# TCDS 6A3: The Boeing Company - Type: Type certificate data sheet - Status: Current - Holder: The Boeing Company - Revision: 28 - Revised: September 27, 2010 - Product: Aircraft, Large Airplane - Certification basis: CAR 4b - Registered aircraft: 7, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/25/fc/25fcbc1fd0de4b86102ea8810975e2f4a75c01253c2a594c345253c0e7a5e186 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/9B7560805C769C3B862577DC005719EA.0001 - Page: https://openairdocs.org/tcds/6A3 ## Models (3) As the data sheet lists them. - DC-6A - USAF C-118A - Navy R6D-1 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 Rev. No. 28 - - - - - - - - - - - - - - - - - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 6A3 Revision 28 BOEING DC-6A Navy R6D-1 USAF C-118A September 27, 2010 AIRCRAFT SPECIFICATION NO. 6A3 Type Certificate Holder The Boeing Company 4000 Lakewood Boulevard Long Beach, California 80808 Type Certificate Ownership Records McDonnell Douglas Cor poration, Long Beach, California merged with The Boeing Company effective January 1, 2010. Transferred Type Certificate to The Boeing Company on September 27, 2010. Douglas Aircraft Company, Inc. Long Beach, California I - Model DC-6A, Approved April 17, 1951 Engines 4 P&W Double Wasps CB-16 or CB-3, CB-17 or CB-4 (.45:1 propeller (Item 101) reduction gearing); 4 P&W R-2800-52W, -83AM5 or -83AM7 (20:9 propeller reduction gearing) Fuel Aviation gasoline (CB-16 or CB-3, R-2800-52W or -83AM5) Grade 100/130. (CB-17 or CB-4, R-2800-52W or -83AM7) Grade 108/135. Engine limits (Straight line manifold pr essure variation with altitudes shown.) H P RPM MP IN.HG. ALT. P&W Double Wasps CB-16 or CB-3, R-2800-52W or -83AM5 Low impeller gear ratio 7.29:1 Take-off (two minutes) (dry) 2050 2700* 55.0 S.L. Take-off (two minutes) (dry) 2050 2700* 53.0 6900' *(See NOTE 3 for propeller governor re-setting prior to "dry" take-off) Take-off (two minutes) (dry) 1950 2800 53.0 S.L. Take-off (two minutes) (dry) 1950 2800 51.0 9800' Take-off (two minutes) (wet) 2400 2800 59.5 S.L. Take-off (two minutes) (wet) 2400 2800 59.0 5000' (See Item 104 for water-alcohol injection installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1800 2600 48.5 S.L. Maximum continuous 1800 2600 46.5 9200' High impeller gear ratio 8.58:1 Maximum continuous 1700 2600 48.5 10000' Maximum continuous 1700 2600 47.5 16800' Note: High impeller gear ratio not applicable to CB-3 engines. P&W Double Wasps CB-4, CB-17, R-2800-52W or -83AM7 Low impeller gear ratio 7.29:1 Take-off (two minutes) (dry) 2200 2800 60.0 S.L. Take-off (two minutes) (dry) 2200 2800 59.0 5200' (critical altitude) Take-off (two minutes) (wet) 2500 2800 62.0 S.L. Take-off (two minutes) (wet) 2500 2800 61.5 3700' (critical altitude) (See Item 104 for water-alcohol injection installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1900 2600 51.5 S.L. Maximum continuous 1900 2600 50.0 7100' Take-off (two minutes) (wet) 1900 2600 50.5 10000' Take-off (two minutes) (wet) 1900 2600 49.0 15700' Maximum continuous 1750 2600 51.5 10000' Maximum continuous 1750 2600 49.5 15000' NOTE: High impeller gear ratio not applicable to CB-3 engines. Airspeed limits Maximum Zero Fuel, Oil and ADI Fluid Gross Weight 83200# Vno (Normal Operating) 289 mph (251 knots) S.L. to 17000' (1) Mach No. = .52 Vne (Never Exceed) 346 mph (301 knots) S.L. to 12000' (1) Mach No. = .585 Va (Maneuvering) 213 mph (185 knots) Vfe (Flaps Down 0° to 30°) 200 mph (174 knots) Vfe (Flaps Down 30° to 50°) 175 mph (152 knots) Vlo (Landing Gear Operation) 200 mph (174 knots) Vle (Landing Gear Extension) 200 mph (174 Knots) (1) Above altitudes shown, reduce speed 6 mph (5 knots) per 1000 feet. C. G. range Applies to 83,200 lbs. zero fuel , oil and ADI fluid gross weight aircraft. Landing gear retraction moment - 220,000 in.lbs. (Moves the C.G. forward) Landing Gear Extended (1) Landing Gear Retracted (2) Forward (3) Aft Forward (3) Aft GROSS WEIGHT %MAC Sta. %MAC Sta. %MAC Sta. %MAC Sta. Up to and including 83,200 lbs. - - - - - - - - - - - - - - - 9.0 409.9 33.0 449.2 85,600 lbs. 11.0 413.2 33.0 449. 2 - - - - - - - - - - - - 102,200 lbs. 14.1 418.3 33.0 449.2 - - - - - - - - - - - - 107,000 lbs. 16.9 422.9 33.0 449.2 13.8 417.7 33.0 449.2 (1) Applies for Take-off and Landing (2) Applies for Enroute Operation (3) Straight line variation in forward C.G. between weights shown Maximum weights Landing : 88,200 lbs. (See NOTE 6 for details). (See NOTE 9) Zero fuel, oil and ADI fluid gross weight : 83,200 lbs. (See NOTE 6 and Airspeed limits for details) (All weight in the airplane above this value must be in fuel, oil and ADI fluid). Takeoff : See table below and NOTE 6. Dump valves are required in accordance with NOTE 1(e) For 3-engine ferrying see NOTE 4 TAKE-OFF WEIGHT Engine Zero Fuel, Oil & ADI Propeller Installation Installation fluid gr oss weight Ham. Std. 43E60/6895 CB-3, CB-16 83,200 lbs. 103,800 lbs. (1) (3) R-2800-52W or 100,000 lbs. (1) R-2800-83AM5 92,200 lbs. (2) CB-17, CB-4 83,200 lbs. 107,000 lbs. (1) (3) R-2800-52W or 103,000 lbs. (1) R-2800-83AM7 95,500 lbs. (2) (1) With anti-detonant injection (See Engine Specification for ADI fluid composition) and 20° take-off flap setting. 3 6A3 (2) With dry power and 20° take-off setting. (3) With automatic feathering propellers. Minimum crew For all revenue flights (passenger and/or cargo) 3 (Pilot and copilot (+48.0) and flight engineer (+69.0)) For all other flights (includi ng test, ferry and training flights) 2 (Pilot and copilot (+48.0)) Additions to the above minimums may be specified by the FAA Air Carrier Safety Division for long range flight s and/or other special conditions. Maximum passengers See NOTE 1(g) for cargo confi guration and NOTE 7 for passenger configuration. Maximum cargo Compartment Station Capac ity (lbs.) Maximum Floor Arm Arrangement No. 1 and 2 Loading #/FT 2 A (belly) 89-221 1960 75 155.0 B (main cabin) 122-221 5940 less Comp't A load 200 171.5 C (belly) 221-281 890 * 75 251.0 D (main cabin) 221-341 8710 less Comp't C load 200 281.0 E (main cabin) 341-421 6400 200 381.0 F (main cabin) 421-520 7920 200 470.5 G (main cabin) 520-600 6400 200 560.0 H (belly) 600-668 1810 75 634.0 J (main cabin) 600-688 5440 less Comp't H load 200 634.0 K (belly) 668-792 3030 75 730.0 L (main cabin) 668-792 7440 less Comp't K load 200 730.0 M (belly) 792-866 1350 30 829.0 N (main cabin) 792-866 2960 less Comp't M load 200 829.0 O (belly) 866-938 1310 30 902.0 P (main cabin) 866-955 3360 less Comp't O load 200 910.0 *When auxiliary power plant (Item 310) is not installed, Compartment C (221-341) capacity may be increased to 1780 lbs. and Compartment D capacity increased to 9660 lbs. less Compartment C load. Arrangement No. 3 (AAL Version) 1 (main cabin) 123-221 5880 less Comp't 8 load 200 172.0 2 (main cabin) 221-311 9600 less Comp't 9 load 200 281.0 3 (main cabin) 311-460 9520 200 400.5 4 (main cabin) 460-560 8000 200 510.0 5 (main cabin) 560-660 8000 less Comp't 10 load 200 610.0 6 (main cabin) 660-800 8400 less Comp't 11 load 200 730.0 7 (main cabin) 800-955 6000 less Comp't 12 load 200 875.0 8 (belly) 89-221 1960 75 155.0 9 (belly) 221-311 1780 75 281.0 10 (belly) 600-660 880 75 630.0 11 (belly) 660-800 1720 *** 730.0 12 (belly) 800-938 700 30 869.0 *** Sta. 660-760: 75#/Ft2, Sta. 760-800: 30#/Ft2 Fuel capacity (See NOTE 1(b), (c) and (d) for data on "System" fuel and "unusable" fuel; NOTE 1(d) for required distribution of fuel load, NOTE 1(e) for "Undumpable" fuel. T o t a l Usable Eight Wing Tank Airplane - 1322 Gallon System: 2 outer wing tanks (#1 and #4 main ) 695 gal. ea. 695 gal. ea. (+460.0) 2 inboard inner wing tanks (#2 and #3 main) 508 gal. ea. 502 gal. ea. (+441.0) 2 outboard inner wing tanks (#1 and #4 alt.) 431 gal. ea. 428 gal. ea. (+444.0) 2 inner wing fuel tanks (#2 and #3 alt.) 527 gal. ea. 524 gal. ea. (+449.0) Eight Wing Tank Airplane - 4934 Gallon System: 2 outer wing tanks (#1 and #4 main ) 695 gal. ea. 695 gal. ea. (+460.0) 2 inboard inner wing tanks (#2 and #3 main) 719 gal. ea. 713 gal. ea. (+451.0) 2 outboard inner wing tanks (#1 and #4 alt.) 526 gal. ea. 523 gal. ea. (+449.0) 2 inner wing fuel cells (#2 and #3 alt.) 527 gal. ea. 524 gal. ea. (+449.0) Eight Wing Tank Airplane - 5042 Gallon System: 2 outer wing tanks (#1 and #4 main ) 695 gal. ea. 695 gal. ea. (+460.0) 2 inboard inner wing tanks (#2 and #3 main) 719 gal. ea. 713 gal. ea. (+451.0) 2 outboard inner wing tanks (#1 and #4 alt.) 580 gal. ea. 576 gal. ea. (+452.0) 2 inner wing fuel cells (#2 and #3 alt.) 527 gal. ea. 524 gal. ea. (+449.0) Eight Wing Tank Airplane - 5404 Gallon System: 2 outer wing tanks (#1 and #4 main ) 695 gal. ea. 695 gal. ea. (+460.0) 2 inboard inner wing tanks (#2 and #3 main 719 gal. ea. 713 gal. ea. (+451.0) 2 outboard inner wing tanks (#1 and #4 alt.) 526 gal. ea. 523 gal. ea. (+449.0) 2 inner wing fuel cells (#2 and #3 alt.) 762 gal. ea. 762 gal. ea. (+468.0) Eight Wing Tank Airplane - 5512 Gallon System: 2 outer wing tanks (#1 and #4 main ) 695 gal. ea. 695 gal. ea. (+460.0) 2 inboard inner wing tanks (#2 and #3 main) 719 gal. ea. 713 gal. ea. (+451.0) 2 outboard inner wing tanks (#1 and #4 alt.) 580 gal. ea. 576 gal. ea. (+452.0) inner wing fuel cells (#2 and #3 a lt.) 762 gal. ea. 762 gal. ea. (+468.0) Ten Wing Tank Airplane - 4722 Gallon or 4736 Gallon System: 2 outer wing tanks (#1 and #4 main ) 360 gal. ea. 360 gal. ea. (+448.0) 2 inboard inner wing tanks (#2 and #3 main) 508 gal. ea. 502 gal. ea. (+441.0) 2 outboard inner wing tanks (#1 and #4 alt.) 519 gal. ea. 516 gal. ea. (+449.0) or 526 gal. ea. 523 gal. ea. 2 inner wing fuel cells (#2 and #3 alt.) 527 gal. ea. 524 gal. ea. (+449.0) 2 auxiliary fuel cells (L.H. and R.H.) 447 gal. ea. 444 gal. ea. (+500.0) Ten Wing Tank Airplane - 5406 Gallon System: 2 outer wing tanks (#1 and #4 main ) 695 gal. ea. 695 gal. ea. (+460.0) 2 inboard inner wing tanks (#2 and #3 main) 508 gal. ea. 502 gal. ea. (+441.0) 2 outboard inner wing tanks (#1 and #4 alt.) 526 gal. ea. 523 gal. ea. (+449.0) 2 inner wing fuel cells (#2 and #3 alt.) 527 gal. ea. 524 gal. ea. (+449.0) 2 auxiliary fuel cells (L.H. and R.H.) 447 gal. ea. 444 ga. ea. (+500.0) Oil capacity (See NOTE 1(b) and (f) regarding "Sys tem" oil and wing fillet oil tank installation.) Hamilton Standard Propeller Installation: 35 gal. in each nacelle (Douglas Dwg. #5342754) (+349.0) & (+379.0) 26 gal. in wing fillet (+565.0) (Required on all aircraft having a fuel sy stem capacity greater than 4322 gallons except when a specific authorization for a fuel:oil ratio greater than 30:1 is approved by the Administrator.) Serial Nos. eligible See Item 401 and NOTE 6 for complete list. Required equipment In addition to the pertinent require d basic equipment specified in CAR 4b, the following items of equipment must be installed: 1(a), 2(a) or (b), 4(a) and 101(a), (b), (c), (d), (e) or (f); 103(a), (b) and (c), or 103(b), (c) and (d), or 103(b), (c) and (e), or 102( b) and (f), or 103(b), (c) and (g), 103(b), (c), and (h) or 103(b), (c) and (i); 105(a); 107(a), (b ), (c), (d) or (e); 201(a), (b), (c), (d), (e), (f), (g), (h), (i), (j) or (k); 202(a), (b) or (c); 203; 204(a), (b), (c) or (d); 205(a), (b) or (c); 206; 207(a), (b), (c), (d), (e), (f), (g), (h), (i), (j) or (k); 208(a), (b), (c), (d), (e), (f), (g), (h), (i), (j), (k) or (l); 301(a), (b), (c) or (d); 302(a); 401 (as applicable); 402(a), (b) or (c); 404(a) or (b); 405(a); 408(a), (b), (c), (d), (e), (f), (g), (h), (i), (j), (k), (l), (m), (n), (o), (p), (q), (r), or (s); 605(a) or (b). II - Models Navy R6D-1 and U.S. Air Force C-118A (DC-6A), Approved December 19, 1951 and August 21, 1952, respectively. (Navy Model R6D-1 and U.S. Air Force Model C-118A basically same as DC-6A airplane except for equipment items and cargo arrangement. See NOTE 5 for differences between Navy Mode l R6D-1, U.S. Air Force Mode l C-118A and Basic Model DC- 6A) Engines 4 P&W Double Wasps CB-16, CB-17 or R-2800-52W (.45:1 propeller reduction gearing) (Item 101(a), (b) or (c).) Fuel Aviation gasoline (CB-16 or R-2800-52W) Grade 100/130. 5 6A3 (CB-17 or R-2800-52W) Grade 108/135 Engine limits P&W Double Wasp CB-16 or R-2800-52W MP Low impeller gear ratio 7.29:1 HP RPM IN.HG. ALT. Take-off (two minutes) (dry) 2050 2700* 55.0 S.L. Take-off (two minutes) (dry) 2050 2700* 53.0 6900' *(See NOTE 3 for propeller governor re-setting prior to "dry" take-off) Take-off (two minutes) (dry) 1950 2800 53.0 S.L. Take-off (two minutes) (dry) 1950 2800 51.0 9800' Take-off (two minutes) (wet) 2400 2800 59.5 S.L. Take-off (two minutes) (wet) 2400 2800 59.0 5000' (See Item 104 for water-alcohol injection installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1800 2600 48.5 S.L. Maximum continuous 1800 2600 46.5 9200' High impeller gear ratio 8.58:1 Maximum continuous 1700 2600 48.5 10000' Maximum continuous 1700 2600 47.5 16800' P&W Double Wasps CB-17 or R-2800-52W Low impeller gear ratio 7.29:1 Take-off (two minutes) (dry) 2200 2800 60.0 S.L. Take-off (two minutes) (dry) 2200 2800 59.0 5200' (critical altitude) Take-off (two minutes) (wet) 2500 2800 62.0 S.L. Take-off (two minutes) (wet) 2500 2800 61.5 3700' (critical altitude) (See Item 104 for water-alcohol injection installation and Engine Specification E-264 for ADI fluid composition) Maximum continuous 1900 2600 51.5 S.L. Maximum continuous 1900 2600 50.0 7100' High impeller gear ratio 8.58:1 Take-off (two minutes) (wet) 1900 2600 50.5 10000' Take-off (two minutes) (wet) 1900 2600 49.0 15700' Maximum continuous 1750 2600 51.5 10000' Maximum continuous 1750 2600 49.5 15000' Airspeed limits Vno (Normal Opera ting) 289 mph (251 knots) True Ind. S.L. to 17000' (1) Mach No. = .52 Vne (Never Exceed) 346 mph (301 knots) True Ind. S.L. to 12000' (1) Mach No. = .585 Va (Maneuvering) 211 mph (183 knots) True Ind. Vfe (Flaps Down 0° to 30°) 200 mph (174 knots) True Ind. Vfe (Flaps Down 30° to 50°) 175 mph (153 knots) True Ind. Vlo (Landing Gear Operation) 200 mph (174 knots) True Ind. Vle (Landing Gear Extended) 200 mph (174 Knots) True Ind. (1) Above altitudes shown, reduce speed 6 mph (5 knots) per 1000 feet. C. G. range Landing gear retraction moment -220,000 in.lbs. (moves the C.G. forward) Landing Gear Extended (1) Landing Gear Retracted (2) Forward (3) Aft Forward (3) Aft GROSS WEIGHT %MAC Sta. %MAC Sta. %MAC Sta. %MAC Sta. Up to and including 83,200 lbs. - - - - - - - - - - - - - - - 9.0 409.9 33.0 449.2 85,600 lbs. 11.0 413.2 33.0 449. 2 - - - - - - - - - - - - 102,200 lbs. 14.1 418.2 33.0 449.2 - - - - - - - - - - - - 103,000 lbs. 14.6 419.0 33.0 449.2 13.0 416.4 33.0 449.2 (1) Applies for Take-off and Landing (2) Applies for Enroute Operation (3) Straight line variation in forward C.G. between weights shown Maximum weights Landing : 88,200 lbs. (See NOTE 6 for details). (See NOTE 9) Zero fuel, oil and ADI fluid gross weight : 83,200 lbs. (See NOTE 6 details) (All weight in the airp lane above this value must be in fuel, oil and ADI fluid). Take-off : See table below and NOTE 6. Dump valves are required in accordance with NOTE 1(e) For 3-engine ferrying see NOTE 4 TAKE-OFF WEIGHT Engine Zero Fuel, Oil & ADI Propeller Installation Installation fluid gr oss weight Ham. Std. CB-16 or 83,200 lbs. 100,000 lbs. (1) R-2800-52W 92,200 lbs. (2) CB-17, or 83,200 lbs. 103,000 lbs. (1) R-2800-52W 95,500 lbs. (2) (1) With anti-detonant injection (See Engine Specification for ADI fluid composition) and 20° take-off flap setting. (2) With dry power and 20° take-off setting. Minimum crew For all revenue flights (passenger and/or cargo) 3 (Pilot and copilot (+48.0) and flight engineer (+69.0)) For all other flights (includi ng test, ferry and training flights) 2 (Pilot and copilot (+48.0)) Additions to the above minimums may be specified by the FAA Air Carrier Safety Division for long range flight s and/or other special conditions. Maximum passengers None. See NOTE 1(g) fo r approved interior arrangement for Model DC-6A and NOTE 5(f) for Model R6D-1 and Model C-118A. Maximum cargo Compartment Station Capacity (lbs.) Maximum Floor Arm Loading #/Ft 2 B-B (belly) 89-221 1960 75 155.0 B (main cabin) (122-221) 5940 less Comp't B-B 200 189.0 C-C (belly) 221-281 ** 890 75 251.0 C (main cabin) 221-281 4800 less Comp't C-C 200 251.0 D (main cabin) 281-341 4800 200 311.0 E (main cabin) 341-405 5120 200 373.0 F (main cabin) 405-470 5200 200 437.5 G (main cabin) 470-535 5200 200 502.5 H (main cabin) 535-600 5200 200 567.5 J-J (belly) 600-688 1000 75 634.0 J (main cabin) 600-668 5445 less Comp't J-J 200 634.0 K-K (belly) 668-730 770 75 699.0 K (main cabin) 668-730 3720 less Comp't K-K 200 699.0 L-L (belly) 730-792 770 * 761.0 L (main cabin) 730-792 3720 less Comp't L-L 200 761.0 M-M (belly) 792-866 390 30 829.0 M (main cabin) 792-866 2960 less Comp't M-M 200 829.0 N-N (belly) 866-938 370 30 902.0 N (main cabin) 866-955 3360 less Comp't N-N 200 910.0 All cargo loading must be secured with the tie-downs provided since there are no retaining net or crash bulkhead provisions. *Sta. 730 to 760 = 75#/FT 2 Sta. 760 to 792 - 30#/Ft 2 **When auxiliary power plant (Item 310) is not insta lled, Compartment C-C (Belly) (221-341) capacity may be increased to 1780 lbs. All weight in compartm ent C-C will be subtracted from compartment C and D (main cabin). 7 6A3 Fuel capacity (See NOTE 1(b), (c) and (d) for data on "System" fuel and "Unusable" fuel; NOTE 1(d) for required distribution of fuel load, NOTE 1(e) for "Undumpable" fuel. T o t a l Usable Ten Wing Tank Airplane - 5406 Gallon System: 2 outer wing tanks (#1 and #4 main ) 695 gal. ea. 695 gal. ea. (+460.0) 2 inboard inner wing tanks (#2 and #3 main) 508 gal. ea. 502 gal. ea. (+441.0) 2 outboard inner wing tanks (#1 and #4 alt.) 526 gal. ea. 523 gal. ea. (+444.0) 2 inner wing fuel tanks (#2 and #3 alt.) 527 gal. ea. 524 gal. ea. (+449.0) 2 auxiliary fuel cells (L.H. and R.H.) 447 gal. ea. 444 gal. ea. (+500.0) Eight Wing Tank Airplane - 5404 Gallon System: 2 outer wing tanks (#1 and #4 main ) 695 gal. ea. 695 gal. ea. (+460.0) 2 inboard inner wing tanks (#2 and #3 main) 719 gal. ea. 700 gal. ea. (+451.0) or (Serial No. 43819 and up) 719 gal. ea. 713 gal. ea. (+451.0) 2 outboard inner wing tanks (#1 and #4 alt.) 526 gal. ea. 523 gal. ea. (+449.0) 2 inner wing fuel cells (#2 and #3 alt.) 762 gal. ea. 762 gal. ea. (+468.0) Oil capacity (See NOTE 1(b) and (f) regarding "Sys tem" oil and wing fillet oil tank installation.) Hamilton Standard Propeller Installation: 35 gal. in each nacelle (Douglas Dwg. #5342754) (+349.0) & (+379.0) 26 gal. in wing fillet (+565.0) (Required on 5406 gallon ten wing tank ai rplanes, and 5404 gallon eight wing tank airplanes) Serial Nos. eligible 43206 and up (For R6D-1) 43565 and up (For C-118A) Required equipment In addition to the pertinent require d basic equipment specified in CAR 4b, the following items of equipment must be installed: 1(a), 2(a) or (b), 3(a), and 101(b) or (c); 103(b), (c) and (d) or 103(b), (c) and (e); 105(a); 107(a), (b), (c) or (d); 201(c), (d), (e) or (f); 202(a); 203; 204(a); 205(a); 206; 207(c), (d), (e), (f), (g) or (h); 208(a), (b), (c) or (d); 301(a), (b) or (c); 302(a); 402(b); 404(a) or (b); 405(a); 408(c); 605(a) or (b). Specifications Pertinent to All Models Datum 63 in. aft of nose (Station 0) MAC 163.6 in. L.E. of MAC (+395.2) Leveling means Bracket at Sta. 387.4 (below floor) and Sta. 4 and 22 (nose wheel well) Control surface movements (May be either arrangement "A" or arrangement "B") Arrangement "A" (Serial No. 12901 only) Aileron (Drooped 1° w/r to wing T.E., wheel neutral. (19° up, 17° down from neutral drooped position. Aileron tab (Faired w/r to aileron T.E., controls neutral ( + 21 1/2° + 1/2° from neutral position. Rudder* + 15 1/2 + 1/2° from neutral faired position. Rudder tab + 19 1/2° + 1/2° from neutral faired position. (T.E. faired with tail cone, control column neutral. (Down 15° + 1/2° from neutral, control column full forward 22° 41' from vertical. Elevator (Up 22° + 1/2° from neutral when elevator trim tab (setting is 5° nose down to 4° nose up. (Up 25° + 1/2° from neutral when elevator trim tab (setting is 7° nose up to 15° nose up. (Up 2 1/2° + 1/2° control neutral - springs each (will produce 3 1/2# preload at T.E. Elevator spring (Down 19° + 1/2° from faired position, control full aft. tab (Up 9° + 1/2° from faired position control full forward. Elevator trim (Down 15° + 1/2° from neutral faired position. tab** (Up 5° + 1/2° from neutral faired position. Arrangement "B" Aileron (Drooped 1° w/r to wing T.E., wheel neutral. (19° up, 17° down from neutral drooped position. Aileron tab (Faired w/r to aileron T.E., controls neutral ( + 21 1/2° + 1/2° from neutral position. Rudder* + 20° + 1/2° from neutral faired position. Rudder tab + 19 1/2° + 1/2° from neutral faired position. (T.E. faired with tail cone, control column neutral. (Down 15° + 1/2° from neutral, control column full 24° 30' from vertical. Elevator (Up 22° + 1/2° from neutral when elevator trim tab ( is 6° nose down to 4° nose up. (Up 25° + 1/2° from neutral when elevator trim tab ( is 4° nose up to 9° nose up. (Up 25° + 1/2° from neutral when elevator trim tab ( is 4° nose up to 9° nose. up. Elevator spring (Up 2 1/2° + 1/2° controls neutral - springs each tab will produce (3 1/2# preload at T.E. (Down 22 1/2° + 1/2° from faired position control full aft. (Up 7 1/2° + 1/2° from faired position, control full forward. Elevator trim (When indicator zer oed T.E. down 2° from faired position. tab** (Down 11° + 1/2° from neutral faired position. (Up 4° + 1/2° from neutral faired position. *Airplanes having 15 1/2° rudder travel may change to + 20° travel Arrangement "B" (See Douglas Service Letter A-214-191/ERH II-G-7, DC6-SC#959. Douglas Dwg. 4394980, E.O. #5328376-AZ) **To provide elevator trim tab limits 11° down and 1° up, accomplish rework per Douglas Service Bulletin DC-6 No. 497. Certification basis Type Certificate No. 6A3. (Transport Category, CAR 4b, as amended to October 1, 1949.) The forward and aft lower belly cargo co mpartments are Class "D" compartments. Smoke detectors, per amendment 4b-2 effective August 25, 1955, or extinguishing provisions are not required. Compliance with ditching provisi ons of 4b.292 has been demonstrated. Maximum approved operational altitude 25,000 ft. Production basis Production Certificate No. 27 Export eligibility Eligible for export to all countries subject to the provisions of MOP 2-4 except as follows: (a) Canada - Landplane only eligible Equipment: Approval for the installation of all items of equipment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). The asterisk denotes that approval has been obtaine d by someone other than the aircraft manufacturer. An item marked with an as terisk may not have been manufactured under a FAA monitored or approved quality control system, and therefore conformity must be determined if the item is not identified by a Form ACA-186, PMA or other evidence of FAA production approval. Propellers and Propeller Accessories (Except De-Icing Equipment) Note: When reversible pitch propellers are installed, the mini mum permissible force at the throttle knobs required to move each throttle from positive to negative thrust position shall be eight pounds in addition to the throttle system friction. 1. (a) 4 Ham. Std. propellers, hubs 43E60, blades 6895-8 2240 lbs. (+272.0) Diameter: Max. 13'5-5/16", min. allowable for repairs 13' 1-9/16". No further tolerance permitted. Pitch settings at 42" sta.: Reverse -8°, Min. low +30° Feathered +96° (approx.) 9 6A3 (b) Deleted - September 24, 1954 (c) 4 Spinners, Ham. Std. 511748 with D ouglas Cowling Interliners 181 lbs. (+276.0) 2. Propeller governors (See NOTE 3 for governor settings for CB-16 engines.) (a) 4 Ham. Std. 5U18-1 52 lbs. (+292.0) (b) 4 Ham. Std. 5U18-11, -24, -61, -114 or -118. 54 lbs. (+293.0) 3. Propeller feathering pumps (a) 4 Pesco IE-777-KL-1 (D ouglas Dwg. #3342196) 64 lbs. (+367.0) Engines and Engine Accessories - Fuel and Oil Systems 101. (a) 4 P&W Double Wasp CB- 16 9600 lbs. (+294.0) & (+324.0) (b) 4 P&W Double Wasps CB- 17 9600 lbs. (+294.0) & (+324.0) (c) 4 P&W R-2800-52W 9600 lbs. (+294.0) & (+324.0) (d) 4 P&W R-2800-83AM7 9600 lbs. (+294.0) & (+324.0) (e) 4 P&W R-2800-83AM5 9600 lbs. (+294.0) & (+324.0) (f) 4 P&W Double Wasps CB-3 9468 lbs. (+294.0) & (+324.0) (g) 4 P&W Double Wasps CB- 4 9468 lbs. (+294.0) & (+324.0) 102. Fuel dump valve system (a) Ten wing tank system (Dougl as Dwg. #5248375-5500) 149 lbs. (+429.0) (b) Ten wing tank system (Douglas Dwg. #5393033-5501 or 5393033-501) 149 lbs. (+429.0) (c) Eight wing tank system (D ouglas Dwg. #5393033) 139 lbs. (+427.5) (d) Eight wing tank system (Douglas Dwg. #5393033) 145 lbs. (+427.0) 103. System fuel and oil (a) System fuel, 4722 gal. or 4736 gal. capacity ten wing fuel 411 lbs. (+458.5) tanks (68.5 gals.) (b) System oil, 35 gal. oil tank installa tion (55.0 gals.) Ham. 413 lbs. (+326.0) Std. propeller installation (c) System oil, wing fillet 26 gal. tank (50% oil - 50% gasoline. 21 lbs. (+472.0) 3.1 gals., 6.77#/gal.) (d) System fuel, 5406 gal. capacity ten wing fuel tanks (66.7 gals.) 400 lbs. (+460.0) (e) System fuel, 5404 gal. capacity eight wi ng fuel tanks (56.2 gals.) 337 lbs. (+466.0) (f) System fuel, 4322 gal. capacity eight wing fuel tanks (41.5 gals.) 249 lbs. (+459.0) (g) System fuel, 5512 gal. capacity eight wi ng fuel tanks (51.7 gals.) 310 lbs. (+467.5) (h) System fuel, 4934 gal. capacity eight wi ng fuel tanks (53.5 gals.) 321 lbs. (+453.0) (i) System fuel, 5042 gal. capacity eight wi ng fuel tanks (49.0 gals.) 294 lbs. (+453.5) 104. (a) Water-alcohol Injection (Dougl as Dwgs. #7352910, #7371946, 244 lbs. (+388.0) #5350629, and #5371664) with Water-a lcohol Regulator, P&W No. 106400E (b) Water-alcohol Injection Fl uid, 39 gal. 291 lbs. (+453.5) 105. (a) 4 Oil Coolers, AiResearch 86764 or 87295 162 lbs. (+351.0) 107. Starters (a) 4 Eclipse 1416-18 110 lbs. (+350.5) (b) 4 Eclipse 36E00-4 113 lbs. (+350.5) (c) 4 Jack & Heintz JH-6ER12, JH -6ESR12 or JH-6BESR12 106 lbs. (+350.5) (d) 4 AN4116R6 112 lbs. (+350.0) (e) 4 Jack & Heintz JH-6CE 108 lbs. (+351.0) Landing Gear 201. 4 Main wheel-brake a ssemblies, 17.00-20, Type III (a) Goodyear Model LF20HBM 768 lbs. (+474.0) Wheel Assembly No. 9540484 Brake Assembly No 9540505 (Max. T.O. Wt. 100,000 lbs., Landing 85,000 lbs.) (b) Goodyear Model LF20HBM 768 lbs. (+474.0) Wheel Assembly No. 9540484 Brake Assembly No 9540504 (Skydrol) (Max. T.O. Wt. 100,000 lbs., Landing 85,000 lbs.) (c) Goodyear Model LF20HBM 747 lbs. (+474.0) Wheel Assembly No. 9540484 Brake Assembly No. 9560164 (d) Goodyear Model LF20HBM 747 lbs. (+474.0) Wheel Assembly No. 9540484 Brake Assembly No. 9560166 (Skydrol) (e) B.F. Goodrich Co., Model 1753M 737 lbs. (+474.0) Wheel Assembly No. H-3-743 Brake Assembly No. H-2-603 (f) B.F. Goodrich Co., Model 1753M 737 lbs. (+474.0) Wheel Assembly No. H-3-743 Brake Assembly No. H-2-602 (Skydrol) (g) B.F. Goodrich Co., Model 1753M 731 lbs. (+474.0) Wheel Assembly No. H-3-743 Brake Assembly No. H-2-630 (h) B.F. Goodrich Co., Model 1753M 731 lbs. (+474.0) Wheel Assembly No. H-3-743 Brake Assembly No. H-2-629 (Skydrol) (i) Goodyear Model LF20HBM 808 lbs. (+474.0) Wheel Assembly No. 9540906 Brake Assembly No. 9560166 (Skydrol) (j) B.F. Goodrich Co., Model 1753M 731 lbs. (+474.0) Wheel Assembly No. H-3-743 Brake Assembly No. H-2-648 (k) Goodyear Model LF20HBM 808 lbs. (+474.0) Wheel Assembly No. 9540906 Brake Assembly No. 9560164 202. 4 Main wheel tires (NOTE: Satisfactory tire inflation pressures are given in the Airplane Maintenance Manual.) (a) 20-ply rating, 15:50x20, Ty pe III, Nylon 645 lbs. (+474.0) (b) 16-ply rating, 15:50x20, Ty pe III, Nylon 640 lbs. (+474.0) (Maximum take-off weight 100,000 lbs.) (c) 20-ply rating, 15:50x20, Type III Nylon (Tubeless) 676 lbs. (+474.0) 203. 4 Main wheel tubes, 15:50x20, Type III, Regular 86 lbs. (+474.0) 204. Nose wheel, 44" (a) Goodyear Model 44NBM, Type I 72 lbs. (+39.0) Wheel assembly No. 9540375 (b) Goodyear Wheel Assembly No. 9540758, Type I 72 lbs. (+39.0) (c) Goodrich Wheel Assembly No. H- 3-866, 16:00-16, Type III 54 lbs. (+39.0) (d) Goodyear Wheel Assembly No. 9540876, Type I 72 lbs. (+39.0) 205. (a) Nose wheel tire, 12-ply rating, 44", Type I, Nylon 105 lbs. (+39.0) (Inflation pressure 70 psi) (b) Nose wheel tire, 14-ply rating, 15: 00-16, Type III, Nylon, 99 lbs. (+39.0) Tubeless (Inflation pressure 70 psi) (c) Nose wheel tire, 12-ply rating, 44" Type I, Nylon, Tubeless 105 lbs. (+39.0) (Inflation pressure 70 psi) 206. Nose wheel tube, 44", Regular 16 lbs. (+39.0) 207. Main gear shock strut assembly Maximum Take-off Weight - 100,000 lbs. (a) 2 Cleveland 8065H (Douglas Dwg. 5344246-502) 1112 lbs. (+475.0) (b) 2 Cleveland 8065HA (Douglas Dwg. 5342446-5502) (Skydrol) 1114 lbs. (+475.0) Maximum Take-off Weight - 107,000 lbs. (c) 2 Cleveland 8065J (Douglas Dwg. 5342446-504) 1065 lbs. (+475.0) (d) 2 Cleveland 8065JA (Douglas Dwg. 5342446-5504) (Skydrol) 1074 lbs. (+475.0) (e) 2 Cleveland 8065K (Douglas Dwg. 5342446-506) 1023 lbs. (+475.0) (f) 2 Cleveland 8065KA (Douglas Dwg. 5342446-5506) (Skydrol) 1032 lbs. (+475.0) (g) 2 Cleveland 8065LA (Douglas Dwg. 5342446-5508) (Skydrol) 1037 lbs. (+475.0) (h) 2 Cleveland 8065L (Douglas Dwg. 5342446-508) 1028 lbs. (+475.0) (i) 2 Cleveland 8065N (Douglas Dwg. 5342446-512) 1033 lbs. (+475.0) (j) 2 Cleveland 8065NA (Douglas Dwg. 5342446-5512) (Skydrol) 1037 lbs. (+475.0) (k) 2 Cleveland 8065M (Douglas Dwg. 5342446-510) 1028 lbs. (+475.0) 11 6A3 208. Nose gear shock strut assembly (a) Cleveland 8488B (Douglas Dwg. 5240509) 301 lbs. (+50.0) (b) Cleveland 8488BA (Douglas Dwg. 5240509-5000) (Skydrol) 303 lbs. (+50.0) (c) Cleveland 8488CA (Douglas Dwg. 5240509-5500) (Skydrol) 298 lbs. (+50.0) (d) Cleveland 8488C (Douglas Dwg. 5240509-500) 296 lbs. (+50.0) (e) Cleveland 8488D (Douglas Dwg. 5240509-502) 294 lbs. (+50.0) (f) Cleveland 8488DA (Douglas Dwg. 5240509-5502) (Skydrol) 298 lbs. (+50.0) (g) Cleveland 8488E (Douglas Dwg. 5240509-504) 284 lbs. (+50.0) (h) Cleveland 8488EA (Douglas Dwg. 5240509-5504) (Skydrol) 286 lbs. (+50.0) (i) Cleveland 8488HA (Douglas Dwg. 5240509-5510) (Skydrol) 306 lbs. (+50.0) (j) Cleveland 8488H (Douglas Dwg. 5240509-510) 304 lbs. (+50.0) (k) Cleveland 8488JA (Douglas Dwg. 5240509-5512) (Skydrol) 306 lbs. (+50.0) (l) Cleveland 8488J (Douglas Dwg. 5240509-512) 304 lbs. (+50.0) Electrical Equipment 301. Generators (a) 4 Eclipse 30E02-5-A 250 lbs. (+355.0) (b) 4 Eclipse 30E02-5-C 244 lbs. (+355.0) (c) 4 General Electric 2CM75D1 244 lbs. (+355.0) (d) 4 General Electric 2CM82D1 240 lbs. (+355.0) 302. Batteries (a) 2 Exide 6FJ-13 164 lbs. (+ 81.0) 310. Auxiliary electrical gene rating system 283 lbs. (+303.0) (Engine-Generator AAF type D-2) (Douglas Dwg. #4363384) Interior Equipment 401. FAA Approved Airplane Flight Ma nual (not required for Models R6D-1 and C-118A in military operation). (A manual containing information required for the Airplane Flight Manual may be carried in lieu thereof in aircraft operated under the provisions of Parts 40, 41 or 42 of the Civil Air Regulations). The following table identifies the Airplane Flight Manuals and the revisions thereof currently approved for each airplane: Date Douglas Latest Approved Latest Airplane Serial Number Report No. Rev. No. Ap. Rev. (a) Deleted September 10, 1953 (b) 43297, 43817, 44075, 44677, 44889, 45058, SM-14157(Slick, 21 12-31-64 45110, 45457, 45458, 45518-45520 (Se NOTE FTL, JAL) 7(f) for passenger configuration) (c) 43839-43841, 44915-44917, 45373-45375 SM-14788(AAL) 10 11-7-63 (d) 44076, 44257 SM-14361(KLM) 13 10-16-57 (e) Deleted October 11, 1955 (f) 44069, 44070, 43296 (See NOTE 7(c) or (e) SM-14848(JAL) 7 2-17-59 for passenger configuration) (g) 44258-44260 SM-14319(PAA) 25 10-12-61 (h) 44420, 44421 SM-14670(SAB) 2 1-25-55 (i) 43707 (R6D-1) SM-14157XX(Slick) Supp. 8-4-55 Rev. #3 (j) 44064 SM-14796(NWA) 16 2-20-64 44071-44074 NWA Supp. Rev. #5 5-22-59 44890, 45499 (See NOTE 7(d), (g) or (h) for passenger configuration) (k) 43404 (R6D-1) SM-14157FTL(FTL) Supp. 12-1-56 Rev. #3 (l) 43818, 43819, 44063 (See NOTE 7(b) for SM-19239(AAZ-UAT) 4 9-20-63 passenger configuration) (m) 44905-44909, 45521, 45522 SM-19501(UAL) 5 12-26-63 Date Douglas Latest Approved Latest Airplane Serial Number Report No. Rev. No. Ap. Rev. (n) Models R6D-1 and C-118A (applies to SM-22594 --- --- aircraft as delivered by the manufacturer. Any subsequent modi fications and changes made to a particular aircraft by the military or an operator that affect the Airplane Flight Manual will require appropriate Manual revisions, which must be submitted to the FAA, Aircraft Engineering Division for approval). (o) 45372 SM-22916(Riddle) --- --- (p) 45226, 45227, 45368, 45369 SM-22947(TC, Air 1 2-24-58 Liban) (q) 45517 SM-23027(ALK) 1 8-24-61 (r) 45474-45476 SM-23074(ONA) 1 8-29-58 (s) 45480, 45481 SM-23152(LAS) 1 12-11-58 (t) 45503, 45504, 45527-45532 SM-23161(NAT, ICA, 3 1-28-59 HCA) Great Lakes Airlines Supp. Rev. #1 dated 7-10-58 required on 45503 and 45504 (u) 45551 SM-14522 (SWA) 3 2-25-55 (v) 45497-45498 SM-14827 (CPA) 8 10-19-61 45500 402. Emergency ladders (NOTE: Suitable evacuati on slides may be installed in lieu of ladders) (a) (Douglas Dwg. #5363735) 19 lbs. (+171.5) (b) (Douglas Dwg. #5402816) 20 lbs. (+178.0) (c) (Douglas Dwg. #3352240) 18 lbs. (+ 69.0) 403. Automatic pilot: (Weight and C.G. shown do not include radio rack items of following installations which are listed under Electrical Equipment of Douglas Master Equipment List). (a) Pioneer PB-10 (3 sevos model 15601-1-A) 137 lbs. (+339.0) (1) Servo stall torques measured at the servo sectors are as follows and are satisfactory for Flight Path Control: Elevator: 88 to 158 in.lbs. (11-20 lbs. @ pilot's control) Aileron: 340 to 494 in.lbs. (14-20 lbs. @ pilot's control) Rudder: 324 to 432 in.lbs. (57-76 lbs.f @ pilot's control) (2) Maximum speed for operation with autopilot is 330 mph TIAS. Minimum terrain clearance for autopilot cruise configurations is 1000 ft.: for approach is 200 ft., pilot's seat belt fastened and hand on control wheel (These clearances do not override any higher minimum operational altitudes). (b) Sperry A-12 (3 servos Douglas Dwg. No. 2403860 or Sperry 150 lbs. (+287.0) Nos. 678919-261 plus 664575; 1 servo No. 65822-11, 658648-11 plus 658774 or 658648-41 plus 658774). (1) Servo stall forces measured at pilot's controls: Elevator: Max. 26 lbs., min. 20 lbs. Aileron: Max. 20 lbs., min. 12 lbs. Rudder: Max. 68 lbs., min. 51 lbs. (Stall forces shown are sa tisfactory for Automatic Approach) (2) Maximum speed for operation with autopilot is 250 mph TIAS. Minimum terrain clearance for autopilot cruise configurations is 1000 ft.: for approach is 200 ft., pilot's seat belt fastened and hand on control wheel (Minimum altitude for each case does not override any higher operational altitudes). (3) When the automatic pilot installation is modified in accordance with DACo Service Letter DC-6 No. 160 dated 9-2-53 and Supp. No. 1 dated 4-21-54 and elevator trim servo 658648-41 is installed, the following elevator servo stall forces and airplane operating speeds for automatic pilot operation apply: Max. 26 lbs., min. 13 lbs. Max. speed: 250 mph TIAS Max. 22 lbs., min. 13 lbs. Max. speed: 330 mph TIAS 13 6A3 (c) Sperry A-12 (3 servos Douglas Dwg. No. 2405685 or Sperry 157 lbs. (+277.0) 678919-161 plus 664575; 1 servo 65822-11, 65848-11 plus 658774 or 658648-41 plus 658774) (1) Servo stall forces measured at pilot's controls: Elevator: Max. 26 lbs., min. 20 lbs. Aileron: Max. 20 lbs., min. 12 lbs. Rudder: Max. 68 lbs., min. 51 lbs. (Stall forces shown are sa tisfactory for Automatic Approach) (2) Maximum speed for operation with autopilot is 250 mph TIAS. Minimum terrain clearance for autopilot cruise configurations is 1000 ft.: for approach is 200 ft., pilot's seat belt fastened and hand on control wheel. (Minimum altitude for each case does not override any higher minimum operational altitudes). (3) When the automatic pilot installation is modified in accordance with DACo Service Letter DC-6 No. 160 dated 9-2-53 and Supp. No. 1 dated 4-21-54 and elevator trim servo 658648-41 is installed, the following elevator servo stall forces and airplane operating speeds for automatic pilot operation apply: Max. 26 lbs., min. 13 lbs. Max. speed: 250 mph TIAS Max. 22 lbs., min. 13 lbs. Max. speed: 330 mph TIAS (d) Sperry A-12 (1 servo PAA No. 44.051. 0001-100 or 102; 2 servos 157 lbs. (+277.0) PAA No. 44.051.0001-101 or -103; 1 servo 658522-11 or 664237-11 or 658648-11 plus 658774 or 658648-41 plus 658774. (1) Servo stall forces measured at pilot's controls: Elevator: Max. 22 lbs., min. 16 lbs. Aileron: Max. 20 lbs., min. 12 lbs. Rudder: Max. 68 lbs., min. 51 lbs. (Stall forces shown are sa tisfactory for Automatic Approach) (2) Maximum speed for operation with autopilot is 250 mph TIAS. Minimum terrain clearance for autopilot cruise configurations is 1000 ft.: for approach is 200 ft., pilot's seat belt fastened and hand on control wheel. (Minimum altitudes for each case does not override any higher minimum operational altitudes). (3) When the automatic pilot installation is modified in accordance with DACo Service Letter DC-6 No. 160 dated 9-2-53 and Supp. No. 1 dated 4-21-54 and elevator trim servo 658648-41 is installed, the following elevator servo stall forces and airplane operating speeds for automatic pilot operation apply: Max. 26 lbs., min. 13 lbs. Max. speed: 250 mph TIAS Max. 22 lbs., min. 13 lbs. Max. speed: 330 mph TIAS (e) Pioneer PB-10 (3 servos model 15601- 1-A, 1 servo model 15620-2A) 148 lbs. (+326.0) (1) Servo stall torques measured at the servo sectors are as follows and are satisfactory for Flight Patch Control: Elevator: 88 to 158 in.lbs. (11-20 lbs. @ pilot's control) Aileron: 340 to 494 in.lbs. (14-20 lbs. @ pilot's control) Rudder: 324 to 432 in.lbs. (57-76 lbs. @ pilot's control) (2) Maximum speed for operation with autopilot is 330 mph TIAS. Minimum terrain clearance for autopilot cruise configurations is 1000 ft.: for approach is 200 ft., pilot's seat belt fastened and hand on control wheel (These clearances do not override any higher minimum operational altitudes). * (f) Lear L-5 servos model 118P, 1 servo model 220-1A) installed 170 lbs. (298.5) in accordance with Lear Dwg. No. 95790. (Weight and arm shown are for complete installation) (1) Servo stall torques at capstan slip clutch are as follows and are satisfactory for automatic approach. Elevator: 85 + 5 in. lbs. Aileron: 75 + 5 in. lbs. Rudder: 85 + 5 in. lbs. (2) Maximum speed for operation with autopilot is 300 mph TIAS. Minimum terrain clearance for autopilot cruise configurations is 1000 ft.: for approach is 200 ft., pilot's seat belt fastened and hand on control wheel (These clearances do not override any higher minimum operational altitudes). (3) With this autopilot installa tion one of the following is required: (a) Slick Airways, Inc. supplementary Airplane Flight Manual Revision to Douglas Report No. 11.57 dated 2-5-52 or (b) An Airplane Flight Manual Revision inco rporating air limitations specified in item (2) above. (g) Sperry A-12 (3 servos Sperry 679803-161 plus 664575. 140 lbs. (+282.0) 1 servo 658618-11 plus 658774 or 658648-4; plus 658771) (1) Servo stall forces measured at pilot's controls: Elevator: Max. 25 lbs., min. 20 lbs. Aileron: Max. 20 lbs., min. 12 lbs. Rudder: Max. 68 lbs., min. 51 lbs. (Stall forces shown are satisfactory for automatic approach) (2) Maximum speed for operation w ith automatic pilot is 250 mph TIAS. Minimum terrain clearance for automatic pilot cruise configuration is 1000 ft., for approach 200 ft., pilot's seat belt fastened and hand on control wheel. (Minimum altitudes for each case does not override operational altitudes). (3) When the automatic pilot installation is modified in accordance with DACo Service Letter No. 160 dated 9-2-53 and Supp. No. 1 dated 4-21-54 and elevator trim servo 658648-41 is installed, the following elevator servo stall forces and airplane operating speeds for automatic pilot operation apply: Max. 26 lbs., min. 13 lbs. Max. speed: 250 mph TIAS Max. 22 lbs., min. 13 lbs. Max. speed: 330 mph TIAS (h) Sperry A-12 (3 servos Sperry 679803-167 plus 664575; 140 lbs. (+282.0) 1 servo 658648-41 plus 658774) (1) Servo stall forces measured at pilot's controls are as follows, and are satisfactory for automatic approach: Elevator: Max. 26 lbs., min. 13 lbs. Aileron: Max. 20 lbs., min. 12 lbs. Rudder: Max. 68 lbs., min. 51 lbs. (2) Maximum speed for operation with autopilot is 250 mph TIAS; if maximum elevator servo stall force is limited to 22 lbs., the maximum speed is 330 mph TIAS. See FAA Approved Airplane Flight Manual for altitude loss during automatic pilot malfunction. 404. Windshield wipers (a) Kearfott or Alco (Douglas #5332419) (Skydrol) 10 lbs. (+ 14.0) (b) Kearfott or Alco (Douglas Dwg. #5332419-5000) (Skydrol) 10 lbs. (+ 14.0) 405. Instruments - in accordance with the following Dwgs. on file with the FAA Regional Office in Los Angeles, California: (a) Douglas Dwg. 7398245 408. Oxygen system (Full face, or equivalent, demand oxygen mask and regulator required for each crew member on flight deck duty). (a) Oxygen system, less bottle (Douglas Dwg. #5329204-532) 7 lbs. (+ 65.0) Oxygen bottle, Kidde 923757 27 lbs. (+ 73.5) (b) Oxygen system, less bottle (Douglas Dwg. #5390822-501) 13 lbs. (+ 61.5) Oxygen bottle, Kidde 923748 21 lbs. (+ 73.0) (c) Oxygen system, less bottles (Dougl as Dwgs. #5397930, 5398732, 34 lbs. (+160.5) 5397988) (Models R6D-1 and C-118A only - See NOTE 5(g)). Oxygen bottles, G-1, D-2, AAF 44D22201 (3) 39 lbs. (+343.5) (d) Oxygen system, less bottles (Douglas Dwg. #5490000-501) 36 lbs. (+ 67.0) Oxygen bottle, Kidde 923748 21 lbs. (+ 74.0) Oxygen bottle, Portable, Scott 5600B-3B-2 8 lbs. (+ 69.0) (e) Oxygen system, less bottle (Douglas Dwg. #5329204-540) 35 lbs. (+ 74.0) Oxygen bottle, Kidde 924051 34 lbs. (+ 65.0) Oxygen bottle, Scott 5600B-3B-2 8 lbs. (+ 65.0) 15 6A3 (f) Oxygen system, less bottle (Douglas Dwg. #5390986-537) 24 lbs. (+ 74.0) Oxygen bottle, Kidde 923748 21 lbs. (+ 64.0) Oxygen bottle, Scott 5600B-3B-2 8 lbs. (+ 65.0) (g) Oxygen system, less bottle (Douglas Dwg. #5329204-544) 35 lbs. (+ 73.0) Oxygen bottle, Kidde 924051 34 lbs. (+ 65.0) Oxygen bottle, Scott 5600-B3-B-2 8 lbs. (+ 65.0) (h) Oxygen system, less bottle (Douglas Dwg. #5390986-543) 35 lbs. (+ 83.0) Oxygen bottle, Kidde 924051 34 lbs. (+ 65.0) Oxygen bottle, Scott 5600-B3-B-2 8 lbs. (+ 65.0) (j) Oxygen system, less bottle (Douglas Dwg. #5329204-546) 35 lbs. (+ 73.0) Oxygen bottle, Kidde 924051 34 lbs. (+ 65.0) Oxygen bottle, Scott 5600-B3-B-2 8 lbs. (+ 65.0) (k) Oxygen system, less bottle (Douglas Dwg. #5348744-502) 28 lbs. (+ 90.0) Oxygen bottle, Kidde 923757 27 lbs. (+ 73.5) Portable oxygen bottle, (UAL Dwg. 9F708) 12 lbs. (+121.0) (l) Oxygen system, less bottle (Douglas Dwg. #5390986-569) 45 lbs. (+ 86.0) Oxygen bottle, Kidde 924051 34 lbs. (+ 65.0) Oxygen bottle, Scott 5600-B-3B-2 8 lbs. (+ 65.0) (m) Oxygen system, less bottle (Douglas Dwg. #5390986-571) 24 lbs. (+ 70.0) Oxygen bottle, Kidde 923748 21 lbs. (+ 73.0) Oxygen bottle, Scott 5600-B-3B-2 8 lbs. (+ 65.0) (n) Oxygen system, less bottle (Douglas Dwg. #5290986-575) 45 lbs. (+ 86.0) Oxygen bottle, Kidde 924051 34 lbs. (+ 65.0) Oxygen bottle, Scott 5600-B-3B-2 8 lbs. (+ 65.0) (o) Oxygen system, less bottle (Douglas Dwg. #5390986-579) 26 lbs. (+ 91.5) Oxygen bottle, Kidde 924051 34 lbs. (+ 65.0) Oxygen bottle, Scott 5600-B-3B-2 8 lbs. (+ 65.0) (p) Oxygen system, less bottle (Douglas Dwg. #5390986-529) 35 lbs. (+ 63.0) Oxygen bottle, Kidde 924051 34 lbs. (+ 65.0) Oxygen bottle, Scott 5600-B-3B-2 8 lbs. (+ 65.0) (q) Oxygen system, less bottle (Douglas Dwg. #5390986-560) 32 lbs. (+ 81.0) Oxygen bottle, Kidde 923748 21 lbs. (+ 65.0) Oxygen bottle, Scott 5600-B-3B-2 8 lbs. (+ 65.0) (r) Oxygen system, less bottle (Douglas Dwg. #5390986-567) 27 lbs. (+ 69.0) Oxygen bottle, Kidde 923748 21 lbs. (+ 65.0) Oxygen bottle, Scott 5600-B-3B2 8 lbs. (+ 65.0) (s) Oxygen system, less bottle (Douglas Dwg. #5390986-585) 43 lbs. (+ 81.0) Oxygen bottle, Kidde 924051 34 lbs. (+ 65.0) Oxygen bottle, Scott 5600-B-3B2 8 lbs. (+ 65.0) Deicing Equipment 501. (a) 2 Wing heaters, Surface Combination Corp. 138 lbs. (+117.0) B88A92 (Douglas Dwg. #5359829-10), (88A92) (Douglas Dwg. #5359829-12), J88A92 (Douglas Dwg. #5406945-9), L88A92 (Douglas Dwg. #5406945-11), M88A92 (Douglas Dwg. #5406945-17), N88A92 (Douglas Dwg. #5406945-19) (b) 2 Wing accessory case (Douglas Dwg. #5359913) 44 lbs. (+397.0) (c) 2 Wing ground blowers, English & Lauer CM-025-4CC 11 lbs. (+408.5) (Douglas Dwg. #7333181) (d) Empennage heater, Surface Combustion Corp. B88A92 69 lbs. (+1003.0) (Douglas Dwg. #5359829-10), C88A92 (Douglas Dwg. #5359829-12), J88A92 (Douglas Dwg. #5406945-9), L88A92 (Douglas Dwg. #5406945-11), (Douglas Dwg. #5406945-17), N88A92 (Douglas Dwg. #5406945-19) (e) Empennage accessory case (Douglas Dwg. #5359913) 22 lbs. (+975.0) (f) Empennage ground blower, English & Lauer CM-050-5CC 9 lbs. (+1016.5) (Doug. Dwg. 7333180) (g) 2 wing accessory case #26C98 32 lbs. (+397.0) (h) Empennage accessory case #26C98 16 lbs. (+975.0) 502. (a) Carburetor and windshield anti-icing system, complete, less alcohol 66 lbs. (+413.0) (b) Anti-icing alcohol (16 gals.) 106 lbs. (+570.0) (c) Carburetor anti-icing system complete, less alcohol 5 lbs. (+413.0) 503. (a) Propeller electrical anti-icing equi pment, less equipment 123 lbs. (+313.0) on Ham. Std. Propellers (Douglas Dwgs. #5344301, #5338222, #5338223, #5362737, #2372408) 504. (a) Propeller electrical anti-icing e quipment on Ham. Std. 24 lbs. (+272.0) 6895-8 blades Miscellaneous 605. Hydraulic fluid in system and reservoir (15.3 gals.) (a) Skydrol 138 lbs. (+340.5) (b) Mineral oil 111 lbs. (+340.5) NOTE 1. (a) Current weight and balance report including list of equipment included in certificated weight empty, and loading instructions, must be in each aircraft at th e time of original certification and at all times thereafter (except in the case of air carrier operators having an approved weight control system). Manufacturer's Master Equipment List contains list of approved equipment in addition to equipment listed in this specification. (b) "System Fuel and Oil" (Item 103), which must be incl uded in the empty weight, is that amount required to fill both systems and the tanks up to the tank outlets to the e ngines, when the airplane is in the level attitude. The propeller feathering oil in aircraft incorporating Hamilton Standard propellers is not considered usable oil and is included in the "System Oil". Th e nacelle oil tank capacities shown in this specification include only the usable oil for which the tanks are to be placarded. All hydrau lic system fluid (Item 605) must also be included in the empty weight of the airplane. (c) The "unusable fuel" is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as defined in CAR 4b.416 and may be obtai ned by taking the difference between the "total" and "usable" tank capacities shown under "Fuel Capac ity." The "unusable fuel" must either be included in the airplane empty weight or be suitabl y accounted for in the airplane weight and balance report. (d) Structural Limitations on Fuel Loading and Usage. All fuel must be distributed equally on both sides of the airplane. All main tanks must be filled equally first, then alternates, then auxiliaries (ten wing tank airplanes). Fuel must be used in the reverse order from fuel lo ading except for take-off, climb and landing, at which time the main tanks must be used. Sa tisfactory alternate fuel loading and usage procedures have been approved and placed in the Approved Airplane Flight Manual. These a lternate procedures may be used in lieu of the above. (e) Fuel dumping. Fuel dump valves (Item 102 must be installed for operation of the airplane at weights in excess maximum landing weight. Refer to FAA Approved Airplane Flight Manual for limitations and cautionary cedures to be observed during the dumping of fuel. Wh en dump system (Item 102) is installed, the amount of ble fuel remaining in the fuel tanks after dumping is as follows: (1) Ten Wing Airplane - 4722 Gal. or 4736 Gal. System Outer inner wing (#1 and #4 main) 112 gal. ea. Inboard inner wing (#2 and #3 main) 102 gal. ea. Outboard inner wing (#1 and #4 alt.) 50 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 120 gal. ea. Auxiliary fuel cells (L.H. and R.H. aux.) 168 gal. ea. (2) Ten Wing Tank Airpla ne - 5406 Gal. Gal. System Outer inner wing (#1 and #4 main) 116 gal. ea. Inboard inner wing (#2 and #3 main) 102 gal. ea. Outboard inner wing (#1 and #4 alt.) 00 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 36 gal. ea. Auxiliary fuel cells (L.H. and R.H. aux.) 168 gal. ea. (3) Eight Wing Tank Airplane - 5404 Gal. & 5512 Gal. System Outer inner wing (#1 and #4 main) 116 gal. ea. Inboard inner wing (#2 and #3 main) 108 gal. ea. Outboard inner wing (#1 and #4 alt.) 00 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 54 gal. ea. (4) Eight Wing Tank Airplane - 1322, 1931 and 5042 Gal. System Outer inner wing (#1 and #4 main) 116 gal. ea. Inboard inner wing (#2 and #3 main) 108 gal. ea. Outboard inner wing (#1 and #4 alt.) 00 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 39 gal. ea. 17 6A3 The total undumpable fuel, oil and ADI fluid must be included in the landing weight. In some cases the amount of undumpable fuel, oil and ADI fluid is greater than the difference between the maximum "Zero Fuel, Oil and ADI Fluid" gross weight and the maximum landing weight. When such is the case, the "Zero Fuel, Oil and ADI Fluid" gross weight used in loading the airplane mu st be reduced by an amount sufficient to insure that the maximum landing weight will not be exceeded after the fuel is dumped. (f) When the oil transfer tank is installed in the wing fillet, the weight of oil carried in that tank plus the system oil (Item 103(c)) must be included in the Zero Fuel, Oil and ADI Fluid gross weight. (g) For the interior arrangement of a particular ai rplane, see approved Douglas Report SM-13977, "Loading Chart and Actual Weight and Balance." That report shows the location of all crew member seats, the location and capacity of all cargo compartments, and the load re strictions on the floor and wall cargo tie down fittings. Cargo compartment must be placarded for the capacities specified in the above report. The airplane must always be loaded within the C.G. limits shown in this specification, accounting for crew movement and use of fuel, oil, and ADI fluid. NOTE 2. The following placard shall be placed on the instrument panel in full view of the pilot: (a) "This airplane shall be operated in compliance w ith the operating limitations specified in the FAA Approved Airplane Flight Manual." NOTE 3. When water-alcohol injection is not used for take-o ff on aircraft equipped with Item 101(a), P&W Double Wasp CB-16 engines, Item 101(c), P&W LR-2800-52W engines. Item 101(e), P&W R-2800-83AM5 engines or Item 101(g) P&W Double Wasps CB-3 engines, the prop governors must be reset prior to take-off in order to limit the dry take-off engine rpm to 2700. NOTE 4. Ferry permits may be issued to all Model DC-6A airp lanes on which one engine is inoperative, with its propeller removed or feathered under the following conditions. (a) Operation of aircraft shall be in accordance with per tinent limitations contained in the applicable portion of the FAA Approved Airplane Flight Manual, pe rtinent appendices, and existing instructions. (b) Maximum take-off weight 81,000 lbs. (Except when limited by runway length specified in Manual). (c) C.G. range: Fwd. C. G. 11.0% MAC (Sta. 413.2) Aft C.G. 28.0% MAC (Sta. 441.0) NOTE 5. The Navy Model R6D-1 and the US AF Model C-118A are similar to the Model DC-6A except for engines, brakes and numerous other differences. Numerous installations installed for the military services do not meet the requirements of the Civil Air Regulations and, therefore, are not approved. Prior to certification as a commercial aircraft, the following must be accomplished: (a) The Troop Bench, Litter and Passenger seat installations have not been approved and must be removed. In the event any of these aircraft are to be certificated fo r carriage of passengers, the interior arrangement, seat and other installations incorporated in the airplane must be demonstrated to comply with the pertinent Civil Air Regulations. (b) The Radio Equipment installation must be replaced with FAA approved equipment. (c) The external filler for the crew oxygen systems must be relocated to a position where there will be not danger of contamination from the drainage of oil, hydraulic flui d, etc. In addition, the oxygen system listed under Item 408(c) does not meet FAA minimum protective oxyge n requirements and the pilot's oxygen flow blinker indicator must be relocated to provide satisfactory vi sibility. Suitable modifications of the oxygen system must be accomplished to comply with the Civil Air Regulations. (d) The urinal installation must be removed from the ai rcraft and a thorough inspection made of the rear of the fuselage and empennage for corrosi on and possible structural damage. All corroded and damaged areas must be suitably replaced or repaired. (e) The wing heater temperature gauge markings do not co mply with the Civil Air Regulations and new markings must be installed. (f) The Automatic Pilot Servo Stall Torque limits do not comply with the Civil Air Regulations on all aircraft, therefore, the automatic pilot must be checked on each aircraft to determine whether the servo stall forces are within the approved limits, and if not , the Automatic Pilot installation must be suitably modified to insure the approved limits are not exceeded. (g) An Air Crew Check List (DACO Dwg. #3482737) is insta lled on some aircraft which is unsatisfactory to the FAA. This Check List must be removed or rendere d inoperative prior to certification. The location of the Check List is such that visibility of the crew is seriously restricted when it is in position for use by the crew. (h) The Operation Limitation Placard on these aircraft must be revised to comply with the Civil Air Regulations. (i) A FAA approved "Loading Chart and Actual Weight and Balance Report" must be provided prior to certification as a civil aircraft. (j) The maintenance, overhaul and modification records of each aircraft must be reviewed for changes made by the military services that may affect the airworthiness of the aircraft. Modifications and changes of equipment which affect the safety or performance of the aircraft must be approved by the FAA. (k) A FAA Approved Airplane Flight Manual must be provi ded for each airplane prior to certification as a civil aircraft. Due to difference in equipment installed on th e military and civil aircraft, the information contained in a FAA Approved Airplane Flight Manual for the Model DC-6A may not be applicable to the Navy R67D-1 or the USAF C-118A. (l) All military aircraft returned to civil operations mu st comply with all applicable Airworthiness Directives. prior to certification of a particular aircraft, it is suggested that the Aircraft Engineering Division, Western Region, L. A., California, be contacted for a complete list of all the modifications necessary. A Statement of Conformity for each individual aircraft, listing all non-conformities at the time of delivery to the military services is on file in that office. The non-conform ities vary from time to time, therefore, the above items may not be a true indication of a ll the changes that may be required. NOTE 6: The following table lists the maximum zero fuel, oil and ADI fluid, landing and take-off weights of the various 8 and 10 wing fuel tank aircraft as they are limited by structur al strength. Although an aircraft may be eligible, from a structural standpoint, for certain take-off weights, the take-off weight may be limited from a performance standpoint due to the propeller and engine combination that is insta lled, the flap setting used and whether water-alcohol injection is used to increase the ta ke-off power. Therefore, the table of take-off weights under maximum weights should also be adhered to in determining the maximum pe rmissible take-off weight of various aircraft. MAXIMUM STRUCTURAL LIMITS Airplane Serial Numbers Zero Fu el, Oil, Landing Take-off Weight 8 Tank 10 Tank and ADI Fluid Weight 8 Tank 10 Tank DC-6A (1) 43817-43819 43296, 43297 83,200 5 88,200 2 107,000 2, 3, 4 107,000 2, 3, 4 43839-43841 44063, 44064 44069-44076 44257-44260 44420, 44421 44677 44889, 44890 44905-44909 44915-44917 45058, 45110 45226, 45227 45368, 45369 45372-45375 45457, 45458 45474-45476 45480, 45481 45497-45500 45503, 45504 45517-45522 45527-45532 45551 C-118A 43565 & up 83,200 5 88,200 2 107,000 2,3,4 R6D-1 43206-43210 83,200 5 88,200 2 106,000 2,3,4 43401-43403 107,000 2,3,4,6 43670 & up 43404 & up 83,200 5 88,200 2 107,000 2,3,4,6 107,000 2,3,4 (1) See Douglas Service Bulletin #455, "Int erchanging of DC-6 Empennage Components and Restrictions Covering Such Interchanges." (2) Item 201(c), (d), (e), (f), (g), (h), (i), (j) or (k) (3) Item 202(a) and 207(c), (d), (e), (f), (g), (h), (i), (j) or (k) (4) 695 gal. capacity outer wing fuel tank re quired for take-off weights above 100,000 lbs. (5) Placard speeds in accordance with Airspeed Limits Table. (6) When center wing is reworked in accordance with D ouglas Dwg. No. 5329195 "AG". (Ref. Douglas Service Letter A-214SRF/12/69/JBL dated 29 September 1952). 19 6A3 NOTE 7. (a) Deleted September 10, 1953. (b) Serial Nos. 43818 and 43819 are eligible for carryi ng 96 airplane occupants (90 passengers including cabin attendants and 6 flight crew per Slick Interior C onfiguration Dwg. No. 60145, Amend. 1, dated June 2, 1953) as modified in accordance with Slick Airways data on file in FAA Western Regional Office (Los Angeles, California). Operation as passenger airplane cove red in Airplane Flight Manual SM-19239 (AAZ-UAT) (See Item 401(1)). (c) Serial No. 43296 is eligible for carrying 47 airplane occupants (40 passengers including 2 cabin attendants and 7 flight crew members per Slick Interior Configura tion Dwg. No. 0295S dated Sept. 1, 1953) as modified in accordance with Slick Airways data on file in F AA Western Regional Office (Los Angeles, California). Operation as passenger airplane covered in Ai rplane Flight Manual SM-14848 (JAL). (See Item 401(f).) (d) Serial Nos. 44071, 44072, 44073 and 44074 are eligible for carrying 82 airplane occupants (77 passengers including one cabin attendant, and 5 flight crew me mbers per Northwest Airlines Dwg. No. 6D16-27107, Rev. A, "General Arrangement - 76 Passenger DC-6A aircra ft") as modified in accordance with Grand Central Aircraft Company data on file in FAA Western Regi onal Office (Los Angeles, California). Operation as passenger airplane covered in Airplane Flight Manual SM-14796 (NWA) (See Item 401(j)). (e) Serial Nos. 44069 and 44070 are eligible for carrying 47 airplane occupants (40 passengers including 2 cabin attendants, and 7 flight crew me mbers per Slick Interior Configuration Dwg. No. 0295S dated Sept. 1, 1953 or Flying Tigers Interior Configuration Dwg. No. PS630A dated Nov. 5, 1953) as modified in accordance with Slick Airways and Flying Tiger Line data on file in FAA Western Regional Office (Los Angeles, California). Flying Tiger Line Supplementary Revision to Airpla ne Flight Manual (page 35a of Douglas Report No. 14848 dated Oct. 8, 1953) is required. (f) Serial No. 44075, 44678 and 44889 are eligible for ca rrying 107 or 111 airplane occupants (101 passengers including cabin attendants and 6 flight crew members or, 105 passengers including cabin attendants and 6 flight crew members per Flying Tigers-Slick Interior C onfiguration Dwg. No. E.O. 60184 "C" dated April 12, 1954) as modified in accordance with Flying Tiger-Slick Air line data on file in FAA Western Regional Office (Los Angeles, California). Flying Tiger Line Supplementary Revision to Airplane Flight Manual (pages 37 and 40C of Douglas Report No. SM-41457 dated November 30, 1955 for Serial Nos. 44075 and 44678, and page 40C dated Jan. 31, 1956 for Se rial No. 44889) is required. (g) Serial No. 44064 is eligible for carrying 84 airplane occupants (80 passengers including cabin attendant and 4 flight crew members per Northwest Airlines Dwg. SK- 29777-1, Rev., "Interior Arrangement - CPAL DC-6A") as modified in accordance with Grand Central Aircra ft Company data on file in FAA Western Regional Office (Los Angeles, California). Operation as passenge r airplane covered in Airplane Flight Manual SM-14796 (NWA) (See Item 401(j)). (h) Serial No. 44890 is eligible for carrying 70 to 82 airp lane occupants (including 2 cain attendants and 4 flight crew members) when modified in accordance with PA C Supplemental Type Certificate dated April 27, 1956. (See Item 401(j) or Appr oved Airplane Flight Manual). NOTE 8. In accordance with the agreement between the Department of Defense and the Civil Aeronautics Board, all air carrier operators utilizing aircraft which have been modified unde r the Civil Reserve Air Fleet Program, Part I, Phase II, may deduct the added weight of the military modification up to a maximum of 50 lbs. for each aircraft so modified. NOTE 9. In accordance with FAR 121.198 and FAR 129.23, aircraft operated by "Air Carriers" for cargo operation only, are permitted to increase the zero fuel and landing weights by 5% of the zero fuel weight. For aircraft covered by this specification the maximum zero fuel, oil and ADI fluid we ight may be increased to 87,360 lbs. and the maximum landing weight may be increased to 92,360 lbs. In add ition to the operator's normal inspection program, aircraft operated in accordance with FAR 121.198 or FAR 129.23 must be inspected in accordance with "Special Inspection Procedure for Cargo Operation," "Ref. Douglas Report LB -30673," as revised and approved by the FAA. Before returning the airplane to passenger serv ice after being operated at the increased weights in cargo service, the aircraft must be inspected per the above Douglas report. Requests for changes in the inspection procedure must be forwarded to the manufacturer for his recommendations and submitted to the FAA for approval. FAA approved Airplane Flight Manua l revision including performance information for operation at the increased weights should be obtained from the manufacturer. .....END..... ``` ## ADs (82, first 50, in force first) - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2017-06-05](https://openairdocs.org/ad/2017-06-05): Wings · Boeing DC-6, DC-6A, DC-6B and 3 more. Effective May 1, 2017 - [AD 2011-12-01](https://openairdocs.org/ad/2011-12-01): Equipment/Furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 268 more. Effective Aug 1, 2011 - [AD 2011-01-09](https://openairdocs.org/ad/2011-01-09): Oxygen · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 290 more. Effective Feb 9, 2011 - [AD 93-14-12](https://openairdocs.org/ad/93-14-12): Crewmember Protective Breathing Equipment Units · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 201 more. Effective Sep 2, 1993 - [AD 93-11-07](https://openairdocs.org/ad/93-11-07): Structural Integrity · Boeing DC-6, DC-6A, DC-6B and 3 more. Effective Jul 22, 1993 - [AD 89-11-07](https://openairdocs.org/ad/89-11-07): Main Landing Gear Fittings · Boeing DC-6, DC-6A, DC-6B and 6 more. Effective Jun 23, 1989 - [AD 88-04-01](https://openairdocs.org/ad/88-04-01): Vertical Stabilizer Spar Fittings · Boeing DC-6, DC-6A, DC-6B and 3 more. Effective Mar 21, 1988 - [AD 80-12-02 R1](https://openairdocs.org/ad/80-12-02-R1): Wing Fittings, Stringer, Skin Cracks · Boeing DC-6, DC-6A, DC-6B and 3 more. Effective Apr 21, 1987 - [AD 83-20-04](https://openairdocs.org/ad/83-20-04): Horizontal Stabilizer Rear Spar Caps · Boeing DC-6, DC-6A, DC-6B and 3 more. Effective Oct 19, 1983 - [AD 80-22-07](https://openairdocs.org/ad/80-22-07): Nose Gear Torque Link · Boeing DC-6, DC-6A, DC-6B and 3 more. Effective Nov 3, 1980 - [AD 54-23-01](https://openairdocs.org/ad/54-23-01): Fuselage Skin · Boeing DC-6, DC-6A, DC-6B and 3 more. Effective Dec 1, 1978 - [AD 61-05-02](https://openairdocs.org/ad/61-05-02): Emergency Exit Door Hinges · Boeing DC-6, DC-6A and DC-6B. Effective Dec 1, 1978 - [AD 67-13-02](https://openairdocs.org/ad/67-13-02): Operating Limitations · Boeing DC-6, DC-6A, DC-6B and 6 more. Effective Dec 1, 1978 - [AD 74-17-01](https://openairdocs.org/ad/74-17-01): Regulator · Boeing 707-100 Long Body, 707-100B Long Body, 707-100B Short Body and 78 more. Effective Sep 16, 1974 - [AD 65-09-02](https://openairdocs.org/ad/65-09-02): Main Gear Torque Links · Boeing DC-6, DC-6A and DC-6B. Effective May 21, 1965 - [AD 64-03-03](https://openairdocs.org/ad/64-03-03): Blades · Boeing DC-6, DC-6A, DC-6B and 26 more. Effective Mar 1, 1964 - [AD 63-20-03](https://openairdocs.org/ad/63-20-03): Lower Center Spar Caps · Boeing DC-6, DC-6A and DC-6B - [AD 62-25-02](https://openairdocs.org/ad/62-25-02): Main Landing Gear Shock Strut Cylinder · Boeing DC-6, DC-6A, DC-6B and 3 more - [AD 61-23-04](https://openairdocs.org/ad/61-23-04): Spar Caps · Boeing DC-6, DC-6A and DC-6B. Effective Dec 7, 1961 - [AD 61-08-01](https://openairdocs.org/ad/61-08-01): Fuel Transfer · Boeing DC-6, DC-6A, DC-6B and 3 more. Effective May 9, 1961 - [AD 61-04-02](https://openairdocs.org/ad/61-04-02): Spar Caps · Boeing DC-6, DC-6A and DC-6B. Effective Mar 14, 1961 - [AD 60-02-05](https://openairdocs.org/ad/60-02-05): Spar Cap · Boeing DC-6, DC-6A and DC-6B - [AD 53-05-01](https://openairdocs.org/ad/53-05-01): Propellers Slip Rings · Aero Spacelines 377, 377MG, 377SGT and 6 more - [AD 47-42-05](https://openairdocs.org/ad/47-42-05): Curtain Hook Replacements · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-06](https://openairdocs.org/ad/47-42-06): Fire Extinguisher Placard · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-07](https://openairdocs.org/ad/47-42-07): Windshield Handle Spring · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-08](https://openairdocs.org/ad/47-42-08): Horizontal Stabilizer Rivets · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-09](https://openairdocs.org/ad/47-42-09): Aileron Hinge Plates · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-10](https://openairdocs.org/ad/47-42-10): Landing Gear Antiretract Mechanism · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-11](https://openairdocs.org/ad/47-42-11): Horizontal Stabilizer Front Spar Caps · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-12](https://openairdocs.org/ad/47-42-12): Astrodrome Reinforcement · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-13](https://openairdocs.org/ad/47-42-13): Gust Lock Rework · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-14](https://openairdocs.org/ad/47-42-14): Voltage Regulator Bearings · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-16](https://openairdocs.org/ad/47-42-16): Combustion Chamber Inspection · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-17](https://openairdocs.org/ad/47-42-17): Center Spar Web · Boeing DC-6, DC-6A and DC-6B - [AD 47-42-19](https://openairdocs.org/ad/47-42-19): Horizontal Stabilizer Front Spar Cap · Boeing DC-6, DC-6A and DC-6B - [AD 47-51-15](https://openairdocs.org/ad/47-51-15): Brake Relining · Boeing DC-6, DC-6A and DC-6B - [AD 47-51-16](https://openairdocs.org/ad/47-51-16): Flap Support Rework · Boeing DC-6, DC-6A and DC-6B - [AD 48-02-04](https://openairdocs.org/ad/48-02-04): Brake Adjusting Pin Replacement · Boeing DC-6, DC-6A and DC-6B - [AD 48-02-05](https://openairdocs.org/ad/48-02-05): Outboard Accessory Cowling Rework · Boeing DC-6, DC-6A and DC-6B - [AD 48-02-06](https://openairdocs.org/ad/48-02-06): Inboard Nacelle Cover Plates · Boeing DC-6, DC-6A and DC-6B - [AD 48-07-02](https://openairdocs.org/ad/48-07-02): Engine Supercharger Control Actuator · Boeing DC-6, DC-6A and DC-6B - [AD 48-07-03](https://openairdocs.org/ad/48-07-03): Door Rework · Boeing DC-6, DC-6A and DC-6B - [AD 48-10-01](https://openairdocs.org/ad/48-10-01): Ungrounding Modification - Class A · Boeing DC-6, DC-6A and DC-6B - [AD 48-11-01](https://openairdocs.org/ad/48-11-01): Ungrounding Modification - Class B · Boeing DC-6, DC-6A and DC-6B - [AD 48-11-02](https://openairdocs.org/ad/48-11-02): Cabin Supercharger · Boeing DC-6, DC-6A and DC-6B - [AD 48-19-03](https://openairdocs.org/ad/48-19-03): Elevator Trim Tab Operating Mechanism · Boeing DC-6, DC-6A and DC-6B - [AD 48-48-02](https://openairdocs.org/ad/48-48-02): Vacuum Pump Line Replacement · Boeing DC-6, DC-6A and DC-6B All 82: https://openairdocs.org/tcds/6A3/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Douglas DC-6A](https://openairdocs.org/model/douglas-dc-6a): 7 aircraft (registry code 3021706) ## STCs approved under this data sheet (70, first 50) - [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc. - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC ST02962AT](https://openairdocs.org/stc/ST02962AT): Installation of L3 Communications Traffic Alert and Collision Avoidance System Model 791A (TCAS791A). Woven Electronics, LLC - [STC SA863EA](https://openairdocs.org/stc/SA863EA): Incorporation of DME Corporation emergency evacuation slide lighting system. Astronics Luminescent Systems Inc - [STC ST02580AT](https://openairdocs.org/stc/ST02580AT): Lithium cell battery pack to replace currently approved alkaline battery pack used in escape slide emergency light system.. Astronics Luminescent Systems Inc - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA01282NY](https://openairdocs.org/stc/SA01282NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K015 on aircraft powered by Pratt & Whitney radial reciprocating engine Series R-985, R-1340 and R-1830.. Airwolf Filter Corporation - [STC ST02965AT](https://openairdocs.org/stc/ST02965AT): Installation of Collins PN101 Compass System. B/E Aerospace Inc - [STC ST02963AT](https://openairdocs.org/stc/ST02963AT): Installation of Collins ALT-55B Radio Altimeter System. B/E Aerospace Inc - [STC SA3406WE](https://openairdocs.org/stc/SA3406WE): Modification of the oxygen system including the addition of a supply bottle, pressure relief valve, and a microphone in the smoke masks.. United Aeronautical Corporation - [STC ST334CH](https://openairdocs.org/stc/ST334CH): Installation of Superflite 102 fabric.. Aviation Products Systems Inc. - [STC SA1311WE](https://openairdocs.org/stc/SA1311WE): Installation of a United Data Control P/N V557 Voice Recorder in Boeing DC-6, DC-6A, DC-6B aircraft. United Airlines Inc - [STC ST02275AK](https://openairdocs.org/stc/ST02275AK): Approval for Douglas DC-6A and DC-6B aircraft operations on runways with slopes in excess of 2% gradient up to 6% gradient.. Everts Air Cargo - [STC ST981SO](https://openairdocs.org/stc/ST981SO): Deactivation of the cabin pressurization system, conversion of the cargo compartment to a class 'E' compartment, and modification of the ventilation system.. Everts Air Cargo - [STC SA363SO](https://openairdocs.org/stc/SA363SO): Cockpit voice recorder.. Delta Airlines Inc - [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc - [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc. - [STC SA1367GL](https://openairdocs.org/stc/SA1367GL): Surrendered and incorporated into STC ST334CH.. Cooper Aviation Supply Company, Inc. - [STC ST01608CH](https://openairdocs.org/stc/ST01608CH): Installation of brake assemblies, p/n 9560164-2 or 9560166, with non-asbestos linings, p/ns 5013028 and 5013029.. Aircraft Braking Systems Corporation - [STC SA02168AK](https://openairdocs.org/stc/SA02168AK): Installation of hourmeter airspeed switch. For unpressurized aircraft only. Pressurized aircraft must have pressurization system deactivated.. Avalaska Inc - [STC ST02166AK](https://openairdocs.org/stc/ST02166AK): Installation of UPS Aviation Technologies, Inc., GX50/60 GPS Navigator, Capstone configured MX20 Multi-Function display, and UAT transceiver.. Northern Air Cargo Inc. - [STC SA1753WE](https://openairdocs.org/stc/SA1753WE): Installation of VIP core assembly P/N VIP-106-18.. Vibration Isolation Products Corp - [STC SA4-525](https://openairdocs.org/stc/SA4-525): Installation of VIP P/N 106-1J engine mount core.. Vibration Isolation Products Corp - [STC SA1351WE](https://openairdocs.org/stc/SA1351WE): Replace existing fabric on wings, fuselage, empennage, and/or control surfaces, with Ceconite101 material. (262A Series -12). Ceconite Inc - [STC SA1479WE](https://openairdocs.org/stc/SA1479WE): Installation of a Benson portable buffet at fuselage station 141.375.. Evergreen Air Center Inc - [STC SA1769NM](https://openairdocs.org/stc/SA1769NM): Installation of Bulk Liquid Cargo Tanks. Sorm Inc - [STC SA722AL](https://openairdocs.org/stc/SA722AL): Revised limitations to permit operation when takeoff warning system has not been installed.. Ball Brothers, Inc - [STC SA1033NW](https://openairdocs.org/stc/SA1033NW): Installation of a bulk liquid cargo tank system. Flight Structures Inc. - [STC SA4198WE](https://openairdocs.org/stc/SA4198WE): Forward and rear cargo door latch assembly, P/N TAS-3361150, and fitting installation, P/N TAS05359955-8002.. Time Avn Services, Inc - [STC SA1506CE](https://openairdocs.org/stc/SA1506CE): Engine driven cabin air compressors and associated cabin pressurization controls removed.. Petroleum Air Transport, Inc. - [STC SA1083SO](https://openairdocs.org/stc/SA1083SO): Installation of four Pratt & Whitney R-2800-99W engines and Hamilton Standard propellers.. Bellomy-Lawson Aviation Inc - [STC SA1066SO](https://openairdocs.org/stc/SA1066SO): Alternate installation of hydraulic pump utilizing existing engine drive.. Bellomy-Lawson Aviation Inc - [STC SA770SO](https://openairdocs.org/stc/SA770SO): Installation of cargo pallet and container loading and restraint system.. Aeronautical Engineers, Inc - [STC ST484SO](https://openairdocs.org/stc/ST484SO): Installation of cargo restraining bulkhead.. Aeronautical Engineers, Inc - [STC ST964SO](https://openairdocs.org/stc/ST964SO): Installation of cargo interior, installation of cargo restraint and modification of pressurization system.. Bellomy-Lawson Aviation Inc - [STC SA326NW](https://openairdocs.org/stc/SA326NW): Installation of a bulk liquid cargo tank system. Pacific Alaska Airlines Inc - [STC ST974SO](https://openairdocs.org/stc/ST974SO): Installation of extra crew seating and air distribution system.. Bellomy-Lawson Aviation Inc - [STC SA1744WE](https://openairdocs.org/stc/SA1744WE): Installation of oil filter assemblies.. Nelson Filter - [STC ST528SO](https://openairdocs.org/stc/ST528SO): Installation of cargo restraining bulkhead.. Bellomy-Lawson Aviation Inc - [STC ST34GL](https://openairdocs.org/stc/ST34GL): Remove cabin pressurization system, modify cabin air heating and ventilating system.. Zantop Intn'l Airlines, Inc - [STC ST671SO](https://openairdocs.org/stc/ST671SO): Installation of cargo loading/ restraint system for palletized cargo.. Jet Avion Corp - [STC SA1363WE](https://openairdocs.org/stc/SA1363WE): Installation of Fairchild Industrial Products Model A100 cockpit voice recorder system.. Saturn Airways, Inc - [STC SA470CE](https://openairdocs.org/stc/SA470CE): Installation of Fairchild cockpit voice recorder Model A-100.. Universal Airlines, Inc - [STC SA1-580](https://openairdocs.org/stc/SA1-580): Television broadcasting equipment.. Midwest Program on Airborne Television Instruction - [STC SA1082WE](https://openairdocs.org/stc/SA1082WE): Interior arrangements.. AiResearch Aivation Service Co - [STC SA1148WE](https://openairdocs.org/stc/SA1148WE): Interior modifications.. Jay- Dee Aircraft Supply Co - [STC SA12SO](https://openairdocs.org/stc/SA12SO): Altimeter vibrators.. Pan American World Airways Inc - [STC SA1302WE](https://openairdocs.org/stc/SA1302WE): Fairchild A100 voice recorder.. Western Airlines Inc - [STC SA1313WE](https://openairdocs.org/stc/SA1313WE): Fairchild A100 voice recorder.. World Air Center - [STC SA1517WE](https://openairdocs.org/stc/SA1517WE): Interior arrangement for 97 occupants, DME installation, interior emergency lighting installation.. Mercer Enterprises All 70: https://openairdocs.org/tcds/6A3/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.