14 5 mccauley f 5 performance parte e by Libros Aeronáuticos

METRO III ICAO ANNEX 8 PART E â&#x20AC;&#x201C; TAKEOFF PERFORMANCE WET CONTENTS ITEM

PAGE

Takeoff Power Check Chart ................................................................................................................4E-1 Maximum Takeoff Weight Limitation Chart ......................................................................................... 4E-3 Takeoff Speed Schedules B.F. Goodrich Single Rotor Brakes ............................................................................................ 4E-4 Goodyear Aerospace Dual Rotor Brakes ................................................................................. 4E-12 Distance to Accelerate to V1 and Stop B.F. Goodrich Single Rotor Brakes .......................................................................................... 4E-20 Goodyear Aerospace Dual Rotor Brakes ................................................................................. 4E-21 Single Engine Takeoff Distance to 35 Foot Height B.F. Goodrich Single Rotor Brakes .......................................................................................... 4E-22 Goodyear Aerospace Dual Rotor Brakes ................................................................................. 4E-24 Takeoff Flight Path Distance to 1500 Foot Height ............................................................................ 4E-26 Second Segment Climb Gradient ............................................................................................. 4E-30 Close In Obstacle Clearance ...................................................................................................4E-31 Second Segment Acceleration Distance .................................................................................. 4E-32 Third Segment Climb Gradient ................................................................................................. 4E-34 Distant Obstacle Clearance ..................................................................................................... 4E-35 Two Engine Rate of Climb At V50. .................................................................................................... 4E-36

FAA APPROVED: MAY 22/89

PERFORMANCE

4E-i 4MC

METRO III ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4E-ii 4MC

PERFORMANCE

MANUFACTURER'S DATA ISSUED: MAY 22/89

METRO III - ICAO ANNEX 8 TAKEOFF

POWER

CHECK

ASSOCIATED

CHART

- WET EXAMPLE:

CONDITIONS:

GIVEN:

POWER . . . . . . . . . . . . . . . . TAKEOFF (WET) RPM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . ..lOO?/o EGT . . . . .. . . 650°C MAX ALLOWABLE GEN LOAD . . . . . . . .. . . . .. . .. . . . . . 300 AMPS BLEED AIR . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . OFF . . . . . . . . . . . . SEE GRAPH ENG ANTI-ICE SPEED . . . . . . . . . . . . . . .. . .. . . . .. . . . . . . . . . . STATIC

OBTAIN:

OAT = 27°C PRESSURE ALTITUDE = 3,000 FEET ENGINE ANTI-ICE SYSTEM - OFF ENGINE TORQUE = 99 PERCENT

NOTE l

MAXIMUM

OAT

WITH

MINIMUM

OAT

FOR

-10

ENGINE WET

ANTI-ICE

POWER

IS 5°C.

OPERATION

REFERENCE EGT IS THE EGT OBTAINED WHEN ENGINE TORQUE IS SET IN ACCORDANCE CHART AND MUST NOT EXCEED 650°C.

20 OAT (OC)

IS -6°C. REQUIRED WITH THIS

OFF

ON ENGINE ANTI-ICE SYSTEM

FIGURE FAA APPROVED:

MAY 22189

4E-1

PERFORMANCE

4E-1 4MC

METRO III ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4E-2 4MC

PERFORMANCE

FAA APPROVED: MAYDATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89

METRO III - ICAO ANNEX 8 MAXIMUM

TAKEOFF

ASSOCIATED

WEIGHT

LIMITATION

CHART

- WET NOTE

CONDITIONS: .

POWER . . . . . . . . .._................. TAKEOFF (WET) GEN LOAD . . . . . . . . . . . . . . . .. . .. . . . .. . . . . . . . . 300 AMPS BLEED AIR . . .. . . . .. . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ENG ANTI-ICE . . . . . . . . . . . . . . . OFF (SEE NOTE) DOWN (TAKEOFF) GEAR . . . . .. . . . . . .._.............. UP (SECOND AND THIRD SEGMENT) FLAPS . . . . . . . . . . . . . . . . . . . . . . .. . . . . . . .. .. 114 (TAKEOFF) UP (ENROUTE)

REDUCE TAKEOFF WEIGHT WITH ENGINE ANTI-ICE ON. MAXIMUM

OAT

WITH

ENGINE

1,100

ANTI-ICE

POUNDS

(500

kg)

IS 5°C.

THIS WEIGHT IS THE MAXIMUM AT WHICH TAKEOFF CAN BE CONTINUED AFTER AN ENGINE FAILURE IS RECOGNIZED AT OR ABOVE VI.

EXAMPLE: GIVEN: OBTAIN:

OAT = 32°C PRESSURE ALTITUDE = 5,500 FEET TAKEOFF WEIGHT = 13,050 POUNDS

(5920

kg)

16 7

FIGURE FAA APPROVED:

MAY 22189

4E-2

PERFORMANCE

4E-3 4MC

TAKEOFF SPEED SCHEDULE (KIAS) -WET B.F. GOODRICH SINGLE ROTOR BRAKES

1 POUNDS 1

. TAKEOFF IN TEMPERATURE AN0 ALTITUDE CONDITIONS SHOWN TO THE RIGHT OF AND ABOVE THE SOLID. STEPPED LINE IS NOT APPROVED. THE SPEEDS IN THAT AREA OF THE CHART ARE PROVIDED FOR INTERPOLATION ONLY. . REFER

TO FIGURE

4E-2

FOR MAXIMUM

PERMISSIBLE

TAKEOFF

WEIGHTS. I

OUTSIDE 0

‘RES’ RLT IF11

“1 “R 107 -I% 101 101 102 103 - 103 103

103

“2

“50 -

1lU 113 -Es 112 101 111 -loJ 113 102 115 103 117 - 103 119 103 120 103 122

125 12u 123

107

122 m 126 129 131 i-33 135

RIR,

TEHPEIWTURE

“1 “R 109 106 103 101 100 101 101 102 103 103

109 106 103 101 100 101 101 102 103 103

“2 “SO

111 110 110 112 1111

-E

107 -E2

101

-I# 102 -103 103

+I!

1111 JlJ 111 111

125 m 122 122 123 125 127

1001 0

103

200

lr1500 lUOO0 13500 13000 O- 12500 12000 11500 11000 10500 10000 -

107 105 102 101 101 102 102 103 103 103

1111 113 112 111 113 1111 116 118 120 121

125 12u 123 123 125 127 129 132 13u 136

102 -SE 103

-% 116 118 119 121

130 132 13Y -

106 108 -105 102 -% 101 101 - 101 -6% 101 102 102 103 -E 103 103 103

125 E 121 122 in 125

I% 133 -

109 107 1011 101 100 100 101 101 102 103

122 121 122 124 126

I I

107

( ‘Cl

1111 113 111 109 109 111 112 1111 116 118

110 107 105 102 101 100 100 101 102 102

114 113 111 109 109 109 111 113 115 117

“R

“2

105 102 101 100 100

111 109 109 110 111

I I

125 123 122 121 121 122 1211 127 129 132 I

“1

I I

111 108 105 103 101 100 100 100 101 102 ,

I I

111 108 105 103 101 100 100 100 101 102 I

“50

122 121 121 122 1211

I I

1111 113 111 109 109 109 110 112 1111 116 I

“RI

106 103 102 101 100

I I

124 112 123 109 122 107 120 1011 120 103 121 102 122 101 12’l 100 126 100 129 101 I

I “2I”SOl

“11

“RI

“21’50

zm -I 3 0 --

I 0

D 0 D z z m x 00

021

6OT

611

601

021

601 601

021

201 EOI hOI SO1

IIIIllIIIIIIIIIIl

z z

121 121 021 021 611 611

a 0

601 601 601 601 601 601

001 101 201 EOI 1101 SO1

001 101 201 EOI 7101 SO1

221 011 001 121 601 101 021 601 201 021 601 EOI 021 601 7101 611'6Ol'f1OI'hOI 6II 601 901 121 III 801

E21 221 121 021 021 611 021 121 221

III 011 601 601 601 601 601 III &II

001 001 101 201 EOI fiO1 SO1 801 011

001 101 201 EOI hO1 901 801

001 001 101 201 EOI hO1 SO1 801 011

201 101 101 ooi 001 101 EOI SO1 801 011

911 7111 211 ii1 601 601 601 III EII 7111

EOI 901 601 011

601 901 601 III

101 101 001 001 101

II21 211 101 101 L21 ill1 221 011 001 001 S21 211 121 601 101 101 E21 111 021 601 101 101 12[ 011 021 601 201 201 021 601 021'601'E01'&01'021'601'201'201-021~601~101~I01-221 021 601 SO1 SO1 021 601 121 III LO1 LO1 121 III Cd1 El1 011 011 E2[ &II h21 hl1 211 601 h21 i111

921 f-121 221 121 021 021 021 121 E2 hz:

hI1 211 011 601 601 601 601 III E d:

101 101 001 101 101 201 hOI 901 21; 60

101 101 001 101 101 201 hOI 901 601 III

621 921 h21 2ii 121 021 021 221 EZL h21

%ji hOI LO1 011

t%I 111 El1 hII

101 001

211 011

EOI 201

811 911

221 011 001 001 S2I &II 101 101 821 SlI 201 201 IEI -121 601 001 001 E21 III 001 001 S21 &II 101 101 821 102116011 121 601 021 601 101 101 121 011 001 001 h21 021 601 201 201 021 601 101 101 221 ~611~60~~h01~~01~02~~601t~01t&01~021~601i201~201~D21~601~001~001~221~011~~01~001~~2~i211~~01~101~00S21 611 601 SO1 SO1 021 601 h01 i101 021 601 &bI EOI 121 121 III LO1 LO1 121 111 901 901 221 ET1 011 011 E21 El1 801 801 E21 hI1 211 III h21 fill III III 521 h21

Illllllllll

OSA

221

OS*

Ej(

OSA

Cl.1 'SlH013M

dd03XVl3lEISSIYY~3d

MlWlXVW

3MlltA~3dW~i

tlOdZ-393MflW

Oltl333tl

201 101 101 oar 001 101 EOI SO1 801 011

ED1 201 101 001 toi hOI LO1 011

O&I 821 521 E21 121 OZI 221 EZI fi2T

2&I O&I L21 s21 E21 121 121 221 EZI S21

hE1 ZEI L21 i-l21 iii 221 h21 S21

OSA

LII SII &II III 011 601 III EII hII

811 LIT fiI1 ii1 III 601 601 III &II hI1

021 811 ilI1 211 t11i III &II hI1

UItl

EOI 201 101 001 001 201 SO1 LO1 011

EOI 201 201 101 001 001 101 hOI LO1 601

EOI EOI 101 101 101 EOI 901 801

EOI 201 101 001 001 201 SO1 LO1 011

EOl 201 201 roi 001 001 101 h01 LO1 601

EOl EOI 101 101 iti1 EOl 901 801

EEI iE1 621 921 n21 121 221 fi2I S21

h&I Z&I OEI ii1 SLI E21 221 221 I'121 S21

SE1 E&I 821 921 %I E21 I121 S21

OS&

021 EOI EOI 8iI EOI EtlI 911 201 201 hI1 101 101 III 101 101 CIII~OOI~OOI‘OOS2I 011 101 101 III EOI EOI EII 901 901 hI1 801 801

021 611 LII -. SII EII III 011 III EII hI1

121 611 911 fill iii 111 &II bI1

EOI EOI 201 .%I 101 001 101 EOI SO1 801

EOI EOI 201 101 iii 201 SO1 801

klA

00001 OOSOI. 00011 OOSII 00021 000&I OOSEI OOOhI OOSfiI

EOI 00001 EOI OOSOI< 201 -_. DC-IO11 _-_.. 201 OOSII 101 00021. 001 OOS21 101,OOOEI EOI OOSEI SO1 OOOhI 801 OOShI

EOI EOI

000s

OOOh

00001 OOSOI

201 101 itli 201 SO1 801

000&I 00S;EI 0OOi11 OOShI

1sa-u SE&

3UISltlQ

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NI d303XVl.

Ihiatnvni .-. -. . _-

S3YVklS tlOlOkl3lDNIS 13M - kVl)l) 3lfNJ3H3S

H3lkKl000 ‘zl’9 Cl33dS ddO3YVl

METRO III ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4E-6 4MC

PERFORMANCE

FAA APPROVED: MAYDATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89

FAA APPROVED:

4E-3 (continued)

PERFORMANCE

FIGURE

METRO III - ICAO ANNEX 8

MAY 22189

4E-7 4MC

4E-8 4MC

4E-3 (continued) FAA APPROVED:

METRO III - ICAO ANNEX 8

FIGURE

PERFORMANCE

MAY 22189

TAKEOFF SPEED SCHEDULE (KIAS) -WET B. F. GOODRICH SINGLE ROTOR BRAKES /CAUTION/

piiziig

. TAKEOFF IN TEMPERATURE AND ALTITUDE CONDITIONS SHOWN TO THE RIGHT OF AND ABOVE THE SOLID. STEPPED LINE IS NOT APPROVED. THE SPEEDS IN THAT AREA OF THE CHART ARE PROVIDED FOR INTERPOLATION ONLY. . REFER

TO FIGURE

4E-2

FOR MAXIMUM

PERMISSIBLE

TAKEOFF

WEIGHTS. I

OUTSIDE PIES! ALT IF11

W!lSS IK

-6

“1

“R

108

3001

8580 61loo 6200 6000 5800 5600 suoo 5200 5000 U800 11600

11001

6580 8UOO 6200 6000 5800 5600 51100 5200 5000 m 4600

108 108 im i-E 1OY 1011 102 102 i-in E-i 101 101 3% 102 103 103 -

% 102 103 103 -

6580 6r100 6200 6000 5800 5600 suoo 5200 e 11800 U600

i-m 106

i% 100

i% 100 pcJg 101 101 102 i-m 103 -

5001

Es 101

#I!

iii 101 102 103 103 103 -

KS 101 10.2 i-m 103 joJ -

%Y 101 102 103 103 -

101

"SO

I "1

RIR 30

“SO “1

."2 -

11’4 113 112

125 12Y 123

108 106 10’4

114

125

1211 % 123 110 122 122 ii! 123 113 125 1111 127 ii-G 129 118 131 119 133 -

110 108 105 103 101 100 100 101 101 102 103

1111 125 ii-3 121 112 122 121 iii 121 110 122 123 34 125 1111 127 116 129 ii-ii 131 -

110 108 106 1OU 102 101 100 100 101 101 102

1111 113 112 110 109

12Y 123 122 121 120 121

E 111 113 i-is 116 -

122

110 109 107 105 103 102 101 100 100 101 101

123 125

127 129

TEMPERFITURE

f ‘Cl

I “11

“RI

“2~“5C~~

50 “1

“R

1111

107 105 i-m 103 102 m-i 100 100

110 109 109 109 109 i-m 109 110 --

1111 rn 112 110 109 109

i-E 105

109 109

3 110 111 ii-2 -

% 102 101 i-m -

s-z 109 109 i-65 -

!E 110 109 109 109 110 iii 113 115 -

111 109 107 105 103 102 101 100

1111 113 112 110 109 109 109 110

1211 123 122 121 120 120 121 121

109 109 108 106 1OY 103 102 101

112 110 1OQ 106 1011 103 102 101

i-i-u 113 K 109 i% 109 109 iii3 112 -

105 i-55 1OY 103 102 101

109

109 109 109 c

METRO III ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4E-10 4MC

PERFORMANCE

FAA APPROVED: MAYDATA 22/89 MANUFACTURER'S ISSUED: MAY 22/89

FIGURE 4E-3 (continued) PERFORMANCE

METRO III - ICAO ANNEX 8

FAA APPROVED: MAY 22189

4E-11 4MC

TAKEOFF SPEED SCHEDULE (KIAS) -WET GOODYEAR AEROSPACE DUAL ROTOR BRAKES lPOUNDSj

. TAKEOFF IN TEMPERATURE AND ALTITIJOE CONDITIONS SHOWN TO THE RIGHT OF AN0 ABOVE THE SOLID. STEPPED LINE IS NOT APPROMO. THE SPEEDS IN THAT AREA OF THE CHART ARE PROVIDED FOR INTERPOLATION . REFER

I PRESS GRCISS RLT WT (FTI I ‘LBs)

S.L.

-6 “2

“50

“1

“R

“2

“SO

“1

“R

“2

“50

“1

“50

“1

“R

“1

114 113

125 110 1211 107

110 107

1111 121 113 123

11.1 109

109 110 111 113 115 117

102 101 100 100 101 102

11’4 116 118 119 121 123

127 129 131 133 135 137

101 102 103 103 103 103

113 115 117 119 120 122

125 127 130 132 13Y 136

101 101 102 103 103 103

112 12Y 1111 126 116 129 118 131 119 133 121 135

100 101 101 102 103 103

110 112 1111 116 118 120

122 1211 126 129 131 133

101 100 100 101 102 103

107 1OY 102 101 101 102 103 103 103 103

107 1011 102 101 101 102 103 103 103 103

114 113 112 112 113 115 117 119 120 122

125 12Y 121 12Y 126 128 130 133 134 137

107 105 102 101 101 101 102 103 103 103

107 105 102 101 101 101 102 10 ‘3 10 3 103

1111 113 111 111 112 1111 116 118 119 121

125 1211 123 123 121 126 129 131 133 135

108 106 103 101 100 101 102 102 103 103

114 113 111 110 111 113 11’4 117 118 120

125 12Y 122 122 123 125 127 130 132 13Y

109 107 104 101 100 100 101 101 102 103

109 107 1011 101 100 100 101 101 102 103

11’4 113 111 109 109 111 112 11’4 116 118

125 123 122 121 121 122 121 127 129 132

111 108 105 103 101 100 100 100 101 102

111 108 105 103 101 100 100 100

1lY 113 111 109 110 111 113 115 117 119

125 123 122 121 122 123 125 128 130 133

1111 113 111 109 109 109 111 113 115 117

12Y 123 122 120 120 121 123 125 127 130

“2

I I I I I I I I I I I I I I I I r--1---1--

107 105 102 101 101 102 102 103 103 103

1111 113 112 111 113 1111 116 118 120 121

125 121 123 123 125 127 129 132 131 136

108 105 102 101 101 101 102 103 103 103

1111 113 111 110 111 113 115 117 119 120

125 121 122 122 123 126 128 130 133 135

109 106 1CIY 101 100 100 101 102 103 103

109 106 10’4 101 100 100 101 102 103 103

110 107 105 102 101 100 100 101 102 102

TAKEOFF

WEIGHTS.

50 “50

102 102 103 103 103 103

107 105 102 101 101 102 102 103 103 103

PERMISSIBLE

110

102 102 103 103 103 103

IIIIII

FOR MAXIMUM

[‘Cl

32500 12000 11500 11000 10500 10000

111500 lUOO0 13500 13000 12500 12000 11500 ,110OO 10500 10000

“R

462

TEMPERRTURE

lYSO0 106 106 114 125 107 107 11’4 125 108 108 1111 125 109 109 lliOO0 1011 1OY 113 1211 loll 104 113 12Y 105 105 113 12Y 106 106 ~13500l102~1021112~129~102~102~112~123~102~102~111~123~103~103~111112211051105111111221106~~106~

111500 F1llOOO 13500 13000 12500 12000 11500 11000 10500 10000

“1

RIR

“2

I 2000

OUTSIDE

“R

I 1000

TO FIGURE

121 122 12Y 126 128 13 1

“R

55 “2

1111 113 111 3 109 102 109 101 109 100 110 100’111 101 113 102 115 111 109

114 1211 112 112 114 113 123 109 109 113 111 122 107 107 111 109 120 1011 104 109 109 120 103 103 109 109 121 102 102 109 110 122 101 101 109 112 12’4 1001100~110~12 ~liifili~~l~oilioilii3l~26,~oo,~oo,~~2,~2~ _ _-_ 10; _ __101111411~61100~100~111~12 _-_

“50

“1

“R

“2

v50

1211 1?3 121-107 120 104 120 102 t20 102 121 101 123 100 125 100 128 101

107 104 102 102 101 100 100 101

111 109 109 109 109 110 111 113

121 120 126 120 121 121 123 126

1211 123 121 120 120 120 121 2 3

105 103 102 101 100 100

109 109 109 109 109 110

120 120 120 120 121 122

105 103 102 101 100 100 I

111 109 106 103 102 101 100 100 101 101

1111 113 111 109 109 109 109 110 112 114

12Y 1?3 121 120 120 120 121 122 1211 127

107 105 103 103 102 101 100 100

111 109 109 109 109 109 110 112

121 120 119 120 120 121 122 124

1011 103 102 101 100 100

109 109 109 109 109 110

119 120 120 120 121 122

0 D 0 D Z Z

m x 00

TAKEOFF SPEED SCHEDULE (KIAS) -WET GOODYEAR AEROSPACE DUAL ROTOR BRAKES fiziEJ

reiiimq

* REFER

OUTSIDE ‘RESS GRUSS -6 I / I ALT WT Ffl 1 fL6S) 1 v,I VRI v21v56I

10 I

, v, 1 v~I

I v2(v5o1

RIR

, v,l

30 I v21vsoi

v1 1 %I

I ‘21’501

108 105 102 101

1111 113 111 111

125 121 123 122

108 106 103 101

11Y 113 111 110

125 1211 122 121

110 107 1OY 102

110 107 1011 102

11Y 113 111 109

125 123 122 121

111 108 106 103

11Y 113 111 109

12Y 123 121 120

11500 ,110OO 10500 10000

102 103 103 103

116 118 119 121

128 131 133 135

101 102 103 103

1lY 116 118 120

127 129 132 13Y

101 101 102 103

112 113 116 118

129 126 128 131

100 100 101 102

110 111 113 115

121 123 125 128

lY500 lYOO0 13500

108 10s 103

108 105 103

11Y 113 111

125 121 122

109 107 104

109 107 iou

1111 125 113 123 iii 122

110 108

1111 113

12Y 123

112 109

112 09-

1111 121

In5

Ins

111

177

In6

~L-l.... IUB lUt3 1110001106

106

11Y 113

I.--l...1 125 110 12’4

107

110 107

13S00l103l103l111~122llOSllOSllllll?7ll~~ll~~llllll7llln7lln7

13000 soor I 12500 12000 11500 ,llOOO 10500 10000

101 100 101 101 102 103 103

4E-2

FOR MAXIMUM

112 110 107 1011 103 102 101 100 100 101

TAKEOFF

110 110 112 1111 116 118 120

121 122 121 126 129 131 133

102 101 100 100 101 102 103

1111 1211 111 113 123 109

111 109

1111 124 113 123

. .

109 109 110 111 113 115 117

_--

1111 113 111 109 109 109 109 109 111 113

50 I

, ‘1 1 ‘RI

1211 122 121 126105 120 1011 120 103 120 102 121 101 123 100 125 100

105 1OY 103 102 101 100 100

I ‘21’501

109 109 109 109 109 109 110

119 119 120 120 121 121 122

_--

---

_--

120 120 121 123 125 128 130

103 102 101 100 100 101 101

109 120 105 109 120 103 109 120 102 110 121 101 111~123~101~101 Il7ll7=xllnnltnn

_-.

105 103 102 IO1

122

111 109 109 109 109 ,109 110

121 120 120 120 120 121 122

-I 3 0I 0

Z Z

. . . . ^ .. --I

55 I I I ‘1 1 “RI v21v50

D 0 D

113

WEIGHTS.

[‘Cl

UO 1 I I ‘1 1 %I v2jv501 112 110 107 1011 103 102 101 100 100 101

PERMISSIBLE

‘3~1u0~100~1091121~101~101l109~120~102~102~1uYl1~u[1u~~1~ 100 100 111 123 100 100 109 121 101 101 113 125 100 100 110 122

1101

.--

TO FIGURE

TEMPERRTURE

1YSOO slYOOO 13500 13000

11500~102~102~115~1 ..---

. TAKEOFF IN TEMPERATURE AND ALTITUDE CONDITIONS SHOWN TO THE RIGHT OF AND ABOVE THE SOLID. STEPPED LINE IS NOT APPROVED. THE SPEEDS IN THAT AREA OF THE CHART ARE PROVIDED FOR INTERPOLATION

108 106 1011 1011 103 102 101

108 111 106 109 1011 109 1011 109 103 109 102 109 101 109

121 119 119 120 120 120 121

105 1OY 103 102

10s 1011 103 102

109 109 109 109

119 120 120 120

m x 00

METRO III ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4E-14 4MC

PERFORMANCE

FAA APPROVED: MAY 22/89

TAKEOFF SPEED SCHEDULE (KIAS) -WET GOODYEAR AEROSPACE DUAL ROTOR BRAKES [POUNDSI

* TAKEOFF SPEEDS . REFER

OUTSIDE ‘RES’ RLT LFT)

10 vl

RIR

H TEMPERATURE

AND ALTITUDE

CONDITIONS

lN THAT AREA OF THE CHART ARE PROVIDED TO FIGURE

TEMPERRTURE

4E-2

FOR MAXIMUM

PERMISSIBLE

SHOWN

TO THE

FOR INTERPOLATION TAKEOFF

WEIGHTS.

[ ‘Cl

I ‘RI

v21v501

‘1 1 +I/

v21v50t

‘11

%lI

v2iv50i

‘1

1 ‘RI

v21v50

111 111 108 106 103 SE 100 100 101 102

108 106 103 101 101 100 100 mi 102

111 109 m 1011 102 101 101 100 100 101

112 109 106 104 102 101 101 100 100 101

112

z! 105

E 105 103 102 101 100 100 101

6001

800 E 101 % 101

I c)

D 2 z

4E-16 4MC

4E-4 (continued) FAA APPROVED:

METRO III - ICAO ANNEX 8

FIGURE

PERFORMANCE

MAY 22189

TAKEOFF SPEED SCHEDULE (KIAS) -WET GOODYEAR AEROSPACE DUAL ROTOR BRAKES I KILOGRAMS

TAKEOFF SPEEDS

f REFER

IJUTSIDE ‘RESS 1 RLT IFTI

3000

-6 I'KG

FllR

IN TEMPERATURE

AND ALTITUDE

CONDITIONS

IN THAT AREA OF THE CHART ARE PROVIDED TO FIGURE

4E-2

TEMPERATURE

FOR MAXIMUM

SHOWN

FOR INTERPOLATION

PERMISSIBLE

TAKEOFF

"50

“1

“R

"50

106 106 103 101 101 101 101 102 103 103 103

1111 113 112 111 111 112 1111 116 116 119 120

125 12U 123 123 123 125 127 129 131 133 134

108 106 1011 102 100 100 101 102 102 103 103

106 106 1OU 102 100 100 101 102 102 103 103

11U 113 112 110 110 111 113 11U 116 116

125 12U 123 122 122 123 125 127 129 131

119 133 103 103 117 130 102 102 115 127 101 101 112 1211 100 100 110 122

108

111

125

109

1111 125

110

6560 6YOO 6200 6000 5800 5600 5UOO 5200 5000 U800 4600

108 106 103 101 101 101 101 102 103 103 103

6580

108

“1 110 108 105 103 101 100 100 101 101 102

“R 110 106 105 103 101 100 100 101 101 102

110

“2 “50 1111 125 113 123 112 122 110 121 109 121 109 121 110 122 112 1211 113 126 115 128

1111 12U

“1

"50

111 109 107 IOU 102 101 101 100 100 101

111 109 107 1011 102 101 101 100 100 101

1lU 113 112 110 109 109 109 110 111 113

12U 123 122 121 120 120 121 122 123 125

112 110 106 105 1011 103 102 101 100 100

112

11U

121

"13 112 110 108 to5 1011 103 102 101 100 100

"50

1111 113 112 110 109 109 109 109 109 111

12U 123 l?? 120 120 120 120 121 121 122

107 105 109 103 102 101 100

107 105 1OU 103 102 101 100

110 109 109 109 109 lo9 109

120 119 119 120 120 120 121

6UO0 106 106 113 121 107 107 113 12U 106 106 113 123 110’ 110 113 123 111 111 113 122 620Ci 1011 1011 112 123 105 105 112 122 106 106 112 122 107 107 112 122 109 109 112 121

uooo

5000

6000 5600 5800

102 101 101

102 111 101 110 101’112

122 122 12U

102 101 100

110 109 110

121 121 122

1011 1011 110 102 102 109 101 101 109

121 120 120

105 103 102

110 109 109

120 120 120

106 101 103

106 104 103

110 109 109

120 119 120

106 105

5200 5000 U800 US00

102 102 103 103

115 117 118 120

128 130 132 13’4

101 102 102 103

113 1111 116 116

125 127 129 131

100 101 101 102

110 112 1111 115

122 12Y 126 128

100 100 100 101

109 110 111 113

121 122 123 125

102 101 100 lob

102 101 100 100

109 109 110 111

120 121 121 123

103 103 109 120 102 102 lo9 120 101~~101~~109~121 100 100 109 121

6580 6UO0 6200 6000 5600

106 106 1OU 102

106 106 1011 102

11U 113 112 110

125 1211 123 122

110 106 106 103

110 108 106 103

1111 113 112 110

12U 123 122 121

111 109 107 105

1111 113 112 110

1211 123 122 121

112 110 106 106

1111 113 112 110

12U 123 121 120

107

110

120

5400

106 105

109 109

119 119

101 101 113 126 100 100 111 123 100 100 109 121 101 101 109 120 103 103 109 120 1011 1011 109 119

5600

100 100 110 122 101 101 109 120 103 103 109 120 1011 1OU 109 120 105 105 109 119 100 100 111 123 101 101 109 121 102 102 109 120 103 103 109 120 10’4 1011 109 119

SUOO

101

5200

101 101 1111 127 100 100 111 123 100 100 110 121 101 101 109 120 103 103 109 120 1OU 1011 109 120

5000 U600 11600

102 103 103

101 102 103 103

112 116 118 119

125 129 131 133

100 101 102 102

110 113 115 116

122 125 127 129

101 100

109 111

121 122

102 101

109 109

120 121

103 102

109 109

120 120

105 103

lo9 109

119 120

101 101 112 1211 100 100 110 122 101 101 109 121 102 102 109 120 101

101

1111 126

100

112

121

100

WEIGHTS.

[‘Cl

TO THE

100

110

122

101

109

120

"50

METRO III ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4E-18 4MC

PERFORMANCE

FAA APPROVED: MAY 22/89

TAKEOFF SPEED SCHEDULE (KIAS) -WET GOODYEAR

AEROSPACE

DUAL

ROTOR

BRAKES 1CAUTION)

. TAKEOFF IN TEMPERANRE AND ALTITUDE CONDITIONS SHOWN TO THE RIGHT OF AND ABOVE THE SOLID, STEPPED LINE IS NOT APPROVED. THE SPEEDS IN THAT AREA OF THE CHART ARE PROVIDED FOR INTERPOLATION 1 ONLY.

fizGGGE1

. REFER

OUTSIDE ‘MSS GRDSS

RLT IF11

6000

7000

WT 'KG )

-6 "1

"50

U6DO

109 107 105 102 101 100 100 101 102 102 103

11U 113 112 110 109 110 111 113 115 117 118

125 12U 122 121 121 122 123 125 127 130 132

111 109 106 1011 102 101 101 100 100 101 102

6580,110 61100 6200 _ 6000 5800 5600 r 51100 5200 5000 YSOO Y600

108 105 103 101 100 100 100 lo1 102 102

110 108 105 103 101 100 100 100 101 102 102

1lY 113 112 110 109 109 110 111 113 115 117

1211 123 122 121 120 121 122 123 125 126 130

6580 6UO0 6200 6000 5800 5600 5400 5200 5000 U800

110 109 106 1OU 102 101 100 100 100 101

111 109 106 1011 102 101 100 100 100 101

11U 113 112 110 109 109 109 110 111 113

121 123 122 121 120 120 121 122 123 126

Y6OD

102

115

128

6580 6UO0 6200 6000 5600 5600 5yOO 5200 5000 4800

FllR

TO FIGURE

TEMPEIWTURE

“50

“1

“IT

“2

111 109 106 1Oy 102 101 101 100 100 101 102

1111 113 112 110 109 109 109 110 111 113 115

12y 123 122 121 120 120 121 122 123 125 127

112 110 108 105 1OY 102 102 101 100 100 101

112 110 108 105 1011 102 102 101 100 100 101

1111 113 112 110 109 109 109 109 110 111 112

1211 123 111 111 113 122 122 109 109 112 121 ..^ .^^ 120 107 107 11~ l?u 120 105 105 109 119 106[106~109~119~ 1 I I 120 1011 1Oy 109 119 1051105110911191 I I 120 103 103 109 120 105 105 109 119 121 102 102 109 120 121 101 101 109 121 1031103~1o9~~2o~~Oy~lOU~~Og~~20~ ~~~~~~~~~~~~110~121~102t102~1091121)103110311091120~ 125j10011OD .---_ _-_ 110 122 101 101 110 121 102 102 10911201 I I 1 I

111 109 107 105 103 102 101 101 100 100 101

112 110 107 105 103 102 101 101 100 100 101

llrl 113 112 110 109 109 109 109 110 111 113

12y 123 122 121 120 120 120 121 122 123 125

113 111 108 106 1011 103 103 102 101 100 100

113 111 109 106 1OU 103 103 102 101 100 100

1111 113 112 110 109 109 109 109 109 110 111

IEY 122 121, 120 120 120 120 120 121 121 123

112 110 108 106 1011 103 102 101 100 100 100

ll? 110 108 106 1Oy 103 102 101 100 100 100

1lU 113 112 110 109 109 109 109 109 110 112

:2324

103 102 101 100

“1

“R

“1

AIv 109 109 109 109 109 109 110

“so

112 121 109 120 JO7 120 105 120 1OU 120 103 120 103 121 102 122 101 12U 100

112 109 10; 10

113 112 110 109 1011 109 103 109 103 109 102 109 101 109 100 110

122 121 1PO 119 119 120 120 120 121 122

106 105 105 1OU 103 102 101

106 105 105 1011 103 102 101

109 109 109 109 109 109 110

“2

“50

"Fl

"50

m II Tz1 0

I 1 I

0 D

lrv,119, 119 120 120 120 121 121

119 119 119 120 120 120 121

WEIGHTS.

"50

IV/ 106 :oy05

“2

TAKEOFF

106h06~109h19~ 105 105 109 1011 1011 109 103 103 109 103 103 lo9 102 102 110

119 120 120 120 121

106 105 1Oy 1OU 103

119 119 120 120 120

6 000

PERMISSIBLE

107 106 105 1011 103 102 101 100

“Fi

FOR MAXIMUM

L-C)

4E-2

106 109 105 109 1011 109 1OU 109 103 110

I I I I I I I 105 109 103

105 10~ 103

log 109 110

120 120 120

D z z

m x 00

METRO III - ICAO ANNEX 8 DISTANCE TO ACCELERATE TO V, AND STOP B.F. GOODRICH SINGLE ROTOR BRAKES ASSOCIATED

CONDITIONS:

EXAMPLE:

POWER .. . .. . . .. . . .. . .. . . . .. . . . . . . . TAKEOFF (WET) GEN LOAD . . . . . . . . . . . . . . . . . . .. . .. . . . .. . . . . . 300 AMPS AIR . . . . . . . . . . .. . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED ENG ANTI-ICE . . . . . . . OFF (SEE NOTE) RUNWAY . . . . .. . . . . . . .. . DRY, HARD SURFACE FLAPS . . . .. . .. . . . .. . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . .. . .. . . l/4 (FIGURE 4E-3) DECISION SPEED . . . . ..Vl ANTI-SKID . . . . . . . . . . . . . .._............... ON OR OFF NOSE WHEEL STEERING . ..ON OR OFF

r--y1 . MAXIMUM THE l

WEIGHT

DOWNWIND WEIGHTS

GIVEN:

OBTAIN:

TAKEOFF WEIGHT MAY NOT DETERMINED FROM FIGURE

TAKEOFFS PROHIBITED ABOVE THE TAILWIND LIMIT

-WET

AT LINE.

OAT = 10% PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) HEADWIND = 20 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) V1 SPEED = 101 KIAS ACCELERATE-STOP DISTANCE = 3,100 FEET (945 m)

EXCEED 4E-2

NOTE

INCREASE PERCENT

ACCELERATE-STOP DISTANCE WITH ENGINE ANTI-ICE ON.

MAXIMUM

OAT

1 1

GROSS l

GROSS 7

WEIGHT 6

WITH

ENGINE

ANTI-ICE

IS 5%.

(1000 kg) 5

OAT (OC)

GROSS WEIGHT

FIGURE 4E-20 4MC

(1,000

POUNDS)

WIND

(KNOTS)

RUNWAY SLOPE (PERCENT)

4E-5

PERFORMANCE

FAA APPROVED:

MAY 22189

; I-

METRO III - ICAO ANNEX 8 DISTANCE TO ACCELERATE TO V, AND STOP - WET GOODYEAR AEROSPACE DUAL ROTOR BRAKES ASSOCIATED

CONDITIONS:

EXAMPLE:

POWER .. .... .... .................... TAKEOFF WET) GEN LOAD ..... ............................ 300 AMPS BLEED AIR .............. ........ ....... ... ........ ....OFF ENG ANTI-ICE ..... ..........OFF (SEE NOTE) RUNWAY .. .. ...... ..... DRY, HARD SURFACE FLAPS ............... .. .... .... .. ............................ l/4 DECISION SPEED ......Vl (FIGURE 4E-4) NOSE WHEEL STEERING ...ON OR OFF

GIVEN:

OAT = 10°C PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) HEADWIND = 20 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) OBTAIN: ‘.‘I SPEED = 101 KIAS ACCELERATE -STOP DISTANCE = 3,200 FEET (975 m)

I MAXIMUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FIGURE 4E-2.

INCREASE ACCELERATE - STOP DISTANCE FNNOTE PERCENT WITH ENGINE ANTI-ICE ON. l

MAXIMUM

OAT WITH ENGINE ANTI-ICE

BY 1.1

ON IS 5°C.

GROSS WEIGHT (1000 kg) 5 7 6

-20

20 OAT (OC)

FAA APPROVED: MAY 22189

15 14 13 12 11 10 GROSS WEIGHT (3,000 POUNDS)

FIGURE 4E-6 PERFORMANCE

0 10 20 30 WIND (KNOTS)

0 1 2 RUNWAY SLOPE (PERCENT)

4E-21 4MC

METRO III - ICAO ANNEX 8 SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT -WET B.F. GOODRICH SINGLE ROTOR BRAKES NOTE MAXIMUM

OAT WITH ENGINE ENGINE

ANTI-ICE (METERS)

ANTI-ICE

ON IS 5Â°C.

EFFECTS

100

120

8,000 GROSS WEIGHT, POUNDS (kg) 10,000 (4540) 11,000 (4990) 12,000 (5440) 13,000 (5900) 14,000 (6350) 14,500 (6580)

6,000

100

200 (FEET)

300

400

INCREASE IN TAKEOFF DISTANCE WITH ENGINE ANTI-ICE ON

FIGURE 4E-7 4E-22 4MC

PERFORMANCE

FAA APPROVED:

MAY 22189

METRO III - ICAO ANNEX 8 SINGLE ENGINE B.F. GOODRICH ASSOCIATED

TAKEOFF DISTANCE TO 35 FOOT SINGLE ROTOR BRAKES CONDITIONS:

HEIGHT

- WET

EXAMPLE:

POWER . . . . .. . . . . . . . . . . . . . . . . . . . . . . TAKEOFF (WET) GEN LOAD . . . . ...I......................... 300 AMPS AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED ENG ANTI-ICE . . . . . . . . . . . . OFF (SEE GRAPH) RUNWAY . . . . . . . . . . . . . . . DRY, HARD SURFACE V , SPEED . . . . .. . . . . . . .. . . . . . . . . . . . . . . FIGURE 4E-3 V R SPEED . . . . .. . . .. . . .. . . . . . . . . . . . . . . FIGURE 4E-3 V 2 SPEED . . . . . . . .. . . . . . . .. . . . . . . . . . . . FIGURE 4E-3 FLAPS . . .. . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 114 ANTI-SKID . . . . . . .. . . . . . . .. . . . .. . .. . . . .. . . ON OR OFF NOSE WHEEL STEERING . ..ON OR OFF

GIVEN:

OAT = 10Â°C PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 14,000 POUNDS (6350 HEADWIND = 20 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) V1 SPEED = 105 KIAS VR SPEED = 105 KIAS V2 SPEED = 113 KIAS TAKEOFF DISTANCE = 4,430 FEET (1350

OBTAIN:

kg)

NOTE MAXIMUM TAKEOFF WEIGHT MAY NOT THE WEIGHT DETERMINED FROM FIGURE

FOR TAKEOFF FIELD LENGTH ENGINE TAKEOFF DISTANCES ENGINE TAKEOFF DISTANCES

EXCEED 4E-2.

GROSS 7

WEIGHT 6

(1000

DETERMINATION, SINGLE ARE LONGER THAN TWO FACTORED BY 1 .15.

kg) 5

-20

20 OAT (OC)

15 GROSS

FIGURE FAA APPROVED:

MAY 22189

14 13 WEIGHT

12 11 10 (1,000 POUNDS)

0 WIND

20 (KNOTS)

RUNWAY SLOPE (PERCENT)

4E-7 (continued)

PERFORMANCE

4E-23 4MC

METRO III - ICAO ANNEX 8 SINGLE ENGINE TAKEOFF GOODYEAR AEROSPACE

DISTANCE TO 35 FOOT HEIGHT - WET DUAL ROTOR BRAKES NOTE MAXIMUM OAT WITH ENGINE ANTI-ICE ON IS 5Â°C. ENGINE

ANTI-ICE (METERS)

EFFECTS

100

120

8,000

6,000

(FEET) INCREASE IN TAKEOFF DISTANCE WITH ENGINE ANTI-ICE ON

FIGURE 4E-8 4E-24 4MC

PERFORMANCE

FAA APPROVED: MAY 22/89

METRO III - ICAO ANNEX 8 SINGLE ENGINE TAKEOFF GOODYEAR AEROSPACE ASSOCIATED

DISTANCE TO 35 FOOT DUAL ROTOR BRAKES

CONDITIONS:

HEIGHT

- WET

EXAMPLE:

POWER .. ...................... .. TAKEOFF (WET) GEN LOAD ................................. 300 AMPS BLEED AIR .............. ... ... ..... ... .... .... .... ....OFF ENG ANTI-ICE .. .... ... ...OFF (SEE GRAPH) RUNWAY ............... DRY, HARD SURFACE V , SPEED . ..... ........_.............FIGURE 4E-3 V R SPEED . ..... ........ .............. FIGURE 4E-3 V 2 SPEED .. .... ... ..... .............. FIGURE 4E-3 FLAPS ............................................ ... .... .... 114 NOSE WHEEL STEERING ...ON OR OFF

GIVEN:

OAT = 10°C PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 14,000 POUNDS (6350 kg) HEADWIND = 20 KNOTS RUNWAY SLOPE = 1 PERCENT (UPHILL) OBTAIN: VI SPEED = 105 KIAS VR SPEED = 105 KIAS V2 SPEED = 113 KIAS TAKEOFF DISTANCE = 4,430 FEET (1350 m)

NOTE MAXIMUM TAKEOFF WEIGHT MAY NOT EXCEED THE WEIGHT DETERMINED FROM FIGURE 4E-2.

FOR TAKEOFF FIELD LENGTH DETERMINATION, SINGLE ENGINE TAKEOFF DISTANCES ARE LONGER THAN TWO ENGINE TAKEOFF DISTANCES FACTORED BY 1.15.

GROSS WEIGHT (1000 kg) 7 6 5 9

-20

20 OAT (“C)

15 14 13 12 11 10 GROSS WElGHT (1,000 POUNDS)

FIGURE FAA APPROVED:

MAY 22/89

0 10 20 30 WIND (KNOTS)

0 1 2 RUNWAY SLOPE (PERCENT)

4E-8 (continued)

PERFORMANCE

4E-25 4MC

METRO III ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT â&#x20AC;&#x201C; WET

TWO ENGINE TAKEOFF WITH ENGINE FAILURE RECOGNIZED AT V1 , FLAPS 1/4

AFTER TAKEOFF, GEAR IS RETRACTED

MAINTAIN V 2 CLIMB TO 400 FEET WITH 1/4 FLAPS

ACCELERATE TO V YSE , RETRACT FLAPS AT V 2 +5 KNOTS AND FEATHER INOPERATIVE PROPELLER

VYSE

400 FT (120 m)

V2 VR

SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT (FIGURE 4E-7 OR 4E-8)

REDUCE POWER TO MCP AND CONTINUE CLIMB TO 1,500 FEET END OF FLIGHT PATH

START OF TAKEOFF ROLL

An estimate of the horizontal distance required to clear an obstacle up to 1,500 feet above the runway, or the required climb gradient to clear an obstacle along the takeoff flight path, may be obtained by using Figures 4E-7 through 4E-13. The takeoff flight path is as follows:

1,500 FEET (457 m)

35 FT (10.7 m) SECOND SEGMENT CLIMB (FIGURES 4E-9 AND 4E-10)

SECOND SEGMENT ACCELERATION (FIGURE 4E-11)

THIRD SEGMENT CLIMB (FIGURES 4E-12 AND 4E-13)

The takeoff flight path consists of four phases defined as follows: 1. SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT (FIGURE 4E-7 OR 4E-8). Both engines are assumed to operate normally to speed V1 where one engine is recognized as failed and the takeoff is continued on one engine. This phase ends when the airplane reaches 35 feet above the runway surface at V2. 2. SECOND SEGMENT CLIMB (FIGURES 4E-9 and 4E-10). The second segment climb is a constant V2 climb starting at a height of 35 feet above the runway surface and ends at a height of 400 feet above the runway. The landing gear is fully retracted at the start of this phase, flaps remain at 1/4, and the propeller on the inoperative engine is windmilling in the NTS mode. Figures 4E-9 and 4E-10 present net climb gradient.

4E-26 4MC

PERFORMANCE

FAA APPROVED: MAY 22/89

METRO III ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – WET (continued) 3. SECOND SEGMENT ACCELERATION (FIGURE 4E-11). This phase is an acceleration at 400 feet height from V2 to VYSE. The flaps are retracted at V2 + 5 knots, the propeller on the inoperative engine is feathered and takeoff power is maintained until VYSE is obtained. 4. THIRD SEGMENT CLIMB (FIGURE 4E-12 and 4E-13). The third segment climb is at VYSE with maximum continuous power set. It starts at 400 feet and is completed at 1500 feet above the runway surface. Figures 4E-12 and 4E-13 present net climb gradient. The following are three examples to illustrate the use of the flight path data charts. EXAMPLE 1 Ð DETERMINATION OF TOTAL DISTANCE TO 1500 FEET Given:

OAT = 10oC Airport Pressure Altitude = 2000 feet Gross Weight = 13,000 pounds (5900 kg) Headwind = 20 knots Runway Slope = 1 percent (uphill) Engine Anti-ice off B.F. Goodrich Single Rotor Brakes

FAA APPROVED: MAY 22/89

to 35 feet to 400 feet to accelerate to VYSE to 1500 feet (4.76 nautical miles)

PERFORMANCE

4E-27 4MC

METRO III ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – WET (continued) EXAMPLE 2 Ð CLOSE IN OBSTACLE CLEARANCE Given:

OAT = 10oC Airport Pressure Altitude = 2,000 feet Gross Weight = 13,000 pounds (5900 kg) Headwind = 20 knots Runway Slope = 1 percent (uphill) Engine Anti-ice off B.F. Goodrich Single Rotor Brakes Obstacle Height = 350 feet* (107 meters) Obstacle Distance From Brake Release = 17,900 feet (5455 meters)

Obtain: 1. Single Engine Takeoff Distance to 35 Foot Height (Figure 4E-7) = 3,900 feet (1190 meters). 2. Obstacle horizontal distance from the 35 foot height point equals the total obstacle distance minus the distance to 35 feet height. 17,900 Ð 3,900 = 14,000 feet (4265 meters). 3. Second Segment Climb Gradient (Figure 4E-9) = 8.6%. 4. To obtain the required climb gradient to clear the close in obstacle, enter Figure 4E-11 at 350 feet* and at 14,000 feet distance. Obtain required climb gradient of 2.25%. 5. Since the required gradient, 2.25%, is less than the actual gradient, 8.6%, this obstacle will be cleared. *NOTE This example computes the horizontal distance to climb to the obstacle height of 350 feet. To provide additional clearance above the obstacle (e.g., 35 feet), the desired additional clearance must be added to the obstacle height before entering Figure 4E-11.

4E-28 4MC

PERFORMANCE

FAA APPROVED: APPROVED: MAY MAY 22/89 22/89 FAA REVISED: OCT 17/94

METRO III ICAO ANNEX 8 TAKEOFF FLIGHT PATH DISTANCE TO 1500 FOOT HEIGHT – WET (continued) EXAMPLE 3 Ð DISTANT OBSTACLE CLEARANCE Given:

OAT = 10oC Airport Pressure Altitude = 2000 feet Gross Weight = 13,000 pounds (5900 kg) Headwind = 20 knots Runway slope = 1 percent (uphill) Engine Anti-ice off B. F. Goodrich Single Rotor Brakes Obstacle Height = 700 feet* (213 meters) Obstacle Distance from Brake Release = 25,150 feet (7665 meters)

Obtain: 1. Single Engine Takeoff Distance to 35 Foot Height (Figure 4E-7) = 3,900 feet (1190 meters). 2. Second Segment Climb Gradient (Figure 4E-9) = 8.6%. 3. Enter Figure 4E-10 at 400 feet and proceed to 8.6%. Obtain 4,250 feet (1295 meters) to climb to 400 feet. 4. Second Segment Acceleration Distance (Figure 4E-11) = 2,000 feet (610 meters) to accelerate from V2 to VYSE. 5. The horizontal distance from the end of the second segment acceleration to the obstacle equals 25,150 Ð 3,900 Ð 4,250 Ð 2,000 = 15,000 feet (4570 meters). 6. Enter Figure 4E-13 at 700 feet* height and 15,000 feet distance. Obtain required gradient of 2.0%. 7. The Third Segment Climb Gradient (Figure 4E-12) = 5.9%. 8. Since the required gradient, 2.0%, is less than the actual gradient of 5.9%, the obstacle will be cleared. *NOTE This example computes the horizontal distance to climb to the obstacle height of 700 feet. To provide additional clearance above the obstacle (e.g., 35 feet), the desired additional clearance must be added to the obstacle height before entering Figure 4E-13.

FAA APPROVED: MAY 22/89 REVISED: OCT 17/94

PERFORMANCE

4E-29 4MC

METRO Ill - ICAO ANNEX 8 TAKEOFF SECOND

FLIGHT PATH DISTANCE TO 1500 FOOT SEGMENT CLIMB GRADIENT-WET

HEIGHT

(continued) ASSOCIATED

CONDITIONS:

POWER .................... TAKEOFF (WET) GEN LOAD ......................... 300 AMPS BLEED AIR .................................... OFF ...... OFF (SEE NOTE) ENG ANTI-ICE CLIMB SPEED ...... V2 (FIGURE 4E-3 OR 4E-4 UP GEAR ................................................ FLAPS .............................................. 114 EXAMPLE: GIVEN:

AIRPORT OAT = 10Â°C AIRPORT PRESSURE ALTITUDE = 2,M)O FEET GROSS WEIGHT = 13,ooO POUNDS (5900 kg) HEADWIND = 20 KNOTS OBTAIN: V2 CLIMB SPEED = 110 KIAS SECOND SEGMENT CLIMB GRADIENT = 8.6 PERCENT NOTE I I l REDUCE CLIMB GRADIENT BY 1.5 PERCENT GRADIENT WITH ENGINE ANTI-ICE ON. l

-2

6 NET CLIMB

0 GRADIENT

FIGURE 4E-30 4MC

10 (PERCENT)

MAXIMUM

OAT WITH

ENGINE

ANTI-ICE

ON IS 5%.

4E-9

PERFORMANCE

FAA APPROVED:

MAY 22/89

TO 1500 FOOT -WET

TAKEOFF FLIGHT PATH DISTANCE CLOSE IN OBSTACLE CLEARANCE ASSOCIATED

CONDITIONS:

GIVEN:

1000

OBSTACLE OBSTACLE 35 FOOT REQUIRED

OBTAIN:

HORIZONTAL 500

(continued)

EXAMPLE:

POWER .__.____...__..,.._,.,,.......... TAKEOFF (WET) GEN LOAD .. . . .. .. .. . .. . .. . . . . . . . . . . . . . . .. . .. . . 300 AMPS BLEED AIR .,.......,..,..,,............................... OFF ENG ANTI-ICE . . . . . . . . . . . . . . ON OR OFF CLIMB SPEED .. ..V2 (FIGURE 4E-3 OR 4E-4) GEAR . . . . . . . . . . . .. . .. . . .. . .. . . . . . . . . . . . . . . .. . . .. . . . . . .. . . . . . . . . . . UP FLAPS . . . . .. . . . . .. . . . . . .. . . . . . . . . . . . . . . . . . . . . . .. . . .. . . . . . . . . . . . . . 114

HEIGHT

1500

DISTANCE 2000

HEIGHT ABOVE THE RUNWAY HORIZONTAL DISTANCE FROM POINT = 14,000 FEET (4265 m) GRADIENT = 2.25 PERCENT

FROM 35 FOOT HEIGHT 2500

POINT (METERS) 3000

SURFACE

3500

350

FEET

(107

4000

400

350

m x

100

HORIZONTAL I 0

I 0.2

I 0.4

I 0.6

DISTANCE

1.0 HORIZONTAL

FROM 35 FOOT HEIGHT

1.2 DISTANCE

I 1.4 (NAUTICAL

POINT (FEET)

I 1.6 MILES)

I 1.6

I 2.0

I 2.2

I 2.4

I 2.6

METRO III - ICAO ANNEX 8 TAKEOFF SECOND

FLIGHT SEGMENT

PATH DISTANCE ACCELERATION MAXIMUM

TO 1500 FOOT DISTANCE-WET NOTE OAT WITH ENGINE ENGINE

: E

600

ANTI-ICE

HEIGHT

(continued)

ANTI-ICE

ON IS 5Â°C.

EFFECTS

(METERS) 1200

1800

2400

10,000

3000

8,000

2400

6,000

1800

i5c

600

0 0

2,000 ACCELERATION

4,000 (FEET) DISTANCE.

FIGURE 4E-32 4MC

6,000 ENGINE

ANTI-ICE

8,000 OFF

4E-11

PERFORMANCE

FAA APPROVED:

MAY 22/89

METRO III - ICAO ANNEX 8 TAKEOFF SECOND

FLIGHT SEGMENT

ASSOCIATED

PATH DISTANCE ACCELERATION

TO 1500 FOOT DISTANCE-WET

CONDITIONS:

HEIGHT

(continued)

EXAMPLE:

POWER . . . . .. . . . . . . . . . . . . . . . . . . . . . . TAKEOFF (WET) GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 300 AMPS BLEED AIR . . . . . . . . . . . . . . . . . .. . . . . . . .. . . . .. . .. . . . .. . .. . OFF ENG ANTI-ICE . . . . . . .. . . . . OFF (SEE GRAPH) ACCELERATE TO VYSE . . . ..FlGURE 4F-2 GEAR . . . .. . . . .. . .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . .. . . . . l/4 (SEE NOTE)

GIVEN:

OBTAIN:

AIRPORT OAT = 10Â°C AIRPORT PRESSURE ALTITUDE = 2,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) HEADWIND = 20 KNOTS VYSE CLIMB SPEED = 126 KIAS SECOND SEGMENT ACCELERATION DISTANCE = 2,000 FEET (610 m)

NOTE ACCELERATE V YSE PRIOR GROSS 7

WEIGHT 6

TO TO

(1000

THE LESSER OF RAISING FLAPS.

KIAS

kg) 5 10

0 -20

0 AIRPORT

40 OAT

(OC)

14 GROSS

13 WEIGHT

12 (1,000

11 POUNDS)

10 WIND

(KNOTS)

FIGURE 4E-11 (continued) FAA APPROVED:

MAY 22189

PERFORMANCE

4E-33 4MC

METRO III - ICAO ANNEX 8 TAKEOFF FLIGHT THIRD SEGMENT

PATH CLIMB

DISTANCE GRADIENT

TO 1500 FOOT HEIGHT (continued) - DRY, BLEED AIR OFF

60 ASSOC!ATED

CONDITIONS:

POWER . . . . . . . . . . . . . . . . . . MAX CONTINUOUS GEN LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3M) AMPS BLEED AIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ENG ANTI-ICE . . . . . . . . . . OFF (SEE NOTE) CLIMB SPEED VySE (FIGURE 4F-2) GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP

EXAMPLE:

GIVEN:

AIRPORT OAT = 10°C AIRPORT PRESSURE ALTITUDE = Z.CGO FEET GROSS WEIGHT - 13,ooO POUNDS (59OOk@ HEADWIND = 20 KNOTS VySE CLIMB SPEED - 126 KIAS THIRD SEGMENT CLIMB GRADIENT - 5.9 PERCENT

OBTAIN:

-20

MAXIMUM

OAT

WITH

ENGINE

ANTI-ICE

IS 5°C.

-2

4 NET CLIMB

6 GRADIENT

FIGURE 4E-34 4MC

6 (PERCENT)

4E-12

PERFORMANCE

FAA APPROVED:

MAY 22/89

TAKEOFF DISTANT

FLIGHT PATH DISTANCE OBSTACLE CLEARANCE

ASSOCIATED

CONDITIONS:

TO 1500 FOOT HEIGHT - DRY, BLEED AIR OFF

(continued)

EXAMPLE:

POWER . . .. . . MAX CONTINUOUS GEN LOAD .. . .. . .. ... . .. .._............ 300 AMPS BLEED AIR .,,,.......................,....,....... OFF ENG ANTI-ICE . .. .. .. .. . .. .. . .. .. . ON OR OFF CLIMB SPEED . ...V YSE (FIGURE 4F-2) GEAR .. .. . . .. .. .. . .. .. . ... . .. . .. .. .. .. . .. . ... . .. . .. .. .. . . UP FLAPS . .. . .. . ... . .. . .. .. .. .. . .. . .. .. .. . .. .. . ... . .. . .. .. . UP

GIVEN:

OBSTACLE OBSTACLE SECOND REQUIRED

OBTAIN:

HORlZONTAL

DISTANCE

FROM

END

OF SECOND

HEIGHT ABOVE THE RUNWAY SURFACE HORIZONTAL DISTANCE FROM END OF SEGMENT ACCELERATION = 15,000 FEET GRADIENT = 2.0 PERCENT

SEGMENT

ACCELERATION

POINT

= 700

FEET

(4570

(213

(METERS)

m x 00

I 0

I 1

I 2

I 3

I 4

I 5

I 6 HORlZONTAL

I 7 DISTANCE

(NAUTICAL

I 8 MILES)

I 9

I 10

I 11

I 12

A 13

METRO III - ICAO ANNEX 8 TWO ENGINE RATE OF CLIMB AT V,, -WET ASSOCIATED

CONDITIONS:

EXAMPLE:

POWER ................... TAKEOFF (WET) GEN LOAD .. ...................... 300 AMPS BLEED AIR ................. .... ........ ......OFF ENG ANTI-ICE ... ...OFF (SEE NOTE) CLIMB SPEED .....V50 (FIGURE 4E-3 OR 4E-4) GEAR .................. ... .. .. ...................... UP FLAPS ...... ..... ... ... ............................. 114

GIVEN:

OAT = 10°C PRESSURE ALTITUDE = 4,000 FEET GROSS WEIGHT = 13,000 POUNDS (5900 kg) OBTAIN: V50 CLIMB SPEED = 121 KIAS RATE OF CLIMB = 3,100 FEET PER MINUTE

REDUCE RATE OF CLIMB BY 425 FEET PER MINUTE

MAXIMUM

OAT WITH ENGINE ANTI-ICE

ON IS 5°C.

30 P-. 2 0

-10 7

15 3 0

5 B Q

=. !i $j 3

10 1.800

2.000

2.200

2,400

2,600

2,800

3,000

3,200

3,400

3,600

RATE OF CLIMB (FEET PER MINUTE)

FIGURE 4E-14 4E-36 4MC

PERFORMANCE

FAA APPROVED: MAY 22189