MCDONNELL DOUGLAS CORPORATION

DOUGLAS AIRCRAFT COMPANY

DC/MD-10

AIRPLANE

CHARACTERISTICS FOR

AIRPORT PLANNING

DAC-67803A REPRINTED JANUARY 1991

REVISION A APRIL 2004

MAY 2011 iv

DC/MD-10 AIRPLANE CHARACTERISTICS LIST OF REVISIONS

Page Date Original 1 to 190 January 1991

Rev A April 2004

Title Page April 2004 iv April 2004 v April 2004 vi April 2004 2 April 2004 5 April 2004

135 April 2004 136 April 2004 137 April 2004 138 April 2004

140-A April 2004 141-A April 2004 163-A April 2004 164-A April 2004 165-A April 2004 166-A April 2004 167-A April 2004 168-A April 2004

iv June 2010

133 June 2010 134 June 2010 162 June 2010 163 June 2010 164 June 2010

2 May 2011

CONTENTS

Page

1.0 SCOPE ............................................................................................................................. 1 1.1 Purpose ................................................................................................................... 1 1.2 Introduction ............................................................................................................ 2 1.3 Inclusion of MD-10-10F/-30F Information ........................................................... 2 2.0 AIRPLANE DESCRIPTION ........................................................................................... 3 2.1 General Airplane Characteristics ........................................................................... 3 2.2 General Airplane Dimensions ................................................................................ 6 2.3 Ground Clearances ................................................................................................. 12 2.4 Interior Arrangements ............................................................................................ 14 2.5 Passenger Cabin Cross Section .............................................................................. 18 2.6 Lower Compartment Containers ............................................................................ 25 2.7 Door Clearances ..................................................................................................... 29 2.7.1 Passenger Loading Doors ............................................................................. 30 2.7.2 Cargo Loading Doors ................................................................................... 34 2.7.3 Critical Interference Path Door/Sill Wing Clearance ................................... 41 3.0 AIRPLANE PERFORMANCE ....................................................................................... 43 3.1 General Information ............................................................................................... 43 3.2 Payload/Range ....................................................................................................... 44 3.2.1 Payload/Range .............................................................................................. 44 3.2.2 Payload/Range (Metric) ............................................................................... 52 3.3 FAR Takeoff Runway Length Requirements ........................................................ 60 3.4 FAR Landing Runway Length Requirements ........................................................ 64 3.5 Approach Speed (Threshold) ................................................................................. 67 4.0 GROUND MANEUVERING .......................................................................................... 69 4.1 General Information ............................................................................................... 69 4.2 Turning Radii, No Slip Angle ................................................................................ 70 4.3 Minimum Turning Radii ........................................................................................ 72 4.4 Visibility From Cockpit in Static Position ............................................................. 74 4.5 Runway and Taxiway Turn Paths .......................................................................... 75 4.5.1 More than 90º Turn – Runway to Taxiway .................................................. 75 4.5.2 90º Turn – Runway to Taxiway ................................................................... 77 4.5.3 90º Turn – Taxiway to Taxiway ................................................................... 79 4.5.4 90º Turn – Taxiway to Taxiway ................................................................... 81 4.6 Runway Holding Bay Apron .................................................................................. 83 4.7 Minimum Parking Space Requirements ................................................................ 85 4.7.1 Minimum Parking Space Requirements (Feet) ............................................ 85 4.7.2 Minimum Parking Space Requirements (Meters) ........................................ 88 5.0 TERMINAL SERVICING .............................................................................................. 91 5.1 Airplane Servicing Arrangement (Typical) ........................................................... 91 5.2 Terminal Operations, Turnaround Station ............................................................. 93 5.3 Terminal Operations, Enroute Station ................................................................... 99 5.4 Ground Service Connections ................................................................................. 105 5.5 Engine Starting Pneumatic Requirements .............................................................. 113 5.6 Ground Pneumatic Power Requirements ............................................................... 116 5.7 Preconditioned Airflow Requirements ................................................................... 117 5.8 Ground Towing Requirements ............................................................................... 118

APRIL 2004 v

CONTENTS

Page

APRIL 2004 vi

6.0 OPERATING CONDITIONS ......................................................................................... 121 6.1 Jet Engine Exhaust Velocities and Temperatures .................................................. 121 6.1.1 Jet Engine Exhaust Velocity Contours, Breakaway Power .......................... 122 6.1.2 Jet Engine Exhaust Velocity Contours, Takeoff Power ............................... 124 6.1.3 Jet Engine Exhaust Velocity Contours, Idle Power ..................................... 127 6.1.4 Jet Engine Exhaust Temperature .................................................................. 130 6.2 Airport and Community Noise ............................................................................... 131 7.0 PAVEMENT DATA ....................................................................................................... 133 7.1 General Information ............................................................................................... 133 7.2 Footprint ................................................................................................................. 135 7.3 Maximum Pavement Loads ................................................................................... 137 7.4 Landing Gear Loading on Pavement ..................................................................... 139 7.4.1 Loads on Main Landing Gear Group ........................................................... 139 7.4.2 Center Gear and Wing Gear Loading on Pavement ..................................... 141 7.5 Flexible Pavement Requirements, U.S. Army Corps of Engineers Design Method S-77-1 ........................................................................................... 144 7.6 Flexible Pavement Requirements, LCN Conversion ............................................. 148 7.7 Rigid Pavement Requirements, Portland Cement Association Design Method .... 152 7.8 Rigid Pavement Requirements, LCN Conversion ................................................. 156 7.9 ACN-PCN Reporting System ................................................................................ 162 7.9.1 Aircraft Classification Numbers (ACNs) ..................................................... 162 7.9.2 ACN-PCN System Background ................................................................... 169 8.0 POSSIBLE DC-10/MD-10 DERIVATIVE AIRPLANES .............................................. 173 9.0 SCALE DRAWINGS ...................................................................................................... 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

MAY 2011 2

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: AirportTechnology@boeing.com 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-10-10F 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-10-10F and MD-10-30F Freighters.

April 2004

5

SERIES 10CF 30CF 40CF MD-10-10F MD-10-30F

MODE PSGR CARGO PSGR CARGO PSGR CARGO CARGO CARGO

ENGINE CF6-6D CF6-50C JT9D-59A* CF6-6D CF6-50C

MAXIMUM RAMP WEIGHT POUNDS

KILOGRAMS

443,000

200,942

443,000

200,942

558,000

253,105

558,000

253,105

558,000

253,105

558,000

253,105

443,000

200,942

583,000

264,444

MAXIMUM LANDING WEIGHT POUNDS

KILOGRAMS

363,500

164,881

363,500

164,881

411,000

186,427

411,000

186,427

411,000

186,427

411,000

186,427

375,000

170,097

436,000

197,766

MAXIMUM TAKEOFF WEIGHT POUNDS

KILOGRAMS

440,000

199,581

440,000

199,581

555,000

251,744

555,000

251,744

555,000

251,744

555,000

251,744

440,000

199,581

580,000

263,084

OPERATING WEIGHT EMPTY POUNDS

KILOGRAMS

243,750

110,563

215,444

97,724

268,751

121,904

238,036

107,971

272,773

123,728

242,058

109,796

216,000

97,976

236,500

107,275

MAXIMUM ZERO FUEL WEIGHT

POUNDS

KILOGRAMS

335,000

151,954

335,000

151,954

391,000

177,355

391,000

177,355

391,000

177,355

391,000

177,355

355,000

161,025

414,000

187,787 MAXIMUM STRUCTURAL

PAYLOAD (WEIGHT LIMITED)

POUNDS

KILOGRAMS

91,250

41,390

119,556

54,230

122,249

55,451

152,964

69,383

118,227

53,627

148,942

67,559

139,000

63,049

177,500

80,512

MAXIMUM CARGO VOLUME CUBIC FEET

CUBIC METERS

4,597

130.17

16,845

477.05

4,618

130.77

16,866

477.65

4,618

130.77

16,866

477.65

14,200

402.1

14,200

402.1

SEATING CAPACITY (STD/MAX)

STANDARD

MAXIMUM

255

399

0

0

255

399

0

0

255

399

0

0

0

0

0

0

USABLE FUEL CAPACITY U.S. GALLONS

LITERS

21,762***

82,376

21,762***

82,376

36,652

137,509

36,652

137,509

36,652

137,509

36,652

137,509

21,762

82,376

36,652

137,509 * 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

THIS PAGE LET BLANK INTENTIONALLY

68

133 JUNE 2010

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:

134 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.

April 2004 135

54 IN (137 CM)(TYPICAL)

64 IN (163 CM)(TYPICAL)

72 FT 4.6 IN (22.06 M)

(10.67 M)

24 IN(61 CM)

35 FT

41 FT 3 IN(12.57 M)

UNITS SERIES 10 AND 10CF MD-10-10F MAXIMUM DESIGN TAXI

WEIGHT LB KG

458,000 207,746

443,000 200,941

PERCENT OF WEIGHT ON MAIN GEAR % SEE SECTION 7.4

NOSE GEAR TIRE SIZE IN. 37 x 14 - 14 37 x 14 - 14

NOSE GEAR TIRE PRESSURE

PSI KG/CM2

165 11.60

165 11.60

MAIN GEAR TIRE SIZE IN. 50 X 20 - 20 H54 X 21 - 24

MAIN GEAR TIRE PRESSURE

PSI KG/CM2

195 13.71

155 10.90

7.2.1 FOOTPRINT MODEL DC-10 SERIES 10, 10CF AND

MD-10 SERIES 10F

April 2004 136

25 IN(64 CM)

54 IN (137 CM)(TYPICAL)

64 IN (163 CM)(TYPICAL)

72 FT 4.6 IN (22.06 M)

30 IN. 37.5 IN.

35 FT

(76 CM) (95 CM)

(10.67 M)

41 FT 3 IN(12.57 M)

UNITS SERIES 30, 30CF, 40, 40CF MD-10-30F

MAXIMUM DESIGN TAXI WEIGHT

LB KG

583,000 264,445

583,000 264,445

PERCENT OF WEIGHT ON MAIN

GEAR % SEE SECTION 7.4

NOSE GEAR TIRE SIZE IN. 40 x 15.5 - 16 40 x 15.5 - 16

NOSE GEAR TIRE PRESSURE

PSI KG/CM2

185 13.01

185 13.01

WING AND CENTER GEAR TIRE SIZE IN. 52 X 20.5 - 23 H54 X 21 - 24

WING GEAR TIRE PRESSURE

PSI KG/CM2

177 12.45

175 12.30

CENTER GEAR TIRE PRESSURE

PSI KG/CM2

153 10.76

145 10.19

7.2 .2 FOOTPRINT

MODEL DC-10 SERIES 30, 30CF, 40, 40CF AND

MD-10 SERIES 30F

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

WING GEAR Vw

Hw PER STRUT

MAX STATIC STATIC + MAX STEADY AT AIRPLANE UNITS DESIGN AT BRAKING LOAD AT BRAKING INSTANTANEOUS

MODEL TAXI MOST 10 FT/SEC2 STATIC 10 FT/SEC2 BRAKING WEIGHT FWD C.G. DECEL AFT C.G. DECEL (m = 0.8)

SERIES 10, 10CF LB 458,000 50,243 84,959 213,680 71,501 170,944

KG 207,746 22,790 38,537 96,923 32,433 77,538 MD-10- 10F LB 443,000 47,454 80,705 207,123 68,798 165,698 FREIGHTER KG 200,941 21,525 36,607 93,949 31,206 75,159

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

NOSE GEAR WING GEAR CENTER GEAR VN VN Vw Hw Vc Hc

AIRPLANE MODEL UNITS

MAX DESIGN

TAXI WT

STATIC AT

FWD C.G.

STATIC + BRAKING

10 FT/SEC^2

STATIC AT AFT

C.G.

STEADY BRAKING

10 FT/SEC^2

INST BRAKING (M=0.8)

STATIC AT AFT

C.G.

STEADY BRAKING

10 FT/SEC^2

INST BRAKING (M=0.8)

LB 583,000 72,234 112,229 218,767 74,278 175,014 94,746 32,170 75,797 SERIES 30, 30CF, 40,

40CF 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 MD-10- 30F FREIGHTER 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

April 2004 140-A

80 85 90 95 100200

240

280

320

100

120

10 15 20 25 30

% MAC

MAXIMUM RAMP WEIGHT 443,000 LB

C.G. FOR ACNCALCULATIONS

360

200

240

280

320

360

440

400400

440

480

140

160

180

200

AIRPLANEGROSSWEIGHT(1000 KG)

AIRPLANEGROSSWEIGHT(1000 LB)

WEIGHTON MAINLANDINGGEARS(1000 LB)

7.4.1-A LANDING GEAR LOADING ON PAVEMENT MODEL MD-10 SERIES 10F

April 2004 141-A

80

PERCENT OF WEIGHT ON MAIN GEAR

85 90 95 100250

300

350

400

120

140

10 15 20 25 30

% MAC

MAXIMUM RAMP WEIGHT 583,000 LB

C.G. FOR ACNCALCULATIONS

450

250

300

350

400

450

550

500500

550

600

160

180

200

220

AIRPLANEGROSSWEIGHT(1000 KG)

AIRPLANEGROSSWEIGHT(1000 LB)

WEIGHTON MAINLANDINGGEARS(1000 LB)

240

260

7.4.2-A LANDING GEAR LOADING ON PAVEMENT MODEL MD-10 SERIES 30F

163 JUNE 2010

7.9.1 AIRCRAFT CLASSIFICATION NUMBER - FLEXIBLE PAVEMENT

MODEL DC-10 SERIES 10 AND 10CF

April 2004

163-A

100 150 200 250 300 350 400 450 5000

20

40

60

80

100

(1,000 LB)

60(1,000 KG)

CODE D - CBR 3 (ULTRA LOW)CODE C - CBR 6 (LOW)CODE B - CBR 10 (MEDIUM)CODE A - CBR 15 (HIGH)

H54 X 21-24 36 PR TIRES PRESSURE CONSTANT AT 155PSI

AIRCRAFT

AIRCRAFT GROSS WEIGHT

80 100 120 140 160 180 200 220

CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT

CLASSIFICATIONNUMBER(ACN)

7.9.1-A AIRCRAFT CLASSIFICATION NUMBER - FLEXIBLE PAVEMENT

MODEL MD-10 SERIES 10F

164 JUNE 2010

7.9.2 AIRCRAFT CLASSIFICATION NUMBER - FLEXIBLE PAVEMENT

MODEL DC-10 SERIES 30, 30CF, 40, AND 40CF

April 2004

164-A

200 250 300 350 400 450 500 550 60020

60

(1,000 LB)

100(1,000 KG)

CODE D - CBR 3 (ULTRA LOW)CODE C - CBR 6 (LOW)CODE B - CBR 10 (MEDIUM)CODE A - CBR 15 (HIGH)

H54 X 21-24 36 PR TIRESPRESSURE CONSTANT AT 175PSI

AIRCRAFT GROSS WEIGHT

120 140 160 180 200 220 240 260

CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT

AIRCRAFTCLASSIFICATIONNUMBER(ACN)

7.9.2-A AIRCRAFT CLASSIFICATION NUMBER - FLEXIBLE PAVEMENT MODEL MD-10 SERIES 30F

WING GEAR

April 2004

165-A

200 250 300 350 400 450 500 550 60020

40

60

80

100

120

(1,000 LB)

100(1,000 KG)

CODE D - CBR 3 (ULTRA LOW)CODE C - CBR 6 (LOW)CODE B - CBR 10 (MEDIUM)CODE A - CBR 15 (HIGH)

H54 X 21-24 36 PR TIRES PRESSURE CONSTANT AT 145PSI

AIRCRAFT GROSS WEIGHT

120 140 160 180 200 240 260 280

CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT

AIRCRAFTCLASSIFICATIONNUMBER(ACN)

7.9.3-A AIRCRAFT CLASSIFICATION NUMBER - FLEXIBLE PAVEMENT

MODEL MD-10 SERIES 30F CENTER GEAR

April 2004

166-A

100 150 200 250 300 350 400 450 500

(1,000 LB)

60(1,000 KG)

CODE D - k=75 (ULTRA LOW)CODE C - k=150 (LOW)CODE B - k=300 (MEDIUM)CODE A - k=550 (HIGH)

H54 X 21-24 36 PR TIRES PRESSURE CONSTANT AT 155PSI

AIRCRAFT GROSS WEIGHT80 100 120 140 160 180 200 220

CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT

AIRCRAFTCLASSIFICATIONNUMBER(ACN)

7.9.4-A AIRCRAFT CLASSIFICATION NUMBER - RIGID PAVEMENT

MODEL MD-10 SERIES 10F

April 2004

167-A

200 250 300 350 400 450 500 550 60020

40

60

80

100

120

(1,000 LB)

100(1,000 KG)

CODE D - k=75 (ULTRA LOW)CODE C - k=150 (LOW)CODE B - k=300 (MEDIUM)CODE A - k=550 (HIGH)

H54 X 21-24 36 PR TIRES PRESSURE CONSTANT AT 175PSI

AIRCRAFT GROSS WEIGHT

120 140 160 180 200 220 240 260

CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT

AIRCRAFTCLASSIFICATIONNUMBER(ACN)

7.9.5-A AIRCRAFT CLASSIFICATION NUMBER - RIGID PAVEMENT

MODEL MD-10 SERIES 30F WING GEAR

April 2004

168-A

200 250 300 350 400 450 500 550 60020

40

60

80

100

120

(1,000 LB)

100(1,000 KG)

CODE D - k=75 (ULTRA LOW)CODE C - k=150(LOW)CODE B - k=300 (MEDIUM)CODE A - k=550 (HIGH)

H54 X 21-24 36 PR TIRES PRESSURE CONSTANT AT 145PSI

AIRCRAFT GROSS WEIGHT

120 140 160 180 200 220 240 260

CG AT MOST AFT POSITION FOR MAXIMUM RAMP WEIGHT

AIRCRAFTCLASSIFICATIONNUMBER(ACN)

7.9.6- A AIRCRAFT CLASSIFICATION NUMBER - RIGID PAVEMENT MODEL MD-10 SERIES 30F

CENTER GEAR

(Limited to1.75 MPa)

(Limited to1.25 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.

APRIL 2004 173

APRIL 2004 174

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