REPORT MDC K0388
REVISION “F”
ISSSUED MAY 2011
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 address to:
Boeing Commercial Airplanes
P.O. Box 3707
Seattle, Washington 98124-2207
U.S.A.
Attention: Manager, Airport Technology
Mail Code: 20-93
Email:
[email protected]
REVISIONS
MD-11 AIRPLANE CHARACTERISTICS FOR AIRPORT PLANNING
REV. A NOV. 12, 1990 PAGE 2–2 2–3 2–14 2–15 3–1 3–2 3–3 3–4 3–5 3–6 3–7 3–8 3–9 3–10 3–1 1 3–12 3–13 3–14 3–15 3–16 3–17 REV. B FEB. 2, 1991 PAGE 2–2 2–3 2–5 2–25 2–27 4–4 4–5 4–8 5–12 7–4 7–5 7–7 7–9 7–1 1 7–13 7–15 7–21 7–22 7–23 7–24 REV. C MAY 22, 1991 PAGE 5–7 7–7 4–3 REV. D NOV. 30, 1993 PAGE 2–2 2–3 2–4 2–5 2–16 2–18 2–23 2–24 2–25 2–27 Section 3 4–3 4–7 5–3 5–12 6–9 7–2 7–4 7–5 7–6 7–7 7–9 7–11 7–13 7–15 7–21 7–22 7–23 7–24 REV. E AUG. 31, 1998 PAGE 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
REVISIONS (CONTINUED)
MD-11 AIRPLANE CHARACTERISTICS FOR AIRPORT PLANNING
REV. F JUNE 2010
PAGE MAY 2011 PAGE 7-1
7-18 7-21
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
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
1.0 SCOPE
1.1 Purpose 1.2 Introduction
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 the using 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
1-2 MAY 2011
1.2 Introduction
This document conforms to NAS 3601. It provides 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.
For further information contact:
Boeing Commercial Airplanes
P.O. Box 3707
Seattle, Washington 98124-2207
U.S.A.
Attention: Manager, Airport Technology
Mail Code: 20-93
Email:
[email protected]
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
2.0 AIRPLANE DESCRIPTION
2.1 General Airplane Characteristics — MD-11
Maximum Design Taxi Weight (MTW). Maximum weight for ground maneuvering as limited by aircraft strength (MTOW plus taxi fuel).
Maximum Design Landing Weight (MLW). Maximum weight for landing as limited by aircraft strength and airworthiness requirements.
Maximum Design Takeoff Weight (MTOW). Maximum weight for takeoff as limited by aircraft strength and airworthiness requirements. (This is the maximum weight at the start of the takeoff run.)
Operating Empty Weight (OEW). Weight of structure, power plant, furnishing, systems, unusable fuel and other unusable propulsion agents, and other items of equipment that are considered part of a particular airplane configuration. OEW also includes certain standard items, personnel, equipment, and supplies necessary for full operations, excluding usable fuel and payload.
Maximum Design Zero Fuel Weight (MZFW). Maximum weight allowed before usable fuel and other specified usable agents must be loaded in defined sections of the aircraft as limited by strength and airworthiness requirements.
Maximum Payload. Maximum design zero fuel weight minus operational empty weight. Maximum Seating Capacity. The maximum number of passengers certified or anticipated for certification.
Maximum Cargo Volume. The maximum space available for cargo. Usable Fuel. Fuel available for aircraft propulsion.
2.0 AIRPLANE
DESCRIPTION
2.1 GENERAL
AIRPLANE
CHARACTERISTICS
MODEL MD-1
1
GE
ENGINE
MAXIMUM DESIGN T AXI WEIGHT* MAXIMUM DESIGN T AKEOFF WEIGHT MAXIMUM DESIGN LANDING WEIGHT OPERA TING EMPTY WEIGHT MAXIMUM DESIGN ZERO FUEL WEIGHT MAXIMUM P A YLOAD (WEIGHT -LIMITED) MAXIMUM SEA TING CAP ACITYMAXIMUM CARGO VOLUME MAXIMUM USABLE
FUEL MODEL ENGINE P ASSENGER COMBI (6 P ALLET) FREIGHTER CF6-80C2 CF6-80C2 CF6-80C2 * OPTIONAL MTW : 608,500 LB (276,016 kg) 613,000 LB (278,057 kg) 621,000 LB (281,686 kg) 628,000 LB (284,861 kg) 633,000 LB (287,122 kg) CONVERTIBLE FREIGHTER CF6-80C2 LB kg LB kg LB kg LB kg LB kg LB kg STD MAX FT 3 m 3 U.S. GAL liters LB kg 605,500 274,655 602,500 273,294 430,000 195,048 283,975 128,808 400,000 181,440 116,025 52,632 323 410 5,566 157.6 38,615 146,173 258,721 117,356 P ASSENGER ’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 49,391 323 410 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 66,549 214 290 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 73,942 298 410 21,288 602.3 38,615 146,173 258,721 117,356 REV E
2.0 AIRPLANE
DESCRIPTION
2.1 GENERAL
AIRPLANE
CHARACTERISTICS
MODEL MD-1
1
P&W
ENGINE
MAXIMUM DESIGN T AXI WEIGHT* MAXIMUM DESIGN T AKEOFF WEIGHT MAXIMUM DESIGN LANDING WEIGHT OPERATING EMPTY WEIGHT
MAXIMUM DESIGN ZERO FUEL WEIGHT MAXIMUM P A YLOAD (WEIGHT -LIMITED) MAXIMUM SEA TING CAP ACITY MAXIMUM CARGO VOLUME MAXIMUM USABLE FUEL MODEL ENGINE P ASSENGER COMBI (6 P ALLET) FREIGHTER 4460 * OPTIONAL MTW : CONVERTIBLE FREIGHTER LB kg LB kg LB kg LB kg LB kg LB kg STD MAX FT 3 m 3 U.S. GAL liters LB kg 605,500 274,655 602,500 273,294 430,000 195,048 283,975 128,808 400,000 181,440 116,025 52,632 323 410 5,566 157.6 38,615 146,173 258,721 117,356 P ASSENGER ’ER’ 633,000 287,122 630,500 285,988 430,000 195,048 291,120 132,049 400,000 181,440 108,880 49,391 323 410 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 66,549 214 290 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 73,942 298 410 21,288 602.3 38,615 146,173 258,721 117,356 4460 4460 4460 4460 608,500 LB (276,016 kg) 613,000 LB (278,057 kg) 621,000 LB (281,686 kg) 628,000 LB (284,861 kg) 633,000 LB (287,122 kg)
2–4 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 SP AN 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 ENGINES 200 FT 11 IN. (61.2 m) WITH PW4460 ENGINES
SEE SECTION
VERTICAL CLEARANCE MIN CLEARANCE CRITICAL WT AND CG MAX CLEARANCE CRITICAL WT AND CG A B C D E F G H I J K L M N O P R S T U V W X 28 – 7 27 – 1 15 – 9 7 – 4 15 – 8 9 – 2 15 – 7 8 – 10 8 – 10 15 – 4 29 – 5 57 – 6 7 – 10 3 – 2 9 – 8 10 – 8 12 – 4 23 – 4 32 – 7 37 – 3 15 – 8 10 – 3 15 – 5 8.71 8.27 4.81 2.23 4.78 2.80 4.75 2.69 2.69 4.67 8.97 17.53 2.38 0.96 2.93 3.25 3.77 7.11 9.93 11.35 4.80 3.12 4.70 29 – 2 28 – 6 17 – 5 8 – 9 16 –11 10 – 3 16 – 3 9 – 9 9 – 9 16 – 3 30 – 9 58 – 10 8 – 5 4 – 5 10 – 5 11 – 7 13 – 4 25 – 7 33 – 6 38 – 2 17 – 1 11 – 4 16 – 3 8.89 8.69 5.31 2.67 5.16 3.12 4.95 2.97 2.97 4.95 9.37 17.93 2.57 1.35 3.17 3.53 4.06 7.80 10.21 11.63 5.21 3.45 4.95
FT – IN. METERS FT – IN. METERS
* = GE CF6–80C2 D1F
H = STANDARD CENTER CARGO DOOR V = FREIGHTER
I = COMBI CENTER CARGO DOOR X = COMBI MAIN DECK DOOR
2.3 GROUND CLEARANCES
MODEL MD-11
36.89 IN. (93.70 cm) R GROUND 76.15 IN. (193.42 cm) A B C D F G X I/H J W K L P O M N R S T U WINGLET DETAIL· MAXIMUM AND MINIMUM CLEARANCES OF INDIVIDUAL LOCATIONS ARE GIVEN FOR COMBINATIONS OF AIRPLANE LOADING/UNLOADING ACTIVITIES THAT PRODUCE THE GREATEST VARIATION AT EACH LOCATION. ZERO ROLL ANGLE AND LEVEL GROUND WERE ASSUMED FOR ANALYSIS. · IT IS RECOMMENDED THAT APPROXIMATELY ± 3 INCHES (0.1 m) BE ALLOWED
FOR VERTICAL EXCURSIONS DUE TO VARYING STRUT AND TIRE INFLATIONS, PAVEMENT UNEVENNESS, ETC.
*
2.4
INTERIOR
ARRANGEMENTS
2.4.1
P
ASSENGERS –
MIXED-CLASS
SEA
TING
MODEL MD-1
1
GALLEY A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T A TTENDANT SEA T GALLEY A TTENDANT LA V A T OR Y SEA T LA V A T OR Y A TTENDANT SEA T GALLEY A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T GALLEY A TTENDANT SEA T LA V A T OR Y CLOSET LA V A T OR Y 2R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 2L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 1R ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm) 1L ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm) CLOSET 3R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 3L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 4R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 4L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm)323
SEA
TS,
34
FIRST
CLASS
— 6
ABREAST,
289
COACH
— 9
ABREAST
2.4.2
P
ASSENGERS –
ECONOMY
SEA
TING
MODEL
MD-11
GALLEY A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T GALLEY A TTENDANT LA V A T OR Y SEA T LA V A T OR Y A TTENDANT SEA T GALLEY A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T CLOSET GALLEY LA V A T OR Y A TTENDANT SEA T 1R ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm) 2L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 1L ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm) 3L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 4L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 2R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 3R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 4R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm)379
SEA
TS
— 9
ABREAST
2.4.3
P
ASSENGERS –
HIGH-DENSITY
SEA
TING
MODEL MD-1
1
GALLEY A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T A TTENDANT SEA T GALLEY A TTENDANT LA V A T OR Y SEA T LA V A T OR Y A TTENDANT SEA T GALLEY A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T A TTENDANT SEA T GALLEY CLOSET CLOSET LA V A T OR Y LA V A T OR Y 2R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 3R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 4R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 4L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 3L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 1R ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm) 2L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 1L ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm)410
SEA
TS
— 10
ABREAST
2. 4. 4
P
ASSENGERS
–
MIXED-CLASS
SEA
TING
MODEL MD-1
1
COMBI
C/A GALLEY A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T GALLEY A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T CLOSET GALLEY LA V A T OR Y A TTENDANT SEA T LA V A T OR Y 6 P ALLETS 1R ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm) 2R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 3R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 4R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) DEACTIV A TED 4L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) DEACTIV A TED 3L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 2L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 1L ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm)214
SEA
TS,
34
FIRST
CLASS
— 6
ABREAST,
180
COACH
— 9
ABREAST
GALLEY LA V A T OR Y CARGO DOOR 160 BY 102 IN. (406 BY 259 cm)2.4.5 P
ASSENGERS - ECONOMY SEA
TING
MODEL MD-11 COMBI
2L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 2R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) A TTEND ANT SEA T A TTEND ANT SEA T A TTEND ANT SEA T A TTEND ANT SEA T A TTEND ANT SEA T A TTEND ANT SEA T GALLEY GALLEY GALLEY GALLEY L AVA T O R Y L AVA T O R Y L AVA T O R Y L AVA T O R Y L AVA T O R Y L AVA T O R Y 1L ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm) 1R ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm) 3L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 3R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 4R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) DEA CTIV A TED 4L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) DEA CTIV A TED 6 P ALLETSCARGO DOOR 160 BY 102 IN.
(406 BY 259 cm)
261 SEA
TS - 9
ABREAST
G 2 G1 G3 G4 G5 S G10 REV E2. 4.
6
P
ASSENGERS
–
HIGH-DENSITY
SEA
TING
MODEL MD-1
1
COMBI
GALLEY A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T GALLEY A TTENDANT SEA T LA V A T OR Y A TTENDANT SEA T CLOSET GALLEY LA V A T OR Y A TTENDANT SEA T LA V A T OR Y 6 P ALLETS 1L ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm) 1R ENTR Y DOOR 32 BY 76 IN. (81.3 BY 193.0 cm) 2R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 3R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 4R ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) DEACTIV A TED 2L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 3L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) 4L ENTR Y DOOR 42 BY 76 IN. (106.7 BY 193.0 cm) DEACTIV A TED290
SEA
TS
— 10
ABREAST
LA V A T OR Y CARGO DOOR 160 BY 102 IN. (406 BY 259 cm)2.5 CABIN CROSS SECTION
2.5.1 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
3 IN. (TYP) (7.6 cm)
2.5.2 BUSINESS CLASS
MODEL 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 E2.5.3 ECONOMY
MODEL 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) (48.3 cm) (106.7 cm) 18 IN. (TYP)(45.7 cm) REV E2.5.4 HIGH-DENSITY
MODEL 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 E2.5.5 CROSS SECTION – CARGO
MODEL 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
LD5 LD7 LD9 LD11 LD21 LD3 LD6 (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 m3) (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 14L 15L 16L 17L 14C 13C 18C 64 IN. (162.6 cm) 102-IN. (259.1 cm) DOOR MAIN CARGO LOADED COMPARTMENT
LENGTH = 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 BARRIER NET 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
2.6 LOWER COMPARTMENT
2.6.1 CARGO COMPARTMENTS – CONTAINERS
MODEL MD-11
GROSS WEIGHT 7,000 LB EACH (3,175.2 kg) TARE WEIGHT 600 LB EACH (272.2 kg) GROSS WEIGHT 3,500 LB EACH (1,587.6 kg) TARE WEIGHT 320 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 ONLY 18 CONTAINERS
70- BY 66-IN. (177.8 BY 167.6 cm) CARGO DOOR RIGHT SIDE ONLY 14 CONTAINERS
BULK CARGO
BULK CARGO DOOR LEFT SIDE ONLY 30 BY 36 IN. (76.2 BY 91.4 cm)
2.6.2 CARGO COMPARTMENTS – CONTAINERS/PALLETS
MODEL MD-11
GROSS WEIGHT 10,300 LB EACH (4,672.1 kg) TARE WEIGHT 248 LB EACH (112.5 kg) GROSS WEIGHT 3,500 LB EACH (1,587.6 kg) TARE WEIGHT 320 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) 6–96 BY 125 PALLETS 2,667 FT3 (75.52 m3) 6–88 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 ONLY 6 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 ONLY
14 CONTAINERS
BULK CARGO DOOR LEFT SIDE ONLY 30 BY 36 IN. (76.2 BY 91.4 cm) 125 IN. (317.5 cm) 88 IN. (223.5 cm) 64 IN. (162.56 cm) CONTAINERS
CENTER COMP ARTMENT PALLETS FWD COMP ARTMENT 6–96 BY 125-IN. PALLETS EACH 444 FT3 (12.57 m3 ) TOTAL 2,664 FT3 (75.41 m3) 6–88 x 125 PALLETS EACH 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
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) FLOORDOOR ACTUATOR HANDLE
SEE SECTION 2.3 FOR HEIGHT ABOVE GROUND
ELEVATION FLOOR/DOOR SILL 96 IN. (244 cm) UPWARD INTERIOR SLIDING DOOR SECTION A-A LOOKING FOR WARD
121 IN. (307 cm)
183 IN.
(465 cm) 38 IN. (97 cm)
ÉÉÉÉÉÉ
ÉÉÉÉÉÉ
2.7.1 CLEARANCES, PASSENGER LOADING DOORS, DOOR NO. 2
MODEL MD-11
DMC005–19 PLAN VIEW A A 76 IN. (193 cm) FLOOR DOOR ACTUATOR HANDLESEE SECTION 2.3 FOR HEIGHT ABOVE GROUND
ELEVATION SECTION A-A LOOKING FORWARD AIRPLANE NOSE 48 FT 1 IN. (14.66 m) UPWARD INTERIOR SLIDING DOOR FLOOR/DOOR SILL CONSTANT SECTION 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
ÉÉÉÉÉ
ÉÉÉÉÉ
2.7.1 CLEARANCES, PASSENGER LOADING DOORS, DOOR NO. 3
MODEL MD-11
DMC005–20 PLAN VIEW A A 76 IN. (193 cm) FLOOR DOOR ACTUATOR HANDLESEE SECTION 2.3 FOR HEIGHT ABOVE GROUND
ELEVATION SECTION A-A LOOKING FORWARD AIRPLANE NOSE 95 FT 2 IN. (29.01 m) UPWARD INTERIOR SLIDING DOOR FLOOR/DOOR SILL CONSTANT SECTION 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
ÉÉÉÉÉ
ÉÉÉÉÉ
2.7.1 CLEARANCES, PASSENGER LOADING DOORS, DOOR NO. 4
MODEL MD-11
DMC005–21 PLAN VIEW A A FLOOR DOOR ACTUATOR HANDLESEE SECTION 2.3 FOR HEIGHT ABOVE GROUND
ELEVATION SECTION A-A LOOKING FORWARD AIRPLANE NOSE 155 FT 3 IN. (47.32 m) FWD FLOOR/DOOR SILL UPWARD INTERIOR
SLIDING 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)
2.7.2 CARGO LOADING DOORS – MAIN DECK
MODEL MD-11F/CF
DMC005–82 SECTION A-A LOOKING AFT 102-IN. (259 cm) DOOR ELEVATION PLAN VIEW A 140 IN. (356 cm) 102 IN. (259 cm) MAIN CARGO DOORCONSTANT SECTION DIA = 237 IN. (602 cm) 38 FT (11.6 m) A ÉÉÉÉÉ ÉÉÉÉÉ
SEE SEC. 2.3 FOR HEIGHT ABOVE GROUND 165 DEG POSITION FULL OPEN 85 DEG POSITION REV D 97.5-IN. (248 cm) STACK HEIGHT FREIGHTER 92.0-IN. (234 cm) STACK HEIGHT CONVERTIBLE FREIGHTER
2.7.2 CARGO LOADING DOORS – MAIN DECK
MODEL MD-11 COMBI
SECTION A-A LOOKING FOR WARD
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) AIRPLANE NOSE 141 FT 8 IN. (43.2 m) FLOOR FWD 102-IN. (259 cm) DOOR 97.5-IN. (248 cm) STACK HEIGHT REV E
2.7.3 CARGO LOADING DOORS, LOWER DECK
FORWARD DOOR
MODEL MD-11
DMC005–94 PLAN VIEW AIRPLANE NOSE 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) FLOORDOOR ACTUATOR PANEL SWITCH AND CONTROLS
ÉÉÉÉ
ÉÉÉÉ
SEE SECTION 2.3 FOR GROUND CLEARANCE
SECTION A-A
211.3 IN. (537 cm)
CRITICAL CLEARANCE LIMIT LOOKING FORWARD 19.7 IN.
(50 cm)
89.8 IN. (228 cm) CONSTANT SECTION DIA
= 237 IN. (602 cm)
135 DEG FULL OPEN
2.7.3 CARGO LOADING DOORS, LOWER DECK
CENTER CARGO DOOR
MODEL MD-11
DMC005–96 PLAN VIEW AIRPLANE NOSE 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 FOR GROUND CLEARANCE A A WING FILLET 144 FT 0 IN. (43.9 m) 70 IN. (178 cm) 15.9 IN. (40 cm)
DOOR ACTUATOR PANEL SWITCH AND CONTROLS
2.7.3 CARGO LOADING DOORS, LOWER DECK
CENTER CARGO DOOR (OPTIONAL FOR OTHER MODELS)
MODEL MD-11 COMBI
Chap2–Text PLAN VIEW AIRPLANE NOSE ELEVATION ÉÉÉÉ 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 FOR GROUND CLEARANCE 104 IN. (264 cm) A A WING FILLET 139 FT 7 IN. (42.55 m) 27 IN. DOOR ACTUATOR PANEL SWITCH AND CONTROL 44 IN. (112 cm) 116 IN. (295 cm) REV D
2.7.3 CARGO LOADING DOORS, LOWER DECK
AFT BULK CARGO DOOR
MODEL MD-11
PLAN VIEW AIRPLANE NOSE ELEVATION SECTION A-A CRITICAL CLEARANCE LIMITLOOKING FOR WARD 23.8 IN. (60 cm)
70.5 IN. (179 cm) 152 DEG FULL OPEN
SEE SECTION 2.3 FOR GROUND 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) REV E
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
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
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)
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, limited space, or high risk of jet blast damage. For these reasons, ground maneuvering requirements should be coordinated with the using airlines prior to layout planning.
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 CENTERSTURNING CENTERS
MAXIMUM
NOTE: ACTUAL OPERA TING DATA MAY BE GREATER THAN VALUES SHOWN SINCE TIRE SLIPP AGE IS NOT CONSIDERED IN THESE CALCULATIONS. CONSUL T AIRLINE FOR OPERATING PROCEDURES R3 MEASURED FROM OUTSIDE FACE OF TIRE.
STEERING ANGLE (DEG) R–1 R–2 R–3 R–4 R–5 R–6 153.7 120.2 95.5 76.3 60.7 47.6 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 18.5 14.5 11.1 8.0 5.3 2.7 194.9 161.4 136.7 117.5 101.9 88.8 77.5 67.6 58.5 50.2 59.4 49.2 41.7 35.8 31.1 27.1 23.6 20.6 17.8 15.3 194.0 164.3 143.5 128.2 116.6 107.8 100.9 95.6 91.4 88.2 59.1 50.1 43.7 39.1 35.5 32.9 30.8 29.1 27.9 26.9 262.6 229.5 205.2 186.4 171.2 158.5 147.6 138.0 129.4 121.5 80.0 70.0 62.5 56.8 52.2 48.3 45.0 42.1 39.4 37.0 205.7 178.2 159.4 145.9 136.1 128.7 123.1 118.8 115.6 113.8 62.7 54.3 48.6 44.5 41.5 39.2 37.5 36.2 35.2 34.7 220.2 189.5 167.7 151.3 138.5 128.3 119.9 112.9 107.0 102.0 67.1 57.8 51.1 46.1 42.2 39.1 36.5 34.4 32.6 31.1 25 30 35 40 45 50 55 60 65 70 MAXIMUM TURNING CENTER FOR ILLUSTRATION PURPOSES
STEERING ANGLES (DEGREES)
4.3 MINIMUM TURNING RADII
MODEL MD-11
TAIL R6 X NOSE TIRE R3 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 TRACKMEASURED 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 8–DEG MAIN GEAR TIRE SCRUB TYPE TURN EFFECTIVE TURN ANGLE TIRE SLIP ANGLE X FT/m Y FT/m A FT/m R3 FT/m R4 FT/m R5 FT/m R6 FT/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 2 1 SLIP
4.4 VISIBILITY FROM COCKPIT IN STATIC POSITION
MODEL MD-11
DMC005–42 ÉÉ
ÉÉ
PILOT’S EYE POSITION
PILOT’S EYE POSITION 36 DEG 20 DEG 20 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 VISION WITH HEAD ROTATED ABOUT SPINAL COLUMN
PILOT’S EYE POSITION 21 IN. (53.3 cm) 40 DEG 31 DEG 45 DEG WITH HEAD MOVED 14 IN. OUTBOARD (35.6 cm) 45 DEG 31 DEG 40 DEG
NOT TO BE USED FOR LANDING APPROACH VISIBILITY
4.5 RUNWAY AND TAXIWAY TURN PATHS
4.5.1 MORE THAN 90-DEG TURN – RUNWAY TO TAXIWAY
MANEUVERING METHOD – COCKPIT OVER CENTERLINE
MODEL MD–11
DMC005-89 75 FT (22.86 m) ÉÉ ÉÉCOCKPIT REFERENCE POINT
15 FT (4.57 m) CLEARANCE LINE
PATH OF MAIN GEAR TIRE EDGE 150-FT R (45.72 m) 150 FT (45.72 m) RUNWAY CENTER-LINE 45 DEG
NOTE: THE MINIMUM MAIN GEAR TIRE-TO-TAXIWAY
PAVEMENT EDGE CLEARANCE SHOWN IS APPROXIMATELY 15 FT (4.57 m) TAXIWAY CENTER-LINE ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ 100-FT R (30.48 m) ADDITIONAL FILLET REQUIRED REV B
4.5.2 MORE THAN 90-DEGREE TURN – RUNWAY TO TAXIWAY
MANEUVERING METHOD — JUDGMENTAL OVERSTEERING
MODEL MD–11
DMC005–88 100-FT R (30.48 m) 150-FT R (45.72 m) 75 FT (22.86 m) É É CL CL 45 DEG 150 FT (45.72 m)PATH OF NOSE GEAR TIRE EDGE 15 FT (4.57 m ) CLEARANCE LINE TAXIWAY CENTERLINE RUNWAY CENTERLINE PATH OF MAIN GEAR 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 APPROXIMATELY 15 FT (4.57 m)
15 FT (4.57 m) CLEARANCE LINE
4.5.3 90-DEGREE TURN – TAXIWAY TO TAXIWAY
MANEUVERING METHOD — COCKPIT OVER CENTERLINE
MODEL MD-11
DMC005–90
75 FT (22.86 m)
NOTE: THE MINIMUM MAIN GEAR TIRE-TO-TAXIWAY PAVEMENT EDGE CLEARANCE SHOWN IS APPROXIMATELY 15 FT (4.57 m)
PATH OF MAIN GEAR TIRE EDGE (AIRCRAFT DIRECTION AS SHOWN)
75 FT (22.86 m) CL TAXIWAY CENTERLINE PATH OF COCKPIT REFERENCE POINT
COCKPIT REFERENCE POINT
É É 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
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
4.5.5 90-DEGREE TURN – RUNWAY TO TAXIWAY
MANEUVERING METHOD — COCKPIT OVER CENTERLINE
MODEL MD–11
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
4.6 RUNWAY HOLDING BAY (APRON)
MODEL MD-11
DMC005–93
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 MAIN GEAR TIRE EDGE
20 FT (6.10 m) 15 FT (4.57 m) TAXIWAY CENTERLINE RUNWAY CENTERLINE 20 FT (6.10 m) SHOULDER
NOTE: THE MINIMUM MAIN GEAR TIRE-TO-PAVEMENT EDGE CLEARANCE SHOWN IS APPROXIMATELY 15 FT (4.57 m) 97 FT (29.57 m) ÉÉ ÉÉ É É PATH OF NOSE GEAR 150 FT (45.72 m) 75 FT (22.86 m) ÉÉ ÉÉ
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
5.0 TERMINAL SERVICING
5.1 AIRPLANE SERVICING ARRANGEMENT (TYPICAL)
5.1.1 AIRPLANE SERVICING ARRANGEMENT — TYPICAL TURNAROUND
MODEL MD-11
DMC005–43 É
É
É
CARGO PALLET TRAIN
CARGO LOADER EXTENSION
LOWER DECK CARGO LOADER GALLEY SERVICE VEHICLES TOW VEHICLE POTABLE WATER VEHICLE PASSENGER LOADING BRIDGES
FUEL SERVICE VEHICLE
CABIN SERVICE VEHICLE BULK CARGO DOLLY TRAIN BULK CARGO LOADER LAVATORY SERVICE VEHICLE GALLEY SERVICE VEHICLE
LOWER DECK CARGO LOADER
CONTAINER DOLLY TRAIN
FUEL SERVICE VEHICLE
NOTE: THE AIRCRAFT AUXILIARY POWER UNIT SUPPLIES ELECTRICAL, PNEUMATIC AIR, AND PRECONDITIONED AIR.
5.0 TERMINAL SERVICING
5.1.2 AIRPLANE SERVICING ARRANGEMENT — TYPICAL TURNAROUND
MODEL MD-11 COMBI
DMC005–44 ÉÉ
ÉÉ ÉÉ
CARGO PALLET TRAIN CARGO LOADER EXTENSION
LOWER DECK CARGO LOADER GALLEY SERVICE VEHICLES TOW VEHICLE POTABLE WATER VEHICLE PASSENGER LOADING BRIDGE FUEL SERVICE VEHICLE
BULK CARGO DOLLY TRAIN BULK CARGO LOADER LAVATORY SERVICE VEHICLE LOWER DECK CARGO LOADER
CONTAINER DOLLY TRAIN
FUEL SERVICE VEHICLE
NOTE: THE AIRCRAFT AUXILIARY POWER UNIT SUPPLIES ELECTRICAL, PNEUMATIC AIR, AND PRECONDITIONED AIR.
CARGO PALLET TRAIN
MAIN DECK CARGO LOADER
5.0 TERMINAL SERVICING
5.1.3 AIRLINE SER VICING ARRANGEMENT — TYPICAL TURNAROUND
MODEL MD-11F/CF
CARGO PALLET TRAIN
LOWER DECK CARGO LOADER
FUEL SERVICE VEHICLE
BULK CARGO TRAILER FUEL SERVICE VEHICLE
MAIN-DECK CARGO LOADER
BULK CARGO LOADER
CREW STAIRS
CARGO PALLET TRAIN
LOWER DECK CARGO LOADER WITH LD–3
NOTE: THE AIRCRAFT AUXILIARY POWER UNIT SUPPLIES ELECTRICAL, PNEUMATIC, AND PRECONDITIONED AIR
CONTAINER DOLLY TRAIN
5.2 TERMINAL
OPERA
TIONS,
TURNAROUND
5.2.1 TURNAROUND
MODEL MD-1
1
ENGINE RUNDOWN 1.0 CHECK LOGBOOK 1.5 W ALKAROUND INSPECTION 9.0 CHECK LOGBOOK 1.5 MONIT OR ENGINES 3.0 CLEAR FOR DEP AR TURE 1.0 POSITION P ASSENGER BRIDGE 0.5 DEPLANE P ASSENGERS 5.6 CABIN SERVICING (9-MAN CREW)
19.5 SER VICE FOR W ARD AND MID GALLEY 25.6 SER
VICE AFT GALLEY
27.1 ENPLANE P ASSENGERS 16.2 REMOVE P ASSENGER BRIDGE 0.5 FOR W ARD CONT AINER REMOV AL 18.0 AFT CONT AINER REMOV AL 14.0 BULK CARGO REMOV AL 12.8 FOR W ARD CONT AINER LOADING 18.0 AFT CONT AINER LOADING 14.0 BULK CARGO LOADING 12.8 FUEL SER VICES 16.6 LA V A T OR Y SER VICE 15.3 POT ABLE W A TER SER VICE 13.8 OPERA TIONS MIN
COCKPIT CREW VICE PASSENGER SER BAGGAGE AND CARGO OTHER SERVICE 50 40 30 20 10 TIME (MINUTES) 51.4 MINUTES NOTES: 1. CRITICAL TIME P A TH 4. 1,562-GPM REFUELING RA TE USING TWO HYDRANT VEHICLES 2. ESTIMA TES BASED ON 34 FIRST CLASS AND 289 COACH 5. UPPER GALLEY CONFIGURA TION WITH FWD, MID, AND AFT GALLEYS 3. DEPLANING AND ENPLANING THROUGH DOORS NO. 1 AND 2 6. AFT GALLEY CLOSED OFF DURING P A R T OF P ASSENGER ENPLANEMENT DUTIES
5.3 TERMINAL
OPERA
TIONS,
EN
ROUTE
ST
A
TION
MODEL MD-1
1
ENGINE RUNDOWN 1.0 CHECK LOGBOOK 1.5 W ALKAROUND INSPECTION 9.0 CHECK LOGBOOK 1.5 MONIT OR ENGINES 3.0 CLEAR FOR DEP AR TURE 1.0 POSITION P ASSENGER BRIDGE 0.5 DEPLANE P ASSENGERS 3.0 CABIN SERVICING (2-MAN CREW)
6.7 SER VICE MID GALLEY 7.6 SER VICE FOR W ARD AND AFT GALLEY 6.7 ENPLANE P ASSENGERS 9.0 REMOVE P ASSENGER BRIDGE 0.5 FOR W ARD CONT AINER REMOV AL 10.0 AFT CONT AINER REMOV AL 8.0 BULK CARGO REMOV AL 7.1 FOR W ARD CONT AINER LOADING 7.7 AFT CONT AINER LOADING 6.2 BULK CARGO LOADING 7.1 FUEL SER VICES (TIME A V AILABLE) 12.0 LA V A T OR Y SER VICE 9.1 POT ABLE W A TER SER VICE 5.4 OPERA TIONS MIN
COCKPIT CREW VICE PASSENGER SER BAGGAGE AND CARGO OTHER SERVICE
20 10 TIME (MINUTES) 23.6 MINUTES NOTES: 1. CRITICAL TIME P A TH 5. 962-GPM REFUELING RA TE USING TWO TRUCKS 2. 55 -PERCENT LOAD FACT OR; 17 FIRST CLASS AND 160 COACH 6. UPPER GALLEY CONFIGURA TION WITH FWD, MID, AND AFT GALLEYS 3. DEPLANING THROUGH DOORS NO. 1 AND 2 7. AFT GALLEY CLOSED OFF DURING P A R T OF P ASSENGER ENPLANEMENT 4. ENPLANING FIRST CLASS PSGRS THROUGH NO. 1 DOOR AND COACH PSGRS THROUGH NO. 2 DOOR 30 DUTIES
5.4 GROUND SERVICE CONNECTIONS
MODEL MD–11
SCALE 0 5 m 0 10 20 FT ÉÉ ÉÉ ÉÉ 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 ELECTRICAL FUEL LAVATORY FUEL VENT FUEL VENT DMC005–48 LAVATORY5.4 GROUND
SER
VICE
CONNECTION
DA
T
A
MODEL MD-1
1
5.4.1 HYDRAULIC SYSTEM TWO SER VICE CONNECTIONS: A. SER VICE PANEL CONT AINING PRESSURE AND TEST ST AND CONNECTIONS, 3,000 PSI (21 MPa) A T 50 GPM (189 lPM) MAXIMUM B. RESER VOIR FILL CONNECTIONS, 60 PSI (414 kP A) 5.4.2 ELECTRICAL SYSTEM TWO SER VICE CONNECTIONS, 90 KV A, EA. 1 15 VOL T, 400 HZ , 3 PHASE 5.4.3 OXYGEN — INDEPENDENT AIRCREW AND P ASSENGER SYSTEMS AIRCREW OXYGEN SYSTEM PASSENGER OXYGEN SYSTEM
5.4.4 FUEL SYSTEM TWO PRESSURE SER VICE POINTS IN EACH WING LEADING EDGE. 1,250 GPM (4,731 lPM) THROUGH 2 POINTS — 1,600 GPM (6,056 lPM) THROUGH 4 POINTS A T 50 PSIG (345 kP A) TOT AL USABLE CAP ACITY 38,652 U.S. GALLONS (146,296 l) 6,075 U.S. GALLONS (22,945 l) EACH WING T ANK 1 AND 2 9,767.9 U.S. GALLONS (36,968 l) NUMBER 2 T ANK 13,001 U.S. GALLONS (49,208 l) CTR WING AUX T ANK UPPER 1,643 U.S. GALLONS (6,217 l) UNDER WING AUX T ANK LOWER 2,000 U.S. GALLONS (7,570 l) T AIL AUX T ANK RIGHT WING SER VICE RECEPT ACLES LEFT WING SER VICE RECEPT ACLES FUEL
VENT WING RIGHT
FUEL VENT WING LEFT T AIL AUX T ANK VENT 5.4.5 PNEUMA TIC SYSTEM TWO 3-IN. SER VICE CONNECTIONS FOR ENGINE ST AR T AND AIR CONDITIONING 5.4.6 PRECONDITIONED AIR TWO 8-IN. CONNECTIONS FOR AIR CONDITIONING 5.4.7 POT ABLE W A TER SYSTEM ONE SER VICE CONNECTION FOUR-T ANK SYSTEM 64 U.S. GALLONS EACH (242 l) — T O T AL SYSTEM CAP ACITY 256 GAL (969 LITERS) 5.4.8 LA V A TOR Y SYSTEM NUMBER OF T OILETS SER VICE LOCA TION 1 ( 1) FORW ARD ( 2) UP T O 12 AFT SER VICE CAP ACITIES W ASTE HOLDING 260 U.S. GALLONS (984 l) DIST ANCE AFT OF NOSE DIST ANCE FROM AIRPLANE CENTERLINE HEIGHT ABOVE GROUND MAXIMUM METERS FT — IN. MINUMUM METERS FT — IN. METERS FT — IN. METERS FT — IN. RIGHT SIDE LEFT SIDE METERS FT — IN. 126 – 0 1 18 – 10 30 – 6 107 – 10 107 – 10 32.87 32.87 38.40 36.22 9.30 3 – 4 1 – 2 1.02 0.36 9 – 1 2.77 9 – 8 2.95 9 – 5 2.87 10 – 0 3.05 7 – 4 2.24 8 – 9 2.67 124 – 3 58 – 4 179 – 9 15 – 8 42 – 3 12.88 42– 3 12.88 14 – 8 14 – 8 4.47 4.47 15 – 5 15 – 5 4.70 4.70 25 – 2 7.67 6 – 7 2.01 10 – 10 3.30 12 – 4 3.76 15 – 2 4.62 6 – 2 1.88 12 – 3 3.73 13 – 1 1 4.24 40 – 6 12.34 3 – 4 1.02 8 – 0 2.44 9 – 1 2.77 13 – 10 (2) 4.22 (2) 9 – 5 (2) 2.87 (2) 10 – 8 (2) 3.25 (2) 163 – 8 49.89 9 – 9 2.97 1 1 – 3 3.43 ( 1) FREIGHTER – 1 T OILET FOR W ARD LOCA TION ( 2) FREIGHTER ONL Y CYLINDER IN A VIONICS COMP ARTMENT , CONNECTED T O MANIFOLD. POR T ABLE CYLINDER
FOR CREW INFLIGHT
COMP ARTMENT . CHEMICAL OXYGEN SYSTEM IN MODULES IN OVERHEAD ST ORAGE RACKS, LA V A T ORIES, AND A TTENDANT ST A-TIONS, POR T ABLE CYLINDERS FOR FIRST AID 37.87 37.87 54.79 17.78 4.78 4 – 2 1.27 124 – 3 58 – 4 17.78 14 – 0 14 – 0 19 – 4 5.89 15 – 1 15 – 1 21 – 3 6.48 C L C L C L C L C L C L C L C L 4.27 4.27 4.60 4.60
5.5 ENGINE STARTING PNEUMATIC REQUIREMENTS
MODEL MD-11 GE ENGINE
DMC005–49 0 10 20 30 40 50 60 70 80 140 120 100 60 REQUIRED AIRFLOW (LB/MIN) (PSIA) 160 80 200 180 220 240 –40 –20 0 20 40 60 80 100 120 20 REQUIRED PRESSURE A T GROUND 30 50 40 60 70 CONNECT OR (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 PNEUMATIC SYSTEM PRESSURE 51 PSIG (65.7 PSIA AT SEA LEVEL)
MAXIMUM ALLOWABLE PNEUMATIC SYSTEM TEMPERATURE 500°F (260°C)
MAXIMUM ALLOWABLE PNEUMATIC SYSTEM PRESSURE 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 CAN BE DEPICTED. THE LINE DEPICTED IS FOR A 46-SECOND START TIME, WHICH IS AN ARBITRARY VALUE.
PRESSURE AT GROUND CONNECTOR
AMBIENT AIR TEMPERATURE
(°F)
5.5 ENGINE STARTING PNEUMATIC REQUIREMENTS
MODEL MD-11 P&W ENGINE
DMC005–50 0 10 20 30 40 50 60 70 80 250 200 150 50 REQUIRED AIRFLOW (LB/MIN) PSIA 300 100 400 350 –40 –20 0 20 40 60 80 100 120 20 REQUIRED PRESSURE A T GROUND 30 50 40 60 70 CONNECT OR (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) PW4460
MAXIMUM ALLOWABLE PNEUMATIC SYSTEM PRESSURE 51 PSIG (65.7 PSIA AT SEA LEVEL)
MAXIMUM ALLOWABLE PNEUMATIC SYSTEM TEMPERATURE 500°F (260°C)
MAXIMUM ALLOWABLE PNEUMATIC SYSTEM PRESSURE 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 CAN BE 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)
5.6 GROUND PNEUMATIC POWER REQUIREMENTS
MODEL MD-11
DMC005–51 0 20 40 60 80 280 240 200 LB/MIN 320 400 360 1.0 1.2 1.4 1.6 1.8AIR SUPPLY PRESSURE (kg/cm2 ABS) T O T A L AIRFLOW (kg/MIN) 180 160 140 120 100 HEATING
MINUTES TO HEAT CABIN TO 75°F (24°C)
• INITIAL CABIN TEMPERATURE –25°F (–32°C) • DULL DAY
• OUTSIDE AIR TEMPERATURE –40°F (–40°C) • NO CABIN OCCUPANTS OR ELECTRICAL LOAD
• MAX TEMPERATURE AT GROUND CONN 440°F (227°C) • MAX ALLOWABLE SUPPLY PRESSURE 45 PSIG
• MIN TEMPERATURE NOT LESS THAN 200°F (93°C) • BOTH GROUND CONNECTIONS USED
ABOVE O.A.T • THREE-PACK OPERATION
• DOORS CLOSED 0 20 40 60 80 250 200 LB/MIN300 400 350 1.0 1.2 1.4 1.6 1.8 T O T A L AIRFLOW (kg/MIN) 180 160 140 120 100
AIR SUPPLY PRESSURE (kg/cm2 ABS)
COOLING
MINUTES TO COOL CABIN TO 75 F (24 C)
• INITIAL CABIN TEMPERATURE 115°F (46°C) • BRIGHT DAY
• OUTSIDE AIR TEMPERATURE 103°F (40°C) REL HUM 42% • NO CABIN OCCUPANTS OR ELECTRICAL LOAD
• MAX TEMPERATURE AT GROUND CONN 440°F (227°C) • MAX ALLOWABLE SUPPLY PRESSURE 45 PSIG
• MIN TEMPERATURE NOT LESS THAN 200°F (93°C) • BOTH GROUND CONNECTIONS USED
ABOVE O.A.T • THREE-PACK OPERATION
• DOORS CLOSED
100
16 20 24 28
(PSIA)
DMC005–53–54
5.7 PRECONDITIONED AIRFLOW REQUIREMENTS
MODEL MD-11
AIR SUPPLY TEMPERATURE 600 30 50 70 90 110 500 400 300 200 100 T O T A L AIRFLOW 260 220 180 140 100 60 0 10 20 30 40
MAXIMUM ALLOWABLE PRESSURE AT GROUND CONNECTION (25 INCHES WATER)
1 3 2 4 5 6 1 2 3 4 5 6 CABIN AT 75°F (24°C), 410 OCCUPANTS, BRIGHT DAY (SOLAR IRRADIATION),
SAME AS 1 EXCEPT CABIN AT 85°F
SAME AS 1 EXCEPT CABIN AT 70°F
CABIN AT 70°F (21°C), 50 CABIN OCCUPANTS, OVERCAST DAY (NO
SAME AS 4 EXCEPT –20°F
SAME AS 4 EXCEPT –40°F
MAXIMUM ALLOWABLE TEMPERATURE CONDITIONED AIR GROUND CART
REQUIREMENTS USING BOTH CONNECTORS
25 20 17 15 10 5 3 1 1 3 2 4 5 6 PRESSURE A T
GROUND CONNECTION (INCHES OF W
A TER) 40 35 30 25 20 15 10 7 5 2 PRESSURE A T
GROUND CONNECTION (INCHES OF W
A TER) (°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 T O T A L AIRFLOW 260 220 180 140 100 60 (kg/MIN) (LB/MIN)
CONDITIONED AIR GROUND CART REQUIREMENTS USING ONE CONNECTOR
103°F (39°C) DAY
(29°C)
(21°C), NO CABIN OCCUPANTS, FIVE CREW MEMBERS ONLY
SOLAR IRRADIATION), 0°F (–18°C) DAY
(–29°C) DAY
(–40°C) DAY
5.8 GROUND
T
OWING
REQUIREMENTS
MODEL MD-1
1
T O T A L TRACTION WHEEL LOAD 60 0 2 0 4 06 08 0 0 1 0 2 03 04 0 40 20 0 (1,000 LB) (1,000 kg) 30 20 10 0 DRA WBAR PULL (1,000 kg) (1,000 LB) 633 600 500 400 300 (1,000 kg) (1,000 LB) 300 250 200 150 100 AIRPLANE GROSS WEIGHT 01234 PERCENT SLOPE·
UNUSUAL BREAKA W A Y CONDITIONS NOT REFLECTED·
ESTIMA TED FOR T OW VEHICLES WITH RUBBER TIRES·
COEFFICIENTS OF FRICTION ( m ) — APPROXIMA TE WET ASPHAL T m = 0.75 ICE m = 0.05 DR Y CONCRETE OR ASPHAL T m = 0.8 HARD SNOW m = 0.2BACKING AGAINST GROUND
IDLE THRUST NO ENGINE THRUST 550 450 350 250 REV E WET CONCRETE m = 0.57
6.0 OPERATING CONDITIONS
6.1 Jet Engine Exhaust Velocities and Temperatures
6–1
6.0 OPERATING CONDITIONS
6.1 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 THRUST 60 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 50 100 150 200 250 300 350 400 450 500 FEET METERS -100 45 35 45 35
AXIAL DISTANCE BEHIND AIRPLANE PLAN ELEVATION 45 35 45 35 GROUND PLANE CONVERSION FACTOR 1 MPH = 1.6 km PER HOUR HEIGHT ABOVE GROUND CL DIST ANCE FROM AIRPLANE C L 10
6–2
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 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 ELEVATION FEET METERS –100
AXIAL DISTANCE BEHIND AIRPLANE
GROUND PLANE CONVERSION FACTOR 1 MPH = 1.6 km PER HOUR 35 35 35 35 CL DIST ANCE FROM AIRPLANE C L HEIGHT ABOVE GROUND PLAN 5
6–3
6.1.2 JET ENGINE EXHAUST VELOCITY CONTOURS, BREAKAWAY POWER (ESTIMATED)
MODEL MD-11 GE ENGINE
6–4
6.1.2 JET ENGINE EXHAUST VELOCITY CONTOURS, BREAKAWAY POWER (ESTIMATED)
MODEL MD-11 P&W ENGINE
80
NOTES: 1. ENGINE PW4000
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. RAMP GRADIENT WILL AFFECT REQUIRED TAXI AND BREAKAWAY THRUST 6. SEA LEVEL STATIC — STANDARD DAY
7. ALL ENGINES AT SAME THRUST 8. 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 PLANE CONVERSION FACTOR 1 MPH = 1.6 km PER HOUR CL DIST ANCE FROM AIRPLANE C L HEIGHT ABOVE GROUND 35 45 60 75 35 45 60 75 5
6–5
6.1.3 JET ENGINE EXHAUST VELOCITY CONTOURS, TAKEOFF POWER (ESTIMATED)
MODEL MD-11 GE ENGINE
80
NOTES: 1. ENGINE CF6-80C2D1F
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 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 FEET METERS -100
AXIAL DISTANCE BEHIND AIRPLANE PLAN
ELEVATION GROUND PLANE
CONVERSION FACTOR 1 MPH = 1.6 km PER HOUR HEIGHT ABOVE GROUND 35 45 60 75 100 35 45 60 100 150 200 75 CL DIST ANCE FROM AIRPLANE C L 150 200 5
6–6
6.1.3 JET ENGINE EXHAUST VELOCITY CONTOURS, TAKEOFF 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 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 PLANE CONVERSION FACTOR 1 MPH = 1.6 km PER HOUR CL DIST ANCE FROM AIRPLANE C L HEIGHT ABOVE GROUND 35 MPH TO 1,865 FT (568 m) 35 45 60 75 100 150 200 45 MPH TO 1,365 FT (416 m) 60 MPH TO 945 FT (288 m) 75 MPH TO 710 FT (216 m) 35 45 60 75 100 150 200 35 MPH TO 1,865 FT (568 m) 5
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.
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 community’s transportation system and, as such, is vital to its growth. However, the airport must also be 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, are dependent 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 both temperature 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.
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.
CONDITION 1 CONDITION 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
7.0 PAVEMENT DATA
7.1 General Information 7.2 Footprint
7.3 Maximum Pavement Loads
7.4 Landing Gear Loading on Pavement 7.5 Flexible Pavement Requirements 7.6 Flexible Pavement Requirements, LCN
Conversion
7.7 Rigid Pavement Requirements 7.8 Rigid Pavement Requirements, LCN
Conversion
7.9 ACN-PCN Reporting System; Flexible and Rigid Pavements
