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CAP 10B - CAP10C

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1. Conditions Weight 800 kg Standard atmosphere 10 C Engine Vi speed Zp 500 ft Zp 5 000 ft Zp 10 000 ft rpm km h kt km h kt km h kt 2 350 232 125 205 111 197 106 2 450 242 131 217 117 208 112 2 700 270 146 247 133 237 128 Original issue 31 January 2002 Document 1000809 GB Page 5 8 Revision 0 PERFO RMANCE CAP 10C 5 8 LANDING DISTANCE Sea level standard atmosphere weight of 830 kg paved runway Touchdown speed 100 km h 54 kt 15 m clearance speed eoa Coro dese cipe xd da er AEN 120 km h 65 kt Landing run and 15 m clearance 600 m 1 969 ft Landing as o ERREUR 360 m 1 180 ft 5 9 GLIDE CHARACTERISTICS 140 km h 76 kt flaps retracted Sink 4 m s 787 ft min DAU O P about 10 5 10PERFORMANCE IN ICING CONDITIONS Flight in known icing conditions is forbidden Original issue 31 January 2002 Document 1000809 GB Page 5 9 Revision 0 PERFORMANCE CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 5 10 Revision 0 PERFORMANCE 6 WEIGHT AND CENTRE OF GRAVITY CAP 10C 6 1 PresentallOll ee ee nese 6 3 6 2 Register of weight and centre of gravity 6 3 6 3 Weighing procedure cesses 6 3 6 4 Weight and centre of gravity breakdown
2. 6 5 6 5 List of equipmient oueusssssceic epoca escudo vins 6 12 Original issue 31 January 2002 Document 1000809 GB Page 6 1 Revision 0 WEIGHT AND CENTRE OF GRAVITY CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 6 2 Revision 0 WEIGHT AND CENTRE OF GRAVITY CAP 10C 6 WEIGHT AND CENTRE OF GRAVITY 6 1 PRESENTATION This section is approved by the French Airworthiness Authorities D G A C Direction G n rale de l A ronautique Civile It contains necessary and useful information to fly the aircraft in complete safety 6 2 REGISTER OF WEIGHT AND CENTRE OF GRAVITY Changes in structure or equipment that affect the weight and centre of gravity are listed in the A C Individual Inspection Record I I R to allow for permanent monitoring of aircraft changes throughout its service life 6 3 WEIGHING PROCEDURE Longitudinal levelling left horizontal canopy rail The weighing procedure is described in the A C Individual Inspection Record The aircraft weighing and centre of gravity report is included in the A C Individual Inspection Record IIR Original issue 31 January 2002 Document 1000809 GB Page 6 3 Revision 0 WEIGHT AND CENTRE OF GRAVITY CAP 10C m v 4 7A MEC ERA KCN M Kl ing and centre of gravity report h 6 3 1 Example of weig OVSO B1Q JUOD ep esiA ejoujuoo ep esiA 087 9c
3. hinges and control Deflection and cable tension Rudder TAD ere hinges and control Elevator E hinges and control Tail wheel Tail wheel rubber Good condition Conjugation springs Condition and operation Aft left fuselage Static port ee ET CLEAN NOT CLOGGED Tank drains qty 21 CHECKED Inspection door under fuselage Closed and locked Tank CAN CLOSED and LOCKED Original issue 31 January 2002 Document 1000809 GB Page 4 6 Revision 0 NORMAL PROCEDURES CAP 10C Pilot and passenger seat bet ATTACHED Master switch E OFF Alternator switch OFF E Get Ee EE OFF Electrical equipment eens OFF Flaps trim switch as appropriate ON Avionics switch as appropriate ON Wl fl LEAN Cockpit beatng CLOSED 4 3 3 Starting up cold engine Master switch cccccseecceseeceeeeeseees ON NUR RETRACTED CHECKED Anti collision obt ON Throttle ever PUSHED FULL THROTTLE let FULL RICH Tank selector switch FWD Electric lun ON Fuel flow meter CHECKED Electric Elte Eege STOP Throttle lever eeeeeeseees 1 cm le St LEAN ISO cce coe cibis aora ER Rd dU ad 1 2 EE on request Original issue 31 January 2002 Document 1000809 GB Page 4 7 Revision 0 NORMAL PROCEDURES Mixture Throttle lev
4. Engine speed EN check 2300 rpm x 50rpm Initial CUM o RT 140 km h 76 kt Se RETRACTED 91 m 300 ft Normal climb 2c acorde steht 160 km h 86 kt clean config 4 3 10 Climb speed Best climb angle VXx 130 km h 70 kt cat U 120 km h 65 kt cat A Optimum climb Vy allowing for Best climb rate Vz max 160 km h 86 kt clean config To obtain the best rate of climb Vz max keep full power and check the engine speed for 2 350 rpm retract flaps check pressures and temperatures Original issue 31 January 2002 Document 1000809 GB Page 4 11 Revision 0 NORMAL PROCEDURES CAP 10C 4 3 11 Cruise In cruising flight you are advised to use the mixture control at all altitudes Consumption is then reduced and can be diminished by about 15 The maximum continuous engine speed of 2 700 rpm must in no event be exceeded To obtain the best mixture slowly reduce the mixture going from the full rich position until you obtain maximum power in the case of a fixed pitch propeller gradually reduce the mixture until the tachometer shows start of engine speed loss If the aircraft is equipped with an EGT indicator this point represents the maximum temperature We advise enriching the mixture until the temperature is 50 F generally 2 graduations below the maximum observed temperature Where there is no EGT we advise you to enrich the mixture by rotati
5. APPROVED AIRPLANE FLIGHT MANUAL amp PILOT S OPERATING HANDBOOK Manufacturer APEX Aircraft 1 route de Troyes 21121 DAROIS FRANCE Serial No 316 Registration No HB SBE Type CDN de type CAP 10B Commercial denomination CAP 10C THIS DOCUMENT MUST BE CARRIED IN THE AIRPLANE AT ALL TIMES THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT AND ADDITIONAL INFORMATION PROVIDED BY THE MANUFACTURER This airplane Flight Manual is the English translation of the French approved Airplane Flight Manual which remains the reference in any case Date of approval and signature of certificating authority 27 JUIN 2002 IEAAC P AURADE CAP 10C LOG OF REVISIONS pen ae EE Description of revision number pages Section 2 Limitations Placards 1 Feb 2003 2 44 Placard concerning use of GPS Date of revision Name title amp signature 25 MAR 2003 IEEAC P AURADE Original issue 31 january 2002 Document 1000809 GB Page Revision 1 dated February 2003 LOG OF REVISIONS CAP 10C Page mtentionely left blank Original issue 31 january 2002 Document 1000809 GB Page Il Revision 0 LOG OF REVISIONS CAP 10C CONTENTS Sections 1 GENERAL 2 LIMITATIONS 3 EMERGENCY PROCEDURES 4 NORMAL PROCEDURES 5 PERFORMANCE 6 WEIGHT AND BALANCE 7 AIRPLANE AND SYSTEMS DESCRIPTION 8 H
6. m 2 10 2 12 Flight corndliliolis seed eegne erEedeER 2 10 213 TEE 2 10 2 14 Wing outer skin color requirement 2 11 2 15 Various limitatiols noce otio tote cape eee rene ee nn 2 11 DES 2 11 Original issue 31 January 2002 Document 1000809 GB Page 2 1 Revision 0 LIMITATIONS CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 2 2 Revision 0 LIMITATIONS CAP 10C 2 LIMITATIONS 2 1 PRESENTATION The limitations included in this section are approved by the French Airworthiness Authorities D G A C Direction G n rale de l Aviation Civile 2 2LIMIT SPEEDS 2 2 1 Category U IAS Speed km h kt mph Observations Maximum full Maximum speed at which you can fully deflection V4 20D 108 tee deflect the control surfaces Maximum Maximum speed with flaps extended flaps 160 86 99 extended Ver A exceed 340 184 241 Speed never to be exceeded NE Maximum Speed not to be exceeded in normal normal 300 162 186 operation operation Vyno Original issue 31 January 2002 Document 1000809 GB Page 2 3 Revision 0 LIMITATIONS CAP 10C 2 2 2 Category A IAS Speed km h kt mph Observations Maximum full Maximum speed at which you can fully deflection V4 SE deflect the control surfaces Maximum Maxim
7. 0c V DES oe 02 n 5x essei 95 afp nuer ouoDoje jueujeBueuo ep 1e eBeJueo ep seiur 95 95e13u85 ce LE OE 6c 8c Le 9c Sc vc EC Ce Vc Oc GL 8l B3 esseiN am Sg 9plA e asseui e suep esiiduioo 9j anpisoJ eouesse uoneunojul Jnog euue ouu enbiueu poJoe epJoo e ep ue epuer bd Zd SpA Splog By 62u849J81 e e odde Jed epiA e 3jueuJolA Aly eno eoup enoy eayoneb enoy p E D pn 18 zp 92U9J9J9J e e Id zd QXzd LP so ediouud sano xne eouejsiq w Jei e ep Seug 64 epi e spiod 106 0 OCL c1 0 GO vz 0 9L Z Soil jueAv By w souss9jos e e uoddeij sed Wueuuoi w 13149 ap seJg Dal splod sensy eujeul s ep uejd np w og e anjon ep enbeye p pJoq sousuajoy SJOLUOA ep IEIUOZUOU IeJ NESAIN Ld gt jeu splog ICH n splod 00s ure 9 V 6y naow almy PIA e spiod u 9 2 np souejsiq 3q SU9S ep N 39VMH LIN3O 13 ddSdd 3d IWaysA SJJOYd SUIS eje D0bdV9 UO AIOYLNOO 3G TSNCIAIGNI 3HISIO3H SUI 4 Page 6 WEIGHT AND CENTRE OF GRAVITY Document 1000809 GB Revision 0 Original issue 31 January 2002 CAP 10C 6 4 WEIGHT AND CENTRE OF GRAVITY BREAKDOWN The centre of gravity reference is defined by the leading edge of the reference profile located 1 30
8. Vx 130 km h 70 kt cat U 120 km h 65 kt cat A Optimum climb Vy allowing for Best climb rate Vz max 150 km h 81 kt 15 flap 160 km h 86 kt clean config Descent M 200 km h 108 kt Approach NETTEN EE 150 km h 81 kt 15 flap 120 km h 65 kt Full flaps Recommended speed for turbulence penetration 200 km h 108 kt Maximum demonstrated crosswind 37 km h 20 kt Original issue 31 January 2002 Document 1000809 GB Page 4 3 Revision 0 NORMAL PROCEDURES CAP 10C 4 3 CHECK LIST OF NORMAL PROCEDURES 4 3 1 Pre flight inspection Cockpit Make certain cockpit is clean Master switch OFF Alternator switch eeseesssse OFF E et Ee EE OFF Fuel selector switch OPEN FWD TANK CAUTION For aerobatics the rear tank must be empty and the ELT must be removed Flight controls Met FREE in CORRECT DIRECTION Engine controls ene veneto hne FREE Battery Contact ON Stall warning indicator CHECKED Warning NOMS atc tnecnraee tu xs CHECKED Fuel AUG SS sioe s sesaootina c M px taedis CHECKED Battery COlLBCL usu ice oinnia ite OFF Seat belts and harnesses CHECKED Canopy attachment CHECKED Release handle CHECKED Before getting down from aircraft Fu
9. start SECTION 3 Original issue 31 January 2002 Document 1000809 GB Page 4 17 Revision 0 NORMAL PROCEDURES CAP 10C Summary CAP10 s behaviour in spin can be summarised as follows Spin stick against direction of spin e calm e low speed e long recovery time Spin stick in direction of spin e turbulent to very turbulent e high speed and unstable e short recovery time Original issue 31 January 2002 Document 1000809 GB Page 4 18 Revision 0 NORMAL PROCEDURES CAP 10C 5 1 PERFORMANCE Det Presentfdlloli eseu 5 3 5 2 Anemometric calibration 5 3 5 3 Safety e e 5 5 54 Stall SCC pP 5 6 5 5 Takeoff distance unge 5 6 5 6 Rate of cliMb Pm 5 8 5 7 Level flight performance cruise 5 8 5 8 Lapngding gelanEg gceg Seege sed ERC 5 9 5 9 Glide characteristics ssss 5 9 5 10 Performance in icing conditions 5 9 Original issue 31 January 2002 Document 1000809 GB Page 5 1 Revision 0 PERFORMANCE CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 5 2 Revision 0 PERFORMANCE CAP 10C o PERFORMANCE 5 1 PRESENTATION Unless otherwise indicated the parameters given in this section are valid at sea level in standard atmosphere and with a weight of 830 kg 5 2 ANEMOMETRIC CALIBRATION ANEMOMETRIC CALIBRATION in km h 2
10. 1 PRESENTATION This section is D G A C approved 3 2 RECOMMENDED SPEED Best glide speed 140 km h 76 kt 3 3 CHECK LISTS 3 3 1 Engine failure or loss of power on takeoff and in flight Before takeoff Engine speed less than 2 250 rpm or sudden drop interrupt takeoff Loss of power after takeoff RPM 214 700 TPM Mr Integrate down wind leg land immediately RPM lt 1 700 rpm ZS BOO JEC landing along A C axis 30 Original issue 31 January 2002 Document 1000809 GB Page 3 3 Revision 0 EMERGENCY PROCEDURES CAP 10C 300 lt Z lt 600 feet ssssssee quick troubleshooting forced landing ahead of aircraft 120 Z O00 TSG e rerai apply forced landing procedure return to runway possible 3 3 2 Engine shut down during a spin Immediately follow spin recovery procedure After spin recovery follow engine re start instructions 3 3 3 Re starting engine at altitude Tank selector switch OPEN FULLEST TANK Master Switch iae rena correr otra inus CONNECTED ON E Gei E NEN TOT 1 2 Throttle Jever MID TRAVEL lt FULL RICH Dive to reach about 280 km h 151 kt IAS In all cases loss of altitude will be about 300 metres 984 ft If the engine stalls at low altitude or if the propeller stops accelerate the procedure using the starter 3 3 4 Smoke and or fire On ground Fue
11. 2002 Document 1000809 GB Page 9 1 Revision 0 SUPPLEMENTS CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 9 2 Revision 0 SUPPLEMENTS CAP 10C 1 1 INTRODUCTION Writing in progress Original issue 31 January 2002 Document 1000809 GB Page 9 3 Revision 0 SUPPLEMENTS
12. 4 0 00508 3 785 4 546 0 946 1 852 0 0689 68 95 33 86 0 453 5 9 0 539 0 621 3 281 39 37 0 03937 197 0 264 0 220 1 057 0 539 14 51 0 0145 0 02953 2 205 9 5 32 Document 1000809 GB CAP 10C kilometres km kilometres km metres m metres m millimetres mm metres second m s litres l litres l litres I kilometres hour km h bars bar hectopascals hpa millibars mbar kilogrammes kg degrees Celsius C nautical miles nm statute miles mile feet ft inches in inches in feet min ft min US gallons gallons imp quarts US Knots kt pound square inch psi pound square inch psi inches of mercury in Hg pound Ib degrees Fahrenheit F Page 1 11 GENERAL CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 1 12 Revision 0 GENERAL CAP 10C 2 LIMITATIONS MEME IL gt E 2 3 22 LimisDOBUSu sid csigcicccecte a staseevcecedidedastaisceccattedianet 2 3 2 3 An mometric markings been 2 5 2 4 Engine limitations eeseeeeeessse 2 5 2 5 Engine instrument markings 2 7 2 6 Miscellaneous instrument markings 2 8 2 Weights eC 2 8 2 8 ba Elbling aaka aaan 2 9 X XD E 2 9 2 10 Limit load FaCiD IS ianitor unis oie co cosa nddesee 2 10 ngEc
13. 59 F the sea level pressure is 1013 2 mb 29 92 inches of mercury the temperature gradient from seal level to the altitude where T is 56 5 C 69 7 F is 0 00198 C foot and 0 C above OAT Outside Ambient Temperature Std Standard temperature temperature of 15 C 59 F at sea level with a decrease of about 2 C 1000 feet 6 5 C 1000 m Zp Pressure altitude altitude measured using a barometer with the reference pressure equal to 1013 2 mb 29 92 inches of mercury Zd Density altitude altitude at which a particular density is encountered in standard atmosphere The density altitude takes the real temperature into account Original issue 31 January 2002 Document 1000809 GB Page 1 10 Revision 0 GENERAL 1 13CONVERSION Nautical miles nm Statute miles mile Feet ft Inches in Inches in Feet min US gallons Gallons imp Quarts US Knots kt ft min Pounds per square inch psi Pounds per square inch psi Inches of mercury in Hg Pound Ib Degrees Fahrenheit F 32 Kilometres km Kilometres km Metres m Metres m Millimetres mm Metres second m s Litres I Litres I Litres I Kilometres hour km h Bars bar Hectopascals hpa Millibars mbar Kilogrammes kg Degrees Celsius C Original issue 31 January 2002 Revision 0 X X X X 0X X X KK X X X X X X X KK KK KK KKK KK KK X 1 852 1 609 0 305 0 0254 25
14. YMBOLS ABBREVIATIONS AND TERMINOLOGY CAUTION means that failure to observe the corresponding procedure may lead to immediate or significant degradation of flight safety REMARK means that failure to observe the corresponding procedure may lead to a minor degradation of flight safety in the relatively longer term NOTE used to draw attention to a point that has no direct consequences on safety but that is important or out of the ordinary Original issue 31 January 2002 Document 1000809 GB Page 1 9 Revision 0 GENERAL IAS Indicated airspeed speed read on the anemometer CAS Calibrated airspeed indicated airspeed with instrument and anemometric error corrected TAS True airspeed calibrated airspeed with altitude temperature and compressibility taken into account Manoeuvring speed maximum speed at which you can fully deflect the control surfaces Speed never to be exceeded for positive or negative snap manceuvres Maximum speed flaps extended Speed never to be exceeded Vyno Maximum speed in normal operation Vs Stalling speed Vso Stalling speed in landing configuration flaps fully extended maximum weight Best climb angle speed Best rate of climb speed speed allowing maximum climb speed to be obtained Vz max Vertical speed ISA International Standard atmosphere airis a perfect dry gas the sea level temperature is 15 C
15. ft 10 id 9 e t09 10 C increase in 10 1 1 5 1 05 ambient temperature Dry grass 1 short 13 cm 20 1 2 20 1 2 length 13 25 cm 25 1 25 30 1 3 Wet grass 1 short 25 1 25 30 96 1 3 long 30 96 1 3 40 96 1 4 Rising Dropping 0 SE 10 1 1 10 1 4 Tailwind component h 10 km h 20 96 1 2 20 1 2 EE 25 or more 1 25 or 25 or more 1 25 or ground Additional safety factor 1 33 143 if raw data 1 Increased effect for taxiing distances on takeoff landing Any change in the technique normally used in operation is likely to lead to increased distances Factors are accumulative and must be multiplied Original issue 31 January 2002 Revision O Document 1000809 GB Page 5 5 PERFORMANCE 5 4 STALL SPEED CAP 10C Configuration Flaps clean Throttle idle Weight Level flight Turn 30 Turn 45 Turn 60 kg Ib km h kt km h kt km h kt km h kt 830 1830 99 54 106 57 118 64 140 76 Configuration Flaps 15 Throttle idle Weight Level flight Turn 30 Turn 45 Turn 60 kg Ib km h kt km h kt km h kt km h kt 830 1830 91 49 98 53 108 58 129 70 Configuration Flaps 40 Throttle idle Weight Level flight Turn 30 Turn 45 Turn 60 kg Ib km h kt km h kt km h kt km h kt 830 1830 86 46 92 50 102 55 122 66 5 5 TAKEOFF DISTANCE Se
16. the windshield along the aircraft axis The AFT tank filling hole is located behind the canopy on the left side The stand by electric pump comes into operation by flicking a switch located on the lower panel of the instrument panel CAUTION The AFT tank must be empty for any Aerobatic manoeuvres 7T 9 ELECTRICAL EQUIPMENT Electrical generation is obtained from an alternator that supplies a 12 volt battery through a voltage regulator The installation is of the single wire type with return by the ground earth The battery allows for autonomous start up of the aircraft If necessary you can check operation of the electrical circuit through an ammeter located on the instrument panel 7 10LIGHTING AND BEACON LIGHTS The CAP10B can be equipped with the following lights Anti collision Rotating Landing light Navigation lights Original issue 31 January 2002 Document 1000809 GB Page 7 10 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C 7 11 HEATING AND VENTILATION Heating in the cockpit is obtained by letting in air heated by the exhaust manifold A pull knob placed on the lower left part of the instrument panel controls the flow of hot air let into the cockpit Two ventilation holes placed on either side of the windshield or the canopy let in outside air 7 12PRESSURE SAMPLE 7 12 1 Static Static pressure is sampled through two pressure ports placed on either side of the fuselag
17. then 1 2 Permitted engine drop 125 rpm per magneto Maximum difference between magnetos 50 rpm fe PETERE RR E RN TR test E el e E canarias cut off test lt TE LEAN then RICH Original issue 31 January 2002 Document 1000809 GB Page 4 9 Revision 0 NORMAL PROCEDURES CAP 10C 4 3 8 Vital actions before takeoff Engine Tank selector switch FWD PUMOMOMY suec besie pev ccnl UE poda VERO MERE CHECKED le ut SET MAX POWER Master switchen ON Alternator switch esesssse ON Battery charge EN CHECKED E el e E 1 2 Flight controls Elevator 0 cece ec eecececececcecececececeeaeaeeececeees free in correct direction Lateral control free in correct direction Rudder pedals free in correct direction Elevator tab esee CHECKED then NEUTRAL gi FULL FLAPS then 15 Equipment Mechanical accelerometer reset Altimeter EE SET d EE SET Cockpit Eege Closed and locked Seat belt and hammesses ATTACHED Drake RELEASED Original issue 31 January 2002 Document 1000809 GB Page 4 10 Revision 0 NORMAL PROCEDURES CAP 10C FULL THROTTLE eee CHECKED 2 250 x 50 rpm T M from 50 km h 27 kt n 110 km h 59 kt Propeller torque is to the left on this aircraft
18. 00809 GB Page 6 9 Revision 0 WEIGHT AND CENTRE OF GRAVITY CAP 10C Balance must be included between 20 and 30 category U Maximum weight 830 kg 1 830 Ib Empty weight a1 use of aircraft data in its real configuration Take residual quantities unusable of oil and fuel into account The empty weight a1 the lever arm b1 and moment c1 must be taken from the aircraft weight and centre of gravity register Weight of fuel use 0 72 kg litre 6 Ib gal Standard hourly consumption 180 hp to 2 700 rpm 14 5 Gal h 55 I h 135 hp to 2 450 rpm 75 11 Gal h 42 I h 117 hp to 2 350 rpm 65 8 5 Gal h 32 l h The maximum load in the luggage hold is 50 kg evenly distributed Moment weight x lever arm A sum of a1 to a6 C sum of c1 to c6 850 CO Q o WN Weight kg o o N N Q oa eo c eo eo eo eo a a o a Q o Balance Original issue 31 January 2002 Document 1000809 GB Page 6 10 Revision 0 WEIGHT AND CENTRE OF GRAVITY 6 4 6 Example of calculation in category U Pilot 85 kg Co pilot 75 kg R servoir avant AFT tank Luggage 50 kg 25 kg about 35 litres 45 kg about 63 5 litres Fuel consumption planned during flight 60 kg about 83 litres Weight and centre of gravity assessment before flight CAP 10C Revision 0 Weight Lever
19. 1 2464 1005 3297 Temp Weight 780 kg 1 720 Ib Weight 830 kg 1 830 Ib Zp Takeoff run 15m Takeoff run 15m C F m ft m ft m ft m ft 15 5 287 942 372 1221 304 997 394 1293 0 0 32 306 1004 395 1296 324 1063 418 1371 15 59 330 1083 425 1394 350 1148 450 1476 30 86 396 1299 502 1647 420 1378 538 1765 760 m 15 5 320 1050 413 1355 340 1116 437 1434 2493 ft 0 32 380 1247 487 1598 403 1322 516 1693 2500 ft 15 59 455 1493 587 1926 483 1585 622 2041 30 86 554 1818 721 2366 588 1929 763 2503 1520 m 15 5 429 1408 554 1818 455 1493 587 1926 4987 ft 0 32 521 1709 680 2231 553 1814 720 2362 5000 ft 15 59 640 2100 842 2763 679 2228 892 2927 201 86 792 2598 1063 3488 840 2756 1125 3691 Original issue 31 January 2002 Document 1000809 GB Page 5 7 Revision 0 PERFORMANCE 5 6 RATE OF CLIMB Sea level standard atmosphere weight of 830 kg 1 830 Ib Optimum climbing speed Vy 160 km h 86 kt Full AG Wy EE 5 1 m s 1 004 ft min The operational ceiling is limited to 5 000 m 16 404 ft 5 6 1 Climb time Standard atmosphere weight 830 kg 1 830 Ib Altitude Climb time m ft min 0 0 0 1 000 3 280 4 2 000 6 560 7 3 000 9 840 12 4 000 13 120 22 5 7 LEVEL FLIGHT PERFORMANCE CRUISE CAP 10C
20. 2 FLIGHT CONTROLS The elevator control is of the combined type with rods and cables A central rod located in the forward part of the fuselage is connected through a bellcrank to two cables connected directly to the elevator The elevator is equipped with an irreversible tab The lateral control system is of the rigid type The ailerons are controlled by rods and the spar has a torque tube running through it The yaw control comprises two rudder pedals that actuate the rudder through two cables Original issue 31 January 2002 Document 1000809 GB Page 7 4 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C The rudder pedals equipped with stirrups to retain the feet in inverted flight are not adjustable The rudder designed in identical fashion to the vertical stabiliser is aerodynamically compensated by a horn balance It is equipped with a recessed automatic tab The high lift device comprises high lift flaps located on each half wing on the trailing edge close to the root section 7 3 FLIGHT INSTRUMENTS As required by French Civil Aviation Requirements the CAP10 must at least be equipped with the following flight instruments for day V F R and for aerobatics an airspeed indicator aside slip indicator ball for normal flight an altimeter amagnetic compass an electronic accelerometer The following instruments can also be installed avertical speed indicator a side slip indicator ball for i
21. 40 220 200 180 160 140 Calibrated airspeed Vc in km h 120 100 120 140 160 180 200 220 240 Indicated airspeed Vi in km h Original issue 31 January 2002 Document 1000809 GB Page 5 3 Revision 0 PERFORMANCE CAP 10C ANEMOMETRIC CALIBRATION in kt 130 120 110 100 90 80 Calibrated airspeed Vc kt 70 60 60 70 80 90 100 110 120 130 Indicated airspeed Vi kt For aircraft equipped with an AN 5812 type USA pitot probe the stalling speeds indicated in landing configuration full flaps are significantly lower Thus the new speeds vary from 60 km h 32 kt to 65 km h 35 kt Moreover the difference between the two types of probes USA standard is proportional to the deflection of the flaps For zero degrees we measure 85 km h 46 kt for probe AN 5812 as against 95 km h 51 kt for the standard probe In inverted flight these speeds are respectively 79 km h 43 kt as against 114 km h 62 kt Original issue 31 January 2002 Document 1000809 GB Page 5 4 Revision 0 PERFORMANCE 5 3 SAFETY FACTORS CAP 10C Takeoff Landing ge Increase in Increase in Conditions distance to Factor distance from Factor 15 m obstacle 15 m obstacle 10 o aircraft weight 20 96 12 10 14 increase Increase of airfield 5 altitude by 1000
22. 590 m GAS E 1 316 m Mobile area EN 0 659 m Deflection 18 2 1 3 8 Landing gear Main BI MC CTS 2 06 m Wheel dimension ccceeceeeeee seen eeeees 380 x 150 Tyre inflation Dreseure 2 bars Shock absorber inflation pressure 8 bars Auxiliary Tyre dimension eeessssusss 6 x 200 Original issue 31 January 2002 Document 1000809 GB Page 1 6 Revision 0 GENERAL 1 4 POWER PLANT Manufacturer LYCOMING Model type AEIO 360 B2F Power and rpm CAP 10C Power Engine speed nominal 180 hp 2 700 rpm cruise 75 2 450 rpm economy cruise 65 2 350 rpm 1 5 PROPELLER Number 1 1 Manufacturer HOFFMANN EVRA Model HO 29 HM 180 170 CAP 3 180 170 H5 F Number of blades 2 2 Diameter 180 cm 71 in 180 cm 71 in Type Fixed pitch Fixed pitch 1 6 FUEL 1 6 1 Grade Minimum e TT 91 96 1 6 2 Quantities Overall Oouantitv nennen in fwd tank SEHR kee ee NR Original issue 31 January 2002 Revision 0 111 kg 245 Ib 54 kg 119 Ib 56 9 kg 125 Ib Document 1000809 GB 154 litres 41 US Gal 75 litres 20 US Gal 79 litres 21 US Gal Page 1 7 GENERAL Usable quantity E FWD tank 72 litres AFT tank 78 litres 1 7 OIL 1 7 1 Characteristics and grade For longer engine life you are advised to use Up to 50 hours erect cucu ssseceiadesndadescrsteveets mineral oil E
23. ANDLING SERVICING AND MAINTENANCE 9 SUPPLEMENTS Original issue 31 january 2002 Document 1000809 GB Page III Revision 0 CONTENTS CAP 10C Page mtentionaely left blank Original issue 31 january 2002 Document 1000809 GB Page IV Revision 0 1 1 1 2 1 3 1 4 1 5 1 6 1 7 1 8 1 9 1 10 1 11 1 12 1 13 Original iss Revision 0 CAP 10C 1 GENERAL InNtrodUCtionN E 1 3 Presentation uu cctueutensteceracietincssoeeecitattieeceetedoseciien 1 3 Three view drawings eese 1 4 Power plant se ae Aaaa arp RE Eu RE MEE 1 7 Propeller eT m 1 7 Qi e BM 1 7 e e X 1 8 Certified maximum weights 1 8 Characteristic weights eeeeeeeeesesese 1 9 Cockpit Dimensions eeeeeeeeee eene 1 9 Characteristic loads otto teret tein deed oen de 1 9 Symbols abbreviations and terminology 1 9 lg n 1 11 ue 31 January 2002 Document 1000809 GB Page 1 1 GENERAL CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 1 2 Revision 0 GENERAL CAP 10C 1 GENERAL 1 1 INTRODUCTION This document contains information to be provided to the pilot as required by regulation JAR 23 and additional information provided by the manufacturer It integrates th
24. AP 10C EE 140 km h Mixture esses IDLE CUT OFF Fuel selector switch CLOSED MAKE FORCED LANDING or EVACUATE AIRCRAFT 3 4 4 Engine high cylinder temperature Climbing Stop climb Engine speed reduce Wl dee full rich Oil Temperature monitor Return to airfield Level flight Engine speed REDUCE We INCREASE RICHNESS If t fails TO CN OD DE land as soon as possible 3 4 5 Oil failure Pressure zero temperature normal or rising Engine speed EE REDUCE to 1 700 rpm Avoid accelerations and engine speed changes Troubleshoot for possible electrical failure Original issue 31 January 2002 Document 1000809 GB Page 3 8 Revision 0 EMERGENCY PROCEDURES CAP 10C Return to closest airfield while monitoring parameters If engine seizes before airfield land in countryside Pressure zero temperature zero light off SIE et Check If gauges On KEE check circuit breaker 3 4 6 Fuel Low reading on fuel flow meter Electric DUMP sc isanssibacecccadettntdacsesssasnadessins ON Mixture sa re full rich Engine speed ANEN optimum to avoid vibrations Return to closest airfield with engine out type integration High reading or fuel flow fluctuations Engine speed avoid vibrations if necessary Return to closest airfield while monitoring cylinder temperature 3 4 7 Mechanical pump failure Stand by electric pump ON If the en
25. O 360 B2F Max engine speed and max continuous 2 700 rpm Document 1000809 GB Page 2 5 LIMITATIONS Original issue 31 January 2002 Revision 0 CAP 10C 2 4 1 Oil pressure Noa 4 22 bar to 6 33 bar Precaution eese 1 76 bar to 4 22 bar Maximum on start up 7 03 bar 2 4 2 Oil temperature MaX MUM ERR RENE E 118 C 244 F 2 4 3 Oil capacity Cat U Cat A Minimum 2 qt 1 9 litre 2 qt 1 9 litre Maximum 8 qt 7 6 litres 6 qt 5 7 litres 2 4 4 Cylinder temperature En E 260 C 500 F 2 4 5 Fuel pressure Maximum at pump outlet 3 16 bar Minimum at pump outlet 0 98 bar 2 4 6 Fuel quality Minimum grade esee 91 96 Original issue 31 January 2002 Document 1000809 GB Page 2 6 Revision 0 LIMITATIONS CAP 10C 2 4 7 Oil characteristics Ambient temperature Characteristic above 15 C 59 F SAE 50 from 12 C 10 4 F to 32 C 90 SAE 40 F from 18 C 0 4 F to 21 C 70 SAE 30 F below 12 C 10 4 F SAE 20 2 4 8 Propeller Number 1 Manufacturer HOFFMANN EVRA Propeller 180 cm 180 cm diameter 2 5 ENGINE INSTRUMENT MARKINGS Red line Yellow arc Green arc Yellow arc Red line Instrument Lower Fly with Normal Fly with Upper limit cautio
26. TION For aerobatic flight only the fwd tank must be used The aft tank must be empty CAUTION Flaps must be retracted for aerobatic flight CAUTION Electrical flap system switched off in Category A A C equipped with an electrical tab system switched off in Category A Original issue 31 January 2002 Document 1000809 GB Page 2 9 Revision 0 LIMITATIONS CAP 10C 2 10LIMIT LOAD FACTORS At max weight Category U Category A Flaps retracted positive n 4 4 6 Flaps retracted negative n 1 8 4 5 Flaps extended positive n 2 2 Flaps extended negative n 1 8 2 2 11CREW Minimum 1 pilot in left seat Maximal 1 pilot or trainee in left seat 1 passenger or instructor 2 12FLIGHT CONDITIONS Day VFR in non icing conditions 2 13FUEL Total quantity occae d sert puc dde punt a apes 154 litres 75 litres Fwd tank 79 litres Aft tank Usable quantity s Fwd tank 72 litres Aft tank 78 litres Unusable fuel enitn Fwd tank 3 litres Aft tank 1 litre Minimum quantity for aerobatics 10 litres usable in Fwd tank The minimum quantity of petrol to ensure perfect engine operation on switches from positive flight to negative flight and vice versa is set at 10 litres 2 6 US Gal 7 2 kg 16 Ib usable quantity in the front tank Original issue 31 January 2002 Document 1000809 GB P
27. a level standard atmosphere weight of 830 kg paved runway Original issue 31 January 2002 Revision 0 Takeoff speed 110 km h 59 kt 15 m clearance speed 115 km h 62 kt Takeoff run and 15 m clearance 450 m 1 476 ft Takeoff rUn een 350 m 1 148 ft Document 1000809 GB Page 5 6 PERFORMANCE 5 5 1 Zp pressure altitude T temperature in degrees Celsius Influences of altitude and temperature CAP 10C Weight 680 kg 1 500 Ib Weight 730 kg 1 609 Ib Zp EH Takeoff run 15m Takeoff run 15m C F m ft m ft m ft m ft 15 5 258 847 353 1158 272 892 352 1155 0 0 32 275 902 354 1161 290 951 374 1227 15 59 297 974 381 1250 313 1027 402 1319 201 86 356 1168 455 1493 376 1234 480 1575 760 m 15 5 288 945 370 1214 304 997 390 1280 2493 ft 0 32 341 1119 437 1434 360 1181 461 1513 2500 ft 15 59 410 1345 527 1729 432 1417 556 1824 30 86 499 1637 646 2119 526 1726 682 2238 1520 m 15 5 386 1266 497 1631 407 1335 524 1719 4987 ft 0 32 469 1539 609 1998 495 1624 643 2110 5000 ft 15 59 576 1890 755 2477 607 1992 797 2615 30 86 713 2339 953 3127 75
28. age 2 10 Revision 0 LIMITATIONS CAP 10C 2 14WING OUTER SKIN COLOR REQUIREMENT In order to limit the temperature of the main spar a white colored area must cover the upper wing surface This area must overlap the surface area of the spar by 50 mm on either side see diagram below Area with colour restrictions 2 15VARIOUS LIMITATIONS No smoking Do not leave objects on the floor 2 16LABELS Flaps control Original issue 31 January 2002 Document 1000809 GB Page 2 11 Revision 0 LIMITATIONS CAP 10C Manoeuvring speed VA CAT A VA 235 km h CAT U VA 200 km h Procedure to recover from unintentional spin Unintentional spin recovery Full opposite rudder Pitch up Ailerons in neutral As soon as you come out of spin controls to neutral and pull out gently Original issue 31 January 2002 Document 1000809 GB Page 2 12 Revision 0 LIMITATIONS CAP 10C Limitations INDICATED AIRSPEEDS CATA CAT U VNE 340 km h 184 kt Vue 340 km h 184 kt VA 235 km h 127 kt VA 200 km h 108 kt VAD 160 km h 86 kt Vso 79 km h 43 kt Vso 86 km h 46 kt WEIGHT AND BALANCE CAT A CAT U Maximum weight 780 kg Maximum weight 830 kg Front balance limit 20 96 Front balance limit 20 96 Rear balance limit 26 96 Rear balance limit 30 96 AUTHORISED MANOEUVRES CAT A CAT U All aerobatic manoeuvres and idle Al
29. arm Moment kg m m kg Empty weight 550 0 297 163 35 Pilot 85 0 6 51 Passenger 75 0 6 45 Usable fuel FWD tank 25 0 243 6 08 Usable fuel AFT tank 45 1 26 56 7 Luggage 50 1 1 55 Totals weight and moment 830 0 440 364 98 Balance of MAC 0 440 1 5 x100 2932 in kg m and m kg Weight and centre of gravity assessment after flight Weight Lever arm Moment kg m m kg Empty weight 550 0 297 163 35 Pilot 85 0 6 51 Passenger 75 0 6 45 Usable fuel FWD tank 10 0 243 2 43 Usable fuel AFT tank 0 1 26 0 Luggage 50 1 1 55 Totals weight and moment 770 0 405 311 92 o arp E nk 0 405 1 5 x100 2701 Original issue 31 January 2002 Document 1000809 GB Page 6 11 WEIGHT AND CENTRE OF GRAVITY CAP 10C Weight kg Cc o o c eo c eo eo eo a Q Balance 6 5 LIST OF EQUIPMENT The list of airborne instruments is included in the A C Individual Inspection Record l I R Original issue 31 January 2002 Document 1000809 GB Page 6 12 Revision 0 WEIGHT AND CENTRE OF GRAVITY CAP 10C 7 AIRCRAFT AND SYSTEMS DESCRIPTION MEME luco sioececsnenceetece eee wennecianieerewenneccaeerteenameseaete ees 7 3 7 2 Flight CON ONS RET 7 4 7 3 Flight instruments erre oec renun reme in rnniunn ed 7 5 ZA Landing gear and ground handling 7 5 TB HBHabitabilify ieeciieieesp ai ecocp geet 7 6 7 6 Power platt e 7 6 T4 Prop ller eT 7 9 L FUCI SYST Mm 7 9 7 9 E
30. ats side by side between which there is the electric elevator trim control and its indicator Each seat is equipped with a longitudinal adjustment 7 6 POWER PLANT 7 6 1 Description The CAP10B is equipped with an American LYCOMING AEIO 360 B2F engine Characteristics 4 flat cylinders with direct drive and air cooling Original issue 31 January 2002 Document 1000809 GB Page 7 6 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C This injection engine develops a nominal power of 180 hp at 2 700 rpm for a fuel consumption of 14 5 GPH 55 I h It develops 135 hp at 2 450 rpm 75 consumption 11 GPH 42 I h 117 hp at 2 350 rpm 65 consumption 8 5 GPH 32 I h It is secured to a welded steel tubular craddle and drives a fixed pitch propeller The engine cowl is made of glass fibre laminate and self extinguishing resin Two side doors allow for customary inspections Disassembly of the cowl is quick and easy 7 6 2 Engine controls Engine management involves throttle mixture start button and magneto selector switch The throttle control comprises two slide levers located against the wall for the left seat on the central part of the instrument panel for the right seat A knurled wheel located on the lower axis of the left seat throttle lever means you can adjust the unit s stiffness The mixture control lever red located at the left end of the instrument panel allows fine adjustment of the mixtu
31. d airspeed being capable of exceeding 180 km h tendency to dive more to right than to left Risk of Va being exceeded during spin and recovery Immediately apply instructions for recovery as soon as speed reaches 180 km h Original issue 31 January 2002 Document 1000809 GB Page 4 16 Revision 0 NORMAL PROCEDURES CAP 10C 4 4 3 Influence of stick position CAUTION The stick position roll control has an influence on the CAP10 s behaviour during spin Stick to counter spin For example in left spin the stick to the right tends to level spin out and as a result reduce the indicated airspeed CAUTION In the case of spin with centre of gravity aft this manoeuvre may prove to be dangerous by exacerbating the tendency to level out and delaying the recovery time Stick in direction of spin For example in left spin the stick to the left tends to agitate and or deepen the spin and as a result increase the indicated airspeed CAUTION Whatever the centre of gravity this manoeuvre may prove to be dangerous due to the increased risk of e turbulent to very turbulent spin e increase in speed e transition to a flick roll In all cases listed above apply the instructions for recovery see 4 4 1 In the event of engine shut down during spin immediately apply the instructions for recovery from spin then apply the instructions for engine re
32. e 7 12 2 Dynamic total Dynamic pressure is sampled through a Pitot type head located on the left underwing You can heat up the Pitot tube using an electrical resistor 7 13STALL WARNING SYSTEM A red light on the upper left panel of the instrument panel warns of onset of stall 7 14AVIONICS The originally fitted radionavigation equipment includes as a minimum a VHF transceiver The aircraft can also be equipped with the following instruments transponder alticoder intercom Original issue 31 January 2002 Document 1000809 GB Page 7 11 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C GPS VOR ILS An ELT is offered as an option The equipment configuration for each CAP10 forms part of its Individual Inspection Record I I R The instruments specific to an aircraft are described in section 9 Supplements Original issue 31 January 2002 Document 1000809 GB Page 7 12 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C 7 15INSTRUMENT PANEL This section is customised according to the aircraft 7 15 1 Upper panel 3 324 9 6 7108 11 13 12 14 15 16 17 Mike peadset Master n ee ol oer 20 212223 24 25 93126 27 28 29 30 20 CAP 10C Serial nr 316 1 Stall warning light 17 Stopwatch 2 VOR ILS indicator 3 not used 4 Mike headset jacks 5 Master alternator switches 6 Alternator breaker l Parking brakes 8 Cabin heat 9 Switches 10 Annu
33. e 1 LEE detergent oil Recommended viscosity according to air temperature Temperature Viscosity Above 15 C 59 F SAE 50 From 1 to 32 C 30 2 to 89 6 F SAE 40 From 18 to 21 C 0 4 to 69 8 F SAE 30 Below 12 C 10 4 F SAE 20 Oil capacity Cat U Cat A Minimum 2 qt 1 9 litres 2 qt 1 9 litres Maximum 8 qt 7 6 litres 6 qt 5 7 litres 1 8 CERTIFIED MAXIMUM WEIGHTS Category U Category A Weight kg Ib kg Ib Maximum takeoff weight 830 1 930 780 1 720 Maximum landing weight 800 1 764 780 1 720 Maximum load in 50 110 Forbidden luggage compartment Original issue 31 January 2002 Document 1000809 GB Page 1 8 Revision 0 GENERAL CAP 10C 1 9 CHARACTERISTIC WEIGHTS Empty weight ENN 540 kg 1190 Ib Maximum payload 290 kg 639 Ib These values are given for information The empty weight specific to an aircraft is indicated in the weighting and centring report inserted in the Aircraft Individual Inspection Record l I R 1 10COCKPIT DIMENSIONS Width maximum 1 05 m 3 44 ft Height maximum sssssss 0 98 m 3 21 ft 1 11C HARACTERISTIC LOADS Wing loading with weight of 830 kg 1930 Ib 76 5 kg m 16 5 Ib Sq ft Weight power ratio 180 hp 4 5 kg hp 10 6 Ib hp 1 128
34. e aircraft flight manual approved by the French Airworthiness Authorities D G A C Unless otherwise stated the speeds used in this flight manual are indicated air speeds 1 2 PRESENTATION The trade name CAP10C is the commercial denomination for the CAP10B as from serial number 300 This trade name is also associated with application of major change 000302 SB No 000302 The CAP10B is certified in the Utility and Aerobatics categories in accordance with regulation AIR 2052 and its amendments dated 10 November 1969 Major change 000302 to the CAP10C is certified in the Utility and Aerobatics categories in accordance with regulation JAR 23 and its amendments dated 11 March 1994 The CAP10B is a two seater training aircraft specially designed for advanced training and aerobatics instruction The side by side seat arrangement and comfort of its cockpit together with its high speed and long range make it a good travel aircraft Its instrument panel can accommodate all the radio equipment needed for VFR navigation This is a low wing single engine aircraft with conventional landing gear It is equipped with a 180 hp LYCOMING AEIO 360 B2F engine featuring an inverted flight tank Original issue 31 January 2002 Document 1000809 GB Page 1 3 Revision 0 GENERAL CAP 10C 1 3 THREE VIEW DRAWINGS 2nM Sy i 4 Flight line 1 e C T
35. ed handle on the canopy Pull the handle slightly downwards Tilt the handle 90 to the left and forward Raise the canopy while pushing it upward Evacuation Release the seat belt Evacuation If the aircraft is in a spin or a turn evacuation must where possible be in the outward direction on the trailing edge of the wing Pilot and passenger are to stay bunched up as long as possible to avoid being caught by the aircraft when the parachute opens Original issue 31 January 2002 Document 1000809 GB Page 3 11 Revision 0 EMERGENCY PROCEDURES CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 3 12 Revision 0 EMERGENCY PROCEDURES CAP 10C 4 NORMAL PROCEDURES 4 1 Presentallolksssvcsvacodt ik cedonnxs xD Eege ed 4 3 42 ET TE 4 3 4 3 Check list of normal procedures 4 4 4A SPINS eee em 4 15 Original issue 31 January 2002 Document 1000809 GB Page 4 1 Revision O NORMAL PROCEDURES CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 4 2 Revision 0 NORMAL PROCEDURES CAP 10C 4 NORMAL PROCEDURES 4 1 PRESENTATION This section describes the procedures for normal operation Normal procedures associated with optional systems are in section 9 Supplements 4 2 SPEEDS I Cop TT 110 km h 59 kt Kielen W 160 km h 86 kt Best climb angle
36. el TANI f visual inspection SIT closed and locked Original issue 31 January 2002 Document 1000809 GB Page 4 4 Revision 0 NORMAL PROCEDURES CAP 10C Sa hinges and control MT hinges and control Balance plates and deflection FILO dE clean not clogged Main landing gear shock absorber checked and tyre inflated Underwing inspection door locked Fwd fuselage Tank CAIN er checked LEE MEC checked Lower inspection door closed and locked Cowl left door closed and locked tt condition and attachment SDIPITIGF escccccccssencnnscccescassiececcaasiaedareandecees condition and attachment Air EEN free ON GY Cle checked 6 qt maximum for aerobatics Cowl right door iore relie Er ette closed and locked Right wing Main landing gear shock absorber checked and tyre inflated Underwing inspection door locked Original issue 31 January 2002 Document 1000809 GB Page 4 5 Revision 0 NORMAL PROCEDURES CAP 10C EIER MOM hinges and control Balance plates and deflection le hinges and control Rear right fuselage lee Sanaa eee eee eae eer clean and not clogged Antennas ENN VISUAL INSPECTION Eege locked Horizontal stabiliser Horizontal stabiliser ATTACHMENT Elevator and vertical stabiliser
37. er 4 3 4 Starting up hot engine Master switch Anti collision light as appropriate Throttle lever Mixture Magnetos Starter Mixture Throttle lever 4 3 5 Engine he Engine speed ating CAP 10C RICH as soon as engine is running set for 1 000 rpm ON ON 4 to 5 cm LEAN 1 2 on request RICH as soon as engine is running set for 1 000 rpm 1 000 to 2 000 rpm Do not exceed 1 000 rpm for the first minute Oil pressure CHECKED 4 to 6 bars If the oil pressure did not rise to above 1 8 bar within 30 seconds after start up stop the engine and proceed with verification Fuel pressure Cut off test magnetos Alternator switch Original issue 31 J Revision 0 anuary 2002 Document 1000809 GB Page 4 8 NORMAL PROCEDURES CAP 10C Battery charge CHECKED Electrical equipment eee ON Ke 5 min if use intended Takeoff is authorised when the oil temperature reaches the green zone 4 3 6 Taxiing Parking BFaKO reta da suae cba ptm n RO CU RE RELEASED Brakes and conjugation test DONE When starting off make certain the tail wheel conjugation is operative by checking that the aircraft responds correctly to rudder pedal movements 4 3 7 Run up Te APPLIED use the pedals Temperatures and Dressures CHECKED le SIBI E NE TT FULL RICH Magnetos check at 1 800 rpm 1 then 1 2 2
38. flight 25 kg about 35 litres Weight and centre of gravity assessment before flight Weight Lever arm Moment kg m m kg Empty weight 546 5 0 346 189 09 Pilot 85 0 6 51 Passenger 75 0 6 45 Usable fuel FWD tank 40 0 243 9 72 Totals weight and moment 746 5 0 3688 275 37 Balance of MAC in kg m and m kg B 1 5 x 100 24 59 Original issue 31 January 2002 Document 1000809 GB Page 6 8 Revision 0 WEIGHT AND CENTRE OF GRAVITY CAP 10C Weight and centre of gravity assessment after flight Weight Lever arm Moment kg m m kg Empty weight 546 5 0 346 189 09 Pilot 85 0 6 51 Passenger 79 0 6 45 Usable fuel FWD tank 15 0 243 3 65 Totals weight and moment 721 5 0 39 281 44 Balance 96 of MAC in kg m and m kg B 1 5 x100 26 01 96 850 800 750 Weight kg o o N Q c eo eo eo eo a a o a Q Balance 6 4 5 Loading in category U Weight Lever arm Moment kg m m kg Empty weight a1 b1 c1 a1xb 1 Pilot a2 0 55 to 0 65 c2 a2 x b2 Passenger a3 0 55 to 0 65 c3 a3 x b3 Usable fuel FWD tank a4 0 243 c4 a4 x b4 Usable fuel AFT tank a5 1 26 c5 a5 x b5 Luggage a6 1 1 c6 a6 x b6 Totals weight and moment A Xan B C A C Xcn Balance 96 of MAC kom Ge Ge B 1 5 x 100 Original issue 31 January 2002 Document 10
39. gine stops apply instructions from S Engine restart 3 4 8 Electrical failure Alternator failure and battery discharged Symptoms ammeter discharge Oil pressure dropping to O or unstable Original issue 31 January 2002 Document 1000809 GB Page 3 9 Revision 0 EMERGENCY PROCEDURES CAP 10C Horizon amp directional gyro warning flags Electrical equipment aaannnneannnnaeeneeeeaen off load as much as possible SITE immediately switch to front tank Fly back to airfield No further oil pressure and temperature reading No operation gauge stall warning horizon turn and bank indicator heading indicator radio VOR Pitot heating stand by electric pump electronic accelerometer Alternator failure Symptoms ammeter discharge Electrical equipment nasnnsnennnnneeneeeaen off load as much as possible Return to airfield while monitoring oil pressure Battery failure No way to detect in flight Only starter is disabled 3 5 SPIN Instructions for recovery from positive or negative unintentional spin Klee TE full opposite rudder opposite direction of rotation STEE nose up sector Lateral COPIFOL a eres tope rotae eodeni enia neutral Original issue 31 January 2002 Document 1000809 GB Page 3 10 Revision 0 EMERGENCY PROCEDURES CAP 10C As soon as spin stops set controls to neutral and pull out gently 3 6 EVACUATING THE AIRCRAFT Opening and releasing the canopy Seize the r
40. icant is 8 qt 7 6 I Original issue 31 January 2002 Document 1000809 GB Page 7 8 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C For longer engine service life you are advised to use mineral oil for the first 50 hours flight then dispersant oil 7 6 5 Ignition The engine is equipped with an ignition system for which high voltage is sent directly to the sparking plugs 7 6 6 Cooling The engine is designed to be air cooled Deflectors ensure overpressure on one side of the cylinders Overpressure forces the air through the cooling fins 7 6 7 Exhaust The CAP10B is equipped with a open exhaust 7 7 PROPELLER Two fixed pitch propellers are certified to be installed on the aircraft Hoffmann HO 29 HM 180 170 Evra 3 180 170 H5 F 7 8 FUEL SYSTEM The CAP10B is equipped with two tanks located in the fuselage The main tank is placed forward behind the firewall This tank is equipped with a valve device allowing for fuel supply in inverted flight The auxiliary tank is placed in the fuselage to the aft of the cockpit under the luggage hold Original issue 31 January 2002 Document 1000809 GB Page 7 9 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C Overall capacity is 154 litres 41 US Gal representing 111 kg 245 Ib fuel weight The FWD tank capacity is 75 litres 20 US Gal while that for the AFT tank is 79 litres 21 US Gal The FWD tank filling hole is located in front of
41. l aerobatic manoeuvres including spins are authorised spins are forbidden except for stalls lazy eights zooms and turns not exceeding 60 bank angle LOAD FACTORS CAT A CAT U Flaps retracted 6 4 5 Flaps retracted 4 4 1 8 OPERATIONAL LIMITATIONS CAP10 is certified for VFR condition only Flight in known icing conditions is forbidden Original issue 31 January 2002 Document 1000809 GB Page 2 13 Revision 0 LIMITATIONS CAP 10C Manoeuvres Single seater Twin seater Manoeuvres km h kt km h kt Loop 220 119 230 124 Half roll 210 113 220 119 Slow roll 220 119 230 124 Dynamic manoeuvre 160 86 160 86 Inverted loop 250 135 270 146 Stall turn Hammerhead 200 108 200 108 Navaids GPS limited to day VFR in view of the ground or the sea Original issue 31 January 2002 Revision 1 dated February 2003 Document 1000809 GB Page 2 14 LIMITATIONS CAP 10C 3 EMERGENCY PROCEDURES 3 1 estate eege 3 3 3 2 Recommended speed 3 3 3 3 Check lists E 3 3 34 System failures uode eebe 3 7 SS WE p mec 3 10 3 6 Evacuating the atrcraft ees KEEN KEREN 3 11 Original issue 31 January 2002 Document 1000809 GB Page 3 1 Revision 0 EMERGENCY PROCEDURES CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 3 2 Revision 0 EMERGENCY PROCEDURES CAP 10C 3 EMERGENCY PROCEDURES 3
42. l selector switch CLOSED ei Ge Wee PEE D OFF ELE OFF lt Al IDLE CUT OFF Master SWIRCM BE OFF CANO M UNLOCKED Normal landing apply brakes with care 3 3 7 Ditching Transmit Mayday Approach strong wind rough sea up wind Approach low wind strong swell parallel to swell mii C H FULL FLAPS Original issue 31 January 2002 Document 1000809 GB CAP 10C Page 3 6 Revision 0 EMERGENCY PROCEDURES CAP 10C Canopy eebe eebe UNLOCKED ee ele E LINE OF FLIGHT Face lte Protect face folded clothing Evac ati ON D if necessary let cockpit fill to balance pressure so you can open the canopy Life jackets icm inflated 3 4 SYSTEM FAILURES 3 4 1 Landing without elevator control If the elevator control breaks you can make a landing using the elevator trim tab If balance is less than or equal to 21 it is essential to land in clean configuration without extending the flaps 3 4 2 Landing without lateral control If the aileron control breaks you can control the aircraft using the rudder pedals on condition that you limit banking to a value of less than 15 Use the left pedal to bank left and vice versa 3 4 3 Propeller Blade breaks This leads to extremely strong vibrations BS ME REDUCE by bringing nose up sharply WAC MOTOS Me OFF Original issue 31 January 2002 Document 1000809 GB Page 3 7 Revision 0 EMERGENCY PROCEDURES C
43. l selector switch CLOSED Original issue 31 January 2002 Document 1000809 GB Page 3 4 Revision 0 EMERGENCY PROCEDURES CAP 10C Be gel PUSHED FULL THROTTLE RIESEN FULL RICH After engine shut down WEOMCTOS T OFF Alternator eee OFF Master switch censes OFF EVACUTE AIRCRAFT WITHOUT PRECIPITATION In flight Fuel selector switch CLOSED Throttle ever PUSHED FULL THROTTLE le te FULL RICH After engine shut down E ele Mac OFF Alternator EE C OFF Master switch seseeeessseesse OFF MAKE A FORCED LANDING or EVACUATE AIRCRAFT 3 3 5 Landing in countryside with engine running Choose a suitable landing area Transmit position message Wald TIGHT Final eielge ler engine on 100 105 km h FULL FLAPS As soon as landing accomplished Fuel selector switch CLOSED Original issue 31 January 2002 Document 1000809 GB Page 3 5 Revision 0 EMERGENCY PROCEDURES Contacts EEEN OFF Master switch eese OFF Dea CUT ee IDLE CUT OFF Normal landing apply brakes with care 3 3 6 Forced landing with engine shut down Speed MENT RC 140 km h Choose a landing area Troubleshoot Try to re start Transmit Mayday missis CNET T TIGHT Use flaps to shorten final approach as appropriate Final approach speed 120 km h Fue
44. lectrical equipment sssss 7 10 7 10 Lighting and beacon lights 7 10 7 11 Heating and ventilation 7 11 7 12 Pressure sample eerie ene eege 7 11 7 13 Stall warning system eeeeeesese 7 11 n DE e 7 11 7 15 Instrument pariel u oie eios tactus echo nume Gage usies dun iq onn cie 7 13 Original issue 31 January 2002 Document 1000809 GB Page 7 1 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 7 2 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C 7 AIRCRAFT AND SYSTEMS DESCRIPTION 7 1 AIRFRAME 7 1 1 Fuselage The fuselage made of spruce or hemlock is a truss type construction It comprises two sides assembled using four main frames including the vertical stabiliser the firewall and the fuselage wing junction frame In the forward part the truss type structure is reinforced by an inner skin of African mahogany plywood three millimetres thick The structure is covered with a dome of African mahogany plywood 2 millimetres thick 7 1 2 Wings The wings are made of a single part and are of the single spar type with two torsion boxes located on either side of the main spar The main spar has a wood carbon structure The ailerons and the flaps are secured to a
45. lls must always happen in clean configuration 4 3 18 ELT The emergency beacon must be removed by the pilot or a mechanic before any aerobatic flight 4 4SPINS Spinning on CAP10 is authorised with engine on idle in category A The loss of altitude is about 400 feet per rotation i e 120 metres Each spin rotation takes about 2 seconds 4 4 1 Instructions for recovery from positive or negative spin Positive spin R dd f o P full opposite rudder opposite to direction of rotation Elevator E nose up sector Lateral control nk roll towards spin Original issue 31 January 2002 Document 1000809 GB Page 4 15 Revision 0 NORMAL PROCEDURES CAP 10C Negative spin lee TE full opposite rudder opposite to direction of rotation Elevator EE nose up sector Lateral control codici nonis neutral If the rudder elevators or ailerons are not kept in the position indicated above recovery still remains possible but will tend to take more time In all events you must BE SURE TO KEEP DIRECTION OF RUDDER FULL OPPOSITE TO DIRECTION OF ROTATION 4 4 2 Influence of centre of gravity CAUTION Mainly by acting on the aircrafts attitude the centre of gravity has tremendous influence on CAP 10 s behaviour in spin Aft C G 24 to 26 Flat attitude about 50 indicated airspeeds of about 150 km h tendency to level out more to left than to right Fwd C G 22 to 20 Dive attitude up to 70 indicate
46. m from the aircraft plane of symmetry The reference chord length is 1 50 m C of G limit Category U Category A Front C of G 0 30 m 20 0 30 m 20 96 Rear C of G 0 45 m 30 0 39 m 26 6 4 1 Method Assess weights Make certain that the maximum weight is not exceeded Calculate the centre of gravity Make certain that balance is within limits Locate the point total weight and centre of gravity on the graph The point will then be within the weight and centre of gravity envelope Loading is acceptable if the point remains in the weight and centre of gravity envelope throughout the flight To make certain that the point remains within the envelope throughout the flight the pilot will calculate the centre of gravity at the end of the flight taking the fuel consumed into account Original issue 31 January 2002 Document 1000809 GB Page 6 5 Revision 0 WEIGHT AND CENTRE OF GRAVITY CAP 10C 6 4 2 Loading category A Weight Lever arm Moment kg m m kg Empty weight a1 b1 c1 7a1xb1 Pilot a2 0 55 to 0 65 c2 a2 x b2 Passenger a3 0 55 to 0 65 c3 a3 x b3 Usable fuel FWD tank a4 0 243 c4 a4xb4 Totals weight and moment A Xan B C A C Xcn Balance B o in kg m and m kg EE i Balance must be between 20 and 26 category A Maximum weight 780 kg 1 720 Ib Empty weight a1 use of aircraft data in its real configuration Take residual q
47. n KE Flight line 2n06 N 8n06 Original issue 31 January 2002 Document 1000809 GB Page 1 4 Revision 0 GENERAL 1 3 1 Wings CAP 10C Surface APCA cccccceececseseecescesseeeseeeees 10 85 m 3 02 e ere ee eee 8 06 m Wing aspect ratio E 5 96 DIC OR E 5 TWS lenene ee 0 Profile anette nee NETTE PN een nee NACA 23012 1 3 2 Ailerons Percentage of span sssuse 44 96 Mean relative width 29 Deflection re 25 2 Rue EEN 0 67 m 1 3 3 Flaps Percentage of span 32 Mean relative width 25 96 Deflection se 15 40 2 Unit area ERR RR 0 487 m 1 3 4 Fuselage Overall length 7m Internal width sssssse 1 054 m Height TO 2 34 m Blue PRI EE E OR 0 487 m Original issue 31 January 2002 Revision O Document 1000809 GB Page 1 5 GENERAL CAP 10C 1 3 5 Horizontal stabilizer Span EE 2 90 m Total surface are 1 86 m Horizontal stabilizer area 1 00 m Mobile area ertet repere oca 0 86 m Aspect ratio wa ccwescvwecsartovsiadaasvntsadensertersvered 4 52 Deflection T 29 42 1 3 6 Electrical elevator trim tab la ACE EE 0 057 m Deflection EE 17 2 1 3 7 Vertical stabilizer ago E 1
48. n for 1 one minute at 1 100 rpm Engine speed ENEE 1 100 rpm Original issue 31 January 2002 Document 1000809 GB Page 4 13 Revision 0 NORMAL PROCEDURES CAP 10C Oil Pressure getest eege CHECKED lt ft LEAN MagnetOS M TR OFF Alternator switch ccccseeeseeeeeeeeeeees OFF Anti collision eege ege Sege OFF Bier EXTENDED Master SWINCN ue ooi aoro ete be E Eid OFF Tank selector switch CLOSED 4 3 16 Manoeuvres For any aerobatics manoeuvre e the overall weight of the aircraft must be less than 780 kg 1 720 Ib e centre of gravity must be forward of 26 96 e afttank must be empty use fwd tank Minimum recommended speeds when beginning trick Single seater Two seater Manoeuvres km h kt km h kt Loop 220 119 230 124 Split S 210 113 220 119 Slow roll 220 119 230 124 Snap manoeuvre 140 76 140 76 Inverted loop 250 135 270 146 Wingover 200 108 200 108 Electrical flaps system switched off in category A A C equipped with an electrical tab switch system off in category A Original issue 31 January 2002 Document 1000809 GB Page 4 14 Revision 0 NORMAL PROCEDURES CAP 10C 4 3 17 Stalls You can perform stalls with or without engine in all permitted weight and C G configurations Generally stalling is not preceded by warning signs Only the indicator light comes on in a positive stall In negative flight sta
49. n operation caution limit ngine speer 500 to 2700 2 700 rpm Oil temperature 60 to 118 118 C F 140 to 244 244 cM 6610204 20410260 260 iC F 151 to 399 399 to 500 500 Oll pressure 1 76 to 4 22 4 22 to 6 33 7 03 bar Original issue 31 January 2002 Document 1000809 GB Page 2 7 Revision 0 LIMITATIONS CAP 10C 2 6 MISCELLANEOUS INSTRUMENT MARKINGS 2 6 1 Accelerometer Green arc Yellow arc Red arc 5 to 6 6 to 6 2 39109 3510 45 4 5to 6 2 2 6 2 Voltmeter and ammeter Instrument Red line Green arc Yellow arc Red line Lower limit Normal use Range for uu Upper limit caution Voltmeter V 12 12 13 8 13 8 Ammeter A 2 2 to 52 53 to 60 60 2 7 WEIGHTS Category U Category A Maximum takeoff 830 k 780 k weight g g Maximum landing weight 800 kg 780 kg Maximum load in 50 kg distributed forbidden luggage compartment evenly Pilots 2 2 with parachutes Fuel 75 154 Fwd tank only 110 8 kg 54 kg Original issue 31 January 2002 Document 1000809 GB Page 2 8 Revision O LIMITATIONS CAP 10C 2 8C G LIMITS Weight kg Centring Limits Category U Category A Centre of gravity 20 30 20 26 Maximum weight 830 kg 780 kg 2 9 FLIGHT Cat U intentional spins forbidden Cat A aerobatics authorised powered spins forbidden CAU
50. nciator lights 26 Trim flaps switch Original issue 31 January 2002 Document 1000809 GB Page 7 13 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C 27 Flap control Panel light warning light 13 Side slip indicator inverted flight Eee Audio panel COM1 NAV GPS T VHF2 XPDR Circuit breakers Fuel gauges voltmeter ammeter Avionics master switch Instrument post lights 14 15 16 Oil temperature oil pressure 32 EGT CHT 7 15 2 Tanks selector switch The tank selector switch is located on the central lower part of the instrument panel It has three positions Closed FWD tank AFT tank In the position where no tank is selected the tank selector pallet prevents access to the start pushbutton Original issue 31 January 2002 Document 1000809 GB Page 7 14 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION 8 HANDLING SERVICING AND MAINTENANCE 1 1 Introduction MERE 3 Original issue 31 January 2002 Document 1000809 GB Page 8 1 Revision 0 HANDLING SERVICING AND MAINTENANCE CAP 10C Page intentionally left blank Original issue 31 January 2002 Document 1000809 GB Page 8 2 Revision 0 HANDLING SERVICING AND MAINTENANCE CAP 10C 1 1 INTRODUCTION Writing in progress Original issue 31 January 2002 Document 1000809 GB Page 8 3 Revision 0 HANDLING SERVICING AND MAINTENANCE CAP 10C 9 SUPPLEMENTS 1 1 Introduction MERE 3 Original issue 31 January
51. ng the mixture knob over two complete turns Also see the Engine User s Manual 4 3 12 Descent lt oul FULL RICH DEI THE FULLEST Engine speed 1 700 to 1 800 rpm Recommended speed 200 km h 108 kt Pitot heat MK according to weather conditions 4 3 13 Approach Speed flaps 18 150 km h 81 kt Speed flaps 40 2 0 eccccessesseeeeeeeeeees 120 km h 65 kt Original issue 31 January 2002 Document 1000809 GB Page 4 12 Revision 0 NORMAL PROCEDURES CAP 10C 4 3 14 Interrupted landing Go around Configuration cccceccceesseeeeeeeeeeeeeeees FULL THROTTLE Full flaps Best rate of climb speed Vy 135 km h 73 kt RECTUS 15 To obtain the best rate of climb Vz max keep full power and check the engine speed for 2 350 rpm retract flaps adjust speed for best rate of climb i e 160 km h 86 kt and check pressures and temperatures In category A these performance levels are improved in relation to reduction in weight 4 3 15 Engine shut down Parking brake esse ON If brakes are used intensively during landing and taxiing up to the parking area do not apply the parking brake before the wheels have cooled down use chocks Electrical equipment seers OFF Cut off test 1 000 rpm DONE then 1 2 For a short taxiing period before shut down let the engine ru
52. nverted flight an artificial horizon aturn and bank indicator adirectional gyro aturn and bank indicator ball and needle a stopwatch a second mechanical accelerometer 7 4 LANDING GEAR AND GROUND HANDLING The landing gear is conventional main landing gear auxiliary tailwheel Original issue 31 January 2002 Document 1000809 GB Page 7 5 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C 7 4 1 Main landing gear The hydropneumatic main landing gear with a track of 2 06 metres has two wheels equipped with disc brakes and associated hydraulic controls The wheels are equipped with 380x150 mm tyres inflated to 2 bars You can activate the parking brake using a handle on the instrument panel 7 4 2 Auxiliary landing gear The auxiliary landing gear is equipped with a solid tyre tailwheel measuring 6 x 200 mounted on a rubber shock absorber Orientation of the tailwheel is controlled by deflection of the rudder Slaving is ensured through two springs For ground manoeuvres the roller is automatically disconnected as soon as its orientation exceeds twenty degrees 7 5 HABITABILITY You access the cockpit through the jettisonable canopy by sliding it backwards Two handles on the forward central part one on the inside and the other on the outside mean you can open it and close lock it A single red handle on the inside can be used to jettison the canopy in a single movement The cockpit has two se
53. re ratio Setting is implemented using a micrometric screw Press the central part of the knob to disconnect this screw The far rear position of this control corresponds to the leanest mix choke The start button is a pushbutton activating the electric starter This pushbutton which is located on the lower central part of the instrument panel is not accessible when the tank selector switch is in the closed position Original issue 31 January 2002 Document 1000809 GB Page 7 7 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C The magneto selector switch controlled by a removable key is placed above the starter pushbutton It has four positions 0 off 1 magneto 1 2 magneto 2 1 2 magnetos 1 and 2 CAUTION You can only withdraw the key when it is in the 0 position 7 6 3 Engine instrumentation The CAP10B must be equipped with the following instruments at least tachometer rev counter fuel flow indicator manifold pressure indicator oil pressure indicator oil temperature indicator fuel gauges It can be equipped optionally with acylinder temperature indicator an exhaust gas temperature indicator an ammeter avoltmeter 7 6 4 Lubrication system The lubrication system allows for normal lubrication of the engine in inverted flight with minimum loss of oil including during advanced aerobatic manoeuvres with significant and frequent negative load factors The quantity of lubr
54. secondary spar This comprises two booms made of spruce or hemlock joined by two birch plywood webs The ribs are built according to a truss type structure made of spruce or hemlock A birch plywood skin 1 5 millimetres thick covers the wings The ailerons occupy 43 8 of the wingspan Two pallets on each aileron ensure Static balance Original issue 31 January 2002 Document 1000809 GB Page 7 3 Revision 0 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C 7 1 3 Horizontal stabiliser The horizontal stabiliser is of conventional design and comprises a stabiliser and an elevator equipped with an electrically controlled tab The single spar type stabiliser features a torsion box and is secured to the fuselage at four points It rests on a spruce or hemlock cradle allowing for its setting to be adjusted The spar built of spruce or hemlock is also conventionally designed It includes two booms joined by two birch plywood webs to which the ribs are glued The skin is made of African mahogany plywood The elevator is designed identically and is made of a single part hinged at three points on the stabiliser It is completely coated in plywood and has a recessed tab electrically controlled by the pilot It is partially balanced and is aerodynamically compensated by two horn balances 7 1 4 Vertical stabiliser The vertical stabiliser which belongs through its construction to the fuselage is of the single spar type with a torsion box 7
55. uantities unusable of oil and fuel into account The empty weight a1 the lever arm b1 and the moment c1 must be taken from the aircraft weight and centre of gravity report in the A C Individual Inspection Record I I R R I C Weight of fuel use 0 72 kg litre 6 Ib gal Hourly consumption in aerobatics about 44 Uh Moment weight x lever arm A sum of a1 to a4 C sum of c1 to c4 Original issue 31 January 2002 Document 1000809 GB Page 6 6 Revision 0 WEIGHT AND CENTRE OF GRAVITY CAP 10C Me MM MM T T T T T T T T T T T Weight kg Balance 6 4 3 Example of maximum forward balance in category A CAUTION An extremely light pilot flying alone with the main tank full may reach the forward balance limit Weight Lever arm Moment kg m m kg Empty weight 550 0 297 163 4 Pilot 83 0 6 49 8 Passenger 0 0 6 0 Usable fuel FWD tank 40 0 243 9 72 Totals weight and moment 673 0 302 203 4 Balance of MAC e in kg m and m kg B 1 5 x 100 20 2 Original issue 31 January 2002 Document 1000809 GB Page 6 7 Revision 0 WEIGHT AND CENTRE OF GRAVITY CAP 10C a h k i i i i i T W i i i i i i Weight kg Balance 6 4 4 Example of maximum aft balance in category A CAP 10s with battery aft have higher aft balance Pilot 85 kg Co pilot 75 kg FWD tank 40 kg about 55 litres Fuel consumption planned during
56. um speed with flaps extended flaps 160 86 99 extended Ver e exceed 340 184 241 Speed never to be exceeded NE Maximum Speed not to be exceeded in normal use normal 300 162 186 operation Vno Never exceed Speed never to be exceeded for positive for snap 160 86 99 2 negative snap manoeuvres manoeuvres Van Original issue 31 January 2002 Document 1000809 GB Page 2 4 Revision 0 LIMITATIONS CAP 10C 2 3 ANEMOMETRIC MARKINGS All markings are only valid in Category A Value or range Mark indicated Meaning airspeed IAS Flaps extended range 79 to 160 km h The lower limit is the stalling speed at White maximum weight in landing configuration 43 to 86 kt speed are 49 te 99 mph Vso H The upper limit is the maximum speed with flaps extended Vez Normal operation range The lower limit is the stalling speed at Green oo RIT maximum weight 780kg in clean 51 to 162 kt speed arc configuration Vs 59 to 186 mph que a The upper limit is the maximum cruising speed Vyo 300 to 340 km h Must be flown with caution and only in Yellow smooth air 162 to 184 kt Deeg speed arc Lower limit Vno 186 to 211 mph ERC Upper limit Vue Red limit 340 km h Maximum speed for use Vye line 184 kt 211 mph Yellow 235 km h Va acne 127 kt Maximum speed at which you can fully 146 mph deflect the control surfaces 2 4 ENGINE LIMITATIONS Manufacturer esee LYCOMING Model PM AEI

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