fokker 50 limitations

GENERAL LIMITATIONS

Minimum crew

Cockpit: Two pilots Maximum number of passenger seats

Sixty-two (62) Maximum operating altitudes

Maximum operating pressure altitude: 25.000 feet

Maximum take-off and landing pressure altitude: 8.000 feet

Maximum and minimum operating temperatures

Maximum: ISA +35ºC Minimum: Minus 54ºC (all altitudes) Runway slope limits

Take-off and landing: 2% up to 2% down Manoeuvring load limits

Flaps up: +2.5 G to -1.0 G Flaps down: +2.0 G to 0.0 G The positive G limits the angle of bank in turns and the severity of pull up manoeuvres. Instrument colour markings

Normal operating range: Green Caution range: Amber Limit of operation: Red

��MASS LIMITATIONS

Maximum masses

Maximum masses KG

Ramp / taxi 20.865 Take-off* 20.820 Landing* 19.730 Zero Fuel 18.600 * May be reduced by performance requirements.

Fokker 50 - Limitations

Center of gravity


SPEED LIMITATIONS

All speed limitations in KIAS unless indicated otherwise. All altitudes mentioned in this section are pressure altitudes. Maximum operating limit speed (Vmo)

Up to 21.000 feet: 224 KIAS

Above 21.000 feet: Vmo decreases linearly to reach 206 KIAS at 25.000 feet

The maximum operating speed shall not deliberately be exceeded in any regime of flight (climb, cruise or descent), except where a higher speed is specifically authorized for test flight purposes. Maximum design manoeuvring (Va)

Va: 175 KIAS Full application of rudder and/or aileron controls, as well as manoeuvres that involve an angle of attack near the stall should be confined to speeds below Va. Rough air speed (Vr)

Vr: 165 KIAS Maximum flap extend speed (Vfe)

5º: 180 KIAS 10º: 180 KIAS 15º: 180 KIAS 20º: 160 KIAS 25º: 160 KIAS 35º: 140 KIAS Prolonged use of flaps other than for take-off and landing is prohibited. Maximum landing gear operating speeds (Vlo = Vle)

Extension (Vle): 170 KIAS Operating (Vlo): 170 KIAS


Minimum control speeds (upper limits) (Vmca, Vmcg, Vmcl)

Minimum control speed Flap setting KIAS Vmca 5º 87

Vmca 10º 86

Vmca 15º 85

Vmcg 5º 80

Vmcg 10º 84

Vmcg 15º 84

Vmcl 25º 90

Vmcl 35º 90

Minimum manoeuvring speeds and flap setting

Flap setting Minimum manoeuvring speed 0º 140 KIAS

10º 130 KIAS

20º 120 KIAS

25º 110 KIAS

Bank angle limits

Below minimum manoeuvring speed: 15º Maximum bank angle: 30�

Manoeuvring speed after take-off

Normal manoeuvring speed after take-off: Flaps extended: V2 + 10 KIAS Flaps retracted: Vfr + 10 KIAS Climb speeds

If climb speed is reduced to below 140 KIAS a rather pronounced propeller induced airframe vibration will occur. Window heat unserviceable speed limitation

If the window heat is inoperative the speed must be restricted to maximum 180 KIAS at

altitudes below 10.000 ft and TAT below 18�C.


Stall speeds

FAA stall speed The stall speed graph below provides FAA stall speeds for low altitudes and at various flapsettings. The stall speeds, which largely depend on the flight techniques used to enter the stall, are obtained under the following conditions:

• Aircraft correctly trimmed for straight and level flight at a steady speed 20-40% above the expected stall speed.

• No pre-stall-entry trim changes

• Speed reduced by elevator control at approximately 1 knot per second.

• Idle thrust

• Forward center of gravity position

The FAA stall speed is used to set the legal minima for take-off manoeuvring and landing speeds. 1 G stall speed The 1 G stall speed is the speed corresponding to an angle of attack at which Clmax is reached. At lower speeds the lift becomes less than the aircraft weight and the aircraft commences to sink. The 1 G stall speeds are slightly higher than the FAA stall speeds.


WEATHER LIMITATIONS

1.5.1. Maximum wind velocities (including gusts)

Maximum wind velocities from any direction for which the flight control lock provides protection.

65 Kts

Maximum demonstrated crosswind component for take-off and landing on a hard dry runway.

33 Kts

Maximum tailwind component 10 Kts

For CAT II operation the maximum demonstrated wind velocities are:

• Total wind 20 Kts

• Crosswind component 15 Kts

• Tailwind component 10 Kts

Maximum crosswind and tailwind components, against braking action

Coefficient Braking action Maximum crosswind component

Maximum tailwind component

0.40 and above 5 / good 33 10

0.39 - 0.36 4 / good/medium 25 7

0.35 - 0.30 3 / medium 15 5

0.29 - 0.26 2 / medium/poor 10 3

0.25 and below 1 / poor 5 0

Operation from contaminated runway

Maximum depth of precipitation on the runway for take-off. Take-off should not be attempted when more than 12.7 mm of standing water, or depth of slush or snow equivalent to more than 12.7 mm of water, covers a significant part of the required field length within the required width of the runway. Use Route Performance Manual to determine maximum allowed take-off mass and required take-off speeds. Crosswind limit with runway width less than 40 meters

If the usable runway width is less than 40 m, the maximum allowed crosswind components must be reduced according to the table below:

Usable runway width (m) 39 35 30

Crosswind reduction (Kts) 1 5 10


Maximum door operation limit

Doors The maximum wind speed, including gusts, for operation of any door is 64 KIAS. NOTE: Service doors (3): Above 22 KIAS (incl. gusts) take extreme care, not to

release the door before the completely closed- or open position has been reached.


POWER PLANT LIMITATIONS

1.6.1. Engine and propeller type

Engine: Pratt & Whitney PW 125 B Propeller: Dowty Rotol © R352/6 - 123 - F/1

Dowty Rotol © R352/6 - 123 - F/2

Engine and propeller limitations

CONDITION TIME TORQUE ITT RPM (%) (%) (2) (�C) Nh Nl Np (1) MAX. TO/GA 10 min 102 800 102.7 104.7 100

NORMAL TO 10 min 92 See

graph 101.6 101.6 100

MAX. CONT Unlimited 87.5 800 102.7 104.7 100

MAX. CLIMB Unlimited 100 800 - - 85

MIN. GND IDLE - - - 66 - -

STARTING 5 sec - 950 - - -

TRANSIENT 20 sec 115 840 103.8 104.3 115

For operation with PROP EC fault (overspeed governor):

CONDITION TIME TORQUE ITT RPM (%) (%) (�C) Nh Nl Np (1) MAX. TO/GA 10 min 96 800 102.7 104 106

MAX. CONTINOUS Unlimited 82.5 800 102.7 104 106

NOTE: • Np fluctuations of +/- 0.5% are allowed relative to 85% and 100%.

• Torque fluctuations +/- 2% during take-off roll (at 60KIAS) and climb are considered acceptable.

• Torque fluctuations +/- 1% during cruise are considered acceptable. • Torque split of 6% during cruise is considered acceptable.


Propeller operating limits WARNING: Do not attempt to select ground idle in flight. In case of failure of the flight

idle stop, this would lead to loss of control from which recovery may not be possible.

To avoid high propeller stresses, stabilised ground operation in the propeller RPM range of 65% to 90% NP is not permitted with the airplane static. Excluded from this limitation is the use of reverse during ground manoeuvring in engine EC operating mode. Manual propeller control

When the propeller is manually controlled the speed must be restricted to max. 220 KTAS. NOTE: This specific speed limit is expressed in Knots True Air Speed (KTAS)

instead of the usual KIAS!

Oil pressure

Minimum 40 Psi

Normal operating range 55 – 65 Psi

Transient Minimum

Maximum

40 Psi

100 Psi

Oil temperature

For starting Minimum (without preheat) - 54�C

GND IDLE

Minimum Maximum

- 54�C

+115�C

Minimum 0�C Minimum in icing conditions +45�C, on both engines for

more than 3 minutes before take-off. (The 3 minute period starts when the oil temperature

of both engines is above 45�C)

Maximum, continuous +115�C

Operation above GND IDLE

Maximum, 20 minutes +125�C


Approved oils

Mobil Jet on II Mobil Jet on 254 Castrol 5000 Esso Turbo on 2380 Exxon Turbo on 2380 Aeroshell Turbine 01 500 Auxiliary Power Unit (APU)

The Auxiliary Power Unit (APU) may be used on the ground only.


FUEL SYSTEM LIMITATIONS

Approved fuels

Normal Fuels Type Kerosene type Jet A, Jet A-1 and military equivalent High flash point JP-5

Alternate Fuels* Type Wide-cut fuel Jet B and military equivalent NOTE: * If 'alternate' fuel is used, take-off is not allowed when one or more fuel

pumps are inoperative. Mixing of fuels

If the fuel consists of a mixture of 'normal' and ‘any amount of alternate fuel’, the tanks must be considered to contain 'alternate' fuel. Usable fuel tank capacity

Main tank 5136 Litres

(including collector tank) 4160 Kilograms

(at 15�C and 0.81 kg/litre)

Maximum fuel asymmetry

Aircraft mass (kg) Maximum fuel asymmetry 20820* 150 kg

19.005 and below 500 kg

*Linear interpolation may be applied between 19.005 and 20.820 kg.


AUTOPILOT LIMITATIONS

En route operation

The minimum altitude with the autopilot engaged shall be deducted from data on altitude lost during malfunction test as presented in section 3 Emergency Procedures. Approaches

When using an instrument approach facility, the minimum height to which the autopilot may be used is 50 feet when coupled to an ILS. Use of the AP and FD is limited to glide slope elevation angles ranging from 2º up to and including 4º for approaches with CAT 1 weather limits. CAT II operations are limited to glideslope elevation angles ranging from 2.5 degrees up to and including 3 degrees. Use of touch-control steering

When Touch-Control Steering (TCS) is used the bank angle is limited to 40º.


MISCELLANEOUS LIMITATIONS

Cabin differential pressure

Maximum differential pressure: (relief valve setting).

5.7 Psi

In case of cracked cabin window: 4.0 Psi

Maximum bank angle below 500 feet

If a turn is required below 500 feet AGL limit bank angle to 15�. Communications

During flight below 10.000 feet all communications should be accomplished with headset and boommike type equipment. Flap position in icing conditions

In icing conditions flap 35� shall not be selected above 300 feet AAL. Noise limitations

Compliance with the ICAO Annex 18 Chapter 3 limits has been shown for the following configurations:

• Take-off with flaps 5�

• Approach flaps 25�; two engines

• Approach flaps 35�; two engines

Electrical limitations

Display selector LH electric display RH electric display GENERATOR

LOAD (%) GEN 1 GEN 2

Continuous 100 5 minutes 113 5 seconds 150

TRU LOAD (5)

TRU 1 TRU 2

Continuous 100 2 minutes 133 5 seconds 300


fokker 50 limitations

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