TCDS 4A10

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