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CAP 10B

1. 7 11 7 13 Stall warning system 7 11 Z 14 AVIONICS uuu 7 11 7 15 Instrument panel 7 13 Edition 1 30 August 2010 Document 4EXNO22 Page 7 1 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION DYN ERO CAP 10C AK GROUP Page intentionally left blank Edition 1 30 August 2010 Document 4EXNO22 Page 7 2 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION JA CAP 10C DYNZ XE ANKK lt GROUP 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 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 sp
2. 3 11 Edition 1 30 August 2010 Document 4EXNO22 Page 3 1 Revision 1 AK GROUP 3 EMERGENCY PROCEDURES EMERGENCY PROCEDURES CAP 10C CAP 10C DYN XERO AK GROUP Page intentionally left blank Edition 1 30 August 2010 Document 4EXNO22 Page 3 2 Revision 1 EMERGENCY PROCEDURES JA CAP 10C DYNZSE AK GROUP 3 EMERGENCY PROCEDURES 3 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 RPM2 1700rTBID E S Integrate down wind leg land immediately HPM 1 700 rpm Z lt 300 feet landing along A C axis 30 Edition 1 30 August 2010 Document 4EXNO22 Page 3 3 Revision 1 EMERGENCY PROCEDURES CAP 10C DYN XERO sROLIP 300 lt Z lt 600 feet quick troubleshooting forced landing ahead of aircraft 1203 Z gt pen eeeeianeeebieehe gees 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
3. 1 cm MIX P CN LEAN MAagnel S EE CROP DES 1 2 Edition 1 30 August 2010 Document 4EXNO22 Page 4 7 Revision 1 NORMAL PROCEDURES A CAP 10C DYNZSERO AK G sROUP eirig det T EN on request Mixture er RICH as soon as engine is running Throttle lever set for 1 000 rpm 4 3 4 Starting up hot engine Master switch ON Anti collision light as appropriate ON Throttle lever 4 to 5 cm MITUT E e rene RE EEEE LEAN Magnetos 1 2 Stateira E EEE EENES on request EIERE RICH as soon as engine is running Throttle lever set for 1 000 rpm 4 3 5 Engine heating Engine speed 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 CHECKED Cut off test magnetos DONE Edition 1 30 August 2010 Document 4EXNO22 Page 4 8 Revision 1 NORMAL PROCEDURES JA CAP 10C DYNZ AXE AK GROUP
4. AEIO 360 B2F Max engine speed and max continuous Edition 1 30 August 2010 Revision 1 2 700 rpm Document 4EXNO22 Page 2 5 LIMITATIONS DYN XERO ew GSGROUP 2 4 1 Oil pressure Normal 4 22 bar to 6 33 bar Precaution 1 76 bar to 4 22 bar Maximum on start up 7 03 bar bz ar gU jag eR E RH 118 244 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 Maximum 260 500 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 91 96 Edition 1 30 August 2010 Document 4EXNO22 Page 2 6 Revision 1 LIMITATIONS DYN XERO e GROUP 2 4 7 Oil characteristics Ambient temperature Characteristic above 15 59 F SAE 50 from 12 10 4 F to 32 90 SAE 40 P from 18 0 4 F to 21 70 SAE 30 P below 12 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
5. ON Alternator switch ON Battery charge CHECKED Magnetos 1 2 Flight controls Elevaior eee eececeecececcececeececeecececaececaeneees free in correct direction Lateral control free in correct direction Rudder pedals free in correct direction Elevator tab CHECKED then NEUTRAL o pe uuu man Sanu FULL FLAPS then 15 Equipment Mechanical accelerometer reset Altimeter SET Vie OECD SET Cockpit GAMO DY T Closed and locked Seat belt and harnesses ATTACHED Brakes ee eee en ae LM EL LA S EE RELEASED Edition 1 30 August 2010 Document 4EXNO22 Page 4 10 Revision 1 NORMAL PROCEDURES JA CAP 10C DYNZ XE ANKK lt GROUP 4 3 9 Takeoff Throttle lever FULL THROTTLE Maximum engine speed CHECKED 2 250 50 rpm BE Te m HS from 50 km h 27 kt Takeoff speed 110 km h 59 kt NOTE Propeller torque is to the left on this aircraft Engine speed check 2300 rpm 50rpm Initial climb M pH N 140 km h 76 kt gi P
6. 450 m 1 476 ft BE udi eT 350 m 1 148 ft Edition 1 30 August 2010 Document 4EXNO22 Page 5 6 Revision 1 PERFORMANCE DYN XERO n sFROUP 5 5 1 Influences of altitude and temperature Zp pressure altitude T temperature in degrees C elsius Temp Weight 680 kg 1 500 Ib Weight 730 kg 1 609 Ib Zp Takeoff run 15m Takeoff run 15m C 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 30 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 751 2464 1005 3297 Temp Weight 780 kg 1 720 Ib Weight 830 kg 1 830 Ib Zp Takeoff run 15m Takeoff run 15m C m ft m ft m ft m ft 15 5 287 942 372 1221 304 997 394 1293 0 0 32 306 1004 395
7. Red line Yellow arc Green arc Yellow arc Red line Instrument Lower Fly with Normal Fly with Upper limit caution operation caution limit ngine spog 500 to 2700 2 700 rpm Oil temperature 60 to 118 118 F 140 to 244 244 muni NR 6610204 20410260 260 p 151 to 399 3991o 500 500 C F el pressure 1 76 to 4 22 4 22 to 6 33 7 03 bar Edition 1 30 August 2010 Document 4EXNO22 Page 2 7 Revision 1 LIMITATIONS A CAP 10C DYNZSERO AK GROUP 2 6 MISCELLANEOUS INSTRUMENT MARKINGS 2 6 1 Accelerometer Green arc Yellow arc Red arc 5to6 6 to 6 2 3 91095 3510 45 4510 62 2 6 2 Voltmeter and ammeter Instrument Red line Green arc Yellow arc Red line Lower limit Normal use Range for caution Upper limit 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 weight 830 kg 780 kg Maximum landing weight 800 kg 780 kg Maximum load in 50 kg distributed ob daan luggage compartment evenly Pilots 2 2 with parachutes Fuel 75 1541 Fwd tank only 110 8 kg 54 kg Edition 1 30 August 2010 Document 4EXNO22 Page 2 8 Revision 1 LIMITATIONS DYN ERO CAP 10C AK GROUP 2 8 C G LIMITS Weight kg Centring Limits Category U Category A Centre of gravity 20 30 20 26 Maximum weight 830 kg 78
8. OI GOO IN CO OO O 7 15 3 Lower panel p n n n TR m Se Se W i WW i M dap cde Ju ff Si Ehe c r _ _ aoa ZEE BUE MEE FL E d 7 Circuit breakers Switches 9 10 11 12 ooi ic N Edition 1 30 August 2010 Document 4EXNO22 Page 7 14 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION DYN XERO n sFROUP 7 15 4 Switches Oo J O C1 O N 7 15 5 Circuit breakers 666606060600 Q9 QD Ce 1 Ai 10 A 2 A 11 A 3 A 12 A 4 A 13 A 5 A 14 A 6 A 15 A 7 A 16 A 8 A 17 A 9 A 18 A Edition 1 30 August 2010 Document 4EXNO22 Page 7 15 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION DYN ERO CAP 10C AK GROUP 7 15 6 Tanks selector switch The tank selector switch is located on the central lower part of the instrument panel It has three positions Closed s FWD tank AFT tank In the position where no tank is selected the tank selector pallet prevents access to the start pushbutton Edition 1 30 August 2010 Document 4EXNO22 Page 7 16 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION CAP 10C DYNZXERO AK GROUP 8 HANDLING SERVICING AND MAINTENANCE Edition1 30 August 2010 Document 4EXNO22 Page 8 1 Revision 1 H
9. aba RETRACTED 91 m 300 ft Normal climb 160 km h 86 kt clean config 4 3 10 Climb speed Best climb angle 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 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 Edition 1 30 August 2010 Document 4EXNO22 Page 4 11 Revision 1 NORMAL PROCEDURES A CAP 10C DYNZSERO AK G sROUP 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 rom 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 50T generally 2 graduations below the maximum observed temperature Where there is no EGT we advise you to enrich the mixture by rotating the mixture knob over tw
10. JA CAP 10C DYNZ XE ANKK lt GROUP 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 Takeoff 110 km h 59 kt Normal climb 160 km h 86 kt Best climb angle 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 p e d 200 km h 108 kt Approach 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 Edition 1 30 August 2010 Document 4EXNO22 Page 4 3 Revision 1 NORMAL PROCEDURES A CAP 10C DYNZSERO AK G sROU FP 4 3 CHECK LIST OF NORMAL PROCEDURES 4 3 1 Pre flight inspection Cockpit Make certain cockpit is clean Master switch OFF Alternator switch OFF Magnetos OFF Fuel selector switch OPEN FWD TANK CAUTION For aerobat
11. full in the direction of spin up to the rotation stop Negative spin R dd r ge aes full opposite direction of rotation up to the rotation stop zz i o REC aaa nose up sector up to the rotation stop Aileron control eene 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 aircraft s attitude the centre of gravity has tremendous influence on CAP10 s behaviour in spin Aft C G 24 to 26 Flat attitude about 509 indicated airspeeds of ab out 150 km h tendency to level out more to left than to right Edition 1 30 August 2010 Document 4EXNO22 Page 4 16 Revision 1 NORMAL PROCEDURES DYN XERO n sROUP Fwd C G 22 to 20 Dive attitude up to 70 indicated 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 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 lef
12. Alternator switch ON Battery charge CHECKED Electrical equipment ON Rear tank test 5 min if use intended Takeoff is authorised when the oil temperature reaches the green zone 4 3 6 Taxiing Parking brake 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 SE APPLIED use the pedals Temperatures and pressures CHECKED IECH eege ee FULL RICH Magnetos check at 1 800 rpm 1 then 1 2 2 then 1 2 Permitted engine drop 125 rpm per magneto Maximum difference between magnetos 50 rpm e e test Magnetos cut off test Mixture LEAN then RICH Edition 1 30 August 2010 Document 4EXNO22 Page 4 9 Revision 1 NORMAL PROCEDURES A CAP 10C DYNZSERO AK G sROUP 4 3 8 Vital actions before takeoff Engine Tank selector switch FWD Aulonomy CHECKED NEE yqasayisiusohakispauphya SET MAX POWER Master switch
13. ANEMOMETRIC CALIBRATION in kt Co eo pe eo cO eo Co CH Calibrated airspeed Vc kt o CH N o e CH 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 Edition 1 30 August 2010 Document 4EXNO22 Page 5 4 Revision 1 PERFORMANCE JA CAP 10C DYNZ AXE AK GROUP 5 3 SAFETY FACTORS Takeoff Landing Conditions Increase in Increase in distance to Factor distance from Factor 15 m obstacle 15 m obstacle 10 aircraft weight 20 12 10 96 14 increase Increase of airfield A altitude by 1000 ft 10 i SS b 10 increase in 10 14 5 1 05 ambient temperature Dry grass 1 short 13 cm 20 1 2 20 1 2 length 13 25 cm 25 96 1 25 30 96 1 3 Wet grass 1 short 25 96 1 25 30 96 1 3 long 30 96 1 3 40 96 1 4 Rising Dropping 2 slope 10 1 1
14. DYNZ WE AK GROUP Eeer UNLOCKED Touchdown LINE OF FLIGHT Face protection Protect face folded clothing Evacuation if necessary let cockpit fill to balance pressure so you can open the canopy Life jackets 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 2196 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 ss M REDUCE by bringing nose up sharply Magnetos OFF Edition 1 30 August 2010 Document 4EXNO22 Page 3 7 Revision 1 EMERGENCY PROCEDURES DYN ERO CAP 10C AK GROUP When IAS lt 100 km h the propeller stops e T M M 140 km h Mixture emen IDLE CUT OFF Fuel selector switch CLOSED MAKE FORCED LANDING or EVACUATE AIRCR
15. title amp signature 04 October 2012 EASA 10041663 Edition 1 30 August 2010 Document 4EXNO22 Page Revision 1 LOG OF REVISIONS DYN XERO n AK GROUP Page intentionely left blank Edition 1 30 August 2010 Document 4EXNO22 Page II Revision 1 LOG OF REVISIONS DYNZXERO un AK GROUP CONTENTS Sections 1 GENERAL 2 LIMITATIONS 3 EMERGENCY PROCEDURES 4 NORMAL PROCEDURES 5 PERFORMANCE 6 WEIGHT AND BALANCE 7 AIRPLANE AND SYSTEMS DESCRIPTION 8 HANDLING SERVICING AND MAINTENANCE 9 SUPPLEMENTS Original issue 30 August 2010 Document 4EXNO22 Page Ill Revision 1 CONTENTS DYN XERO geg AK GROUP Page intentionely left blank Edition 1 30 August 2010 Document 4EXNO22 Page IV Revision 1 CONTENTS DYNZXERO AK GROUP CAP 10C 1 GENERAL 1 1 Introduction 1 3 1 2 Presentation 1 3 1 3 Three view drawings eese 1 4 1 4 PowWer plant ec 1 7 1 5 PROD GUM e 1 7 TO tel 1 7 TZ o e 1 8 1 8 Certified maximum weights 1 8 1 9 Characteristic weights 1 9 1 10 Cockpit Dimensions 1 9 1 11 Characteristic l
16. 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 30 86 792 2598 1063 3488 840 2756 1125 3691 Edition 1 30 August 2010 Document 4EXNO22 Page 5 7 Revision 1 PERFORMANCE Revision 1 Z CAP 10C DYNZSERO AK GROUP 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 power 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 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
17. Fuel A 2 10 2 14 Wing outer skin color requirement 2 11 2 15 Various limitations 2 11 2 16 ADS Ss 2 11 Edition 1 30 August 2010 Document 4EXNO22 Page 2 1 Revision 1 LIMITATIONS DYNZAERO E AK GROUP Page intentionally left blank Edition 1 30 August 2010 Document 4EXNO22 Page 2 2 Revision 1 LIMITATIONS JA CAP 10C DYNZ XE ANKK lt GROUP 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 2 LIMIT SPEEDS 2 2 1 Category U IAS Speed km h kt mph Observations Maximum full Maximum speed at which you can fully deflection V4 EO EE deflect the control surfaces Maximum Maximum speed with flaps extend ed flaps 160 86 99 extended Ver um exceed 340 184 211 Speed never to be exceeded NE Maximum Speed not to be exceeded in normal normal 300 162 186 operation operation Vno Edition 1 30 August 2010 Document 4EXNO22 Page 2 3 Revision 1 LIMITATIONS A CAP 10C DYNZSERO AK GI sROUP 2 2 2 Category A IAS Speed km h kt mph Observations Maximum full Maximum speed at which you can fully deflection V4 Bed Rd 3426 deflect the control surfaces Maximum
18. 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 All aerobatic manoeuvres including spins are authorised spins are forbidden except for stalls lazy eights zooms and turns not exceeding 60 bank angle LOAD FACTORS CATA 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 Edition 1 30 August 2010 Document 4EXNO22 Page 2 13 Revision 1 LIMITATIONS DYNZXERO ui AK GROUP 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 Edition 1 30 August 2010 Document 4EXNO22 Page 2 14 Revision 1 LIMITATIONS DYNZXERO SEE Zo nna Beene ee ee eee 3 3 3 2 Recommended speed 3 3 xe E 3 3 344 System failures 3 7 OI Un uu 3 10 3 6 Evacuating the aircratft
19. 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 Edition 1 30 August 2010 Document 4EXNO22 Page 7 6 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION JA CAP 10C DYNZ AXE AK lt C GROUP This injection engine develops a nominal power of 180 hp at 2 700 rpm for a fuel consumption of 14 5 GPH 55 l h It develops 135 hp at 2 450 rpm 7596 consumption 11 GPH 42 l h 117 hp at 2 350 rpm 65 consumption 8 5 GPH 32 l 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 onthe 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 mixture ratio Setting is implemented using a micrometric screw Press the central part o
20. 0 From 18 to 21 C 0 4 to 69 8 F SAE 30 Below 12 10 4 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 ERR kg Ib kg Ib Maximum takeoff weight 830 1 930 780 1 720 Maximum landing weight 800 1 764 7 80 1 720 Maximum load in luggage compartment 50 110 Forbidden Edition 1 30 August 2010 Document 4EXNO22 Page 1 8 Revision 1 GENERAL CAP 10C DYNZXERO AK GROUP 1 9CHARACTERISTIC WEIGHTS Empty weigoht 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 0 98 m 3 21 ft 1 11CHARACTERISTIC LOADS Wing loading with weight of 830 kg 1930 lb 76 5 kg m 16 5 Ib Sq ft Weight power ratio 180 hp 4 5 kg hp 10 6 Ib hp 1 128 YMBOLS ABBREVIATIONS AND TERMINOLOGY CAUTION means that failure to observe the corresponding proc
21. 0 kg 2 9 FLIGHT Cat U intentional spins forbidden Cat A aerobatics authorised powered spins forbidden CAUTION 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 Edition 1 30 August 2010 Document 4EXNO22 Page 2 9 Revision 1 LIMITATIONS A CAP 10C DYNZSERO AK GI sROUP 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 154 litres 75 litres Fwd tank 79 litres Aft tank Usable quantity Fwd tank 72 litres Aft tank 78 litres Unusable fuel 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 fligh
22. 1 PERFORMANCE GEN WE E E e E 5 3 5 2 Anemometric calibration 5 3 5 3 Safety e 5 5 5 4 Saiallspeed 5 6 55 Takeoff distance 5 6 5 6 Rate of climb 5 8 5 7 Level flight performance cruise 5 8 58 Landing distance eee er ne ee oa 5 9 5 9 Glide characteristics 5 9 5 10 Performance in icing conditions 5 9 Edition 1 30 August 2010 Document 4EXNO22 Page 5 1 Revision 1 PERFORMANCE DYN XERO cap toc AK GROUP Page intentionally left blank Edition 1 30 August 2010 Document 4EXNO22 Page 5 2 Revision 1 PERFORMANCE JA CAP 10C DYNZ XE AFK C GROUP 5 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 240 220 200 180 160 140 Calibrated airspeed Vc in km h 120 100 100 120 140 160 180 200 220 240 Indicated airspeed Vi in km h Edition 1 30 August 2010 Document 4EXNO22 Page 5 3 Revision 1 PERFORMANCE A CAP 10C DYNZSERO AK G sROUP 7
23. 10 1 1 Tailwind component B e 10 km h 20 96 1 2 20 96 1 2 Wet or snow covered 25 or more 1 25 or 25 or more 1 25 or ground Additional safety factor 1 33 1 43 if raw data increased distances 1 Increased effect for taxiing distances on takeoff landing Any change in the technique normally used in operation is likely to lead to Factors are accumulative and must be multiplied Edition 1 30 August 2010 Revision 1 Document 4EXNO22 Page 5 5 PERFORMANCE A CAP 10C DYNZSERO AK GROUP 5 4 STALL SPEED 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 Sea level standard atmosphere weight of 830 kg paved runway Takeoff speed 110 km h 59 kt 15 m clearance speed 115 km h 62 kt Takeoff run and 15 m clearance
24. 26 0 Luggage 40 1 5 60 Totals weight and moment 760 0 417 316 92 Balance 96 of MAC B 5 in kg m and m kg 0 417 1 5 x100 27 8 o Edition 1 30 August 2010 Document 4EXNO22 Page 6 11 Revision 1 WEIGHT AND CENTRE OF GRAVITY DYN ERO CAP 10C AK GROUP co a o co e o Ann SS sat UL 3 _ o gt N a e a o o o Weight kg o e o Balance 96 6 5 LIST OF EQUIPMENT The list of airborne instruments is included in the A C Individual Inspection Record I 1 R Edition 1 30 August 2010 Document 4EXNO22 Page 6 12 Revision 1 WEIGHT AND CENTRE OF GRAVITY JA CAP 10C DYNZ XE ANKK lt GROUP 7 AIRCRAFT AND SYSTEMS DESCRIPTION fal PRUNING m 7 3 7 2 Flight controls D 7 4 73 Flight instruments 7 5 7 4 Landing gear and ground handling 7 5 Ge scglsme 7 6 7 6 Power dn e 7 6 Of PROC OT aa 7 9 K Fu e lsystem uu I 7 9 7 9 Electrical equipment 7 10 7 10 Lighting and beacon lights 7 10 7 11 Heating and ventilation 7 11 7 12 Pressure sample
25. 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 4EXNO22 CAP 10C 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 Celsiu s 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 Fahren heit F Page 1 11 GENERAL JA CAP 10C DYNZ XE ANKK lt GROUP 2 LIMITATIONS HUI cup et c 2 3 2 2 Limit speedS e 2 3 23 An mometric markings 2 5 2 4 Engine limitations 2 5 2 5 Engine instrument markings 2 7 2 6 Miscellaneous instrument markings 2 8 2 7 Welight8 u 2 8 28 C G Limits 2 9 29 Flight 2 9 2 10 Limit load Factors 2 10 2 11 CreW Pc 2 10 2 12 Flight conditions 2 10 2 13
26. AFT 3 4 4 Engine high cylinder temperature Climbing Stop climb Engine speed reduce Mixture full rich Oil temperature monitor Return to airfield Level flight Engine speed REDUCE lees INCREASE RICHNESS If t fails to drop land as soon as possible 3 4 5 Oil failure Pressure zero temperature normal or rising Engine speed REDUCE to 1 700 rpm Avoid accelerations and engine speed changes Troubleshoot for possible electrical failure Edition 1 30 August 2010 Document 4EXNO22 Page 3 8 Revision 1 EMERGENCY PROCEDURES JA CAP 10 DYNZ WE AK GROUP Return to closest airfield while monitoring parameters If engine seizes before airfield land in countryside Pressure zero temperature zero light off Fuel gauges check If gauges on 0 check circuit breaker 3 4 6 Fuel Low reading on fuel flow meter Electric pump ON Mixture full rich Engine speed optimum to avoid vibrations Return to closest airfield with engine out type integration High re
27. AIRCRAFT FLIGHT MANUAL amp PILOT OPERATING HANDBOOK DYN XERO CAP 10B AIRCRAFT FLIGHT MANUAL APPROVED AIRPLANE FLIGHT MANUAL amp PILOT S OPERATING HANDBOOK Manufacturer AUPA DYN AERO 19 rue de l aviation 21121 DAROIS FRANCE Serial No Registration No 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 Le DYNZXERO uu AK GROUP LOG OF REVISIONS Revision Date ber Revised pages Description of revision 0 30 August 2010 All Edition 1 passage APEX DYN AVIATION Date of revision 0 Name title amp signature 30 August 2010 C ROBIN HOD Een n pag Revised pages Description of revision number 1 04 10 2012 Page 2 12 Revision 1 Spin recovery CAP10C 3 10 3 11 4 7 4 15 4 16 6 6 Recommendation regarding pilot and 6 9 6 11 6 12 passenger seat belts locking 7 15 7 16 Update the information regarding luggage lever arm and Instrument panel Date of revision 1 Name
28. ANDLING SERVICING AND MAINTENANCE DYN E RO CAP 10C AK GROUP Page intentionally left blank Edition1 30 August 2010 Document 4EXNO22 Page 8 2 Revision 1 HANDLING SERVICING AND MAINTENANCE CAP 10C DYNZXERO AK GROUP 9 SUPPLEMENTS Edition 1 30 August 2010 Document 4EXNO22 Page 9 1 Revision 1 SUPPLEMENTS CAP 10C DYN XERO AK GROUP Page intentionally left blank Edition 1 30 August 2010 Document 4EXNO22 Page 9 2 Revision 1 SUPPLEMENTS
29. AVITY JA CAP 10C DYNZ XE ANKK lt GROUP 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 Edition 1 30 August 2010 Document 4EXNO22 Page 6 3 Revision 1 WEIGHT AND CENTRE OF GRAVITY DYN XERO AK GROUP CAP 10C 6 3 1 Example of weighing and centre of gravity report PROCES VERBAL DE PESEE ET DE CENTRAGE N DE SERIE Serial n IMMATRICULATION Registration Couleur DOMAINE DE MASSE et CENTRAGE Masse kg MASSE ET CENTRAGE A Dm Empty weight and moment ROUE PD L1 Main R wheel m kg m K Masse kg Bras de Levier m Momenti Lever arm Moment Corde de r f rence 1 50 Reference chord 1 50 R f rence verticale bord d attaque du profil de r f
30. EXNO22 Page 7 8 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION JA CAP 10C DYNZ XE ANKK lt GROUP 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 Edition 1 30 August 2010 Document 4EXNO22 Page 7 9 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION Z CAP 10C DYNZ XERO AK CI sROU JP 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 the windshield a
31. Maximum speed with flaps extended flaps 160 86 99 extended Ver vil exceed 340 184 211 Speed never to be exceeded 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 en 86 99 9 negative snap manoeuvres manoeuvres VAD Edition 1 30 August 2010 Document 4EXNO22 Page 2 4 Revision 1 LIMITATIONS DYN AE GROUP 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 E 79 to 160 km h The lower limit is the stalling speed at ite 43 to 86 kt maximum weight in landing configuration speed arc 49 w GE Vso emp The upper limit is the maximum speed with flaps extended Vrz Normal operation range The lower limit is the stalling speed at Green EC maximum weight 780kg in clean speed arc 59 to 186 mph configuration Vs P The upper limit is the maximum cruising speed V o 300 to 340 km h Must be flown with caution and only in ellow 162 to 184 kt smooth air speed arc 186 to 211 mph Lower limit Vno P Upper limit Vye Red limit rd Maximum speed for use Vye ue 211 mph Mellow 235 km h VA imitiine 127 kt Maximum speed at which you can fully 146 mph deflect the control surfaces 2 4 ENGINE LIMITATIONS Manufacturer LYCOMING Model
32. ROUP A sum of a1 to a4 C sum of c1 to c4 NI e eo Weight kg o c eo 16 18 20 22 24 26 28 30 32 Balance 96 6 4 4 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 B 1 5 x 100 20 2 in kg m and m kg Edition 1 30 August 2010 Revision 1 Document 4EXNO22 WEIGHT AND CENTRE OF GRAVITY DYN ERO CAP 10C AK GROUP Weight kg Q o gt N co co e a e a e a e eo eo eo eo eo Cc a o a e o Balance 96 6 4 5 Example of maximum aft balance in category A CAP10s 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 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 96 of MAC SR SEET EC B 1 5 x 100 2 24 59 Edition 1 30 August 2010 Doc
33. ading 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 engine stops apply instructions from Engine restart 3 4 8 Electrical failure Alternator failure and battery discharged Symptoms ammeter discharge Oil pressure dropping to 0 or unstable Edition 1 30 August 2010 Document 4EXNO22 Page 3 9 Revision 1 EMERGENCY PROCEDURES JA CAP 10 DYNZXERO AK GROUP Horizon amp directional gyro warning flags Electrical equipment off load as much as possible F uel22 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 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 Engine on idle immediately geo D passa full opposite direction of rotation up to the rotation stop Ed
34. der fuselage Closed and locked Tank eM CLOSED and LOCKED Edition 1 30 August 2010 Document 4EXNO22 Page 4 6 Revision 1 NORMAL PROCEDURES JA CAP 10C DYNZ XE AKK GROUP 4 3 2 Before starting up Parking brake ON SLET E TOT ADJUSTED and LOCKED Pilot and passenger seat belts ATTACHED Putting belt s lock above the harnesses lock is preferable Master switch OFF Alternator switch OFF Magnetos OFF Electrical equipment OFF Flaps trim switch as appropriate ON Avionics switch as appropriate ON MIXU SPA LEAN Cockpit heating CLOSED 4 3 3 Starting up cold engine Master switch ON aiio TERRE TEES RETRACTED CHECKED Anti collision light ON Throttle lever PUSHED FULL THROTTLE Mixture FULL RICH Tank selector switch FWD Electric pump ON Fuel flow meter CHECKED Electric pump STOP Throttle lever_
35. edure 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 Edition 1 30 August 2010 Document 4EXNO22 Page 1 9 Revision 1 GENERAL DYNZXERO um 3F2C UJFP 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 Va Manoeuvring speed maximum speed at which you can fully deflect the control surfaces Van Speed never to be exceeded for positive or negative snap manoeuvres Vee Maximum speed flaps extended Vne Speed never to be exceeded Vno Maximum speed in normal operation Vs Stalling speed Vso Stalling speed in landing configuration flaps fully extended maximum weight Vx Best climb angle speed Vy Best rate of climb speed speed allowing maximum climb speed to be obtained Vz max Vz Vertical speed ISA International Standard atmosphere airis a perfect dry gas the sea level temperature is 15 59F the sea level pressure is 1013 2
36. ement 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 Edition 1 30 August 2010 Document 4EXNO22 Page 1 3 Revision 1 GENERAL CAP 10C DYNZXERO AK GROUP 1 3 THREE VIEW DRAWINGS mE lt 4n33 Flight line lt lt lt Tn gt Gin Flight line b N pap Edition 1 30 August 2010 Document 4EXNO22 Page 1 4 Revision 1 GENERAL DYNZXERO AK GROUP 1 3 1 Wings CAP 10C Revision 1 Surface area 10 85 m SE 8 06 m Wing aspect ratio 5 96 B7 a 1 e LTE 9 Io 0 isi MR RR REN NACA 23012 1 3 2 Ailerons Percentage of span 44 96 Mean relative width 2996 Deflection 25 2 Unit area 0 67 m 1 3 3 Flaps Percentage of span 32 96 Mean relative width 25 96 Def
37. f 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 Edition 1 30 August 2010 Document 4EXNO22 Page 7 7 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION A CAP 10C DYNZSERO AK GI sROU JP 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 O 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 lubricant is 8 qt 7 6 I Edition 1 30 August 2010 Document 4
38. ics the rear tank must be empty and the ELT must be removed Flight controls FREE in CORRECT DIRECTION Engine controls FREE Battery contact ON Stall warning indicator CHECKED Warning lights CHECKED Fuel gauges CHECKED Battery contact OFF Seat belts and harnesses CHECKED Canopy attachment CHECKED Release handle CHECKED Before getting down from aircraft Fueltank sireci visual inspection F el Cap DS closed and locked Edition 1 30 August 2010 Document 4EXNO22 Page 4 4 Revision 1 NORMAL PROCEDURES JA CAP 10C DYNZ XE AK C GROUP Left wing gi EE hinges and control AlS ON E hinges and control Balance plates and deflection Eegeregie clean not clogged Main landing gear shock absorber checked and tyre inflated Underwing inspection door locked Fwd fuselage Tank drain checked Pince checked Lower inspection door closed and locked Cowl left door closed and loc
39. ion vide Empt Pilote pilot Passager Passenge Essence avant Fuel main Bagages Baggages Avion charg Loaded CENTRAGE Balance Tableau de chargement Loading Cas de chargement Essence paxe zess Plein essence Full operating 2Px To T Charge utile kg Contr le Date et visa Date et Visa Document 4EXNO22 Page 6 4 WEIGHT AND CENTRE OF GRAVITY JA CAP 10C DYNZ XE ANKK lt GROUP 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 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 96 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 Edition 1 30 August 2010 Document 4EXNO22 Page 6 5 Revisio
40. 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 Edition 1 30 August 2010 Document 4EXNO22 Page 7 4 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION JA CAP 10C DYNZ AXE AK GROUP 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 a magnetic compass an electronic accelerometer The following instruments can also be installed a vertical speed indicator aside slip indicator ball for inverted flight an artificial horizon aturn and bank indicator adirectional gyro aturn and bank indicator bal
41. ition 1 30 August 2010 Document 4EXNO22 Page 3 10 Revision 1 EMERGENCY PROCEDURES CAP 10C DYNE AK GROUP Elevator nose up sector up to the rotation stop Aileron control eene neutral 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 red 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 Edition 1 30 August 2010 Document 4EXNO22 Page 3 11 Revision 1 EMERGENCY PROCEDURES DYN XERO e GROUP 4 NORMAL PROCEDURES SMELL I poculo Me 4 3 4 2 Speeds 4 3 43 Check list of normal procedures 4 4 E SPINS u n u S SS P u us 4 15 Edition 1 30 August 2010 Document 4EXNO22 Page 4 1 Revision 1 NORMAL PROCEDURES DYNZAERO E AK GROUP Page intentionally left blank Edition 1 30 August 2010 Document 4EXNO22 Page 4 2 Revision 1 NORMAL PROCEDURES
42. ked Propeller condition and attachment EE eegene condition and attachment AININ eT EE free Oil level m checked 6 qt maximum for aerobatics Cowl right door closed and locked Riqht winq Main landing gear shock absorber checked and tyre inflated Underwing inspection door locked Edition 1 30 August 2010 Document 4EXNO22 Page 4 5 Revision 1 NORMAL PROCEDURES A CAP 10C DYNZSERO AK G sROUP Aileron hinges and control Balance plates and deflection qc asnuman sns ns s Duman hinges and control Rear right fuselage Static head WEE clean and not clogged PATRI RIRs C NINE NT VISUAL INSPECTION EE locked Horizontal stabiliser Horizontal stabiliser ATTACHMENT Elevator and vertical stabiliser hinges and control Deflection and cable tension Rudder b zo PR rnnr hinges and control Elevator tab hinges and control Tail wheel Tail wheel rubber Good condition Conjugation springs Condition and operation Aft left fuselage Statie DO assa ace dete sro ee CLEAN NOT CLOGGED Tank drains qty 2 CHECKED Inspection door un
43. 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 Edition 1 30 August 2010 Document 4EXNO22 Page 5 8 PERFORMANCE JA CAP 10C DYNZ AXE AK C GROUP 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 120 km h 65 kt Landing run and 15 m clearance 600 m 1 969 ft Landing riil EOS 360 m 1 180 ft 5 9 GLIDE CHARACTERISTICS I or n 140 km h 76 kt flaps retracted SINK E 4 m s 787 ft min WIRE io us osa HEROICO NEAN about 10 5 10PERFORMANCE IN ICING CONDITIONS Flight in known icing conditions is forbidden Edition 1 30 August 2010 Document 4EXNO22 Page 5 9 Revision 1 PERFORMANCE DYN XERO GROUP 6 WEIGHT AND CENTRE OF GRAVITY CAP 10C 61 of ouo 6 3 6 2 Register of weight and centre of gravity 6 3 6 3 Weighing procedure 6 3 6 4 Weight and centre of gravity breakdown 6 5 65 List of equipment E 6 12 Edition 1 30 August 2010 Document 4EXNO22 Page 6 1 Revision 1 WEIGHT AND CENTRE OF GRAVITY DYNZAERO E AK GROUP Page intentionally left blank Edition 1 30 August 2010 Document 4EXNO22 Page 6 2 Revision 1 WEIGHT AND CENTRE OF GR
44. l and needle astopwatch a second mechanical accelerometer 7 4 LANDING GEAR AND GROUND HANDLING The landing gear is conventional main landing gear auxiliary tailwheel Edition 1 30 August 2010 Document 4EXNO22 Page 7 5 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION A CAP 10C DYNZSERO AK G sROUP 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 seats side by side between which there is the electric elevator trim control and its indicator Each seat is
45. l equipment OFF Cut off test 1 000 rpm DONE then 1 2 For a short taxiing period before shut down let the engine run for 1 one minute at 1 100 rpm Edition 1 30 August 2010 Document 4EXNO22 Page 4 13 Revision 1 NORMAL PROCEDURES DYN XERO AK CSI sROUP P Engine speed 1 100 rpm Oil pressure CHECKED Mixture LEAN Magnetos OFF Alternator switch OFF Anti collision OFF EE EXTENDED Master switch 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 aft tank 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 electrica
46. l tab switch system off in category A Edition 1 30 August 2010 Document 4EXNO22 Page 4 14 Revision 1 NORMAL PROCEDURES JA CAP 10C DYNZ XE AK C GROUP 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 stalls 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 4 SPINS 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 Intended flat spin should be started at an altitude sufficient to allow crew emergency evacuation at not lower than 3000 ft 4 4 1 Instructions for recovery from positive or negative intentional spin Positive spin R dder ar nee M full opposite direction of the rotation up to the rotation stop Elevator nose up sector up to the rotation stop Aileron control in the direction of spin up to the rotation stop Edition 1 30 August 2010 Document 4EXNO22 Page 4 15 Revision 1 NORMAL PROCEDURES A CAP 10C DYNZSERO AK G sROUP Aileron control in case of flat spin
47. lection 15 40 2 Ji area u naa ku eee te ier een seer Ree oe 0 487 m 1 3 4 Fuselage Overall length 7m Internal width 1 054 m iz p irme recor Camere eee mane erty 2 34 m Unt AlE T 0 487 m Edition 1 30 August 2010 Document 4EXNO22 Page 1 5 GENERAL DYN ERO CAP 10C AK GROUP 1 3 5 Horizontal stabilizer EEN 2 90 m Total surface area 1 86 m Horizontal stabilizer area 1 00 m Mobile area 0 86 m Aspect ratio 4 52 DSTO CUO NERONE NM 25 2 1 3 6 Electrical elevator trim tab Surface 0 057 m Detflection 17 2 1 3 7 Vertical stabilizer als Sone vs PER 1 590 m Total area 1 316 m Mobile area 0 659 m RI ee cccatcese ss secccsteenddaeriecesecccetiaessoeeds 18 2 1 3 8 Landing gear Main ic ee eer eee nents nee error 2 06 m Wheel dimension 380 x 150 Tyre inflation pressure 2 bars Shock absorber inflation pressure 8 bars Auxiliary Tyre dimensi
48. long 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 7 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 10 LIGHTING AND BEACON LIGHTS The CAP10B can be equipped with the following lights Anti collision Rotating Landing light Navigation lights Edition 1 30 August 2010 Document 4EXNO22 Page 7 10 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION JA CAP 10C DYNZ XE ANKK lt GROUP 7 11HEATING 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 fu
49. mb 29 92 inches of mercury thetemperature gradient from seal level to the altitude where T is 56 5 C 69 7 f is 0 00198 C foot and 0C a bove OAT Outside Ambient Temperature Std Standard temperature temperature of 15 59F at sea level with a T 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 Edition 1 30 August 2010 Document 4EXNO22 Page 1 10 Revision 1 GENERAL DYNZXERO AK GROUP 1 13CONVERSION Nautical miles nm Statute miles mile Feet ft Inches in Inches in Feet min US gallons Gallons imp Quarts US Knots kt Pounds per square inch psi Pounds per square inch psi Inches of mercury in Hg Pound Ib Degrees Fahrenheit E 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 ft min Edition 1 30 August 2010 Revision 1 X x x X X X X x X x x x x x x X x x x x x x X X x x x x x Se 1 852 1 609 0 305 0 0254 25 4 0 00508 3 785 4 546 0 946 1 852 0 0689 68 95 33 86 0 453 5
50. n 1 WEIGHT AND CENTRE OF GRAVITY A CAP 10C DYNZSERO AK G sROUP P 6 4 2 Lever arms Depending on the seat position the Pilot and Passenger lever arms are between 0 55 m seat forward position and 0 65 m seat rear position The Luggage lever arm is between 1 2 m forward on the luggage shelf and 1 8 m aft on the luggage shelf Lever arm of the Usable fuel FWD tank 0 243 m Lever arm of the Usable fuel REAR tank 1 260 m 6 4 3 Loading category A Weight Lever arm Moment kg m m kg Empty weight al b1 cl alxbl 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 5 in kg m and m kg B 1 5 x 100 Yo 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 quantities 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 Edition 1 30 August 2010 Document 4EXNO22 Page 6 6 Revision 1 WEIGHT AND CENTRE OF GRAVITY DYN ERO CAP 10C AK G
51. ng Choose a suitable landing area Transmit position message Harnesses o cs Ree rie uu a een TIGHT Final approach engine on 100 105 km h FULL FLAPS As soon as landing accomplished Fuel selector switch CLOSED Edition 1 30 August 2010 Document 4EXNO22 Page 3 5 Revision 1 EMERGENCY PROCEDURES DYNZXERO AK GROUP Contacts E OFF Master switch OFF MEUM Eege Eed IDLE CUT OFF Normal landing apply brakes with care 3 3 6 Forced landing with engine shut down Speed I 140 km h Choose a landing area Troubleshoot Try to re start Transmit Mayday e TIGHT Use flaps to shorten final approach as appropriate Final approach speed 120 km h Fuel selector switch CLOSED Magnetos OFF Alternator OFF EISE u anna IDLE CUT OFF Master switch OFF CANO cats ee UNLOCKED Normal landing apply brakes with care 3 3 7 Ditching Transmit Mayday CAP 10C Approach strong wind rough sea up wind Approach low wind strong swell parallel to swell gc E FULL FLAPS Edition 1 30 August 2010 Document 4EXNO22 Page 3 6 Revision 1 EMERGENCY PROCEDURES JA CAP 10
52. o complete turns Also see the Engine User s Manual 4 3 12 Descent Mixture FULL RICH LE etc THE FULLEST Engine speed 1 700 to 1 800 rpm Recommended speed 200 km h 108 kt lxi cu P according to weather conditions 4 3 13 Approach Speed flaps 15 150 km h 81 kt Speed flaps 40 s 120 km h 65 kt Edition 1 30 August 2010 Document 4EXNO22 Page 4 12 Revision 1 NORMAL PROCEDURES DYNE un AFI GROUP 4 3 14 Interrupted landing Go around Configuration FULL THROTTLE Full flaps Best rate of climb speed Vy 135 km h 73 kt gr T MM u suwas 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 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 Electrica
53. oads 1 9 1 12 Symbols abbreviations and terminology 1 9 1 13 Conversion le 1 11 Edition 1 30 August 2010 Document 4EXNO22 Page 1 1 Revision 1 GENERAL DYN XERO um AK GROUP Page intentionally left blank Edition 1 30 August 2010 Document 4EXNO22 Page 1 2 Revision 1 GENERAL CAP 10C DYNZXERO AK GROUP 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 the 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 arrang
54. on 6 x 200 Edition 1 30 August 2010 Document 4EXNO22 Page 1 6 Revision 1 GENERAL DYN AK GROUP 1 4 POWER PLANT Manufacturer Model type Power and rpm LYCOMING AEIO 360 B2F CAP 10C Power Engine speed nominal 180 hp 2 700 rpm cruise 75 96 2 450 rpm economy cruise 65 96 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 grade 1 6 2 Quantities Overall quantity In FWD tank AFT tank Edition 1 30 August 2010 Revision 1 154 litres 41 US Gal 111 Kg 245 Ib 54 kg 119 Ib 56 9 kg 125 Ib Document 4EXNO22 75 litres 20 US Gal 79 litres 21 US Gal Page 1 7 GENERAL DYN ERO CAP 10C AK GROUP Usable quantity 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 16 50 TOES coercet torte Gb ba tuns mineral oil Subsequently detergent oil Recommended viscosity according to air temperature Temperature Viscosity Above 15 C 59F SAE 50 From 1 to 392 30 2 to 89 6F SAE 4
55. rence situ 1 30 m du plan de sym trie de l avion Mise a niveau rail de verri re horizontal C G datum Levelling Conditions de la pes e plein d huile quipements figurants au Registre de essence non utilisable comprise dans la masse Weighing conditions full operating equipement listed in the inspection unusable fuel inclued in empty Avion vide CENTRAGE Balance CENTRAGE EXTREME Most foreward C El ment Masse kg Element Weight Bras de Levier m Lever arm Avion vide Empt Pilote pilot Passager Passenge Essence avant Fuel main Bagages Baggages Avion charg Loaded CENTRAGE Balance En cas de possibilit de d passement des limites ci dessus remplir le tableau de chargement qui les limitations d emport de passagers d essence et de pour differents cas de In case of excess fill out loading table which grives weight of passengers fuel and baggage in each case of Nota 1 V rifier le centrage pour l emport de bagages de carburant 1 Check balance if you take baggage and optional 2 En plus du 3 Facultif 2 In addition to 3 Optional Edition 1 30 August 2010 Revision 1 ROUE PG L 1 Main L wheel ROULETTE Tailwheel Essence non utilis Unusable Moment m kg El ment Moment m K Element Weight CENTRAGE EXTREME Most aft C Masse kg Bras de Levier m Lever arm Moment m kg Moment m K Av
56. ruce 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 Edition 1 30 August 2010 Document 4EXNO22 Page 7 3 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION A CAP 10C DYNZSERO AK GI sROUP P 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 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
57. selage 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 14 AVIONICS The originally fitted radionavigation equipment includes as a minimum aVHF transceiver The aircraft can also be equipped with the following instruments transponder alticoder intercom Edition 1 30 August 2010 Document 4EXNO22 Page 7 11 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION DYN ERO CAP 10C AK GROUP GPS VOR ILS An ELT is offered as an option The equipment configuration for each CAP10 forms part of its Individual Inspection Record IR The instruments specific to an aircraft are described in section 9 Supplements Edition 1 30 August 2010 Document 4EXNO22 Page 7 12 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION DYN ERO CAP 10C AK GROUP 7 15INSTRUMENT PANEL This section is customised according to the aircraft 7 15 1 Upper panel 1 2 3 4 5 6 7 8 9 10 17 16 15 14 13 12 11 10 ie 1 N Co Wu 6 5 7 Side slip indicator inverted 16 flight 9 18 Edition 1 30 August 2010 Document 4EXNO22 Page 7 13 Revision 1 AIRCRAFT AND SYSTEMS DESCRIPTION DYN ERO CAP 10C AK GROUP 7 15 2 Lights
58. switch OPEN FULLEST TANK Master switch CONNECTED ON Ee Ile E 1 2 Throttle lever MID TRAVEL REH 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 Fuel selector switch CLOSED Edition 1 30 August 2010 Document 4EXNO22 Page 3 4 Revision 1 EMERGENCY PROCEDURES JA CAP 10 DYNZXE AK GROUP Throttle lever E edema errecklaceeessacsen PUSHED FULL THROTTLE Wl ti FULL RICH After engine shut down Magnetos OFF Alternator a RE ba E RAE OFF Master switch OFF EVACUTE AIRCRAFT WITHOUT PRECIPITATION In flight Fuel selector switch CLOSED Throttle lever PUSHED FULL THROTTLE Wl u Saul uuu sayasqa FULL RICH After engine shut down Magnetos OFF PCW ANON unn unus as OFF Master switch OFF MAKE A FORCED LANDING or EVACUATE AIRCRAFT 3 3 5 Landing in countryside with engine runni
59. t 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 Edition 1 30 August 2010 Document 4EXNO22 Page 4 17 Revision 1 NORMAL PROCEDURES DYN AERO m F lt O UP In the event of engine shut down during spin immediately apply the instructions for recovery from spin then apply the instructions for engine re start SECTION 3 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 Edition 1 30 August 2010 Document 4EXNO22 Page 4 18 Revision 1 NORMAL PROCEDURES JA CAP 10C DYNZ XE AFK C GROUP 5
60. t 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 Edition 1 30 August 2010 Document 4EXNO22 Page 2 10 Revision 1 LIMITATIONS DYN ERO CAP 10C AK GROUP 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 Edition 1 30 August 2010 Document 4EXNO22 Page 2 11 Revision 1 LIMITATIONS DYN ERO CAP 10C AK GROUP Trim control Manoeuvring speed VA CAT A VA z 235 km h CAT U VA z 200 km h Procedure to recover from unintentional spin Unintentional spin recovery Engine idle immediately Full opposite rudder up to the rotation stop Pitch up sector up to the rotation stop Ailerons in neutral As soon as spins stops set controls to neutral and pull out gently Edition 1 30 August 2010 Document 4EXNO22 Page 2 12 Revision 1 LIMITATIONS JA CAP 10C DYNZ XE ANKK lt GROUP Limitations INDICATED AIRSPEEDS CAT A CAT U Vue 340 km h 184 kt Vu 340 km h 184 kt VA 235 km h 127 kt VA 200 km h 108 kt Vso 79 km h 43 kt
61. ument 4EXNO22 Page 6 8 Revision 1 WEIGHT AND CENTRE OF GRAVITY DYN ERO CAP 10C AK GROUP 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 75 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 Weight kg Balance 96 6 4 6 Loading in category U Weight Lever arm Moment kg m m kg Empty weight al b1 cl alxb1 Pilot a2__ 0 55 to 0 65 c2 a2 x b2 Passenger a3 0 55to 0 65 c3 a3 x b3 Usable fuel FWD tank a4 0 243 c4 a4xb4 Usable fuel AFT tank a5 1 26 c5 ab x b5 Luggage a6 1 2 to 1 8 c6 a6 x b6 Totals weight and moment A Xan B C A C Xcn Balance 96 of MAC B in kg m and m kg B 1 5 x 100 Yo Edition 1 30 August 2010 Document 4EXNO22 Page 6 9 Revision 1 WEIGHT AND CENTRE OF GRAVITY DYN ERO CAP 10C AK GROUP 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
62. 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 I 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 gt N e a e o o o Weight kg o a o gt e CH Cc a a e eo 0 22 24 26 28 3 Balance 96 0 32 Edition 1 30 August 2010 Document 4EXNO22 Page 6 10 Revision 1 WEIGHT AND CENTRE OF GRAVITY JA CAP 10C DYNZ SERO AK GROUP 6 4 7 Example of calculation in category U Pilot 85 kg Co pilot 75 kg R servoir avant 25 kg about 35 litres AFT tank 45 kg about 63 5 litres Luggage 40 kg Fuel consumption planned during flight 60 kg about 83 litres Weight and centre of gravity assessment before 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 25 0 243 6 08 Usable fuel AFT tank 45 1 26 56 7 Luggage 40 1 5 60 Totals weight and moment 820 0 451 369 97 Balance 96 of MAC B in kg m and m kg 0 451 1 5 x100 30 Yo 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

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