# TCDS H3WE: MD Helicopters LLC - Type: Type certificate data sheet - Status: Current - Holder: MD Helicopters LLC - Revision: 32 - Revised: May 30, 2024 - Product: Aircraft, Rotorcraft - Certification basis: CAR 6 - Registered aircraft: 718, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/dc/88/dc88884d77e95ac210f6a3cc7e9b8e686fd41f6a81aaf65acc35594289317601 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID190975937020240531154320.0001 - Page: https://openairdocs.org/tcds/H3WE ## Models (12) As the data sheet lists them. - 369D - 369E - 600N - 369F - 369FF - 369HS - 369HM - 500N - 369HE - 369H - 369 (Army YOH-6A) - 369A (Army OH-6A) ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text 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) 1,550°F (843°C) - C20B only 1,650°F (899°C) - C20R/2 only Measured Gas Temp. During Start (10 sec. limit) 1,490°F (810°C) to 1,700°F (927°C) (1 Sec. 1700°F) Gas Producer rpm, N1 (15 Sec. limit) 54,028 (106%) Output Shaft rpm, N2 (15 Sec. limit) 6,798 (113%) at Idle to 6,316 (105%) at Takeoff Rotor Speed and Engine Operating Speeds Limits and Speeds for 250C20B or 250-C20R2 Power Off (Rotor) Power Off (Rotor) Maximum: 523 rpm Maximum: 492 rpm/103 % N2 Minimum: 410 rpm* Minimum: 487 rpm / 102% N2 * Minimum with 4-bladed tail rotor installed: 415 rpm. H3WE Page 15 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.) Airspeed Limits VNE (Never Exceed Speed) at sea level is 152 knots (175 mph) CAS. For reduction of VNE with altitude and temperature: The 369D autorotation VNE at sea level is 127 knots (146 mph) CAS. The 369E autorotation VNE at sea level is 130 knots (150 mph) CAS. Center of Gravity (C.G.) Range Longitudinal Lateral Gross Weight (lb.) Forward (Sta.) Aft* (Sta.) Left (in.) Right (in.) 3000 99 103 -3 +3 1538 99 107.4 -3 +3 * Varies linearly between points shown. NOTE: Facing forward, + indicates right and – indicates left of helicopter centerline. Leveling Means Plumb bob at Sta. 92.64 Maximum Weight 3,000 lb. See NOTE 1 for weight and balance report. See NOTE 9 for maximum weight of 369D (Restricted Category Helicopter). Number of Seats 1 at Sta. 71.5, 2 at Sta. 73.5, 2 at Sta. 105 for basic configuration only. Maximum Cargo 1,300 lb. at 115 lb/sq-ft, Sta. 78.5 to 124. See NOTE 9 for external cargo information Fuel Capacity Fuel System Total Tank Capacity (lb.) Trapped Fuel * (lb.) Total Unusable Fuel ** (lb.) Usable Fuel Capacity (lb.) 369A8100 416 0 12.5 403 369H90029 (self sealing) 402 0 12.5 389 369F8100*** 391 0 18.2 372 *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. *** Crash Resistant Fuel System – Serial numbers 0626E and subsequent 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. 133.3) Transmission Oil (lb. at Sta. 105.0 6.00 11.60 Note: Oil capacities are total tank capacities over and above trapped oil. H3WE Page 16 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.) Maximum Operating Altitude 16,000 ft. density altitude. For 369E with 250-C20B Engine and Crash Resistant Fuel System – 11,500ft, pressure altitude. Main Rotor Blade Movements Collective pitch (Relative to rigging position): Up and Down 14.25° to 18.0° Cyclic pitch (Relative to rigging position): Forward 17° to 18.5° Aft 7° to 9.3° Left 7° to 9.3° Right 5.5° to 8.5° Tail Rotor Blade Movements 369D21600 Tail Rotor Assembly (2-bladed) Collective pitch thrust to right 27° to 27° thrust to left -13° to -15° 369D21620 Tail Rotor Assembly (4-bladed) Collective pitch thrust to right 31° to 32° thrust to left -13° to -15° Horizontal Stabilizer Incidence 8.92° to 9.42° measured relative to a line perpendicular to the main rotor mast centerline. Manufacturer’s Serial Numbers 369D 0003 and up 369E 0001 and up See NOTE 5 for serial numbers not eligible. See NOTE 6 for serial number coding. Certification Basis Basic Aircraft 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. Model 369E Glass Cockpit Installations All basic aircraft requirements with the glass cockpit required installations certified under 14 CFR Part 27 Amendment 27-1 through 27-47, dated 30 January 2012. Model 369E Crash Resistant Fuel System All basic aircraft requirements with the crash resistant fuel system installation certified under 14 CFR Part 27.952 (Original), 14 CFR 27.963 (27-30), 27.967 (Original), 27.973 (Original), and 27.975 (27-35). H3WE Page 17 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.) Type Certificate H3WE amended: 369D December 8, 1976 369D (Restricted Category): November 28, 1979 369E December 15, 1982 Dates of Application for amended Type Certificate: 369D May 30, 1974 369D (Restricted Category): November 26, 1979 369E December 10, 1982 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. Equipment (cont’d) 369D 369-E-5008 Model 369D Equipment List 369E 369-E-5009 Model 369E Equipment List Approved Publications Rotorcraft Flight Manuals 369D CSP-D-1 Dated December 8, 1976 369E (Basic) CSP-E-1 Dated November 23, 1982 369E (Glass) CSP-E-2 Dated May 26, 2022 V Model 369F (Normal Category Helicopter), Approved July 29, 1983 Model 369FF (Normal Category Helicopter), Approved July 11, 1985 See NOTE 12 for conversion of 369F to 369FF. 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-C30. Refer to MDH Drawing 369D28640 for engine configuration used in production (S/N 0128FF and prior). RRC P/N 23062052 used in production effective S/N 0129FF and subs and earlier S/N if Technical Bulletin TB369F-004 is incorporated. 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 E1GL Note #10 for emergency use mixtures and limits. Note: Fuels containing Tri-cresyl-phosphate additives shall not be used. JP – 5 not allowed with Crash Resistant Fuel System Equipped helicopters. H3WE Page 18 V Model 369F (Normal Category Helicopter), Approved July 29, 1983 Model 369FF (Normal Category Helicopter), Approved July 11, 1985 (cont.) Engine Limits Ratings for 369F Takeoff (5 min) Max. Continuous Shaft Horsepower 375 350 Torque 327.4 ft-lb (52.5 psi) 305.6 ft-lb (48.9 psi) Gas Producer rpm, N1 53,550 (105%) 53,550 (105%) Output Shaft rpm, N2 6,016 (100%) 6,016 (100%) Measured Gas Temp. 1,414°F (768°C) 1,281°F (694°C) Engine Limits (cont’d) Ratings for 369FF Takeoff (5 min) Max. Continuous Shaft Horsepower 425* 350 Torque 371.0 ft-lb* (59.6 psi) 305.6 ft-lb (48.9 psi) Gas Producer rpm, N1 53,550 (105%) 53,550 (105%) Output Shaft rpm, N2 6,016 (100%) ,6016 (100%) Measured Gas Temp. 1,414°F (768°C) 1,281°F (694°C) * 0 to 50 KIAS. Transient Limits for 369F and 369FF Measured Gas Temp. During Start and shutdown (10 sec. limit) 1,518°F (826°C) to1,700°F (927°C) (1 sec. at 1,700 F) During Power Change in Flight 1,518°F (826°C) to 1,625°F (885°C) Gas Producer rpm, N1 (10 sec. limit) 54,060 (106%) Output Shaft rpm, N2 (10 sec. limit) 6,377 (106%) Rotor Limits and Engine Operating Speeds Power Off (Rotor) Power On (Engine) Maximum: 508 rpm Maximum: 477 rpm / 100% N2 Minimum: 410 rpm Minimum: 473 rpm / 99% N2 Airspeed Limits VNE (Never Exceed Speed) at sea level is 152 knots (175 mph) CAS. For reduction of VNE with altitude and temperature: Rotorcraft Flight Manual Autorotation V NE at sea level is 127 knots (146 mph) CAS. Center of Gravity (C.G.) Range Longitudinal Lateral Gross Weight (lb.) Forward *(Sta.) Aft** (Sta.) Gross Weight (lb.) Left *** (in.) Right *** (in.) 3,100 99 103.3 3,100 -3 +3 2,600 99 104.8 2,000 -3 +3 1,700 101.7 107.5 1,700 -1.7 +1.7 *Varies linearly between 2600 lb. and 1700 lbs. **Varies linearly between 3100 lb. and 1700 lbs. ***Varies linearly between 2000 lb. and 1700 lbs. H3WE Page 19 V Model 369F (Normal Category Helicopter), Approved July 29, 1983 Model 369FF (Normal Category Helicopter), Approved July 11, 1985 (cont.) Leveling Means Plumb bob at Sta.92.64. Maximum Weight 3,350 lb. Serial numbers 0340FF and subsequent. Serial numbers with TB369F-015 applied. 3,100 lb. All other serial numbers. See NOTE 1 for weight and balance report. Number of Seats 1 at Sta. 71.5, 2 at Sta. 73.5, 2 at Sta. 105 for basic configuration only. Maximum Cargo 1,300 lb. at 115 lb./sq-ft, Sta. 78.5 to 124. See NOTE 9 for external cargo information. Fuel Capacity Fuel System Total Tank Capacity (lb.) Trapped Fuel * (lb.) Total Unusable Fuel ** (lb.) Usable Fuel Capacity (lb.) 369A8100 416 0 12.5 403 369H90029 (self sealing) 402 0 12.5 389 369F8100*** 391 0 18.2 372 * 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. *** Crash Resistant Fuel System – Serial Numbers 0334FF and Subsequent 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. 133.3) Transmission Oil (lb. at Sta. 105.0 6.00 11.60 Note: Oil capacities are total tank capacities over and above trapped oil. Maximum Operating Altitude 16,000 ft. density altitude Main Rotor Blade Movements Collective Pitch (relative to rigging position): Up and Down 14.25° to 18.0° Cyclic Pitch (relative to rigging position): Forward 17° to 18.5° Aft 7° to 9.3° Left 7° to 9.3° Right 5.5° to 8.5° H3WE Page 20 V Model 369F (Normal Category Helicopter), Approved July 29, 1983 Model 369FF (Normal Category Helicopter), Approved July 11, 1985 (cont.) Tail Rotor Blade Movements 369D21600 Tail Rotor Assembly (2-blades) Collective Pitch Thrust to Right 27° to 29° Thrust to Left -13° to -15° Horizontal Stabilizer Incidence 7.50° to 8.00° measured relative to a line perpendicular to the main rotor mast centerline. Manufacturer’s Serial Numbers 369F 0003 and up. 369FF 0001 through 0599 0600 through 0699 (369E conversion with pre-generic wiring) 0700 and up (369E conversion with generic wiring) See NOTE 5 for serial numbers not eligible. See NOTE 6 for serial number coding. Certification Basis Basic Aircraft 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, and FAR 21.21 providing for equivalent level of safety in lieu of CAR 6.412. 14 CFR Part 36, amendments 36-1 through 36-30, Appendix J. Glass Cockpit Installations All basic aircraft requirements with the glass cockpit required installations certified under 14 CFR Part 27 Amendment 27-1 through 27-47, dated 30 January 2012. Crash Resistant Fuel System All basic aircraft requirements with the crash resistant fuel system installation certified under 14 CFR Part 27.952 (Original), 14 CFR 27.963 (27-30), 27.967 (Original), 27.973 (Original), and 27.975 (27-35). Type Certificate H3WE amended 369F July 26, 1983 369FF July 11, 1985 Dates of Application for amended Type Certificate 369F January 7, 1983 369FF June 6, 1985 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 following reports: 369F 369-E-5010 Model 369F Equipment List 369FF 369-E-5011 Model 369FF Equipment List H3WE Page 21 V Model 369F (Normal Category Helicopter), Approved July 29, 1983 Model 369FF (Normal Category Helicopter), Approved July 11, 1985 (cont.) Approved Publications Rotorcraft Flight Manuals 369F CSP-F-1 Dated July 29, 1983 369FF (Basic) CSP-FF-1 Dated July 11, 1985 Reissued October 25, 1985 369FF (Glass) CSP-FF-2 Dated June 14, 2018 VI Model 500N (Normal Category Helicopter), Approved September 12, 1991 See NOTE 14 for noise characteristics. Engine Rolls-Royce Corporation (formerly Allison Engine Company) 250-C20R/2. Refer to MDH Drawing 369D28702 for engine configuration. The MDH part number and ship effectivity are shown in the HMI IPC as reference. 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 E1GL Note #10 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 425 375 Torque 371.0 ft. - lb. (101.8 psi) 327.4 ft .- lb. (89.8 psi) Gas Producer rpm, N1 53,519 (105%) 53,519 (105%) Output Shaft rpm, N2 6,016 (100%) 6,016 (100%) Measured Gas Temp. 1,490°F (810°C) 1,385°F (752°C) Transient Limits for 250-C20R/2 Takeoff (5 min) Shaft Horsepower 425 Torque 371.0 ft. - lb. (101.8 psi) Gas Producer rpm, N1 53,519 (105%) Output Shaft rpm, N2 6,016 (100%) Rotor Limits and Engine Operating Speed Power Off (Rotor) Power On (Engine) Maximum: 508 rpm Maximum: 477 rpm / 100% N2 Minimum: 410 rpm Minimum: 473 rpm / 99% N2 Airspeed Limits VNE (Never Exceed Speed) at sea level is 152 knots (175 mph) CAS. For reduction of VNE with altitude, and temperature see Rotorcraft Flight Manual. Autorotation VNE at sea level is 130 knots (149 mph) CAS. H3WE Page 22 VI Model 500N (Normal Category Helicopter), Approved September 12, 1991 (cont.) Center of Gravity (C.G.) Range Longitudinal Lateral Gross Weight (lb.) Forward * (Sta.) Aft** (Sta.) Gross Weight Weight left*** (in.) Right*** (in.) 3350 99 105.5 3350 -3 +3 2600 99 107.8 2000 -3 +3 1796 101.4 110.3 1796 -2.2 +2.2 *Varies linearly between 2600 lbs. and 1796 lbs. **Varies linearly between 3350 lbs. and 1796 lbs. ***Varies linearly between 2000 lbs. and 1796 lbs. Note: Facing forward, + indicates right, and - indicates left of helicopter centerline. Leveling Means Plumb bob at Sta. 92.64. Maximum Weight 3,350 lb. See NOTE 1 for weight and balance report. Number of Seats 1 at Sta. 71.5, 2 at Sta. 73.5, 2 at Sta. 105 Maximum Cargo 1,300 lb. at 115 lb/sq-ft, Sta. 78.5 to 124. See NOTE 9 for external cargo information. Fuel Capacity Fuel System Total Tank Capacity (lb.) Trapped Fuel* (lb.) Total Unusable Fuel** (lb.) Usable Fuel Capacity (lb.) 369A8100 416 0 12.5 403 369H90029 (self sealing) 402 0 12.5 389 * 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 usable fuel. F uel weights are based on JP-4 fuel. Oil Capacity Engine Oil (lb. at Sta. 133.3) Transmission Oil (lb. at Sta. 105.0) 6.00 11.60 Note: Oil capacities are total tank capacities over and above trapped oil. Maximum Operating Altitude 20,000 ft. density altitude. Main Rotor Blade Movements Collective Pitch (relative to rigging position): Up and Down 14.25° to 18.0° Cyclic Pitch (relative to rigging position): forward 17° to 18.5º aft 7º to 9.3° left 7º to 9.3° H3WE Page 23 VI Model 500N (Normal Category Helicopter), Approved September 12, 1991 (cont.) Fan Blade Movements 500N5010 NOTAR Fan Installation Minimum 26º ±1º (Rig Position) Full Right Pedal 52º ±2º Full Left Pedal 71º ±2º Horizontal Stabilizer Incidence -1.9° nose down with respect to waterline plane. Vertical Stabilizer Movements Left Vertical* Right Vertical** Leading Edge Left*** -6.5º ± 0.5º -4.0º ± 0.5º Leading Edge Right*** +22.5º ± 0.5º +8.0º ± 0.5º Travel, minimum linear in. at trailing edge 6.46 2.70 *Connected to directional control system. **Connected to yaw SAS. ***Relative to rigging position Manufacturer’s Serial Numbers LN001 and up 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. In addition, height velocity testing is required to 7000 feet, in accordance with paragraphs 6.111 and 6.116, as amended by Amendment 6-7, issued October 8, 1963. 14 CFR Part 36, amendments 36-1 through 36-18, Appendix J. 14 CFR Part 27 sections listed below are applicable to the NOTAR system Regulations Amendments 27.143* (a), (b), (c), (d), (e) 27-21 27.399 27-1 27.571 27-18 27.605 (b) 27-16 27.672** 27-21 27.927 (b) 27-12 27.1529 27-18 * Replaces CAR 6.121 (a), (b), (c), (e) ** Applicable to the yaw stability augmentation system. Type Certificate H3WE amended 500N September 12, 1991 Dates of Application for amended Type Certificate 500N July 11, 1988 H3WE Page 24 VI Model 500N (Normal Category Helicopter), Approved September 12, 1991 (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 following reports: 500N 500N-CE-0059 Model 500N Basic Weight Checklist Approved Publications Rotorcraft Flight Manuals 500N CSP-520N-1 Dated September 12, 1991 VII Model 600N (Normal Category Helicopter) Approved May 15, 1997 Aircraft Type Designator (FAA & ICAO) HU60 Engine Rolls Royce Corporation (formerly Allison Engine Company) 250-C47M 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 E1GL Note #10” for emergency use mixtures and limits. Note: Fuels containing Tri-cresyl-phosphate additives shall not be used. Engine Oil Engine oil conforming to MIL-PRF-7808 or MIL-PRF-23699 and subsequent revisions are authorized for use. See Rolls-Royce Corporation (formerly Allison Engine Company) Operation and Maintenance Manual, CSP21004 (latest revision), for approved oil manufacturers. H3WE Page 25 VII Model 600N (Normal Category Helicopter) Approved May 15, 1997 (cont.) Engine Limits Ratings Takeoff (5 min.) Max. Continuous Shaft Horsepower 600 shp 530 shp Torque 524 ft-lb. (600 Q(3) ) 463 ft-lb. (530 Q(3) ) Gas Producer rpm (N1) 53,550 (105%) 53,550 (105%) Output Shaft and Power Turbine rpm (N2) (Same as Continuous.) 6858 rpm output shaft, 34,941 rpm power turbine (114%)(2) at autorotation torque varying linearly to 6443 rpm output shaft, 32,826 rpm power turbine (107.1%) at 590(1) ft-lbs torque. Turbine Outlet Temp. 1435oF (779oC) 1,340oF (727oC) less than 10,000 ft. pressure altitude. ,1256oF (680 oC) 10,000 ft. pressure altitude or greater. Transient Ratings Condition Time Limit Parameter Limit Torque 10 seconds 576 ft-lbs (660 Q(3) ) Turbine Outlet Temperature Start and Shutdown 10 seconds 1,550oF (843oC) to but not including 1700oF (927oC) Start and Shutdown 1 second 1,700oF (927oC) During Power Change in Flight 12 seconds 1,435oF (779oC) to 1,662oF (905oC) Gas Producer rpm, N1 10 seconds 54,060 rpm, 106 % Output Shaft and Power Turbine rpm, N2 15 seconds 7,159 rpm output shaft, 36,474 rpm power turbine (119%)(2) at autorotation torque varying linearly to 6,557 rpm output shaft, 33,409 rpm power turbine (109%) at 590(1) ft-lbs torque. (1)Note: Aircraft torque limit is 524 ft-lb. (2)Note: Aircraft Rotor RPM limit is 106.4%. (3)Note: Torque unit. H3WE Page 26 VII Model 600N (Normal Category Helicopter) Approved May 15, 1997 (cont.) Rotor Limits and Engine Operating Speeds Power Off (Rotor/Engine) Power On (Rotor/Engine) Maximum - 506 rpm (106.4%) Maximum - 480.1 rpm/101%(3) N2 Minimum - 428 rpm (90%) Minimum - 470.6 rpm/99%(3) N2 (3)Note: ECU Governs Rotor RPM between 99.25% and 100.75%. Airspeed Limits VNE (Never Exceed Speed) power-on at sea level is 155 knots (178 mph) IAS for 3,600 lbs. or less internal gross weight; 145 knots (167 mph) IAS for 3,601 lbs. to 3,800 lbs. internal gross weight; 135 knots (156 mph) IAS for 3801 lbs or more internal gross weight. VNE power-off (autorotation) at sea level is 115 knots (132 mph) IAS. For reduction of VNE with altitude and temperature, see FAA approved Rotorcraft Flight Manual. Center of Gravity See FAA approved Rotorcraft Flight Manual for variation of CG limit with gross weight, nominal limits are 91.0 to 100.0 longitudinal, -5.0 to +5.0 lateral. Leveling Means Plumb bob at station 81.54. Maximum Weight 4,100 lbs. (1860 kg) at sea level. See RFM for variation of maximum weight with density altitude. See NOTE 16 for weight and balance report. Minimum Crew 1 (pilot) Maximum Occupants 8 (includes crew) Maximum Cargo 1350 lbs. at 115 lb. / sq. ft., sta. 48.5 to 124.0. 612 kg at 561.5 kg / sq. meter, sta 48.5 to 124.0 Outside Air Temperature Limits -40 to + 51.9 C (-40 to +125F) (OAT at Sea Level See RFM for variation at altitude) Engine Cold Start Limits -40°C (-40°F) Fluid Capacity Liters Imp. Gal. U.S. Gal. Fuel Usable 433.8 95.5 114.6 Unusable 6.1 1.3 1.6 Total 439.9 96.8 116.2 Main Trans. Oil Total 6.62 1.46 1.75 Hydraulic Fluid (Rotor Brake) Total 0.118 0.026 0.031 Engine Oil Total 2.95 0.65 0.78 Maximum Operating Altitude 20,000-ft density altitude, 18.700-ft pressure altitude with JP-4 or Jet-B, or 20,000-ft pressure altitude with Jet-A, Jet-A1, JP-5, or JP-8; whichever is lower. Main Rotor Blade Movements Collective Pitch (relative to rigging position) Up to Down 17.1° to 21.6° H3WE Page 27 VII Model 600N (Normal Category Helicopter) Approved May 15, 1997 (cont.) Main Rotor Blade Movements (cont) Cyclic (relative to rigging position) Forward 18.2° to 19.7° Aft 11.5° to 13.5° Left 7.6° to 9.6° Right 5.2° to 7.2° Fan Blade Movements Minimum 26° ± 1° Full Right Pedal 54° ± 2° Full Left Pedal 73° ± 2° Horizontal Stabilizer Incidence 1.9° nose down with respect to waterline plane. Vertical Stabilizer Movements Vertical Stabilizer (relative to rigging position) Left Right Leading Edge Left -10.5° ± 0.5° -14.5° ± 0.5° Leading Edge Right +23.5o  1o +19.5o  1o Travel, minimum linear inches at trailing edge 7.1 inches 7.1 inches Certification Basis Basic Aircraft 14 CFR Part 27 dated October 2, 1964, through Amendment 27 -30 with the following deviations: 27.562 and 27.863 excluded (earlier models did not have these requirements); 27.561 at Amendment 27-24; 27.607 at Amendment 27-3; 27.785 at Amendment 27-20; 27.1325 at Amendment 27-12; 14 CFR Part 36, amendments 36-1 through 36-21, Appendix J. Special Condition High-Intensity Electromagnetic Radiation Fields (H.I.R.F.) protection per 14 CFR 21.16 effective January 29, 1997, as published in the Federal Register FR 66, Page No. 4134, dated January 29, 1997. Equivalent Level of Safety The N1 gauge has shown compliance to 27.1549(b) through an alternate means. Glass Cockpit Installations 14 CFR Part 27 Amendments 27-1 through 27-47, dated January 30, 2012. H3WE Page 28 VII Model 600N (Normal Category Helicopter) Approved May 15, 1997 (cont.) Manufacturer’s Serial Numbers S/N RN003 and subsequent See “NOTE 6” for serial number coding. 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. Approved Publications Rotorcraft Flight Manuals 600N (Basic) CSP-600RFM-1 Dated May 15, 1997 600N (Glass) CSP-600RFM-2 Dated July 26, 2017 Airworthiness Limitations Section (ALS) CSP-600HMI-2, Section 04-00-00 of the MDH Model Helicopters Model 600N Basic Handbook of Maintenance Instructions VIII Data Pertinent to all Models Service Life Limits See NOTE 3 for list of life limited components for 369, 369A, 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, and 369FF aircraft manufactured on or before June 20, 1991. See Airworthiness Limitations Section (ALS) of Handbook of Maintenance Instruction (HMI) for the life limited components for 369D, 369E, 369F, and 369FF aircraft manufactured after June 20, 1991. See Airworthiness Limitations Section of HMI for the life-limited components for 500N and 600N aircraft. The HMI ALS and the Life Limit Schedule (NOTE 3 of the TCDS) specify that Service Life Limited parts are retired according to an FAA approved schedule. These values of retirement or service life cannot be increased without approval by FAA engineering. Production Basis Production Certificate No. 410NM was utilized through February 18, 1999 for the 369, 369A, 369H, 369HM, 369HS, 369HE, 369D, 369E, 369F, 369FF, 500N, and 600N helicopters. Effective February 18, 1999 the Type Certificate (TC) No. H3WE was transferred to MD Helicopters Inc. (MDH), the new TC holder. MDH has licensed back to McDonnell Douglas Helicopter Company (MDHC) to build the 369E, 369FF, 500N, and 600N helicopters under a new Production Certificate No. 714NM. Effective February 19, 1999 the following serial number helicopters were built under PC 714NM. 369E 0542 and 0543 369FF 0134 through 0137 500N LN086 through LN089 600N RN047, RN052 and RN054 H3WE Page 29 VIII Data Pertinent to all Models (cont.) Production Basis (cont.) On November 5, 1999 MD Helicopters, Inc. received Production Certificate PC 715NM under which MDH was authorized to manufacture the 369E, 369FF, 500N and 600N helicopters. Effective November 5, 1999 the following serial number helicopters and subsequent will be built under PC715NM. 369E 0544 and subsequent 369FF 0138 and subsequent 500N LN090 and subsequent 600N RN053, RN055 and subsequent NOTE 1 A current weight and balance report, including a list of equipment included in certificated empty weight and loading instructions, must be provided for each helicopter at the time of original airworthiness certification and at all times thereafter, except in the case of operators having an approved weight control system. NOTE 2 The following placard must be installed in clear view of the pilot: "This Helicopter must be operated in compliance with the operating limitations specified in the Rotorcraft Flight Manual.” For additional placards, see Rotorcraft Flight Manual. NOTE 3 Information essential to the proper maintenance of these helicopters is contained in the Manufacturer's Handbook of Maintenance Instructions (HMI) which is provided with each civil helicopter at the time of delivery to the operator. These handbooks specify that Service Life Limited parts are retired according to an FAA approved schedule. These values of retirement or service life cannot be increased without approval by FAA engineering. For Models 369D, 369E, 369F, and 369FF aircraft manufactured after June 20, 1991, see the Airworthiness Limitations Section of the HMI for the Limited Life Schedule. For Model 500N and 600N aircraft see the Airworthiness Limitations Section of the HMI f or the Limited Life Schedule. Model Applicability Codes for Aircraft Manufactured on or Prior to June 20, 1991 A Model 369 For a list of critical parts and life limits contact: Federal Aviation Administration Manager Los Angeles Aircraft Certification Office 3960 Paramount Boulevard Lakewood, California 90712-4137 B Model 369 For a list of critical parts and life limits contact: Federal Aviation Administration Manager Los Angeles Aircraft Certification Office 3960 Paramount Boulevard Lakewood, California 90712-4137 H3WE Page 30 VIII Data Pertinent to all Models (cont.) C Model 369A; S/N 1446 and up or S/N 0001 through 1445 with M30242 Kit; and Models 369HM, 369HS, and 369HE; S/N 0001 and up with Rolls-Royce Corporation (formerly Allison Engine Company) 250-C18A or 250-C18C engine, unless otherwise noted. D Model 369H, 369HM, 369HS; S/N 0101 and up with Rolls-Royce Corporation (formerly Allison Engine Company) 250-C20 engine, unless otherwise noted. E Model 369D; S/N 003 and up, Model 369E S/N 0001 and up, Model 369F S/N 0003 and up and Model 369FF S/N 0001and up, unless otherwise noted. Limited Life Schedule Applicability: Component see Note (1) B, C, D Part Number (5) B Hours /TE (11) C Hours /TE (11) D Hours /TE (11) E Part Number (5) E Hours /TE (11) Folding pin, main rotor 369A1004 5760 5760 5760 369A1004-BSC 369A1004-3 369A1004-5 2850 2850 7600 Applicability: Component see Note (1) B, C, D Part Number (5) B Hours /TE (11) C Hours /TE (11) D Hours /TE (11) E Part Number (5) E Hours /TE (11) Blade, main rotor(7) S/N 0001 to 3499 369A1100-501 1655 1570 1570 S/N 3500 & Sub A000 & Sub 369A1100-501 2440 2440 2440 S/N 3500 & Sub A000 & Sub 369A1100-503 2440 2440 2440 S/N 3500 & Sub A000 & Sub 369A1100-505 2440 2440 2440 S/N D139 thru D203, D209 thru D223 369A1100-507 1,750 /10,600 TE (11) 2440 1,750 /10,600 TE (11) 2440 1,750 /10,600 TE (11) 2440 S/N 3500 & Sub 369A1100-511 3500 3500 3500 Blade, main rotor 369D & 369E blades except listed below: 369D21100 3530 S/N H664, H665, H667, H669, H671, H672, H674, H676, H679, H680, H683, thru H724, H726 thru H999 & J000 thru J039, J041 thru J055 369D21100-517 2,500 /15,000 TE (11) H3WE Page 31 Applicability: Component see Note (1) B, C, D Part Number (5) B Hours /TE (11) C Hours /TE (11) D Hours /TE (11) E Part Number (5) E Hours /TE (11) Blade, main rotor 369F & 369FF except blades listed below 369D21102 3430 S/N 1976 thru 2100, 2106 thru 2115 369D21102-517 2500 /15,000 TE (11) Hub sub-assy., main rotor 369A1201 8900 8900 8900 369D21201 8,900 Pitch housing, main rotor 369A1300 6200 6200 6200 369D21300 9100 369A (Military use only) 369D21300- 501 6200 6200 Retention straps, main rotor(2) 369A1210 2774(2) 2774(2) 2774(2) 369D21210(2) 2770(2) Vertical hinge pin, main rotor 369A1220 369D21220 5490 5490 4220 4220 4220 4220 369A1220 369D21220 6120 6120 Vertical hinge links, main rotor 369A1234 2860 2650 2650 369H1203- BSC, -21, and - 31 6396 6396 6396 369H1203-BSC, - 21, and -31 5762 369H1203-51, and -61 10600 10600 10600 369H1203-51, and -61 11080 Mast assy., main rotor 369A2014 369D22014 5710 5710 5710 5710 5710 5710 369D22014 10450 Lead-Lag Damper 369D21400-501 6060 369D21400-503 (9) M50452 (9) 369A (Military use only) *With 369D21300-501 pitch housing 369D21400- 503 *(9) (9) Long. Idler bellcrank 369A7301 6500 Long. mixer bellcrank 369A7603 13600 H3WE Page 32 Applicability: Component see Note (1) B, C, D Part Number (5) B Hours /TE (11) C Hours /TE (11) D Hours /TE (11) E Part Number (5) E Hours /TE (11) Driveshaft, main rotor 369A5500 369A5520 6500 1990 3960 1740 3960 1300 369D & 369E 369D25510 5020 369F & 369FF 369D25510 3675 Driveshaft, Main trans. (Bendix) 369A5510 3700 3700 3700 369A5510 3790 Driveshaft coupling, main trans. 369H5660 4300 Blade, tail rotor (fiberglass) 369A1710 369A1607 2861 2861 2861 2861 Blade, tail rotor (Aluminum) (10) 369A1613- BSC, -3, -501, -503, -505, - 507, and -509 5600 5600 5600 369D & 369E 369D21613 5200 369D21613-11 -31, -41, & -51 5140 369F & 369FF 369D21606 5140 Blade, tail rotor (4-blade). 369D & 369E only 369D21615 10000 Driveshaft, tail rotor 369F &369FF 369A5518 8730 8730 8730 369D25518 369DSK152-11 369D25518-503 13900 13900 14610 Gearshaft, tail rotor input assy.(1) 369A5406 1800 1800 1800 Gearshaft, tail rotor output assy.(1) 369A5406 2940 2940 2940 Input Gearshaft assembly, tail rotor(1) 369F, 369FF 369A5425* *Except 369A5425-5, which is replaced "on condition". 1800 1800 1800 369D25434 369D25434 12000 3365 Output Gearshaft assembly, tail rotor 369D25430 7290 H3WE Page 33 Applicability: Component see Note (1) B, C, D Part Number (5) B Hours /TE (11) C Hours /TE (11) D Hours /TE (11) E Part Number (5) E Hours /TE (11) Strap assembly tail rotor *When installed with fiberglass tail rotor blades, P/N 369A1710- BSC, -9, - 11, -13, or 369A1607-BSC 369A1706 369A1706* 5100 3250 5100 3250 5100 3250 369A1706 5100 Hub assy., tail rotor 369A1725 3450 Tailboom(6) 369A3500 2674 2450 369D3500 10300 369A & 369HM 2674 2177 Except: 369A & 369HM with 369A1620 tail rotor 1800 1800 1800 369HS & 369HE with 369A1620 tail rotor 2030 2030 2030 369H, 369H, 369HM, 369HS, & 369HE 369A3500-619 1880 1880 1880 Tailboom attach bolts(6) 369A & 369HM Except: 369A, 369HM, 369HS, & 369A1620 tail rotor NAS625-14 MS21250- 05014 2598 2598 2598 2400 2504 2504 2400 2400 2400 MS21250-06014 21950 Horizontal Stab.(6) 369A, 369H, 369HE, 369HM, 369HS Except: 369A & 369HM with 369A1620 aluminum tail rotor 369H, 369HE & 369HS with 369A1620 aluminum tail rotor 369D 369E 369F & 369FF 369A3600 3,150 3,050 3,450 3,050 3,050 3,450 3,050 3,450 369D23601 421-087-505 421-087-905 421-087-503 421-087-903 7,700 7,700 7,700 7,700 7,700 Vertical Stab. 369D & 369E 369F & 369FF 369D23600 369D23600-505 12,700 3,300 H3WE Page 34 Applicability: Component see Note (1) B, C, D Part Number (5) B Hours /TE (11) C Hours /TE (11) D Hours /TE (11) E Part Number (5) E Hours /TE (11) Upper Vertical Stab.(6) 369A , 369H, 369HE, 369HM, 369HS except: 369A & 369HM with 369A1620 aluminum tail rotor 369H, 369HS & 369HE with 369A1620 aluminum tail rotor 369A3625 3,840 3,280 3,840 3,840 3,280 3,840 3,280 3,840 Coupling, tail rotor shaft 369A5501 369H925643 7080 7080 7080 7080 7080 369A5501 369H925643 4980 4980 Damper assy., Landing Gear 369A6300 (4) (4) For 369A (only) 369A6350 (4) Emergency Float (Option) 369H, 369HM, 369HS & 369HE, 369D, 369E, 369F, & 369FF 369H90121 (8) (8) (8) 369D292473-5 -6, -9, -10, -11, and -12 (8) Utility Float Kit 369DSK66 3190 Kit (Option), Stabilizer Support 369D/E only 369D292036 3190 Footnotes to the Limited Life Schedule (1) Life limited components interchanged between models or configurations, including Model 369 series where applicable, must be restricted in the lowest service life indicated for the models or configurations affected. Life limited components removed at retirement are to be destroyed or conspicuously marked to prevent inadvertent return to service. Parts are applicable only on models under which a service is listed. (2) The service life for the strap retention system is a calculated maximum. In actual fact, the strap retention system is an on-condition replacement in accordance with MDH Service Bulletin HN- 214/DN-154/EN-44/FN-33. (3) Used with 369H90123 Rotor Brake Kit. (Not applicable on Model 369A). (4) Must be overhauled at 1200 hour intervals per manufacturer's instructions. (5) Service life shown for basic part number applies to all dash-numbered versions unless otherwise indicated. (6) Applicable to all models and configurations except as noted. H3WE Page 35 (7) Blade serialization sequence as follows: 0001 - 9999, A001 - Z999, AA01 - ZZ99 (8) A life limit of five (5) years from date of manufacture has been established for the Holex, Inc., P/N 12552-1 (Walter Kidde P/N 281993) and Holex, Inc., P/N12754-1 (TAVCO P/N 5003527) SQUIB CARTRIDGES. (9) The 369D21400-503 and 50452 damper assemblies are to continue being inspected for deterioration every 600 hours up to a total time of 4200 hours and every 300 hours thereafter until deterioration is sufficient to retire assembly. Allowable deterioration is denoted in the Handbooks of Maintenance Instructions for the Model 369D, 369E, 369F, and 369FF helicopters. (10) The 369A1613-7, -9, and -11 tail rotor blades are for military use only (OH-6A) and are not FAA certified for Model 369H series helicopters. (11) These Blades are Subject Flight Hour Factoring. See applicable Service Bulletin SB369H -243R3, SB369D-195R3, SB369E-088R3 or SB369F-075R3, SB500N-015R3, SB600N-007R2 dated July 13, 1998 and FAA AD 98-15-26. TE = Torque Events is defined as the transition to a hover from forward flight. For this definition of TE, Forward Flight is considered to be flight at any airspeed after attaining transitional lift. NOTE 4 The following information applies to the U.S. standard and export airworthiness certification of Hughes Model 369 (YOH-6A) and 369A (OH-6A) helicopters: a) The Hughes Model 369 (YOH-6A) and 369A (OH-6A) helicopters were only produced for and delivered to military customers. To meet the basic eligibility requirements for a U.S. standard and export airworthiness certificate, Hughes Model 369 (YOH-6A) and 369A (OH-6A) helicopters must have been issued an FAA Form 8130-2 (previously FAA Form 970), “FAA Conformity Certificate – Military Aircraft”, prior to delivery to the U.S. Army. Civil conversion of these helicopters requires certain modifications to be made in accordance with the applicable FAA approved type design data which forms the basis of Type Certificate H3WE. b) Government furnished equipment identified in Hughes Report No. 369 -X-0008, dated June 24, 1964 must be removed from Hughes Model 369 (YOH-6A) helicopters to be eligible for a U.S. standard and export airworthiness certificate. c) The FAA approved parts and equipment identified as required in Hughes Report No. 369 -E- 5002, dated April 15, 1966 must be installed on Hughes Model 369A (OH -6A) helicopters to be eligible for a U.S. standard and export airworthiness certificate. d) Information essential to the proper maintenance of the Hughes Model 369A (OH-6A) helicopters is contained in the latest version of U.S. Army Technical Manual TM 55 -1520-214- 23 and is applicable to civil converted Hughes Model 369A (OH-6A) helicopters. However, civil conversion of these helicopters in accordance with the applicable NOTE 4.a) above will result in configuration changes to these helicopters which are not included in TM 55-1520-214- 23. Maintenance information associated with the configuration changes do es not exist and must be furnished and submitted, by the applicant for an airworthiness certificate, to the FAA Ft. Worth Aircraft Evaluation Group (FTW-AEG) for review and acceptance prior to issuance of a U.S. standard and export airworthiness certificate. See NOTE 3 and Service Life Limits section of this TCDS above for maintenance information and a list of life limited components for civil converted Hughes Model 369 (YOH-6A) and 369A (OH-6A) helicopters. H3WE Page 36 VIII Data Pertinent to all Models (cont.) Note 4 (cont.) e) Operational information and operating limitations essential for the proper operation of the Hughes Model 369 (YOH-6A) helicopters is contained in the FAA approved Flight Manual for the Hughes Model 369 (YOH-6A) Helicopter, dated July 17, 1968, or later FAA approved revision and is applicable to civil converted Hughes Model 369 (YOH -6A) helicopters. However, civil conversion of these helicopters in accordance with the applicable NOTE 4.a) above will result in configuration changes to these helicopters which may effect the operation of these helicopters. Operational information and operating limitations essential for the proper operation of the Hughes Model 369A (OH-6A) helicopters is contained in the FAA approved Owners Manual for the Hughes Model 369A (OH-6A) Helicopter, dated June 16, 1975, or later FAA approved revision and is applicable to civil converted Hughes Model 369A (OH -6A) helicopters. However, civil conversion of these helicopters in accordance with the applicable NOTE 4.a) above will result in configuration changes to these helicopters which may effect the operation of these helicopters. Helicopter operational and operating limitation information associated with configuration changes must be furnished and submitted, by the applicant for an airworthiness certificate, to the FAA Los Angeles Aircraft Certification Office (LAACO) in the form of a Rotorcraft Flight Manual (RFM) for review and FAA approval prior to issuance of a U.S. standard and export airworthiness certificate. f) Historical records must be made available and evaluated to determine if any major repairs and alterations, including the installation of various U.S. Army replacement parts, were performed on Hughes Model 369 (YOH-6A) and 369A (OH-6A) helicopters by the U.S. Army. Any major repairs and alterations, including the installation of U.S. Army replacement parts, must be removed unless FAA approved in order for helicopters to be eligible for a U.S. standard and export airworthiness certificate. g) The use of a rotorcraft operating or flight manual other than the FAA approved manual identified in the applicable NOTE 4.e), must be FAA approved in order for helicopters to be eligible for a U.S. standard and export airworthiness certificate. h) Hughes Model 369 (YOH-6A) and 369A (OH-6A) helicopters surplused from other than U.S. Armed Forces of the United States are not eligible for issuance of a U.S. standard and export airworthiness certificate or issuance of an FAA restricted category type certificate. NOTE 5 The following list of aircraft serial numbers are those used for foreign military helicopters and/or special production, and are not eligible for a U.S. standard airworthiness certificate. H3WE Page 37 VIII Data Pertinent to all Models (cont.) Note 5 (cont.) 369D Derivative Serial Numbers Not Eligible 0026 0046 0056 0186 0194 0202 0210 0278 0279 0280 0281 0322 0323 0324 0325 0340 0366 0367 0368 0369 0402 0407 0408 0409 0410 0411 0418 0425 0426 0427 0428 0430 0435 0443 0468 0469 0470 0504 0508 0511 0520 0523 0550 0551 0552 0553 0569 0570 0571 0597 0598 0599 0608 0615 0616 0617 0618 0620 0642 0643 0644 0645 0666 0667 0668 0669 0682 0684 0685 0686 0687 0712 0713 0722 0723 0740 0741 0760 0761 0781 0782 0783 0802 0803 0804 0805 0948 0956 0965 0972 0977 0989 1001 1005 1047 1056 1061 1071 1081 1093 1107 1116 1222 1235 1236 1237 1241 1242 1243 1244 1245 1246 1247 1248 1249 1250 1251 1252 1253 1256 1257 1266 1267 1276 1277 1287 1288 369E Derivative Serial Numbers Not Eligible 0081 0102 0103 0104 0112 0113 0114 0124 0125 0131 0132 0137 0138 0139 0142 0153 0154 0158 0159 0160 0161 0162 0163 0164 0171 0172 0173 0174 0175 0176 0183 0184 0185 0186 0212 0213 0214 0254 0257 0263 0264 0265 0269 0272 0271 0273 0274 0275 0277 0278 0279 0283 0284 0285 0286 0289 0290 0291 0294 0295 0296 0297 0298 0299 0300 0305 0306 0307 0308 369F AND 369FF Derivative Serial Numbers Not Eligible 0007 0008 0016 0017 0018 0019 0020 0021 0022 0024 0025 0026 0027 0028 0029 0030 0031 0032 0033 0034 0035 0036 0037 0038 0039 0040 0043 0045 0047 0048 0051 0053 0054 0055 0057 0059 0069 0070 0071 0072 0073 0074 0084 0085 0090 0091 0118 0132 0179 0180 0181 0182 0183 0184 0214 0215 0216 0217 0218 0219 0220 0221 0222 0223 0224 0225 0252 0256 0257 0258 0259 0260 0261 0262 0263 0264 0265 0266 0267 0268 0271 0272 0273 0274 0275 0276 0277 0278 0278 0280 0281 0282 0283 0284 0285 0286 0287 0288 0289 0290 0291 0292 0293 0294 0295 0296 0297 0298 0299 0300 0301 0302 0303 0304 0305 0306 0307 0308 0309 0310 0311 0312 0313 0314 0315 0316 0319 0700 0701 0702 0703 0704 0705 0706 0707 0708 H3WE Page 38 VIII Data Pertinent to all Models (cont.) NOTE 6 Aircraft serial numbers are coded to show the month and year of manufacture in that sequence. Examples: 640103, 1150015E 6 11 4 5 0103 0015 E Month of Manufacture 6 - June 11 - November Year of Manufacture 4 - 1964 5 - 1965 Serial Number in Consecutive order from 0001 for each model (this is the number used for S/N applicability requirements) Additional designation as noted below Model 369A helicopters, S/N 1079 through 1099, utilize an alpha numeric serialization system. The letters used are A, B, C, D, E, F, G, J, K, L, N, P, R, T, U, W, and Y. First aircraft of the block is S/N 1079A, the second is 1079B, etc. Model 369HM helicopters carry the letter M following the serial number. This was effective with Ship S/N 0004M. Model 369HE helicopters carry the letter E following the serial number. This was effective with Ship S/N 0101E. The helicopters listed below have been or will be delivered without the manufacturing date coding as part of the serial number: 369D S/N 1068, 1087, 1095; S/N 1100 and subsequent. 369E S/N 0001 and subsequent 369F S/N 0003 and subsequent 369FF S/N 0001 and subsequent 500N S/N LN001 and subsequent 600N S/N RN003 and subsequent NOTE 7 For all operations below 40º F ambient temperature all fuel, except MIL -G-5572 (Aviation Gasoline), must contain anti-icing additive conforming to MIL-I-27686 in concentrations of 0.035 per cent by volume minimum 0.15 percent by volume maximum. See Rotorcraft Flight Manual for checking concentrations and blending. NOTE 8 For Model 369A the maximum weight may be increased to 2550 pounds when the M30242 "OH-6A revised operating limits-kit, modification" is incorporated. For additional limitations when this kit is installed see Fuel, Engine Limits, Transient Limits, Rotor Limits, and Engine Operating Speeds, and NOTE 3. H3WE Page 39 VIII Data Pertinent to all Models (cont.) NOTE 9 Model 369H Series aircraft, Serial No. 0101 and up, with the 369H90065 or 369H90072 Cargo Hook installed meet the structural and design requirements of the certification basis provided the weight in excess of the normal category gross weight is not imposed on the landing gear, when operated at 3000 pounds gross weight in accordance with the limits of the approved Rotorcraft Flight Manual Supplement for the cargo hook. The retirement times listed in NOTE 3 are not changed. Model 369D Series aircraft, Serial No. 003 and up, and Model 369E Series aircraft, Serial No. 0001 and up, with 369H90072 Cargo Hook installed, meet the structural and design requirements of the certification basis, provided the weight in excess of the normal category gross weight is not imposed on the landing gear, when operated at 3550 pounds gross weight in accordance with the limits of the approved Rotorcraft Flight Manual Supplement for the Cargo Hook. The retirement times listed in NOTE 3 are not changed Model 369D Series Aircraft operated in the Restricted Category with the 429 -4537 Jettisonable Load Kit installed meet the structural and design requirements of the certification basis, prov ided the weight in excess of 3000 pounds must be external jettisonable. Maximum takeoff and power -on landing gross weight is 3550 pounds. The retirement times listed in NOTE 3 are not changed. Model 369F Series aircraft, Serial No. 0003 and up, and Model 369FF Series aircraft, Serial No. 0001 and up, with Cargo Hook installed, meet the structural design requirements of the certification basis, provided the weight in excess of the normal category gross weight is not imposed on the landing gear, when the Model 369F is operated at 3550 pounds gross weight or when Model 369FF is operated at 3750 pounds gross weight in accordance with the limits of the approved Rotorcraft Flight Manual Supplement (as applicable to the Model 369F or 369FF) for Cargo Hook. The ret irement times listed in NOTE 3 are not changed Model 500N aircraft, Serial No. LN0001 and up, with Cargo Hook installed, meet the structural design requirements of the certification basis, provided the weight in excess of the normal category gross weight is not imposed on the landing gear, when the Model 500N is operated at 3850 pounds gross weight in accordance with the limits of the approved Rotorcaraft Flight Manual. The retirement times listed in the Airworthiness Limitations Section of the HMI are not changed. NOTE 10 Inspect the P/N 369A5364 Sprag Assembly, 369A5352 Outer Race, and 369A5353 Inner Race of P/N 369A5350-603 Overrunning Clutch Assembly in Model 369E, 369F, and 369FF helicopters for wear in the cages and sprags of the sprag assembly, inner and outer race every 300 hours and replace the sprag assembly every 1800 hours of total service time in accordance with MDH Service Bulletin EN-3 or FN- 3, as appropriate. NOTE 11 Inspect the main rotor drive shaft, P/N 369D25510, in Model 369E, 369F, and 369FF for cracks and damage every 300 hours in accordance with MDH Service Bulletin EN-4 or FN-4, as appropriate. NOTE 12 The Model 369F Series aircraft may be converted to a Model 369FF Series aircraft with the installation of those parts called out on Drawing 369D290100. NOTE 13 Models 369D and 369E with alternate engine (Rolls-Royce Corporation - formerly Allison Engine Company) 250-C20R/2) are approved with the kits/options identified on 369D290000, Revision G, or later approved revisions and Kit Compatibility Substantiation Report No. 369 -CE-195, dated March 28, 1989, or latest approved revision. H3WE Page 40 VIII Data Pertinent to all Models (cont.) NOTE 14 NOISE CHARACTERISTICS. Model 369D and 369E helicopters with the Rolls-Royce Corporation (formerly Allison Engine Company) 250-C20B engine installed have not been tested for noise in accordance with the requirements of FAR Part 36. Therefore, they are Stage 1 helicopters. Substitution of Rolls-Royce Corporation 250-C20R/2 engine results in no acoustic change. Thus, Model 369D and 369E aircraft with the 250-C20R/2 engine installed are also Stage 1 helicopters. Model 369FF helicopter with the Rolls-Royce Corporation 250-C30 engine has been tested for noise and demonstrated compliance with the requirements of FAR Part 36, therefore, the Model 369FF is a Stage 2 helicopter. The Model 500N has demonstrated compliance with FAR Part 36, Appendix H, through Amendment 36-18, for Stage 2 helicopters. The Model 600N has demonstrated compliance with FAR part 36, Appendix J, through Amendment 36 - 21. NOTE 15 The Model 369E helicopter may be converted to Model 369FF helicopter with the installation of those parts called out on Drawing 369D292202, Revision A, dated 7/29/94, or later FAA approved revision, and in accordance with MDHS Report No. 369-CE-293, “E-FF Conversion Report”, Revision N/C, dated 9/94, or later FAA approved revision. The following is a list of 369Es converted to 369FFs: Was: 369E S/N Became: 369FF S/N Date of Certificate of Airworthiness as 369FF 0292 0075FF April 29, 1993 0228 0600FF January 31, 1996 0287E 0601FF May 01, 1998 0128E 0602FF October 8, 1998 0095E 0603FF September 22, 2015 0247E 0604FF December 03, 2015 0343E 0605FF September 20, 2017 0311E 0606FF July 31, 2020 0288E 0607FF March 05, 2021 0365E 0608FF May 05, 2022 BT890001* 0700FF (1) 0422 0701FF (1) 0369E 0702FF (1) 0052E 0703FF (1) 0094E 0704FF (1) 0468E 0705FF (1) 0381E 0706FF (1) 0391E 0707FF (1) 0355E 0708FF (1) 0242E 0709FF March 16, 2009 0545E 0710FF April 28, 2010 0481E 0711FF February 17, 2012 0573E 0712FF September 9, 2015 0595E 0713FF September 9, 2015 0575E 0714FF January 8, 2016 0581E 0715FF January 9, 2016 H3WE Page 41 0571E 0716FF July 17, 2017 0606E 0717FF July 27, 2017 0601E 0718FF September 25, 2020 0484E 0719FF May 10, 2021 0541E 0720FF June 29, 2023 VIII Data Pertinent to all Models (cont.) NOTE 15 (cont.) (1) These helicopters were built for foreign military and are not eligible for an FAA Certificate of Airworthiness (See NOTE 5). NOTE 16 For Model 600N, a current Weight and Balance Report (MDHS’ Basic Weight and Balance Record) listing the helicopter certificated empty (basic) weight and loading instructions including a List of Equipment (MDHS’ MD-600N Required/Optional Equipment List is provided as a separate document) must be provided for each helicopter at the time the helicopter’s original airworthiness certification is issued. This Basic Weight and Balance Record shall be kept current as the configuration, affecting the helicopter’s weight and balance, is changed. The MDHS Basic Weights Checklist Record (Chart A) an d Basic Weight Checklist Supplement for the Model 600N contains needed reference data for the Weight and Balance Record. A copy of the current MDHS Basic Weight and Balance Record shall be kept in the helicopter. The certificated basic weight and corresponding center of gravity locations includes all transmission, hydraulic and engine oil/fluids as well as trapped/unusable fuel. NOTE 17 The model 600N rotorcraft employs electronic engine controls, commonly named Full Authority Digital Engine Controls (FADEC) and is recognized to be more susceptible to Electromagnetic Interference (EMI) than rotorcraft that have only manual (non-electronic) controls (EMI may be the result of radiated or conducted interference.) For this reason modifications that add or change systems that have the potential for EMI, must either be qualified to an FAA acceptable standard or tested at the time of installation for interference to the FADEC. This type of testing must employ the particular FADEC’s diagnostic techniques and external diagnostic techniques. The test procedure must be FAA approved. NOTE 18 Extension of the basic fuel capacity over 148.1 US gal. (Main Fuel Tank – 114.6 US Gal, plus Fuel Tank - 33.5 US Gal) for the Model 600N may require reevaluation of the FADEC control system reliability due to time limited exposure determinations made during certification. NOTE 19 The Model 600N is prohibited from flying in falling or blowing snow with the standard engine inlet screen installed. NOTE 20 NOTE 21 Any changes to the type design of this helicopter by means of an amended type certificate (TC), supplemental type certificate (STC), or amended STC, requiring instructions for continued airworthiness (ICA) must be submitted through the project aircraft certification office (ACO) for review and acceptance by the Fort Worth -Aircraft Evaluation Group (FTW-AEG) Flight Standards District Office (FSDO) prior to the aircraft delivery, or upon issuance of the first standard airworthiness certificat e for the affected aircraft, whichever occurs later as prescribed by Title 14 CFR § 21.50. Type design changes (major repairs or alterations) by means of a FAA Form 337 (field approval) that require ICA’s must have those ICA’s reviewed by the field approving FSDO. To operate in U.S. airspace, the following aircraft serial numbers are production equipped to meet the crash resistant fuel system certification basis requirements per section 44737 of Title 49 U.S.C.: Model 369FF serial number (s/n) 0334FF and subsequent, Model 369E serial number 0626E and subsequent, and Model 600N s/n RN003 and subsequent. -END- ``` ## ADs (107, first 50, in force first) - [AD 2026-21-05](https://openairdocs.org/ad/2026-21-05): Engine/transmission coupling · MD Helicopters 369D, 369E, 369F and 3 more. Effective Nov 27, 2026 - [AD 2026-19-01](https://openairdocs.org/ad/2026-19-01): Rotorcraft flight control · MD Helicopters 369, 369 (Army YOH-6A), 369A and 11 more. Effective Oct 20, 2026 - [AD 2025-17-11](https://openairdocs.org/ad/2025-17-11): tail rotor control system · MD Helicopters 369 (Army YOH-6A), 369A (Army OH-6A), 369D and 9 more. Effective Oct 10, 2025 - [AD 2024-20-07](https://openairdocs.org/ad/2024-20-07): Emergency Equipment; Emergency Flotation Section · Apical Emergency Float Kit, P/N 20498 (STC SR00780LA or 12 others). Effective Dec 5, 2024 - [AD 2023-11-07](https://openairdocs.org/ad/2023-11-07): Ground Proximity System · Airbus Helicopters 47, 206, 210 and 237 more. Effective Jun 22, 2023 - [AD 2021-22-11](https://openairdocs.org/ad/2021-22-11): Tail Rotor Control System · MD Helicopters 369D, 369E, 369F and 7 more. Effective Jan 10, 2022 - [AD 2020-18-20](https://openairdocs.org/ad/2020-18-20): Main Rotor Blade · MD Helicopters 369A, 369D, 369E and 7 more. Effective Oct 28, 2020 - [AD 2020-11-07](https://openairdocs.org/ad/2020-11-07): Main Rotor System · MD Helicopters 369D, 369E, 369FF and 6 more. Effective Jun 30, 2020 - [AD 2020-06-11](https://openairdocs.org/ad/2020-06-11): Main Rotor Control · MD Helicopters 600N. Effective Apr 28, 2020 - [AD 2019-05-04](https://openairdocs.org/ad/2019-05-04): Main Rotor Blade · MD Helicopters 369A, 369D, 369E and 7 more. Effective Apr 17, 2019 - [AD 2016-05-09](https://openairdocs.org/ad/2016-05-09): Fuel Quantity Indicating System · MD Helicopters 369A, 369D, 369E and 7 more. Effective Apr 15, 2016 - [AD 2016-04-15](https://openairdocs.org/ad/2016-04-15): Main Rotor Blades · MD Helicopters 369A, 369D, 369E and 6 more. Effective Mar 31, 2016 - [AD 2016-01-19](https://openairdocs.org/ad/2016-01-19): Rotorcraft Tail Boom · MD Helicopters 500N and 600N. Effective Feb 25, 2016 - [AD 2013-19-24](https://openairdocs.org/ad/2013-19-24): Tail Rotor Blades · MD Helicopters 369A, 369D, 369E and 6 more. Effective Dec 5, 2013 - [AD 2013-05-16](https://openairdocs.org/ad/2013-05-16): Tailboom assembly · MD Helicopters 369D, 369E, 369F and 1 more. Effective Apr 30, 2013 - [AD 2013-03-03](https://openairdocs.org/ad/2013-03-03): Tail rotor blades · MD Helicopters 500N, 600N and MD900. Effective Mar 15, 2013 - [AD 2008-22-52](https://openairdocs.org/ad/2008-22-52): Yaw Stability Augmentation System · MD Helicopters 500N and 600N. Effective Dec 15, 2008 - [AD 2008-20-05](https://openairdocs.org/ad/2008-20-05): Fuselage · MD Helicopters 600N. Effective Oct 27, 2008 - [AD 2008-15-03](https://openairdocs.org/ad/2008-15-03): Tail rotor (T/R) blade abrasion strip · MD Helicopters 369A, 369D, 369E and 6 more. Effective Sep 3, 2008 - [AD 2007-12-23](https://openairdocs.org/ad/2007-12-23): Landing gear fairing support assembly · MD Helicopters 369A, 369D, 369E and 7 more. Effective Jul 19, 2007 - [AD 2007-09-51](https://openairdocs.org/ad/2007-09-51): Tail rotor blade · MD Helicopters 369, 369A, 369D and 7 more. Effective Jul 5, 2007 - [AD 2007-05-51](https://openairdocs.org/ad/2007-05-51): Lateral mixer output link assembly (mixer link) · MD Helicopters 600N. Effective May 7, 2007 - [AD 2005-21-02](https://openairdocs.org/ad/2005-21-02): Main rotor blade (blade) · Main rotor blades P/N 500P2300-501/503/505 (Helicopter Technology STC SR01050LA or 2 others). Effective Nov 1, 2005 - [AD 2004-22-12](https://openairdocs.org/ad/2004-22-12): Fuselage Station 75 Control Support Bracket Assembly · MD Helicopters 600N. Effective Dec 3, 2004 - [AD 2004-20-08](https://openairdocs.org/ad/2004-20-08): Forward and center thruster control cable assembly connector (connector) · MD Helicopters 500N and 600N. Effective Oct 21, 2004 - [AD 2003-16-11](https://openairdocs.org/ad/2003-16-11): Main rotor drive shaft assembly (drive shaft) · MD Helicopters 600N. Effective Sep 30, 2003 - [AD 2002-13-05 R1](https://openairdocs.org/ad/2002-13-05-R1): Tail rotor gearbox · Aerometals tailboom, P/N 369X23500-505, 507 (STC SH5055NM or SH4801NM). Effective Feb 25, 2003 - [AD 2002-20-05](https://openairdocs.org/ad/2002-20-05): Rescue hoists · Agusta A109, A109A, A109A II and 31 more. Effective Nov 7, 2002 - [AD 2000-25-52](https://openairdocs.org/ad/2000-25-52): Main rotor blade · MD Helicopters 369A, 369D, 369E and 6 more. Effective Feb 6, 2001 - [AD 2000-08-22](https://openairdocs.org/ad/2000-08-22): Turbine Outlet Temperature (TOT) Indicating System · MD Helicopters 369D, 369E, 500N and 1 more. Effective May 22, 2000 - [AD 2000-04-21](https://openairdocs.org/ad/2000-04-21): Fuel Hose · MD Helicopters 600N. Effective Apr 5, 2000 - [AD 99-25-08](https://openairdocs.org/ad/99-25-08): Thruster Control Cable Conduit Cap · MD Helicopters 500N and 600N. Effective Mar 1, 2000 - [AD 99-20-12](https://openairdocs.org/ad/99-20-12): Bracket P/N 369F5190-1 · MD Helicopters 369D, 369E, 369FF and 2 more. Effective Nov 4, 1999 - [AD 99-17-18](https://openairdocs.org/ad/99-17-18): Flight Control Components · MD Helicopters 600N. Effective Sep 24, 1999 - [AD 99-13-09](https://openairdocs.org/ad/99-13-09): Fork Assembly Inspection · MD Helicopters 369D and 369E. Effective Aug 4, 1999 - [AD 99-08-07](https://openairdocs.org/ad/99-08-07): Engine Control And Warning System · MD Helicopters 369E, 369FF, 500N and 1 more. Effective Apr 21, 1999 - [AD 99-04-12](https://openairdocs.org/ad/99-04-12): Input Shaft Coupling Assembly · MD Helicopters 369D, 369E, 369FF and 3 more. Effective Mar 23, 1999 - [AD 98-21-12](https://openairdocs.org/ad/98-21-12): Overrunning Clutch Retainer Inspection · MD Helicopters 369D, 369E, 369FF and 1 more. Effective Oct 22, 1998 - [AD 98-14-03](https://openairdocs.org/ad/98-14-03): Transponders · Cessna 172, 172A, 172B and 230 more. Effective Aug 16, 1998 - [AD 98-15-26](https://openairdocs.org/ad/98-15-26): Main Rotor Blade Cracking Inspection · MD Helicopters 369A, 369D, 369E and 8 more. Effective Aug 3, 1998 - [AD 98-07-19](https://openairdocs.org/ad/98-07-19): Tail Rotor Control Rod Assembly · MD Helicopters 369F and 369FF. Effective May 7, 1998 - [AD 98-09-02](https://openairdocs.org/ad/98-09-02): Overrunning Clutch Assembly Outer Race · MD Helicopters 369, 369A, 369D and 8 more. Effective May 6, 1998 - [AD 97-15-08](https://openairdocs.org/ad/97-15-08): Transmission Output Drive Gear · MD Helicopters 369D, 369E, 369F and 2 more. Effective Aug 4, 1997 - [AD 96-10-09](https://openairdocs.org/ad/96-10-09): Blade Root End Crack Inspection · MD Helicopters 369, 369A, 369D and 8 more. Effective May 29, 1996 - [AD 96-08-03](https://openairdocs.org/ad/96-08-03): Hardpoint Assemblies · Hardpoints (Flight Trails Helicopters STC SH6080NM). Effective May 20, 1996 - [AD 95-03-13](https://openairdocs.org/ad/95-03-13): Main Rotor Blade Attach Lugs · MD Helicopters 369, 369A, 369D and 7 more. Effective Mar 21, 1995 - [AD 95-03-11](https://openairdocs.org/ad/95-03-11): Tail Rotor Bade Inspection · MD Helicopters 369, 369A, 369D and 7 more. Effective Mar 1, 1995 - [AD 94-24-04](https://openairdocs.org/ad/94-24-04): Pitch Control Assembly · MD Helicopters 369D, 369E, 369F and 1 more. Effective Dec 13, 1994 - [AD 93-18-05](https://openairdocs.org/ad/93-18-05): Fuel Vent Line · MD Helicopters 369D, 369E, 369F and 2 more. Effective Dec 21, 1993 - [AD 93-07-10](https://openairdocs.org/ad/93-07-10): Airspeed Limitations · External cargo container (Gajon Associates STC SH1134EA). Effective Jul 6, 1993 All 107: https://openairdocs.org/tcds/H3WE/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Hughes Helicopters HUGHES 369D](https://openairdocs.org/model/hughes-helicopters-hughes-369d): 207 aircraft (registry code 4470706) - [MD Helicopters 369FF](https://openairdocs.org/model/md-helicopters-369ff): 94 aircraft (registry codes 3030002, 3030015) - [Mcdonnell Douglas Helicopter 369E](https://openairdocs.org/model/mcdonnell-douglas-helicopter-369e): 83 aircraft (registry code 3027369) - [Hughes 369HS](https://openairdocs.org/model/hughes-369hs): 69 aircraft (registry code 4470728) - [MD Helicopters 369E](https://openairdocs.org/model/md-helicopters-369e): 42 aircraft (registry codes 3030008, 3030014) - [Hughes 369A](https://openairdocs.org/model/hughes-369a): 32 aircraft (registry code 4470503) - [Hughes Helicopters 369E](https://openairdocs.org/model/hughes-helicopters-369e): 29 aircraft (registry code 4470707) - [Mcdonnell Douglas Helicopter 500N](https://openairdocs.org/model/mcdonnell-douglas-helicopter-500n): 27 aircraft (registry code 3027374) - [Hughes OH-6A](https://openairdocs.org/model/hughes-oh-6a): 24 aircraft (registry code 4470905) - [Mcdonnell Douglas Heli 369FF](https://openairdocs.org/model/mcdonnell-douglas-heli-369ff): 17 aircraft (registry code 3027371) - [Mcdonnell Douglas Helicopter 600N](https://openairdocs.org/model/mcdonnell-douglas-helicopter-600n): 14 aircraft (registry code 3027377) - [MD Helicopters 500N](https://openairdocs.org/model/md-helicopters-500n): 13 aircraft (registry code 3030001) - [MD Helicopters 600N](https://openairdocs.org/model/md-helicopters-600n): 12 aircraft (registry code 3030003) - [Hughes 369A (OH-6A)](https://openairdocs.org/model/hughes-369a-oh-6a): 11 aircraft (registry code 4470506) - [Hughes 369](https://openairdocs.org/model/hughes-369): 5 aircraft (registry code 4470702) - [Hughes Helicopters 369FF](https://openairdocs.org/model/hughes-helicopters-369ff): 5 aircraft (registry code 4470709) - [Hughes OH-6](https://openairdocs.org/model/hughes-oh-6): 4 aircraft (registry code 4470904) - [Mcdonnell Douglas Heli 500-E](https://openairdocs.org/model/mcdonnell-douglas-heli-500-e): 4 aircraft (registry code 3027372) - [Summa 369D](https://openairdocs.org/model/summa-369d): 4 aircraft (registry code 056266I) - [Hughes 369HE](https://openairdocs.org/model/hughes-369he): 3 aircraft (registry code 4470720) - [Hughes 500C](https://openairdocs.org/model/hughes-500c): 3 aircraft (registry code 4470805) - [MD Helicopters 369HS](https://openairdocs.org/model/md-helicopters-369hs): 3 aircraft (registry code 3030012) - [Hughes 369F](https://openairdocs.org/model/hughes-369f): 2 aircraft (registry code 4470708) - [MD Helicopters 369HM](https://openairdocs.org/model/md-helicopters-369hm): 2 aircraft (registry code 3030011) - [Hughes 369H](https://openairdocs.org/model/hughes-369h): 1 aircraft (registry code 4470718) - [Hughes/Batto John 369A (OH-6A)](https://openairdocs.org/model/hughes-batto-john-369a-oh-6a): 1 aircraft (registry code 4470710) - [Hughes/Helicopter Assocs 369A](https://openairdocs.org/model/hughes-helicopter-assocs-369a): 1 aircraft (registry code 4470703) - [Mcdonnell Douglas Helicopter 520N](https://openairdocs.org/model/mcdonnell-douglas-helicopter-520n): 1 aircraft (registry code 3027376) - [Mcdonnell Douglas Helicopter H-6](https://openairdocs.org/model/mcdonnell-douglas-helicopter-h-6): 1 aircraft (registry code 3027378) - [Mcdonnell Douglas Mdhs 369E](https://openairdocs.org/model/mcdonnell-douglas-mdhs-369e): 1 aircraft (registry code 3030019) - [MD Helicopters 369A](https://openairdocs.org/model/md-helicopters-369a): 1 aircraft (registry code 3030006) - [MD Helicopters 500E](https://openairdocs.org/model/md-helicopters-500e): 1 aircraft (registry code 303001E) - [Summa 369HS](https://openairdocs.org/model/summa-369hs): 1 aircraft (registry code 05617KC) - [Hughes 369C](https://openairdocs.org/model/hughes-369c): 0 aircraft (registry code 4470704) - [Hughes 369HM](https://openairdocs.org/model/hughes-369hm): 0 aircraft (registry code 4470722) - [Hughes 369S](https://openairdocs.org/model/hughes-369s): 0 aircraft (registry code 4470730) - [Hughes 500](https://openairdocs.org/model/hughes-500): 0 aircraft (registry code 4470802) - [Hughes 500-E](https://openairdocs.org/model/hughes-500-e): 0 aircraft (registry code 4470807) - [Hughes 500D](https://openairdocs.org/model/hughes-500d): 0 aircraft (registry code 4470806) - [Hughes YOH-6A](https://openairdocs.org/model/hughes-yoh-6a): 0 aircraft (registry code 4470901) - [Hughes/Asbill 369A (OH-6A)](https://openairdocs.org/model/hughes-asbill-369a-oh-6a): 0 aircraft (registry code 4470501) - [Hughes/Dudley K P 369A](https://openairdocs.org/model/hughes-dudley-k-p-369a): 0 aircraft (registry code 4470505) - [Mcdonnell Douglas Heli 500](https://openairdocs.org/model/mcdonnell-douglas-heli-500): 0 aircraft (registry code 3027373) - [Mcdonnell-Douglas Helicopter 369F/530F](https://openairdocs.org/model/mcdonnell-douglas-helicopter-369f-530f): 0 aircraft (registry code 3027370) - [MD Helicopter 369H](https://openairdocs.org/model/md-helicopter-369h): 0 aircraft (registry code 3030010) - [MD Helicopters 369](https://openairdocs.org/model/md-helicopters-369): 0 aircraft (registry code 3030005) - [MD Helicopters 369D](https://openairdocs.org/model/md-helicopters-369d): 0 aircraft (registry code 3030007) - [MD Helicopters 369F](https://openairdocs.org/model/md-helicopters-369f): 0 aircraft (registry code 3030009) - [MD Helicopters 369HE](https://openairdocs.org/model/md-helicopters-369he): 0 aircraft (registry code 3030013) ## STCs approved under this data sheet (354, first 50) - [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position Light System, and applicable associated power supplies. Whelen Aerospace Technologies - [STC SR12192LA](https://openairdocs.org/stc/SR12192LA): Installation of MD Helicopters (MDH), LLC, Super D20B kit. MD Helicopters, LLC - [STC SR12311LA](https://openairdocs.org/stc/SR12311LA): Installation of MD Helicopters (MDH), LLC, Super D20R kit in accordance with FAA approved MDH Master Data List. MD Helicopters - [STC SR12310LA](https://openairdocs.org/stc/SR12310LA): Installation of MD Helicopters (MDH), LLC, 530N configuration kit. MD Helicopters, LLC - [STC SR01050LA](https://openairdocs.org/stc/SR01050LA): Installation of main rotor blades P/N 500P2300-501/503/505. Helicopter Technology Company - [STC SR12092IB](https://openairdocs.org/stc/SR12092IB): Manufacturing and Installation of Cargo Hold Nets. ICARUS AERO INC. - [STC SR01059LA](https://openairdocs.org/stc/SR01059LA): Installation of right side dual utility mount. Airfilm Camera Systems LLC - [STC SH133WE](https://openairdocs.org/stc/SH133WE): Installation of C-75 cargo rack set.. Isolair Inc. - [STC SH3686NM](https://openairdocs.org/stc/SH3686NM): Installation of an Isolair Model3700-110 spray tank system. (500N restricted category). Isolair Inc. - [STC SR01106DE](https://openairdocs.org/stc/SR01106DE): Installation of Crash Resistant Auxiliary Fuel Tank i. Aerospace Composites Solutions Inc. - [STC SR00181IB](https://openairdocs.org/stc/SR00181IB): Installation of alternate Cabin Door Latches to replace OEM door locks. Aerologic LLC - [STC SR00709AT](https://openairdocs.org/stc/SR00709AT): Installation of Starter-Generator Cooling Kit. Precision Heli-Support LLC - [STC SR00771LA](https://openairdocs.org/stc/SR00771LA): Installation of right-side utility mount.. Airfilm Camera Systems LLC - [STC SR00772LA](https://openairdocs.org/stc/SR00772LA): Installation of left-side utility mount.. Airfilm Camera Systems LLC - [STC SR00862LA](https://openairdocs.org/stc/SR00862LA): Installation of aft belly utility mount.. Airfilm Camera Systems LLC - [STC SR01078LA](https://openairdocs.org/stc/SR01078LA): Installation of right side dual utility mount, in accordance with FAA Approved Aero Pacific Master Drawing List for Right Side Dual Utility Mount, MDL 6003, dtd 4/15/00 or later FAA approved revision.. Airfilm Camera Systems LLC - [STC SR04637CH](https://openairdocs.org/stc/SR04637CH): Replacement of existing main ship battery with Lithium Ion Battery and installation of Annunciator Control Panel. Airwolf Aerospace LLC - [STC SR00068DE](https://openairdocs.org/stc/SR00068DE): Installation of infrared imaging system.. Dart Aerospace Company - [STC SH5247NM](https://openairdocs.org/stc/SH5247NM): Installation of external pod, camera mount, and 12 volt power provision.. Dart Aerospace USA Inc. - [STC SR00146IB](https://openairdocs.org/stc/SR00146IB): nstallation of the Integrated Health and Usage Monitoring System (HUMS). RMCI Canada Inc. - [STC SR02120SE](https://openairdocs.org/stc/SR02120SE): Installation of Garmin GTN 6XX/7XX Navigation System. Garmin International Inc. - [STC SH2735NM](https://openairdocs.org/stc/SH2735NM): Installation of pneumatic door actuators.. Dart Aerospace USA Inc. - [STC SR02808LA](https://openairdocs.org/stc/SR02808LA): Installation of MD500 Side Pull Kit. Aerocraft Incorporated - [STC SH5206NM](https://openairdocs.org/stc/SH5206NM): Installation of two underfuselage jacking hard points.. Dart Aerospace USA Inc. - [STC SR00376DE](https://openairdocs.org/stc/SR00376DE): Installation of laser mapping system.. Dart Aerospace USA Inc. - [STC SR04160CH](https://openairdocs.org/stc/SR04160CH): Installation of Heli-Preheat Kit, p/n TA3089-1 for 115 volt application. HARTZELL PROPELLER INC - [STC SR00043LA](https://openairdocs.org/stc/SR00043LA): Installation of clip on Main Rotor Swashplate. Pac West Helicopters Inc. - [STC SH3319NM](https://openairdocs.org/stc/SH3319NM): Installation of Precise Flight Pulselite Control Unit in the Landing /Taxi Recognition Visual Control Light system,. Precise Flight Inc - [STC SR01778SE](https://openairdocs.org/stc/SR01778SE): Installation of Onboard Systems International Cargo Hook Kits and Load Weigh Kit. Onboard Systems International LLC - [STC SH1837NM](https://openairdocs.org/stc/SH1837NM): Installation of a fore-and-aft medical evacuation litter(s) kit.. MD Helicopters LLC - [STC SH2262NM](https://openairdocs.org/stc/SH2262NM): Installation of a fore-and-aft medical evacuation litter(s) kit.. MD Helicopters LLC - [STC SH2263NM](https://openairdocs.org/stc/SH2263NM): Installation of a fore-and-aft medical evacuation litter(s) kit.. MD Helicopters LLC - [STC SR00902DE](https://openairdocs.org/stc/SR00902DE): Installation of External Equipment Mounts for provisions. MD Helicopters Inc - [STC SR00923DE](https://openairdocs.org/stc/SR00923DE): Installation of Genesys AeroSystems Avionics Display Upgrade. MD Helicopters Inc - [STC SR09178RC](https://openairdocs.org/stc/SR09178RC): Installation of a vapor-cycle air conditioning system with a belt driven compressor.. MD Helicopters LLC - [STC SR04680NY](https://openairdocs.org/stc/SR04680NY): Installation of Human External Cargo (HEC) Long-Line Kit. Boost Human External Cargo Systems Inc. - [STC SR00314AT](https://openairdocs.org/stc/SR00314AT): Installation of engine firewall in Hughes 369 model helicopter. Thoroughbred Aviation Maintenance Inc - [STC SR00450AT](https://openairdocs.org/stc/SR00450AT): Installation of a seat pan inspection panel.. Thoroughbred Aviation Maintenance Inc - [STC SR00823AT](https://openairdocs.org/stc/SR00823AT): This modification will allow the installation or rear extended cabin step. Thoroughbred Aviation Maintenance Inc - [STC SR00829AT](https://openairdocs.org/stc/SR00829AT): Installation of front extended cabin step.. Thoroughbred Aviation Maintenance Inc - [STC SR01839AT](https://openairdocs.org/stc/SR01839AT): Installation of cyclic friction levers. Thoroughbred Aviation Maintenance Inc. - [STC SR02859AT](https://openairdocs.org/stc/SR02859AT): Installation of Part Number 369HT21004 main rotor hub fairing as a direct replacement for OEM Part Number 369D21004-11 (BSC). Thoroughbred Aviation Maintenance Inc - [STC SR03265AT](https://openairdocs.org/stc/SR03265AT): Modification of engine gearbox breather system by the installation of Heli-Tech "HT800-Engine Gearbox Breather Kit", P/N HT800. Thoroughbred Aviation Maintenance Inc - [STC SR04175AT](https://openairdocs.org/stc/SR04175AT): Installation of the HT400 Inspection Panel Kit. Thoroughbred Aviation Maintenance Inc - [STC SR02693LA](https://openairdocs.org/stc/SR02693LA): Installation of a redundant system for the primary Cargo Hook system when conducting Human External Cargo (HEC) external loads operations. Onboard Systems International LLC - [STC SH4908NM](https://openairdocs.org/stc/SH4908NM): Fabrication of Onboard Systems Model 200-034-00, 200-034-01, and 200-034-02 Load Weigh Kits. Onboard Systems International - [STC SR00407SE](https://openairdocs.org/stc/SR00407SE): Fabrication of Onboard Systems Model 200-187-00 cargo hook kit. Onboard Systems International LLC - [STC SR00525SE](https://openairdocs.org/stc/SR00525SE): Fabrication of Onboard Systems Model 200-231-00 and 200-231-01 Cargo Hook Attach Point Kit and installation of these Cargo Hook Attach Point Kits. Onboard Systems International - [STC SR00892SE](https://openairdocs.org/stc/SR00892SE): Fabrication of Onboard Systems International Model 200-264-00, 200-264-01, and 200-264-02 Cargo Hook Kits.. Onboard Systems International - [STC SH1152NW](https://openairdocs.org/stc/SH1152NW): Installation of the Automatic Flagman Model 135 Control Stick Grip. Air Products & Parts LLC All 354: https://openairdocs.org/tcds/H3WE/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.