# TCDS 4A10: The Boeing Company - Type: Type certificate data sheet - Status: Current - Holder: The Boeing Company - Revision: 27 - Revised: September 27, 2010 - Product: Aircraft, Large Airplane - Certification basis: CAR 4b - Registered aircraft: 5, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/42/54/42545eb6005064b12de5ed838ebdc052126fe798003a04538b1e697581871dba - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/86A5B57F8C2B41A5862577DD006ADDCF.0001 - Page: https://openairdocs.org/tcds/4A10 ## Models (3) As the data sheet lists them. - DC-7 - DC-7C - DC-7B ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 27 - - - - - - - - - - - - - - - - - - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 4A10 Revision 27 BOEING DC-7 DC-7B DC-7C September 27, 2010 AIRCRAFT SPECIFICATION NO. 4A10 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 in 1997. Transferred Type Certificate to The Boeing Company on September 27, 2010. Douglas Aircraft Company, Inc., Santa Monica, California merged with McDonnell Aircraft Corporation August 25, 1967 I - Model DC-7, Approved November 12, 1953 Engines Item 101(a) or (b). Fuel Aviation gasoline: Grade 115/145 Engine limits (Straight line manifold pr essure variation with altitudes shown.) (See NOTE 2 for additional limitations and placards.) M P H P RPM IN.HG. ALT. Wright 972TC18DA2 or 972TC18DA4 Low impeller gear ratio 6.46:1 Take-off (two minutes) (dry) 3250 2900 56.5 S.L. Take-off (two minutes) (dry) 3250 2900 53.0 5000' (critical altitude) Maximum continuous 2600 2600 47.5 S.L. Maximum continuous 2650 2600 45.0 6500' High impeller gear ratio 8.67:1 Take-off (two minutes) (dry) 2535 2600 49.5 12800' Take-off (two minutes) (dry) 2550 2600 49.0 15200' (critical altitude) Maximum continuous 2405 2600 48.5 9550' Maximum continuous 2450 2600 47.0 16400' Wright 972TC18DA4 engines when operate d at 972TC18DA2 powers are considered equal to, or better than, 972TC18DA2 engines. Airspeed limits Maximum Zero Fuel and (T.I.A.S.) Oil Gross Weight 88,350#, 90,250# or 91,300# Vno (Normal Operating) 310 mph (269 knots) S.L. to 13000' (1) Mach No. = .52 Vne (Never Exceed) 360 mph (313 knots) S.L. to 11000' (1) Mach No. = .585 Va (Maneuvering) 228 mph (198 knots) 4A10 2 Vfe (Flaps Down 0° to 30°) 200 mph (174 knots) Vfe (Flaps Down 30° to 50°) 180 mph (156 knots) Vlo (Landing Gear Operation) 200 mph (174 knots) I - Model DC-7 (cont'd) Vle (Landing Gear Extension) (2) 200 mph (174 knots) Vll (Landing Light Extension) 250 mph (217 knots) (1) For speeds between altitudes shown and 25000 ft., see FAA approved Airplane Flight Manual. (2) Main gear, when operated as "Speed Brake," 300 mph (260 knots) S.L. to 21000' Alt. Vne 21000' to 25000' Alt. C. G. range Applies to 88,350 lbs., 90,250 lb. and 91,300 lb. zero fuel and oil gross weight aircraft. Landing gear retraction moment - 234, 800 in. lb. (Moves the C.G. forward) Gross Weight Landing Gear Extended (1) Landing Gear Retracted (2) Forward (3) Aft Forward (3) Aft % MAC Sta. % MAC Sta. % MAC Sta. % MAC Sta. Up to & including 89,300 lbs. 11.0 413.2 32. 5 448.4 8.0 408.3 32.5 448.4 122,200 lbs. 17.0 423.0 32.5 448.4 15.1 419.9 32.5 448.4 (1) Applies for Take-off and Landing (2) Applies for Enroute Operation (3) Straight line variation in fo rward C.G. between weights shown. Maximum weights Landing : 95,000 lb. or 97,000 lb. (See NOTE 4 for details). Zero fuel and oil gross weight : 88,350 lb., 90,250 lb. or 91,300 lb. (All weight in the airplane above this weight must be in fuel and oil) (See NOTES 1 and 4 for additional details). Take-off : See Table below and NOTE 4. Dump valves are required in accordance with NOTE 1(e). 3-engine ferrying : See NOTE 3. TAKE-OFF WEIGHT Engine Installation Zero, Fuel, and Oil Gross Weight Propeller Installation Ham. Std. 34E60 with 6921-8 blades Wright 88,350# 114,600# (1) 972TC18DA2 90,250# or 122,200# (1) (2) 972TC18DA4 91,300# (1) Dry power and 20° take-off flap setting. (2) 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 (including test, ferry and training flights) 2. (Pilot and copilot (+48.0)) Additions to the above minimums may be specified by the FAA for long range flights and/or other special conditions. Maximum passengers 70 - 99 (Paragraph 4b.362(c) of Amend. 4b-4 effective December 20, 1951) (See NOTE 1(f) regarding approve d interior arrangements.) Maximum baggage Information rela tive to procedures to be followed in determining maximum cargo compartment capacities based upon fuselage strength and maximum floor loading for interior arrangements with various fore and af t seat spacings and with four (4) or five (5) abreast seating may be found in Douglas Service Bulletin DC-7 #248, reissued October 15, 1958. Also see NOTE 1(f). Fuel capacity See NOTE 1(b) and (c) for data on "Sys tem" and "Usable" fuel; NOTE 1(d) for required distribution of fuel load; NOTE 1(e) for "Undumpable" fuel.) Eight Wing Tank Airplane - 5512 Gallon System: Total Usable 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) 3 4A10 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 a lt.) 762 gal. ea. 762 gal. ea. (+468.0) Eight Wing Tank Airplane - 4512 Gallon System: I - Model DC-7 (cont'd) 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) Oil capacity See NOTE 1(b) regarding "System" oil. 40 gal. in each nacelle (Douglas Dwg. #5461656 (+345.0) & (+379.0) 46 gal. in each nacelle (Douglas Dwg. #5461656) (+345.0) & (+379.0) (Required on all airplanes having fuel system of 4722 gallons and up). Serial Nos. eligible 44122 and up (See Item 401 and NOTE 4 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 (c); 3(a); 101(a); 102(a) and (c) or (d) and (b) or (c); 103(a); 104(a), (b) or (d); 105(a); 201(a), (b), (c), (d) or (e); 202(a); 203(a); 204(a); 205(a); 206(a); 301(a), (b), (c), (d) or (e); 303)a); 401(a), (b), (c) or (d); 403(a) or (b); 404(a); 406(a) or (b). II - Model DC-7B Approved May 25, 1955 (See NOTES 1(g), 4 and 7 for aircraft modified to cargo configuration). Engines Item 101(b),101(c) or 101(d) Fuel Aviation gasoline: Grade 100/130, 108/135 or 115/145 Engine limits (Straight line manifold pr essure variation with altitudes shown.) (See NOTE 2 for additional limitations and placards.) M P HP RPM IN.HG. ALT. Wright 972TC18DA4 or 988TC18EA4 or 988TC18EA4. (Item 1(b) required) Low impeller gear ratio 6.46:1 Take-off (two minutes) (dry) 3250 2900 56.5 S.L. Take-off (two minutes) (dry) 3250 2900 53.5 5500' (critical altitude) Maximum continuous 2700 2600 49.0 S.L. Maximum continuous 2700 2600 47.0 5800' High impeller gear ratio 8.67:1 Take-off (two minutes) (dry) 2535 2600 49.5 13300' Take-off (two minutes) (dry) 2550 2600 49.0 15200' (critical altitude) Maximum continuous 2405 2600 48.5 10050' Maximum continuous 2450 2600 47.0 16400' Wright 972TC18DA4, 988TC18EA1 or 988TC18EA4. (Grade 100/130 or 108/135 Fuel) (Note: See take-off weight table) Low impeller gear ratio 6.46:1 Take-off (1 1/2 minutes) (dry) 2880 2900 51.0 S.L. Take-off (1 1/2 minutes) (dry) 2950 2900 48.0 8500' (critical altitude) Maximum continuous 2380 2600 44.0 S.L. Maximum continuous 2450 2600 41.5 9400' High impeller gear ratio: Operation not permitted with Grade 100/130 or 108/135 fuel. Wright 988TC18EA1 and/or 988TC18EA4 engines when operated at 972TC18DA4 powers are considered equal to, or better than, 972TC18DA4 engines. Airspeed limits Maximum Zero Fuel and (T.I.A.S.) Oil Gross Weight 96,000# Vno (Normal Operating) 310 mph (269 knots) S.L. to 13000' (1) Mach No. = .52 Vne (Never Exceed) 360 mph (313 knots) 4A10 4 S.L. to 11000' (1) Mach No. = .585 Va (Maneuvering) 231 mph (201 knots) II - Model DC-7B (cont'd) Airspeed limits (cont'd) Vfe (Fla ps Down 0° to 20°) 220 mph (191 knots) Vfe (Flaps Down 20° to 30°) 200 mph (174 knots) Vfe (Flaps Down 30° to 50°) 187 mph (162 knots) Vlo (Landing Gear Operation) 200 mph (174 knots) Vle (Landing Gear Extension) (2) 200 mph (174 knots) Vll (Landing Light Extension) 250 mph (217 knots) (1) For speeds between altitudes shown and 25000 ft., see FAA approved Airplane Flight Manual. (2) Main gear, when operated as "Speed Brake," 300 mph (260 knots) S.L. to 21000' Alt. Vne 21000' to 25000' Alt. C. G. range Applies to 96,000 lbs. zer o fuel and oil gross weight aircraft. Landing gear retraction moment - 241, 000 in. lb. (Moves the C.G. forward) Gross Weight Landing Gear Extended (1) Landing Gear Retracted (2) Forward (3) Aft Forward (3) Aft % MAC Sta. % MAC Sta. % MAC Sta. % MAC Sta. Up to & including 91,630 lbs. 11.0 413.2 32. 5 448.4 8.0 408.3 32.5 448.4 126,000 lbs. 16.9 422.9 32.5 448.4 16.1 421.5 32.5 448.4 (1) Applies for Take-off and Landing (2) Applies for Enroute Operation (3) Straight line variation in fo rward C.G. between weights shown. Maximum weights Landing : 102,000 lbs. (See NOTE 4 for details including increased weights for cargo operation). Zero fuel and oil gross weight : 96,000 lbs. (All weight in the airplane above this weight must be in fuel and oil) (See NOTES 1 and 4 for additional details). Take-off : See Table below and NOTE 4. Dump valves are required in accordance with NOTE 1(e). 3-engine ferrying : See NOTE 3. TAKE-OFF WEIGHT Engine Installation Zero, Fuel, and Oil Gross Weight Propeller Installation Ham. Std. 34E60 with 6921-8 blades Wright 972TC18DA4 96,000# 116,900# (1)(4) or (1)(2)(4)(9) 988TC18EA1 or or 98,000# (10) 117,900* (1)(5) or (1)(2)(5)(9) 988TC18EA4 124,272# (1)(2)(7) 124,450# (1)(2)(6) 126,000# (1)(2) or (2)(8) (1) Dry power and 20° take-off flap setting. (2) With automatic feathering propellers. (3) Deleted January 7, 1960. (4) Without nacelle (saddle) fuel tanks. (5) With nacelle (saddle) fuel tanks. (6) Wt. limit when 4512 gal. fuel system and 46 gal. oil nacelle tanks installed. (7) Wt. limit when 4512 gal. fuel system and 40 gal. nacelle oil tanks installed. (8) Dry power and 10° take-off flap setting. (9) When Grade 100/130 or 108/135 fuel is used. (See engine limits). (10) DC-7B Cargo (See table in NOTE 4 for serial numbers eligible). 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 (including 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 flights and/or other special conditions. 5 4A10 II - Model DC-7B (cont'd) Maximum passengers 70 - 99 (Paragraph 4b.362(c) of Amend. 4b-4 effective December 20, 1951) (See NOTE 1(f) regarding approved interior arrangements.) Maximum baggage Information rela tive to procedures to be followed in determining maximum cargo compartment capacities based upon fuselage strength and maximum floor loading for interior arrangements with various fore and af t seat spacings and with four (4) or five (5) abreast seating may be found in Douglas Se rvice Bulletin DC-7 #248, reissued October 15, 1958. Also see NOTE 1(f). Fuel capacity See NOTE 1(b) and (c) for data on "Sys tem" and "Usable" fuel; NOTE 1(d) for required distribution of fuel load; NOTE 1(e) for "Undumpable" fuel.) Eight Wing Tank Airplane - 4512 Gallon System: Total Usable 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. 724 gal. ea. (+449.0) 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) 2 inner wing fuel cells (#2 and #3 alt.) 762 gal. ea. 762 gal. ea. (+468.0) Eight Wing Tank Airplane - 6378 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.) 793 gal. ea. 789 gal. ea. (+452.0) 2 inner wing fuel cells (#2 and #3 alt.) 982 gal. ea. 982 gal. ea. (+463.0) Eight Wing Tank Airplane - 6474 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.) 841 gal. ea. 837 gal. ea. (+455.0) 2 inner wing fuel cells (#2 and #3 alt.) 982 gal. ea. 982 gal. ea. (+463.0) Oil capacity See NOTE 1(b) regarding "System" oil) 46 gal. in each nacelle (Douglas Dwg. #5461656-501) (+345.0) & (+379.0) 26 gal. in wing fillet (Required on all (+565.0) airplanes incorporating 46 gal. nacelle oil tanks and a fuel system greater than 5512 gal.) 56 gal. in each nacelle (Douglas Dwg. #5533656) (+345.0) & (+379.0) (Required on aircraft incorpor ating the 6474 gal. fuel system) Serial Nos. eligible 44700 and up (See Item 401 and NOTE 4 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) and (b); 2(a) or (c); 3(a) or (b); 101(b), (c) or (d); 102(a), (c) and (f) or 102(g), and (i) or 102(c), (e) and (f), or 102(c) and (d) or 102(b) and (d); 103(a); 104(a), (b) or (d); 105(a); 201(a), (b), (c), (d) or (e); 202(a); 203(a); 204(a); 205(b), (c) or (e); 206(a), (b), (c) or (d); 301(a), (b), (c), (d) or (e); 303(a); 401(e), (f), (g), (h), (i), (p), (s), (t) or (x); 403(a) or (b); 404(a); 406(a) or (b). III - Model DC-7C, Approved May 15, 1956 (See NOTES 1(g), 4 and 7 for aircraft modified to cargo) Engines Item 101(c) or 101(d) Fuel Aviation gasoline: Grade 115/145, 100/130 or 108/135 4A10 6 III - Model DC-7C (cont'd) Engine limits (Straight line manifold pr essure variation with altitudes shown.) (See NOTE 2 for additional limitations and placards.) M P H P RPM IN.HG. ALT. Wright 988TC18EA1 or 988TC18EA4 (Grade 115/145 fuel) (See below for modified ratings) Low impeller gear ratio 6.46:1 Take-off (five minutes) (dry) 3400 2900 58.5 S.L. Take-off (five minutes) (dry) 3400 2900 56.0 4000' (critical altitude) Maximum continuous 2860 2650 51.0 S.L. Maximum continuous 2920 2650 49.0 4800' High impeller gear ratio 8.67:1 Take-off (five minutes) (dry) 2540 2600 49.5 13500' Take-off (five minutes) (dry) 2550 2600 49.0 15200' (critical altitude) Maximum continuous 2410 2600 48.5 10000' Maximum continuous 2450 2600 47.0 16400' NOTE: When the fuel injection pump timing is modified to 15° -15° the following listed reduced power ratings must be used: Low impeller gear ratio 6.46:1 Take-off (1 1/2 minutes) (dry) 3250 2900 56.5 S.L. Take-off (1 1/2 minutes) (dry) 3250 2900 53.5 5500' (critical altitude) Maximum continuous 2700 2600 49.0 S.L. Maximum continuous 2750 2600 47.0 5800' High impeller gear ratio 8.67:1 Maximum continuous 2405 2600 48.5 10050' Maximum continuous 2450 2600 47.0 16400' Engines so modified will be identified by ha ving the letter "B" stamped on the data plate immediately following the engine serial number and the appropriate rating restamped. Wright 988TC18EA1 or 988TC18EA4 (Grade 100/130 or 108/135 Fuel) (Note: See take-off weight table) Low impeller gear ratio 6.46:1 Take-off (1 1/2 minutes) (dry) 2880 2900 51.0 S.L. Take-off (1 1/2 minutes) (dry) 2950 2900 48.0 8500' Maximum continuous 2380 2600 44.0 S.L. Maximum continuous 2450 2600 41.5 9400' High impeller gear ratio: Operation not permitted with Grade 100/130 or 108/135 fuel. Airspeed limits Maximum Zero Fuel (C.A.S.) Oil Gross Weight 101,500# Vno (Normal Operating) 310 mph (269 knots) S.L. to 13000' (1) Mach No. = .52 Vne (Never Exceed) 360 mph (313 knots) S.L. to 11000' (1) Mach No. = .585 Va (Maneuvering) 220 mph (191 knots) Vfe (Flaps Down 0° to 20°) 220 mph (191 knots) Vfe (Flaps Down 20° to 30°) 200 mph (174 knots) Vfe (Flaps Down 30° to 50°) 187 mph (162 knots) Vlo (Landing Gear Operation) 200 mph (174 knots) Vle (Landing Gear Extension) (2) 200 mph (174 knots) Vll (Landing Light Extension) 250 mph (217 knots) 7 4A10 III - Model DC-7C (cont'd) Airspeed limits (1) or speeds between altitudes shown and 25000 ft., see FAA approved Airplane Flight (C.A.S.) Manual. (2) Main gear, when operated as "Speed Brake," 300 mph (261 knots) S.L. to 17,000' Alt. 292 mph (254 knots) 17,000' to 22,500' Alt. Vne 22,500' to 25,000' Alt. C. G. range Applies to 101,500 lbs. zer o fuel and oil gross weight aircraft. Landing gear retraction moment - 224, 000 in. lb. (Moves the C.G. forward) Gross Weight Landing Gear Extended (1) Landing Gear Retracted (2) Forward (3) Aft Forward (3) Aft % MAC Sta. % MAC Sta. % MAC Sta. % MAC Sta. Up to & including 103,150 lbs. 14.4 417.5 32.5 448.0 11.7 413.0 32.5 448.0 140,000 lbs. 19.3 425.7 32.5 448.0 18.3 424.1 32.5 448.0 143,000 lbs. 21.0 428.6 29.5 443.0 20.0 427.0 29.5 443.0 144,750 lbs. (4) 22.4 431.1 26.9 438.6 21.4 429.4 26.9 438.6 (1) Applies for Take-off and Landing (2) Applies for Enroute Operation (3) Straight line variation in fo rward C.G. between weights shown. (4) For cargo aircraft eligible for 144,750 lb. take off weight. (See Structural Limits Table, NOTE 4.) Maximum weights Landing : 109,000 lbs. or 111,000 lbs. (See NOTE 4 for details including increased weights for cargo operation). Zero fuel and oil gross weight : 101,500 lbs. (All weight in the airplane above this wei ght must be in fuel and oil in the wing) (See NOTES 1 and 4 for additional details). Take-off : See Table below and NOTE 4. Dump valves are required in accordance with NOTE 1(a). 3-engine ferrying : See NOTE 3. TAKE-OFF WEIGHT Engine Installation Zero, Fuel, and Oil Gross Weight Propeller Installation Ham. Std. 34E60 with 7019-2 blades Wright 129,000# (1)(2)(4) 988TC18EA1 or 101,500# or 131,350# (1) (5) 988TC18EA4 106,400# (6) 141,750 lbs. (1)(2) 143,000 lbs. (2)(3) 144,750 lbs. (2)(3)(6) (1) Dry power and 20° takeoff flap setting. (2) With automatic feathering propellers. (3) Dry power and 10° take-off flap setting (4) When Grade 100/130 or 108/135 fuel is used. Maximum landing wt. 109,000# (See Engine Limits) (5) Without automatic feathering propellers. (6) DC-7C cargo (See table in NOTE 4 for serial numbers eligible). Minimum crew For all revenue flights (passenger and/or cargo) 3 crewmembers. (Pilot and copilot (+8.0) and flight engineer (+29.0)) For all other flights (including test, ferry and training flights) 2 crewmembers. (Pilot and copilot (+8.0)) Additions to the above minimums may be specified by the FAA for long range flights and/or other special conditions. Maximum passengers 70 - 99 (Paragraph 4b.362(c) of Amend. 4b-4 effective December 20, 1951) (See NOTE 1(f) regarding approved interior arrangements.) 4A10 8 III - Model DC-7C (cont'd) Maximum baggage Information rela tive to procedures to be followed in determining maximum cargo compartment capacities based upon fuselage strength and maximum floor loading for interior arrangements with various fore and af t seat spacings and with four (4) or five (5) abreast seating may be found in Douglas Se rvice Bulletin DC-7 #328, dated October 15, 1958. Also see NOTE 1(f). Fuel capacity See NOTE 1(b) and (c) for data on "Sys tem" and "Usable" fuel; NOTE 1(d) for required distribution of fuel load; NOTE 1(e) for "Undumpable" fuel.) Eight Wing Tank Airplane - 7824 Gallon System: Total Usable 2 outer wing tanks (#1 and #4 main) 695 gal. ea. 695 gal. ea. (+460.0) 2 inboard inner wing tanks (#2 and #3 ma in) 719 gal. ea. 713 gal. ea. (+451.0) 2 outboard inner wing tanks (#1 and #4 a lt.) 841 gal. ea. 837 gal. ea. (+455.0) 2 inner wing fuel cells (#2 and #3 alt.) 1657 gal. ea. 1657 gal. ea. (+463.0) Oil capacity See NOTE 1(b) regarding "System" oil) 56 gal. in each nacelle (Douglas Dwg. #5533656) (+345.0) & (+379.0) 26 gal. in wing fillet (+565.0) Serial Nos. eligible 44872 and up (See Item 401 and NOTE 4 for complete list.) Required equipment In addition to the pertinent requi red basic equipment specified in CAR 4b, the following items of equipment must be installed: 1(b) or (c); 2(a), (b) or (c); 3(a) or (b); 101(c) or (d); 102(h), (i) and (j); 103(a); 104(a), (b) or (d); 105(b); 201(f) or (g); 202(b); 203(b); 204(b); 205(f), (g) (h) or (i); 206(e) or (h); 301(a), (b), (c), (d), (e) or (f); 303(b); 401(j), (k), (l), (m), (n), (o), (q), (r), (u), (v) or (w); 403(c) or (d); 404(a); 406(c). SPECIFICATIONS PERTINENT TO ALL MODELS Datum 63 in. aft of nose (Station 0) (Model DC-7 and DC-7B) 103 in. aft of nose (Station 0) (Model DC-7C) (With Douglas radome nose insta lled, add 12.8 inches to datum.) MAC 163.6 in. (L.E. of MAC +395.2) (Model DC-7 and DC-7B) 168.8 in. (L.E. of MAC +393.2) (Model DC-7C) Leveling means Bracket at Sta. 387.4 (below floo r) and sta. 4 and 22 (nose wheel well) (DC-7 and DC-7B) Bracket at Sta. 387.4 (below floor) and St a. -36 and -20.6 (nose wheel well) (DC-7C) Control surface movements Aileron Drooped 1° w/r to wing T.E., wheel neutral. 19° up, 19° down from neutral drooped position. Aileron spring Faired w/r to aileron T.E., controls neutral tab + 21 1/2° + 1/2° from neutral position. Aileron trim Faired w/r to aileron T.E. + 15° + 15° + 1/2°, L.H. tab Aileron only Rudder + 20° + 1/2° from neutral faired position. (DC-7 and DC-7B) + 17° + 1/2° from neutral faired position. (DC-7C) Rudder spring + 20° + 1/2° from neutral faired position. tab Rudder trim + 20° + 1/2° from neutral faired position. With rudder in neutral. 9 4A10 All Models (cont'd) Elevator T.E. faired with tail cone, control column neutral (13°30' fwd. of vertical) Down 15° + 1/2° from neutral, control column forward 24°30' from vertical. Up 25° + 1/2° from neutral, control column 8°5' aft from vertical. Elevator spring Up 2° +0°-1/2°, controls neutral - springs each tab will produce 5# preload at T.E.; 5.7# on DC-7B and DC-7C. Down 19° + 1/2° from faired position, control full aft. Up 9° + 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. On DC-7B and DC-7C and when shortened elevator trim tabs are installed on DC-7 aircraft per Douglas Dwg. No. 5500480, the following tab settings are applicable: Down 13° + 1/2° from neutral faired position. Up 4° + 1/2° from neutral faired position. Certification basis Type Certificate No. 4A10 (Trans port Category, CAR 4b, as amended July 20, 1950, and amendments 4b-1, 4b-3, Paragraph 4b.362(a) , (b) and (c) of 4b-4, and 4b.5 ) The forward and aft lower belly cargo compartm ents are Class "D" Compartments. Smoke detectors, per Amendment 4b-2 effective August 25, 1955, or extinguishing provisions are not required.) See NOTE 6 for ICAO eligibility. Compliance with ditching provisions of 4b.261 has been demonstrated. Maximum approved operational altitude 25,000 ft. This altitude may be increased to a maximum of 28,000 ft. when an FAA approved oxygen system, meeting the requirements of CAR 4b.651 effective July 20, 1950, has been installed. The oxygen system installed in the aircraft shoul d be reviewed for compliance with these requirements. Production basis Production Certificate No. 27. Export eligibility Eligible for export to all countries subject to the existing export procedures except as follows: (a) Canada - Landplane only eligible. (b) Great Britain - Complies with U.S. requirements, and with British ARB Special conditions including fatigue requirements as interpreted by ARB communications to the FAA dated 9/18/56 and 10/18/56. Maximum weights for export airplane are contained in FAA Approved Airplane Flight Ma nual (Item 401.m) but when airplane is operated in the U.S. the weights must not exceed those shown in this specification. EQUIPMENT: Propellers and Propeller Accessories 1. Propellers (including electrical anti-icing provisions installed on propeller assembly such as boots, slip rings, blad e and hub electrical equipment.) (a) 4 Ham. Std. propellers, hubs 34E60, blades 6921-8 3193 lbs. (+262.0) Diameter: Max. 13'6-1/8", min. allowable for repairs 13' 2-3/8". No further reduction permitted. Pitch settings at 42" sta.: Reverse -14°, Min. low +29.5° Feathered +94° (approx.) (See NOTE 2(b) for placard) (b) 4 Spinners, Ham. Std. 502875, 508529 or 526379, with Douglas 144 lbs. (+272.0) Cowling Interliners. Required with Item 101(b), (c) or (d) 4A10 10 Propellers and Propeller Accessories (cont'd) (c) 4 Ham. Std. hubs 34E60, bl ades 7019-2 (DC-7C) 3240 lbs. (+262.0) Diameter: Max. 13'11-7/8", min. allowable for repairs 13' 8-1/2". No further reduction permitted. Pitch settings at 42" sta.: Reverse -14°, Min. low +27.5° Feathered +94° (approx.) (See NOTE 2(c) for placard) 2. Propeller governors (a) 4 Ham. Std. 5U18-40, -41, -46, -66, -70, -72, -106, -107 or 54 lbs. (+293.0) -113 equipped with Deterjet M odel DJ-1025 governor by-pass valve. (b) 4 Ham. Std. 5U18-58 or -105 equipped with Deterjet Model 56 lbs. (+293.0) DJ-1025 governor by-pass valve (c) 4 Ham. Std. 5AA22-1, 5AA22-2, 5AA22-4, 5AA22-5. 3. Propeller feathering pumps (a) 4 Pesco 1E-777-UL-1 56 lbs. (+367.0) (b) 4 Adel 51300 100 lbs. (+367.0) Engine and Engine Accessories - Fuel and Oil Systems 101. (a) 4 Wright Double Row Turbo Cy clone 972TC18DA2 with 14200 lbs. (+307.0) 16:7 propeller reduction gearing (b) 4 Wright Double Row Turbo Cyclone 972TC18DA4 with 16:7 14200 lbs. (+307.0) propeller reduction gearing (c) 4 Wright Double Row Turbo Cycl one 988TC18EA1 with 14580 lbs. (+307.0) 16:7 propeller reduction gearing (d) 4 Wright Double Row Turbo Cyclone 988TC18EA4 with 16:7 14700 lbs. (+307.0) propeller reduction gearing 102. System fuel and oil (a) System fuel, 5512 gal. capacity eight wing fuel 374 lbs. (+460.0) tanks (62.4 gals.) (b) System oil, 40 gal. oil tank in stallation (86.8 gal.) 651 lbs. (+324.0) (c) System oil, 46 gal. oil tank installation (86.0) 645 lbs. (+324.0) (d) System fuel, 4512 gal. capacity eight wing fuel tanks 356 lbs. (+446.5) (59.4 gal.) (e) System fuel, 6378 gal. capacity eight wi ng fuel tanks (58.4 gals.) 350 lbs. (+458.0) (DC-7B) (f) System oil, wing fillet 26 gal. ta nk (50% oil - 50% gas) 21 lbs. (+472.0) (3.1 gal.) (DC-7B) (g) System fuel, 6474 gal. capacity eight wi ng fuel tanks (63.6 gals.) 382 lbs. (+462.0) (DC-7B) (h) System fuel, 7824 gal. capacity eight wi ng fuel tanks (70.4 gals.) 422 lbs. (+463.0) (DC-7C) (i) System oil, 56 gal. oil tank in stallation (86.6 gal.) 648 lbs. (+324.0) (DC-7B and DC-7C) (j) System oil, 26 gal. wing fillet tank (3.7 gal.) (DC-7C) 25 lbs. (+472.0) 50% oil, 50% gasoline - 67°F 65% oil, 35% gasoline - 37°F 80% oil, 20% gasoline - 27°F 103. (a) 4 oil coolers, AiResear ch 87410-24 or 151240-24 220 lbs. (+352.0) 104. Starters (a) 4 Eclipse 36E00-4 113 lbs. (+351.0) (b) 4 Jack & Heintz JH-6ESR12 105 lbs. (+351.0) (c) Deleted December 6, 1954 (d) 4 Jack & Heintz JH-6CE 108 lbs. (+351.0) 105. Fuel dump valve and controls system (a) Eight wing tank system (Dougl as Dwg. #5393033 and 5397701) 147 lbs. (+427.0) (b) Eight wing tank system (Douglas Dwg. #5393033-511 and 5397701-505) 158 lbs. (+424.0) (DC-7C) 11 4A10 Landing Gear 201. 4 Main wheel-brake a ssemblies, 17.00-20, Type III (a) Goodyear 1018 lbs. (+474.0) Wheel Assembly No. 9560208 Brake Assembly No. 9560229 or 9560245 (Maximum take-off weight 126,000 lbs., landing 102,000 lbs.) (b) Goodyear 1018 lbs. (+474.0) Wheel Assembly No. 9560208 Brake Assembly No. 9560231 (Skydrol) or No. 9560246 (Skydrol) (Maximum take-off weight 126,000 lbs., landing 102,000 lbs.) (c) Goodyear, 1064 lbs. (+474.0) Wheel Assembly No. 9540862 Brake Assembly No. 9560231 (Skydrol) or No. 9560246 (Skydrol) Maximum take-off weight 126,000 lbs., landing 102,000 lbs.) (d) Goodyear 1120 lbs. (+474.0) Wheel Assembly No. 9540753 Brake Assembly No. 9560883 (Inboard) Brake Assembly No. 9560886 (Outboard) (Maximum take-off weight 126,000 lbs., landing 102,000 lbs.) (e) Goodyear 1064 lbs. (+474.0) Wheel Assembly No. 9540662 Brake Assembly No. 9560245 (Maximum take-off weight 126,000 lbs., landing 102,000 lbs.) (f) Goodyear (DC-7C) 988 lbs. (+474.0) Wheel Assembly No. 9540934 Brake Assembly No. 9560286 (Skydrol) (g) Goodyear (DC-7C) 988 lbs. (+474.0) Wheel Assembly No. 9540934 Brake Assembly No. 9560285 202. 4 Main wheel tires (NOTE: Satisfactor y tire inflation pressures are given in the Airplane Maintenance Manual.) (a) 20-ply rating, 15:50x20, Type III, Ny lon with regular tubes 744 lbs. (+474.0) (b) 22-ply rating, 17:00x20, Type III, Nylon tubeless (DC-7C) 676 lbs. (+474.0) 203. Nose wheel 44", Type I (a) Goodyear Model 44NBM 72 lbs. (+39.0) Wheel Assembly No. 9540758 (b) Goodrich 16:00-16, Type III (DC-7C) 50 lbs. (-1.0) Wheel Assembly #H-3-866 (Douglas Dwg. #3535153) 204. Nose wheel tire (a) 14-ply rating, 44", Type I, Nyl on, with regular tube 135 lbs. (+39.0) (b) 14-ply rating, 15:00 x 16, Type III, Nylon tubeless (DC-7C) 99 lbs. (-1.0) 205. Main gear shock strut assembly (a) 2 Cleveland 9243A (Douglas Dwg. #5479610-1) 1094 lbs. (+476.0) (Maximum take-off weight 122,200 lbs., landing 97,000 lbs.) (b) 2 Cleveland 9243BA (Douglas Dwg. #5479610-5501) (Skydrol) 1105 lbs. (+476.0) (Maximum take-off weight 126,000 lbs., landing 102,000 lbs.) (c) 2 Cleveland 9483A (Douglas Dwg. #5500288) 1131 lbs. (+476.0) (Maximum take-off weight 126,000 lbs., landing 102,000 lbs.) (d) 2 Cleveland 9243AA (Douglas Dwg. #5479610-5001) (Skydrol) 1103 lbs. (+476.0) (Maximum take-off weight 122,200 lb s., maximum landing weight 97,000 lbs.) (e) 2 Cleveland 9243B (Douglas Dwg. #5479610-501) 1075 lbs. (+476.0) (Maximum take-off weight 126,000 lb s., maximum landing weight 102,000 lbs.) (f) 2 Cleveland 9515A (Douglas Dwg. #5532246) (DC-7C) 1126 lbs. (+476.0) Maximum take-off weight 143,000 lbs ., maximum landing weight 111,000 lbs.) (g) 2 Cleveland 9515AA (Douglas Dwg. #5532246-5001) (DC-7C) 1132 lbs. (+476.0) (Maximum take-off weight 143,000 lb s., maximum landing weight 111,000 lbs.) (h) 2 Cleveland 9515A (Douglas Dwg. #5532246) modified per 1126 lbs. (+475.8) Douglas Dwg. 5776766 or 5776025) (Maximum take-off weight 144,750 lbs.) (m aximum landing weight 111,000 lbs.) (DC-7C) 4A10 12 Landing Gear (cont'd) (i) 2 Cleveland 9515AA (Douglas Dwg. #5532246- 5001) modified per 1132 lbs. (+475.8) Douglas Dwg. 5776766 or 5776025 (Maximum take-off gross weight 144,750 lb s.) (Maximum landing weight 111,000 lbs.) (DC-7C) 206. Nose gear shock strut assembly (a) Cleveland 9242A (Douglas Dwg. #5479590) 276 lbs. (+50.0) (b) Cleveland 9242BA (Douglas Dwg. #5479590-5501)(Skydrol) 278 lbs. (+50.0) (c) Cleveland 9242B (Douglas Dwg. #5479590-501) 276 lbs. (+50.0) (d) Cleveland 9242AA (Douglas Dwg. #5479590-5001) 278 lbs. (+50.0) (e) Cleveland 9516A (Douglas Dwg. #5532242) (DC-7C) 302 lbs. (+9.5) (f) Cleveland 9242C (Douglas Dwg. #5479590-503) 285 lbs. (+50.0) (g) Cleveland 9242CA (Douglas Dwg. #5479590-5503) (Skydrol) 290 lbs. (+50.0) (h) Cleveland 9516AA (Douglas Dwg. #5532242-5001) (DC-7C)(Skydrol) 305 lbs. (+9.5) Electrical Equipment 301.Generators (a) 4 General Electric, 2CM 244A1 or A5 258 lbs. (+350.0) (a) 4 Eclipse 30-E02-5C or later 250 lbs. (+350.0) (c) 4 General Electric 2CM244A2 or A6 254 lbs. (+350.0) (d) 4 General Electric 2CM244C1A or C2 268 lbs. (+350.0) (e) 4 General Electric 2CM 244A2A or A6A 258 lbs. (+350.0) (f) 3 General Electric 2CM244C1A 201 lbs. (+356.0) 303. Batteries (a) 2 Exide 6FH-13 164 lbs. (+81.0) (b) 2 Exide 6FH-13 (DC-7C) 164 lbs. (+41.0) (c) 2 Oldham 6BPA5-4 (DC-7C) 164 lbs. (+41.0) (d) 2 Electric Auto-Lite T-88 (DC-7C) 164 lbs. (+41.0) (e) 2 Japan Storage 6FIJ-13-888 (DC-7C) 170 lbs. (+41.0) Interior Equipment 401. FAA Approved Airplane Fli ght Manual. (A manual containing information required for the Airplane Flight Manual may be carried in lieu thereof in aircraft operated under the provisions of the Federal Air Regulation 121.) The following table identifies the Airplane Flight Manual and the revisions thereto currently approved for each airplane. D a t e Douglas Latest Approved Latest Airplane Serial Number Report No. Rev. No . Ap. Rev. (a) 44122-44146 SM-14980 AA (DC-7) 21 3-21-67 45098-45106 (b) 44171-44174 SM-15129 NAL (DC-7) 16 3-21-67 (c) 44261-44264 SM-18252 Delta (DC-7) 19 3-21-67 44435 44679-44684 (d) 44265-44287 SM-18268 UAL (DC-7) 15 3-21-67 44289 44903-44904 45143-45149 45151-45154 45356-45358 45360 45482-45490 (e) 44864-44870 SM-18874 PAA (DC-7B) 11 3-21-67 (f) 44852-44858 SM-18875 EAL (DC-7B) 14 3-21-67 44860-44863 45082-45089 45330-45349 45447-45451 45453, 45454 45456 (g) 44700-44704 SM-18876 PAG (DC-7B) 11 3-21-67 45244 13 4A10 Interior Equipment (cont'd) D a t e Douglas Latest Approved Latest Airplane Serial Number Report No. Rev. No . Ap. Rev. (h) 44910-44912 SM-19577 SAA (DC-7B) 8 3-21-67 45477 (i) 44921-44925 SM-19618 AAL (DC-7B) 11 3-21-67 45232-45239 45397-45407 (j) 44873-44881 SM-19821 PAA, PAB 19 4-17-67 44883-44886 45090-45097 CMA (DC-7C) 45121-45125 45127-45130 (k) 44926-44933 SM-20002 SAS (DC-7C) 21 4-17-67 45211-45215 45325 (l) 45068-45071 SM-22568 BNF (DC-7C) 17 4-17-67 45073, 45074 (m) 45111-45120 SM-22604 BOAC (DC-7C) 11 3-21-67 (n) 45061, 45062 SM-22637 SWA (DC-7C) 21 4-17-67 45190, 45191 45553 (o) 45158, 45159 SM-22638 SAB (DC-7C) 16 4-17-67 45161, 45162 45308-45310 45495 (p) 45193-45196 SM-22697 CAL (DC-7B) 6 3-21-67 45525 (q) 45203 SM-22727 NWA (DC-7C) 22 4-17-67 45205-45210 45463-45467 (r) 45180-45189 SM-22751 KLM (DC-7C) 17 4-17-67 45545-45549 (s) 45311-45314 SM-22809 Delta (DC-7B) 5 7-25-67 45350-45355 (t) 45362-45365 SM-22900 NAL (DC-7B) 5 3-21-67 (u) 45228-45230 SM-22936 ALI (DC-7C) 13 4-17-67 45541, 45542 (v) 45367, 45446 SM-22951 TAI (DC-7C) 10 5-1-67 (w) 45468-45471 SM-22999 JAL (DC-7C) 14 4-17-67 (x) 45150, 45155 SM-23723 UAL (DC-7B) 4 3-21-67 45156, 45357 45359, 45361 402. 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) Sperry A-12 (DC-7) (3 servos Sperry 679803-167 plus 664575 157 lbs. (+279.0) or 678917-167 plus 664575, 1 servo 658648-41 plus 658774) (1) (a) Servo stall forces measured at pilot's controls: Elevator: Maximum 31 lbs., Minimum 25 lbs. (Forces are exclusive of elevator downspring effect) Aileron: Maximum 29 lbs., Minimum 20 lbs. Rudder: Maximum 66 lbs., Minimum 51 lbs. (b) Corresponding servo stall torques measured at servo: Elevator: Maximum 162 in. lbs., Minimum 130 in. lbs. Aileron: Maximum 106 in. lbs., Minimum 74 in. lbs. Rudder: Maximum 159 in. lbs., Minimum 122 in. lbs. (Servo torques are measured with the control system cable disconnected) (Minimum stall forces are satisfactory fo r automatic approach and beam guidance control.) 4A10 14 (2) Maximum speed for autopilot operation is 310 mph (269 knots) CAS. (See FAA Approved Airplane Flight Manual fo r altitude loss during automatic pilot malfunctions.) (b) Pioneer PB-10 (3 servos Pioneer 15601-1-A, 1 servo 15620-2-A) 157 lbs. (+333.0) (1) (a) Servo stall forces measured at pilot's controls: Elevator: Maximum 33 lbs., Minimum 26 lbs. (Forces are exclusive of elevator downspring effect) Aileron: Maximum 35 lbs., Minimum 17 lbs. Rudder: Maximum 62 lbs., Minimum 48 lbs. (b) Corresponding servo stall torques measured at servo: Elevator: Maximum 263 in. lbs., Minimum 205 in. lbs. Aileron: Maximum 574 in. lbs., Minimum 287 in. lbs. Rudder: Maximum 350 in. lbs., Minimum 270 in. lbs. (Servo torques are measured with the control system cable disconnected) (Minimum stall forces have not b een demonstrated for flight path control) (2) Maximum speed for automatic p ilot operation is 310 mph (269 knots) CAS. (See FAA Approved Airplane Flight Manual fo r altitude loss during automatic pilot malfunction.) (c) Sperry A-12 (For all DC-7B and for DC-7 Serial No. 44435 only) 157 lbs. (+279.0) (2 servos, aileron and rudder, 678919-167 plus 664575 or 679803-167 plus 664575, 1 servo, elevator, 678919-168 plus 664575 or 679803-168 plus 664575, 1 servo, elevator tab, 658648-41 plus 658774). (1) Servo stall forces measured at servo with control system cables disconnected (Minimum stall forces are satisfactory fo r automatic approach and beam guidance control.) Elevator: Maximum 144 in. lbs., Minimum 119 in.lbs. Aileron: Maximum 106 in. lbs., Minimum 75 in. lbs. Rudder: Maximum 159 in. lbs., Minimum 128 in. lbs. Corresponding servo forces measured at pilot's c ontrols (exclusive of system friction and elevator and rudder spring effects): Elevator: Maximum 28 lbs., Minimum 23 lbs. Aileron: Maximum 29 lbs., Minimum 20 lbs. Rudder: Maximum 66 lbs., Minimum 53 lbs. (2) Maximum speed for autopilot operation is 310 mph (269 knots) CAS. (See FAA Approved Airplane Flight Manual fo r altitude loss during automatic pilot malfunction.) (d) Sperry A-12 (for DC-7C) (3 servos, a ileron, rudder and elevator, 193 lbs. (+210.0) 679803-161 with 664575 drum or 678919-161 with 664575 drum. 1 servo unit, elevator trim tab 658648-41 with 658771 drum. Douglas Dwg. #5481884-503 and #3612243) (1) Servo stall torques measur ed at the servos with control system cables disconnected (Minimum stall forces are satisfactory for automatic a pproach and beam guidance control) Elevator: Maximum 173 in. lbs., Minimum 112 in. lbs. Aileron: Maximum 134 in. lbs., Minimum 97 in. lbs. Rudder: Maximum 220 in. lbs., Minimum 160 in. lbs. (2) Maximum speed for operation with autopilot is 310 mph (269 knots) CAS. (See FAA Approved Airplane Flight Manual fo r altitude loss during automatic pilot malfunction.) (e) Pioneer PB-10 (for DC-7B) 157 lbs. (+333.0) (3 servos 15611-1B, 1 elevator tab servo 15620-2A). (1) Servo stall torques measured at servos with control cables disconnected. (These forces have not been de monstrated for Flight Path Control) Elevator: Maximum 285 in. lbs., Minimum 205 in. lbs. Aileron: Maximum 460 in. lbs., Minimum 365 in. lbs. Rudder: Maximum 445 in. lbs., Minimum 350 in. lbs. (2) See Airplane Flight Manua l for maximum operating speed with automatic pilot operation and for altitude loss resulting from malfunction of automatic pilot system. (f) Sperry A-12 (For DC-7C) 198 lbs. (+240.0) (2 servos-aileron and rudder, 678919-161 or 679803-161, with 664575 drums, 1 servo-elevator, either 658680-461 plus Douglas Dwg. #2612468, or 1776288-461; with drum, either 664575 plus Douglas Dwg. #2612467, or 1776287; 1 elevator tab servo 658648-41 with drum 658774). 15 4A10 (1) Servo stall torques measured at servos with control cables disconnected: (Minimum stall forces are satisfactory fo r automatic approach and beam guidance control.) Aileron: Maximum 134 in. lbs., Minimum 97 in. lbs. Rudder: Maximum 210 in. lbs., Minimum 156 in. lbs. Elevator: Torque is controlled by the limiting mechanism and is not adjustable. (2) See Airplane Flight Manual for maximu m operating speed with automatic pilot operation and for altitude loss resulting from malfunction of automatic pilot system. (g) Pioneer PB-10A (For DC-7C) 162 lbs. (+330.0) (2 servos 15613-1B (aileron and rudder); 1 servo 15601-1A (elevator) and 1 elevator tab servo 15620- 2A) (Douglas Dwg. #5611982-505 with modification, Douglas Dwg. #2612484). (1) Servo stall torques measured at the servos with control system cables disconnected: (These forces are satisfactory for flight path control). Aileron: Maximum 540 in. lbs., Minimum 400 in. lbs. Rudder: Maximum 500 in. lbs., Minimum 340 in. lbs. Elevator: Torque is controlled by the limiting mechanism and is not adjustable. (2) See Airplane Flight Manual for maximum operating speed with automatic pilot operation and for altitude loss resulting from malfunction of automatic pilot system. (h) Sperry A-12 (DC-7C) 201 lbs. (+240.0) (2 Servos - aileron and rudder - 678919-161 or 679803-161, with 664575 drums; 1 servo - elevator, either 658680-461 plus DACO Dwg. #2612468, or Sperry 1776288-461, with Drum 664575 plus DACO Dwg. 2612467 or Sperry 1776287; 1 elevator tab servo 669388-41 with drum 675011) (1) Servo stall torques measured at servos with control cables disconnected. Aileron: Maximum 134 in. lbs., Minimum 97 in. lbs. Rudder: Maximum 210 in. lbs., Minimum 156 in. lbs. Elevator: Torque is controlled by the limiting mechanism and is not adjustable. (Minimum stall forces are satisfatory fo r automatic approach and beam guidance control). (2) See Airplane Flight Manual for maximu m operating speed with automatic pilot operation and for altitude loss resulting from malfunction of automatic pilot system. 403. Windshield wipers (a) ALCO (Douglas Dwg. #5332419) 10 lbs. (+40.0) (b) ALCO (Douglas Dwg. #5332419-5500) (Skydrol) 10 lbs. (+40.0) (c) ALCO (Douglas Dwg. #5332419-5500) (Skydrol) (DC-7C) 10 lbs. (+26.0) (d) ALCO (Douglas Dwg. #5332419-500) (DC-7C) 10 lbs. (+26.0) 404. Instruments - in accordance with the following draw ings on file with the Western Regional FAA Office: (a) Douglas Dwg. #7483145 405. Emergency evacuation devices (a) Slide (AAL Dwg. #ADE-5389 or EAL 87-SL1050) 27 lbs. (+720.0) (b) Slide (AAL Dwg. #FDD-3419), (SAS #11D11094) or PAA #L-1970, 24 lbs. (+933.0) L-3380-200 or L-3382-500) (c) Emergency ladder (Douglas Dwg. #5354942) 22 lbs. (+717.0) (d) Slide (PAA #L-1970, or #L-3382-100, or -300, or -400) 29 lbs. (+720.0) (e) Slide (Douglas Dwg. #5580979, AAL Dwg. #FFD-3419) 24 lbs. (+830.0) (f) Slide (AAL Dwg. #FDD-3419) or (EAL #87-SL-1051) 24 lbs. (+907.0) (g) Deleted April 18, 1956 (h) Emergency ladder (Douglas Dwg. #3352240) 18 lbs. (+760.0) (i) Slide (DACO #2613245) or (UAL #6F-5127-10 or 11) 23 lbs. (+720.0) (j) Slide (DACO #5613248) or (UAL #6F-5127-12) 27 lbs. (+933.0) (k) Emergency ladder (DACO #3352240) (DC-7B Cargo) 18 lbs. (+120.0) (l) Emergency ladder (DACO #3352240) 18 lbs. (+150.0) (m) Emergency ladder (DACO #3352240) (DC-7C) 18 lbs. (+110.0) (n) Emergency ladder (DACO #3352240) (DC-7C) 18 lbs. (+870.0) (o) Emergency ladder (DACO #3352240) (DC-7C) 18 lbs. (+118.0) (p) Emergency ladder (DACO #3352240) (DC-7C) 18 lbs. (+910.0) 406.Hydraulic fluid in system and reservoir (a) Skydrol (14.5 U.S. gals.) 130 lbs. (+332.5) (b) Mineral oil (14.5 U.S. gals.) 105 lbs. (+340.5) (c) Skydrol (16.5 U.S. gals.) (DC-7C) 148 lbs. (+331.5) (d) Mineral oil (16.5 U.S. ga ls.) (DC-7C) 120 lbs. (+331.5) 4A10 16 Deicing Equipment 501. (a) 2 Wing heaters, Surface Combination Corp. J88A92 138 lbs. (+417.0) (DACO #5406845-9), L88A92 (DACO #5406945-11) or M88A92 (DACO #5406945-17) or N88A92 (DACO #5406945-19) (b) Empennage heater, Surface Combustion Corp. J88A92 69 lbs. (+1025.0) (DACO #5406945-9), L88A92 (DACO #5406945-11) or M88A92 (DACO #5406945-17) or N88A92 (DACO #5406945-19) 502. (a) Carburetor anti-icing flui d (17.8 gals.) 118 lbs. (+620.0) 503. (a) Propeller electrical anti-icing equi pment, less equipment 53 lbs. (+283.0) on propellers (b) Propeller electrical anti-icing equi pment, less equipment 60 lbs. (+282.0) on propellers (DC-7C) 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 a ddition to equipment listed in this publication. (b) "System Fuel and Oil" (Item 102), which must be in cluded in the empty weight, is that amount required to fill both systems and the tanks up to the tank outlets to the engines, when the airplane is in the level attitude. The propeller feathering oil in aircraft incorporating Hamilt on 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 hydraulic system fluid (See Item 406) 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, th en alternates. Fuel must be used in the reverse order from fuel loading except for take-off, climb and landing, at which time the main tanks must be used. Not more than 75 gallons (450 lbs.) of fuel should be used from each main tank on take-off prior to changing to alternates. Satisfactory alternate fuel loading and usage proce dures have been approved and placed in the FAA approved Airplane Flight Manual. These alternate pr ocedures may be used in lieu of the above. (e) Fuel dumping - Fuel dump valves (Item 105) must be installed for operation of the airplane at weights in excess of maximum landing weight. Re fer to FAA Approved Airplane Flight Manual for limitations and cautionary procedures to be observed during the dumping of fuel. When dump system (Item 105) is installed, the amount of usable fuel remaining in the fuel tanks after dumping is as follows: (1) Eight Wing Tank Airplane 5512 Gal. System 4512 Gal. Systems Outer wing (#1 and #4 main) 141 gal. ea. 141 gal. ea. Inboard inner wing (#2 a nd #3 main) 137 gal. ea. 147 gal. ea. Outboard inner wing (#1 and #4 a lt.) 0 gal. ea. 0 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 54 gal. ea. 39 gal. ea. (2) Eight Wing Tank Airplane 6378 or 6474 Gal. System Outer wing (#1 and #4 main) 148 gal. ea. Inboard inner wing (#2 and #3 main) 158 gal. ea. Outboard inner wing (#1 and #4 alt.) 0 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 54 gal. ea. (3) Ten Wing Tank Airplane (DC-7C) 7824 Gal. System Outer wing (#1 and #4 main) 156 gal. ea. Inboard inner wing (#2 and #3 main) 158 gal. ea. Outboard inner wing (#1 and #4 alt.) 0 gal. ea. Inboard wing fuel cells (#2 and #3 alt.) 90 gal. ea. The total undumpable fuel and oil must be included in the landing weight. When Wright DA3 or DA4 engines are installed on aircraft originally incorporating DA2 engines and the power utilized is greater than that approved for the DA2 engine, the standpipes in the main tank must be of sufficient height to result in 148 gallons of undumpable fuel in each of #1 and #4 main tanks and 158 gallons of undumpable fuel in each of #2 and #3 main tanks. 17 4A10 (f) For the interior arrangement of a particular airplane , see approved Douglas Report SM-14762 (DC-7 and DC-7B) or SM-19487 (DC-7C). "Loading Chart and Actual Weight and Balance." That report shows the location of all passenger and crew member seats; location and capacity of all cargo and baggage compartments, buffets, storage spaces and coatrooms; and location and capacity of lounges and lava tories for each of the different sleeper and dayplane arrangements covered by the above-menti oned report. Lounges, lavatories, and baggage or cargo compartments must be placarded for the capacities specified in the above report. Th e airplane must always be loaded within the C.G. limits specified in this specification, accounting for crew and passenger movement, and use of fuel and oil. (g) For interior configuration of DC-7 airplanes converted to cargo see approved Douglas Report SM-23562, "Loading Chart and Actual Weight and Balance for DC -7 Airplanes Converted to Cargo." This report shows the location of all crew member seats and location and capacity of all cargo compar tments. Cargo compartments must be placarded for the capacities specified in the above report. NOTE 2. The following placard shall be placed on the instrument pa nel in full view of the pilot or when appropriate, the instruments should be properly marked: (a) "This airplane shall be operated in compliance w ith the operating limitations specified in the FAA Approved Airplane Flight Manual." (b) "Avoid continuous ground operation betw een 1300 and 1600 rpm." (With Item 1(a).) (c) "Avoid continuous ground operation betw een 1200 and 1550 rpm." (With Item 1(c).) NOTE 3. (a) Ferry permits may be issued to all Model DC-7 se ries airplanes on which one engine is inoperative, with its propeller removed or feathered under the following conditions: (1) Operation of aircraft shall be in accordance with pertinent limitations contained in the applicable portion of the FAA Approved Airplane Flight Ma nual pertinent appendices, and existing instructions. (2) (a) Maximum take-off weight 100,000 lbs. *(DC-7 and DC-7B) (b) Maximum take-off we ight 105,000 lbs. *(DC-7C) *(Except when limited by runway length sp ecified in FAA Approved Airplane Flight Manual). (3) (a) C.G. range: 13% (Sta. 416.5) to 22% (Sta. 413.2) (Gear Down) (Model DC-7 and DC-7B) (b) C.G. range: 14.6% (Sta. 417.8) to 24% (Sta. 433.7) (Gear Down) (Model DC-7C) NOTE 4: The following table lists the maximum zero fuel and oil, landing and take-off weights of the DC-7 Series aircraft as it is limited by structural 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 installed and the flap setting used . Therefore, the table of take- off weights under maximum weights should also be adhered to in determining th e maximum permissible take-off weight of various aircraft. MAXIMUM STRUCTURAL LIMITS Airplane Serial Numbers Zero Fuel; Oil and ADI Fluid Landing Weight Takeoff Weight MODEL DC-7 44122-44128 88,350# 95,000# 122,200# (1) 44142 88,350# 95,000# 122,200# (1) 90,250# (4) 97,000# (4) 44129-44141 44171-44174 88,350# 95,000# 116,622# (2) 44261-44264 116,800# (3) 44129-44141 90,250# (4) 97,000# (4) 118,522# (2)(4) 118,700# (3)(4) 44143-44146 44265-44287 90,250# 97,000# 122,200# (1) 44289, 44435 44679-44684 90,250# 97,000# 118,522# (2) 44903, 44904 91,300# 97,000# 122,200# (1) 45098-45106 45143-45149 45151-45154 45356, 45358 45360 45482-45490 4A10 18 MODEL DC-7B Airplane Serial Numbers Zero Fuel; Oil and ADI Fluid Landing Weight Takeoff Weight 44700-44702 44704 124,272# (2) 44852-44870 96,000# 102,000# 124,450# (3) 44910-44912 126,000# (1), (5) or (7) 45082, 45083 45085-45089 45193-45196 45235-45237 45244 45311-45314 45330-45355 45362-45365 45389 45401, 45402 45404-45407 45447-45451 45453, 45454 45456 45477, 45525 MODEL DC-7B (Cargo) (11) (14) (18) Airplane Serial Numbers Zero Fuel; Oil and ADI Fluid Landing Weight Takeoff Weight 44703 98,000# 104,000# 126,000# (1), (5) or (7) 44921-44925 45232-45234 45238, 45239 45397, 45398 45400, 45403 45150, 45155 98,000# 104,000# 126,000# (1), (5) or (7) 45156, 45357 and (12) 45359, 45361 MODEL DC-7C (15) 44875-44880 101, 500# 109,000# 140,000# (8) 111,000 (9)(10) 143,000# (8)(9) 44873, 44874 44885, 44886 101,500# 109,000# 143,000# (8) 44928-44933 111,000# (9)(10) 45061 101,500# 109,000# 143,000# (8) 111,000# (9)(10) 144,750# (18) 45068-45071 101,500# 109,000# 143,000# (8) 45074 111,000# (10) 45090-45097 45111-45118 45121-45125 45127 45161, 45162 45180-45183 45205, 45325 45158, 45159 101,500# 109,000# 143,000# (8) 111,000# (10) 144,750# (18) 45187, 45189 101,500# 111,000# 143,000# (8) 45206, 45210 45211 45230 45308-45310 19 4A10 MODEL DC-7C (15) (cont'd) 45367, 45446 101,500# 111,000# 143,000# (8) 144,750# (18) 45468, 45469 101,500# 111,000# 143,000# (8) 45495 45541, 45542 45545-45549 45553 MODEL DC-7 CARGO (13)(14)(16)(18) 44881, 44883 106,400# 113,000# 143,000# (8) 44884, 44926 44927, 45062 45119, 45120 45191, 45203 45207, 45208 45212-45214 45228, 45229 45464-45466 45471 45130 106,100# 113,000# 143,000# (8) 45184-45186 144,750# (17) 45188, 45190 45463, 45467 45470 (1) With 8 wing tank 5512 gallon fuel system installation. (2) With 8 wing tank 4512 gallon fuel system and 40 gallon oil tank (Item 102b) installation. (3) With 8 wing tank 4512 gallon fuel system and 46 gallon oil tank (Item 102c) installation. (4) These aircraft have all the struct ural provisions for the higher zero fuel and landing weights except the rework described on Douglas Drawings 5500249 "Rework - Fr ont Spar Ldg. Gear Fitting Inst." and 5500485 "Service Rework - Center Spar Landing Gear Fitting Area." Upon completion of the rework, the higher zero fuel and landing weights may be realized. Where indica ted, the take-off weight may also be increased. (5) With 8 wing tank 6378 gallon fuel system installation. (6) Deleted January 7, 1960. (7) With 8 wing tank 6474 gallon fuel system. (8) With 8 wing tank 7824 gallon fuel system installation. (9) Rework described on Douglas Dwgs. 5479663 "F" Change, "Rib Installation - Outer Wing Rear Tank Section" and 5482259 "AF" Change "Panel Inst. - Outer Wing Re ar Section Top Skin and Stringers" must be accomplished. (Ref.: Douglas Service Le tter A-213- 2326/WES to PAA dated August 9, 1956). (10) Rework described on Douglas Dr awing 4654428, "Service Rework, Rear Spar Vertical Stiffener Attach. Sta. 55 C.V.", must be accomplished. (See Douglas Service Letter A-215-8217/ERM to DC-7C operators, dated 4/19/57, Service Bulletin DC-7 #240 and Drawing 5532261 "CV" Change). (11) DC-7B aircraft modified per approved Douglas type design data for cargo operation (12) Basic DC-7 aircraft converted to DC-7B (cargo). These aircraft must have new nameplates installed per Douglas Dwg. No. 2768055 to indicate the c hange in model designation and date of conversion. (13) DC-7C aircraft modified per approved Douglas type design data for cargo operation. (14) When operating as a passenger carrying airplane, th e fuselage loading, including the weight of passengers, baggage or cargo, seats and all other interior equi pment must not exceed the loading limit of the fuselage. (15) For airplanes with Serial Nos. 45111-45118, 45180-45183, 45187, 45189, 45545-45549, the zero fuel weight may be increased to 102,500 lbs. when the aircraft is loaded so that the floor structural loading does not exceed the equivalent of 28.8 lbs./in. from Sta. 63 to Sta. 880 (5 abreast seating at 33" O.C.); 23 lb./in. from Sta. 880 to Sta. 913 (4 abreast seating at 33" O.C.); 118 lb./in. from Sta. 913 to Sta. 948 (2 abreast seating at 33" O.C.). Maximum cargo placards: Fwd. belly compartment 6000 lbs.; aft belly compartment 6230 lbs. The appropriate loading schedule must be prepared to assure that these limits are not exceeded. 4A10 20 (16) DC-7C, Serial Nos. 45062, 45128, 45130, 45190, 45212 and 45463 through 45467 were modified per approved type design data to incorporate a large cargo door and cargo floors and delivered to the owner for further modifications for carrying cargo or passengers. Th e FAA Approved Airplane Flight Manual was revised to prohibit the carriage of passengers or cargo. Upon completion of approved modifications for passenger or cargo operation, the FAA Approved Airplane Flight Manual must be appropriately revised. If these aircraft are to be used in cargo operation, compliance with CAR 4b.359, .382 and .384 must be demonstrated. (17) Rework required in accordance with Douglas Dr awing No. 2776260 "Wing Assem. - Center Wing" and Douglas Drawing No. 5776025 "Gear Assemb. - Landing". (18) Rework required in accordance with Douglas Draw ing No. 5776766, "Service Rework - Increased M.T.O.G.W.", and Douglas DC-7 Service Bulletin No. 240 must also be accomplished. (19) Certain aircraft were modified per approved Type Design Data so that the main cabin cargo compartment complies with the Class "E" category requirements of CAR 4b.383(e). The modification included (1) ventilating system air shutoff valve assemblies, Douglas P/N 276176-5; (2) sealed bulkhead between the crew and main cargo compartment; (3) C-O-TWO-74800 smoke det ector indicator and piping per Douglas Drawings 5761887 (DC-7B) or 2770709 (DC-7C), and (4) fire resistant lining of the main cabin fuselage structure. Some of the aircraft incorporated part of the above and others di d not incorporate any of the above installations. Compliance with the appropriate sec tions of CAR 4b.382 to .384 must be demonstrated if these aircraft are to be operated as cargo carriers. NOTE 5. In accordance with the agreement between the Department of Defense and the Civil Aeronautics Board, all air carrier operators utilizing aircraft which have been m odified under the Civil Reserve Air Fleet Program, Part I, Phase II, may deduct the added weight of the military modifications up to a maximum of 50 pounds for each aircraft so modified. NOTE 6. The Model DC-7B airplane has been found to comply with the standards of Category A of Annex 8 to the Convention of International Civil Aviation, entitled "Air worthiness of Aircraft," as amended to March 1951, with the following exceptions: (a) Chapter 7 Sub-Part 7.2.5.3 Paragraph 4, unless oil filter screens per Douglas Dwgs. 5461656 are incorporated. (b) Chapter 9 Sub-Part 9.4.2.2(d), unless fuel capacity placard adjacent to fuel selector controls per Douglas Drawing 2461348 is incorporated. (c) Chapter 9 Sub-Part 9.3 "Aeropl ane Flight Manual," unless Airplane Flight Manual amended to include Section III D for ICAO Requirements. NOTE 7. In accordance with special Civil Ai r Regulations SR-411B, aircraft operated by air carriers for cargo operation only, are permitted to increase zero fuel and landing weights by 5% of the maximum zero fuel weight. For DC-7B cargo aircraft covered by this specifica tion the maximum zero fuel, oil and ADI fluid weight may be increased to 102,900 lbs. and the maximum landing weight to 108,900 lbs. For DC-7C cargo aircraft covered by this specification the maximum zero fuel, oil and ADI fluid weight may be in creased to 111,720 lbs. and the maximum landing weight to 118,320 lbs. In addition to the operator's normal inspec tion program, aircraft operated in accordance with SR-411B must be inspected in accordance w ith Douglas Report SM-23577, "Special Inspection Procedure," as revised and approved by the FAA. Requests for changes in the insp ection procedure must be forwarded to the manufacturer for recommendations and submitted to the FAA for approval. .....END..... ``` ## ADs (26, 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 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 2004-22-01](https://openairdocs.org/ad/2004-22-01): Cargo restraint strap assemblies · Cargo restraint straps (Airline Container Manufacturing STC ST01004NY). 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Effective Mar 1, 1964 - [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 61-08-01](https://openairdocs.org/ad/61-08-01): Fuel Transfer · Boeing DC-6, DC-6A, DC-6B and 3 more. 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Effective Jul 29, 1996 ## Registered aircraft by registry model (OpenAirDocs) - [Douglas DC-7](https://openairdocs.org/model/douglas-dc-7): 2 aircraft (registry code 3021802) - [Douglas DC-7B](https://openairdocs.org/model/douglas-dc-7b): 2 aircraft (registry code 3021804) - [Douglas DC-7C](https://openairdocs.org/model/douglas-dc-7c): 1 aircraft (registry code 3021806) - [Douglas DC-7BF](https://openairdocs.org/model/douglas-dc-7bf): 0 aircraft (registry code 3021805) - [Douglas DC-7CF](https://openairdocs.org/model/douglas-dc-7cf): 0 aircraft (registry code 3021807) - [Douglas DC-7F](https://openairdocs.org/model/douglas-dc-7f): 0 aircraft (registry code 3021808) ## STCs approved under this data sheet (59, 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 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 SA2709WE](https://openairdocs.org/stc/SA2709WE): Installation of 3000 gallon external retardant tanks under the fuselage at the wing center section.. United Aeronautical Corporation - [STC SA3015WE](https://openairdocs.org/stc/SA3015WE): Installation of LH and RH upper viewing windows above side cockpit windows.. United Aeronautical Corporation - [STC ST334CH](https://openairdocs.org/stc/ST334CH): Installation of Superflite 102 fabric.. Aviation Products Systems Inc. - [STC SA796WE](https://openairdocs.org/stc/SA796WE): Wing flap attachments modification. S/Ns 44903, 44904. 45143 thru 45149, 45151 thru 45154, 45356, 45358, 45360, 45482 thru 45490. Boeing Company - [STC SA364SO](https://openairdocs.org/stc/SA364SO): Cockpit voice recorder.. Delta Airlines Inc - [STC SA1369GL](https://openairdocs.org/stc/SA1369GL): Surrendered and incorporated into STC ST334CH.. Cooper Aviation Supply Company, Inc. - [STC ST01004NY](https://openairdocs.org/stc/ST01004NY): Installation of cargo restraint straps.. Airline Container Manufacturing Co Inc - [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 SA3103NM](https://openairdocs.org/stc/SA3103NM): Installation of military model R-3350-42(STC SE2004NM) or R-3350-93(STC SE2007NM) engines.. Tulare Aircraft Service - [STC SA2047SO](https://openairdocs.org/stc/SA2047SO): Installation of an unpressurized aft cargo door.. Aeronautical Engineers, Inc - [STC SA3102NM](https://openairdocs.org/stc/SA3102NM): Installation of military model R-3350-42 (STC SE2004NM) or R-3350-93 (STC No. SE2007NM) engines.. Tulare Aircraft Service - [STC SA3093NM](https://openairdocs.org/stc/SA3093NM): Installation of military model R-3350-42 (STC SE2004NM) or R-3350-93 (STC SE2007NM) engines.. Tulare Aircraft Service - [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 ST484SO](https://openairdocs.org/stc/ST484SO): Installation of cargo restraining bulkhead.. Aeronautical Engineers, Inc - [STC ST631SO](https://openairdocs.org/stc/ST631SO): Installation of loading and restraint system for palletized cargo.. Jet Avion Corp - [STC SA470CE](https://openairdocs.org/stc/SA470CE): Installation of Fairchild cockpit voice recorder Model A-100.. Universal Airlines, Inc - [STC SA7SO](https://openairdocs.org/stc/SA7SO): Radome and radar antennae mount provisions for up to 22-inch diameter antennae, RAC AVQ-10 or Bendix RDR-1 (X/C Band).. Tempo Design Corp - [STC SA493SW](https://openairdocs.org/stc/SA493SW): Installation of 104-passenger interior arrangement.. American Airlines Inc - [STC SA103WE](https://openairdocs.org/stc/SA103WE): Interior arrangement for 104 passengers.. Camaero Inc - [STC SA1068WE](https://openairdocs.org/stc/SA1068WE): Interior arrangement.. California Airmotive Corporation - [STC SA1075WE](https://openairdocs.org/stc/SA1075WE): AVQ9 radar altimeter, APN9 Loran receiver, AT144 HF transmitter and AR144 HF receiver.. California Airmotive Corporation - [STC SA10SO](https://openairdocs.org/stc/SA10SO): Provisioned for installation of10,000 pound military pallet.. Pan American World Airways Inc - [STC SA1361WE](https://openairdocs.org/stc/SA1361WE): Fairchild Industrial Products Model A100, cockpit voice recorder system.. Saturn Airways Inc - [STC SA176NW](https://openairdocs.org/stc/SA176NW): Installation of Fairchild Andover Model 204 auxiliary power unit for ground use only.. Butler Aircraft Co - [STC SA214WE](https://openairdocs.org/stc/SA214WE): Passenger interior arrangements and cargo interior.. Pacific Airmotive Corp - [STC SA23SO](https://openairdocs.org/stc/SA23SO): Observer's seat fuselage Station 55.. Riddle Airlines Inc - [STC SA294WE](https://openairdocs.org/stc/SA294WE): Door in floor for cabin access.. AiResearch Aivation Service Co - [STC SA3-311](https://openairdocs.org/stc/SA3-311): Wheels 150741-1 and/or 150741-5 and brake assembly 150835-5.. Bendix Aviation Corporation - [STC SA30SO](https://openairdocs.org/stc/SA30SO): Two emergency exits at stations437.9 - 460.5 from Type IV to Type III modified.. Riddle Airlines Inc - [STC SA314WE](https://openairdocs.org/stc/SA314WE): Passenger interior arrangements and cargo interior for operation of aircraft at 106,400 pounds zero fuel weight.. Pacific Airmotive Corp - [STC SA35SO](https://openairdocs.org/stc/SA35SO): Access hole in horizontal stabilizer.. Riddle Airlines Inc - [STC SA4-124](https://openairdocs.org/stc/SA4-124): Station 122 bulkhead.. Pan American World Airways Inc. - [STC SA4-255](https://openairdocs.org/stc/SA4-255): Aft cabin lounge.. AiResearch Aivation Service Co - [STC SA4-328](https://openairdocs.org/stc/SA4-328): Step kit added to fore and aft cargo door.. National Aircraft Corp - [STC SA4-329](https://openairdocs.org/stc/SA4-329): Step kit added to fore and aft cargo door.. National Aircraft Corp - [STC SA4-330](https://openairdocs.org/stc/SA4-330): Step kit added to fore and aft cargo door.. National Aircraft Corp - [STC SA4-355](https://openairdocs.org/stc/SA4-355): Interior modification coach to mixed class.. AiResearch Aivation Service Co - [STC SA4-405](https://openairdocs.org/stc/SA4-405): Interior modification to mixed class.. AiResearch Aivation Service Co - [STC SA4-442](https://openairdocs.org/stc/SA4-442): Modification of communication equipment to provide navigator station.. American Airlines Inc - [STC SA4-507](https://openairdocs.org/stc/SA4-507): Deterjet DJ1025 valve in place of Wright torquemeter booster pump upper housing per STC SEW-10.. Pan American World Airways Inc. - [STC SA4-54](https://openairdocs.org/stc/SA4-54): Passenger/cargo interior arrangement configurations.. Pan American World Airways Inc. - [STC SA4-91](https://openairdocs.org/stc/SA4-91): One 4-piece divan left-hand side inboard facing and one 2-place divan right-hand side aft facing from Station 891 aft to pressure dome.. AiResearch Aivation Service Co - [STC SA425WE](https://openairdocs.org/stc/SA425WE): Single Federal (ITT) Type AFN3544 distance measuring equipment system.. American Airlines Inc - [STC SA469CE](https://openairdocs.org/stc/SA469CE): Fairchild A-100 cockpit voice recorder.. Northwest Airlines Inc - [STC SA500EA](https://openairdocs.org/stc/SA500EA): Installation of microvision operational all-weather landing system.. Bendix Corporation - [STC SA588WE](https://openairdocs.org/stc/SA588WE): Ceconite 101 covering of rudder.. Cooper Engineering Corporation All 59: https://openairdocs.org/tcds/4A10/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.