Airport Planning MD11.pdf

8/11/2019 Airport Planning MD11.pdf

1/126

REPORT MDC K0388

REVISION E

ISSUED: AUGUST 1998

MD-11

AIRPLANE CHARACTERISTICS

FOR AIRPORT PLANNING

OCTOBER 1990

To Whom It May Concern:

This document is intended for airport planning purposes.Specific aircraft performance and operational requirements are

established by the airline that will use the airport under consideration.

Questions concerning the use of this document should be

addressed to:

Boeing Commercial Airplane Group

P.O. Box 3707Seattle, Washington 98124-2207 USA

Attention: Manager, Airport Technology

Mail Code 67-KR

Phone: (425) 237-0126 FAX: (425) 234-0044

DOUGLAS AIRCRAFT COMPANY

Website: www.boeing.com/airports


2/126

REVISIONS

MD-11 AIRPLANE CHARACTERISTICS FOR AIRPORT PLANNING

REV. A

NOV. 12, 1990PAGE

22

23

214

215

31

32

33

34

35

36

37

38

39

310

311

312

313

314

315

316

317

REV. B

FEB. 2, 1991PAGE

22

23

25

225

227

44

45

48

512

74

75

77

79

711

713

715

721

722

723

724

REV. C

MAY 22, 1991PAGE

57

77

43

REV. D

NOV. 30, 1993PAGE

22

23

24

25

216

218

223

224

225

227

Section 3

43

47

53

512

69

72

74

75

76

77

79

711

713

715

721

722

723

724

REV. E

AUG. 31, 1998PAGE

i to ii

1-2

2-2 to 2-5

2-10

2-12-2-15

2-17 to 2-19

2-24

2-28

3-1

4-2 to 4-3

4-8 to 4-9

5-3

5-7

5-12

6-9

7-4 to 7-7

7-9

7-11

7-13

7-15

7-21 to 7-24

8-1

REV PAGE


3/126

v

CONTENTS

Section Page

1.0 SCOPE 1-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.1 Purpose 1-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

1.2 Introduction 1-2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.0 AIRPLANE DESCRIPTION 2-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.1 General Airplane Characteristics 2-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.2 General Airplane Dimensions 2-4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.3 Ground Clearances 2-5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.4 Interior Arrangements 2-6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.5 Cabin Cross Section 2-12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.6 Lower Compartment 2-17. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

2.7 Door Clearances 2-19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.0 AIRPLANE PERFORMANCE 3-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.1 General Information 3-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.2 Payload-Range 3-2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.3 FAR Takeoff Runway Length Requirements 3-10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

3.4 FAR Landing Runway Length Requirements 3-16. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.0 GROUND MANEUVERING 4-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.1 General Information 4-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.2 Turning Radii, No Slip Angle 4-2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.3 Minimum Turning Radaii 4-3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.4 Visibility from Cockpit 4-4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.5 Runway and Taxiway Turn Paths 4-5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4.6 Runway Holding Bay (Apron) 4-10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.0 TERMINAL SERVICING 5-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.1 Airplane Servicing Arrangement (Typical) 5-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.2 Terminal Operations, Turnaround 5-4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.3 Terminal Operations, En Route Station 5-5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.4 Ground Service Connections 5-6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.5 Engine Starting Pneumatic Requirements 5-8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.6 Ground Pneumatic Power Requirements 5-10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.7 Preconditioned Airflow Requirements 5-11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

5.8 Ground Towing Requirements 5-12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6.0 OPERATING CONDITIONS 6-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6.1 Jet Engine Exhaust Velocities and Temperatures 6-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

6.2 Airport and Community Noise 6-8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


4/126

vi

CONTENTS (CONTINUED)

Section Page

7.0 PAVEMENT DATA 7-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.1 General Information 7-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .7.2 Footprint 7-4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.3 Maximum Pavement Loads 7-5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.4 Landing Gear Loading on Pavement 7-6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.5 Flexible Pavement Requirements 7-8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.6 Flexible Pavement Requirements, LCN Conversion 7-10. . . . . . . . . . . . . . . . . . . . . . . . . .

7.7 Rigid Pavement Requirements 7-12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.8 Rigid Pavement Requirements, LCN Conversion 7-14. . . . . . . . . . . . . . . . . . . . . . . . . . . .

7.9 ACN-PCN Reporting System 7-18. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

8.0 POSSIBLE MD-11 DERIVATIVE AIRPLANES 8-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

9.0 MD-11 SCALE DRAWINGS 9-1. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


5/126

1.0 SCOPE

1.1 Purpose

1.2 Introduction


6/126

11

REV E

1.0 SCOPE

1.1 Purpose

This document provides, in a standardized format, airplane characteristics data for general airport

planning. Since operational practices vary among airlines, specific data should be coordinated with theusing airlines prior to facility design. Douglas Aircraft Company should be contacted for any additional

information required.

Content of this document reflects the results of a coordinated effort by representatives of the following

organizations:

Aerospace Industries Association

Airports Council International

Air Transport Association of America

International Air Transport Association

The airport planner may also want to consider the information presented ine the CTOL Transport

Aircraft: Characteristics, Trends, and Growth Projections, available from the US AIA, 1250 Eye St.,

Washington DC 20005, for long range planning needs. This document is updated periodically and

represents the coordinated efforts of the folllowing organizations regarding future aircraft growth trends:

International Coordinating Council of Aerospace Industries Association

Airports Council International

Air Transport Association of America

International Air Transport Association


7/126

12

REV E

1.2 Introduction

This document conforms to NAS 3601. It provides Model MD-11 characteristics for airport operators,

airlines, and engineering consultant organizations. Since airplane changes and available options may alter

the information, the data presented herein must be regarded as subject to change. Similarly, for airplanes

not yet certified, changes can be expected to occur.

For further information, contact:


P.O. Box 3707

Seattle, Washington 98124-2207

USA

Attention: Manager, Airport Technology

Mail Code 67-KR

or

Phone: 425-237-0126

FAX: 425-234-0044

Website: www.boeing.com/airports

Note, this document is available electronically at the following website:

www.boeing.com/airports


8/126

13

REV E

THIS PAGE INTENTIONALLY LEFT BLANK


9/126

2.0 AIRPLANE DESCRIPTION

2.1 General Airplane Characteristics

2.2 General Airplane Dimensions

2.3 Ground Clearances

2.4 Interior Arrangements

2.5 Cabin Cross Section

2.6 Lower Compartment

2.7 Door Clearances


10/126


11/126

22

2.0AIRPLANEDESCRIPTION

2.1GENERALAIRPLAN

ECHARACTERISTICS

MODELMD-11

GEENGINE

MAXIMUMDESIGNTAXIWEIGHT*

MAXIMUMDESIGNTAKEOFFWEIGHT

MAXIMUMDESIGNLANDINGWEIGHT

OPERATINGEMPT

YWEIGHT

MAXIMUMDESIGNZEROFUELWEIGHT

MAXIMUMPAYLO

AD(WEIGHT-LIMITED)

MAXIMUMSEATINGCAPACITY

MAXIMUMCARGOVOLUME

MAXIMUM

USABL

EFUEL

MODEL

ENG

INE

PASSENGER

COMBI

(6PALLET)

FREIGHTER

CF6-80C2

CF6-80C2

CF6-80C2

*OPTIONALM

TW:608

,500LB(276,016kg)

613

,000LB(278,057kg)

621

,000LB(281,686kg)

628

,000LB(284,861kg)

633

,000LB(287,122kg)

CONVERTIBLE

FREIGHTER

CF6-80C2

LBkgLBkgLBkgLBkgLBkgLBkgSTD

MAX

FT3

m3

U.S.GAL

liters

LBkg

605,500

274,655

602,500

273,294

430,000

195,048

283,975

128,808

400,000

181,440

116,025

52,632

323410

5,566

157.6

38,615

146,173

258,721

117,356

PASSENGER

ER

CF6-80C2

633,000

287,122

630,500

285,988

430,000

195,048

291,120

132,049

400,000

181,440

108,880

49,391

323410

5,288

149.7

41,615

157,529

278,821

126,470

605,500

274,655

602,500

273,294

458,000

207,749

283,975

128,808

430,000

195,048

146,707

66,549

214290

9,152

259.2

38,615

146,173

258,721

117,356

605,500

274,655

602,500

273,294

471,500

213,872

248,567

112,748

451,300

204,710

202,733

91,962 0 0

21,530

609.7

38,615

146,173

258,721

117,356

605,500

274,655

602,500

273,294

471,500

213,872

288,296

130,768

451,300

204,710

163,004

73,942

298410

21,288

602.3

38,615

146,173

258,721

117,356

REV E

**OPTIONALMLW(FREIGHTERO

NLY):491,500LB(222,944kg)


12/126

23

2.0AIRPLANED

ESCRIPTION

2.1GENERALAIRPLAN

ECHARACTERISTICS

MODELMD-11P&WENGINE

MAXIMUMDESIGNTAXIWEIGHT*

MAXIMUMDESIGNTAKEOFFWEIGHT

MAXIMUMDESIGNLANDINGWEIGHT

OPERATINGEMPT

YWEIGHT

MAXIMUMDESIGNZEROFUELWEIGHT

MAXIMUMPAYLO

AD(WEIGHT-LIMITED)

MAXIMUM

SEATINGCAPACITY

MAXIMUM

CARGOVOLUME

MAXIMUM

USABL

EFUEL

MODEL

ENG

INE

PASSENGER

COMBI

(6PALLET)

FREIGHTER

4460

*OPTIONALMTW:

CONVERTIBLE

FREIGHTER

REV E

LBkgLBkgLBkgLBkgLBkgLBkgSTD

MAX

FT3

m3

U.S.GAL

liters

LBkg

605,500

274,655

602,500

273,294

430,000

195,048

283,975

128,808

400,000

181,440

116,025

52,632 32

3410

5,566

157.6

38,615

146,173

258,721

117,356

PASSENGER

ER

633,000

287,122

630,500

285,988

430,000

195,048

291,120

132,049

400,000

181,440

108,880

49,391 3

23410

5,288

149.7

41,615

157,529

278,821

126,470

605,500

274,655

602,500

273,294

458,000

207,749

283,975

128,808

430,000

195,048

146,707

66,549 21

4290

9,152

259.2

38,615

146,173

258,721

117,356

605,500

274,655

602,500

273,294

471,500

213,872

248,567

112,748

451,300

204,710

202,733

91,962

0 021,530

609.7

38,615

146,173

258,721

117,356

605,500

274,655

602,500

273,294

471,500

213,872

288,296

130,768

451,300

204,710

163,004

73,942 29

8410

21,288

602.3

38,615

146,173

258,721

117,356

4460

4460

4460

4460

608,500LB(276,016kg)

613,000LB(278,057kg)

621,000LB(281,686kg)

628,000LB(284,861kg)

633,000LB(287,122kg)


13/126

24

19 FT 9 IN.(6.0 m)

35 FT 0 IN.(10.7 m)

170 FT 6 IN. (51.97 m) **

26 FT 10 IN.(8.2 m)

75 FT 10 IN.(23.1 m)

2.2 GENERAL AIRPLANE DIMENSIONS

MODEL MD-11

SCALE

0 5 m

0 10 20 FT

*SP AN AT WING TIP DIMENSION POINT= 165 FT 7 IN. (50.5m) WITH FUEL

**MAXIMUM SPAN WITH FUEL/NOMINAL SP AN WITHOUT FUEL= 169 FT 10 IN. (51.8M)

10

30

REV E

148 FT 8 IN. (45.3 m)

136 FT 6 IN. (41.6 m)*

59 FT 2 IN(18.0 m)

79 FT 6 IN.(24.2 m)

WINGTIP DIMENSION POINT

44 FT 1 IN.(13.4 m)

80 FT 9 IN. (24.6 m)

192 FT 5 IN. (58.6 m)

99 FT 4 IN.(30.3 m)

9 FT 7 IN.(2.9 m)

27 FT 10 IN.(8.5 m)

202 FT 2 IN. (61.6 m) WITH CF6-80C2D1F ENGINES200 FT 11 IN. (61.2 m) WITH PW4460 ENGINES

SEESECTION

2.3


14/126


15/126

26

2.4INTERIORAR

RANGEMENTS

2.4.1PASSENGERSM

IXED-CLASSSEATING

MODELM

D-11

GALLEY

ATTENDANTSEAT

LAVATO

RY

ATTENDANTSEAT

ATTENDANTSEAT

GALLEY

AT

TENDANT

LAVATORY

SEAT

LAVATORY

ATTE

NDANT

SEAT

GALLEY

ATTENDA

NTSEAT

LAVATOR

Y

ATTENDANTSEAT

GALLEY

ATTENDANTSEAT

LAVATORY

CLOSET

LAVATORY

2R

ENTRYDOOR

42

BY76IN.

(106.7

BY193.0

cm)

2LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

1R

ENTRYDO

OR

32BY76IN.

(81.3

BY193.0

cm)

1LENTRYDO

OR

32BY76IN.

(81.3

BY193.0

cm)

CLOSET

3R

ENTRYDOOR

42BY

76IN.

(106.7

BY193.0

cm)

3LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

4R

ENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

4LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

323SEATS,34FIRSTCLASS

6ABREAST,289COACH

9ABREAST


16/126

27

2.4.2PASSENGERSECONOMYSEATING

MODEL

MD-11

GALLEY

ATTEND

ANTSEAT

LAVAT

ORY

ATTENDANTSEA

T

LAVATORY

ATTENDANTSEAT

GALLEY

AT

TENDANT

LAVATORY

SEAT

LAVATORY

ATTE

NDANT

SEAT

GALLEY

ATTENDANT

SEAT

LAVATORY

ATTENDANTSEAT

CLOSET

GALLEY

LAVATORY

ATTENDANTSEAT

1RE

NTRYDO

OR

32BY76IN.

(81.3

BY193.0

cm)

2LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

1LENTRYDOOR

32BY

76IN.

(81.3

BY193.0

cm)

3LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

4LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

2R

ENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

3R

ENTRYDOOR

42BY7

6IN.

(106.7

BY193.0

cm)

4R

ENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

379SEATS

9ABREAST


17/126

28

2.4.3PASSENGERSHIGH-DENSITYSEATING

MODEL

MD-11

GALLEY

ATTENDA

NTSEAT

LAVATO

RY

ATTENDANTSEAT

ATTENDANTSEAT

GALLEY

AT

TENDANT

LAVATORY

SEAT

LAVATORY

ATTENDANT

SEAT

GALLEY

ATTENDA

NTSEAT

LAVATOR

Y

ATTENDANTSEAT

ATTENDANTSEAT

GALLEY

CLOSET

CLOSET

LAVATORY

LAVATORY

2RE

NTRYDOOR

42

BY76IN.

(106.7

BY193.0

cm)

3R

ENTRYDOOR

42BY

76IN.

(106.7

BY193.0

cm)

4R

ENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

4LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

3LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

1R

ENTRYDO

OR

32BY76IN.

(81.3

BY193.0

cm)

2LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

1LENTRYDOOR

32BY76IN.

(81.3

BY193.0

cm)

410SEATS

10ABREAST


18/126

29

2.4.4PASSENGERSM

IXED-CLASSSEATING

MODELMD

-11COMBI

C/A

GALLEY

ATTEND

ANTSEAT

LAVAT

ORY

ATTENDANTSEA

T

LAVATORY

ATTENDANTSEAT

GALLEY

ATTENDA

NTSEAT

LAVATORY

ATTENDANTSEAT

CLOSET

GALLEY

LAVATORY

ATTENDANTSEAT

LAVATORY

6PA

LLETS

1R

ENTRYD

OOR

32BY76IN.

(81.3

BY193.0

cm)

2R

ENTRYDOOR4

2BY76IN.

(106.7

BY193.0

cm)

3R

ENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

4R

ENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

DEACTIVATED

4LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

DEACTIVATED

3LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

2LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

1LENTRYDOO

R

32BY76IN.

(81.3

BY193.0

cm)

214SEATS,34FIRSTCLASS

6ABREAST,180COACH

9ABREAST

GALLEY

LAVATORY

CARGOD

OOR

160BY102IN.

(406BY259cm)


19/126

210

2.4.5PASSENGERS-ECONOMYSEATING

MODELMD-11COMBI

2LE

NTRYDOOR42BY76IN.

(106

.7BY193.0cm)

2RENTRY

DOOR42BY76IN.

(106.7BY193.0cm)

ATTENDANTSEAT

ATT

ENDANTSEAT

ATTENDANTSEAT

ATTENDANTSEAT

AT

TENDANTSEAT

ATTENDANTSEAT

GALLEY

GALLEY

GALLEY

GALLEY

LAVATORY

LAVATORY

L

AVATORY

LAVAT

ORY

LAVATORY

LAVATORY

1LENTRY

DOOR32BY76IN.

(81.3B

Y193.0cm)

1RENTRY

DOOR32BY76IN.

(81.3

BY193.0cm)

3LENTRYDOOR42BY76IN.

(106.7BY193.0cm)

3RENTRYDOOR42BY

76IN.

(106.7BY193.0cm)

4RENTRYDOOR

42BY76IN.

(106.7BY193.0cm)

DEACTIVATED

4LENTRYDOOR

42BY76IN.

(106.7BY193.0cm)

DEACTIVATED

6

PALLE

TS

CARGODOOR

160BY102IN.

(406BY259cm)

261SEATS-9ABREAST

G2G1

G3

G4

G5

S

G10

REV E


20/126

211

2.4.6PASSENGERSH

IGH-DENSITYSEATING

MODELMD-11COMBI

GALLEY

ATTENDA

NTSEAT

LAVATO

RY

ATTENDANTSEAT

LAVATORY

ATTENDANTSEAT

GALLEY

ATTENDANTSEAT

LAVATOR

Y

ATTENDANTSEAT

CLOSET

GALLEY

LAVATORY

ATTENDANTSEAT

LAVATORY

6P

ALLETS

1LENTRYDOOR

32BY76IN.

(81.3

BY193.0

cm)

1R

ENTRYDO

OR

32BY76IN.

(81.3

BY193.0

cm)

2R

ENTRYDOOR

42

BY76IN.

(106.7

BY193.0

cm)

3R

ENTRYDOOR

42BY

76IN.

(106.7

BY193.0

cm)

4R

ENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

DEACTIVATED

2LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

3LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

4LENTRYDOOR

42BY76IN.

(106.7

BY193.0

cm)

DEACTIVATED

290SEATS

10ABREAST

LAVATORY

CARGODO

OR

160BY102IN.

(406BY259

cm)


21/126

212

2.5 CABIN CROSS SECTION2.5.1 FIRST CLASS

MODEL MD-11

57 IN. (TYP) 26.50 IN.

CARGO

66 IN.(167.6 cm)

95 IN.(241.3 cm)

125.5 IN. (318.8 cm)

164 IN. (416.6 cm)

237 IN. (602.0 cm)

0.50 IN.(1.3 cm) 21.50 IN.

(TYP)

8 IN. (TYP)(20.3 cm)

3 IN.(TYP)

(7.6 cm)

SERVICE MODULE

(144.8 cm) (67.3 cm) (54.6 cm)

REV E


22/126

213

3 IN. (TYP)(7.6 cm)

2.5.2 BUSINESS CLASSMODEL MD-11

50 IN. (TYP)

25.25 IN.11.75 IN.

(TYP)(29.8 cm)

20.50 IN.(TYP)

CARGO

66 IN.(167.6 cm)

95 IN.(241.3 cm)

125.5 IN. (318.8 cm)

164 IN. (416.6 cm)

237 IN. (602.0 cm)

0.50 IN.(1.3 cm) 73.50 IN. (186.69 cm)

(52.1 cm)(64.1 cm)

(127 cm)

REV E


23/126

214

2.5.3 ECONOMYMODEL MD-11

42 IN. (TYP)2 IN. (TYP)

(5.1 cm)

19 IN.(TYP)

CARGO

66 IN.(167.6 cm)

95 IN.(241.3 cm)

125.5 IN. (318.8 cm)

164 IN. (416.6 cm)

237 IN. (602.0 cm)

0.50 IN.(1.3 cm)

9.5 IN. (TYP)(24.1 cm)

102 IN. (259.1 cm)

(48.3cm)

(106.7 cm)18 IN. (TYP)

(45.7 cm)

REV E


24/126

215

2.5.4 HIGH-DENSITYMODEL MD-11

57.50 IN. (TYP)2 IN. (TYP)

(5.1 cm)

16.50 IN.(TYP)

76 IN. (193.0 cm)

CARGO

66 IN.(167.6 cm)

95 IN.(241.3 cm)

125.5 IN. (318.8 cm)

164 IN. (416.6 cm)

237 IN. (602.0 cm)

0.50 IN.(1.3 cm)

9.25 IN.(TYP)(23.5 cm)

16.50 IN.(TYP)(41.9 cm)(41.9

cm)

(146.1 cm)

REV E


25/126

216

2.5.5 CROSS SECTION CARGOMODEL MD-11F/CF

DMC005-15

88 BY 108 IN.(223.5 BY 274.3 cm)

88 BY 125 IN.(223.5 BY 317.5 cm)

96 BY 125 IN.(243.8 BY 317.5 cm)

TYPICAL CARGO SECTION

LD5LD7LD9LD11

LD21

LD3LD6

(26) 88- BY 125-IN. PALLETS = 14,542 FT3(411.8 m3)

1R 2R

1L 2L

(26) 96- BY 125-IN. PALLETS = 15,514 FT3(439.3 m

3)

(34) 88- BY 108-INCH PALLETS = 15,537 FT3(440.0 m3)

3R

3L

4R

4L

5R

5L

6R

6L

7R

7L

8R

8L

9R

9L

10R

10L

11R

11L

12R

12L

BARRIER NET

1R

1L 2L

2R 3R 4R 5R 6R 7R 8R 9R 10R 11R 12R 13R 14R 15R 16R 17R

4L 5L 6L 7L 8L 9L 10L 11L 12L 13L 15L 16L14L 17L

14C

13C

18C

64 IN.(162.6 cm)

102-IN.(259.1 cm)

DOOR

MAIN CARGO LOADED COMPARTMENTLENGTH = 144 FT 4 IN. (44.0 m)FLAT FLOOR AREA = 2,614.5 FT2(242.9 m2)BULK VOLUME = 22,048 FT3*(624.3 m3)

* BULK VOLUME IS WATER VOLUME OF CABIN BETWEEN BARRIERNET AND AFT BULKHEAD

97.5-IN. (247.7 cm)STACK HEIGHT

FREIGHTER

REV D

(26) 88- BY 125-IN. PALLETS = 13,521 FT3(382.9 m3)

(26) 96- BY 125-IN. PALLETS = 14,508 FT3(410.8 m3)

FREIGHTER

CF

FREIGHTER


26/126

217

2.6 LOWER COMPARTMENT

2.6.1 CARGO COMPARTMENTS CONTAINERS

MODEL MD-11

GROSS WEIGHT7,000 LB EACH(3,175.2 kg)

TARE WEIGHT600 LB EACH(272.2 kg)



32 HALF WIDTH CONTAINERS;EACH 158 FT3 (4.47 m3)TOTAL 5,056 FT3(143.17 m3)

LD3 CONTAINER

160 IN.(406.4 cm)

60.4 IN.(153.4 cm)

44 IN.(111.76 cm)

125 IN.(317.5 cm)64 IN.

(162.56 cm)

79.0 IN.

(200.7 cm)

60.4 IN.(153.4 cm)

64 IN.(162.56 cm)

61.5 IN.(156.2 cm)

16 FULL WIDTH CONTAINERS;EACH 320 FT3(9.06 m3)TOTAL 5,120 FT3(144.98 m3)

32 LD3 CONTAINERS 5,056 FT3(143.17 m3)

BULK CARGO 510 FT3(14.44 m3)

TOTAL 5,566 FT3(157.61 m3)

104- BY 66-IN. (264.2 BY 167.6 cm)CARGO DOOR RIGHT SIDE ONLY18 CONTAINERS

70- BY 66-IN. (177.8 BY 167.6 cm)CARGO DOOR RIGHT SIDE ONLY 14CONTAINERS

BULK CARGO

BULK CARGO DOORLEFT SIDE ONLY30 BY 36 IN.(76.2 BY 91.4 cm)

LD6 CONTAINER

REV E


27/126

218

2.6.2 CARGO COMPARTMENTS CONTAINERS/PALLETS

MODEL MD-11





14 HALF WIDTH CONTAINERS; (LD3)

EACH 158 FT3 (4.47 m3)TOTAL 2,212 FT3 (62.64 m3)

LD3 CONTAINER

79.0 IN.(200.7 cm)

60.4 IN.(153.4 cm)

64 IN.(162.56 cm)

61.5 IN.(156.2 cm)

696 BY 125 PALLETS 2,667 FT3 (75.52 m3)

688 BY 125 PALLETS 2,268 FT3(64.20 m3)14 LD3 CONTAINERS 2,212 FT3(62.58 m3)

BULK CARGO 510 FT3(14.44 m3)

TOTAL 4,990 FT3(141.22 m3)

104- BY 66-IN. (264.2 BY 167.6 cm)CARGO DOOR RIGHT SIDE ONLY6 PALLETS

70- BY 66-IN. (177.8 BY 167.6 cm)OPTIONAL 104- BY 66-IN. (264.2 BY 167.6 cm)CARGO DOOR RIGHT SIDE ONLY14 CONTAINERS

BULK CARGO DOORLEFT SIDE ONLY30 BY 36 IN.(76.2 BY 91.4 cm)

125 IN.(317.5 cm)

88 IN.(223.5 cm)

64 IN.(162.56 cm)

CONTAINERSCENTER COMPARTMENT

PALLETSFWD COMPARTMENT

696 BY 125-IN. PALLETSEACH 444 FT3(12.57 m3)

TOTAL 2,664 FT3(75.41 m3)

688 x 125 PALLETSEACH 378 FT3(10.70 m3)TOTAL 2,268 FT3 (64.2 m3)

88 BY 125-IN. PALLET (223.5 BY 317.5 cm)

OR

OR

REV E


28/126

219

2.7 DOOR CLEARANCES

2.7.1 CLEARANCES, PASSENGER LOADING DOORS, DOOR NO. 1

MODEL MD-11

32 IN. (81 cm)

PLAN VIEW

A

A

16 FT 8 IN.(5.08 m)

6 IN. (15 cm)

8 IN.(20 cm)

76 IN.(193 cm)

FLOOR

DOOR ACTUATOR HANDLE

SEE SECTION 2.3 FORHEIGHT ABOVE GROUND

ELEVATION

FLOOR/DOOR SILL

96 IN. (244 cm)

UPWARD INTERIORSLIDING DOOR

SECTION A-ALOOKING FORWARD

121 IN.(307 cm)

183 IN.(465 cm)

38 IN. (97 cm)

REV E


29/126

220

2.7.1 CLEARANCES, PASSENGER LOADING DOORS, DOOR NO. 2MODEL MD-11

DMC00519

PLAN VIEW

A

A

76 IN.(193 cm)

FLOOR



ELEVATION


AIRPLANENOSE 48 FT 1 IN.

(14.66 m)


FLOOR/DOOR SILL

CONSTANTSECTION

DIA = 237 IN.(602 cm)

136.5 IN.(347 cm)

7.5 IN.(19 cm)

6 IN. (15 cm)

42 IN. (107 cm)

42 IN. (107 cm)

FWD


30/126

221


DMC00520

PLAN VIEW

A

A

76 IN.(193 cm)

FLOOR



ELEVATION


AIRPLANENOSE

95 FT 2 IN.

(29.01 m)


FLOOR/DOOR SILL

CONSTANTSECTION

DIA = 237 IN.(602.0 cm)

136.5 IN.(347 cm)

7.5 IN.

(19 cm)6 IN. (15 cm)

42 IN. (107 cm)

42 IN. (107 cm)

FWD


31/126

222


DMC00521

PLAN VIEW

A

A

FLOOR



ELEVATION


AIRPLANENOSE 155 FT 3 IN.

(47.32 m)

FWD

FLOOR/DOOR SILL

UPWARD INTERIORSLIDING DOOR 123.5 IN.

(314 cm)

103.2 IN.(262 cm)

76 IN.(193 cm)

7.5 IN.(19 cm)

6 IN. (15 cm)

42 IN. (107 cm)

42 IN.(107 cm)

207.2 IN.

(526 cm)


32/126

223

2.7.2 CARGO LOADING DOORS MAIN DECKMODEL MD-11F/CF

DMC00582

SECTION A-ALOOKING AFT

102-IN.(259 cm)DOOR

ELEVATION

PLAN VIEW

A

140 IN.(356 cm)

102 IN.(259 cm)

MAIN CARGO DOOR

CONSTANT SECTIONDIA = 237 IN.

(602 cm)

38 FT (11.6 m)

A

SEE SEC. 2.3 FORHEIGHT ABOVE

GROUND

165 DEG POSITION

FULL OPEN

85 DEG POSITION

REV D

97.5-IN.(248 cm) STACK

HEIGHTFREIGHTER

92.0-IN.(234 cm)

STACK HEIGHTCONVERTIBLE

FREIGHTER


33/126

224

2.7.2 CARGO LOADING DOORS MAIN DECK

MODEL MD-11 COMBI


ELEVATION

PLAN VIEW

A

A

160 IN.(406 cm)

102 IN.(259 cm)

SEE SECTION 2.3 FOR HEIGHT ABOVE GROUND

42 IN.(107 cm)

AIRPLANENOSE

141 FT 8 IN.(43.2 m)

FLOORFWD

102-IN.(259 cm)DOOR

97.5-IN.(248 cm)

STACK HEIGHT

REV E


34/126

225

2.7.3 CARGO LOADING DOORS, LOWER DECKFORWARD DOOR

MODEL MD-11

DMC00594

PLAN VIEW

AIRPLANENOSE

59 FT 2 IN.(18.03 m)

104 IN.(264 cm)

15.9 IN. (40 cm)

ELEVATION

A

A

66 IN. (168 cm)

44 IN. (112 cm)

FLOOR

DOOR ACTUATOR PANELSWITCH AND CONTROLS

SEE SECTION 2.3 FORGROUND CLEARANCE

SECTION A-A

211.3 IN.(537 cm)

CRITICAL CLEARANCE LIMITLOOKING FORWARD 19.7 IN.

(50 cm)

89.8 IN.(228 cm)

CONSTANT SECTION DIA= 237 IN. (602 cm)

135 DEG FULL OPEN

REV D


35/126

226

2.7.3 CARGO LOADING DOORS, LOWER DECKCENTER CARGO DOOR

MODEL MD-11

DMC00596

PLAN VIEW

AIRPLANENOSE

ELEVATION

44 IN. (112 cm)

SECTION A-A

198.6 IN.(504 cm)

CRITICAL CLEARANCE LIMIT

LOOKING FORWARD

19.7 IN. (50 cm)

126.1 IN.(320 cm)

CONSTANT SECTION DIA= 237 IN. (602 cm)

158 DEG FULL OPEN

113.2 IN.(288 cm)

60 IN. (152 cm)

66 IN.(168 cm)


A

A

WING FILLET

144 FT 0 IN.(43.9 m)

70 IN.(178 cm)

15.9 IN.(40 cm)

DOOR ACTUATOR PANELSWITCH AND CONTROLS


36/126

227

2.7.3 CARGO LOADING DOORS, LOWER DECKCENTER CARGO DOOR (OPTIONAL FOR OTHER MODELS)

MODEL MD-11 COMBI

Chap2Text

PLAN VIEW

AIRPLANENOSE

ELEVATION

SECTION A-A

198.6 IN.(504 cm)

CRITICAL CLEARANCE LIMIT

LOOKING FORWARD

19.7 IN. (50 cm)

126.1 IN.(320 cm)

158 DEG FULL OPEN

FILLET AT FWD DOOR JAMB

113.2 IN.(288 cm)

60 IN. (152 cm)

66 IN.(168 cm)

SEE SECTION 2.3 FORGROUND CLEARANCE104 IN.

(264 cm)

A

A

WING FILLET

139 FT 7 IN.(42.55 m)

27 IN.

DOOR ACTUATORPANEL SWITCHAND CONTROL

44 IN.(112 cm)

116 IN.(295 cm)

REV D


37/126

228

2.7.3 CARGO LOADING DOORS, LOWER DECK

AFT BULK CARGO DOOR

MODEL MD-11

PLAN VIEW

AIRPLANENOSE

ELEVATION

SECTION A-ACRITICAL CLEARANCE LIMIT

LOOKING FORWARD

23.8 IN. (60 cm)

70.5 IN. (179 cm)

152 DEG FULL OPEN


A

A

VENT DOOR HANDLE

160 FT 6 IN.(48.92 m)

21 IN. (53 cm)

5 IN. (13 cm)

DOOR CONTROL PANEL

36 IN. (91 cm)

18 IN. (46 cm)

10 IN. (25 cm)

30 IN. (76 cm)

158.3 IN.(402 cm)

119 IN.(302 cm)

77 IN.(196 cm)

93.5 IN.(237 cm)

REV E


38/126

2-29

REV E



39/126

3.0 AIRPLANE PERFORMANCE

3.1 General Information

3.2 Payload-Range

3.3 FAR Takeoff Runway Length Requirements

3.4 FAR Landing Runway Length Requirements


40/126

3-1

3.0 AIRPLANE PERFORMANCE


Figures 3.2.1 through 3.2.8 present payload-range information for a specific Mach number cruise at the

fuel reserve condition shown.

Figures 3.3.1 through 3.4.2 represent FAR takeoff and landing field length requirements for FAA

certification.

Standard day temperatures for the altitudes shown are tabulated below:

ELEVATION STANDARD DAY TEMPERATURE

FEET METERS F C

0 0 59 15

2,000 610 51.9 11.1

4,000 1,219 44.7 7.1

6,000 1,829 37.6 3.1

8,000 2,438 30.5 0.8

Note: These data are provided for information only and are not to be used for flight planning purposes.

For specific performance data/analysis, contact the using airline or the Airport Technology Group at

(425) 237-0126 or:


P.O. Box 3707

Seattle, Washington 98124-2207

USA

Attn: Manager, Airport Technology

Mail Code 67-KR

REV E


41/126


42/126


43/126


44/126


45/126


46/126


47/126


48/126


49/126


50/126


51/126


52/126


53/126


54/126


55/126


56/126


57/126

4.0 GROUND MANEUVERING


4.2 Turning Radii, No Slip Angle

4.3 Minimum Turning Radii

4.4 Visibility from Cockpit

4.5 Runway and Taxiway Turn Paths

4.6 Runway Holding Bay (Apron)


58/126

41

4.0 GROUND MANEUVERING


This section provides airplane turning capability and maneuvering characteristics.

For ease of presentation, these data have been determined from the theoretical limits imposed by the

geometry of the aircraft, and where noted, provide for a normal allowance for tire slippage. As such, they

reflect the turning capability of the aircraft in favorable operating circumstances. The data should only be

used as guidelines for determining such parameters and to obtain the maneuvering characteristics of this

aircraft type.

In the ground operating mode, varying airline practices may demand that more conservative turning

procedures be adopted. Airline operating techniques will vary in level of performance over a wide range

of circumstances throughout the world. Variations from standard aircraft operating patterns may be

necessary to satisfy physical constraints within the maneuvering area, such as adverse grades, limitedspace, or high risk of jet blast damage. For these reasons, ground maneuvering requirements should be

coordinated with the using airlines prior to layout planning.


59/126

42

4.2 TURNING RADII, NO SLIP ANGLE

MODEL MD-11

25

30

40

50

35

45

55

60

65

70

R1

R2

R6

R4

R3

R5

TURNING RADII DEPICTED

REPRESENT THEORETICAL

GEOMETRIC TURN CENTERS

TURNING CENTERS

MAXIMUM

NOTE: ACTUAL OPERATING DATA MAY BE GREATER

THAN VALUES SHOWN SINCE TIRE SLIPPAGE IS

NOT CONSIDERED IN THESE CALCULATIONS.

CONSULT AIRLINE FOR OPERATING PROCEDURES

R3 MEASURED FROM OUTSIDE FACE OF TIRE.

STEERING

ANGLE (DEG)

R1 R2 R3 R4 R5 R6

153.7

120.2

95.5

76.3

60.747.6

36.3

26.3

17.3

9.0

FT m FT m FT m FT m FT m FT m

46.8

36.6

29.1

23.3

18.514.5

11.1

8.0

5.3

2.7

194.9

161.4

136.7

117.5

101.988.8

77.5

67.6

58.5

50.2

59.4

49.2

41.7

35.8

31.127.1

23.6

20.6

17.8

15.3

194.0

164.3

143.5

128.2

116.6107.8

100.9

95.6

91.4

88.2

59.1

50.1

43.7

39.1

35.532.9

30.8

29.1

27.9

26.9

262.6

229.5

205.2

186.4

171.2158.5

147.6

138.0

129.4

121.5

80.0

70.0

62.5

56.8

52.248.3

45.0

42.1

39.4

37.0

205.7

178.2

159.4

145.9

136.1128.7

123.1

118.8

115.6

113.8

62.7

54.3

48.6

44.5

41.539.2

37.5

36.2

35.2

34.7

220.2

189.5

167.7

151.3

138.5128.3

119.9

112.9

107.0

102.0

67.1

57.8

51.1

46.1

42.239.1

36.5

34.4

32.6

31.1

25

30

35

40

4550

55

60

65

70 MAXIMUM

TURNING CENTER

FOR ILLUSTRATION

PURPOSES

STEERING ANGLES (DEGREES)

REV E


60/126

43

4.3 MINIMUM TURNING RADII

MODEL MD-11

TAILR6

X

NOSE TIRER3

NOSE

R5

WING TIP

R4

Y

MAXIMUM STEERING

ANGLE 70 DEG

EFFECTIVE

TURN ANGLE

TURN

CENTER

A

PAVEMENT

WIDTH FOR

180-DEG TURN

NOSE GEAR RADII TRACK

MEASURED FROM OUTSIDE

FACE OF TIRE

NORMAL TURNS

SYMMETRICAL THRUST AND NO DIFFERENTIAL

BRAKING. SLOW CONTINOUS TURN. AFT CENTER OF

GRAVITY AT MAX RAMP WEIGHT

LIGHTLY BRAKED TURN

UNSYMMETRICAL THRUST AND LIGHT DIFFEREN -

TIAL BRAKING. SLOW CONTINUOUS TURN. AFT

CENTER OF GRAVITY AT MAX RAMP WEIGHT

MINIMUM RECOMMENDED RADIUS TO AVOID EXCESSIVE

TIRE WEAR. LIMITED BY 8DEG MAIN GEAR TIRE SCRUB

TYPE

TURN

EFFECTIVE

TURN ANGLE

TIRE SLIP

ANGLE

X

FT/m

Y

FT/m

A

FT/m

R3FT/m

R4FT/m

R5FT/m

R6FT/m

60.8 DEG

72.0 DEG

9.2 DEG

2.0 DEG

81.2

81.6

81.2

45.3

26.5

42.1

160.6

134.6

155.8

94.7

87.5

93.1

136.4

118.5

133.4

118.1

112.6

116.9

111.9

100.0

109.8

24.7

24.9

24.7

13.8

8.1

12.8

49.0

41.0

47.5

28.9

26.7

28.4

41.6

36.1

40.7

36.0

34.3

35.6

34.1

30.5

33.5

1

2

3

3

21

REV E

SLIP


61/126

44

4.4 VISIBILITY FROM COCKPIT IN STATIC POSITIONMODEL MD-11

DMC00542

PILOTS EYE POSITION

PILOTS EYE POSITION

36 DEG

20 DEG20 FT 8 IN.

(6.3 m)

50 FT 4 IN.(15.3 m) 6 FT 11 IN. (2.1 m) (REF)

20 FT 11 IN. (6.4 m)

27 FT 10 IN. (8.5 m)

135 DEG

MAXIMUM AFT VISIONWITH HEAD ROTATEDABOUT SPINAL COLUMN

PILOTS EYE POSITION21 IN.(53.3 cm)

40 DEG

31 DEG

45 DEG

WITH HEADMOVED 14 IN.

OUTBOARD(35.6 cm)

45 DEG

31 DEG

40 DEG

NOT TO BE USED FORLANDING APPROACH VISIBILITY

REV B


62/126

45

4.5 RUNWAY AND TAXIWAY TURN PATHS4.5.1 MORE THAN 90-DEG TURN RUNWAY TO TAXIWAYMANEUVERING METHOD COCKPIT OVER CENTERLINE

MODEL MD11

DMC005-89

75 FT(22.86 m)

COCKPIT REFERENCE POINT

15 FT (4.57 m)CLEARANCE LINE

PATH OF MAINGEAR TIRE EDGE

150-FT R(45.72 m)

150 FT(45.72 m)

RUNWAYCENTER-

LINE

45DEG

NOTE: THE MINIMUM MAIN GEAR TIRE-TO-TAXIWAYPAVEMENT EDGE CLEARANCE SHOWN IS APPROXIMATELY15 FT (4.57 m)

TAXIWAYCENTER-

LINE

100-FT R

(30.48 m)

ADDITIONAL FILLETREQUIRED

REV B


63/126

46

4.5.2 MORE THAN 90-DEGREE TURN RUNWAY TO TAXIWAYMANEUVERING METHOD JUDGMENTAL OVERSTEERING

MODEL MD11

DMC00588

100-FT R

(30.48 m)150-FT R(45.72 m)

75 FT(22.86 m)

CL

CL45 DEG

150 FT(45.72 m)

PATH OF NOSE GEAR TIRE EDGE

15 FT (4.57 m )CLEARANCE LINE

TAXIWAYCENTERLINE

RUNWAYCENTERLINE


NOTE:1. EFFECTIVE STEERING ANGLE-APPROX 30 DEG (33-DEG STEERING, 3-DEG NOSE GEAR SLIP)

2. THE MINIMUM MAIN GEAR TIRE-TO-TAXIWAY

PAVEMENT EDGE CLEARANCE SHOWN IS APPROXIMATELY15 FT (4.57 m)

15 FT (4.57 m)CLEARANCE LINE


64/126

47

4.5.3 90-DEGREE TURN TAXIWAY TO TAXIWAYMANEUVERING METHOD COCKPIT OVER CENTERLINE

MODEL MD-11

DMC00590

75 FT(22.86 m)

NOTE: THE MINIMUM MAIN GEAR TIRE-TO-TAXIWAYPAVEMENT EDGE CLEARANCE SHOWN ISAPPROXIMATELY 15 FT (4.57 m)

PATH OF MAIN GEAR TIRE EDGE(AIRCRAFT DIRECTION AS SHOWN)

75 FT(22.86 m)

CL

TAXIWAYCENTERLINE

PATH OFCOCKPITREFERENCEPOINT


150 FT (45.72 m)

83 FT (25.30 m)

150 FT (45.72 m)

83 FT (25.30 m)

APPROX 15 FT (4.57 m)

250-FT (76.20 m) LEAD-IN

(TYPICAL 4 PLACES)

CL

REV D


65/126

48

4.5.4 90-DEGREE TURN TAXIWAY TO TAXIWAY

MANEUVERING METHOD JUDGMENTAL OVERSTEERING

MODEL MD-11

75 FT

(22.86 m)

NOTES:

1. THE INTERSECTION FILLET IS DETERMINED

FROM THE GEOMETRY OF THE CRITICAL

AIRCRAFT AND THE STEERING PROCEDURE

THAT WILL BE USED.

2. 33-DEGREE STEERING ANGLE, 3-DEGREE

NOSE GEAR SLIP (30-DEGREE EFFECTIVE

STEERING ANGLE)

3. THE MINIMUM MAIN GEAR TIRE-TO-TAXIWAY

PAVEMENT EDGE CLEARANCE SHOWN IS

APPROXIMATELY 15 FT (4.57 m)

15-FT (4.57 m) CLEARANCE LINE

PATH OF MAIN GEAR TIRE EDGE

75 FT

(22.86 m)

CL

CL

16.8 FT (5.12 m)

105-FT (32.00 m) R

TAXIWAY

CENTERLINE

15 FT (4.57 m)

PATH OF NOSE GEAR TIRE EDGE


REV E


66/126

49

4.5.5 90-DEGREE TURN RUNWAY TO TAXIWAY

MANEUVERING METHOD COCKPIT OVER CENTERLINE

MODEL MD11

75 FT

(22.86 m)CL

150 FT

(45.72 m)



(RUNWAY-TO-TAXIWAY DIRECTION)

ADDITIONAL FILLET REQUIRED

85-FT (25.91 m) R

150-FT (45.72 m) R


(TAXIWAY-TO-RUNWAY DIRECTION)


(RUNWAY-TO-TAXIWAY DIRECTION)

NOTE: THE MINIMUM MAIN GEAR TIRE-TO-TAXIWAY

PAVEMENT EDGE CLEARANCE SHOWN IS

APPROXIMATLY 15 FT (4.57 m)

RUNWAY

CENTERLINE

TAXIWAY

CENTERLINE

REV E


67/126

410

4.6 RUNWAY HOLDING BAY (APRON)MODEL MD-11

DMC00593


PATH OF NOSE GEAR TIRE

20 FT (6.10 m)

263 FT (80.16 m)

40 FT(12.19 m)

PATH OF NOSE GEAR


20 FT(6.10 m)

15 FT (4.57 m)

TAXIWAYCENTERLINE RUNWAY

CENTERLINE

20 FT(6.10 m)

SHOULDER

NOTE: THE MINIMUM MAIN GEAR TIRE-TO-PAVEMENT EDGE CLEARANCE SHOWN ISAPPROXIMATELY 15 FT (4.57 m)

97 FT (29.57 m)

PATH OFNOSE GEAR

150 FT (45.72 m)75 FT(22.86 m)


68/126

4-11

REV E



69/126

5.0 TERMINAL SERVICING

5.1 Airplane Servicing Arrangement (Typical)

5.2 Terminal Operations, Turnaround Station

5.3 Terminal Operations, En Route Station

5.4 Ground Service Connections

5.5 Engine Starting Pneumatic Requirements

5.6 Ground Pneumatic Power Requirements

5.7 Preconditioned Airflow Requirements

5.8 Ground Towing Requirements


70/126

51

5.0 TERMINAL SERVICING5.1 AIRPLANE SERVICING ARRANGEMENT (TYPICAL)

5.1.1 AIRPLANE SERVICING ARRANGEMENT TYPICAL TURNAROUNDMODEL MD-11

DMC00543

CARGO PALLET TRAIN

CARGO LOADER EXTENSION

LOWER DECKCARGO LOADER

GALLEYSERVICEVEHICLES

TOWVEHICLE

POTABLE WATERVEHICLE

PASSENGERLOADING BRIDGES

FUEL SERVICE VEHICLECABINSERVICE VEHICLE

BULK CARGODOLLY TRAIN

BULK CARGOLOADER

LAVATORYSERVICEVEHICLE

GALLEY SERVICEVEHICLE

LOWER DECK CARGOLOADER

CONTAINER DOLLYTRAIN

FUEL SERVICE VEHICLE

NOTE: THE AIRCRAFT AUXILIARY POWER UNITSUPPLIES ELECTRICAL, PNEUMATIC AIR,AND PRECONDITIONED AIR.


71/126

52

5.0 TERMINAL SERVICING5.1.2 AIRPLANE SERVICING ARRANGEMENT TYPICAL TURNAROUND

MODEL MD-11 COMBI

DMC00544

CARGO PALLET TRAIN

CARGO LOADER EXTENSION

LOWER DECKCARGO LOADER

GALLEY SERVICEVEHICLES

TOW

VEHICLE

POTABLE WATERVEHICLE

PASSENGERLOADING BRIDGE


BULKCARGODOLLYTRAIN

BULK CARGOLOADER

LAVATORYSERVICEVEHICLE

LOWER DECK CARGOLOADER

CONTAINER DOLLYTRAIN


NOTE: THE AIRCRAFT AUXILIARY POWER UNIT SUPPLIESELECTRICAL, PNEUMATIC AIR, AND PRECONDITIONED AIR.

CARGO PALLET TRAIN

MAIN DECKCARGO LOADER


72/126

53

5.0 TERMINAL SERVICING

5.1.3 AIRLINE SERVICING ARRANGEMENT TYPICAL TURNAROUND

MODEL MD-11F/CF

CARGO PALLET TRAIN

LOWER DECK CARGO

LOADER


BULK CARGOTRAILER


MAIN-DECK

CARGO LOADER

BULK CARGO

LOADER

CREW STAIRS

CARGO PALLET TRAIN

LOWER DECK CARGO

LOADER WITH LD3

NOTE: THE AIRCRAFT AUXILIARY POWER UNIT SUPPLIES ELECTRICAL,

PNEUMATIC, AND PRECONDITIONED AIR

CONTAINER DOLLY

TRAIN

REV E


73/126

54

5.2TERMINALOPERATIONS,TURNAROUND

5.2.1TURN

AROUND

MODELMD-11

ENGINERUNDOWN

1.0

CHECKLOGBOOK

1.5

WALKAROUNDINSPECTION

9.0

CHECKLOGBOOK

1.5

MONITORENGINES

3.0

CLEARFORDEPARTURE

1.0

POSITIONPASSENGERBRIDGE

0.5

DEPLANEPASSENGERS

5.6

CABINSERVICING(9-MANCREW)

19.5

SERVICEFORWARDANDMIDGALLEY

25.6

SERVICEAFTGALLEY

27.1

ENPLANEPASSENGERS

16.2

REMOVEPASSENGER

BRIDGE

0.5

FORWARDCONTAINERREM

OVAL

18.0

AFTCONTAINERREMOVAL

14.0

BULKCARGOREMOVAL

12.8

FORWARDCONTAINERLOADING

18.0

AFTCONTAINERLOADING

14.0

BULKCARGOLOADING

12.8

FUELSERVICES

16.6

LAVATORYSERVICE

15.3

POTABLEWATERSERVICE

13.8

OPERATIONS

MIN

COCKPITCREWPASSENGERSERVICE BAGGAGEANDCARGO

OTHERSERVICE

50

40

30

20

10

TIME(MINUTES)

51.4MINUTES

NOTES:

1.

CRITICALTIMEPATH

4.1,562

-GPM

REFUELINGRATEUSINGTWOHYDRANTVEHICLES

2.ESTIMATESBASE

DON34FIRSTCLASSAND289COACH

5.UPPE

R

GALLEYCONFIGURATIONWITHFWD,MID,ANDAFTGALLEYS

3.DEPLANINGAND

ENPLANINGTHROUGHDOORS

NO.1AND2

6.AFT

GALLEYCLOSEDOFFDURINGPARTOFPASSENGER

ENPLANEMEN

T

DUTIES


74/126

55

5.3TERMINALOPERATIONS,ENROUTESTATION

MODELMD-11

ENGINERUNDOWN

1.0

CHECKLOGBOOK

1.5

W

ALKAROUNDINSPECTION

9.0

CHECKLOGBOOK

1.5

M

ONITORENGINES

3.0

CLEARFORDEPARTURE

1.0

POSITIONPASSENGER

BRIDGE

0.5

DEPLANEPASSENGERS

3.0

CABINSERVICING(2-MANCREW)

6.7

SERVICEMIDGALLEY

7.6

SERVICEFORWARDANDAFTGALLEY

6.7

ENPLANEPASSENGERS

9.0

REMOVEPASSENGERBRIDGE

0.5

FORWARDCONTAINERREMOVAL

10.0

AFTCONTAINERREMOVAL

8.0

BULKCARGOREMOVAL

7.1

FORWARDCONTAINERLOADING

7.7

AFTCONTAINERLOADING

6.2

BULKCARGOLOADING

7.1

FUELSERVICES(TIMEAVAILABLE)

12.0

LAVATORYSERVICE

9.1

POTABLEWATERSERVICE

5.4

OPERATIONS

MIN

COCKPITCREWPASSENGERSERVICE BAGGAGEANDCARGO

OTHERSERVICE

20

10

TIME(MINUTES)

23.6MINUTES

NOTES:

1.

CRITICALTIMEPATH

5.962-G

PM

REFUELINGRATEUSINGTWOTRUCKS

2.55-PERCENTLOA

DFACTOR;17FIRSTCLASSAND160COACH

6.UPPE

R

GALLEYCONFIGURATIONWITHFWD,MID,ANDAFTGALLEYS

3.DEPLANING

THR

OUGHDOORSNO.1AND2

7.AFT

GALLEYCLOSEDOFFDURINGPARTOFPASSENGER

ENPLANEMEN

T

4.ENPLANINGFIRSTCLASSPSGRSTHROUGHNO.1DOORAND

COACHPSGRSTHROUGHNO.2DOOR

30

DUTIES


75/126

56

5.4 GROUND SERVICE CONNECTIONSMODEL MD11

SCALE

0 5 m

0 10 20 FT

10

30

PRECONDITIONED AIR

FUEL

ELECTRICAL

JACK POINT

FUEL VENT

JACK POINT

POTABLE WATER

PNEUMATIC

FUEL

FUEL VENT

HYDRAULIC

JACK POINT

FUEL VENT

PRECONDITIONED AIR

POTABLE WATER

PNEUMATIC

ELECTRICALFUEL

LAVATORY

FUEL VENT

FUEL VENT

DMC00548

LAVATORY


76/126

57

5.4GROUNDSERVICE

CONNECTIONDATA

MODELMD-11

5.4.1HYDRAULICSYSTEM

TWOSERVICECONNECT

IONS:

A.SERVICEPANELCONTAININGPRESSUREANDTESTSTAND

CONNECTIONS,3,000

PSI(21MPa)AT50GPM

(189lPM)MAXIMUM

B.RESERVOIRFILLCON

NECTIONS,60PSI(414kPA)

5.4.2ELECTRICALSYSTEM

TWOSERVICECONNECTIONS,90KVA,EA.115VOLT,400HZ,3PHASE

5.4.3OXYGEN

INDEPENDENTA

IRCREWANDPASSENGERSYSTEMS

AIRCREWOXYGENSYSTEM

PASSENGEROXYGENSYSTEM

5.4.4FUELSYSTEM

TWOPRESSURESERVICE

POINTSINEACHWINGLEADINGEDGE.

1,250GPM

(4,731lPM)TH

ROUGH2POINTS

1,600GPM

(6,056lPM)

THROUGH4POINTSAT5

0PSIG(345kPA)

TOTALUSABLECAPACITY

38,652U.S.GALLONS(1

46,296l)

6,075U.S.GALLONS(22,945

l)EACHWINGTANK1

AND2

9,767.9U.S.GALLONS(36,968l)NUMBER2TANK

13,001U.S.GALLONS(49,208

l)CTRWING

AUXTANKUPPER

1,643U.S.GALLONS(6,217l)UNDERWING

AUXTANKLOWER

2,000U.S.GALLONS(7,570l)TAILAUXTANK

RIGHTWINGSERVICERE

CEPTACLES

LEFTWINGSERVICEREC

EPTACLES

FUELVENTWINGRIGHT

FUELVENTWINGLEFT

TAILAUXTANKVENT

5.4.5PNEUMATICSYSTEM

TWO3-IN.SERVICECONN

ECTIONSFORENGINESTARTANDAIR

CONDITIONING

5.4.6PRECONDITIONED

AIR

TWO8-IN.CONNECTIONS

FORAIRCONDITIONING

5.4.7POTABLEWATERSYSTEM

ONESERVICECONNECTION

FOUR-TANKSYSTEM

64U.S.GALLONSEACH(242l)

TOTALSYSTEM

CAPACITY256GAL

(969LITERS)

5.4.8LAVATORYSYSTEM

NUMBEROFTOILETS

SERVICELOCATION

1(1)

FORWARD(2)

UPTO12

AFT

SERVICECAPACITIES

WASTEHOLDING260U.S

.GALLONS(984l)

DISTANCEAFT

OFNOSE

DISTANCEFROM

AIRPLANECENTERLINE

HEIGHTA

BOVEGROUND

MAXIMUM M

ETERS

FTIN.

MINUMUM M

ET

ERS

FT

IN.

METERS

FTIN.

METERS

FT

IN.

RIGHTSIDE

LEFTSIDE

METERS

FT

IN.

1260

11810

306

10710

10710

32.87

32.87

38.40

36.22

9.30

34

12

1.02

0.36

91

2.77

98

2.95

95

2.87

100

3.05

74

2.24

89

2.67

1243

584

1799

158

423

12.88

423

12.88

148

148

4.47

4.47

155

155

4.704.70

252

7.67

67

2.01

1010

3.30

124

3.76

152

4.62

62

1.88

123

3.73

1311

4.24

406

12.34

34

1.02

80

2.44

91

2.77

1310(2)

4.22(2)

95(2)

2.87

(2)

108(2)

3.25(2)

1638

49.89

99

2.97

113

3.43

(1)FREIGHTER1TOILETFOR

WARDLOCATION

(2)FREIGHTERONLY

CYLINDERINAVIONICSCOMPARTMENT,CONNECTED

TOMANIFOLD.PORTABLE

CYLINDERFORCREW

INFLIGHTCOMPARTMENT.CHEMICALOXYGENSYSTEM

IN

MODULESINOVERH

EADSTORAGERACKS,LAVATORIES,ANDATTENDANTSTA-

TIONS,PORTABLECY

LINDERSFORFIRSTAID

37.87

37.87

54.79

17.78

4.78

42

1.27

1243

584

17.78

140

140

194

5.89

151

151

213

6.48

CLCL

CLCL

CLCL

CLCL

REV E

4.27

4.27

4.60

4.60


77/126

58

5.5 ENGINE STARTING PNEUMATIC REQUIREMENTSMODEL MD-11 GE ENGINE

DMC00549

0 10 20 30 40 50 60 70 80

140

120

100

60

REQUIREDAIRFLOW(

LB/MIN)

(PSIA)

160

80

200

180

220

240

40 20 0 20 40 60 80 100 120

20

REQUIREDPRESSUREATGROUND

30

50

40

60

70

CONNECTOR(PSIA)

118

110

100

90

80

70

60

50

40

30

5.0

4.5

4.0

3.5

3.0

2.5

2.0

1.5

(kg/MIN)

(kg/cm

ABS)

2

1.0 2.0 3.0 4.0 5.0

-40 -30 -20 -10 0 10 20 30 40 50

(kg/cm2ABS)

CF6-80C2D1FMAXIMUM ALLOWABLE PNEUMATICSYSTEM PRESSURE 51 PSIG

(65.7 PSIA AT SEA LEVEL)

MAXIMUM ALLOWABLE PNEUMATICSYSTEM TEMPERATURE 500F (260C)

MAXIMUM ALLOWABLE PNEUMATIC SYSTEMPRESSURE 51 PSIG

FOR A 46-SECOND START AT SEA LEVEL*

* THERE IS NO SATISFACTORY DEFINITION FOR REQUIRED PRESSURE AT GROUND CONNECTOR SO THAT A SINGLE LINE CANBE DEPICTED. THE LINE DEPICTED IS FOR A 46-SECOND START TIME, WHICH IS AN ARBITRARY VALUE.

PRESSURE AT GROUND CONNECTOR

AMBIENT AIR TEMPERATURE

(F)

(C)


78/126

59

5.5 ENGINE STARTING PNEUMATIC REQUIREMENTSMODEL MD-11 P&W ENGINE

DMC00550

0 10 20 30 40 50 60 70 80

250

200

150

50

REQUIREDAIRFLOW(

LB/MIN)

PSIA

300

100

400

350

40 20 0 20 40 60 80 100 120

20

REQUIREDPRESSUREATGROUND

30

50

40

60

70

CONNECTOR(PSIA)

120

110

100

90

80

70

60

50

40

30

5.0

4.5

4.0

3.5

3.0

2.5

2.0

1.5

(kg/MIN)

(kg/cm

ABS)

2

1.0 2.0 3.0 4.0 5.0

-40 -30 -20 -10 0 10 20 30 40 50

(kg/cm2ABS)

PW4460MAXIMUM ALLOWABLE PNEUMATICSYSTEM PRESSURE 51 PSIG

(65.7 PSIA AT SEA LEVEL)

MAXIMUM ALLOWABLE PNEUMATICSYSTEM TEMPERATURE 500F (260C)

MAXIMUM ALLOWABLE PNEUMATIC SYSTEMPRESSURE 51 PSIG

FOR A 46-SECOND START AT SEA LEVEL*

* THERE IS NO SATISFACTORY DEFINITION FOR REQUIRED PRESSURE AT GROUND CONNECTOR SO THAT A SINGLE LINE CANBE DEPICTED. THE LINE DEPICTED IS FOR A 46-SECOND START TIME, WHICH IS AN ARBITRARY VALUE.

150

140

130

180

170

160

190

PRESSURE AT GROUND CONNECTOR

AMBIENT AIR TEMPERATURE

(

F)

(C)


79/126

510

5.6 GROUND PNEUMATIC POWER REQUIREMENTSMODEL MD-11

DMC00551

0 20 40 60 80

280

240

200

LB/MIN320

400

360

1.0 1.2 1.4 1.6 1.8AIR SUPPLY PRESSURE

(kg/cm2ABS)

TOTALAIRFLOW(

kg/M

IN)

180

160

140

120

100

HEATING

MINUTES TO HEAT CABIN TO 75F (24C) INITIAL CABIN TEMPERATURE 25F (32C) DULL DAY OUTSIDE AIR TEMPERATURE 40F (40C) NO CABIN OCCUPANTS OR ELECTRICAL LOAD MAX TEMPERATURE AT GROUND CONN 440F (227C) MAX ALLOWABLE SUPPLY PRESSURE 45 PSIG MIN TEMPERATURE NOT LESS THAN 200F (93C) BOTH GROUND CONNECTIONS USED

ABOVE O.A.T THREE-PACK OPERATION DOORS CLOSED

0 20 40 60 80

250

200

LB/MIN

300

400

350

1.0 1.2 1.4 1.6 1.8

TOTALAIRFLOW(

kg/MIN)

180

160

140

120

100

AIR SUPPLY PRESSURE(kg/cm2ABS)

COOLING

MINUTES TO COOL CABIN TO 75 F (24 C) INITIAL CABIN TEMPERATURE 115F (46C) BRIGHT DAY OUTSIDE AIR TEMPERATURE 103F (40C) REL HUM 42% NO CABIN OCCUPANTS OR ELECTRICAL LOAD MAX TEMPERATURE AT GROUND CONN 440F (227C) MAX ALLOWABLE SUPPLY PRESSURE 45 PSIG MIN TEMPERATURE NOT LESS THAN 200F (93C) BOTH GROUND CONNECTIONS USED

ABOVE O.A.T THREE-PACK OPERATION DOORS CLOSED

100

16 20 24 28(PSIA)

(PSIA) 25 30 35 40 45


80/126

511

DMC0055354

5.7 PRECONDITIONED AIRFLOW REQUIREMENTSMODEL MD-11

AIR SUPPLY TEMPERATURE

600

30 50 70 90 110

500

400

300

200

100

TOTALAIRFLOW

260

220

180

140

100

60

0 10 20 30 40

MAXIMUM ALLOWABLE PRESSURE ATGROUND CONNECTION (25 INCHES WATER)

1

32

4

5 6

1

2

3

4

5

6

CABIN AT 75F (24C), 410 OCCUPANTS,BRIGHT DAY (SOLAR IRRADIATION),

SAME AS 1 EXCEPT CABIN AT 85F

SAME AS 1 EXCEPT CABIN AT 70F

CABIN AT 70F (21C), 50 CABINOCCUPANTS, OVERCAST DAY (NO

SAME AS 4 EXCEPT 20F

SAME AS 4 EXCEPT 40F

MAXIMUM ALLOWABLE TEMPERATURE

CONDITIONED AIR GROUND CARTREQUIREMENTS USING BOTH CONNECTORS

25

20

17

15

10

5

3

1

1

3 2

4

5

6

PRESS

UREATGROUNDCONNECTION(INCHE

SOFWATER)

40

35

30

25

20

15

10

7

5

2

PRES

SUREATGROUNDCONNECTION(INCH

ESOFWATER)

(F)

(C)

30 50 70 90 110

0 10 20 30 40

AIR SUPPLY TEMPERATURE

(F)

(C)

(kg/MIN)

(LB/MIN)

600

500

400

300

200

100

TOTALAIRFLOW

260

220

180

140

100

60

(kg/MIN)

(LB/MIN)CONDITIONED AIR GROUND CART

REQUIREMENTS USING ONE CONNECTOR

103F (39C) DAY

(29C)

(21C), NO CABIN OCCUPANTS,FIVE CREW MEMBERS ONLY

SOLAR IRRADIATION), 0F (18C) DAY

(29C) DAY

(40C) DAY

190F (88C)


81/126

512

5.8GROUNDTOWINGREQUIREMENTS

MODELMD-11

TOTALTRACTIONWHEELLOAD

600

20

40

60

80

0

10

20

30

40

40 200

(1,000LB)

(1,000kg)

30

20

10 0

DRAWBARPULL

(1,000kg)

(1,000LB)

633600

500

400

300

(1,000kg)

(1,000LB)

300

250

200

150

100

AIRPLANE

GROSSWEIGHT

0

1

2

3

4

PERCENTSL

OPE

UNUSUALBREAKAWAYCON

DITIONSNOTREFLECTED

ESTIMATEDFORTOW

VEHIC

LESWITHRUBBERTIRES

COEFFICIENTSOFFRICTION

(m)

APPROXIMATE

WET

ASPHALT

m=0.75

ICEm

=0.05

DRYCONCRETEORASPHALTm

=0.8

HARDSNOW

m

=0.2

BACKING

AGAINST

GROUND

IDLE

THRUST

NO

ENGINE

THRUST

550

450

350

250

REV E

WETCONCRETE

m

=0.57


82/126

5-13

REV E



83/126

6.0 OPERATING CONDITIONS

6.1 Jet Engine Exhaust Velocities and

Temperatures

6.2 Airport and Community Noise


84/126

61

6.0 OPERATING CONDITIONS6.1 JET ENGINE EXHAUST VELOCITIES AND TEMPERATURES

6.1.1 JET ENGINE EXHAUST VELOCITY CONTOURS, IDLE POWER (ESTIMATED)MODEL MD-11 GE ENGINE

80

NOTES: 1. ENGINE CF6-80C2

2. THESE CONTOURS ARE TO BE USED AS GUIDELINES ONLY SINCE THE

OPERATIONAL ENVIRONMENT VARIES GREATLY OPERATIONAL SAFETY

ASPECTS ARE THE RESPONSIBILITY OF THE USER OR PLANNER

3. ALL VELOCITY VALUES ARE STATUTE MILES PER HOUR

4. CROSSWINDS WILL HAVE CONSIDERABLE EFFECT ON CONTOURS

5. SEA LEVEL STATIC STANDARD DAY

6. ALL ENGINES AT SAME THRUST60

40

20

0

20

15

5

FEET METERS

80

60

40

20

0

20

15

10

5

FEET METERS

0 15 30 45 60 75 90 105 120 135 150

0 50 100 150 200 250 300 350 400 450 500FEET

METERS

-100

4535

4535

AXIAL DISTANCE BEHIND AIRPLANE

PLAN

ELEVATION

45 35 4535

GROUND PLANE

CONVERSION FACTOR

1 MPH = 1.6 km PER HOUR

HEIGHTABOVEGROUND

CL

DIS

TANCEFROM

AIRPLANECL

10


85/126

62

6.1.1 JET ENGINE EXHAUST VELOCITY CONTOURS, IDLE POWER (ESTIMATED)MODEL MD-11 P&W ENGINE

80

NOTES: 1. ENGINE PW4460

2. THESE CONTOURS ARE TO BE USED AS GUIDELINES ONLY SINCE THE

OPERATIONAL ENVIRONMENT VARIES GREATLY OPERATIONAL SAFETY

ASPECTS ARE THE RESPONSIBILITY OF THE USER OR PLANNER

3. ALL VELOCITY VALUES ARE STATUTE MILES PER HOUR

4. CROSSWINDS WILL HAVE CONSIDERABLE EFFECT ON CONTOURS

5. SEA LEVEL STATIC STANDARD DAY

6. ALL ENGINES AT SAME THRUST60

40

20

0

20

15

10

FEET METERS

80

60

40

20

0

20

15

10

5

FEET METERS

0 15 30 45 60 75 90 105 120 135 150

0 50 100 150 200 250 300 350 400 450 500

ELEVATION

FEET

METERS

100


GROUND PLANECONVERSION FACTOR

1 MPH = 1.6 km PER HOUR

35

35

35

35

CL

DIS

TANCEFROM

A

IRPLANECL

HEIGHTABOVEGROUND

PLAN

5


86/126

63

6.1.2 JET ENGINE EXHAUST VELOCITY CONTOURS, BREAKAWAY POWER (ESTIMATED)MODEL MD-11 GE ENGINE


87/126

64

6.1.2 JET ENGINE EXHAUST VELOCITY CONTOURS, BREAKAWAY POWER (ESTIMATED)MODEL MD-11 P&W ENGINE

80

NOTES: 1. ENGINE PW40002. THESE CONTOURS ARE TO BE USED AS GUIDELINES ONLY SINCE THE

OPERATIONAL ENVIRONMENT VARIES GREATLY OPERATIONAL SAFETYASPECTS ARE THE RESPONSIBILITY OF THE USER OR PLANNER

3. ALL VELOCITY VALUES ARE STATUTE MILES PER HOUR4. CROSSWINDS WILL HAVE CONSIDERABLE EFFECT ON CONTOURS5. RAMP GRADIENT WILL AFFECT REQUIRED TAXI AND BREAKAWAY THRUST6. SEA LEVEL STATIC STANDARD DAY7. ALL ENGINES AT SAME THRUST8. 605,500 LB GROSS WEIGHT

60

40

20

0

20

15

10

FEET METERS

80

60

40

20

0

20

15

10

5

FEET METERS

0 15 30 45 60 75 90 105 120 135 150

0 50 100 150 200 250 300 350 400 450 500

PLAN

ELEVATION

FEET

METERS

100


GROUND PLANECONVERSION FACTOR1 MPH = 1.6 km PER HOUR

CL

DISTANCEFRO

M

AIRPLANECL

HEIGHTABOVEGROUND

35

45

6075

354560

75

5


88/126

65

6.1.3 JET ENGINE EXHAUST VELOCITY CONTOURS, TAKEOFF POWER (ESTIMATED)MODEL MD-11 GE ENGINE

80

NOTES: 1. ENGINE CF6-80C2D1F2. THESE CONTOURS ARE TO BE USED AS GUIDELINES ONLY SINCE THE

OPERATIONAL ENVIRONMENT VARIES GREATLY OPERATIONAL SAFETYASPECTS ARE THE RESPONSIBILITY OF THE USER OR PLANNER.

3. ALL VELOCITY VALUES ARE STATUTE MILES PER HOUR.4. CROSSWINDS WILL HAVE CONSIDERABLE EFFECT ON CONTOURS5. SEA LEVEL STATIC STANDARD DAY6. ALL ENGINES AT SAME THRUST

60

40

20

0

20

15

10

FEET METERS

80

60

40

20

0

20

15

10

5

FEET METERS

0 15 30 45 60 75 90 105 120 135 150

0 50 100 150 200 250 300 350 400 450 500FEET

METERS

-100


PLAN

ELEVATION GROUND PLANE

CONVERSION FACTOR1 MPH = 1.6 km PER HOUR

HEIGHTABOVEGROUND

35

45

60

75

100

3545

60

100150

200

75

CL

DISTANCEFROM

AIRPLANECL

150

2005


89/126

66

6.1.3 JET ENGINE EXHAUST VELOCITY CONTOURS, TAKEOFF POWER (ESTIMATED)MODEL MD-11 P&W ENGINE

80

NOTES: 1. ENGINE PW44602. THESE CONTOURS ARE TO BE USED AS GUIDELINES ONLY SINCE THE

OPERATIONAL ENVIRONMENT VARIES GREATLY OPERATIONAL SAFETYASPECTS ARE THE RESPONSIBILITY OF THE USER OR PLANNER

3. ALL VELOCITY VALUES ARE STATUTE MILES PER HOUR4. CROSSWINDS WILL HAVE CONSIDERABLE EFFECT ON CONTOURS5. SEA LEVEL STATIC STANDARD DAY6. ALL ENGINES AT SAME THRUST

60

40

20

0

20

15

10

FEET METERS

80

60

40

20

0

20

15

10

5

FEET METERS

0 15 30 45 60 75 90 105 120 135 150

0 50 100 150 200 250 300 350 400 450 500

PLAN

ELEVATION

FEET

METERS

100


GROUND PLANECONVERSION FACTOR1 MPH = 1.6 km PER HOUR

CL

DISTANCEFROM

AIRPLANECL

HEIGHTABOVE

GROUND

35 MPH TO 1,865 FT (568 m)

35

45

60

75

100

150200

45 MPH TO 1,365 FT (416 m)

60 MPH TO 945 FT (288 m)

75 MPH TO 710 FT (216 m)

3545

6075

100150200

35 MPH TO 1,865 FT (568 m)

5


90/126

67

6.1.4 Jet Engine Exhaust Temperature (MD-11, All Engine Models)

Jet engine exhaust temperature contour lines have not been presented because the adverse effects of

exhaust temperature at any given position behind the aircraft fitted with these high-bypass engines are

considerably less than the effects of exhaust velocity.


91/126

68

6.2 Airport and Community Noise

Airport noise is of major concern to the airport and community planner. The airport is a major element of

the communitys transportation system and, as such, is vital to its growth. However, the airport must alsobe a good neighbor, and this can be accomplished only with proper planning. Since aircraft noise extends

beyond the boundaries of the airport, it is vital to consider the impact on surrounding communities. Many

means have been devised to provide the planner with a tool to estimate the impact of airport operations.

Too often they oversimplify noise to the point where the results become erroneous. Noise is not a simple

subject; therefore, there are no simple answers.

The cumulative noise contour is an effective tool. However, care must be exercised to ensure that the

contours, used correctly, estimate the noise resulting from aircraft operations conducted at an airport.

The size and shape of the single-event contours, which are inputs into the cumulative noise contours, aredependent upon numerous factors. They include:

1. Operational Factors

(a) Aircraft Weight Aircraft weight is dependent on distance to be traveled, en route

winds, payload, and anticipated aircraft delay upon reaching the destination.

(b) Engine Power Settings The rates of ascent and descent and the noise levels emitted at

the source are influenced by the power setting used.

(c) Airport Altitude Higher airport altitude will affect engine performance and thus can

influence noise.

2. Atmospheric Conditions Sound Propagation

(a) Wind With stronger headwinds, the aircraft can take off and climb more rapidly

relative to the ground. Also, winds can influence the distribution of noise in surrounding

communities.

(b) Temperature and Relative Humidity The absorption of noise in the atmosphere along

the transmission path between the aircraft and the ground observer varies with bothtemperature and relative humidity.

3. Surface Condition Shielding, Extra Ground Attenuation (EGA)

Terrain If the ground slopes down after takeoff or up before landing, noise will be reduced

since the aircraft will be at a higher altitude above the ground. Additionally, hills, shrubs,

trees, and large buildings can act as sound buffers.


92/126

69

All of these factors can alter the shape and size of the contours appreciably. To demonstrate the effect of

some of these factors, estimated noise level contours for two different operating conditions are shown

below. These contours reflect a given noise level upon a ground level plane at runway elevation.

As indicated by these data, the contour size varies substantially with operating and atmospheric

conditions. Most aircraft operations are, of course, conducted at less than maximum gross weights

because average flight distances are much shorter than maximum aircraft range capability and average

load factors are less than 100 percent. Therefore, in developing cumulative contours for planning

purposes, it is recommended that the airlines serving a particular city be contacted to provide operational

information.

In addition, there are no universally accepted methods for developing aircraft noise contours or for

relating the acceptability of specific noise zones to specific land uses. It is therefore expected that noise

contour data for particular aircraft and the impact assessment methodology will be changing. To ensure

that currently available information of this type is used in any planning study, it is recommended that it be

obtained directly from the Office of Environmental Quality in the Federal Aviation Administration in

Washington, D.C.

It should be noted that the contours are shown here only to illustrate the impact of operating and

atmospheric conditions and do not represent the single-event contour of the family of aircraft described in

this document. It is expected that the cumulative contours will be developed as required by planners using

the data and methodology applicable to their specific study.

REV E

CONDITION 1CONDITION 2

CONDITION 1

LANDING:

MAXIMUM DESIGN LANDING WEIGHT

10-KNOT HEADWIND

3-DEG APPROACH

84oF

HUMIDITY 15%

TAKEOFF:

MAXIMUM DESIGN TAKEOFF WEIGHT

ZERO WIND

84oF

HUMIDITY 15%

CONDITION 2

LANDING:

85% OF MAXIMUM DESIGN LANDING WEIGHT

10-KNOT HEADWIND

3-DEG APPROACH

59oF

HUMIDITY 70%

TAKEOFF:

80% OF MAXIMUM DESIGN TAKEOFF WEIGHT

10-KNOT HEADWIND

59oF

HUMIDITY 70%


93/126


94/126

71

7.0 PAVEMENT DATA


A brief description of the following pavement charts will facilitate their use for airport planning. Each

airplane configuration is shown with a minimum range of four loads imposed on the main landing gear to

aid in interpolation between the discrete values shown. All curves are plotted at constant specified tire

pressure at the highest certified weight for each model.

Subsection 7.2 presents basic data on the landing gear footprint configuration, tire sizes, and tire

pressures.

Subsection 7.3 lists maximum vertical and horizontal pavement loads at the tire ground interfaces for

certain critical conditions.

Subsection 7.4 presents a chart showing static loads imposed on the main landing gear struts for theoperational limits of the airplane. These main landing gear loads are used for interpreting the pavement

design charts. All pavement requirements are based on the wing gear because the center gear is less

demanding under normal conditions.

Subsection 7.5 presents a pavement requirement chart for flexible pavements. Flexible pavement design

curves are based on the format and procedures set forth in Instruction Report No. S-77-1, Procedures for

Development of CBR Design Curves, published in June 1977 by the U.S. Army Engineer Waterways

Experiment Station, Soils and Pavements Laboratory, Vicksburg, Mississippi.

The following procedure is used to develop the flexible pavement curves:

1. Having established the scale for pavement depth at the bottom and the scale for CBR at the

top, an arbitrary line is drawn representing 6,000 annual departures.

2. Values of the aircraft gross weight are then plotted.

3. Additional annual departure lines are drawn based on the load lines of the aircraft gross

weights already established.

4. An additional line is drawn to represent 10,000 coverages, statistically the number of maximumstresses the aircraft causes in the pavement. This is used to calculate the flexible pavement Aircraft

Classification Number.

Subsection 7.6 provides LCN conversion curves for flexible pavements. These curves have been plotted

using procedures and curves in the International Civil Aviation Organization (ICAO) Aerodrome Design

Manual, Part 3 Pavements, Document 9157-AN/901, 1977. The same charts have plots of equivalent

single-wheel load versus pavement thickness.


95/126

REV D

72

Subsection 7.7 provides rigid pavement design curves prepared with the use of the Westergaard equations

in general accord with the relationships outlined in the 1955 edition of Design of Concrete Airport

Pavement, published by the Portland Cement Association, 33 W. Grand Ave., Chicago, Illinois, but

modified to the new format described in the 1968 Portland Cement Association publication, Computer

Program for Airport Pavement Design by Robert G. Packard. The following procedure is used to develop

the rigid pavement design curves.

1. Having established the scale for pavement thickness to the left and the scale for allowable

working stress to the right, an arbitrary load line is drawn representing the main landing gear

maximum weight to be shown.

2. All values of the subgrade modulus (K-values) are then plotted using the maximum load line,

as shown.

3. Additional load lines for the incremental value of weight on the main landing gear are then

established on the basis of the curve for K = 300 lb/in.3already established.

Subsection 7.8 presents LCN conversion curves for rigid pavements. These curves have been plotted

using procedures and curves in the ICAO Aerodrome Design Manual, Part 3 Pavements, Document

9157-AN/901, 1977. The same charts include plots of equivalent single-wheel load versus radius of

relative stiffness. The LCN requirements are based on the condition of center-of-slab loading. Radii of

relative stiffness values are obtained from Subsection 7.8.1.

Subsection 7.9 provides ACN data prepared according to the ACN-PCN system described in Aerodromes,

Annex 14 to the Convention on International Civil Aviation. ACN is the Aircraft Classification Number

and PCN is the corresponding Pavement Classification Number.

ACN-PCN provides a standardized international airplane/pavement rating system replacing the various S,

T, TT, LCN, AUW, ISWL, etc., rating systems used throughout the world. An aircraft having an ACN

equal to or less than the PCN can operate without restriction on the pavement. Numerically, the ACN is

two times the derived single-wheel load expressed in thousands of kilograms, where the load is on a

single tire inflated to 1.25 MPa (181 psi) that would have the same pavement requirements as the aircraft.

Computationally, the ACN-PCN system uses PCA program PDILB for rigid pavements and S-77-1 for

flexible pavements to calculate ACN values. The method of pavement evaluation is the responsibility of

the airport, with the results of its evaluation presented as follows:


96/126

73

Chap7Text64

PAVEMENTTYPECODE

RIGID

FLEXIBLE

R

F

SUBGRADECATEGORYCODE

HIGH(K = 150

MN/M3)(OR CBR= 15%)

MEDIUM(K = 80MN/M3)(OR CBR= 10%)

LOW(K = 40MN/M3)(OR CBR= 6%)

ULTRALOW(K = 20MN/M3)(OR CBR= 3%)

A

B

C

D

TIREPRESSURECATEGORYCODE

HIGH

(NO LIMIT)

MEDIUM(LIMITED TO1.5 MPa)

LOW(LIMITED TO1.0 MPa)

VERY LOW(LIMITED TO0.5 MPa)

W

X

Y

Z

EVALUATIONMETHODCODE

TECHNICAL

USINGAIRCRAFT

T

U

PAVEMENTCLASSIFI-

CATIONNUMBERPCN

(BEARINGSTRENGTHFOR UN-RESTRICTEDOPERATIONS)

(s)

REPORT EXAMPLE: PCN 80/R/B/W/T


97/126

74

7.2 FOOTPRINTMODEL MD-11

MAXIMUMRAMP WEIGHT 633,000 LB (287,129 kg)

PERCENT OF WEIGHT ON MAIN GEAR SEE SECTION 7.4

NOSE TIRE SIZE 40 x 15.5 16

NOSE TIRE PRESSURE 180 PSI (12.7 kg/cm2)

WING AND CENTER GEAR TIRE SIZE H54 x 21.0 24

WING GEAR TIRE PRESSURE 206 PSI (14.4 kg/cm2)

CENTER GEAR TIRE PRESSURE 180 PSI (12.7 kg/cm2)

25 IN. (64 cm)

80 FT 9 IN. (24.61 m)

54 IN. (137 cm)

TYP

64 IN. (163 cm)TYP

37.5 IN.(95 cm)

41 FT 3 IN.(12.57 m)

35 FT(10.67 m)

30 IN. (76 cm)

REV E


98/126

75

7.3 MAXIMUM PAVEMENT LOADSMODEL MD-11

VN

HW

HC

VW VC

PAVEMENT LOADS FOR CRITICAL COMBINATIONS OF WEIGHT AND CG POSITIONSVN = VERTICAL NOSE GEAR GROUND LOAD PER STRUTVW= VERTICAL WING GEAR GROUND LOAD PER STRUTVC = VERTICAL CENTER GEAR GROUND LOAD PER STRUTHW = HORIZONTAL WING GEAR GROUND LOAD PER STRUT FROM BRAKINGHC = HORIZONTAL CENTER GEAR GROUND LOAD PER STRUT FROM BRAKING

LB 633,000 54,900 93,000 245,400 80,800 170,000 106,300 35,000 73,600

kg 287,129 24,903 42,184 111,313 36,651 77,112 48,218 15,876 33,385

MODELMD-11

RAMPWEIGHT STATIC

STEADYBRAKING* STATIC

STEADYBRAKING*

INSTBRAKING** STATIC

STEADYBRAKING*

INSTBRAKING**

NOSE GEAR (1)FORWARD CG

WING GEAR (2)AFT CG

CENTER GEAR (1)AFT CG

VN VN VW HW VC HC

* AIRCRAFT DECELERATION = 10 FT/SEC 2. HWAND HCASSUME DEC ELERATION FROM B RAKING ONLY** INSTANTANEOUS BRAKING; COEFFICIENT OF FRICTION = 0.8

REV E


99/126

REV E

76

7.4 Landing Gear Loading on Pavement

7.4.1 Loads on the Main Landing Gear Group

For the MD-11, the main gear group consists of two wing gears plus one center gear.

In the example for the MD-11, the gross weight is 470,000 pounds, the percent of weight on the main

gears is 94.33 percent, and the total weight on the three main gears is 443,351 pounds.


100/126

77

7.4 LANDING GEAR LOADING ON PAVEMENTMODEL MD-11

PERCENT WEIGHT ON MAIN GEAR

600

80 85 90 95 100

550

500

450

400

350

300

250

200

650

CG FOR ACNCALCULATIONS

W

EIGHTONMAINLANDINGGEARGROUP(1,0

00LB)

AIRCRAFTGROSS

WEIGHT(1

,000LB)

275

250

225

200

175

150

125

100

600

550

500

450

400

350

300

250

AIRCRAFTGROSSWEIGHT(1,0

00kg)

PERCENT MAC

0 5 10 15 20 25 30 35 633

650

300

REV E

94.33

506.4


101/126

78

7.5 Flexible Pavement Requirements U.S. Army Corps of Engineers Method (S-77-1)

To determine the airplane weight that can be accommodated on a particular flexible pavement, the

thickness of the pavement, the subgrade CBR, and the annual departure level must be known.

In the example shown for the MD-11, for a CBR of 7.0, an annual departure level of 6,000, and a flexible

pavement thickness of 36 inches, the main gear group loading is 450,000 pounds.

The line showing 10,000 coverages is used for ACN calculations, which are shown in another subsection.


102/126

79

7.5 FLEXIBLE PAVEMENT REQUIREMENTSU.S. ARMY CORPS OF ENGINEERS/FAA DESIGN METHOD

MODEL MD-11

REV E

PAVEMENT THICKNESS (IN)

* 20 YEAR SERVICE LIFE

10,000 COVERAGES

(USED FOR ACN

CALCULATIONS)

MAX POSSIBLE MAIN

GEAR GROUP LOAD

AT MAX RAMP WEIGHT

AND AFT CG

1,200

3,000

6,000

15,000

25,000

ANNUAL

DEPARTURES*

WEIGHT ON

MAIN GEARS

LB KG

250,000 (113,398)

300,000 (136,078)

350,000 (158,758)

400,000 (181,437)

450,000 (204,119)

500,000 (226,799)

597,100 (270,845)

SUBGRADE STRENGTH (CBR)

3 4 5 76 8 9 10 20 30 40 50

3 4 5 76 8 9 10 20 30 40 50

NOTE: H54 x 21.0-24 TIRES; TIRE PRESSURE CONSTANT AT 206 PSI (14.5 kg/cm )2


103/126

710

7.6 Flexible Pavement Requirements, LCN Conversion

To determine the airplane weight that can be accommodated on a particular flexible airport pavement,

both the LCN of the pavement and the thickness (h) of the pavement must be known.

In the example for the MD-11, the flexible pavement thickness is 30 inches, the LCN is 76, and the main

landing gear group weight is 350,000 pounds.


104/126

711

7.6 FLEXIBLE PAVEMENT REQUIREMENTS LCN CONVERSIONMODEL MD-11

FLEXIBLE PAVEMENTTHICKNESS (IN.)

150

160

10 15 20 30 40 50 6070 80

NOTE: EQUIVALENT SINGLE-WHEEL LOADS ARE DERIVED BY METHODS SHOWN IN ICAO AERODROME MANUAL,PART 2, PAR. 4.1.3

1

Documents

Airport Planning MD11.pdf