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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 © bvdz
Boeing 727-200
role : medium-range jet airliner
importance : ****
first flight : 27 July 1967 operational : December 1967 Northwest Airlines
country : United States of America
ICAO aircraft type designator : B722
production : 727-200 : 310 aircraft at Renton, USA
general information :
In August 1965, Boeing announced an extended version of the 727, with a maximum
capacity for 189 passengers. The fuselage was lengthened by 6.1m by placing an 3.05m
fuselage section(“plug’’) in front and behind the wing. The Air France was the first
European customer to order the aircraft in June 1966. In December 1967, Northeast
Airlines was the first to put the 727-200 into service. In 1972, production was
switched to the 727-200 "advanced" with higher MTOW, more powerful engines and
more fuel and a new interior.
Sales were very good and soon the 727 became the most built jetliner.
primary users : Northwest Airlines, Trans Caribbean, Pacific Southwest, Panam,
Eastern Airlines
Accommodation :
flight crew : 3 cabin crew : 4
flight crew consist of pilot, co-pilot and flight engineer
passengers : seating for 134 in two class : 20 first class and 114 coach class seats ( 34 -in
pitch) high density seating for max 189 passengers (equal to exit limit)
engine : 3 Pratt & Whitney JT8D-7B turbofan engines of 64.0 [KN] (14388 [lbf])
Chord at root : 7.70 [m] at tip 2.34 [m] measured tail angle : 10°
dimensions :
wingspan : 32.92 [m], length overall: 46.69 [m], length of fuselage : 41.51 [m] height :
10.36 [m] wing area gross : 157.9 [m^2] fuselage exterior width : 3.76 [m]
weights :
manufacturer’s weight empty : 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 usable fuel : 24039 [kg] (30623 [litres])
performance :
Max. operating Mach number (Mmo) : 0.899 [Mach] (1014 [km/hr]) at 6585 [m]
critical Mach speed : 0.85 [Mach]
max. cruising speed : 958 [km/hr] (Mach 0.880 ) at 9150 [m] (41 [%] power)
economic cruising speed : 914 [km/hr] (Mach 0.84 ) at 9150 [m]
service ceiling : 10730 [m]
range with max fuel and MTOW : 3890 [km] (ATA domestic fuel reserves - 370.0 [km]
alternate)
description :
*Cantilever low-wing monoplane with retractable landing gear with nose wheel
engines attached to the tail, landing gear attached to the wings, fuel tanks in the wings
*Wings : aluminium alloy 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 average thickness/chord ratio : 11.0 [%], sweep angle 3/4
chord: 32.0 [°] incidence at root : 2.00 [°], dihedral : 3.0 [°]
*Tail Unit: Cantilever all-metal structure with tailplane mounted at tip of fin
*Fuselage : Pressurized semi-monocoque fail safe structure of elliptical 0 section
Northwest Airlines Boeing 727-251 N252US, c/n 19971 November 1968
calculation : *1* (dimensions) :
wing chord at root : 7.70 [m]
wing chord at tip : 2.34 [m]
measured geometric tail-angle : 11.0 [° ]
taper ratio : 0.304 [ ]
mean wing chord : 4.80 [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) : 5157.7 [kg/hr] (6570.3 [litre/hr]) at 33 [%] power
fuel burn per seat per hour (average seating) : 40.68 [litre], sfc : 80.6 [kg/KN/h]
calculation : *3* (weight) :
weight engine(s) dry : 4500.0 [kg] = 23.44 [kg/KN]
weight 45.9 litre oil tank : 3.90 [kg]
oil tank filled with 1.2 litre oil : 1.1 [kg]
oil in engine 2.4 litre oil : 2.1 [kg]
weight all fuel lines and pumps containing 243 litres fuel : 64.8 [kg]
weight engine cowling : 499.2 [kg]
weight thrust reversers : 288.0 [kg]
total weight propulsion system : 5359 [kg](6.9 [%])
***************************************************************
Accommodation cabin facilities :
3 galleys and 3 lavatories
typical 2-class cabin layout for 134 passengers : economy : pitch : 86.4 [cm] 34.0 [-in]
( 3+3 ) seating in 24.0 rows
first class pitch : 96.5 [cm] 38.0 [-in] at 4 -abreast
weight passenger seats (width 51.3 [cm]) : 739.1 [kg]
weight cabin crew seats : 20.0 [kg]
weight flight crew seats : 63.0 [kg]
high density seating passengers : 189 [pax] at mainly 6 -abreast seating in 32.6 rows,
pitch 71.1 [cm] 28.0 [-in]
pax density, normal seating : 0.750 [m2/pax], high density seating : 0.532 [m2/pax]
weight 3 lavatories : 78.2 [kg]
American Airlines 727-223 American Airlines galley
weight 2 galleys : 97.2 [kg]
weight overhead stowage for hand luggage (total : 8.0 [m3] = 166 55x35x25cm carry-on
trolleys) : 124.4 [kg]
*note : possible not enough overhead stowage in high density configuration*
weight 3 wardrobe closets : 59.6 [kg]
weight 3 movie screens : 21.4 [kg]
weight 50 windows (41 x 28 cm) made of acrylic glass : 212.5 [kg]
weight 2 (1.83 x 0.86 [m]) main entry doors : 95.5 [kg]
weight 3 (1.52 x 0.76 [m]) crew/service doors : 105.2 [kg]
**at high density seating some toilets/closets/galleys need to be removed to make place for
additional seating
weight hydraulically-operated airstair for ventral entrance : 94.0 [kg]
weight 2 (main door size : 1.12 x 1.37 [m]) freight doors (belly) : 101.3 [kg]*
total usable belly baggage/cargo hold volume : 41.4 [m3]
passenger compartment volume : 124 [m3]
cabin volume (usable), excluding flight deck : 188 [m3]
United 727-200 interior
passenger cabin max width (trim to trim): 3.56 [m] cabin length : 28.23 [m] max cabin
height : 2.18 [m] floor area : 91.0 [m2], cabin width at floor : 3.23 [m]
at normal seating 10.3 [%] of cabin floor area is occupied by toilets & galleys
weight cabin facilities : 1717.3 [kg]
safety facilities :
weight 4 type III over wing emergency exits (0.51 x 0.96 [m]): 64.7 [kg]
evacuation time with 189 passengers : 44 [sec]
weight 4 hand fire extinguisher : 11 [kg]
central aisle : 0.48 [m] wide
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 87.1 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 91.6 [kg]
weight safety equipment & facilities : 378 [kg]
fuselage construction :
fuselage aluminium frame : 9009 [kg]
floor loading (payload/m2): 191 [kg/m2]
weight rear pressure bulkhead : 182.8 [kg]
fuselage covering ( 341.3 [m2] duraluminium 3.09 [mm]) : 2771.5 [kg]
weight paint fuselage : 71.7 [kg]
weight aluminium floor beams : 535.7 [kg]
weight cabin furbishing : 798.6 [kg]
weight cabin floor : 1328.1 [kg]
weight (sound proof) isolation : 336.9 [kg] TO-noise level : 116.0 [EPNdB]
weight empty 102 [litre] potable water tanks : 9.0 [kg]
weight empty waste tank : 5.7 [kg]
weight engine mounts : 96 [kg]
weight fuselage structure : 15144.6 [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 VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]
weight Sperry automatic flight control system, with SP-50 auto-pilot : 25.0 [kg]
weight Cat II minima DH 30m RVR >=350m autoland system : 20.0 [kg]
weight artificial horizons, gyro-compass, radio altimeters : 7 [kg]
weight engine monitoring gauges & control switches : 21 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]
weight avionics : 153.0 [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 [bar] (kg/cm2)
pressurized fuselage volume : 263 [m3] cabin air refreshment time : 2.7 [min]
weight air-conditioning and pressurization system : 164 [kg]
weight Auxiliary Power Unit (APU) : 37.6 [kg]
weight lighting : 44.2 [kg]
weight 3 independent 210 [bar] hydraulic systems : 80.8 [kg]
weight engine-driven 40kVA electricity generators : 33.5 [kg]
weight 22Ah battery : 28.5 [kg]
weight controls : 17.2 [kg]
weight stick pusher anti-stall warning system : 15 [kg]
weight systems : 420.9 [kg]
total weight fuselage : 17814 [kg](22.8 [%])
***************************************************************
Libyan Arab Airlines 727-224 5A-DAH c/n 20244 with Tu104B CCCP-42439 c/n 920901 behind at London Heathrow.
wing construction :
total weight aluminium ribs (109 ribs) : 2718 [kg]
weight 6 wing fuel tanks empty for total 30623 [litre] fuel : 459 [kg]
weight 122 [litre] vent surge tanks : 15 [kg]
weight fuel dump system : 60 [kg]
weight wing covering (painted aluminium 3.64 [mm]) : 3105 [kg]
total weight aluminium spars : 4083 [kg]
weight wings : 9906 [kg]
weight wing/square meter : 62.74 [kg]
weight bleed air thermal leading-edge anti-icing : 36.2 [kg]
weight ailerons (5.3 [m2]) : 166.7 [kg]
weight fin (33.1 [m2]) : 1352.7 [kg]
weight rudder (6.1 [m2]) : 184.0 [kg]
weight tailplane (horizontal stabilizer) (34.9 [m2]): 1208.0 [kg]
weight elevators (8.8 [m2]): 149.4 [kg]
weight paint wing & tail surfaces : 94.9 [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 trailing edge flaps (36.0 [m2] extended) : 965.9 [kg]
weight leading edge Krueger flaps (11.6 [m2]) : 177.2 [kg]
weight spoilers (7.4 [m2]) : 118.9 [kg]
weight airbrakes (0.0 [m2]) : 0.0 [kg]
total weight wing construction : 14921 [kg] (33.7 [%])
*******************************************************************
landing gear :
tire pressure main wheels : 11.74 [Bar] (nitrogen), ply rating : 28 PR
tire speed limit : 338 [km/hr]
total tyre footprint : 0.39 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 51 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 33 [ ] Can also operate from unpaved runways subgrade B
wheel pressure : 17182.0 [kg]
wheel track 5.72 [m], wheelbase : 19.28 [m]
Main gear tire size 49 x 17 inch. = 124 x 43 [cm]
weight 4 Dunlop 49.0 x 17.0 main wheels (1245 [mm] by 432 [mm]) : 543.3 [kg]
weight 2 nose wheels : 135.8 [kg]
weight heavy-duty hydraulic disc brakes : 72.6 [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 : 1009.8 [kg]
weight undercarriage struts with axle 3149.4 [kg]
total weight landing gear : 4998.7 [kg] (6.4 [%]
*******************************************************************
********************************************************************
calculated empty weight : 43093 [kg](55.2 [%])
aircraft equipment and service utensils :
weight oil for 4.9 hours flying : 37.6 [kg]
unusable fuel in engine and tanks 260.3 litre fuel : 204.3 [kg]
weight lifejackets : 60.3 [kg]
weight 2 life rafts : 83.8 [kg]
weight catering : 65.3 [kg]
weight water : 90.1 [kg]
weight crew : 567 [kg]
weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous
items : 129 [kg]
operational weight empty : 44330 [kg] (56.8 [%])
Measured tail angle : 10°
********************************************************************
useful load breakdown :
weight 134 passengers : 10318 [kg]
weight luggage : 2144 [kg]
weight cargo : 4908 [kg] (cargo + luggage/m3 belly : 142.9 [kg/m3])
zero fuel weight (ZFW): 61700 [kg](79.0 [%])
weight fuel for landing (1.2 hours flying) : 6400 [kg]
max. landing weight (MLW): 68100 [kg](87.2 [%])
max. fuel weight : 68369 [kg] (87.5 [%])
payload with max fuel : 105 passengers + luggage 9731 [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]
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.
calculation : *5* (loads) :
manoeuvre load : 1.2 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.8 [g]
design flight time : 1.45 [hours]
design cycles : 34200 sorties, design hours : 49590 [hours]
max. wing loading (MTOW & flaps retracted) : 495 [kg/m2]
wing stress (2 g) during operation : 145 [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) : 17.67 ["]
angle of attack at economic cruise speed : 1.43 ["]
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 (clean): 1.13 [ ]
max. lift coefficient ( 33 [° ] flaps) : 2.06 [ ]
Trans Caribbean N8790R Boeing 727-2A7
drag coefficient at max. speed : 0.0290 [ ]
drag coefficient at econ. cruise speed : 0.0275 [ ]
induced drag coefficient at econ. cruise speed : 0.0053 [ ]
drag coefficient (zero lift) : 0.0222 [ ]
lift/drag ratio at econ. speed : 6.39 [ ]
calculation : *8* (speeds) :
Risk of tailstrike when taking off with OEI (engine failure), pilot must not rotate to fast
minimum control speed (Vmc): 264 [km/u] (142.8 [kt])
minimum unstick speed (Vmu) at TO angle 12.0 ° : 293 [km/u] (158 [kt])
take-off decision speed (V1) : 286 [km/u] (154 [kt])
take-off rotation speed (VR) : 302 [km/u] (163 [kt])
United Airlines 727-222 N7625U c/n 19542
lift-off speed (VLOF) : 322 [km/u] (174 [kt]) at pitch angle : 10.0 [°]
take-off safety speed (V2) : 325 [km/u] (175 [kt])
flap retraction speed (V3) at 500m (OW loaded : 72942 [kg]): 319 [km/u] (172 [kt])
steady initial climb speed (V4) : 351 [km/u] (189 [kt])
climb speed (to FL150 with 66 [%] power) : 539 [km/hr] (291 [kt])
max. endurance speed (Vbe): 676 [km/u] min. fuel/hr : 4073 [kg/hr] at height : 10058 [m]
max. range speed (Vbr): 868 [km/u] (0.83 [mach]) min. fuel consumption : 4.91 [kg/km] at
cruise height : 11582 [m]
max. cruising speed : 958 [km/hr] (517 [kt]) at 9150 [m] (power:40 [%])
max. operational speed (Mmo) : 1014 [km/hr] (Mach 0.90 ) at 6585 [m] (power:57 [%])
airflow at cruise speed per engine : 99.6 [kg/s]
speed of thrust jet : 1885 [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])
stalling speed clean at 500 [m] height at Max.Landing Weight : 68100 [kg]): 288 [km/u]
(156 [kt])
Air France 727-228 about to land.
final approach speed (landing speed) at sea-level with 33 [°] flaps VREF (max. landing
weight): 244 [km/u] (132 [kt])
ICAO Aircraft Approach Category (APC) : C
stalling speed at sea-level with 33 [°] flaps VSO (max. landing weight): 188 [km/u]
(102 [kt]
stalling speed at sea-level with 33 [°] flaps VSO at 78100 [kg] AUW): 201 [km/u]
(109 [kt]
rate of climb (max. continuous power) at sea-level ROC (loaded, 66 % power) : 794
[m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1004 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 66 % power on remaining
engines) : 216 [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: 213
[m/min] (3.6 [m/s])
calculation : *9* (regarding various performances) :
low wheel pressure, can also take off from unpaved runways
Brake kinetic energy capacity : 2133 [KW]
727-200 CAR take-off 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
FAR TO balanced runway length (TOFL) requirement at TOW 78100 [kg] standard day
at SL (distance to 10.7m height x 1.15): 2551 [m]
ICAO Aerodrome Reference Code : 4C
Take-off flap setting : 20 [° ]
+++ FAA certification landing distance : +++
landing weight : 68100 [kg], TE flap setting : 33 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers, glideslope : 3.00 [°]
727-200 CAR landing runway, sea-level, dry runway at MLW 68100 kg (150132 lb) : 5100 ft : 1554m, 30° flaps
FAR landing field length ISA at SL, dry runway : 1552 [m] (5092 [ft])
FAR landing field length ISA at SL, wet runway: 1763 [m] (5783 [ft])
max. lift/drag ratio : 12.82 [ ]
climb to 5000 [m] with max payload : 5.83 [min]
climb to 10000 [m] with max payload : 17.93 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
max. ceiling fully loaded (mtow- 60 min.fuel): 72942 [kg] ) : 16700 [m]
ceiling limited by max. pressure differential 14950 [m]
max. theoretical ceiling (OWE + 60 min.fuel) : 18600 [m] with flying weight :49488 [kg]
calculation *10* (action radius & endurance) :
range with max. payload: 2758 [km] with 17370.0 [kg] max. useful load (68.2 [%] fuel)*
range with high density pax: 2721 [km] with 189 passengers (67.4 [%] fuel)*
range with typical two-class pax: 3636 [km] with 134 passengers (88.6 [%] fuel)*
Range with max pay. load (MTOW 78100 kg) : 725 nm > 1325 km
Range with max fuel ( MTOW 78100 kg) : 2100 nm > 3890 km
(jane’s all the world aircraft 170-71 page 289 : 1867 nm > 3460 km with ATA domestic reserves, AUW 79380 kg)
Ferry range : 2425 nm > 4491 km
range with max.fuel and MTOW : 4135 [km] with 7 crew and 105 passengers and 0
[kg] cargo*
ferry range (calculated): 4376 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 43630 [litre] fuel : 6065 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 503118 [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): 141606 [paskm/hour]
oil and fuel consumption per tonkm : 0.310 [kg]
calculation *11* (operating cost) :
fuel cost per hour at econ.speed (6570 [litre]):3942 [eur] (21 [pax-km/litre fuel])
fuel cost per seat 1000km flight (148 [pax] 2-class seating): 29.18 [eur/1000PK]
oil cost per hour: 28 [eur]
crew cost per hour : 900 [eur]
list price 2024 : 102 [mln USD]
average flying hours in 1 year : 2537 [hours] technical life : 20 [year]
real average service life : 20 [years]
depreciation : 20 [years] to 10% residual value
financing interest per flying hour : 902 [EUR]
write off per flying hour : 1666 [EUR]
mean time between engine failure (MTBF) : 5462 [hr]
can continue fly on 2 engines, low risk for emergency landing for PUF
workhours per day : 10.55 [hr]
average flight hours till crash : 1.31 [mln hr] (517 service years)
safe flight hours till fatality : 14797 [hr] (5.8 service years)
reservation pax liability/flying hour : 8.71 [SDR*] (10.88 [eur])
Trump Shuttle 727-254 N915TS c/n 20252/783 landing at New York, La Guardia, September 1989. In August 1989 on approach to Boston airport the nose landing gear could not be lowered. A nose-wheel up landing was performed followed by an emergency evacuation with no casualties. Damage was minor and the aircraft was back in service one month later .
insurance cost per hour : 359 [eur] insurance rate : 2.4 [%]
engine maintenance cost per hour : 355.6 [eur]
wing maintenance cost per hour : 239.6 [eur]
fuselage maintenance cost per hour : 324.64 [eur]
tire life (time till worn out) : 88 [cycles]
maintenance cost per hour (excluding engines): 1338 [eur]
direct operating cost per hour: 9501 [eur], DOC per km : 10.40 [eur]
DOC per seat 1000km flight (148 [pax] 2-class seating): 67.10 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 52.48 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.57 [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 : 3.56 [eur/pax]
airport landing fee / passenger : 3.56 [eur/pax]
retour ticket price 1000km trip : 210.41 [eur/pax]
price retour ticket Schiphol-Barcelona : 247.31 [eur/pax]
12 fatal accidents with a total of 1063 fatalities > see the accident file
notes : of all classic jetliners :
Literature :
Jane’s all the world aircraft 1970-71 page 287,288
KIJK straalverkeersvliegtuigen page 58
Verkeersvliegtuigen B. Van der Klaauw page 13
Jane s Commercial Transport Aircraft page 57
Verkeersvliegtuigen Moussault page 144
The Flier's handbook page 90
Observer’s aircraft page 40
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)
https://www.boeing.com/commercial/airports/plan-manuals
rescue : https://www.boeing.com/commercial/airports/rescue-fire
confidence rating regarding source data : medium - all information is only available from news, social media or unofficial sources
Pan Am 727-235 N4735 at London Heathrow
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 08 May 2026 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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