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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
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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
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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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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1.0 SCOPE
1.1 Purpose
1.2 Introduction
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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
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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:
Boeing Commercial Airplane Group
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
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13
REV E
THIS PAGE INTENTIONALLY LEFT BLANK
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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
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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)
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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)
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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
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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
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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
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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
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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)
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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
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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)
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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)
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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)
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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)
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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)
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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
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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)
GROSS WEIGHT3,500 LB EACH(1,587.6 kg)
TARE WEIGHT320 LB EACH(145.2 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
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2.6.2 CARGO COMPARTMENTS CONTAINERS/PALLETS
MODEL MD-11
GROSS WEIGHT10,300 LB EACH(4,672.1 kg)
TARE WEIGHT248 LB EACH(112.5 kg)
GROSS WEIGHT3,500 LB EACH(1,587.6 kg)
TARE WEIGHT320 LB EACH(145.2 kg)
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
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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)
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2.7.1 CLEARANCES, PASSENGER LOADING DOORS, DOOR NO. 2MODEL MD-11
DMC00519
PLAN VIEW
A
A
76 IN.(193 cm)
FLOOR
DOOR ACTUATOR HANDLE
SEE SECTION 2.3 FORHEIGHT ABOVE GROUND
ELEVATION
SECTION A-ALOOKING FORWARD
AIRPLANENOSE 48 FT 1 IN.
(14.66 m)
UPWARD INTERIORSLIDING DOOR
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
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2.7.1 CLEARANCES, PASSENGER LOADING DOORS, DOOR NO. 3MODEL MD-11
DMC00520
PLAN VIEW
A
A
76 IN.(193 cm)
FLOOR
DOOR ACTUATOR HANDLE
SEE SECTION 2.3 FORHEIGHT ABOVE GROUND
ELEVATION
SECTION A-ALOOKING FORWARD
AIRPLANENOSE
95 FT 2 IN.
(29.01 m)
UPWARD INTERIORSLIDING DOOR
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
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2.7.1 CLEARANCES, PASSENGER LOADING DOORS, DOOR NO. 4MODEL MD-11
DMC00521
PLAN VIEW
A
A
FLOOR
DOOR ACTUATOR HANDLE
SEE SECTION 2.3 FORHEIGHT ABOVE GROUND
ELEVATION
SECTION A-ALOOKING FORWARD
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)
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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
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2.7.2 CARGO LOADING DOORS MAIN DECK
MODEL MD-11 COMBI
SECTION A-ALOOKING FORWARD
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
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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
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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)
SEE SECTION 2.3 FORGROUND CLEARANCE
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
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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
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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
SEE SECTION 2.3 FORGROUND CLEARANCE
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)
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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
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3-1
3.0 AIRPLANE PERFORMANCE
3.1 General Information
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:
Boeing Commercial Airplane Group
P.O. Box 3707
Seattle, Washington 98124-2207
USA
Attn: Manager, Airport Technology
Mail Code 67-KR
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4.0 GROUND MANEUVERING
4.1 General Information
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)
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4.0 GROUND MANEUVERING
4.1 General Information
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.
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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)
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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
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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
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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
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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
PATH OF MAINGEAR TIRE EDGE
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
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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
COCKPIT REFERENCE POINT
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
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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
15-FT (4.57 m) CLEARANCE LINE
REV E
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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)
COCKPIT REFERENCE POINT
15-FT (4.57 m) CLEARANCE LINE
(RUNWAY-TO-TAXIWAY DIRECTION)
ADDITIONAL FILLET REQUIRED
85-FT (25.91 m) R
150-FT (45.72 m) R
15-FT (4.57 m) CLEARANCE LINE
(TAXIWAY-TO-RUNWAY DIRECTION)
PATH OF MAIN GEAR TIRE EDGE
(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
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4.6 RUNWAY HOLDING BAY (APRON)MODEL MD-11
DMC00593
PATH OF MAIN GEAR TIRE EDGE
PATH OF NOSE GEAR TIRE
20 FT (6.10 m)
263 FT (80.16 m)
40 FT(12.19 m)
PATH OF NOSE GEAR
PATH OF MAINGEAR TIRE EDGE
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)
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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
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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.
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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
FUEL SERVICE VEHICLE
BULKCARGODOLLYTRAIN
BULK CARGOLOADER
LAVATORYSERVICEVEHICLE
LOWER DECK CARGOLOADER
CONTAINER DOLLYTRAIN
FUEL SERVICE VEHICLE
NOTE: THE AIRCRAFT AUXILIARY POWER UNIT SUPPLIESELECTRICAL, PNEUMATIC AIR, AND PRECONDITIONED AIR.
CARGO PALLET TRAIN
MAIN DECKCARGO LOADER
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5.0 TERMINAL SERVICING
5.1.3 AIRLINE SERVICING ARRANGEMENT TYPICAL TURNAROUND
MODEL MD-11F/CF
CARGO PALLET TRAIN
LOWER DECK CARGO
LOADER
FUEL SERVICE VEHICLE
BULK CARGOTRAILER
FUEL SERVICE VEHICLE
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
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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
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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
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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
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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
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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)
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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)
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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
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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)
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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
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6.0 OPERATING CONDITIONS
6.1 Jet Engine Exhaust Velocities and
Temperatures
6.2 Airport and Community Noise
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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
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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
AXIAL DISTANCE BEHIND AIRPLANE
GROUND PLANECONVERSION FACTOR
1 MPH = 1.6 km PER HOUR
35
35
35
35
CL
DIS
TANCEFROM
A
IRPLANECL
HEIGHTABOVEGROUND
PLAN
5
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6.1.2 JET ENGINE EXHAUST VELOCITY CONTOURS, BREAKAWAY POWER (ESTIMATED)MODEL MD-11 GE ENGINE
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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
AXIAL DISTANCE BEHIND AIRPLANE
GROUND PLANECONVERSION FACTOR1 MPH = 1.6 km PER HOUR
CL
DISTANCEFRO
M
AIRPLANECL
HEIGHTABOVEGROUND
35
45
6075
354560
75
5
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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
AXIAL DISTANCE BEHIND AIRPLANE
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
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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
AXIAL DISTANCE BEHIND AIRPLANE
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
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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.
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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.
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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%
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7.0 PAVEMENT DATA
7.1 General Information
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.
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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:
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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
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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
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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
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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.
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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
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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.
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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
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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.
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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