BHT-206B3-FM-1 - JET RANGER III FLIGHT MANUAL

Revision.........10 .............. 12 DEC 83 Revision .......... 4 .............. 12 JUL 94 Revision ......... 11 .............. 16 DEC 83 Revision .......... 5 . NOT FAA APPROVED Revision ......... 12 .............. 06 JUN 84 Revision .......... 6 .............. 14 SEP 95 Revision ......... 13 .............. 26 OCT 84 Revision .......... 7 .............. 27 FEB 97 Revision ......... 14 .............. 26 SEP 85 Revision .......... 8 ............. 6 OCT 00 Revision ......... 15 .............. 11 NOV 86 October 6, 2000 Rev. 8 C/D DOT APPROVED ORGANIZATION GENERAL INFORMATION BHT-206B3-FM-1 /--- The Rotorcraft Flight Manual is divided into four sections and Appendix A as follows: Section 1 - Section 2 - Section 3 - LIMITATIONS NORMAL PROCEDURES EMERGENCYAND MALFUNCTION PROCEDURES Section 4 - PERFORMANCE Appendix - OPTIONAL EQUIPMENT A SUPPLEMENTS Sections 1 through 4 contain DOT approved data necessary to operate the basic helicopter in a safe and efficient manner. Appendix A contains a list of 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 Manual (BHT- 206B3-MD-1) contains additional information to be used in conjunction with the Flight Manual and optional equipment supplements, as applicable. The manual is divided into four sections as follows: 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. Rev. 6 i BHT-206B3-FM-1 DOT APPROVED USE OF PROCEDURAL May and need not have been used WORDS only when application of a procedure is optional. The concept of procedural word usage and Will has been used only to indicate intended meaning which has been adhered futurity, never to indicate a mandatory to in preparing this manual is as follows: procedure. - Shall has been used only when application of a procedure is mandatory. “Should” has been used only when application of a procedure is recommended. - II Rev. 6 FAA APPROVED BHT-206B3-FM-1 Section 1 Paragraph TABLE OF CONTENTS Page Number 1-3 1-3 1-3 1-3 1-3 1-3 1-4 1-4 1-4 1-4 1-4 l-6 1-5 1-6 1-5 1-5 1-5 1-5 l-10 l-10 l-10 l-11 l-11 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 LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .......... TYPE OF OPERATION . . . . . . . ~ .......................................................... NIGHT FLIGHT LIMl TATIONS ................................................ FLIGHT WITH DOOR(S) OFF . . ................................................. FLIGHT WITH OPTIONAL EQ UIPMENT INSTALLED FLIGHT CREW . . . . . . . . . . . . . . . . . . . . . . . . ............................. ALTITUDE LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .............. AIRSPEED LIMITATIONS.. .. .......................................................... AFT DOOR(S) OFF ........................................................... FORWARD DOOR(S) OFF .................................................... WEIGHT LIMITATION us . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PO LONGITUDINAL CENTER OF GRAVITY LIMITS ............................. DOOR(S) OFF ................................................................. LATERAL CENTER OF GRAVITY LIMITS .................................... . LIMITATIONS .................................................... WER PLANT POWER TURBINE (N2) OPERATING RPM POWER ON . . . . N2 TRANSIENT OVERSPEED GAS PRODUCE TORQUE LIMITS .. . . . . . . . . TURBINE OUTLET TEMPERATI . . . . . . . I -- . .. ... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .............. LIMITS . . ........................................ R IN (N1) RPM LIMITS.. ........................................ ............................................... URE (TOT) LIMITS.. ......................... ENGINE OIL PRESSURE LIMITS.. ........................................... ENGINE OIL TEMPERATURE LIMITS ........................................ FUEL PRESSURE LIMITS .................................................... ENGINE STARTER LIMITATIONS.. ............................................... ENGINE ANTIICE LIMITATIONS ................................................... TRANSMISSION OIL LIMITATIONS ............................................... OIL PRESSURE.. ............................................................. OIL TEMPERATURE ................................. ROTOR (NR) LIMITATIONS .............. POWER ON ............................................. POWER OFF.. ....................... LOADMETER LIMITATIONS ....................................................... FUEL LIMITATIONS ............................................................... ENGINE OIL LIMITATIONS.. ...................................................... TRANSMISSION AND TAIL ROTOR GEARBOX OIL TYPE LIMITATIONS ........ INSTRUMENT MARKINGS.. ....................................................... Rev. 3 1`-11 BHT-206B3-FM-1 FAA APPROVED Paragraph TABLE OF CONTENTS (Cont) Page Number PLACARDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LIST OF FIGURES Figure Number Title l-l 1-2 Center of gravity vs gross weight ........................................ Lateral vs longitudinal CG limits ......................................... 1-3 N2 transient overspeed limits ............................................ l-4 I Instrument markings ...................................................... 1-6 Placards ................................................................... l-12 Page Number 1-6 1-8 l-10 1-13 1-17 1-2 Rev. 2 TC APPROVED BHT-206B3-FM-1 Section 1 LIMITATIONS Do not exceed Airspeed and Center of Gravity Limitations. Compliance with the limitations section is required by appropriate operating rules. Protracted rearward and sideward flight prohibited. Intentional use of transient limits is prohibited. External Cargo Loading limited to 3350 pounds (1519.6 kilograms) gross weight Turn anti-collision light OFF during flight with any combination of door(s) OFF. in or near visible moisture to prevent reflections and possible pilot vertigo. Flight with forward door(s) OFF is Keep cabin glass clean to prevent halation. prohibited with litters. TYPE OF OPERATION FLIGHT WITH OPTIONAL EQUIPMENT INSTALLEDThe basic helicopter is approved for five place seating and is certified for land The following equipment shall be installed operation under day or night VFR nonicing when conducting flight operations in conditions. falling and/or blowing snow to reduce possibility of engine flameout: Flight operations are approved with the of flameout: landing gear crosstube fairings installed or the Particle Separator Engine Air The Particle Separator Engine Air a removed. Induction System Kit (BHT-206B3-FMS-10), WIGH Deflector Kit (BHT-206B3-FMS-12), and NIGHT FLIGHT LIMITATIONS Engine (Automatic) Re-ignition Kit (BHT- 206B3-FMS-18). Night flight operation is limited to visual contact flight conditions. Orientation shall Refer to appropriate Flight Manual be maintained through visual reference to Supplement(s) for additional Limitations, ground objects solely as a result of lights Procedures, and Performance Data. on the ground or adequate celestial illumination. FLIGHT CREW FLIGHT WITH DOOR(S) OFF The minimum flight crew consists of one All unsecured items must be removed from pilot who shall operate the helicopter from cabin. the right crew seat. October 6, 2000 Rev. 8 1-3 BHT-206B3-FM-1 FAA APPROVED The left crew seat may be used for an AFT DOOR(S) OFF additional pilot when the approved dual controls are installed. Vne 100 MPH IAS (87 KIAS) power ON or OFF. ALTITUDE LIMITATIONS FORWARD DOOR(S) OFF 3000 POUNDS (1360.8 KILOGRAMS) GROSS Vne 80 MPH IAS (69 KIAS) power ON or WEIGHT AND BELOW OFF. Maximum operating - 20,000 feet pressure WARNING altitude. WARNING ABOVE 3000 POUNDS (1360.8 KILOGRAMS) AIRSPEEDS IN EXCESS OF GROSS WEIGHT AIRSPEED LIMITATIONS DOOR(S) OFF WILL CAUSE CYCLIC FORE Maximum operating - 13,500 feet density AND AFT STICK REVERSAL AND altitude. FUSELAGE BUFFETING. WEIGHT LIMITATIONS AIRSPEED LIMITATIONS WEIGHT LIMITATIONS 3,000 POUNDS (1360.8 KILOGRAMS) GROSS CAUTION WEIGHT AND BELOW LOADS THAT RESULT IN GROSS Vne 150 MPH IAS (130 KIAS) sea level to WEIGHTS ABOVE 3200 POUNDS 3,000 feet density altitude. Decrease Vne SHALL BE CARRIED ON THE 4.0 MPH IAS (3.5 KIAS) per 1,000 feet CARGO HOOK AND SHALL NOT above 3,000 feet density altitude. Maximum BE IMPOSED ON THE LANDING pressure altitude - 20,000 feet. GEAR. Maximum gross weight for takeoff and ABOVE 3,000 POUNDS (1360.8 KILOGRAMS) Maximum gross weight for takeoff and GROSS WEIGHT Internal - 3200 pounds (1451.5 Vne 140 MPH IAS (122 KIAS) sea level to kilograms). 3,000 feet density altitude. Decrease Vne 8.0 MPH IAS (7.0 KIAS) per 1,000 feet above 3,000 feet density altitude. Maximum density altitude - 13,500 feet. Refer to Airspeed Placard for Indicated Airspeed (IAS). 85 TO 100% TORQUE TAKEOFF POWER RANGE Vne 92 MPH IAS (80 KIAS). 1-4 Rev. 2 FAA APPROVED BHT-206B3-FM-1 External - 3350 pounds (1519.5 kilograms). LATERAL CENTER OF GRAVITY LIMITS FRONT SEAT WEIGHT 3.0 inches (76.2 millimeters) left of helicopter centerline. Minimum - 170 pounds (77.1 kilograms). NOTE 4.0 inches (101.6 millimeters) right of helicopter centerline. Ballast as required to maintain NOTE weight empty CG within limits. Refer to Center of Gravity vs Lateral CG limits vary depending Weight Empty chart in BHT- on longitudinal CG location. Refer 206B3-MM-1. to Lateral vs Longitudinal CG limits chart, figure 1-2. LONGITUDINAL CENTER OF GRAVITY LIMITS POWER PLANT LIMITATIONS Center of gravity limits are from station ALLISON Model 250-C20B Engine or 250- 106.0 (2692.4 millimeters) to 114.2 (2900.7 C20J Engine. The 250-C20B engine millimeters); however, the aft limits are limitations contained herein are applicable variable depending upon gross weight. to the 250-C20J engine. Refer to Center of Gravity vs Gross Weight Chart (figure l-l) and BHT-206B3-MD-1. POWER TURBINE (N2) OPERATING RPM LIMITS NOTE Station 0 (datum) is located 55.16 inches (1401.1 millimeters) forward of forward jack point centerline. POWER ON Minimum - 97%. Maximum - 100%. DOOR(S) OFF No change from basic helicopter CG with only the aft cabin door(s) OFF. USE OF THE THROTTLE TO Center of gravity limits are from station CONTROL RPM IS NOT 106.0 (2692.4 millimeters) to 110.0 (2794.0 AUTHORIZED. (REFER TO millimeters) with one or both forward SECTION 3, EMERGENCY AND door(s) OFF or any combination of forward MALFUNCTION PROCEDURES and aft cabin door(s) OFF. FOR EXCEPTION.) Actual weight change shall be determined after doors, etc., have been removed and N2 TRANSIENT OVERSPEED ballast readjusted if necessary, to return LIMITS empty weight center of gravity to within allowable limits. Refer to figure 1-3. l-5 BHT-206B3-FM-1 FAA APPROVED - CENTER OF GRAVITY VS GROSS WEIGHT ENGLISH UNITS LBS. 111.6 lN. I IN.+ 106 107 106 109 110 111 112 113 114.2 LONGITUDINAL CENTER OF GRAVITY 206900-2410 Figure l-l. Center of gravity vs gross weight (Sheet 1 of 2) l-6 Rev. 2 FAA APPROVED BHT-206B3-FM-1 - kg. 1451.5 1400 1350 1300 1100 1050 1000 950 907.2 CENTER OF GRAVITY VS. GROSS WEIGHT METRIC UNITS 2634.6 mm 1100 kg. mm -2692.4 2725 2750 2775 2794 2625 2850 2675 2900.7 LONGITUDINAL CENTER OF GRAVITY Figure 1-1. Center of gravity vs gross weight (Sheet 2 of 2) 1-7 BHT-206B3-FM-1 FAA APPROVED IN. 106 - 108- 110- 112- 114.2- LATERAL VS LONGITUDINAL CG LIMITS ENGLISH UNITS - 2.3 IN. - IN.-+ -3 -2 -1 0 1 2 3 4 -LEFT RIGHT- LATERAL CENTER OF GRAVITY Figure 1-2. Lateral vs longitudinal CG limits (Sheet 1 of 2) l-6 FAA APPROVED BHT-206B3-FM-1 LATERAL VS LONGITUDINAL CG LIMITS METRIC UNITS - mm + BHT-206B3-FM-1 FAA APPROVED GAS PRODUCER (N1) RPM LIMITS Maximum - 105%. Transient - 106% (maximum of 15 seconds). TORQUE LIMITS I Takeoff - 100% (5 minute limit). Transient - 110% (5 second limit. Intentional use prohibited). Maximum Continuous - 65%. TOT OR 100% TORQUE MAY CAUSE N1 TOPPING WITH RESULTANT ROTOR DROOP. During Starting and Shutdown - 610 to 927°C (10 seconds maximum). TURBlNE OUTLET TEMPERATURE (TOT) LIMITS Some hellcopters are equipped wlth a red warning light on the TOT gage. The light illuminates when either of the following conditions are exceeded: Takeoff - 610°C (5 minute limit). 612 to 927°C for 10 seconds Maximum Continuous - 738°C 927°C or higher for 1 second 32% 107 104 103 100 During Power Transient - 810 to 843°C (6 seconds maximum. Intentional use prohibited). I ENGINE TORQUE % N2 TRANSIENT OVERSPEED LIMITS 15 SECONDS MAXIMUM. SHADED AREA REPRESENTS ALLOWABLE OVERSPEED. Figure 1-3. N2 transient overspeed limits l-10 FAA APPROVED BHT-206B3-FM-1 Some helicopters are equipped with a red warning light with or without gage marked at 999°C on TOT. ENGINE OIL PRESSURE LIMITS Minimum - 50 PSI. Below 76.5% Gas Producer RPM - 50 PSI Minimum. Between 76.5 and 94.2% Gas Producer RPM - 90 PSI Minimum. Above 94.2% Gas Producer RPM - 115 PSI Minimum. Maximum - 130 PSI. ENGINE OIL TEMPERATURE LIMITS Continuous operation - 0°C to 107°C. Maximum - 107°C. FUEL PRESSURE LIMITS Minimum - 4.0 PSI. Maximum - 30.0 PSI. Fuel boost pumps shall be ON during normal engine operations. ENGINE STARTER LIMITATIONS Limit starter energizing time to the following: External Power Battery 25 Seconds - ON 40 Seconds - ON 30 Seconds - OFF 60 Seconds - OFF 25 Seconds - ON 40 Seconds - ON 30 Seconds - OFF 60 Seconds - OFF 25 Seconds - ON 40 Seconds - ON 30 Minutes - OFF 30 Minutes - OFF ENGINE ANTI-ICE LIMITATIONS Engine anti-ice shall not be used in ambient temperatures above 4.4°C (40°F). Engine anti-icing shall be ON for flight in visible moisture in temperature below 4.4°C (4O°F). TRANSMISSION OIL LIMITATIONS OIL PRESSURE Minimum Continuous operation Maximum - 30 PSI - 30 to 50 PSI - 70 PSI OIL TEMPERATURE Continuous operation Maximum - 15 to 110°C - 110°C ROTOR (NR) LIMITATIONS I POWER ON Minimum - 97%. Maximum - 100%. NOTE Transient rotor RPM droop down to 96% is permitted but should not exceed 5 seconds. Rev. 3 l-11 BHT-206B3-FM-1 FAA APPROVED 50% to 60% - Accelerate through this range as rapidly as practical with cyclic ENGINE OIL LIMITATIONS control in neutral. POWER OFF Minimum - 90% rotor RPM. Maximum - 107% rotor RPM. Aircraft turbine engine oil, MIL-L-7808, MIL-L-23699, or DOD-L-65734 (AS). (Refer to BHT-206B3-MD-1 for list of approved lubricants.) Operation with MIL-L-23699 and DOD-L- 65734 (AS) limited to ambient temperature above -40°C (-4O°F). LOADMETER LIMITATIONS NOTE Maximum - 70%. FUEL LIMITATIONS Turbine fuel ASTM-D 1655, Type B, or MIL- T-5624, Grade JP-4, may be used at all ambient temperatures. Operation with turbine fuels ASTM-D 1655, Type A or A-l. MIL-T-5624, Grade JP-5 or MIL-T-83133, -Grade JP-8 is limited to ambient temperatures of -18°C (0°F) or above unless helicopter is equipped with a fuel pressure gage which has a red triangle marking at 6 PSI (figure l-4). Helicopters equipped with a fuel pressure gage which has a red triangle at 6 PSI (figure 1-4) may operate with turbine fuels ASTM-D 1655. Type A or A-1. MIL-T-5624. Grade JP-5 or b&T-63133, Grade JP-8 at temperatures of -32°C (-25°F) and above providing fuel pressure is 6 PSI or above. Refer to Allison Model 250-C20 Operation and Maintenance Manual and BHT-206B3-MD-1 regarding mixing of oils of different brands, types, and manufacturers. TRANSMISSION AND TAIL ROTOR GEARBOX OIL TYPE LIMITATIONS Oil Type - MIL-L-7808, MIL-L-23699, or DOD-L-65734 (AS). Operation with MIL-L-23699 and DOD-L- 65734 (AS) is limited to ambient temperatures above -40°C (-40°F). INSTRUMENT MARKINGS Refer to figure 1-4. Helicopters equipped with airframe mounted fuel filter do not require the use PLACARDS of anti-icing additive at any ambient temperature. Refer to Allison 250-C20 Refer to figure 1-5. series Operation and Maintenance Manual for AVGAS Mix, Cold Weather Fuel, and Blending Instructions. l-12 Rev. 2 FAA APPROVED BHT-206B3-FM-1 INSTRUMENT MARKINGS BHT-206B3-FM-1 FAA APPROVED 1-14 Rev. 2 FAA APPROVED BHT-206B3-FM-1 INSTRUMENT MARKINGS BHT-206B3-FM-1 INSTRUMENT MARKINGS FAA APPROVED BHT-206B3-FM-1 PLACARDS 2068 AIRSPEED LIMITATIONS MPH - I AS Placards required with MPH airspeed indicator installed. Figure 1-5. Placards (Sheet 1 of 4) Rev. 2 BHT-206B3-FM-1 FAA APPROVED 2068 AIRSPEED LIMITS-KNOTS-IAS PLACARDS (Cont) I Placards required with KNOTS airspeed indicator installed. Figure 1-5. Placards (Sheet 2 of 4) 1-16 Rev. 2 DOT APPROVED BHT-206B3-FM-1 PLACARDS (Cont) The following 2068 Airspeed Limitations placard is installed in helicopter serial number 3567 and subsequent. 206B AIRSPEED LIMITATIONS-KNOTS-IA 16 78 87 96 18 78 87 20 78 Figure 1-6. Placards (Sheet 3 of 4) Rev. 6 1-19 BHT-206B3-FM-1 PLACARDS (Cont) FWD DOOR(S) OFF VNE 80 MPH (69 KNOTS) C.G. 106-l 10 (Located on both forward door frame posts.) DOT APPROVED THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED HELICOPTER FLIGHT MANUAL MINIMUM PILOT WEIGHT 170 LBS (These placards located on the inside of baggage compartment door.) CARGO MUST BE SECURED IN ACCORDANCE WITH FLIGHT MANUAL INSTRUCTION MAX ALLOWABLE WEIGHT 250 LBS. MAX ALLOWABLE WEIGHT PER SQ. FT. 86 LBS. Figure 1-6. Placards (Sheet 4 of 4) l-20 Rev. 6 FAA APPROVED BHT-206B3-FM-1 TABLE OF CONTENTS Paragraph INTRODUCTION ................................................................... OPERATING LIMITATIONS.. ...................................................... FLIGHT PLANNING.. .............................................................. TAKEOFF AND LANDING DATA ............................................. WEIGHT AND BALANCE ..................................................... PREFLIGHT CHECK.. ............................................................. BEFORE EXTERIOR CHECK.. .................................................... EXTERIOR CHECK ................................................................ 1. FUSELAGE - CABIN RIGHT SIDE. ....................................... 2. FUSELAGE - CENTER RIGHT SIDE.. .................................... 3. FUSELAGE - AFT RIGHT SIDE.. ......................................... 4. FUSELAGE - FULL AFT. ................................................. 6. FUSELAGE - AFT LEFT SIDE. ........................................... 6. FUSELAGE - CABIN LEFT SIDE. ........................................ 7. FUSELAGE - FRONT. .................................................... INTERIOR CHECK.. ............................................................... ENGINE PRESTART CHECK.. .................................................... ENGINE STARTING ................................................................ PRELIMINARY HYDRAULICS CHECK ............................................ ENGINE RUNUP CHECK .......................................................... HYDRAULICS 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 2-4 2-4 2-4 2-5 2-6 2-6 2-7 2-8 2-8 2-8 2-9 2-10 2-10 2-10 2-11 2-11 2-11 2-12 2-12 2-13 Page Number 2-1 Exterior check .. . . . . . . . . . . . . . . . . .. . . . . . . . . .. . .. . . . .. . . . . . . . . . . . . . . . . . . . .. . . 2-4 2-112-2 FAA APPROVED BHT-206B3-FM-1 Section2 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. 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 for a detailed explanation of each operating limitation. Anytime an operating limitation is exceeded, an appropriate entry shall be made in the helicopter logbook. The entry shall state which limit was exceeded, the duration of time, the extreme value attained, and any additional information essential in determining the maintenance action required. 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 flight to be performed and destination. Select appropriate performance charts to be used from Section 4. TAKEOFF AND LANDING DATA Refer to Section 1 for takeoff and landing weight limits and to Section 4 for performance information. WEIGHT AND BALANCE Determine prior weight and balance of the helicopter as follows: Consult applicable weight and balance instructions provided in BHT-206B3-MD- 1. Compute takeoff and anticipated landing gross weight, check helicopter center of gravity (CG) locations, and ascertain weight of fuel, oil, payload, etc. Ensure weight and balance limitations listed in Section 1 have not been exceeded. PREFLIGHT CHECK The pilot is responsible for determining whether the helicopter is in condition for 2-3 BHT-206B3-FM-1 DOTAPPROVED safe flight. Refer to figure 2-1 for preflight check sequence. NOTE The preflight check is not intended to be a detailed mechanical inspection, but a guide to help the pilot check the condition of the helicopter. It may be made as comprehensive as conditions warrant at the discretion of the pilot. Ensure that the helicopter has been serviced as required. Battery - Connected. EXTERIOR CHECK 1. FUSELAGE - CABIN RIGHT SIDE. Right static port - Condition. 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. Cabin doors - Condition and security. Windows - Condition and security. Landing gear - Condition. Ground handling wheel removed. BEFORE EXTERIOR CHECK Flight planning - Completed. Publications - Check. 2. FUSELAGE - CENTER RIGHT SIDE. Cabin roof, transmission fairing, and engine air inlet area - Cleaned of all debris and accumulated snow and ice. Figure 2-1. Exterior check 2-4 Rev. 7 DOT APPROVED BHT-206B3-FM-1 Hydraulic reservoir - Oil level. Hydraulic system filter - Bypass indicator retracted. Hydraulic actuators and lines - Condition, security, interference, leakage. Forward fairlng - Secured. Access door - Secured. TRANSMISSION AREA Main drivesheft forward coupling - I Condition, security, and grease leakage. Check Temo-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. Transmission - Oil level and area for leaks. Transmission and mounts - Security and condition. Isolation mount - Condition. Drag pin - Security and evidence of contact with static stop plate. Access door - Secured. Air induction cowling - Secured. Engine Inlet and plenum - Condition; clear of obstructions. Fuel filler cap - Visually check level. Secure cap. Fuel sump - Drain fuel sample as follows: FUEL BOOST AFT and FWD circuit breakers - Out. BAT switch - On. FUEL VALVE switch - OFF. Fuel drain or button - Depress, drain sample, then release. NOTE Apply the following procedure to the airframe (A/F) fuel filter kit and/or engine fuel pump filter. A/F fuel filter (If Installed) - Drain and check before first flight of the day as follows: FUEL VALVE switch - ON. FUEL BOOST AFT and FWD circuit breakers - In. CAUTION LT circuit breaker - In. Fuel filter drain valve - Open, drain sample, then close. NOTE Filter test switch Is located on top of fuel filter. Fuel filter test switch - Depress and check A/F FUEL FILTER caution light on. Release switch and check light out.- FUEL VALVE switch - OFF. BAT switch - OFF. POWER PLANT AREA 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. IF ANY TEMP-PLATE IS MISSING OR HAS BLACK DOTS MAINTENANCE PERSONNEL SHALL ASSIST IN DETERMINING AIRWORTHINESS. Engine - Condition; security of attachments. Engine mounts - Condition and security. Rev. 7 2-5 BHT-206B3-FM-1 FAA APPROVED Throttle linkage - Condition, security, and freedom of operation. Fuel control and governor - Evidence of leakage. Hoses and tubing - Chafing, security, and condition. Exhaust stack and clamp - Security and condition. Engine cowl - Secure. Generator cooling scoop - Clear of debris. Right exhaust cover - Removed. THE ENGINE OIL TANK SIGHT GAGE MOUNTED ON LEFT SIDE IS NOT INDICATIVE OF ACTUAL OIL QUANTITY. OIL QUANTITY SHALL BE CHECKED WITH DIPSTICK. Oil tank - Oil level, leaks, security, and cap secure. Access door - Secured. Aft fairing - Secured. 3. FUSELAGE - AFT RIGHT SIDE. Fuselage - Condition. Tail rotor driveshaft cover - Condition and secured. Tailboom - Condition. Horizontal stabilizer and position light - Condition and security. Main rotor blade - Condition. 4. FUSELAGE - FULL AFT. Vertical fin - Condition. Tail rotor guard - Condition and security. Anti-collision light - Condition. Aft position light - Condition. - Tail rotor gearbox - Oil level, leaks and security. Tail rotor - Tiedown removed, condition and free movement. Tail rotor controls - Condition and security. Tail rotor blade - Condition. Tip block for rivet damage, corrosion, and seal condition. 5. FUSELAGE - AFT LEFT SIDE. FAILURE TO REMOVE ROTOR TIEDOWNS BEFORE ENGINE STARTING MAY RESULT IN SEVERE DAMAGE AND POSSIBLE INJURY. Main rotor blade - Tiedown removed; condition. Tailboom - Condition. A Tail rotor driveshaft cover - Condition and secured. Horizontal stabilizer and position light - Condition and security. Fuselage - Condition. Baggage compartment - Cargo tied down; door secure. - 2-6 FAA APPROVED BHT-206B3-FM-1 Forward tail rotor driveshaft coupling - TRANSMISSION AREA Condition of splined adapter and freedom of rotation of witness pin (if installed). Transmission and mounts - Condition and security; area for leaks. Oil cooler blower shaft hanger bearings - Grease leakage and overheating. Isolation mount - Condition. Oil cooler blower - Clear of obstruction Access door - Secured. and condition. Oil cooler -Condition and leaks. 6. FUSELAGE - CABIN LEFT SIDE. Oil cooler access door - Secured. Cabin roof, transmission fairing, and Aft fairing - Secured. engine air inlet area - Cleaned of all debris and accumulated snow and ice. Left exhaust cover - Removed. Rotor head reservoirs (oil lubricated) - POWERPLANT AREA Visible oil levels. Engine - Condition security of Main rotor hub and yoke - Condition and attachments cracks. Engine mounts - Condition and security. Pitch horn trunnion bearing - Wear and security. Exhaust stack and clamp - Condition and security. Main rotor pitch links - Condition, cracks, and security of attachment bolts and Evidence of fuel and oil leaks. locking hardware. Hoses and tubing for chafing and Swashplate assembly - Condition, condition. security of attached controls, and boot condition. Linear actuator and governor control linkage - Condition and security. Control linkages to swashplate - Condition, security of attachment bolts Engine anti-ice valve and linkage - and locking hardware. Condition and security. Forward fairing and access door - Tail rotor driveshaft - Condition of Secured. splines, couplings and freedom of movement. Cabin doors - Condition and security. Engine cowling - Secured. Windows - Condition and security. Air induction cowling-Secured. Landing gear - Condition. Ground handling wheel removed. Engine inlet and plenum - Condition; clear of obstruction. Left static port - Condition. 2-7 BHT-206B3-FM-1 TC APPROVED 7. FUSELAGE - FRONT. HYDRAULIC SYSTEM switches. On helicopters prior to this, Exterior surfaces - Condition. switches are placarded ENGINE DE-ICING and CONTROL BOOST, Windshield - Condition and cleanliness. respectively. Battery and vent lines - Condition and Flight controls - Release friction; check security. freedom of movement and adjust to (cyclic) neutral/(collective) flat pitch Battery access door - Secured. position and pedals neutral. Pitot tube - Cover removed, clearof Throttle - Check freedom of full travel Pitot tube - Cover removed, clear of obstructions. and flight idle stop operation. Check copilot throttle if installed. Return to External power door- Condition and closed position. security. security ~LDG LTS switch - OFF. Landing light glass - Condition. ANTI-ICING ENGINE DE-ICING or ENGINE ANTI-ICING Antennas - Condition and security. switch - OFF. Main rotor blade Condition CONTROL BOOST or HYDRAULIC SYSTEM Main rotor blade - Condition. switch - ON. External power - Connect (if desired). FUEL VALVE switch - ON, guard closed. FUEL VALVE switch - ON, guard closed. INTERIOR CHECK Altimeter - Set to field elevation. Cabin interior - Cleanliness and security Instruments/Gages - Static position at of equipment. zero. Fire extinguisher - Security and Overhead switches - OFF. condition. First aid kit - Secure (if installed). NOTE Effective helicopter S/N 4128 and Copilot controls (if installed) - Security prior: for daylight operations, and proper installation. ensure INST LT switch (rheostat) is OFF. If the INST LT switch is Copilot seat belt - Secured (if solo). on, the caution lights can be dimmed and may not be visible. Cabin loading - Refer to BHT-206B3-MD-1. Cabin doors - Secured. Effective helicopter S/N 4129 and subsequent: With the INST LT switch (rheostat) on and caution light selector positioned to DIM, ENGINE PRESTART CHECK the caution lights are dimmed to a fixed intensity and can not be NOTE adjusted by the INST LT switch. Helicopters serial number 3567 GEN switch - OFF. and subsequent are equipped with ENGINE ANTI-ICING and Circuit breakers - In (as required). 2-8 Rev. 8 October 6, 2000 FAA APPROVED BHT-206B3-FM-1 I BAT switch - On for battery start; On for Engine oil pressure - indication of GPU start: OFF for battery cart start. increase. Observe TRANS OIL PRESS, ENG OUT, and ROTOR LOW RPM caution/warning light segments illuminated and applicable Throttle - Open to flight idle at 15% gas audio signal(s) operative. producer RPM with Turbine Outlet - Temperature (TOT) at or below 150°C. WRN HORN MUTE button (if installed) - Press to mute. NOTE - Engine out audio may be deactivated. CAUTION LT TEST button - Press to test illumination of each segment utilized. Turbine outlet temperature (TOT LT TEST) button (if Installed) - Press, check TOT light illuminates. ROTOR LOW RPM system - Check as follows: (if WRN HORN MUTE button is installed, the following does not apply.) Collective pitch - Increase; check ROTOR LOW RPM light and audio On. A START SHOULD NOT BE ATTEMPTED AT Nl SPEEDS BELOW 12%. Use the following guide for desired Nl starting speed versus outside air temperature: N1 RPM TEMP °C (°F) 15% Above 7° (45°) 13% -16 to +7° (0 to 45”) 12% Below -16° (0°) . Collective pitch - Full down; check ROTOR LOW RPM light On and audio Off. Flight controls - Neutral/fiat pitch DURING THE FIRST FEW position, apply friction (if needed). SECONDS OF THE START THE TOT WILL ACCELERATE AT A FUEL BOOST AFT and FWD circuit FAIRLY RAPID RATE AND SHALL breakers - in; check fuel pressure within BE CLOSELY MONITORED. limits and FUEL PUMP caution light off. ANTI COLL LT switch - On (if required). Turbine outlet temperature (TOT) - Monitor to avoid hot start. Abort start if either the 927°C maximum or the 810 to ENGINE STARTING 927°C MAXIMUM 10 SECONDS transient limitation is about to be exceeded by Collective pitch - Full down. depressing the engine IDLE REL button, CLOSE THROTTLE and continue to motor Throttle - Full closed. the starter until TOT decreases to less than 810°C. Some helicopters are equipped Rotors - Clear. with a red warning light-on the TOT gage. if limits are exceeded or light illuminates, Starter - Engage (observe Engine Starter consult Allison Engine Operation and Limitations, Section 1). Maintenance Manual. 2-9 BHT-206B3-FM-1 FAA APPROVED IF THE MAIN ROTOR IS NOT ROTATING BY 25% GAS PRODUCER SPEED (N1), ABORT THE START. Starter - Release at 56% gas producer RPM (N1). Engine and transmission oil - Check pressures increasing. IF THE ENGINE HAS BEEN SHUT DOWN FOR MORE THAN 15 MINUTES, STABILIZE AT IDLE Power turbine (N2) governor - Check SPEED FOR ONE MINUTE range 97 to 100% RPM. BEFORE INCREASING POWER. NOTE During cold temperature operations, stabilize engine at idle speed of 60 to 62% gas producer RPM (N1) until oil temperature reaches a minimum of 0°C. Gas producer RPM (N1) - Check for 60 to 62%. External power - Disconnect; BAT On. PRELIMINARY HYDRAULICS CHECK NOTE Uncommanded control movement or motoring with hydraulic system off may indicate hydraulic system malfunction. HYDRAULIC SYSTEM or CONTROL BOOST switch - OFF, then ON. ENGINE RUN-UP CHECK Smoothly and firmly advance throttle at a continuous rate to full open position, maintaining collective pitch down and cyclic control in neutral. NOTE If temperature is 4.4°C (40°F) or below and visible moisture is present, the engine anti-icing system shall be ON. ENGINE DEICING or ENGINE ANTI-ICING switch - ON (if conditions warrant. Observe TOT rise). PITOT HEAT switch (if installed) - ON in visible moisture with temperature below 4.4°C (40°F). Throttle - Open to 70% gas producer RPM. HYDRAULICS CHECK GEN switch - On. NOTE Radio equipment - On. ELT (if installed) - Check for inadvertent transmission. POS LT 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 2-10 FAA APPROVED BHT-206B3-FM-1 indication of a malfunctioning Power turbine N2 - Set for 100% in flat control actuator. pitch. Collective - Full down, friction removed. TAKEOFF Rotor rpm (Nr) - Set to 100%. HYDRAULIC SYSTEM or CONTROL BOOST switch - OFF. Cyclic - Centered, friction removed. 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 cyclic. Collective - Check for normal operations by increasing collective control slightly (1 to 2 inches). Repeat 2 to 3 times as required. Return to full down position. Collective pitch - Increase to hover. Directional control - As required to maintain desired heading. Cyclic control - Apply as required to accelerate smoothly. Collective - Apply as required to obtain desired rate of climb and airspeed. Monitor engine limits and adjust collective, as necessary. IN-FLIGHT OPERATIONS Pedals (if hydraulically boosted) - Displace slightly left and right. Note an Airspeed - As desired (not to exceed Vne increase in force required to move pedal in at flight altitude or maximum allowable for each direction. door(s) off flight configuration). HYDRAULIC SYSTEM or CONTROL BOOST switch - ON. Cyclic and collective friction - Set as desired. AIRSPEEDS IN EXCESS OF AIRSPEED LIMITATIONS DOOR(S) OFF WILL CAUSE CYCLIC BEFORE TAKEOFF CONTROL REVERSAL OF FORE AND AFT POSITION GRADIENT AND FUSELAGE BUFFETING. Electrical equipment - Check: reset as required. PITOT HEAT switch (if installed) - ON in Lighting - As desired. visible moisture with temperature below 4.4°C (40°F). INST LT switch (rheostat) - As desired. ENGINE DEICING or ENGINE ANTI-ICING Radio - Check as required. switch - ON, in visible moisture when temperature is below 4.4°C (40°F). I Throttle - Full open. NOTE Power and flight instruments - Normal operating range. TOT will increase when ENGINE ANTI-ICING is switched ON. Generator load - Below 70% (Note - normal load is 10-20%). Maximum pressure altitude is 20,000 feet. 2-11 BHT-206B3-FM-1 FAA APPROVED NOTE It is recommended that approved oxygen equipment be used when operating at altitudes above 10,000 feet. DESCENT AND LANDING Flight controls - Adjust friction desired. Throttle - Full open. Power turbine RPM (N2) - 97 to 100%. NOTE Decreasing the collective pitch into the low power realm may result in a RPM overspeed condition. For prolonged low power approaches the RPM can be controlled by a small amount of collective pitch increase (no significant torque increase) and/or by beeping down the N2 governor speed controller to 100% RPM. This will maintain governing within limits during low power descents, however, the GOV RPM switch should be beeped to INCR as collective is applied. (See N2 transient Overspeed Limits in Section 1.) Flight path - As required for type approach being made. LDG LTS switch - On as required. ENGINE SHUTDOWN as of Throttle - Flight idle. Check engine deceleration time. Full RPM to 65% Nl should take 3-5 seconds. Consult Allison Engine Operation and Maintenance manual if these times are exceeded. WRN HORN MUTE button (if installed) - Press to mute. Flight controls - Position for shutdown; apply friction. ENGINE DEICING or ENGINE ANTI-ICING switch - OFF. TOT - Stabilized at flight idle speed for two minutes. ELT (if installed) - Check for inadvertent transmission. IDLE REL button - Depress and roll throttle firmly to full closed position. TO ENSURE ENGINE CUTOFF, HOLD THROTTLE IN CLOSED POSITION UNTIL N1 DECELERATES TO 0 AND TOT IS STABILIZING. DO NOT TURN BAT SWITCH OFF UNTIL N1 IS 0 AND TOT STABILIZED. TOT - Check decreasing. During rotor coast down, apply cyclic to minimize static stop contact. Radio equipment - OFF. FUEL VALVE switch - OFF. GEN switch - OFF. All switches (except BAT) - OFF. BAT switch - OFF after N1 is zero and TOT stabilized. Pilot should remain at flight controls until rotor has come to a complete stop. 2-12