TCDS 6A4

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 6A4 Revision 31 BOEING DC-6B Navy R6D-1Z September 27, 2010 AIRCRAFT SPECIFICATION NO. 6A4 Type Certificate Holder The Boeing Company 4000 Lakewood Boulevard Long Beach, California 90808 Type Certificate Ownership Record 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., Sa nta Monica, California merged with McDonnell Douglas Corporation effective August 25, 1967 I - Model DC-6B, Approved April 11, 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 Double Wasps CA-15 or R-2800-83AM3, -52W, -83AM5 or -83AM7 (20:9 propeller reduction gearing) Fuel Aviation gasoline: (CA-15, CB-16 or CB-3, R-2800-52W, -83AM3 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.) M P HP RPM IN.HG. ALT. P&W Double Wasp 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 e ngine limits not applicable to CB-3 engines. P&W Double Wasps CA-17 or CB-4*, 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' I - Model DC-6B (cont'd) (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 50.0 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 e ngine limits not applicable to CB-4 engines. P&W Double Wasp CA-15 Low impeller gear ratio 7.29:1 Take-off (two minutes) (dry) 2100 2800 53.5 S.L. Take-off (two minutes) (dry) 2100 2800 52.5 3400' (critical altitude) Take-off (two minutes) (wet) 2400 2800 56.5 S.L. Take-off (two minutes) (wet) 2400 2800 56.0 1000' (critical altitude) Maximum continuous 1900 2600 47.5 S.L. Maximum continuous 1900 2600 46.5 4900' Maximum continuous 1800 2600 45.0 S.L. Maximum continuous 1800 2600 44.0` 6500' High impeller gear ratio 9.45:1 Maximum continuous 1600 2600 46.5 10000' Maximum continuous 1600 2600 45.0 16200' P&W R-2800-83AM3 Low impeller gear ratio 7.29:1 Take-off (two minutes) (dry) 2100 2800 54.0 S.L. Take-off (two minutes) (dry) 2100 2800 52.5 3400' Take-off (two minutes) (wet) 2400 2800 56.5 S.L. Take-off (two minutes) (wet) 2400 2800 56.0 1000' Maximum continuous 1800 2600 45.0 S.L. Maximum continuous 1800 2600 44.0 6500' Maximum continuous 1700 2500 44.0 S.L. Maximum continuous 1700 2500 42.0 6500' High impeller gear ratio 9.45:1 Maximum continuous 1600 2600 46.5 10000' Maximum continuous 1600 2600 45.0 16200' Maximum continuous 1500 2500 43.0 10000' Maximum continuous 1500 2500 42.00 16000' Airspeed limits (T.I.A.S.) Max. zero fuel, Oil and A.D.I. Fluid Gross Weight 80000# 83200* Vno (Normal Operating 300 mph (261 knots) 289 mph (251 knots) S.L. to 15000' (1) S.L. to 17000' (1) Mach No. = .52 Mach No. = .52 Vne (Never Exceed) 360 mph (313 knots) 346 mph (301 knots) S.L. to 10,000' (1) S.L. to 12,000' (1) Mach No. = .585 Mach No. = .585 Va (Maneuvering) 204 mph (177 knots) 213 mph (185 knots) Vfe (Flaps Down 0° to 30°) 200 mph (174 knots) 200 mph (174 knots) Vfe (Flaps Down 30° to 50°) 175 mph (152 knots) 175 mph (152 knots) I - Model DC-6B (cont'd) Vlo (Landing Gear Operation) 200 mph (174 knots) 200 mph (174 knots) Vle (landing Gear Extension) 200 mph (174 knots) 200 mph (174 knots) (1) Above altitudes shown, reduce speed 6 mph (5 knots) per 1000 feet) C. G. range Applies to 80,000 lbs. zero fuel, oil, and ADI fluid gross weight aircraft. Landing gear retraction moment - 210,000 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 & including 80,000 lbs. - - - - - - - - - - - - 9.0 409.9 33.0 449.2 85,000 lbs. 11.0 413,2 33.0 449.2 - - - - - - - - - - - - 100,000 lbs. 13.0 416.4 33.0 449.2 11.7 414.4 33.0 449.2 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.) Up to & including 84,900 lbs. - - - - - - - - - - - - 9.0 409.9 33.0 449.2 87,500 lbs. 11.0 413.2 33.0 449.2 - - - - - - - - - - - - 103,800 lbs. 14.2 418.4 33.0 449.2 - - - - - - - - - - - - 107,000 lbs. 16.0 421.4 33.0 449.2 13.6 417.4 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 : 85,000 lbs., 88,200 lbs. (See NOTE 6 for details). Zero fuel, oil, and A.D.I. fluid gross weight : 80,000 or 83,200 lbs. (See NOTE 6 and Airspeed lim its for details). (All weight in the airplane above these values must be in fuel, oil, and A.D.I. fluid in the wing.) 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 Installation Zero, fuel, oil and ADI Fluid gross weight Propeller Installation Hamilton Standard 43E60/6895A CB-3, CB-16, R-2800-52W or -83AM5 80,000 lbs. 100,000 lbs. (1) 92,200 lbs. (2) 83,200 lbs. 103,800 lbs. (1) (3) 100,000 lbs. (1) 92,200 lbs. (2) CA-15 83,200 lbs. 102,800 lbs. (1) (2) CB-4, CB-17, R-2800-52W 107,000 lbs. (1)&(3) or (3)&(4) or -83AM7 83,200 lbs. 103,000 lbs. (1) 95,500 lbs. (2) (1) With anti-detonant injection (see engine specificati on for A.D.I. Fluid composition) and 20° take-off flap setting. (2) With dry power and 20° take-off flap setting. (3) With automatic feathering propellers. (4) With anti-detonant injection and 10° take-off flap 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 Flight Standards Division for long range flight s and/or other special conditions. Maximum passengers Variable - see NOTE 1( g) for approved interior arrangements.) I - Model DC-6B (cont'd) Maximum baggage Information relative to pr ocedures to be followed in determining maximum cargo compartment capacities based upon fuselage strength and maximum floor loading for interior arrangements with various fore and aft seat spacings and with four (4) or five (5) abreast seating may be found in Douglas Service Bulletin DC-6 #787, dated October 15, 1958. Also see NOTE 1(g). Fuel capacity See NOTE 1(b), (c), and (d) for data on "System" fuel and "Unusable" fuel; NOTE 1(d) for required distribution of fu el load; NOTE 1(e) for "Undumpable" fuel.) Eight Wing Tank Airplane - 3992 Gallon System: Total Usable 2 outer wing tanks (#1 and #4 ma in) 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 cells (#2 and #3 alt.) 362 gal. ea. 362 gal. ea. (+438.0) Eight Wing Tank Airplane - 4322 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 cells (#2 and #3 alt.) 527 gal. ea. 524 gal. ea. (+449.0) Eight Wing Tank Airplane - 4512 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) Eight Wing Tank Airplane - 4734 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) 719 gal. ea. 700 gal. ea. (+451.0) or 2 inboard inner wing tanks (#2 a nd #3 main) 719 gal. ea. 713 gal. ea. (+451.0) (Serial No. 43819 and up) 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 - 4934 Gallon System: 2 outer wing tanks (#1 and #4 ma in) 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. (+470.0) 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. 700 gal. ea. (+451.0) or 2 inboard inner wing tanks (#2 a nd #3 main) 719 gal. ea. 713 gal. ea. (+451.0) (Serial No. 43819 and up) 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. 700 gal. ea. (+451.0) or 2 inboard inner wing tanks (#2 a nd #3 main) 719 gal. ea. 713 gal. ea. (+451.0) (Serial No. 43819 and up) 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.) 762 gal. ea. 762 gal. ea. (+468.0) I - Model DC-6B (cont'd) Ten Wing Tank Airplane - 4248 Gallon or 4262 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. (+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.) 210 gal. ea. 210 gal. ea. (+471.0) 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. (+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 gal. ea. (+500.0) Ten Wing Tank Airplane - 4918 Gallon or 4932 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) 519 gal. ea. 516 gal. ea. (+449.0) or 526 gal. ea. 523 gal. ea. (+449.0) 2 inner wing fuel cells (#2 and #3 alt.) 527 gal. ea. 527 gal. ea. (+449.0) 2 auxiliary fuel cells (L.H. and R.H.) 210 gal. ea. 210 gal. ea. (+471.0) Ten Wing Tank Airplane - 5392 Gallon or 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) 519 gal. ea. 516 gal. ea. (+449.0) or 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 gal. ea. (+500.0) Oil capacity See NOTE 1(b) and (f) regarding "Sys tem" oil and wing fillet oil tank installation.) 35 gal. in each nacelle (Douglas Dwg. #5342754) (+349.0) & (+379.0) 26 gal. in wing fillet (Requi red on all aircraft having a (+565.0) fuel system 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 43257 and up (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), 101(a), (b), (c), (d ), (e), (f), (g), (h) or (j); 103(a) and (c) or 103(b), (c) and (d), or 103 (c), (d) and (e), or 103(c), (d) and (f), or 103(c), (d) and (g), or 103(c), (d) and (h), or 103(c), (d) and (j), or 103(c) and (k), or 103(c) and (l), or 103(c), (d) and (m) or 103(c), (d) and (n) or 103(c), (d) and (o); 105(a) or (b); 108(a), (b), (c) or (d); 201(a), (b), (c), (d), (e), (f), (g), (h), (i), (j), (k) or (l); 202(a) or (b) and 203 or 202(c); 204(a) or (b) or (c); 205(a) and 206, or 205(b); 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), (l) or (m); 301(a), (b), (c) or (d); 302(a), (b), (c) or (d); 401; 402(a), (b), (c), (d), (e), (f) or (g); 404(a) or (b); 405(a); 608(a), (b). II - Model Navy R6D-1Z (DC-6B) Approved April 25, 1952 (The Navy Model R6D-1Z is basically the same as DC-6B airplane except having a special staff executive interior arrangement. See NOTE 7 for differences between Navy Model R6D-1Z and DC-6B.) Engines 4 P&W Double Wasps R-2800-52W or CB-17 (.45:1 propeller reduction gearing) (Item 101(b) or (c). Fuel Aviation gasoline: Grade 108/135 M P HP RPM IN.HG. ALT. P&W Double Wasp R-2800-52W or CB-17 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 50.0 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 Oper ating) 289 mph (251 knots) True Ind. S.L. to 17000' (1) (Mach No. = .52) Vne (Never Exceed) 346 mph (301 knots) S.L. to 12,000' (1) Mach No. = .585 Va (Maneuvering) 211 mph (183 knots) True Ind. Vfe (Flaps Down 0° to 30°) 200 mph (174 kts) True Ind. Vfe (Flaps Down 30° to 50°) 175 mph (152 knots) True Ind. Vlo (Landing Gear Operation) 200 mph (174 knots) True Ind. Vle (landing Gear Extension) 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 & including 83,200 lbs. - - - - - - - - - - - - 9.0 409.9 33.0 449.2 Up to & including 85,600 lbs. 11.0 413.2 33.0 449.2 - - - - - - - - - - - - Up to & including 102,200 lbs. 14.1 418.2 33.0 449.2 - - - - - - - - - - - - Up to & including 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 II - Model Navy R6D-1Z (DC-6B) (cont'd) Maximum weights Zero fuel, oil, and ADI fluid gross weight 83,200 lbs. (1) Landing 88,200 lbs. Takeoff 103,000 lbs. (2)(4)(5) Takeoff 102,200 lbs. (3)(4)(5) (1) All weight in the airplane above this value must consist of fuel, oil, and ADI fluid in the wing. (2) With anti-detonant injecti on (see Engine Specification for ADI fluid composition) and 20  takeoff for flap setting. (3) With dry power and 20  takeoff flap setting. (4) Dump valves are require d, in accordance with Note 1(e). (5) For 3-engine ferrying, see Note 4. 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 Flight Standards Division for long range flight s and/or other special conditions. Maximum passengers 33 Maximum cargo Compartment Station Capacity Arm Fwd upper convertible 143-160 500 lbs. ea. side (+149.5) Fwd upper convertible 160-217 *1500 lbs. ea. side (+183.5) Aft belly 600-843 5490 lbs. (+715.0) Fwd belly 90-280 4330 lbs. (+185.0) Coat room & baggage 434-480 1050 lbs. (+457.0) R . H . Stowage 434-480 690 lbs. (+457.0) L . H . *When transverse gate is installed. Fuel capacity (See Note 1(b), (c), and (d) for data on "System" fuel and "Unusable" fuel; and Note 1(d) for required distribution of fuel load; Note 1(e) for "Undumpable" fuel.) 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 a lt.) 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) Oil capacity See Note 1(b) and (f) regarding "S ystem" oil and wing fillet oil tank installation.) Hamilton Standard propeller installation: 35 gal. in each nacelle (+349.0) & (+379.0) (Douglas Dwg. #5342754) 26 gal. in wing fillet (+565.0) (Required on 5406 gallon ten wing tank airplanes) Control surface movements (Same as arrangement "B" under Specifications pertinent to all models) Serial nos. eligible 43517 Required equipment In addition to the pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: 1(a), 2(a) or (b), 4(a), 101(c); 103(c), (d) and (e); 105(a) or (b); 108(a), (b) or (c); 201(c), (d), (e), (f), (g), or (h); 202(a); 203; 204(a) or (b); 205(a); 206; 207(c), (d), (e), (f), (g) or (h); 208(a), (b), (c) or (d); 301(a), (b), (c) or (d); 302(a); 402(f); 404(a) or (b); 405(a); 608(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 to 22 (nose wheel well). Control surface movements (May be either arrangement "A" or arrangement "B") Arrangement "A" 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 + 20° + 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 tab ( full aft. (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 + 20° + 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 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 zeroed T.E. down 2° from faired tab** ( position. (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 4° up, accomplish rework per Douglas Service Bulletin DC-6 No. 497. Certification basis Type Certificate No. 6A4 (Trans port Category, CAR 4b, as amended 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. (See NOTE 5 for ICAO eligibility.)