: 3.706 km AR: 4.448 km AR: 4.077 km
(2.102 nmi) (2.001 nmi) (2.402 nmi) (2.201 nmi)

Kapasitas bahan 9335 kg (20580 pon) 12971 kg (28596 pon)
bakar maksimum
41,000 ft (12,500 m)
Tinggi
penerbangan Max 3,500 FPM

Kecepatan 0.42:1 0.39:1 0.41:1 0.39:1
menanjak
Bentang lambung dan kabin
Daya dorong 3,01 m (9 ft 11 in)
dibanding berat 2,74 m (9 ft 0 in)
3,35 m (11 ft 0 in)
Lebar luar 2,00 m (6 ft 7 in)

Lebar dalam

Tinggi luar

Tinggi dalam

AIRCRAFT YANG BEROPERASI DI INDONESIA
HAWKER 400

General characteristics

 Crew: 2 pilots
 Capacity: 7–9 passengers, 5,600 lb useful load
 Length: 48 ft 5 in (14.76 m)
 Wingspan: 43 ft 10 in (13.36 m)
 Height: 13 ft 11 in (4.24 m)
 Empty weight: 10,500 lb (4,763 kg)
 Max takeoff weight: 16,300 lb (7,394 kg)
 Pressurization: 9.1 psi (0.63 bar)
 Cabin height: 4.75 ft (1.45 m)
 Cabin width: 4.92 ft (1.50 m)
 Powerplant: 2 × Williams International FJ44-4A-32 turbofan, 3,200 lbf (14 kN) thrust

each

Performance

 Maximum speed: 468 kn (539 mph, 866 km/h) (Mach 0.78 MMO)
 Cruise speed: 447 kn (514 mph, 828 km/h) High Speed Cruise, at FL450

 Stall speed: 92 kn (106 mph, 171 km/h) (full flaps)
 Range: 2,160 nmi (2,490 mi, 4,000 km) at 45,000 ft (13,700 m)
 Service ceiling: 45,000 ft (13,700 m)
 Fuel burn at high-speed cruise: 913 lb/h (414 kg/h) at 447 kn TAS at FL450
 Fuel burn at long-range cruise: 761 lb/h (345 kg/h) at 425 kn TAS at FL450

CESSNA CITATION EXCEL

General characteristics

 Crew: 2
 Capacity: 9 passengers and 7,400 lb (4,077 kg) useful load
 Length: 52 ft 6 in (16.0 m)
 Wingspan: 56 ft 4 in (17.17 m)
 Height: 17 ft 2 in (5.23 m)
 Empty weight: 12,800 lb (5,806 kg)
 Max takeoff weight: 20,200 lb (9,163 kg)
 Powerplant: 2 × Pratt & Whitney Canada PW545C turbofans, 4,119 lbf (18.32 kN) thrust

each

Performance

 Cruise speed: 441 kn (507 mph, 816 km/h) true airspeed

 Range: 1,858 nmi (2,138 mi, 3,441 km)
 Service ceiling: 45,000 ft (13,716 m)
 Rate of climb: 3,500 ft/min (17.78 m/s)

BOEING 737

Specifications

Boeing 737 Characteristics[204]

Variant 737-100 737-200 737-300/- 737-600/-700/-800/- 737 MAX-

400/-500 900 7/8/9/10[205][206]

Cockpit Two
crew

2- 85 : 12F 73Y 102 : 14F@38" 126/147/110 108/128/160/177 138/162/178/188
class seats 88Y@34"

1- 103@34" - 115@34" - 140+/159- 123- 153/178/193/204
class seats 118@30" 130@30" 168/122-132 130/140+/175+/177-

215

Exit limit 124 136 149/188/145 149/149/189/220 172/200/220/230

Length 94 ft (29 m) 100 ft 2 in 102–120 ft 102–138 ft (31– 116.7–143.7 ft
(30.53 m) (31–37 m) 42 m) (35.56–43.8 m)

Span 93 ft (28 m) 94 ft 9 in 112 ft 7 in (34.32 m) 117 ft 10 in
(28.88 m) winglets: 117 ft 5 in (35.92 m)

(35.79 m)

Wing[207] 979.9 sq ft (91.04 m2), 25° sweep 1,341.2 sq ft 1,370 sq ft
(124.60 m2) (127 m2)[208]

Height 37 ft (11 m) 36 ft 6 in 41 ft (12 m) 40 ft 4 in
(11.13 m) (12.29 m)

Width Fuselage: 148 inches (3.8 m), Cabin: 139.2 inches (3.54 m)

Cargo 650 cu ft 875 cu ft 882– 720–1,826 cu ft 1,543–1,814 cu ft
(18 m3) (24.8 m3) 1,373 cu ft 20.4–51.7 m3 43.7–51.4 m3
25.0–38.9 m3

MTOW 110,000 lb 128,100 lb 133,500– 144,500–187,700 lb 177,000–
(50,000 kg) (58,100 kg) 150,000 lb 65,500–85,100 kg 194,700 lb
60,600– 80,300–88,300 kg
68,000 kg

OEW 62,000 lb 65,300 lb 70,440– 80,200–98,495 lb MAX 8: 99,360 lb
(28,000 kg) (29,600 kg) 76,760 lb 36,378–44,677 kg 45,070 kg[209]
31,950–
34,820 kg

Fuel 4,720US gal / 5,970US gal / 5,311USgal 6,875-7,837 US gal 6,853 US gal
25,941 L
capacity 17,865L 22,596L[a] 20,100L 26,022-29,666 L

Speed Mach 0.745–Mach 0.82 (430–473 kn; 796– Mach 0.785 (453 kn; 838 km/h) Cruise
876 km/h) Cruise—MMO[208]

Takeoff[b] 6,099 ft 7,500– 6,161–7,598 ft
(1,859 m)[207] 8,690 ft 1,878–2,316 m[207]
2,290–
2,650 m[210]

2,060–

Range 1,540 nmi 2,600 nmi 2,375 nmi 2,935–3,010 nmi 3,300–3,850 nmi
6,110–7,130 km
(2,850 km)[211] (4,800 km)[c][212] 3,815– 5,436–5,575 km[213]

4,398 km[210]

Ceiling[208] 37,000 ft (11,300 m) 41,000 ft (12,500 m)

Engines(×2) Pratt & Whitney JT8D-7/-9/- CFM56-3 CFM56-7 series CFM LEAP-1B
15/-17 series

Thrust(×2) 14,000 lbf 14,500– 20,000– 20,000–27,000 lbf up to 29,300 lbf
(62 kN)[211] 16,400 lbf 23,500 lbf 89–120 kN (130 kN)
64–73 kN[212] 89–105 kN

AIRBUS A320 FAMILY

Specifications[edit]

Subtype A318[35] A319[32] A320[28] A321[29]

Cockpit crew Two

Exit 136 160 195/190 230

limit EASA[87]/FAA[1

13]

1-class max. 132 at 29–30 in 156 at 28–30 in 186 at 29 in 236 at 28 in
seating[114] (74–76 cm) pitch (71–76 cm) pitch (74 cm) pitch[115] (71 cm) pitch[116]

1-class, typical[114] 117 at 32 in 134 at 32 in 164 at 32 in 199 at 32 in
(81 cm) pitch (81 cm) pitch (81 cm) pitch (81 cm) pitch

2-class, typical[114] 107 (8F @ 38 in, 124 (8F @ 38 in, 150 (12F @ 36 in, 185 (16F @ 36 in,
138Y @ 32 in) 169Y @ 32 in)
99Y @ 32 in) 116Y @ 32 in)

Cargo volume 21.20 m3(749 cu f 27.70 m3(978 cu f 37.40 m3(1,321 cu f 51.70 m3(1,826 cu f

t) t) t) t)

Unit load devices 4× LD3-45 7× LD3-45 10× LD3-45

Length 31.44 m (103 ft 33.84 m (111 ft 37.57 m (123 ft 44.51 m (146 ft
2 in) 0 in) 3 in) 0 in)

Wingspan 34.10 m (111 ft 35.8 m (117 ft 5 in) [c]
11 in)

Wing area[27] 124 m2 (1,330 sq ft), 10.3 aspect ratio 128 m2(1,380 sq ft)
, 10 AR

Wingsweep 25 degrees[117]

Height 12.56 m (41 ft 11.76 m (38 ft 7 in)
2 in)

Fuselage 4.14 m (13 ft 7 in) height, 3.95 m (13 ft 0 in) width, 3.70 m (12 ft 2 in) cabin width

MTOW 68 t (150,000 lb) 75.5 t 78 t (172,000 lb) 93.5 t (206,000 lb)
(166,000 lb)

Max. payload 15 t (33,000 lb) 17.7 t (39,000 lb) 19.9 t (44,000 lb) 25.3 t (56,000 lb)

Fuel capacity 24,210 L 24,210–30,190 L 24,210–27,200 L 24,050–30,030 L
6,400 US gal 6,400– 6,400– 6,350–

7,980 US gal 7,190 US gal 7,930 US gal

OEW[114] 39.5 t (87,100 lb) 40.8 t (89,900 lb) 42.6 t (93,900 lb) 48.5 t (107,000 lb)