TCDS 6A3

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