TCDS A1SO

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Rev. No. 17 10 9 11 9 10 11 10 11 10 10 11 13 13 17 17 16 Page No. 18 19 20 21 22 23 Rev. No. 17 17 14 17 17 17 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A1SO Revision 17 LOCKHEED 382 382B 382E 382F 382G 382J November 15, 2019 TYPE CERTIFICATE DATA SHEET NO. A1SO This data sheet, which is a part of Type Certificate No. A1SO, prescribes conditions and limitations under which the product, for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Lockheed Martin Corporation Lockheed Martin Aeronautis Company 86 South Cobb Drive Marietta, Georgia 30063-0655 I. - Model 382 (Hercules) Transport Category Aircraft), Approved 16 February 1965 (See NOTE 5.) Engines 4 Allison Turbo-prop 501-D22A ` Engine Type Certificate No. E-282 Fuel Commercial aviation turbine fuels conforming to ASTM Specification No. D1655-59T, types Jet B, Jet A-1, or Jet A, or commercial equivalents of MIL-J-5624, grade JP-4 or JP-5. Lubricating Oil Synthetic oil conforming to Allison Commercial Service Letter CSL-1002 Engine Limits Static, standard day, sea level: Turbine Inlet Temp. Torque Oil Temp Take-off (5 minutes) 19,600 in. lb. 40°C - 100°C 1077°C Maximum continuous 1010°C 19,600 in.lb. 60°C - 85°C Rated Speed: 100% - 13,820 erpm Propeller and Propeller Limits 4 Hamilton Standard hydromatic propellers Hub 54H60-91/54H60-117 Blade A7111D-2 Propeller Type Certificate No. P-906 Diameter: 13 ft. 6 in. 2% reduction allowable for repair Single rotation, four blade assembly with governing speed setting 1020 prpm (13,820 erpm). Propeller assembly is complete with spinner, feathering and reversing provision, constant speed control, negative torque control, synchrophaser, and electrical ice control. A1SO 2 of 23 Blade angles See NOTE 3 Feather 92.5° ± 0.20° (a) (b) Low pitch stop (min. flt. Idle) 23.25° ± 0.50° (a) Ground start 4.75° ± 0.75° (b) Ground idle 1.0° ± (c) Reverse -7.0 ± 1.0° (b) Propeller Oil MIL-H-5606B Airspeed Limits VMO Maximum operating) See Fig. 1-2 VA (Maneuvering) of approved VB (Turbulent air penetration) Airplane Flight Manual VFE (Take-off & approach, 50%) 183K VFE (Landing, 100%) 145K VLO (Landing gear operation) 168K VLE (Landing gear extended) 168K VLL (Landing light extended) 168K Heated Windshield Limitations If electric windshield heat is operative, it must be used for all flight operations. Operation without electric windshield heat, on any or all portions of the windshield, is permissible provided (1) the airplane is not flown in known icing conditions, and (2) the maximum speed limit below 10,000 ft. is 187 KCAS. Weight & C.G. Limits Most Fwd. C.G. Most Aft C.G. (gear up or down) Condition Wt./lbs. %MAC F.S. %MAC F.S. Ramp 155,800 23.3 525.7 30 536.8 Take-off 155,000 23.2 525.5 30 536.8 Landing 130,000 20.2 520.6 30 536.8 Zero fuel 120,000 18.8 518.3 30 536.8 Datum Trim Station -493.0 (F.S. 94.0), W.L. 142.98, B. L. O.O. (NAS 221 screw head on bottom of forward fuselage, 71.0" forward of center of line of nose gear strut.) M.A.C. 164.5"; leading edge M.A.C. Trim Station -39.6 (F.S. 487.4) Leveling Means Provisions for leveling by plumb line are installed in the cargo compartment on the left side at approximately Trim Station +110 (F.S. 637). A plumb line support bracket is located on the fuselage side panel at approximately W.L. 252, B.L. 64L, and a leveling plate is located on top of the cargo floor curb at approximately W.L. 150 B.L. 64L. Minimum Crew Three (3) - Pilot, Co-pilot, and Flight Engineer Passengers None. Approved for cargo only. Cargo Compartment Length 48.3 Width 9 ft/. 11½ in. Height 9 ft. Usable volume 4,536 cu. ft. Maximum cargo See SMP 521-2. 3 of 23 A1SO Loading data for approved loading schedule are contained in Lockheed Report ER-9511. Individual aircraft weight and balance data are contained in Lockheed Report SMP 521-2. Class E cargo compartment. Cargo must be loaded in compliance with loading placard, Lockheed Drawing 398251-1. When cargo restraining (barrier) net is installed, the 393487-15 placard is a required part of the installation. Maximum Fuel Quantity Tank Usable Fuel Total Fuel F.S. Arm (full) (T.S.) 1 (outboard) 9,238 lbs. 9,331 lbs. 545.2 +18.2 2 (inboard) 8,437 lbs. 8,578 lbs. 555.0 +28.0 3 (inboard) 8,437 lbs. 8,578 lbs. 555.0 +28.0 4 (outboard) 9,238 lbs. 9,331 lbs. 545.2 +18.2 ** Left Aux. 6,269 lbs. 6,329 lbs. 556.7 +29.7 ** Right Aux. 6,269 lbs. 6,329 lbs. 556.7 +29.7 *** Left External 9,355 lbs. 9,465 lbs. 551.2 +24.2 *** Right External 9,355 lbs. 9,465 lbs. 551.2 +24.2 *** 66,598 lbs. *67,406 lbs. (549.9) **** Left External 9,355 lbs. 9,499 lbs. 551.2 +24.2 **** Right External 9,355 lbs. 9,499 lbs. 551.2 +24.2 **** 66,598 lbs. *67,474 lbs. (549.9) * Does not include line fuel. (See NOTE 1(c)). ** Optional tank installations. *** Optional external tank installation (Lockheed P/N 388236) **** Optional external tank installation (Lear Siegler P/N 305J001) Maximum fuel quantity These fuel weights are not to be exceeded. (Tank volume may be calculated using fuel density of 6.9 lbs./gal.) Arm varies with fuel loading. Reference loading data, Lockheed Report SMP 521-2, for approved fuel loading information. See NOTE 1 for unusable fuel. Oil Capacity Four (4) independent tanks, one in each nacelle above the engine (Arm 442.0, Trim Station -85.0). Capacity for each, 8 gallons usable, total 12 gallons. Capacity for all, 32 gallons usable, total 48 gallons. See NOTE 1 for system oil. Maximum operating altitude 32,600 feet Other operating limitations Aircraft shall be operated in compliance with the operating limitations specified in the FAA approved Airplane Flight Manual. Manufacturer's Serial 3946 is a Model 382 and is only aircraft numbers eligible by incorporation of STC ST396SO. (See NOTE 5). II. Model 382B (Hercules) (transport aircraft), approved 5 October 1965 (See NOTE 5) Engines 4 Allison turbo-prop 501-D22 Engine Type Certificate No. E-282 Fuel Commercial aviation turbine fuels conforming to ASTM Specification No. D1655-59T, types Jet B, Jet A-1, or Jet A, or commercial equivalents of MIL-J-5624, grade JP-4, or JP-5. Lubricating Oil Synthetic oil conforming to Allison Commercial Service Letter CSL-1002 A1SO 4 of 23 Engine limits Static, Standard day, sea level: Turbine Inlet Temp. Torque Oil Temp Take-off (5 minutes) Model 382B 977°C 19,600 in. lb. 40°C - 100°C Maximum continuous 932°C 18,000 in.lb. 60°C - 85°C Rated Speed: 100% - 13,820 erpm Propeller and Propeller Limits 4 Hamilton Standard hydromatic propellers Hub 54H60-91/54H60-117 Blade A7111C-2/A7111D-2 Propeller Type Certificate No. P-906 Diameter: 13 ft. 6 in. 2% reduction allowable for repair Single rotation, four blade assembly with governing speed setting 1020 prpm (13,820 erpm). Propeller assembly is complete with spinner, feathering and reversing provision, constant speed control, negative torque control, synchrophaser, and electrical ice control. Blade angles See NOTE 3 Feather 92.5° ± 0.20° (a) (b) Low pitch stop (min. flt. idle) 23.25° ± 0.50° (a) Ground start 4.75° ± 0.75° (b) Ground idle 1.0° (c) Reverse -7.0° ± 1.0° (b) Propeller Oil MIL-H-5606B Airspeed Limits VMO (Maximum operating) See Fig. 1-2 VA (Maneuvering) of approved VB (Turbulent air penetration) Airplane Flight Manual VFE (Take-off & approach, 50%) 183K VFE (Landing, 100%) 145K VLO (Landing gear operation) 168K VLE (Landing gear extended) 168K VLL (Landing light extended) 168K Heated windshield limitations If electric windshield heat is operative, it must be used for all flight operations. Operation without electric windshield heat, on any or all portions of the windshield, is permissible provided (1) the airplane is not flown in known icing conditions, and (2) the maximum speed limit below 10,000 ft. is 187 KCAS. Weight & C.G. Limits Condition Wt./lbs. Most Fwd. C.G. Most Aft C.G. (gear up or down) %MAC F.S. %MAC F.S. Ramp 155,800 23.3 525.7 30 536.8 Take-off 155,000 23.2 525.5 30 536.8 Landing 130,000 20.2 520.6 30 536.8 Zero fuel 117,943 18.4 517.6 30 536.8 The above weights pertain to an aircraft configuration which does not have pylon tanks installed. Consult the FAA approved Airplane Flight Manual for proper weight and center-of-gravity restrictions. 5 of 23 A1SO Datum Trim Station - 493.0 (F.S. 94.0), W.L. 142.98, B.L. 0.0 (NAS 221 screw head on bottom of forward fuselage, 71.0" forward of center line of nose gear strut.) M.A.C. 164.5"; leading edge M.A.C. Trim Station -39.6 (F.S. 487.4) Leveling Means Provisions for leveling by plumb line are installed in the cargo compartment on the left side at approximately Trim Station +110 (F.S. 637). A plumb line support bracket is located on the fuselage side panel at approximately W.L. 252, B.L. 64L, and a leveling plate is located on top of the cargo floor curb at approximately W.L. 150, B.L. 64L. Minimum Crew Three (3) - Pilot, Co-pilot, and Flight Engineer. See AFM for fourth member of some versions. Passengers None. Approved for cargo only. Cargo compartment Length 40 ft. Width 9 ft. 11½ in. Height 9 ft. Usable Volume 3,780 cu. ft. Maximum cargo See SMP 521. Loading data for approved loading schedules are contained in Lockheed Report ER-8083. Individual aircraft weight and balance data are contained in Lockheed Report SMP 521. Class E cargo compartment. Cargo must be loaded in compliance with loading placard, Lockheed Drawing 393487-11. When cargo restraining (barrier) net is installed, the 393487-11 placard is a required part of the installation. Maximum fuel quantity Aircraft S/N 4101 through 4581. See NOTE 9 for aircraft S/N 4582 and up. Tank Usable Fuel Total Fuel F.S. Arm (Full) T.S. 1 (outboard) 9,238 lbs. 9,331 lbs. 545.2 +18.2 2 (inboard) 8,437 lbs. 8,578 lbs. 555.0 +28.0 3 (inboard) 8,437 lbs. 8,578 lbs. 555.0 +28.0 4 (outboard) 9,238 lbs. 8,331 lbs. 545.2 +18.2 ** Left Aux. 6,269 lbs. 6,329 lbs. 556.7 +29.7 ** Right Aux. 6,269 lbs. 6,329 lbs. 556.7 +29.7 *** Left External 9,355 lbs. 9,465 lbs. 551.2 +24.2 *** Right External 9,355 lbs. 9,465 lbs. 551.2 +24.2 66,598 lbs. *67,406 lbs. (549.9) **** Left External 9,355 lbs. 9,499 lbs. 551.2 +24.2 **** Right External 9,355 lbs. 9,499 lbs. 551.2 +24.2 **** 66,598 lbs. *67,474 lbs. (549.9) * Does not include line fuel (See NOTE 1 (c)). ** Optional tank installations. *** Optional external tank installation (Lockheed P/N 388236) **** Optional external tank installation (Lear Siegler P/N 305J001) The above fuel weights are not to be exceeded (Tank volume may be calculated using fuel density of 6.9 lbs./gal.) Arm varies with fuel loading. Reference Weight and Balance data, Lockheed Report SMP 521, for approved fuel loading information. See NOTE 1 for unusable fuel. A1SO 6 of 23 Oil Capacity Four (4) independent tanks, one in each nacelle above the engine (Arm 442.0). Capacity for each, 8 gallons usable, total 12 gallons. Capacity for all, 32 gallons usable, total 48 gallons. See NOTE 1 for system oil. Maximum operating altitude 32,600 feet Other operating limitations Aircraft shall be operated in compliance with the operating limitations specified in the FAA approved Airplane Flight Manual. Manufacturer's Serial Number 4101 and up. III. - Model 382E (Hercules) (transport aircraft), approved 4 October 1968 (See NOTE 5) Engines 4 Allison turbo-prop 501-D22A Engine Type Certificate No. E-282 Fuel Commercial aviation turbine fuels conforming to ASTM Specification No. D 1655-59T, types Jet B, Jet A-1, or Jet A, or commercial equivalents of MIL-J-5624, grade JP-4 or JP-5. Lubricating Oil Synthetic oil conforming to Allison Commercial Service Letter CSL-1002. Engine Limits Static, standard day, sea level: Turbine inlet Temp Torque Oil Temp Take-off (5 minutes) 1077°C 19,600 in-lbs. 40°C - 100°C Maximum continuous 1010° 19,600 in-lbs. 60°C - 85°C Rated Speed: 100% - 13,820 erpm Propeller and Propeller Limits 4 Hamilton Standard hydromatic propellers Hub 54H60-91/54H-60117 Blade A7111C-2/A7111D-2 Propeller Type Certificate No. P-906 Diameter: 13 ft. 6 in. 2% reduction allowable for repair Single rotation, four blade assembly with governing speed setting 1020 prpm (13,820 erpm). Propeller assembly is complete with spinner, feathering and reversing provisions, constant speed control, negative torque control, synchrophaser, and electrical ice control. Blade angles See NOTE 3 Feather 92.5° ± 0.20° (a) (b) Low pitch stop (min. flt. idle) 23.25° ± 0.50° (a) Ground start 4.75° ± 0.75° (b) Ground idle 1.0° (c) Reverse -7.0° ± 1.0° (b) Propeller Oil MIL-H-5606B 7 of 23 A1SO Airspeed Limits VMO (Maximum operating) See Fig. 1-2 VA (Maneuvering) of approved VB (Turbulent air penetration) Airplane Flight Manual VFE (Take-off & approach, 50%) 183K VFE (Landing, 100%) 145K VLO (Landing gear operation) 168K VLE (Landing gear extended) 168K VLL (Landing light extended) 168K Heated Windshield If electric windshield heat is operative, it must be used for all flight operations. Limitations Operation without electric windshield heat, on any or all portions of the windshield, is permissible provided (1) the airplane is not flown in known icing conditions, and (2) the maximum speed limit below 10,000 ft. is 187 KCAS. Weight & C.G. Limits Condition Wt./lbs. Most Fwd. C.G. Most Aft C.G. (gear up or down) %MAC F.S. %MAC F.S. Ramp 155,800 23.3 525.7 30 536.8 Take-off 155,000 23.2 525.5 30 536.8 Landing 130,000 20.2 520.6 30 536.8 Zero fuel 120,000 18.8 518.3 30 536.8 The above weights pertain to an aircraft configuration which includes a structurally heavier wng (S/N 4299 and up) and does not have pylon tanks installed. Consult the FAA approved Airplane Flight Manual for proper weight and center gravity restrictions. Datum Trim Station - 493.0 (F.S. 94.0), W.L. 142.98, B.L. O.O (NAS 221 screw head on bottom of forward fuselage, 71.0" forward of center line of nose gear strut.) M.A.C. 164.5"; leading edge M.A.C. Trim Station -39.6 (F.S. 487.4) Leveling Means Provisions for leveling by plumb line are installed in the cargo compartment on the left side at approximately Trim Station +110 (F.S. 637). A plumb line support bracket is located on the fuselage side panel at approximately W.L. 252, B.L. 64L, and a leveling plate is located on top of the cargo floor curb at approximately W.L. 150, B.L. 64L. Minimum Crew Three (3) - Pilot, Co-pilot, and Flight Engineer. Passengers None, approved for cargo only. Cargo compartment Length 48.3 ft. Width 9 ft. 11½ in. Height 9 ft. Usable Volume 4,536 cu. ft. Maximum cargo See SMP 521-2. Loading data for approved loading schedules are contained in Lockheed Report ER-9511. Individual aircraft weight and balance data are contained in Lockheed Report SMP 521-2. Class E cargo compartment. Cargo must be loaded in compliance with loading placard, Lockheed Drawing 398251-1. When cargo restraining (barrier) net is installed, the 393487-15 placard is a required part of the installation. A1SO 8 of 23 Maximum fuel quantity Aircraft S/N 4101 through 4581. See NOTE 9 for aircraft S/N 4582 and up. Tank Usable Fuel Total Fuel F.S. Arm (Full) T.S. 1 (outboard) 9239 lbs. 9331 lbs. 545.2 +18.2 2 (inboard) 8437 lbs. 8578 lbs. 555.0 +28.0 3 (inboard) 8437 lbs. 8578 lbs. 555.0 +28.0 4 (outboard) 9238 lbs. 9331 lbs. 545.2 +18.2 ** Left Aux. 6269 lbs. 6329 lbs. 556.7 +29.7 ** Right Aux. 6269 lbs. 6329 556.7 +29.7 *** Left External 9355 lbs. 9465 lbs. 551.2 +24.2 *** Right External 9355 lbs. 9465 lbs. 551.2 +24.2 66,598 lbs. *67,406 lbs. (549.9) **** Left External 9355 lbs. 9499 lbs. 551.2 +24.2 **** Right External 9355 lbs. 9499 lbs. 551.2 +24.2 **** 66,598 lbs. *67,474 lbs. (549.9) * Does not include line fuel (See NOTE 1 (c)). ** Optional tank installations. *** Optional external tank installation (Lockheed P/N 388236) **** Optional external tank installation (Lear Siegler P/N 305J001) The above fuel weight are not to be exceeded. (Tank volume may be calculated using fuel density of 6.9 lbs./gal.). Arm varies with fuel loading. Reference loading data, Lock heed Report SMP 521-2, for approved fuel loading information. See NOTE 1 for unusable fuel. Oil Capacity Four (4) independent tanks, one in each nacelle above the engine (Arm 442.0, Trim Station -85.0). Capacity for each, 8 gallons usable, total 12 gallons. Capacity for all, 32 gallons usable, total 48 gallons. See NOTE 1 for system oil. Maximum operating altitude 32,600 feet Other operating limitations Aircraft shall be operated in compliance with the operating limitations specified in the FAA approved Airplane Flight Manual. Manufacturer's Serial Numbers 4299 and up, 4101 through 4298 by incorporation of STC STC395SO (See NOTE 5) . IV. - Model 382 F (Hercules) (transport aircraft), approved 3 December 1969 (See NOTE 5) Engines 4 Allison turbo-prop 501-D22 Engine Type Certificate No. E-282 Fuel Commercial aviation turbine fuel conforming to ASTM Specification No. D 1655-59T, types Jet B, Jet A-1, or Jet A, or commercial equivalents of MIL-J-5624, grade JP-4, or JP-5. Lubricating Oil Synthetic oil conforming to Allison Commercial Service Letter CSL-1002 Engine Limits Static, standard day, sea level: Turbine Inlet Temp. Torque Oil Temp. Take-off (5 minutes) Model 382F 977°C 19,600 in-lb. 40°C - 100°C Maximum continuous 932°C 18,000 in-lb. 60°C - 85°C Rated Speed: 100% - 13,820 erpm 9 of 23 A1SO Propeller and Propeller Limits 4 Hamilton Standard hydromatic propellers Hub 54H60-91/54H60-117 Blade A7111C-2/A7111D-2 Propeller Type Certificate No. P-906 Diameter: 13 ft. 6 in. 2% reduction allowable for repair Single rotation four blade assembly with governing speed setting 1020 prpm (13,820 erpm). Propeller assembly is complete with spinner, feathering and reversing provisions, constant speed control, negative torque control, synchrophaser, and electrical ice control. Blade angles See NOTE 3 Feather 92.5° ± 0.20° (a) (b) Low pitch stop (min. flt. idle) 23.25° ± 0.50° (a) Ground start 4.75° ± 0.75° (b) Ground idle 1.0° ± (c) Reverse -7.0 ± 1.0° (b) Propeller Oil MIL-H-5606B Airspeed Limits VMO Maximum operating) See Fig. 1-2 VA (Maneuvering) of approved VB (Turbulent air penetration) Airplane Flight Manual VFE (Take-off & approach, 50%) 183K VFE (Landing, 100%) 145K VLO (Landing gear operation) 168K VLE (Landing gear extended) 168K VLL (Landing light extended) 168K Heated Windshield If electric windshield heat is operative, it must be used for all flight operations. Operation without electric windshield heat, on any or all portions of the windshield, is permissible provided (1) the airplane is not flown in known icing conditions, and (2) the maximum speed limit below 10,000 ft. is 187 KCAS. Weight & C.G. Limits Condition Wt./lbs. Most Fwd. C.G. Most Aft C.G. (gear up or down) %MAC F.S. %MAC F.S. Ramp 155,800 23.3 525.7 30 536.8 Take-off 155,000 23.2 525.5 30 536.8 Landing 130,000 20.2 520.6 30 536.8 Zero fuel 120,000 18.8 518.3 30 536.8 The above weights pertain to an aircraft configuration which includes a structurally heavier wing (S/N 4299 and up) and does not have pylon tanks installed. Consult the FAA approved Airplane Flight Manual for proper weight and center-of-gravity restrictions. Datum Trim Station -493.0 (F.S. 94.0), W.L. 142.98, B.L. 0.0 (NAS 221 screw head on bottom of forward fuselage, 71.0" forward of center line of nose gear strut.) M.A.C. 164.5"; leading edge M.A.C., Trim Station -39.6 (F.S. 487.4) Leveling Means Provisions for leveling by plumb line are installed in the cargo compartment on the left side at approximately Trim Station +110 (F.S. 637). A plumb line support bracket is located on the fuselage side panel at approximately W.L. 252, B.L. 64L, and a leveling plate is located on top of the cargo floor curb at approximately W.L. 150, B.L. 64L. A1SO 10 of 23 Minimum Crew Three (3) - Pilot, Co-Pilot, and Flight Engineer Passengers None. Approved for cargo only. Cargo Compartment Length 48.3 Width 9 ft. 11½ in. Height 9 ft. Unusable volume 4,536 cu. ft. Maximum cargo See SMP 521-2. Loading data for approved loading schedule are contained in Lockheed Report ER-9511. Individual aircraft weight and balance data are contained in Lockheed Report SMP 521-2. Class E cargo compartment. Cargo must be loaded in compliance with loading placard, Lockheed Drawing 398251-1. When cargo restraining (barrier) net is installed, the 393487-15 placard is a required part of the installation. Maximum fuel quantity Aircraft S/N 4101 through 4581. See NOTE 9 for aircraft S/N 4582 and up. Tank Usable Fuel Total Fuel F.S. Arm (Full) T.S. 1 (outboard) 9238 lbs. 9331 lbs. 545.2 +18.2 2 (inboard) 8437 lbs. 8578 lbs. 555.0 +28.0 3 (inboard) 8437 lbs. 8578 lbs. 555.0 +28.0 4 (outboard) 9238 lbs. 8331 lbs. 545.2 +18.2 ** Left Aux. 6269 lbs. 6329 lbs. 556.7 +29.7 ** Right Aux. 6269 lbs. 6329 lbs. 556.7 +29.7 *** Left External 9355 lbs. 9465 lbs. 551.2 +24.2 *** Right External 9355 lbs. 9465 lbs. 551.2 +24.2 66,598 lbs. *67,406 lbs. (549.9) **** Left External 9355 lbs. 9499 lbs. 551.2 +24.2 **** Right External 9355 lbs. 9499 lbs. 551.2 +24.2 **** 66,598 lbs. *67,474 lbs. (549.9) * Does not include line fuel (See NOTE 1 (c)). ** Optional tank installations. *** Optional external tank installation (Lockheed P/N 388236) **** Optional external tank installation (Lear Siegler P/N 305J001) The above fuel weights are not to be exceeded. (Tank volume may be calculated using fuel density of 6.9 lbs./gal.) Arm varies with fuel loading. Reference loading data, Lockheed Report 521-2, for approved fuel loading information. See NOTE 1 for system oil. Oil Capacity Four (4) independent tanks, one in each nacelle above the engine (Arm 442.0, Trim Sta. - 85.0). Capacity for each, 8 gallons usable, total 12 gallons. Capacity for all, 32 gallons usable, total 48 gallons. Maximum operating altitude 32,600 feet Other operating limitations Aircraft shall be operated in compliance with the operating limitation specified in the FAA approved Airplane Flight Manual. Manufacturer's Serial Numbers 4299 and up, 4101 through 4298 by incorporation of STC serial numbers ST425SO (See NOTE 5). 11 of 23 A1SO V. - Model 382G (Hercules) (Transport Aircraft), approved October 7, 1970, See NOTE 5) Engines 4 Allison turbo-prop 510-D22A Engine Type Certificate No. E-282 Fuel Commercial aviation turbine fuels conforming to ASTM Specification No. D 1655-59T, types Jet B, Jet A-1, or Jet A, or commercial equivalents of MIL-J-5624, grade JP-4 or JP-5. Lubricating Oil Synthetic oil conforming to Allison Commercial Service Letter CSL-1002. Engine Limits Static, standard day, sea level: Turbine Inlet Temp. Torque Oil Temp. Take-off (5 minutes) 1077°C 19,600 in lbs. 40°C - 100°C Maximum continuous 1010°C 19,600 in. lbs. 60°C - 85°C Rated Speed: 100% - 13,820 erpm Propeller and Propeller Limits 4 Hamilton Standard hydromatic propellers Hub 54H60-91/54H60-117 Blade A7111C-2/A7111D-2 Propeller Type Certificate No. P-906 Diameter: 13 ft. 6 in. 2% reduction allowable for repair Single rotation, four blade assembly with governing speed setting 1020 prpm (13,820 erpm). Propeller assembly is complete with spinner, feathering and reversing provisions, constant speed control, negative torque control, synchrophaser, and electrical ice control. Blade angles See NOTE 3 Feather 92.5° ± 0.20° (a) (b) Low pitch stop (min. flt. idle) 23.25° ± 0.50° (a) Ground start 4.75° ± 0.75° (b) Ground idle 1.0° (c) Reverse -7.0 ± 1.0° (b) Propeller Oil MIL-H-5606B Airspeed Limits VMO Maximum operating) See Fig. 1-2