# TCDS 6A4: The Boeing Company - Type: Type certificate data sheet - Status: Current - Holder: The Boeing Company - Revision: 31 - Revised: September 27, 2010 - Product: Aircraft, Large Airplane - Certification basis: CAR 4b - Registered aircraft: 9, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/e0/e1/e0e179f4b4d692594892d682ce055752af7b6e024c44add30b90b33789aa831d - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/3AA076D9212D45D0862577DD006B8CF1.0001 - Page: https://openairdocs.org/tcds/6A4 ## Models (2) As the data sheet lists them. - Navy R6D-1Z - DC-6B ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text 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.) 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 equi pment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). The asterisk denotes that approval has been obtained by someone other than the aircraft manufacturer . An item marked with an asterisk 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", mi n. allowable for repairs 13' 1-9/16". No further tolerance permitted. Pitch settings at 42" sta.: Reverse -8°, Min. low +30° Feathered +96° (approx.) (b) Deleted June 28, 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, -34, -61, -69, -108, -114 or -118. 54 lbs. (+293.0) 3. Propeller feathering pumps (a) 4 Pesco 1E-777-KL-1 (D ouglas Dwg. #3342196) 64 lbs. (+367.0) Engine 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 Double Wasp CA-15 9440 lbs. (+294.0) & (+324.0) (e) 4 P&W R-2800-83AM3 9468 lbs. (+294.0) & (+324.0) (f) 4 P&W R-2800-83AM7 9600 lbs. (+294.0) & (+324.0) (g) 4 P&W R-2800-83AM5 9600 lbs. (+294.0) & (+324.0) (h) 4 P&W Double Wasps CB-4 9468 lbs. (+294.0) & (+324.0) (j) 4 P&W Double Wasps CB-3 9468 lbs. (+294.0) & (+324.0) 102. Fuel dump valve system (a) Ten wing tank system (Douglas Dwg. #5393033-5501 & -501) 149 lbs. (+428.5) (b) Deleted June 15, 1953 (c) Eight wing tank system (Dougl as Dwg. #5393033-503) 139 lbs. (+427.5) 103. System fuel and oil (a) System fuel, 4248 or 4262 gal. capacity ten wing fuel tanks (64.65 gals.) 382 lbs. (+454.5) (b) System fuel, 4722 or 4736 gal. capacity ten wing fuel tanks (68.5 gals.) 411 lbs. (+458.5) (c) System oil, 35 gal. oil tank in stallation (55.0 gal.) 413 lbs. (+326.0) Ham. Std. propeller installation (d) System oil, wing fillet 26 gal. tank (50% oil - 50% gasoline, 21 lbs. (+472.0) 3.1 gals., 6.77#/gal.) (e) System fuel, 5392 or 5406 gal. capacity ten wing fuel tanks (66.7 gal.) 400 lbs. (+460.0) (f) System fuel, 5404 gal. capacity eight wing fuel tanks (56.2 gals.) 337 lbs. (+466.0) (g) System fuel, 5512 gal. capacity eight wi ng fuel tanks (51.7 gals.) 310 lbs. (+467.0) (h) System fuel, 4734 gal. capacity eight wi ng fuel tanks (58.0 gals.) 348 lbs. (+464.0) (j) System fuel, 4512 gal. capacity eight wi ng fuel tanks (51.5 gals.) 309 lbs. (+450.5) (k) System fuel, 3992 gal. capacity eight wi ng fuel tanks (34.0 gal.) 204 lbs. (+449.0) (l) System fuel, 4322 gal. capacity eight wi ng fuel tanks (41.5 gals.) 249 lbs. (+459.0) (m) System fuel, 5042 gal. capacity eight wi ng fuel tanks (49.0 gals.) 294 lbs. (+454.0) (n) System fuel, 4934 gal. capacity eight wi ng fuel tanks (53.5 gals.) 321 lbs. (+453.0) (o) System fuel, 4918 or 4932 gal. capacity eight wing fuel tanks (62.6 gal.) 371 lbs. (+456.0) 104. (a) Water-alcohol Injection (Douglas 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. (+435.0) 105. (a) 4 Oil Coolers, AiResearch 86764 162 lbs. (+351.0) (b) 4 Oil Coolers, AiResearch 87295 162 lbs. (+351.0) 108. Starters (a) 4 Eclipse 36E00-4 113 lbs. (+350.5) (b) 4 Jack & Heintz JH-6ER12, JH-6 ESR12 or JH-6BESR-12 106 lbs. (+350.5) (c) 4 AN4116R6 112 lbs. (+350.5) (d) 4 Jack & Heintz JH-6CE 108 lbs. (+351.0) Landing Gear 201. 4 Main wheel-brake assemblies, 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) B.F. Goodrich Co., Model 1753M 737 lbs. (+474.0) Wheel Assembly No. H-3-743 Brake Assembly No. H-2-603 (d) B.F. Goodrich Co., Model 1753M 737 lbs. (+474.0) Wheel Assembly No. H-3-743 Brake Assembly No. H-2-602 (Skydrol) (e) Goodyear Model LF20HBM 747 lbs. (+474.0) Wheel Assembly No. 9540484 Brake Assembly No. 9560164 (f) Goodyear Model LF20HBM 747 lbs. (+474.0) Wheel Assembly No. 9540484 Brake Assembly No 9560166 (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) B.F. Goodrich Co., Model 1753M 731 lbs. (+474.0) Wheel Assembly No. H-3-743 Brake Assembly No. H-2-648 (j) B.F. Goodrich Model 1753M 731 lbs. (+474.0) Wheel Assembly No. H-3-743 Brake Assembly No. H-2-647 (Skydrol) (k) Goodyear Model LF20HBM 808 lbs. (+474.0) Wheel Assembly No. 9540906 Brake Assembly No. 9560164 (l) Goodyear Model LF20HBM 808 lbs. (+474.0) Wheel Assembly No. 9540906 Brake Assembly No 9560166 (Skydrol) 202. 4 Main wheel tires (NOTE: Satisfactory tire inflation pressures are given in the Airplane Maintenance Manual.) (a) 20-ply rating, 15:50x20, Type III, Nylon 645 lbs. (+474.0) (b) 16-ply rating, 15:50.x20, Ty pe III, Nylon 540 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 (a) Goodyear Wheel Assembly, No. 9540375, 44", Type I 72 lbs. (+39.0) (b) Goodyear Wheel Assembly, No. 9540758, 44", Type I 72 lbs. (+39.0) (c) Goodrich Wheel Assembly No. H-3- 866, 16:00-16, Type III 54 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) 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. 5342446-502) 1061 lbs. (+475.0) (b) 2 Cleveland 8065H (Douglas Dwg. 5342446-5502) (Skydrol) 1069 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 8065L (Douglas Dwg. 5342446-508) 1028 lbs. (+475.0) (h) 2 Cleveland 8065LA (Douglas Dwg. 5342446-5508) (Skydrol) 1037 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) 208. Nose gear shock strut assembly (a) Cleveland 8488B (Douglas Dwg. 5250509) 301 lbs. (+50.0) (b) Cleveland 8488BA (Douglas Dwg. 5240509-5000) (Skydrol) 303 lbs. (+50.0) (c) Cleveland 8488C (Douglas Dwg. 5240509-500) 296 lbs. (+50.0) (d) Cleveland 8488CA (Douglas Dwg. 5240509-5000) (Skydrol) 298 lbs. (+50.0) (e) Cleveland 8488D (Douglas Dwg. 5240509-502) 295 lbs. (+50.0) (f) Cleveland 8488DA (Douglas Dwg. 5240509-5502) (Skydrol) 290 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 8488F (Douglas Dwg. 5240509-506) 292 lbs. (+50.0) (j) Cleveland 8488H (Douglas Dwg. 5240509-510) 304 lbs. (+50.0) (k) Cleveland 8488HA (Douglas Dwg. 5240509-5510) (Skydrol) 306 lbs. (+50.0) (l) Cleveland 8488J (Douglas Dwg. 5240509-512) 304 lbs. (+50.0) (m) Cleveland 8488JA (Douglas Dwg. 5240509-5512) (Skydrol) 304 lbs. (+50.0) Electrical Equipment 301. Generators (a) 4 Eclipse 30E02-5-A or 30E02-5-C 250 lbs. (+355.0) (b) 4 General Electric 2CM75D1 244 lbs. (+355.0) (c) 4 General Electric 2CM75D1A 250 lbs. (+355.0) (d) 4 General Electric 2CM82D1 244 lbs. (+355.0) 302. Batteries (a) 2 Exide 6FH-13 160 lbs. (+81.0) (b) 2 Gould D-88 160 lbs. (+81.0) (c) 2 Globelite 160 lbs. (+81.0) (d) 2 Autolite 160 lbs. (+81.0) Interior Equipment 401. FAA Approved Airplane Flight Manual (not required for Models R6D-1Z 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. Douglas Latest Approved Date of Latest Airplane Serial Number Report No. Revision Number Approved Rev. (a) 43257-43259 13965 (UAL, (CAL) 20 3/8/67 43261, 43262 43276 43291, 43292 43298-43300 43539-43542 43561-43563 44080, 44081 44689 (b) 43263-43273 13966 (AAL), (CAL) 19 3/10/67 43543-43547 43564 43845-43847 44056-44060 44082-44083 (c) 43274-43275 14045 (Swissair) 9 2-25-55 (d) 43518-43535 14319 (PAA) 28 3-10-67 43838, 44061 44102-44121 44424-44428 (e) 43536, 43537 14340 (PAG) 11 12-31-58 44255, 44256 (f) 43550-43555 14361 (KLM) 18 4-18-67 (g) 43548, 43549 14381 (SAS) 5 12-1-52 (h) Deleted Oct. 11, 1955 (i) 43559, 43560 14438 (ARAMCO) 7 10-16-57 45059 (j) 43738-43743 14494 (NAL) 7 4-2-57 43820, 43821 (k) 43750 14522 (Swissair) 6 3-10-67 44087-44089 (l) 43744-43746 14531 (SAS) 5 3-10-67 43748, 43749 (m) 43822 14536 (WAL) 12 3-10-67 43824-43826 44429-44431 44434, 45060 45063-45067 45173-45179 45321-45324 45534-45538 Douglas Latest Approved Date of Latest Airplane Serial Number Report No. Revision Number Approved Rev. (n) 43842 14591 (CPA) --- --- (o) 43828-43832 14670 (SAB) 3 7-11-55 44175, 44176 44695 (p) 43833, 43834 14748 (TAI) 5 3-14-63 44696, 44697 (q) 43836, 43837 14796 (NWA) 19 3-10-67 44698, 44699 45197-45199 45201, 45202 45319, 45320 45501, 45502 (r) 43844, 44062 14827 (CPA) 9 3-10-67 44891, 44892 45078, 45079 45326-45329 45497 (s) 44251-44254 14887 (ALI) 5 4-20-67 44888, 44913 (t) 45417, 45419 18337 (LAI) 4 3-31-58 (u) 44432, 44433 14848 (JAL) 7 2-17-59 (v) 44687, 44688 18615 (TAA) 6 11-16-62 45107-45109 45472, 45473 (w) 44690-44692 18700 (LAN) 4 7-15-64 45513-45516 (x) 44693, 44694 18735 (ANA) 3 10-16-57 45076, 45077 (y) 43557, 43558 19239 (AAZ-UAT) 4 9-20-63 44871 45478, 45479 (z) 44893-44902 19501 (UAL) 6 3-8-67 45131-45137 45491-45494 (aa) 45216-45225 22681 (NEA) 2 3-8-67 (ab) 45496, 45523 23137 (CPC, ETA) --- --- 45524, 45533 (ac) 45505, 45506 23208 (MCA, OAL, CAT, JAT) 1 3-10-67 45539, 45540 45543, 45544 45550, 45563 45564 402. Emergency ladders (NOTE: Suitable evacuation slides may be installed in lieu of ladders) (a) (Douglas Dwg. #3352240) 20 lbs. (+686.0) (b) (Douglas Dwg. #3352240) 20 lbs. (+600.0) (c) (Douglas Dwg. #3352240) 20 lbs. (+172.0) (d) (Douglas Dwg. #3352240) 20 lbs. (+715.0) (e) (Douglas Dwg. #3352240) 20 lbs. (+720.0) (f) (Douglas Dwg. #3481141) 18 lbs. (+142.0) (g) (Douglas Dwg. #3352240) 20 lbs. (+947.0) 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 servos 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. @ 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 DACo. #2403860 or Sperry 150 lbs. (+287.0) 678919-261 plus 664575; 1 servo 658522-11, 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.: 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 (c) Sperry A-12 (3 servos DACo. #2405685 or Sperry 157 lbs. (+277.0) 678919-161 plus 664575; 1 servo 658522-11, 658648-11 plus 658774 or 658648-11 plus 658774) (1) Servo stall torques 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 altitudes 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 (d) Sperry A-12 (1 servo PAA No. 44.051. 001-100 or 102; 2 servos 157 lbs. (+277.0) PAA No. 44.051.001-101 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 hi gher 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. 12 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 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. @ 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 (3 servos model 118P, 1 ser vo model 2204A) 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) The Airplane Flight Manual must be revised to incorporating the limitations specified in (2) above. (g) Sperry A-12 (3 servos 679803-161 plus 664575; 140 lbs. (+282.0) 1 servo 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 satisfactory 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 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 (i) Pioneer PB-10 (3 servos 15611-1B, 1 servo 15620-2A) 148 lbs. (+326.0) (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. @ 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). (j) Sperry A-12 (3 servos 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. (k) Pioneer PB-10 (3 servos 15611-1B) 137 lbs. (+339.0) (1) Servo stall torques measured at the servo sectors are as follows; and are satisfactory for Flight Control: Elevator: 88 to 158 in.lbs. (11-20 lbs. at pilot's control) Aileron: 340 to 494 in.lbs. (14-20 lbs. at pilot's control) (2) Maximum speed for operation w ith automatic pilot is 330 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 (These clearances do not override any higher minimum operational altitudes). (l) Pioneer PB-10 (3 servos 15613-1-B, 1 servo 15620-2A) 148 lbs. (+326.0) (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. at pilot's control) Aileron: 340 to 494 in.lbs. (14-20 lbs. at pilot's control) Rudder: 324 to 432 in.lbs. (57-76 lbs. at pilot's control) (2) Maximum speed for operation with autopilot is 330 mph TIAS. Minimum terrain clearance for autopilot cruise configuration 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). 404. Windshield wipers (a) Kearfott or Alco (Douglas 5332419) 10 lbs. (+14.0) (b) Kearfott or Alco (Douglas Dwg. 5332419-5000) (Skydrol) 10 lbs. (+14.0) 405. Instruments - in accordance with the following drawings on file with the FAA Western Regional Office: (a) Douglas Dwg. 7399795 Deicing Equipment 501. (a) 2 Wing heaters, Surface Combination Corp. 138 lbs. (+417.0) B88A92 (Douglas Dwg. #5359829-10), E88A92 (Douglas Dwg. 5406945-5), H88A92 (Douglas Dwtg. 5406845-7) , 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 12 lbs. (+408.5) (Douglas Dwg. #7333181) (d) Empennage heater, Surface Combustion Corp. 69 lbs. (+1003.0) B88A92 (Douglas Dwg. #5359829-10), E88A92 (Douglas Dwg. 5406945-5), H88A92 (Douglas Dwg. #5406945-7), J88A92 (Douglas Dwg. #5406945-9), L88A92 (Douglas Dwg. #5406945-11), M88A92 (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 & La uer CM-050-5CC 9 lbs. (+1016.5) (Doug. Dwg. 7333180) (g) 2 wing accessory case #26098 32 lbs. (+397.0) (h) Empennage accessory case #26098 16 lbs. (+975.0) 502. (a) Carburetor and windshield anti-ic ing system, complete, 65 lbs. (+413.0) less alcohol (b) Anti-icing alcohol (16 gals.) 106 lbs. (+570.0) (c) Carburetor anti-icing system co mplete, less alcohol 59 lbs. (+413.0) 503. (a) Propeller electrical anti-icing equi pment, less equipment 123 lbs. (+318.0) on Ham. Std. Propellers (Douglas Dwgs. #5344301, #5338222, #5338223, #5362737, #2372408) 504. (a) Propeller electrical anti-icing equi pment on Ham. Std. 24 lbs. (+272.0) 6895-8 blades Miscellaneous 605. Hydraulic fluid in system and reservoir (14.5 gals.) (a) Skydrol 130 lbs. (+340.5) (b) Mineral oil 105 lbs. (+340.5) NOTE 1. (a) Current weight and balance report including list of e quipment included in certificated weight empty, and loading instructions, must be in each aircraft at the time of or iginal 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 add ition 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 (See Item 608) 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 obt ained by taking the difference between the "total" and "usable" tank capacities shown under "Fuel Capacity." The "unusable fuel" must either be included in the airplane empty weight or be suitably 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 of maximum landing weight. Refe r to FAA Approved Airplane Flight Manual for limitations and cautionary procedures to be observed during the dumping of fuel. When dump system (Item 102) is installed, the amount of usable fuel remaining in the fuel tanks after dumping is as follows: (1) Ten Wing Tank Airplane - 4248 Gal. and 4262 Gal. Systems Outer 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.) 0 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 36 gal. ea. Auxiliary fuel cells (L.H. and R.H. aux.) 21 gal. ea. (2) Ten Wing Tank Airplane - 4722 Gal. and 4736 Gal. Systems Outer 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.) 0 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) Ten Wing Tank Airplane - 5392 Gal. or 5406 Gal. System Outer 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.) 0 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 36 gal. ea. Auxiliary fuel cells (l.H. & R.H. aux.) 168 gal. ea. (4) Eight Wing Tank Airplane - 5404 Gal. and 5512 Gal. Systems Outer 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.) 0 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 54 gal. ea. (5) Eight Wing Tank Airplane - 4734 Gal. System Outer wing (#1 and #4 main) 112 gal. ea. Inboard inner wing (#2 and #3 main) 108 gal. ea. Outboard inner wing (#1 and #4 alt.) 0 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 54 gal. ea. (6) Eight Wing Tank Airplane - 4322 Gal., 4512 Gal., 4934 Gal., and 5042 Gal. S y s t e m s Outer 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.) 0 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 39 gal. ea. (7) Eight Wing Tank Airplane - 3992 Gal. System Outer wing (#1 and #4 main) 116 gal. ea. Inboard wing (#2 and #3 main) 108 gal. ea. Outboard inner wing (#1 and #4 alt.) 0 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 19 gal. ea. (8) Ten Wing Tank Airplane - 4918 Gal. and 4932 Gal. Systems Outer 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.) 0 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 36 gal. ea. Auxiliary fuel cells (L.H. & R.H. Aux.) 21 gal. ea. The total undumpable fuel, oil and ADI fluid must be incl uded 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 must be re duced by an amount sufficient to insure that the maximum landing weight will not be exceeded after 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(d)) 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-13912, "Loading Chart and Actual Weight and Balance." That report show s the location of all passenger and crew member seats; location and capacity of all cargo and baggage compartments, buffets, storage spaces, and coat-rooms; and location and capacity of lounges and lavatories for each of the different sleeper and day-plane arrangements covered by the above mentional report. Lounges, la vatories, and baggage or cargo compartments 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 and passenger 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 P&W Double Wasp CB-16 engines, Item 101(a) or P&W Wasp CB-3 engines, Item 101(i), th e propeller 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-6B 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. This airplane has been found to comply with the standards for Category A of Annex 8 to the Convention on International Civil Aviation, entitled "Airworthiness of Aircraft" as amended to March 1951, with the following exceptions: (a) Chapter 7 Sub-Part 7.2.5.3 Pa ragraph 4, unless oil filler screens per Douglas Dwg. 5344416, change "BD" are incorporated. (b) Chapter 9 Sub-Part 9.4.2.2 (d), unless fuel capacity placard adjacent to fuel selector controls per Douglas Dwg. 4406020 are incorporated. (c) Chapter 9 Sub-Part 9.3 "Aeroplan e Flight Manual," unless Airplane Flight Manual amended to include Section VI ICAO Requirements. (d) Chapter 2 Sub-Part 2.4.4 "Stalling, Symmetrical Power," unless wing spoilers are installed. 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 in stalled, the flap setting used and whether water-alcohol injection is used to increase the take-off power. Therefore, the table of take-off weights under maximum weights should also be adhered to in determining the maxi mum permissible take-off weight of various aircraft. MAXIMUM STRUCTURAL LIMITS (1) MODEL DC-6B Airplane Serial Numbers Zero Fuel, Oil Landing Takeoff Weight 8 Tank 10 Tank and ADI Fluid Weight 8 Tank 10 Tank 43738-43741 43257-43259 43743 43261-43276 80,000 5 85,000 100,000 100,000 43820, 43821 43291, 43292 43825, 44255 43298-43300 44256, 44434 43536, 43537 43539-43547 43561-43564 43822, 43824 43845-43847 44057 44059, 44060 44080, 44083 43274-43276 43298-43300 80,000 5 85,000 106,000 2,3,4 43539-43542 43561-43563 43536, 43537 83,200 5,6 88,200 2,6 100,000 43825 43822, 43824 44434 83,200 5,7 88,200 2,7 100,000 100,000 43738-43743 43820, 43821 83,200 5,8 88,200 2,8 100,000 43527, 43529 43517, 43518 43531-43535 43520, 43521 83,200 5 88,200 2,7 107,000 2,3,4 107,000 2,3,4 43548-43555 43523, 43524 43557-43558 43526 43560 43536, 43537 43738-43741 43822, 43824 43743-43746 43845-43847 43820, 43821 44057, 44059 43825 44060 MODEL DC-6B (cont'd) Airplane Serial Numbers Zero Fuel, Oil Landing Takeoff Weight 8 Tank 10 Tank and ADI Fluid Weight 8 Tank 10 Tank 43828-43834 44080-44083 43836-43838 43842, 43844 44062 44087-44089 44103-44106 44109-44113 44115-44121 44105-44170 44175, 44176 44251-44256 44417, 44419 44424-44425 44427 44432-44434 44690-44699 44871 44892-44902 45059, 45060 45063 45065-45067 45076, 45077 45079, 45109 45131-45137 45173-45176 45178 45197-45199 45201, 45202 45216, 45225 45319-45324 45327-45329 45478 45491-45494 45496, 45497 45501, 45502 45505, 45506 45514, 45516 45523, 45524 45533-45540 45543, 45544 45550 45563, 45564 MODEL DC-6B CARGO (9), (10) Airplane Serial Numbers Zero Fuel, Oil Landing Takeoff Weight 8 Tank 10 Tank and ADI Fluid Weight 8 Tank 10 Tank 43528, 43530 43519, 43522 43826, 44061 43525, 44056 44102, 44107 44689 44108, 44114 44428-44431 44687, 44688 83,200 5 88,200 2 107,000 2,3,4 107,000 2,3,4 44888 44891, 44913 45064, 45078 45107, 45108 45177, 45179 45326 45472, 45473 45515 (1) See Douglas Service Bulletin #455, "Interchanging of DC-6 Empennage Components and Restrictions Covering Such Interchanges." (2) Item 201(c), (d), (e), (f), (g), (h), (i), (j), (k) or (l) required. (3) Item 202(a) or 202(c), and 207(c), (d), (e ), (f), (g), (h), (i), (j) or (k) required. (4) 695 gal. capacity outer wing fuel tank required. Douglas Drawing #5717880 "Service Rework-Outer Wing Installation" describes the modi fications required to replace the 360 Gallon outer wing with the 695 Gallon outer wing. Drawing #5717880-500 also describes the modifi cations required to replace the 695 Gallon outer wing with the 360 Gallon outer wing. Appropriate revisions to the FAA Approved Airplane Flight Manual including satisfactory fuel loading schedules, changes to weight limits, fuel system changes, performance limitations, etc. should be submitted to the FAA for approval. (5) Placard speeds in accordance with Airspeed Limits Table. (6) Fuel loading and usage procedure included on page 2 of FAA Approved Airplane Flight Manual, Douglas Report SM-14340, Rev. 8, dated Sept ember 10, 1956, must be followed. Fuel loading and usage procedures outlined in NOTE 1(d) of this specification does not apply to these aircraft at these weights. (7) Fuel loading and usage procedures included on page 2 of FAA Approved Airplane Flight Manual, Douglas Report SM-14536, Rev. 5 dated Ma rch 11, 1957, must be followed. Fuel loading and usage procedures outlined in NOTE 1(d) of this specification do not apply to these aircraft at these weights. (8) Fuel loading and usage procedures included on page 2 of FAA Approved Airplane Flight Manual, Douglas Report SM-14494, Rev. 6 dated Ma rch 11, 1957, must be followed. Fuel loading and usage procedures outlined in NOTE 1(d) of this specification do not apply to these aircraft at these weights. (9) DC-6B aircraft modified per approved Douglas Type Design Data for cargo operation. (10) When operating as a passenger carrying airplane, th e fuselage loading, including the weight of passengers, baggage or cargo, seats, and all other interior equipment must not exceed the loading limit of the fuselage. NOTE 7. The Navy model R6D-1Z is similar to the model DC-6 B in that it is a passenger carrying airplane except having a different interior arrangeme nt and other minor changes. The Military excepti ons are as follows: (a) A FAA Approved Airplane Flight Ma nual must be provided prior to certification as a civil aircraft (not required for military operation). (b) A FAA Approved Loading Chart and Actual Weight a nd Balance Report must be provided prior to certification as a Civil aircraft (not required for military operation). (c) Radio equipment installation according to Douglas Drawings #5398379, 5405401, 5403923, 2406948 and 2406958. The above radio equipment is not FAA approve d and must be removed from the airplane and replaced with FAA approved equipment prior to certification as a civil aircraft. (d) The crew oxygen system installed according to Douglas Drawings #539730 and 5403390 does not meet the minimum oxygen supply re quirements for crew protective oxygen. A satisfactory oxygen system must be provided prior to certification as a civil aircraft. (e) Aft passenger compartment in accordance with Dougl as Drawing #5350451, unless restricted to 5 persons or provisions are made to keep door (S tation 720) open during take-off and landing. (f) All military aircraft returned to civil operations mu st comply with all applicable Airworthiness Directives. 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 Civil Aeronautics Board Special Re gulation 411B, aircraft operated by "Air Carriers" for cargo operation only, are permitted to increase the zero fuel and landing weights by 5% of the maximum zero fuel weight. For DC-6B aircraft covered by this specification, the maximum zero fuel, oil and ADI fluid weight may be increased to 87,360 lbs. and the maximum landing weight may be incr eased to 92,360 lbs. In addition to the operator's normal inspection program, aircraft operated in accordance with SR-411B 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 service after be ing 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 recomme ndations 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/6A4/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Douglas DC-6B](https://openairdocs.org/model/douglas-dc-6b): 9 aircraft (registry code 3021712) ## STCs approved under this data sheet (95, 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 SA1170NW](https://openairdocs.org/stc/SA1170NW): Modify type design by installing bulk liquid cargo tank assembly. Everts Air Cargo - [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 SA2721WE](https://openairdocs.org/stc/SA2721WE): Install external retardant tank.. 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 SA4-1466](https://openairdocs.org/stc/SA4-1466): Conversion of DC-6B interior from coach to first class arrangement per United Air Lines Drawing 15F-1800 change "C".. United Airlines Inc - [STC SA528WE](https://openairdocs.org/stc/SA528WE): Interior modifications for two 85 occupant configurations and rework of seats to provide removable arm rests as described on United Air Lines Approved Drawing List Nos. COA 6-3023 dated October 14, 1963, COA 6-3036 dated October 28, 1963, and COA 6-3053, Revision B, dated August 21, 1964.. 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 ST03076AT](https://openairdocs.org/stc/ST03076AT): Descriptive data pertaining to this installation are considered inadequate for duplication in other products. This approval is limited to only the installation made in Boeing 737-700, Serial No. 30754. Installation of executive interior. BE Aerospace - [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 SA1368GL](https://openairdocs.org/stc/SA1368GL): 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 SA661SW](https://openairdocs.org/stc/SA661SW): Interior arrangement.. Sierra Industries, Inc - [STC SA2-952](https://openairdocs.org/stc/SA2-952): Installation of fiberglass covering.. Razorback Fabrics 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 ST869SO](https://openairdocs.org/stc/ST869SO): Installation of a swing tail.. Aeronautical Engineers, Inc - [STC ST595SO](https://openairdocs.org/stc/ST595SO): Installation of exhaust system bracket.. Atlas Aircraft Corporation - [STC SA1510CE](https://openairdocs.org/stc/SA1510CE): 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 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 ST974SO](https://openairdocs.org/stc/ST974SO): Installation of extra crew seating and air distribution system.. Bellomy-Lawson Aviation Inc - [STC SA229NW](https://openairdocs.org/stc/SA229NW): Installation of 82 passenger configuration. Pacific Alaska Airlines Inc - [STC ST536SO](https://openairdocs.org/stc/ST536SO): Installation of aft cargo door.. Aeronautical Engineers, Inc - [STC ST597SO](https://openairdocs.org/stc/ST597SO): Installation of aft cargo door.. Aeronautique Engr Inc - [STC ST535SO](https://openairdocs.org/stc/ST535SO): Installation of cargo floor.. Aeronautical Engineers, Inc - [STC ST843SO](https://openairdocs.org/stc/ST843SO): Installation of aft cargo door.. Aeronautical Engineers, Inc - [STC SA181NW](https://openairdocs.org/stc/SA181NW): Installation of bulk liquid cargo tank system. Pacific Alaska Airlines Inc - [STC SA100NW](https://openairdocs.org/stc/SA100NW): Installation of cargo door, a 6 "G" barrier bulkhead, and a class "E" cargo compartment.. Rosembalm Aviation - [STC ST514SO](https://openairdocs.org/stc/ST514SO): Installation of forward cargo door.. Bellomy-Lawson Aviation Inc - [STC SA157NW](https://openairdocs.org/stc/SA157NW): Installation of bulk liquid cargo tank system. Pacific Alaska Airlines Inc - [STC SA2861WE](https://openairdocs.org/stc/SA2861WE): Installation of rear cargo door system GA61104.. Gary Aircraft Corp - [STC ST528SO](https://openairdocs.org/stc/ST528SO): Installation of cargo restraining bulkhead.. Bellomy-Lawson Aviation Inc - [STC ST555SO](https://openairdocs.org/stc/ST555SO): Installation of rear cargo door.. Bellomy-Lawson Aviation Inc All 95: https://openairdocs.org/tcds/6A4/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.