MCDONNELL DOUGLAS CORPORATION DOUGLAS AIRCRAFT ...

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)


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


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


20 200 (1,000 LB) (1,000 KG)

250

100

300

120

140

350

400

160

180

450

200

500

220

550

240


7.9.2-A AIRCRAFT CLASSIFICATION NUMBER - FLEXIBLE PAVEMENT MODEL MD-10 SERIES 30F WING GEAR April 2004

600

260


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


40

20 200 (1,000 LB) (1,000 KG)

250

100

300

120

140

350

160

400

180

450

200

500

240

550

260


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


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


7.9.5-A AIRCRAFT CLASSIFICATION NUMBER - RIGID PAVEMENT MODEL MD-10 SERIES 30F WING GEAR April 2004

260


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


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


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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