Guimbal Cabri G2 Flight Manual Download | Manualshive

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Hélicoptères Guimbal

SECTION 7

CABRI G2

SYSTEMS DESCRIPTIONS

Original issue

Approved under DOA EASA.21J.211

7-3

Transmission

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 to the gearbox input.
The power is transmitted :

•

forward to main gearbox, and

•

aft to the tail rotor transmission.

The main gearbox contains a splash-lubricated spiral bevel-gear set
which transmits power 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.

Thrust
bearing

To the tail

gearbox

Engine

Attachment
to central
structure

Freewheel

Primary
transmission

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Summary of Contents for Cabri G2

Page 1: ...re approved under Hélicoptères Guimbal DOA EASA 21J 211 This flight manual includes the material required to be furnished to the pilot by EASA CS 27 and Part 21 This manual should not be used for any operation or instruction unless it is in current status The helicopter s operator is responsible for maintaining this manual in a current status in accordance with the list of current pages AIX EN PRO...

Page 2: ...B Approved under DOA EASA 21J 211 Original issue INTENTIONALLY BLANK ...

Page 3: ... AND BALANCE LIMITATIONS METRIC UNITS 2 11 SENSORS FAILURES 2 12 PLACARDS 2 13 SECTION 3 EMERGENCY PROCEDURES 3 I INTRODUCTION 3 1 POWER FAILURES 3 2 DITCHING 3 4 IN FLIGHT ENGINE RESTART 3 5 ENGINE FIRE 3 6 ELECTRICAL FIRE 3 7 TAIL ROTOR FAILURE 3 8 YAW CONTROL FAILURE 3 8 ENGINE GOVERNOR FAILURE 3 9 EPM FAILURES 3 9 AURAL WARNINGS 3 12 EPM PARAMETERS OUT OF LIMITATIONS 3 12 EPM ALARMS 3 14 CAUTI...

Page 4: ...T VY 50 KT IAS 5 6 TAKE OFF DISTANCE 5 10 GLIDE DISTANCE IN AUTOROTATION 5 10 SOUND EXPOSURE LEVEL 5 10 SECTION 6 WEIGHT AND BALANCE 6 I GENERAL 6 1 CENTER OF GRAVITY STANDARD DEFINITIONS 6 3 WEIGHT AND CG POSITION DETERMINATION 6 4 SECTION 7 SYSTEMS DESCRIPTION 7 I AIRFRAME 7 1 DYNAMIC SYSTEMS 7 2 ENGINE INSTALLATION 7 5 ELECTRICAL CIRCUIT 7 6 ELECTRONIC PILOT MONITOR EPM 7 11 BARC 7 17 OTHER EQU...

Page 5: ...r to Section 9 B pages are FAA only pages that cancel and replace original pages with the same page number Ex page 2 1 B replaces 2 1 for FAA approval only The following table gives EASA approved pages Page number Issue number Page number Issue number Section 2 Limitations 2 1 B 08 2 i 10 2 2 10 2 ii 2 3 10 2 4 10 2 15 10 2 5 10 2 16 10 2 6 B 10 1 2 7 B 10 1 2 8 10 2 9 10 2 10 10 2 11 10 2 12 10 2...

Page 6: ...ber Page number Issue number Section 4 Normal procedures 4 1 10 4 i 10 1 4 2 09 4 ii 4 3 09 4 4 09 4 5 07 4 6 09 4 7 09 4 8 09 4 9 08 4 10 09 3 4 11 08 4 12 05 4 13 4 14 10 4 15 09 4 16 08 4 17 08 4 18 4 19 09 2 4 20 05 Section 5 Performance 5 1 5 i 5 2 5 ii 5 3 5 4 10 5 5 10 5 6 09 3 5 7 5 8 05 5 9 5 10 Issue 10 1 ...

Page 7: ...8 D B 10 1 Section 0 Introduction 0 1 B 10 1 0 7 09 0 2 B 10 1 0 8 09 0 3 B 10 1 0 9 09 0 4 10 0 10 09 1 0 5 09 0 11 09 3 0 6 09 0 12 10 1 Section 1 General 1 1 1 i 09 1 2 1 ii 1 3 03 1 4 10 1 8 07 1 5 1 6 07 1 7 09 Section 6 Weight and balance 6 1 03 6 i 08 6 2 6 ii 6 3 6 4 10 6 5 10 6 6 08 Section 7 Systems description 7 1 09 7 i 03 7 2 09 3 7 ii 7 3 03 7 4 07 7 5 02 7 6 10 7 7 09 3 7 8 07 7 9 0...

Page 8: ...der DOA EASA 21J 211 Original issue Page number Issue number Page number Issue number Section 7 Continued Systems description 7 15 09 3 7 16 10 7 17 03 7 18 03 7 19 07 7 20 03 Section 8 Handling and servicing 8 1 09 3 8 i 10 8 2 10 8 ii 8 3 10 8 4 10 Issue 10 ...

Page 9: ...cent procedure suppressed 3 5 3 15 4 9 4 11 Addition of a STARTER caution light 7 8 16 09 2008 Approved under the authority of DOA EASA 21J 211 7 9 Breaker panel update 7 15 Low fuel indication warning 2 5 17 09 2008 EASA R A 01530 02 9 1 GPS 19 05 2009 Approved under DOA EASA 21J 211 according to FSA 09 003 9 2 to 9 4 Night VFR 19 05 2009 EASA R C 03230 9 5 to 9 10 Night VFR 19 05 2009 Approved u...

Page 10: ... distributor 4 9 Note suppression 7 5 Modified clutching system description 19 05 2009 Approved under the authority of DOA EASA 21J 211 according to FSA 09 003 7 8 7 10 Typos battery breaker order Auxiliaries is push pull 7 7to 7 9 2 12 Note for optionals 7 10 Battery breaker drawing correction Add on ELT use 7 12 Explanation of EPM restart in welcome page 7 13 Note for brightness equalization 7 1...

Page 11: ...rb heat 3 13 3 14 Oil P yellow zone Carb heat suppr 4 12 Carb Heat proc 4 15 4 19 Proc correction 9 1 Limitation update 6 1 1 3 1 i 7 i 7 3 C D Wording 07 06 2010 Approved under DOA EASA 21J 211 according to FSA 10 003 7 11 7 13 Screenshot update 7 16 7 20 Carb heat pages shift 7 18 Ref to night lights 04 D 0 1 to 0 4 Section 9 Supplements are managed independently 05 11 2010 Approved under DOA EA...

Page 12: ...n 7 10 Direct battery breaker correction 8 i 8 1 à 4 Doors removal 06 2 1 Authorisation for flight under snow 18 01 2013 EASA AFM approval 10043301 0 1 0 3 0 8 07 0 1 to 0 4 0 8 0 10 Page revisions 12 03 2013 Approved under DOA EASA 21J 211 0 2 0 6 Page 4 7 not modified at issue 02 1 4 Approved fuel 1 6 to 1 8 New abbreviations and page shift 2 5 2 6 Limitations for additional fuels 05 03 2013 Maj...

Page 13: ...nder DOA EASA 21J 211 6 7 6 8 Fuel density 7 4 Rotor brake description wording transmission driveshaft 7 8 Interm Avionics relay 7 12 7 19 Rotor in Flying mode is page 7 17 not 7 16 7 13 Sensor page description 7 14 Error in Start indicator description 8 2 Tie down 08 C Pages change December 4th 2014 EASA AFM Approval 10051479 0 1 0 2 0 3 0 9 0 10 Page revisions 1 4 FAA engine STC 2 i 2 2 Page lay...

Page 14: ...ic 7 9 Radio conf 7 11 EPM indications 08 FAA only B pages D B 0 1 B 0 2 B 0 3 B Table of content Introduction December 4th 2014 EASA AFM Approval 10051479 2 1 B Limitations 2 5 B 2 6 B 4 i B 4 2 B 4 15 B Allowed fuel 09 Section 0 0 1 B 0 2 B 0 3 B Revision Issue and pages updates March 30th 2015 EASA AFM Approval 10052795 2 5 Precision on fuel management 2 13 2 14 4 6 4 8 7 1 Left cabin luggage b...

Page 15: ...removal installation 09 2 FAA only pages 0 1 B 3 15 B Correction of FAA only B pages October 29th 2015 09 3 0 1 0 2 to 0 4 0 11 0 12 Revision tables January 3rd 2017 EASA AFM Approval 10060625 3 1 3 7 to 3 9 3 12 3 13 3 14 3 15 3 16 Land as soon as practicable becomes Land as soon as possible to harmonize with industry standard 2 5 7 15 Warning becomes Caution 2 4 Min oil press bar value rounded 2...

Page 16: ...8 2 9 5 min power Limitations 2 12 2 13 4 1 4 14 Update for new PWR limit 3 8 Tail rotor failure proc precision to roll off throttle 5 4 5 5 Addition of perf curves up to ISA 30 C 6 4 6 5 Weights update 7 6 Sketch update 7 11 Change in EPM display degraded mode display 7 12 Addition of return to Flight log page 7 16 Precision on manual carb heat operation note 4 8 i 8 2 to 8 4 Flight controls remo...

Page 17: ... 211 1 i Section 1 General INTRODUCTION 1 1 THREE VIEW OF THE CABRI G2 1 2 DESCRIPTIVE DATA 1 3 Main rotor 1 3 Tail rotor 1 3 Transmission 1 3 Powerplant 1 4 Fuel 1 4 SYMBOLS AND ABBREVIATIONS 1 5 CONVERSION FACTORS 1 7 Metric to Imperial US units 1 7 Imperial US to metric units 1 7 Issue 09 ...

Page 18: ...Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1 ii Approved under DOA EASA 21J 211 Original issue INTENTIONALLY BLANK ...

Page 19: ...ch particular situation Pilot must 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 i...

Page 20: ...Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1 2 Approved under DOA EASA 21J 211 Original issue Three view of the CABRI G2 ...

Page 21: ...er 7 20 m 23 6 feet Nominal rotor speed 530 RPM Blade chord 180 mm 7 1 in Tail rotor Type Shrouded Number of blades 7 Diameter 600 mm 23 6 in Nominal rotor speed 5148 RPM Blade chord 42 mm 1 6 in Transmission Primary transmission Belt 0 855 1 reducing ratio Main rotor gearbox Spiral bevel gear 11 47 reducing ratio Tail rotor gearbox Spiral bevel gear 25 11 increasing ratio Issue 03 ...

Page 22: ...700 rpm 160 hp Nominal speed 2650 RPM Cooling system Direct drive squirrel cage blower Ignition systems Magneto Bendix Electronic ignition system LSE Plasma II HG Solid state capacitor discharge ignition system Variable timing advance Fuel Maximum fuel capacity 170 L 45 U S gal Unusable fuel 1 5 L 0 4 U S gal Approved types AVGAS 100 LL Unrestricted AVGAS UL 91 Unrestricted See Oil additive for br...

Page 23: ...Above ground level Z Geometric altitude Zp Pressure altitude Z Relative density altitude h Geometric height Power Engine parameters FLO First MLI limit is Full throttle limit MCP Maximum continuous power MLI Multiple limit indicator NR Rotor speed NM Engine speed PWR First MLI limit is Power limit Hover Take off Landing IGE In ground effect OGE Out of ground effect HIGE Hover in ground effect HOGE...

Page 24: ...l issue Fuel AKI RON MON 2 Anti Knock Index MON Motor Octane Number RON Research Octane Number RVP Reid Vapor Pressure Miscellaneous BB Battery breaker CPU Central processing unit H V Height Velocity MGB Main gearbox RPM Revolutions per minute TGB Tail gearbox VFR Visual flight rules Issue 07 ...

Page 25: ...nds lb liters L 0 2642 gallons U S U S gal liters L 1 0567 quarts qt millibar mbar 0 0295 inches of mercury in hg bars bar 14 5038 pounds per square inch psi Imperial US to metric units Multiply By To obtain inches in 25 40 millimeters mm feet ft 0 3048 meters m nautical miles nm 1 8520 kilometers km pounds lb 0 4536 kilograms kg gallons U S U S gal 3 7854 liters L quarts qt 0 9464 liters L inches...

Page 26: ...Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1 8 Approved under DOA EASA 21J 211 Original issue INTENTIONALLY BLANK Issue 07 ...

Page 27: ...ENT MARKINGS 2 2 FLIGHT ENVELOPE LIMITATIONS 2 3 Altitude limitation 2 3 Outside air temperature limitation 2 3 Airspeed limits 2 4 Rotor speed limits 2 4 POWERPLANT LIMITATIONS 2 5 TRANSMISSION LIMITATIONS 2 9 WEIGHT AND BALANCE LIMITATIONS IMPERIAL UNITS 2 10 WEIGHT AND BALANCE LIMITATIONS METRIC UNITS 2 11 SENSORS FAILURES 2 12 PLACARDS 2 13 Issue 10 ...

Page 28: ...Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2 ii EASA Approved Original issue INTENTIONALLY BLANK ...

Page 29: ...cing conditions is prohibited Flight in falling snow is prohibited if heated Pitot is not installed MOD14 075 or corresponding SB Minimum crew is one pilot on the right seat Left seat harness must be buckled when seat is empty In this case 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...

Page 30: ...ng limits The pointer should not enter red zones or exceed red limits during normal operation Red cross hatch Indicates power off VNE Yellow or amber Precautionary or special operating procedure range Green Normal operating range White or Blue Other indications On the EPM related numerical values are marked with the same color code Issue 10 ...

Page 31: ...ue EASA Approved 2 3 Flight envelope limitations Altitude limitation Maximum operating altitude Zp 13 000 ft Outside air temperature limitation Maximum temperature ISA 30 C limited to 45 C Minimum operating temperature 20 C Minimum storage temperature 30 C Issue 10 ...

Page 32: ...IAS 2 kt IAS per 1000 feet Zp Caution range 0 45 kt IAS Rotor speed limits Power on Maximum 540 RPM Green arc 515 to 540 RPM Minimum 515 RPM Power off Maximum 610 RPM Caution range 540 610 RPM Normal range 515 540 RPM Caution range 450 515 RPM Minimum 450 RPM Minimum transient 410 RPM Rotor brake operation Maximum 150 RPM High NR horn 594 RPM Low NR horn 466 RPM Issue 10 ...

Page 33: ... cylinder head temperature CHT 260 C 500 F Maximum recommended CHT for shut down 180 C 356 F Maximum oil temperature 118 C 245 F Minimum recommended oil temperature before applying full power 60 C 140 F Oil pressure Maximum 7 9 bar 115 psi Maximum for flight 6 6 bar 95 psi Minimum for take off CLUTCH light OFF 3 8 bar 55 psi Minimum during idle 1 7 bar 25 psi Fuel pressure Maximum 0 55 bar 8 psi M...

Page 34: ...2 6 B EASA Approved Issue 10 1 Fuel Maximum tank capacity 170 L 45 U S gal Unusable fuel quantity 1 5 L 0 4 U S gal Caution Do not rely on fuel quantity indication when LOW FUEL light is ON or EPM warning is active Approved grades AVGAS 100LL AVGAS UL91 ...

Page 35: ... Above 16 C 60 F SAE 50 1 C to 32 C 30 F to 90 F SAE 40 18 C to 21 C 0 F to 70 F SAE 30 18 C to 32 C 0 F to 90 F SAE 20W50 Below 12 C 10 F SAE 20 Note 1 Refer to latest Lycoming service Instruction 1014 for lubricating oil recommendations Note 2 Add Lycoming additive LW16 702 or equivalent to oil when using unleaded fuel during break in Oil quantity Oil sump capacity 5 7 L 6 U S Quarts Minimum oil...

Page 36: ...o After 5 minutes in the yellow arc it becomes red showing maximum duration has elapsed o Limitations to use the yellow arc Limited to 5 minutes and a maximum airspeed of 30 kt IAS AVGAS only Using alternate grades refer to 2 6 Fuel forbids the use of the yellow arc Throttle FLO limit it corresponds to full throttle power FLO limit corresponds to the maximum power that the engine can deliver The r...

Page 37: ...Continuous yellow arc threshold Main Gearbox temperature Caution light Issue 10 PWR limit mode FLO limit mode Red radial mark Maximum rated power 5 minutes Max 30 kt IAS AVGAS Power indication Limitations Red radial mark with arc Full throttle power Yellow arc threshold Maximum rated power Continuous After 1 min in the yellow arc the 5 min countdown indicator appears After 5 min ...

Page 38: ...43 lb Point 1 1036 lb 83 5 in Point 2 1102 lb 83 5 in Point 3 1543 lb 79 7 in Point 4 1543 lb 75 4 in Point 5 1213 lb 75 4 in Note Rotor axis is X 78 7 in Y 0 in Lateral Balance diagram 75 77 79 81 83 85 Xcg in Ycg in 3 1 0 0 3 1 Longitudinal Weight and Balance diagram 1 3 4 5 1000 1100 1200 1300 1400 1500 75 77 79 81 83 85 Fore Aft in lb 78 7 2 Issue 10 ...

Page 39: ...kg Point 1 470 kg 2120 mm Point 2 500 kg 2120 mm Point 3 700 kg 2025 mm Point 4 700 kg 1915 mm Point 5 550 kg 1915 mm Note Rotor axis is X 2000 mm Y 0 mm Lateral Balance diagram 80 0 80 1900 1950 2000 2050 2100 2150 Xcg mm Ycg mm Issue 10 mm Longitudinal Weight and Balance diagram 5 4 3 1 450 500 550 600 650 700 1900 1950 2000 2050 2100 2150 Fore Aft kg 2 ...

Page 40: ...ature Pressure Limit MLI to 85 in PWR mode 95 for 5 minutes or 100 in FLO mode T induction Carb heat test control through NR drop CHT Avoid long hover Carb T 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 Fu...

Page 41: ...Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2 13 Placards On cabin ceiling Issue 10 ...

Page 42: ...l tank filler cap s Under cabin heater control In clear view of all occupants Note if the aircraft is approved for night VFR refer to Section 9 Supplements On the right and left side of central console CLOSE IN CASE OF ENGINE FIRE The following placard can still be used if unleaded fuels are not used ...

Page 43: ...ply with C G limit MAX LOAD comply with C G limit 1 kg 2 lb 40 kg 88 lb Forward luggage compartment Forward luggage compartment under pilot seat Main luggage compartment When left seat luggage brackets are installed AUX 12V D C 5A protected 13 7 V D C Issue 10 Install cap on cyclic root Max weight 80 kg 175 lb ...

Page 44: ...Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2 16 EASA Approved Original issue Starting S N 1045 with MOD 12 010 next to rear bow fitting Tie down only Issue 10 ...

Page 45: ...r failure hover below 8 feet AGL 3 3 Power failure during take off 3 3 Other in flight power failures 3 3 DITCHING 3 4 IN FLIGHT ENGINE RESTART 3 5 ENGINE FIRE 3 6 ELECTRICAL FIRE 3 7 TAIL ROTOR FAILURE 3 8 YAW CONTROL FAILURE 3 8 ENGINE GOVERNOR FAILURE 3 9 EPM FAILURES 3 9 AURAL WARNINGS 3 12 EPM PARAMETERS OUT OF LIMITATIONS 3 12 EPM ALARMS 3 14 CAUTION WARNING LIGHTS 3 15 ...

Page 46: ...Hélicoptères Guimbal SECTION 3 CABRI G2 EMERGENCY PROCEDURES 3 ii EASA Approved Original issue INTENTIONALLY BLANK ...

Page 47: ...SSIBLE 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 In addition to procedures Warnings Cautions and Notes can highlight specific p...

Page 48: ...nd 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 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 Rotor speed decreasing and lo...

Page 49: ...lective 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 4 Select landing area and man...

Page 50: ...iding distance to reach a better landing area Best glide ratio is obtained at airspeed approximately 80 kt IAS no wind Increase airspeed with high headwind Recommended NR is mid yellow arc 480 RPM 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 distanc...

Page 51: ...Stabilize autorotation 2 Check boost pump ON fuel valve OPEN 3 Check mixture full forward RICH 4 Check both ignition switches ON upward 5 Apply about 50 throttle 90 twist grip 6 Press starter button Note 1 Governor may be kept engaged or not Note 2 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...

Page 52: ...otor brake 5 Wait for complete rotor stop before evacuating the cabin In flight Once fire is confirmed LAND IMMEDIATELY 1 Shut cabin heater OFF 2 Lower the collective to enter autorotation as per procedure page 3 3 3 Shut fuel valve OFF 4 Shut fuel pump OFF 5 Above 8000 feet AGL increase airspeed to 90 kt IAS to accelerate the descent 6 Perform an autorotation landing according to pages 3 3 and 3 ...

Page 53: ...nitor rotor speed Note Remaining electrical equipment 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 POSSIBLE Notes With MASTER and alternator both OFF engine still operates with both ignitions but without the g...

Page 54: ...nor OFF 2 Adjust power to maintain 70 to 80 kt IAS 3 Reach an appropriate surface for an autorotation running landing 4 Enter autorotation roll off throttle to its stop and carry out a full autorotation landing Reduce airspeed as late as you can Land with as much airspeed as the surface permits Yaw control failure Hovering IGE 1 LAND IMMEDIATELY 2 Lower the collective slowly enough to land smoothl...

Page 55: ...loss of EPM display 1 LAND AS SOON AS POSSIBLE 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 Control 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 synch...

Page 56: ...case of one of following parameters loss the MLI shifts automatically to a degraded mode Engine speed Throttle position OAT Ambiant air pressure Degraded mode is signaled by the MLI indication displayed in yellow CONTINUE FLIGHT EPM CPU overtemperature failure When overtemperature is detected the EPM displays this warning then shuts down 30 seconds later Refer to Complete loss of EPM display proce...

Page 57: ...ping 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 rotor speed indication CONTINUE FLIGHT Loss of automatic carb...

Page 58: ...il pressure is lost with Plasma ignition ON in conjunction with OIL P red warning light to warn that engine ignition is HOT at startup 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 color inverted and blink during 10 seconds when exceeding limit Parameter Ex...

Page 59: ...Allow to warm up Oil P Red arc 7 9 bar 115 PSI Cold starting allow engine to warm up Flight reduce power If stays into red arc LAND AS SOON AS POSSIBLE Yellow arc 6 6 7 9 bar 95 115 psi Normal at cold starting and during engine warm up Flight reduce power If stays into yellow arc LAND AS SOON AS POSSIBLE Yellow arc 1 7 3 6 bar 25 52 psi Normal at idle Flight CLUTCH light should light soon after Re...

Page 60: ...ndication of a problem such as noise vibration or MGB temperature light LAND IMMEDIATELY If there is no other indication of a problem LAND AS SOON AS POSSIBLE Fire Red Engine compartment fire Refer to procedure page 3 6 LAND IMMEDIATELY Parameter Exceeds Corrective actions LOW FUEL Display in Red 10 L 2 6 U S gal Check with LOW FUEL warning light If ON LAND IMMEDIATELY BATT Battery charge Yellow C...

Page 61: ...ors are desynchronized from engine Apply collective to resynchronize If blinking stops CONTINUE FLIGHT and keep rotor synchronized with engine if blinking does not stop see below If rotors are synchronized with engine Disengage the governor Control Engine Rotor RPM with twist grip CONTINUE FLIGHT BRAKE Amber Rotor brake engaged Disengage and lock OIL P Red Low oil pressure LAND IMMEDIATELY MGB T A...

Page 62: ...LAND AS SOON AS POSSIBLE Caution Prolonged flight without alternator can result in loss of electronic and electrical equipment CLUTCH Amber Belt tensioning clutching detensioning declutching Refer to normal procedure clutch pressure too low or Belt worn out Reduce power until light is off If continuous Reduce IAS to 50 kt IAS LAND AS SOON AS POSSIBLE Be prepared to enter autorotation NR High Amber...

Page 63: ...FLIGHT CHECK 4 7 BEFORE STARTING ENGINE 4 9 STARTING THE ENGINE 4 11 BEFORE TAKE OFF 4 12 TAKE OFF PROCEDURE 4 13 CLIMB 4 14 CRUISE AND OR LEVEL FLIGHT 4 14 FLIGHT TIME MANAGEMENT 4 14 APPROACH AND LANDING 4 16 ENGINE ROTOR SHUTDOWN 4 16 DISENGAGEMENT WITH ENGINE OFF 4 16 TRAINING 4 17 Power failure in hover in ground effect practice 4 18 Autorotation practice 4 18 Aborting autorotation practice 4...

Page 64: ...Hélicoptères Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES 4 ii EASA Approved Original issue INTENTIONALLY BLANK ...

Page 65: ...efinitions page 3 1 Airspeeds for safe operation Use of yellow arc power 5 minutes AVGAS only Max 30 kt IAS Take off and climbs 50 kt IAS Best range 80 kt IAS Autorotation also see page 3 2 50 kt IAS Never exceed speed VNE power on 130 kt IAS 2kt IAS per 1000 feet Zp Never exceed speed VNE power off 110 kt IAS 2kt IAS per 1000 feet Zp Doors Operation with one or two door s removed is allowed with ...

Page 66: ...k helicopter performance according to Section 5 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 where checks are done by a qualified mechanic this check may be carried out daily before the first flight of...

Page 67: ...t leading edge Leading edge hand check for damage or debonding Tips bolts Check lockwiring Right door hinges Check Door hinge safety pins early models only Installed Windshield condition and cleanliness Check Sideslip string indicator Check Lower windows condition and cleanliness Check Landing light Check Pitot tube Cover removed check Static pressure port Plug removed check Front gear bow attachm...

Page 68: ...k Engine and baffling general condition Check Engine skirts condition and attachment Check Exhaust pipes Check Heat muff and hose condition No cracks Mixture control Check Throttle control Check Air box attachment Check Auto carburetor heat Check cold Engine connector Locked Engine mount condition Inspect for cracks or corrosion Engine rubber mounts Check Magneto connection Check Fuel pump and hos...

Page 69: ...nd tighten Engine mount condition Inspect for cracks or corrosion Fuel line condition Check Clutch distributor and attachment Tight no leak Oil cooler pipes No leak VHF antenna Check Engine cooling intake screen Inspect and clean Winter air flow restrictor check if installed Ignition wires Check Engine and baffling general condition Check Rotor brake Check pads and clearance Flex coupling and bolt...

Page 70: ...n check All control rod ends Free without looseness Droop stop ring Visual check Rotating and non rotating scissors Free with moderate looseness Swashplate Check no free play Main gearbox upper fitting Check Air intake and MGB compartment No foreign object Engine air intake screen Inspect and clean Blades leading edge No debonding Step down and slam luggage door Inside the cockpit Stroking seats U...

Page 71: ...Main rotor blades each 3 Leading edge hand check for damage or debonding Right door hinges Check Pitot tube Cover removed check Static pressure port Plug removed check Left door hinges Check Station 2 Fuel cap Closed secured and key locked if equipped Front and main gear bow condition Check Landing gear pants and skid condition Check Skid shoes Check Left bear paw if installed Check locked Cowling...

Page 72: ...tachments Check Muffler exhaust Check Cowling Latched Front and main gear bow condition Check Landing gear pants and skid condition Check Skid shoes Check Left bear paw if installed Check locked Open the luggage door step for main rotor examination Rotor hub General check Air intake and MGB compartment No foreign object Engine air intake screen Inspect and clean Blades leading edge No debonding St...

Page 73: ...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 12 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 CHT OIL T CARB T Fuel quantity Check Governor OFF check GOV OFF li...

Page 74: ...r 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 1 Make sure the wind is less than 20 kt 2 Hold the collective down 3 Hold the cyclic slightly aft 4 Maintain the RPM steady in the yellow green arc 5 Watch the person in lateral sector and allow by a head sign Do not move the cyclic while t...

Page 75: ... Engine indicators Synchronized CLUTCH light Wait for OFF Note 1 Manual fuel injections raise the collective lever to approx one third of its stroke so that mechanical correlation allows large throttle strokes Then roll the twist grip back and forth 2 3 times This actuates the carburetor mechanical acceleration pump and injects fuel in the inlet manifold Note 2 Cold weather starting After a failed...

Page 76: ...ncreases CARB HEAT AUTO 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 Governor ON Roll in throttle check governor engages from NR 400 RPM Check rotor speed in green arc Before take off Oi...

Page 77: ...uld 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 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...

Page 78: ...MLI Maximum endurance speed is 50 kt IAS Best range speed is 80 kt IAS Flight time management The EPM has two features to ease flight management A fuel flow computer giving different data described page 7 15 A 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 l...

Page 79: ...Hélicoptères Guimbal SECTION 4 CABRI G2 NORMAL PROCEDURES Issue 08 EASA Approved 4 15 B INTENTIONALLY BLANK ...

Page 80: ... Idle Stable CLUTCH Switch to disengage Wait 10 seconds check light is ON Mixture Pull OFF to shut down Ignition switches OFF Landing light and NAV light OFF Alternator OFF Fuel pump OFF Rotor brake On request under 150 RPM white mark Rotor Stopped Strobe OFF Radio Cleared and OFF Hourmeter and EPM flight time Noted MASTER OFF Note The CLUTCH switch is active only if the MASTER switch is left ON d...

Page 81: ...es described in Section 3 to follow them in case of an actual failure Autorotation must only be practiced over an area that would minimize hazards associated with an actual engine failure Smooth and hard surface 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 attemp...

Page 82: ...tle through its spring ramp to its stop 4 Maintain IAS between 30 and 50 kt IAS 50 kt IAS recommended by controlling longitudinal cyclic 5 Slightly increase collective if required to keep rotor speed in the green arc 6 At about 60 feet AGL apply aft cyclic to raise the helicopter nose smoothly and continuously 7 As ground closes on apply forward cyclic to level the helicopter while raising the col...

Page 83: ...ot 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 A flight instructor should make the student familiar with the NR lights 1 Select an appropriate flight phase with little workload 2 Mask the EPM screen with a paper or the night vision filter 3 Switch NR to Backup 4 Control the flight in ...

Page 84: ...tice To simulate an engine governor failure in flight proceed as follows 1 Switch off governor 2 Adjust twist grip in order to maintain engine rotor speed in the middle of green arc 3 Carry out a standard landing Note The mechanical correlation is designed to minimize pilot workload in case of manual regulation Issue 05 ...

Page 85: ...ection 5 Performance AIRSPEED CALIBRATION 5 1 ROTOR STARTING AND STOPPING LIMIT 5 2 HEIGHT VELOCITY DIAGRAM 5 3 HOVER OUT OF GROUND EFFECT 5 4 HOVER IN GROUND EFFECT 5 5 RATE OF CLIMB AT VY 50 KT IAS 5 6 TAKE OFF DISTANCE 5 10 GLIDE DISTANCE IN AUTOROTATION 5 10 SOUND EXPOSURE LEVEL 5 10 ...

Page 86: ...Hélicoptères Guimbal SECTION 5 CABRI G2 PERFORMANCE 5 ii EASA Approved Original issue INTENTIONALLY BLANK ...

Page 87: ... 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 Airspeed indicator calibration 0 10 20 30 40 50 60 70 80 90 100 110 120 130 0 10 20 30 40 50 60 70 80 90 100 110 120 130 Indicated Airspeed kt Calibrated Airspeed kt ...

Page 88: ...ping 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 ...

Page 89: ...st at lower altitudes temperatures and weights During take off the pilot should pay attention 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 2 500 200 100 300 400 Vy 45 100 10 20 30 50 40 60 70 80 90 50 10 8 IAS kt Height AGL feet Avoid operati...

Page 90: ...t Issue 10 OGE hover performance 20 C OAT ISA 30 C No wind Engine speed 2650 RPM Max Continuous Power 0 ft 2000ft 10 000ft 4000ft 6000ft 12 000ft 8000ft Z max 14 200 ft Standard atmosphere Zp 470 kg 500 kg 650 kg 1100 lb 1400 lb 700 kg 1500 lb Gross weight 550 kg 600 kg 1300 lb 1200 lb Standard atmosphere 30 C ...

Page 91: ...ated at maximum reduced weight M max 835 kg refer to following pages for reduced weight computation Standard atmosphere 30 C Issue 10 IGE hover performance Skid height 2 feet No wind 20 C OAT ISA 30 C Engine speed 2650 RPM Max Continuous Power Gross weight 0 ft 2000ft 10 000ft 4000ft 6000ft 12 000ft 8000ft Zp 1300 lb 470 kg 500 kg 550 kg 600 kg 650 kg 1100 lb 1200 lb 1500 lb 1400 lb 700 kg Standar...

Page 92: ...t 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 20 C and Zp 4000 ft Issue 09 3 Outside air temperature 20 C OAT ISA 30 C A 10 C 10 C 0 C 20 C 30 C 40 C 20 C Pressure altitude ...

Page 93: ...Hélicoptères Guimbal SECTION 5 CABRI G2 PERFORMANCE Original issue EASA Approved 5 7 Reduced weight computation 400 kg 1200 kg 600 kg 800 kg 1000 kg A Reduced weight Weight ...

Page 94: ...imb 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 20 C OAT ISA 30 C Engine speed 2650 RPM Max Continuous power Issue 05 10 000 ft 5 000 ft A Pression altitude Outside air temperature 0 ft 13 000 ft ...

Page 95: ...Hélicoptères Guimbal SECTION 5 CABRI G2 PERFORMANCE Original issue EASA Approved 5 9 Rate of climb computation 0 ft min 3000 ft min 1 000 ft min 2000 ft min A Reduced weight Rate of climb ...

Page 96: ...e 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 3 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 establis...

Page 97: ...SECTION 6 CABRI G2 WEIGHT AND BALANCE Original issue Approved under DOA EASA 21J 211 6 i Section 6 Weight and balance GENERAL 6 1 CENTER OF GRAVITY STANDARD DEFINITIONS 6 3 WEIGHT AND CG POSITION DETERMINATION 6 4 Issue 08 ...

Page 98: ...Hélicoptères Guimbal SECTION 6 CABRI G2 WEIGHT AND BALANCE 6 ii Approved under DOA EASA 21J 211 Original issue INTENTIONALLY BLANK ...

Page 99: ...e weight and balance envelope specified in Section 2 Operation outside these loading limits can result in degraded safety Note Due to fuel position the CG location will vary during the flight especially laterally During flight preparation the pilot should ensure that the helicopter CG location stays within specified limits until consumption of all fuel Issue 03 ...

Page 100: ...Hélicoptères Guimbal SECTION 6 CABRI G2 WEIGHT AND BALANCE 6 2 Approved under DOA EASA 21J 211 Original issue INTENTIONALLY BLANK ...

Page 101: ...the plane defined by Z axis and tail rotor transmission axis positive rearward 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 0 mm Z 2000 mm Notes The helicopter is not leveled when on a horizontal ground The tail rotor transmission is angled 2 downward when...

Page 102: ...metric units Item Weight kg Arm X mm Arm Y mm Mom X Mom Y Equipped aircraft EW 1 AX 1 AY 1 MX 1 MY 1 Right occupant and seat 1300 320 Left occupant and seat 5 1300 280 Doors right 4 1250 600 left 600 Main luggage compartment 1854 323 Front luggage compartment 325 0 Fuel 2 2 3 3 Supplements 6 6 6 6 Total Sum GW MX GW MY GW Sum MX Sum MY 1 Report aircraft equipped weight data 2 Use 0 72 kg L for AVG...

Page 103: ...uggage compartment 12 8 0 Fuel 2 2 3 3 Supplements 6 6 6 6 Total Sum GW MX GW MY GW Sum MX Sum MY 1 Report aircraft equipped weight data 2 Use 6 0 lb gal for AVGAS density and 6 3 lb gal for automotive gasoline density 3 For fuel position use Fuel Quantity X Y 0 to 13 U S gal 72 2 in 12 3 in 13 to 40 U S gal 74 2 in 13 3 in 40 to 45 U S gal 74 9 in 13 5 in 4 Use 6 8 lb negative weight when a door ...

Page 104: ...Hélicoptères Guimbal SECTION 6 CABRI G2 WEIGHT AND BALANCE 6 6 Approved under DOA EASA 21J 211 Original issue INTENTIONALLY BLANK Issue 08 ...

Page 105: ...LECTRICAL CIRCUIT 7 7 Switches 7 7 Breaker panel 7 9 Battery breakers 7 10 Instrument panel and console 7 10 Emergency locating transmitter 7 10 ELECTRONIC PILOT MONITOR EPM 7 11 Flight screen 7 11 Starting sequence 7 11 Flight log page 7 12 Configuration and settings page 7 13 Sensors and alarms test page 7 13 Start indicator 7 14 Clock Stopwatch Flight time counter 7 14 Fuel flow modes 7 15 Carb...

Page 106: ...Hélicoptères Guimbal SECTION 7 CABRI G2 SYSTEMS DESCRIPTIONS 7 ii Approved under DOA EASA 21J 211 Original issue INTENTIONALLY BLANK ...

Page 107: ...bilizer Two composite cabin doors enable passenger pilot access One composite door enables external access to the luggage 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 b...

Page 108: ...l thrust bearing which ensures pitch flap and lead lag motions They have a two section thick stainless steel leading edge cap which protects them 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 g...

Page 109: ...The power is transmitted forward to main gearbox and aft to the tail rotor transmission The main gearbox contains a splash lubricated spiral bevel gear set which transmits power 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 ...

Page 110: ...ain 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 throttle control and to allow governor motion The collective stick is equipped with a friction mechanism which is controlled by the...

Page 111: ...s 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 fi...

Page 112: ...around the mast and gearbox It is forced by a squirrel cage blower directly driven by the engine Warm air is exhausted below the engine Fuel system The fuel system comprises a single crash resistant fuel tank an submersed electric booster pump the engine driven pump a shut down valve a gascolator FUEL TANK Filler cap Electrical pump Cutoff valve Vent Engine pump Pressure sender Gascolator Flow sen...

Page 113: ...ights BARC backup PLASMA ignition system Doors remote control the 13 7 V Auxiliary power socket Some supplemental equipment see Section 9 Starting protections On ground the system prevents from cranking the engine if It is already running and cranking switched has been released for more than 80 seconds The anti theft system is activated and doors are locked through remote control whatever actual l...

Page 114: ...ator Starter relay Avionics relay Starting logic Motor Hour meter Counting logic Doors Lock Backup Normal Mute NR Low Fuel NR lights Horn a EPM Magneto inhibition during starting 13 7 V Aux socket CARB HEAT Alim 1 Alim 1 Trim Carb heat EPM Plasma ALT Radios starter EPM Hr meter BARC main Pump Clutch Landing light Strobe Trim Nav lights Warn light BARC backup BB Auxiliar ies BB Master relay BB BARC...

Page 115: ...t page Note 2 Radio Avionics breaker value and number vary depending on radio avionics configuration In case of additional equipment refer to corresponding supplement in Section 9 for breaker panel description Radios Avionics Starter 5 BARC 1 supply from BUS Intermediate starter relay Starter logic Very low rotor speed relay Governor MGB temp ALT Clutch light Oil P Brake Gov Off Day VFR map light ...

Page 116: ...r and an intercom Space is available for additional equipment Emergency locating transmitter The ELT is located inside the luggage compartment It is attached to the main bulkhead by a strap in the lower corner The ELT switch should be in ARMED position Then the 3 position switch on the breaker panel can be used for remote control ON transmission enables manual activation of the ELT ARMED stand by ...

Page 117: ...es MLI Multiple limit indicator Engine and rotor speed indicator Fuel gage fuel flow Carburetor temperature Cylinder head temperature Engine oil temperature Engine oil pressure Fuel pressure Outside air temperature Battery charging rate Exhaust gas temperature CO alarm Clock Flight time Stopwatch CHRONO Keys Magnetic Chips and carburetor heating message box Fire alarm location 1 3 5 4 2 Carburetor...

Page 118: ... flying mode signal refer to page 7 17 After an unexpected power cut in this condition the EPM flight screen recovers within seconds Restart in the Flight log page can be done by pressing key 3 for 1 sec while on the ground with rotors and engine stopped Flight log page This page presents for each of the last 36 flights The date and time of the engine start up The technical time refer to page 7 14...

Page 119: ...rms test page The amber caution icons indicate failures and alarms that were detected during the last flight The amber FAILED indicates a line sensor failure during the self test Note it is important to distinguish between MGB TGB chips line failure left column and MGB TGB Alarm triggering right column Issue 09 Line sensor failure Line sensor failure during last flight only for frequency measureme...

Page 120: ...00 RPM It discounts the warming cooling and briefing times in a flight Its display is frozen when NR drops below 400 RPM and is reset zero only on the next flight when NR increases above 100 RPM The flight time is counted when rotor is turning from and until NR 100 RPM It is not displayed on main page At the end of a flight technical and flight times are recorded in the flight log pages refer to p...

Page 121: ...ompute approximate flight time to starvation based on instantaneous fuel flow averaged about one minute Displays during 2 min after startup Instantaneous fuel flow Automatically displayed when approximate fuel quantity is below 10 liters 2 6 U S gal Caution Do not rely on fuel quantity indication when caution light is ON or EPM warning is active Average fuel flow Calculate average flow since fligh...

Page 122: ...d by one brick Note 1 During ground run or at low power setting with a warm engine T induction may be biased by carburetor body heat radiation For this reason a brick can appear whereas the heating valve is closed Note 2 In automatic mode the EPM gradually opens the valve as needed to maintain Tcarb out of the yellow zone The amount of heating is given by the indicator In manual mode the pilot can...

Page 123: ...e switched off during 45 seconds make also sure that NR switch is on MAIN In case of an electrical bus failure the BARC can be switched to a direct battery backup supply Rotor in flying mode signal Signal activation when NR 450 RPM Signal deactivation when NR 400 RPM Main and backup modes Continuous Power off maximum NR threshold NR 594 RPM Intermittent horn Flashing Power on maximum NR red limit ...

Page 124: ...tem 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 400 RPM and self disengages below The pilot can disengage it by two ways Using the G...

Page 125: ...dividual security code 1 is up 0 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 luggage door using the backup key From the luggage door reach the right cabin door lock From the right seat open the left door lock Use above procedure...

Page 126: ...e small cabin luggage 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 luggage 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...

Page 127: ...proved under DOA EASA 21J 211 8 i Section 8 Handling and servicing GENERAL 8 1 FUEL 8 1 ENGINE OIL 8 1 GEARBOXES OIL 8 1 GROUND HANDLING 8 1 PARKING AND TIE DOWN 8 2 DUAL CONTROLS REMOVAL AND INSTALLATION 8 2 DOORS REMOVAL AND INSTALLATION 8 3 JUMP STARTING THE ENGINE 8 4 Issue 10 ...

Page 128: ...Hélicoptères Guimbal SECTION 8 CABRI G2 HANDLING AND SERVICING 8 ii Approved under DOA EASA 21J 211 Original issue INTENTIONALLY BLANK ...

Page 129: ...stalled alone Fuel gage will still function in this case with the same accuracy Engine oil Refer to page 2 7 for approved oil types and quantities Check oil level with the dipstick Gearboxes oil Refer to page 2 7 for approved oil For both main and tail gearboxes Check oil level while helicopter is sitting on a horizontal surface without ground handling wheels Add oil when level is below half level...

Page 130: ...llective stick is secured by a locking sleeve and pedals by a self locking pin Removal action the locks to remove the controls Installation install the controls until they are secured For the collective maintain the locking sleeve pushed while plugging the stick Rotate the stick until the sleeve locks Caution make sure that the controls are locked after they are put in place Cyclic control removal...

Page 131: ...in which is longer then engage the upper pin 3 Snap the gas spring rod end on its sphere and install the small locking pin in the rod end For initial design without self locking hinges the procedure is as follows Door removal 1 Open the door 2 Remove the small circular locking clip from gas spring attachment on the fuselage side Snap the rod end off 3 Remove the two hinges lock pins and save the w...

Page 132: ...Only use 12V lead acid battery for jump starting Proceed in following order 1 Connect the red cable to helicopter battery plus 2 Connect it to the external battery plus 3 Connect the black cable to helicopter battery ground 4 Connect it to the external battery ground 5 Start the engine with left cowling open 6 Remove in opposite order Caution a dead battery is not airworthy and should not be jump ...

Page 133: ...Hélicoptères Guimbal CABRI G2 Comfort in Autorotation Better with Rotor Inertia ...

Page 134: ...Hélicoptères Guimbal CABRI G2 INTENTIONALLY BLANK ...

Page 135: ... throttle is being opened The throttle butterfly position hence the priming pump motion is indicated by the MLI indicator when in START mode engine stopped blue pointer It helps warming the battery to switch the landing and position lights ON during several minutes prior to starting However always switch them OFF before attempting to start To start the engine 1 Electric pump ON 2 Raise the collect...

Page 136: ...2 As long as the engine is in its running in period with monograde straight mineral oil first 50 hours it is recommended to preheat the engine before attempting to start below 10 C 14 F The very high viscosity of such monograde oil at these cold temperatures increases the starter torque and current while battery has low power Moreover the clutch cylinder being actuated by the engine oil in this ca...

Page 137: ...ht in particular is forbidden HG would also like to point out that the Cabri G2 is equipped with a standard reciprocating engine that is not designed for aerobatic particularly low G flights it looses all its power under those conditions But unlike in an airplane a helicopter engine may stall unexpectedly under forbidden low G operation and or high nose down pitch rate This is due to the freewheel...

Page 138: ...Hélicoptères Guimbal SERVICE LETTER CABRI G2 SL 11 001 A 2 2 Original issue INTENTIONALLY BLANK ...

Page 139: ... issue this Service Letter in order to point out some specific characteristics of such tail rotors These characteristics are common to all helicopters equipped with a Fenestron and are covered by several publications including Eurocopter Service Letters N 1673 67 04 CW rotors and 1692 67 04 CCW rotors Important notes Spinning at the high rates that can be achieved in both directions by applying an...

Page 140: ...cing most of the thrust required in forward flight to counter the main rotor torque and increasing overall efficiency This also permits safe powered flight in case of a tail rotor or transmission failure This implies that this lift is unwanted in autorotation requiring the pilot to apply significant left pedal for symmetrical flight However unsymmetrical flight is not dangerous it should be correc...

Page 141: ...Hélicoptères Guimbal LETTRE SERVICE CABRI G2 SL 12 001 A Original issue 3 10 INTENTIONALLY BLANK ...

Page 142: ...ower thus in the requirement for anti torque thrust A rapid decrease in the tail fin lift the angle of attack of which is at its maximum and cannot compensate anymore the loss of airspeed They tend to provoke a departure in yaw to the left requiring a quick and large right pedal input Moreover three additional factors may increase this effect If the pilot is surprised by the departure in yaw he wi...

Page 143: ...G2 SL 12 001 A Original issue 5 10 Wind from right Critical case Loss of control scenario 2 Pilot does not apply sufficient right pedal 1 Fin stalls 3 High yawing rate Loss of control Rotor thrust Fin lift Fin is at its maximum angle of attack ...

Page 144: ... SERVICE LETTER CABRI G2 SL 12 001 A 6 10 Original issue Rotor thrust Fin lift 1 Fin lift disappears 4 The pilot adds a large amount of right pedal No wind 2 The pilot adds right pedal to compensate Good approach scenario ...

Page 145: ...CE CABRI G2 SL 12 001 A Original issue 7 10 Approach with frozen pedals 0 1 Fin stalls Its sideslip increases with decreasing airspeed The helicopter is stabilized in yaw Rotor thrust Fin lift No wind 3 High yawing rate Loss of control ...

Page 146: ... G2 SL 12 001 A 8 10 Original issue Wind from left Conservative case Normal scenario Rotor thrust Fin lift 0 3 The pilot adds only a moderate amount of right pedal No fin lift No fin lift 1 The pilot already applies some amount of right pedal ...

Page 147: ...y raising the collective to increase the ground clearance This will result in a yawing acceleration to the left When the spot turn is to the left the instinctive reaction will increase the yawing rate and could disorient the pilot When the spot turn is to the right this instinctive reaction will stop the yaw CCW rotors and CW rotors Note that described scenarios are exactly the same with CW rotati...

Page 148: ...wing to the left before it gets faster Keep the pedal to its stop until the rotation stops completely Advice 3 When practicing spot turns at low height above the ground always do it on the power pedal to the right in the Cabri G2 case Then raising the collective in case of problem will stop the spin Advice 4 When aiming at a landing site close to helicopter IGE hover ceiling above the power transi...

Page 149: ...s an alternate fuel under conditions of supply that are commented hereafter and by respecting additional limitations that have low impact on practical use Caution The pilot should be aware that using automotive gasoline in an aircraft engages his responsibility to comply with the Flight Manual requirements unlike for AVGAS which is a certified grade Caution It is the responsibility of the operator...

Page 150: ...ium term Therefore their absence in the fuel used has to be ensured There is a simple way to do that based on the alcohol property to be absorbed by water just add a volume of water to a gasoline sample shake and check that water volume has not increased This check has to be done for each batch of gasoline Dedicated detection kits simple to use are available on the market Below is a selection of w...

Page 151: ...and rules vary from one country to another In general summer grade corresponds to an RVP pressure of 60 kPa This characteristic allows to use gasoline in the same conditions as AVGAS Winter grade generally corresponds to an RVP pressure of 90 kPa slightly less than the lower limit of the standard That is why a corresponding intermediate curve is also given in the Flight Manual Caution It is not gu...

Page 152: ...nter or Summer grade if known Name of the person responsible for the purchasing In some occurrences confusion has occurred between automotive gasoline grades because of unaware person purchasing it Regardless its grade and quality of storage automotive gasoline has a limited life Check with your supplier the recommended period of use If not available it is recommended that gasoline is used within ...

Page 153: ...f the pilot does not react properly Engine governor failure is covered by Flight Manual procedure page 3 9 based on the fact that the governor by design can be overtaken at any time by the pilot whatever the cause of the degraded behavior This Service Letter details the consequences of a throttle position sensor failure in order to allow optimal reaction of the pilot and lower pilot workload Histo...

Page 154: ...ignal is off range the EPM detects it and warns the pilot as follows On the ground the MLI on START mode displays XXX red In flight the MLI digital indication is displayed with a yellow background Example In the same conditions when the rotor desynchronizes the blue GOV light flashes and the engine governor stops moving When rotor resynchronizes the blue GOV light goes out and the engine governor ...

Page 155: ... procedure page 3 9 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 with twist grip 4 CONTINUE FLIGHT 2 When the rotor is synchronized the governor may be switched back ON to resume normal governed flight Avoid intentional maneuvers that could lead to desynchronization of rotor engine Steep descent with lo...

Page 156: ...Hélicoptères Guimbal SERVICE LETTER CABRI G2 SL 15 001 A 4 4 Original issue INTENTIONALLY BLANK ...

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