performance data atr72-500

51/1998

ATR 72-500 PERFORMANCE DATA

ATR 72-500

PERFORMANCE DATA

DV/MT n° 490.018January 1997

51/1998


TABLE OF CONTENTS

INTRODUCTION

MAIN CHARACTERISTICS

REGULATORY PERFORMANCE

• TAKE-OFF

• LANDING

• ONE-ENGINE-OUT CEILING

EN ROUTE PERFORMANCE

OPERATIONAL POSSIBILITIES

51/1998


INTRODUCTION

51/1998


INTRODUCTION

Deep changes occured in the airline industry with deregulation of air transport or erratic fuel price evolution which led the commuters to a dramatic competition.Today to achieve the best operating results absolutely necessary to compete, the airlines must operate the most suitable aircraft meeting two contradictory requirements :- lowest direct operating cost,- best passenger comfort.

ATR superior technology is evidenced by the greater performance of its products when compared to similary powered competitors.

This brochure presents the ATR 72-500 performance. This aircraft is the latest improvement to ATR family and is fitted with Pratt & Whitney Canada PW127F engines and Hamilton Standard six blade 568F propellers.

The ATR 72-500 has been designed and built to respond to the specific needsof the regional carriers, with the following key points in mind :

- In terms of economics : . New technology and fuel efficient engines, . Extensive use of composites allowing dramatic reduction in weights, . State of the art cockpit and avionics, . Low maintenance costs due to extensive design to maintain philosophy, . Optimized capacity, . World-wide product support.These items providing the lowest operating cost per seat.

- In terms of passenger appeal : . High cruise and block speed, . High level of comfort due to generous dimensions and increased baggage overhead bin capacity and improvement of aesthetics of interior, . Low internal noise level.

The ATR 72-500, in addition, will offer in terms of performance : . High allowable payload from short runways, . Increased climb gradient from airfields with severe obstacle problems, . Excellent take-off performance out of "hot and high" airfields.

51/1998


ABBREVIATIONS AND UNITS

CAS Calibrated Air SpeedIAS Indicated Air SpeedISA International Standard AtmosphereM Mach numberMLW Maximum landing weightMMO Maximum operating Mach R/C Rate of climbTAS True air speedVR Rotation speedVSR 1g stalling speedVso Stalling speed in landing configurationV2 Take-off safety speed reached before 35ft heightVMCA Minimum control speed in flightVMCL Minimum control speed in flight (Landing configuration)WAT Weight, altitude, temperatureZp Pressure altitudedaN decaNewton°C Celsius degreeft/min feet per minuteft foot or feetsq.ft square footft3 cubic footcu.ft cubic foothr hour in inch = "kg kilogramkt knotkW kiloWattlb poundm meterm2

square meterm3 cubic metermin minutenm nautical mileshp shaft horsepower

51/1998



51/1998



MAIN DIMENSIONS

Overall length 27.166 m 89 ft 1.5 inOverall height 7.650 m 25 ft 1 inWing span 27.050 m 88 ft 9 inWing area 61 m2 657 sq.ft

WEIGHTS AND LOADINGS BASIC OPTIONAL

Maximum ramp weight 22,180 kg 48,898 lb 22,670 kg 49,978 lbMaximum take-off weight 22,000 kg 48,501 lb 22,500 kg 49,603 lbMaximum landing weight 21,850 kg 48,170 lb 22,350 kg 49,273 lbMaximum zero fuel weight 20,000 kg 44,092 lb 20,300 kg 44,753 lbOperational empty weight 12,850 kg 28,329 lb 12,850 kg 28,329 lbMaximum payload 7,150 kg 15,763 lb 7,450 kg 16,424 lbMaximum fuel load 5,000 kg 11,023 lb 5,000 kg 11,023 lbMaximum wing loading 353.8 73.822 361.84 75.500 (daN/m2 - lb/sq.ft)

POWERPLANT

Engine manufacturer Pratt and Whitney Aircraft of Canada LtdEngine designation PW 127 FThermodynamic power 2,397 kW 3,215 shpFlat rated at 2,051 kW 2,750 shpSpecific fuel consumption 0.298 kg/kW.hr 0.490 lb/shp.hrPropeller Hamilton Standard 568 F /6 bladesPropeller diameter 3,93 m 12 ft 11 in

51/1998


THREE VIEW DRAWING

27.166 m(89'1.5")

10.77 m(35'4")

7.65

m(2

5'1"

)

Wing area 61 m2 (657 sq.ft)

Ø 3.93 m(12'11")

27.050 m(88'9")

4.10 m(13'5")

8.10

m(2

6'7"

)

51/1998


ACCOMMODATIONS

CABIN

Cabin length 19.214 m 63 ft 0.5 in

Cabin width 2.570 m 8 ft 5.2 inCabin height 1.900 m 6 ft 2.8 in

Configuration 68 passengers at 31" pitch

BAGGAGE COMPARTMENT

Forward baggage compartment volume 5.80 m3 204.8 cu.ft

Rear baggage compartment volume 4.80 m3 169.5 cu.ft

Overhead bins volume 3.15 m3 111.2 cu.ftTotal baggage volume 13.75 m3 485.5 cu.ft

(incl. overhead bins)

Total baggage volume per pax 0.202 m3 7.14 cu.ft

DOOR APERTURES

Entrance door 0.635 x 1.727 m 25 x 68 in

Cargo door 1.295 x 1.575 m 51 x 62 in

2 emergency exits Type III 0.508 x 0.914 m 20 x 36 in

1 emergency exit Type IPilot emergency hatch 0.483 x 0.508 m 19 x 20 in

51/1998


CABIN LAYOUT68 SEATS AT 31" PITCH VERSION

FRONT CARGO DOOR

: ATTENDANT SEAT: BAGGAGE COMPARTMENT: GALLEY: EMERGENCY EXIT: STOWAGE: TOILET: CARGO DOOR: ENTRANCE DOOR: SERVICE DOOR

ABGIST

CDEDSD

0.51 m/20"

1.98 m/78" 13.8 m/543"

2.23 m/88"0.34 m/13.5"

▲SD

▲

RD

CD

4.8 m3

169.5 cu.ft

19.21 m/756.5"

3 m3

106 cu.ft

2.8 m3

99 cu.ft

14.10 m/555"

A

G

T

B

B

B

A

0.47 m/18.5"

G

51/1998


FUSELAGE CROSS SECTION

The ATR 72-500 cross section has been sized to offer maximum comfort to

the passenger.

In the passenger configuration the cabin offers a greater comfort than any

competitor due to its bilobed fuselage cross section.

Each seat row is located next to a window.

With respect to the current ATR 72 aircraft, the ATR 72-500 will benefit froma new interior, with improvement in such areas as :

• Aesthetics, with smooth shapes and better lightning, and incorporation of ahandrail on the edge of the overhead bins ;

• Overhead bins capacity, with a 40% volume increase without reducing the

passenger cabin volume ; the new overhead bins are 2 meters long witha total capacity of 3.13 m3 (0.0474 m3/pax on the 68 seats configuration).

• New materials with very good acoustic characteristics assuring noise absorption and improving passenger comfort.

51/1998


0.457 m(18")

0.440 m(17.3")

2.263 m(89") 2.570 m

(101.2")

1.90

0 m

(74.

8")

CABIN CROSS SECTION

51/1998


FLIGHT ENVELOPEISA

TAS (kt)

40030020010000

5.

10.

15.

20.

25.

30.

PRESSURE ALTITUDE(1,000 ft) .

M =

CA

S =

60 k

t

100

kt

140

kt

180

kt

220

kt

260

kt

25,000 ft

MM

O = 0.55

VSO

CA

S =

85 k

t (M

LW)

Max

Ope

ratin

g Sp

eed

CAS

= 2

50 k

t

0.1 0.2 0.3 0.4 0.5 0.6

36/1998


STALLING SPEEDSMINIMUM STALL SPEED - VSR

WEIGHT (1,000 kg)

70

75

80

85

90

95

100

105

110

115

15.14. 19. 21. 23.

CAS (kt)

120

16. 17. 18. 20. 22.

FLAPS 30° / GEAR DOWN

FLAPS 15° / GEAR UP

FLAPS 0° / GEAR UP

51/1998


REGULATORY PERFORMANCE

TAKE-OFF

LANDING

ONE-ENGINE-OUT CEILING

51/1998


TAKE-OFF

51/1998


TAKE-OFF

The take-off performance are given for a 15° flap setting

The balanced field lengths versus take-off weights are given in the following charts for :

ISA

ISA + 5°CISA + 10°C

ISA + 15°C


ISA + 30°C

and from sea level to 8,000 ft airport altitude.

These values comply with FAR 25 requirements (including amendment 42)and JAR 25 requirements (including amendment 5).

51/1998


TAKE-OFFPROCEDURES AND REQUIREMENTS ACCORDING TO FAR 25

V = 0 VefENGINEFAILURE

2 engines operating 1 engine operating

Vlof

V1 TAKE-OFF DECISION SPEED V2

35 ft

TAKE-OFF DISTANCE

TAKE-OFF RUN

TAKE-OFF DISTANCES

V = 0 V = 0

2 engines operating No engine

ACCELERATE - STOP DISTANCE

BALANCED FIELD LENGTH

V1 STOP DECISION SPEED

ENGINE REDUCTION

CLIMB GRADIENT ONE ENGINE INOPERATIVE

2nd SEGMENT FINAL TAKE-OFFMINIMUM SPEED V2 = 1.13VSR V = 1.18VSR

FLAP SETTING 15° 0°

LANDING GEAR UP UPENGINE RATING TAKE-OFF MAX CONTINUOUS

AIR CONDITIONING OFF OFF

ALTITUDE ABOVEAIRPORT 1,500 ft

REQUIRED GROSSCLIMB GRADIENT 2.4% 1.2%

VefENGINEFAILURE

36/1998


TAKE-OFFMAXIMUM OPERATIONAL WEIGHT

2nd SEGMENT CONDITIONFLAPS 15°

AIRPORT PRESSURE ALTITUDE (1,000 ft)

WEIGHT (1,000 kg)

0.

1.

2.

3.

4.

5.

6.

7.

8.

9.

19.18. 20. 21. 22.

MINIMUM SPEED :V2 = 1.13 VSR

V2 > 1.1 VMCA

+ 30 M.T

.O.W

.

TEMPERATURE (°C)

ISA+ 5+ 10+ 15+ 20+ 25

36/1998


TAKE-OFFCLIMB GRADIENT

2nd SEGMENT CONFIGURATIONFLAPS 15°

GROSS CLIMBGRADIENT (%)

WEIGHT (1,000 kg)

MINIMUM REQUIREDCLIMB GRADIENT (2.4%)

+30

0.

0.

1.

2.

3.

4.

5.

6.

7.

8.

9.

19.

Ref

eren

ce li

ne

TEMPERATURE

(°C)

18.

+20

+10ISA 2.

4.6.

8.

1.3.

5.7.

9.

20. 21. 22. 23.17.

10.

AIRPORT PRESSURE

ALTITUDE (1,000 ft)

MINIMUM SPEED :V2 = 1.13 VSR

V2 > 1.1 VMCA

36/1998


TAKE-OFFMAXIMUM OPERATIONAL WEIGHT

2nd SEGMENT CONDITIONFLAPS 15°

WEIGHT (1,000 kg)

0.

1.

2.

3.

4.

5.

6.

7.

8.

9.

19.18. 20. 21. 22.

M.T

.O.W

.

TEMPERATURE (°C)

ISA+ 5+ 10+ 15+ 20+ 25

V2 = 1.3 VSR Optimum speed providingthe best climb rate from

an unlimited runway


+ 30

36/1998



2nd SEGMENT CONFIGURATIONFLAPS 15°


WEIGHT (1,000 kg)

MINIMUM REQUIREDCLIMB GRADIENT (%)

+30

0.

0.

1.

2.

3.

4.

5.

6.

7.

8.

9.

19.

Ref

eren

ce li

ne

TEMPERATURE

(°C)

18.

+20

+10ISA 2.

4.6.

8.

1.3.

5.7.

9.

20. 21. 22. 23.17.

10.

AIRPORT PRESSURE

ALTITUDE (1,000 ft)

V2 = 1.3 VSR Optimum speed providingthe best climb rate from

an unlimited runway

36/1998


TAKE-OFFMAXIMUM OPERATIONAL WEIGHTFINAL TAKE-OFF CONFIGURATION

FLAPS 0°

WEIGHT (1,000 kg)

0.

1.

2.

3.

4.

5.

6.

7.

8.

9.

19.18. 20. 21. 22.

M.T

.O.W

.

TEMPERATURE (°C)

ISA+ 5+ 10+ 15+ 20+ 25


+ 30

V = 1.18 VSR

36/1998



FINAL TAKE-OFF CONFIGURATIONFLAPS 0°


WEIGHT (1,000 kg)

MINIMUM REQUIREDCLIMB GRADIENT (1.2%)

0.

1.

2.

3.

4.

5.

6.

7.

8.

9.

19.

Ref

eren

ce li

ne

18. 20. 21. 22. 23.17.

10.

V = 1.18 VSR

+30

0.

TEMPERATURE(°C)

+20+10

ISA2.

4.6.

8.

1.3.

5.7.

9.AIRPORT PRESSURE

ALTITUDE (1,000 ft)

36/1998


3,00

0

PRES

SUR

E A

LTIT

UD

E 8,

000

(ft)

TAKE-OFFBALANCED FIELD LENGTH

ISA

17. 19. 21.

WEIGHT (1,000 kg)

0.9

1.3

1.0

1.1

1.2

1.5

1.4

M.T

.O.W

.

18. 20. 22.

1.6

1.7

VR = 1.05 VMCA

7,00

06,

000

5,00

04,

000

2,00

01,

000

S.L.

BALANCED FIELD LENGTH (1,000 m)

2nd SEGMENT LIMITATION

16.

V2 = 1.13 VSR

36/1998


3,00

0

PRES

SUR

E A

LTIT

UD

E 8,

000

(ft)


ISA + 5°C

17. 19. 21.

WEIGHT (1,000 kg) M.T

.O.W

.

18. 20. 22.

VR = 1.05 VMCA

7,00

06,

000

5,00

04,

000

2,00

01,

000

S.L.


16.

V2 = 1.15 VSR

V2 = 1.13 VSR

0.9

1.3

1.0

1.1

1.2

1.5

1.4

1.6

1.7


36/1998


3,00

0

PRES

SUR

E A

LTIT

UD

E 8,

000

(ft)

VR = 1.05 VMCA

7,00

0

6,00

05,

000

4,00

02,

000

1,00

0S.L

.


ISA + 10°C

17. 19. 21.


.O.W

.

18. 20. 22.


16.

V2 = 1.15 VSR

V2 = 1.13 VSR

0.9

1.3

1.0

1.1

1.2

1.5

1.4

1.6

1.7


36/1998


3,00

0

PRES

SUR

E A

LTIT

UD

E 8,

000

(ft)


ISA + 15°C

17. 19. 21.


.O.W

.

18. 20. 22.

VR = 1.05 VMCA

7,00

06,

000

5,00

04,

000

2,00

01,

000

S.L.


16.

V2 = 1.15 VSR

V2 = 1.13 VSR

0.9

1.3

1.0

1.1

1.2

1.5

1.4

1.6

1.7


36/1998


3,00

0

PRES

SUR

E A

LTIT

UD

E 8,

000

(ft)


ISA + 20°C

17. 19. 21.


.O.W

.

18. 20. 22.

VR = 1.05 VMCA

7,00

06,

000

5,00

04,

000

2,00

01,

000

S.L.


16.

V2 = 1.15 VSR

V2 = 1.13 VSR

0.9

1.3

1.0

1.1

1.2

1.5

1.4

1.6

1.7


36/1998


3,00

0

PRES

SUR

E A

LTIT

UD

E 8,

000

(ft)


ISA + 25°C

17. 19. 21.


.O.W

.

18. 20. 22.

VR = 1.05 VMCA

7,00

06,

000

5,00

04,

000

2,00

01,

000

S.L.


16.

V2 = 1.15 VSR

V2 = 1.13 VSR

V2 = 1.17 VSR

0.9

1.3

1.0

1.1

1.2

1.5

1.4

1.6

1.7


36/1998


3,00

0

PRES

SUR

E A

LTIT

UD

E 8,

000

(ft)


ISA + 30°C

17. 19. 21.

WEIGHT (1,000 kg)

18. 20. 22.

VR = 1.05 VMCA

7,00

06,

000

5,00

04,

000

2,00

01,

000

S.L.


16.

V2 = 1.15 VSR

V2 = 1.13 VSR

V2 = 1.17 VSR

0.9

1.3

1.0

1.1

1.2

1.5

1.4

1.6

1.7


15.

51/1998


LANDING

51/1998


LANDING

The landing performance are given for the following flap settings :

Approach Landing

15° 30°

The following charts show the landing field length required for destination

and alternate airports.

Assumptions :

• hard dry and smooth runway,

• anti skid units operative,• no propeller reverse.

The limitations on landing weight are based on approach climb gradient

requirements.

All these data comply with FAR 25 and JAR 25 requirements.

51/1998


LANDINGPROCEDURES AND REQUIREMENTS ACCORDING TO FAR 25

LANDING DISTANCES

V = 0

touc

h do

wn

LANDING DISTANCE

CLIMB GRADIENT

APPROACH LANDING

1 engine operating 2 engines operating 1 engine inoperative

FLAP SETTING 15° 30°

LANDING GEAR UP DOWNENGINE RATING GO AROUND GO AROUND

AIR CONDITIONING OFF OFF

REQUIRED CLIMB GRADIENT 2.1% 3.2%

FLARE RUN

50 ft

V = 1.23VSR

LANDING FIELD LENGTH REQUIRED :destination : landing distance / 0.6

alternate : landing distance / 0.7

36/1998


LANDINGAPPROACH SPEEDS 1.23 VSR

WEIGHT (1,000 kg)

85

90

95

100

105

110

115

120

125

130

15.14. 19. 21. 23.

CAS (kt)

16. 17. 18. 20. 22.

FLAPS 30° / GEAR DOWN

FLAPS 15° / GEAR UP

VMCL

36/1998


LANDINGMAXIMUM OPERATIONAL WEIGHT

APPROACH CONDITION FLAPS 15°

WEIGHT (1,000 kg)

0.

1.

2.

3.

4.

5.

6.

7.

8.

9.

19.18. 20. 21. 22.

M.L

.W.TEMPERATURE (°C)

ISA+ 5+ 10+ 15+ 20+ 25


+ 30

36/1998


LANDINGLANDING FIELD LENGTH

ISA

7.

8.

9.

10.

11.

12.

13.

14.

LANDING FIELD LENGTH (100 m)

8.

9.

10.

11.

12.

13.

14.

15.

(1/0.7) (1/0.6)

AIRPORT PRESSURE ALTITUDE

(1,000 ft)

9.8.

7.

6.5.

4.3.

2.1.

S.L.

15. 16. 17.18.

19.

20.

21.

22.

23.

M.L.W.

WEIGHT (1

,000 kg)

APPROACH / CLIMBGRADIENT LIMITATION

51/1998


ONE-ENGINE-OUT CEILING

51/1998


ONE-ENGINE-OUT

The net ceiling (1.1% margin) complies with FAR 25 and JAR 25 requirements.

The reference conditions are :

• one engine operating at maximum continuous power,• anti-icing off,

• air conditioning on above 10,000 ft, off below 10,000 ft.

18/1998


ONE-ENGINE-OUTNET CEILING

PRESSURE ALTITUDE(1,000 ft)

5.

10.

15.

20. 10.

25.

20.

15.

5.

0.1. 2.

∆z (1,000 ft)

Zp(1,000 ft)

GEOMETRIC ALTITUDEH = Zp + ∆z

0.

ISA

+ 5

°IS

A +

10°

ISA + 15

°

ISA + 20°

ISA

+5

+10

+15

+20

TEMPERATURE (°C)

16.

17.

18.

19.

WEIG

HT (1,000 kg)

20.

21.

22.

21.

22.

23.

M.T.O.W.

Air Conditioning ON

Air Conditioning OFF

51/1998


EN ROUTE PERFORMANCE

CLIMB

CRUISE

DESCENT

HOLDING

51/1998


CLIMB

51/1998


CLIMB

Climb performance are presented for the following climb speeds :

IAS = 170 kt

IAS = 190 kt

Rate of climb is presented for :

ISA

ISA + 10°C

ISA + 20°C

For each speed the charts give the operational ceiling and the fuel, distance,

time required to climb from sea level to cruise altitude.

36/1998


PRESSU

RE A

LTITUD

E (1,000 ft)

CLIMB - 2 ENGINESIAS = 170 ktRATE OF CLIMB

ISA

23.

0.0

2.0

0.5

1.0

1.5

3.0

2.5

RATE OF CLIMB(1,000 ft/min)

21.

19.

17.

15.

INITIAL CLIMB WEIGHT (1,000 kg) 0.5.

10.

15.

20.

25.

36/1998


PRESSU

RE A

LTITUD

E (1,000 ft)


ISA + 10°C

23.

0.0

2.0

0.5

1.0

1.5

3.0

2.5


21.

19.

17.

15.

INITIAL CLIMB WEIGHT (1,000 kg)0.

5.

10.

15.

20.

25.

36/1998


PRESSURE ALTITUDE (1,000 ft)


ISA + 20°C

23.

0.0

2.0

0.5

1.0

1.5

3.0

2.5


21.

19.

17.

15.

INITIAL CLIMB WEIGHT (1,000 kg)

0.

5.

10.

15.

20.

18/1998


CLIMB - 2 ENGINESIAS = 170 kt

OPERATIONAL CEILING

R/C - 300 ft/min


15.

17.

19.

21.

23.

ISA

TEM

PERATURE (°

C)

+5

+10

+15

+20

PR

ES

SU

RE

ALT

ITU

DE

(1,

000

ft)

R/C - 200 ft/min

20.

25.


15.

17.

19.

21.

23.

ISA

TEM

PERATURE (°

C)+5

+10

+15

+2015.

20.

25.

18/1998



FUEL

FUEL(kg)

400.

20.

PR

ES

SU

RE

ALT

ITU

DE

(1,0

00 ft

)

200 ft/min

500.

300.

200.

100.

00.+ 20+ 10ISA

TEMPERATURE(°C)

Ref

eren

ce li

ne

17.

INITIAL CLIMB WEIGHT(1,000 kg)

15.21. 19.23.

300 ft/min

15.

10.

5.

0.

25.

18/1998



DISTANCE

DISTANCE(nm)

160.

20.

PR

ES

SU

RE

ALT

ITU

DE

(1,0

00 ft

)

200 ft/min

200.

120.

80.

40.

00.+ 20+ 10ISA

TEMPERATURE(°C)

Ref

eren

ce li

ne

17.


15.21. 19.23.

300 ft/min

15.

10.

5.0.

140.

180.

100.

60.

20.

25.

18/1998



TIME

TIME(min)

25.

20.

PR

ES

SU

RE

ALT

ITU

DE

(1,0

00 ft

)

200 ft/min 30.

20.

15.

10.

5.

+ 20+ 10ISA

TEMPERATURE(°C)

Ref

eren

ce li

ne

17.


15.21. 19.23.

300 ft/min

15.

10.

5.

0.

25.

0.

22.

36/1998


PRESSU

RE A

LTITUD

E (1,000 ft)


ISA

23.

0.0

2.0

0.5

1.0

1.5

3.0

2.5


21.

19.

17.

15.


5.

10.

15.

20.

36/1998


PRESSU

RE A

LTITUD

E (1,000 ft)


ISA + 10°C

23.

0.0

2.0

0.5

1.0

1.5

3.0

2.5


21.

19.

17.

15.


5.

10.

15.

20.

36/1998


PRESSU

RE A

LTITUD

E (1,000 ft)


ISA + 20°C

23.

0.0

2.0

0.5

1.0

1.5

3.0

2.5


21.

19.

17.

15.


0.

5.

10.

15.

36/1998



OPERATIONAL CEILING

R/C - 300 ft/min

PR

ES

SU

RE

AL

TIT

UD

E (

1,00

0 ft

) 16.

22.

INITIAL CLIMB WEIGHT

(1,000 kg)

15.

17.

19.

21.

23.

ISA

TEM

PER

ATU

RE

(°C

)+5

+10

+15

+20

20.

18.

14.

12.

18.

22.

20.

16.

14.

R/C - 200 ft/min

INITIAL CLIMB WEIGHT

(1,000 kg)

15.

17.

19.

21.

23.

ISA

TEM

PERATU

RE (°C

)+5

+10

+15

+20

18/1998



FUEL

FUEL(kg)

400.

19.

PR

ES

SU

RE

ALT

ITU

DE

(1,0

00 ft

)

200 ft/min

500.

300.

200.

100.

00.+ 20+ 10ISA

TEMPERATURE(°C)

Ref

eren

ce li

ne

17.


15.21. 19.23.

300 ft/min

15.

10.

5.0.

20.21.22.

23.

18/1998



DISTANCE

DISTANCE(nm)

160.

20.

PR

ES

SU

RE

ALT

ITU

DE

(1,0

00 ft

)

200 ft/min

200.

120.

80.

40.

00.+ 20+ 10ISA

TEMPERATURE(°C)

Ref

eren

ce li

ne

17.


15.21. 19.23.

300 ft/min

15.

10.

5.0.

140.

180.

100.

60.

20.

19.

21.

22.

23.

18/1998



TIME

TIME(min)

25.

20.

PR

ES

SU

RE

ALT

ITU

DE

(1,

000

ft)

200 ft/min30.

20.

15.

10.

5.

+ 20+ 10ISA

TEMPERATURE(°C)

Ref

eren

ce li

ne

17.


15.21. 19.23.

300 ft/min

15.

10.

5.

0. 0.

22.

23.

21.

19.

17.

51/1998


CRUISE

51/1998


CRUISE

The cruise performance are presented at maximum cruise power for :

ISAISA + 5°C

ISA + 10°C


and for long range cruise :

ISA

ISA + 5°C

For each temperature, the charts give the specific range versus speed.

36/1998


PR

ES

SU

RE

AL

TIT

UD

E (1,000 ft)

CRUISE - 2 ENGINESSPECIFIC RANGE

MAX. CRUISEISA

0.20

0.40

0.25

0.30

0.35

0.50

0.45

SPECIFIC RANGE(nm/kg)

WEIGHT (1,000 kg)15. 25.

230 240 250

TAS (kt)

260 270 280 290

17.19.

21.

23.

22.

20.

17.

15.

13.

10.

8.

5.4.

2.S.L.

23.15.

36/1998


PR

ES

SU

RE

AL

TIT

UD

E (1,000 ft)


MAX. CRUISEISA + 5°C

0.20

0.40

0.25

0.30

0.35

0.50

0.45


WEIGHT (1,000 kg)15. 25.

230 240 250

TAS (kt)

260 270 280 290

17.19.

21.

22.22.

20.

17.

15.

13.

10.

7.

5.

2.S.L.

36/1998


PR

ES

SU

RE

AL

TIT

UD

E (1,000 ft)



0.25

0.45

0.30

0.35

0.40

0.55

0.50


WEIGHT (1,000 kg)15. 25.

230 240 250

TAS (kt)

260 270 280 290

17.19.

21.

22.

22.

20.

17.

15.

13.

10.

7.

5.

S.L.

36/1998


PR

ES

SU

RE

AL

TIT

UD

E (1,000 ft)



0.25

0.45

0.30

0.35

0.40

0.55

0.50


WEIGHT (1,000 kg) 15. 25.

230 240 250

TAS (kt)

260 270 280 290

17.

19.

21.

22.

22.

20.

17.

15.

13.

10.

5.

S.L.

36/1998


PR

ES

SU

RE

AL

TIT

UD

E (1,000 ft)



0.25

0.45

0.30

0.35

0.40

0.55

0.50


WEIGHT (1,000 kg) 15.25.

230 240 250

TAS (kt)

260 270 280 290

17.

19.

21.

22.

22.

20.

17.

15.

13.

10.

5.

S.L.

36/1998


PRESSURE ALTIT

UDE (1,00

0 ft)


LONG RANGEISA

0.30

0.50

0.35

0.40

0.45

0.60

0.55


WEIGHT (1,000 kg)

25.

180 190 200

TAS (kt)

210 220 230 240

18.

21.20.

22.

20.

16.

15.

14.

10.

5.

250

36/1998


PRESSURE ALTIT

UDE (1,00

0 ft)


LONG RANGEISA + 5°C

0.30

0.50

0.35

0.40

0.45

0.60

0.55


WEIGHT (1,000 kg)

25.

180 190 200

TAS (kt)

210 220 230 240

18.

21.20.

22.

20.

16.

15.

14.

10.

5.

250

51/1998


DESCENT

51/1998


DESCENT

Descent performance are given for the following descent speeds :

IAS = 200 kt

IAS = 220 ktIAS = 250 kt

Descent performance are presented in the form of time, distance and fuel

required to descend from cruise altitude to 1,500 ft.

The cabin rate of descent is equivalent to 400 ft/min at sea level.

18/1998


DESCENTIAS = 200 kt

TIME, DISTANCE, FUELISA

WEIGHT (1,000 kg)

PR

ES

SU

RE

ALT

ITU

DE

(1,

000

ft)

25.18.

13.20.

15.

10.

5.

0.5.0. 10. 15.

TIME (min)

WEIGHT (1,000 kg)25.

18.14.20.

15.

10.

5.

0.20.0. 50.

DISTANCE (nm)

WEIGHT (1,000 kg)

25.18.

14.20.

15.

10.

5.

0.50.0. 100. 150.

FUEL (kg)

10. 30. 40. 60. 70.

22.

22.

22.

18/1998


DESCENTIAS = 220 kt


WEIGHT (1,000 kg)

PR

ES

SU

RE

ALT

ITU

DE

(1,

000

ft)

25.

14.

20.

15.

10.

5.

0.5.0. 10. 15.

TIME (min)


14.

20.

15.

10.

5.

0.20.0. 50.

DISTANCE (nm)

WEIGHT (1,000 kg)

25.

18.20.

15.

10.

5.

0.50.0. 100. 150.

FUEL (kg)

10. 30. 40. 60. 70.

22.18.

18.22.

22.

14.

18/1998


DESCENTIAS = 250 kt


WEIGHT (1,000 kg)

PR

ES

SU

RE

ALT

ITU

DE

(1,

000

ft)

25.

14.

20.

15.

10.

5.

0.5.0. 10. 15.

TIME (min)


14.

20.

15.

10.

5.

0.20.0. 50.

DISTANCE (nm)


18.

20.

15.

10.

5.

0.50.0. 100. 150.

FUEL (kg)

10. 30. 40. 60. 70.

22.18.

18.22.

22.

14.

51/1998


HOLDING

18/1998


HOLDINGFUEL CONSUMPTION, SPEED

ISA

WEIGHT (1,000 kg)

18.16. 20. 22.14.

160

150

140

130

IAS(kt)

550

500

450

400

350

FUEL(kg/hr)

15.10.

5.1.5

14.

16.

18.

20.

22.

PRESSURE ALTITUDE(1,000 ft)

WEIG

HT (1,000 kg)

51/1998


OPERATIONAL POSSIBILITIES

51/1998


PAYLOAD / RANGEOPERATIONAL ASSUMPTIONS

MANŒUVRING ALLOWANCES

Time Fuel burnt

Starting and taxi-out* 3 min 9 kg

Take-off and acceleration 1.3 min 21 kg

Approach and landing 2 min 14 kg

Taxi-in* 1 min 3 kg--------- -------

7.3 min 47 kg

* Taxi-out and in are performed on one engine.

OPERATING TECHNIQUES

Climb 170 kt IAS

Cruise Max cruise speed at optimum altitude

Descent 220 kt IAS (1,500 ft/min)

FUEL RESERVES

45 min at corresponding cruise power and altitude plus fuel

for flight to the alternate (including climb, cruise and descent).

Alternate = 87 nm

36/1998


OPTIONAL MTOW 22,500 kg (49,600 lb)

PAYLOAD / RANGECHARACTERISTICS

2.

68 PAX * 95 kg

3.

4.

5.

6.

7.

8.

PAYLOAD(1,000 kg)

500 1,000 2,0001,5000.

1.

0

RANGE (nm)

BASIC MTOW22,000 kg (48,500 lb)

HIGH SPEEDISA CONDITIONS

OEW = 12,850 kg (28,329 lb)

51/1998


MISSION PROFILE SELECTION

TECHNIQUE CLIMB CRUISE DESCENT (1,500 ft/min)

Long Range 170 kt IAS Long Range/FL 210-250 200 kt IASHigh Speed 170 kt IAS Max.Cruise Power/FL 160-220 220 kt IASMinimum Time 190 kt IAS Max.Cruise Power/FL 140-180 250 kt IAS

Allowances and fuel reserves :

Taxi out 3 min / 9kg Fuel reserves : 87 nm alternateTaxi in 1 min / 3 kg and 45' flight time at cruise power and altitudeTake-off 1.3 min / 21 kg O.E.W. = 12,850 kg (28,329 lb)Landing 2 min / 14 kg Payload : 68 pax at 95 kg (209 lb)

160

170

190

200

220

250

200250 140

LONGRANGE

CLIMB SPEED(kt IAS)

DESCENT SPEED(kt IAS)

FLIGHT LEVEL

HIGHSPEED

MINIMUMTIME

BLOCK FUEL & BLOCK TIME OPERATIONAL ASSUMPTIONS :

36/1998


BLOCK FUEL(1,000 kg)

0.6

0.8

1.0

0.4

0.2

500 600 700

1.6

1.8

2.0

1.4

1.2

800

2.2

2.4

RANGE (nm)

100 200 300 400

BLOCK FUEL(1,000 kg)

RANGE (nm)

1.2LR

MTHS

BLOCK FUELSECTOR PERFORMANCE

WITH 68 PAX (95 kg)ISA

1.4

1.0

LR

MT

HS

HS : High SpeedLR : Long RangeMT : Minimum Time

36/1998


BLOCK TIME(min)

60

80

100

40

20

500 600 700

160

180

200

140

120

800

220

RANGE (nm)

100 200 300 400

BLOCK TIME(min)

RANGE (nm)

120 LR

MTHS

140

100

LR

MTHS

HS : High SpeedLR : Long RangeMT : Minimum Time

BLOCK TIMESECTOR PERFORMANCE

WITH 68 PAX (95 kg)ISA

performance data atr72-500

Documents

terms of performance

performance dataabbreviations

performance dataatr

greater performance

excellent takeoff performance

performance datadvmt

atr family

block speed