TCDS A-762

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 Rev. No. 21 - - - - - - - - - - - - - - - - - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-762 Revision 21 BOEING C54-DC (Army C-54, Navy R5D) C54A-DC (Army C-54A, Navy R5D-1) C54B-DC (Army C-54B, Navy R5D-2) C54D-DC (Army C-54D, Navy R5D-3) C54E-DC (Army C-54E, Navy R5D-4) C54G-DC (Army C-54G, Navy R5D-5) DC-4 September 27, 2010 AIRCRAFT SPECIFICATION NO. A-762 Type Certificate Holder The Boeing Company 4000 Lakewood Boulevard Long Beach, California 90808 Type Certificate Holder 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 C54-DC, Approved June 6, 1946. See NOTE 4 regarding modifications required for conversion of military models, and NOTE 10 regarding additional speed and load factor limits. Engines See Item 100. Fuel See Item 100. Engine Limits See Item 100. Airspeed Limits See Table “B”, NOTE 9. C.G. Range 16% MAC (381.4) to 32% MAC (407.6) . Range based on “landing gear extended” and applies for take-off, flight and landing. See NOTE 8 regarding extension of rear limit for enroute operation. Maximum Weights See Table “A”, NOTE 9. For 3-engine ferrying, see NOTE 13. Minimum Crew 2 - Pilot and co-pilot at +108.0 Passengers Variable, see approved loading sche dule. See NOTE 6 regarding emergency exit requirements. Maximum Baggage Cu. Ft . Weight Arm Forward Belly 130 2100 lbs. (+228.2) Aft Belly 151 2520 lbs. (+590.5) Crew Room 1500 lbs. (+228.2) Coat Closet 106 500 lbs. (+746.5) Fuel Capacity (without 2 inboard inner wi ng tanks 497 gal. ea. 2982 lbs. ea. (+400.9) Stoner-Mudge Sealing) 2 outboard inner wi ng tanks 425 gal. ea. 2550 lbs. ea. (+404.1) 2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+228.2) (when installed, see NOTE 9) Fuselage Fuel Tanks 464 ga l. ea. 2784 lbs. ea. (+301.0) and (+381.0) When Stoner-Mudge Sealing is incorporat ed, see pertinent report referred to in NOTE 4. Oil Capacity 20 gals. in each inboard nacelle 150 lbs. ea. (+327.0) 20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 50 gals. in fuselage tank 375 lbs. (+223.3) See NOTE 7 regarding fuel load when fuselage oil tank is removed. Serial Nos. Eligible 3050 to 3053 including, 3060 to 3063 including, 3075 and 3111 to 3125 inclusive. Required Equipment 1(a), 100(a), 102(d) , 200, 201, 202, 203, 204, 205, 400, 401. Optional Equipment 1(b), 100(b), (c), (d), (e), (f), or (g), 101, 102(b), (c), (f), or (h), 402, 500. II. Model C-54A-DC, Approved June 6, 1946. See NOTE 4 regarding modifications required for conversion of military models and NOTE 10 regarding additional speed and load factor limits. (Same as C54-DC except for large fuselage door, heavier fuselage plating and stringers, heavier cargo floors and floor beams, increased strength of center wing and cargo and troop carrying provision.) Engine See Item 100. Fuel See Item 100. Engine Limits See Item 100. Airspeed Limits See Table “B”, NOTE 9. C.G. Range 16% MAC (381.4) to 32% MAC (407.6) . Range based on “landing gear extended” and applies for take-off, flight and landing. See NOTE 8 regarding extension of rear limit for enroute operation. Maximum Weights See Table “A”, NOTE 9. For 3-engine ferrying, see NOTE 13. Minimum Crew 2 - Pilot and co-pilot at +108.0 Passengers Variable, see approved loading sche dule. See NOTE 6 regarding emergency exit requirements. Maximum Baggage Cu. Ft. Weight Arm Forward Belly 130 2100 lbs. (+228.2) Aft Belly 151 2520 lbs. (+590.5) Crew Room 1500 lbs. (+228.2) Cabin Floor Loadings (Do not exceed either value shown) Sta. 129-260 1/2 100#/ft 2 or 50#/in. lengthwise of cabin. Sta. 260 1/2-680 200#/ft 2 or 80#/in. lengthwise of cabin. Sta. 680-858 100#/ft 2 or 30#/in. lengthwise of cabin. Fuel Capacity (without Storner- 2 inboard inne r wing tanks 508 gal. ea. 3048 lbs. ea. (+400.9) Mudle Sealing) 2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea. (+404.1) 2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+228.2) Fuselage Fuel Tanks 464 ga l. ea. 2784 lbs. ea. (+301.0) and (+381.0) A-762 3 (When Stoner-Mudge Sealing is incorporat ed, see pertinent report referred to in NOTE 4.) Oil Capacity 20 gals. in each inboard nacelle 150 lbs. ea. (+327.0) 20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 50 gals. in fuselage tank 375 lbs. (+223.3) See NOTE 7 regarding fuel load wh en fuselage oil tank is removed. Serial Nos. Eligible 3054 to 3059 inclusive, 3064 to 3074 inclusive, 3076 to 3110 inclusive, 7445 to 7469 inclusive, 7471 to 7489 inclusive, 10270 to 10424 inclusive. Required Equipment 1(a), 100(a), 102(e) , 200, 201, 202, 203, 204, 205, 400,401. Optional Equipment 1(b), 100(b), (c), (d), (e), (f), or (g), 101, 102(b), (c), (d), (f) or (h), 402, 500. III. Model C54B-DC, Approved June 6, 1946. See NOTE 4 regarding modifications required for conversion of military models, and NOTE 10 regarding additional speed and load factor limits. (Same as the Model C54A-DC, except that outer wing panels incorporate integral fuel tanks and only two fuselage fuel tanks were originally installed.) Engines See Item 100 Fuel See Item 100 Engine Limits See Item 100 Airspeed Limits See Table “B”, NOTE 9 C.G. Range 16% MAC (381.4) to 32% MAC (407.6) . Range based on “landing gear extended” and applies for take-off, flight and landing. See NOTE 8 regarding extension of rear limit for enroute operation. Maximum Weights See Table “A”, NOTE 9. For 3-engine ferrying, see NOTE 13. Minimum Crew 2 - Pilot and co-pilot at +108.0 Passengers Variable, see a pproved loading schedule. Maximum Baggage Cu . ft. Weight Arm Forward Belly 130 2100 lbs. (+228.2) Aft Belly 151 2520 lbs. (+590.5) Crew Room 1500 lbs. (+228.2) Cabin Floor loadings (Do not exceed either value shown). Sta. 129-260 1/2 100#/ft 2 or 50#/in. lengthwise of cabin. Sta. 260 1/2-680 200#/ft 2 or 80#/in. lengthwise of cabin. Sta. 680-858 100#/ft 2 or 30#/in. lengthwise of cabin. Fuel Capacity (Without Stoner- 2 inboard inner wing tanks 508 gal. ea. 3048 lbs. ea. (+400.9) Mudge Sealing) 2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea. (+404.1) 2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+404.5) Fuselage Fuel Tanks 464 ga l. ea. 2784 lbs. ea. (+301.0) and (+381.0) (When Stoner-Mudge Sealing is in corporated, see pertinent report referred to in NOTE 4.) Oil Capacity 20 gals. in each inboard nacelle 150 lbs. ea. (+327.0) 20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 50 gals. in fuselage tank 375 lbs. (+223.3) See NOTE 7 regarding fuel load wh en fuselage oil tank is removed. Serial Nos. Eligible 18324 to 18398inclusive , 27227 to 27251 inclusive, 10425 to 10544 inclusive Required Equipment 1(a), 100(a), 102(c) , 200, 201, 202, 203, 204, 205, 400, 401. Optional Equipment 1(b), 100(b), (c), (d), (e ), (f), or (g), 101, 102(b), or (h), 402, 500 IV. Model C54D-DC, Approved June 6, 1946. See NOTE 4 regarding modifications required for conversion of military models and NOTE 10 regarding additional speed and load factor limits. (Essentially same as C54B-DC except R-2000-7 and R-2000-11 engines installed in C54D-DC while R-2000-7 engines originally installed in C54B-DC.) Engines See Item 100 Fuel See Item 100 Engine Limits See Item 100 Airspeed Limits See Table “B”, NOTE 9 C.G. Range 16% MAC (381.4) to 32% MAC (407.6) . Range based on “landing gear extended” and applies for take-off, flight and landing. See NOTE 8 regarding extension of rear limit for enroute operation. Maximum Weights See Table “A”, NOTE 9. For 3-engine ferrying, see NOTE 13. Minimum Crew 2 - Pilot and co-pilot at +108.0 Passengers Variable, see a pproved loading schedule. Maximum Baggage Cu . Ft. Weight Arm Forward Belly 130 2100 lbs. (+228.2) Aft Belly 151 2520 lbs. (+590.5) Crew Room 1500 lbs. (+228.2) Cabin Floor loadings (Do not exceed either value shown.) Sta. 129-260 1/2 100#/ft 2 or 50#/in. lengthwise of cabin Sta. 260 1/2-680 200#/ft 2 or 80#/in. lengthwise of cabin Sta. 680-858 100#/ft 2 or 30#/in. lengthwise of cabin Fuel Capacity (Without Stoner- 2 inboard inne r wing tanks 508 gal. ea. 3048 lbs. ea. (+400.9) Mudge Sealing) 2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea. (+404.1) 2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+404.5) Fuselage Fuel Tanks 464 ga l. ea. 2784 lbs. ea. (+301.0) (When Stoner-Mudge Sealing is incorporat ed, see pertinent report referred to in NOTE 4.) Oil Capacity 20 gals. in each inboard nacelle 150 lbs. ea. (+327.0) 20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 50 gals. in fuselage tank 375 lbs. (+223.3) See NOTE 7 regarding fuel load wh en fuselage oil tank is removed. Serial Nos. Eligible 10545 to 10869 inclusive, 22149 to 22203 inclusive Required Equipment 1(a), 100(c), 102(c) , 200, 201, 202, 203, 204, 205, 400, 401. Optional Equipment 1(b), 100(a), (b), (d), (e ), (f), or (g), 101, 102(b), or (h), 402, 500 A-762 5 V. Model C54E-DC, Approved June 6, 1946. See NOTE 4 regarding modifications required for conversion of military models and NOTE 10 regarding additional speed and load factor limits. (Same as C54B-DC except for engine installation, omission of remaining fuselage tanks, fuel cells installed in center wing between inboard nacelle and side of fuselage, installation of soundproofing, cabin upholstering, buffet, lounge in rear of cabin and removable passenger seats.) Engines See Item 100. Fuel See Item 100. Engine Limits See Item 100. Airspeed Limits See Table “B”, NOTE 9. C.G. Range 16% MAC (381.4) to 32% MAC (407.6) . Range based on “landing gear extended” and applies for take-off, flight and landing. See NOTE 8 regarding extension of rear limit for enroute operation. Maximum Weights See Table “A”, NOTE 9. For 3-engine ferrying, see NOTE 13. Minimum Crew 2 - Pilot and co-pilot at +108.0 Passengers Variable, see approved loading schedule Maximum Baggage Cu . ft. Weight Arm Forward Belly 130 2100 lbs. (+228.2) Aft Belly 151 2520 lbs. (+590.5) Crew Room 1500 lbs. (+228.2) Rear Cabin 500 lbs. (+711.2) Coat Closet 200 lbs. (+795.0) Cabin Floor loadings (Do not exceed either value shown) Sta. 129-260 1/2 100#/ft 2 or 50#/in. lengthwise of cabin. Sta. 260 1/2-680 200#/ft 2 or 80#/in. lengthwise of cabin. Sta. 680-858 100#/ft 2 or 30#/in. lengthwise of cabin. Fuel Capacity (Without Stoner- Mudge Sealing) 2 inboard inner wing tanks 508 gal. ea. 3048 lbs. ea. (+400.9) 2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea. (+404.1) 2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+404.5) 2 inner wing fuel cells 362 gal. ea. 2172 lbs. ea. (+397.5) (When Stoner-Mudge Sealing is in corporated, see pertinent report referred to in NOTE 4. Oil Capacity 20 gals. in each inboard nacelle 150 lbs. ea. (+327.0) 20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 50 gals. in fuselage tank 375 lbs. (+223.3) See NOTE 7 regarding fuel load wh en fuselage oil tank is removed. Serial Nos. Eligible 27242 to 27376 inclusive Required Equipment 1(a), 100(b), 102(a) , 200, 201, 202, 203, 204, 205, 400, 401 Optional Equipment 1(b), 100(a), (c), (d), (e), (f), or (g), 101, 102(g) or (h), 402, 500. VI. Model C54G-DC, Approved June 6, 1946. See NOTE 4 Regarding modifications required for conversion of military models, and NOTE 10 regarding additional speed and load factor limits. (Same as C54E-DC, except troop carrying provisions installed instead of passenger interior.) Engines See Item 100. Fuel See Item 100. Engine Limits See Item 100. Airspeed Limits See Table “B”, NOTE 9. C.G. Range 16% MAC (381.4) to 32% MAC (407.6). Range based on “landing gear extended” and applies for take-off, flight and landing. See NOTE 8 regarding extension of rear limit for enroute operation. Maximum Weights See Table “A”, NOTE 9. For 3-engine ferrying, see NOTE 13. Minimum Crew 2 - Pilot and co-pilot at +108.0 Passengers Variable, see a pproved loading schedule. Maximum Baggage Cu . Ft. Weight Arm Forward Belly 130 2100 lbs. (+228.2) Aft Belly 151 2520 lbs. (+590.5) Crew Room 1500 lbs. (+228.2) Cabin Floor Loadings (Do not exceed either value shown). Sta. 129-260 1/2 100#/ft 2 or 50#/in. lengthwise of cabin. Sta. 260 1/2-680 200#/ft 2 or 80#/in. lengthwise of cabin. Sta. 680-858 100#/ft 2 or 30#/in. lengthwise of cabin. Fuel Capacity (Without Stoner- Mudge Sealing) 2 inboard inner wing tanks 508 gal. ea. 3048 lbs. ea. (+400.9) 2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea. (+404.1) 2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+404.5) 2 inner fuel cells 362 gal. ea. 2172 lbs. ea. (+397.5) (When Stoner-Mudge Sealing is in corporated, see pertinent report referred to in NOTE 4. Oil Capacity 20 gals. in each inboard nacelle 150 lbs. ea. (+327.0) 20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 50 gals. in fuselage tank 375 lbs. (+223.3) See NOTE 7 regarding fuel load wh en fuselage oil tank is removed. Serial Nos. Eligible 35929 to 36090 Required Equipment 1(a), 100(b), 102(a) , 200, 201, 202, 203, 204, 205, 400, 401 Optional Equipment 1(b), 100(a), (c), (d), (e ), (f) or (g), 101, 102(g) or (h), 402, 500 A-762 7 VII. Model DC-4, Approved June 6, 1946. See NOTE 10 regarding additional speed and load factor limits. Engine See Item 100 Fuel See Item 100 Engine Limits See Item 100 Airspeed Limits See Table “B”, NOTE 9 C.G. Range 16% MAC (381.4) to 32% MAC (407.6). Range based on “landing gear extended” and applies to take-off, flight and landing. See NOTE 8 regarding extension of rear limit for enroute operation. Maximum Weights See Table “A”, NOTE 9. For 3-engine ferrying, see NOTE 13. Minimum Crew 2 - Pilot and Co-pilot at +108.0 Passengers Variable, see a pproved loading schedule. Maximum Baggage Cu. Ft. Weight Arm Forward Belly 130 2100 lbs. (+228.2) Aft Belly 151 2520 lbs. (+590.5) Left Hand Forward (Sta. 171-260) Dwg. 5326973 2210 lbs. (+212.5) or (Sta. 164.5-620) Dwg. 5326376, 5326376-500, 5326791 and 5326646 2320 (+212.5) or (Sta. 218.5-260) Dwg. 5326646 1110 lbs. (+239.3) or (Sta. 193.5-260) Dwg. 5327107 1760 lbs. (+227.3) or (Sta. 129.0-214.5) Dwg. 5326809 1700 lbs. (+171.5) Right Hand Forward (Sta. 184.0-260) Dwg. 5326791, 5327107, 5326810, 5326811, 5338233, 5338179 (Oil Tank Installed) 1300 lbs. (+222.0) or (Sta. 171.5-260) Dwg. 5326646 (Oil Tank Installed) 1470 lbs. (+219.2) or (Sta. 171.0-260) Dwg. 5326376, 5326809 (Oil Tank Installed) 1610 lbs. (+215.5) With Oil Tank Removed, Dwg. 5326376-500, 5326973 2270 lbs. (+215.5) Aft Center Closet (Sta. 828.0-858.0) Dwg. 5326750 200 lbs. (+843.0) Aft Left Closet (Sta. 732.0-806.0) Dwg. 5326171 200 lbs. (+763.0) or (With tiedowns, capacity may be increased to 600 lbs.) (Sta. 742.5-806.5) Dwg. 5326965 200 lbs. (+774.5) or (Sta. 768.5) Dwg. 5326538 200 lbs. (+787.5) or (Sta. 781.5-809.5) Dwg. 5327444 200 lbs. (+770.5) or (Sta. 788.0-812.0) Dwg. 533681, 5240767 200 lbs. (+800.0) Aft Right Closet (Sta. 750.0-806.0) Dwg. 5327319 200 lbs. (+778.0) Cabin Floor Loadings (Do not exceed either value shown) Sta. 129-260 1/2 100#/ft 2 or 50#/in. lengthwise of cabin. Sta. 260 1/2-680 200#/ft 2 or 80#/in. lengthwise of cabin. Sta. 680-858 100#/ft 2 or 30#/in. lengthwise of cabin. Fuel Capacity (Without Stoner- Mudge Sealing) 2 inboard inner wing ta nks 508 gal. ea. 3048 lbs. ea. (+400.9) 2 outboard inner wing tanks 431 gal. ea. 2586 lbs. ea. (+404.1) 2 outer wing tanks 499 gal. ea. 2994 lbs. ea. (+404.5) 2 inner wing fuel cells 362 gal. ea. 2172 lbs. ea. (+397.5) (When Stoner-Mudge Sealing is inco rporated, the actual capacity of each tank must be determined, and airplane placarded accordingly.) Oil Capacity 20 gals. in each inboard nacelle 150 lbs. ea. (+327.0) 20 gals. in each outboard nacelle 150 lbs. ea. (+357.0) 50 gals. in fuselage area 375 lbs. (+223.3) See NOTE 7 regarding fuel load wh en fuselage oil tank is removed. Serial Nos. Eligible 42904 and up Required Equipment 1(a), 100(d), 102(a) , 200, 201, 202, 203, 204, 205, 400, 401. Optional Equipment 1(b), 100(a), (b), (c), (e ), (f), or (g), 101, 102(g), or (h), 402, 500 Specifications Pertinent to All Models Datum 3 inches aft of nose MAC 163.6 in. L.E. of MAC is (+355.2) Leveling Means Leveling brackets are located in th e nose wheel well and aft of the aft belly cargo compartment. The rear leveling br acket may be reached through the access door in the aft bulkhead cargo compartment. Control Surface Rudder  20 Elevators 25  up, 15 down Ailerons 15  up, 11 1/2 down Flaps 45  down All trim tabs  15 Certification Basis Type Certificate No. 762 (Com bination CAR 4a dated November 1, 1943, and 4b dated November 9, 1945) Compliance with the ditching provisions of 4b.292 (4b.261) has been demonstrated. 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: Canada - landplane only eligible Equipment Propellers and Propeller Accessories (Except Deicing Equipment) 1. 4 propellers (a) Ham. Std., hubs 23E50, blades 6507-0 1852 lb. (+262.2) (To be used on P & W engines only) For interchangeable blade models , see Propeller Spec. No. 603 (NOTE 6) Diameter Max 13’3/8”, min. allowable for repairs 12’9” No further reduction permitted Min. low pitch setting at 42 in. sta. 21  Placard required for all P & WA Twin Wasp and R-2000 series engines (See NOTE 2b) A-762 9 Propellers and Propeller Accessories (Except Deicing Equipment) (cont’d) 1. (b) Ham. Std., hubs 23E50, blades 6519-12 1792 lb. (+262.7) (To be used on Wright 736C9HD1 engines only) (See NOTE 2e) For interchangeable blade models , see Propeller Spec. No. 603 (NOTE 6) Diameter Max. 12’1/4”, min. allowable for repairs 11’9 -3/8” No further reduction permitted Min. low pitch setting at 42 in. sta. 21  2. 4 propeller governors (a) Ham. Std. 4G8 26 lb (+277.0) (b) Woodward WH44 or WH45 (Equivalent to Ham. Std. 4G8-P30M) 26 lb. (+277.0) (c) Ham. Std. 5G8 (To be used on Wr ight 736C9HD1 engines only) 38 lb. (+273.0) Engines and Engine Accessories - Fuel and Oil Systems 100. 4 engines (a) P&W 2SD-G or R-2000-7 -2:1 pr opeller reduction gearing 6232 lb. (+275.3) Fuel 100 min. grade aviation gasoline and (+305.1) Limits HP RPM MP In. Hg ALT Low impeller gear ratio 7.15:1 Take-off (2 minutes) 1350 2700 50.0 - - - - Maximum continuous 1100 2550 42.0 S.L. Maximum continuous 1100 2550 41.0 7400’ High impeller gear ratio 8.47:1 Maximum continuous 1000 2550 42.0 10000’ Maximum continuous 1000 2550 41.5 12400’ (Straight line manifold pressu re variation with altitudes shown). Placard required See NOTE 2b (b) P&W 2SD1G or R-2000 -9-2:1 propeller reduction gearing 6288 lb. (+275.3) Fuel 100 min grade aviation gasoline and (+305.1) Limits HP RPM MP In. Hg ALT Low impeller gear ratio 7.15:1 Takeoff (2 minutes) 1450 2700 50.0 - - - - Maximum continuous 1100 2550 38.5 S.L. Maximum continuous 1100 2550 36.5 8300’ High impeller gear ratio 9.52:1 Maximum continuous 1000 2550 39.0 10000’ Maximum continuous 1000 2550 37.5 17700’ (Straight line manifold pressu re variation with altitudes shown) Placard required See NOTE 2b (c) P&W R-2000-11 - 2:1 propeller reduction gearing 6232 lb. (+275.3) Fuel 100 min grade aviation gasoline and (+305.1) Limits HP RPM MP In. Hg ALT Low impeller gear ratio 7.15:1 Takeoff (2 minutes) 1350 2700 46.0 - - - - Maximum continuous 1100 2550 38.5 S.L. Maximum continuous 1100 2550 36.5 8300’ High impeller gear ratio 9.52:1 Maximum continuous 1000 2550 39.0 10000’ Maximum continuous 1000 2550 37.5 17700’ (Straight line manifold pressure variation with altitudes shown) Placard required See NOTE 2b (d) P&W 2SD13G or R-2000-11M2 - 2:1 propeller reduction gearing 6288 lb. (+275.3) Fuel 100 min grade aviation gasoline and (+305.1) Limits HP RPM MP In. Hg ALT Low impeller gear ratio 7.15:1 Takeoff (2 minutes) 1450 2700 50.0 - - - - Maximum continuous 1200 2550 42.0 S.L. Maximum continuous 1200 2550 40.5 5200’ High impeller gear ratio 9.52:1 Maximum continuous 1100 2550 44.0 7000’ Maximum continuous 1100 2550 43.0 15000’ (Straight line manifold pre ssure variation with altitudes shown) Placard required See NOTE 2b Elevator Control Column Balance Weights required per NOTE 8. (e) Wright 736C9HD1 - 16:9 propeller reduction gearing 5440 lb. (+268.2) Fuel 100 min grade aviation gasoline and (+290.8) Limits HP RPM MP In. Hg ALT Low impeller gear ratio 7.21:1 Takeoff (2 minutes) 1425 2700 51.5 S.L. Maximum continuous 1275 2500 46.5 S.L. Maximum continuous 1275 2500 45.5 3500’ High impeller gear ratio 8.69:1 Maximum continuous 1125 2500 44.5 7800’ Maximum continuous 1125 2500 44.5 10600’ (Straight line manifold pre ssure variation with altitudes shown) Placard required See NOTE 2b See NOTE 2(c) regarding removal of cruise restriction Elevator Control Column Balance Weights required per NOTE 8. See NOTE 11 regardi ng installation requirements. (f) P&W D-5 or R-2000-7M2 - 2:1 prope ller reduction gearing 6300 lb. (+275.3) Fuel 100 min grade aviation gasoline and (+305.1) Limits HP RPM MP In. Hg ALT Low impeller gear ratio 7.15:1 Takeoff (2 minutes) 1450 2700 50.0 S.L. Maximum continuous 1200 2550 42.5 S.L. Maximum continuous 1200 2550 41.5 7000’ (Straight line manifold pre ssure variation with altitudes shown.) Placard required See NOTE 2b Elevator Column Balance Weights required per NOTE 8 (g) P & W D-3 -2:1 propeller reduction gearing 6340 lb. (+275.3) Fuel 100 min grade aviation gasoline and (+305.1) Limits HP RPM MP in Hg ALT Low impeller gear ratio 7.15:1 Takeoff (2 minutes) 1450 2700 50.0 S.L. Maximum continuous 1200 2550 42.0 S.L. Maximum continuous 1200 2550 40.5 5200’ (Straight line manifold pre ssure variation with altitudes shown) Placard required See NOTE 2b Elevator Column Balance Weights required per NOTE 8 A-762 11 101. (a) Dump valve installation (Dougl as Dwgs. 5326098, 5327000, 5327001 171 lb (+406.1) 5327006, 5327009, 5327014, 5327025, 5327027, 5327101) (b) Dump valve installation (Douglas Dwg. 5326874) 88 lb (+394.8) (c) Standpipe installation (Douglas Dwgs 5327101F, 5327006E) 2 lb (+411.0) (d) Sandpipe installation (Douglas Dwgs. 5327006E, 5327101F) Delta 1 lb (+411.0) (e) Dump valve installation (Douglas Dwgs. 5327000, 5327001, 5327006, and 5327027) 116 lb (+394.5) 102. System fuel and oil. See NOTE 1b for definition. (a) 8 wing tanks (C54F-DC, C54G-DC, DC-4) 340 lb. (+360.7) (b) 6 wing tanks (C54-DC, C54A-DC, C54B-DC, C54D-DC) 296 lb. (+354.7) (c) 6 wing and 2 fuselage tanks (C54B-DC, C54D-DC) 328 lb. (+349.4) (d) 4 wing tanks and nacelle oil (C54-DC, C54A-DC) 221 lb. (+344.9) (e) 4 wing and 4 fuselage tanks (C54-DC, C54A-DC) 323 lb. (+344.2) (f) 4 wing and 3 fuselage tanks (C54-DC, C54A-DC) 307 lb. (+344.6) (g) 6 wing tanks (C54E-DC, C54G-DC, DC-4) 324 lb. (+358.7) (h) Item 102(a), (b), (c), (e), (f) or (g) when installed less fuselage oil tank may be reduced -38 lb, (+333.1) 119. Nacelle, cowling, contro ls, lines, etc., forward of firewall in changing to Wright 736C9HD1 installation -411 lbs.