BHT-407-FM-1 - ROTORCRAFT FLIGHT MANUAL

REVISION 1 — 25 JULY 2002 BHT-407-FM-1 The following Warning is not applicable to helicopters on which all kits and customizing installations have been qualified and approved by Bell Helicopter. WARNING THE HELICOPTER MAY CONTAIN INSTALLATIONS, PARTS, OR PROCESSES CERTIFIED BY PARTIES OTHER THAN BELL HELICOPTER TEXTRON. BELL HELICOPTER CAN NOT CONFIRM THAT SUCH INSTALLATIONS HAVE BEEN FULLY QUALIFIED OR CONFORMED TO BELL HELICOPTER DESIGN CRITERIA. AS A RESULT OF SUCH INSTALLATIONS, BELL HELICOPTER SUPPLIED DATA MAY NOT BE VALID CONCERNING IN-FLIGHT HANDLING QUALITIES, WEIGHT AND BALANCE, OR HELICOPTER PERFORMANCE. IF MULTIPLE STC KITS OR SIMILAR INSTALLATIONS ARE INCORPORATED, THERE MAY BE NOT VALID TEST DATA TO QUALIFY THE HELICOPTER AS MODIFIED BY THESE INSTALLATIONS. FOR REVISED DATA, CONTACT THE OWNER OF THE INSTALLED STC OR THE SUPPLIER FOR THE APPLICABLE APPROVAL OF EACH INSTALLATION. NP 17 DEC 2002 Additional copies of this publication may be obtained by contacting: Commercial Publication Distribution Center Bell Helicopter Textron Inc. P. O. Box 482 Fort Worth, Texas 76101-0482 NOTICE PAGE BHT-407-FM-1 NOTE Revised text is indicated by a black vertical line. Insert latest revision pages; dispose of superseded pages. LOG OF REVISIONS Original........................0 ................... 09 FEB 96 Revision .....................1 ................... 08 MAR 96 Revision ......................2 ................... 09 MAY 96 Revision .....................3 ................... 30 JUL 96 Revision .....................4 ................... 04 NOV 96 Revision ......................5 ................... 24 JUN 97 Revision ......................6 ................... 03 JUL 98 Revision ...................... 7................... 04 SEP 98 Revision ...................... 8................... 17 APR 00 Reissue ....................... 0................... 17 DEC 02 Revision ...................... 1................... 10 MAR 04 Revision ...................... 2................... 29 NOV 04 Revision ...................... 3................... 26 APR 05 Revision ...................... 4................... 29 JUN 05 LOG OF PAGES REVISION REVISION NO. NO. PAGE PAGE Cover......................................................... 0 Title............................................................ 4 NP .............................................................. 0 A/B............................................................. 4 C/D............................................................. 4 E/F ............................................................. 4 i — ii .......................................................... 0 iii/iv ............................................................ 0 1–1— 1–5 .................................................. 0 1–6 ............................................................. 3 1–7 — 1–13 ............................................... 0 1–14 ........................................................... 3 1–15 — 1–19 ............................................. 0 1-20............................................................ 3 2–1/2–2 ...................................................... 0 2–3 — 2–5 ................................................. 0 2-6 ............................................................. 2 2-7 — 2-10 ................................................ 0 2-11 ........................................................... 4 2-12 — 2-16 .............................................. 0 2–17/2–18 ................................................. 0 3–1/3–2 ..................................................... 0 3–3 — 3–20 ............................................... 0 4–1/4–2 ..................................................... 0 4–3 — 4–50 ............................................... 0 4–51 /4–52 ................................................ 0 5–1 — 5–18 ............................................... 0 5–19/5–20 ................................................. 0 A–1/A–2 .................................................... 0 A–3 — A–4................................................ 2 29 JUN 2005 Rev. 4 A/B BHT-407-FM-1 LOG OF TC APPROVED REVISIONS Original ....................... 0................... 09 FEB 96 Revision ..................... 1................... 08 MAR 96 Revision ...................... 2................... 09 MAY 96 Revision ...................... 3................... 30 JUL 96 Revision ...................... 4................... 04 NOV 96 Revision ...................... 5................... 24 JUN 97 Revision ...................... 6................... 03 JUL 98 Revision ......................7 ...................04 SEP 98 Revision ......................8 ...................17 APR 00 Reissue........................0 ...................17 DEC 02 Revision ......................1 ...................10 MAR 04 Revision ......................2 ...................29 NOV 04 Revision ......................3 ...................26 APR 05 Revision ......................4 ...................29 JUN 05 29 JUN 2005 Rev. 4 C/D APPROVED DATE CHIEF, FLIGHT TEST FOR DIRECTOR — AIRCRAFT CERTIFICATION TRANSPORT CANADA BHT-407-FM-1 LOG OF FAA APPROVED REVISIONS Original ....................... 0....................09 FEB 96 Revision ..................... 1....................08 MAR 96 Revision ...................... 2....................09 MAY 96 Revision ...................... 3....................30 JUL 96 Revision ...................... 4....................04 NOV 96 Revision ...................... 5....................24 JUN 97 Revision ...................... 6....................18 MAY 99 Revision ......................7 ................... 18 MAY 99 Revision ......................8 ................... 05 MAY 00 Reissue........................0.................... 24 SEP 03 Revision ......................1.................... 11 MAR 04 Revision ......................2 ................... 07 DEC 04 Revision ......................3 ................... 04 MAY 05 Revision ......................4 .................... 30 JUN 05 29 JUN 2005 Rev. 4 E/F BHT-407-FM-1 GENERAL INFORMATION ORGANIZATION This Rotorcraft Flight Manual is divided into five sections and an appendix as follows: Sections 1 through 4 contain Transport Canada (TC) approved data necessary to operate basic helicopter in a safe and efficient manner. Section 5 contains weight and balance data necessary for flight planning. Appendix A contains a list of approved supplements for optional equipment, which shall be used in conjunction with basic Flight Manual when respective optional equipment kits are installed. Manufacturer's Data manual (BHT-407-MD-1) contains information to be used in conjunction with Flight Manual. Manufacturer's data manual is divided into four sections: TERMINOLOGY WARNINGS, CAUTIONS, AND NOTES Warnings, cautions, and notes are used throughout this manual to emphasize important and critical instructions as follows: WARNING A N O P E R A T I N G P R O C E D U R E , PRACTICE, ETC., WHICH, IF NOT CO RRECTLY FOLLOWED, COULD RESULT IN PERSONAL INJURY OR LOSS OF LIFE. CAUTION A N O P E R A T I N G P R O C E D U R E , PRACTICE , ETC., W HICH IF NO T S T R I C T L Y O B S E R V E D , C O U L D R E S U L T I N D A M A G E T O O R DESTRUCTION OF EQUIPMENT. NOTE An operating procedure, condition, etc., which is essential to highlight. USE OF PROCEDURAL WORDS 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. SHOULD has been used only when application of a procedure is recommended. Section 1 — LIMITATIONS Section 2 — NORMAL PROCEDURES Section 3 — EMERGENCY AND MALFUNCTION PROCEDURES Section 4 — PERFORMANCE Section 5 — WEIGHT AND BALANCE Appendix A — OPTIONAL EQUIPMENT SUPPLEMENTS Section 1 — SYSTEMS DESCRIPTION Section 2 — HANDLING AND SERVICING Section 3 — CONVERSION CHARTS AND TABLES Section 4 — EXPANDED PERFORMANCE 17 DEC 2002 i BHT-407-FM-1 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, ACRONYMS AND PLACARDING Abbreviations, acronyms and placarding used throughout this manual are defined as follows: ADF — Automatic direction finder AIR COND — Air conditioner A/F — Airframe ALT — Altimeter ANTI COLL LT — Anticollision light ATT — Attitude AUTO — Automatic AUX — Auxiliary BATT — Battery BIT — Built in test BL — Buttock line BLO — Blower BRT — Bright °C — Degrees Celsius CAUT — Caution CAUT LT — Caution lights CG — Center of gravity CKPT — Cockpit CM — Centimeter (s) COMM — Communication CONT — Control dBA — Decibel, “A” type filter DC — Direct current DG — Directional gyro DOT — Department of Transport ECS — Environmental control system ECU — Engine control unit ELT — Emergency locator transmitter ENCDG — Encoding ENG — Engine ENG ANTI ICE — Engine anti icing °F — Degrees Fahrenheit FADEC — Full authority digital engine control FS — Fuselage station FT or ft — Foot, feet FWD — Forward GEN — Generator GOV — Governor GPS — Global positioning system GPU — Ground power unit GW — Gross weight H D — Density altitude HG — Inches of mercury HMU — Hydromechanical unit Hp — Pressure altitude HYD — Hydraulic HV — Height-velocity ICAO — International Civil Aviation Organization ICS — Intercommunication system IFL — Inflate ii 17 DEC 2002 BHT-407-FM-1 IGE — In ground effect IGNTR — Ignitor IN — Inch(es) INSTR CHK — Instrument check INSTR LT — Instrument light KCAS — Knots calibrated airspeed KG or kg — Kilogram(s) KIAS — Knots indicated airspeed KTAS — Knots true airspeed L — Liter(s) LB(S) or lb(s) — Pound(s) LDG LTS — Landing lights L/FUEL — Left fuel LT — Light MAN — Manual MCP — Maximum continuous power MD — Manufacturer's Data MGT — Measured gas temperature MM or mm — Millimeter(s) NAV — Navigation NG — Gas producer RPM NP — Power turbine RPM NR — Rotor RPM OAT — Outside air temperature OBS — Omni bearing selector OGE — Out of ground effect OVSPD — Overspeed PART SEP — Particle separator PASS — Passenger(s) PMA — Permanent Magnetic Alternator POS LT — Position light PRESS — Pressure PSI — Pounds per square inch PTT — Press to Test PWR — Power QTY — Quantity R/FUEL — Right fuel RECP — Receptacle RLY — Relay RPM — Revolutions per minute RTR — Rotor s/w Ver Soft ware version SEL — Sound exposure level SHP — Shaft horsepower SL — Sea level SPKR — Speaker Sq — Square SYS — System T/R — Tail rotor TCA — Transport Canada Aviation TEMP — Temperature TRQ — Torque VFR — Visual flight rules VHF — Very high frequency VNE — Never exceed velocity VOR — VHF omnidirectional range WL — Water line WARN — Warning XFR — Transfer XMSN — Transmission XPDR — Transponder 17 DEC 2002 iii/iv TC APPROVED BHT-407-FM-1 17 DEC 2002 1-1 Section 1 LIMITATIONS 111 Paragraph Number Page Subject TABLE OF CONTENTS INTRODUCTION ......................................................................... 1-1.................... 1-3 BASIS OF CERTIFICATION ....................................................... 1-2.................... 1-3 TYPES OF OPERATION............................................................. 1-3.................... 1-3 PASSENGERS ...................................................................... 1-3-A................ 1-3 CARGO.................................................................................. 1-3-B................ 1-3 FLIGHT CREW ............................................................................ 1-4.................... 1-3 CONFIGURATION....................................................................... 1-5.................... 1-3 REQUIRED EQUIPMENT...................................................... 1-5-A................ 1-3 OPTIONAL EQUIPMENT ..................................................... 1-5-B................ 1-4 DOORS REMOVED.............................................................. 1-5-C................ 1-4 WEIGHT AND CENTER OF GRAVITY ....................................... 1-6.................... 1-4 WEIGHT................................................................................. 1-6-A................ 1-4 CENTER OF GRAVITY ......................................................... 1-6-B................ 1-4 AIRSPEED................................................................................... 1-7.................... 1-4 ALTITUDE ................................................................................... 1-8.................... 1-5 MANEUVERING .......................................................................... 1-9.................... 1-5 PROHIBITED MANEUVERS ................................................. 1-9-A................ 1-5 CLIMB AND DESCENT......................................................... 1-9-B................ 1-5 SLOPE LANDING ................................................................. 1-9-C................ 1-5 NOT USED .................................................................................. 1-10.................. 1-5 AMBIENT TEMPERATURES ...................................................... 1-11.................. 1-5 ELECTRICAL .............................................................................. 1-12.................. 1-5 GENERATOR ........................................................................ 1-12-A.............. 1-5 STARTER .............................................................................. 1-12-B.............. 1-5 POWER PLANT .......................................................................... 1-13.................. 1-5 GAS PRODUCER RPM (NG) ................................................ 1-13-A.............. 1-6 POWER TURBINE RPM (NP) ............................................... 1-13-B.............. 1-6 MEASURED GAS TEMPERATURE (MGT) .......................... 1-13-C.............. 1-6 ENGINE TORQUE ................................................................. 1-13-D.............. 1-6 FUEL PRESSURE ................................................................. 1-13-E .............. 1-6 ENGINE OIL PRESSURE ..................................................... 1-13-F .............. 1-6 ENGINE OIL TEMPERATURE .............................................. 1-13-G.............. 1-7 TRANSMISSION ......................................................................... 1-14.................. 1-7 TRANSMISSION OIL PRESSURE........................................ 1-14-A.............. 1-7 TRANSMISSION OIL TEMPERATURE ................................ 1-14-B.............. 1-7 ROTOR ........................................................................................ 1-15.................. 1-7 BHT-407-FM-1 TC APPROVED 1-2 17 DEC 2002 Paragraph Number Page Subject TABLE OF CONTENTS (CONT) ROTOR RPM — POWER ON ............................................... 1-15-A.............. 1-7 ROTOR RPM — POWER OFF ............................................. 1-15-B.............. 1-7 HYDRAULIC................................................................................ 1-16 ................. 1-7 FUEL AND OIL............................................................................ 1-17 ................. 1-7 FUEL ..................................................................................... 1-17-A.............. 1-7 OIL......................................................................................... 1-17-B.............. 1-8 ROTOR BRAKE .......................................................................... 1-18 ................. 1-8 NOT USED .................................................................................. 1-19 ................. 1-8 INSTRUMENT MARKINGS AND PLACARDS........................... 1-20 ................. 1-8 Figure Title Number Number Page LIST OF FIGURES Gross weight longitudinal center of gravity limits ................. 1-1 ................... 1-9 Gross weight lateral center of gravity limits ........................... 1-2 .................. 1-11 Placards and decals .................................................................. 1-3 .................. 1-13 Ambient air temperature limitations ........................................ 1-4 .................. 1-16 Instrument markings ................................................................. 1-5 .................. 1-17 TC APPROVED BHT-407-FM-1 17 DEC 2002 1-3 Section 1 LIMITATIONS 1 1-1. INTRODUCTION Co m plia nc e w it h lim ita t ion s s ec t ion is required by appropriate operating rules. Anytime an operating limitation is exceeded, a n a p p r o p ri a t e e n t r y s h a l l b e m a d e i n helicopter logbook. Entry shall state which limit was exceeded, duration of time, extreme value attained, and any additional information essential in determining maintenance action required. I n t e n t i o n a l u s e o f t r a n s i e n t l i m i t s i s prohibited. Torque events shall be recorded. A torque event is defined as a takeoff or lift, internal or external load (BHT-407-MD-1). Landings shall be recorded. Run-on landings shall be recorded separately. A run-on landing is defined as one where t h e r e i s f o r w a r d g r o u n d t r a v e l o f t h e helicopter greater than three feet with the weight on the skids. 1-2. BASIS OF CERTIFICATION This helicopter is certified under FARs Part 27 a n d 3 6 , A p p e n d i x J . A d d it i o n a l ly, i t is approved under Canadian Airworthiness Manual Chapters 516 (ICAO Chapter 11) and 527, Sections 1093 (b) (1) (ii) and (iii), 1301-1, 1557 (c) (3), 1581 (e) and 1583 (h). 1-3. TYPES OF OPERATION 1-3-A. PASSENGERS Basic configured helicopter is approved for seven place seating and is certified for land operation under day or night VFR nonicing conditions. 1-3-B. CARGO The maximum allowable cabin deck loading for cargo is 75 pounds per square foot (3.7 kilograms per 100 square centimeters). The maximum allowable baggage compartment deck loading is 86 pounds per square foot (4.2 kilograms per 100 square centimeters) with a maximum allowable weight of 250 pounds (113.4 kilograms). Refer to BHT-407-MD-1 for cargo restraint and tiedown locations. Cargo must be properly secured by tiedown devices to prevent the load from shifting u n d e r a n t i c i p a t e d f l i g h t a n d g r o u n d operations. If the m ission requires both passengers and cargo to be transported together, the cargo must be loade d and s e c u r e d s o t h a t i t d o e s n o t o b s t r u c t passenger access to exits. 1-4. FLIGHT CREW Minimum flight crew consists of one pilot who shall operate helicopter from right crew seat. Left crew seat may be used for an additional pi lo t w he n a pp ro v e d d ua l c on t ro ls a re installed. 1-5. CONFIGURATION 1-5-A. REQUIRED EQUIPMENT A functional flashlight is required for night flights. FADEC system software shall be version 5.202. BHT-407-FM-1 TC APPROVED 1-4 17 DEC 2002 1-5-B. OPTIONAL EQUIPMENT The snow deflector kit (BHT-407-FMS-4) shall b e i n s t a l l e d w h e n c o n d u c t i n g f l i g h t operations in falling and/or blowing snow. R e f e r t o a p p r o p r i a t e f l i g h t m a n u a l s u p p l e m e n t ( s ) ( F M S ) f o r a d d i t i o n a l limitations, procedures, and performance data for optional equipment. 1-5-C. DOORS REMOVED NOTE Indicated altitude may be up to 100 feet lower than actual altitude with crew door(s) removed. Flight with any combination of doors removed is approved. With litter door removed, left passenger door shall be removed. Refer to Airspeed limitations. With door(s) removed, determine weight change and adjust ballast if necessary. Refer to Section 5. NOTE All unsecured items shall be removed from cabin when any door is removed. 1-6. WEIGHT AND CENTER OF GRAVITY 1-6-A. WEIGHT Maximum approved internal GW for takeoff and landing is 5000 pounds (2268 kilograms). Minimum GW for flight is 2650 pounds (1202 kilograms). Minimum weight at fuselage station 65.0 is 170 pounds (77.1 kilograms). Maximum approved GW with jettisonable external load for takeoff and landings is 6000 pounds (2722 kilograms). 1-6-B. CENTER OF GRAVITY 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 Section 5 for loading tables and instructions. NOTE Ballast as required to maintain most forward or most aft CG within GW flight limits (Figure 1-1). For standard passenger and fuel loadings, applicable Weight empty center of gravity chart in BHT-407-MM-1 may be used to determine required ballast. For longitudinal CG limits refer to Gross weight longitudinal center of gravity limits chart (Figure 1-1). For lateral CG limits refer to Gross weight lateral center of gravity limits (Figure 1-2). 1-7. AIRSPEED Basic V NE is 140 KIAS, sea level to 3000 feet H D . Decrease V NE for ambient conditions in accordance with AIRSPEED LIMITATIONS placards and decals (Figure 1-3). V NE at 93.5 to 100% TORQUE (takeoff power) is 100 KIAS, not to exceed placarded V NE . V NE is 100 KIAS or placarded VNE , whichever is less, when takeoff loading is in shaded area of the Gross weight lateral center of gravity limits (Figure 1-2). V NE is 100 KIAS with any door(s) removed, not to exceed placarded VNE. V NE is 100 KIAS or placarded VNE , whichever is less for steady state autorotation. 7&$33529(' %+7)0 0D[LPXPDOORZDEOHDLUVSHHGIRUVLGHZDUG DQGUHDUZDUGIOLJKWRUFURVVZLQGKRYHULV .7$6 6XVWDLQHG KRYHU DQG YHUWLFDO WDNHRII ODQGLQJ RSHUDWLRQ JUHDWHU WKDQ RQH PLQXWH ZLWK WDLOZLQG UHODWLYH ZLQGV ZLWKLQ “ ƒ RI WDLO JUHDWHU WKDQ  NQRWV LV SURKLELWHG  $/7,78'( 0D[LPXPRSHUDWLQJDOWLWXGHLVIHHW+S 7(0325$5<5(9,6,2175²-$1  TC APPROVED BHT-407-FM-1 17 DEC 2002 1-5 Maximum allowable airspeed for sideward and rearward flight or crosswind hover is 35 KTAS. 1-8. ALTITUDE Maximum operating altitude is 20,000 feet H D or 20,000 feet HP, whichever is lower. 1-9. MANEUVERING 1-9-A. PROHIBITED MANEUVERS Aerobatic maneuvers are prohibited. 1-9-B. CLIMB AND DESCENT Maximum rate of climb is 2,000 feet per minute. 1-9-C. SLOPE LANDING Slope landings are limited to 10° side slopes, 10° nose up slope or 5° nose down slope. 1-10. NOT USED 1-11. AMBIENT TEMPERATURES Maximum sea level ambient air temperature f o r o p e r a t i o n i s + 5 1 . 7 ° C ( + 1 2 5 ° F ) a n d decreases with H P at standard lapse rate of 2°C (3.6°F) per 1000 feet to 20,000 feet. Refer to Ambient air temperature limitations chart (Figure 1-4). M i n i m u m a m b i e n t a i r t e m p e r a t u r e f o r operation at all altitudes is −40 °C (−40°F). ENG ANTI ICE shall be ON in visible moisture when OAT is below 5°C (40 °F). 1-12. ELECTRICAL 1-12-A. GENERATOR 1-12-B. STARTER NOTE 28 VDC GPU for starting shall be limited to 500 amps. 1-13. POWER PLANT Rolls-Royce model 250-C47B. NOTE Intentional use of any power transient is prohibited. Continuous operation, up to 10,000 feet H p 0 to 180 Amps Maximum continuous up to 10,000 feet Hp 180 Amps Continuous operation, above 10,000 feet H p 0 to 170 Amps Maximum continuous above 10,000 feet H p 170 Amps Transient, 2 minutes 180 to 300 Amps Transient, 5 seconds 300 to 400 Amps 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 BHT-407-FM-1 TC APPROVED 1-6 Rev. 3 26 APR 2005 1-13-A. GAS PRODUCER RPM (NG) 1-13-B. POWER TURBINE RPM (NP) NOTE ENGINE OVSPD warning light will illuminate when NP versus TORQUE is between 102.4% NP at 100% TORQUE and 108.6% NP at 0% TORQUE. When operating in MANUAL mode NP should be maintained between 95% and 100%. 1-13-C. MEASURED GAS TEMPERATURE (MGT) GAUGE P/N 407-375-001-101/-103 NOTE Either MGT gauge may be installed. GAUGE P/N 407-375-001-105 AND SUB 1-13-D. ENGINE TORQUE NOTE Use of takeoff power is limited to 100 KIAS, not to exceed placarded V NE . 1-13-E. FUEL PRESSURE 1-13-F. ENGINE OIL PRESSURE NOTE When 130 PSI is exceeded during start, operate engine at idle until oil pressure drops below 130 PSI. Continuous operation 63 to 105% Maximum continuous operation 105% Transient, 10 seconds 105.1 to 106% Avoid continuous operations 68.4 to 87.1% Minimum 99% Continuous operation 99 to 100% Maximum continuous 100% Maximum transient, 15 seconds 102.1 to 107% NP Continuous operation 100 to 727°C Maximum continuous 727°C Takeoff, 5 minutes 727 to 779°C Maximum for takeoff 779°C Transient, 12 seconds 780 to 826°C Maximum starting, do not exceed 10 seconds above 826°C or 1 second at 927°C. 927 °C Continuous operation 100 to 727°C Maximum continuous 727°C Takeoff, 5 minutes 727 to 779°C Maximum for takeoff 779°C Transient, 12 seconds 780 to 905°C Maximum starting, do not exceed 10 seconds above 843°C or 1 second at 927°C. 927°C Continuous operation 0 to 93.5% Maximum continuous 93.5% Takeoff, 5 minute 93.5 to 100% Transient, 5 seconds 105% Minimum 8 PSI Continuous operation 8 to 25 PSI Maximum 25 PSI Minimum below 79% NG 50 PSI Minimum from 79 to 94% NG 90 PSI Minimum above 94% NG 115 PSI Maximum 130 PSI Maximum cold starts only 200 PSI 7&$33529(' %+7)0 * (1*,1( 2,/ 7(03(5$785( &RQWLQXRXVRSHUDWLRQ WRƒ& 0D[LPXP ƒ& &$87,21 ,) +29(5,1* :,7+ $ 7$,/:,1' * 5 ( $ 7 ( 5  7 + $ 1    . 1 2 7 6  $ 7 2 $ 7  $ % 2 9 (    ƒ &     ƒ )  % & / 2 6 ( / <  0 2 1 , 7 2 5  ( 1 * , 1 ( $ 1 '  7 5 $ 1 6 0 , 6 6 , 2 1  2 , / 7 ( 0 3 ( 5 $ 7 8 5 ( 6   , )  ( 1 * , 1 ( 2 5  7 5 $ 1 6 0 , 6 6 , 2 1  2 , / 7 ( 0 3 ( 5 $ 7 8 5 ( 6  5 , 6 ( $%1250$//<% 7851 ,172 :,1'% 5('8&( 32:(5 25 75$16,7,21 7 2  ) 2 5 : $ 5 '  ) / , * + 7  8 1 7 , / 7(03(5$785('(&5($6(6 127( 3RVLWLYHWHPSHUDWXUHLQGLFDWLRQLVZKHQ WKHVHFRQGVHJPHQWRIWKHWUHQGDUFLV LOOXPLQDWHG  75$160,66,21 7(0325$5<5(9,6,2175²-$1  TC APPROVED BHT-407-FM-1 1-13-G. ENGINE OIL TEMPERATURE Continuous operation 0 to 107°C Maximum 107°C If hovering with a tailwind greater than 10 knots at OAT above 37.8°C (100°F), closely monitor engine oil temperature. The oil temperature may be reduced by either turning into wind, reducing power or transition to forward flight. NOTE Positive temperature indication is when the second segment of the trend arc is illuminated. 1-14. TRANSMISSION TEMPORARY REVISION (TR-10) — 15 FEB 2002 1-7 TC APPROVED BHT-407-FM-1 17 DEC 2002 1-7 1-13-G. ENGINE OIL TEMPERATURE NOTE Positive temperature indication is when the second segment of the trend arc is illuminated. 1-14. TRANSMISSION 1-14-A. TRANSMISSION OIL PRESSURE 1-14-B. TRANSMISSION OIL TEMPERATURE 1-15. ROTOR 1-15-A. ROTOR RPM — POWER ON NOTE When operating in MANUAL mode NR should be maintained between 95% and 100%. 1-15-B. ROTOR RPM — POWER OFF CAUTION F O R A U T O R O T A T I V E T R A I N I N G MAINTAIN STEADY STATE NR ABOVE 90%. 1-16. HYDRAULIC Hydraulic fluid MIL-H-5606 may be used at all ambient temperatures. 1-17. FUEL AND OIL 1-17-A. FUEL Fuel conforming to 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 following specifications are limited to ambient temperatures of −32°C (-25°F) and above: ASTM-D-1655, Type A or A-1 MIL-T-5624, Grade JP-5 (NATO F-44) MIL-T-83133, Grade JP-8 (NATO F-34). For operations below −32 °C (-25 °F), refer to Rolls-Royce Operation and Maintenance Manual for cold weather fuel and blending instructions. Continuous operation 0 to 107°C Maximum 107°C Minimum 30 PSI Continuous operation 40 to 70 PSI Maximum 70 PSI Continuous operation 15 to 110°C Maximum 110°C Continuous operation 99 to 100% Maximum continuous 100% Minimum 85% Continuous operation 85 to 107% Maximum 107% BHT-407-FM-1 TC APPROVED 1-8 17 DEC 2002 1-17-B. OIL 1-17-B-1. OIL − ENGINE Oil conforming to MIL-L-7808 (NATO O-148), DOD-L-85734 (Turbine oil 555) or MIL-L-23699 ( N AT O O - 1 5 6 ) i s l i m i t e d t o a m b i e n t temperatures above −40 °C (−40 °F). NOTE Refer to Rolls-Royce Operation and Maintenance Manual and BHT-407-MD- 1 manual for approved oils and mixing of oils of different brands, types, and manufacturers. 1-17-B-2. OIL − TRANSMISSION AND TAIL ROTOR GEARBOX NOTE It is recommended DOD-L-85734 oil be used in transmission and tail rotor gearbox to maximum extent allowed by temperature limitations. Oil conforming to DOD-L-85734 is limited to ambient temperatures above −40°C (−40°F). Oil conforming to MIL-L-7808 (NATO O-148) is limited to ambient temperatures below −18°C (−0°F). 1-18. ROTOR BRAKE Rotor brake (if installed) application is limited to ground operation after engine has been shut down and NR has decreased to 40% or lower. For emergency stops, apply rotor brake any time after engine is shut down. Engine starts with rotor brake engaged are prohibited. 1-19. NOT USED 1-20. INSTRUMENT MARKINGS AND PLACARDS Refer to Figure 1-3 for Placards and decals. Refer to Figure 1-5 for Instrument markings. NOTE Illustrations shown in Figure 1-5 are artist representations and may or may not depict actual approved instruments due to printing limitations. Instrument operating ranges and limits shall agree with those presented in this section. TC APPROVED BHT-407-FM-1 17 DEC 2002 1-9 Figure 1-1. Gross weight longitudinal center of gravity limits (Sheet 1 of 2) 118 119 120 121 122 123 124 125 126 127 128 129 130 FUSELAGE STATION - INCHES 2400 2600 2800 3000 3200 3400 3600 3800 4000 4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 6200 GROSS WEIGHT - POUNDS 6000 5000 4500 2800 2650 120.5 127.6 119.5 119.0 128.0 129.0 EXTERNAL LOAD ONLY LONGITUDINAL C.G. M407_FM-1__FIG_1-1_(1_OF_2).WMF BHT-407-FM-1 TC APPROVED 1-10 17 DEC 2002 Figure 1-1. Gross weight longitudinal center of gravity limits (Sheet 2 of 2) 3000 3025 3050 3075 3100 3125 3150 3175 3200 3225 3250 3275 3300 FUSELAGE STATION - MILLIMETERS 1100 1200 1300 1400 1500 1600 1700 1800 1900 2000 2100 2200 2300 2400 2500 2600 2700 2800 GROSS WEIGHT - KILOGRAMS LONGITUDINAL C.G. 2268 EXTERNAL LOAD ONLY 3241 3061 2722 3035 2041 1270 1202 3023 3251 3277 M407_FM-1__FIG_1-1_(2_OF_2).WMF TC APPROVED BHT-407-FM-1 17 DEC 2002 1-11 Figure 1-2. Gross weight lateral center of gravity limits (Sheet 1 of 2) -5 -4 -3 -2 -1 0 1 2 3 4 5 BUTTOCK LINE - INCHES 2400 2600 2800 3000 3200 3400 3600 3800 4000 4200 4400 4600 4800 5000 5200 5400 5600 5800 6000 6200 GROSS WEIGHT - POUNDS 5000 -1.5 LATERAL C.G. EXTERNAL LOAD ONLY MAX AIRSPEED 100 KIAS -0.9 1.4 2.0 -4.0 -2.5 3.0 4.0 3500 2650 3500 6000 EXTERNAL LOAD ONLY MAX AIRSPEED 100 KIAS EXTERNAL LOAD ONLY MAX AIRSPEED 100 KIAS M407_FM-1__FIG_1-2_(1_OF_2).WMF BHT-407-FM-1 TC APPROVED 1-12 17 DEC 2002 Figure 1-2. Gross weight lateral center of gravity limits (Sheet 2 of 2) -125 -100 -75 -50 -25 0 25 50 75 100 125 BUTTOCK LINE - MILLIMETERS 1100 1200 1300 1400 1500 1600 1700 1800 1900 2000 2100 2200 2300 2400 2500 2600 2700 2800 GROSS WEIGHT - KILOGRAMS LATERAL C.G. EXTERNAL LOAD ONLY MAX AIRSPEED 100 KIAS EXTERNAL LOAD ONLY MAX AIRSPEED 100 KIAS EXTERNAL LOAD ONLY MAX AIRSPEED 100 KIAS -102 -64 76 102 1588 1588 1202 -39 52 2268 -23 36 2722 M407_FM-1__FIG_1-2_(2_OF_2).WMF TC APPROVED BHT-407-FM-1 17 DEC 2002 1-13 Figure 1-3. Placards and decals (Sheet 1 of 3) Airspeed limits shown are valid only for corresponding altitudes and temperatures. Hatched areas indicate conditions which exceed approved temperature or density altitude limitations. Location: Between Pilot and Copilot seats 0 2 4 6 8 10 12 14 16 18 20 52 137 45 139 132 125 40 140 133 126 119 35 140 135 128 120 113 30 140 137 129 122 115 108 25 140 138 131 124 116 109 102 95 20 140 140 133 125 118 111 103 96 89 0 140 140 140 132 125 117 110 103 95 88 -25 140 140 140 135 130 125 119 111 104 97 89 -40 137 133 128 123 118 114 110 105 101 97 93 PRESSURE ALTITUDE FT x 1000 407 AIRSPEED LIMITATIONS - KIAS OAT °C MAXIMUM AUTOROTATION VNE 100 KIAS EMERGENCY PEDAL STOP RELEASE PULL ONLY MAINT. RESET REQUIRED Location: Forward of Overhead Console M407_FM-1__FIG_1-3_(VNE).WMF BHT-407-FM-1 TC APPROVED 1-14 Rev. 3 26 APR 2005 Figure 1-3. Placards and decals (Sheet 2 of 3) FUEL FUEL SYSTEM USABLE CAPACITY BASIC AIRCRAFT 127 U.S. GALLONS - 483 LITERS WITH 407-706-011 AUX KIT 147 U.S. GALLONS = 559 LITERS SEE FLIGHT MANUAL FOR APPROVED FUELS AVOID CONT OPS 68.4% TO 87.1% NP Location: Above fuel filler cap. THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED FLIGHT MANUAL Location: Bottom and centered on instrument panel. CARGO MUST BE SECURED IN ACCORDANCE WITH FLIGHT MANUAL INSTR Location: Inside of baggage door. 407-FM-1-3-2 DO NOT APPLY ROTOR BRAKE ABOVE 40% RPM Location: Near rotor brake (if installed). Location: Instrument panel. TC APPROVED BHT-407-FM-1 17 DEC 2002 1-15 Figure 1-3. Placards and decals (Sheet 3 of 3) FADEC SOFTWARE VERSION 5.202 WITH DIRECT REVERSION TO MANUAL INSTALLED. REFER TO FLIGHT MANUAL FOR OPERATION Location: Instrument panel. BHT-407-FM-1 TC APPROVED 1-16 17 DEC 2002 Figure 1-4. Ambient air temperature limitations -40 -30 -20 -10 0 10 20 30 40 50 60 AMBIENT AIR TEMPERATURE - °C 0 2,000 4,000 6,000 8,000 10,000 12,000 14,000 16,000 18,000 20,000 PRESSURE ALTITUDE - FT -40 -20 0 20 40 60 80 100 120 140 AMBIENT AIR TEMPERATURE - °F MINIMUM OAT FLIGHT LIMIT MAXIMUM OAT EXAMPLE: AT HP = 7000 FT MAX OAT = 37.8°C (100°F) MIN OAT = - 40°C (- 40°F) FLIGHT LIMIT MAXIMUM H D FLIGHT LIMIT M407_FM-1__FIG_1-4.EMF TC APPROVED BHT-407-FM-1 17 DEC 2002 1-17 Figure 1-5. Instrument markings (Sheet 1 of 4) ENGINE ENGINE OI OIL P L PRESSURE RESSURE 50 50 PSI PSI 50 50 to to 90 90 PS PSII 90 90 to to 11 115 P 5 PSI SI 11 115 t 5 too 130 130 PS PSII 130 130 PS PSII 200 200 PS PSII ENGINE ENGINE OI OIL T L TEMPERA EMPERATURE TURE 0 t 0 too 107 107 CC 107 107 CC Minimum Minimum Operation Operation below below 79% 79% NG NG RPM RPM Continuous Continuous operation operation below below 94% 94% NG NG RP RPMM Maximum Maximum for for continuous continuous operation operation Maximum Maximum for for cold cold st start art Continuous Continuous operation operation Maximum Maximum Continuous Continuous operation operation TRANSMISSIO TRANSMISSION O N OIL IL PRESSURE PRESSURE 30 30 PS PSII 40 40 to to 70 70 PS PSII 70 70 PS PSII TRANSMISSIO TRANSMISSION O N OIL IL TEMPERA TEMPERATURE TURE 15 15 to to 1110 10 CC 1110 10 CC Minimum Minimum Continuous Continuous operation operation Maximum Maximum Continuous Continuous operation operation Maximum Maximum NG NG (GAS (GAS PRODUCER PRODUCER RPM) RPM) 63 63 to to 105% 105% 105% 105% 106% 106% Continuous Continuous operation operation Maximum Maximum continuous continuous operation operation Maximum Maximum transient, transient, 10 10 seconds seconds M407_FM-1__FIG_1-5_(1_OF_4).EPS BHT-407-FM-1 TC APPROVED 1-18 17 DEC 2002 Figure 1-5. Instrument markings (Sheet 2 of 4) NP NP (POWER (POWER TURBINE TURBINE RPM) RPM) 99% 99% Minimu Minimum 99 99 to 100% 100% Continuous Continuous operatio operation 100% 100% Maximu Maximum c m continuous ontinuous NR NR (ROT (ROTOR OR RPM) RPM) 85% 85% 85 to 107% 107% 107% 107% Minimum Minimum (power (power off) off) Continuous Continuous operatio operation ( n (power power off) off) Maximum Maximum (power (power off) off) M407_FM-1__FIG_1-5_(2_OF_4).EPS TRQ TRQ (TORQUE) ORQUE) 0 t 0 to 93.5% 93.5% 93. 93.5 t 5 to 100% 100% 100% 100% Continuous Continuous operatio operation 5 m 5 minut inute t e takeoff akeoff range range Maximum Maximum Either Either gage gage may may be be inst installe alled MGT MGT (MEASURED (MEASURED GAS GAS TEMPERA TEMPERATURE) TURE) 100 100 to 727 727 C 727 727 to 779 779 C 779 779 C 826 826 C or or 843 843 C 927 927 C Continuous Continuous operatio operation 5 m 5 minut inute t e takeoff akeoff range range Maximum Maximum for takeoff akeoff Beginning Beginning of 10 seconds seconds range range for starting Maximum Maximum for start and and shut shutdown down (1 second second maximum) maximum) PN 407-375-001-105 AND SUB PN 407-375-001-101/-103 * * TC APPROVED BHT-407-FM-1 17 DEC 2002 1-19 Figure 1-5. Instrument markings (Sheet 3 of 4) BHT-407-FM-1 TC APPROVED 1-20 Rev. 3 26 APR 2005 Figure 1-5. Instrument markings (Sheet 4 of 4) 407FM_1_0001 DC LOAD DC LOAD FUEL PRESSURE FUEL PRESSURE * Either gauge may be installed. * P/N 407-075-024-101 * P/N 407-075-024-103, 407-375-007-105 or 407-375-007-107 170 Amps 0 to 180 Amps 180 Amps 180 Amps 170 Amps 300 Amps 400 Amps 8 PSI 8 PSI 8 to 25 PSI 8 to 25 PSI 25 PSI 25 PSI Maximum continuous above 10,000 FT Hp Continuous operation Maximum Maximum Maximum continuous above 10,000 FT Hp Maximum transient, 2 minutes Maximum transient, 5 seconds Continuous operation Continuous operation Maximum Maximum Minimum Minimum VERTICAL SPEED INDICATOR 2,000 Feet per minute up Maximum