TCDS 6A5

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Rev. No. 25 - - - - - - - 24 - - - - - - Page No. 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 Rev. No. - 24 - - - - - - - - - - - - - 24 DEPARTMENT OF TRANSPORATION FEDERAL AVIATION ADMINISTRATION 6A5 Revision 25 LOCKHEED 1049-54 1049B-55 (Navy R7V-1) 1049C-55 1049D-55 1049E-55 1049F-55 (USAF C-121C) 1049G-82 1049H-82 July 23, 2012 AIRCRAFT SPECIFICATION NO. 6A5 This data sheet which is part of Type Certificate No. 6A5 prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Lockh eed Martin Aeronautics Company 86 South Cobb Drive Marietta, GA 30063 Type Certificate Holder Record Lockheed Aircraft Corporation Burbank, California I - Model 1049-53 deleted June 9, 1953. All 1049-53 aircraft converted to Model 1049-54. II - Model 1049-54, Approved May 14, 1952 Engines 4 Wright Cy clones 975C18CB-1 with 16:7 reduction gear ratio Fuel AN grade 115/145 (See NOTE 15 for e ngine limits when using low grade fuel) Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 48.0 in.hg., 2600 rpm (2400 hp) (Straight line manifold pressu re variation with altitude to 5300 ft.) 46.0 in. hg., 2600 rpm (2400 hp) Take-off (2 minutes): (Sea level) 54.5 in.hg., 2900 rpm (2800 hp) (Straight line manifold pressu re variation with altitude to 4500 ft.) 52.5 in.hg., 2900 rpm (2800 hp). High impeller ratio 8.67:1 Maximum continuous: (10,800 ft.) 47.5 in.hg., 2600 rpm (2000 hp) (Straight line manifold pressure variation with altitude to 16,000 ft.) 46.0 in.hg., 2600 rpm (2000 hp). Airspeed limits Vno (Normal Opera tion) 300 mph (260 knots) True Ind. (Above 11,000' reduce speed 10 mph ( 9 knots) for each additional 2000') Vne (Never Exceed) 338 mph (293 knots) True Ind. (Above 11,000' reduce speed 12 mph ( 11 knots) for each additional 2000') Va (Maneuvering) 208 mph (180 knots) True Ind. Vf (Takeoff position-60%) 212 mph (184 knots) True Ind. 6A5 2 Vf (Approach position-66%) 186 mph (161 knots) True Ind. Vf (80%) 177 mph (153 knots) True Ind. Vf (Landing position-100%) 171 mph (148 knots) True Ind. Vlo (Landing Gear Operati on) 190 mph (165 knots) True Ind. Vle (Landing Gear Extensi on) 190 mph (165 knots) True Ind. Mach No. - Never Exceed .54 C.G. range See NOTE 1(b) for required loading and gear retraction moment. Condition Weight Landing Fwd. Limit Aft. Limit lbs. gear sta. %MAC sta. %Mac Take-off 120,000* Down 665.8* 21.0 685.2 32.0 98,500* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 98,500 Down 660.5 18.0 685.2 32.0 o r l e s s Cruising 120,000* Up 661.5* 18.6 688.7 34.0 Flight 98,500* Up 655.2* 15.0 688.7 34.0 o r l e s s * Straight line variation between these values. Weight limits Landing 98,500 lb s. See NOTE 8 for higher weight (See NOTE 15 for Take-off 120,000 lbs. (Dump valves are required) limits when using Maximum zero fuel weight 93,500 lbs. S ee NOTES 1(e) for fuel loading and 8 for low grade fuel) higher weight. 3-engine ferrying 100,000 lbs. See FAA Approved Airplane Flight Manual for applicable restrictions. Minimum crew 3. Pilot and Copilot at +190 and Flight Engineer at +226. Passengers Maximum 88 (CAR 4b.433). See Appr oved Weight and Balance Report for actual number and location. Baggage Maximum capacity of internal baggage and storage compartments: Vol. Max. Floor Cap. Compt. (cu. ft.) loading psf (lbs. ) C.G. Fwd. cargo compartment, fwd. portion F.S. 333.6 to 482 72 70 1440 (+407.8) Fwd. cargo compartment, aft portion F.S. 482 to 638 194 70 3880 (+560) Aft cargo compartment, fwd. portion F.S. 750 to 932 230 70 4600 (+841) Aft cargo compartment, aft portion F.S. 932 to 1139.8 160 70 3200 (+1036) -67 interior Left hand fwd. 450 (+ 497) Right hand fwd. 700 (+ 497) Left hand aft 600 (+1150) Wash water, -67 interiors 209 (+1075) Galley water, -67 interiors 125 (+ 380) Galley installation and supplie s, 67 interiors 45 (a) (a) Galley areas between Stations 260 a nd 343.5 are structurally satisfactory for a uniformly distributed load over the en tire area of 45 psf or a uniformly distributed load of 55 psf on each side of the 20 inch aisle. Galley installations and their contents shall not exceed these loadings. Fixed equipment such as galleys shall be listed on the Approved Equipment List together with pertinent weights and arms. Fuel capacity See NOTE 1(c) regard ing "Usable fuel and System Oil." Tanks 2 and 3 (inboard) ( 790 gal. ea.) 9,480 lbs. (+692) Tanks 1 and 4 (middl e) (1555 gal. ea.) 18,660 lbs. (+689) Tanks 2a and 3a (outboard) ( 565 gal. ea.) 6,780 lbs. (+687) Tank 5 (center section ( 730 gallons ) 4,380 lbs. (+694) when installed) Oil capacity See NOTE 1(c) regardi ng "Unusable Fuel and System Oil." 3 6A5 (a) (2 inboard tanks (with aux. tank) and (58 gal.ea.) 870 lbs. (+584) (2 outboard tanks (with aux. tank); or (58 gal.ea.) 870 lbs. (+603). (b) (2 inboard tanks (without aux. tank) and (55 gal.ea.) 825 lbs. (+584) (2 outboard tanks (without aux. tank) (55 gal.ea.) 825 lbs. (+603). Serial Nos. eligible 1049/4001 th rough 1049/4024 (See Equipment Item 400) Required equipment In addition to th e pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: Items 1(a) or (c); 101(a) or (b); 103(a ); 104(a); 105(a); 107(a) or (b); 200(a) or (b); 201(a); 202(a)(1), (2) or (3); 203(a) or (b); 204(a)(1), (a)(2) or (b)(1); 205(a) or (b); 206(a) or (b); 300(a); 301(a); 303(a) or (b); 400; 440; 441(a) or (b); 508(a). III - Model 1049B-55 (Navy R7V-1), Approved October 28, 1953. (Same as Model 1049-54 except engines, design weights, and certain structural changes. This airplane is basically a cargo rather than passenger carrier) (See NOTE 5 for modifications necessary for civil conversion of R7V-1). Engines 4 Wright Cyclones 972TC18DA1 with 16:7 reduction gear ratio and 6.52:1 Turbo drive r a t i o . Fuel AN grade 115/145 (See NOTE 16 for e ngine limits when using low grade fuel) Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 47.5 in.hg., 2600 rpm (2600 hp) (Straight line manifold pressure vari ation with altitude to 6500 ft.) 45.0 in. hg., 2600 rpm (2650 hp) Takeoff (2 minutes): (Sea level) 56.5 in.hg., 2900 rpm (3250 hp) (Straight line manifold pressure vari ation with altitude to 5000 ft.) 53.0 in.hg., 2900 rpm (3250 hp). High impeller ratio 8.67:1 Maximum continuous: (9,550 ft.) 48.5 in.hg., 2600 rpm (2400 hp) (Straight line manifold pressure vari ation with altitude to 16,400 ft.) 47.0 in.hg., 2600 rpm (2450 hp). Airspeed limits Vno (Normal Opera tion) 300 mph (260 knots) True Ind. (Above 12,500' reduce speed 11 mph ( 10 knots) for ea. additional 2000') Vne (Never Exceed) 338 mph (293 knots) True Ind. (Above 12,500' reduce speed 13 mph ( 11 knots) for ea. additional 2000') Va (Maneuvering) 218 mph (189 knots) True Ind. Vf (Takeoff position-60%) 220 mph (191 knots) True Ind. Vf (Approach position-66%) 200 mph (174 knots) True Ind. Vf (80%) 200 mph (174 knots) True Ind. Vf (Landing position-100%) 180 mph (156 knots) True Ind. Vlo (Landing Gear Operati on) 190 mph (165 knots) True Ind. Vle (Landing Gear Extensi on) 190 mph (165 knots) True Ind. Mach No. - Never Exceed .56 C.G. range See NOTE 1(b) for required loading and gear retraction moment. Condition Weight Landing Fwd. Limit Aft. Limit lbs. gear sta. %MAC sta. %Mac Take-off 135,000* Down 667.2* 21.0 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 110,000* Down 661.6 18.0 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 133,000* Up 665.8* 21.0 688.7 34.0 Flight 90,000* Up 655.2* 15.0 688.7 34.0 o r l e s s * Straight line variation between these values. 6A5 4 Weight limits Landing 110,000 lbs. (See NOTE 16 for Takeoff 133,000 lbs. # with auto-feathe ring (Dump valves are required.) See limits when using Equipment Item 1 (b), or (c) or (d) for takeoff weight low grade fuel) with auto feathering inoperative. #130,000 lbs. for serial No s. 4101 through 4139 unless modified in accordance with NOTE 6. Maximum zero fuel weight 105,000 lb s. See NOTE 1(e) for fuel loading. 3-engine ferrying 100,000 lbs. See FAA Approved Airplane Flight Manual for applicable restrictions. Minimum crew 3. Pilot and Co-pilot at +190 and Flight Engineer at +226. Passengers All Serial Numbers originally cer tificated as cargo carriers. See NOTE 9 for conversion to pa ssenger configuration. Maximum cargo Maximum Maximum Floor Compartment Station Cap. (lbs.) loading psf Arm C (Main Cabin) 260-287 1000** 300 274 D (Main Cabin) 287-370 3900 300 329 E (Main Cabin) 370-444 6100 300 408 F (Main Cabin) 444-509 5400 300 477 G (Main Cabin) 509-583 6100 300 546 H (Main Cabin) 583-656 6100 300 620 I (Main Cabin) 656-732 6300 300 694 J (Main Cabin) 732-806 6100 300 769 K (Main Cabin) 806-879 6100 300 842 L (Main Cabin) 879-953 6100 300 916 M (Main Cabin) 953-1026 6100 300 989 N (Main Cabin) 1026-1158 7200 300 1089 O (Main Cabin) 1158-1258 2900 300 1198 Q (Lower Cargo Compt) 334-482 2800 70 402 R (Lower Cargo Compt) 482-638 5040 70 558 S (Lower Cargo Compt) 750-932 5950 70 821 T (Lower Cargo Compt) 932-1140 6370 70 1004 Maximum combined accumu lated load of both cabin and lower cargo compartments from extremities of cabin toward main frames: Forebody Afterbody From Sta. 260 to From Sta. 1258 forward to: Sta. 287 300 lbs. Sta. 1158 2,900 lbs. Sta. 370 3,900 lbs. Sta. 1026 7,200 lbs. Sta. 444 6,900 lbs. Sta. 953 9,800 lbs. Sta. 509 9,700 lbs. Sta. 879 14,100 lbs. Sta. 583 14,700 lbs. Sta. 806 18,300 lbs. Sta. 656 20,800 lbs. Sta. 732 23,500 lbs. ** Including radio and galley equipment (700#) in compartment C. All cargo loading must be secured with the tie-downs provided since there are no restraining or crash bulkhead provisions. Fuel capacity See NOTE 1(c) regard ing "Unusable Fuel & System Oil." Tanks 2 and 3 (inboard) ( 790 gal. ea.) 9,480 lbs. (+692). Tanks 1 and 4 (middle) (1555 gal. ea.) 18,660 lbs. (+689) Tanks 2a and 3a (outboard) ( 565 gal. ea.) 6,780 lbs. (+687). Tank 5 (center section) ( 730 gallons) 4,380 lbs. (+694) 5 6A5 Oil capacity See NOTE 1(c) regardi ng "Unusable Fuel & System Oil." 2 inboard tanks (40 gal. ea.) 600 lbs. (+634) 2 outboard tanks (40 gal. ea.) 600 lbs. (+636) 1 auxiliary cell (center section) (67 gallons) 502 lbs. (+674) Serial Nos. eligible 1049B/4101 through 1049B/4111; 1049B/4122 through 1049B/4130; 1049B/4133 through 1049B/4150; 1049B/4152 through 1049B/4160; and 1049B/4167 through 1049B/4169. Required equipment In addition to th e pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: Items 1(b), (c) or (d); 101(c), (d), (e), (f), (g) or (h); 103(b) or (c); 104(b) or (c); 105(a); 107(b); 200(b); 201(a); 202(a)(2) or (3); 203(b); 204(a)(1), (a)(2) or (b)(1); 205(a) or (b); 206(a) or (b); 300(b); 301(a); 303(c) or (e); 400; 440; 441(e); 508(a). IV - Model 1049C-55, Approved June 9, 1953, and Model 1049E-55, Approved May 26, 1954. (Same as Model 1049-54 except engines, design weights, structural changes of wings, fuselage, nacelles and landing gear, and installation of sealed "Class D" lower cargo compartments. The Model 1049E-55 is the same as the Model 1049C-55 with miscellaneous structural revisions.) Engines 4 Wright Compound 972TC18DA1 with 16:7 reduction gear ratio and 6.52:1 Turbo drive ratio. (Also eligible with 972TC18DA3, 988TC18EA3, and 988TC18EA6. See Item 111 for engine limits with these engines) Fuel AN grade 115/145 (See NOTE 16 for e ngine limits when using low grade fuel) Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 47.5 in.hg., 2600 rpm (2600 hp) (Straight line manifold pressure va riation with altitude to 6500 ft.) 45.0 in. hg., 2600 rpm (2650 hp) Takeoff (2 minutes at sea level; 5 minutes at 7500 ft.; straight line variation of takeoff power time with altitude to 7500 ft.): (Sea level) 56.5 in.Hg., 2900 rpm (3250 hp) (Straight line manifold pressure vari ation with altitude to 5000 ft.) 53.0 in.Hg., 2900 rpm (3250 hp) High impeller ratio 8.67:1 Maximum continuous: (9550 ft.) 48.5 in.hg., 2600 rpm (2400 hp) (Straight line manifold pressure vari ation with altitude to 16,400 ft.) 47.0 in.hg., 2600 rpm (2450 hp). Airspeed limits Vno (Normal Opera tion) 300 mph (260 knots) True Ind. (Above 12,500' reduce speed 11 mph ( 10 knots) for each additional 2000') Vne (Never Exceed) 338 mph (293 knots) True Ind. (Above 12,500' reduce speed 13 mph ( 11 knots) for each additional 2000') Va (Maneuvering) 218 mph (189 knots) True Ind. Vf (Takeoff position-60%) 220 mph (191 knots) True Ind. Vf (Approach position-66%) 200 mph (174 knots) True Ind. Vf (80%) 200 mph (174 knots) True Ind. Vf (Landing position-100%) 180 mph (156 knots) True Ind. Vlo (Landing Gear Operati on) 190 mph (165 knots) True Ind. Vle (Landing Gear Extensi on) 190 mph (165 knots) True Ind. Mach No. - Never Exceed .56 6A5 6 C.G. range See NOTE 1(b) for required loading and gear retraction moment. Condition Weight Landing Fwd. Limit Aft.Limit lbs. gear sta. %MAC sta. %Mac Take-off 133,000* Down 670.3* 23.5 685.2 32.0 90,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 110,000* Down 664.9 20.5 685.2 32.0 90,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 133,000* Up 665.8* 21.0 688.7 34.0 Flight 90,000* Up 655.2* 15.0 688.7 34.0 o r l e s s * Straight line variation between these values. Weight limits Landing 110,000 lbs. S ee NOTE 13 for higher landing weight. (See NOTE 16 for Takeoff 133,000 lbs. with autofeat hering (Dump valves are required. limits when using See Equipment Item 1(b), (c), (d), (e) or (f) low grade fuel.) for takeoff weight with autofeathering inoperative, and NOTE 7 for takeoff weight when oil transfer system is not installed. See NOTE 12 for higher takeoff weight. Maximum zero fuel weight 103,500 lb s. See NOTE 1(e) for fuel loading. 3-engine ferrying 100,000 lbs. See FAA Approved Airplane Flight Manual for applicable restrictions. Minimum crew 3. Pilot and Co-pilot at +190 and Flight engineer at +226. Passengers Maximum 99 occupant s (passengers plus crew) (CAR 4b.433 and SR 389 effective October 27, 1952.) See Approved Wei ght and Balance Report for actual number and location. Baggage Maximum capacity of intern al baggage and storage compartments: Vol. Max. Floor Cap. Compt. (cu. ft.) loading psf (lbs. ) C.G. (A) Fwd. cargo compartment, fwd. portion F.S. 334 to 482 77 70 1500 (+402) (B) Fwd. cargo compartment, aft portion F.S. 482 to 638 194 70 3880 (+558) (C) Aft cargo compartment, fwd. portion F.S. 750 to 932 230 70 4600 (+821) (D) Aft cargo compartment, aft portion F.S. 932 to 1140 194 70 3880 (+1004) Coat closet 200 (+1000) Coat closets L. & R. 400 (+1165) Wash water 500 (+ 980) Galley areas between Stations 930 and 1014 and 10" from airplane centerline R.H. side is structurally satisfactory for a maximum total load of 2,300 pounds, with a maximum unit floor loading of 70 pounds per square foot. Galley storage area between Stations 930 and 950 and 10" from airplane centerline L.H. side is structurally satisfactory for a maximum total load of 500 pounds with a maximum unit floor loading of 90 pounds per square foot. Cabin Cargo Compartment A (optiona l) Fus. Sta. 260-339 R.H. 900 (+309) Cabin Cargo Compartment B ( optional) Fus. Sta. 339-467.5 5200* (+403) *With lower cargo Compartment A empty. Maximu m capacity must be decreased by the amount of any load carried in lo wer cargo Compartment A. 7 6A5 Fuel capacity See NOTE 1(c) regard ing "Usable fuel and System Oil." Tanks 2 and 3 (inboard) ( 790 gal. ea.) 9,480 lbs. (+692) Tanks 1 and 4 (middle) (1555 gal. ea.) 18,660 lbs. (+689) Tanks 2a and 3a (outboard) ( 565 gal. ea.) 6,780 lbs. (+687) Tank 5 (center section) ( 730 gal. ea.) 4,380 lbs. (+694) Oil capacity See NOTE 1(c) regardi ng "Unusable Fuel and System Oil." 2 inboard tanks (40 gal. ea.) 600 lbs. (+634) 2 outboard tanks (40 gal. ea.) 600 lbs. (+636). 1 auxiliary cell (center sect.) (67 gal. ea.) 502 lbs. (+674) Serial Nos. eligible 1049C/4501 through 1049C/4548; 1049E/4549 through 1049E/4665, 1049E/4573, 1049E/4574; 1049E/4578 through 1049E/4581; 1049E/4606, 1049E/4607; 1049E/4613 through 1049E/4615. Required equipment In addition to th e pertinent required basic equipment specified in CAR 4b, the following items of equipment must be installed: Items 1(b), (c), (d), (e) or (f); 101(c), (d ), (e), (f), (g) or (h); 103(b) or (c); 104(b) or (c); 105(a); 107(b); 200(b); 201(a); 202(a)(2 ) or (3); 203(b); 204(a)(1), (a)(2) or (b)(1); 205(a) or (b); 206(a) or (b); 300(b); 301( a); 303(c) or (e); 400; 440; 441(c), (d) or (f); 508(a). V - Model 1049D-55, Approved August 12, 1954. (Same as Model 1049B-55 except for passenger seat installation, additional emergency exits are installed, and the lower cargo compartments are Class D per CAR 4b-383(d).) Engines 4 Wright Compound 972TC18DA1 with 16:7 reduction gear ratio and 6.52:1 Turbo drive ratio. (Also eligible with 972TC18DA3, 988TC18EA3 and 988TC18EA6. See Item 111 for engine limits with these engines) Fuel AN grade 115/145 (See NOTE 16 for e ngine limits when using low grade fuel) Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 47.5 in.hg., 2600 rpm (2600 hp) (Straight line manifold pressure va riation with altitude to 6500 ft.) 45.0 in. hg., 2600 rpm (2650 hp) Takeoff (2 minutes at sea level; 5 minutes at 7500 ft.; straight line variation of ta keoff power time with altitude to 7500 ft.): (Sea level) 56.5 in.hg., 2900 rpm (3250 hp) (Straight line manifold pressure va riation with altitude to 5000 ft.) 53.0 in.hg., 2900 rpm (3250 hp). High impeller ratio 8.67:1 Maximum continuous: (9550 ft.) 48.5 in.hg., 2600 rpm (2400 hp) (Straight line manifold pressu re variation with altitude to 16,400 ft.) 47.0 in.hg., 2600 rpm (2450 hp). Airspeed limits Vno (Normal Opera tion) 300 mph (260 knots) True Ind. (Above 12,500' reduce speed 11 mph ( 10 knots) for each additional 2000') Vne (Never Exceed) 338 mph (293 knots) True Ind. (Above 12,500' reduce speed 13 mph ( 11 knots) for each additional 2000') Va (Maneuvering) 218 mph (189 knots) True Ind. Vf (Takeoff position-60%) 220 mph (191 knots) True Ind. Vf (Approach position-66%) 200 mph (174 knots) True Ind. Vf (80%) 200 mph (174 knots) True Ind. Vf (Landing position-100%) 180 mph (156 knots) True Ind. Vlo (Landing Gear Operati on) 190 mph (165 knots) True Ind. Vle (Landing Gear Extensi on) 190 mph (165 knots) True Ind. Mach No. - Never Exceed .56 6A5 8 C.G. range See NOTE 1(b) for required loading and gear retraction moment. (A) Passenger or Mi xed Cargo-Passenger Loading Condition Weight Landing Fwd. Limit Aft.Limit lbs. gear sta. %MAC sta. %Mac Take-off 133,000* Down 670.23* 23.5 685.2 32.0 90,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 110,000* Down 661.6* 20.5 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 133,000* Up 665.8* 21.0 688.7 34.0 Flight 90,000* Up 655.2* 15.0 688.7 34.0 o r l e s s *Straight line variation between these values. (B) All Cargo Loading Condition Weight Landing Fwd. Limit Aft.Limit lbs. gear sta. %MAC sta. %Mac Take-off 133,000* Down 670.23* 21.8 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Landing 110,000* Down 661.6* 18.6 685.2 32.0 105,000* Down 660.5* 18.0 685.2 32.0 o r l e s s Cruising 133,000* Up 665.8* 21.0 688.7 34.0 Flight 90,000* Up 655.2* 15.0 688.7 34.0 o r l e s s *Straight line variation between these values. Weight limits Landing 110,000 lbs. (See NOTE 11 for Takeoff 133,000 lbs. with autofeat hering (Dump valves are required. higher weights; See Equipment Item 1(b), (c), (d), (e) or (f) NOTE 16 for weight for takeoff weight with autofeathering inoperative, limits when using low and NOTE 7 for takeoff weight when oil transfer grade fuel; NOTE 19 system is not installed. Maximum zero fuel weight for application of SR-411A) 105,000 lbs. See NOTE 1(e) for fuel loading. 3-engine ferrying 100,000 lbs. See FAA Approved Airplane Flight Manual for applicable restrictions. Minimum crew passengers 3. Pilot and Copilot at +190 and Flight Engineer at +226. Maximum 112 occupants (passengers plus crew) (CAR 4b. 433 and SR 389 effective October 27, 1952.) See approved Weight and Balan ce Report for actual number and location. 9 6A5 Maximum cargo Ma ximum Maximum Floor Compartment Station Cap. (lbs.) loading psf Arm A (Main Cabin) 260-339 2900 300 300 B (Main Cabin) 339-444 7200 300 392 C (Main Cabin) 444-509 5400 300 477 D (Main Cabin) 509-583 6100 300 546 E (Main Cabin) 583-656 6100 300 620 F (Main Cabin) 656-732 6300 300 694 G (Main Cabin) 732-806 6100 300 769 H (Main Cabin) 806-879 6100 300 842 I (Main Cabin) 879-953 6100 300 916 J (Main Cabin) 953-1026 6100 300 989 K (Main Cabin) 1026-1158 7700 300 1089 L (Main Cabin) 1158-1258 3400 300 1198 A (Lower Cargo Compt) 334-482 2800 70 402 B (Lower Cargo Compt) 482-638 5040 70 558 C (Lower Cargo Compt) 750-932 5950 70 821 D (Lower Cargo Compt) 932-1140 6370 70 1004 Maximum combined accu mulated load of both cabin and lower cargocompartments from extremities of cabin toward main frames: Forebody Afterbody From Sta. 260 to: From Sta. 1258 forward to: Sta. 339 2,900 lbs. Sta. 1158 3,400 lbs. Sta. 444 7,200 lbs. Sta. 1026 7,700 lbs. Sta. 509 10,000 lbs. Sta. 953 10,300 lbs. Sta. 583 15,000 lbs. Sta. 879 14,600 lbs. Sta. 656 21,100 lbs. Sta. 806 18,800 lbs. Sta. 732 24,000 lbs. All cargo loading must be secured with the tie-downs provided since there are no restraining or crash bulkhead provisions. Fuel capacity See NOTE 1(c) regard ing "Unusable Fuel & System Oil." Tanks 2 and 3 (inboard) ( 790 gal. ea.) 9,480 lbs. (+692). Tanks 1 and 4 (middle) (1555 gal. ea.) 18,660 lbs. (+689) Tanks 2a and 3a (outboard) ( 565 gal. ea.) 6,780 lbs. (+687). Tank 5 (center section) ( 730 gallons) 4,380 lbs. (+694) Oil capacity See NOTE 1(c) regardi ng "Unusable Fuel & System Oil." 2 inboard tanks (40 gal. ea.) 600 lbs. (+634) 2 outboard tanks (40 gal. ea.) 600 lbs. (+636) 1 auxiliary cell (center section) (67 gallons) 502 lbs. (+674) Serial Nos. eligible 1049D/4163 through 1049D/4166