TCDS H3WE

H3WE Page 1 DEP ARTMENT OF TRANSPORT A TION FEDERAL A VIA TION ADMINISTRA TION TYPE CERTIFICATION DATA SHEET NO. H3WE This data sheet, which is part of Type Certificate No. H3WE, prescribes conditions and limitations under which the Product fo r which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations and, where specified, the Federal Aviation Regulations. Type Certificate Holder: MD Helicopters, LLC 4555 E. McDowell Road Mesa, Arizona 85215-9734 USA Phone: (480) 346-6300 Type Certificate Ownership Record: McDonnell Douglas Helicopter Systems transferred ownership of TC H3WE to MD Helicopters Inc. on February 18, 1999. List of Effective Pages Page. No. 1 13 15 16 17 18 19 20 21 22 23 28 29 34 39 40 41 Rev. No. 32 32 32 32 32 32 32 32 32 32 32 32 32 32 32 32 32 Page. No. 1 17 19 20 41 Rev. No. 31 31 31 31 31 Page. No. 1 16 17 40 Rev. No. 29 29 29 29 Page. No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 29 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 Page. No. 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 Rev. No. 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 28 Page No. 41 Rev No. 28 H3WE Revision 32 MD Helicopters, LLC 369 (Army YOH-6A) 369A (Army OH-6A) 369H, 369HM, 369HS, 369HE 369D, 369E, 369F, 369FF 500N, 600N Date: May 30, 2024 H3WE Page 2 I Model 369 (Army YOH-6A) (Normal Category Helicopter), Approved June 30, 1964 See NOTE 4 regarding modifications required for conversion of Military Models. Engine Rolls-Royce Corporation (formerly Allison Engine Company) 250-C10 (T63-A-5) Fuel MIL-DTL-5624, Grade JP-4, and JP-5 Aviation Fuels MIL-DTL-83133 Grade JP-8 Aviation Fuel ASTM D-1655 Jet A, A-1 or Jet B ASTM D-6615 Jet B Chinese Specification GB6537-94 Grade RP-3 See “Rotorcraft Flight Manual” for alternate fuels. See “NOTE 4.e)” for FAA Approved Rotorcraft Flight Manual. See “NOTE 7” for Anti-Icing additive. See “Engine TCDS E4CE Note #9” for emergency use mixtures and limits. Note: Fuels containing Tri-cresyl-phosphate additives shall not be used. Engine Limits Ratings Takeoff (5 min) Max. Continuous Shaft Horsepower 250 212 Torque 219 ft - lb (91%) 186 ft - lb (77%) Gas Producer rpm, N1 52,142 (102%) 52,142 (102%) Output Shaft rpm, N2 6,180 (103%) 6,180 (103%) Measured Gas Temp. 1,360F (738C) 1,280°F (693°C) Transient Limits Note: Adequate cooling has been demonstrated to a 117°F day. Power and torque ratings and limits are indicated values. Actual values are 2.5 hp higher. Measured Gas Temp. (6 sec. limit) 1,550°F (843°C) Measured Gas Temp. During Start (6 sec. limit) 1,700°F (927°C) Gas Producer rpm, N1 (15 Sec. limit) 52,654 (103%) Output Shaft rpm, N2 (15 Sec. limit) 6,600 (110%) at Idle to 6,300 (105%) at Takeoff Rotor Limits and Engine Operating Speeds Power-Off (Rotor) Power-On (Engine) Maximum: 514 rpm Maximum: 103% N2 Minimum: 400 rpm Minimum: 99% N2 Airspeed Limits VNE (Never Exceed Speed) at sea level is 128 knots (148 mph) CAS. Center of Gravity (C.G.) Range Longitudinal: Sta. 97 to 104 Lateral: 3 inches right and left of helicopter centerline Leveling Means Plumb bob at Sta. 92.16 Maximum Weight 2,100 lb. See NOTE 1 for weight and balance report. Number of Seats 2 at Sta. 73.5, 2 at Sta. 105 Maximum Cargo 1,350 lb. at 115 lb/sq.ft, Sta. 78.5 to 125 H3WE Page 3 I Model 369 (Army YOH-6A) (Normal Category Helicopter), Approved June 30, 1964 (cont.) Fuel Capacity Fuel System Total Tank Capacity (lbs.) Trapped Fuel * (lbs.) Total Unusable Fuel ** (lbs.) Usable Fuel Capacity (lbs.) Tank Sump Location (Sta.) 369-8100 383 0.56 3.10 380 98.2 * Fuel which cannot be drained from the tanks, through the drain provided, with the helicopter in the normal ground attitude. ** Fuel which cannot be used safely in all flight attitudes, and which must be included in the empty weight. This includes trapped fuel Note: Fuel capacities are total tank capacities over and above unusable fuel. Fuel weights are based on JP-4 fuel. Oil Capacity Engine Oil (lb. at Sta. 122.5) Transmission Oil (lb. at Sta. 103.5) 11.25 6.94 Note: Oil capacities are total tank capacities over and above trapped oil. Maximum Operating Altitude 20,000 ft. Main Rotor Blade Movements Collective Pitch at 0.75R (Relative to rigging position): Up and Down 6.5° (± 0.5°) Cyclic pitch (Relative to rigging position): Forward 16° (± 1°) Aft 8° (± 1°) Left 7.25° (± 0.75°) Right 6.25° (± 0.75°) Main Rotor Blade Damper Setting Torque to move the damper shaft through the low load stage: 240 in-lb. minimum, 300 in-lb. maximum. Tail Rotor Blade Movements Collective pitch Thrust to right +27° Thrust to left -12° Manufacturer’s Serial Numbers 0011 through 0015. See “NOTE 4” for configuration and eligibility requirements applicable to the Hughes Model 369 (YOH-6A) helicopter. See “NOTE 6” for serial number coding. Certification Basis CAR 6 dated December 20, 1956, including Amendments 6-1 through 6-4 and Special Conditions, "Conditions Establishing Compensating Factors Providing an Equivalent Level of Safety Under Civil Air Regulations, Section 6.10, for Light Turbine Powered Helicopters," dated October 2, 1962, except Condition 15a. Type Certificate H3WE issued June 30, 1964. Date of Application for Type Certificate: November 13, 1961. H3WE Page 4 I Model 369 (Army YOH-6A) (Normal Category Helicopter), Approved June 30, 1964 (cont.) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. All required equipment that must be installed as well as optional equipment installations are listed in the following reports. Model Report Number Title 369 369-E-5001 Model 369 Equipment List For a list of model 369 critical parts and life limits contact: Federal Aviation Administration Manager Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137 II - Model 369A (Army OH-6A) (Normal Category Helicopter), Approved August 24, 1966 See NOTE 4 regarding modifications required for conversion of Military Helicopters. Engine Rolls-Royce Corporation (formerly Allison Engine Company) 250-C10B (T63-A- 5A) Fuel MIL-DTL-5624, Grade JP-4, and JP-5 Aviation Fuels MIL-DTL-83133 Grade JP-8 Aviation Fuel ASTM D-1655 Jet A, A-1 or Jet B ASTM D-6615 Jet B Chinese Specification GB6537-94 Grade RP-3 See “Rotorcraft Flight Manual” for alternate fuels. See “NOTE 4.e)” for FAA Approved Rotorcraft Flight Manual. See “NOTE 7” for Anti-Icing additive. See “Engine TCDS E4CE Note #9” for emergency use mixtures and limits. Note: Fuels containing Tri-cresyl-phosphate additives shall not be used. H3WE Page 5 II - Model 369A (Army OH-6A) (Normal Category Helicopter), Approved August 24, 1966 (cont.) Engine Limits Ratings Applicable to S/N 0001 through 1445 Takeoff (5 min) Max. Continuous Shaft Horsepower* 250 212 Torque* 219 ft-lb (75 psi) 186 ft-lb (63.5 psi) Gas Producer rpm, N1 53,165 (104%) 53,165(104%) Output Shaft rpm, N2 6,180 (103%) 6,180 (103%) Measured Gas Temp. 1,380°F (749°C) 1,280°F (693°C) * Power and torque ratings and limits are indicated valued. Actual values are 2.5 hp higher. Ratings applicable to S/N 1446 and up, or S/N 0001 through 1445 when modified per NOTE 8 Takeoff (5 min) Max. Continuous Shaft Horsepower* 278 243 Torque* 236 ft-lb (80.3 psi) 208 ft-lb (70 psi) Gas Producer rpm, N1 53,165 (104%) 53,165 (104%) Output Shaft rpm, N2 6,240 (104%) 6,240 (104%) Measured Gas Temp. 1,380°F (749°C) 1,280°F (693°C) Transient Limits applicable to S/N 0001 and up Measured Gas Temp. (6 sec. limit) 1550°F (843°C) Measured Gas Temp. During Start (10 sec. limit) 1700°F (927°C) Gas Producer rpm, N1 (15 Sec. limit) 53676 (105%) Note: Adequate cooling has been demonstrated to at 117°F day. Rotor Limits and Engine Operating Speeds S/N 0001 through 1445 Power Off (Rotor) Power On (Engine) Maximum: 514 rpm Maximum: 103% N2 Minimum: 400 rpm Minimum: 100% N2 II - Model 369A (Army OH-6A) (Normal Category Helicopter), Approved August 24, 1966 (cont.) Rotor Limits and Engine Operating Speeds (Cont’d) S/N 1446 and up, or S/N 0001 through 1445 when modified per NOTE 8 Power Off (Rotor) Power On (Engine) Maximum: 514 rpm Maximum: 104% N2 Minimum: 400 rpm Minimum: 103% N2 Airspeed Limits For S/N 0001 through 1445, VNE (Never Exceed Speed) at sea level is 124 knots (143 mph) CAS. For S/N 1446 and up, or S/N 0001 through 1445 when modified per NOTE 8, V NE at sea level is 130 knots (150 mph) CAS. For reduction of VNE with altitude and temperature, and doors off, see “NOTE 4.e)” for FAA Approved Rotorcraft Flight Manual. Center of Gravity (C.G.) Range Longitudinal: Sta. 97 to 104 H3WE Page 6 Lateral: 3 inches right and left of helicopter centerline Leveling Means Plumb bob at Sta. 92.64 Maximum Weight S/N 0001 through 1445: 2,400-lb. S/N 1446 and up: 2,550 lb. S/N 0001 through 1445 when modified per NOTE 8: 2,550 lb. See NOTE 1 for weight and balance report. Number of Seats 2 at Sta. 73.5, 2 at Sta. 105 Maximum Cargo 950 lb. at 115 lb./sq. ft., Sta. 78.5 to 124 Fuel Capacity Fuel System Total Tank Capacity (lbs) Trapped Fuel** (lbs) Total Unusable Fuel *** (lbs) Usable Fuel Capacity (lbs) Tank Sump Location (Sta) 369A8100 402 0.16 1.50 400 98.2 M30273 (Gravity filled) 359 0.73 2.91 356 98.3 M30273 (Pressure filled.)* 329 0.73 2.91 326 98.0 * Pressure refueling not permitted on civil helicopters ** Fuel, which cannot be drained from the tank through the drain, provided - with the helicopter in the normal ground attitude. *** Fuel which cannot be used safely in all flight attitudes, and which must be included in the empty weight. This includes trapped fuel. Note: Fuel capacities are total tank capacities over and above unusable fuel. Fuel weights are based on JP-4 fuel. H3WE Page 7 II - Model 369A (Army OH-6A) (Normal Category Helicopter), Approved August 24, 1966 (cont.) Oil Capacity Engine Oil (lb. at Sta. 138.2) Transmission Oil (lb. at Sta. 105) 5.90 7.00 Note: Oil capacities are total tank capacities over and above trapped oil. Maximum Operating Altitude See “NOTE 4.e)” for FAA Approved Rotorcraft Flight Manual. Main Rotor Blade Movements Collective pitch (Relative to rigging position): Up and Down 15.5° (±1.25°) Cyclic pitch (Relative to rigging position): Forward 16° (±1°) Aft 8.5° (±0.5°) Left 8.25° (±1.25°) Right 6.25° (±0.75°) Note: Collective low pitch stop to be established in accordance with RFM or HMI to obtain proper autorotation rpm. Main Rotor Blade Damper Setting Torque to move the damper shaft through the low load stage: 265 in-lb., minimum; 325 in-lb. maximum. Tail Rotor Blade Movements Collective pitch Thrust to right +28° (+2°, -0°) Thrust to left -13° (±1°) Manufacturer’s Serial Numbers 0001 and up Model 369A helicopters serial numbers 1100 through 1445 and 1079A through 1080A have been manufactured under the Delegation Option Authorization provisions of FAR 21. Acting as Delegation Option Manufacturer Number WE -1, Hughes Tool Company, Aircraft Division, was authorized to issue Airworthiness Certificates for serial numbers noted above under the Delegation Option Authorization provisions of FAR 21. See NOTE 4 for configuration and eligibility requirements applicable to the Hughes Model 369A (OH-6A) helicopter. See NOTE 6 for serial number coding. Certification Basis CAR 6 dated December 20, 1956, including Amendments 6-1 through 6-4 and Special Conditions, "Conditions Establishing Compensating Factors Providing an Equivalent Level of Safety Under Civil Air Regulations, Section 6.10, for Light Turbine Powered Helicopters," dated October 2, 1962, as revised February 8, 1966. Type Certificate H3WE amended August 24, 1966. Date of Application for Amended Type Certificate: August 19, 1965. H3WE Page 8 II - Model 369A (Army OH-6A) (Normal Category Helicopter), Approved August 24, 1966 (cont.) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. All required equipment that must be installed as well as optional equipment installations are listed in the following reports. Model Report Number Title 369A 369-E-5002 Model 369A Equipment List See Limited Life Schedule of this TCDS. III Model 369H (Normal Category Helicopter), Approved November 15, 1966 Model 369HM (Normal Category Helicopter), Approved April 8, 1968 Model 369HS (Normal Category Helicopter), Approved January 3, 1969 Model 369HE (Normal Category Helicopter), Approved May 21, 1969 Engine Rolls-Royce Corporation (formerly Allison Engine Company) 250-C18A or 250- C18C Alternate engine: Rolls-Royce Corporation (formerly Allison Engine Company) 250-C20 Note: Model 369HM, 369HS, and 369HE helicopters, S/N 0101 and up, are eligible for installation of the alternate engine when modified in accordance with Hughes Drawing M50031, Revision A, or later approved revision, including M50033. Fuel MIL-DTL-5624, Grade JP-4, and JP-5 Aviation Fuels MIL-DTL-83133 Grade JP-8 Aviation Fuel ASTM D-1655 Jet A, A-1 or Jet B ASTM D-6615 Jet B Chinese Specification GB6537-94 Grade RP-3. See “Rotorcraft Flight Manual” for alternate fuels. See “NOTE 7” for Anti-Icing additive. See “Engine TCDS E4CE Note #9” for emergency use mixtures and limits. Note: Fuels containing Tri-cresyl-phosphate additives shall not be used. Engine Limits Ratings for 250-C18A or 250C18C Takeoff (5 min) Max. Continuous Shaft Horsepower 278 243 Torque 236 ft-lb (80.3 psi) 208 ft-lb (70 psi) Gas Producer rpm, N1 53,165 (104%) 53,165 (104%) Output Shaft rpm, N2 6,240 (104%) 6,240 (104%) Measured Gas Temp. 1,380°F (749°C) 1,280°F (693°C) H3WE Page 9 III Model 369H (Normal Category Helicopter), Approved November 15, 1966 Model 369HM (Normal Category Helicopter), Approved April 8, 1968 Model 369HS (Normal Category Helicopter), Approved January 3, 1969 Model 369HE (Normal Category Helicopter), Approved May 21, 1969 (cont.) Engine Limits (cont’d) Transient Limits for 250-C18 or 250-C18C Measured Gas Temp. (6 sec. limit) 1,550°F (843°C) Measured Gas Temp. During Start (10 sec. limit) 1,700°F (927°C) Gas Producer rpm, N1 (15 Sec. limit) 53,676 (105%) Output Shaft rpm, N2 (15 Sec. limit) 6,600 (110%) at Idle to 6,340 (105.7%) at Takeoff Torque: 90 psi for 10 sec. 100 psi for 3 sec. Ratings for 250-C20 Takeoff (5 min) Max. Continuous Shaft Horsepower 278 243 Torque 236 ft-lb (64.5 psi) 208 ft-lb (56 psi) Gas Producer rpm, N1 53,000 (104%) 53,000 (104%) Output Shaft rpm, N2 6,240 (104%) 6,240 (104%) Measured Gas Temp. 1,460°F (793°C) 1,358°F (737°C) Transient Limits for 250-C20 Measured Gas Temp. (6 sec. limit) 1,550°F (843°C) Measured Gas Temp. During Start (10 sec. limit) 1,700°F (927°C) Gas Producer rpm, N1 (15 Sec. limit) 53,518 (105%) Output Shaft rpm, N2 (15 Sec. limit) 6,798 (113%) at Idle to 6,497 (108.7%) at Takeoff Torque 72 psi for 10 sec. 80 psi for 3 sec. Rotor Limits and Engine Operating Speeds Limits and Speeds for 250-C18A or 250-C18C Power Off (Rotor) Power On (Engine) Maximum: 514 rpm Maximum: 104% N2 Minimum: 400 rpm Minimum: 103% N2 Limits and Speeds for 250-C20 Power Off (Rotor) Power On (Engine) Maximum: 523 rpm Maximum: 104% N2 Minimum: 400 rpm Minimum: 103% N2 Airspeed Limits VNE (Never Exceed Speed) at sea level is 130 knots (150 mph) CAS. For reduction of VNE with altitude, and temperature, see Rotorcraft Flight Manual. H3WE Page 10 III Model 369H (Normal Category Helicopter), Approved November 15, 1966 Model 369HM (Normal Category Helicopter), Approved April 8, 1968 Model 369HS (Normal Category Helicopter), Approved January 3, 1969 Model 369HE (Normal Category Helicopter), Approved May 21, 1969 (cont.) Center of Gravity (C.G.) Range 369H, 369HM, and 369HS; S/N 0001 through 0100 Longitudinal: Sta. 97 to 104 Lateral: 3 inches right and left of helicopter centerline 369HM, 369HS, and 369HE; S/N 0101 and up Longitudinal Lateral Gross Weight (lb.) Forward (Sta.) Aft (Sta.) Left (in.) Right (in.) 2401 to 2550 99 104 -3 +3 2201 to 2400 97 104 -3 +3 2001 to 2200 97 104 -3 +4 2001 to 2200 97 105 -1 +3 2000 or Below 97 104 -3 +5 2000 or Below 97 106 -1 +3 Note: Facing forward, + indicates right, and – indicates left of helicopter centerline. Leveling Means Plumb bob at Sta. 92.64 Maximum Weight 369H, 369HM, and 369HS; S/N 0001 through 0100: 2,400 lb. 369HM, 369HS, and 369HE; S/N 0101 and up: 2,550 lb. See NOTE 1 for weight and balance report. See NOTE 9 for external cargo information. Number of Seats 369H, 369HS, and 369HE: 1 at Sta. 71.5, 2 at Sta. 73.5, 2 at Sta. 105. 369HM: 2 at Sta. 73.5, 2 at Sta. 105. Maximum Cargo 50 lb. evenly distributed in utility storage compartment at Sta. 55. 369H, 369HM, and 369HS; S/N 0001 through 0100: 950 lb. at 115 lb./sq. ft., Sta. 78.5 to 124 369HM, 369HS, and 369HE; S/N 0101 and up: 1300 lb. at 115 lb./sq. ft., Sta. 78.5 to 124 Fuel Capacity Model and Applicable Serial Numbers Total Tank Capacity (lbs.) Trapped Fuel * (lbs.) Total Unusable Fuel ** (lbs.) Usable Fuel Capacity (lbs.) 369H - All S/Ns 416 1.40 3.40 413 369HM 0001 thru 0100M 402 0.16 1.50 400 0101M and up 402 0.16 2.50 399 369HS 0001S thru 0100S 416 1.40 3.40 413 0101S and up 416 1.40 3.70 412 369HE 0101E and up 416 1.40 3.70 412 H3WE Page 11 III Model 369H (Normal Category Helicopter), Approved November 15, 1966 Model 369HM (Normal Category Helicopter), Approved April 8, 1968 Model 369HS (Normal Category Helicopter), Approved January 3, 1969 Model 369HE (Normal Category Helicopter), Approved May 21, 1969 (cont.) Fuel Capacity (cont’d) *Fuel which cannot be drained from the tank through the drain provided - with the helicopter in the normal ground attitude **Fuel which cannot be used safely in all flight attitudes, and which cannot be included in the empty weight. This includes trapped fuel. Note: Fuel capacities are total tank capacities over and above unusable fuel. Fuel weights are based on JP-4 fuel. Oil Capacity Engine Oil (lb. at Sta. 138.2) Transmission Oil (lb. at Sta. 105.0) 5.90 7.00 Note: Oil capacities are total tank capacities over and above trapped oil. Maximum Operating Altitude See Rotorcraft Flight Manual. Main Rotor Blade Movements Collective pitch (Relative to rigging position): Up and Down 15.5° (±1.25°) Cyclic pitch (Relative to rigging position): Forward 16° (±1°) Aft 8.5° (±0.5°) Left 8.25° (±1.25°) Right 6.25° (±0.75°) Note: Collective low pitch stop to be established in accordance with RFM or HMI to obtain proper autorotation rpm. Main Rotor Blade Damper Setting Torque to move the damper shaft through the low load stage: P/N Minimum Torque (in - lb) Maximum Torque (in - lb) 369A1400 265 325 369A1417 190 200 369ASK1939 190 200 369A1423 190 200 Tail Rotor Blade Movements 369A1620 Tail Rotor Assembly (aluminum blades) Collective pitch thrust to right +27° (±1°) thrust to left -15° (±1°) 369A1600 Tail Rotor Assembly (fiberglass blades) Collective pitch thrust to right +28° (+2°, -0°) thrust to left -13° (±1°) H3WE Page 12 III Model 369H (Normal Category Helicopter), Approved November 15, 1966 Model 369HM (Normal Category Helicopter), Approved April 8, 1968 Model 369HS (Normal Category Helicopter), Approved January 3, 1969 Model 369HE (Normal Category Helicopter), Approved May 21, 1969 (cont.) Manufacturer’s Serial Numbers 369H 0001 through 0005 369HM 0001 through 0004, 0005M and up 369HS 0001S and up 369HE 0001E and up The following helicopters have been manufactured under Delegation Option Authorization provisions of FAR 21. Acting as Delegation Option Manufacturer Number WE-1, Hughes Tool Company, Aircraft Division, was authorized to issue Airworthiness Certificates for the following helicopters under the Delegation Option Authorization provisions of FAR 21. 369H 0001 through 0005 369HE 0101E through 0110E 0201E through 0215E 369HM 0001 through 0004 0005M through 0021M 0030M through 0054M 0201M through 0204M 369HS 0001S through 0002S 0101S through 0130S 0201S through 0215E See NOTE 6 for serial number coding. Certification Basis CAR 6 dated December 20, 1956, including Amendments 6-1 through 6-4 and Special Conditions, "Conditions Establishing Compensating Factors Providing an Equivalent Level of Safety Under Civil Air Regulations, Section 6.10, for Light Turbine Powered Helicopters," dated October 2, 1962, as revised February 8, 1966. Models 369H, 369HM, 369HS, and 369HE were approved under the Delegation Option Authorization provisions of FAR 21. Type Certificate H3WE Amended: 369H November 15, 1966 369HS January 3, 1969 369HM April 8, 1968 369HE May 21, 1969 Dates of Application for Amended Type Certificate: 369H September 8, 1965 369HS August 12, 1968 369HM February 16, 1968 369HE August 12, 1968 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. All required equipment that must be installed as well as optional equipment installations are listed in the following reports. Model Report Number Title 369H 369-E-5003 Model 369H Equipment List 369HM 369-E-5005 Model 369HM Equipment List (S/N 0001 through 0004) H3WE Page 13 III Model 369H (Normal Category Helicopter), Approved November 15, 1966 Model 369HM (Normal Category Helicopter), Approved April 8, 1968 Model 369HS (Normal Category Helicopter), Approved January 3, 1969 Model 369HE (Normal Category Helicopter), Approved May 21, 1969 (cont.) Equipment (cont’d) Model Report Number Title 369HM 369-E-5006 Model 369HM Equipment List (S/N 0005M and subsequent) Model Report Number Title 369HS 369-E-0004 Model 369HS Equipment List 369HE 369-E-5007 Model 369HE Equipment List Approved Publications Rotorcraft Flight Manuals Model Configuration Date 369HM A September 13, 1973 369HM B May 3, 1974 369HM C October 5, 1793 369HS A December 21, 1977 369HS B December 21, 1977 369HE A August 14, 1973 369HE B August 14, 1973 IV Model 369D (Normal Category Helicopter), Approved 8 December 1976 Model 369D (Restricted Category Helicopter), Approved 28 November 1979 Model 369E (Normal Category Helicopter), Approved 15 December 1982 See NOTE 14 for noise characteristics. See NOTE 15 for conversion of model 369E to Model 369FF. Engine Rolls-Royce Corporation (formerly Allison Engine Company) 250-C20B with Bendix fuel control Alternate engine: Rolls-Royce Corporation (formerly Allison Engine Company) 250-C20R/2 Note: Model 369D and 369E helicopters are eligible for installation of the alternate engine when modified in accordance with drawing 369D298000, Revision C, or later FAA approved revisions. Refer to MDH Drawing 369D28702 for engine configuration. The MDH part number and ship effectivity are shown in the HMI IPC as reference. H3WE Page 14 IV Model 369D (Normal Category Helicopter), Approved 8 December 1976 Model 369D (Restricted Category Helicopter), Approved 28 November 1979 Model 369E (Normal Category Helicopter), Approved 15 December 1982 (cont.) Fuel MIL-DTL-5624, Grade JP-4, and JP-5 Aviation Fuels MIL-DTL-83133 Grade JP-8 Aviation Fuel ASTM D-1655 Jet A, A-1 or Jet B ASTM D-6615 Jet B Chinese Specification GB6537-94 Grade RP-3 See “Rotorcraft Flight Manual” for alternate fuels. See “NOTE 7” for Anti-Icing additive. See “Engine TCDS E4CE Note #9” for emergency use mixtures and limits. Note: Fuels containing Tri-cresyl-phosphate additives shall not be used. Engine Limits Ratings for 250-C20B Takeoff (5 min) Max. Continuous Shaft Horsepower 375 350 Torque 318 ft. - lb. (87.2 psi) 297 ft. - lb.(81.3 psi) Gas Producer rpm, N1 53,519 (105%) 53,519 (105%) Output Shaft rpm, N2 6,196 (103%) 6,196 (103%) Measured Gas Temp. 1,490°F (810°C) 1,360°F (738°C) Ratings for 250-C20R/2 Takeoff (5 min) Max. Continuous Shaft Horsepower 375 350 Torque 318 ft. - lb. (87.2 psi) 297 ft.- lb. (81.3 psi) Gas Producer rpm, N1 53,519 (105%) 53,519 (105%) Output Shaft rpm, N2 6,196 (103%) 6,196 (103%) Measured Gas Temp. 1,490°F (810°C) 1,385°F (752°C) Transient Limits for 250-C20B or 250-C20R/2 Measured Gas Temp. (6 sec. limit) 1,490°F (810°C)