AIRCRAFT INVESTIGATION
weight and performance calculations for the AI(R) RJ85 Avroliner
***** PRELIMINARY FILE ****
AI(R) RJ85 Avroliner
role : short range jet airliner
importance : ****
first flight : 23 March 1992 operational : April 1993 (Crossair)
country : United-Kingdom
design : Bob Grigg (chief-designer)
production : 79 aircraft
general information :
Re-engined Bae 146-200.
primary users : Lufthansa, Air France, Crossair
flight crew : 2 cabin crew : 3 passengers : 85 (2+3 layout, 84cm pitch) to 112 (3+3 layout,
74cm pitch)
engine : 4 Alliedsignal LF507 turbofan engines of 31.14 [KN](7000.4 [lbf])
dimensions :
wingspan : 26.21 [m], length : 28.55 [m], height : 8.59 [m]
wing area : 77.3 [m^2]
weights :
operating empty weight : 24600 [kg] max. structural payload : 11233 [kg]
Zero Fuel weight (ZFW) : 35833 [kg] max. landing weight (MLW) : 0 [kg]
max.take-off weight : 42184 [kg] weight fuel : 9382 [kg] (11728 [liter])
performance :
Max. operating Mach number (Mmo) : 0.71 [Mach] (789 [km/hr]) at 7500 [m]
normal cruise speed : 747 [km/hr] (Mach 0.68 ) at 9000 [m] (30 [%] power)
service ceiling : 11000 [m]
range with max fuel : 4006 [km] and allowance for 437.1 [km] diversion and 30 [min] hold
description :
high-winged 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: 15.0 [°]
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 : 2.95 [m] at 50% wingspan
mean wing chord : 2.95 [m]
calculated average wing chord tapered wing with rounded tips: 2.93 [m]
wing aspect ratio : 8.89 []
seize (span*length*height) : 6428 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 12.5 [kg/hr]
fuel consumption (econ. cruise speed) : 1541.4 [kg/hr] (1926.7 [litre/hr]) at 30 [%] power
distance flown for 1 kg fuel : 0.48 [km/kg] at 9000 [m] height, sfc : 41.4 [kg/KN/h]
total fuel capacity : 11728 [litre] (9382 [kg])
calculation : *3* (weight)
weight engine(s) dry : 2512.0 [kg] = 20.17 [kg/KW]
weight 91.9 litre oil tank : 7.81 [kg]
oil tank filled with 0.8 litre oil : 0.7 [kg]
oil in engine 20.8 litre oil : 18.7 [kg]
fuel in engine 15.3 litre fuel : 11.21 [kg]
weight fuel lines 11.7 [kg]
weight engine cowling 373.7 [kg]
total weight propulsion system : 2936 [kg](7.0 [%])
***************************************************************
fuselage aluminium frame : 6224 [kg]
typical cabin layout for 85 passengers : average pitch : 81 [cm] ( 3+2 ) seating in 17.0 rows
pax density (normal seating) : 0.70 [m2/pax]
high density seating passengers : 112 at 6 -abreast seating in 18.7 rows, pitch 74 [cm]
weight 2 toilets : 26.1 [kg]
weight 4 hand fire extinguisher : 13 [kg]
weight 3 galleys : 63.8 [kg]
weight overhead stowage for hand luggage : 29.7 [kg]
weight 2 closets : 8.5 [kg]
weight 36 windows : 32.4 [kg]
weight lifejackets : 38.2 [kg]
weight oxygen masks & oxygen generators : 55.2 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 22.7 [kg]
weight 4 entrance/exit doors : 48.0 [kg]
weight 2 freight doors (belly) : 8.0 [kg]
extra main deck space for freight/mail/luggage etc. : 0.78 [m3]
On 28 November 2016, a chartered Avro RJ85, registration CP-2933, flying from
Viru Viru International Airport
in Bolivia to
Medellín
, Colombia, as
LaMia Flight 2933
, crashed 10.5 miles (17 km) south of
José María Córdova International Airport
.
Among the passengers were members of the Brazilian football team
Associação Chapecoense de Futebol
who were travelling to play their away leg of the
Final of the 2016 Copa Sudamericana
in Medellín. Of the 77 people on board, 71 died.
cabin volume (usable), excluding flight deck : 143.13 [m3]
passenger cabin max.width : 3.41 [m] cabin length : 17.53 [m] cabin height : 2.18 [m]
pressure at cruise height 12192.00 [m] : 0.19 [kg/cm2] cabin pressure : 0.77 [kg/cm2]
weight rear pressure bulkhead : 130.0 [kg]
weight air pressurization system : 32.6 [kg]
fuselage covering ( 218.5 [m2] duraluminium 2.39 [mm]) : 1373.3 [kg]
weight floor beams : 219.8 [kg]
weight cabin furbishing : 438.1 [kg]
weight cabin floor : 730.3 [kg]
fuselage (sound proof) isolation : 157.8 [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. : 38.0 [kg]
weight APU / engine starter: 15.6 [kg]
weight lighting : 21.2 [kg]
weight electricity generator : 21.2 [kg]
weight controls : 11.9 [kg]
weight seats : 450.0 [kg]
weight 5864 [litre] main central fuel tanks empty : 328.4 [kg]
weight air conditioning : 128 [kg]
total weight fuselage : 10505 [kg](24.9 [%])
***************************************************************
total weight aluminium ribs (731 ribs) : 1504 [kg]
weight engine mounts : 62 [kg]
weight fuel tanks empty for total 5864 [litre] fuel : 328 [kg]
weight wing covering (painted aluminium 5.14 [mm]) : 2144 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2242 [kg]
weight wings : 5890 [kg]
weight wing/square meter : 76.20 [kg]
weight rubber de-icing boots : 28.8 [kg]
weight fin & rudder (8.0 [m2]) : 608.8 [kg]
weight stabilizer & elevator (8.7 [m2]): 663.2 [kg]
weight flight control hydraulic servo actuators: 40.6 [kg]
weight fowler flaps (5.6 [m2]) : 219.4 [kg]
total weight wing surfaces & bracing : 7842 [kg] (18.6 [%])
*******************************************************************
wheel pressure : 9280.5 [kg]
weight 4 Dunlop main wheels (1130 [mm] by 174 [mm]) : 1020.2 [kg]
weight 2 Dunlop nose wheels : 255.0 [kg]
weight hydraulic wheel-brakes : 35.8 [kg]
weight pneumatic-hydraulic shock absorbers : 47.8 [kg]
weight wheel hydraulic operated retraction system : 525.0 [kg]
weight undercarriage struts with axle 714.7 [kg]
total weight landing gear : 2598.5 [kg] (6.2 [%]
*******************************************************************
D-AVRM RJ85 Lufthansa Regional, 6-abreast seating
********************************************************************
calculated empty weight : 23881 [kg](56.6 [%])
weight oil for 6.4 hours flying : 80.2 [kg]
weight catering : 159.5 [kg]
weight water : 63.8 [kg]
weight crew : 405 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 10 [kg]
operational weight empty : 24600 [kg] (58.3 [%])
********************************************************************
weight 85 passengers : 6545 [kg]
weight luggage : 1037 [kg]
weight cargo : 3651 [kg]
zero fuel weight (ZFW): 35833 [kg](84.9 [%])
weight fuel for landing (1.0 hours flying) : 1541 [kg]
max. landing weight (MLW): 37374 [kg](88.6 [%])
max. fuel weight : 33982 [kg] (80.6 [%])
payload with max fuel : 92 passengers+luggage 8202 [kg]
published maximum take-off weight : 42184 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 339 [kg/KN]
power loading (operational without useful load) : 319 [kg/kN]
power loading (Take-off) 1 PUF: 452 [kg/KN]
max. total take-off power : 124.6 [KN]
calculation : *5* (loads)
manoeuvre load : 3.8 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.7 [g]
design flight time : 3.75 [hours]
design cycles : 14698 sorties, design hours : 55176 [hours]
operational wing loading : 5039 [N/m^2]
wing stress (3 g) during operation : 198 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.71 ["]
max. angle of attack (stalling angle, clean) : 11.27 ["]
angle of attack at max. speed : 2.59 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.38 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
max. lift coefficient full flaps : 1.41 [ ]
induced drag coefficient at max.speed : 0.0068 [ ]
drag coefficient at max. speed : 0.0414 [ ]
drag coefficient (zero lift) : 0.0346 [ ]
lift/drag ratio at max. speed : 9.12 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 40643 [kg]): 309 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 266 [km/u]
V : 381.15 te laag, Cl > Clmax berekening PR nodig klopt niet meer cl : 1.74 line 216
flying weight (fw) : 36128.1927770668
landing speed at sea-level (normal landing weight : 37263 [kg]): 306 [km/hr]
max. rate of climb speed : 586 [km/hr] at sea-level
max. endurance speed : 381 [km/u] min. fuel/hr : 1234 [kg/hr] at height : 2134 [m]
max. range speed : 739 [km/u] min. fuel consumption : 1.929 [kg/km] at cruise height : 9144 [m]
cruising speed : 747 [km/hr] at 9000 [m] (power:26 [%])
max. operational speed (Mmo) : 789.00 [km/hr] (Mach 0.71 ) at 7500 [m] (power:33.3 [%])
airflow : 459.9 [kg/s]
speed of thrust jet : 1038 [km/hr]
climbing speed at sea-level (loaded) : 1887 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 1790 [m/min]
climbing speed at 1000 [m] with 2 engines out (2xPUF / MTOW) : 1732 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 378.2 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 1885 [m]
take-off distance at sea-level over 15 [m] height : 1963 [m]
landing run : 1841 [m]
landing run from 15 [m] : 2923 [m]
lift/drag ratio : 12.34 [ ]
max. theoretical ceiling : 14400 [m] with flying weight :40643 [kg] line 3359
climb to 1000m with max payload : 0.54 [min]
climb to 2000m with max payload : 1.05 [min]
climb to 3000m with max payload : 1.54 [min]
climb to 5000 [m] with max payload : 2.42 [min]
minimum flying speed at 11000 [m] : 653 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:40643 [kg] ) : 14400 [m]
calculation *10* (action radius & endurance)
published range : 4006 [km] with 5 crew and 9318 [kg] useful load and 96.2 [%] fuel
range : 3078 [km] with 5 crew and 11233.0 [kg] useful load and 73.9 [%] fuel
range max. fuel : 4166 [km] with 85 passengers with each 12.2 [kg] luggage and 1405 [kg] cargo and 100 [%] fuel
range : 3668 [km] with 112 passengers with each 12.2 [kg] luggage and 88.0 [%] fuel
Available Seat Kilometres (ASK) : 354125 [paskm]
max range theoretically with additional fuel tanks total 21980.0 [litre] fuel : 9116 [km]
useful load with range 500km : 16552 [kg]
useful load with range 500km : 85 passengers
production (theor.max load): 12365 [tonkm/hour]
production (useful load): 8391 [tonkm/hour]
production (passengers): 63495 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.126 [kg]
fuel cost per paskm : 0.024 [eur]
crew cost per paskm : 0.009 [eur]
Technische Daten > length 30.99 [m] and abfluggewicht (MTOW) 44.200 [kg] are not correct, these facts more compare with the RJ100 !
economic hours : 22300 [hours] is less then design hours
time between engine failure : 466 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
writing off per paskm : 0.014 [eur]
insurance per paskm : 0.0008 [eur]
maintenance cost per paskm : 0.012 [eur]
direct operating cost per paskm : 0.060 [eur]
direct operating cost per tonkm (max. load): 0.310 [eur]
direct operating cost per tonkm (normal useful load): 0.457 [eur]
The RJ85 has airbrakes in it’s tail, making more steep approaches possible.
Literature :
Air International mrt’98 page 189
Air International aug’00 page 096
Aircraft Performance Database > RJ85 (eurocontrol.int)
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