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weight and performance calculations for the Boeing 727-200

Olympic Airways Boeing 727-284 SX-CBA c/n 20003, sunny afternoon at Schiphol airport.

Boeing 727-200

role : medium-range jet airliner

importance : ****

first flight : 27 July 1967 operational : December 1967 Northwest Airlines

country : United States of America

design :

production : 727-200 : 310 aircraft at Renton, USA

general information :

Stretched version of the 727 raising capacity to max. 189 pax.

Fuselage stretched by 3.05 [m]

primary users : Northwest Airlines, Trans Caribbean, Pacific Southwest, Panam,

Eastern Airlines

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) high density seating for 189 passengers (equal to exit limit)

engine : 3 Pratt & Whitney JT8D-7B turbofan engines of 64.0 [KN] (14387.5 [lbf])

Chord at root : 7.70 [m] at tip 2.34 [m]

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 : 42981 [kg]

operating empty weight : 44330 [kg] max. structural payload : 17370 [kg]

Zero Fuel weight (ZFW) : 61700 [kg] max. landing weight (MLW) : 68100 [kg]

max.take-off weight : 78100 [kg] weight fuel : 24498 [kg] (30623 [litres])

performance :

Max. operating Mach number (Mmo) : 0.90 [Mach] (1014 [km/hr]) at 6585 [m]

critical Mach speed : 0.85 [Mach]

max. cruising speed : 958 [km/hr] (Mach 0.88 ) at 9150 [m] (39 [%] power)

economic cruising speed : 914 [km/hr] (Mach 0.84 ) at 9150 [m]

service ceiling : 10730 [m]

range with max fuel and MTOW : 3460 [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 trailing edge 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]

wing chord at tip : 2.34 [m]

Northwest Airlines Boeing 727-251 N252US, c/n 19971 November 1968

taper ratio : 0.304 [ ]

mean wing chord : 4.80 [m]

calculated average wing chord tapered wing with rounded tips: 4.90 [m]

wing aspect ratio : 6.86 []

Oswald factor (e): 0.676 []

seize (span*length*height) : 15924 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 6.7 [kg/hr]

fuel consumption (econ. cruise speed) : 5846.4 [kg/hr] (7307.9 [litre/hr]) at 38 [%] power

distance flown for 1 kg fuel : 0.16 [km/kg] at 9150 [m] height, sfc : 80.6 [kg/KN/h]

total fuel capacity : 30623 [litre] (24498 [kg])

calculation : *3* (weight)

weight engine(s) dry : 4500.0 [kg] = 23.44 [kg/KN]

weight 41.7 litre oil tank : 3.54 [kg]

oil tank filled with 1.2 litre oil : 1.1 [kg]

oil in engine 2.4 litre oil : 2.1 [kg]

fuel in engine 10.5 litre fuel : 7.68 [kg]

weight fuel lines : 73.5 [kg]

weight engine cowling : 499.2 [kg]

weight thrust reversers : 288.0 [kg]

total weight propulsion system : 5375 [kg](6.9 [%])

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Accommodation cabin facilities:

3 galleys and 3 lavatories

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 : 189 [pax] at 6 -abreast seating in 31.5 rows,

pitch 75.0 [cm] 29.5 [-in]

pax density, normal seating : 0.63 [m2/pax], high density seating : 0.48 [m2/pax]

weight 3 lavatories : 41.3 [kg]

American Airlines 727-223 American Airlines galley

weight 3 galleys : 130.5 [kg]

United 727-200 interior

weight overhead stowage for hand luggage : 50.8 [kg]

weight 2 wardrobe closets : 29.0 [kg]

weight 10 movie screens : 82.9 [kg]

weight 53 windows (47x38cm) : 47.4 [kg]

weight 4 (1.83 x 0.88 [m]) main entry doors : 196.9 [kg]

weight 1 (1.52 x 0.76 [m]) service doors : 35.5 [kg]

The 727 had some military uses, as well. Since the aft stair could be opened in flight, the Central Intelligence Agency used them to drop agents and supplies behind enemy lines in  Vietnam . The possibility to jump from the 727 in flight was used by D.B Cooper who hijacked a Northwest Orient Airlines 727-051 N467US on 24 November 1971 and escaped with the ransom money by jumping from the ventral stairway.

weight ventral stairway : 94.0 [kg]

weight 2 (1.37 x 1.10 [m]) freight doors (belly) : 80.5 [kg]

total belly baggage/cargo hold volume : 41.06 [m3]

cabin volume (usable), excluding flight deck : 188 [m3]

passenger compartment volume : 124 [m3]

passenger cabin max.width : 3.56 [m] cabin length : 28.23 [m] cabin height : 2.19 [m]

floor area : 91.1 [m2]

weight cabin facilities : 1459.7 [kg]

safety facilities:

weight 4 type III over wing emergency exits (51x91 cm): 60.2 [kg]

evacuation time with 189 passengers : 40 [sec]

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 : 400 [kg]

fuselage construction:

fuselage aluminium frame : 9117 [kg]

floor loading (payload/m2): 191 [kg/m2]

weight rear pressure bulkhead : 190.0 [kg]

fuselage covering ( 341.3 [m2] duraluminium 3.21 [mm]) : 2876.6 [kg]

weight floor beams : 649.3 [kg]

weight cabin furbishing : 802.5 [kg]

weight cabin floor : 1328.9 [kg]

weight (sound proof) isolation : 246.4 [kg]

weight empty 98 [litre] potable water tank : 8.7 [kg]

weight empty waste tank : 5.4 [kg]

weight engine mounts : 96 [kg]

weight fuselage structure : 15320.5 [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 Sperry automatic flight control system, with SP-30 auto-pilot : 25.0 [kg]

weight artificial horizons, compass, alti-meters : 7 [kg]

weight engine monitoring gauges & control switches : 9 [kg]

weight avionics : 98.0 [kg]

Systems:

Air-conditioning and pressurization system maintains sea level conditions up to 6700 [m]

and gives equivalent of 2250 [m] at 12200 [m]. pressure differential : 0.60 [bars]

(kg/cm2) pressurized fuselage volume : 409 [m3]

weight air-conditioning and pressurization system : 211 [kg]

weight APU / engine starter: 32.0 [kg]

weight lighting : 47.9 [kg]

weight 210 bar hydraulic system : 53.8 [kg]

weight engine-driven 40kVA electricity generators : 36.2 [kg]

weight 22Ah battery : 12.0 [kg]

weight controls : 17.2 [kg]

weight systems : 410.1 [kg]

total weight fuselage : 17688 [kg](22.6 [%])

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average Take-off weight : 76316 [kg](97.7 [%])

total weight aluminium ribs (822 ribs) : 2753 [kg]

weight 7 wing fuel tanks empty for total 30623 [litre] fuel : 1715 [kg]

weight wing covering (painted aluminium 4.26 [mm]) : 3634 [kg]

total weight aluminium spars (multi-cellular wing structure) : 3575 [kg]

weight wings : 9962 [kg]

weight wing/square meter : 63.09 [kg]

weight thermal leading-edge anti-icing : 36.2 [kg]

weight ailerons (5.30 [m2]) : 167.6 [kg]

weight fin (33.09 [m2]) : 1360.3 [kg]

weight rudder (6.10 [m2]) : 185.0 [kg]

weight tailplane (stabilizer) (34.92 [m2]): 1214.8 [kg]

weight elevators (8.91 [m2]): 152.06 [kg]

weight flight control hydraulic servo actuators: 26.5 [kg]

Eastern Airlines Boeing 727-225 N8846E c/n 20444 approaching New York, La Guardia with trailing edge slotted flaps and leading edge slats extended

weight triple slotted flaps (36.04 [m2] extended) : 742.8 [kg]

weight leading edge Krueger flaps (8.12 [m2]) : 125.8 [kg]

weight spoilers (7.4 [m2]) : 119.5 [kg]

total weight wing construction : 15808 [kg] (35.7 [%])

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Main gear tire size 49 x 17 inch. = 124 x 43 [cm]

tire pressure main wheels : 11.74 [Bar] (nitrogen), ply rating : 28 PR

tire speed limit : 364 [km/hr]

total tyre footprint : 0.39 [m2]

Aircraft Classification Number, MTOW on rigid runway and medium subgrade

strength (B) : 34 [ ]

Can also operate from unpaved runways subgrade B

wheel pressure : 17182.0 [kg]

weight 4 Dunlop main wheels (1240 [mm] by 431 [mm]) : 583.9 [kg]

weight 2 nose wheels : 146.0 [kg]

weight multi-disc wheel-brakes : 61.7 [kg]

weight Hydro-air flywheel detector type anti-skid units : 5.4 [kg]

weight oleo-pneumatic shock absorbers : 82.3 [kg]

weight wheel hydraulic operated retraction system : 884.7 [kg]

weight undercarriage struts with axle 2615.5 [kg]

total weight landing gear : 4379.5 [kg] (5.6 [%]

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calculated empty weight : 43250 [kg](55.4 [%])

weight oil for 4.3 hours flying : 33.8 [kg]

weight lifejackets : 65.2 [kg]

weight 3 life rafts : 90.6 [kg]

weight catering : 108.8 [kg]

weight water : 87.0 [kg]

weight crew : 648 [kg]

weight crew lugage,nav.chards,flight doc.,miscell.items : 46 [kg]

operational weight empty : 44330 [kg] (56.8 [%])

Trans Caribbean N8790R Boeing 727-2A7

********************************************************************

weight 145 passengers : 11165 [kg]

weight luggage : 2320 [kg]

weight cargo : 3885 [kg] (cargo+luggage/m3 belly : 137 [kg/m3])

zero fuel weight (ZFW): 61700 [kg](79.0 [%])

weight fuel for landing (1.1 hours flying) : 6400 [kg]

max. landing weight (MLW): 68100 [kg](87.2 [%])

max. fuel weight : 68828 [kg] (88.1 [%])

payload with max fuel : 100 passengers+luggage 9272 [kg]

published maximum take-off weight : 78100 [kg] (100.0 [%])

calculation : * 4 * (engine power)

power loading (Take-off) : 407 [kg/KN]

power loading (Take-off) 1 PUF: 610 [kg/KN]

max. total take-off power : 192.0 [KN]

calculation : *5* (loads)

manoeuvre load : 6.9 [g] at 1000 [m]

limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.5 [g]

design flight time : 1.50 [hours]

design cycles : 21475 sorties, design hours : 32212 [hours]

max. wing loading (MTOW & flaps retracted) : 495 [kg/m2]

wing stress (2 g) during operation : 144 [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) : 11.81 ["]

max. angle of attack (full flaps) : 14.76 ["]

angle of attack at max. speed : 0.31 ["]

calculation : *7* (lift & drag ratios

lift coefficient at angle of attack 0° : 0.16 [ ]

lift coefficient at max. speed : 0.19 [ ]

lift coefficient at max. angle of attack : 1.13 [ ]

max. lift coefficient full flaps : 1.97 [ ]

drag coefficient at max. speed : 0.0323 [ ]

drag coefficient at econ. cruise speed : 0.0311 [ ]

induced drag coefficient at econ. cruise speed : 0.0053 [ ]

drag coefficient (zero lift) : 0.0259 [ ]

lift/drag ratio at econ. speed : 5.74 [ ]

calculation : *8* (speeds

take-off decision speed (V1) : 222 [km/u] (120 [kt])

lift-off speed (VLOF) : 248 [km/u] (134 [kt])

take-off safety speed (V2) : 264 [km/u] (143 [kt])

steady initial climb speed (V4) : 290 [km/u] (157 [kt])

flap retraction speed (V3) at 500m (OW loaded : 72254 [kg]): 319 [km/u] (172 [kt])

climb speed (to FL150 with 67 [%] power) : 506 [km/hr] (273 [kt])

max. endurance speed (Vbe): 592 [km/u] min. fuel/hr : 4385 [kg/hr] at height : 8534 [m]

max. range speed (Vbr): 823 [km/u] (0.76 [mach]) min. fuel consumption : 6.15 [kg/km]

at cruise height : 9449 [m]

max. cruising speed : 958 [km/hr] (517 [kt]) at 9150 [m] (power:44 [%])

max. operational speed (Mmo) : 1014 [km/hr] (Mach 0.90 ) at 6585 [m] (power:64 [%])

airflow at cruise speed per engine : 99.6 [kg/s]

speed of thrust jet : 1980 [km/hr]

initial descent speed 10000 - 7315 [m]: Mach 0.72

descent speed 7315 - 3048 [m]: 519 [km/u] (280 [kt])

approach speed 3048 - 500 [m] (clean): 389 [km/u] (210 [kt])

minimum control speed (MCS) Vmca (clean): 303 [km/u] (163 [kt])

final approach speed (landing speed) at sea-level with full flaps VREF

(max. landing weight): 245 [km/u] (132 [kt])

ICAO Aircraft Approach Category (APC) : C

stalling speed at sea-level with full flaps VSO (max. landing weight): 188 [km/u]

rate of climb at sea-level ROC (loaded, 67 % power) : 724 [m/min]

rate of climb at sea-level ROC (loaded, 75% power) : 899 [m/min]

rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power

on remaining engines) : 1336 [m/min]

rate of descent from FL240 to FL100 (7315m > 3048m): 1067 [m/min] (3501 [ft/min])

rate of descent during approach with landing gear extended, with use of spoilers: 457

[m/min] (1499 [ft/min])

calculation : *9* (regarding various performances)

low wheel pressure, can also take off from unpaved runways

take-off distance at sea-level concrete runway : 2254 [m]

ICAO Aerodrome Reference Code : 4C

727-200 CAR takeoff runway length, standard day, sea level, mtow 78100 kg (172178 lb) : 8365 ft (2550 m), with 62.29 KN JT8D-7 engines, with 64.00 KN JT8D-7B engines : 2502 m, with T-O distance over 10.7m : 2379m

take-off distance (C.A.R) at sea-level over 10.7 [m] height : 2379 [m]

FAR TO runway length requirement at MTOW, standard day at SL (ASDA): 2502 [m]

landing run (MLW) : 611 [m]

727-200 CAR landing runway, sea-level, dry runway at MLW 68100 kg (150132 lb) : 5100 ft : 1554m, 30° flaps

landing distance (C.A.R.) from 15 [m] at SL, dry runway : 1557 [m]

landing distance (C.A.R.) from 15 [m] at SL, wet runway : 1857 [m]

FAR landing runway length requirements at SL : 1550 [m]

max. lift/drag ratio : 11.87 [ ]

climb to 5000 [m] with max payload : 6.39 [min]

climb to 10000 [m] with max payload : 19.67 [min]

descent time from 10000 [m] to 250 [m] : 24.33 [min]

ceiling limited by max. pressure differential 14950 [m]

theoretical ceiling fully loaded (mtow- 60 min.fuel: 72254 [kg] ) : 16700 [m]

calculation *10* (action radius & endurance)

range with max. payload: 2510 [km] with 17370.0 [kg] max. useful load (66.9 [%] fuel)*

range with high density pax: 2477 [km] with 189 passengers (66.1 [%] fuel)*

range with typical two-class pax: 3137 [km] with 145 passengers (82.8 [%] fuel)*

Range with MTOW 78500 kg (173000 lb) & max.fuel : 3830 km (2070 nm), with ATA domestic reserves : 3460 km (jane’s all the world aircraft 170-71 page 289. Ferry range : 2425 nm = 4491 km

range with max.fuel : 3830 [km] with 8 crew and 100 passengers and 100.0 [%] fuel*

ferry range : 4019 [km] with 3 crew and zero payload (100.0 [%] fuel)*

max range theoretically with additional fuel tanks total 42963 [litre] fuel : 5508 [km]*

* calculated ranges without fuel reserves

Available Seat Kilometres (ASK) : 463390 [paskm]

useful load with range 1000km : 17370 [kg]

useful load with range 1000km : 189 passengers

production (theor.max load): 16640 [tonkm/hour]

production (useful load): 16640 [tonkm/hour]

production (passengers): 147847 [paskm/hour]

oil and fuel consumption per tonkm : 0.352 [kg]

calculation *11* (operating cost)

fuel cost per hour (7308 [litre]):4384 [eur] (20 [pax-km/litre fuel])

fuel cost per seat 1000km flight (154 [pax] 2-class seating): 29.66 [eur/1000PK]

oil cost per hour: 28 [eur]

crew cost per hour : 1050 [eur]

list price 2023 : 115 [mln USD]

average flying hours in 1 year : 2700 [hours] technical life : 12 [year]

real average service life : 14 [years]

economic hours (average real flown hours) : 37800 [hours]

financing interest per flying hour : 990 [EUR]

write off per flying hour : 2612 [EUR]

time between engine failure : 14696 [hr]

can continue fly on 2 engines, low risk for emergency landing for PUF

workhours per day : 11.10 [hr]

average flight hours till crash : 1.07 [mln hr] (395 service years)

safe flight hours till fatality : 12068 [hr] (4.5 service years)

reservation pax liability/flying hour : 10.67 [SDR*] (13.34 [eur])

insurance cost per hour : 119 [eur]

United Airlines 727-222 N7625U c/n 19542

engine maintenance cost per hour : 114.2 [eur]

wing maintenance cost per hour : 231.6 [eur]

fuselage maintenance cost per hour : 303.36 [eur]

tire life (time till worn out) : 112 [cycles]

maintenance cost per hour (excluding engines): 1650 [eur]

direct operating cost per hour: 10961 [eur]

DOC per seat 1000km flight (154 [pax] 2-class seating): 74.14 [eur/1000PK]

DOC per seat 1000km flight (high density seating): 60.54 [eur/1000PK]

DOC per kg cargo for a 1000km flight : 0.66 [eur/kg] (= DOC/tonkm)

passenger service charge (depart at Schiphol): 11.34 [eur]

security service charge (depart at Schiphol): 10.08 [eur]

airport take-off fee / passenger : 3.02 [eur/pax]

airport landing fee / passenger : 3.02 [eur/pax]

retour ticket price 1000km trip : 223.52 [eur/pax]

price retour ticket Schiphol-Barcelona : 264.30 [eur/pax]

accidents with fatalities > see the accident file

Notes : smallest floor-area of its category with 91.1 [m2]

Libyan Arab Airlines 727-224 5A-DAH c/n 20244

Literature :

Wikipedia

Observers airliners page 39

Aircraft – Boeing 727-200 – Northwest Airlines History Center

https://contentzone.eurocontrol.int/aircraftperformance/default.aspx ?

The Problem With The Boeing 727's Rear Door (simpleflying.com)

Jane’s all the world aircraft 1970-71 page

https://www.boeing.com/search/results.html?q=airplane+characteristics

confidence rating regarding source data : medium - all information is only available from news, social media or unofficial sources

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

Pan Am 727-235 N4735 at London Heathrow

(c) B van der Zalm 08 October 2023 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4

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