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Cabri-G2 POH - Core Helicopters

1. 4 20 Issue 02 EASA Approved 4 i H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES INTENTIONALLY BLANK 4 ii EASA Approved Original issue H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES The information in section 4 Normal procedures is approved by EASA General This section contains instructions and procedures for operating the helicopter from the planning stage through all the mission 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 They cannot replace pilot s appreciation of each particular situation Airspeeds for safe operation Take off and climbs neue EE 50 kt IAS Best range uo eee ret itineri dente ned 80 kt IAS Autorotation also see page 3 2 50 kt IAS Never exceed speed power on 130 kt IAS 2kt IAS per 1000 feet Zp Never exceed speed Vne power 110 kt IAS 2kt IAS per 1000 feet Zp Doors Operation with one or two door s r moved lis allowed with no additional limitation in the Whole flight envelope Each 5 equipped with a restraining strap which enables partial opening f
2. 100 FLO Full Full Maximum throttle throttle rated power power power Maximum rated power Available power indication First limit mode First limit mode PWR FLO Drive system limitations Main Gearbox power limitation 4 1 1 5e 100 PWR on MLI Mai Gearbox temperature pK OO Caution tight Original issue EASA Approved 2 7 H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS Weight and balance limitations Imperial units Maximum Gross Weight 1543 Ib Longitudinal Weight and Balance diagram 3 Ib 2 1500 1400 1300 4 1200 1100 1 1000 75 77 79 81 83 85 POINT T idein 1038 Ib 83 4 in POINT 1543 Ib 79 7 in 1543 Ib 75 4 in 1213 Ib 75 4 in Lateral Balance diagram 3 1 LL 4 H E 00 o gt 3 1 75 77 79 81 83 85 in Note Rotor axis X 78 7 in 0 2 8 EASA Approved Original issue H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS Weight and balance limitations metric units Maximum Gross Weight 700 kg Longitudinal Weight and Balance diagram 3 kg 2 700 650 600 550 4 500 1 450 1900 1950 2000 2050 2100 2150 mm 471 kg 2120 hts 700 kg 2025 mm tel 700 kg 1915 mm POINT A Si dit ns sert 550 kg 1915 mm Lateral Balance diagram E 80
3. aaa 7 1 Gieneral n iati fet e tro ea ht fle tete tenens 7 1 Landing gears 7 1 EH mE 7 1 DYNAMIC SYSTEMS Lene ent datas damien ire EYE deere 7 2 Main fOlor iot ente aieo en 7 2 gro EE 7 2 Drive System uet etr ete e nr E docere 7 8 Flight controls ra reati edi c 7 4 Hotot brake 3 uso inicie e is 7 4 ENGINE INSTALLATION lr Fee tec e t e tees 7 5 Engilie e tei shoes p 7 5 EE Ea 7 5 Alt INQUCHON BE E 7 5 Igtiltion SVSIem rae etre te aed agrada Tego Ei 7 5 Cooling SVSlBlTy etie t e e SEI OE e DR XE n i 7 6 Fuel System 7 6 ELECTRICAL CIRCUIT et E toa e A es 7 7 SWIIGheS veneti tro te AR a ivan der vett edd 7 7 Breaker partiel dete ende ta e eren 7 9 Battery breakers 1 oc iii e E permis 7 10 Instrument panel and console 7 10 Emergency locating transmitter eese 7 10 ELECTRONIC PILOT MONITOR 7 11 Flight Sere eD s t ii rti re agere 7 11 Starting sequence 7 12 Flight log page ee ene een en a ee 7 12 Configuration and settings page nen 7 13 Sensors and alarms test page 000000000000 ptt 7 13 Start indicator d MD 7114 Clock Stopwatch Flight time coun
4. 6 nnne nennen nnn nennen nnn nn nnn nnn nane 2 4 DRIVESYSTEM LIMITATIONS ete rte rere ze a c teca red 2 7 WEIGHT AND BALANCE LIMITATIONS IMPERIAL UNITS eene 2 8 WEIGHT AND BALANCE LIMITATIONS METRIC UNITS eene 2 9 SENSORS FAILURES ete Peri etre LA eee tee eet e eee 2 10 PLACARDS 2 11 Original issue EASA Approved 2 i H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS INTENTIONALLY BLANK 2 ii EASA Approved Original issue H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS The information in section 2 Limitations is approved by EASA General limitations Only day VFR is approved Aerobatic flight is prohibited Voluntary in flight engine shut down is prohibited Flight in known icing conditions is prohibited Flight under snow is prohibited Minimum crew is one pilot on the right seat Left seat harness must be buckled when seat is empty Left controls removal is recommended Operation is approved with the left seat removed only if the left controls are removed Operation is approved with either or both doors removed or unlocked and partially open for ventilation In these cases no loose object is allowed in the cabin Speed limitations are the same than ones with doors installed and closed Color code for instrument markings Red MEE Indicates operating limits The pointer should no
5. Check Exhaust Pipe Sisir eme eder a edil e tiere ede eaten Check Heat muff and hose condition No cracks Mixture Control iiec tr tetto i eer eta tied Check Throttle control eno Check Air box attachment i Rn etae cede c Check Auto Carburetor heat Check cold Engine Connector sete cee eo ve eer S epa ches Locked Engine mount condition Inspect for cracks or corrosion Engine rubber Check Magneto connection Check Fuel pump and hose erbe No leak Oil cooler air hose 4 8 Check Flexible push pull control eem e Check Left tail boom att chments No crack Cotter pitis m Ed ATA IST 1 5 6 7 2 02 Installed EX 9 19 191 12 Close and lock front latch Station 3 Left tail boom side general No damage Horizontal 22 22 Shake and inspect Strobe light ROtOr dUCt ne edite i ie te ves eed Bae eee Clean Tail rotor blades condition Clean no impact Tail rotor blades Slack 1 Check all 7 Tail skid and attachment neeeennneeeeeeeeenennnessennrrrnsseennrnnnnesenee Check EASA Approved Original issue H licopteres Guimbal SE
6. Regulator Alternator Ammeter A BATTERY Horizon Directional B Plasma U Electronic Directional 5 Turn coord Cabin lights B Turn coordinator Inst panel A lights R Cabin lights Co Nav Nav lights ori amm Issue 02 Approved under DOA EASA 21J 211 9 7 H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS Breaker panel Two breakers are added to the breaker panel one in direct battery and the other on the main bus BARC Ancillaries Warning Horizon Spare Turncoord Plasma main lights Governor Directional Cabin lights Artificial horizon Turn coord Plasma Directional Gyro Cabin lights direct battery direct battery 9 8 Approved under DOA EASA 21J 211 Issue 02 H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS Air conditioning Not applicable Pop out floats Not applicable Issue 02 Approved under DOA EASA 21J 211 9 9 H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS INTENTIONALLY BLANK 9 10 Approved under DOA EASA 21J 211 Issue 02 H licopteres Guimbal CABRI G2 H licopteres Guimbal CABRI G2 INTENTIONALLY BLANK For information only
7. 4 7 BEFORE STARTING ENGINE 00sssccccceccesessecceeseccesssseceeeeeceeeaseceeeeseaaensseeeseees 4 9 STARTING THE ENGINE 5 Soe enon es tete tee iet dese Sladek edes et pee Re tees 4 11 BEFORE TAKE OFF costa ded iori re vae dera opa ace Ed dd rx Va go una 4 12 TAKE OFF 4 13 ns Ne rer LA ce 4 14 CRUISE AND OR LEVEL FLIGHT cccccccccccccccccceccceeeeeeceececeusuceeecucueeeueueeeueneneneess 4 14 FLIGHT TIME 1 1 4 14 AUTOMATIC CARBURETOR HEAT csssecceeceeeeeessecceeceeeaeeesseeeseeeeenaeeeeeeeseeeeees 4 15 APPROACH AND LANDING 1 1 4 15 ENGINE ROTOR SHUTDOWN ccccccsesseecceeeccesssseeeeeeeceeeessececeeeceeaaeeeeeeeeeneaes 4 16 DISENGAGEMENT WITH ENGINE 4 16 TAAN N G a 4 17 Power failure in hover in ground effect practice 4 18 Autorotation practice 2200 4 2210000000000 00000000 nnne nnne 4 18 Autorotation practice abortion 4 19 EPM failure practice dresse Aus erret 4 19 Engine governor failure practice
8. Noted 2 cie a ie ite ir e OFF Note 1 The CLUTCH switch is active only if the MASTER switch is left ON during a few seconds Note 2 It is possible that the CLUTCH light goes ON again after the engine has quit Disengagement with engine OFF If the engine was shut down or has stalled_while it was clutched switch CLUTCH on disengage The MASTEB switch can then be switched OFF after a few seconds Engine disengaged the complete declutching can take a few minutes 4 16 EASA Approved Issue 02 H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Training Caution The Cabri G2 has a very capable rotor giving her comparatively permissive autorotation characteristics This allows efficient training and practice from different situations and using different piloting techniques Following procedures are given as guidelines and should be followed for best safety However pilot and instructor should keep in mind that power failure training is a very demanding practice requiring a high level of awareness good health and personal condition and aircraft in perfect airworthy state Power failure practice must be limited to the strict needs of instruction and maintaining good proficiency Never practice autorotation as a show Pilot must stay familiar with procedures described in Section 3 and follow them in case of a real failure Smooth and hard surface
9. 0 C y 10 C 1 20 1 1 1 1 1 1 0 ft 5 000 ft 10 000 ft 13 000 ft Pression altitude 56 lt lt ISA 30 C Engine speed 2650 RPM Max Continuous power 5 8 EASA Approved Original issue H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE Rate of climb computation Reduced weight A 0 ft min 1 000 ft min 2000 ft min 3000 ft min Rate of climb Original issue EASA Approved 5 9 H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE Take off distance Take off distance following recommended take off profile described page 5 3 with 50 feet obstacle at corresponding HIGE maximum gross weight is 330 m 1080 feet Glide distance in autorotation In stabilized autorotation with collective fully down rotor speed stays within power off rotor speed range The following performance is then Minimum rate of descent 1770 feet min at IAS 49 kt IAS 0 8 kt IAS per 1000 feet Zp Best angle of glide 0 60 nm per 1000 feet at IAS 78 kt IAS 1 8 kt IAS per 1000 feet Zp Sound exposure level Cabri G2 flyover sound exposure level is 75 7 dB SEL Confidence interval 0 3 dB This measurement was established taking into account Vh 4 OO0 kKi IAS sound exposure level was determined under ICAO regulation Annex 16 volume 1 2 part chapter 11
10. The instrument panel presents i velle a c urcu AZ Qz HOT MASTER STROBE PUMP ALT NAV LT LDG LT COLD CARB HEAT Issue 02 Approved under DOA EASA 21J 211 7 7 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Voltage Regulator ET a relay BB Ammeter a Mena BATTERY Direct ay Starter QOO battery Radios amp starter Q Starter UNS Gov Ce Gov Off Starting CPLasMA gt Plasma CID Electronic 2 ignition 2 9 Magneto inhibition during starting 13 7 V Aux socket ocu 69 0 5 Auxiliar ies BARC backup BB Backup Normal Ami B Warn light Mute B A Nav lights Horn bi i BARC R A gt Nav lights Landing light Alim 1 3 Landing gt i lt light lights B Low Fuel Pump Cluteh Strobe Trim p Strobe light 2 us HEAT mi axl Clutching 4 way EPM logic distributor Carb BB Battery breaker Hotwire Note If cabin lights or gyroscopic instruments are installed refer to Night VFR supplement description for wiring 7 8 Approved under DOA EASA 21J 211 Issue 02 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Breaker panel The breaker panel is located on the cabin bulkhead between the two seats The breakers are marked to indicate their function They are of push pull type Caution Some systems are
11. Main mode Normal operation Green light is inactive Mute Mutes the continuous NR horn self reactivation LOW FUEL functions LOW FUEL light lights on when independent sensor is set off less than 12 L Lighting is signaled by a short tone Caution light should be preferred to EPM indication in case of doubt Other equipments Pitot Static system The Pitot tube is non heated It is located under the helicopter belly The static port is located just aft of it Engine governor An electric engine governor helps the pilot control the engine speed When engaged it acts on the twist grip to control throttle Once switched on the governor engages above 2000 RPM NR f 400 RPM and self disengages below aa M 4 pilot can disengage it by Awa ways Using Pe Gov sw itch located On the tip of the stick GOV OFF light then comes on EN Forcing the twist grip to NM lt 2000 RPM for an engine failure simulation pm At any time a friction clutch in the governor motor enables the pilot to overtake it by acting on the twist grip The pilot can easily disengage the governor while overtaking its action Original issue Approved under DOA EASA 21J 211 7 17 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Doors lock Anti theft Remote doors lock is provided by a small radio transmitter It uses a radi
12. Note 1 Depending on belt condition and temperature the rotor may slightly engage from engine start In this case engage clutch to avoid prolonged belt slippage Note 2 Maintain throttle on idle stop during clutching to preserve belt Note 3 As the rotor begins to spin a stick rotation may occur Centerthe sticksmoothly Note 4 ALT light may flicker at idle Check ALT lights goes off above 1500 RPM Issue 02 EASA Approved 4 11 H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Ignition test Set engine speed 2000 RPM upper purple radial mark Maximum drop on 300 RPM lower radial mark Maximum drop on Plasma e 100 RPM Set rotor speed between 420 RPM NR 450 RPM Carburetor heating automatic test starts after 5 seconds Check Carb heat OK is displayed If Carb h test failed is displayed apply the following procedure 1 Set Carburetor heat switch to Cool position 2 Note carburetor temperature when stabilized 3 Set carburetor heat switch to Hot position 4 Check that carb heat temperature increases If it increases switch to Auto and monitor Carb temp gage If not consider that carburetor heater is inoperative 1 Avoid prolonged flight at low power setting 2 Monitor Carb temp gage Wait for Oil temp increase as needed Governor Check rotor speed
13. Tail rotor DEUM Shrouded Number of DIAde S rav re rer cu n ern 7 DIAMETER 600 mm 23 6 in Nominal rotor speed 5148 RPM Blade chord 42 mm 1 6 in Drive system Primary transmlsslOn 2 s Aiden en tent Belt 0 855 1 reducing ratio Main rotor gearbox eee de Spiral bevel gear 11 47 reducing ratio Tail rotor gearbox Spiral bevel gear 25 11 increasing ratio Issue 02 Approved under DOA EASA 21J 211 1 3 H licopteres Guimbal SECTION 1 1 4 CABRI G2 GENERAL Powerplant Model hag Ahn Textron Lycoming O360 J2A with STC EASA E S 01001 Type uet Four cylinders horizontally opposed direct drive air cooled normally aspirated carburetor equipped one magneto and one electronic ignition system Displacement sinio recepere ees 5 9 L 361 cu in Power rating continuous 108 kW 2585 through 2700 RPM 145 shp Nomirnal speed eg eee 2650 RPM Cooling system Direct drive squirrel cage blower Ignition systems Magne tos excretion c ae ehe Bendix Electronic ignition system LSE Plasma HG Solid state capacitor discharge ignition system Variable timing advance Fuel Maximum fuel capacity 170L
14. an a E Hover in ground effect HOGE dim BEN Hover out of ground effect Weight balance B B M de Centre of gravity WTOW 2x iii es dete need pere tee Maximum take off weight Equipment tates see Electronic Pilot Monitor BARG HS Boitier Alarme Rotor et Carburant Fuel and rotor alarm device RRM GOV aah tte nettle den lie PM tu Engine governor Original issue Approved under DOA EASA 21J 211 1 5 H licopteres Guimbal SECTION 1 CABRI G2 GENERAL Miscellaneous aba epe Battery breaker AERE Height Velocity Main gearbox RPM sde aee eite Revolutions per minute EE Tail gearbox MER gites Visual flight rules Conversion factors Note The Cabri G2 EPM display can be set to either Metric or Imperial units Refer to page 7 13 Metric to Imperial units Multiply eene To obtain millimeters mm 0 0394 ri hehe inches in meters 2 2 1 312008 deese feet ft kilometers KM 0 5400 nautical miles nm kilograms kg 232046 a detentus pounds Ib liters E iiem 0 2642 gallons U S U S gal liters ss n e het 1 0567 ier quarts qt millibar mbar 0 0295 inches of
15. gt The clutch may have stayed engaged or engage unexpectedly allowing the rotor to turn at starter engagement The blades can be very dangerous particularly at low speed and with gusts or wind They are very heavy and flexible Never engage the starter while the area is not completely clear of people and foreign objects in a 6 meter 20 foot radius The blades may turn unexpectedly The pilot must not leave the cockpit as long as the engine or the rotor turns He must wait complete stop Sirictly forbid all people presence in the rotor area 6 meter 20 foot radius while the engine is running or the rotor is turning unless controlled by the pilot in command as follows To allow a person enter or exit the cabin or rotor area 6 meter 20 foot radius the pilot must Make sure the wind is less than 20 kt Hold the collective down Hold the cyclic slightly aft Maintain the RPM steady in the yellow green arc Watch the person in lateral sector and allow by a head sign Do not move the cyclic while the person has started moving towards the helicopter OVP OO NM It is the pilot s responsibility to make sure that take offsand landing 45 clear from all people that could be endanger d all people approaching the helicopter are welhvawafe of above warnings and briefed to 1 Stay clear 6 meters 20 feet of the helicopter 2 Watch thewpilotland wait his sign before mov
16. 4 9 caution light 4 11 7 8 16 09 2008 Approved under the 7 9 Breaker panel authority of DOA update 5 21 211 7 15 Low fuel indication 2 5 warning 17 09 2008 EASA R A 01530 02 9 1 GPS Approved under the authority of DOA EASA 21J 211 9 2 to Night VFR EASA R C03230 9 4 9 5 Night VFR Approved under the to a thorityrof DOA 9 10 EASA 21J 211 2740 Gage gt charge EASA R C03230 3 15 Clutch light EASA R C03230 4 2 Procedure update EASA R C03230 4 9 4 11 4 12 4 16 1 3 Drive line DOA EASA 21J 211 gearbox EASA reference number or approved under the authority of DOA EASA 21J 211 Issue 02 Approved under DOA EASA 21J 211 0 5 H licopteres Guimbal CABRI G2 INTRODUCTION Revision Page Revision object Approval Approval reference number date 02 4 3 Tight EASA R C03230 4 7 5Lockwiring 4 5 Manifold gt distributor 4 9 Note suppression 7 5 Modified Approved under the clutching system authority of DOA description EASA 21J 211 7 8 Typos battery 7 10 breaker order Auxiliaries is push pull 7 7to Note for optional 7 9 amp 2 12 7 10 Battery breaker drawing correction Add on ELT use 7 13 Note for brightness equalization 7 18 Code procedure update Note update EASA reference number or approved under the authority of DOA EASA 21J 211 0 6 Approved under DOA EASA 21J 211 O
17. Check Lower windows condition and cleanliness Check landing light iet ii en Check Pitot t be nee dee Cover removed check Static pressure Plug removed check Front gear bow Check door NINgeS iie t e a heise Check Door hinge safety Installed Issue 02 EASA Approved 4 3 H licopteres Guimbal SECTION 4 Station 2 CABRI G2 NORMAL PROCEDURES Fuel Cape T tdi Locked Navigation lights eicit ce eere rt Check Front and main gear bow condition Check Landing gear pants and skid Check 5 5 Check Fuel manifold 5 5 2 5 2 ntes taedet tees No leak Drain DRIN nes Sample Cowling hinge Check Open the left engine cowling Battery strapiisis rite tee atia Check Battery terminals Tightened m All set MAP Nes e RR RR RR Re dedere Check Transmission belt 5 ior ctt ten Check Belt slack 2 Ariel eee een Check Electronic ignition coils attachment eeereeeene Check Ignition WIFGS e ege tec e t enr e nie Eb edet Check Engine and baffling general condition Check Engine skirts condition and
18. during 2 min after startup e Value at the end of flight is stored in log p ke P FUEL litres page 31 4 Lih moy Issue 01 Approved under DOA EASA 21J 211 7 15 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS BARC BARC Fuel and rotor alarm device It is designed as an alternate mean in case of EPM failure It should be preferred in case of doubt When the MASTER is switched ON the BARC conducts a testing sequence for caution warning lights on the instrument panel and the rotor speed horn In case of an electrical bus failure the BARC can be switched to a direct battery backup supply Main and backup modes Backup mode only Continuous Power off maximum NR threshold NR 2 594 RPM Intermittent horn Green NR arc Flashing 515 RPM lt lt 540 RPM Power on maximum NR limit NR gt 540 RPM Also comes ON at non flying NR to prevent from draining Flashing the battery low Power on minimum NR red limit NR 515 RPM Continuous Power off minimum NR threshold NR s 466 RPM Continuous horn gt n 0 n For infor Rotor in flying mode signal Signal activation when NR 2 450 RPM Signal deactivation when NR lt 400 RPM 7 16 Approved under DOA EASA 21J 211 Original issue H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Switch functions Backup mode BARC is powered directly by the battery Central green light is active
19. MASTER switch is ON The turn coordinator is powered in direct battery when the PLASMA is switched ON 9 4 EASA Approved Issue 02 H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS 7 Systems description Instrument panel The instrument panel for night VFR is the wide version Gyroscopic instruments are installed on the upper part of the panel and combined with current instruments as shown Turn coordinator EPM Night Directional vision gyro filter Altimeter Airspeed indicator Artificial Horizon Optional Vertical speed indicator rt B vision filter reduces EPM brightness in direct vision and most notably after reflection in the windshield Issue 02 Approved under DOA EASA 21J 211 9 5 H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS Cabin lighting The instrument panel is lighted by four LEDs embedded the overhead control module They are powered by activation of the navigation lights NAV LT switch EPM amp keys enable to adjust panel light and EPM backlight level at the same time The ratio between the two can be set refer to maintenance manual Instrument panel lights White reading lights are embedded in the overhead module and controlled by a three position switch ozin 9 6 Approved under DOA EASA 21J 211 Issue 02 H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS Electrical system Night VFR configuration
20. where checks are done by a qualified mechanic this check may be carried out daily before the first flight of the day In this case an inter flight check should be done between each flight refer to page 4 7 Preliminaries Removeairffame covers pitot and static plugs blade tie downs and exhaust plug a In cold weather remove all frost ice or snow Purpose of the following inspection is to Visually check the helicopter general condition Detect leakage indications Detect aluminum fretting marks dark powder marks Detect steel fretting marks black or brown marks residues Detect overheating marks color changing Detect damages impacts scratches cracks frictions corrosion 4 2 EASA Approved Original issue H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Note All castellated nut must be locked by cotter pin Lockwire must be tight Torque seal marks must be intact Definition of Cabri G2 inspection stations Station 1 Main rotor blades each 3 Clean particularly at leading edge Leading edge hand check for damage or debonding Tips bolts _ RR Check lockwiring Right dooh hinges 7 RS ES Check Door hinge safety pins LL a EE Installed Windshield condition and cleanliness Check Sideslip string
21. 130 120 110 100 90 80 70 60 50 Calibrated Airspeed kt 40 30 20 10 0 0 10 20 30 40 50 60 70 80 90 100 110 120 130 Indicated Airspeed kt Notes Calibrated airspeed is equal to true airspeed at sea level in standard conditions Indicated airspeed assumes zero instrument error Difference with calibrated airspeed is caused by pressure ports installation Original issue EASA Approved 5 1 H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE Rotor starting and stopping limit Maximum demonstrated wind for rotor start up or shut down 40 Kt including gusts Caution When starting or stopping the rotor in strong wind lower fully the collective to its stop and keep the cyclic in neutral position Apply rotor brake frankly from the specified speed DO NOT release until full stop 5 2 EASA Approved Original issue H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE Height Velocity diagram Height AGL feet 400 Avoid operation in this area 300 200 Associated take off profile 50 10 EE 8 2 2 10 20 30 4050960 70 80 90 100 VAS kt 45 MY Note With a view tol simplicity the same domain was demonstrated regardless of altitude and temperature It means that some margin exist at lower altitudes temperatures and weights During take off the pilot should pay attention
22. 45 U S gal Unusable f el ER ibm 1 5L 0 4 U S gal Approved fuel grade PE 8 62 IE 100 LL Approved under DOA EASA 21J 211 Original issue H licopteres Guimbal SECTION 1 CABRI G2 GENERAL Symbols and abbreviations Symbol or abbreviation Designation Speeds CASE IN TEE ee Us Nr ce sont ess Calibrated airspeed IAS xi eie eee tem ed Indicated airspeed TASSE ae MIS dun eM ar e at True airspeed sees ailes Never exceed speed Vpn Letter ette cutis Best rate of climb speed Meteorology ISA ne MU ep Ede International standard atmosphere nu th Outside air temperature cp Hcr Outside air pressure Oise ire oe ei eire se e atone Relative air density Altitude Height AGE eos me ese Above ground level Z vegan e dg ec peg e tete Geometric altitude Lol Pressure altitude VT IEEE Density altitude Mint tue aee t edere pete erectus Geometric height Power Engine parameters A First MLI limit is Full throttle limit je dina See Maximum continuous power MEI a ete ee Multiple limit indicator ata oe a te Ee hee et Rotor speed iei etre e due e deed Engine speed ERREUR First MLI limit is Power limit Hover Take off Landing In groundhetfect OGE Ty Out of ground effect
23. 8 1 ENGINE OI p EE 8 1 GEARBOXES ere ete E E eoe e erede we pepe tte 8 1 GROUND EHANDEING 2 etre erbe e tes e Per EA 8 1 PARKING AND TIE DOWN ctbucsauctedes sa redde 8 2 JUMP STARTING THE ENGINE eene enne nnne n nnne n nnn 8 2 Original issue Approved under DOA EASA 21J 211 8 H licopt res Guimbal SECTION 8 CABRI G2 HANDLING AND SERVICING INTENTIONALLY BLANK 8 ii Approved under DOA EASA 21J 211 Original issue H licopt res Guimbal SECTION 8 CABRI G2 HANDLING AND SERVICING General This section outlines procedures recommended for handling and maintaining the Cabri G2 Every Cabri G2 owner should stay in contact with H licopt res Guimbal or approved source to obtain the latest service and maintenance information Fuel Refer to page 2 5 for approved fuel Refueling while the engine or the rotor are turning is forbidden Fuel tank may be topped off A slight increase in maximum tank capacity is possible by refueling with the left ground handling wheel installed alone Fuel gage will still function in this case with the same accuracy Engine oil Refer to page 2 5 for approved oil types and quantities Check oil level with the dipstick Gearboxes oil Refer to page 2 5 for approved oil For both main and tail gearboxes Check oil level while helicopter is sitting on a horizontal surface without ground handling w
24. E o 9 gt 80 gt 1900 1950 2000 2050 2100 2150 mm Note Rotor 2000 Y 0 Original issue EASA Approved 2 9 SECTION 2 LIMITATIONS H licopteres Guimbal CABRI G2 2 10 Sensors failures When the MASTER is switched on the EPM carries out a self test and displays a test page refer to page 7 13 Only one flight should be performed after one of following parameters are displayed Failed with following restrictions Failed parameter Flight restriction Use Section 5 to compute available performance OAT Apply margin on temperature Brasetire Limit MLI to 95 PWR and 100 FLO the smallest Ignore carb heat test Control carb heat manually Use carb heat below 80 MLI CHT Avoid long hover Carb T Ignore carb heat test Control carb heat manually Use carb heat below 80 MLI ManP Use Section 5 to compute available performance Throttle Use Section 5 to compute available performance Oil T Avoid prolonged hover Monitor CHT Oil P Monitor CLUTCH and OIL P lights Fuel Q Perform an accurate fuel planing MGB TGB corresponding plug attake off Battery charge electrical loads Keep cabin heat closed Garb heatcontrol Ignore carb heat test Control carb heat manually Use carb heat below 80 MLI EASA Appr
25. ENGINE Uc SEGTION 5 PERFORMANCE ri etie e re ERE ede ass 5 AIRSPEED CALIBRATION n ROTOR STARTING AND STOPPING LIMIT nnne 5 2 HEIGHT VELOGCITY BIAGRAM 22 5 orient hee ip eassehapevsctbuseaeschessaearbesuseatbeate HOVER OUT OF GROUND EFFECT HOVER IN GROUND EFFECT RATE OF CLIMB AT VY 50 KT IAS TAKEOFF DISTANCE nead Cte fe Seat eo eec e Da D ues GLIDE DISTANCE IN AUTOROTATION SOUND EXPOSURE LEVEL 2 SECTION 6 WEIGHT AND BALANCE GENERAL CENTER OF GRAVITY STANDARD DEFINITIONS HELICOPTER WEIGHING PROCEDURE WEIGHT AND CG POSITION nnns SECTION 7 SYSTEMS DESCRIPTION AIRFRAME ncaa at ane de asd tad ead adage tad A DYNAMIC SYSTEMS ENGINE INSTALLATION ELECTRICAL CIRCUIT eiie nnnc ELECTRONIC PILOT MONITOR EPM ENGINE OIL GEARBOXES OIL 1 2 22 GROUND HANDLING PARKING TIE DOWN E JOM STARTING THE ENGINE 22 2 ms ride ai etes e ee etae De eee odere NIGHT VFR AIR CONDITIONING POP OUT EEONTS 2 3 erri A Approved under DOA EASA 21J 211 Issue 02 H licopteres Gu
26. Stabilize autorotation Check boost pump ON fuel valve OPEN Check mixture full forward RICH Check both ignition switches ON upward Apply about 50 throttle 90 twist grip Press starter button Governor may be kept engaged or not Do not worry for engine very fast acceleration There is no risk of overtorque at re synchronization Be prepared to yawing to the left if power recovers In absence of perceivable sound the STARTER light gives a visual clue that the starter is actually energized EASA Approved 3 5 H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Engine fire Engine fire can be detected when the EPM fire warning lights up FIRE On the ground 1 2 Shut cabin heater OFF Shut fuel valve OFF When engine quits 3 4 5 Switch all switches OFF Pull rotor brake Wait for complete rotor stop before evacuating the cabin In flight Once fire is confirmed LAND IMMEDIATELY 1 2 o Shut cabin heater OFF Lower the collective to enter autorotation as per procedure page 3 3 Shut fuel valve OFF Shut fuel pump OFF Above 8000 feet AGL increase airspeed to 90 kt IAS to accelerate the descent Perform an autorotation landing according to pages 3 3 and 3 4 Pull rotor brake Wait for complete rotor stop before evacuating the cabin EASA Approved Original issue H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Elect
27. a forgiving practice respect a maximum of 5 feet height Avoid practice at maximum gross weight Autorotation practice Lower collective full down Counteract yaw motion by applying left pedal Roll off throttle through its spring ramp to its stop Maintain IAS between 30 and 50 kt IAS 50 kt IAS recommended by controlling longitudinal cyclic Slightly increase collective if required to keep rotor speed in the green arc At about 60 feet AGL apply aft cyclic to raise the helicopter nose smoothly and continuously As ground closes on apply forward cyclic to level the helicopter while raising the collective to stop sink rate e With a 50 kt IAS approach landing requires a longer distance but is easier to manage Litile action is required on the collectivercontrolrsifice the flare will stop the sink rate A30 kt IAS approach needs smaller cleared area for landing but is more difficult to manage Use pedals to minimize ground drift Once stopped lower the collective When autorotation is stabilized with collective full down the rotor speed should stay in the authorized range whatever the weight and the altitude in flight envelope Caution If airspeed drops below 30 kt IAS push frankly the cyclic forward 4 18 to recover airspeed EASA Approved Original issue H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Autorotation practice abortion If power recovery is decided during autorotation 1 R
28. governor OFF 2 Adjust power to maintain 70 to 80 kt IAS 3 Reach an appropriate surface for an autorotation running landing 4 Carry out a full autorotation landing Reduce airspeed as late as you can Land with as much airspeed as the surface permits Use small power inputs to correct yaw Yaw control failure Hovering IGE 1 LAND IMMEDIATELY 2 Lower the collective slowly enough to land smoothly while rolling off throttle to reduce yawing nose to th right Other flight cases 1 EAND AS SOON AS PRACTICABLE 2 AdjusttAS to 70 80 kt IAS 3 Adjust power to minimize sideslip and keep nose to the right 4 Reach appropriate surface for a running landing Carry out a cautious landing Reduce airspeed as late as you can Land with as much airspeed as the surface permits Use small power inputs to correct yaw Note Prefer wind from the right 3 8 EASA Approved Original issue H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Engine governor failure Engine governor failure can be detected by the following e Rotor Engine speed is not regulated in green arc and throttle extreme position is not reached Rotor Engine speed changes in level flight e If there is a doubt roll the twist grip slightly and check grip s reaction When it is detected 1 Hold the twist grip firmly and overtake the governor action 2 Switch governor OFF 3 Regulate Rotor Engine speed in the middle of green arc wi
29. grouped on the same breaker If a circuit breaker pops off wait a few seconds before resetting it Do not try twice Radios Landing Nav lights Strobe EPM Alternator Pump Starter light Trim Hourmeter Clutch ee OY CADAT ODA vo ag aye aie Landing light light Strobe light Voltage Electric trim regulator Transponder Altitude encoder EPM Fuel pump COM Radio BARC 2 supply Clutch release Intercom Hourmeter Carburetor heating Starter relay BARC Warning Spare Spare Spare Plasma main Governor lights mE BARC Intermediate starter MGB temp Plasma 1 supply relay ALT direct battery from BUS Starter logic Clutch light Very low rotor speed Oil P relay Brake Governor Gov Off Note The Plasma is the only direct battery breaker on the panel Other battery breakers are located in the battery shelter refer to next page The breaker values are given in Amperes on the breaker Note f cabin lights or gyroscopic instruments are installed refer to night VFR supplement Section 9 for breaker panel description Issue 02 Approved under DOA EASA 21J 211 7 9 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Battery breakers Four direct battery lines are protected by breakers located in the battery shelter Remote door locking Magneto disabling during cranking function 13 7 V
30. in section 3 emergency procedures is approved by EASA Introduction The following emergency procedures describe the actions the pilot must take relative to the various possible failures that can occur However depending on the many variable external environments such as the type of terrain flown over the pilot may have to adapt to the situation according to his experience To help the pilot in his decision process three recommendations are used e LAND IMMEDIATELY LAND AS SOON AS PRACTICABLE Emergency conditions are urgent and require landing at the nearest landing site at which a safe landing can be made CONTINUE FLIGHT Continue flight as planned Repair at the destination according to maintenance manual Note Immediate action that the pilot shall take or main parameters are written in bold characters Original issue EASA Approved 3 1 H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Power failures General Engine failure can be detected by Yaw acceleration nose to the right Engine noise level decreases e Tachometer needles desynchronization on the EPM engine decreases OIL P warning on the EPM and OIL P red light coming ON Plasma beeper e Rotor speed decreasing and low NR horn Caution A slow decay in engine power caused by carburetor icing or air filter clogging is compensated by the governor and can be overlooked by the pilot The MLI indication will not change while in P
31. mercury in hg bars bar 5 eni 14 5038 pounds per square inch psi Imperial to metric units Multiply eere By uices tiia To obtain R 25 40 5 als millimeters mm feet ft s nina 0 3048 manne meters m nautical miles nm 1 8520 i e kilometers km pounds lb bed 0 4536 kilograms kg gallons U S U S gal 3 7854 M 7 liters L quarts dt 959404 ER ES A liters L inches mercury in hg i L 1 3 millibar mbar pounds per square inch psi 0 olei 57 bar bar 1018 25 mbar 29 92 in hg Temperature Fahrenheit degrees Celsius degrees 9 5 C 32 F 32 5 9 1 6 Approved under DOA EASA 21J 211 Original issue H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS Section 2 Limitations 2505 6 2 1 COLOR CODE FOR INSTRUMENT 0 2 1 FLIGHT ENVELOPE 2 2 Altitude limitation uiui eee ooo ee ea e eera 2 2 Outside air temperature limitation 2 2 Airspeed litmills 2 o iei i e E TI 2 2 Rotor speed TIMMS Airi AEA 2 8 POWERPLANT
32. not ensured The pilot should therefore check its accuracy with respect to approved documentation BENDIX KING KMD 150 The GPS use is limited to day VFR in sight of the ground This label should appear on or next to the GPS Position integrity given by the GPS is not ensured The pilot should therefore check its accuracy through other navigation means available GPS user manual should be on board 7 Description Refer to GPS user manual If a 0115 installed together with the GNS 430W refer to GPS user manual for information on use Issue 02 EASA Approved 9 1 H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS Night VFR 1 General This supplement applies specifically to the Night VFR version of the Cabri G2 If only part of the required optional equipments are installed the configuration is approved for day VFR only This supplement then also provides information on these equipments In order to be approved for night VFR the Cabri G2 must feature the following equipments Instrument panel lights with backup mode in direct battery Two lights to read maps controlled through a switch the overhead control module This same switch also controls the instrument panel lighting backup mode Wide instrument panel Three gyroscopic instruments installed as per this supplement Refer to page 9 5 Artificial horizon Directional gyroscope Turn coordinator In addition the specific night vi
33. should be preferred to practice running landings In order to familiarize with Cabri G2 landing attitude practice powered running landings before autorotation training Caution Before attempting running landings check thoroughly carbide wear shoes An unexpected drift during a running landing is a clue to a carbide shoe failure Always check incase of doubt Dufing autorotation training try to Keep the helicopter skids level at touchdown to avoid unpleasant pitch d wn and bouncing 19 ground is not smooth and if the rotor speed is too low when the helicopter touches the ground a pitch oscillation can happen leading to an uncomfortable landing In that case the pilot has to keep the cyclic control in the neutral position in order to prevent induced oscillations Original issue EASA Approved 4 17 H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES PO Note 1 Note 2 Note 3 Note 4 BON Note Power failure in hover in ground effect practice Roll off throttle frankly until on its stop Counteract yaw motion by applying left pedal Increase collective as ground approaches to smooth landing Push collective down once landed If the helicopter is light it may bounce after a first touch down The Cabri G2 has no natural tendency to depart in roll or pitch after failure No systematic corrective cyclic action is needed A slight forward motion at impact is recommended for better control For
34. warns the pilot when the LOW FUEL light goes on Note The continuous horn can be temporarily muted by setting the NR switch to MUTE It reengages itself when the condition disappears Beeper warning A high frequency continuous beep warns the pilot in three situations e when oil pressure is lost with Plasma ignition ON in conjunction with OIL P red warning light e to warn that engine ignition is hot at startup e to prevent from leaving the Plasma ignition ON when leaving the helicopter MASTER OFF as well as ON EPM parameters out of limitations Note All EPM parameters are displayed in corresponding colour inverted and blink during 10 seconds when exceeding limit Parameter Exceeds Corrective actions 1 Move carb heater switch to HOT 2 Check temp gets out of yellow and CONTINUE FLIGHT gt f stays avoid prolonged flight at low power Carb T Yellow arc setting gt In case of carb icing LAND AS SOON AS PRACTICABLE Carry on a cautious landing Refer to page 3 2 for detection means 3 12 EASA Approved Original issue H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Parameter Exceeds Corrective actions e f in hover land or depart in translation e f in translation reduce power CHT Red arc gt If indication stays into red arc LAND AS SOON AS PRACTICABLE Once landed keep nominal NR for cooling e f in hover
35. 5 10 EASA Approved Original issue H licopt res Guimbal SECTION 6 CABRI G2 WEIGHT AND BALANCE Section6 Weight and balance GENERAL Ne nets M Cou ee a ete 6 1 CENTER OF GRAVITY STANDARD DEFINITIONS ss 6 3 HELICOPTER WEIGHING PROCEDURE 6 4 WEIGHT AND CG POSITION DETERMINATION Original issue Approved under DOA EASA 21J 211 6 i H licopt res Guimbal SECTION 6 CABRI G2 WEIGHT AND BALANCE INTENTIONALLY BLANK 6 ii Approved under DOA EASA 21J 211 Original issue H licopt res Guimbal SECTION 6 CABRI G2 WEIGHT AND BALANCE General The helicopter must only be flown within the weight and balance envelope specified in Section 2 Operation outside these loading limits can result in degraded safety Note The fuel is not located at the helicopter center of gravity and a change in CG location will occur during flight particularly laterally Pilot must make sure that helicopter CG location stays within specified limits until consumption of all fuel Original issue Approved under DOA EASA 21J 211 6 1 H licopt res Guimbal SECTION 6 CABRI G2 WEIGHT AND BALANCE INTENTIONALLY BLANK 6 2 Approved under DOA EASA 21J 211 Original issue H licopt res Guimbal SECTION 6 CABRI G2 WEIGHT AND BALANCE Center of gravity Standard definitions The Cabri G2 frame axis are defined as follows e Z axis is parallel to the main rotor shaft positive upward e X axis is n
36. AL PROCEDURES Engine governor failure practice Switch off governor Adjust twist grip in order to maintain engine rotor speed in the middle of green arc Note The mechanical correlation is designed so that a pattern can be flown in normal conditions from a stabilized hover with engine rotor speed in the green arc without twist grip adjustment 4 20 EASA Approved Original issue H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE Section5 Performance AIRSPEED CALIBRATION 5 1 ROTOR STARTING AND STOPPING LIMIT 5 2 HEIGHT VELOCITY 2 5 3 HOVER OUT OF GROUND 5 4 HOVER IN GROUND EFFECT 0 00cececeeeeeeeeeeeeeeeceeeeeeeeeeeeeeeeseseseeeeeeeeeeeseeeseees 5 5 RATE OF CLIMB VY 50 KT IAS 5 6 TAKE FF DISTAN E cer eu rater err rae Tana va Fac evi gage Pa pae tdi Vra DE EUR 5 10 GLIDE DISTANCE IN 5 10 SOUND 5 10 Original issue EASA Approved 5 H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE INTENTIONALLY BLANK 5 ii EASA Approved Original issue H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE The information in section 5 Performance is approved by EASA Airspeed calibration
37. Aux socket Auxiliaries Master relay Voltage regulator Voltage reference for alternator regulator BARC backup power supply BARC backup Note They are push breakers except for the Auxiliaries one refer to page 7 18 Instrument panel and console The standard flight instruments include airspeed indicator altimeter vertical speed indicator magnetic compass and the EPM Space is available for one additional conventional instrument Refer to Night VFR supplement Section 9 for wide instrument panel optional The basic avionics stack includes a VHF transceiver transponder and an intercom Space is available for additional equipment Emergency locating transmitter The ELT is located inside the baggage compartment It is attached to the main bulkhead by a strap in the lower corner ELT switch should be in ARMED position Then the 3 position switch on the breaker panel can be used for remote control e transmission enables manual activation of the ELT e ARMED stand by mode to enable automatic activation by the shock sensor Unless there is an emergency the switch must stay in that position For additional features refer to ELT operation manual 7 10 Approved under DOA EASA 21J 211 Issue 02 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Electronic Pilot Monitor EPM Flight screen MLI Engine and rotor Fuel gage Multiple limit indicator speed indicator fu
38. CABRI G2 Flight Manual Helicopter serial N Helicopter registration EASA Type certificate N R 145 Section 2 3 4 5 and 9 are approved by EASA Other sections are approved under H licopt res Guimbal DOA EASA r it THC he mat 4101 0 pilot ould not be used for any operation or instruction unless it is in current status r helicopter s operator is responsible for maintaining this manual in a current status in accordance with the list of current pages gt GUIMBAL AIX EN PROVENCE FRANCE www guimbal com INTENTIONALLY BLANK H licopteres Guimbal CABRI G2 TABLE OF CONTENT Table of content SECTION O 1 SECTION 1 GENERAL INTRODUCTION 2 22 contes THREE VIEW OF THE CABRI G2 DESCRIPTIVE DATA De Do eee eid tiene SYMBOLS AND ABBREVIATIONS th tb epe CONVERSION FACTORS 3 x ane etc Gharavi nhieu SEGTIOIN 2 EIMETATIONGS iiie price nett dunes GENERAL LIMITATIONS eene COLOR CODE FOR INSTRUMENT MARKINGS FLIGHT ENVELOPE LIMITATIONS POWERPLANT LIMITATIONS DRIVE SYSTEM LIMITATIONS ccccccscscssssesesceseseseeceeseseaes WEIGHT AND BALANCE LIMITATIONS IMPERIAL UNITS WEIGHT AND BALANCE LIMITATIONS METRIC UNITS SENSORS FAILURES sssssssinseineieehieerisererinritereennne ee PAE TAE T A E EE ant EAA AA A SE
39. CTION 3 EMERGENCY PROCEDURES 2 INTRODUCTION Aic POWER FAILURES DITCHING ente erint IN FLIGHT ENGINE RESTART ENGINE FIRE ELECTRICAL FIRE WAIL BOTOR EAIBURE NAW CONTROL FAILURE ELE ENGINE GOVERNOR FAILURE EPM AURAL WARNINGS o e o eL eco EPM PARAMETERS OUT CF LIMITATIONS 441 1 2 ese heo EPM ALARMS CAUTION WARNING LIGHIS SEGTION 4 lt NORMAL PROCEDURES LS AE iii GENERALI foal esI lead Gen AIRSPEEDS FOR SAFE OPERATION DOORS DOORS LOCK AND ANTI THEFT ccceescccecceccesessceeeceecessssueeeececcesssseeeeeeceestsaeeeees BEFORE RLIGHT DAILY OR PRE FLIGHT CHECKS INTER FLIGHT CHECK BEFORE STARTING ENGINE STARTING THE ENGINE BEFORE TAKE OFF TAKE OFF PROCEDURE 55 2 rrt cans sven nhs ra e re PM Pv auda Issue 02 Approved under DOA EASA 21J 211 C H licopteres Guimbal CABRI G2 TABLE OF CONTENT CLIMB ath s he ud e M CRUISE AND OR LEVEL FLIGHT AUTOMATIC CARBURETOR HEAT APPROACH AND LANDING ENGINE ROTOR SHUTDOWN DISENGAGEMENT WITH
40. CTION 4 CABRI G2 NORMAL PROCEDURES Station 4 Tripod attachments cioe eit e ehe eee b ue Check Tail gear box oil level eene Check Chip detector eerie Locked Pitch lever and rod Check free play Horizontal stabilizer oreet eti Check Rear transmission tube Check while turning main rotor Right tail boom side general condition No damage Transmission bearings bolts and plugs Check tight Station 5 Muffler exhaust Check shake Right cowling Check Open the right engine cowling Right tail boom attachments No crack Colter PINS eo tpe EDITAE Installed Muffler No crack or interference with engine frame cette te Locked no leak Engine oil Check 4 to 6 Qt and tighten Engine mount condition Inspect for cracks or corrosion Fuel line condition ert metere inen Check Clutch distributor and Tight no leak Oil coolet pipes 2 otc eter er herd No leak gt ere meet iiem Check Engine cooling intake lt Inspect and clean Ignition W
41. Checked ON Collective Down friction on AltimMete MEME Set All switche S tt asa ern edet or Co ceo veu Ed OFF Carburetor heating switch Auto MASTER e ein east Backup NR green Checked ON Lights and NR horn automatic check Monitored all working PR except STARTER EPM starts Watch flight log Push 2 key to enter configuration page Set configuration as desired refer to page 7 13 Push 1 key to freeze flight log page push again to carry on Watch self test If a parameter is failed the page stays until acknowledged Refer to page 2 10 for no go parameters Watch flight screen No alarm except OIL P FUEL P OIL T CARB T if OAT corresponds If engine is cold Cross check OAT CHTZGIL T CARB TT Fuel quantity V PT Jad Pl Check GovBiinor dE m ISI EV OFF check GOV OFF light ON NI UE I OR Forward full rich Note 1 Before starting NR green light GOV OFF OIL P ALT lights are on CLUTCH light may also be ON Note 2 The EPM has preflight functions described page 7 11 and following pages Issue 02 EASA Approved 4 9 H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES gt gt gt
42. GHTS Switch ON during starting procedure EPM night vision installed Caution If the night flight is started during the day the filter should be placed within pilot s reach Starting the engine Once the engine is started eui a Switch ON MAP BACKUP LIGHTS sse Switch OFF EPM instrument panel light brightness Adjust Before take off Artificial horizon 2 Cage if the ground is horizontal Otherwise it should be caged in stabilized straight level flight gts tete eive eroe eines Switch ON Caution Translation close to the ground should be carried out at very low speed in order to be able to stop as soon as an obstacle is detected Zones with lighted markers should be preferred Climb Landing light Switch OFF 200 feet above the ground Cruise and or level flight Directional gyroscope Regularly set according to compass reading in straight level flight as needed Artificial horizon Cage in stabilized straight level flight as Needed Approach and l nding Landing4ightz A6 LR Switch ON in f nal approach above 200 ft Shutdown MAP FBACKUP LIGHTS Switch OFF before leaving the helicopter Note The directional gyroscope and the artificial horizon are powered when
43. Maximum endurance speed 50 kt IAS Best range speed 5 80 kt IAS Flight time management The EPM has two features to ease flight management e A fuel flow computer giving different data described page 7 15 e flight time counter displaying the real flight time to be logged described page 7 14 The flight time display is frozen at rotor shutdown until next start up and is stored in the EPM flight log page The average fuel flew during ongoing flight is Stored lin the EPM flight log page One flight is counted from rotor start up to rotor shutdown Caution The fuel gage and fuel flow indication have a lower accuracy than their display Always perform a cautious fuel planning and take adequate reserve for the kind of operation Always trust the LOW FUEL warning light as per page 3 15 4 14 EASA Approved Original issue H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Automatic carburetor heat Automatic carburetor heat system is meant to decrease pilot workload However the pilot should always monitor icing risk and manually put carburetor heating in Hot position in case of doubt Conditions conducive to carburetor icing are high humidity fog rain or when operating near water or at low power Caution A slow decay in engine power caused by carburetor icing or air filter clogging is compensated by the go
44. TION The following table gives the pages approved under DOA EASA 21J 211 Page number Revision number Page number Revision number Cover Table of content Section 0 Introduction Section 1 General 02 Section 6 Weight and balance Section 7 Systems description Issue 02 Approved under DOA EASA 21J 211 0 3 H licopteres Guimbal CABRI G2 INTRODUCTION Page Revision Page Revision number number number number 7 15 01 7 16 7 17 7 18 02 7 19 7 20 Section 8 8 1 Handling and 8 2 servicing Section 9 9 5 02 Supplements 9 6 02 9 7 02 9 8 02 9 9 02 9 10 02 0 4 Approved under DOA EASA 21J 211 Issue 02 H licopteres Guimbal CABRI G2 The reference of this flight manual is J40 001 the following table INTRODUCTION The revisions are given in Revision Page Revision object Approval Approval reference number date Original issue 14 12 2007 TC EASA R 145 approved by EASA letter D 2007 CPRO ALE 55199 01 3 10 Carb heat manual 17 09 2008 EASA R A 01530 4 12 test transferred to section 4 4 9 Normal 4 11 procedure correction 4 15 Steep descent procedure suppressed 3 5 Addition of a 3 15 Starter engaged
45. URES cccccccsssseccecccecceesseceececeeeessseceeeceeeaesscceeeeeeeaeaseeeeeeeseeaganeees 3 2 Gelieral o s NR sid nie et arlene Bod 3 2 Power failure hover below 8 feet AGL 3 3 Power failure during take off 3 3 Other in flight power failures esses 3 3 DITOHING ES 3 4 IN FLIGHT ENGINE RESTART 3 5 ENGINE EIRE eedem ttes artem Ede tete reda ceste Deed ede evade 3 6 ELEGTRIGAL FIRE sud fte eria e ec ra a ce tua odeur xi dater ete ta due du 3 7 TAL ROTOR FAILURE CE Reg 3 8 YAW CONTROL FAILURE 3 8 ENGINE GOVERNOR FAILURE 3 9 0 3 9 AURAL WARNINGS su des Anar dad couse 3 12 EPM PARAMETERS OUT OF 3 12 EPM ALARMS vdvo cedo dede 3 14 CAUTION WARNING LIGHTS 0 2 3 15 Original issue EASA Approved 3 i H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES INTENTIONALLY BLANK 3 ii EASA Approved Original issue H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES The information
46. WR mode but will rapidly shift to FLO mode then increase to 100 Primary transmission failure can be detected by High yaw rate nose to the right Engine noise level increases Tachometer needles desynchronization on the EPM engine increases Eventual engine overspeed only if the governor is OFF e Rotor speed decreasing and low NR horn In case of a primary transmission failure apply following power failure actions Roll off the twist grip as soon as possible Warning Safe landing not be possible if the power failure occurs within the unsafe zone of the H V diagram refer to section 5 Operation inside this zone should be avoided EASA Approved Original issue H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Power failure hover below 8 feet AGL The helicopter will normally exhibit little or no tendency to depart in pitch or roll hence requiring little correction 1 Use left pedal input to counter yawing to the right 2 Cushion landing by raising collective until high pitch stop if necessary 3 Once landed lower the collective Power failure during take off Take off acceleration is the most critical situation for a power failure to occur requiring moderate and rapid pilot reaction 1 Use left pedal input to counter yawing to the right 2 Use aft cyclic to level the helicopter 3 Before having reached 30 kt IAS do not lower the collective 4 f IAS is
47. above 30 kt IAS slightly pitch up while slightly lowering the collective if needed to prevent climbing 5 When approaching the ground raise the collective to cushion contact 6 Use pedals to minimize ground drift 7 Once stopped lower the collective Other in flight power failures All cases 1 Lower the collective immediately and maintain full down 2 Use pedals to control yaw 3 Maintain IAS between 30 and 50 kt IAS 50 kt IAS recommended Select landing area and manoeuvre to land into the wind Adjust collective to centre NR green arc When the landing is nsured consider engine restarting if enough time s availables Refer to page 3 5 74 At about 60 feet AGL apply aft cyclic to raise the helicopter nose smoothly and continuously Below 50 kt IAS this manoeuvre will not stop sink rate 8 As ground closes on apply forward cyclic to level the helicopter while raising the collective to stop sink rate 9 Use pedals to minimize ground drift 10 Once stopped lower the collective D OR Note Average manoeuvre requires about 200 to 300 m 650 to 1000 feet free of high obstacle Original issue EASA Approved 3 3 H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Note During an emergency autorotation always monitor airspeed carefully Increasing airspeed above 50 kt IAS makes the landing easier but requires a longer landing area Confined landing area W
48. as noise vibration or MGB Chips Gearbox temperature light degradation LAND IMMEDIATELY Amber 9 If there is no other indication of a problem LAND AS SOON AS PRACTICABLE Engine Fire Refer to procedure page 3 6 Red LAND IMMEDIATELY Vie Carb heat is Anticipate a reduction of available power effective Refer to page 3 2 3 14 EASA Approved Original issue H licopteres Guimbal CABRI G2 SECTION 3 EMERGENCY PROCEDURES Caution Warning lights Light Signification Corrective actions STARTER Starter is energized Release starter button as needed the ground Flip MASTER switch OFF CANCEL FLIGHT STARTER If stays when starter In flight engine Flip MASTER switch OFF intained button is released running Flip NR switch gt Backup maintained Starter relay is stuck LAND AS SOON AS PRACTICABLE Failed engine restart In autorotation Terminate autorotation GOV OFF Governor is Monitor Engine Rotor RPM disengaged with twist grip CONTINUE FLIGHT BRAKE Rotor brake engaged Disengage and lock OIL P Low oil pressure LAND IMMEDIATELY 1 Move to 50 80 kt IAS translation 2 I MGB T stays on if light is MGB T jos 2 accompanied any indication of a p problem such as noise or vibration LAND AS SOON AS PRACTICABLE About 12 liters LAND AS SOON AS PRACTICABLE Avoid sideslips amp sharp manoeuvres LOW PER de If EPM reads lt 10 li
49. ck CowWlihg 12 cre eee vete Latched Front and main gear bow condition Check Landing gear pants and skid Check Skid Sh068 4 5 utro te tun e oh ed cot iei bin eee Check Open the baggage door step for main rotor examination Rotor hub uites eie ren General check Air intake and MGB compartment No foreign object Engine air intake Inspect and clean Blades leading edge No debonding Step down and slam baggage door Inside the cockpit Main controls condition ape Check Pedals ee ee Check Objects inside a ae E E EN D D Stowed Removable controls if installed 5 1 1 1 LA I ES Check 4 8 EASA Approved Original issue H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Before starting engine Harness ESen OD E Both fastened ient All objects correctly secured Full travel free Collective 5 Friction released full travel free CYCGliG Me dites etienne cu Full travel free SISTERE EDT DIDIT In TET Checked Fuel shi tsoff VAIVG ccesapeianncenesanesaaanieaeeeeads
50. el flow 87 30 alarm RPM FUEL liters location 650 2 35 FL h MLI 0 600 74 6 5 0 16 CARB T C CHT C OIL T C OIL P bar FUEL P bar BATT OAT EGT 8 765 11 14 0 00 Carburetor Cylinder head Engine oil Engine oil Fuel temperature temperature temperature pressure pressure mH N Battery Outside air Exhaust gas Clock Flight time charging rate temperature temperature Stopwatch CHRONO CO alarm Magnetic Chips and carburetor heating message box Original issue Approved under EASA 21J 211 7 11 H licopt res Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Starting sequence The EPM is powered through the MASTER switch The functioning synoptic after switching on is as follows Master switch ON lt gt Test Hot start NO Welcome page active during 3 seconds Flight log page active during 4 seconds Configuration page Language Units Hour Date Dim ratio Sensors and lines test Alarms or failures during previous flight Hot start Flight screen EPM Shut off by switching off Master Note Hot start is defined by Rotor in flying mode signal refer to page 7 16 After unexpected power cut in this condition the EPM flight screen recovers within seconds Flight log page This page presents for each of the last 15 flights date and time of the engine star
51. ftequipped weight data 2 Use 0 72 kg L for AVGAS density For precise fuel position use Fuel Quantity Y Le 1805 300 150 1 1966 330 150 10 170 Li mp 1941 341 Use 4 2 kg negative weight when a door is removed Use 5 5 kg when left seat is removed Original issue Approved under DOA EASA 21J 211 6 7 H licopt res Guimbal SECTION 6 CABRI G2 WEIGHT AND BALANCE In Imperial units Item Weight ArmX ArmY wom x Mom y Ib in in Equipped aircraft EW AX AY MX MY Right seat 51 2 12 6 Left seat 9 51 2 11 Doors o 49 2 23 6 Main baggage 73 127 compartment Front baggage 128 0 compartment Fuel 2 e o Sum MY Report aircraft equipped weight data 2 Use 6 0 Ib gal for AVGAS density For precise fuel position use Fuel Quantity gt Y 0 to 13 U S gal 714in 11 8 in 13 to 40 U S gal nasaan oaeesiennssenenene 77 4in 13in 40 to 45 U S gal 76 4in 13 4 Use 9 2 lb negative weight when a door is removed Use 12 1 1 when left seat is removed 6 8 Approved under DOA EASA 21J 211 Original issue H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Section7 Systems description AIRFRAME
52. guration page The flight time counter is counting the time spent S NR 2 450 0 and until NR lt 400 RPM It discounts the warming cooling 22 0 Its display is froze h sand et only on ne rne cu Fr is record 7 1 The stopwatch can be activated and started instantly by pressing the 1 key once It then replaces the flight time display The flight time display comes back after 20 s of stopwatch being inactive at zero or by pressing 2 key twice from stopped state ed in the flight log page refer to 7 14 Approved under DOA EASA 21J 211 Original issue y H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Fuel flow modes Three different fuel flow display modes can be selected by pressing the 3 Key cyclically Remaining flight time Instantaneous fuel flow Average fuel flow Remaining flight time e Standard mode at startup e Compute approximate flight time to starvation based on instantaneous fuel flow averaged about one minute P e Displays during 2 min after startup FUEL litres 1 37 h vol Instantaneous fuel flow e Automatically displayed when approximate fuel quantity is below 10 liters 2 6 U S gal Warning Do not rely on fuel quantity indication when caution light is ON or EPM warning is active E 0 FUEL litres 38 Lih ES me at ion v on J Calculate average flow since flight start based on flight time counter e Displays
53. he inter flight check that should be carried out in the case described page 4 2 Station 1 Main rotor blades each 3 Leading edge hand check for damage or debonding Right door hinges dl Et om EE IY Check Pitot tube RER ET Cover removed check Static pjessure port peek eect Li IR Pluglremoved check t efvdoorhihiges EX E ee COCA ESS Check Station 2 Fuel Capitaine wield hed Locked Front and main gear bow condition Check Landing gear pants and skid condition Check Skid ShO8S ei inen etri ete itte pietre mpeg Check Latched Original issue EASA Approved 4 7 H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Station 3 Left tail boom attachments Check Horizontal Shake and inspect c Clean Tall rotor blades enc No impact Tail skid and attachment Check Station 4 Tripod attachments cei nee Check Tail gear box oil level Check Chip detector its oett Locked Horizontal stabilizer Station 5 Right tail boom attachments Check Muffler exnausti dente eie Che
54. heels Add oil when level is below red circle 1 3rd diameter Ground handling Use enly approved ground handling wheels on dedicated attachment points Use the vertical tail gearbox supporttube as a handle to raise the helicopter nose and maneuver Caution Do not use the shroud structure as a handle The tail rotor blades may be damaged and could cause fingers injury Additional people can push the helicopter on the engine cowlings or main gear bow Original issue Approved under DOA EASA 21J 211 8 1 H licopt res Guimbal SECTION 8 CABRI G2 HANDLING AND SERVICING Parking and tie down Parking the helicopter on a soft surface may cause it to tilt back due to aft center of gravity when empty In case of doubt for long time parking place a hard piece of wood beneath the skid aft tips before removing the wheels Tie down should only be done by straps attaching the landing gear Avoid leaving the helicopter exposed to direct sunlight without shielding the canopy with external cover or internal survival blanket Tie the blades with appropriate straps in case of strong wind or high gusts Keep the straps loose to avoid stressing the blades Jump starting the engine Jump starting the engine is an acceptable practice in case of a low battery Only use 12V lead acid battery for jump starting Proceed in following order Connect the red cable to helicopter battery plus 2 Connect it to the external battery plus 3 Connect
55. height L2 6 4 Approved under DOA EASA 21J 211 Original issue H licopt res Guimbal SECTION 6 CABRI G2 ary WEIGHT AND BALANCE Install a piece of angle or half round on the two front scales to bear the skids on a precise point Set the scales zero Lift the helicopter nose by lowering the tail and install it on the three scales The front scales position should be forward of skid pants as shown selected to ensure a 10 to 20 kg 20 to 40 Ib load on the tail skid Remove the wheels Level the helicopter by adjusting tail skid shim Use a carpenter level on the main rotor hub or prefer a clinometer on the tail cone upper surface 2 nose up as shown Stretch a thin wire between the two contact points of helicopter skids Attach a plumb line to safety wire securing the two rear bolts clamping the main landing bow pe k Bal PILE 7 LL LR SS VE KE L1 SD Measure the horizontal distance L1 between the wire and the plumb line L1 is positive when plumb is aft Measure LL and LR as shown Measure the horizontal distance L2 between the tail fin lower leading edge and the tail skid contact point on the scale Note the three scales readings Mleft Mright and Maft Original issue Approved under DOA EASA 21J 211 6 5 H licopteres Guimbal CABRI G2 3 Calculation SECTION 6 WEIGHT AND BALANCE Report these data in following table to dete
56. hen landing spot is confined maintain IAS to 30 kt IAS in descent Landing spot can be estimated by looking between the pilot pedals Caution Anticipate that sink rate will not stop until final collective raise Failure above 2000 feet AGL It may be practicable to increase gliding distance to reach a better landing area e Best glide ratio is obtained at airspeed approximately 80 kt IAS no wind Increase airspeed with high headwind e Recommended NR is mid yellow arc 480 RPM e At about 300 feet AGL reduce IAS between 30 and 50 kt IAS 50 kt IAS recommended check NR in green arc and refer to the above procedure Airspeed and rotor speed adjustments will reduce the gliding distance Expect a PRACTICAL glide ratio between 2 1 and 3 1 or 0 7 to 1 nautical mile at 2000 feet AGL Ditching a Apply same procedures as for landing 2 Head equally between the wind and wave direction 3 Reduce forward and vertical speed to minimum possible before contact with water 4 Keep collective up after contact to help rotor deceleration EASA Approved Original issue H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES In flight engine restart Attempt engine restart only when the autorotation is stabilized on the trajectory to an appropriate landing area and sufficient time is available If successful power recovery can take only a few seconds DOV Goss Note 1 Note 2 Note 3 Issue 01
57. i eS En Engine and baffling general Check Rotor brake Check pads and clearance Flex coupling and bolts eeeeeeeeeeerererreerrnnens Tight no crack Upper pulley 5 5 13 0 nm poH ac rite etie gates Check Clutch actuator 4 Retracted Main gear box oil level fl Check Chip es Locked InspectiOmd on 77 PVC Ner nme Closed Engine skirts condition and attachment Check EMA 91 2 Check Carburetor heating Check Air intake duct and hose ssssesseesereeeriessrrrnsrirrsrrirrerrirnsrrrnsene Check Gascolator drain eo TTT Sample Fuel flow sender nni ener ese regn Check Aft landing gear Check GOWlitlg tk cette teet Lectt Me Close and lock both latches Front and main gear bow condition Check Landing gear pants and skid condition Check Skid Sho6s ir itera billed ae ees een ren Check Issue 02 EASA Approved 4 5 H licopteres Guimbal 4 6 EASA Approved SECTION 4 CABRI G2 NORMAL PROCEDURES Navigation lights uio tasted each coy hetero Check Open the baggage door step for main rotor examination Blade bo
58. imbal CABRI G2 Section 0 INTRODUCTION Introduction This document is the Pilot operating handbook and EASA approved rotorcraft flight manual of the CABRI G2 Rotorcraft The following table gives EASA approved pages Page number Revision number Page number Revision number Section 2 Limitations 2 1 2 2 2 3 2 4 2 5 01 2 6 2 7 2 8 2 9 2 10 02 2 11 2 12 02 2 13 2 14 Section 3 Emergency procedures 3 1 3 2 3 3 3 4 3 5 01 3 6 3 7 3 8 3 9 3 10 01 371 3 12 3 13 3 14 3 15 01 3 16 Issue 02 Approved under DOA EASA 21J 211 0 1 H licopteres Guimbal CABRI G2 INTRODUCTION Page number Revision number Page number Revision number Section 4 Normal procedures 4 1 4 2 02 4 3 02 4 4 4 5 02 4 6 4 7 02 4 8 02 4 10 4 11 02 4 12 02 4 13 4 14 4 15 01 4 16 02 4 17 4 18 4 19 4 20 Section 5 Performance 5 1 5 2 5 4 5 5 5 7 5 8 5 19 Section 9 Supplements 9 4 9 2 9 4 0 2 Approved under DOA EASA 21J 211 Issue 02 H licopteres Guimbal CABRI G2 INTRODUC
59. in green arc Check BARC backup green light lights ON Roll off throttle to idle Check needles desynchronization Check lower BARC light blinks when NR in yellow arc Check warning horn when NR approaches lower red limit Switch BARC to mute warning horn This will also switch to normal mode Check idle stabilization Roll in throttle check that governor engages from NR 400 RPM Before take off Oil temperature 5 4 ses ee 60 C 140F minimum for max power Doors andi ET Closed or secured with strap M M M M EM eee Both fastened Pressures and temperatures Green arcs Warning and caution lights OFF Performance calculation first limit checked MLI Landing light and NAV light As needed HadlO e As needed Collective friction issues eee Released 4 12 EASA Approved Issue 02 H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Take off procedure On clear flat area Apply collective pitch progressively to stabilize hover at 2 feet skid height Adjust cyclic trim Check engine parameters in green arcs and warning caution lights OFF Apply slight forward cyclic to accelerate at a constant height At 45 kt IAS rotate to reach and maintain 50 kt IAS Once climb i
60. ing into the rotor area 3 Bend forward and keep hands cloths and objects low 4 Move in the lateral area in pilot s sight 4 10 EASA Approved Original issue H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Starting the engine Headset auge nens ON Hadlo 2 ien aene Eni dete ON if needed Altimeter Setting 22 222 Correlated with ATC information Compass heading indication Verified ij c EE ON pump 2 eite ON check Fuel pressure increase Manual fuel injections As needed Throttle ssi eren Monitor on EPM START 0 to 15 96 Rotor brake Apply check the light lock forward Full rich forward Ignitions magneto and ON check beeper DC CE Clear Radio clearance if needed Starion A een ee ee a cfe Bs tats Activate STARTER light checked ON and back OFF when switch is released After engine starts Idle 096 START on MLI AltetnatO ON check ALT goes off Check oil pressure light OFF within 30 seconds of starting If not shutdown the engine by mixture off oiim Engage and lock switch check light is Rotor and Engine Synchronized it orit tote ets Wait for OFF
61. land or depart in translation e f in translation reduce power Redare gt if indication stays into red arc LAND AS SOON AS PRACTICABLE Once landed keep nominal NR for cooling here Wait to apply full power Allow to warm up Radars Cold starting allow engine to warm up e Flight reduce power gt 7 9 bar 115 PSI If stays into red arc Oil P LAND AS SOON AS PRACTICABLE Redarc LAND AS SOON AS PRACTICABLE 1 7bar Monitor OIL P warning light 25 PSI gt If ON LAND IMMEDIATELY Red arc 1 Check boost pump ON 0 03 bar 2 Reduce power and reach Vy 50 kt IAS Fuel P 0 5 PSI LAND AS SOON AS PRACTICABLE Redarc 1 Switch bo st pump OFF 7 0 55 bar 2 CheCcka decrease AB PSI LAND AS SOON AS PRACTICABLE Display Red lt 10L Check with LOW FUEL warning light ESEL 26 U S gt If ON LAND IMMEDIATELY gal Batter Check ALT switch ON char 2 Yellow Switch unnecessary electrical charges OFF 9 CONTINUE FLIGHT Original issue EASA Approved 3 13 H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES EPM Alarms Alarm Signification Corrective actions 1 Shut cabin heater OFF Carbon 2 Open vents co monoxide 3 Ground or hover change heading Amber cabin 4 If symptoms of CO poisoning headache pollution drowsiness dizziness accompany light LAND IMMEDIATELY If alarm is accompanied by any indication of MGB TGB a problem such
62. lts redd ede eed e ess Check Elastomeric thrust bearings Check elastomer condition Main rotor hub Check nicks or corrosion Lead lag dampers Elastomer condition 2 2 No crack 43 oil a eae dade Free without looseness All control rod ends Free without looseness Dr op stop Visual check Rotating and non rotating scissors Free with moderate looseness ceive tiie Check no free play Main gear box Upper Check Air intake and MGB compartment No foreign object Engine air intake Inspect and clean Blades leading edge No debonding Step down and slam baggage door Inside the cockpit Stroking seats Upper slide sistent Rem c ss Aligned Attachmeritz 2 date eor e ee Pe cedes Check Ha triesses top eret e ner erede Check Main controls condition Check nde neun Check Objects inside ona nete det Stowed Removable controls if installed Check Instruments ANd switches Check ou RE see In Original issue H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Inter flight check This paragraph describes t
63. m against erosion due to sand dust and precipitations Each blade is linked to the rotor hub via an elastomeric lead lag damper made of a single cylindrical layer of special rubber The blades are restrained in flapping down by a reciprocal droop stop ring guided in the rotor hub They are restrained in flapping up by an upper positive stop Tail rotor The tail rotor is shrouded in the vertical fin It has seven reinforced plastic injected blades Pitch change is permitted by their stainless steel laminated tension torsion pack The tail rotor hub is directly mounted on driven by the tail gearbox and its piteh control mechanisM is part of the gearbox The tail gearbox is rigidly supported inside the shroud by a three tube mount The frontitube houses the tail rotor driving shaft Approved under DOA EASA 21J 211 Original issue H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Drive system To the tail gearbox Freewheel Primary Thrust transmission bearing Attachment to central structure The primary transmission is composed of a pulley directly bolted to the engine output flange a poly V belt transmitting the power and an Upper pulley connected through a freewheeling unit tosthe gearbox input The powers transmitted e forward to main gear box and e aftito the tail rotor transmission main gearbox contains a splash lubricated spiral bevel gear set which transmits powe
64. n doors enable passenger pilot access One composite door enables external access to the baggage compartment Landing gear The main landing gear is composed of two tubular bows and two skids It is attached to the fuselage by soft elastomeric mounts giving adequate frequency tuning against ground resonance There is no damper The landing skids are protected against abrasion by a set of carbide wear shoes Seating The cabin features two high energy absorbing stroking seats improving occupants protection in case of a crash The left seat pan can be removed to carry large cabin baggage Original issue Approved under DOA EASA 21J 211 7 1 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS 7 2 Dynamic systems Main rotor The Cabri G2 main rotor is a three bladed fully articulated soft in plane rotor The rotor hub is forged from aluminum alloy and attached to the stainless steel mast by a large splines and cones attachment with a thrust nut The hub is belted with a tough fiberglass winding which increases its tolerance to damage The blades are made of carbon and fiberglass reinforced composite with a large internal steel tip weight and lead balance weight to increase rotor inertia Their fork attachment is directly connected to an elastomeric spherical thrust bearing which ensures pitch flap and lead lag motions They have a two section thick stainless steel leading edge cap which protects the
65. n the right side of the fuselage It can accept two standard trolley cabin suitcases It is accessible from the outside through a hinged door and from the cabin through a small access hole limited to soft objects Another baggage compartment is provided in the cabin to stow the removable passenger controls and some small cabin baggage camera drink etc It is accessible from a small door in front of the passenger pedals It features a cigarette lighter socket for auxiliary power output Soft baggage like clothes can be stowed under the stroking seats Ventilation and heating Each door has an adjustable fresh air vent For a better ventilation at lower airspeeds and particularly in a hover doors must be partially opened during flight using the cord strap A cabin heater defogger is provided It takes its air from the engine cooling blower The control knob is located between the two seats on the central console In case of fire shutting the heater off prevents fire from crossing the firewall through heating system Original issue Approved under DOA EASA 21J 211 7 19 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS INTENTIONALLY BLANK 7 20 Approved under DOA EASA 21J 211 Original issue H licopt res Guimbal SECTION 8 CABRI G2 HANDLING AND SERVICING Section 8 Handling and servicing GENERAL M oh oe tect deed Bos latte 8 1 l
66. o security code to control the cabin doors locks and enable disable the engine starter Note The starter is enabled when the Rotor in flying mode signal is active see page 7 16 whatever the antitheft state The antitheft can be disabled starter enabled if not needed Peel off the CODE label on the left side of the central console below the instrument console Locate the small 8 switch line Key the 8 bit helicopter individual security code 1 is up O is down To activate the antitheft back just scramble the switches If the transmitter is not operative following procedure permits to fly Locate the backup key lock on the right firewall above the Gascolator Open the baggage door using the backup key From the baggage door reach the right cabin door lock From the right seat open the left door lock Use above procedure to disable the anti theft Note The remote door locking circuit has very small standby current drain However when storing the helicopter for more than a month pull the Auxiliaries battery breaker inside the battery shelter Lights The helicopter is equipped with 7 18 strobe light atop verticaltin navigation lights on fuselage sid s a landing light in the nose Approved under DOA EASA 21J 211 Issue 02 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Cabin and amenities Baggage compartments A 200 liter baggage compartment is provided i
67. ollin throttle until governor engages 2 Gradually raise collective pitch to stop autorotation and descent 3 Control yaw during power recovery with pedals Note Do not worry for very fast engine acceleration There is no risk of overtorque at re synchronization Be prepared to yawing to the left when power recovers EPM failure practice In order to be efficient this practice should be carried out without engine governor A flight instructor should make the student familiar with the NR lights Select an appropriate flight phase with little workload Mask the EPM screen with a paper Disengage the governor Make the student control the rotor speed using twist grip control monitoring the Low NR and High NR caution lights The central light is inactive PONS He may also simulate a more realistic EPM failure with electric power failure 1 Select an appropriate flight phase with little workload 2 Switch ALT OFF 3 Switch MASTER OFF Caution Only direct battery systems stay powered Noticeably BARC governor and avionics are Do not Switch MASTER OFF before having switched OFF ALT switch 4 Switch the NR switch to backup to power the BARC 5 Make the student control the rotor speed using twist grip control monitoring the three NR lights The central light green is on when NR is in the green arc Original issue EASA Approved 4 19 H licopteres Guimbal SECTION 4 CABRI G2 NORM
68. or venting purpose Operation is allowed with no additional limitation with one or two doors unlatched in this way partially opened secured by the restraining strap In all these cases make sure that all harnesses are buckled and secure all loose objects Warn passenger to keep head arms and objects inside the cabin to avoid high velocity airstream Original issue EASA Approved 4 1 H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Doors lock and anti theft To unlock lock the doors press the corresponding button on the key ring radio transmitter Check the flashing strobe light confirmation If the transmitter is ineffective check the Auxiliaries breaker inside the battery box Unlocking locking the doors also enables disables the engine starter if active refer to page 7 18 Note The starter is enabled when the rotor is turning above 400 RPM whatever the antitheft state Before flight The pilot should be familiar with helicopter limitations detailed in Section 2 of this manual The pilot should have checked weight and balance Refer to Section 2 and Section 6 of this manual The pilot should check helicopter performance according to Section 2 of this manual The pilot should carry out a pre flight check before each flight Daily or Pre flight checks The following check must be carried out before each flight However if the helicopter is operated by a single pilot or in an organization
69. ormal to Z axis in the plane defined by Z axis and tail rotor transmission axis positive rearward e Y axis is deduced from the two others so that the XYZ frame is direct Positive Y are on the helicopter right side Datum is defined such that main gearbox center coordinates are X 2000 mm Y z 0 mm Z 2000 mm X 2000 mm Yz Z 2000 mm Notes The helicopter is leveled when a horizontal ground The tail rotor transmission is angled 2 downward when the helicopter is leveled Original issue Approved under DOA EASA 21J 211 6 3 H licopt res Guimbal SECTION 6 CABRI G2 WEIGHT AND BALANCE Helicopter weighing procedure 1 Aircraft preparation e Drain fuel using drain on Gascolator boost pump e Fill engine oil and gearboxes to full marks e Make sure all checked items on equipment list are installed in their proper location e Make sure copilot controls are installed or stowed inside Make sure aircraft is clean and remove any foreign item in cabin and baggage compartments such as charts tools or rags e Mark helicopter equipment list to show exactly which equipment is installed e Close the doors and cowlings Install wheels 2 Weighing e Select a horizontal ground e Install three scales at appropriate distances corresponding to the rear skid pants and the tail skid The tail scale should be on a box or a stool with shims to adjust tail skid
70. oved Original issue H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS Placards cabin ceiling VNE POWER ON Zp ft IAS kt VNE POWER OFF subtract 20 kt cabin ceiling COMPASS DATE HEADING FOR STEER 0 Original issue EASA Approved 2 11 H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS Above the fuel tank filler AVGAS 100LL 170 Litres Max 45 US Gal Under cabin heater control CLOSE IN CASE OF ENGINE FIRE In clear view of all occupants Note if the aircraft is approved for night VFR refer to Section 9 Supplements NO SMOKING thewright anddeft side of central console No hard object under seat 2 12 EASA Approved Issue 02 H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS Forward baggage compartment MAX LOAD comply with C G limit 5 kg 11 Ib AUX 13 7 V D C 5A protected Main baggage compartment comply with C G limit GPS dependingyoninstalled type Limited to VFR in sight of the ground Original issue EASA Approved 2 13 H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS INTENTIONALLY BLANK 2 14 EASA Approved Original issue H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Section3 Emergency procedures ere erra arti Ero tee 3 1 POWER FAIL
71. psi Minimum siens I 0 02 0 3 6 5 0 16 OIL P bar FUEL P bar EASA Approved Original issue H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS Fuel Approved grade ss AVGAS 100LL Maximum tank capacity 170L 45 U S gal Unusable fuel 1 5L 0 4 U S gal Warning Do not rely on fuel quantity indication when Caution light is ON or EPM warning is active Engine Oil After break in use multigrade MIL L 22851 Ashless dispersant SAE 15W50 or 20W50 During break in 50 hours use straight mineral oil MIL L 6082B OAT Grade Above 27 80f SAE 60 Above 16C 60F SAE 50 1Cto32C 30f to 90F SAE 40 18Cto21C OF to 70F SAE 30 Below 120 10 SAE 20 quantity Oll sump capacity eiat none 5 7L 6 U S Quarts Minimum oil quantity for 3 8 L 4 0 5 Quarts Gearboxes oil Use H licopt res Guimbal referenced HG30 0039 85W 140 Issue 01 EASA Approved 2 5 H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS INTENTIONALLY BLANK 2 6 EASA Approved Original issue H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS Indicated power on MLI MAXIMUM cccccccseeseeccecceeeceesseceeccceeaeesseececeeeaeeesseceeeeetaaaeeseeeeeeeeaes 100 Maximum ated cesi 100 PWR Full
72. r off 0400000000 nnne nnne nnn 610 RPM Caution range eres 540 610 RPM Normal aerem 515 540 RPM Caution range Esse 450 515 RPM Minimum 450 Rotor brake operation Dee eee 150 RPM High NR horn 2 224 4 22 1 594 RPM Low NR horn 466 RPM Original issue EASA Approved 2 3 H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS 2 4 Powerplant limitations Operating limitations Engine speed Maximum engine 888 2700 RPM Normal range a eme T 2565 2700 RPM Minimum engine speed 2585 RPM Temperature Maximum cylinder head temperature cosas 260C 500 F Maximum recommended CHT for shut 180 356 Maximum oil 118 245 f Minimum recommended oil temperature before take off 60 n 140 F Oil pressure 7 9 115 psi Helicopter minimum for take off CLUTCH light OFF L 3 6 bar 52 psi Minimum during 2 0 nn n n n n nes 1 6 bar 25 psi Fuel pressure T 0 55 bar 8
73. r to the rotor mast It is equipped with a filler plug breather a sight gage and a self closing magnetic chip detector The main gearbox upper and lower casings act as a tough central structure rigidly bolted in the middle of the fuselage structure Original issue Approved under DOA EASA 21J 211 7 3 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS 7 4 The steel tail rotor transmission shaft runs inside the tail cone on three ball bearings A disc rotor brake is installed on the fore portion of tail transmission shaft The brake jaws are actuated through a cable control from an overhead control quadrant The tail gearbox contains a splash lubricated spiral bevel gear set which transmits power to the tail rotor It also incorporates the tail rotor pitch control mechanism It is equipped with a filler plug breather a sight gage and a self closing magnetic chip detector Flight controls The Cabri G2 has dual flight controls which includes cyclic stick collective stick and pedals Left controls are totally removable without tools if needed They can be stowed in the cabin baggage compartment Cyclic and collective controls actuate main rotor blade pitch through push pull rods bellcranks and the swashplate Yaw control is transmitted from the pedals to the tail rotor by a long flexible push pull control The collective stick grip is divided into one fixed part and one twist grip to enable sensitive thro
74. revent overpower CONTINUE FLIGHT 2 Make a cautious landing in conditions requiring not more power than previous take off MLI degraded modes In case of one of following parameters loss the MLI shifts automatically to a degraded mode e Engine speed e Throttle position e e Ambient air pressure Degraded mode is signalled by the MLI indication displayed in yellow CONTINUE FLIGHT 3 10 EASA Approved Issue 01 H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Loss of engine speed sensor Detected by the indication XXX on engine EPM indicator and loss of governor frozen twist grip 1 Refer to NR indicator for engine speed indication 2 Overtake the governor by firmly gripping the twist grip 3 Once NR is in green arc switch governor OFF 4 Regulate throttle manually to keep the NR in green arc CONTINUE FLIGHT Loss of main rotor speed sensor Detected by the indication XXX on rotor EPM indicator 1 Keep powered flight no de synchronization no fast descent nor autorotation practice 2 Refer to NM indicator for engine speed indication CONTINUE FLIGHT Original issue EASA Approved 3 11 H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Aural warnings Loud horn warning A continuous tone warns the pilot when rotor speed approaches low speed limit An intermittent tone warns the pilot when rotor speed approaches high speed limit A short tone
75. rical fire Can be detected by a strong smell of burning and or by smoke 1 Switch alternator OFF 2 Switch MASTER OFF Note EPM and NR lights are no longer powered 3 Move NR switch to Backup position 4 Use NR lights Backup position to monitor rotor speed Note Remaining electrical equipments are those on direct battery BARC backup and ignition system Refer to page 7 7 for electrical system description If fire source is determined switch the other systems ON If electric fire continues LAND IMMEDIATELY If not LAND AS SOON AS PRACTICABLE Notes e With MASTER and alternator both OFF engine still operates with both ignitions With MASTER OFF and NR switch on Backup following lights are still operative gt High Normal and Low NR gt LOW FUEL caution Original issue EASA Approved 3 7 H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES Tail rotor failure It could consist either in a tail rotor transmission failure or in a tail rotor loss This failure can be detected by sudden yaw acceleration nose to the left and or totally ineffective pedals Caution Nose to the right probable engine failure Nose to the left probable tail rotor failure Hovering IGE 1 LAND IMMEDIATELY 2 Reduce throttle in order to reduce left yaw rate 3 Cushion contact with the ground by applying collective pitch up to high stop if necessary Other flight cases 1 Switch
76. riginal issue H licopteres Guimbal SECTION 1 CABRI G2 GENERAL Section 1 General INTRODUCTION haa pr 1 1 THREE VIEW OF THE 02 1 2 1 3 o olde pm 1 3 Nm IR LN LA CORAM 1 3 Drive syslai od eau dedito ae 1 3 PFowWerplant i dee 1 4 lee s es 1 4 SYMBOLS AND ABBREVIATIONS esse 1 5 CONVERSION FACTORS i E Mr nee rene 1 6 Metric to Imperial units ete eter t Henne tn 1 6 Imperial to metric units 1 6 Original issue Approved under DOA EASA 21J 211 1 i H licopteres Guimbal SECTION 1 CABRI G2 GENERAL INTENTIONALLY BLANK 1 ii Approved under DOA EASA 21J 211 Original issue H licopteres Guimbal SECTION 1 CABRI G2 GENERAL Introduction This Flight Manual is designed as an operating guide for the pilot It includes material required to be furnished to the pilot by EASA CS 27 and Part 21 It also contains supplementary data supplied by the helicopter manufacturer This manual is intended to give the pilot the best possible information and to help him find the best answer to most operational situation However it cannot replace pilot s appreciation of each particular situation Pilot mu
77. rmine the helicopter empty weight and moments In millimeters Weight Arm X Arm Y Mom X Mom Y Mleft 2212 11 LL Mright 2212 11 LR Maft 5913 L2 90 AX AY Sum EW MX EW MY EW Sum MX Sum MY In inches Weight Arm X Arm Y Mom X Mom Y Mleft 87 L1 LL Mright 87 L1 LR Maft 233 12 4 AY Sum EW MY EW Sum MX Sum MY 6 6 Approved under DOA EASA 21J 211 Original issue H licopt res Guimbal SECTION 6 CABRI G2 WEIGHT AND BALANCE Weight and CG position determination Before each flight the pilot should determine helicopter gross weight and CG position in order to check that helicopter CG limits shown page 2 6 are not exceeded and to determine performance Refer to Section 5 This can be done with the following table 1 Determine all the weights in the first column 2 Compute longitudinal and lateral moments 3 Sum each three columns 4 Calculate total arms by dividing moments by total weight In metric units Weight ArmX Arm Y Mom X Mom Y Equipped aircraft EW AX AY MX MY Right seat 1300 2 Left seat 9 1300 280 Doors 9 1250 600 Main baggage 1854 323 compartment Front baggage 325 0 compartment Fuel 2 2 9 Sum MY Report aircra
78. s stabilized adjust power as needed Rate of climb should not exceed 500 ft min below 100 feet in order to ease piloting in case of an engine failure 7 Follow take off profile shown on Height Velocity diagram shown page 5 3 D OR om Note 1 Take off is possible without increasing power in case of a very slow acceleration on hard surface Note 2 Take off run may be shortened by raising slightly the collective to compensate for height loss if power margin enables it On other surface confined area or surrounded by obstacles Refer to HOGE performance page 5 4 Adapt accelefation proced re to environment by keeping rotor disk above horizen afid avoiding as far as possible Height Velocity limiting area refer to page5 3 Original issue EASA Approved 4 13 H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Climb Prescribed climb speed is 50 kt IAS Adjust power to obtain desired rate of climb Maximum allowed power is indicated by 100 on MLI If full throttle is reached 100 FLOW on the MLI the rotor speed may decrease In this case slightly lower the collective to recover rotor speed Cruise and or Level flight All parameters eee om end Green arcs Warning and caution lights OFF Fuel remainirig rico rei er oe nate eri eL Linee eine e Redes Check Economy cruise is obtained with 9096 on MLI Fast cruise is obtained with 100 on MLI
79. sion filter should be positioned on EPM screen to prevent disturbing reflections in the windshield Note Additional equipment may be required by approved operational regulation 2 Limitations Category of operation This helicopter i is approved for ham y y VER The correspqgding placard should bein clear view of the occupants d Placard for overhead cabin lights switch BACKUP MAP LIGHTS ON OFF 9 2 EASA Approved Issue 02 H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS 3 Emergency procedures In case of an electrical failure causing the loss of instrument panel lighting the pilot should activate the BACKUP MAP LIGHTS switch In case of an Artificial horizon failure OFF flag the pilot should refer to the turn coordinator which is powered in direct battery through the PLASMA ignition switch Each gyroscopic instruments is equipped with a red flag which appears when the instrument is inoperative In this case the pilot should no longer trust the indications of the corresponding instrument Caution In case of an alternator failure ALT light on or charge indicator in the yellow zone the pilot should limit the remaining flight time to 30 minutes Issue 02 EASA Approved 9 3 H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS 4 Normal procedures Day VFR procedures still apply The following actions should be added for night VFR flight Before starting engine MAP BACKUP LI
80. st maintain adequate ground and flight instruction and good proficiency in the type of helicopter To achieve the required level of safety the helicopter pilot in command must be familiar with this manual s content with other safety related available information and with all the regulation covering aircraft operation that are relevant in the country of operation He is responsible for determining that the helicopter is safe for flight and for operating it in respect to this manual and above information The helicopters owner is responsible for maintaining the aircraft in approved airworthy condition and for maintaining this manual in a current status in accordance with the list of current pages Original issue Approved under DOA EASA 21J 211 1 1 H licopteres Guimbal SECTION 1 CABRI G2 GENERAL Three view of the CABRI G2 0 83 32 7in 2 5 8 2 2 37 m 7 78f 6 34 m 20 78 8 05 m 26 4ft rotor turning 4 079 1 6 5 25 ft 1 2 Approved under DOA EASA 21J 211 Original issue H licopteres Guimbal SECTION 1 CABRI G2 GENERAL Descriptive data Main rotor Type HIS cee ee nts cat abate Articulated soft in plane Nurmber of Dlades 5 5 2 i iae 3 Diameter directe nene tiec eee eere ds 7 20 m 23 6 feet Nominal rotor speed 530 Blade chord idu reb pe eet 180 mm 7 1 in
81. t ISA 30C Engine speed 2650 RPM Max Continuous Power A wind speed of 35 kt at all headings was demonstrated at sea level A wind speed of 25 kt at all headings was demonstrated at maximum reduced weight M omax 835 kg refer to following pages for reduced weight computation Original issue EASA Approved 5 5 H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE Rate of climb at Vy 50 kt IAS To determine the maximum rate of climb first determine the reduced weight as follows 1 Locate A on the left curves from outside temperature and pressure altitude 2 Report A on the right curves and read the reduced weight from weight Note The example is given for M 700 kg OAT 206 and Zp 4000 ft Pressure altitude Of 200 400 800 7 7 10 000 owe 13 0007 20 106 0c 10 20 30 40 Outside air temperature 56 lt Text lt ISA 30T 5 6 EASA Approved Original issue H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE Reduced weight computation 400 kg 600 kg 800 kg 1000 kg 1200 kg Reduced weight Original issue EASA Approved 5 7 H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE Determine maximum rate of climb as follows 1 Locate A on the left curves from pressure altitude and outside air temperature 2 Report A on the right curves and find climb rate from reduced weight 45 C Outside air temperature 30 C 20 C SSS ss a ae a A 10
82. t enter red zones or exceed red limits during normal operation Red cross Indicates power off hatch Yellowof or special operating procedure amber range Green pu Normal operating range White or Other indications Blue On the EPM related numerical values are marked with the same color code Original issue EASA Approved 2 1 H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS Flight envelope limitations Altitude limitation Maximum operating altitude Zp 13 000 ft Outside air temperature limitation Maximum temperature ISA 30C limited to 45C Minimum operating temperature 5 Minimum storage temperature 30 Airspeed limits VINE mire 130 kt IAS 2 kt IAS per 1000 feet Zp VNE 110 kt IAS 2 kt IAS per 1000 feet Zp Caution range 0 45 kt IAS 2 2 EASA Approved Original issue H licopteres Guimbal SECTION 2 CABRI G2 LIMITATIONS Rotor speed limits Power on 200000000000 222 2 002 540 CIC T BU tu 1 n 515 to 540 RPM 7 515 RPM Powe
83. t up e The flight time refer to page 7 14 e average fuel consumption refer to page 7 15 7 12 Approved under DOA EASA 21J 211 Original issue H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Configuration and settings page English gt gt 55 gt gt gt gt z g 2 Previous Brightness equalization Note Brightness equalization is used with the instrument panel lighting It is set during maintenance Sensors and alarms test page Sensor OAT Pressure T induction Flowmeter Carb heat test CPU heat Alarms Throttle Fire Oil T MGB chips Oil P TGB chips Fuel Q co Fuel P Power supply Fire MGB chips TGB chips Battery Memory battery CONTINUE Cooling fan Carb heat control The amber caution icons indicate failures that were detected during the last flight The amber FAILED indicates a line sensor failure during the self test Issue 02 Approved under DOA EASA 21J 211 7 13 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Start indicator In START mode MLI indicates the throttle position to assist the pilot to start the engine Mode activation when NR gt 420 RPM Mode deactivation when NR s 300 RPM Clock Stopwatch Flight time counter 4 05 n vol AB 4 6 0 05 P HUILE bar P FUEL bar 19 17 0 01 The clock is a continuous display 12 or 24 hour format can be selected through confi
84. ter 124 470 PLAN E 7 14 Fuel flow modes RE 1220 A PA E21 0l 3 7 15 BARG 7 Y 78 9 RM eee 7 16 An roO pj B WM RB LN 7 17 7 17 Engine QOVGINOM 7 17 Dootsock Ahtl theft 3 7 18 Lights unxit d tri di Mt tudo tors 7 18 CABIN AND entr annee tran anne 7 19 Baggage compartments 7 19 Ventilation and heating sse 7 19 Original issue Approved under DOA EASA 21J 211 T i H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS INTENTIONALLY BLANK T ii Approved under DOA EASA 21J 211 Original issue H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Airframe General The Cabri G2 airframe is composed of three sections e The main fuselage including cabin central structure baggage and fuel compartments It is all made of composite sandwich e The engine section isolated between a front and an aft firewalls It is made of the steel truss engine mount and composite cowlings e aft structure a composite shell combining the tail boom the fins and the tail rotor shroud with the horizontal stabilizer Two composite cabi
85. ters 2 6 U S gal LAND IMMEDIATELY Alternator regulator Check ALT switch ON ALT or battery charging Switch QFF unnecessary electrical __ malfunction charges CONTINUE FLIGHT Belt tensiohing clutching duce power until light is Bure NT E continuous Reduce IAS to 50 kt IAS clutch pressure LAND AS SOON AS PRACTICABLE too low Be prepared to enter autorotation NR High Raise the collective or Reduce throttle NR Low Increase power or Lower the collective Note Blinking light corresponds to Yellow arc on EPM Continuous light warns when approaching Red limit tachometer Issue 02 EASA Approved 3 15 H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES INTENTIONALLY BLANK 3 16 EASA Approved Original issue H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Section 4 Normal procedures GENERAL 5 E 4 1 AIRSPEEDS FOR SAFE 7 4 1 Bee 4 1 DOORS LOCK AND 2 nennen 4 2 itera cu tie e erae rsen ae ex de Lo Ee cai re ruv eco Pu rende Doa dendo 4 2 DAILY OR PRE FLIGHT CHECKS 0 00 0 4 2 INTER FLIGHT 11 nennen
86. th twist grip 4 LAND AS SOON AS PRACTICABLE Caution Always overtake the governor and stabilize NR in green arc before any other action is taken EPM failures Complete loss of EPM display 1 LAND AS SOON AS PRACTICABLE 2 Switch NR switch to Back up position check green light 3 Rotor Engine speed is controlled by the governor and can be checked using high and low NR warning lights 4 Monitor carburetor heat manually Select cold position at high power Select hot position at low power 5 In this case if LOW FUEL lights LAND IMMEDIATELY Erratic engine rotor speed de synchronization Reduce power gradually If d e Synchronization indication continues 1 Ref rto NR lights indicator for reliable rotor speed 2 Switch the engine governor OFF 3 Monitor the rotor speed in the lower green arc 4 LAND AS SOON AS PRACTICABLE If de synchronization stops 1 Consider the EPM is operative and the transmission is questionable 2 Limit power to avoid any de synchronization reading 3 LAND AS SOON AS PRACTICABLE 4 Conduct a cautious landing with minimum power and gradual power increase Refer to procedure page 3 2 Original issue EASA Approved 3 9 H licopt res Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES MLI failure Detected by the indication XXX on MLI 1 Above 5500 feet Zp you will always be limited by full throttle Below 5500 feet Zp do not exceed 80 kt IAS in level flight to p
87. the black cable to helicopter battery ground 4 Connect it to the external battery ground 5 6 Start the engine with left cowling open Remove in opposite order Caution a dead battery is not airworthy and should not be jump started 8 2 Approved under DOA EASA 21J 211 Original issue H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS Section9 Supplements List of supplements and optionals Incompatibility of operation Effect on performance data GPS a oceans Steet etait NIGHTAVE Bine etse tent A AIR CONDITIONING Eo POP OUT FLOATS Important note The information contained herein supplements or supersedes the information given in the basic flight manual and or flight manual supplements listed above Issue 02 Approved under DOA EASA 21J 211 9 H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS INTENTIONALLY BLANK 9 ii Approved under DOA EASA 21J 211 Issue 02 H licopt res Guimbal SECTION 9 CABRI G2 SUPPLEMENTS GPS 1 General This supplement details data specific for approved GPS The following GPS are approved on Cabri G2 GARMIN GNS 430W for night and day VFR BENDIX KING KMD 150 for day VFR 2 Limitations GARMIN GNS 430W The GPS use is limited to VFR in sight of the ground This label should appear on or next to the GPS GPS database information correctness is
88. to avoid this zone In addition he should limit the rate of climb to a maximum of 500 feet min below 100 feet AGL in order to limit the loss of rotor speed in case of power failure see procedure page 3 3 Original issue EASA Approved 5 3 H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE Hover Out of Ground Effect Zp I 12 000ft Standard atmosphere I 10 0008 I 4 x k t k I 8000 2 max 14 200 ft I I I 1 6000ft I I I I I I I 4000ft I I I I I I 2000ft i I I t t t I A i I I 0 ft 1 1 470kg 500 kg 550 kg 600 Kg 650 kg 700 kg 8m MH b JL J 1 UEM GE M 9 0 110045 1200 Ib 130016 140015 1500 Ib Gross weight OGE hover performance 50 lt lt ISA 30C No wind Engine speed 2650 RPM Max Continuous Power 5 4 EASA Approved Original issue H licopt res Guimbal SECTION 5 CABRI G2 PERFORMANCE Hover In Ground Effect Zp 12 O00ft Standard atmosphere 10 000ft 1 I 1 I 8000ft 6000ft 4000ft 2000ft 0 ft 470 kg 500 kg 550 kg 600 kg 650 kg 700 kg 1100 Ib 1200 lb 1300 16 1400 Ib 1500 Ib IGE hover performance Gross weight Skid height 2 feet No wind lt l
89. ttle control and to allow governor motion The collective stick is equipped with a friction mechanism which is controlled by the pilot without releasing his hands from the controls The cyclic sticks have no friction mechanism but a dual axis electric trim allowing to completely release the static forces in flight This trim system is controlled either by the pilot or the copilot through a circuit which gives priority to the one who activates itifirst Rotor brake A brake allows the pilot to stop quickly the rotor after flight This rotor brake Is mounted on the tail rotor transmission It is actuated by a cable connected to a pull handle located above the pilot yellow handle Approved under DOA EASA 21J 211 Original issue H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Engine installation Engine The engine is a four cylinder direct drive carbureted gasoline engine It is installed in the central compartment suspended through elastomeric vibration mounts It moves slightly to control the main transmission belt tension for clutch engagement disengagement Clutch The clutch tension actuator is fed by engine oil pressure through a four way distributor controlled by the CLUTCH switch This system is frozen in case the electrical power is shutdown A non return valve maintains the pressure in case of engine stoppage or oil pressure loss A gas spring maintains the engine disengaged d
90. uring prolonged stop The CLUTCH light lights OFF when the pressure of the oil feeding the distributor is above 3 6 bar In the clutched position it means that the belt is tensioned In the declutched position it means that the clutch cylinder is on its declutched stop Air induction The engine air intake is located inside the main gearbox compartment on the right side It is fed in fresh air by the front inlet above the cabin A wire screen prevents foreign object ingestion The air is ducted down the firewall to an air filter box behind the carburetor This air box includes an electrically actuated butterfly valve which controls the carburetor heating and their filter Both cold and hot air are filtered air intake temperature probe located inside the air filter sends the carburetor inlet temperature to the EPM Ignition system The engine has a dual plug mixed ignition system comprising One magneto with constant timing e One solid state electronic capacitor discharge system with variable timing The electronic system is direct fed by the battery through a dedicated circuit breaker located on the cabin breaker panel Issue 02 Approved under DOA EASA 21J 211 7 5 H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Cooling system The engine is air cooled with an additional oil cooler Cooling air enters the upper cowling plenum around the mast and gearbox It is forced by a squirrel cage blo
91. vernor and can be overlooked by the pilot The MLI indication will not change while in PWR mode but will rapidly shift to FLO mode then increase to 100 Approach and landing Approach with 50 kt IAS 500 ft min Land on clear area The targets eei ne 50 kt IAS 50 ft AGL 500 ft min Flare gently with cyclic to reduce rate of descent and forward speed Gently raise the collective to stop in ground effect hovering at 2 feet skid height Issue 01 EASA Approved 4 15 H licopteres Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Engine Rotor shutdown Collectives Down friction on Ico nn OFF Engine cooling 420 lt Nr lt 450 RPM until CHT lt 180C bp tiit Stable GLUTGE Switch disengage check light is Wait for de synchronization needles split or for CLUTCH light to go OFF I Pull OFF to shut down Ignition SWItChes i eter ceret terere ei et e OFF Landing light and NAV OFF Alternator einer deii creer edge re ere etes ea OFF Fuel p mip 2 titt idees Peto certe RE ER ies OFF Rotor On request under 150 RPM white mark PROTO e PER is ce Re E eae Stopped D Ace 81270 pem Cleared and OFF Hourmeter and EPM flight time
92. wer directly driven by the engine Warm air is exhausted below the engine Fuel system The fuel system comprises asingle crash resistant fuel tank an submersed electric booster pump the engine driven pump a shut down valve a gascolator Vent Filler cap FUEL TANK Engine pump Cutoff valve electrical Drain Gascolator Flow sender Drain 7 6 Approved under DOA EASA 21J 211 Original issue H licopteres Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS Electrical circuit The electrical systems are powered by a 12 V 25 ampere hour battery located in the left engine compartment and a 13 7 V 60 A alternator controlled by a voltage regulator A main breaker panel is provided in the cabin and a secondary breaker panel is located inside the battery shelter Various switches are located on the instrument panel The MASTER switch disconnects all the systems from the battery except NR lights BARC backup PLASMA ignition system Doors remote control the 13 7 V Auxiliary power socket Some supplemental equipments see Section 9 Starting protections On ground before clutching the system prevents from cranking the engine if e Itis already running e The anti theft system is activated During flight the anti theft system is disabled to permit engine restart in any situation Clutching feature Clutching is disabled when the rotor brake is applied or seized Switches

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