omwings Fokker F-28 Fellowship
 
  OPERATING LIMITATIONS
 
 
  NOTE: Modified for MS Flight Simulator, do not use in real aircraft
 
  1.01   Maximum Operating Weights
1.02   Fuel Distribution
1.03   Loading
1.04   Center of Gravity
1.05   Speed Limitations
1.06   Flight Load Accelleration Limits
1.07   Operational Limitations
1.08   Engines
1.09   Fuel System
1.10   Center Wing Tank
1.11   Auxiliary Power Unit
1.12   Automatic Pilot
1.13   Maximum Fueling and Defueling Pressure
1.14   Electrical System
1.15   Cabin Pressurization
1.16   Instrument Colour Marking
1.17   Hydraulic System
1.18   Take-off and Landing Speeds
 
 
  1.01 Maximum Operating Weights  
           
    MAXIMUM TAKE-OFF / LANDING WEIGHT

The maximum weight approved for take-off varies with airport altitude,
ambient field static air temperature, available runway length, runway
slope and wind component existing at time of take-off.

The Maximum Take-off Weight shall in no case exceed
29,480 kg (65,000 lb).

The Maximum Landing Weight shall in no case exceed
26,760 kg (59,000 lb).

MAXIMUM ZERO FUEL WEIGHT 24,720 kg (54,500lb)
 
 
  1.02 Fuel Distribution  
           
    Fuel must be distributed between the two main tanks in such a way,
that an asymmetry of 680 kg (1,500 lb) is not exceeded.
 
 
  1.03 Loading  
           
    The aircraft must be loaded in accordance with an approved loading
schedule based upon authorized weights and associated center of
grafity limits.
 
 
  1.04 Center of Gravity  
           
    The center of grafity of the aircraft must be maintained between the
forward and aft limits shown in the table appropriate to the conditions.

The center of gravity limits as shown, apply to the landing gear extended
and retracted configuration.

The datum referred to is Station 0, which is located 2220 mm
(87.4 inches) in front of forward leveling pin in nose wheelbay
(tip of a/c nose).

The Mean Aerodynamic Chord (MAC) is 3506 mm (138.03 inches).
The leading edge of the Mean Aerodynamic Chord is 10797,5 mm
(425,10 inches) aft of datum.

The following center of gravity limits shall be adhered to:
 

Landing Gear Extended

Gross Weight

Forward

Aft

 

Aft of datum

%MAC

Aft of datum

%MAC

kgf

lbf

mm

inches

mm

inches


29,480

27,800

and lower

 
65,000

60,800

and
lower


11466

11429

11429
 


451,43

449,95

449,95
 


19,07

18,00

18,00
 


12025

12025

12025
 


473.41

473,41

473,41
 


35,00

35,00

35,00
 
 
 

Landing Gear Retracted

Gross Weight

Forward

Aft

 

Aft of datum

%MAC

Aft of datum

%MAC

kgf

lbf

mm

inches

mm

inches


29,480

27,440

and lower

 
65,000

60,500

and
lower


11437

11393

11393
 


450,27

448,56

448,56
 


18,24

17,00

17,00
 


12095

12095

12095
 


476.17

476,17

476,17
 


37,00

37,00

37,00
 
 

The C of G limits for weights between the given figures shall be interpolated linearly.
 
 
  1.05 Speed Limitations  
           
    Unless otherwise designated, all speeds in this F-28 Flight Handbook
are indicated airspeeds (IAS).

VMO / MMO MAXIMUM OPERATING SPEED

The maximum operating speed shall not be deliberately exceeded in
any regime of flight (climb, cruise or descent), expect where a higher
speed is specifically authorized for flight test or pilot training operations.

VD / MD MAXIMUM DESIGN DIVING SPEED
 

 
 
    VA MANOEUVRING SPEED

The manoeuvring speeds to be adhered to are limited by those
manoeuveres involving either angles of attack near the stall or by
loads due to full application of rudder and aileron controls.
 

 
 
    VFE MAXIMUM FLAP EXTENDED SPEED AND ALTITUDE

Flapsettings:

up to 25 deg.

      200 Knots IAS up to 15,000 ft
      180 Knots IAS up to 20,000 ft

42 deg.

       165 Knots IAS up to 20,000 ft

VLO MAXIMUM LANDING GEAR OPERATING SPEED AND ALTITUDE

The maximum speed at which the landing gear may be extended or retracted is:

      200 Knots IAS up to 15,000 ft
      180 Knots IAS up to 20,000 ft

Note: The nose landing gear may not retract at speeds above
         180 Knots IAS.

VLE MAXIMUM LANDING GEAR EXTENDED SPEED AND ALTITUDE

The maximum speed with landing gear extended and locked is:

      200 Knots IAS up to 15,000 ft
      180 Knots IAS up to 20,000 ft

MAXIMUM LANDING,
TAXI AND FLARE-OUT LIGHTS EXTENDED SPEED

VMO / MMO is the maximum speed with the landing lights, taxi lights
                 and flare-out lights extended.

MAIN LANDING GEAR DOOR,
MAXIMUM ALTERNATE RETRACTION SPEED

The maximum speed during retraction of the wheel doors by means
of the winch is:

Flapsettings: 25 deg. 155 Knots IAS
                    42 deg. 140 Knots IAS

The maximum speed after wheel doors have been retracted to the intermediate position, (door not fully closed) by means of the winch is:

Flapsettings: 25 deg. 180 Knots IAS
                    42 deg. 155 Knots IAS
 
 
  1.06 Flight Load Accelleration Limits  
           
    Flap up :    + 2.5 g and – 1.0 g
Flap down: + 2.0 g and 0.0 g

The above acceleration limits restrict the permissible severity of pull-up manoeuvres and restrict the permissible angle of bank in coordinated steady level turns for flap UP to 66 degrees and for flap DOWN to 60 degrees.
 
 
  1.07 Operational Limitations  
           
    Runway slope   + 2% up to -2%
    Limiting tail wind component   10 knots
    Maximum operating altitude   35,000 ft
    Maximum take-off and landing altitude   8,000 ft
    Minimum take-off and landing altitude   -1,000 ft
    Maximum take-off and landing and
enroute temp.
 
ISA + 35 deg. C
    Minimum take-off and landing temperature   -54 deg. C
    Minimum enroute temperature   -70 deg. C
    Maximum crosswind   30 knots
 
 
  1.08 Engines  
           
    Manufacturer: Rolls-Royce Limited
Number and Type: (2) Two-shaft Bypass Jet Engines
“RB.183” MK.555-15P.
Bypass Ratio: 1.0
 

Engine Limitations

Conditions

% HP RPM

% LP RPM

TGT (°C)

Time Limit


Starting and Relight
 

-

-

570

2 seconds


Max. Take-off
 

102.5

109.5

565

10 minutes
(see note 1)


Max. Continuous

Operational
essential

Climb

Cruise
 



98.5
 

97.5

96.5

95.0
 



108.5
 

108.5

108.5

108.5
 



520
 

510

500

480
 



Unrestricted
 

-

-

-
 


Ground Idle
 

51.0 – 52.0

-

520

(see note 2)


Max. Overspeed
 

105.5

115.5

-

20 seconds
(see note 3)


Max. Overspeed
rature during
take-off
 


-


-


585


20 seconds
 
    Notes:

1. Use of maximum take-off power for normal schedule operation is
    limited to a maximum period of 5 minutes. In the event of an engine
    failure the remaining engine may be operated at take-off power for
    maximum total period of 10 minutes.

2. These limits are adjustment limits, applicable to a warm engine.
    For a cold engine, directly after starting, the limit is 47% to
    53% HP rpm.

3. If the overspeed limitations (RPM or time) are exceeded, the engine
    should be shut down.

 

OIL PRESSURE

Minimum acceptance at max. take-off rpm            34 psi.
Minimum to complete flight at max. cont. rpm.      25 psi.
Normal at max. continuous rpm                           30 – 55 psi.
Minimum at ground idling                                    16 psi.
 

OIL TEMPERATURE

Conditions

Temp.

Time

Remarks

Maximum

+120 deg C

15 minutes

Maximum during transient overshoots on reducing rpm at top of climb

 
Maximum
 

 
+100 deg C

 
Unrestricted

 


Minimum
 


 -40 deg C

 
For starting

 

 
Minimum
 


 -30 deg C

 
For opening up

 
 
    OIL QUANTITIES

System total capacity : 13.6 Litres or 3.6 U.S.Gal. or 3.0 Imp.Gal.
Oil tank capacity :          6.8 Litres or 1.8 U.S.Gal. or 1.5 Imp.Gal.
Usable oil :                    5.1 Litres or 1.35 U.S.Gal. or 1.1 Imp.Gal.
 
 
  1.09 Fuel System  
           
    USABLE FUEL

Maximum usable fuel in main tanks (total)

Pressure fueling : 9,640 Litres or 2.551 U.S.Gal. or 2.121 Imp.Gal.
Overwing fueling : 9,740 Litres or 2.573 U.S.Gal. or 2.143 Imp.Gal.

Center wing tank (if installed): 3,300 Litres or 882 U.S.Gal. or 726 Imp.Gal.


Center wing tank, freight configuration:
3,100 Litres or 820 U.S.Gal. or 683 Imp.Gal.


FUEL TEMPERATURE

Maximum at HP pump inlet (15 minutes) + 110 deg C
(Maximum during transient overshoots on reducing rpm at top of climb)

Maximum at HP pump inlet (unrestricted) + 90 deg C
 
 
  1.10 Center Wing Tank (if installed)  
           
    - If the required fuel load exceeds the capacity of the main tanks, the
  center wing tank may be filled with the excess only.

- In flight the center wing tank fuel load must be transferred to the main
  tanks as soon as the fuel load remaining in each main tank is 2,948 kg
  (6,500 lb).
 
 
  1.11 Auxiliary Power Unit  
           

Condition

Max. RPM (%)

Max. TGT (deg C)


Start

Transient 10 seconds

Unrestricted
 


-

110

105
 


705

705

650
 
 
 
  1.12 Automatic Pilot  
           
    With the autopilot engaged the following applies:

> One pilot shall be strapped in his seat
> VMO / MMO and VFE shall be adhered to

The minimum height down to which the autopilot may be used during
coupled ILS-approaches is 50 ft.

Wind velocity limits for CAT 2 operations are:
      Max. wind velocity :            20 knots
      Max. crosswind velocity :    15 knots
      Max. tailwind velocity :        10 knots
 
 
  1.13 Maximum Fueling and Defueling Pressures  
           
    Maximum allowable fueling pressure at the hose connection: 50 psi.
Defueling suction : 11 psi.
 
 
  1.14 Electrical System  
           
    GENERATORS ( include APU generator)    
           
    Continuous rating of each generator:
 		   20 KVA
(1.0 AC load meter)
           
    Overload rating of each generator:
 		   25 KVA for 3 hours
(1.25 AC load meter)
     
    TRANSFORMER RECTIFIER UNITS
         
    Continuous rating of each TRU:   100 A (28 V DC)
         
    C.S.D. Limitations

OIL TEMPERATURE
         
    Max. oil inlet temperature
(unrestricted)		   120 deg C
 
         
    Max. oil inlet temperature
(15 minutes)

 		   140 deg C
(Maximum during transient overshoot on
reducing rpm)
         
    Max. oil temperature rise
(normal operation)		   10 deg C
(Toutlet – Tinlet)
         
    Max. oil temperature rise
(full generator load and / or
 single generator operation)		   15 deg C
(Toutlet – Tinlet)
 
 
 
  1.15 Cabin Pressurization  
           
    The maximum cabin pressure differential (relief valve setting) is 7.75 psi.
The cabin must be depressurized for landing.
 
 
  1.16 Instrument Colour Marking  
           
    GREEN    - Normal Operating Range
YELLOW  - Caution Range
RED         - Limit of Operation
 
 
  1.17 Hydraulic System  
           
   

The hydraulic pressure must be 3000 psi.

 +200
-100
 
 
  1.18 Take-Off and Landing Speeds  
           
    The take-off and landing speeds are obtained as follows:

It is assumed that V1 = VR.

For take–off with flaps 28 deg or 11 deg the take-off speeds are based
on V2 0 = 1.20 VS

For take-off with flaps 6 deg V2´s ranging from 1.20 to 1.30 VS may be scheduled in order to increase the take-off weight for those conditions where sufficient runway length is available but a climb limit exists.

Enter the booklet at the correct weight page.
On the lower chart find V2, VFR and VFC for the particular flap setting.

To calculate VR:

Enter the upper chart at the field elevation, move horizontally to the OAT line and vertically to the particular flap bracket and find ^V.
Substract ^V from V2 to find VR (=V1).
At the bottom of the lower page the threshold speeds for landing are presented.
 

 

TAKE-OFF

FLAP

6°

11°

18°

V2 / VS

1.20

1.25

1.30

V2

142

148

153

136

131

VFR 0

151

153

151

VFC

178
 
 

LANDING

FLAP

0°

25°

42°

VTHR

163

136

125