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weight and performance calculations for the Fokker F28 Fellowship Mk.1000
***** PRELIMINARY FILE ****
Aero Continente F28 Mk.1000 coming in for landing.
Fokker F28 Fellowship Mk.1000
role : jet airliner
importance : ****
first flight : operational : March 1969
country : The Netherlands
design :
production : 60 aircraft
general information :
Cabin width : 3.10 [m] cabin length : 13.10 [m] cabin height : 2.02 [m]
Fuel consumption : 2800 kg/h at max cruise speed 848 km/hr (3.3 kg/km) 1480 kg/hr
at econ. Cruise speed 666 km/hr (2.2 kg/km)
primary users : KLM
Accommodation:
flight crew : 2 cabin crew : 3
passengers : seating for 65 in all- economy- class seats ( 31 -in pitch)
engine : 2 Rolls Royce Spey Junior RB-183-2 turbofan engines of 43.82 [KN](9851.0 [lbf])
dimensions :
wingspan : 23.58 [m], length : 27.4 [m], height : 8.47 [m]
wing area : 76.4 [m^2]
weights :
operating empty weight : 16144 [kg] max. structural payload : 8629 [kg]
Zero Fuel weight (ZFW) : 24773 [kg] max. landing weight (MLW) : 0 [kg]
max.take-off weight : 29480 [kg] weight fuel : 10432 [kg] (13040 [liter])
performance :
Max. operating Mach number (Mmo) : 0.75 [Mach] (848 [km/hr]) at 6400 [m]
normal cruise speed : 817 [km/hr] (Mach 0.76 ) at 10000 [m] (30 [%] power)
service ceiling : 10700 [m]
range with max fuel : 3280 [km] and allowance for 329.3 [km] diversion and 30 [min] hold
description :
low-wing cantilever monoplane with retractable landing gear with nose wheel
tapered multi-cellular wing with flush-riveted stressed skin
with Fowler flaps airfoil : NACA
sweep angle 3/4 chord: 16.0 [°]
engines attached to the tail, landing gear attached to the wings, fueltanks in the wings
construction : all-metal aluminium-alloy stressed-skin construction with pressurized fuselage
fuselage shape : 0
calculation : *1* (dimensions)
measured wing chord : 3.24 [m] at 50% wingspan
mean wing chord : 3.24 [m]
calculated average wing chord tapered wing with rounded tips: 3.33 [m]
wing aspect ratio : 7.28 []
seize (span*length*height) : 5472 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 43.8 [kg/hr]
fuel consumption (econ. cruise speed) : 2289.7 [kg/hr] (2862.1 [litre/hr]) at 30 [%] power
distance flown for 1 kg fuel : 0.36 [km/kg] at 10000 [m] height, sfc : 88.0 [kg/KN/h]
total fuel capacity : 13040 [litre] (10432 [kg])
calculation : *3* (weight)
weight engine(s) dry : 2800.0 [kg] = 31.95 [kg/KN]
weight 237.0 litre oil tank : 20.14 [kg]
oil tank filled with 0.6 litre oil : 0.5 [kg]
oil in engine 14.6 litre oil : 13.1 [kg]
fuel in engine 10.8 litre fuel : 7.89 [kg]
weight fuel lines 13.0 [kg]
weight engine cowling 262.9 [kg]
total weight propulsion system : 3118 [kg](10.6 [%])
***************************************************************
fuselage aluminium frame : 3179 [kg]
typical cabin layout for 65 passengers : economy : pitch : 79 [cm] ( 3+2 ) seating in 13.0 rows
pax density (normal seating) : 0.56 [m2/pax]
high density seating passengers : 80 at 5 -abreast seating in 16.1 rows, pitch 76 [cm]
weight 1 toilets : 20.8 [kg]
weight 3 hand fire extinguisher : 10 [kg]
weight 1 galleys : 58.5 [kg]
weight overhead stowage for hand luggage : 22.8 [kg]
weight 1 closets : 13.0 [kg]
weight 28 windows : 25.2 [kg]
weight 2 overwing emergency exits : 29.4 [kg]
weight lifejackets : 29.2 [kg]
weight oxygen masks & oxygen generators : 42.2 [kg]
weight emergency flare installation : 10 [kg]
weight 2 emergency evacuation slides : 27.1 [kg]
weight 2 entrance/exit doors : 68.5 [kg]
weight 2 freight doors (belly) : 49.0 [kg]
cabin volume (usable), excluding flight deck : 88.31 [m3]
passenger cabin max.width : 3.10 [m] cabin length : 13.09 [m] cabin height : 2.02 [m]
floor area : 36.6 [m2]
pressure difference :0.46 [kg/cm2]
weight rear pressure bulkhead : 78.7 [kg]
weight air pressurization system : 20.5 [kg]
fuselage covering ( 162.3 [m2] duraluminium 1.75 [mm]) : 746.9 [kg]
Aero Continente F28 Mk.1000 5-abreast interior, reg. OB-1779-P
weight floor beams : 136.6 [kg]
weight cabin furbishing : 258.2 [kg]
weight cabin floor : 405.4 [kg]
fuselage (sound proof) isolation : 117.1 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight dual cloud-collision radar : 25.0 [kg]
weight radio direction finding (RDF) equipment : 5.0 [kg]
weight Sperry Integrated Flight System : 11.0 [kg]
weight artificial horizon : 1.1 [kg]
weight instruments. : 36.0 [kg]
weight APU / engine starter: 21.9 [kg]
weight lighting : 16.2 [kg]
weight electricity generator : 16.2 [kg]
weight controls : 11.3 [kg]
weight seats : 350.0 [kg]
weight air conditioning : 98 [kg]
weight engine mounts : 44 [kg]
total weight fuselage : 5815 [kg](19.7 [%])
***************************************************************
total weight aluminium ribs (465 ribs) : 1051 [kg]
weight fuel tanks empty for total 13040 [litre] fuel : 730 [kg]
weight wing covering (painted aluminium 2.93 [mm]) : 1210 [kg]
total weight aluminium spars (multi-cellular wing structure) : 951 [kg]
F28 Mk.1000 cockpit in the Norsk Luftfartsmuseum
weight wings : 3213 [kg]
weight wing/square meter : 42.05 [kg]
weight rubber de-icing boots : 25.9 [kg]
weight fin & rudder (6.5 [m2]) : 272.3 [kg]
weight stabilizer & elevator (8.6 [m2]): 362.0 [kg]
weight fowler flaps (5.5 [m2]) : 121.4 [kg]
total weight wing surfaces & bracing : 4725 [kg] (16.0 [%])
*******************************************************************
wheel pressure : 6485.6 [kg]
weight 4 Dunlop main wheels (1000 [mm] by 154 [mm]) : 761.5 [kg]
weight 2 Dunlop nose wheels : 190.4 [kg]
weight hydraulic wheel-brakes : 24.8 [kg]
weight pneumatic-hydraulic shock absorbers : 33.0 [kg]
weight wheel hydraulic operated retraction system : 338.4 [kg]
weight undercarriage struts with axle 327.2 [kg]
total weight landing gear : 1675.3 [kg] (5.7 [%]
*******************************************************************
********************************************************************
calculated empty weight : 15333 [kg](52.0 [%])
weight oil for 4.8 hours flying : 211.1 [kg]
weight catering : 104.4 [kg]
weight water : 41.8 [kg]
weight crew : 405 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 49 [kg]
operational weight empty : 16144 [kg] (54.8 [%])
********************************************************************
weight 65 passengers : 5005 [kg]
weight luggage : 1040 [kg]
weight cargo : 2584 [kg]
zero fuel weight (ZFW): 24773 [kg](84.0 [%])
weight fuel for landing (1.0 hours flying) : 2290 [kg]
max. landing weight (MLW): 27063 [kg](91.8 [%])
max. fuel weight : 26576 [kg] (90.1 [%])
payload with max fuel : 31 passengers+luggage 2904 [kg]
published maximum take-off weight : 29480 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 336 [kg/KN]
power loading (operational without useful load) : 323 [kg/kN]
power loading (Take-off) 1 PUF: 673 [kg/KN]
max. total take-off power : 87.6 [KN]
calculation : *5* (loads)
manoeuvre load : 6.2 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.4 [g]
design flight time : 3.21 [hours]
design cycles : 7468 sorties, design hours : 23985 [hours]
operational wing loading : 3624 [N/m^2]
wing stress (3 g) during operation : 259 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.81 ["]
max. angle of attack (stalling angle, clean) : 12.01 ["]
angle of attack at max. speed : 0.69 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.21 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
max. lift coefficient full flaps : 1.42 [ ]
induced drag coefficient at max.speed : 0.0026 [ ]
drag coefficient at max. speed : 0.0214 [ ]
drag coefficient (zero lift) : 0.0188 [ ]
lift/drag ratio at max. speed : 9.68 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 27190 [kg]): 254 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 228 [km/u]
landing speed at sea-level (normal landing weight : 26990 [kg]): 262 [km/hr]
max. rate of climb speed : 666 [km/hr] at sea-level
max. endurance speed : 550 [km/u] min. fuel/hr : 1408 [kg/hr] at height : 8839 [m]
max. range speed : 724 [km/u] min. fuel consumption : 2.244 [kg/km] at cruise height : 8839 [m]
cruising speed : 817 [km/hr] at 10000 [m] (power:22 [%])
max. operational speed (Mmo) : 848.00 [km/hr] (Mach 0.75 ) at 6400 [m] (power:32.0 [%])
airflow : 121.0 [kg/s]
speed of thrust jet : 1591 [km/hr]
climbing speed at sea-level (loaded) : 2186 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 2063 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 317.2 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 1244 [m]
take-off distance at sea-level over 15 [m] height : 1320 [m]
landing run : 1345 [m]
landing run from 15 [m] : 2269 [m]
lift/drag ratio : 14.87 [ ]
max. theoretical ceiling : 17200 [m] with flying weight :27190 [kg] line 3359
climb to 1000m with max payload : 0.46 [min]
climb to 2000m with max payload : 0.89 [min]
climb to 3000m with max payload : 1.30 [min]
climb to 5000 [m] with max payload : 2.04 [min]
minimum flying speed at 10700 [m] : 525 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:27190 [kg] ) : 17200 [m]
calculation *10* (action radius & endurance)
published range : 3280 [km] with 5 crew and 4144 [kg] useful load and 88.1 [%] fuel
range : 1680 [km] with 8629.0 [kg] max. useful load (45.1 [%] fuel)
range : 2602 [km] with 65.0 passengers with each 16 [kg] luggage and 69.9 [%] fuel
range max. fuel : 3722 [km] with 2904.0 [kg] useful load and 100.0 [%] fuel
Available Seat Kilometres (ASK) : 169102 [paskm]
max range theoretically with additional fuel tanks total 16670.0 [litre] fuel : 5944 [km]
useful load with range 500km : 11935 [kg]
useful load with range 500km : 65 passengers
production (theor.max load): 9751 [tonkm/hour]
production (useful load): 7050 [tonkm/hour]
production (passengers): 53105 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.239 [kg]
fuel cost per paskm : 0.044 [eur]
crew cost per paskm : 0.011 [eur]
economic hours : 22300 [hours] is less then design hours
time between engine failure : 962 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.011 [eur]
insurance per paskm : 0.0008 [eur]
maintenance cost per paskm : 0.005 [eur]
direct operating cost per paskm : 0.071 [eur]
direct operating cost per tonkm (max. load): 0.389 [eur]
direct operating cost per tonkm (normal useful load): 0.538 [eur]
Literature :
Fokker F28 Fellowship - Wikipedia
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx
Verkehrsflugzeuge page 77
Verkeersvliegtuigen Moussault page 72
Jane’s commercial transport aircraft page 127
Fokker F 28 1000 Fellowship — The National Norwegian Aviation Museum
DISCLAIMER Above calculations are based on published data, they must be
regarded as indication not as facts.
Calculated performance and weight may not correspond with actual weights
and performances and are assumptions for which no responsibility can be taken.
Calculations are as accurate as possible, they can be fine-tuned when more data
is available, you are welcome to give suggestions and additional information
so we can improve our program. For copyright on drawings/photographs/
content please mail to below mail address
(c) B van der Zalm 27 June 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4