BHT-206L3-FM-1 - LONG RANGER III FLIGHT MANUAL

Revision .................. 4 ....................... 03 MAR 99 Revision .................. 5 ....................... 18 DEC 01 Revision .................. 6 ....................... 26 APR 05 26 APR 2005 Rev. 6 C/D BHT-206L3-FM-1 APPROVED: DATE: CHIEF, FLIGHT TEST FOR DIRECTOR — AIRCRAFT CERTIFICATION TRANSPORT CANADA LOG OF FAA APPROVED REVISIONS Original ....................0 ....................... 09 DEC 81 Revision ...................1 .......................29 NOV 82 Revision ...................2 ....................... 12 DEC 83 Revision ...................3 ....................... 26 OCT 84 Revision ...................4 ...................... 14 MAR 85 Revision ...................5 ....................... 21 OCT 86 Revision ...................6 ........................24 JUL 87 Revision ...................7 .......................09 MAY 88 Revision ...................8 ....................... 14 OCT 88 Revision ...................9 ....................... 12 SEP 89 Revision ................ 10 ....................... 04 DEC 89 Revision ................ 11 ....................... 25 MAY 90 Reissue.................... 0 ....................... 28 OCT 92 Revision .................. 1 ....................... 09 AUG 93 Revision .................. 2 ........................ 14 SEP 95 Revision .................. 3 ........................ 04 JUN 97 Revision .................. 4 ....................... 15 MAR 99 Revision .................. 5 ........................ 15 JAN 02 Revision .................. 6 ....................... 04 MAY 05 26 APR 2005 Rev. 6 E/F DOT APPROVED BHT-206L3-FM-1 GENERALINFORMATION ORGANIZATION This Rotorcraft Flight Manual is divided into four sections and an appendix as follows: Section 1 - LIMITATIONS Section 2 - NORMAL PROCEDURES Section 3 - EMERGENCY AND MALFUNCTION PROCEDURES Section 4 - PERFORMANCE Appendix - OPTIONAL EQUIPMENT A SUPPLEMENTS Sections 1 through 4 contain the DOT approved data necessary to operate the basic helicopter in a safe and efficient manner. Appendix A contains the approved supplements for optional equipment, which shall be used in conjunction with the basic Flight Manual when the respective optional equipment kits are installed. The Manufacturer’s Data (BHT-206L3-MD-1) manual, contains information to be used in conjunction with the Flight Manual. The manual is divided into four sections: Section 1 - WEIGHT AND BALANCE Section 2 - SYSTEMS DESCRIPTION Section 3 - OPERATIONAL INFORMATION Section 4 - HANDLING/SERVICING/ MAINTENANCE 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. USE OF PROCEDURAL WORDS The concept of procedural word usage and intended meaning which has been adhered to in preparing this manual is as follows: “Shall” has been used only when application of a procedure is mandatory. Rev. 2 i BHT-206L3-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: AC - Alternating Current A/F - Airframe ANTI COLL LT - Anticollision Light APU BAT C CG DC DECR ECS ELT ENG F ft GEN GOV - Alternate Power Unit - Battery - Celsius - Center of Gravity - Direct Current - Decrease - Environmental Control System - Emergency Locater Transmitter - Engine - Fahrenheit - Foot, Feet - Generator - Governor Hd - Hg - HP - HYDR - IDLE REL - IFR - IGE - IN - INCR - INST LT - KCAS - kg - LBS - KIAS - KTAS - LDG LTS - LT - MCP - mm - MPH OAT - OGE - POS LT - PSI - QTY - RLY - RPM DOT APPROVED Density Altitude Mercury Pressure Altitude Hydraulic Idle Release Instrument Flight Rules In Ground Effect Inch(es) Increase Instrument Light Knots Calibrated Airspeed Kilograms Pounds Knots Indicated Airspeed Knots True Airspeed Landing Lights Light Maximum Continuous Power millimeter Miles Per Hour (Statute) Outside Air Temperature Out of Ground Effect Position Light Pounds per Square Inch Quantity Relay Revolutions Per Minute ii Rev. 2 FAA APPROVED BHT-206L3-FM-1 SL - Sea Level TOT or - Turbine Outlet Temperature TURB OUT TEMP T/R - Tail Rotor TRANS - Transmission VFR - Visual Flight Rules Vne - Never Exceed Velocity WRN - Warning XMSN - Transmission FAA APPROVED BHT-206L3-FM-1 Paragraph TABLE OF CONTENTS 1-1 1-2 - 1-3 1-4 1-5 1-6 1-7 1-8 1-9 1-10 1-11 1-12 1-13 1-14 1-15 1-16 1-17 1-18 1-19 1-20 1-21 1-22 1-23 1-24 1-25 1-26 1-27 1-28 1-29 1-30 1-31 1-32 1-33 1-34 1-35 1-36 1-37 GENERAL ................................................................ BASIS OF CERTIFICATION .............................................. TYPE OF OPERATION ................................................... OPTIONAL EQUIPMENT.. ............................................... FLIGHT CREW ........................................................... WElGHT/CG .............................................................. WEIGHT ............................................................. CENTER OF GRAVITY - LONGITUDINAL ......................... CENTER OF GRAVITY - LATERAL ................................ DOOR(S) OFF ....................................................... AIRSPEED ............................................................... ALTITUDE ................................................................ AMBIENT AIR TEMPERATURE.. ........................................ MANEUVERING .......................................................... ELECTRICAL ............................................................. GENERATOR ........................................................ POWERPLANT ........................................................... GAS PRODUCER RPM.. ............................................ POWER TURBINE RPM ............... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . T OT) . . . . . . . . . . . . . . . . . . . . . . . . . TURBINE OUTLET TEMPERATURE ( ENGINE TORQUE .................... FUEL PRESSURE .................... ENGINE OIL PRESSURE.. ........... ENGINE OIL TEMPERATURE.. ...... .............................. .............................. .............................. .............................. .............................. ANTIICE ............................... STARTER ............................................................ TRANSMISSION .......................................................... TRANSMISSION OIL PRESSURE.. ................................. TRANSMISSION OIL TEMPERATURE .............................. ROTOR ................................................................... ROTOR RPM - POWER ON.. ...................................... ROTOR RPM - POWER OFF ....................................... FUEL AND OIL.. ......................................................... FUEL ................................................................ ENGINE OIL.. ....................................................... TRANSMISSION AND TAIL ROTOR GEARBOX OIL ............... HYDRAULIC .............................................................. Page Number 1-3 1-3 1-3 1-3 1-3 1-3 1-3 1-4 1-4 1-4 1-4 1-4 1-4 1-4 1-8 1-8 1-8 1-8 1-8 1-8 1-9 1-9 1-9 1-9 1-10 1-10 1-10 1-10 1-10 1-10 1-10 1-10 1-10 1-10 1-11 1-11 1-11 l-1 BHT-206L3-FM-1 FAA APPROVED Figure Number LIST OF FIGURES Title Page Number 1-1 Gross weight center of gravity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-5 1-2 Placards and decals....................................................... 1-6 1-3 Instrument markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-12 1-2 TC APPROVED BHT-206L3-FM-1 Section 1 . 1-1. GENERAL Flight with any combination of doors off is approved. Refer to AIRSPEED limitations. Compliance with limitations section is required by appropriate operating rules. 1-4. OPTIONAL EQUIPMENT Anytime an operating limitation is exceeded, an appropriate entry shall be made in The following equipment shall be installed helicopter logbook. Entry shall state which when conducting flight operations in falling limit was exceeded, the duration of time, the and/or blowing snow to reduce possibility of extreme value attained, and any additional engine flameout: information essential in determining maintenance action required. The Snow Deflector Kit or the Particle Separator Engine Air Induction System Intentional use of transient limits is Kit and the Snow Deflector Kit. (See BHT- prohibited. 206L3-FMS-3 and BHT-206L3-FMS-7.) Torque events shall be recorded. A torque Refer to appropriate Flight Manual event is defined as a takeoff or a load lift Supplement(s) for additional limitations, (internal or external), procedures, and performance data. 1-2. BASIS OF 1-5. FLIGHT CREW CERTIFICATION The minimum flight crew consists of one pilot This helicopter is certified under Civil Air who shall operate the helicopter from the Regulation, Parts 6, Rotorcraft Airworthiness, right crew seat Normal Category. The left crew seat may be used for an 1-3. TYPE OF OPERATION additional pilot when the approved dual controls are installed. seven-place seating and is certified for land * H operation under day or night VFR nonicing conditions. 1-7. WEIGHT Flight operations are approved with the .. .... landing gear crosstube fairings installed or CAUTION removed. LOADS THAT RESULT IN GROSS NOTE WEIGHTS ABOVE 4,150 POUNDS (1882.4 KG) SHALL BE CARRIED ON All unsecured items shall be removed AN APPROVED EXTERNAL LOAD KIT from cabin when any door is removed. AND SHALL NOT BE IMPOSED ON LANDING GEAR. 18 DEC 2001 Rev. 5 1-3 BHT-206L3-FM-1 DOTAPPROVED Maximum internal approved gross weight for takeoff and landing is 4,150 pounds (1882.4 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. 1-8. CENTER OF GRAVITY - LONGITUDINAL For gross weight longitudinal center of gravity limits, refer to figure l-l. 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 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-206L3-MD-1 for loading tables and instructions. 1-9. CENTER OF GRAVITY - LATERAL Lateral center of gravity limits are 4.0 inches (102 mm) left of and 3.5 inches (89 mm) right of fuselage centerline. 1-4 Rev. 4 1-10. DOOR(S) OFF Determine weight change after doors have been removed and adjust ballast if necessary. Refer to BHT-206L3-MD-1. 1-11. AIRSPEED Basic V,, is 130 KIAS (150 MPH) sea level to 3,000 feet density altitude. Decrease V,, for ambient conditions in accordance with AIRSPEED LIMITATIONS placard (figure 1- 2). V ne is 84 KIAS (96 MPH) at 85 to 100% TORQUE takeoff power. Vne, is 90 KIAS (104 MPH) with any door(s) off, not to exceed placarded Vne. 1-12. ALTITUDE Maximum operating pressure altitude is 20,000 feet. NOTE For high altitude pressure operation, refer to appropriate rules for oxygen requirements. 1-13. AMBIENT AIR TEMPERATURE The maximum sea level ambient air temperature for operation is +51.7°C (+125°F) and decreases with pressure altitude at the standard lapse rate of 2°C (3.6°F)/1000 feet to 20,000 feet. 1-14. MANEUVERING Aerobatic maneuvers are prohibited. FAA APPROVED BHT-206L3-FM-1 -119.2 (3026) Figure 1-1. Gross weight center of gravity 1-5 BHT-206L3-FM-1 TC APPROVED |IU~~~ P/N 206-075-770-101 i" e *0S a Z s NOTE Airspeed limitations panel 206-075-770-101 Is applicable if Technical Bulletin 206L-01-209 has not been accomplished. Airspeed limits shown are valid only for the corresponding altitudes and temperatures. Dashes indicate conditions which exceed approved temperature or density altitude limitations. 206L3FM_121 Figure 1-2. Placards and decals (Sheet I of 3) 4 1-6 Rev. 5 18 DEC 2001 TC APPROVED BHT-206L3-FM-1 P/N 206-075-770-107 NOTE Airspeed limitations panel 206-075-770-107 is applicable when Technical Bulletin 206L-01-209 has been accomplished. Airspeed limits shown are valid only for the corresponding altitudes and temperatures. Dashes indicate conditions which exceed approved temperature or density altitude limitations. Figure 1-2. Placards and decals (Sheet 2 of 3) TC APPROVED BHT-206L3-FM-1 26 APR 2005 Rev. 6 1-7 Figure 1-2. Placards and Decals (Sheet 3 of 3) AVOID CONT OPS 71.8% TO 91.5% N2 Location: Instrument panel. 206L3FM_1_0001 BHT-206L3-FM-1 TC APPROVED 1-8 Rev. 6 26 APR 2005 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 THE THROTTLE TO CONTROL RPM IS NOT AUTHORIZED. (REFER TO SECTION 3, EMERGENCY PROCEDURES — ENGINE OVERSPEED FOR EXCEPTION.) NOTE Refer to Allison Operation and Maintenance Manual for transient overspeed limits. 1-20. TURBINE OUTLET TEMPERATURE (TOT) WARNING EXCEEDING 768°C TURB OUT TEMP OR 100% TORQUE CAN CAUSE GAS PRODUCER TOPPING WITH RESULTANT ROTOR RPM DROOP. 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 97% Continuous operation 97 to 100% Maximum continuous 100% Transient overspeed range 100 to 103% Continuous operation 100 to 716°C Maximum continuous 716°C 5 minute takeoff range 716 to 768°C Maximum for takeoff 768°C Maximum transient (Do not exceed 10 seconds above 768°C). 871°C Maximum for starting and shutdown (Do not exceed 10 seconds above 768°C.) 927°C -- - DOTAPPROVED NOTE Intentional use of power transient area (768 to 871°C) is prohibited. The TURB OUT TEMP gage is equipped with a red warning light that will illuminate when either of the following conditions occur: 770 to 927°C more than 10 seconds or above 927°C. 1-21. ENGINE TORQUE Continuous operation 0 to 85% Maximum continuous 85% 5 minute takeoff range 85 to 100% Maximum for takeoff Maximum transient (Do not exceed 5 seconds above 100%. Intentional use prohibited.) 100% 105% 1-22. FUEL PRESSURE Minimum Continuous operation 4 PSI 4 to 25 PSI Maximum 25 PSI BHT-206L3-FM-1 Minimum Continuous operation 4 PSI 4 to 25 PSI Maximum Minimum for use of type A, A-l, or JP-5 fuel, or any mixture of these, at ambient temperature below - 18°C (0°F) 25 PSI 8 PSI 1-23. ENGINE OIL PRESSURE Minimum below 79% 50 PSI GAS PRODUCER (N,) RPM Minimum from 79 to 90 PSI 94% GAS PRODUCER (N,) RPM Minimum above 94% 115 PSI GAS PRODUCER RPM (N1) RPM Maximum 130 PSI 1-24. ENGINE OIL TEMPERATURE Continuous operation 0 to 107°C Maximum 107°C I l Gage with red triangle at 8 psi. Rev. 4 1-9 BHT-206L3-FM-1 DOT APPROVED 1-25. ANTI-ICE The maximum ambient temperature for use I of engine anti-ice is 4.4°C (40°F). ENGINE ANTI-ICING shall be ON for flight I in visible moisture in temperature below 4.4°C (40°F). 1-26. STARTER Limit starter energize time to the following: 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 1-27. TRANSMISSION 1-26. TRANSMISSION OIL PRESSURE Minimum Continuous operation Maximum 30 PSI 40 to 70 PSI 70 PSI 1-29. TRANSMISSION OIL TEMPERATURE Continuous operation 15 to 110°C Maximum 110°C 1-30. ROTOR 1-31. ROTOR RPM - POWER ON Minimum transient (Do not exceed 5 seconds) - 95% Minimum Continuous operation Maximum continuous Maximum transient during low power descent. (Do not exceed 6 minutes above 100%.) 97% 97 to 100% 100% 103% 1-32. ROTOR RPM - POWER OFF Minimum 90% Maximum 107% 1-33. FUEL AND OIL 1-34. FUEL Turbine fuel ASTM-D-1655, Type B, or MIL- T-5624, Grade JP-4, may be used at all ambient temperatures. 1-10 DOT APPROVED BHT-206L3-FM-1 Turbine fuel ASTM-D-1655, Type A or A-l, or MIL-T-5624, Grade JP-5, (NATO F-44), or MIL-T-83133, Grade JP-8, (NATO F-34), limited to ambient temperatures above . - -17.8% (0°F). Turbine fuel ASTM-D-1655, Type A or A-l, or MIL-T-5624, Grade JP-5, (NATO F-44), or MIL-T-83133, Grade JP-8, (NATO F-34), limited to ambient temperatures -32°C (-25°F) and above when equipped with fuel pressure gage with red triangle at 6 psi. NOTE Anti-icing fuel additives are not required for any ambient temperature. fer to Allison Operation and intenance Manual for cold weather fuel and blending instructions. Re Ma 1-35. ENGINE OIL Turbine oil MIL-L-7808 may be used at all ambient temperatures. DOD-L-85734(AS) or MIL-L-23699 limited to ambient temperatures above -40°C (-40°F). NOTE Refer to Allison Operation and Maintenance Manual and BHT- 206L3-MD-1 manual for approved oils and mixing of oils of different brands, types, and manufacturers. 1-36. TRANSMISSION AND TAIL ROTOR GEARBOX OIL Turbine oil MIL-L-7808 may be used at all ambient temperatures. DOD-L-85734(AS) or MIL-L-23699 limited to ambient temperatures above -40°C (-40°F). 1-37. HYDRAULIC Hydraulic fluid MIL-H-5606 may be used at all ambient temperatures. Rev. 4 1-11 BHT-206L3-FM-1 DOT APPROVED ENGINE OIL PRESSURE 50 PSI Mhmum 50 to so PSI Operation below 79% Nl RPM so to 115 PSI Continuous operatmn below 94% Nl RPM 115 to 130 PSI Contmuous operation 130 PSI Maximum ENGINE OIL TEMPERATURE m 0 to 107oc Continuous operation - Maximum TRANSMISSION OIL PRESSURE 30 PSI Mmlmum 40 to 70 PSI Continuous operatlo” 70 PSI Maximum TRANSMISSION OIL TEMPERATURE 15 to 110°C Continuous operatmn 110°C Maxmum GAS PRODUCER RPM (Nl, Continuous operation Maximum L206075-205-l Figure 1-3. instrument markings (Sheet 1 of 3) 1-12 Rev. 4 . DOT APPROVED BHT-206L3-FM-1 TORQUE 0 to 85% 85 to 100% 100% TURBINE OUTLET m 100 to716 C r” 716fo768 C 768 C @ 927 C a Warn1nq lqht Continuous operatmn 5 Mmute takeoff range Maximum TEMPERATURE Continuous operatmn 5 Minute takeoff range Manmum for takeoff MaxImum for start and shutdown (1 second max ) TOT between 770 and 927 C longer than 10 seconds. or TOT above 927 C NOTE Range Mark at 999 “C Any one of the two turbme outlet temperature gages may be mstalled I” hellcopter P O W E R TURBINE R P M (N2) 97% 97% to 100% 100% 100 to 103% Minimum Continuous operation Maximum continuous Transient overspeed range f 5 minutes rmx.) Mnmum (power off) Continuous operat,on (power off) Mawmum (power off) Fiaure 1-3. Instrument markings (Sheet 2 of 3) BHT-206L3-FM-1 DOT APPROVED AIRSPEED :o 130 Knots IO Knots 130 Knots Continuous operation Maximum for autorotation Maximum FUEL QUANTITY 0 Empty (zero usable) “L LUAU I 90% Maximum FUEL PRESSURE 4 PSI Minimum 4 to 25 PSI Continuous operatio I 25 PSI Maximum I NOTE: Either indicator may be installed. m DC LOAD n Maximum FUEL PRESSURE m 4PSI Minimum 0 25 PSI Continuous operation PSI Maximum A 8 PSI Minimum Type A, A-l, or JP-5 fuel below 18°C (O°Fj Figure 1-3. Instrument markings (Sheet 3 of 3) 1-14 Rev. 4 FAA APPROVED BHT-206L3-FM-1 Paragraph TABLE OF CONTENTS 2-1 2-2 2-3 2-4 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-l 6 2-19 2-20 2-21 2-22 2-23 2-24 2-25 2-26 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 ..................................... 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 2-5 2-6 2-6 2-7 2-8 2-8 2-9 2-10 2-11 2-11 2-l 1 2-11 2-12 2-12 2-12 2-13 2-13 Page Number 2-l Preflight check sequence . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 2-112-2 FAA APPROVED BHT-206L3-FM-1 2-1. INTRODUCTION This section contains instructions and procedures for operating the helicopter from the planning stage, through actual flight conditions, to securing the helicopter after landing. Normal and standard conditions are assumed in these procedures. Pertinent data in other sections is referenced when applicable. The instructions and procedures contained herein are written for the purpose of standardization and are not applicable to all situations. 2-2. OPERATING LIMITATIONS The minimum and maximum limits, and the normal and cautionary operating ranges for the helicopter and its subsystems are indicated by instrument markings and placards. The instrument markings and placards represent careful aerodynamic calculations that are substantiated by flight test data. Refer to Section 1, -- LIMITATIONS, for a detailed explanation of each operating limitation. 2-3. FLIGHT PLANNING Each flight should be planned adequately to ensure safe operations and to provide the pilot with the 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 the helicopter as follows: 1. Consult BHT-206L3-MD-1 for instructions. 2. Compute takeoff and anticipated landing gross weight, check helicopter center of gravity (CG) locations, and determine weight of fuel, oil, payload, etc. 3. Ensure weight/CG limits listed in Section 1 have not been exceeded. 2-6. PREFLIGHT CHECK The pilot is responsible for determining whether the helicopter is in condition for safe flight. Refer to figure 2-l for preflight check sequence. NOTE The preflight check is not intended to be a detailed mechanical inspection, but simply a guide to help the pilot check the condition of the helicopter. It may be as comprehensive as conditions warrant at the discretion of the pilot. Rev. 1 2-31 BHT-206L3-FM-1 FAAAPPROVED Figure 2-1. Preflight check sequence 2-4 DOT APPROVED BHT-206L3-FM-1 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. 3. Hydraulic system filters - Bypass indicator retracted. 4. Hydraulic actuators and lines - Condition, security, interference, leakage. 2-7. BEFORE EXTERIOR CHECK 5. 6. Forward fairing - Secured. -- 1. Flight planning - Completed. 2. Publications - Checked. 3. Gross weight and CG - Computed. 4. Helicopter servicing - Completed. 5. Battery - Connected. Transmission - Check oil level. Verify actual presence of oil in sight gage. 7. Transmission oil cooler lines - Condition and security. 6. Nodal beam - Check condition and security of elastomeric bearings, elastomeric straps, and fore and aft restraint damper. 9. 2-8. EXTERIOR CHECK 2-9. FUSELAGE - CABIN RIGHT Main driveshaft forward coupling - Condition, security, and grease leakage. Check Temp-Plates (four places) for evidence of elevated temperature indicated by dot changing color to black. SIDE 1. 2. 3. 4. 5. 2-10. 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 - Secured, condition, and aligned. FUSELAGE - CENTER RIGHT SIDE 1. Engine inlet - Condition; remove inlet covers. 2. Cabin roof, transmission cowling, and engine air inlet area - Cleaned of all debris and accumulated snow and ice; cowling secured. IF ANY TEMP-PLATE IS MISSING OR HAS BLACK DOTS MAINTENANCE PERSONNEL SHALL ASSIST IN DETERMINING AIRWORTHINESS. 10. Access door - Secured. 11. Rotor head - Condition. 12. Fuel filler cap - Visually check fuel level and cap secured. 13. Fuel sump - Drain fuel sample as follows: a. FUEL BOOST circuit breakers - out. b. BAT switch - On. c. FUEL VALVE switch - OFF. d. PUSH FOR FUEL SUMP DRAIN button - Press, drain sample, then release. Rev. 3 2-5 BHT-206L3-FM-1 DOTAPPROVED NOTE Forward fuel cells can be drained manually as desired. 14. A/F fuel filter - Drain and check before first flight of the 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. Fuel filter test button - Press and check FUEL FILTER caution light illuminated. Release switch and check light extinguished. 16. FUEL VALVE switch - OFF. 17. BAT switch - OFF. 16. Powerplant Area a. Main driveshaft aft coupling - Condition, security, and grease leakage. Check Temp-Plates (four places) for evidence of elevated temperature indicated by dot changing color to black. IF ANY TEMP-PLATE IS MISSING OR HAS BLACK DOTS, MAINTENANCE PERSONNEL SHALL ASSIST IN DETERMINING AIRWORTHINESS. b. Engine - Condition; security of attachments. Evidence of oil leakage. c. 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. f. Hoses and tubing - Chafing, security, and condition. 19. Engine cowl - Secured. 20. Generator cooling scoop - Clear of debris. 21. Oil tank - Oil level, leaks, security, and cap secured. 22. Access door - Secured. 23. Aft fairing - Secured. 2-11. FUSELAGE - AFT RIGHT SIDE 1. Fuselage - Condition. 2. Tail. rotor driveshaft cover - Condition and security. 3. Tailboom - Condition. 4. Horizontal stabilizer and position light - Condition and security. 5. Sync elevator - Check lateral freedom, bearing play, and clear of obstructions. 6. Main rotor blade - Condition. 2-12. FUSELAGE - FULL AFT 1. Vertical fin - Condition. 2. Tail rotor guard - Condition and security. 3. Anticollision light - Condition and security of lens. 4. Aft position light - Condition. 5. Tail rotor gearbox - Oil level, leaks and security. 2-6 Rev. 3 DOT APPROVED 6. Tail rotor - Tiedown removed, condition and free movement. 7. Tail 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. Main rotor blade - Tiedown removed; condition. 2. Tailboom - Condition. 3. Tail rotor driveshaft cover - Condition and security. 4. Horizontal stabilizer and position light - Condition and security. 6. Sync elevator - Check lateral freedom, bearing play, and clear of obstructions. 6. Fuselage - Condition. 7. Forward tail rotor driveshaft coupling - Condition of splined adapter. 6. Oil cooler blower shaft hanger bearings - Evidence of grease leakage and overheating. 9. Oil cooler blower - Clear of obstruction and condition. 10. Oil cooler - Condition and leaks. BHT-206L3-FM-1 11. Oil cooler access door - Secured. 12. Aft fairing - Secured. 13. Baggage compartment - Cargo tied down, door secured. 14. Exhaust cover - Removed. 15. Powerplant Area a. Engine - Condition; security of attachments. b. Engine mounts - Condition and security. c. Exhaust stack - Condition and security. d. Evidence of fuel and oil leaks. e. Hoses and tubing for chafing and condition. f. Pneumatic lines - Condition and security. g. Linear actuator and governor control linkage - Condition and security. h. Tail rotor driveshaft - Condition of splines, couplings, and freedom of movement. i. Air induction diffuser hose - Condition and security. j. Engine cowling - Secured. k. Air Induction cowling - Secured. I. Cabin roof, transmission cowling, engine air inlet area, and plenum - Clear of all debris and accumulated snow and ice; cowling secured. 16. Transmission Area 2-7 BHT-206L3-FM-1 DOT APPROVED a. Nodal beam - Condition and security of elastomeric bearings, elastomeric strap, and fore and aft restraint damper. I b. Transmission oil filter bypass button - Ensure not extended. c. Main driveshaft forward coupling - Condition and evidence of grease leakage. Check paint strip for evidence of overheat indicated by brown color. d. Cockpit indicator pressure lines - Condition and security. e. Access door - Secured. 2-14. FUSELAGE - CABIN LEFT SIDE 1. Main rotor hub and yoke - Condition. 2. Main rotor blade doublers and skin - Condition. 3. Pitch horn trunnion bearing - Wear and security. 4. Main rotor pitch links - Condition and security of attachment bolts and locking hardware. 6. Swashplate assembly - Condition, security of attached controls, and boot condition. 6. Control linkages to swashplate - Condition, security of attachment bolts and locking hardware. 7. Forward fairing and access door - Secured. 6. Cabin doors and hinge pins - Condition and security. 9. Windows - Condition and security. 2-8 Rev. 4 10. Hydraulic reservoir - Check fluid level. 11. Landing gear - Condition and ground handling wheel removed. 12. Forward and aft crosstube fairings - Secured, condition and aligned. 13. Left static port - Condition. 2-15. FUSELAGE - FRONT 1. Exterior surfaces - Condition. 2. Windshield - Condition and cleanliness. 3. Battery and vent lines - Condition and security. 4. HOUR METER circuit breaker - In. 5. FUEL BOOST LEFT circuit breaker - In. 6. Battery access door - Secured. 7. Pitot tube - Cover removed, clear of obstruction. 6. External power door - Condition and security. NOTE APU should be 500 amperes or less to reduce risk of starter damage from overheating. 9. Landing light glass - Condition. 10. Antennas - Condition and security. 11. Main rotor blade - Condition. 12. External power - Check BAT switch OFF and APU connected as desired. DOT APPROVED BHT-206L3-FM-1 2-16. INTERIOR AND PRESTART CHECK 1. Cabin interior - Clean; equipment secured. I 2. Fire extinguisher - Condition and security. 3. Cabin loading - Refer to BHT- 206L3-MD-1 to maintain CG within limits. 4. Passenger seat belts - Secured. 5. Copilot seat belt - Secured (if solo). 6. Doors - Secured. 7. Flight controls - Loosen frictions; check freedom of travel; position for start. Tighten frictions as desired. 8. Throttle - Check freedom of travel and IDLE REL operation. Return to closed position. 9. LDG LTS switch - OFF. 10. ENGINE ANTI-ICING switch - OFF. 11. HYDRAULIC SYSTEM switch - ON. 12. Radio and navigation equipment - OFF. 13. ALTIMETER - Set to field elevation. 14. Instruments - Static at zero. 15. FREE AIR temperature - Note indication. 16. Overhead switches - OFF. NOTE Effective helicopter S/N 51001 through 51389: For daylight operations, ensure INST LT switch (rheostat) is OFF. If the INST LT switch Is on, the caution lights can be dimmed and may not be visible. Effective helicopter S/N 51390 and subsequent: With the INST LT switch (rheostat) on and CAUTION LIGHT switch positioned to DIM, the caution lights are dimmed to a fixed intensity and can not be adjusted by the INST LT switch. 17. Overhead circuit breakers - In. BOTH FUEL BOOST PUMPS SHALL BE ON DURING ENGINE OPERATION. 18. 19. 20. 21. 22. 23. 24. 25. 26. 27. 28. BAT switch - ON for battery or GPU start. BAT switch - OFF for battery cart start. Observe ENG OUT, TRANS OIL PRESS. ROTOR LOW RPM. and GEN FAIL caution/warning’ light segments illuminated and applicable audio signal(s) operative. External power - Connected (if used). Applicable RPM audio signals - Check. WRN HORN MUTE button (if installed) - Press to mute. CAUTION LT TEST button - Press to test. TOT LT TEST button - Press; ensure red light on TURB OUT TEMP gage illuminates. FUEL VALVE switch - ON, guard closed. Check FUEL pressure indication. FUEL QTY - Check. Rotor low RPM audio - Check as follows (if WARN HORN MUTE button is installed, disregard): Rev. 4 2-9 BHT-206L3-FM-1 DOTAPPROVED Collective pitch - Increase; ensure audio on. Fully down; ensure audio off. 29. Cyclic and pedals - Positioned for start. 30. POS LT switch - On for night operation. 31. ANTI COLL LT switch - On. 2-I 7. ENGINE STARTING 1. Collective pitch - Fully down. 2. GOV RPM switch - DECR for 3 seconds. 3. Throttle - Fully closed. 4. Rotors - Clear. NOTE If TOT gage has a red triangle at 826°C refer to BHT-206L3-FMS-17 for alternate 10 second start limit. 5. STARTER button - Press to engage. (Observe engine starter limitations.) 6. TURB OUT TEMP - 150°C or below. . I ENGINE STARTS BELOW 716°C TURB OUT TEMP FROM INTRODUCTION OF FUEL AND IN EXCESS OF 40 SECONDS MAY BE DETRIMENTAL TO TURBINE COMPONENTS. OPTIMUM STARTS OCCUR WHEN THE STARTING TURB OUT TEMP IS MAINTAINED BETWEEN 716°C AND 768°C, WITH START TIMES LESS THAN 40 SECONDS. NOTE At the appropriate GAS PRODUCER RPM and TURB OUT TEMP, introduce fuel with the throttle to obtain the initial TURB OUT TEMP rise. Observe the 927°C limit. After initial TURB OUT TEMP rise. modulate throttle to maintain’ TURB OUT TEMP between 716°C and 768°C. This sequence should provide optimum starts in less than 40 seconds from the introduction of fuel. If limits are exceeded or TURB OUT TEMP warning light illuminates, refer to Model 206L-3 Maintenance Manual. 7. Throttle - At 12% GAS PRODUCER RPM modulate to idle to maintain 716°C to 768°C TURB OUT TEMP during start cycle. 8. TURB OUT TEMP - Monitor. (Do not exceed 10 seconds above 768°C or a maximum of 927°C.) I...........*..*..CAUTION . . . . . . . . . . . . . . . . . IF MAIN ROTOR IS NOT ROTATING BY 25% GAS PRODUCER RPM. ABORT START. NOTE ENG OUT light extinguishes at 55 ± 3% GAS PRODUCER RPM. 9. STARTER - Release at 58% GAS PRODUCER RPM. 10. ENG OIL and XMSN OIL pressures - Check. DOWN FOR MORE THAN 15 2-10 Rev. 4 FAA APPROVED BHT-206L3-FM-1 MINUTES, STABILIZE AT IDLE FOR ONE MINUTE BEFORE INCREASING POWER. 5. Flight controls - Check freedom with minimum friction. NOTE NOTE During cold temperature operations, stabilize at idle until ENG OIL temperature reaches 0°C. 11. GAS PRODUCER - 63 to 65% RPM. 12. Auxiliary power - Disconnect. BAT switch - On. The HYDRAULIC SYSTEMS CHECK is to determine proper operation of the 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. 13. Throttle - Open to 70% GAS PRODUCER RPM. 14. GEN switch - On. 2-20. HYDRAULIC SYSTEMS CHECK 2-18. PRELIMINARY 1. Collective - Fully down. HYDRAULIC SYSTEMS 2. ROTOR - 100% RPM. CHECK 3. HYDRAULIC SYSTEM switch - OFF. NOTE 4. Cyclic - Centered. Uncommanded control movement or motoring with hydraulic system off may indicate hydraulic system malfunction. HYDRAULIC SYSTEM switch - OFF, then ON. 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 appoximately one inch). Center 6. Collective - Check for normal 2-19. ENGINE RUNUP operations by increasing collective control slightly (1 to 2 inches). Repeat 2 to 3 times as required. - 1. Throttle - Increase smoothly to fully Return to fully down position.’ open position. Check ROTOR LOW RPM caution light extinguished at 7. HYDRAULIC SYSTEM switch - ON. 90% ROTOR RPM. 6. Cyclic and collective friction - Set 2. GOV RPM switch - Check POWER TURBINE governor actuator range 97 to 100% RPM; set at 100% RPM. as desired. 9. ENGINE ANTI-ICING switch - ON; check for TURB OUT TEMP increase. 3. Radio and navigation equipment - ON. 4. ELT (if installed) - Check for Inadvertent transmission. 10. ENGINE ANTI-ICING switch - OFF; check TURB OUT TEMP returns to normal; then switch ON if required. Rev. 1 2-11 BHT-206L3-FM-1 FAA APPROVED NOTE If temperature is below 4.4°C (40°F) and visible moisture is present, the ENGINE ANTI-ICING shall be ON. 2-21. BEFORE TAKEOFF 1. Light switches - As required. 2. INST LT switch (rheostat) - As desired. 3. Radio(s) - Check as required. 4. Flight controls - Position and adjust frictions for takeoff. 5. Throttle - Fully open. Check 100% POWER TURBINE RPM. 2-23. IN-FLIGHT OPERATIONS 1. AIRSPEED - As desired (not to exceed Vne, at flight altitude). 2. 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 is ON, TURB OUT TEMP will increase. Monitor TURB OUT TEMP when selecting ENGINE ANTI-ICING at high power settings. 3. ALTIMETER - Within limits. 6. Engine, transmission, and electrical instruments - Within limits. NOTE 7. Flight and navigation instruments - Check. Maximum pressure altitude is 20,000 feet. For high altitude operation, refer to appropriate 6. FUEL QTY - Note indication. operating rules for oxygen requirements. 9. FUEL QTY switch (if installed) - FWD. Note fuel remaining in forward cells. 2-22. TAKEOFF 4. FUEL QTY gage - For helicopters equipped with FUEL QTY switch, check fuel is transferring from forward to main cell at total fuel quantity approximately 407 LBS and below. 1. Collective pitch - Increase to hover. 2. Directional control - As required to 2-24. DESCENT AND maintain desired heading. LANDING 3. Cyclic control - Apply as required to accelerate smoothly. 4. Collective - Apply minimum necessary to obtain desired rate of climb and airspeed. Monitor engine limits and adjust collective as necessary. 1. Flight controls - Adjust friction as desired. 2. Throttle - Fully open. Check 97 to 100% POWER TURBINE RPM. NOTE Decreasing the collective pitch to low power may result in RPM overspeed. For prolonged low 12-12 Rev. 1 FAA APPROVED BHT-206L3-FM-1 power approaches, RPM can be controlled by a small amount of collective pitch increase (no significant torque increase) and/or by decreasing the GOV RPM switch to obtain 100% POWER TURBINE RPM. This will maintain POWER TURBINE RPM within limits during low Dower descents: however, the 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. 2-25. ENGINE SHUTDOWN 1. 2. 3. 4. 5. 6. - 7. 6. 9. LDG LTS switch OFF. Throttle - Reduce to idle stop. Check ROTOR LOW RPM caution light illuminated and audio on (with WRN HORN MUTE installed) at 90% ROTOR RPM. WRN HORN MUTE button (if installed) - Press to mute. Flight controls - Position for shutdown, apply friction. ENGINE ANTI-ICING switch - OFF. TURB OUT TEMP - Stabilized at idle for two minutes. ELT (if installed) - Check for inadvertant transmission. Radios and navigation equipment - OFF. IDLE REL button - Press and hold. TO ENSURE ENGINE CUTOFF, HOLD THROTTLE IN CLOSED POSITION UNTIL GAS PRODUCER DECELERATES TO 0% RPM AND TURB OUT TEMP IS STABILIZED. 10. Throttle - Closed; check TURB OUT TEMP and GAS PRODUCER RPM decreasing, ENG OUT warning light illuminated, and audio on at 55 ± 3% GAS PRODUCER RPM. 11. WRN HORN MUTE button (if Installed) - Press to mute. NOTE The left fuel boost pump will continue to operate until the FUEL VALVE switch is positioned to OFF. This pump operates directly from the battery and will not be deactivated when the BAT switch is OFF. Battery power will be depleted if switch remains on. 12. 13. FUEL VALVE switch - OFF. During rotor coast down, displace cyclic slightly into direction of wind to minimize static stop contact. 14. Pilot - Remain at flight controls until rotor has come to a complete stop. 15. GEN switch - OFF. 16. All overhead switches - OFF. 17. BAT switch - OFF. 2-26. AFTER EXITING HELICOPTER If any of the following conditions exist: Rev. 1 2-13 BHT-206L3-FM-1 1. Thunderstorms are In the local area or forecasted. 2. Winds in excess of 20 knots or a gust spread of 15 knots exists or is forecasted. 3. Helicopter Is parked within 150 feet of hovering or taxiing aircraft that are in excess of basic gross weight of helicopter. 4. Helicopter to be left unattended. Perform the following: 1. Moor aft main rotor blade with tiedown assembly by drawing blade FAA APPROVED down lightly against the static stop and tying web strap to tailboom. 2. Moor tail rotor with tiedown strap and tie loosely to tailboom to prevent excessive flapping. 3. Install exhaust cover and engine Inlet covers. NOTE Refer to BHT-206L3-MD-1 for additional tiedown data. I 2-14 Rev. 1 DOT APPROVED BHT-206L3-FM-1 Section3 Paragraph TABLE OF CONTENTS 3-1 3-2 3-3 3-4 3-5 3-6 3-7 3-6 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 3-1 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 3-6 3-9 3-9 3-9 3-10 3-10 3-10 3-11 3-11 3-11 3-11 3-12 Page Number Rev. 3 3-113-2 DOT APPROVED BHT-206L3-FM-1 - Section3 3-1. INTRODUCTION The following procedures contain the indications of failures or malfunctions which affect safety of the crew, the helicopter, ground personnel or property; the use of emergency features of primary and backup systems; and appropriate warnings, cautions, and explanatory notes. Tables 3-1 and 3-2 list fault conditions and corrective actions for warning lights and caution lights respectively. I Helicopter should not be operated following any precautionary landing until cause of malfunction has been determined and corrective action taken. 3-2. DEFINITIONS The following terms indicate the degree of urgency in landing the helicopter. LAND AS SOON AS POSSIBLE Land without delay at the nearest suitable area (i.e., open field) at which a safe approach and landing is reasonably assured. LAND AS SOON AS PRACTICAL The landing site and duration of flight are at the discretion of the pilot. Extended flight beyond the nearest approved landing area is not recommended. The following terms are used to describe the operating condition of a system, subsystem, assembly, or component. Affected Normal Fails to operate in the intended or usual manner. Operates in the intended or usual manner. All procedures listed herein assume the pilot gives first priority to helicopter control and a safe flight path. 3-3. CABIN VENTILATION Ventilation of the cabin to protect occupants from the affects of toxic fumes, smoke etc., shall be immediately performed as follows: 1. VENT - Open. 2. Cabin windows - Open for maximum ventilation. Table 3-1. Warning lights PANEL WORDING FAULT CONDITION CORRECTIVE ACTION (audio if functional) GAS PRODUCER less than Verify engine condition. Accomplish 55 ± 3% RPM; POWER engine failure procedure. TURBINE RPM decreasing BATTERY HOT Battery overheating. Turn BAT switch OFF and land as Temperature 140°F (60°C) soon as practical. If BATTERY RLY or higher. caution light illuminates, land as soon as possible. Rev. 4 3-3 BHT-206L3-FM-1 DOTAPPROVED Table 3-1. Warning lights (Cont) PANEL WORDING FAULT CONDITION CORRECTIVE ACTION LITTER DOOR OPEN Litter door not securely Close door securely before flight. If latched. light illuminates during flight, land as soon as practical. Table 3-2. Caution lights PANEL WORDING FAULT CONDITION CORRECTIVE ACTION ROTOR LOW RPM (audio & light) ROTOR below 90% RPM FUEL LOW Approximately 50-75 LBS of fuel remain. ENG CHIP Metallic particles in engine oil. TRANS CHIP Metallic particles in transmission oil. FUEL FILTER A/F fuel filter clogged. T/R CHIP Metallic particles in tail rotor gearbox oil. GEN FAIL Failure of generator. TRANS OIL PRESS XMSN OIL pressure is below minimum. TRANS OIL TEMP XMSN OIL temperature is at or above red line. BATTERY RLY Battery relay has malfunctioned to closed position with BAT switch OFF. Battery will not drop off line. Reduce collective pitch and ensure throttle is fully open. Light and audio should cease when ROTOR increases above approximately 90% RPM. Reduce power; verify fault with gage. Land as soon as possible. Reduce power; verify fault with gage. Land as soon as possible. If BATTERY HOT light is illuminated, land as soon as possible. Verify FUEL QTY. Land as soon as practical. Land as soon as possible. Land as soon as possible. Land as soon as possible. Clean before next flight. Land as soon as possible. GEN switch - RESET then ON. If GEN FAIL light remains illuminated, GEN switch - OFF. Land as soon as practical. I 3-4 Rev. 3 DOT APPROVED Table 3-2. Caution lights (Cont) BHT-206L3-FM-1 PANEL WORDING R/FUEL PUMP FAULT CONDITION CORRECTIVE ACTION Right pump of the dual Descend below 6,000 feet pressure boost pump assembly altitude if flight permits. Land as failed. soon as practical IF BOTH FUEL BOOST PUMPS FAIL, UNUSABLE FUEL MAY BE AS HIGH AS 160 POUNDS (73 KILOGRAMS) DUE TO INABILITY TO TRANSFER FUEL FROM FORWARD CELLS. I L/FUEL PUMP Left pump of the dual boost Descend below 6,000 feet pressure pump assembly failed. altitude if flight permits. Land as soon as practical. 3-4. ENGINE EMERGENCIES 3-5. ENGINE FIRE DURING START OR SHUTDOWN *INDICATIONS: 1. Excessive TURB OUT TEMP. 2. Visible smoke or fire. *PROCEDURE: 1. Throttle - Closed. 2. FUEL VALVE switch - OFF. - 3. STARTER switch - Press to motor engine until TURB OUT TEMP stabilizes at normal temperature. 4. Shut down and exit helicopter. 3-6. ENGINE FIRE DURING FLIGHT *INDICATIONS: 1. Smoke. 2. Fumes. 3. Fire. *PROCEDURE: 1. 2. 3. 4. 5. 6. Throttle - Closed. Immediately enter autorotation. FUEL VALVE switch - OFF. BAT switch - OFF. GEN switch - OFF. Execute autorotative descent and landing. Rev. 3 3-5