TCDS H1NE

Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 Rev 48 20 23 20 20 24 21 21 21 48 48 44 44 44 44 47 48 45 41 43 40 48 48 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H1NE Revision No 48 Sikorsky Models S-76A S-76B S-76C S-76D January 29, 2021 TYPE CERTIFICATE DATA SHEET NO. H1NE This data sheet, which is part of Type Certificate (TC) Number H1NE, 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 (TC) HOLDER: Sikorsky Aircraft Corporation 6900 Main Street Stratford, CT 06497-9129 I. MODEL NUMBER S-76A (Transport Helicopter, Category B), Approved November 21, 1978 (Transport Helicopter, Category A), Approved January 9, 1979 ENGINES 2 Allison Engine Company Model 250-C30, or 2 Model 250-C30S, or 1 each Model 250-C30 and Model 250-C30S. (See Note 11.) FUEL PRIMARY: JP-4/JP-5**/JP-8/Jet A**/Jet A1**/Jet B/GB6537-94(RP-3)** ALTERNATE: **AVGAS/Jet A, A1, or JP5 mixture. Do not use above 4oC (40oF). (See Note 5.) ** For operations below 4oC (40oF), anti-ice additive required. (See Note 6.) ENGINE LIMITS SEA LEVEL STATIC / STANDARD DAY TORQUE LIMITS GAS GENERATOR SPEED LIMITS (N1) POWER TURBINE INLET(T5) Takeoff (5 minutes) Maximum Continuous OEI (30 minutes) OEI (2-1/2 minutes) 16 second transient (OEI) 10 second Transient (Starting) 104.6% 104.6% 104.6% 111.2% 111.2% to 155.0% - - - 53,550 (105.0%) 53,550 (105.0%) 53,550 (105.0%) 53,550 (105.0%) - - - 53,550 (105.0%) to 54,060 (106%) 768 Deg C 768 Deg C 798 Deg C 826 Deg C - - - 826 to 927 Deg C OUTPUT SHAFT (N2) Normal Range 95% to 107% Maximum Continuous Varies linearly from 114% at flight autorotation to 107.1% at 2½ -minute power. Maximum 15-second Varies linearly from 119% at flight autorotation to 109% at 2½-minute power. Page 2 of 23 H1NE Engine torque 100% = 564 foot-pounds See Flight Manual for T5 (power turbine inlet temperature) limits and power turbine (N2) speed limits. ROTOR LIMITS POWER OFF Maximum 115% Nr (336 r.p.m.) Minimum 87% Nr (255 r.p.m.) POWER ON Maximum 107% Nr (313 r.p.m.) Minimum 100% Nr (dual engine operation) Minimum 96% Nr (one engine inoperative) (OEI) AIRSPEED LIMITS VNE (never exceed) Power On: 155 knots (CAS), 155 knots (IAS). See Flight Manual for variations of V NE with gross weight and density altitude. VLE/VLO (gear extended, gear operating): 130 knots (CAS), 130 knots (IAS). VNE Power Off: 135 knots (CAS), 141 knots (IAS). Below 80 lbs. fuel remaining per tank, reduce airspeed to 120 knots (CAS), 126 knots (IAS) or less. CENTER OF GRAVITY (C.G.) RANGE 193 198 198.3 197.8 204.3 205.0 SEE NOTE 10 202 205 210 6,100 6,500 6,900 8,500 8,750 8,750 10,300 10,500 Minimum allowable weight (6,100 lbs.) Gross Weight (lbs.) Station - Inches 6,900 For effect of landing gear position, refer to loading section of flight manual. Page 3 of 23 H1NE LATERAL C.G. LIMITS + 3.5 inches maximum EMPTY WEIGHT C.G. RANGE None DATUM 200 inches forward of main rotor centroid LEVELING MEANS Leveling plate at STA 176, BL 35, L.H. and plumb line from upper frame of the aft doorway MAXIMUM WEIGHT 10,500 lbs MINIMUM CREW 2 (IFR) 1 (IFR) when appropriately equipped and operating to approved flight manual or flight manual supplement. (See Note 15.) 1 (VFR) NUMBER OF SEATS 2 cockpit 13 cabin maximum MAXIMUM BAGGAGE 600 lbs. FUEL CAPACITY 286.4 gals. (281.2 usable) at (216.7) (See Note 1.) OIL CAPACITY 1.27 gals. per engine at (231.0) MAXIMUM OPERATING (DENSITY) ALTITUDE Enroute 15,000 feet Takeoff and landing 6,900 feet or 11,000 feet (for helicopters incorporating Sikorsky Kit P/N 76070-30005) AMBIENT TEMPERATURE LIMITS: -34.4oC (-30oF) to ISA +36.7oC; not to exceed 48.9oC (120oF) ROTOR BLADE CONTROL MOVEMENTS For rigging information refer to Maintenance Manual. MANUFACTURER'S SERIAL NUMBERS 76006, 76007, 760001 thru 760122, 760130 thru 760261, 760263 thru 760268, 760270 thru 760298, 7 60300 thru 760302, 760304, 760364, 760366, 760369 thru 760371, 760373, 760374 are eligible. II. MODEL NUMBER S-76B (Transport Helicopter, Category B), Approved October 31, 1985 (Transport Helicopter, Category A), Approved February 3, 1987 ENGINES 2 Pratt & Whitney Canada (PWC) Model PT6B-36 (Category B only, reference S-76B Flight Manual, Supplement No. 2) or 2 PWC Model PT6B-36A or 2 PWC Model PT6B-36B (reference S-76B Flight Manual, Supplement No. 11) FUEL JP-4***/ JP-5**/JP-8/Jet A*/Jet A1*/GB6537-94(RP-3)* Fuels with anti-ice additive can be used without temperature limitation. *Fuels without anti-ice additive shall be mixed with appropriate additive below +4 oC (40 oF ). (See Note 6.) ** Not to be used below -26oC (-15oF). *** JP4 not to be used above 10,000 feet pressure altitude. OIL PWA 521, Type I or II Low temperature limits for starting: Type I oil usable to -54oC (-65oF) Type II oil usable to -40oC (-40oF) For approved oil brands, see PWC Service Bulletin No. 11001 Page 4 of 23 H1NE ENGINE AND TRANSMISSION LIMITS SEA LEVEL STATIC / STANDARD DAY ENGINE TORQUE LIMITS TRANSMISSION TORQUE LIMITS GAS GENERATOR SPEED LIMITS(N1) POWER TURBINE INLET (T5) FOR MODEL PWC PT6B-36 Takeoff (5 minutes) Maximum Continuous OEI (2-1/2 minutes) OEI (30 minutes) 15 second Transient 10 second Transient 5 second Transient (OEI) 5 second Transient (Starting) 2 second Transient(Starting) 133.0 % 120.0 % 141.0 % * 133.0 % - - - 152.0 % * - - - - - - - - - 100.0 % 100.0 % 136.0 % 128.0 % - - - 105.0 % 150.0 % * - - - - - - 100.0 % 100.0 % 101.6 % 100.0 % - - - 101.8 % - - - - - - - - - 816 deg C 776 deg C 850 deg C 816 deg C 870 deg C - - - - - - 940 deg C 1090 deg C * EEC will limit available single-engine torque to 136 % FOR MODEL PWC PT6B-36A Takeoff (5 minutes) Maximum Continuous OEI (2-1/2 minutes) OEI (30 minutes) 10 second Transient 5 second Transient (OEI) 5 second Transient (Starting) 2 second Transient (Starting) 133.0 % 120.0 % - - - 141.0 % * 152.0 % * - - - - - - - - - 100.0 % ** 100.0 % ** 136.0 % * 128.0 % 115.0 % ** 150.0 % * - - - - - - 100.0 % 100.0 % - - - 101.6 % 101.8 % - - - - - - - - - 816 deg C 776 deg C - - - 844 deg C 870 deg C - - - 940 deg C 1090 deg C * EEC will limit available single-engine torque to 136 % ** EEC will limit available dual-engine torque to total of 202 % FOR MODEL PWC PT6B-36B Takeoff (5 minutes) Maximum Continuous OEI (2-1/2 minutes) OEI (30 minutes) 10 second Transient 10 second Transient 5 second Transient (OEI) 5 second Transient (Starting) 2 second Transient(Starting) 133.0 % 120.0 % - - - 141.0 %* 152.0 %* - - - - - - - - - - - - 100.0 %** 100.0 %** 136.0 %* 128.0 % 115.0 %** - - - 150.0 %* - - - - - - 102.6 % 102.6 % - - - 104.2 % 104.7 % - - - - - - - - - - - - 816 deg C 776 deg C - - - 844 deg C - - - 870 deg C - - - 940 deg C 1090 deg C * EEC will limit available single-engine torque to 136 % ** EEC will limit available dual-engine torque to total of 202 % ROTOR LIMITS POWER OFF Maximum 115% Nr (336 r.p.m.) Minimum 91% Nr (266 r.p.m.) POWER ON Maximum 108% Nr (316 r.p.m.) except with torque below 26%, then 110% Nr Minimum 106% Nr (dual engine operation) Minimum 100% Nr (one engine inoperative) (OEI) Page 5 of 23 H1NE AIRSPEED LIMITS VNE (never exceed) Power On: 155 knots (IAS). See Flight Manual for variations of V NE with temperature and pressure altitude. With PT6B-36A, or PT6B -36B, VNE above 10,000 feet density altitude at actual gross wei ghts greater than 11,000 pounds is BROC (best -rate-of- climb) airspeed. VLE/VLO (gear extended/gear operating): 130 knots (IAS) VNE Power Off: 136 knots (IAS) Below 80 lbs. fuel remaining per tank, avoid sustained pitch down attitudes in excess of 5o nose low. CENTER OF GRAVITY (C.G.) RANGE 11,700 11,400 11,000 9,500 9,250 8,500 7,500 7,350 GROSS WEIGHT (lbs) 194 197 198.4 199.2 204.3 205 208.2 210 11,400 205 204.3199.2 11,700 197 11,000 198.4 210 9,250 7,500 199 7,350 (minimum allowable weight) STATION - INCHES PWC Model PT6B-36A and PT6B-36B Engines PWC Model PT6B-36 Engines For effect of landing gear position, refer to loading section of flight manual. LATERAL C.G. LIMITS Up to 11,400 lbs: +3.5 inches maximum Above 11,400 lbs: +2.5 inches maximum EMPTY WEIGHT C.G. RANGE None DATUM 200 inches forward of main rotor centroid LEVELING MEANS Leveling plate at STA 176, BL 35, L.H. and plumb line from upper frame of the aft doorway Page 6 of 23 H1NE MAXIMUM WEIGHT With PWC PT6B-36 engines: 11,400 pounds With PWC PT6B-36A engines: 11,700 pounds With PWC PT6B-36B engines: 11,700 pounds MINIMUM CREW 2 (IFR) 1 (IFR) when appropriately equipped and operating to approved flight manual or flight manual supplement (See Note 15.) 1 (VFR) NUMBER OF SEATS 2 cockpit 13 cabin maximum MAXIMUM BAGGAGE 600 lbs. FUEL CAPACITY 286.4 gals. (281.2 usable) at (216.7) (See Note 1.) OIL CAPACITY 2.0 gals. per engine MAXIMUM OPERATING (DENSITY) ALTITUDE PT6B-36 PT6B-36A PT6B-36B Enroute Takeoff and Landing Cat. B: Cat. A: 10,000 feet 10,000 feet - - - 15,000 feet 15,000 feet 5,000 feet 15,000 feet 15,000 feet 5,000 feet AMBIENT TEMPERATURE LIMITS -34.4oC (-30oF) to ISA +38oC not to exceed 49oC (120oF) with bleed air Environmental Control Unit (ECU) off or not installed. -34.4oC (-30oF) to ISA +35oC not to exceed 43oC (109oF) with bleed air ECU on. ROTOR BLADE CONTROL MOVEMENTS For rigging information, refer to Maintenance Manual. MANUFACTURER'S SERIAL NUMBERS 76005, 760262, 760299, 760303, 760310 thru 760363, 760365, 760367, 760368, 760372, 760379 thru 760382, 760387, 760391, 760393, 760395, 760399, 760403, 760404, 760409, 760410, 760413, 760414, 760416, 760425, 760427 through 760430, 760433, 760437, 760439, 760441 through 760445, 760447 through 760452, 760454, 760455, 760458, 760462, 760465, 760507, 762976 are eligible. III. MODEL NUMBER S-76C (Transport Helicopter, Category B), Approved March 15, 1991 (Transport Helicopter, Category A), Approved April 12, 1991 ENGINES 2 Turbomeca Arriel 1S1 or 2 Turbomeca Arriel 2S1 or 2 Turbomeca Arriel 2S2 (See Note 16.) FUEL JP-4***/JP-5**/JP-8/Jet A*/Jet A1*/Jet B*/GB6537-94(RP-3)* Fuels with anti-ice additive can be used without temperature limitation. * Fuels without anti -ice additive shall be mixed with appropriate additive below +4oC (40oF). (See Note 6.) ** Not to be used below -26oC (-15oF). *** Applicable to Arriel 1S1 only Page 7 of 23 H1NE OIL 5 cst synthetic oil for normal use For approved types and brands, refer to S-76C Flight Manual, Sikorsky P/N SA 4047 -76C-1 (W/Arriel 1S1 engine configuration) or S -76C Flight Manual, Sikorsky P/N SA 4047 -76C-10 and SA 4047-76C-14 (W/Arriel 2S1 engine configura tion), or SA 4047 -76C-15 (W/Arriel 2S2 engine configuration). ENGINE AND TRANSMISSION LIMITS Arriel 1S1 Configuration SEA LEVEL STATIC / STANDARD DAY ENGINE TORQUE LIMITS TRANSMISSION TORQUE LIMITS GAS GENERATOR SPEED LIMITS(N1) POWER TURBINE INLET (T5) Takeoff Maximum Continuous OEI(2-1/2 minutes) OEI (Maximum Continuous)) 20 second Transient (OEI) 20 second Transient 10 second Transient 5 second Transient (OEI) 5 second Transient(Starting) 104.0 % 104.0 % 127.0 % 110.0 % 148.0 % - - - - - - - - - - - - 100.0 % 100.0 % 136.0 % 128.0 % - - - - - - 115.0 % 150.0 % - - - 100.0 % 100.0 % 102.7 %** 102.2 %* 105.35 %*** 105.35 %*** - - - - - - - - - 845 deg C 845 deg C 885 deg C 868 deg C 920 deg C - - - - - - - - - 865 deg C * Cockpit gauge biased to read 101.2 % ** Cockpit gauge biased to read 101.7 % *** Cockpit gauge biased to read 104.35 % Arriel 2S1 Configuration SEA LEVEL STATIC / STANDARD DAY ENGINE TORQUE LIMITS TRANSMISSION TORQUE LIMITS GAS GENERATOR SPEED LIMITS(N1) POWER TURBINE INLET (T5) Takeoff (5 minutes) 30 minute (see Note 13) Maximum Continuous OEI (30 second) OEI (2 minutes) OEI (Maximum Continuous) 20 second Transient 10 second Transient 10 second Transient (starting) 5 second Transient(OEI) 103.7 % 103.7 % 103.7 % 134.6 % 126.7 % 116.7 % 160.4 % - - - - - - - - - 100.0 % 100.0 % 100.0 % 136.0 % 136.0 % 128.0 % - - - 115.0 % - - - 150.0 % 101.2 %* 101.2 %* 99.0 %** 105.8 %**** 102.4 %*** 101.2 %* 102.3 %*** - - - - - - - - - 912 deg C 912 degC 877 deg C 1000 deg C 941 deg C 912 deg C - - - - - - 865 deg C - - - * Cockpit gauge biased to read 100.0 % ** Cockpit gauge biased to read 97.8 % *** Cockpit gauge biased to read 101.2 % **** Cockpit gauge biased to read 104.6 % Page 8 of 23 H1NE Arriel 2S2 Configuration SEA LEVEL STATIC / STANDARD DAY ENGINE TORQUE LIMITS TRANSMISSION TORQUE LIMITS GAS GENERATOR SPEED LIMITS(N1) POWER TURBINE INLET (T5) Takeoff (5 minutes) 30 minute (see Note 13) Maximum Continuous OEI (30 second) OEI (2 minutes) OEI (Maximum Continuous) 20 second Transient 10 second Transient 10 second Transient (starting) 5 second Transient(OEI) 103.7 % 103.7 % 103.7 % 134.9 % 127.0 % 115.0 % 160.4 % - - - - - - - - - 100 % 100 % 100 % 136 % 136 % 128 % - - - 115.0 % - - - 150.0 % 101.88 %* 101.88 %* 99. 71 %** 105.89 %*** 102.38 %**** 101.28 %***** 102.98 %****** - - - - - - - - - 930 deg C 930 deg C 893 deg C 996 deg C 944 deg C 926 deg C - - - - - - 840 deg C - - - * Cockpit gauge biased to read 100.0 % ** Cockpit gauge biased to read 97.8 % *** Cockpit gauge biased to read 103.9 % **** Cockpit gauge biased to read 100.5 % ***** Cockpit gauge biased to read 99.4 % ****** Cockpit gauage biased to read 101.1% Engine Torque 100% = 657.6 foot-pounds ROTOR LIMITS POWER OFF Maximum 115% Nr (336 r.p.m.) Minimum 91% Nr (266 r.p.m.) POWER ON Maximum 108% Nr (316 r.p.m.) except 109% for less than 20 seconds (w/2S1 engine only) Maximum 108% Nr (316 r.p.m.) except with torque below 26%, then 110% Nr (w/1S1 engine only) Minimum 106% Nr (dual engine operation) Minimum 100% Nr (one engine inoperative) (OEI) AIRSPEED LIMITS VNE (never exceed) Power On: 155 knots (IAS). See Flight Manual for variations of VNE with temperature and pressure altitude. VLE/VLO(gear extended/gear operating): 130 knots (IAS) VNE Power Off: 136 knots (IAS) Below 80 lbs. fuel remaining per tank, avoid sustained pitch down attitude s in excess of 5o nose low. Page 9 of 23 H1NE CENTER OF GRAVITY (C.G.) RANGE 11,700 11,000 9,500 9,250 8,500 7,500 7,350 Gross Weight (lbs) 194 197 199.2 204.3 208.2 210 204.3199.2 11,700 197 11,000 210 9,250 7,500 199 7,350 (minimum allowable weight) STATION - INCHES For effect of landing gear position, refer to loading section of flight manual. LATERAL C.G. LIMITS Up to 11,400 lbs: +3.5 inches maximum Above 11,400 lbs: +2.5 inches maximum Below 10,800 lbs (w/hoist load, hover only): +4.5 inches maximum EMPTY WEIGHT C.G. RANGE None DATUM 200 inches forward of main rotor centroid LEVELING MEANS Leveling plate at STA 176, BL 35, L.H. and plumbline from upper frame of the aft doorway MAXIMUM WEIGHT 11,700 lbs. MINIMUM CREW 2 (IFR) 1 (IFR) when appropriately equipped and operating to approved flight manual or flight manual supplement (See Note 15.) 1 (VFR) NUMBER OF SEATS 2 cockpit 13 cabin maximum MAXIMUM BAGGAGE 600 lbs. FUEL CAPACITY 286.4 gals. (281.2 usable) at (216.7) (see Note 1) OIL CAPACITY 1.27 gals. per engine Page 10 of 23 H1NE MAXIMUM OPERATING (DENSITY) ALTITUDE With 1S1 Engine Configuration Enroute 15,000 feet Takeoff and landing Cat. B: 11,000 feet Cat. A: 5,000 feet With 2S1 or 2S2 Engine Configuration Enroute 15,000 feet Takeoff and landing Cat. B: 15,000 feet Cat. A: 5,000 feet AMBIENT TEMPERATURE LIMITS: -34.4oC (-30oF) to ISA +37oC; not to exceed 49oC (120oF) ROTOR BLADE CONTROL MOVEMENTS For rigging information refer to Maintenance Manual. MANUFACTURER'S SERIAL NUMBERS Sikorsky Aircraft Corporation under Production Certificate Number 105: 760269, 760375 through 760378, 760383 through 760386, 760388 through 760390, 760392, 760394, 760396 through 760398, 760400 through 760402, 760405 through 760408, 760411, 760412, 760415, 760417 through 760424, 760426, 760431, 760432, 760434 through 760436, 760438, 760440, 760446, 760453, 760456, 760457, 760459 through 760461, 760463, 760464, 760466 through 760506, 760508 through 760634, 760636, 760637, 760639, 760641, 760643, 760645, 760647 through 760652, 760654 through 760657, 760659 through 760685, 760687 through 760689, 760691 through 760693, 760695 through 760700, 760702, 760703, 760705 through 760707, 760709, 760710, 760712, 760713, 760715, 760716, 760718, 760719, 760721, 760722, 760724, 760725, 760727, 760728, 760730, 760732, 760733, 760735, 760736, 760738, 760742, 760744, 760749, 760752, 760761, 760769, 760794, 760797, 760805 through 760822 are eligible. Keystone Helicopter Corporation for Production under Type Certificate Only: 760635, 760638, 760640, 760642, 760644, 760646, 760653 and 760658 are eligible. Keystone Helicopter Corporation under Production Certificate Number 121NE: 760686*, 760690, 760694, 760701, 760704, 760708, 760711, 760714, 760717, 760720, 760723, 760726, 760729, 760731, 760734, 760737, 760739 through 760741, 760743, 760745 through 760748, 760750, 760751, 760753 through 760760, 760762 through 760768, 760770 through 760793, 760795, 760796, 760798 through 760804 are eligible. * 760686 originally designated as eligible for production by Keystone Helicopter Corporation under Type Certificate Only and redesignated upon issuance of Production Certificate Number 121NE. IV. MODEL NUMBER S-76D (Transport Helicopter, Category B), Approved October 12, 2012 (Transport Helicopter, Category A), Approved December 19, 2013 ENGINES 2 Pratt and Whitney Canada PW210S FUEL ISSUING AUTHORITY TYPE (1) SPECIFICATION FUEL TEMPERATURE RANGE (2) Commercial Jet A ASTM D1655 –40°C (–40°F) to 52°C (126°F) Jet A-1 ASTM D1655 –40°C (–40°F) to 52°C Page 11 of 23 H1NE (126°F) No. 3 Jet Fuel PRC GB6537 –40°C (–40°F) to 52°C (126°F) Military JP-5 MIL-DTL-5624 –40°C (–40°F) to 52°C (126°F) JP-8 MIL-DTL-83133 –40°C (–40°F) to 52°C (126°F) NOTES: 1. Any approved fuel or mixture of approved fuels may be used. Refer to the Pratt & Whitney Canada PW210S Maintenance Manual for a complete li st of acceptable and alternate/emergency fuels. 2. Fuel anti-icing additive must be used below 4°C (40°F) for fuels supplied without anti -icing additive. See Note 6. OIL Brand Supplier AeroShell Turbine Oil 500 AeroShell Turbine Oil 560 Shell Oil Company BP Turbo Oil 2380 Air BP Castrol 5000 Castrol Ltd. Mobil Jet Oil II Exxon Mobil Chemical Company Turbonycoil 600 II Nyco S.A. POWERPLANT LIMITS OPERATING CONDITION TIME ENGINE TORQUE LIMIT (%) ITT (C) NG (%) NP (%) TAKEOFF AEO 5 MIN 100 (1) 932-924 (1)(2) 100.0 (1) 108 HIP AEO (3) 30 MIN 100 (1) 924 (1) 100.0 (1) 108 MAXIMUM CONTINUOUS AEO -- 100 (1) 886 98.8 108 TRANSIENT AEO 20 SEC 136 980 101.8 118 30 SEC OEI 30 SEC 140 (1) 1006 (1) 102.7 (1) 108 2 MIN OEI 2 MIN 136 (1) 980 (1) 101.8 (1) 108 MAXIMUM CONTINUOUS OEI -- 128 (1) 924 (1) 100.0 (1) 108 TRANSIENT OEI 5 SEC 145 (30 SEC OEI) 1015 (30 SEC OEI) 103.3 (30 SEC OEI) 115 141 (2 MIN OEI) 989 (2 MIN OEI) 102.3 (2 MIN OEI) 20 SEC 136 (Max Cont OEI) 980 (Max Cont OEI) 101.8 (Max Cont OEI) 118 GROUND IDLE 20 SEC -- 790 -- -- -- -- 760 -- -- Page 12 of 23 H1NE OPERATING CONDITION TIME ENGINE TORQUE LIMIT (%) ITT (C) NG (%) NP (%) STARTING 2 SEC -- 825 -- -- 60 SEC -- 750 (4) -- -- NOTES: 1. Shaded boxes with bold numbers denote EEC controlled limiter values. 2. When the ITT increases above 886 C, the Takeoff and Maximum Continuous OEI ITT limits will decrease from 932 C to 924 C over a 3 minute period. The limits increase back to 932 C when the ITT decreases below 886C. 3. Hovering at Increased Power (HIP): Use of Takeoff limits during hover oper ations in excess of 5 minutes. 4. ITT limiting occurs at 740C. An automatic abort will be commanded (on ground only) if the ITT reaches 765C. 5. Limit in parentheses refers to currently selected OEI limit. Engine Torque 100% = 657.6 foot-pounds DRIVE SYSTEM LIMITS APPROVED GEARBOX OILS TYPE LOW TEMPERATURE LIMIT BP Turbo Oil 25 (Preferred) –40°C / –40°F Other Approved DOD-PRF-85734 Oils –40°C / –40°F MAIN GEARBOX TORQUE ALL ENGINES OPERATING (AEO) MGB TORQUE (%) NO INSPECTION REQUIRED INSPECTION REQUIRED 0% to 100% Continuous 100% to 115% 10 SEC >10 SEC >115% Any Occurrence ONE ENGINE INOPERATIVE (OEI) MGB TORQUE (%) NO INSPECTION REQUIRED INSPECTION REQUIRED 0% to 128% Continuous 128% to 136% 2 MIN >2 MIN 136% to 140% 30 SEC >30 SEC 140% to 150% 5 SEC >5 SEC >150% Any Occurrence Page 13 of 23 H1NE MGB OIL PRESSURE Maximum: 120 PSI Cautionary: 90 PSI to 120 PSI Normal: 50 PSI to 90 PSI Cautionary: 20 PSI to 50 PSI Minimum: 20 PSI MGB OIL TEMPERATURE (see Note 22) With v303 Software With v400 Software Maximum: 135°C Maximum: 135°C Cautionary: 120°C to 135°C Cautionary: 115°C to 135°C Normal: 15°C to 120°C Normal: 15°C to 115°C Cautionary: –20°C to 15°C Cautionary: –20°C to 15°C Minimum: –20°C Minimum: –20°C ROTOR LIMITS POWER OFF Maximum: 115% Normal: 91% to 115% Minimum 91% Transient Minimum: 74% Transient Minimum at touchdown while executing an autorotative landing: 68% POWER ON Maximum: 115% Cautionary: 108% to 115% Normal Operating Rotor Speed (AEO): 106% to 108% Cautionary (AEO): 91% to 106% Normal Operating Rotor Speed (OEI above best rate of climb airspeed): 106% to 108% Normal Operating Rotor Speed (OEI up to best rate of climb airspeed): 100% to 108% Cautionary (OEI): 91% to 100% Transient Minimum: 91% Transient Minimum at touchdown during an OEI landing: 68% AIRSPEED LIMITS VNE (never exceed) Power On: 155 knots (IAS). See Flight Manual for variations of VNE PWR ON with density altitude. VNE(gear extended/gear operating): 130 knots (IAS) VNE Power Off: 136 knots (IAS). See Flight Manual for variation of V NE PWR OFF with density altitude. Page 14 of 23 H1NE CENTER OF GRAVITY (C.G.) RANGE Page 15 of 23 HINE CENTER OF GRAVITY LIMITS AT VARIOUS GROSS WEIGHTS FOR LATERAL CG GREATER THAN ‡ 2.5 INCHES UP TO AND INCLUDING ‡ 3.5 INCHES NOTE: DATUM IS 200 INCHES FORWARD OF ROTOR CENTROID 11,400 ￾ 11 11.0001 203.3 205.6 202.0 GROSS WEIGHT - 1,000 LB 199.0 210.0 9,500 - 9,500 - 9,250 8,586 7,350 208.3 193 194 195 196 197 198 199 200 201 202 203 204 205 206 207 208 209 210 211 CENTER OF GRAVITY - INCHES AFT OF DATUM CENTER OF GRAVITY LIMITS AT VARIOUS GROSS WEIGHTS FOR LATERAL CG GREATER THAN ‡ 3.5 INCHES UP TO AND INCLUDING + 4.5 INCHES NOTE: DATUM IS 200 INCHES FORWARD OF ROTOR CENTROID 10,800 - 196.6 207.0 GROSS WEIGHT - 1,000 LB 194.0 210.0 - 9,500 - 9,250 - 7,350 _208.3_ 193 194 199 200 201 0202% 203 204 205 206 207 208 209 210 211 CENTER OF GRAVITY - INCHES AFT OF DATUM Page 16 of 23 HINE Note: For the above charts, the effect of landing gear retraction on center of gravity need not be considered. The