Fokker 100

The Netherlands


  Development
 

The Fokker 100 is a medium size twin-turbofan airliner from former Fokker. Low operational costs and scant competition in the 100-seat short-range class led to strong sales when it was introduced in the late 1980s, but sales fell as competition increased. Production ended in 1997 with 283 airplanes delivered. In August 2009, 229 Fokker 100 aircraft remained in airline service with 47 airlines around the world.

Fokker began the search for an F28 replacement with the 110/130 seat 'SUPER F28', for service entry in 1984. This later became the F29 project, and the manufacturer even considered using Boeing 737 fuselages for a maximum of 180 seats. This did not materialize, and Fokker along with McDonnell Douglas, drew up plans for a 150 seat 737 look alike, known as the MDF-100. This also never came to be.

Fokker choose to stretch its twin-engine F-28, replacing the original Rolls-Royce 182-3 spey by a pair of Rolls-Royce Tay 620 engines. The Fokker 100 does not have eyebrow windows above the main cockpit windows as on the Fokker F28 and featured a new generation avionics at that time. This way the F-100 airliner was born. The aircraft project was given the name of F.28-100. F-100 development began in 1983 and the first prototype flew in November 1986. The F-100 was built as an international project with MBB (later DASA) building the center fuselage and tail, and Shorts Brothers building the wings. The Fokker 100 is a complete redesign of the Fokker 50, which rivals the BAE 146. It had longer wings, a longer fuselage that would seat over 100 passengers and a "glass" cockpit featuring 6 large displays.

The F-100 booked its first order, 10 aircraft for Swissair, in 1984, these beginning to be delivered in 1988. After the first order, it would be three long years before another order was booked. In 1986 Fokker signed an agreement with GPA (an Ireland based lease company) forming GPA Fokker 100 Ltd. which purchased aircraft and placed them with airlines around the world. In 1988, Fokker flew an uprated Tay 650 powered version, which American Airlines ordered 75 aircraft with 75 options. US Air also ordered this version.

The Tay powered F-100 was regarded as a sports car by the pilots who flew it. Not lacking in power it has been common to see them take-off without the use of flaps, and power management was key to keep it from over-speeding at cruise.

Although there are no subtypes, the F-100 was available with many seating and exit/door configurations. After a slow start the F-100 experienced tremendous success with 290 aircraft ordered from 18 countries by December 1995 but due to the demise of Fokker Aircraft BV in 1997, production ceased.

 

Exterior Dimensions


Horizontal tail
Wing
Area:

21.72 m2

CL,max @ takeoff:

2.17

Area:

93.5 m2

Aspect ratio:

4.64

Taper ratio:

0.235

Aspect ratio:

8.43

Quarter-chord sweepback angle:

26o

Quarter-chord sweepback angle:

17.45o

Mean aerodynamic chord:

3.80 m


Interior Dimensions


Standard layout for 107 seats @ 32"pitch

A = Cabin attendant seat
G = Gallery
L = Lavatory
S = Stowage
W = Wardrobe
C = Carry-on baggage compartment

Cabin length (excl. flight deck) 21.19 m (69 ft 6.2 in)
Cabin width   3.10 m (10 ft 2.0 in)
Cabin height   2.01 m   (6 ft 7.0 in)

Interior Volumes

Overhead bins   5.15 m3 (182 ft3)
Stowage’s / Wardrobes   1.70 m3   (60 ft3)
Carry-on baggage compartment   1.30 m3   (46 ft3)
Forward cargo hold   9.48 m3 (335 ft3)
Aft cargo hold   7.24 m3 (256 ft3)
Total luggage & cargo volume 24.87 m3 (879 ft3) excluding under-seat stowage

 


Weights

EMPTY WEIGHTS
Fokker 100 with Tay 620 engines:
Fokker 100 with Tay 650 engines:
Fokker 100 with Tay 650 engines and
MTOW of 45,810kg (101.000 lb):
24,593 kg (54,217 lb)
24,727 kg (54,514 lb)

24,747 kg (54,558 lb)

 

WEIGHTS

Standard weights Intermediate optional weights

High optional weights
(with Tay 650 engines)

MTW
MTOW
MLW
MZFW
MSP (Tay 620 engines)
MSP (Tay 650 engines)
43,320 kg (95,500 lb)
43,090 kg (95,000 lb)
38,780 kg (85,500 lb)
35,835 kg (79,000 lb)
11,242 kg (24,783 lb)
11,108 kg (24,486 lb)
44,680 kg (98,500 lb)
44,450 kg (98,000 lb)
39,915 kg (88,000 lb)
36,740 kg (81,000 lb)
12,147 kg (26,783 lb)
12,013 kg (26,486 lb)
46,040 kg (101,500 lb)
45,810 kg (101,000 lb)
39,915 kg ( 88,000 lb)
36,740 kg ( 81,000 lb)
----------
11,993 kg (26,442 lb)

 

FUEL
Fuel capacity:
At Fuel Density 0.8029 kg/l (6.70 lb/USGal):
13,365 l (3,531 USGal)

10.731 kg (23,658 lb)

 


Performance

MAXIMUM SPEEDS
Vmo: 320 kts CAS
Mmo: 0.77
Maximum TAS: 462 kts (856 km/hr)

 

MAXIMUM OPERATING ALTITUDE
Service ceiling: 35,000 ft (10,667 m)

 

LANDING FIELD LENGTH
At Sea-level
At 2,000 ft elevation
Conditions:
4,180 ft (1,275 m)
4,360 ft (1,330 m)
- Typical landing field length
- No wind
- No slope
- Dry runway
- Independent of temperature

 

PERFORMANCE ASSUMPTION
Reserves:


Maneuvering allowances:
En-route:
Payload:
Overshoot at destination to 1,500 ft
200 nm diversion at minimum fuel speed schedule
45 min. holding at alternate destination at 1,500 ft
22 minutes and 500 kg (1,100 lb) fuel
ISA, no wind
107 passengers @ 91 kg (200 lb)

 

PAYLOAD vs RANGE with TAY 620 ENGINES

 BLOCK TIME vs RANGE

BLOCK FUEL vs RANGE

TAKE-OFF FIELD LENGTH vs RANGE


Technical Highlights

ENGINE

Max. Take-off thrust (ISA, Sea-level, static)
Flat-rated to
Bypass Ration
Overall Ratio
Pressure Ratio
Fan Diameter
Length
Cruise Fuel Consumption
Basic Engine Weight
Rolls-Royce Tay 620
6,282 kg (13,850 lb)
30�C (86�F)
3.04:1
16.0
15.8:1
44.0"
94.8"
0.69 lb/hr/lb
3135 lb
Rolls-Royce Tay 650
6,849 kg (15,100 lb)
30�C (86�F)
3.06:1
16.4
16.2:1
44.8"
94.8"
0.69 lb/hr/lb
3340 lb
EXTERIOR NOISE   (EPNdb)

MTOW
MLW

A=Fly-over   B=Side-line   C=Approach
Chapter 3 / Stage III limit
Certification noise level
Margin
Rolls-Royce Tay 620
43,090 kg (95,000 lb)
38,870 kg (85,500 lb)

  A          B         C 
89.0      94.8     98.7
83.4      89.3     93.1
-5.6        -5.5     -5.6
Rolls-Royce Tay 650
44,450 kg (98,000 lb)
39,915 kg (88,000 lb)

  A          B         C 
89.0      94.9     98.8
81.8      91.7     93.0
-7.2       -3.2      -5.8
AUXILIARY POWER UNIT (APU)
Type Garrett GTCP 36-150rr

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