Aircraft investigation >>>>>>> HOME PAGE
weight and performance calculations for the Airbus A318
***** PRELIMINARY FILE ****
Air France Airbus A318-100 F-GUGA coming in to land at London Heathrow airport (LHR). Air France is the largest operator of the A318.
Airbus A318
role : mid-range jet airliner
importance : ****
first flight : 15 January 2002 operational : July 2003 with Frontier
country : EU-consortium
design :
production : 81 aircraft
general information :
Smallest Airbus. Is an A319 shortened by 2.39m (4 frames). For propulsion, the new PW6000 engine with the CFM56 as an alternative was chosen. In the end there were major problems with the PW6000, it had to be modified poignantly, which took a few years! Partly because of this, the A318 has not been a great success so far. The cabin width is 3.70m. Aspect Ratio: 9.48.
primary users : Air France, Tarom, Frontier, British Airways
Accommodation:
flight crew : 2 cabin crew : 4
passengers : seating for 107 in two class : 8 first class and 99 economy class seats
( 32 -in pitch) or 120 passengers all-economy class. exit limit : 136 passengers
engine : 2 Pratt & Whitney PW6000 turbofan engines of 102.4 [KN](23020.0 [lbf])
dimensions :
wingspan : 34.09 [m], length : 31.44 [m], height : 12.56 [m]
wing area : 122.6 [m^2]
weights :
empty weight : 39500 [kg]
operating empty weight : 39500 [kg] max. structural payload : 15000 [kg]
Zero Fuel weight (ZFW) : 54500 [kg] max. landing weight (MLW) : 57500 [kg]
max.take-off weight : 68000 [kg] weight fuel : 19368 [kg] (24210 [liter])
performance :
Max. operating Mach number (Mmo) : 0.82 [Mach] (922 [km/hr]) at 7000 [m]
normal cruise speed : 852 [km/hr] (Mach 0.81 ) at 11250 [m] (29 [%] power)
service ceiling : 11250 [m]
range with max fuel : 5740 [km] and allowance for 656.6 [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: 25.0 [°]
engines attached with pylons to the wing, main landing gear attached to the wings, fuel tanks in the wings and fuselage
construction : all-metal aluminium-alloy stressed-skin construction with pressurized fuselage
fuselage shape : 0
calculation : *1* (dimensions)
measured wing chord : 3.60 [m] at 50% wingspan
mean wing chord : 3.60 [m]
calculated average wing chord tapered wing with rounded tips: 3.57 [m]
wing aspect ratio : 9.48 []
seize (span*length*height) : 13462 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 20.5 [kg/hr]
fuel consumption (econ. cruise speed) : 2532.7 [kg/hr] (3165.9 [litre/hr]) at 29 [%] power
distance flown for 1 kg fuel : 0.34 [km/kg] at 11250 [m] height, sfc : 42.2 [kg/KN/h]
total fuel capacity : 24210 [litre] (19368 [kg])
calculation : *3* (weight)
weight engine(s) dry : 4578.0 [kg] = 22.35 [kg/KN]
weight 188.7 litre oil tank : 16.04 [kg]
oil tank filled with 1.3 litre oil : 1.2 [kg]
oil in engine 34.2 litre oil : 30.7 [kg]
fuel in engine 25.1 litre fuel : 18.43 [kg]
weight fuel lines 24.2 [kg]
weight engine cowling 614.4 [kg]
total weight propulsion system : 5283 [kg](7.8 [%])
***************************************************************
fuselage aluminium frame : 10244 [kg]
typical cabin layout for 107 passengers : economy : pitch : 81 [cm] ( 3+3 ) seating in
18.5 rows
pax density (normal seating) : 0.67 [m2/pax]
high density seating passengers : 127 at 6 -abreast seating in 21.2 rows, pitch 79 [cm]
weight 3 toilets : 39.5 [kg]
weight 5 hand fire extinguisher : 16 [kg]
weight 1 galleys : 100.9 [kg]
weight overhead stowage for hand luggage : 37.4 [kg]
weight 2 closets : 21.4 [kg]
weight 39 windows : 35.1 [kg]
weight 2 overwing emergency exits : 53.1 [kg]
weight lifejackets : 48.1 [kg]
weight oxygen masks & oxygen generators : 69.5 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 52.8 [kg]
weight 4 entrance/exit doors : 247.8 [kg]
weight 2 freight doors (belly) : 88.5 [kg]
cabin volume (usable), excluding flight deck : 205.59 [m3]
passenger cabin max.width : 3.70 [m] cabin length : 21.39 [m] cabin height : 2.18 [m]
floor area : 71.3 [m2]
pressure difference :0.46 [kg/cm2]
weight rear pressure bulkhead : 186.1 [kg]
weight air pressurization system : 43.1 [kg]
fuselage covering ( 289.4 [m2] duraluminium 2.91 [mm]) : 2223.6 [kg]
weight floor beams : 418.9 [kg]
weight cabin furbishing : 579.9 [kg]
weight cabin floor : 725.7 [kg]
fuselage (sound proof) isolation : 210.1 [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: 51.2 [kg]
weight lighting : 26.8 [kg]
weight electricity generator : 26.8 [kg]
weight controls : 13.7 [kg]
weight seats : 565.0 [kg]
weight 12105 [litre] main central fuel tanks empty : 677.9 [kg]
weight air conditioning : 160 [kg]
total weight fuselage : 16780 [kg](24.7 [%])
***************************************************************
total weight aluminium ribs (966 ribs) : 2425 [kg]
weight engine mounts : 102 [kg]
weight fuel tanks empty for total 12105 [litre] fuel : 678 [kg]
weight wing covering (painted aluminium 4.84 [mm]) : 3201 [kg]
total weight aluminium spars (multi-cellular wing structure) : 4275 [kg]
weight wings : 9901 [kg]
weight wing/square meter : 80.76 [kg]
weight rubber de-icing boots : 37.5 [kg]
weight fin & rudder (13.5 [m2]) : 1091.4 [kg]
weight stabilizer & elevator (13.8 [m2]): 1114.8 [kg]
weight flight control hydraulic servo actuators: 72.8 [kg]
weight fowler flaps (8.2 [m2]) : 336.0 [kg]
total weight wing surfaces & bracing : 13334 [kg] (19.6 [%])
*******************************************************************
Tarom A318 interior
wielen naar verhouding erg zwaar
wheel pressure : 14960.0 [kg]
weight 4 Dunlop main wheels (1130 [mm] by 174 [mm]) : 2259.1 [kg]
weight 2 Dunlop nose wheels : 564.8 [kg]
weight hydraulic wheel-brakes : 54.5 [kg]
weight pneumatic-hydraulic shock absorbers : 72.7 [kg]
weight undercarriage struts with axle -106.5 [kg]
total weight landing gear : 2969.6 [kg] (4.4 [%]
*******************************************************************
********************************************************************
calculated empty weight : 38367 [kg](56.4 [%])
weight oil for 8.1 hours flying : 165.6 [kg]
weight catering : 252.3 [kg]
weight water : 201.8 [kg]
weight crew : 486 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 28 [kg]
operational weight empty : 39500 [kg] (58.1 [%])
********************************************************************
weight 107 passengers : 8239 [kg]
weight luggage : 1712 [kg]
weight cargo : 5049 [kg]
zero fuel weight (ZFW): 54500 [kg](80.1 [%])
weight fuel for landing (1.2 hours flying) : 3000 [kg]
max. landing weight (MLW): 57500 [kg](84.6 [%])
max. fuel weight : 58868 [kg] (86.6 [%])
payload with max fuel : 98 passengers+luggage 9132 [kg]
published maximum take-off weight : 68000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 332 [kg/KN]
power loading (operational without useful load) : 306 [kg/kN]
power loading (Take-off) 1 PUF: 664 [kg/KN]
max. total take-off power : 204.8 [KN]
calculation : *5* (loads)
manoeuvre load : 5.2 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.6 [g]
design flight time : 4.72 [hours]
design cycles : 12678 sorties, design hours : 59789 [hours]
operational wing loading : 5010 [N/m^2]
wing stress (3 g) during operation : 186 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.68 ["]
max. angle of attack (stalling angle, clean) : 11.02 ["]
angle of attack at max. speed : 1.23 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.26 [ ]
lift coefficient at max. angle of attack : 1.13 [ ]
max. lift coefficient full flaps : 1.40 [ ]
induced drag coefficient at max.speed : 0.0030 [ ]
drag coefficient at max. speed : 0.0301 [ ]
drag coefficient (zero lift) : 0.0271 [ ]
lift/drag ratio at max. speed : 8.62 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 65467 [kg]): 313 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 263 [km/u]
V : 487.04 te laag, Cl > Clmax berekening PR nodig klopt niet meer cl : 1.42 line 216
flying weight (fw) : 57701.0
landing speed at sea-level (normal landing weight : 57273 [kg]): 302 [km/hr]
max. rate of climb speed : 670 [km/hr] at sea-level
max. endurance speed : 487 [km/u] min. fuel/hr : 1676 [kg/hr] at height : 6096 [m]
max. range speed : 779 [km/u] min. fuel consumption : 2.484 [kg/km] at cruise height : 9449 [m]
cruising speed : 852 [km/hr] at 11250 [m] (power:20 [%])
max. operational speed (Mmo) : 922.00 [km/hr] (Mach 0.82 ) at 7000 [m] (power:34.3 [%])
airflow : 271.7 [kg/s]
speed of thrust jet : 1647 [km/hr]
climbing speed at sea-level (loaded) : 2319 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 2096 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 382.7 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 1831 [m]
take-off distance at sea-level over 15 [m] height : 1903 [m]
landing run : 1818 [m]
landing run from 15 [m] : 2886 [m]
lift/drag ratio : 14.40 [ ]
max. theoretical ceiling : 15900 [m] with flying weight :65467 [kg] line 3359
climb to 1000m with max payload : 0.45 [min]
climb to 2000m with max payload : 0.88 [min]
climb to 3000m with max payload : 1.28 [min]
climb to 5000 [m] with max payload : 2.01 [min]
minimum flying speed at 11250 [m] : 671 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:65467 [kg] ) : 15900 [m]
calculation *10* (action radius & endurance)
published range : 5740 [km] with 6 crew and 11437 [kg] useful load and 88.1 [%] fuel
range : 4541 [km] with 15000.0 [kg] max. useful load (69.7 [%] fuel)
range : 6240 [km] with 107.0 passengers with each 16 [kg] luggage and 95.8 [%] fuel
range max. fuel : 6515 [km] with 9132.0 [kg] useful load and 100.0 [%] fuel
Available Seat Kilometres (ASK) : 667666 [paskm]
max range theoretically with additional fuel tanks total 35625.0 [litre] fuel : 11474 [km]
useful load with range 500km : 27014 [kg]
useful load with range 500km : 107 passengers
production (theor.max load): 23016 [tonkm/hour]
British Airways operated a A318 between London and New York. It had only business class seats to provide exclusive service. Due to corona this operation was cancelled in July 2020 leaving only the A318 in service with Air France and Tarom.
production (useful load): 12780 [tonkm/hour]
production (passengers): 91164 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.111 [kg]
fuel cost per paskm : 0.028 [eur]
crew cost per paskm : 0.008 [eur]
economic hours : 55750 [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 : 0.006 [eur]
insurance per paskm : 0.0008 [eur]
maintenance cost per paskm : 0.011 [eur]
direct operating cost per paskm : 0.054 [eur]
direct operating cost per tonkm (max. load): 0.213 [eur]
direct operating cost per tonkm (normal useful load): 0.384 [eur]
Literature :
volkskrant 27 april 1999
British Airways To End Airbus A318 Service | Airways Magazine
www.flybernhard.de
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
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