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weight and performance calculations for the Boeing 727-200adv
Syrian Airlines 727-269adv YK-AGE c/n 22361 Schiphol October 1997 © bvdz
Boeing 727-200adv
role : medium-range jet airliner
importance : ****
first flight : 3 March 1972 operational : July 1972 (All Nippon Airways)
country : United States of America
design :
production : 935 aircraft
general information :
More powerful version with higher MTOW. Redesigned interior with superjet-look.
primary users : All Nippon, TWA, Turkish Airlines, Air Maroc, Iberia, TAP, Eastern
Airlines, Mexicana, Delta Airlines, Iran Air, Lufthansa, Syrian Airlines, Royal Air
Maroc, Braniff, Air France, Northwest Airlines, Royal Jordanian airlines, Top Air.
Accommodation:
flight crew : 3 cabin crew : 5
flight crew consist of pilot, co-pilot and flight engineer
passengers : seating for 145 in two class : 14 first class and 131 coach class seats
( 34 -in pitch) exit limit : 189 passengers
engine : 3 Pratt & Whitney JT8D-15 turbofan engines of 69.96 [KN] (15727.4 [lbf])
Lufthansa Boeing 727-230(adv) D-ABKT c/n 21623
dimensions :
wingspan : 32.92 [m], length : 46.69 [m], height : 10.36 [m]
wing area : 157.9 [m^2] fuselage exterior width : 3.76 [m]
weights :
empty weight : 42100 [kg]
operating empty weight : 45356 [kg] max. structural payload : 18144 [kg]
Zero Fuel weight (ZFW) : 63500 [kg] max. landing weight (MLW) : 70080 [kg]
max.take-off weight : 86405 [kg] weight fuel : 27101 [kg] (33876 [liter])
performance :
Max. operating Mach number (Mmo) : 0.90 [Mach] (1017 [km/hr]) at 6585 [m]
normal cruise speed : 964 [km/hr] (Mach 0.89 ) at 9145 [m] (36 [%] power)
economic cruise speed : 917 [km/hr] (Mach 0.84 ) at 9145 [m]
service ceiling : 10060 [m]
range with max fuel : 4077 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
cantilever low-wing monoplane with retractable landing gear with nose wheel
Wings : two main spar fail-safe wing structure with triple slotted TE flaps with slotted
LE slats on outer wing and Krueger LE flaps on inboard third of wing ,with spoilers
airfoil : Boeing. Sweep angle 3/4 chord: 32.0 [°]
engines attached to the tail, landing gear attached to the wings, fuel tanks in the wings
calculation : *1* (dimensions)
wing chord at root : 7.70 [m]
mean wing chord : 4.80 [m]
calculated average wing chord tapered wing with rounded tips: 4.90 [m]
wing aspect ratio : 6.86 []
seize (span*length*height) : 15924 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 7.1 [kg/hr]
fuel consumption (econ. cruise speed) : 5588.4 [kg/hr] (6985.4 [litre/hr]) at 44 [%] power
distance flown for 1 kg fuel : 0.16 [km/kg] at 9145 [m] height, sfc : 61.0 [kg/KN/h]
total fuel capacity : 33876 [litre] (27101 [kg])
calculation : *3* (weight)
weight engine(s) dry : 4800.0 [kg] = 22.87 [kg/KN]
weight 51 litre oil tank : 4.31 [kg]
oil tank filled with 1.3 litre oil : 1.2 [kg]
oil in engine 2.6 litre oil : 2.3 [kg]
fuel in engine 11.5 litre fuel : 8.40 [kg]
weight fuel lines 70.2 [kg]
weight engine cowling 545.7 [kg]
weight thrust reversers 314.8 [kg]
total weight propulsion system : 5747 [kg](6.7 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 145 passengers : economy : pitch : 86.4 [cm]
34.0 [-in] ( 3+3 ) seating in 25.3 rows
weight seats : 765.0 [kg]
high density seating passengers : 187 [pax] at 6 -abreast seating in 31.1 rows,
pitch 73.7 [cm] 29.0 [-in]
pax density, normal seating : 0.63 [m2/pax], high density seating : 0.49 [m2/pax]
weight 3 lavatories : 43.3 [kg]
weight 2 galleys : 167.4 [kg]
weight overhead stowage for hand luggage : 50.8 [kg]
weight 3 wardrobe closets : 29.0 [kg]
weight 53 windows : 47.4 [kg]
weight 5 1.83x0.86 [m] entrance/exit doors : 278.1 [kg]
weight ventral stairway : 94.0 [kg]
weight 2 (130x122 cm) freight doors (belly) : 112.1 [kg]
total belly baggage/cargo hold volume : 46.20 [m3]
passenger compartment volume : 120 [m3]
passenger cabin max.width : 3.56 [m] cabin length : 28.23 [m] cabin height : 2.11 [m]
floor area : 91.4 [m2]
weight cabin facilities : 1493.0 [kg]
safety facilities:
weight 4 over wing emergency exits (91x51 cm): 106.0 [kg]
weight 7 hand fire extinguisher : 22 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 94.2 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 99.1 [kg]
weight safety equipment & facilities : 445 [kg]
fuselage construction:
fuselage aluminium frame : 12062 [kg]
floor loading (payload/m2): 199 [kg/m2]
weight rear pressure bulkhead : 190.9 [kg]
fuselage covering ( 341.3 [m2] duraluminium 3.23 [mm]) : 2896.5 [kg]
weight floor beams : 639.6 [kg]
weight cabin furbishing : 776.1 [kg]
weight cabin floor : 1315.0 [kg]
fuselage (sound proof) isolation : 246.9 [kg]
weight empty 89 [litre] potable water tank : 7.9 [kg]
weight empty waste tank : 14.5 [kg]
weight engine mounts : 105 [kg]
weight fuselage structure : 18254.4 [kg]
Avionics:
weight VHF radio and Selcal : 9.0 [kg]
weight flight and service attendants intercom : 5.0 [kg]
weight dual cloud-collision radar : 25.0 [kg]
weight weather radar : 25.0 [kg]
weight VOR/ILS,RMI,DME,radio altimeter : 12.0 [kg]
weight Integrated Flight System / auto-pilot : 23.0 [kg]
weight artificial horizons, compass, alti-meters : 7 [kg]
weight ground proximity warning system (GPWS) : 6 [kg]
weight engine monitoring gauges & control switches : 9 [kg]
weight avionics : 96.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up
to 6550 [m] and gives equivalent of 2000 [m] at 11200 [m]. pressure differential :
0.59 [bars] (kg/cm2). Pressurized fuselage volume : 409 [m3]
weight air-conditioning and pressurization system : 209 [kg]
weight APU / engine starter: 35.0 [kg]
weight lighting : 47.9 [kg]
weight three independent 207 bar hydraulic systems : 53.1 [kg]
weight engine-driven 40kVA electricity generators : 36.2 [kg]
weight 22Ah battery : 12.0 [kg]
weight controls : 17.2 [kg]
weight systems : 410.7 [kg]
total weight fuselage : 20700 [kg](24.0 [%])
***************************************************************
total weight aluminium ribs (920 ribs) : 3081 [kg]
weight 7 fuel tanks empty for total 33876 [litre] fuel : 1897 [kg]
weight wing covering (painted aluminium 3.25 [mm]) : 2770 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2731 [kg]
weight wings : 8582 [kg]
weight wing/square meter : 54.35 [kg]
weight thermal leading-edge anti-icing : 36.2 [kg]
Braniff colourful superjet-look interior
weight ailerons (5.3 [m2]) : 144.4 [kg]
weight fin (33.1 [m2]) : 1172.2 [kg]
weight rudder (6.1 [m2]) : 159.5 [kg]
weight tailplane (stabilizer) (34.9 [m2]): 1047.1 [kg]
weight elevators (8.9 [m2]): 131.1 [kg]
weight flight control hydraulic servo actuators: 26.5 [kg]
Royal Air Maroc Boeing 727-2B6(adv) CN-RMP c/n 21298
weight triple slotted flaps (36.0 [m2] extended) : 639.5 [kg]
weight leading edge slats (14.8 [m2]) : 224.9 [kg]
weight spoilers (7.4 [m2]) : 103.9 [kg]
total weight wing surfaces & bracing : 14164 [kg] (16.4 [%])
*******************************************************************
tire pressure main wheels : 10.83 [Bar] (nitrogen), ply rating : 30 PR
tire speed limit : 364 [km/hr] total footprint : 0.59 [m2]
Aircraft Classification Number, MTOW on rigid runway and medium subgrade
strength (B) : 29 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 19009.1 [kg]
weight 4 Dunlop main wheels (1270 [mm] by 534 [mm]) : 930.5 [kg]
weight 2 nose wheels : 232.6 [kg]
weight multi-disc wheel-brakes : 63.5 [kg]
weight flywheel detector type anti-skid units : 5.4 [kg]
weight oleo-pneumatic shock absorbers : 84.7 [kg]
weight wheel hydraulic operated retraction system : 736.9 [kg]
weight undercarriage struts with axle 1594.0 [kg]
total weight landing gear : 3647.6 [kg] (4.2 [%]
*******************************************************************
********************************************************************
calculated empty weight : 44258 [kg](51.2 [%])
weight oil for 5.1 hours flying : 41.5 [kg]
weight lifejackets : 65.2 [kg]
weight 3 life rafts : 90.6 [kg]
weight catering : 98.4 [kg]
weight water : 78.8 [kg]
weight crew : 648 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 75 [kg]
operational weight empty : 45356 [kg] (52.5 [%])
********************************************************************
weight 145 passengers : 11165 [kg]
weight luggage : 2320 [kg]
weight cargo : 4659 [kg] (cargo+luggage/m3 belly : 138 [kg/m3])
zero fuel weight (ZFW): 63500 [kg](73.5 [%])
weight fuel for landing (1.2 hours flying) : 6580 [kg]
max. landing weight (MLW): 70080 [kg](81.1 [%])
max. fuel weight : 72457 [kg] (83.9 [%])
payload with max fuel : 150 passengers+luggage 13948 [kg]
published maximum take-off weight : 86405 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 412 [kg/KN]
power loading (Take-off) 1 PUF: 618 [kg/KN]
max. total take-off power : 209.9 [KN]
calculation : *5* (loads)
Air France Boeing 727-228adv F-GCDC c/n 22083
manoeuvre load : 8.2 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.1 [g]
design flight time : 1.36 [hours]
design cycles : 24007 sorties, design hours : 32598 [hours]
max. wing loading (MTOW & flaps retracted) : 547 [kg/m2]
wing stress (2 g) during operation : 179 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.94 ["]
max. angle of attack (stalling angle, clean) : 13.50 ["]
max. angle of attack (full flaps) : 17.70 ["]
angle of attack at max. speed : 0.45 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.16 [ ]
lift coefficient at max. speed : 0.20 [ ]
lift coefficient at max. angle of attack : 1.27 [ ]
max. lift coefficient full flaps : 2.24 [ ]
drag coefficient at max. speed : 0.0357 [ ]
drag coefficient at econ. cruise speed : 0.0390 [ ]
induced drag coefficient at econ. cruise speed : 0.0057 [ ]
drag coefficient (zero lift) : 0.0333 [ ]
lift/drag ratio at max. speed : 5.52 [ ]
calculation : *8* (speeds
take-off safety speed (V2) : 252 [km/u]
take-off (initial climb) speed (Vto) : 302 [km/u]
stalling speed clean at sea-level (OW loaded : 80817 [kg]): 289 [km/u]
max. rate of climb speed : 462 [km/hr] at sea-level
max. endurance speed (Vbe): 478 [km/u] min. fuel/hr : 3955 [kg/hr] at height : 5486 [m]
max. range speed (Vbr): 791 [km/u] min. fuel consumption : 5.769 [kg/km] at cruise height : 9449 [m]
cruising speed : 964 [km/hr] at 9145 [m] (power:47 [%])
max. operational speed (Mmo) : 1017 [km/hr] (Mach 0.90) at 6585 [m] (power:65.6 [%])
airflow at cruise speed per engine : 98.3 [kg/s]
speed of thrust jet : 2167 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.75
descent speed 7315 - 3048 [m]: 537 [km/u]
approach speed 3048 - 500 [m] (clean): 463 [km/u]
stalling speed clean at 500 [m] height at Max.Landing Weight : 70080 [kg]): 276 [km/u]
final approach speed at sea-level with full flaps (Vapp): 229 [km/u]
ICAO Aircraft Approach Category (APC) : C
landing speed at sea-level (normal landing weight(Vtd): 69991 [kg]): 203 [km/hr]
stalling speed at sea-level with full flaps (max. landing weight): 176 [km/u]
rate of climb at sea-level ROC (loaded) : 607 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF / MTOW) : 511 [m/min]
rate of descent: 457 [m/min]
calculation : *9* (regarding various performances)
low wheel pressure, can also take off from unpaved runways
take-off distance at sea-level concrete runway : 1821 [m]
take-off distance at sea-level gravel/packed earth field : 2652 [m]
ICAO Aerodrome Reference Code : 4C
take-off distance at sea-level over 15 [m] height : 2011 [m]
balanced runway length at MTOW and at SL (FAR) : 2906 [m]
landing run (MLW) : 830 [m]
landing run (C.A.R.) from 15 [m] at SL, dry runway : 1161 [m]
landing run (C.A.R.) from 15 [m] at SL, wet runway : 1461 [m]
lift/drag ratio : 11.02 [ ]
climb to 5000 [m] with max payload : 7.62 [min]
climb to 10000 [m] with max payload : 23.44 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 14550 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 80817 [kg] ) : 16800 [m]
calculation *10* (action radius & endurance)
range with max. payload: 3727 [km] with 18144.0 [kg] max. useful load (84.5 [%] fuel)*
range with high density pax: 3857 [km] with 187 passengers (87.3 [%] fuel)*
range with typical two-class pax: 4455 [km] with 145 passengers (100.0 [%] fuel)*
range with max.fuel : 4447 [km] with 8 crew and 150 passengers and 100.0 [%] fuel*
ferry range : 4694 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 52039.0 [litre] fuel : 7027 [km] *
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 676591 [paskm]
useful load with range 1000km : 18144 [kg]
useful load with range 1000km : 187 passengers
production (theor.max load): 17491 [tonkm/hour]
production (useful load): 17491 [tonkm/hour]
production (passengers): 149326 [paskm/hour]
oil and fuel consumption per tonkm : 0.320 [kg]
calculation *11* (operating cost)
fuel cost per hour (6985 [litre]):4191 [eur] (21 [pax-km/litre fuel])
fuel cost per seat 1000km flight (155 [pax] 2-class seating): 28.07 [eur/1000PK]
oil cost per hour: 30 [eur]
crew cost per hour : 1050.000 [eur]
list price 2023 : 117 [mln USD]
average flying hours in 1 year : 2600 [hours] technical life : 13 [year]
economic hours : 32598 [hours] is limited by technical life
financing interest per flying hour : 1053 [EUR]
write off per flying hour : 3099 [EUR]
time between engine failure : 641 [hr]
4 January 1990 Northwest Boeing 727-251adv N280US c/n 21159 looses an engine in flight and made an emergency landing at Tampa.
can continue fly on 2 engines, low risk for emergency landing for PUF
average flight hours till crash : 2.32 [mln hr] (890 service years)
safe flight hours till fatality : 29027 [hr]
reservation pax liability/flying hour : 4.44 [SDR*] (5.55 [eur])
Wednesday 12 June 1985 Alia Royal Jordanian Airlines Boeing 727-2D3 JY-AFW c/n 22271 JT8D-17 engines, first flight Jan 1981 flight RJ402 from Beirut, Lebanon to Amman, Jordan. Hijacked in flight by 5 Shiite Arab men. After returning to Beirut the occupants were released after which the hijackers blew the aircraft up with explosives
insurance cost per hour : 67 [eur]
engine maintenance cost per hour : 780 [eur]
maintenance cost per hour (excluding engines): 3229 [eur]
direct operating cost per hour: 13505 [eur]
DOC per seat 1000km flight (155 [pax] 2-class seating): 90.44 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 74.97 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.77 [eur/kg] (= DOC/tonkm)
passenger service charge (depart at Schiphol): 11.34 [eur]
security service charge (depart at Schiphol): 10.08 [eur]
Top Air 727-2F2(Adv) TC-IYA c/n 22999
airport take-off fee / passenger : 3.33 [eur/pax]
airport landing fee / passenger : 3.33 [eur/pax]
retour ticket price 1000km trip : 260.74 [eur/pax]
price retour ticket Schiphol-Barcelona : 310.48 [eur/pax]
accidents with fatalities > see the accident file
Literature :
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.boeing.com/search/results.html?q=airplane+characteristics
observers airliners page 39
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 14 April 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4