TCDS A12EA

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev No. 54 54 16 16 13 54 15 16 13 54 19 19 16 54 19 16 54 54 30 54 Page No. 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 Rev. No. 54 54 54 54 54 54 54 54 26 46 46 54 54 54 54 26 53 47 47 47 Page No. 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 Rev. No. 54 45 27 30 25 54 44 54 54 54 54 53 53 54 53 52 47 52 54 53 Page No. 61 62 63 Rev. No. 54 54 53 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A12EA Revision 54 Gulfstream G-1159 G-1159A G-1159B G-IV GV GV-SP GIV-X April 21, 2026 TYPE CERTIFICATE DATA SHEET NO. A12EA This data sheet which is part of Type Certificate No. A12EA prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations and Federal Aviation Regulations. Type Certificate Holder: Gulfstream Aerospace Corporation 500 Gulfstream Road Savannah, Georgia 31408 I. Model G-1159, Gulfstream II (Transport Category), Approved October 19, 1967. Engines 2 Rolls Royce Spey RB (163) 511-8 (Type Certificate E2EU) Fuel Kerosene American ASTM D 1655 Jet A ASTA D 1655 Jet A-1 MIL-DTL-83133 Grade JP-8 British DEF STAN 91-087 DEF STAN 91-091 Canadian CAN/CGSB 3.23 CIS T-1, TS-1 & RT (GOST 10227-86) T-7, (GOST 12308-66) French DCSEA 134 Romanian 3754/73 CS-3 AFQRJOS Bulletin No. 12 JP-4 Wide Cut Type (See NOTE 5) American ASTM D 1655-89 Jet B MIL-T-5624N Grade JP-4 Canadian CAN/CGSB 3.22-M86 CIS T-2 (GOST 10027-86) German TL 9130-006 Issue 6 A12EA Page 2 Fuel (con’t) JP-5 High Flash-Point Type American MIL-DTL-5624 Grade JP-5 British DEF STAN 91-086 Canadian 3-GP-24Ma French DCSEA 144 German TL 9130-007 Issue 4 Fuel shall conform to the specification as listed or to subsequent revisions found in the latest approved Airplane Flight Manual. Oil Castrol 3C and 325 Aeroshell Turbo Oil 390 and 500 Esso/Exxon 2380 Mobil Jet Oil II Chevron Jet Engine Oil 5 Caltex RPM Jet Engine Oil 5 Texaco S.A.T.O. 7730 NOTE: Mixing of oils is not recommended for APU. Oil shall conform to the specification as listed or to subsequent revisions found in the latest approved Airplane Flight Manual. Engine Limits Static Thrust (std. day) S.L. Takeoff (5 min.) 11,400 lb. Maximum continuous 10,940 lb. Maximum permissible engine rotor operating speeds: N1 (low compressor) (106.6%) 8,950 rpm N2 (high compressor) (100.1%) 12,500 rpm Maximum permissible temperatures: Turbine outlet gas (Trimmer Resistors, Inc.) Takeoff (5 min.) 585°C Maximum continuous 540°C Momentary maximum during starts and relights 570°C Maximum with reverse thrust (30 second limit) 490°C Maximum over-temperature (20 second limit) 610°C Engines with S.B. Sp 77-43 (20 second limit) 615°C (120 second limit) 595°C Oil inlet 100°C Oil inlet (15 min. limit) 120°C Fuel inlet temperature to engine high pressure pump 90°C Fuel inlet temperature (15 min. limit) 110°C Maximum Air Bleed Extraction (Percent of no bleed mass flow) Maximum engine high pressure bleed 2.45% Maximum engine low pressure bleed 3.65% Auxiliary Power Unit (APU) AirResearch GTCP-36-6: S/N 1 thru 248 and 775 Maximum permissible exhaust gas temperature 700°C Maximum rotor speed - all conditions 110% APU alternator load rating 20Kva APU rated output shaft power 10hp (with 50 lb. per min. bleed air and ambient temperate of 113°F) Page 3 A12EA APU (con’t) AirResearch GTCP-36-100G: S/N 250 thru 299, except 252 Maximum permissible exhaust gas temperature - - Up to 60% rpm during start 988°C 60% - 100% during start 821C° to 732°C (linear decrease) - Running 732°C Maximum rotor speed - all conditions 110% APU alternator load rating 20Kva (with 46.6 lb. per min. bleed air and 50hp ambient temperature of 103°F) Airspeed Limits (CAS) Vmo (Maximum operating) Sea level to 24,100 ft. 423 mph 367 knots Mmo = .85 @ 24,100 ft and above Va (Maneuvering) 245 mph 213 knots Vsb (Speed brake) Sea level to 28,100 ft. 389 mph 338 knots Msb = .85 @ 28,100 ft. and above Vfe (Flaps down to 39°) 196 mph 170 knots (Flaps down to 20°) 253 mph 220 knots (Flaps down to 10°) 288 mph 250 knots Vlo (Landing gear operation) 259 mph 225 knots Vle (Landing gear extended) 288 mph 250 knots Vmca (Minimum control air) 117 mph 102 knots Vll (Landing light operation) 288 mph 250 knots Maximum Operating Altitude 43,000 feet (airplanes modified by Aircraft Service Change 299 are approved to 45,000 feet.) Maximum Weight (lb.) Aircraft S/N With ASC* Max. Zero Fuel Max. Ramp Max. Take-Off Max. Landing 1 thru 82 & 775 - - 38,000 58,000 57,500 51,430 1 thru 82 & 775 10A & 41 39,000 60,000 59,500 55,000 83 thru 100 - - 39,000 60,000 59,500 55,000 1 thru 100 & 775 81 42,000 62,500 62,000 58,500 101 thru 216 - - 42,000 62,500 62,000 58,500 1 thru 216 and 775 256 42,000 65,300 64,800 58,500 217 thru 299, except 249, 252 & 775 233 42,000 65,300 64,800 58,500 *See NOTE 6 Datum Station 0 is 45 inches forward of the jig point at the centerline of the airplane in the nose wheel well. M.A.C. 147.28 in. (L.E. of M.A.C. = Fuselage Station 404.13) Fuel Capacity S/N 1 thru 82 & 775: Gravity or Pressure Fueling: Total 22,620 lb. Usable 22,500 lb. Arm* +433.0 S/N 1 thru 82 & 775 with ASC 41 & ASC 10A, and S/N 83 thru 216: Gravity or Pressure Fueling: Total 23,400 lb. Usable 23,300 lb. Arm* 435.9 Fuel weights based upon fuel density of 6.75 lb. per gal. See NOTE 1 for system fuel and unusable fuel. A12EA Page 4 *Arm based on ground static attitude (-1.5° FRL) Oil Capacity Engine Oil 13.7 lb./14.6 U.S. pints-left engine (Arm = +564.0) 14.6 lb./15.6 U.S. pints-right engine (Arm = +564.0) APU Oil 5.1 lb./5.4 U.S. pints (Arm = +620.0) Oil weights based upon oil density of 7.5 lb. per gal. See NOTE 1 for system oil. Capacities shown are for engine oil tankage only. Total engine oil is an additional 14 lb. per engine. Serial No. Eligible S/N 1 thru 216, including 775; & S/N 217 thru 299 with Aircraft Service Change 233, except S/N 249 and 252. Page 5 A12EA GULFSTREAM G-1159 WEIGHT AND CENTER OF GRAVITY ENVELOPE AT GROUND STATIC ATTITUDE 30 32 34 36 38 40 42 33,000 34,000 35,000 36,000 37,000 38,000 39,000 40,000 41,000 42,000 ZER O G R O S S W EIG HT - PO UN D S CENTER OF GRAVITY - % MAC A B C GULFSTREAM AEROSPACE G11 5 9 (INCLUDING TIP TA NK A IRPLANE) WEIGHT AND BALA NCE DATA ALLOWABLE ZERO FUEL GROSS WEIGHT CG ENVELOPE IF THE ZFGW IS W ITHIN T HE ENV ELOPE, T HE FUELED A IRCRA FT WILL BE WITHIN F A A A PPROVED LIMI TS FO R A LL FUE L LOA DINGS. AIRPLANE SERIAL NO. WITH ASC ENVELOPE 1 THRU 82 AND 775 1 THRU 82 AND 775 83 THRU 100 1 THRU 100 AND 775 100 AND SUB EXCLUDING 775 A B B C C 10A AND 41 81 OR 200 A12EA Page 6 II. Model G-1159, Gulfstream II (Transport Category), Increased Range Airplane (Tip Tanks), Approved May 13, 1977. Engines 2 Rolls Royce Spey RB (163-25) 511-8 (Type Certificate E2EU) Fuel Kerosene American ASTM D 1655 Jet A ASTA D 1655 Jet A-1 MIL-DTL-83133 Grade JP-8 British DEF STAN 91-087 DEF STAN 91-091 Canadian CAN/CGSB 3.23 CIS T-1, TS-1 & RT (GOST 10227-86) French DCSEA 134 Romanian 3754/73 CS-3 AFQRJOS Bulletin No. 12 JP-4 Wide Cut Type (See NOTE 5) American ASTM D 1655-89 Jet B MIL-T-5624N Grade JP-4 Canadian CAN/CGSB 3.22 M86 CIS T-2 (GOST 10027-86) German TL 9130-006 Issue 6 JP-5 High Flash-Point Type American MIL-DTL-5624 Grade JP-5 British DEF STAN 91-086 Canadian 3-GP-24Ma French DCSEA 144 German TL 9130-007 Issue 4 Fuel shall conform to the specifications as listed or to subsequent revisions found in the latest approved Airplane Flight Manual. Oil Castrol 3C and 325 Aeroshell Turbo Oil 390 and 500 Esso/Exxon 2380 Mobil Jet Oil II Chevron Jet Engine Oil 5 Caltex RPM Jet Engine Oil 5 Texaco SATO 7730 NOTE: Mixing of oils is not recommended for APU. Oil shall conform to the specifications as listed or to subsequent revisions found in the latest approved Airplane Flight Manual. Engine Limits Static Thrust (std. day) S.L. Takeoff (5 min.) 11,400 lb. Maximum continuous 10,940 lb. Maximum permissible engine rotor operating speeds: N1 (low compressor) (106.6%) 8,950 rpm N2 (high compressor) (100.1%) 12,500 rpm Page 7 A12EA Engine Limits (con’t) Maximum permissible temperatures: Turbine outlet gas (Trimmer Resistors, Inc.) Takeoff (5 min.) 585°C Maximum continuous 540°C Momentary maximum during starts and relights 570°C Maximum with reverse thrust (30 second limit) 490°C Maximum over-temperature (20 second limit) 610°C Engines with S.B. Sp 77-43 (20 second limit) 615°C (120 second limit) 595°C Oil inlet 100°C Oil inlet (15 min. limit) 120°C Fuel inlet temperature to engine high pressure pump 90°C Fuel inlet temperature (15 min. limit) 110°C Maximum Air Bleed Extraction (Percent of no bleed mass flow) Maximum engine high pressure bleed 2.45% Maximum engine low pressure bleed 3.65% Auxiliary Power Unit (APU) AirResearch GTCP-36-6: S/N 1 thru 248 and 775 Maximum permissible exhaust gas temperature 700°C Maximum rotor speed - all conditions 110% APU alternator load rating 20Kva APU rated output shaft power 10hp (with 50 lb. per min. bleed air and ambient temperature of 113°F) AirResearch GTCP-36-100G: S/N 250 thru 299, except 252 Maximum permissible exhaust gas temperature - - Up to 60% rpm during start 988°C 60% - 100% during start 821°C to 732°C (linear decrease) -Running 732°C Maximum rotor speed - all conditions 110% APU alternator load rating 20Kva APU rated output shaft power 50hp (with 46.6 lb. per min. bleed air and ambient temperature of 103°F) Airspeed Limits (CAS) Vmo (Maximum operating) 345 mph (300 knots) at S.L. to 389 mph (338 knots) at 28,100 ft. Mmo = .85 @ 28,100 ft and above Va (Maneuvering) 184 mph 160 knots Vsb (Speed brake) Sea level to 33,500 ft. 345 mph 300 knots Msb = .85 @ 33,500 ft. and above Vfe (Flaps down to 39°) 196 mph 170 knots (Flaps down to 20°) 253 mph 220 knots (Flaps down to 10°) 288 mph 250 knots Vlo (Landing gear operation) 259 mph 225 knots Vle (Landing gear extended) 288 mph 250 knots Vmca (Minimum control air) 117 mph 102 knots Vll (Landing light operation) 288 mph 250 knots A12EA Page 8 Maximum Operating Altitude 43,000 feet (airplanes modified by Aircraft Service Change 299 are approved to 45,000 feet.) Maximum Weight (lb.) Aircraft S/N With ASC* Max. Zero Fuel Max. Ramp Max. Take-Off Max. Landing 1 thru 216 & 775 200 42,000 66,000 65,500 58,500 217 thru 299, except 249 & 252 - - 42,000 66,000 65,500 58,500 *See NOTE 6 and "Serial No. Eligible." Datum Station 0 is 45 inches forward of the jig point at the centerline of the airplane in the nose wheel well. M.A.C. 147.28 in. (L.E. of M.A.C. = Fuselage Station 404.13) Fuel Capacity Gravity or Pressure Fueling: Total 26,936 lb. Usable 26,800 lb. Arm* +445.2 Fuel weights based upon fuel density of 6.75 lb. per gal. See NOTE 1 for system fuel and unusable fuel. *Arm based on ground static attitude (-1.5°FRL) Oil Capacity Engine Oil 13.7lb./14.6 U.S. pints-left engine (Arm = +564.0) 14.6 lb./15.6 U.S. pints-right engine (Arm = +564.0) APU Oil 5.1 lb./5.4 U.S. pints (Arm = +620.0) Oil weights based upon oil density of 7.5 lb. per gal. See NOTE 1 for system oil. Capacities shown are for engine oil tankage only. Total engine oil is an additional 14 lb. per engine. Serial No. Eligible S/N 1 thru 216 and 775 with Aircraft Service Change 200; and S/N 217 thru 299, except 249 and 252. Page 9 A12EA GULFSTREAM G-1159 WEIGHT AND CENTER OF GRAVITY ENVELOPE AT GROUND STATIC ATTITUDE (WITH TIP TANKS) 30 32 34 36 38 40 42 33,000 34,000 35,000 36,000 37,000 38,000 39,000 40,000 41,00 0 42,00 0 ZER O G R O S S W EIG HT - PO UN D S CENTER OF GRAVITY - % MAC A B C GULFSTREAM AE ROSPACE G11 59 (INC LUDIN G TIP TA NK A IRPLANE) WEI GHT AND BA LA NCE DATA ALLOWABL E ZERO FUEL GROS S WEIG HT CG ENV ELOPE IF TH E ZFGW IS WIT HIN THE EN VELOPE, THE FUEL ED A IRCRA FT WILL BE WITHIN FA A A P PROVED LIMITS FOR A LL F UEL LOA DINGS. AIRPLANE SERIA L NO. WITH ASC ENVELOPE 1 THRU 82 AND 775 1 THRU 82 AND 775 83 THRU 100 1 THRU 100 AND 775 100 AND SUB EXCLUDING 775 A B B C C 10A AND 41 81 OR 200 A12EA Page 10 III. Model G-1159A, Gulfstream III (Transport Category), Approved September 22, 1980. The G-1159A is the same as the G-1159 except for the following differences: (a) Wing: Span is increased 6 feet, chord increased forward of original front beam, contour changed forward of mid-chord, and 5-foot winglets added. (b) Fuselage: Addition of a 2-foot section aft of main door, radome extended and contour modified, and new curved windshield and support structure. (c) Maximum takeoff weight increased to 68,200 lb./69,700 lb. (d) Various changes to autopilot, flight instruments, and engine instruments. Engines 2 Rolls Royce Spey RB (163-25) 511-8 (Type Certificate E2EU) Fuel Kerosene American ASTM D 1655 Jet A ASTM D 1655 Jet A-1 MIL-DTL-83133 Grade JP-8 British DEF STAN 91-087 DEF STAN 91-091 Canadian CAN/CGSB 3.23 CIS T-1, TS-1 & RT (GOST 10227-86) French DCSEA 134 Romanian 3754/73 CS-3 AFQRJOS Bulletin No. 12 JP-4 Wide Cut Type (See NOTE 5) American ASTM D 1655-89 Jet B MIL-T-5624N Grade JP-4 Canadian CAN/CGSB 3.22 M86 CIS T-2 (GOST 10027-86) German TL 9130-006 Issue 6 JP-5 High Flash-Point Type American MIL-DTL-5624 Grade JP-5 British DEF STAN 91-086 Canadian 3-GP-24Ma French DCSEA 144 German TL 9130-007 Issue 4 Fuel shall conform to the specifications as listed or to subsequent revisions found in the latest approved Airplane Flight Manual. Page 11 A12EA Oil Castrol 3C and 325 Aeroshell Turbo Oil 390 and 500 Esso/Exxon 2380 Mobil Jet Oil II Chevron Jet Engine Oil 5 Caltex RPM Jet Engine Oil 5 Texaco SATO 7730 NOTE: Mixing of oils is not recommended for APU. Oil shall conform to the specifications as listed or to subsequent revisions found in the latest approved Airplane Flight Manual. Engine Limits Static Thrust (std. day) S.L. Takeoff (5 min.) 11,400 lb. Maximum continuous 10,940 lb. Maximum permissible engine rotor operating speeds: N1 (low compressor) (106.6%) 8,950 rpm N2 (high compressor) (100.1%) 12,500 rpm Maximum permissible temperatures: Turbine outlet gas (Trimmer Resistors, Inc.) Takeoff (5 min.) 585°C Maximum continuous 540°C Momentary maximum during starts and relights 570°C Maximum with reverse thrust (30 second limit) 490°C Maximum over-temperature (20 second limit) 610°C Engines with S.B. Sp 77-43 (20 second limit) 615°C (120 second limit) 595°C Oil inlet 100°C Oil inlet (15 min. limit) 120°C Fuel inlet temperature to engine high pressure pump 90°C Fuel inlet temperature (15 min. limit) 110°C Maximum Air Bleed Extraction (Percent of no bleed mass flow) Maximum engine high pressure bleed 2.45% Maximum engine low pressure bleed 3.65% Auxiliary Power Unit (APU) AirResearch GTCP-36-100G Maximum permissible exhaust gas temperature - - Up to 60% rpm during start 988°C 60% - 100% during start 821°C to 732°C (linear decrease) -Running 732°C Maximum rotor speed - all conditions 110% APU alternator load rating 20Kva APU rated output shaft power 50hp (with 46.6 lb. per min. bleed air and ambient temperature of 103°F) A12EA Page 12 Airspeed Limits (CAS) Vmo (Maximum operating) Sea level to 28,000 ft. 392 mph 340 knots Mmo = .85 @ 28,000 ft and above Va (Maneuvering) 237 mph 206 knots Vsb (Speed brake) Sea level to 28,000 ft. 392 mph 340 knots Msb = .85 @ 28,000 ft. and above Vfe (Flaps down to 39°) 195 mph 170 knots (Flaps down to 20°) 253 mph 220 knots (Flaps down to 10°) 288 mph 250 knots Vlo (Landing gear operation) 259 mph 225 knots Vle (Landing gear extended) 288 mph 250 knots Vmca (Minimum control air) 117 mph 102 knots Vmcg (Minimum control ground) 103 mph 89 knots Maximum Operating Altitude 45,000 feet Maximum Weight (lb.) Aircraft S/N With ASC * Max. Zero Fuel Max. Ramp Max. Take-Off Max. Landing 249, 252, 300 thru 426, and 875 - - 42,000 68,700 68,200 58,500 249, 252, 300 thru 426, and 875 70 44,000 70,200 69,700 58,500 427 & Sub - - 44,000 70,200 69,700 58,500 * See NOTE 6. Datum The zero datum is 21 inches forward of the jig point at the centerline of the airplane in the nose wheel well or 193 inches forward of Fuselage Station 193B. M.A.C. 165.4 in. (L.E. of M.A.C. = Fuselage Station 387.8) Fuel Capacity S/N 249, 252, 300 thru 371, and 875: Gravity or Pressure Fueling: Total 28,014 lb. Usable 27,900 lb. Arm* 430.4 S/N 372 and subsequent and S/N 875, 249, 252, and 300 thru 371 with ASC 30: Gravity or Pressure Fueling: Total 28,444 lb. Usable 28,300 lb. Arm* +423.3 Fuel weights based upon fuel density of 6.75 lb. per gal. *Arm based on ground static attitude (-1.5° FRL) Oil Capacity Engine Oil 13.7 lb./14.6 U.S. pints-left engine (Arm = +564.0) 14.6 lb./15.6 U.S. pints-right engine (Arm = +564.0) APU Oil 4.75 lb./5.4 U.S. pints (Arm = +620.0) Oil weights based upon oil density of 7.5 lb. per gal. See NOTE 1 for system oil. Capacities shown are for engine oil tankage only. Total engine oil is an additional 14 lb. per engine. Serial No. Eligible S/N 249, 252, 300 and subsequent, including S/N 875. Page 13 A12EA GULFSTREAM G-1159A WEIGHT AND CENTER OF GRAVITY ENVELOPE AT GROUND STATIC ATTITUDE 34 36 38 40 42 44 4635,000 36,000 37,000 38,000 39,000 40,000 41,000 42,000 43,000 44,000 ZER O G R O S S W EIG HT - PO UND S CENTER OF GRAVITY - % MAC GULFSTREAM AEROSPACE G1 1 5 9 A WEIGHT AND BALANCE DATA ALLOWABLE ZERO FUEL GROSS WEIGHT CG ENVELOPE IF THE ZFGW IS WITHIN THE EN VELOPE, TH E FUELED A IRCRA FT WILL BE WITHIN FA A A PPROVED LIMITS F OR A LL F UEL LOA DINGS. 48 AIRPLANE SERIAL NO. WITH ASC ENVELOPE 2 4 9 , 2 5 2 , 3 0 0 THRU 4 2 8 INCLUDING 8 7 5 2 4 9 , 2 5 2 , 3 0 0 THRU 4 2 6 INCLUDING 8 7 5 2 4 9 , 2 5 2 , 3 0 0 THRU 4 2 6 INCLUDING 8 7 5 A B C C 70 PT I 70 PT II - 4 2 7 A ND SUBS 3 5 .1 3 6 .6 C B A 4 2 .8 M AXIM UM ZERO FUEL GROSS W EIGHT 4 3 .7 4 1 ,3 3 3 4 0 .1 M AXIM UM ZERO F UEL GROSS WEIGHT ASC 7 0 A12EA Page 14 IV. Model G-1159B, Gulfstream G-IIB (Transport Category), Approved September 17, 1981. The G-1159B is the same as the G-1159 except for the following differences: (a) Wing: Span is increased 6 feet, chord increased forward of original front beam, contour changed forward of mid-chord, and 5-foot winglets added. (b) Fuselage: Addition of optional extended modified contour radome. (c) Maximum takeoff weight increased to 68,200 lb./69,700 lb. (d) Various changes to autopilot, flight instruments, and fuel quantity instruments. NOTE: Model G-1159, all serial numbers, are eligible for identification as Model G-1159B when modified in accordance with GAC Aircraft Service Change (ASC) 300. Engines 2 Rolls Royce Spey RB (163-25) 511-8 (Type Certificate E2EU) Fuel Kerosene American ASTM D 1655 Jet A ASTA D 1655 Jet A-1 MIL-DTL-83133 Grade JP-8 British DEF STAN 91-087 DEF STAN 91-091 Canadian CAN/CGSB 3.23 CIS T-1, TS-1 & RT (GOST 10227-86) French DCSEA 134 Romanian 3754/73 CS-3 AFQRJOS Bulletin No. 12 JP-4 Wide Cut Type (See NOTE 5) American ASTM D 1655-89 Jet B MIL-T-5624N Grade JP-4 Canadian CAN/CGSB 3.22 M86 grade CIS T-2 (GOST 10027-86) German TL 9130-006 Issue 6 JP-5 High Flash-Point Type American MIL-DTL-5624 Grade JP-5 British DEF STAN 91-086 Canadian 3-GP-24Ma French DCSEA 144 German TL 9130-007 Issue 4 Fuel shall conform to the specifications as listed or to subsequent revisions found in the latest approved Airplane Flight Manual. Oil Castrol 3C and 325 Aeroshell Turbo Oil 390 and 500 Esso/Exxon 2380 Mobil Jet Oil II Chevron Jet Engine Oil 5 Caltex RPM Jet Engine Oil 5 NOTE: Mixing of oils is not recommended for APU. Oil shall conform to the specifications as listed or to subsequent revisions found in the latest approved Airplane Flight Manual. Page 15 A12EA Engine Limits Static Thrust (std. day) S.L. Takeoff (5 min.) 11,400 lb. Maximum continuous 10,940 lb. Maximum permissible engine rotor operating speeds: N1 (low compressor) (106.6%) 8,950 rpm N2 (high compressor) (100.1%) 12,500 rpm Maximum permissible temperatures: Turbine outlet gas (Trimmer Resistors, Inc.) Takeoff (5 min.) 585°C Maximum continuous 540°C Momentary maximum during starts and relights 570°C Maximum with reverse thrust (30 second limit) 490°C Maximum over-temperature (20 second limit) 610°C Engines with S.B. Sp 77-43 ( 20 second limit) 615°C (120 second limit) 595°C Oil inlet 100°C Oil inlet (15 min. limit) 120°C Fuel inlet temperature to engine high pressure pump 90°C Fuel inlet temperature (15 min. limit) 110°C Maximum Air Bleed Extraction (Percent of no bleed mass flow) Maximum engine high pressure bleed 2.45% Maximum engine low pressure bleed 3.65% Auxiliary Power Unit (APU) AirResearch GTCP-36-100G Maximum permissible exhaust gas temperature - - Up to 60% rpm during start 988°C 60% - 100% during start 821°C to 732°C (linear decrease) -Running 732°C Maximum rotor speed - all conditions 110% APU alternator load rating 20Kva APU rated output shaft power 50hp (with 46.6 lb. per min. bleed air and ambient temperature of 103°F) AiResearch GTCP-36-6 Maximum permissible exhaust gas temperature 700°C Maximum rotor speed - all conditions 110% APU Alternator load rating 20Kva APU rated output shaft power 10hp (with 50 lb. per min. bleed air and ambient temperature of 113°F) A12EA Page 16 Airspeed Limits (CAS) Vmo (Maximum operating) Sea level to 28,000 ft. 392 mph 340 knots Mmo = .85 @ 28,000 ft and above Va (Maneuvering) 237 mph 206 knots Vsb (Speed brake) Sea level to 28,000 ft. 392 mph 340 knots Msb = .85 @ 28,000 ft. and above Vfe (Flaps down to 39°) 195 mph 170 knots (Flaps down to 20°) 253 mph 220 knots (Flaps down to 10°) 288 mph 250 knots Vlo (Landing gear operation) 259 mph 225 knots Vle (Landing gear extended) 288 mph 250 knots Vmca (Minimum control air) 115 mph 100 knots Vmcg (Minimum control ground) 103 mph 89 knots Maximum Operating Altitude 45,000 feet Maximum Weight (lb.) Aircraft Mod. No. With ASC * Max. Zero Fuel Max. Ramp Max. Take-Off Max. Landing 1 & Sub. - - 42,000 68,700 68,200 58,500 1 & Sub. 275 44,000 70,200 69,700 58,500 * See NOTE 6. Datum Station 0 is 45 inches forward of the jig point at the centerline of the airplane in the nose wheel well. M.A.C. 165.39 in. (L.E. of M.A.C. = Fuselage Station 387.81) Fuel Capacity Modification Nos. 1 thru 8 Gravity or Pressure Fueling: Total 28,014 lb. Usable 27,900 lb. Arm* +430.4 Modification Nos. 9 and subsequent. Gravity or Pressure Fueling: Total 28,444 lb. Usable 28,300 lb. Arm* +423.3 Fuel weights based upon fuel density of 6.75 lb. per gal. *Arm based on ground static attitude (-1.5° FRL) Oil Capacity Engine Oil 13.7 lb./14.6 U.S. pints-left engine (Arm = +564.0) 14.6 lb./15.6 U.S. pints-right engine (Arm = +564.0) APU Oil 4.75 lb./5.4 U.S. pints (Arm = +620.0) Oil weights based upon oil density of 7.5 lb. per gal. See NOTE 1 for system oil. Capacities shown are for engine oil tankage only. Total engine oil is an additional 14 lb. per engine. Serial No. Eligible G-1159; S/N 1 thru 299, including 775, excluding 249 & 252, when modified by Aircraft Service Change 300. Page 17 A12EA GULFSTREAM G-1159B WEIGHT AND CENTER OF GRAVITY ENVELOPE AT GROUND STATIC ATTITUDE 34 36 38 40 42 44 4635,000 36,000 37,000 38,000 39,000 40,000 41,000 42,000 43,000 44,000 ZER O G R O S S W EIG HT - PO UND S CENTER OF GRAVITY - % MAC GULFSTREAM AEROSPACE G1 1 5 9 B WEIGHT AND BALANCE DATA ALLOWABLE ZERO FUEL GROSS WEIGHT CG ENVELOPE