CABRI G2 Flight Manual

FLIGHT TIME MANAGEMENT................................................................................ 4-14 FUEL QUANTITY MANAGEMENT WITH ALTERNATE FUEL ........................................ 4-15 APPROACH AND LANDING .................................................................................. 4-16 ENGINE / ROTOR SHUTDOWN............................................................................. 4-16 DISENGAGEMENT WITH ENGINE OFF.................................................................. 4-16 TRAINING ......................................................................................................... 4-17 SECTION 5 PERFORMANCE ........................................................................... 5-I 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 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 ........................................................................................... 7-7 ELECTRONIC PILOT MONITOR - EPM ................................................................. 7-11 BARC .............................................................................................................. 7-17 OTHER EQUIPMENTS ......................................................................................... 7-18 CABIN AND AMENITIES ....................................................................................... 7-20 SECTION 8 HANDLING AND SERVICING ....................................................... 8-I GENERAL ........................................................................................................... 8-1 FUEL .................................................................................................................. 8-1 ENGINE OIL ......................................................................................................... 8-1 GEARBOXES OIL ................................................................................................. 8-1 GROUND HANDLING ............................................................................................ 8-1 PARKING AND TIE-DOWN ..................................................................................... 8-2 JUMP-STARTING THE ENGINE ............................................................................... 8-2 DOORS REMOVAL AND INSTALLATION ................................................................... 8-2 SECTION 9 SUPPLEMENTS Issue 08 Hélicoptères Guimbal CABRI G2 INTRODUCTION Original issue Approved under DOA EASA.21J.211 0-1 Section 0 Introduction This document is the Pilot Operating Handbook and EASA approved rotorcraft Flight Manual of the CABRI G2 Rotorcraft. The following tables give the list of approved pages and the list of changes. For flight manual supplements tables (approved pages and revisions log), refer to Section 9. If rotorcraft is operated under FAA certification, this manual should be updated with some FAA specific pages, numbered with “B”, replacing original ones. The following table gives EASA approved pages. Page number Issue number Page number Issue number Section 2 Limitations 2-1 08 2-i 08 2-2 08 2-ii 2-3 08 2-4 05 2-5 09 2-6 08 2-7 03 2-8 05 2-9 05 2-10 09 2-11 2-12 07 2-13 09 2-14 09 Section 3 Emergency procedures 3-1 3-i 3-2 3-ii 3-3 3-4 07 3-5 01 3-6 3-7 03 3-8 05 3-9 07 3-10 09 3-11 03 3-12 03 3-13 07 3-14 05 3-15 09.1 3-16 08 Issue 09.1 Hélicoptères Guimbal CABRI G2 INTRODUCTION 0-2 Approved under DOA EASA.21J.211 Original issue Page number Issue number Page number Issue number Section 4 Normal procedures 4-1 4-i 08 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 4-11 08 4-12 05 4-13 4-14 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 05 5-5 05 5-6 05 5-7 5-8 05 5-9 5-10 5-11 5-12 Issue 09.2 Hélicoptères Guimbal CABRI G2 INTRODUCTION Original issue Approved under DOA EASA.21J.211 0-3 The following table gives the pages approved under DOA EASA.21J.211 : Page number Issue number Page number Issue number Cover A Table of content B C 08 D 08 Section 0 Introduction 0-1 09.1 0-7 09 0-2 09.2 0-8 09 0-3 09.2 0-9 09 0-4 09.2 0-10 09.1 0-5 09 0-6 09 Section 1 General 1-1 1-i 09 1-2 1-ii 1-3 03 1-4 08 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 09 6-5 09 6-6 08 Section 7 Systems description 7-1 09 7-i 03 7-2 7-ii 7-3 03 7-4 07 7-5 02 7-6 7-7 09 7-8 07 7-9 09 7-10 05 7-11 09 7-12 09 7-13 09 7-14 09 Issue 09.2 Hélicoptères Guimbal CABRI G2 INTRODUCTION 0-4 Approved under DOA EASA.21J.211 Original issue Page number Issue number Page number Issue number Section 7 - Continued Systems description 7-15 01 7-16 03 7-17 03 7-18 03 7-19 07 7-20 03 Section 8 Handling and servicing 8-1 05 8-i 05 8-2 09.2 8-ii 8-3 09.2 8-4 05 Issue 09.2 Hélicoptères Guimbal CABRI G2 INTRODUCTION Original issue Approved under DOA EASA.21J.211 0-5 The reference of this flight manual is J40-001. The revisions are given in the following table : Issue number Page Revision object Approval date Approval reference (*) - - Original issue 14/12/2007 TC EASA.R.145 approved by EASA letter D(2007) CPRO/ALE/55199 01 3-10 4-12 Carb heat manual test transferred to section 4 17/09/2008 EASA.R.A.01530 4-9 4-11 Normal procedure correction 4-15 Steep descent 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 under DOA EASA.21J.211 according to FSA-09-003 2-10 Gage  charge 19/05/2009 EASA.R.C.03230 3-15 Clutch light 4-2 4-9 4-11 4-12 4-16 Procedure update 1-3 Drive line  gearbox 19/05/2009 DOA EASA.21J.211 (*) EASA reference number or “approved under the authority of DOA EASA.21J.211” Issue 09 Hélicoptères Guimbal CABRI G2 INTRODUCTION 0-6 Approved under DOA EASA.21J.211 Original issue (*) EASA reference number or “approved under the authority of DOA EASA.21J.211” Issue number Page Revision object Approval date Approval reference (*) 02 4-3 Tight  Lockwiring 19/05/2009 EASA.R.C.03230 4-5 Manifold  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 7-7 to 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 7-16 Explanation of re- initiation of testing sequence 7-18 Code procedure update Note update Issue 09 Hélicoptères Guimbal CABRI G2 INTRODUCTION Original issue Approved under DOA EASA.21J.211 0-7 Issue number Page Revision object Approval date Approval reference (*) 03 This issue is associated with MOD EPM 10-009. 2.4 Oil P. indicator 21/07/2010 EASA.R.C.03496 Major modification approval 10031011 2-7 MLI supplements 2-10 Carb. Heat proc 2-13 Addition of socket 3-7 Note update 3-11 3-12 Carb 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 EASA.21J.211 according to FSA 10-011. 05 2-2, 4- 9/11, 5-4 to -6, 5-8 -20°C extension 13/12/2010 Major modification approval 10032992 3-4/5/8/9 3-14 - 16 4-5/8/16 4-20, 2-4 Procedure update Issue 09 Hélicoptères Guimbal CABRI G2 INTRODUCTION 0-8 Approved under DOA EASA.21J.211 Original issue Issue number Page Revision object Approval date Approval reference (*) 05 2-8/9 CG Update 13/12/2010 Major modification approval 10032992 2-13 Correction D, 2-1, 0-1/2/3/5 0-7, 7-8, 7-9, 8-1 Update 13/12/2010 Approved under DOA EASA.21J.211 according to FSA 10- 018 6-4/5 Level measurement 6-7/8 Fuel CG Correction 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 Major Change Approval EASA 10043929 2-12 Fuel placard 2-13 Data & Tie-down placards 3-4/9 4-19 Wording : “monitor” ”control” 3-10 CPU overtemp 3-13 Ref 3-15  3-16 3-15 GOV light update 3-16 Table shift Issue 09 Hélicoptères Guimbal CABRI G2 INTRODUCTION Original issue Approved under DOA EASA.21J.211 0-9 Issue number Page Revision object Approval date Approval reference (*) 07 4-2 Performance to be checked in chapter 5 05/03/2013 Major Change Approval EASA 10043929 4-5 Winter air flow restrictor check 4-6 Line shifted from previous page 6-5 Weighing ref. point 12/03/2013 Approved under 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 layout 2-1 Limitations 2-3 Transient low RPM limit 2-6 Lubricating oil recommendations 2-5, 4-i, D, 4-2, 4-15 Alternate fuel temporary use Temporary green pages integrated. Issue 09 Hélicoptères Guimbal CABRI G2 INTRODUCTION 0-10 Approved under DOA EASA.21J.211 Original issue (*) EASA reference number or “approved under the authority of DOA EASA.21J.211” Issue number Page Revision object Approval date Approval reference (*) 08 3-15, 3-16 Addition of name of colors D, 6-i, 6-4, 6-5, 6-6 Weighing procedure suppression 4-3, 4-4, 4-6, 4-7 Daily checks update 4-9, 4-11, 7-7 Starting procedure 4-16 Page layout 4-17 Autorotation training precisions 7-7 Cranking logic 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 brackets 4-4, 4-6, 4-7, 4-8, 6-4 6-5. Bear paws 3-10, 7-11 to 7-14 New EPM display software (1.6) 1-i, 1-7, 2-10, 4-2, 4-3, 4-15, 7-7, 7-9. wording 09.1 3-15, 0-1 0-3, 0-10, 0-1.B, 0-3.B Proc. for low fuel with automotive gasoline May 13th, 2015 Approved under DOA EASA.21J.211 Issue 09.1 Hélicoptères Guimbal CABRI G2 INTRODUCTION Original issue Approved under DOA EASA.21J.211 0-11 (*) EASA reference number or “approved under the authority of DOA EASA.21J.211” Issue number Page Revision object Approval date Approval reference (*) 09.2 0-2, 0-3, 0-4, 0-11, 0-12 Addition of log of issue & approved pages update October 21st, 2015 Approved under DOA EASA.21J.211 4-19 Title wording Validated for FAA through EASA validation support letter AGR/aro/CT.3/00600 45478-001, dated October 29th, 2015 8-2, 8-3 Doors with self- locking hinges removal & installation 09.2 FAA only pages 0-1.B, 3-15.B Correction of FAA only “B” pages October 29th, 2015 Issue 09.2 Hélicoptères Guimbal CABRI G2 INTRODUCTION 0-12 Approved under DOA EASA.21J.211 Original issue INTENTIONALLY BLANK Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL Original issue Approved under DOA EASA.21J.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 Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1-ii Approved under DOA EASA.21J.211 Original issue INTENTIONALLY BLANK Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL Original issue Approved under DOA EASA.21J.211 1-1 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 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 is responsible for determining that the helicopter is safe for flight, and for operating it in respect to this manual and above information. The helicopter’s 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. Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1-2 Approved under DOA EASA.21J.211 Original issue Three-view of the CABRI G2 Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL Original issue Approved under DOA EASA.21J.211 1-3 Descriptive data Main rotor Type ............................................................. Articulated, soft-in-plane Number of blades ................................................................................. 3 Diameter ...................................................................................... 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 Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1-4 Approved under DOA EASA.21J.211 Original issue Powerplant Model ..................................................... Textron Lycoming O360-J2A with STC EASA.E.S.01001 / STC FAA SE03495NY Type .......................... Four cylinders, horizontally opposed, direct drive, air cooled, normally-aspirated, carburetor-equipped, one magneto and one electronic ignition system Displacement ..................................................................................5,9 L (361 cu.in) Power rating (continuous) ............. 108 kW @ 2585 through 2700 RPM (145 shp) 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 break-in in Limitations section) Alternate types Automotive unleaded gasoline..................... Refer to Limitations Note : All these types are mixable, in any proportion. Issue 08 Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL Original issue Approved under DOA EASA.21J.211 1-5 Symbols and abbreviations Symbol or abbreviation Designation Speeds CAS ......................................................................... Calibrated airspeed IAS............................................................................. Indicated airspeed TAS .................................................................................. True airspeed VNE ......................................................................... Never-exceed speed Vy .....................................................................Best rate-of-climb speed Meteorology ISA.................................................... International standard atmosphere OAT ................................................................... Outside air temperature P ............................................................................. Outside air pressure  ............................................................................... Relative air density Altitude / Height AGL .......................................................................... 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 ............................................................ Hover out of ground effect Weight and balance CG ................................................................................ Centre of gravity MTOW .............................................................Maximum take-off weight Equipment EPM.................................................................... Electronic Pilot Monitor BARC ................................................ Boîtier Alarme Rotor et Carburant (Fuel and rotor alarm device) RRM / GOV ................................................................. Engine governor Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1-6 Approved under DOA EASA.21J.211 Original 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 Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL Original issue Approved under DOA EASA.21J.211 1-7 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/US units Multiply ....................................... By ..................................... To obtain millimeters (mm) ...........................0,0394............................... inches (in) meters (m) ....................................3,2808.................................... feet (ft) kilometers (km) .............................0,5400................. nautical miles (nm) kilograms (kg) ...............................2,2046............................. pounds (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 of mercury (in.hg) ................33,86........................ millibar (mbar) pounds per square inch (psi) ........0,0689..................................bar (bar) 1013,25 mbar = 29.92 in.hg Temperature Fahrenheit degrees / Celsius degrees F = 32 .C 5 9  C = 32) .(F 9 5  Issue 09 Hélicoptères Guimbal SECTION 1 CABRI G2 GENERAL 1-8 Approved under DOA EASA.21J.211 Original issue INTENTIONALLY BLANK Issue 07 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-i Section 2 Limitations GENERAL LIMITATIONS ................................................................................... 2-1 COLOR CODE FOR INSTRUMENT MARKINGS ....................................................... 2-2 FLIGHT ENVELOPE LIMITATIONS ....................................................................... 2-2 Altitude limitation .................................................................................... 2-2 Outside air temperature limitation .......................................................... 2-2 Airspeed limits........................................................................................ 2-3 Rotor speed limits .................................................................................. 2-3 POWERPLANT LIMITATIONS ............................................................................. 2-4 TRANSMISSION LIMITATIONS ........................................................................... 2-7 WEIGHT AND BALANCE LIMITATIONS (IMPERIAL UNITS) ....................................... 2-8 WEIGHT AND BALANCE LIMITATIONS (METRIC UNITS) .......................................... 2-9 SENSORS FAILURES ..................................................................................... 2-10 PLACARDS .................................................................................................. 2-11 Issue 08 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-ii EASA Approved Original issue INTENTIONALLY BLANK Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-1 The information in section 2, Limitations, is approved by EASA. General limitations Flight rules: Only day VFR is approved. Refer to Night VFR supplement J40-901 for night VFR approbation. Aerobatic flight is prohibited. Voluntary in-flight engine shut down is prohibited. Voluntary in-flight declutching is prohibited. Flight conditions: Flight in known icing conditions is prohibited. Flight in falling snow is authorised provided that snow condition is compatible with non-icing condition and horizontal visibility is above 1500 m. Note: If snow accretion on windshield is significant, land or transition to forward flight. 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 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 those with doors installed and closed. Issue 08 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-2 EASA Approved Original issue Color code for instrument markings Red Indicates operating 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. 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 08 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-3 Airspeed limits VNE power-on ......................................................................... 130 kt IAS -2 kt IAS per 1000 feet Zp VNE power-off ......................................................................... 110 kt 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 08 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-4 EASA Approved Original issue Powerplant limitations Operating limitations Engine speed Maximum engine speed ......................................................... 2700 RPM Normal range ................................................................ 2585-2700 RPM Minimum engine speed, power-on ......................................... 2585 RPM Temperature Maximum 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) .................................. 3.6 bar (52 psi) Minimum during idle .................................................................... 1.6 bar (25 psi) Fuel pressure Maximum .................................................................................. 0.55 bar (8 psi) Minimum .................................................................................. 0.02 bar (0.3 psi) Issue 05 Starting and warm-up range Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-5 Fuel Maximum tank capacity ................................................................. 170 L (45 U.S. gal) Unusable fuel quantity .................................................................... 1.5 L (0.4 U.S. gal) Warning : Do not rely on fuel quantity indication when LOW FUEL light is ON or EPM warning is active. Approved grades ....................................................................................... AVGAS 100LL ......................................................................................... AVGAS UL91 Alternate grades Automotive unleaded gasoline can be used temporarily if it complies with EN228 or ASTM D4814 and following conditions : Minimum octane rating .............................................................98 (*) Alcohols (ethanol, methanol, etc.) ................................ Zero content (*) (RON ≥ 98 and MON ≥ 87) or AKI ≥ 93 Note : refer to page 4-15 for management of possible fuel gage error. Flight envelope restriction, in absence of detailed analysis of gasoline characteristics : Note : Above grades can be mixed. If the mix contains any automotive gasoline, altitude restriction applies. Issue 09 0 2000 4000 6000 8000 10000 12000 15 20 25 30 35 40 45 Zp, ft Fuel temperature 60 70 80 90 100 110 °C °F Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-6 EASA Approved Original issue If operator has access to his fuel supply characteristics, following restriction may be used instead of the above conservative chart : RVP ≤ 60 kPa (9 psi) ................................. No flight envelope restriction 60 kPa (9 psi) ≤ RVP ≤ 90 kPa (13 psi)....... curve raised by 3000 ft Zp : Note : Exceeding this flight restriction will result in engine roughness, then loss of power. Engine Oil After break-in, use multigrade oil ....................................... 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°C (80°F) SAE 60 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 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 quantity for take-off ..................................................... 3.8 L (4 U.S. Quarts) Gearboxes oil Use Hélicoptères Guimbal oil HG30-0039 (85W140). Issue 08 0 2000 4000 6000 8000 10000 12000 15 20 25 30 35 40 45 Zp, ft Fuel temperature 60 70 80 90 100 110 °C °F Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-7 Indicated power on MLI The Multiple Limits Indicator displays the engine power status, based on engine manifold absolute pressure, with two limits :  Power (PWR) limit, which corresponds to the engine rated power of 108 kW (145 hp),  Throttle (FLO) limit, which corresponds to full throttle power. At sea level in standard conditions, FLO limit corresponds to an engine power of 134 kW (180 hp).  Their relative positions vary with engine inlet air temperature and altitude,  Both limits should not to be exceeded at any time,  The indicator (pointer and digits) displays power delivered by the engine in terms of margin to the first of these limits. Note 1 : The red radial PWR mark shows that the limit could be exceeded if the pilot requires too much power. He should control the flight not to exceed it. Note 2 : The red FLO arc warns the pilot that the limit cannot mechanically be exceeded in order to help him anticipate. Maximum ................................................................................................. 100 % Maximum rated ............................................................................... 100 % PWR Full throttle ....................................................................................... 100 % FLO Transmission limitations Main Gearbox power limitation ...................................... 100 % PWR on MLI Main Gearbox temperature ...................................................... Caution light PWR limit mode Maximum rated power Full throttle power Available power indication FLO limit mode Full throttle power Issue 03 Maximum rated power Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-8 EASA Approved Original issue Weight and balance limitations (Imperial units) Maximum Gross Weight ................................................................... 1543 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 05 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-9 Weight and balance limitations (metric units) Maximum Gross Weight .................................................................... 700 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 05 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 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-10 EASA Approved Original issue 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 OAT Use Section 5 to compute available performance Apply a margin on temperature Pressure Limit MLI to 95% in PWR mode 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 Fuel Q Perform an accurate fuel planning MGB/TGB Chips Hand-check corresponding plug at take-off Battery charge Minimize electrical loads CO Keep cabin heat closed Carb. heat control Control carb. heat manually Use carb. heat below 80% MLI Issue 09 Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS Original issue EASA Approved 2-11 HEADING FOR STEER COMPASS DATE : 0 45 90 135 180 225 270 315 Placards  On cabin ceiling :  On cabin ceiling : 0 2000 4000 6000 8000 10 000 12 000 13 000 130 126 122 118 114 110 106 104 VNE POWER OFF SUBTRACT 20 kt VNE POWER ON Zp (ft) Vi (kt) IAS subtract Hélicoptères Guimbal SECTION 2 CABRI G2 LIMITATIONS 2-12 EASA Approved Original issue  Above the fuel 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 Issue 07 The following placard can still be used if unleaded fuels are not used :