MCDONNELL DOUGLAS CORPORATION DOUGLAS AIRCRAFT COMPANY DC/MD-10 AIRPLANE CHARACTERISTICS FOR AIRPORT PLANNING DAC-67803A REPRINTED JANUARY 1991 REVISION A APRIL 2004
DC/MD-10 AIRPLANE CHARACTERISTICS LIST OF REVISIONS Page Original 1 to 190
January 1991
Rev A Title Page iv v vi 2 5 135 136 137 138 140-A 141-A 163-A 164-A 165-A 166-A 167-A 168-A
April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004 April 2004
iv 133 134 162 163 164
June 2010 June 2010 June 2010 June 2010 June 2010 June 2010
2
May 2011
MAY 2011
Date
iv
CONTENTS Page 1.0 1.1 1.2 1.3 2.0 2.1 2.2 2.3 2.4 2.5 2.6 2.7 2.7.1 2.7.2 2.7.3 3.0 3.1 3.2 3.2.1 3.2.2 3.3 3.4 3.5 4.0 4.1 4.2 4.3 4.4 4.5 4.5.1 4.5.2 4.5.3 4.5.4 4.6 4.7 4.7.1 4.7.2 5.0 5.1 5.2 5.3 5.4 5.5 5.6 5.7 5.8
SCOPE ............................................................................................................................. Purpose ................................................................................................................... Introduction ............................................................................................................ Inclusion of MD-10-10F/-30F Information ........................................................... AIRPLANE DESCRIPTION ........................................................................................... General Airplane Characteristics ........................................................................... General Airplane Dimensions ................................................................................ Ground Clearances ................................................................................................. Interior Arrangements ............................................................................................ Passenger Cabin Cross Section .............................................................................. Lower Compartment Containers ............................................................................ Door Clearances ..................................................................................................... Passenger Loading Doors ............................................................................. Cargo Loading Doors ................................................................................... Critical Interference Path Door/Sill Wing Clearance ................................... AIRPLANE PERFORMANCE ....................................................................................... General Information ............................................................................................... Payload/Range ....................................................................................................... Payload/Range .............................................................................................. Payload/Range (Metric) ............................................................................... FAR Takeoff Runway Length Requirements ........................................................ FAR Landing Runway Length Requirements ........................................................ Approach Speed (Threshold) ................................................................................. GROUND MANEUVERING .......................................................................................... General Information ............................................................................................... Turning Radii, No Slip Angle ................................................................................ Minimum Turning Radii ........................................................................................ Visibility From Cockpit in Static Position ............................................................. Runway and Taxiway Turn Paths .......................................................................... More than 90º Turn – Runway to Taxiway .................................................. 90º Turn – Runway to Taxiway ................................................................... 90º Turn – Taxiway to Taxiway ................................................................... 90º Turn – Taxiway to Taxiway ................................................................... Runway Holding Bay Apron .................................................................................. Minimum Parking Space Requirements ................................................................ Minimum Parking Space Requirements (Feet) ............................................ Minimum Parking Space Requirements (Meters) ........................................ TERMINAL SERVICING .............................................................................................. Airplane Servicing Arrangement (Typical) ........................................................... Terminal Operations, Turnaround Station ............................................................. Terminal Operations, Enroute Station ................................................................... Ground Service Connections ................................................................................. Engine Starting Pneumatic Requirements .............................................................. Ground Pneumatic Power Requirements ............................................................... Preconditioned Airflow Requirements ................................................................... Ground Towing Requirements ...............................................................................
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1 1 2 2 3 3 6 12 14 18 25 29 30 34 41 43 43 44 44 52 60 64 67 69 69 70 72 74 75 75 77 79 81 83 85 85 88 91 91 93 99 105 113 116 117 118
CONTENTS Page 6.0 6.1 6.1.1 6.1.2 6.1.3 6.1.4 6.2 7.0 7.1 7.2 7.3 7.4 7.4.1 7.4.2 7.5 7.6 7.7 7.8 7.9 7.9.1 7.9.2 8.0 9.0
OPERATING CONDITIONS ......................................................................................... Jet Engine Exhaust Velocities and Temperatures .................................................. Jet Engine Exhaust Velocity Contours, Breakaway Power .......................... Jet Engine Exhaust Velocity Contours, Takeoff Power ............................... Jet Engine Exhaust Velocity Contours, Idle Power ..................................... Jet Engine Exhaust Temperature .................................................................. Airport and Community Noise ............................................................................... PAVEMENT DATA ....................................................................................................... General Information ............................................................................................... Footprint ................................................................................................................. Maximum Pavement Loads ................................................................................... Landing Gear Loading on Pavement ..................................................................... Loads on Main Landing Gear Group ........................................................... Center Gear and Wing Gear Loading on Pavement ..................................... Flexible Pavement Requirements, U.S. Army Corps of Engineers Design Method S-77-1 ........................................................................................... Flexible Pavement Requirements, LCN Conversion ............................................. Rigid Pavement Requirements, Portland Cement Association Design Method .... Rigid Pavement Requirements, LCN Conversion ................................................. ACN-PCN Reporting System ................................................................................ Aircraft Classification Numbers (ACNs) ..................................................... ACN-PCN System Background ................................................................... POSSIBLE DC-10/MD-10 DERIVATIVE AIRPLANES .............................................. SCALE DRAWINGS ......................................................................................................
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121 121 122 124 127 130 131 133 133 135 137 139 139 141 144 148 152 156 162 162 169 173 175
1.0
SCOPE 1.1 Purpose 1.2 Introduction 1.3 Inclusion of MD-10-10F/-30F Information
1.0
SCOPE 1.1
Purpose
This document provides, in a standardized format, the recommended minimum airplane characteristics data that are needed for general airport planning information. The DC-10 data in this document are for each series considering airport operations. Since operational practices vary among airlines, specific data should be coordinated with the using airlines prior to facility design. The Douglas Aircraft Company should be contacted for any additional information required. Content of the document reflects the results of a coordinated effort by representatives from the following organizations: Aerospace Industries Association Airport Operators’ Council International Air Transport Association of America International Air Transport Association
APRIL 2004
1
1.2
Introduction
This document conforms to NAS 3601. It provides McDonnell Douglas DC-10 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] Website: www.boeing.com/airports
1.3
Inclusion of MD-10-10F/-30F Freighter Information
This document has been partially revised to incorporate key information for the MD-1010F and MD-10-30F Freighters. The main change was the incorporation of the MD-11 landing gear tires and carbon brakes onto the MD-10-10F and the MD-10-30F Freighters. The general airplane characteristics table and select pages from section 7 of the document pertaining to pavement data were the only pages revised. All existing charts and diagrams for the DC-10 that were not revised can still be considered valid for the MD-1010F and MD-10-30F Freighters.
MAY 2011
2
SERIES
10CF
MODE
PSGR
ENGINE
30CF CARGO
PSGR
40CF CARGO
PSGR
MD-10-10F
MD-10-30F
CARGO
CARGO
CARGO
CF6-6D 443,000 443,000
CF6-50C 558,000 558,000
JT9D-59A* 558,000 558,000
CF6-6D 443,000
CF6-50C 583,000
200,942 363,500
200,942 363,500
253,105 411,000
253,105 411,000
253,105 411,000
253,105 411,000
200,942 375,000
264,444 436,000
164,881 440,000
164,881 440,000
186,427 555,000
186,427 555,000
186,427 555,000
186,427 555,000
170,097 440,000
197,766 580,000
199,581 243,750
199,581 215,444
251,744 268,751
251,744 238,036
251,744 272,773
251,744 242,058
199,581 216,000
263,084 236,500
110,563 335,000
97,724 335,000
121,904 391,000
107,971 391,000
123,728 391,000
109,796 391,000
97,976 355,000
107,275 414,000
151,954 91,250
151,954 119,556
177,355 122,249
177,355 152,964
177,355 118,227
177,355 148,942
161,025 139,000
187,787 177,500
41,390 4,597
54,230 16,845
55,451 4,618
69,383 16,866
53,627 4,618
67,559 16,866
63,049 14,200
80,512 14,200
130.17 255
477.05 0
130.77 255
477.65 0
130.77 255
477.65 0
402.1 0
402.1 0
U.S. GALLONS
399 21,762***
0 21,762***
399 36,652
0 36,652
399 36,652
0 36,652
0 21,762
0 36,652
LITERS
82,376
82,376
137,509
137,509
137,509
137,509
82,376
137,509
POUNDS MAXIMUM RAMP WEIGHT KILOGRAMS POUNDS MAXIMUM LANDING WEIGHT KILOGRAMS POUNDS MAXIMUM TAKEOFF WEIGHT KILOGRAMS POUNDS OPERATING WEIGHT EMPTY KILOGRAMS MAXIMUM ZERO FUEL WEIGHT
5
MAXIMUM STRUCTURAL PAYLOAD (WEIGHT LIMITED)
POUNDS KILOGRAMS POUNDS KILOGRAMS CUBIC FEET
MAXIMUM CARGO VOLUME CUBIC METERS SEATING CAPACITY (STD/MAX)
STANDARD MAXIMUM
USABLE FUEL CAPACITY
* FOR JT9D-20 ENGINE VERSION, SUBTRACT 515 POUNDS FROM OWE ** FOR NONEXTENDED CTR CARGO COMPARTMENT, REDUCE VOLUME 21 CU FT (SEE PAGE 27) ***FUEL CAPACITY WITH AUXILIARY CENTER WING TANK, 26,647 GALLONS FOR 572,000 POUND MTOGW: • ADD 379 POUNDS TO OWE AND SUBTRACT 379 POUNDS FROM MAXIMUM STRUCTURAL PAYLOAD • INCREASE LANDING WEIGHT TO 421,000 POUNDS
2.1 GENERAL AIRPLANE CHARACTERISTICS MODEL DC-10 SERIES 10CF, 30CF, 40CF, AND MD-10 SERIES 10F AND 30F April 2004
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68
7.0 PAVEMENT DATA 7.1 General Information A brief description of the pavement charts that follow will help in their use for airport planning. Each airplane configuration is depicted with a minimum range of four loads imposed on the main landing gear to aid in interpolation between the discrete values shown. All curves for any single chart represent data based on rated loads and tire pressures considered normal and acceptable by current aircraft tire manufacturer's standards. Section 7.2.1 and 7.2.2 present basic data on the landing gear footprint configuration, maximum design taxi loads, and tire sizes and pressures. Maximum pavement loads for certain critical conditions at the tire-to-ground interface are shown in Section 7.3.1 and 7.3.2. Pavement requirements for commercial airplanes are customarily derived from the static analysis of loads imposed on the main landing gear struts. Paragraph 7.4.1 and Figures 7.4.1 and 7.4.2 are provided in order to determine these loads throughout the stability limits of the airplane at rest on the pavement. These main landing gear loads are used as the point of entry to the pavement design charts, interpolating load values where necessary. The flexible pavement design curves paragraph 7.5 and Figures 7.5.1 through 7.5.3 are based on procedures set forth in Instruction Report No. S-77-1, "Procedures for Development of CBR Design Curves," dated June 1977, and as modified according to the methods described in ICAO Aerodrome Design Manual, Part 3, Pavements, 2nd Edition, 1983, Section 1.1 (The ACN/PCN Method), and utilizing the alpha factors approved by ICAO in October 2007. Instruction Report No. S-77-1 was prepared by the U.S. Army Corps of Engineers Waterways Experiment Station, Soils and Pavements Laboratory, Vicksburg, Mississippi. Rigid pavement design curves Paragraph 7.7 and Figures 7.7.1 through 7.7.3 have been prepared with the Westergaard equation in general accordance with the procedures outlined in the Design of Concrete Airport Pavement (1955 edition) by Robert G. Packard, published by the American Concrete Pavement Association, 3800 North Wilke Road, Arlington Heights, Illinois 60004-1268. These curves are modified to the format described in the Portland Cement Association publication XP6705-2, Computer Program for Airport Pavement Design (Program PDILB), 1968, by Robert G. Packard. The following procedure is used to develop the rigid pavement design curves such as those shown in Section 7.7.1 through 7.7.3: 133 JUNE 2010
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.
Values of the subgrade modulus (k) are then plotted as shown in Figures 7.7.1 through 7.7.3.
3.
Additional load lines for the incremental values of weight on the main landing gear are drawn on the basis of the curve for k = 300, already established.
All LCN curves have been plotted from data in the International Civil Aviation Organization (ICAO) document 7290-AM/865/2, Aerodrome Manual, Part 2, “Aerodrome Physical Characteristics,” 2nd Edition, 1965. On the same charts showing LCN verusus equivalent single wheel load, there are load plots showing equivalent single wheel load versus pavement thickness for flexible pavements and versus radius of relative stiffness for rigid pavements. Procedures and curves provided in the ICAO Aerodrome Manual – Part 2, Chapter 4 are used to determine equivalent single wheel loads for use in making LCN conversion of rigid pavement requirements.
ICAO has sdopted the ACN/PCN Reporting System, desribed in Paragraph 7.9, which will replace other strength reports systems.
134 JUNE 2010
72 FT 4.6 IN (22.06 M)
41 FT 3 IN(12.57 M) 35 FT(10.67 M)
24 IN (61 CM) 54 IN (137 CM) (TYPICAL)
MAXIMUM DESIGN TAXI WEIGHT PERCENT OF WEIGHT ON MAIN GEAR NOSE GEAR TIRE SIZE NOSE GEAR TIRE PRESSURE MAIN GEAR TIRE SIZE MAIN GEAR TIRE PRESSURE
UNITS LB KG
64 IN (163 CM) (TYPICAL)
SERIES 10 AND 10CF 458,000 207,746
%
MD-10-10F 443,000 200,941 SEE SECTION 7.4
IN. PSI KG/CM 2
37 x 14 - 14
37 x 14 - 14
165 11.60
165 11.60
IN. PSI KG/CM 2
50 X 20 - 20
H54 X 21 - 24
195 13.71
155 10.90
7.2.1 FOOTPRINT MODEL DC-10 SERIES 10, 10CF AND MD-10 SERIES 10F
April 2004
135
72 FT 4.6 IN (22.06 M)
30 IN. (76 CM)
37.5 IN. (95 CM)
35 FT(10.67 M)
25 IN (64 CM)
54 IN (137 CM) (TYPICAL)
MAXIMUM DESIGN TAXI WEIGHT PERCENT OF WEIGHT ON MAIN GEAR NOSE GEAR TIRE SIZE NOSE GEAR TIRE PRESSURE WING AND CENTER GEAR TIRE SIZE WING GEAR TIRE PRESSURE CENTER GEAR TIRE PRESSURE
64 IN (163 CM) (TYPICAL)
UNITS
SERIES 30, 30CF, 40, 40CF
MD-10-30F
LB KG
583,000 264,445
583,000 264,445
%
SEE SECTION 7.4
IN.
40 x 15.5 - 16
40 x 15.5 - 16
PSI KG/CM 2
185 13.01
185 13.01
IN.
52 X 20.5 - 23
H54 X 21 - 24
PSI KG/CM 2 PSI KG/CM 2
177 12.45
175 12.30
153 10.76
145 10.19
7.2 .2 FOOTPRINT MODEL DC-10 SERIES 30, 30CF, 40, 40CF AND MD-10 SERIES 30F
April 2004
41 FT 3 IN (12.57 M)
136
V N = MAXIMUM VERTICAL NOSE GEAR GROUND LOAD PER STRUT AT MOST FORWARD CENTER OF GRAVITY V W = MAXIMUM VERTICAL WING GEAR GROUND LOAD PER STRUT AT MOST AFT CENTER OF GRAVITY Hw = MAXIMUM HORIZONTAL GROUND LOAD PER STRUT FROM BRAKING NOTE: ALL LOADS CALCULATED USING AIRPLANE MAXIMUM DESIGN TAXI WEIGHT
NOSE GEAR VN AIRPLANE MODEL SERIES 10, 10CF MD-10- 10F FREIGHTER
Hw PER STRUT STEADY AT BRAKING INSTANTANEOUS BRAKING 10 FT/SEC2 DECEL (m = 0.8)
MAX DESIGN TAXI WEIGHT
STATIC AT MOST FWD C.G.
LB
458,000
50,243
84,959
213,680
71,501
170,944
KG LB KG
207,746 443,000 200,941
22,790 47,454 21,525
38,537 80,705 36,607
96,923 207,123 93,949
32,433 68,798 31,206
77,538 165,698 75,159
UNITS
STATIC + BRAKING 10 FT/SEC2
WING GEAR Vw MAX LOAD AT STATIC AFT C.G.
DECEL
7.3.1 MAXIMUM PAVEMENT LOADS MODEL DC-10 SERIES 10, 10CF AND MD-10 SERIES 10F April 2004
137
V N = MAXIMUM VERTICAL NOSE GEAR GROUND LOAD PER STRUT AT MOST FORWARD CENTER OF GRAVITY V W = MAXIMUM VERTICAL WING GEAR GROUND LOAD PER STRUT AT MOST AFT CENTER OF GRAVITY V C = MAXIMUM VERTICAL CENTER GEAR GROUND LOAD PER STRUT AT MOST AFT CENTER OF GRAVITY H W = MAXIMUM HORIZONTAL WING GEAR GROUND LOAD PER STRUT FROM BRAKING H C = MAXIMUM HORIZONTAL CENTER GEAR GROUND LOAD PER STRUT FROM BRAKING NOTE: ALL LOADS CALCULATED USING AIRPLANE MAXIMUM DESIGN TAXI WEIGHT
AIRPLANE MODEL
SERIES 30, 30CF, 40, 40CF MD-10- 30F FREIGHTER
UNITS
MAX DESIGN TAXI WT
LB
NOSE GEAR VN VN
Vw
WING GEAR Hw STEADY INST BRAKING BRAKING 10 (M=0.8) FT/SEC^2
CENTER GEAR Hc STEADY STATIC INST BRAKING AT AFT BRAKING 10 C.G. (M=0.8) FT/SEC^2 Vc
STATIC AT FWD C.G.
STATIC + BRAKING 10 FT/SEC^2
STATIC AT AFT C.G.
583,000
72,234
112,229
218,767
74,278
175,014
94,746
32,170
75,797
KG
264,445
32,965
50,906
99,231
33,692
67,454
42,976
14,952
29,215
LB
583,000
71,060
111,375
221,432
74,424
177,145
96,102
32,300
76,882
KG
264,445
32,232
50,518
100,440
33,758
80,352
43,591
14,651
34,873
7.3.2 MAXIMUM PAVEMENT LOADS MODEL DC-10 SERIES 30, 30CF, 40, 40CF AND MD-10 SERIES 30F April 2004
138
% MAC 10
15
20
25
30
AIRPLANE GROSS WEIGHT (1000 LB)
480
440
440
AIRPLANE GROSS WEIGHT (1000 KG) 200
MAXIMUM RAMP WEIGHT 443,000 LB
400
400
360
360
320
320
WEIGHT ON MAIN LANDING GEARS (1000 LB)
180
160
140
280
280 120
C.G. FOR ACN CALCULATIONS
240
240
100
200 80
85
90
95
200 100
7.4.1-A LANDING GEAR LOADING ON PAVEMENT MODEL MD-10 SERIES 10F April 2004
140-A
% MAC 10
15
20
25
30
AIRPLANE GROSS WEIGHT (1000 LB)
600
550
AIRPLANE GROSS WEIGHT (1000 KG) 260
550 MAXIMUM RAMP WEIGHT 583,000 LB 240
500
500 220
450
450
WEIGHT ON MAIN LANDING GEARS (1000 LB)
200
400
400
180
350
350
160
C.G. FOR ACN CALCULATIONS 300
140 300
120 250 80
85
90
95
250 100
PERCENT OF WEIGHT ON MAIN GEAR
7.4.2-A LANDING GEAR LOADING ON PAVEMENT MODEL MD-10 SERIES 30F
April 2004
141-A
7.9.1 AIRCRAFT CLASSIFICATION NUMBER - FLEXIBLE PAVEMENT MODEL DC-10 SERIES 10 AND 10CF 163 JUNE 2010
H54 X 21-24 36 PR TIRES PRESSURE CONSTANT AT 155PSI CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT 100
80
CODE D - CBR 3 (ULTRA LOW) CODE C - CBR 6 (LOW) CODE B - CBR 10 (MEDIUM) CODE A - CBR 15 (HIGH) 60
163-A
AIRCRAFT CLASSIFICATION NUMBER (ACN) 40
20
0 100 (1,000 LB) (1,000 KG)
150
60
200
80
250
100
300
120
350
140
160
400
180
AIRCRAFT GROSS WEIGHT
7.9.1-A AIRCRAFT CLASSIFICATION NUMBER - FLEXIBLE PAVEMENT MODEL MD-10 SERIES 10F
April 2004
450
200
500
220
7.9.2 AIRCRAFT CLASSIFICATION NUMBER - FLEXIBLE PAVEMENT MODEL DC-10 SERIES 30, 30CF, 40, AND 40CF 164 JUNE 2010
H54 X 21-24 36 PR TIRES PRESSURE CONSTANT AT 175PSI CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT
CODE D - CBR 3 (ULTRA LOW) CODE C - CBR 6 (LOW) CODE B - CBR 10 (MEDIUM) CODE A - CBR 15 (HIGH)
164-A
AIRCRAFT CLASSIFICATION NUMBER (ACN) 60
20 200 (1,000 LB) (1,000 KG)
250
100
300
120
140
350
400
160
180
450
200
500
220
550
240
AIRCRAFT GROSS WEIGHT
7.9.2-A AIRCRAFT CLASSIFICATION NUMBER - FLEXIBLE PAVEMENT MODEL MD-10 SERIES 30F WING GEAR April 2004
600
260
H54 X 21-24 36 PR TIRES PRESSURE CONSTANT AT 145PSI CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT 120
100
CODE D - CBR 3 (ULTRA LOW) CODE C - CBR 6 (LOW) CODE B - CBR 10 (MEDIUM) CODE A - CBR 15 (HIGH) 80
165-A
AIRCRAFT CLASSIFICATION NUMBER (ACN) 60
40
20 200 (1,000 LB) (1,000 KG)
250
100
300
120
140
350
160
400
180
450
200
500
240
550
260
AIRCRAFT GROSS WEIGHT
7.9.3-A AIRCRAFT CLASSIFICATION NUMBER - FLEXIBLE PAVEMENT MODEL MD-10 SERIES 30F CENTER GEAR April 2004
600
280
H54 X 21-24 36 PR TIRES PRESSURE CONSTANT AT 155PSI CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT
CODE D - k=75 (ULTRA LOW) CODE C - k=150 (LOW) CODE B - k=300 (MEDIUM) CODE A - k=550 (HIGH)
166-A
AIRCRAFT CLASSIFICATION NUMBER (ACN)
100
150
200
250
300
350
400
450
500
(1,000 LB) (1,000 KG)
60
80
100
120 140 160 AIRCRAFT GROSS WEIGHT
180
200
7.9.4-A AIRCRAFT CLASSIFICATION NUMBER - RIGID PAVEMENT MODEL MD-10 SERIES 10F April 2004
220
H54 X 21-24 36 PR TIRES PRESSURE CONSTANT AT 175PSI CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT 120
100
CODE D - k=75 (ULTRA LOW) CODE C - k=150 (LOW) CODE B - k=300 (MEDIUM) CODE A - k=550 (HIGH)
167-A
80 AIRCRAFT CLASSIFICATION NUMBER (ACN) 60
40
20 200
250
300
350
400
450
500
550
600
(1,000 LB) 100 (1,000 KG)
120
140
160
180
200
220
240
AIRCRAFT GROSS WEIGHT
7.9.5-A AIRCRAFT CLASSIFICATION NUMBER - RIGID PAVEMENT MODEL MD-10 SERIES 30F WING GEAR April 2004
260
H54 X 21-24 36 PR TIRES PRESSURE CONSTANT AT 145PSI CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT 120
100
CODE D - k=75 (ULTRA LOW) CODE C - k=150(LOW) CODE B - k=300 (MEDIUM) CODE A - k=550 (HIGH) 80
168-A
AIRCRAFT CLASSIFICATION NUMBER (ACN) 60
40
20 200
250
300
350
400
450
500
550
600
(1,000 LB) (1,000 KG)
100
120
140
160
180
200
220
240
AIRCRAFT GROSS WEIGHT
7.9.6- A AIRCRAFT CLASSIFICATION NUMBER - RIGID PAVEMENT MODEL MD-10 SERIES 30F CENTER GEAR April 2004
260
(Limited to 1.75 MPa)
(Limited to 1.25 MPa)
8.0
POSSIBLE DC-10/MD-10 DERIVATIVE AIRPLANES
8.0
POSSIBLE DC-10/MD-10 DERIVATIVE AIRPLANES No additional versions of the DC-10/MD-10 series aircraft are currently planned.
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