LONG RANGER IV ROTORCRAFT FLIGHT MANUAL

Section 4 - HANDLING AND SHALL has been used only when SERVICING application of a procedure is mandatory. TERMINOLOGY WARNINGS, CAUTIONS, AND NOTES Warnings, cautions, and notes are used throughout this manual to emphasize important and critical instructions as follows: AN OPERATING PROCEDURE, PRACTICE, ETC., WHICH, IF NOT CORRECTLY FOLLOWED, COULD RESULT IN PERSONAL INJURY OR LOSS OF LIFE. AN OPERATING PROCEDURE, PRACTICE, ETC., WHICH IF NOT STRICTLY OBSERVED, COULD RESULT IN DAMAGE TO OR DESTRUCTION OF EQUIPMENT. NOTE An operating procedure, condition, etc., which is essential to highlight. Rev. 3 i BHT-206L4-FM-1 SHOULD has been used only when application of a procedure is recommended. MAY and NEED NOT have been used Only when application of a procedure is optional. WILL has been used only to indicate futurity, never to indicate a mandatory procedure. ABBREVIATIONS AND ACRONYMS Abbreviations and acronyms used throughout this manual are defined as follows: A/F ANTI COLL LT APU BAT BL C CG DC DECR ELT ENG F FS FT FWD GEN GOV GW HD Hg HP HYDR ICS - Airframe - Anticollision light - Auxiliary power unit - Battery - Buttock line - Celsius - Center of gravity - Direct current - Decrease - Emergency locator transmitter - Engine - Fahrenheit - Fuselage station - Foot, feet - Forward - Generator - Governor - Gross weight - Density altitude - Inches of mercury - Pressure altitude - Hydraulic - Intercommunication system IDLE REL - IGE - IN - INCR - INST LT - KCAS - KG - KIAS - KTAS - L - LB(S) - LDG LTS - LT - MCP - MM - MPH - OAT - OGE - POS LT - PSI - QTY - RLY - RPM - SHP - SL - TOT or - TURB OUT TEMP T/R - TRANS - V - VFR - V - NE WL - WRN - XMSN - Idle release In ground effect Inch(es) Increase Instrument light Knots calibrated airspeed Kilogram(s) Knots indicated airspeed Knots true airspeed Liter(s) Pound(s) Landing lights Light Maximum continuous power Millimeter(s) Miles per hour (statute) Outside air temperature Out of ground effect Position light Pounds per square inch Quantity Relay Revolutions per minute Shaft horsepower Sea level Turbine outlet temperature Tail rotor Transmission Volt(s), voltage Visual flight rules Never exceed velocity Water line Warning Transmission (ii Rev. 1 DOT APPROVED BHT-206L4-FM-1 TABLE OF CONTENTS Paragraph l-l l-2 1-3 l-4 1-5 1-6 1-7 1-6 1-9 l-10 l-11 1-12 1-13 1-14 1-15 1-16 1-17 1-16 1-19 l-20 1-21 l-22 1-23 1-24 l-25 1-26 1-27 1-26 1-29 l-30 1-31 1-32 1-33 1-34 1-35 1-36 1-37 l-36 GENERAL ................................................................ BASIS OF CERTIFICATION.. ............................................ TYPE OF OPERATION.. ................................................. OPTIONAL EQUIPMENT.. ............................................... FLIGHT CREW ........................................................... WEIGHT AND CENTER OF GRAVITY ................................... WEIGHT ............................................................. CENTER OF GRAVITY .............................................. (DELETED) .......................................................... DOORS OFF.. ....................................................... AIRSPEED ............................................................... ALTITUDE ................................................................ AMBIENT AIR TEMPERATURE.. ........................................ MANEUVERING .......................................................... ELECTRICAL ............................................................. GENERATOR ........................................................ POWERPLANT ........................................................... GAS PRODUCER RPM.. ............................................ POWER TURBINE RPM ............................................. TURBINE OUTLET TEMPERATURE (TOT) ......................... ENGINE TORQUE ................................................... FUEL PRESSURE.. ................................................. ENGINE OIL PRESSURE.. .......................................... ENGINE OIL TEMPERATURE.. ..................................... ANTI-ICE ............................................................ STARTER ............................................................ TRANSMISSION .......................................................... TRANSMISSION OIL PRESSURE ................................... TRANSMISSION OIL TEMPERATURE .............................. ROTOR ................................................................... ROTOR RPM - POWER ON.. ...................................... ROTOR RPM - POWER OFF.. ..................................... ROTOR BRAKE .......................................................... FUEL AND OIL.. ......................................................... FUEL ................................................................ ENGINE OIL.. ....................................................... TRANSMISSION AND TAIL ROTOR GEARBOX OIL ............... HYDRAULIC.. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Page Number l-3 1-3 1-3 1-3 1-3 l-4 l-4 l-4 1-4 l-4 l-4 1-4 l-11 l-11 l-11 l-11 l-11 l-11 l-11 l-11 1-12 1-12 1-12 1-12 1-12 1-12 1-12 1-12 1-12 1-13 1-13 1-13 1-13 1-13 1-13 1-13 1-13 1-14 Rev. 4 l-l BHT-206L4-FM-1 DOT APPROVED Figure Number LIST OF FIGURES Title Page Number Gross weight center of gravity limits - U.S. ............................ Gross weight center of gravity limits - Metric .......................... Placards and decals ....................................................... Instrument markings ...................................................... l-2 Rev. 4 TC APPROVED BHT-206L4-FM-1 eSection 1 1-1. GENERAL Flight operations are approved with landing gear crosstube fairings installed or removed. Compliance with limitations section is required by appropriate operating rules. NOTE Anytime an operating limitation is exceeded, an appropriate entry shall be made in All unsecured items shall be removed helicopter logbook. Entry shall state which from cabin when any door is removed. limit was exceeded, duration of time, extreme value attained, and any additional information Flight with any combination of cabin doors off value attained, and any additional information is approved, except that left passenger door essential in determining maintenance action shall be remvedc if litter door required. Refer to AIRSPEED limitations. Intentional use of transient limits is prohibited. 1-4. OPTIONAL EQUIPMENT Torque events shall be recorded. A torque Following equipment shall be installed when event is defined as a takeoff or a load lift conducting flight operations in falling and/or (internal or external). blowing snow to reduce possibility of engine flameout: 1-2. BASIS OF1-2 Snow deflector kit or Particle separator kit CERTIFICATION and Snow deflector kit. (See BHT-206L4-FMS- 3 and BHT-206L4-FMS-7.) This helicopter is certified under Federal Air Regulations Parts 27 and 36, and Civil Air Refer to appropriate flight manual Regulation Part 6. supplement(s) (FMS) for additional limitations, procedures, and performance 1-3. TYPE OF OPERATION data. Basic configured helicopter is approved for 1-5. FLIGHT CREW seven-place seating and is certified for land operation under day or night VFR nonicing Minimum flight crew consists of one pilot who conditions. shall operate helicopter from right crew seat. A functional map light is required for night Left crew seat may be used for an additional flights. pilot when approved dual controls are installed. 04 DEC 2001 Rev. 5 1-3 BHT-206L4-FM-1 DOTAPPROVED 1-6. WEIGHT AND CENTER OF GRAVITY l-7. WEIGHT LOADS THAT RESULT IN GW ABOVE 4,450 POUNDS (2016.5 I KILOGRAMS) SHALL BE CARRIED ON AN APPROVED EXTERNAL LOAD KIT AND SHALL NOT BE IMPOSED ON LANDING GEAR. Maximum internal gross weight is 4,450 pounds (2016.5 kilograms). Minimum combined crew weight at fuselage station 65.0 is 170 pounds (77.1 kilograms) when operating in accordance with the SELECTIVE PASSENGER LOADING placard. l-8. CENTER OF GRAVITY For gross weight longitudinal and lateral center of gravity limits, refer to figures l-l and l-2. The standard helicopter (standard seating and fuel system) is ballasted in accordance with the Weight Empty Center of Gravity chart in the maintenance manual. The SELECTIVE PASSENGER LOADING placard shall be installed and may be used for loading passengers only within appropriate weight limitations without computing center of gravity. When passengers are seated other than in accordance with the selective loading placard or the baggage compartment is utilized, the pilot is responsible for determining weight and balance to ensure gross weight and center of gravity will remain within limits throughout each flight. The helicopter with nonstandard fuel system or seating arrangement is not ballasted in accordance with the Weight l-4 Rev. 4 Empty Center of Gravity chart in the maintenance manual. Selective passenger loading does not apply and the ALTERNATE placard shall be installed. The pilot is responsible for determining weight and balance to ensure gross weight and center of gravity will remain within limits throughout each flight. Refer to BHT-206L4-MD-1 for loading tables and instructions. l-9. (DELETED) I l-10. DOORS OFF Determine weight change after doors have been removed and adjust ballast if necessary. Refer to BHT-206L4-MD-1. l-11. AIRSPEED Basic VNE, is 130 KIAS (150 MPH) from sea level to 3,000 feet HD. Decrease VNE, for ambient conditions in accordance with AIRSPEED LIMITATIONS placard (figure 1- 3). I VNE, is 64 KIAS (97 MPH) at 75 to 100% TORQUE takeoff power. VNE, is 90 KIAS (104 MPH) with any door(s) off, not to exceed placarded VNE,. VNE,is 100 KIAS (115 MPH) for autorotation. l-1 2. ALTITUDE Maximum pressure altitude (Hp) is 20,000 feet. Maximum density altitude (H,) is 10,000 feet when gross weight is above 4150 pounds (1662.4 kilograms). NOTE Refer to applicable rules for high altitude oxygen requirements. 1 DOT APPROVED BHT-206L4-FM-1 4600 119.4 126.4 . 1 3600 3000 2600 2600 2400 2200 116 116 120 122 124 126 126 130 LONGITUDINAL CG FUSELAGE STATION -- INCHES 206L4-FM-1-1-1 Figure l-l. Gross weight center of gravity limits - U.S. (Sheet 1 of 2) Rev. 4 1-5 BHT-206L4-FM-1 DOTAPPROVED 4600 4200 2400 -4 -3 -2 -1 0 1 2 3 4 LATERAL CG BUTTOCK LINES -- INCHES 206L4FM-1-1-2 1-6 Figure l-l. Gross weight center of gravity limits - U.S. (Sheet 2 of 2) Rev. 4 DOT APPROVED BHT-206L4-FM-1 1900 1800 1700 1600 1500 1400 1300 1200 1100 2950 3000 3050 3100 3150 3200 3250 3300 206L4FW-1-2-1 Figure I-2. Gross weight center of gravity limits - Metric (Sheet 1 of 2) Rev. 4 f-7 BHT-206L4-FM-1 DOT APPROVED l-8 2100 2000 1900 1800 1700 1800 1500 1400 1300 1200 1100 -90 -80 -30 0 30 60 - - - - - - - - - - - - BUTTOCK LINES -- MILLIMETERS 1882.4 1088.6 Figure 1-2. Gross weight center of gravity limits - Metric (Sheet 2 of 2) Rev. 4 TC APPROVED BHT-206L4-FM-1 Figure 1-3. Placards and decals (Sheet 1 of 4) 26 APR 2005 Rev. 6 1-9 BHT-206L4-FM-1 TC APPROVED Figure 1-3. Placards and decals (Sheet 2 of 4) 1-10 Rev. 6 26 APR 2005 TC APPROVED BHT-206L4-FM-1 Figure 1-3. Placards and decals (Sheet 3 of 4) 26 APR 2005 Rev. 6 1-10A BHT-206L4-FM-1 TC APPROVED Figure 1-3. Placards and decals (Sheet 4 of 4) AVOID CONT OPS 71.8% TO 91.5% N2 Location: Instrument panel. 206L4FM_1_0001 1-10B Rev. 6 26 APR 2005 TC APPROVED BHT-206L4-FM-1 1-13. AMBIENT AIR TEMPERATURE Maximum sea level ambient air temperature for operation is 51.7°C (125°F) and decreases with H P at standard lapse rate of 2°C (3.6°F) per 1,000 feet to 20,000 feet. 1-14. MANEUVERING Aerobatic maneuvers are prohibited. 1-15. ELECTRICAL 1-16. GENERATOR 1-17. POWERPLANT Allison model 250-C30P. 1-18. GAS PRODUCER RPM 1-19. POWER TURBINE RPM WARNING USE OF THROTTLE TO CONTROL RPM IS NOT AUTHORIZED. (REFER TO SECTION 3, EMERGENCY P R O C E D U R E S — E N G I N E OVERSPEED FOR EXCEPTION.) NOTE R e f e r t o A l l i s o n O p e r a t i o n a n d Maintenance Manual for transient overspeed limits. 1-20. TURBINE OUTLET TEMPERATURE (TOT) CAUTION I N T E N T I O N A L U S E O F P O W E R TRANSIENT TOT ABOVE 768°C IS PROHIBITED. Continuous operation 0 to 90% DC LOAD Maximum 90% DC LOAD Continuous operation 63 to 105% Maximum 105% Maximum transient Do not exceed 10 seconds above 105% 106% Avoid continuous operations 71.8 to 91.5% Minimum 99% Continuous operation 99 to 101% Maximum continuous 101% Transient overspeed range. Do not exceed 5 minutes above 101%. 101 to 104% Continuous operation 100 to 716°C Maximum continuous 716°C 5 minute takeoff range 716 to 768°C Maximum for takeoff 768°C Maximum power-on transient. Do not exceed 10 seconds above 768°C. 871°C Beginning of 10-second time limit for start. Do not exceed 10 seconds above 826°C. 826°C Maximum for start and shutdown. Do not exceed 1 second at 927°C. 927°C 26 APR 2005 Rev. 6 1-11 DOT APPROVED BHT-206L4-FM-1 1-21. ENGINE TORQUE CAUTION I N T E N T I O N A L U S E O F T O R Q U E ABOVE 100% IS PROHIBITED. 1-22. FUEL PRESSURE 1-23. ENGINE OIL PRESSURE 1-24. ENGINE OIL TEMPERATURE 1-25. ANTI-ICE Maximum ambient temperature for use of engine anti-ice is 4.4°C (40°F). ENGINE ANTI-ICING shall be ON for flight in visible moisture in temperature below 4.4°C (40°F). 1-26. STARTER Limit starter energize time to following: 1-27. TRANSMISSION 1-28. TRANSMISSION OIL PRESSURE 1-29. TRANSMISSION OIL TEMPERATURE Continuous operation 0 to 75% Maximum continuous 75% 5 minute takeoff range 75 to 100% Maximum for takeoff 100% Maximum transient. Do not exceed 5 seconds above 100%. 105% Minimum 8 PSI Continuous operation 8 to 26 PSI Maximum 25 PSI Minimum below 79% GAS PRODUCER (N1) RPM 50 PSI Minimum from 79 to 94% GAS PRODUCER (N1) RPM 90 PSI Minimum above 94% GAS PRODUCER (N1) RPM 115 PSI Maximum 130 PSI Continuous operation 0 to 107°C Maximum 107°C External Power Start Battery Start 40 Seconds ON 60 Seconds ON 30 Seconds OFF 60 Seconds OFF 40 Seconds ON 60 Seconds ON 30 Seconds OFF 60 Seconds OFF 40 Seconds ON 60 Seconds ON 30 Minutes OFF 30 Minutes OFF Minimum 30 PSI Continuous operation 40 to 70 PSI Maximum 70 PSI Continuous operation 15 to 110°C Maximum 110°C 1-12 Rev. 4 BHT-206L4-FM-1 DOT APPROVED DOT APPROVED BHT-206L4-FM-1 1-30. ROTOR 1-31. ROTOR RPM - POWER ON Minimum transient. Do not exceed 5 seconds. 95% Minimum 99% Continuous operation 99 to 101% Maximum continuous 101% Maximum transient 104% during low power descent. Do not exceed 5 minutes above 101%. 1-32. ROTOR RPM - POWER OFF Minimum Maximum 90% 107% 1-33. ROTOR BRAKE Rotor brake (if installed) application is limited to ground operation after engine has been shut down and ROTOR RPM has decreased to between 36% and 30%. 1-34. FUEL AND OIL 1-35. FUEL Fuels conforming to the following specifications may be used at all ambient temperatures: ASTM-D-1655, Type B MIL-T-5624, Grade JP-4 (NATO F-40) Fuels conforming to the following specifications are limited to ambient temperatures of -32 °C (-25 °F) and above: ASTM-D-1655, Type A or A-l MIL-T-5624, Grade JP-5 (NATO F-44) MIL-T-83133, Grade JP-8 (NATO F-34) NOTE Anti-icing fuel additives are not required for any ambient temperature. Refer to Allison Operation and Maintenance Manual for cold weather fuel and blending instructions. 1-36. ENGINE OIL Oil conforming to MIL-L-7808 (NATO O- 146) may be used at all ambient Oil conforming to DOD-L-65734 (Turbine oil 555) or MIL-L-23699 (NATO O-156) limited to ambient temperatures above -40 °C (-40 °F). NOTE Refer to Allison Operation and Maintenance Manual and BHT- 206L4-MD-1 manual for approved oils and mixing of oils of different brands, types, and manufacturers. 1-37. TRANSMISSION AND TAIL ROTOR GEARBOX OIL NOTE It is recommended that DOD-L- 65734 oil be used in the transmission and tail rotor gearbox to the maximum extent allowed by temperature limitations. Rev. 4 1-13 BHT-206L4-FM-1 DOT APPROVED Oil conforming to DOD-L-65734 is limited to ambient temperatures above -40 °C (-40 l-38. HYDRAULIC °F). Hydraulic fluid conforming to MIL-H-5606 (NATO H-515) may be used at all ambient Oil conforming to MIL-L-7606 (NATO O- temperatures: 146) is limited to ambient temperatures below -16 °C (0 °F). I 1-14 Rev. 4 DOT APPROVED BHT-206L4-FM-1 ENGINE OIL PRESSURE 50 PSI Minimum 50 to 90 PSI Operation below 79% GAS PRODUCER (N1) RPM GAS PRODUCER (N1) RPM Maximum ENGINE OIL TEMPERATURE Maximum TRANSMISSION OIL PRESSURE 30 PSI Minimum 40 to 70 PSI Continuous operation 70 PSI Maximum TRANSMISSION OIL TEMPERATURE 15 to 110°C Continuous operation 110°C Maximum GAS PRODUCER RPM (N1) 206L4-F-1-4-1 Figure 1-4. Instrument markings (Sheet 1 of 3) Rev. 4 1-15 I BHt-206L4-FM-1 DOT APPROVED NOTE Range mark below warning light is at 999°C. Continuous operation 5 minute takeoff range Maximum TURBINE OUTLET TEMPERATURE 100 to 716°C Continuous Operation 716 to 768°C 5 minute takeoff range Beginning of time limited range for sarting. Minimum 99 to 101% Continuous operation 101% Maximum continuous 101 to 104% Transient overspeed range (5 minutes maximum) ROTOR RPM (NR) Minimum (power off) Continuous operation (power off) Maximum (power off) 206L4-F-1-4-2 Figure 1-4. Instrument markings (Sheet 2 of 3) I 1-16 Rev. 4 DOT APPROVED BHT-206L4-FM-1 AIRSPEED 0 to 130 Knots 100 Knots 130 Knots Continuous operation Maximum for autorotation Maximum FUEL QUANTITY FUEL PRESSURE 8 PSI Minimum Figure 1-4. Instrument markings (Sheet 3 of 3) Rev. 4 l-17/1-18 I FAA APPROVED BHT-206L4-FM-1 Section2 Paragraph TABLE OF CONTENTS 2-1 2-2 2-3 2-6 2-6 2-7 2-6 2-9 2-10 2-11 2-12 2-13 2-14 2-15 2-16 2-17 2-16 2-19 2-20 2-21 2-22 2-23 2-24 2-25 2-26 2-27 INTRODUCTION .......................................................... OPERATING LIMITATIONS .............................................. FLIGHT PLANNING ...................................................... TAKEOFF AND LANDING DATA.. .................................. WEIGHT AND BALANCE.. .......................................... PREFLIGHT CHECK ..................................................... BEFORE EXTERIOR CHECK ............................................ EXTERIOR CHECK ....................................................... FUSELAGE - CABIN RIGHT SIDE.. ............................... FUSELAGE - CENTER RIGHT SIDE.. ............................. FUSELAGE - AFT RIGHT SIDE.. .................................. FUSELAGE - FULL AFT ........................................... FUSELAGE - AFT LEFT SIDE ..................................... CABIN ROOF.. ...................................................... FUSELAGE - CABIN LEFT SIDE .................................. FUSELAGE - FRONT .............................................. INTERIOR AND PRESTART CHECK.. ................................... ENGINE STARTING.. .................................................... PRELIMINARY HYDRAULIC SYSTEMS CHECK ......................... ENGINE RUNUP ......................................................... HYDRAULIC SYSTEMS CHECK ......................................... BEFORE TAKEOFF.. .................................................... TAKEOFF ................................................................ INFLIGHT OPERATIONS ................................................. DESCENT AND LANDING ............................................... ENGINE SHUTDOWN .................................................... AFTER EXITING HELICOPTER .......................................... LIST OF FIGURES Figure Number Title Page Number 2-3 2-3 2-3 2-3 2-3 2-3 2-5 2-5 2-5 2-6 2-6 2-7 2-6 2-6 2-8 2-9 2-10 2-l 1 2-11 2-11 2-11 2-12 2-12 2-12 2-13 2-13 Page Number 2-1 Preflight check sequence . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 2-112-2 BHT-206L4-FM-1 2-1. INTRODUCTION This section contains instructions and procedures for operating helicopter from planning stage, through actual flight conditions, to securing helicopter after landing. Normal and standard conditions are assumed In these procedures. Pertinent data In other sections is referenced when applicable. Instructions and procedures contained herein are written for purpose of standardization and are not applicable to all situations. 2-2. OPERATING LIMITATIONS Minimum and maximum limits, and normal and cautionary operating ranges for helicopter and its subsystems are indicated by instrument markings and placards. Instrument markings and placards represent careful aerodynamic calculations that are substantiated by flight test data. Refer to Section 1, LIMITATIONS, for each operating limitation. 2-3. FLIGHT PLANNING Each flight should be planned adequately to ensure safe operations and to provide pilot with data to be used during flight. Check type of mission to be performed and destination. Select appropriate performance charts to be used from Section 4, PERFORMANCE. 2-4. TAKEOFF AND LANDING DATA Refer to Section 1 for takeoff and landing weight limits and to Section 4 for performance information. 2-5. WEIGHT AND BALANCE Determine proper weight and balance of helicopter as follows: 1. 2. 3. Consult BHT-206L4-MD-1 for Instructions. Determine weight of crew, fuel, oil, and payload; compute takeoff, most forward, most aft, and anticipated landing GW; and check helicopter CG locations. Ensure GW/CG limits listed in Section 1 have not been exceeded. 2-6. PREFLIGHT CHECK Pilot is responsible for determining whether helicopter is in condition for safe flight. Refer to figure 2-1 for preflight check sequence. NOTE Preflight check is not intended to be a detailed mechanical inspection, but simply a guide to 2-3 BHT-206L4-FM-1 FAA APPROVED 206L4-F-2-1 Figure 2-1. Preflight check sequence 2-4 FAA APPROVED BHT-206L4-FM-1 help pilot check condition of helicopter. It may be as comprehensive as conditions warrant at discretion of pilot. All areas checked shall include a visual check for evidence of corrosion, particularly when helicopter is flown near or over salt water or in areas of high industrial emissions. 2-7. BEFORE EXTERIOR CHECK 1. Flight planning - Completed. 2. Publications - Checked. 3. GW and CG - Computed. 4. Helicopter servicing - Completed. 5. Battery - Connected. 2-8. EXTERIOR CHECK 2-9. FUSELAGE - CABIN RIGHT SIDE 1. 2. 3. 4. 5. Right static port - Condition. Cabin doors - Condition and security. Windows - Condition and security. Landing gear - Condition and ground handling wheel removed. Forward and aft crosstube fairings (if installed) - Secured, condition, and aligned. 2-10. FUSELAGE - CENTER RIGHT SIDE 1. Engine inlet - Condition; remove inlet covers. 2. 3. 4. 5. 6. 7. 6. 9. 16. 11. 12. 13. Cabin roof, transmission cowling, and engine air inlet area - Cleaned of all debris and accumulated snow and ice; cowling secured. Hydraulic system filters - Bypass indicator retracted. Hydraulic actuators and lines - Condition, security, interference, leakage. Forward fairing - Secured. Transmission - Check oil level. Verify actual presence of oil in sight gage. Transmission oil cooler lines - Condition and security. Nodal beam - Check condition and security of elastomeric bearings, flexures, and fore and aft restraint damper. Main driveshaft forward coupling - Condition. Access door - Secured. Rotor head - Condition. Fuel filler cap - Visually check fuel level and cap secured. Fuel sump - Drain fuel sample as follows: a. FUEL BOOST circuit breakers - out. b. BAT switch - BAT (On). c. FUEL VALVE switch - OFF. d. PUSH FOR FUEL SUMP DRAIN button - Press, drain sample, then release. 2-5 BHT-206L4-FM-1 2-6 Rev. 4 NOTE Forward fuel cells can be drained manually as desired. 14. A/F fuel filter - Drain and check before first flight of day as follows: a. FUEL VALVE switch - ON. b. FUEL BOOST circuit breakers - In. c. Fuel filter drain valve - Open, drain sample, then close. NOTE Filter test button is located on top of fuel filter. 15. 16. 17. 16. a. b. C. Fuel filter test button - Press and check FUEL FILTER caution light illuminated. Release switch and check light extinguished. FUEL VALVE switch - OFF. BAT switch - OFF. Powerplant area Main driveshaft aft coupling - Condition. Engine - Condition; security of attachments. Evidence of oil leakage. Engine mounts - Condition and security. d. Throttle linkage - Condition, security, and freedom of operation. e. Fuel control and mechanical fuel pump - Security and condition; evidence of leakage, governor air lines. NOTE Fuel control heater valve shall be ON in ambient temperatures below 10 °C (50 °F). When operating in ambient temperatures above 21 °C (70 °F), fuel control heater valve shall be OFF. f. 19. 20. 21. 22. 23. 2-11. SIDE 1. 2. 3. 4. 5. 6. f f DOT APPROVED Fuel control heater valve (if installed) - As required. I Hoses and tubing - Chafing, security, and condition. Engine cowl - Secured. Generator cooling scoop - Clear of debris. Oil tank - Oil level, leaks, security, and cap secured. Access door - Secured. Aft fairing - Secured. USELAGE - AFT RIGHT uselage - Condition. rail rotor driveshaft cover - Condition and security. Tailboom - Condition. Horizontal stabilizer and position light - Condition and security. Synchronized elevator - Check lateral freedom, bearing play, and clear of obstructions. gain rotor blade - Condition. 2-12. FUSELAGE - FULL AFT 1. 2. 3. 4. 5. 6. Vertical fin - Condition. Tail rotor guard - Condition and security. Anticollision light - Condition and security of lens. Aft position light - Condition. Tail rotor gearbox - Oil level (normal oil level is 1/8 inch below line on sight glass), leaks and security. Tail rotor - Tiedown removed, condition and free movement. 20 Oct 1995 FAA APPROVED BHT-206L4-FM-1 7. Tall rotor controls + Condition and security. 6. Tail rotor blades - Condition; tip block security, evidence of corrosion, and seal condition. 2-13. FUSELAGE - AFT LEFT SIDE FAILURE TO REMOVE ROTOR TIEDOWNS BEFORE ENGINE STARTING MAY RESULT IN SEVERE DAMAGE AND POSSIBLE INJURY. 1. 2. 3. 4. 5. 6. Fuselage - Condition. 6. 9. 10. Oil cooler - Condition and leaks. 11. Oil cooler access door - Secured. Main rotor blade - Tiedown removed; condition. Tailboom - Condition. Tail rotor driveshaft cover - Condition and security. Horizontal stabilizer and position light - Condition and security. Synchronized elevator - Check lateral freedom, bearing play, and clear of obstructions. Forward tail rotor driveshaft coupling - Condition of splined adapter. Oil cooler blower shaft hanger bearings - Evidence of grease leakage and overheating. Oil cooler blower - Clear of obstructions and condition. 12. Aft fairing - Secured. 13. Baggage compartment - Cargo tied down, door secured. 14. Exhaust cover - Removed. 15. Powerplant area a. b. C. d. e. f. g- h. i. j- k. I. Engine - Condition; security of attachments. Engine mounts - Condition and security. Exhaust stack - Condition and security. Evidence of fuel and oil leaks. Hoses and tubing for chafing and condition. Pneumatic lines - Condition and security. Linear actuator and governor control linkage - Condition and security. Tail rotor driveshaft - Condition of splines and couplings. Air induction diffuser hose - Condition and security. Engine cowling - Secured. Air induction cowling - Secured. Cabin roof. transmission cowling, engine air inlet area, and plenum - Clear of all debris and accumulated snow and ice; cowling secured. 16. Transmission Area a. Nodal beam - Condition and security of elastomeric bearings, flexures, and fore and aft restraint damper. 2-7 BHT-206L4-FM-1 b. Transmission oil filter bypass button - Ensure not visible. c. Main driveshaft forward coupling - Condition. d. Cockpit indicator pressure lines - Condition and security. e. Access door - Secured. 2-14. CABIN ROOF 1. 2. 3. 4. 5. 6. 7. Main rotor hub and yoke - Condition. Main rotor blade doublers and skin - Condition. Pitch horn trunnion bearing - Wear and security. Main rotor pitch links - Condition and security of attachment bolts and locking hardware. Swashplate assembly - Condition, security of attached controls, and boot condition. Control linkages to swashplate - Condition, security of attachment bolts and locking hardware. Hydraulic reservoir filler cap - Closed and locked. 2-15. FUSELAGE - CABIN LEFT SIDE 1. Forward fairing and access door - Secured. 2. Cabin doors and hinge pins - Condition and security. 3. Windows - Condition and security. 4. Hydraulic reservoir - Check fluid level. 5. 6. 7. FAA APPROVED Landing gear - Condition and ground handling wheel removed. Forward and aft crosstube fairings (if installed) - Secured, condition and aligned. Left static port - Condition. 2-16. FUSELAGE - FRONT 1. 2. Exterior surfaces - Condition. Windshield - Condition and cleanliness. 3. Battery and vent lines - Condition and security. 4. 5. HOUR METER circuit breaker - In. FUEL BOOST LEFT circuit breaker - In. 6. 7. Battery access door - Secured. Pitot tube - Cover removed, clear of obstructions. 6. External power door - Condition and security. 9. Landing light glass - Condition. 10. Antennas - Condition and security. 11. Main rotor blade - Condition. NOTE APU should be 500 amperes or less to reduce risk of starter damage from overheating. 12. External power - Check BAT switch BAT (On) and APU connected as desired. 2-8 TC APPROVED BHT-206L4-FM-1 2-17. INTERIOR AND fixed intensity and can not be adjusted PRESTART CHECK by INST LT switch. 17. Overhead circuit breakers- In. 1. Cabin interior - Clean; equipment secured. WARNING 2. Fire extinguisher - Condition and security. security. BOTH FUEL BOOST PUMPS SHALL BE 3. Cabin loading - Maintain CG within ON DURING ENGINE OPERATION. limits. 18. BAT switch - BAT (On, for battery 4. Passenger seat belts - Secured. start). If APU is used for starting, BAT switch OFF. Observe ENG OUT, 5. Copilot seat belt-Secured (if solo). TRANS OIL PRESS, ROTOR LOW RPM, and GEN FAIL caution lights 6. Doors - Secured. illuminated. 7. Flight controls - Loosen frictions; 19. APU -Connected (if used). check freedom of travel; position for start. Tighten frictions as desired. 20. Applicable RPM audio signals - Check. 8. Throttle - Check freedom of travel and IDLE REL operation. Return to closed 21. WRN HORN MUTE switch - Press to position. mute. 9. LDG LTS switch - OFF. 22. CAUTION LT TEST switch - Press to test. 10. ENGINE ANTI-ICING switch - OFF. 23. TOT LT TEST switch - Press; ensure 11. HYDRAULIC SYSTEM switch - ON. red light on TURB OUT TEMP gage illuminates. Release switch and light 12. Radio and navigation equipment - extinguishes. OFF. OFF 24. FUEL VALVE switch - ON, guard 13. ALTIMETER-Settofield elevation. closed. Check FUEL pressure indication. 25. FUEL QY-- Check. 14. Instruments-mSt at zero. FUEL TY Check. 15. FREE AIR temperature - Note 26. Cyclic and pedals - Positioned for indication. start. start. 16. Overhead switches - OFF. 27. POS LT switch - POS LT for night operation. NOTE 28. ANTI COLL LT switch - ANTI COLL With INST LT switch (rheostat) on and LT CAUTION LIGHT switch positioned to DIM, caution lights are dimmed to a 29. Rotor brake handle (if installed) - Up and latched. 04 DEC 2001 Rev. 5 2-9 BHT-206L4-FM-1 FAA APPROVED 2-18. ENGINE STARTING TURB OUT TEMP during start cycle. 1. Collective - Full down. 8. TURB OUT TEMP Monitor. (Do 8. TURB OUT TEMP - Monitor. (Do 2. GOV RPM switch - DECR for 3 not exceed 10 seconds above 826 I seconds. °C or a maximum of 927 °C.) 3. Throttle - Full closed. CAUTION 4. Rotors - Clear. ..I 5. STARTER switch - Press to IF MAIN ROTOR IS NOT engage. (Observe engine starter ROTATING BY 25% GAS limitations.) PRODUCER (N1) RPM, ABORT 6. TURB OUT TEMP - 150 C or START. below. NOTE ENG OUT light extinguishes at 55 CAUTION 3% GAS PRODUCER (N1) RPM. 9. STARTER - Release at 58% GAS ENGINE STARTS BELOW 716 C PRODUCER (N1)RPM. TURB OUT TEMP FROM INTRODUCTION OF FUEL AND IN 10. ENG OIL and XMSN OIL EXCESS OF 40 SECONDS MAY BE pressures - Check. DETRIMENTAL TO TURBINE COMPONENTS. OPTIMUM . STARTS OCCUR WHEN THE CAUTION STARTING TURB OUT TEMP IS MAINTAINED BETWEEN 716 °C AND 826 °C WITH START TIMES IF ENGINE HAS BEEN SHUT LESS THAN 40 SECONDS. DOWN FOR MORE THAN 15 MINUTES, STABILIZE AT IDLE .NOTE FOR 1 MINUTE BEFORE INCREASING POWER. At the appropriate GAS PRODUCER RPM and TURB OUT NOTE TEMP, introduce fuel with the throttle to obtain the initial TURB During cold temperature OUT TEMP rise. Observe the 927 operations, stabilize at idle until °C limit. After initial TURB OUT ENG OIL and XMSN OIL TEMP rise, modulate throttle to temperatures and pressures are in maintain TURB OUT TEMP normal operating range. between 716 °C and 826 °C. This sequence should provide Refer to Allison Operation and optimum starts in less than 40 Maintenance Manual for cold seconds from the introduction of weather start procedures. fuel. If limits are exceeded or 11. GAS PRODUCER (N) - 63 to TURB OUT TEMP warning light 65% RPM. Illuminates, refer to Allison Operation and Maintenance 12. APU - Disconnect. Manual 14W2. 13. Throttle - Open to 70% GAS 7. Throttle - At 12% GAS PRODUCER (N1) RPM. PRODUCER RPM, modulate to idle to maintain 716 °C to 826 °C. 14. GEN switch - GEN. 2-10 Rev. 1 FAA APPROVED BHT-206L4-FM-1 2-19. PRELIMINARY HYDRAULIC SYSTEMS - CHECK NOTE Uncommanded control movement or motoring with hydraulic system off may indicate hydraulic system malfunction. HYDRAULIC SYSTEM switch - OFF, then ON. 2-20. ENGINE RUNUP 1. Collective - Full down. 1. Throttle - Increase smoothly to full open position. Check ROTOR LOW RPM caution light extinguished at 90% ROTOR RPM. 2. GOV RPM switch - Check POWER TURBINE governor actuator range 99 to 101% RPM; set at 100% RPM. 3. Radio and navigation equipment - ON. 4. ELT (if installed) - Check for inadvertent transmission. 5. Flight controls - Check freedom with minimum friction. 6. ENGINE ANTI-ICING switch - ON; check for TURB OUT TEMP increase. 7. ENGINE ANTI-ICING switch - OFF; check TURB OUT TEMP returns to normal; then switch ON if required. 2-21. HYDRAULIC SYSTEMS CHECK NOTE HYDRAULIC SYSTEMS CHECK is to determine proper operation of hydraulic actuators for each flight control system. If abnormal forces, unequal forces, control binding, or motoring are encountered, it may be an indication of a malfunctioning flight control actuator. 2. ROTOR - 100% RPM. 3. HYDRAULIC SYSTEM switch - OFF. 4. Cyclic - Centered. 5. Check normal operation of cyclic control by moving cyclic in an “X” pattern right forward to left aft, then left forward to right aft (approximately one inch). Center 6. Collective - Check for normal operations by increasing collective slightly (1 to 2 inches). Repeat 2 to 3 times as required. Return to full down position. 7. HYDRAULIC SYSTEM switch - ON. 6. Cyclic and collective friction - Set as desired. NOTE 2-22. BEFORE TAKEOFF If temperature is below 4.4 °C (40 °F) and visible moisture is present, ENGINE ANTI-ICING shall be ON. 1. Light switches - As required. 2. INST LT switch (rheostat) - As desired. 3. Radio(s) - Check as required. 2-11 4. 5. 6. 7. 6. 9. Flight controls - Position and adjust frictions for takeoff. Throttle - Full open. Check 100% POWER TURBINE RPM. Engine, transmission, and electrical instruments - Within limits. Flight and navigation instruments - Check. FUEL QTY - Note Indication. FUEL QTY switch - FWD. Note fuel remaining in forward cells. 2-23. TAKEOFF 1. 2. 3. 4. Collective - Increase to hover. Directional control - As required to maintain desired heading. Cyclic - Apply as required to accelerate smoothly. Apply minimum collective, up to 5% torque above hover power, to obtain desired rate of climb and airspeed. Once clear of the HV diagram shaded areas, adjust power and airspeed as desired. 2-24. IN-FLIGHT OPERATIONS 1. 2. AIRSPEED - As desired (not to ENGINE ANTI-ICING switch - ON In visible moisture when ambient temperature is at or below 4.4 °C (40 “F). NOTE When ENGINE ANTI-ICING switch is ON, TURB OUT TEMP will increase. Monitor TURB OUT TEMP when selecting ENGINE ANTI-ICING at high power settings. 3. ALTIMETER -Within limits. NOTE Maximum H, is 20,000 feet. Refer to applicable operating rules for high altitude oxygen requirements. 4. FUEL QTY switch - FWD, note fuel quantity in forward cells is less than previous check which indicates fuel is transferring from forward to main cell. 2-25. DESCENT AND LANDING 1. Flight controls - Adjust friction as desired. 2. Throttle - Full open. Check 99 to 101% POWER TURBINE RPM. NOTE Decreasing collective to low power may result in RPM overspeed. For prolonged low power approaches, RPM can be controlled by a small amount of collective increase (no significant torque increase) an&or by decreasing GOV RPM switch to obtain 100% POWER TURBINE RPM. This will maintain POWER TURBINE RPM within limits during low power descents; however: GOV RPM switch should be positioned to INCR as collective is increased. (Refer to POWER TURBINE RPM in LIMITATIONS, Section 1.) 3. Flight path - As required for type of approach. 4. LDG LTS switch - As desired. 2-12 TC APPROVED BHT-206L4-FM-1 2-26. ENGINE SHUTDOWN NOTE 1 LDG LTS switch - OFF. Left fuel boost pump will continue to operate until FUEL VALVE switch is 2. Throttle - Reduce to idle stop. Check positioned to OFF. This pump operates ROTOR LOW RPM caution light directly from battery and will not be illuminated and audio on (with WRN deactivated when BAT switch Is OFF. HORN MUTE Installed) at 90% ROTOR Battery power will be depleted if switch RPM. remains on. 3. WRN HORN MUTE switch - Press to 12. FUELVALVE switch -OFF. mute. 13. During rotor coast down, displace 4. Flight controls - Position for cyclic slightly Into direction of wind to shutdown, apply friction. minimize static stop contact. 5. ENGINE ANTI-ICING switch - OFF. CAUTION 6. TURB OUT TEMP - Stabilized at idle for two minutes. AVOID RAPID ENGAGEMENT OF ROTOR BRAKE IF HELICOPTER IS ON 7. ELT (if installed) - Check for ICE OR OTHER SLIPPERY, OR LOOSE inadvertent transmission. SURFACE TO PREVENT ROTATION OF HELICOPTER. 8. Radios and navigation equipment -- 14. Rotor brake handle (if installed) - As OFF. desired. Apply rotor brake between 9. IDLE REL switch - Press and hold. 38% and 30% ROTOR RPM. Return to stowed position after main rotor stops. CAUTION 15. Pilot - Remain at flight controls until rotor has come to a complete stop. TO ENSURE ENGINE CUTOFF, HOLD THROTTLE IN CLOSED 16. GEN switch--OFF. POSITION UNTIL GAS PRODUCER (N1) DECELERATES TO 0% RPM N1 AND TURB OUT TEMP IS 17. All overhead switches - OFF. STABILIZED. STABILIZED. 18. BAT switch - OFF. 10. Throttle - Closed; check TURB OUT TEMP and GAS PRODUCER (N1) RPM 2-27. AFTER EXITING decreasing, ENG OUT warning light HELICOPTER illuminated, and audio on at 55 + 3% GAS PRODUCER (N1) RPM. If any of following conditions exist: 11. WRN HORN MUTE switch - Press to 1. Thunderstorms are in local area or mute. forecasted. 04 DEC 2001 Rev. 5 2-13 BHT-206L4-FM-1 FAA APPROVED 2. Winds in excess of 20 knots or a down lightly against static stop and gust spread of 15 knots exists or is tying web strap to tailboom. forecasted. 2. Moor tail rotor with tiedown strap 3. Helicopter is parked within 150 feet and tie loosely to tailboom to of hovering or taxiing aircraft that prevent excessive flapping. are in excess of basic GW of helicopter. 3. Install exhaust cover and engine inlet covers. 4. Helicopter to be left unattended. Perform following: NOTE Refer to BHT-206L4-MD-1 for 1. Moor aft main rotor blade with R r to BT-2064-M-1 for tiedown assembly by drawing blade additional tiedown data. 2-14 DOTAPPROVED BHT-206L4-FM-1 Paragraph TABLE OF CONTENTS 3-1 3-2 3-3 3-4 3-5 3-6 3-7 3-6 3-9 3-10 3-11 3-12 3-13 3-14 3-15 3-16 3-17 3-16 3-19 3-20 3-21 3-22 INTRODUCTION .......................................................... DEFINITIONS ............................................................. CABIN VENTILATION.. .................................................. ENGINE EMERGENCIES.. ............................................... ENGINE FIRE DURING START OR SHUTDOWN ................... ENGINE FIRE DURING FLIGHT.. ................................... ENGINE FAILURE - HOVERING IN GROUND EFFECT ............ ENGINE FAILURE - OUT OF GROUND EFFECT.. ................. ENGINE RESTART.. ................................................ ENGINE OVERSPEED.. ............................................. ENGINE UNDERSPEED ............................................. ENGINE COMPRESSOR STALLS ................................... ENGINE OIL PRESSURE LOW, HIGH, OR FLUCTUATING.. ....... ENGINE OIL TEMPERATURE HIGH ................................ HYDRAULIC SYSTEM FAILURE.. ....................................... TAIL ROTOR FAILURES.. ............................................... COMPLETE LOSS OF TAIL ROTOR THRUST.. .................... FIXED PITCH FAILURES.. .......................................... ELECTRICAL FAILURES ................................................ GENERATOR FAILURE ............................................. EXCESSIVE ELECTRICAL LOAD ................................... FUEL TRANSFER FAILURE ............................................. LIST OF TABLES Table Number Title 3-l Warning lights ........................................................... 3-3 3-2 Caution lights ............................................................ 3-4 Page Number 3-3 3-3 3-3 3-5 3-5 3-5 3-6 3-6 3-7 3-6 3-6 3-6 3-9 3-9 3-9 3-10 3-10 3-10 3-11 3-11 3-11 3-12 Page Number Rev. 4 3-113-2