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Effective Pages 1 * Dec 05/20142 * Dec 05/2014

Contents 1 * Dec 05/20142 * Dec 05/20143 * Dec 05/20144 * Dec 05/20145 * Dec 05/20146 * Dec 05/2014

Chapter 1 1 * Dec 05/20142 May 28/2001

Chapter 2 1 * Dec 05/20142 * Dec 05/20143 * Dec 05/20144 * Dec 05/20145 * Dec 05/20146 * Dec 05/20147 * Dec 05/20148 * Dec 05/20149 * Dec 05/2014

10 * Dec 05/201411 * Dec 05/201412 * Dec 05/201413 * Dec 05/201414 * Dec 05/201415 * Dec 05/201416 * Dec 05/201417 * Dec 05/201418 * Dec 05/201419 * Dec 05/201420 * Dec 05/201421 * Dec 05/201422 * Dec 05/201423 * Dec 05/201424 * Dec 05/201425 * Dec 05/201426 * Dec 05/201427 * Dec 05/201428 * Dec 05/201429 * Dec 05/201430 * Dec 05/201431 * Dec 05/2014

32 * Dec 05/201433 * Dec 05/201434 * Dec 05/201435 * Dec 05/201436 * Dec 05/201437 * Dec 05/201438 * Dec 05/201439 * Dec 05/201440 * Dec 05/201441 * Dec 05/201442 * Dec 05/201443 * Dec 05/201444 * Dec 05/2014

Chapter 3 1 May 28/20012 May 28/20013 May 28/20014 May 28/20015 May 28/20016 May 28/20017 May 28/20018 May 28/20019 May 28/2001

10 May 28/200111 May 28/200112 May 28/200113 May 28/200114 May 28/200115 May 28/200116 May 28/2001

Chapter 4 1 May 28/20012 May 28/20013 May 28/20014 May 28/20015 May 28/20016 May 28/20017 May 28/20018 May 28/20019 * Dec 05/2014

10 May 28/2001

Chapter 5 1 * Dec 05/20142 * Dec 05/20143 * Dec 05/2014


LIST OF EFFECTIVE PAGES

Chapter Page Date Chapter Page Date

Series: 400

Page 1

Dec 05/2014

The asterisk (*) indicates pages revised, added or deleted by current revision.

EFFECTIVEPAGES

4 * Dec 05/20145 * Dec 05/20146 * Dec 05/20147 * Dec 05/20148 * Dec 05/20149 * Dec 05/2014

10 * Dec 05/201411 * Dec 05/201412 * Dec 05/201413 * Dec 05/201414 * Dec 05/201415 * Dec 05/201416 * Dec 05/2014

Chapter 6 1 * Dec 05/20142 * Dec 05/20143 * Dec 05/20144 * Dec 05/20145 * Dec 05/20146 May 28/20017 * Dec 05/20148 May 28/20019 May 28/2001

10 * Dec 05/201411 * Dec 05/201412 * Dec 05/2014

Chapter 7 1 May 28/20012 May 28/20013 May 28/20014 May 28/20015 May 28/20016 May 28/20017 May 28/20018 May 28/20019 May 28/2001

10 May 28/200111 May 28/200112 May 28/200113 May 28/200114 May 28/2001

Chapter 8 1 May 28/2001

Chapter 9 1 May 28/20012 * Dec 05/20143 * Dec 05/2014

4 * Dec 05/2014


Chapter Page Date Chapter Page Date

Series: 400

Page 2

Dec 05/2014

The asterisk (*) indicates pages revised, added or deleted by current revision.

EFFECTIVEPAGES

CHAPTER 1 PREFACE

Scope 1


TABLE OF CONTENTS

Title Page

Series: 400

Page 1

Dec 05/2014CONTENTS

CHAPTER 2 AIRCRAFT DESCRIPTION

General Information 1General Airplane Characteristics 3Aircraft Dimensions 5Ground Clearances − General Arrangement 6Maximum Ground Clearances−Standard MLG Tires 7Minimum Ground Clearances−Standard MLG Tires 8Maximum Ground Clearances−Optional MLG Tires 9Minimum Ground Clearances−Optional MLG Tires 10Series 400 (Model 402) Standard Interior Configuration 11Series 400 (Model 402) Optional Interior Configuration 14Passenger − Compartment Cross Section 19Floor loading diagram 21FWD Baggage − Compartment Dimensions (StandardInterior Configuration)

23

AFT Baggage Compartment Dimensions (StandardInterior Configuration)

24

AFT Baggage Compartment Dimensions (Optional InteriorConfiguration)

25

Nets and Tiedowns (Standard Interior Configuration) 26Nets and Tiedowns (Optional Interior Configuration) 27Door Clearances 28Forward Passenger − Door Clearances 29Aft Passenger − Door Clearances 30Aft Service − Door Clearances 32Forward Baggage Compartment / Forward Type IEmergency Exit − Door Clearances

34

Aft Baggage−Compartment − Door Clearances 36Exterior Handles 38Minimum Clearance Between Nacelles and Fuselage 40Aft Baggage Compartment Vertical Dimensions (TypicalConfiguration)

41

Ground Clearances − Empennage and Sill of Aft BaggageDoor

42


Title Page

Series: 400

Page 2

Dec 05/2014CONTENTS

CHAPTER 3 AIRCRAFT PERFORMANCE

General Information 1Payload/Range at Maximum Cruise Rating and LongRange Cruise

3

Maximum Permissible Take−Off Weight (Wat Limit) −Flaps 5 Degrees

4


5


6

Take−Off Runway Length Requirements − Flaps 5Degrees

7


8


9

Max. Landing Weight − Landing Flaps 10 and ApproachFlaps 5 Degrees

10


11


12

Unfactored Landing Distance − Flaps 10 Degrees 13Unfactored Landing Distance − Flaps 15 Degrees 14Unfactored Landing Distance − Flaps 35 Degrees 15Landing − Runway Length Required 16


Title Page

Series: 400

Page 3

Dec 05/2014CONTENTS

CHAPTER 4 GROUND MANEUVERING

General Information 1Turning Radii (No Slip Angle) 2Turning Radii Data (No Slip Angle) 3Turning Radius at Minimum Power 4Greater Than 90 Degree Turn − Runway to Taxiway withTracks

5

90 Degree Turn − Runway to Taxiway with Nose Gearand Cockpit Tracks

6

90 Degree Turn − Taxiway to Taxiway with Nose Gearand Cockpit Tracks

7

Runway Holding Bay (Apron) 8Aircraft Tie Down Provisions 9

CHAPTER 5 TERMINAL SERVICING

General Information 1Aircraft Servicing Arrangement (Typical − No APU) 2Rapid Turnaround Using FWD and AFT Doors 5Rapid Turnaround Using FWD Door Only 6Ground Servicing Point Locations 7Ground Service Connections Data 11Electrical Requirements For Engine Starting 14Ground Towing Requirements 15Ground Air Conditioning Requirements − Pre−ConditionedAirplane

16


Title Page

Series: 400

Page 4

Dec 05/2014CONTENTS

CHAPTER 6 OPERATING CONDITIONS AND NOISEDATA

General Information 1Engine Exhaust Temp. Contours at Ground Idle − TopView

2

Engine Exhaust Temp. Contours at Ground Idle − SideView

3

Engine Exhaust Temp. Contours at Flight Idle − Top View 4Engine Exhaust Temp. Contours at Flight Idle − Side View 5Engine Exhaust Temp. Contours at Max. T.O. Power −Top View

6

Engine Exhaust Temp. Contours at Max. T.O. Power −Side View

7

Takeoff and Landing Noise Footprint − 3 DegreeApproach

8

Takeoff and Landing Noise Footprint − 4 DegreesApproach

9

Ramp Noise Test Results for Optional APU 10Propeller Slipstream Velocity Contours at Max TakeoffPower

11

Propeller Slipstream Velocity Contours on Ground 12


Title Page

Series: 400

Page 5

Dec 05/2014CONTENTS

CHAPTER 7 PAVEMENT DATA

General Information 1Landing Gear Footprint 2Maximum Pavement Loads 3Landing Gear Loading on Pavement 4Flexible Pavement Requirements − CBR (32x8.8−16Tires)

5

Flexible Pavement Requirements − CBR (34x10.75−16Tires)

6

Flexible Pavement Requirements − LCN Conversion(32x8.8−16 Tires)

7

Flexible Pavement Requirements − LCN Conversion(34x10.75−16 Tires)

8

Rigid Pavement Requirements − LCN Conversion(32x8.8−16 Tires)

9

Rigid Pavement Requirements − LCN Conversion(34x10.75−16 Tires)

10

Aircraft Classification Number − Flexible Pavement(32x8.8−16 Tires)

11

Aircraft Classification Number − Flexible Pavement(34x10.75−16 Tires)

12

Aircraft Classification Number − Rigid Pavement (32x8.8−16 Tires)

13

Aircraft Classification Number − Rigid pavement(34x10.75−16 Tires)

14

CHAPTER 8 DERIVATIVE AIRCRAFT

General Information 1

CHAPTER 9 SCALED DRAWINGS OF DASH−8 SERIES400

General Information 1Scaled Dash 8, Series 400 (Model 402) Drawing − 1 in. =32 ft (1:384)

2

Scaled (Model 402) Drawing − 1in. = 50 ft (1:600), 1in. =100 ft (1:1200)

3

Scaled Dash 8, Series 400 (Model 402) Drawing − 1:500and 1:1000 (Metric)

4


Title Page

Series: 400

Page 6

Dec 05/2014CONTENTS

CHAPTER 1

PREFACE


THIS PAGE INTENTIONALLY LEFT BLANK

Scope

1. Purpose

A. This manual provides, in a standardized format, airport planning data for the Dash−8,Series 400 (Model 402). Because operational procedures are different for each airlineand operator, the airport planner must coordinate specific data with the user airlinebefore the design of facilities.

B. The data contained in Chapter 3 (Aircraft Performance) is for reference only. Refer tothe applicable Aircraft Flight Manual (AFM) for Model 402 operating−data.

2. Introduction

A. The content of this document conforms to NAS 3601, Revision 6 (15 Jul/94). NAS 3601is the result of agreements between representatives of the organizations that follow:

– Aerospace industries– Airport operators– Air Transport Association of America– International Air Transport Association.

B. This manual provides Model 402 data for airport planners and operators, airlines,architectural and engineering consultant organizations (as well as other interestedindustry agencies). The content of this manual will change as options and aircraftchanges occur. The data contained in this manual represents the typical Dash−8 Series400 (Model 402) aircraft.

C. For more information, contact:

Director, Technical Publications

Regional Aircraft Division

Bombardier Aerospace

Mail Stop N42−25

123 Garratt Blvd., Downsview

Ontario, Canada

M3K 1Y5.

3. A Brief Description of the Dash−8 Series 400 (Model 402) Aircraft

A. The Dash−8 Series 400 (Model 402) is a pressurized, commercial transport airplanethat is designed to accommodate 70 to 86 passengers. This airplane establishes newstandards in speed, comfort and efficiency. A new feature of the Dash−8 series is theNoise and Vibration Suppression (NVS) system, which dramatically reduces cabin noisein flight.


Series: 400

CHAPTER 1Page 1

Dec 05/2014

B. The aircraft is powered by two Pratt and Whitney PW150A turboprop engines. Largediameter, slow−turning, six−bladed Dowty R408 propellers provide high thrust efficiencyand low noise levels.

C. The Dash−8 Series 400 is capable of economic operations over a broad range ofapplications. These are:

– Scheduled airline operations– Resource and regional development work– Corporate and military transport roles.

D. The aircraft is capable of operation in ambient temperatures of between −65 °F (−54°C) and 122 °F and (50 °C), unless otherwise specified. Transfer from one climate toanother can be done without penalties or extensive modifications or adjustment.

E. Significant features of interest to the airport planner include the items that follow:

– The engines are located high and on the wing– The horizontal stabilizer is located on top of the fin– The aircraft has a self−contained airstair entry−door at the forward end of the cabin– Connections for single−point and overwing gravity refueling are provided– All servicing can be accomplished with standard ground equipment– High exhaust outlets produce modest pressure and temperature profiles.


Series: 400

CHAPTER 1Page 2

May 28/2001

CHAPTER 2

AIRCRAFT DESCRIPTION



General Information

1. General

The Model 402 has a maximum take−off weight of up to 64,500 lb (29,257 kg). Othermaximum weight parameters such as taxi weight (also known as ramp weight), landing weightand zero fuel weight are set accordingly.

2. Contents of Chapter

This chapter contains the items that follow:

A. General airplane characteristics and dimensions are shown in Figure 2−1 and Figure2−2.

B. Ground clearances are shown in Figure 2−3, Figure 2−4, Figure 2−5, Figure 2−6 andFigure 2−7.

C. Interior configurations are shown in Figure 2−8, Figure 2−9, Figure 2−10.

D. A cross−section of the passenger compartment is shown in Figure 2−11.

E. A floor loading diagram is shown in Figure 2−12.

F. Dimensions of the forward and aft baggage compartments are shown in Figure 2−13,Figure 2−14, and Figure 2−15.

G. Nets and tiedowns of the aft baggage compartment are shown in Figure 2−16 andFigure 2−17.

H. Clearances for the passenger, the service, the baggage and the forward type Iemergency exit doors are shown in Figure 2−18, Figure 2−19, Figure 2−20, Figure2−21, and Figure 2−22.

I. External handles of the various doors are shown in Figure 2−23.

J. Horizontal clearances between the fuselage and nacelles are shown in Figure 2−24.

K. Vertical dimensions of a typical aft baggage compartment is shown in Figure 2−25.

L. Ground clearances of empennage and sill of aft baggage door is shown in Figure 2−26.

3. Definitions

The definitions that follow are used throughout this manual (refer to Figure 2−1):

A. Maximum Design Taxi Weight (MTW)

This is the maximum weight at which an aircraft can move safely on the ground. Itincludes the fuel for those displacements and the takeoff run.

B. Maximum Design Landing Weight (MLW)

This is the maximum approved weight at which an aircraft can land.


Series: 400

CHAPTER 2Page 1

Dec 05/2014

C. Maximum Design Take−off Weight (MTOW)

This is the maximum approved weight at which an aircraft can start a take−off run.

D. Operational Weight Empty (OWE)

This is the weight of structure, power plant, furnishings, systems, unusable fuel andother items of equipment that are a necessary part of an aircraft configuration. TheOWE also includes certain standard items, personnel, equipment and supplies requiredfor full operations, but does not include usable fuel or payload.

E. Maximum Design Zero Fuel Weight (MZFW)

This is the maximum weight of an aircraft before the usable fuel is loaded on the aircraft.

F. Maximum Payload

This is the weight you get when you subtract the OWE from the MZFW.

G. Maximum Seating Capacity

This is the maximum number of passengers specifically certified or anticipated forcertification.

H. Maximum Cargo Volume

This is the maximum space available for cargo.

I. Usable Fuel

This is the fuel available for the aircraft engines.


Series: 400

CHAPTER 2Page 2

Dec 05/2014

DESCRIPTIONINTERMEDIATE HIGH GROSS

WEIGHT

TANK CAPACITY − USABLE FUEL

MAXIMUM DESIGN TAXI WEIGHT

MAXIMUM DESIGN LANDING WEIGHT

MAXIMUM DESIGN TAKE−OFF WEIGHT

MAXIMUM DESIGN ZERO FUEL WEIGHT

STANDARD TANKS

LEFT

RIGHT

TOTAL

US GALS LBS LITRES KG

862

862

1724

5862

5862

11724

3263

3263

6526

2659

2659

5318

WEIGHT61,900 lb

(28,077 kg)64,130 lb

(29,089 kg)64,700 lb

(29,347 kg)61,700 lb

(27,987 kg)63,930 lb

(28,998 kg)64,500 lb

(29,257 kg)60,500 lb

(27,442 kg)61,750 lb

(28,009 kg)61,750 lb

(28,009 kg)55,500 lb

(25,174 kg)57,000 lb

(25,855 kg)57,000 lb

(25,855 kg)

GROSS

POWERPLANT

DESCRIPTION WEIGHT (PER SIDE)

EXHAUST ONLY (JET PIPE)

1925 lb(873.1 kg)169.5 lb(76.9 kg)555.4 lb

(251.9 kg)

br83

8a01

.dg,

sw

/cm

, jun

19/2

013

APU

APU WET

STARTER/GENERATOR

BASIC GROSSWEIGHT

ENGINE (PWC 150 A, DRESSED,INCLUDING EXHAUST NOZZLE)

PROPELLERS (DOWTY R408, SIX−BLADE,INCLUDES BETA TUBE UNIT AND SPINNER)

139.0 lb(63.0 kg)40.4 lb

(18.3 kg)

DESCRIPTION WEIGHT (PER SIDE)

BASED ON : 6.8 lb /U.S. GALLON (0.775 kg/l)

NOTE


GENERAL AIRPLANE CHARACTERISTICS (Sheet 1 of 2)

Figure 2 − 1Series: 400

CHAPTER 2Page 3

Dec 05/2014

br83

8a02

.dg,

kh,

aug

05/2

013

POWER PLANT WEIGHT BREAKDOWN DETAILS

1. Power plant shipping crate dimensions are 46 in. W x 108 in. L x 54 in.( + 7 in. Pallet=61 in.) H.

2. Assembly wheel weighs 248.48 lb per side (124.24 lb each).

NOTES

DRESSED POWERPLANT

ENGINE (DRY, WITH DRAIN SYSTEM INSTALLED)

FUEL ITEMS

ENGINE HYDRAULIC DRIVE PUMP

P2.7 HBOV DUCT

P2.2 HBOV DUCT

INTAKE ADAPTER AND V−BAND CLAMP

PCU

BRUSH BLOCK BRACKET

AUX PUMP UNIT

2.1

47.0

39.3

12.0

76.6

3.7

2.1

1.7

11.0

8.1

16.9

8.9

6.2

ENGINE MOUNTS SYSTEM

AC GENERATOR

OVERSPEED GOVERNOR

1573.0

DC STARTER GENERATOR

EXHAUST NOZZLE ASSEMBLY

DESCRIPTION WEIGHT PER SIDE (lb)

WEIGHT: 1808.6 lb

3. Brake carbon weighs 138.4 lb per side (69.2 lb each set).


GENERAL AIRPLANE CHARACTERISTICS (Sheet 2 of 2)


CHAPTER 2Page 4

Dec 05/2014

93ft 3in.(28.42m)

43.31in.(1.10m)

28ft 10in.(8.80m)

13ft 6in.(4.11m)

107ft 9in.(32.83m)

101ft 10in.(31.04m)

GROUNDREFERENCE LINE

12ft 4in.(3.76m)

NOTE36ft 10in.(11.22m)

8ft 2in.(2.48m)

30ft 5in.(9.27m)

DIHEDRAL 2.5o

br24

5a01

.dg,

gv,

05/

04/0

1

Refer to Ground Clearance Illustrations.

36.00 in.(91.44 cm)

45ft 9in.(13.99m)


AIRCRAFT DIMENSIONS


CHAPTER 2Page 5

Dec 05/2014

brc7

6a01

.dg,

gg/

gv, 0

5/04

/01

K

J

L

M

N

AB

CE P F QR GHD


GROUND CLEARANCES − GENERAL ARRANGEMENT


CHAPTER 2Page 6

Dec 05/2014

cg35

31a0

1.dg

, cs,

aug

06/2

014

MAXIMUM GROUND CLEARANCE

ITEM HEIGHT FEET METERS

WEIGHT :C.G. :WT ON NLG :

35,387 lb (16,085 kg)STA. X 387.1603743 lb (1701 kg)

ABCDE

F

G

HJKL

MN

P

QR

TOP OF FUSELAGEFLIGHT DECKCABIN FLOORSILL OF AIRSTAIR DOORFUSELAGE GROUND CLEARANCE

SILL OF TYPE II/III EXIT

SILL OF AFT BAGGAGE DOORNACELLE LOWER SURFACEVERTICAL STABILIZERHORIZONTAL STABILIZERWING TIPPROP GROUND CLEARANCEPROP HEIGHT CLEARANCE

SILL OF SERVICE DOOR/TYPE I EXITSILL OF AFT PAX DOOR TYPE I EXIT

11.295.364.454.392.86

4.59

5.167.10

27.2325.9513.113.65

17.14

4.51

5.325.20

3.441.631.361.340.87

1.40

1.572.168.307.914.001.115.22

1.37

1.621.58




35,387 lb (16,085 kg)STA. X 410.9802190 lb (995 kg)

ABCDE

F

G

HJKL

MN

P

QR





11.475.584.644.553.05

4.73

5.017.14

26.9225.6713.113.71

17.19

4.67

5.205.08

3.491.701.411.390.93

1.44

1.532.188.217.833.991.135.24

1.42

1.581.55

NOTES

1. Nose Wheel Tires 22 x 6.5 − 10, inflated to 89 psi (614 kPa) loaded.2. Main Wheel Tires are 32 x 8.8 −16, inflated to 227 psi (1565 kPa) loaded.3. Tire pressures shown are for calculation purposes only. Refer to AMM Ch. 12 for service pressures.

Type II/III emergency exit door is de−activated for the extra capacity configuration.

SILL OF FWD BAGGAGE DOOR/

FORWARD RH TYPE I EXIT DOOR


FORWARD RH TYPE I EXIT DOOR 5

5

Forward type I emergency exit door is installed only on aircraft with extra capacity configuration.5


MAXIMUM GROUND CLEARANCES−STANDARD MLG TIRES


CHAPTER 2Page 7

Dec 05/2014

cg35

32a0

1.dg

, cs,

aug

06/2

014

MINIMUM GROUND CLEARANCE



64,700 lb (29,347 kg)STA. X 398.2806100 lb (2772 kg)

ABCDE

F

G

HJKL

MN

P

QR





10.944.974.074.022.48

4.24

4.956.79

27.0925.7912.823.34

16.82

4.14

5.094.97

3.331.521.241.220.76

1.29

1.512.078.267.863.911.025.13

1.26

1.551.52




64,700 lb (29,347 kg)STA. X 410.9803920 lb (1782 kg)

ABCDE

F

G

HJKL

MN

P

QR





11.185.274.334.252.75

4.43

4.756.86

26.6924.9412.863.42

16.91

4.37

4.944.82

3.411.611.321.290.84

1.35

1.452.098.147.603.921.045.15

1.33

1.511.47

NOTES








5

5


MINIMUM GROUND CLEARANCES−STANDARD MLG TIRES


CHAPTER 2Page 8

Dec 05/2014

cg35

33a0

1.dg

, cs,

aug

06/2

014




35,387 lb (16,085 kg)STA. X 387.1603743 lb (1701 kg)

ABCDE

F

G

HJKL

MN

P

QR





11.315.364.474.412.87

4.63

5.357.18

27.4926.1913.223.74

17.22

4.53

5.495.37

3.451.631.361.340.87

1.41

1.632.198.387.984.031.145.25

1.38

1.671.64




35,387 lb (16,085 kg)STA. X 410.9602190 lb (995 kg)

ABCDE

F

G

HJKL

MN

P

QR





11.495.584.654.583.07

4.77

5.207.23

27.1825.9213.223.79

17.28

4.70

5.375.25

3.501.701.421.390.94

1.45

1.582.208.287.904.031.155.27

1.43

1.641.60

NOTES








5

5


MAXIMUM GROUND CLEARANCES−OPTIONAL MLG TIRES


CHAPTER 2Page 9

Dec 05/2014

cg35

34a0

1.dg

, cs,

aug

06/2

014




64,700 lb (29,347 kg)STA. X 398.2806100 lb (2772 kg)

ABCDE

F

G

HJKL

MN

P

QR





10.934.974.084.042.49

4.27

5.106.86

27.3125.9912.923.41

16.89

4.16

5.235.11

3.331.521.241.230.76

1.30

1.552.098.337.923.941.045.15

1.27

1.591.56




64,700 lb (29,347 kg)STA. X 410.9803920 lb (1782 kg)

ABCDE

F

G

HJKL

MN

P

QR





11.205.274.344.272.85

4.46

4.916.97

26.9025.6412.923.49

16.97

4.39

5.084.96

3.411.611.321.300.87

1.36

1.502.138.207.823.941.065.17

1.34

1.551.51

NOTES








5

5


MINIMUM GROUND CLEARANCES−OPTIONAL MLG TIRES


CHAPTER 2Page 10

Dec 05/2014

PA

SS

EN

GE

R C

AB

IN L

EN

GT

H61

ft 8

in.

(18.

80 m

)

11.0

0 ft.

(3.3

5 m

)

30.0

0 in

. W x

65.

00 in

. H(7

6.20

cm

x 1

.65

m)

24.0

0 in

. W x

65.

00 in

. H(6

0.96

cm

x 1

.65

m)

24.0

0 in

. W x

54.

00 in

. H(6

0.96

cm

x 1

.37

m)

AIR

ST

AIR

/TY

PE

I E

XIT

PA

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OO

R/T

YP

E I

EX

IT

SE

RV

ICE

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OR

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I E

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13

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6

25

br19

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.dg,

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00 (

TY

PE

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AT

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MO

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(78

.74

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ndar

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nfig

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show

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yout

may

var

y w

ith o

ptio

nal

conf

igur

atio

ns.

NO

TE

1. F

orw

ard

bagg

age

com

part

men

t91

.00

ft (

2.58

m )

.2.

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r ba

ggag

e co

mpa

rtm

ent

411.

00 ft

(1

1.64

m )

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ator

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drob

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ht a

ttend

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6. G

alle

y.

LE

GE

ND

33

33

20.2

0 in

. W x

56.

00 in

. H(5

1.31

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x 1

.42

m)

BA

GG

AG

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R24

.00

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x 5

4.00

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(60.

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PE

II/II

I EX

IT

5 ft

9 in

.(1

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m)

BA

GG

AG

E D

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R51

.00

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x59

.00

in. H

(1.3

0 m

x 1

.50

m)


SERIES 400 STANDARD INTERIOR CONFIGURATIONS (Sheet 1 of 2)


CHAPTER 2Page 11

Dec 05/2014

PA

SS

EN

GE

R C

AB

IN L

EN

GT

H61

ft 8

in.

(18.

80 m

)

1

45

6

25

br19

5a02

.dg,

gg/

gw, a

ug5/

2008

SE

RIE

S 4

00 (

TY

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SP

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IFIC

AT

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MO

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L 4

01)

INT

ER

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SE

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S A

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3 IN

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(83

.82

cm)

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urat

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show

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may

var

y w

ith o

ptio

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conf

igur

atio

ns.

NO

TE

11.0

0 ft.

(3.3

5 m

)

20.2

0 in

. W x

56.

00 in

. H(5

1.31

cm

x 1

.42

m)

30.0

0 in

. W x

65.

00 in

. H(7

6.20

cm

x 1

.65

m)

24.0

0 in

. W x

65.

00 in

. H(6

0.96

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x 1

.65

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24.0

0 in

. W x

54.

00 in

. H(6

0.96

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x 1

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GG

AG

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24.0

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. W x

54.

00 in

. H(6

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x 1

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1. F

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GE

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33

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3

5 ft

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.(1

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GG

AG

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.00

in. H

(1.3

0 m

x 1

.50

m)


SERIES 400 STANDARD INTERIOR CONFIGURATIONS (Sheet 2 of 2)


CHAPTER 2Page 12

Dec 05/2014

PA

SS

EN

GE

R C

AB

IN L

EN

GT

H61

ft 8

in.

(18.

80 m

)

11.0

0 ft.

(3.3

5 m

)

30.0

0 in

. W x

65.

00 in

. H(7

6.20

cm

x 1

.65

m)

(1.3

0 m

x 1

.50

m)

24.0

0 in

. W x

65.

00 in

. H(6

0.96

cm

x 1

.65

m)

24.0

0 in

. W x

54.

00 in

. H(6

0.96

cm

x 1

.37

m)

AIR

ST

AIR

/TY

PE

I E

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PA

X D

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SE

RV

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13

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6

25

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TE

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UR

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74 S

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31

INC

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ith o

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conf

igur

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51.0

0 in

W x

59.0

0 in

. H

1. F

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ard

bagg

age

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part

men

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.00

ft (

2.58

m )

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ggag

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(1

1.64

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6. G

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y.

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GE

ND

33

33

20.2

0 in

. W x

56.

00 in

. H(5

1.31

cm

x 1

.42

m)

BA

GG

AG

E D

OO

R24

.00

in. W

x 5

4.00

in. H

(60.

96 c

m x

1.3

7 m

)

TY

PE

II/II

I EX

IT

5 ft.

11

in.

(1.8

1 m

)

ST

A. X

−39

.00

ST

A. X

701.

00

br30

7a01

.dg,

pt/k

mw

, aug

08/2

008


SERIES 400 (MODEL 402) STANDARD INTERIOR CONFIGURATION


CHAPTER 2Page 13

Dec 05/2014

PA

SS

EN

GE

R C

AB

IN L

EN

GT

H61

ft 8

in. (

18.8

0 m

)

1

45

6

25

Layo

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ay v

ary

with

opt

iona

l con

figur

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ns.

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TE

11.0

0 ft.

(3.3

5 m

)3

5 ft

9 in

.(1

.75

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RIE

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00 (

MO

DE

L 4

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INT

ER

IOR

CO

NF

IGU

RA

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N78

SE

AT

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0 IN

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(76

.2 c

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CH

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GG

AG

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in. W

x 5

4.00

in. H

(60.

96 c

m x

1.3

7 m

)

ST

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−39

.00

ST

AX

701.

00

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YP

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x 6

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in. H

(60.

96 c

m x

1.6

5 m

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SE

RV

ICE

DO

OR

/TY

PE

I E

XIT

24.0

0 in

. W x

54.

00 in

. H(6

0.96

cm

x 1

.37

m)

TY

PE

II/II

I EX

IT20

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in. W

x 5

6.00

in. H

(51.

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1.4

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BA

GG

AG

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OO

R51

.00

in. W

x 5

9.00

in. H

(1.3

0 m

x 1

.50

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cg35

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1.dg

, cs,

aug

06/2

014

2. R

ear

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age

com

part

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t36

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3 m

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1. F

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com

part

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ft (

2.58

m )

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3

33

FO

RW

AR

D P

AS

SE

NG

ER

AIR

ST

AIR

DO

OR

30.0

0 in

. W x

65.

00 in

. H(7

6.20

cm

x 1

.65

m)


SERIES 400 OPTIONAL INTERIOR CONFIGURATIONS (Sheet 1 of 5)


CHAPTER 2Page 14

Dec 05/2014

7

6

54

3

2

1

LE

GE

ND

3. L

avat

ory.

1. F

orw

ard

Bag

gage

Com

part

men

t

6. G

alle

y.

4. W

ardr

obe.

5. F

light

atte

ndan

t Sea

t.

7. C

art s

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6

5

51.0

0 ft

(1.4

4 m

).

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0 in

.96

.01

cm11

.00

ft(3

.35

m)

SE

RIE

S 4

00 (

MO

DE

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INT

ER

IOR

CO

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IGU

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AT

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(81

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part

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BA

GG

AG

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x 5

9.00

in. H

(1.3

0 m

x 1

.50

m)

SE

RV

ICE

DO

OR

/TY

PE

I E

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24.0

0 in

. W x

54.

00 in

. H(6

0.96

cm

x 1

.37

m)

PA

X D

OO

R/T

YP

E I

EX

IT24

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in. W

x 6

5.00

in. H

(60.

96 c

m x

1.6

5 m

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TY

PE

II/II

I EX

IT20

.20

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x 5

6.00

in. H

(51.

31cm

x 1

.42

m)

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GG

AG

E D

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R24

.00

in. W

x 5

4.00

in. H

(60.

96 c

m x

1.3

7 m

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ay v

ary

with

opt

iona

l con

figur

atio

ns.

NO

TE

PA

SS

EN

GE

R C

AB

IN L

EN

GT

H61

ft 8

in. (

18.8

0 m

)

6

cg35

35a0

2.dg

, cs,

aug

06/2

014

FO

RW

AR

D P

AS

SE

NG

ER

AIR

ST

AIR

DO

OR

30.0

0 in

. W x

65.

00 in

. H(7

6.20

cm

x 1

.65

m)




CHAPTER 2Page 15

Dec 05/2014

54

31

6

5

PA

SS

EN

GE

R C

AB

IN L

EN

GT

H61

ft 8

in. (

18.8

0 m

)

5 ft

9 in

.(1

.75

m)

11.0

0 ft

(3.3

5 m

)

SE

RIE

S 4

00 (

MO

DE

L 4

02)

INT

ER

IOR

CO

NF

IGU

RA

TIO

N66

SE

AT

S A

T 3

1 in

. (78

.74

cm)

PIT

CH

AN

D 8

SE

AT

S A

T 3

4 in

. (86

.36

cm)

PIT

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X70

1.00

ST

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.00

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2

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ay v

ary

with

opt

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l con

figur

atio

n.

NO

TE

SE

RV

ICE

DO

OR

/TY

PE

I E

XIT

24.0

0 in

. W x

54.

00 in

. H(6

0.96

cm

x 1

.37

m)

TY

PE

II/II

I EX

IT20

.20

in. W

x 5

6.00

in. H

(51.

31cm

x 1

.42

m)

BA

GG

AG

E D

OO

R24

.00

in. W

x 5

4.00

in. H

(60.

96 c

m x

1.3

7 m

)

PA

X D

OO

R/T

YP

E I

EX

IT24

.00

in. W

x 6

5.00

in. H

(60.

96 c

m x

1.6

5 m

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AG

GA

GE

DO

OR

51.0

0 in

. W x

59.

00 in

. H(1

.30

m x

1.5

0 m

)

2. R

ear

bagg

age

com

part

men

t36

5.00

ft (

10.3

3 m

).

3. L

avat

ory.

4. W

ardr

obe.

5. F

light

atte

ndan

t.6.

Gal

ley.

LE

GE

ND

1. F

orw

ard

bagg

age

com

part

men

t91

.00

ft (

2.58

m )

.3

3

33

cg35

35a0

3.dg

, cs,

aug

06/2

014

FO

RW

AR

D P

AS

SE

NG

ER

AIR

ST

AIR

DO

OR

30.0

0 in

. W x

65.

00 in

. H(7

6.20

cm

x 1

.65

m)




CHAPTER 2Page 16

Dec 05/2014

PA

SS

EN

GE

R C

AB

IN L

EN

GT

H61

ft 8

in.

(18.

80 m

)

1

45

6

25

Layo

ut m

ay v

ary

with

opt

iona

l con

figur

atio

n.

NO

TE

11.0

0 ft.

(3.3

5 m

)

24.0

0 in

. W x

54.

00 in

. H(6

0.96

cm

x 1

.37

m)

SE

RV

ICE

DO

OR

/TY

PE

I E

XIT

3

5 ft

9 in

.(1

.75

m)

TY

PE

II/II

I EX

IT20

.20

in. W

x 5

6.00

in. H

(51.

31cm

x 1

.42

m)

BA

GG

AG

E D

OO

R24

.00

in. W

x 5

4.00

in. H

(60.

96 c

m x

1.3

7 m

)

PA

X D

OO

R/T

YP

E I

EX

IT24

.00

in. W

x 6

5.00

in. H

(60.

96 c

m x

1.6

5 m

)

7 S

EA

TS

AT

36

in. (

91.4

4 cm

) P

ITC

H, 1

0 S

EA

TS

AT

34

in. (

86.3

6 cm

) P

ITC

H A

ND

54

SE

AT

S A

T 3

0 in

. (76

.20

cm)

PIT

CH

SE

RIE

S 4

00 (

MO

DE

L 4

02)

TH

RE

E−A

BR

EA

ST

TR

IPL

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LA

SS

INT

ER

IOR

CO

NF

IGU

RA

TIO

N

1. F

orw

ard

bagg

age

com

part

men

t91

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ft (2

.58

m )

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Rea

r ba

ggag

e co

mpa

rtm

ent

365.

00 ft

(10

.33

m )

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Lav

ator

y.4.

War

drob

e.5.

Flig

ht a

ttend

ant.

6. G

alle

y.

LE

GE

ND

33

33

BA

GG

AG

E D

OO

R51

.00

in. W

x 5

9.00

in. H

(1.3

0 m

x 1

.50

m)

ST

A X

701.

00S

TA

X−

39.0

0

cg35

35a0

4.dg

, cs,

aug

06/2

014

FO

RW

AR

D P

AS

SE

NG

ER

AIR

ST

AIR

DO

OR

30.0

0 in

. W x

65.

00 in

. H(7

6.20

cm

x 1

.65

m)




CHAPTER 2Page 17

Dec 05/2014

43

2

1

LE

GE

ND

3. W

ardr

obe.

1. R

ear

bagg

age

com

part

men

t

4. F

light

atte

ndan

t Sea

t.5.

Gal

ley.

4

365.

00 ft

(10

.33

m )

.

11.0

0 ft

(3.3

5 m

)

X70

1.00

ST

AX

−39

.00

ST

A

33

2. L

avat

ory.

BA

GG

AG

E D

OO

R51

.00

in. W

x 5

9.00

in. H

(1.3

0 m

x 1

.50

m)

SE

RV

ICE

DO

OR

/TY

PE

I E

XIT

24.0

0 in

. W x

54.

00 in

. H(6

0.96

cm

x 1

.37

m)

PA

X D

OO

R/T

YP

E I

EX

IT24

.00

in. W

x 6

5.00

in. H

(60.

96 c

m x

1.6

5 m

)

PA

SS

EN

GE

R C

AB

IN L

EN

GT

H61

ft 8

in. (

18.8

0 m

)

5

SE

RIE

S 4

00 (

MO

DE

L 4

02)

EX

TR

A C

AP

AC

ITY

INT

ER

IOR

CO

NF

IGU

RA

TIO

N86

SE

AT

S A

T 2

9 IN

CH

(73

.66

cm)

PIT

CH

TY

PE

II/II

I EM

ER

GE

NC

YE

XIT

DE

−A

CT

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TE

D

Layo

ut m

ay v

ary

with

opt

iona

l con

figur

atio

ns.

NO

TE

FO

RW

AR

D T

YP

E I

EM

ER

GE

NC

Y E

XIT

DO

OR

24.0

0 in

. W x

54.

00 in

. H(6

0.96

cm

x 1

.37

m)

cg35

35a0

5.dg

, cs,

aug

06/2

014

FO

RW

AR

D P

AS

SE

NG

ER

AIR

ST

AIR

DO

OR

30.0

0 in

. W x

65.

00 in

. H(7

6.20

cm

x 1

.65

m)




CHAPTER 2Page 18

Dec 05/2014

br72

1a01

.dg,

gv/

gw, n

ov13

/201

4

106.0 in.(2.69 m)

77.0 in.(1.95 m)

56.5 in.(1.44 m)

24.3 in.(0.62 m)

12.4 in.(0.32 m)

15.8 in.(0.40 m)

20.0 in(0.51 m)

25.9 in.(0.66 m)

99.0 in.(2.51 m)

80.0 in.(2.03 m)

108.8 in.(2.76 m)

GROUND REFERENCE LINE

OVERHEAD STOWAGE BINS(CAPACITY IS 1.67 ft (0.047 m )/PAX.)

3

NOTE

71.8 in.(1.82 m)

1

1

AT DOOR CENTER LINE

101.1 in.(2.56 m)

This dimension is approximate and will vary with aircraft configuration and loading conditions.

15.74 in. (14.6 cm)AT FWD EDGE OF DOOR6.21 in. (15.8 cm) AT AFT EDGE OF DOOR


3

11.37 in. (28.9 cm)

PASSENGER COMPARTMENT(CLASSIC)


PASSENGER COMPARTMENT CROSS SECTION (Sheet 1 of 2)


CHAPTER 2Page 19

Dec 05/2014

106.0 in.

76.1 in.

11.1 in.


OVERHEAD STOWAGE BINS

71.8 in.

1AT DOOR CENTER LINE

81.9 in.

NOTE

1 This dimension is approximate and will vary with aircraft configuration and loading conditions.

11.37 in. (28.9 cm)

101.1 in. (2.56 m)

108.8 in. (2.76 m)

(2.08 m)

(0.28 m)

24.5 in.(0.62 m)

56.3 in.(1.43 m)

(2.69 m)

24.1 in.

20.4 in.(0.52 m)

97.9 in.(2.49 m)

16.0 in.(0.41 m)

(1.93 m)

(1.82 m)

PASSENGER COMPARTMENT(NEXT GEN)

(CAPACITY IS 1.75 ft (0.049 m )/PAX.)3 3

(0.61 m)

br72

1a02

.dg,

gw

, nov

13/2

014


PASSENGER COMPARTMENT CROSS SECTION (Sheet 2 of 2)


CHAPTER 2Page 20

Dec 05/2014

LAV

AT

OR

YS

EA

TR

AIL

S

BA

GG

AG

EC

OM

PA

RT

ME

NT

SE

RV

ICE

DO

OR

GA

LLE

YS

(2)

WA

RD

RO

BE

AF

TF

OR

WA

RD

BA

GG

AG

EC

OM

PA

RT

ME

NT

FO

RW

AR

DP

AS

SE

NG

ER

DO

OR

br29

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l29/

2014

AF

TB

AG

GA

GE

DO

OR

AF

TP

AS

SE

NG

ER

DO

OR

FO

RW

AR

DB

AG

GA

GE

DO

OR

LE

GE

ND

Flo

or p

anel

s th

at c

an s

uppo

rt a

max

imum

floo

r lo

adin

g of

37.

5 lb

/ft

(183

kg/

m )

.

Flo

or p

anel

s th

at c

an s

uppo

rt a

max

imum

floo

r lo

adin

g of

125

.0 lb

/ ft

(610

kg/

m )

.

2 2

2

Flo

or p

anel

s th

at c

an s

uppo

rt a

max

imum

floo

r lo

adin

g of

75.

0 lb

/ft (

366

kg/m

).

2

2

2

70 T

O 7

8 S

EA

TS

CO

NF

IGU

RA

TIO

N−S

ER

IES

400


FLOOR LOADING DIAGRAM (Sheet 1 of 2)


CHAPTER 2Page 21

Dec 05/2014

LE

GE

ND

LAV

AT

OR

YS

EA

TR

AIL

S

BA

GG

AG

EC

OM

PA

RT

ME

NT

SE

RV

ICE

DO

OR

GA

LLE

YW

AR

DR

OB

E

Flo

or p

anel

s th

at c

an s

uppo

rt a

max

imum

floo

r lo

adin

g of

37.

5 lb

/ft

(183

kg/

m )

.

Flo

or p

anel

s th

at c

an s

uppo

rt a

max

imum

floo

r lo

adin

g of

125

.0 lb

/ ft

(610

kg/

m )

.

AF

T

FO

RW

AR

DP

AS

SE

NG

ER

DO

OR

2 2

2

br29

7a02

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jul2

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14

AF

TB

AG

GA

GE

DO

OR

AF

TP

AS

SE

NG

ER

DO

OR

FO

RW

AR

D T

YP

E I

EM

ER

GE

NC

YE

XIT

DO

OR

WIT

HD

ITC

HIN

G D

AM

Flo

or p

anel

s th

at c

an s

uppo

rt a

max

imum

floo

r lo

adin

g of

75.

0 lb

/ft (

366

kg/m

).

2

2

2

86 S

EA

TS

EX

TR

A C

AP

AC

ITY

INT

ER

IOR

CO

NF

IGU

RA

TIO

N−S

ER

IES

400


FLOOR LOADING DIAGRAM (Sheet 2 of 2)


CHAPTER 2Page 22

Dec 05/2014

br75

7a01

.dg,

pt/c

s, ju

l29/

2014

FW

D

CL

X1.00

X70.027.8 in.

(70.6 cm)

5 ft 9 in.(1.75 m)

ACCESSDOOR

FORWARD BAGGAGECOMPARTMENT DOOR/

FORWARD TYPE IEMERGENCY EXIT DOOR

Y11

.80

VIEW LOOKING DOWN

3

NOTES

1. The dimensions shown are measured at floor level.2. Forward baggage compartment and forward baggage

door is removed for the extra capacity configuration.

Type I emergency exit door is installed in forward RH side3for the extra capacity configuration.


FWD BAGGAGE − COMPARTMENT DIMENSIONS (STANDARD INTERIOR CONFIGURATION)


CHAPTER 2Page 23

Dec 05/2014

br75

8a01

.dg,

sw

, 08/

04/9

8

NOTEThe dimensions shown aremeasured at floor level.

X834.54

X783.10

X703.05

48.43 in.(1.23 m)

78.41 in.(1.99 m)

50.15 in.(1.27 m)

76.34 in.(1.94 m)

51.44 in.(1.31 m)

80.05 in.(2.03 m)


AFT BAGGAGE COMPARTMENT DIMENSIONS (STANDARD INTERIOR CONFIGURATION)


CHAPTER 2Page 24

Dec 05/2014

br75

9a01

.dg,

sw

, 08/

04/9

8

NOTEThe dimensions shown aremeasured at floor level.

X834.54

X783.10

X721.70

X703.05

48.43 in.(1.23 m)

78.41 in.(1.99 m)

50.15 in.(1.27 m)

76.34 in.(1.94 m)

51.44 in.(1.31 m)

61.40 in.(1.56 m)

Y−

12.3

5


AFT BAGGAGE COMPARTMENT DIMENSIONS (OPTIONAL INTERIOR CONFIGURATION)


CHAPTER 2Page 25

Dec 05/2014

br87

6a01

.dg,

gg/

pt, 1

2/01

/01

AFTPOSTCENTER

POSTCARGONETS

2000 lb (907 kg)

FORWARD−FLOORTIE−DOWN RINGS (4)

180

120o

o

VIEW LOOKING AFT (NETS AND POLES OMITTED FOR CLARITY)

2000 lb (907 kg)

SIDEWALL (AND AFT BULKHEAD)TIE−DOWN RINGS (12)


NETS AND TIE−DOWNS (DETAIL SPEC. CONFIGURATION)


CHAPTER 2Page 26

Dec 05/2014

FWD

br88

3a01

.dg,

pt,

12/0

1/01

CARGONETS

CENTERPOST

AFT POST

2000 lb (907 kg)

FORWARD−FLOORTIE−DOWN RINGS (4)

180 o

120o

2000 lb (907 kg)

VIEW LOOKING AFT (NETS AND POLES OMITTED FOR CLARITY)

SIDEWALL (AND AFT BULKHEAD)TIE−DOWN RINGS (11)


NETS AND TIE−DOWNS (G3 GALLEY)


CHAPTER 2Page 27

Dec 05/2014

Door Clearances

1. General

The door clearance sheets provide the door size and location of the passenger, service andbaggage compartment doors.

2. The forward passenger (airstair) door opens outwards and downwards and is manuallycontrolled from inside or outside the aircraft.

3. The aft passenger door/Type 1 exit opens inward and upwards, then moves outward andforward.

4. The aft service door/Type 1 exit opens inwards and upwards, then moves outwards andforward.

5. The forward baggage−compartment door opens inward and upward, then moves outwardsand forward.

6. The aft baggage−compartment door opens outwards and upwards.


Series: 400

CHAPTER 2Page 28

Dec 05/2014

br54

0a01

.dg,

gg/

sw, 0

4/10

/99

NOTE

1

2

FS16.70016 ft 3 in.(4.95 m) 20.0 in.

(50.8 cm)

25.74 in. (14.6 cm)AT FWD EDGE OF DOOR6.21 in. (15.8 cm)AT AFT EDGE OF DOOR


VIEW LOOKING INBOARD

VIEW LOOKING AFTSECTION B−B

30.0 in.(76.2 cm)

20.0 in.(50.8 cm)

27.0 in.(68.6 cm)

24.0 in.(61.0 cm)

62.0 in.(1.58 m)

37.0 in.(94.0 cm)

25.0 in.(63.5 cm)

11.37 in. (28.9 cm)AT DOOR CENTER LINE

44.0 in. (1.12 m)

8 ft 6 in. (2.60 m)

9 ft 1 in. (2.77 m) 2

Dimensions are approximate and will vary withaircraft configuration and loading conditions.

Refer to Ground Clearance illustrations.

1

22.0 in.(55.9 cm)


FORWARD PASSENGER − DOOR CLEARANCES


CHAPTER 2Page 29

Dec 05/2014

5 ft. 4 in.(1.64 m)

5 ft. 8 in.(1.72 m)

AFTPASSENGER DOOR(OPEN POSITION)

0.85 in.(21.59 mm)

5 ft. 9 in.(1.75 m)

27.90 in.(70.87 cm)

AFTBAGGAGE DOOR

(REF)

3 ft. 7 in.(1.08 m)

CLEAROPENING

TO NOSEOF A/C

71 ft. 9 in.(21.88 m)

(REF)

0.66 in.(16.76 mm)

GROUNDREFERENCE

LINE

FLOOR LEVEL

14.81 in.(37.62 cm)

br84

5a01

.dg,

gg/

sw, 0

4/10

/99

1

VIEW LOOKING INBOARD ON L/H SIDE

FS 683.450

NOTE

1 Refer to Ground Clearance illustrations.

40.0 in.(1.02 m)


AFT PASSENGER − DOOR CLEARANCES (Sheet 1 of 2)


CHAPTER 2Page 30

Dec 05/2014

CENTER LINE

L/H

24.55 in.(62.36 cm)

27.90 in.(70.87 cm)

AFTBAGGAGE DOOR

(REF)

CLEAR OPENING

3 ft. 9 in.(1.14 m)

AFT PASSENGERDOOR

(OPEN POSITION)

7.73 in.(19.63 cm) 4 ft. 5 in.

(1.34 m)

CL5 ft. 2 in.(1.57 m)

br84

5a02

.dg,

gw

, 08/

04/9

8

FWD

16.41 in.(41.68 cm)

VIEW LOOKING DOWN ON L/H SIDE

VIEW LOOKING FORWARD

AFT PASSENGERDOOR

(OPEN POSITION)

UP

L/H R/H


AFT PASSENGER − DOOR CLEARANCES (Sheet 2 of 2)


CHAPTER 2Page 31

Dec 05/2014

27.90 in.(70.87 cm)

14.81 in.(37.62 cm)

0.66 in.(16.76 mm)

FLOOR LEVEL

AFTSERVICE DOOR

GROUNDREFERENCE

LINE

4 ft. 5 in.(1.36 m)CLEAR

OPENING 4 ft. 10 in.(1.48 m)

0.85 in.(21.59 mm)

3 ft. 7 in.(1.08 m)

71 ft. 9 in.(21.88 m)

(REF)TO NOSE OF A/C

UP

FWD

br46

6a01

.dg,

gg/

sw, 0

4/10

/99

4 ft. 9 in.(1.45 m)

(OPEN POSITION)

1

VIEW LOOKING INBOARD ON R/H SIDE

NOTE

1

FS 683.450


40.0 in.(1.02 m)


AFT SERVICE − DOOR CLEARANCES (Sheet 1 of 2)


CHAPTER 2Page 32

Dec 05/2014

UP

4 ft. 6 in.(1.37 m)

FLOOR LEVEL

AFT SERVICEDOOR

(OPEN POSITION)

1.21 in.(30.73 mm)4 ft. 5 in.

(1.34 m)

CL

5 ft. 2 in.(1.58 m)

br46

6a02

.dg,

gw

, 08/

04/9

8

AFT SERVICEDOOR

(OPEN POSITION)

FWD

L/H

CENTER LINE

24.55 in.(62.36 cm)

CLEAR OPENING

28.90 in.(73.41 cm)

R/HL/H


VIEW LOOKING DOWN ON R/H SIDE

16.41 in.(41.68 cm)


AFT SERVICE − DOOR CLEARANCES (Sheet 2 of 2)


CHAPTER 2Page 33

Dec 05/2014

4 ft. 5 in.(1.36 m)

4 ft. 9 in.(1.45 m)

FLOOR LEVEL

0.85 in.(21.6 mm)

3 ft. 6 in.(1.09 m)

27.90 in.(70.87 cm)

14.81 in.(37.62 cm)

4 ft. 10 in.(1.48 m)

0.66 in.(16.8 mm)

(REF)

TO NOSEOF A/C

GROUNDREFERENCE

LINE

FORWARD BAGGAGE DOOR/FORWARD TYPE 1 EMERGENCY EXIT

(OPEN POSITION)

cg35

36a0

1.dg

, cs/

kmw

, nov

21/2

014

VIEW LOOKING INBOARD ON R/H SIDE

1

FS18.250 16ft. 4in.(4.98m)

40.0 in.(1.02 m)


Forward baggage compartment and forward baggage door isremoved for the extra capacity configuration.

Forward type I emergency exit door is installed in lieu of forwardbaggage compartment door for the extra capacity configuration.

NOTES

2.

3.


FORWARD BAGGAGE COMPARTMENT/FORWARD TYPE 1 EMERGENCY EXIT − DOORCLEARANCES (Sheet 1 of 2)


CHAPTER 2Page 34

Dec 05/2014

27.90 in.(70.87 cm)

24.55 in.(62.35 cm)

CLEAR OPENING

FORWARD BAGGAGE DOOR/FORWARD TYPE 1EMERGENCY EXIT

FWD

4 ft. 6 in.(1.37 m)

FLOOR LEVEL

5 ft. 2 in.(1.58 m)

CL

1.21 in.(30.73 mm)

4 ft. 5 in.(1.34 m)

UP

L/H R/H


cg35

36a0

2.dg

, cs/

kmw

, nov

21/2

014

CENTERLINE

16.41 in.(41.68 cm)

VIEW LOOKING DOWN ON R/H SIDE

L/H

2. Forward baggage compartment and forward baggage door isremoved for the extra capacity configuration.

3. Forward type I emergency exit door is installed in lieu of forward baggage compartment door for the extra capacity configuration.

NOTES

(OPEN POSITION)

FORWARD BAGGAGE DOOR/FORWARD TYPE 1EMERGENCY EXIT(OPEN POSITION)


FORWARD BAGGAGE COMPARTMENT/FORWARD TYPE 1 EMERGENCY EXIT − DOORCLEARANCES (Sheet 2 of 2)


CHAPTER 2Page 35

Dec 05/2014

(2.66 m)

(1.59 m)

(1.06 m)

(1.52 m)

(1.66 m)

OPENPOSITION

FLOOR LEVEL

UP

R/HL/H

br41

2a01

.dg,

pt,

13/0

5/98

CL8 ft. 9 in.

5 ft. 3 in.

ATFS 728.102

5 ft. 5 in.

4 ft. 12 in.

3 ft. 6 in.


ATFS 728.102


AFT BAGGAGE−COMPARTMENT − DOOR CLEARANCES (Sheet 1 of 2)


CHAPTER 2Page 36

Dec 05/2014

(1.50 m)

FS 728.102 FS 783.102

(1.30 m)CLEAR OPENING UP

FWD

(6.0 cm)

FLOOR LEVEL

AFT BAGGAGEDOOR

(OPEN POSITION)

CUTOUT

br41

2a02

.dg,

gg/

kmw

, aug

08/2

008

4 ft. 11 in.

4 ft. 3 in.

2.36 in.

VIEW LOOKING INBOARD ON L/H SIDE

1


NOTE

1 Refer to Ground Clearance illustrations.

(30.5 cm)12.0 in.

HANDLE HEIGHT(WHEN CLOSED)


AFT BAGGAGE−COMPARTMENT − DOOR CLEARANCES (Sheet 2 of 2)


CHAPTER 2Page 37

Dec 05/2014

cg35

38a0

1.dg

, cs,

aug

06/2

014

EXTERIOR OF FWD PASSENGER DOOR EXTERIOR OF AFT PASSENGER DOOR

EXTERIOR OF AFT BAGGAGE DOOR

HANDLE IN OPENPOSITION

PUSHTO

RELEASE

PULL HANDLEAND TURNTO OPEN

STOW STRUTBEFORE CLOSINGBAGGAGE DOOR



(TYPICAL)



DOORLOWERING

ASSISTPUSH

WARNINGKEEP CLEAR

OF DOORPULL HANDLE

OUT AND DOWNTO OPEN

SUPPORT DOORWHILE LOWERING


EXTERIOR HANDLES (Sheet 1 of 2)


CHAPTER 2Page 38

Dec 05/2014

cg35

38a0

2.dg

, cs,

aug

06/2

014




D

D

E

E

F

F

EXTERIOR OF TYPE II / III EMERGENCY EXIT

EXTERIOR OF AFT SERVICE DOOR



PUSH TORELEASE

TURN HANDLE DOWNAND PUSH HATCH IN

EXTERIOR FORWARD BAGGAGEDOOR/ EXTERIOR FORWARD

TYPE I EMERGENCY EXIT DOOR

31.0 in.(78.7 cm)


NOTES


2


EXTERIOR HANDLES (Sheet 2 of 2)


CHAPTER 2Page 39

Dec 05/2014

braa

8a01

.dg,

ab,

26/

08/0

1

NOTES

1. Right side of aircraft is shown, left side is identical.

Drain mast on left side of each nacelle (viewed frombehind the aircraft) protrudes approx. 4 in. (10.2 cm).

The minimum clearance between the nacelle (aft MLG doors)and the fuselage is 96 in. (2.44 m). Right side of theaircraft is shown, left side is identical.

Aft MLG doors protrude approx. 6 in. (15.2 cm) fromboth sides of the nacelles.


MINIMUM CLEARANCE BETWEEN NACELLES AND FUSELAGE


CHAPTER 2Page 40

Dec 05/2014

braa

7a01

.dg,

ab,

26/

03/0

1

63.5 in.(1.61 m)

74.9 in.(1.90 m)

11.5 in.(29.2 cm)


AFT BAGGAGE COMPARTMENT VERTICAL DIMENSIONS (TYPICAL CONFIGURATION)


CHAPTER 2Page 41

Dec 05/2014

cg28

86a0

1.dg

, nn/

kmw

, sep

19/2

013

ITEM HEIGHT FEET (ft) METERS (m)

J VERTICAL STABILIZER (OFF JACKS) 26.7 − 27.2 8.13 − 8.30

JJ VERTICAL STABILIZER (ON JACKS) 27.2 8.30

K HORIZONTAL STABILIZER (OFF JACKS) 25 − 26 7.62 − 7.92

KK HORIZONTAL STABILIZER (ON JACKS) 26.7 8.13

A TAIL (OFF JACKS) 11.8 3.60

AA TAIL (ON JACKS) 13 − 13.9 3.96 − 4.24

G SILL OF AFT BAGGAGE DOOR (OFF JACKS) 5.06 1.54

GG SILL OF AFT BAGGAGE DOOR (ON JACKS) 5.7 1.74

OF

F JA

CK

S

J

ON

JAC

KS

JJ

OF

F JA

CK

S

K

ON

JAC

KS

KK

OF

F JA

CK

S

A

ON

JAC

KS

AA

ON JACKSOFF JACKS

GGG

12 ft 4 in.(3.76 m)

18.2 ft(5.55 m)

1. K and KK values are through C/L of horizontal stabilizer.

2. Dimensions are approximate and will vary with

NOTES

aircraft configuration and loading conditions.

5.07 ft(1.55 m)


AIRCRAFT DIMENSIONS (Sheet 1 of 3)


CHAPTER 2Page 42

Dec 05/2014

cg28

86a0

2.dg

, kh,

nov

12/2

013

ST

AT

IC

A

ON

JAC

KS

AA

ON

JAC

KS

BBB

A/C

LEV

EL

B

ST

AT

IC

BB

GROUND LEVEL

1 LEVEL

2 LEVEL

5 ft.(1.52 m)

9.17 ft.(2.79 m)

14.17 ft.(4.32 m)

27.42 ft.(8.36 m)

ITEM FEET (ft) METERS (m)

A 9.83 3.00

AA 10.67 3.25

B 11.17 3.40

BB 12.42 3.79

BBB 13.25 4.04

Dimensions are approximate andwill vary with A/C configuration andloading conditions.

NOTE

AIRCRAFT EMPENNAGE − PLATFORM WORKING HEIGHTS

12.33 ft.(3.76 m)




CHAPTER 2Page 43

Dec 05/2014

A B CD

E

L K J H G F

A

B

C

FEET (ft) METERS (m)

25.67

12.83

3.22

7.82

3.91

0.98D

E

F

3.61

13.5

27.33

1.10

4.11

8.33

G

H

J

5.07

5.07

4.08

1.55

1.55

1.24

K

L

3.82

10.75

1.16

3.28

ITEM

EMERGENCY EXIT LOCATIONS AND ELEVATIONS

cg28

86a0

3dg,

cs,

sep

08/2

014




CHAPTER 2Page 44

Dec 05/2014

CHAPTER 3

AIRCRAFT PERFORMANCE



General Information

1. General

This chapter contains the performance data of the Dash−8 Series 400 (Model 402) aircraft asrequired for airport planning purposes. This data reflects the performance levels of theDash−8 Series 400, Performance Data (July 1999).

2. The various definitions used in this Chapter are as follows:

A. Maximum Structural Weights

As found in the July 1999 Performance Data, the maximum structural take−off weight is63,750 lbs (28,916 kg), and the maximum landing weight is 61,250 lbs (27,782 kg).

B. WAT Limits

The maximum permissible take−off weight (refer to Figure 3−2, Figure 3−3 and Figure3−4) and landing weight (refer to Figure 3−8, Figure 3−9 and Figure 3−10) are basedon the climb requirements of FAR 25 (one engine inoperative).

C. Take−off Runway Length

The take−off runway length shown in Figure 3−5, Figure 3−6 and Figure 3−7 is thelongest of:

– − The accelerate−stop distance– − The take−off distance to 35 feet altitude with one engine inoperative at V1– − 1.15 times the all engine−operating take−off distance to 35 feet altitude.

D. Landing Runway Length

The landing runway length required in Figure 3−14 is the unfactored landing distance(refer to Figure 3−11, Figure 3−12 and Figure 3−13) multiplied by an operational factorof 1.67 (or 1/0.6) or 1.43 (or 1/0.7). The unfactored landing distance is based on anapproach speed of 1.3 Vs and a screen height of 50 feet.

E. Retardation Devices

The retardation devices that follow are used:

(1) Accelerate−Stop

(a) Maximum main−wheel anti−skid braking.

(b) One propeller in the DISC position, the other one is feathered.

(c) Roll spoilers are extended.

(2) Landing


Series: 400

CHAPTER 3Page 1

May 28/2001

(a) Maximum main−wheel anti−skid braking.

(b) One propeller in the DISC position, the other one is feathered.

(c) Roll spoilers are extended.

F. Standard Day Temperatures

The table that follows shows the standard day temperatures that are used in thisChapter.

STANDARD DAY TEMPERATURES

ELEVATION STANDARD DAY TEMPERATUREFEET METERS °F °C

0 0 59 152000 610 51.9 11.14000 1220 44.7 7.16000 1830 37.6 3.18000 2440 30.5 −0.8

10,000 3050 23.3 −4.8


Series: 400

CHAPTER 3Page 2

May 28/2001

brb1

1a01

.dc,

sw

, 25/

01/0

0


PAYLOAD/RANGE AT MAXIMUM CRUISE RATING AND LONG RANGE CRUISE


CHAPTER 3Page 3

May 28/2001

brb1

2a01

.dc,

pm

, 25/

01/0

0


MAXIMUM PERMISSIBLE TAKE−OFF WEIGHT (WAT LIMIT) − FLAPS 5 DEGREES


CHAPTER 3Page 4

May 28/2001

brb1

3a01

.dc,

sw

, 26/

01/0

0




CHAPTER 3Page 5

May 28/2001

brb1

4a01

.dc,

sw

, 26/

01/0

0




CHAPTER 3Page 6

May 28/2001

brb1

5a01

.dc,

sw

, 26/

01/0

0

RU

NW

AY


TAKE−OFF RUNWAY LENGTH REQUIREMENTS − FLAPS 5 DEGREES


CHAPTER 3Page 7

May 28/2001

brb

16a0

1.dc

, sw

, 26/

01/0

0

RU

NW

AY




CHAPTER 3Page 8

May 28/2001

brb1

7a01

.dc,

sw

, 26/

01/0

0

RU

NW

AY




CHAPTER 3Page 9

May 28/2001

brb1

8a01

.dc,

sw

, 26/

01/0

0


MAX. LANDING WEIGHT − LANDING FLAPS 10 AND APPROACH FLAPS 5 DEGREES


CHAPTER 3Page 10

May 28/2001

brb1

9a01

.dc,

sw

, 27/

01/0

0




CHAPTER 3Page 11

May 28/2001

brb2

0a01

.dc,

sw

, 26/

01/0

0




CHAPTER 3Page 12

May 28/2001

brb2

1a01

.dc,

sw

, 26/

01/0

0


UNFACTORED LANDING DISTANCE − FLAPS 10 DEGREES


CHAPTER 3Page 13

May 28/2001

brb2

2a01

.dc,

sw

, 26/

01/0

0




CHAPTER 3Page 14

May 28/2001

brb2

3a01

.dc,

sw

, 26/

01/0

0




CHAPTER 3Page 15

May 28/2001


LANDING − RUNWAY LENGTH REQUIRED


CHAPTER 3Page 16

May 28/2001

CHAPTER 4

GROUND MANEUVERING



General Information

1. This Chapter supplies data on the items that follow:

– Aircraft turning capability (refer to Figure 4−1, Figure 4−2 and Figure 4−3)– Visibility from cockpit (Note, this information is not available at this time)– Maneuvering characteristics (refer to Figure 4−4, Figure 4−5, Figure 4−6 and Figure 4−7)– Mooring data (refer to Figure 4−8).

2. This data has been determined from the theoretical limits imposed by the geometry of theaircraft and includes normal allowance for tire slippage (as indicated). The purpose of thisChapter is to show the turning capability of the aircraft in favorable operating conditions(without the use of reverse thrust or differential braking). Use this data only as a guideline.

3. It is possible that each airline will use more conservative turning procedures to avoidexcessive tire wear and possible maintenance problems. The operating techniques of eachairline will be different and may be modified because of these physical factors within themaneuvering area:

– Adverse grades– Limited area– High risk of jet engine exhaust or propeller slipstream damage.

4. Because of these reasons the airport planner must coordinate the ground maneuvering datawith the user airline for airport layout plan.


Series: 400

CHAPTER 4Page 1

May 28/2001

6

7

o oo

oo

o

o

o

o

o

o

o

o

o

20o

90 85 8075

7065

6055

50

45

40

35

30

25

TOWING

STEERING

TURNING CENTER FORNOSE−GEAR TURNING

ANGLE. (TYPICAL)

NOSE−GEAR AXLEPROJECTION−LINE.

(TYPICAL)

R−1 (Inner).

R−2 (Outer Gear).

R−3 (Nose Gear).

R−4 (Wing Tip).

R−5 (Nose).

R−6 (Tail).

Dimension "C" Typical. Refer to table for distance of individual points from aircraft center line.

6

7

bra8

5a01

.dg,

pt,

05/0

8/98


TURNING RADII (NO SLIP ANGLE)


CHAPTER 4Page 2

May 28/2001

6083

.87

154.

5064

59.5

016

4.10

6306

.70

160.

2068

31.2

517

3.50

6301

.95

160.

0764

83.9

616

4.70

6721

.27

170.

7050

7.00

538.

3352

5.58

569.

2552

5.17

540.

8056

0.00

2923

.90

74.2

732

99.5

374

.27

3171

.20

80.5

036

71.2

993

.25

3172

.68

80.6

033

53.9

985

.20

3111

.30

79.0

324

3.67

275.

0026

4.25

305.

2526

4.42

279.

5025

9.25

1859

.64

47.2

322

35.2

656

.80

2131

.73

54.1

426

07.0

466

.20

2139

.17

54.3

023

18.2

258

.90

2047

.03

52.0

015

5.00

186.

2517

7.67

217.

2521

7.25

193.

1717

0.58

1319

.17

33.5

016

94.8

043

.05

1616

.16

41.0

520

66.5

952

.50

1629

.56

41.4

018

04.9

645

.85

1506

.57

38.2

010

9.92

141.

2513

4.67

172.

2513

5.83

150.

4212

5.58

988.

0925

.10

1363

.71

34.6

013

10.4

533

.29

1735

.52

44.1

013

29.4

633

.80

1500

.02

38.1

011

75.4

829

.80

82.3

311

3.67

109.

1714

4.67

110.

7512

5.00

97.9

276

1.53

19.3

011

37.1

628

.90

1109

.77

28.1

914

28.2

236

.28

1134

.09

28.8

012

98.7

433

.00

949.

9324

.10

63.5

094

.75

92.0

811

9.00

94.0

810

8.25

79.0

859

4.53

15.1

097

0.15

24.6

096

9.26

24.6

213

41.9

834

.10

998.

5525

.40

1156

.38

29.4

078

1.93

20.0

049

.58

80.8

380

.75

111.

8383

.25

96.3

365

.17

464.

5611

.80

840.

1921

.30

866.

5122

.00

1212

.02

30.7

990

0.42

22.9

010

50.6

326

.70

651.

9616

.56

38.7

570

.00

72.2

510

1.00

75.0

087

.58

54.3

335

9.08

9.12

734.

7118

.70

789.

1420

.04

1106

.55

28.1

082

7.25

21.0

096

9.13

24.6

054

6.48

13.9

029

.92

61.2

565

.75

92.2

568

.92

80.7

545

.50

270.

526.

8764

6.14

16.4

072

9.72

18.5

010

18.0

025

.90

771.

6119

.60

904.

5523

.00

457.

9111

.60

22.5

853

.83

60.8

384

.83

64.3

375

.42

38.1

719

4.02

4.93

569.

6414

.50

683.

5717

.36

941.

5123

.90

728.

8218

.50

852.

2421

.60

381.

419.

6916

.17

47.5

057

.00

78.5

060

.75

71.0

031

.75

126.

303.

2150

1.93

12.7

564

7.62

16.4

587

3.81

22.1

969

5.78

17.6

780

9.15

20.6

031

3.70

7.97

10.5

041

.83

54.0

072

.83

58.0

067

.42

26.1

765

.06

1.65

440.

6811

.19

619.

7015

.70

812.

5720

.60

670.

4017

.03

773.

2319

.60

252.

456.

415.

4236

.75

51.6

767

.75

55.8

364

.42

21.0

08.

570.

2238

4.19

9.75

598.

6115

.20

756.

0919

.20

651.

2316

.50

743.

0318

.90

195.

965.

000.

7532

.00

49.9

263

.00

54.2

561

.92

16.3

3−4

4.48

−1.1

333

1.15

8.41

583.

1114

.80

703.

0617

.90

637.

2816

.20

717.

5818

.20

142.

923.

63−3

.67

27.5

848

.58

58.5

853

.08

59.8

311

.92

−95.

13−2

.41

280.

494.

5057

2.60

14.5

065

2.42

16.6

062

7.87

15.9

069

6.18

17.7

092

.26

2.34

−7.9

223

.00

47.7

554

.33

52.3

358

.00

7.67

−144

.29

−3.6

723

1.34

5.88

566.

6414

.40

603.

2815

.30

622.

5415

.80

678.

3917

.20

43.1

11.

09−1

2.00

19.2

547

.25

50.2

551

.92

56.5

03.

58−1

92.1

4−4

.90

182.

884.

6556

5.00

14.3

555

4.84

14.1

062

1.07

15.7

866

3.97

16.9

0−5

.35

−0.1

4−1

6.00

15.2

547

.08

46.2

551

.75

55.3

3−0

.42

STE

ER

ING

AN

GLE

(DE

GR

EE

S)

R−1

INN

ER

GE

AR

R−2

OU

TER

GE

AR

R−3

NO

SE

GE

AR

R−4

WIN

GTI

PR

−5N

OS

ER

−6TA

ILD

IME

NS

ION

"C"

5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 85 90

in. ft

min

. ftm

in. ft

min

. ftm

in. ft

min

. ftm

in. ft

m

STE

ER

ING

TOW

ING

The

actu

al o

pera

ting

data

will

be

grea

ter t

han

the

valu

es s

how

n be

caus

e tir

e sl

ippa

ge is

not

con

side

red.

The

airp

ort p

lann

er m

ust c

onsu

lt w

ith th

e us

er a

irlin

e fo

r spe

cific

ope

ratin

g pr

oced

ures

.

NO

TE

brb3

9a01

.dg,

pt,

06/0

8/98


TURNING RADII DATA (NO SLIP ANGLE)


CHAPTER 4Page 3

May 28/2001

MINIMUM TURNING CENTER ON MAIN−AXLE GEAR PROJECTION

brc7

2a01

.dg,

sw

, 17/

01/0

0

NOTES

R−6R−4

R−2

R−3

R−5

R−1

70o

APPROX. 2 DUE TO TIRESLIP

o

84 ft. 5 in. (25.7m)MINIMUM PAVEMENT

WIDTH FOR 180 TURN(WITHOUT BACKING UP)

o

STA. X 443.050

ITEM RADIUS

R−1 INNER GEARR−2 OUTER GEARR−3 NOSE GEAR

R−4 WING TIPR−5 NOSE

R−6 ELEVATOR TIP

4 ft. 9 in. (1.52 m)33 ft. 10 in. (10.32 m)50 ft. 7 in. (15.41 m)64 ft. 9 in. (19.74 m)54 ft. 10 in. (16.73 m)62 ft. 9 in. (19.13 m)

1. Dimensions noted are for dry, hard, level surfaces at these tire pressures :227 psi (loaded), 32 x 8.8−16 standard main−wheel tires, and 89 psi (loaded)for 22 x 6.50−10 standard nose−wheel tires.

2. Nose gear steering limit is approximately 70 left and right.o

3. Slip angle of 2 is approximate only and may vary withaircraft configuration, loading and tire wear.

4. Dimensions given for maneuvering clearance and turningradii are minimum recommended limits.

o

5. Tire pressures shown are for calculation purposes only.Refer to AMM Ch. 12 for service pressures.


TURNING RADIUS AT MINIMUM POWER


CHAPTER 4Page 4

May 28/2001

CL

NOSE GEAR CENTER LINETRACK

MAIN GEAR CENTER LINE TRACKS(PORT & STARBOARD)

PILOT’SSTRAIGHTFORWARDVISIONTRACK

The airport planner must consult withthe user airline for specific operatingprocedures.

NOTE

8.33 ft(2.54 m)

75 ft(22.86 m)

TAXIWAY WIDTH

23.08 ft(7.04 m)

100 ft(30.48 m)RADIUS

ft

m

SCALE0 100

0 10 20 30

25 50 75

brb4

4a01

, gv,

06/

08/9

8

NOSE GEARSTEERING ANGLE: 17.3o

150 ft(45.72 m)

CL

132.42 ft(40.36 m)RADIUS


GREATER THAN 90 DEGREE TURN − RUNWAY TO TAXIWAY WITH TRACKS


CHAPTER 4Page 5

May 28/2001

CL

CL





NOTE

6.17 ft(1.88 m)

75 ft(22.86 m)

TAXIWAY WIDTH

23.08 ft(7.04 m)


ft

m

SCALE0 100

0 10 20 30

25 50 75

brb4

3a01

, gv,

06/

08/9

8

NOSE GEARSTEERING ANGLE: 15o

150 ft(45.72 m)


90 DEGREE TURN − RUNWAY TO TAXIWAY WITH NOSE GEAR AND COCKPIT TRACKS


CHAPTER 4Page 6

May 28/2001

CL

CL




NOSE GEARSTEERING ANGLE: 20


NOTE

8.25 ft(2.51 m)

75 ft(22.86 m)

TAXIWAY WIDTH

23.08 ft(7.04 m)


ft

m

SCALE0 100

0 10 20 30

25 50 75

brb4

2a01

, gv,

06/

08/9

8

75 ft(22.86 m)

TAXIWAY WIDTH

o


90 DEGREE TURN − TAXIWAY TO TAXIWAY WITH NOSE GEAR AND COCKPIT TRACKS


CHAPTER 4Page 7

May 28/2001

(PORT & STARBOARD)


75 ft(22.86 m)

TAXIWAY WIDTH

ftm

SCALE0 1000 10 20 30

25 50 75

CL

CL

MAIN GEARCENTER LINE TRACKS

38 ft (11.58 m)MINIMUMCLEARANCE OFMOVING AIRCRAFT

HOLDINGAPRON

23 ft (7.01 m)MIN.

20 ft (6.10 m)MIN.

150 ft(45.72 m)

RUNWAY WIDTH

20 ft (6.10 m)MIN.

brc4

7a01

.dg,

pt,

30/0

3/01


RUNWAY HOLDING BAY (APRON)


CHAPTER 4Page 8

May 28/2001

br99

7a01

.dg,

sw

/gw

, aug

9/20

07

1. Left MLG similar.2. Protect gear with foam rubber

or clean cotton cloths, etc.

NOTES

1. Protective spool.2. Rope.3. Attachments rings.

LEGEND

1

2

AFT

R.H. GEAR

CL

INBOARD APPROX. 40 in.(1 m)

APPROX. 80 in.(2 m)

APPROX. 80 in.(2 m)

3

3

2

2


AIRCRAFT TIE DOWN PROVISIONS (Sheet 1 of 2)


CHAPTER 4Page 9

Dec 05/2014

TOWSPOOLS

BUNGEECORD

APPROX. 3 ft(1 m)

APPROX. 3 ft(1 m)

br99

7a02

.dg,

sw

, 15/

07/9

8


AIRCRAFT TIE DOWN PROVISIONS (Sheet 2 of 2)


CHAPTER 4Page 10

May 28/2001

CHAPTER 5

TERMINAL SERVICING



General Information

1. This chapter supplies ground service information for the Dash−8 Series 400.

A. A typical servicing arrangement (no APU) is shown in Figure 5−1.

B. Terminal operations are shown in Figure 5−2 and Figure 5−3.

C. Locations of ground servicing points are shown in Figure 5−4.

D. Data about the ground service connections is shown in Figure 5−5.

E. The ground−power electrical requirements for engine starting are shown in Figure 5−6.

F. Ground towing requirements are shown in Figure 5−7.

G. Ground air conditioning requirements for pre conditioned airplane are shown in Figure5−8.


Series: 400

CHAPTER 5Page 1

Dec 05/2014

br33

4a01

.dg,

gv/

cs, s

ep09

/201

4

0 5 10 15 20 25

1. Fuel truck.2. Cabin and buffet service vehicle.

LEGEND

3. Ground air−conditioning unit(not required, if optional APU is installed).

4. Tractor with baggage carts.5. Portable stairway.

6. DC electrical−power unit.7. Towing tractor (if required).8. Toilet service vehicle.9. AC electrical−power unit.

(if required, for maintenance activities).

8

7

6

4

9

1

3

2

4

5

m

ft

0 2 4 6 8

SCALE

9

Zone around fuel vents − keep clear during refuelling.

For option 824CH00114, 824SO90105.

NOTES

AIRCRAFT SERVICING ARRANGEMENT (STANDARD CONFIGURATION)


AIRCRAFT SERVICING ARRANGEMENT (TYPICAL − NO APU) (Sheet 1 of 3)


CHAPTER 5Page 2

Dec 05/2014

br33

4a02

.dg,

nn/

cs, s

ep09

/201

4

0 5 10 15 20 25

1. Fuel truck.2. Cabin and buffet service vehicle.

LEGEND

3. Ground air−conditioning unit(not required, if optional APU is installed).

4. Tractor with baggage carts.5. Portable stairway.

6. DC electrical−power unit.7. Towing tractor (if required).8. Toilet service vehicle.9. AC electrical−power unit.

(if required, for maintenance activities).

8

7

6

9

1

3

2

4

5

m

ft

0 2 4 6 8

SCALE

9

AIRCRAFT SERVICING ARRANGEMENT (EXTRA CAPACITY CONFIGURATION)

Zone around fuel vents − keep clear during refuelling.

For option 824CH00114, 824SO90105.

NOTES




CHAPTER 5Page 3

Dec 05/2014

br33

4a03

.dg,

cs,

sep

09/2

014

DC ELECTRICAL POWER MS 3506−1 (AIRCRAFT CONNECTOR);MS 25488 (MATING GROUND CONNECTOR)

AIRCRAFTINTERFACE DETAILS

EQUIPMENTINTERFACE DETAILS

AE9110H AE81617HAE99111H AE81618H8

ADAPTER DUST CAPADAPTERSIZEDESCRIPTION PROTECTIVEPLUG

HYDRAULIC POWER UNIT(PRESSURE)

AE99139J AE81724JAE99140J AE80660J10HYDRAULIC POWER UNIT(RETURN)

AE99149E AE81724EAE99140E AE80660E4HYDRAULIC SERVICING/REPLENISHINGDISPENSER

HYDRAULIC SYSTEM

SYSTEM ADAPTER

PRESSURE REFUELLING MS 24484−2

GROUND AIR CONDITIONING MS 33562 8.00 in. (20.32 cm); RECEPTACLE(OPTIONAL INSTALLATION)

TOILET SERVICING MS 2651−133 ROYLYN ’Y’ DRAIN COUPLINGPLUS STANDARD 1.00 in. (2.54 cm) FILLPORT

GROUND CREW INTERPHONE 300 OHM IMPEDANCE THROAT MICROPHONE WITHSWITCH − AIRCRAFT CONNECTOR72340012−001 (SWITCHCRAFT C−55B);MATING GROUND CONNECTOR PF051B(NATO 4−WAY JACK PLUG)

AC ELECTRICAL POWER CANNON CE9310−10 (AIRCRAFT CONNECTOR)CE9183 (MATING GROUND CONNECTOR)




CHAPTER 5Page 4

Dec 05/2014

0 2 4 6 8 10 12 14 16 18

cg35

02a0

1.dg

, cs,

sep

09/2

014

TIME (MINUTES)ACTIVITY

DESCRIPTIONDEFINITION

Park on ramp

Passengers deplane (fwd door)(aft door)

Refuel

Unload baggage (aft compt.)(fwd compt.)

Service toilet

Housekeeping

Load baggage (aft compt.)(fwd compt.)

Passengers enplane (fwd door)(aft door)

Clear ramp

Park on ramp

Passenger deplane

Refuel

Unload baggage

Service toilet

Housekeeping

Load baggage

Passenger enplane

Clear ramp

Aircraft stops, propellers stop turning, insert chocks.Connect external power and cooling equipment or start APU.

Open forward passenger (airstair) door. Open aft passenger door andposition stairs. Passenger use both doors to deplane with carry−onluggage.

Add fuel for 4 X 200 sm stages.

Remove 1.5 pieces per passenger.

Use standard external servicing−equipment.

Tidy cabin, starting from rear. Service galley.

Load and stack 1.5 pieces per passenger.

Passenger stow carry−on baggage and are seated. Doors are closed.

Disconnect ground, external power and cooling equipment. Startengines and remove chocks.

Forward baggage compartment and forward baggage doorare removed for the extra capacity configuration.

NOTE


RAPID TURNAROUND USING FORWARD AND AFT DOORS


CHAPTER 5Page 5

Dec 05/2014

Forward baggage compartment and forward baggage doorare removed for the extra capacity configuration.

NOTE

0 2 4 6 8 10 12 14 16 18

TIME (MINUTES)ACTIVITY

DESCRIPTIONDEFINITION

Park on ramp

Passengers deplane (fwd door)

Refuel

Unload baggage (aft compt.)(fwd compt.)

Service toilet

Housekeeping

Load baggage (aft compt.)(fwd compt.)

Passengers enplane (fwd door)

Clear ramp

Park on ramp

Passenger deplane

Refuel

Unload baggage

Service toilet

Housekeeping

Load baggage

Passenger enplane

Clear ramp

Aircraft stops, propellers stop turning, insert chocks.Connect external power and cooling equipment or start APU.

Add fuel for 4 X 200 sm stages.

Remove 1.5 pieces per passenger.

Use standard external servicing−equipment.

Tidy cabin, starting from rear. Service galley.

Load and stack 1.5 pieces per passenger.

Passenger stow carry−on baggage and are seated. Doors are closed.

Disconnect ground, external power and cooling equipment. Startengines and remove chocks.

Open forward passenger (airstair) door. Passenger use forwarddoor to deplane with carry−on luggage.

20 22 24

cg35

45a0

1.dg

, cs,

sep

09/2

014


RAPID TURNAROUND USING FORWARD DOOR ONLY


CHAPTER 5Page 6

Dec 05/2014

cg3

539a

01.d

g, c

s, a

ug06

/201

4

31

24

627 8 3 4

19

18

17 15

2621

23

714

1328

9 11

22282026

1918

17 15

12

7

2925 16 30

52

10

32 33 1

0 5 10 15 20 25

SCALE (FT)

1

34

7

GROUND SERVICING POINT LOCATIONS (STANDARD CONFIGURATION)


GROUND SERVICING POINT LOCATIONS (Sheet 1 of 4)


CHAPTER 5Page 7

Dec 05/2014

cg35

39a0

2.dg

, cs,

aug

06/2

014

1. Forward passenger door.2. Aft baggage door.3. Forward baggage door.4. Type II/III emergency exit.5. Aft passenger door.6. Flight compartment emergency exit.7. Interphone connectors (3).8. Lavatory service/ optional wash water service.9. Galley service door/type I emergency exit.

10. Optional auxiliary power unit (APU).11. Optional conditioned air connection. 12. Electrical DC power receptacle.13. Electrical AC power receptacle (optional installation on right nose fuselage).14. Pressure refueling panel and ground point.15. Ground point (overwing−both sides).16. Aircraft ground point (on undercarriage−both sides).17. Gravity fuel filler (over wing−both sides).18. Magnastick (fuel quantity−underwing−both sides).19. Engine oil filler panel.20. No.1 Hydraulic system.21. No.2 Hydraulic system.22. No.3 Hydraulic system.23. Brake accumulator and hydraulic hand pump.24. Emergency landing gear hydraulic reservoir and hand pump.25. Nose landing gear shock strut charging point.26. Main landing gear shock strut charging point (under nacelle−both sides).27. Nose jacking point.28. Wing jacking point (underwing−both sides).29. Nose landing gear jacking point.30. Main landing gear jacking point (both sides).31. Crew oxygen supply.32. Avionics bay.33. Wardrobe.

LEGEND

34. Optional galley water service.

GROUND SERVICING POINT LOCATIONS (STANDARD CONFIGURATION)




CHAPTER 5Page 8

Dec 05/2014

cg3

539a

01.d

g, c

s, s

ep09

/201

4

30

23

526 7 3

18

17

16 14

2520

22

613

1227

8 10

21271925

1817

16 14

11

6

2824 15 29

42

9

31 32 1

0 5 10 15 20 25

SCALE (FT)

1

33

6

GROUND SERVICING POINT LOCATIONS (EXTRA CAPACITY CONFIGURATION)




CHAPTER 5Page 9

Dec 05/2014

cg35

39a0

4.dg

, cs,

sep

09/2

014

1. Forward passenger door.2. Aft baggage door.3. Forward type I emergency exit door.4. Aft passenger door.5. Flight compartment emergency exit.6. Interphone connectors (3).7. Lavatory service/ optional wash water service..8. Galley service door/type I emergency exit.9. Optional auxiliary power unit (APU).

10. Optional conditioned air connection. 11. Electrical DC power receptacle.12. Electrical AC power receptacle (optional installation on right nose fuselage).13. Pressure refueling panel and ground point.14. Ground point (overwing−both sides).15. Aircraft ground point (on undercarriage−both sides).16. Gravity fuel filler (over wing−both sides).17. Magnastick (fuel quantity−underwing−both sides).18. Engine oil filler panel.19. No.1 Hydraulic system.20. No.2 Hydraulic system.21. No.3 Hydraulic system.22. Brake accumulator and hydraulic hand pump.23. Emergency landing gear hydraulic reservoir and hand pump.24. Nose landing gear shock strut charging point.25. Main landing gear shock strut charging point (under nacelle−both sides).26. Nose jacking point.27. Wing jacking point (underwing−both sides).28. Nose landing gear jacking point.29. Main landing gear jacking point (both sides).30. Crew oxygen supply.31. Avionics bay.32. Wardrobe.

LEGEND

33. Optional galley water service.

GROUND SERVICING POINT LOCATIONS (EXTRA CAPACITY CONFIGURATION)




CHAPTER 5Page 10

Dec 05/2014

SYSTEM DISTANCE FROMAIRCRAFT

CENTER LINE

LEFT SIDE RIGHT SIDE

HEIGHTFROM

GROUND

DISTANCEAFT OF NOSE

Ester Based Hydraulic−Fluid)

3 Service Points

−Access door on inboard L/Hnacelle for No. 1 Hyd. System(reservoir capacity is 8 U.S.quarts, (7.57 L)

−Access door on inboard R/Hnacelle for No. 2 Hyd. System(reservoir capacity is 12 U.S.quarts, (11.35 L)

Hydraulic System (Phosphate−

−No. 3 Hyd. System reservoir(located in aft fuselage,2 U.S. quarts, 1.89 L)

Electrical System

Oxygen System

2 Service Connections

−28 volt DC External PowerReceptacle (capacity is 550 Acontinuous, 2000 A peak)

−Charging valve for one 39.8 ft(1100 L) Capacity CrewSupply (in nose compartment)

3

Three 11.0 ft (311L)portable passengercylinders

One 11.0 ft (311L)first−aid portable cylinder(optional)

3

3

52 ft2 in.

15.9 m 12 ft 11 in.

3.94 m 8 ft8 in.

2.64 m

15 ft 11 in.

4.85 m52 ft2 in.

15.9 m 8 ft8 in.

2.64 m

90 ft8 in.

27.6 m 1 ft8 in.

50.1 cm 7 ft8 in.

2.34 m

4 ft11 in.

1.51 m 2 ft6 in.

75.2 cm 3 ft10 in.

1.16 m

51 ft11 in.

15.8 m 12 ft11 in.

3.94 m 8 ft3 in.

2.52 m

4 ft6 in.

1.37 m 1 ft7 in.

48.3 cm 4 ft0 in.

1.22 m

FT M FT M FT M FT M

br88

7a01

.dg,

sw

/cm

, nov

13/2

013

Nacelle Location−115/200 volt A/C ExternalPower Receptacle (capacity is20 KVA MIN.,3−PH.,400Hz)

These measurements are approximate.

These measurements are approximate and will varywith aircraft configuration and loading conditions.

NOTES

Nose Fuselage Location−115/200 volt A/C ExternalPower Receptacle (capacity is20 KVA MIN.,3−PH.,400Hz)

3 ft10 in.

1.16 m

1 Service Connection

4 ft11 in.

1.51 m 2 ft6 in.

75.2 cm

For option 824CH00114 and 824SO90105.


GROUND SERVICE CONNECTIONS DATA (Sheet 1 of 3)


CHAPTER 5Page 11

Dec 05/2014


CENTER LINE


HEIGHTFROM

GROUND

DISTANCEAFT OF NOSE


These measurements are approximate and will vary with aircraft configuration and loading conditions.

br88

7a02

.dg,

sw

, 09/

06/9

8

FT M FT M FT M FT M

Fuel System

Landing Gear System

3 Service Points

−One Single−PointRefuel/Defuel Adapter(on Refuel/Defuel Panel)

−Two over−wing GravityFilling−Points(one on each wing)

−2 pairs of Fuel Vents(one pair under each wing)

3 Servicing Points (Nitrogen)

−One Shock−Strut Valve on eachMain Gear

−One Shock−Strut Valve onNose Gear

−Charging Valve for ParkingBrake Accumulator (behindaccess panel on R/H fuselage atwing root).

1 Servicing Point (Phosphate−EsterBased Hydraulic−Fluid).

−Filling Point for reservoirof Alternate Landing−GearExtension−System(in nose compartment)(1 U.S. quarts, 0.95 L)

58 ft7 in.

49 ft1 in.

49 ft0 in.

51 ft9 in.

6 ft2 in.

52 ft4 in.

4 ft6 in.

17.8 m

14.9 m

14.9 m

15.8 m

1.88 m

15.9 m

1.37 m

33 ft1 in.

34 ft8 in.

14 ft5 in.

10.1 m

10.6 m

4.40 m

14 ft5 in.

33 ft1 in.

34 ft8 in.

14 ft5 in.

3 ft11 in.

2 ft4 in.

4.40 m

10.1 m

10.6 m

4.40 m

1.08 m

71.1 cm

7 ft3 in.

12 ft11 in.

12 ft4 in.

4 ft9 in.

2 ft10 in.

10 ft11 in.

3 ft7 in.

2.22 m

3.94 m

3.75 m

1.44 m

87.5 cm

3.33 m

1.10 m




CHAPTER 5Page 12

Dec 05/2014


CENTER LINE


HEIGHTFROM

GROUND

DISTANCEAFT OF NOSE


These measurements are approximate and will vary with aircraft configuration and loading conditions.

br88

7a03

.dg,

sw

, 09/

06/9

8

FT M FT M FT M FT M

Air Conditioning System

Toilet

Oil

1 Air−Conditioning groundconnection (optional)

−One 8 inch (20.3 cm)receptacle (on R/H side ofaft fuselage)

1 Service Point

−1 Service connection onLavatory Service Panel(capacity of toilet flushreservoir is 3.3 U.S. gallons(13 L))

2 Servicing Points

−Oil Filter behind access dooron L/H side of each nacelle(tank capacity is 5.9 U.S.gallons (22.3 L)

86 ft4 in.

14 ft1 in.

40 ft11 in.

26.3 m

4.29 m

12.5 m 15 ft11 in.

4.85 m

1 ft9 in.

2 ft9 in.

12 ft11 in.

54.2 cm

82.5 cm

3.94 m

6 ft5 in.

3 ft1 in.

9 ft7 in.

1.96 m

93.2 cm

2.91 m




CHAPTER 5Page 13

Dec 05/2014

br29

9a01

.dg,

pt/a

k, a

pr04

/201

3

28

1200−1400

600−800

400

2−3

560

NOMINAL STARTINGVOLTAGE (VDC)

ENGINE START CURRENT REQUIREDFROM GROUND DC POWER

CART ( AMPS )

CORRESPONDING DURATION OFCRANKING (SECONDS)

CONDITIONS AT TYPICAL ENGINE START

12

3

4

5

6

56

1. External DC power receptacle.2. Battery installation.3. DC contactor box (includes start

control relays).4. Overhead console panel.5. Ignition box.6. Starter generator.

LEGEND

NOTE: SET THE GROUND DC POWER CART LIMIT TO 1500 AMPS MINIMUM.


ELECTRICAL REQUIREMENTS FOR ENGINE STARTING


CHAPTER 5Page 14

Dec 05/2014

brc7

3a01

.dg,

sw

, 18/

01/0

0

EXAMPLE :

0

1

2

3

4

5

6

7

0 2 4 6 8 10

1 2 3 4 5

.5

1.0

1.5

2.0

2.5

3.0

1000

KG

.

1000 KG

0 1 2 3 4

RUNWAY SLOPE (PERCENTAGE)

EXAMPLE

AIRCRAFT GROSS

MAX. DESIGN TAXI WEIGHT64,700 lb. (29,347 kg)

ASSOCIATED CONDITIONS1. UNUSUAL BREAKWAY CONDITIONSNOT REFLECTED.2. ESTIMATED FOR TOW VEHICLEWITH RUBBER TIRES.3. COEFFICIENT OF FRICTION ( u )APPROXIMATE.

u

60,000 lb (27,211 kg)

50,000 lb (22,676 kg)

40,000 lb (18,141 kg)

30,000 lb (13,605 kg)

At an aircraft gross weight of 50,000 lb (22,676 kg), an uphill slopeof 2 % and with a wet concrete surface, the coresponding draw bar pullor push required is 3,000 lb (1,360 kg) and the total traction wheelload is 5,250 lb (2,381 kg).

DR

Y C

ON

CR

ETE

=

0.80

WET

ASP

HAL

T =

0.7

5

SNOW C

HAINS

= 0.4

5

WET

CONCRETE

=

0.57

HARD SNOW = 0.20

ICE = 0.05

u

u

uu

u

u

12

TOTAL TRACTION WHEEL LOAD (x 1000 lb)

DR

AW

BA

R P

UL

L (

x 10

00 lb

)

64,700 lb (29,347 kg)

WEIGHT


GROUND TOWING REQUIREMENTS


CHAPTER 5Page 15

Dec 05/2014

0.6

0.5

0.4

0.3

0.2P

RE

SS

UR

E P

SI

DU

CT

ICIN

G L

IMIT

INC

HE

S O

F W

AT

ER

−20 20 40 60 80 10000

5

15

20

25

INLET TEMPERATURE − C

INLET TEMPERATURE − F200 40 60 80 100 120 140 160 180 200

10

DU

CT

OV

ER

HE

AT

CA

UT

ION

brbs

23a0

1.dg

, km

w, j

ul30

/201

4

2.8

0.7

30

Acceptable limitswithin shaded area.

NOTE37

1.08

71

0.1

0.8

0.9

1.0


GROUND AIR CONDITIONING REQUIREMENTS − PRE CONDITIONED AIR


CHAPTER 5Page 16

Dec 05/2014

CHAPTER 6

OPERATING CONDITIONSAND NOISE DATA



General Information

1. Aircraft operating conditions and noise are important to airport and community planners. Whilean airport is a major element in an community transportation system and is vital to its growth,it must be a good neighbor. This can only be accomplished with proper planning. Becauseaircraft noise extends beyond the boundaries of the airport, it is vital to consider the impact onsurrounding communities.

2. The Dash−8, Series 400 aircraft is designed with advanced, quiet, turboprop technology. Itsnoise impact is minimal compared to most aircraft, larger and smaller, currently beingoperated in a typical airport.

3. To help the airport planner to estimate the impact of the Dash−8 Series 400 on airportoperations, the following material is provided:

A. Engine Exhaust Temperature Contours

(1) Data on the exhaust temperature contours at ground idle, flight idle and take−offpower settings are shown in Figure 6−1, Figure 6−2, Figure 6−3, Figure 6−4,Figure 6−5 and Figure 6−6.

B. Airport and Community Noise Data for Powerplants

(1) Data on the takeoff and landing noise footprints for the PW150A powerplants areshown in Figure 6−7 and Figure 6−8.

(2) The Dash−8, Series 400 complies with the Stage 3 noise−level limits under thetrade−off clause specified in FAR 36, Section C36.5b and also under AWM 516and JAR 36 standards. A summary of the certified noise levels, measured andcorrected to these standards, is shown in the table that follows:

FAR 36 Stage 3Noise Limit(EPNdB)

Dash−8 Series 400Noise Level(EPNdB) Margin (EPNdB)

Take−off 89 78.3 +10.7Lateral 94 84.2 +9.8Approach 98 94.9 +3.1

C. Community Noise Data for Optional APU

(1) The results of ramp noise tests for the optional APU are shown in Figure 6−9.

NOTE: Exhaust temperature contours for the optional APU is not available at this time.

D. Propeller/Engine Slipstream Velocity Contours

(1) Data on the Propeller/Engine slipstream velocity contours as on ground (18% and43% torque) and at maximum takeoff power settings are shown in Figure 6−10,and Figure 6−11


Series: 400

CHAPTER 6Page 1

Dec 05/2014

TO

P V

IEW

− G

RO

UN

D ID

LE

020

4060

8010

012

014

0

DIS

TAN

CE

DO

WN

STR

EA

M F

RO

M N

OZZ

LES

(ft)

EXHAUST NOZZLES (ft)−80−60−40−20020406080

AS

SO

CIA

TED

CO

ND

ITIO

NS

:

1. A

LL T

EM

PE

RA

TUR

ES

IN

C.

2. S

EA

LE

VE

L, Z

ER

O W

IND

, IS

A D

AY

.3.

660

RP

M N

P.

4. Z

ER

O P

RO

PE

LLE

R P

RE

SS

UR

E R

ISE

A

SS

UM

ED

.

o

brn1

0a01

.dg,

sw

/km

w, o

ct02

/201

3

4050

6070

8010

015

0

AIR

CR

AFT

SY

MM

ETR

Y P

LAN

E


ENGINE EXHAUST TEMP. CONTOURS AT GROUND IDLE − TOP VIEW


CHAPTER 6Page 2

Dec 05/2014

SID

E V

IEW

− G

RO

UN

D ID

LE

020

4060

8010

012

014

0

DIS

TAN

CE

DO

WN

STR

EA

M F

RO

M N

OZZ

LES

(ft)

EXHAUST NOZZLES (ft)01020304050607080

GR

OU

ND

40

50

60

70

80

100

150

AS

SO

CIA

TED

CO

ND

ITIO

NS

:

1. A

LL T

EM

PE

RA

TUR

ES

IN

C.

2. S

EA

LE

VE

L, Z

ER

O W

IND

, IS

A D

AY

.3.

660

RP

M N

P.

4. Z

ER

O P

RO

PE

LLE

R P

RE

SS

UR

E R

ISE

A

SS

UM

ED

.

o

brn0

9a01

.dg,

sw

/gw

, may

5/20

11


ENGINE EXHAUST TEMP. CONTOURS AT GROUND IDLE − SIDE VIEW


CHAPTER 6Page 3

Dec 05/2014

TO

P V

IEW

− F

LIG

HT

IDL

E

020

4060

8010

012

014

0

DIS

TAN

CE

DO

WN

STR

EA

M F

RO

M N

OZZ

LES

(ft)


AS

SO

CIA

TED

CO

ND

ITIO

NS

:

1. A

LL T

EM

PE

RA

TUR

ES

IN

C.

2. S

EA

LE

VE

L, Z

ER

O W

IND

, IS

A D

AY

.3.

660

RP

M N

P.

4. Z

ER

O P

RO

PE

LLE

R P

RE

SS

UR

E R

ISE

A

SS

UM

ED

.

o

brn0

8a01

.dg,

sw

/km

w, o

ct02

/201

3

4050

6070

8010

015

0

AIR

CR

AFT

SY

MM

ETR

Y P

LAN

E


ENGINE EXHAUST TEMP. CONTOURS AT FLIGHT IDLE − TOP VIEW


CHAPTER 6Page 4

Dec 05/2014

SID

E V

IEW

− F

LIG

HT

IDL

E

020

4060

8010

012

014

0

DIS

TAN

CE

DO

WN

STR

EA

M F

RO

M N

OZZ

LES

(ft)


GR

OU

ND

40

50

60

70

80

100

150

AS

SO

CIA

TED

CO

ND

ITIO

NS

:

1. A

LL T

EM

PE

RA

TUR

ES

IN

C.

2. S

EA

LE

VE

L, Z

ER

O W

IND

, IS

A D

AY

.3.

660

RP

M N

P.

4. Z

ER

O P

RO

PE

LLE

R P

RE

SS

UR

E R

ISE

A

SS

UM

ED

.

o

brn0

7a01

.dg,

sw

/gw

, may

9/20

11


ENGINE EXHAUST TEMP. CONTOURS AT FLIGHT IDLE − SIDE VIEW


CHAPTER 6Page 5

Dec 05/2014

TO

P V

IEW

− M

AX

. TA

KE

−OF

F

020

4060

8010

012

014

0D

ISTA

NC

E D

OW

NS

TRE

AM

FR

OM

NO

ZZLE

S (f

t)


AS

SO

CIA

TED

CO

ND

ITIO

NS

:

1. A

LL T

EM

PE

RA

TUR

ES

IN

C.

2. S

EA

LE

VE

L, Z

ER

O W

IND

, IS

A D

AY

.3.

100

% N

P.

4. Z

ER

O P

RO

PE

LLE

R P

RE

SS

UR

E R

ISE

AS

SU

ME

D.

o

brn0

6a01

.dg,

sw

, 29/

09/9

9

4050

6070

8010

015

0

AIR

CR

AFT

SY

MM

ETR

Y P

LAN

E


ENGINE EXHAUST TEMP. CONTOURS AT MAX. T.O. POWER − TOP VIEW


CHAPTER 6Page 6

May 28/2001

SID

E V

IEW

− M

AX

. TA

KE

−OF

F

020

4060

8010

012

014

0

DIS

TAN

CE

DO

WN

STR

EA

M F

RO

M N

OZZ

LES

(ft)


GR

OU

ND

40

50

60

70

80

100

150

AS

SO

CIA

TED

CO

ND

ITIO

NS

:

1. A

LL T

EM

PE

RA

TUR

ES

IN

C.

2. S

EA

LE

VE

L, Z

ER

O W

IND

, IS

A D

AY

.3.

100

% N

P.

4. Z

ER

O P

RO

PE

LLE

R P

RE

SS

UR

E R

ISE

A

SS

UM

ED

.

o

brn0

5a01

.dg,

sw

, 21/

09/9

9


ENGINE EXHAUST TEMP. CONTOURS AT MAX. T.O. POWER − SIDE VIEW


CHAPTER 6Page 7

Dec 05/2014

brn1

1a01

.dg,

sw

, 30/

09/9

9

HEIGHT ABOVERUNWAY − 1000 FT

DISTANCE TO SIDE1000 − FT

DIS

TAN

CE

FR

OM

RU

NW

AY

TH

RE

SH

OLD

− 1

000

FT

76

54

32

10

12

34

56

7

2520

1510

50

510

1520

25

00

2 2 20

DIS

TAN

CE

FR

OM

RU

NW

AY

TH

RE

SH

OLD

− 1

000

M

70 75

8085

1000

m

1000

m

1000

m

3 D

EG

RE

ES

AP

PR

OA

CH

AT

850

RP

M35

DE

G. F

LAP

S

15.8

1 %

TA

KE

OFF

GR

AD

IEN

TA

T 10

20 R

PM

9.2

%C

LIM

B G

RA

DIE

NT

AT

MA

X. C

LIM

B P

OW

ER

NO

ISE

LE

VE

L (d

BA

)70 75 80 85

AR

EA

EN

CLO

SE

D

(SQ

. MIL

ES

)2.

677

1.26

20.

575

0.27

1

(SQ

. KM

)

6.93

33.

269

1.49

00.

702

AS

SO

CIA

TED

CO

ND

ITIO

NS

:1.

SE

A L

EV

EL.

ISA

+ 1

0 C

., ZE

RO

WIN

D.

2. T

AK

EO

FF W

T. −

63,

250

lb (2

8,75

0 kg

).3.

LA

ND

ING

WT.

− 6

1,25

0 lb

(27,

841

kg).

1 in

. = 6

000

ft.

oS

CA

LE:

CU

TBA

CK

ALT

ITU

DE

1000

ft

0


TAKEOFF AND LANDING NOISE FOOTPRINT − 3 DEGREE APPROACH


CHAPTER 6Page 8

May 28/2001

brn1

2a01

.dg,

sw

, 01/

10/9

9

HEIGHT ABOVERUNWAY − 1000 FT

DISTANCE TO SIDE1000 − FT

DIS

TAN

CE

FR

OM

RU

NW

AY

TH

RE

SH

OLD

− 1

000

FT

76

54

32

10

12

34

56

7

2520

1510

50

510

1520

25

00

2 2 20

DIS

TAN

CE

FR

OM

RU

NW

AY

TH

RE

SH

OLD

− 1

000

M

70 75

8085

1000

m

1000

m

1000

m

4 D

EG

RE

ES

AP

PR

OA

CH

AT

1020

RP

M35

DE

G. F

LAP

S

15.8

1 %

TA

KE

OFF

GR

AD

IEN

TA

T 10

20 R

PM

9.2

%C

LIM

B G

RA

DIE

NT

AT

MA

X. C

LIM

B P

OW

ER

NO

ISE

LE

VE

L (d

BA

)70 75 80 85

AR

EA

EN

CLO

SE

D

(SQ

. MIL

ES

)2.

381

1.14

90.

529

0.25

2

(SQ

. KM

)

6.16

62.

975

1.36

90.

652

AS

SO

CIA

TED

CO

ND

ITIO

NS

:1.

SE

A L

EV

EL.

ISA

+ 1

0 C

., ZE

RO

WIN

D.

2. T

AK

EO

FF W

T. −

63,

250

lb (2

8,75

0 kg

).3.

LA

ND

ING

WT.

− 6

1,25

0 lb

(27,

841

kg).

1 in

. = 6

000

ft.

oS

CA

LE:

CU

TBA

CK

ALT

ITU

DE

1000

ft

0


TAKEOFF AND LANDING NOISE FOOTPRINT − 4 DEGREES APPROACH


CHAPTER 6Page 9

May 28/2001

braa

9a01

.dg,

ab/

cs, j

ul30

/201

4

1 29

4

3302

65.6 ft(20.0 m)

65.6 ft(20.0 m)

21 22 23 24 25

20

19

18

17

16

15

14

13

12 11 10

26

27

28

5

6

7

8

9

(FWDPAX

DOOR)

(AFTPAX

DOOR)

(AFTBAGG.DOOR)

(REFUELING)

(GALLEYSERVICEDOOR)

APU / ECS NOISE READINGSPOSITION dB(A) POSITION dB(A)

123456789

101112131415

708479827981828384858483828382

161718192021222324252627282930

807876747268666367697275777378

OPERATING CONDITIONSAir conditioning packs operating : 2APU shaft speed : 100% or 64,154 RPMAPU normal rated speed : 64,154 RPMAPU shaft load : 65% or 260 Amps (100%=400 Amps)Pneumatic load : 36.3 kg/minAPU exhaust gas temperature : 1,173 CACM operating mode : maximum coolingRecirculation fan : on

o

(FWD BAGG. DOOR/FWD

TYPE IEMERGENCYEXIT DOOR)

Forward type I emergency exit door is installed only on aircraft with extra capacity configuration.NOTE


RAMP NOISE TEST RESULTS FOR OPTIONAL APU


CHAPTER 6Page 10

Dec 05/2014

cg28

66a0

1.dg

, ms,

aug

30/2

013

100 200 300 400 500 600 700 800

200

100

0

−100

−200

−300

PROPELLER/ENGINE SLIPSTREAM VELOCITY CONTOURS(MAXIMUM TAKEOFF POWER)

DIS

TAN

CE

FR

OM

AIR

CR

AFT

CE

NTE

RLI

NE

(FT)

DISTANCE DOWNSTREAM PROPELLER PLANE (FT)

160 ft/sec

20 ft/sec

40 ft/sec60 ft/sec80 ft/sec

100 ft/sec

120 ft/sec

140 ft/sec


PROPELLER / ENGINE SLIPSTREAM VELOCITY CONTOUR AT MAXIMUM TAKEOFF POWER


CHAPTER 6Page 11

Dec 05/2014

cg28

65a0

1.dg

, ms,

aug

30/2

013

PROPELLER/ENGINE SLIPSTREAM VELOCITY CONTOURS (~18% TORQUE)(STATIONARY ON GROUND)

100

0

−100

100 200 300

PROPELLER/ENGINE SLIPSTREAM VELOCITY CONTOURS (~43% TORQUE)(STATIONARY ON GROUND)

100 200 300 400 500

100

0

−100

−200


DIS

TAN

CE

FR

OM

AIR

CR

AFT

CE

NTE

RLI

NE

(FT)


DIS

TAN

CE

FR

OM

AIR

CR

AFT

CE

NTE

RLI

NE

(FT)

50 ft/sec 40 ft/sec 30 ft/sec 25 ft/sec 20 ft/sec

20 ft/sec30 ft/sec60 ft/sec

50 ft/sec

40 ft/sec

70 ft/sec90 ft/sec

80 ft/sec


PROPELLER / ENGINE SLIPSTREAM VELOCITY CONTOUR AS ON GROUND


CHAPTER 6Page 12

Dec 05/2014

CHAPTER 7

PAVEMENT DATA



General Information

1. The pavement requirements for commercial aircraft are customarily derived from the staticanalysis loads imposed on the main landing−gear wheels and tires through the shock struts.

A. Basic data on the landing−gear footprint configuration, maximum−design taxi loads, andtire sizes and pressures are shown in Figure 7−1.

B. Maximum pavement loads for certain critical conditions at the tire−ground interfaces areshown in Figure 7−2.

C. Landing−gear loading on pavement at various aircraft weights is shown in Figure 7−3.

D. The California Bearing Ratio (CBR) for unlimited commercial use at all aircraft weights isshown in Figure 7−4 and Figure 7−5.

E. The minimum Load Classification Number (LCN) for flexible and rigid pavement areshown in Figure 7−6, Figure 7−7, Figure 7−8 and Figure 7−9.

F. The minimum Aircraft Classification Number (ACN) for flexible and rigid pavement areshown in Figure 7−10, Figure 7−11, Figure 7−12 and Figure 7−13.

2. Make sure that all runways or pavements to be used meet these minimum CBR, LCN andACN requirements.


Series: 400

CHAPTER 7Page 1

May 28/2001

brc7

4a01

.dg,

gg/

sw, 1

8/01

/00

MAXIMUM DESIGN TAXI WEIGHT

PERCENTAGE WEIGHT ON MAIN GEAR

NOSE−GEAR TIRE SIZE

NOSE−GEAR TIRE PRESSURE

MAIN−GEAR TIRE SIZE

MAIN−GEAR TIRE PRESSURE

64,700 lb(29,347 kg)

(REFER TO LANDING GEAR LOADING ON

22 x 6.50 − 10

85 PSI (586 kPa) UNLOADED89 PSI (614 kPa) LOADED

32 x 8.8 −16 STANDARD34 x 10.75 − 16 OPTIONAL

STD − 218 PSI (1503 kPa) UNLOADED227 PSI (1565 kPa) LOADED

OPT − 135 PSI (931 kPa) UNLOADED141 PSI (972 kPa) LOADED

PAVEMENT ILLUSTRATION)

15.0 in.(38.1 cm)

19.54 in.(49.63 cm)OPTIONAL

21.0 in.(53.34 cm)STANDARD

45 ft 9 in.(13.94 m)

28 ft 10 in.(8.8 m)

NOTE

Tire pressures shown are for calculation purposes only.Refer to AMM Ch. 12 for service pressure.


LANDING GEAR FOOTPRINT


CHAPTER 7Page 2

May 28/2001

brc7

5a01

.dg,

pt/s

w, 1

8/01

/00

MODEL

402

MAXIMUMDESIGNTAXI

WEIGHT

64,700 lb(29,347 kg)

STATIC(AT MOST

FORWARDC.G.)

6458 lb(2929 kg)

STATIC + BRAKINGAT 10 ft/sec(3.05 m/sec )

DECELERATION

(5514 kg)

MAXIMUMLOAD

OCCURRING ATSTATIC AFT C.G.

30,169 lb(13,682 kg)

AT STEADYBRAKING OF

10 ft/sec(3.05 m/sec )

DECELERATION

9369 lb(4249 kg)

ATINSTANTANEOUS

BRAKING(COEFFICIENT

OF FRICTION 0.8)

24,135 lb(10,946 kg)

VNG

22 2

2

MG (PER STRUT) HV (PER STRUT)

1

2

NOTES:

All loads calculated using aircraft Maximum Design Taxi Weight.V = Maximum Vertical Nose−Gear Ground Load at Most Forward C.G..V = Maximum Vertical Main−Gear Ground Load at Most Aft C.G..H = Maximum Horizontal Ground Load from Braking.

Upper C.G. limit is approximately 12.77 ft (3.89 m) above ground line.

Maximum main−gear horizontal−force excludes the alleviating effect of nose−gear rolling friction.

Instantaneous braking applied during a steady braking run.3

NG

MG

VNG MG

H

V

32

1

12,159 lb


MAXIMUM PAVEMENT LOADS


CHAPTER 7Page 3

May 28/2001

brr3

9a01

.dg,

sw

, 24/

01/0

0

10 20 40

30

40

45

50

55

60

65

70

85.00 95.00 100.00

30

10 20 403090.00

35

30

40

45

50

55

60

65

70

35

61,75O LB

53,000 LB

45,000 LB

35,000 LB

64,700 LB

PERCENT MAC

PERCENT OF WEIGHT ON MAIN GEAR

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(X 1

000

LB)

AIR

CR

AFT

GR

OS

S W

EIG

HT

(X 1

000

LB)

NOTEUnshaded area represents operational limits.


LANDING GEAR LOADING ON PAVEMENT


CHAPTER 7Page 4

May 28/2001

1. Tires are 32 x 8.8−16 (21.0 in. centers), inflated to 227 psi (1565 kPa), loaded.2. Tire pressure is for calculation purposes only, refer to AMM Ch 12 for service pressures.3. Max. Aft C.G. (36% MAC at approx. 94% of weight on MLG).4. U.S. Army Corps of Engineers design method (S−77−1) and FAA design method used.

NOTES

bre5

7a01

.dg,

sw

, 19/

01/0

0

ANNUAL DEPARTURES

3 5 10 20 30

AIRCRAFT WEIGHT64,700 LB55,000 LB45,000 LB35,000 LB

(20 YEAR PAVEMENT LIFE)1,2003,0006,00015,00025,000

3 5 10 20 30

CALIFORNIA BEARING RATIO (CBR)

FLEXIBLE PAVEMENT THICKNESS (INCHES)


FLEXIBLE PAVEMENT REQUIREMENTS − CBR (32X8.8−16 TIRES)


CHAPTER 7Page 5

May 28/2001

3 5 10 20 30

AIRCRAFT WEIGHT64,700 LB55,000 LB45,000 LB35,000 LB

3 5 10 20 30

CALIFORNIA BEARING RATIO (CBR)

FLEXIBLE PAVEMENT THICKNESS (INCHES)

1. Tires are 34 x 10.75−16 (19.5 in. centers), inflated to 141 psi (972 kPa), loaded.2. Tire pressure is for calculation purposes only, refer to AMM Ch 12 for service pressures.3. Max. Aft C.G. (36% MAC at approx. 94% of weight on MLG).4. U.S. Army Corps of Engineers design method (S−77−1) and FAA design method used.

NOTES

bre5

8a01

.dg,

sw

, 19/

01/0

0

ANNUAL DEPARTURES(20 YEAR PAVEMENT LIFE)

1,2003,0006,00015,00025,000


FLEXIBLE PAVEMENT REQUIREMENTS − CBR (34X10.75−16 TIRES)


CHAPTER 7Page 6

May 28/2001

brc9

0a01

.dg,

sw

, 19/

01/0

0

AIR

CR

AFT

WE

IGH

T

1050

1020

3040

50

A −

64,

700

LBB

− 5

5,00

0 LB

C −

45,

000

LBD

− 3

5,00

0 LB

2030

409

87

65

NO

TE

S1.

Tire

s ar

e 32

x 8

.8−1

6 (2

1.0

in. c

ente

rs).

2. 2

27 p

si (1

565

kPa)

infla

tion

pres

sure

(loa

ded)

.3.

Tire

pre

ssur

e is

for c

alcu

latio

n pu

rpos

es o

nly,

refe

r to

AM

M C

h 12

for s

ervi

ce p

ress

ures

.4.

Max

. Aft

C.G

. (36

% a

t app

rox.

94%

of w

eigh

t on

MLG

).

30 20 10 5

ESWL (X 1000 LB)

A B C D

30 20 10 5

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R(L

CN

)P

AV

EM

EN

T TH

ICK

NE

SS

(in.

)

EQUIVALENT SINGLE − WHEEL LOAD (ESWL)(X 1000 LB)


FLEXIBLE PAVEMENT REQUIREMENTS − LCN CONVERSION (32X8.8−16 TIRES)


CHAPTER 7Page 7

May 28/2001

brc9

1a01

.dg,

sw

, 19/

01/0

0

ESWL (X 1000 LB)


LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R(L

CN

)P

AV

EM

EN

T TH

ICK

NE

SS

(in.

)

NO

TE

S1.

Tire

s ar

e 34

x 1

0.75

−16

(19.

5 in

. cen

ters

).2.

141

psi

(972

kP

a) in

flatio

n pr

essu

re (l

oade

d).

3. T

ire p

ress

ure

is fo

r cal

cula

tion

purp

oses

onl

y, re

fer t

o A

MM

Ch

12 fo

r ser

vice

pre

ssur

es.

4. M

ax. A

ft C

.G. (

36%

MA

C a

t app

rox.

94%

of w

eigh

t on

MLG

).

1020

3040

82030 10

A B C D

510

2030

4050

8102030

AIR

CR

AFT

WE

IGH

TA

−64,

700

LBB

−55,

000

LBC

−45,

000

LBD

−35,

000

LB


FLEXIBLE PAVEMENT REQUIREMENTS − LCN CONVERSION (34X10.75−16 TIRES)


CHAPTER 7Page 8

May 28/2001

brc9

2a01

.dg,

sw

, 20/

01/0

0

AIR

CR

AFT

WE

IGH

T

A B C D

30 20 10 510

2030

40

A −

64,

700

LBB

− 5

5,00

0 LB

C −

45,

000

LBD

− 3

5,00

0 LB

30 20 10 5

ESWL (X 1000 LB)


RA

DIU

S O

F R

ELA

TIV

E S

TIFF

NE

SS

(L)

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R(L

CN

)

NO

TE

S1.

Tire

s ar

e 32

x 8

.8−1

6 (2

1.0

in. c

ente

rs).

2. 2

27 p

si (1

565

kPa)

infla

tion

pres

sure

(loa

ded)

.3.

Tire

pre

ssur

e is

for c

alcu

latio

n pu

rpos

es o

nly,

refe

r to

AM

M C

h 12

for s

ervi

ce p

ress

ures

.4.

Max

. Aft

C.G

. (36

% M

AC

at a

ppro

x. 9

4% o

f wei

ght o

n M

LG).

1050

100


RIGID PAVEMENT REQUIREMENTS − LCN CONVERSION (32X8.8−16 TIRES)


CHAPTER 7Page 9

May 28/2001

brc9

3a01

.dg,

sw

, 21/

01/0

0

AIR

CR

AFT

WE

IGH

T

A B C D

30 20 10

1050

100

1020

3040

A −

63,

450

LBB

− 5

5,00

0 LB

C −

45,

000

LBD

− 3

5,31

2 LB

30 20 10

ESWL (X 1000 LB)


RA

DIU

S O

F R

ELA

TIV

E S

TIFF

NE

SS

(L)

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R(L

CN

)

NO

TE

S1.

Tire

s ar

e 34

x 1

0.75

−16

(19.

5 in

. cen

ters

).2.

141

psi

(972

kP

a) in

flatio

n pr

essu

re (l

oade

d).

3. T

ire p

ress

ure

is fo

r cal

cula

tion

purp

oses

onl

y, re

fer t

o A

MM

Ch

12 fo

r ser

vice

pre

ssur

es.

4. M

ax. A

ft C

.G. (

36%

MA

C a

t app

rox.

94%

of w

eigh

t on

MLG

).


RIGID PAVEMENT REQUIREMENTS − LCN CONVERSION (34X10.75−16 TIRES)


CHAPTER 7Page 10

May 28/2001

A

B

C

D

AIR

CR

AFT

CLA

SS

IFIC

ATI

ON

NU

MB

ER

(AC

N)

AIRCRAFT GROSS WEIGHT (LBS)

30000 35000 40000 45000 50000 55000 60000 65000

20

15

10

5

0

A − CBR 15B − CBR 10C − CBR 6D − CBR 3

brc9

4a01

.dg,

sw

, 21/

01/0

0

NOTES1. Tires are 32 x 8.8−16 (21.0 in. centers).2. 227 psi (1565 kPa) inflation pressure (loaded).3. Tire pressure is for calculation purposes only, refer to AMM Ch 12 for service pressures.4. Max. Aft C.G. (36% MAC at approx. 94% of weight on MLG).


AIRCRAFT CLASSIFICATION NUMBER − FLEXIBLE PAVEMENT (32X8.8−16 TIRES)


CHAPTER 7Page 11

May 28/2001

A

B

C

D

AIR

CR

AFT

CLA

SS

IFIC

ATI

ON

NU

MB

ER

(AC

N)


30000 35000 40000 45000 50000 55000 60000 65000

20

15

10

5

0

A − CBR 15B − CBR 10C − CBR 6D − CBR 3

brc9

5a01

.dg,

sw

, 21/

01/0

0



AIRCRAFT CLASSIFICATION NUMBER − FLEXIBLE PAVEMENT (34X10.75−16 TIRES)


CHAPTER 7Page 12

May 28/2001

ABCD

AIR

CR

AFT

CLA

SS

IFIC

ATI

ON

NU

MB

ER

(AC

N)


30000 35000 40000 45000 50000 55000 60000 65000

20

15

10

5

brc9

6a01

.dg,

pt/s

w, 1

8/01

/00

SUBGRADEMODULUS − K

A − 550 LBF/IN −HIGHB − 300 LBF/IN −MEDIUMC − 150 LBF/IN −LOWD − 75 LBF/IN −ULTRA LOW

25


333

3


AIRCRAFT CLASSIFICATION NUMBER − RIGID PAVEMENT (32X8.8−16 TIRES)


CHAPTER 7Page 13

May 28/2001

AB

C

D

AIR

CR

AFT

CLA

SS

IFIC

ATI

ON

NU

MB

ER

(AC

N)


30000 35000 40000 45000 50000 55000 60000 65000

20

15

10

5

brc9

7a01

.dg,

pt/s

w, 1

8/01

/00

25

NOTES1. Tires are 34 x 10.75−16 (19.5 in. centers).2. 141 psi (972 kPa) inflation pressure (loaded).3. Tire pressure is for calculation purposes only, refer to AMM Ch 12 for service pressures.

SUBGRADEMODULUS − K

A − 550 LBF/IN −HIGHB − 300 LBF/IN −MEDIUMC − 150 LBF/IN −LOWD − 75 LBF/IN −ULTRA LOW

333

3

4. Max. Aft C.G. (36% MAC at approx. 94% of weight on MLG).


AIRCRAFT CLASSIFICATION NUMBER − RIGID PAVEMENT (34X10.75−16 TIRES)


CHAPTER 7Page 14

May 28/2001

CHAPTER 8

DERIVATIVE AIRCRAFT



General Information

1. There are no plans to develop any derivative aircraft at this time.


Series: 400

CHAPTER 8Page 1

May 28/2001



CHAPTER 9

SCALED DRAWINGS OFDASH-8 SERIES 400



General Information

1. The scaled drawings that follow can be used to plan/verify runway, ramp and maintenancefacility layouts.

A. The 1 in. = 32 ft. (1:384) scaled drawing is shown in Figure 9−1.

B. The 1 in. = 50 ft (1:600) and 1 in. = 100 ft (1:1200) scaled drawings are shown in Figure9−2.

C. The 1:500 and 1:1000 (Metric) scaled drawings are shown in Figure 9−3.


Series: 400

CHAPTER 9Page 1

May 28/2001

brb0

9a01

.dg,

gv/

cs, j

ul30

/201

4

70o

60o

50o

40o

30o

25o

20o

TURNING RADIUS POINTS

E1NLG

LB1X2

X1

MLG MLG

VE2

FX4

A1A2

X3

B2

70o

1 IN = 32 FT (1:384)

A1A2B1

E1E2FLMLGNLGVX1X2X3

Air conditioning.Ground air−conditioning connection (if no APU is installed).Forward baggage compartment/

Electrical connection (DC).Electrical connection (AC).Pressure refueling point.Lavatory.Main landing gear.Nose landing gear.Fuel vent (on both wings).Forward passenger airstair door.Type II/III emergency exit.Aft passenger door.

LEGEND

B2 Aft baggage compartment.

Turning radius points: 70o

, 60o, 50

o, 40

o, 30

o, 25

o, 20

o.

X4 Galley service door.

Forward type I emergency exit door is installed only on aircraft with extra capacity configuration.NOTES

Type II/III emergency exit door is de−activated for the extra capacity configuration.2

forward type I emergency exit door

2


SCALED DASH 8, SERIES 400 (MODEL 402) DRAWING − 1 IN. = 32 FT (1:384)


CHAPTER 9Page 2

Dec 05/2014

brb4

0a01

.dg,

gv/

cs, j

ul30

/201

4

1 IN = 50 FT (1:600) 1 IN = 100 FT (1:1200)

70o

60o

50o

40o

30o

25o

20o


E1NLG

LB1X2

X1

MLG MLG

V E2F

X4A1

A2

X3

B2

70o

A1A2B1

E1E2FLMLGNLGVX1X2X3



LEGEND



, 60o, 50

o, 40

o, 30

o, 25

o, 20

o.





2


SCALED (MODEL 402) DRAWING − 1 IN. = 50 FT (1:600), 1 IN. = 100 FT (1:1200)


CHAPTER 9Page 3

Dec 05/2014

brb4

1a01

.dg,

gv/

cs, j

ul30

/201

4

SCALE 1:500

70o

60o

50o

40o

30o

25o

20o


E1NLG

L

B1X2

X1

MLG MLG

V E2

FX4

A1A2

X3

B2

70o

SCALE 1:1000

A1A2B1

E1E2FLMLGNLGVX1X2X3



LEGEND



, 60o, 50

o, 40

o, 30

o, 25

o, 20

o.





2


SCALED DASH 8, SERIES 400 (MODEL 402) DRAWING − 1:500 AND 1:1000 (METRIC)


CHAPTER 9Page 4

Dec 05/2014

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