EADS Socata TB 20 Pilot'S Information Manual Download

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Summary of Contents for TB 20

Page 1: ...PILOT S INFORMATION MANUAL TE20...

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Page 3: ...ence and commercial security of its contents must be maintained It must not be used for any purpose other than that for which It is supplied nor may information contained In it be disclosed to unautho...

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Page 5: ...TABLE OF CONTENTS SECTION GENERAL 1 LIMITATIONS 2 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT AND BALANCE 6 DESCRIPTION 7 AIRPLANE HANDLING SERVICING AND MAINTENANCE 8 SUPPLEMENTS...

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Page 7: ...AND ENTRY DIMENSIONS 1 3 1 3 1 3 1 4 1 4 1 5 1 5 1 5 1 5A SYMBOLS ABBREVIATIONS AND TERMINOLOGY 1 6 GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS 1 6 METEOROLOGICAL TERMINOLOGY 1 7 ENGINE POWER TERMINOLOGY...

Page 8: ...I SECTION 1 GENERAL 2 17 m 71 4 775 m 25 5 1 SOCATA MODEL TB 20 I I lj E j Y I I I I 1 2 1 1 I 1 91 m 63 2 E to I l 00 I m Figure 1 1 THREE VIEW DRAWING Pre MOD 151 r June 30 1988 Revision 8...

Page 9: ...SOCATA MODEL TB 20 E I E m m m June 30 1988 Revision 8 I 2 17 m I 7 1 4 7 72 m 25 4 1 91 m 6 32 F I Figure 1 1A THREE VIEW DRAWING Post MOD 151 SECTION 1 GENERAL 1 2A...

Page 10: ...SECTION 1 GENERAL 1 2B INTENTIONALLY LEFT BLANK SOCATA MODEL TB 20 June 30 1988 Revision 8...

Page 11: ...upplements of this I Manual and any airplane country specifics are given in Section Specifics hereto DESCRIPTIVE DATA ENGINE Number of engines 1 Engine Manufacturer AVCO LYCOMING Engine Model Number I...

Page 12: ...ther Refer to Section 8 Handling servicing and maintenance for additional information OIL CAUTION DO NOT MIX DIFFERENT BRANDS OR TYPES OF OIL Oil grades specifications and Viscosity Reference LYCOMING...

Page 13: ...400 kg Landing 3086 Ibs 1400 kg Weight in Baggage Compartment 143 Ibs 65 kg refer to Section 6 for cargo loading instructions AIRPLANE WEIGHTS Refer to the Weight sheet included in the I I A Individua...

Page 14: ...nt Height Minimum Compartment Height Entry Width Entry Height 11 5A Pre MOD 151 4 10 ft 1 25 m 3 45 ft 1 05 m 2 95 ft 0 90 m 2 20 ft 0 67 m 2 03 ft 0 62 m 1 35 ft 0 41 m 2 10 ft 0 64 m 1 44 ft 0 44 m...

Page 15: ...SOCATA MODEL TB 20 June 30 1988 Revision 11 INTENTIONALLY LEFT BLANK SECTION 1 GENERAL 1 5B...

Page 16: ...ering Speed is the maximum speed at which full or abrupt control movements may be used Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position Ma...

Page 17: ...wer is the power developed by the engine Manifold Pressure is a pressure measured in the engine s induction system and is expressed in inches of mercury in Hg Revolutions Per Minute is engine speed AI...

Page 18: ...the number of digits Center of gravity C G C G Limits IUseful Load Is the point at which an airplane or equipment would balance if suspended Its distance from the reference datum is found by dividing...

Page 19: ...ust gas temperature ELT Emergency Locator Transmitter EVAP FAN Evaporator fan EXC Energization F PRESS Fuel pressure It Foot Feet ft min Feet per minute HI High HOR Electric horizon hPa Hectopascal hr...

Page 20: ...ator ATe transponder Communications Transceivers Distance Measuring Equipment Emergency Locator Transmitter High Frequency Horizontal Situation Indicator Instrument Flight Rules Instrument Landing Sys...

Page 21: ...de H hPa 0 1013 2 2000 942 1 4000 875 0 6000 811 9 8000 752 6 10000 696 8 12000 644 3 14000 595 2 16000 549 1 18000 505 9 20000 465 6 January 31 1988 SECTION 1 GENERAL METRIC UNITS TO IMPERIAL AND U S...

Page 22: ...29 09 29 12 29 15 29 18 29 20 990 991 992 993 994 995 996 997 998 999 29 23 29 26 29 29 29 32 29 35 29 38 29 41 29 44 29 47 29 50 1000 1001 1002 1003 1004 1005 1006 1007 1008 1009 29 53 29 56 29 59 29...

Page 23: ...2 5 POWER PLANT LIMITATIONS 2 6 STARTER OPERATION LIMITS 2 7 POWER PLANT INSTRUMENT MARKINGS 2 8 WEIGHT LIMITS 2 9 CENTER OF GRAVITY LIMITS 2 9 MANEUVER LIMITS 2 9 DESIGN LIMIT LOAD FACTORS 2 10 KIND...

Page 24: ...SECTION 2 LIMITATIONS 2 2 INTENTIONALLY LEFT BLANK SOCATA MODEL TB 20 January 31 1988...

Page 25: ...is replaced by VNO in 23 729 a Condition 23 143 as for landing gear extension must be checked up to VNO This airplane must be flown in compliance with the limits specified by placards or markings and...

Page 26: ...xcept in smooth air and then only with care Do not make abrupt or full VA Maneuvering Speed 130 129 control movements above this speed Maximum Flap V E Extended Speed Do not exceed these Take off 130...

Page 27: ...is maximum weight White Arc 59 103 Vso in landing configuration Upper limit is maximum speed permissible with flaps extended Normal Operating Range Lower limit is maximum weight Green Arc 70 150 VS1...

Page 28: ...erature 500 F 260 C Maximum Oil Temperature 244QF 118 C Oil Pressure Minimum 25 psi 1 7 bar Maximum 115 psi 7 9 bars Fuel Pressure Minimum 0 1 psi 7 hPa Maximum 8 psi 552 hPa Fuel Grades See Fuel Limi...

Page 29: ...peration sequence is limited to 10 seconds SECTION 2 LIMITATIONS Should several sequences be necessary respect following spacing 1st sequence wait 1 minute 2nd sequence wait 1 minute 3rd sequence wait...

Page 30: ...18 C Fuel Pressure 0 1 psi 0 1 to 8 psi 8 psi Fuel flow 2 Gall hr 2to25Gallhr 25Gallhr Oil Pressure 25 to 60 psi 1 25 psi and 60 to 90 psi 100 psi 90 to 100 psi r r Oil Pressure 25 to 55 psi 2 25 psi...

Page 31: ...aft of datum at all weights Reference datum Front face of firewall Straight line variation between points Leveling pOint Upper fuselage spar NOTE It is the responsibility ofthe pilot to insure that t...

Page 32: ...168 Litres each 88 8 U S Gallons 336 Litres 86 2 U S Gallons 326 Litres 2 6 U S Gallons 10 Litres Usable fuel up to unusable fuel can be safelyusedduring allnormalairplane maneuvers FOR STEEP NOSE DOW...

Page 33: ...ight with doors open or ajar is prohibited VACUUM GAGE MARKINGS If installed SECTION 2 LIMITATIONS MARKING CORRESPONDING VALUE Green Red lines I June 30 1988 Revision 11 Normal operating from 4 4 to 5...

Page 34: ...ED IN FORM OF PLACARDS MARKINGS AND FLIGHT MANUAL INVERTED FLIGHT AEROBATIC MANEUVERS INTENTIONAL SPINS ICING CONDITIONS MAXIMUM TAKE OFF AND LANDING WEIGHT DESIGN MANEUVERING SPEED VA LIMIT SPEED VNE...

Page 35: ...ONS MAXIMUM TAKE OFF AND LANDING WEIGHT DESIGN MANEUVERING SPEED VA LIMIT SPEED VNE FLAPS EXTENDED MAXIMUM SPEED YFE FLAPS TAKE OFF FLAPS LANDING LANDING GEAR EXTENDED MAXIMUM SPEED VLE LANDING GEAR O...

Page 36: ...Baggage door 65 kg 143 Ibs MAXIMUM 4 Near fuel tank caps FOR LOADING INSTRUCTIONS SEE Vti IGHT AND BAlANCE DATA IN FUGHT MANUAL CARBURANT FUEL KRAFTSTOFF AVGAS 100 LL 43 1 US_ 35 9 UK GAL 163L 5 On th...

Page 37: ...r Markinos in U S Gallons LOG GEAR E M E R G PRESS TO PULL LEFT FUEL SELECTOR RIGHT 43 1 US GAL 431 US GAL c PRESS 0 I c Markings in Litres I June 30 1988 Revision 11 LEFT FUEL SELECTOR RIGHT PRESS 16...

Page 38: ...ION 2 LIMITATIONS 8 Near the wing flap control FLAPS i N I r CTED TAKE 0 NG 9 Near the stabilator tab position indicator I 2 16 NOSE DOWN r I TAKEI OFF I I NOSE SOCATA MODEL TB 20 June 30 1988 Revisio...

Page 39: ...ODEL TB 20 10 Near the rudder trim CRUISE DII T c 2E RUDDER TAB OFF 11 Near landing gear configuration and control 0 0 g N 0 0 g I June 30 1988 Revision 11 A T N A T A I PRESS PULL SECTION 2 LIMITATIO...

Page 40: ...SECTION 2 LIMITATIONS 2 18 INTENTIONALLY LEFT BLANK SOCATA MODEL TB 20 June 30 1988 Revision 11...

Page 41: ...Y AFTER TAKE OFF 3 4 ENGINE FAILURE IN FLIGHT 3 5 LOW OIL PRESSURE LOW FUEL FLOW ENGINE VIBRATION 3 6 3 6 3 6 PROPELLER GOVERNOR FAILURE 3 6 FORCED LANDINGS 3 7 EMERGENCY LANDING WITHOUT ENGINE POWER...

Page 42: ...S PROCEDURE 3 14 LANDING WITH A LANDING GEAR NOT LOCKED 3 14 LANDING WITHOUT STABILATOR CONTROL RADIO MASTER SWITCH FAILURE ELECTRICAL FAILURE IMMEDIATE ACTION ELECTRICAL EOUIPMENT FAILURE ALTERNATOR...

Page 43: ...t planning and good pilot judgment can minimize enroute weather emergencies However should any emergency develop the guidelines in this section should be considered and applied as necessary to correct...

Page 44: ...T OFF OFF OFF OFF ENGINE FAILURE IMMEDIATELY AFTER TAKE OFF I 3 4 Airspeed Mixture Fuel selector Fuel pump If engine does not start Mixture Fuel selector Fuel pump Landing gear lever Land Magneto sele...

Page 45: ...Alternate Air FULLY PULLED If the engine does not start Mixture Throttle Starter When the engine runs windmilling NOTE IDLE CUT OFF 1 2 OPEN ENGAGE if propeller stopped SLOWLY ENRICH UNTIL RE START En...

Page 46: ...lector OPERATING CHECKED SWITCH TANKS ENGINE VIBRATION Engine vibration is generally due to defective spark plugs or too rich a mixture Mixture RESET If vibration persists RPM SET FOR MINIMUM VIBRATIO...

Page 47: ...giving location and intentions ADJUSTED and SECURE AS REQUIRED IDLE CUT OFF OFF OFF AS REQUIRED When the landing is secured Flaps Approach speed Main switch LANDING 70 76 KIAS OFF PRECAUTIONARY LANDIN...

Page 48: ...nd SECURE Airspeed 70 76 KIAS Flight path Parallel to swells Before touch down Main switch OFF Mixture IDLE CUT OFF Fuel selector OFF Magneto selector OFF Touch down FLARE OUT and keep nose high EMERG...

Page 49: ...g all available means fire extinguisher if installed ENGINE FIRE IN FLIGHT Visual detection Fuel selector Mixture Fuel pump Throttle Cabin air cooling demisting After engine has stopped Magneto select...

Page 50: ...VATE If FIRE APPEARS TO BE OUT and electrical power is necessary to continue flight Main switch Circuit breakers Radio electrical switches Cabin air cooling ON CHECK for faulty circuit do not close ON...

Page 51: ...N FULLY PULLED INCREASE POWER without exceeding red line and periodically change RPM to minimize ice buildup on propeller Alternate Air Engine Turn back or change altitude to obtain best outside air c...

Page 52: ...ver DOWN Landing gear lights CHECK GREEN ON Continue flight with landing gear down upto destination or toward an appropriate alternate airfield Maximum airspeed 139 KIAS THE RED LIGHT REMAINS ON WITH...

Page 53: ...D LANDING GEAR FAILS TO EXTEND ONE OR SEVERAL GREEN GEAR DOWN LIGHTS FAIL TO ILLUMINATE Main switch Landing gear lever LDG GEAR circuit breaker Landing gear lights Flaps Maximum airspeed ON DOWN CHECK...

Page 54: ...NG GEAR NOT LOCKED Landing gear position CHECK POSITION WITH THE TOWER LANDING GEAR APPEARS DOWN AND LOCKED LOG GEAR circuit breaker Landing gear lever Emergency landing gear control Precautionary lan...

Page 55: ...s made Retract the landing gear Emergency landing gear control LOG GEAR circuit breaker Landing gear lever Landing on grass if possible Flaps Airspeed PUSHED CLOSED UP LANDING 65 70 KIAS Seats seat be...

Page 56: ...OWN ON FULL RICH HIGH RPM ADJUST SO AS TO MAINTAIN A RATE OF DESCENT LOWER THAN 500 ftjmin FLARE OUT near the ground with the pitch trim CAUTION REDUCE THROTTLE ONLY AFTER TOUCH DOWN RADIO MASTER SWIT...

Page 57: ...Simplified procedure ALTr warning light Pre MOD 182 Voltmeter Green sector Red I yellow sector ALTr FLO switch breaker Post MOD 182 Voltmeter 26 V 29 26 ALTr FLO switch breaker All ALTr warning light...

Page 58: ...ar extension first use the emergency system ELECTRICAL FAILURE CHECK OUT PROCEDURE FOR NIGHT VFR AND IFR ALTERNATOR FAILURE See Figure 3 1 NOTE The use of the norma landing gear extension may induce a...

Page 59: ...I t SUCCESS Check alternator field ALTr FLD CB FAILING Close ALTr FLO 58 and ALT PCB CONTINUE FLIGHT Switch off ALTr FLO 58 then ALT PCB Open Bus 2 0 and Bus 3 0 PCBs r I After switching off try to I...

Page 60: ...SECTOR OR 26 Voltmeter SECTOR OR 26 J I Open BUS 2 BUS 3 0 PCB I LEAVE IMe CONDITIONS LAND AS SOON AS POSSIBLE Check ALTr PCB closed I t SWitch off I reset ALTr FLD 5B t RED OR Restore electrical GREE...

Page 61: ...ntrol Stabilator control Ailerons Spin with flaps action IDLE HOLD OPPOSITE DIRECTION OF ROTATION FULL FORWARD NEUTRAL Same procedure except retract flaps as soon as possible When spinning stops centr...

Page 62: ...milling Zero wind MAXIMUM AERODYNAMIC EFFICIENCY 5 Landing gear up Flaps in landing position Speed 70 KIAS at maximum weight Propeller wind milling Zero wind Height above terrain Feel Landing geer up...

Page 63: ...ONS 4 5 AIRFRAME 4 5 ELECTRICAL SYSTEM 4 8 BEFORE STARTING ENGINE 4 10 ENGINE STARTING 4 11 NORMAL PROCEDURE 4 11 HOT ENGINE PROCEDURE 4 12 FLOODED ENGINE PROCEDURE 4 12 AFTER STARTING ENGINE 4 13 TAX...

Page 64: ...OF CONTENTS Continued SOCATA MODEL TB 20 Page AFTER LANDING 4 20 SHUT DOWN SECURING AIRPLANE 4 20 PARTICULAR USES 4 21 STALLS 4 21 FLIGHT WITH CROSSWIND 4 22 FLIGHT IN TURBULENT AIR 4 22 USE OF DOORS...

Page 65: ...operation of airplane These data are valid for standard airplane used at maximum weight in normal conditions Best rate of climb Landing gear up flaps retracted Landing gear down flaps in landing posi...

Page 66: ...SECTION 4 NORMAL PROCEDURES SOCATA MODEL TB 20 1 c 1 4 4 KEY PREFLIGHT AIRFRAME D PREFLIGHT ELECTRICAL Figure 4 1 PREFLIGHT INSPECTIONS d January 31 1988...

Page 67: ...essure Main switch OFF Fuel selector OPEN on Left Proceed with the external preflight inspection moving clockwise around the airplane 2 L H wing trailing edge Flap and aileron Check controls hinges pl...

Page 68: ...Air intakes Oil pump breather Exhaust pipe Fuel filter draining Fuel filter drain 7 Nose landing gear Towing fork Tire Shock absorber Door Microswitches Landing gear well 8 R H main landing gear Chock...

Page 69: ...and aileron hinges plays deflections 12 R H rear fuselage R H door lock Static port Window panels 13 Stabilizers Fin Rudder and rudder tab Stabilator and stabilator tab Tail cone and Undamaged Check c...

Page 70: ...IA switch V Advisory panel Landing gear indicator lights Fuel gages Flaps Instrument lights Navigation lights Anticollision lights if installed Strobe lights if installed Tested Tested Check RETRACT O...

Page 71: ...light Anticollision light if installed Recognition light if installed Post MOD 151 d Airplane rear part Navigation light Pre MOD 151 Strobe light if installed Anticollision light if installed e Cabin...

Page 72: ...Carried out CLOSED check catches in place OFF Se1 ADJUSTED and SECURE Check for proper operation Check deflection Circuit breakers side panel Magneto selector Emergency landing gear control Radio mast...

Page 73: ...LL FORWARD 1 4 OPEN IDLE CUT OFF ON FULL RICH until fuel flow is displayed 3 to 5 sec then IDLE CUT OFF OFF I Mixture Fuel pump Mixture Fuel pump Area Magneto start selector When the engine starts Mag...

Page 74: ...20 FULL FORWARD 1 4 OPEN IDLE CUT OFF ON FULL RICH for 1 sec then IDLE CUT OFF OFF Clear START 10 sec maxi BOTH FULL RICH Reduce rapidly 1000 to 1200 RPM during heating Refer to Section 2 Limitations...

Page 75: ...d Advisory panel test Landing gear indicator lights test Radio master switch if installed All radios and navaids ON Yellow sector 24 OFF Green sector 26 V 29 ON Checked Positive Positive ON ON Fuel se...

Page 76: ...ng as the oil temperature indicator pointer is within yellow sector Steering the airplane with the rudder pedals only is generally sufficient The combined use of the rudder pedals and the brakes permi...

Page 77: ...LL FORWARD 2000 RPM Propeller Cycle twice maxi 500 RPM drop Return to high RPM FULL FORWARD MAGNETO CHECK Throttle Magneto selector Maximum RPM drop on each magneto Maximum difference between magnetos...

Page 78: ...CKED Free TAKE OFF TAKE OFF TAKE OFF BOTH As required FULL FORWARD FULL RICH Check set to fullest tank ON Green sector Green sector Green sector 26 V 29 Set Heading indicator if installed Set Horizont...

Page 79: ...SAFELY AIRBORNE Brakes Landing gear AT 300ft Flaps AT 1000 ft Fuel pump External lights Air conditioning switch if installed CLIMB Mixture Throttle Propeller Optimum climb speed NOTE Apply RETRACT RET...

Page 80: ...ns see Section 3 Emergency procedures Paragraph Icing Leave icing conditions as soon as possible Remember to push in the Alternate Air control after leaving the icing area and when you are sure there...

Page 81: ...Landing lights ON FULL RICH FULL FORWARD Checked Checked ON SHORT FINAL Flaps Airspeed Standard airspeed LANDING below 103 KIAS See Section 5 Landing Performance Air conditioning switch if installed...

Page 82: ...ghts if installed Taxi light Lights Radio master switch if installed Air conditioning switch if installed Throttle WARNING Set OFF OFF OFF OFF OFF OFF Reduce THE TEST HEREAFTER MUST BE IMPERATIVELY CA...

Page 83: ...xtremely steep pitch attitude If the center of gravity is at or near its aft limit a slight tendency toward wing rocking or a wing drop may occur when the stabilator is deflected near its stop Aerodyn...

Page 84: ...h down LANDING When landing in a strong crosswind use the landing flap sefting Although the crab or combination method of drift correction may be used the wing low method gives the best control Maximu...

Page 85: ...or gusty conditions the doors should be firmly held during opening and closing and should be closed and locked immediately after entering or leaving the airplane The doors must be closed and locked f...

Page 86: ...SECTION 4 NORMAL PROCEDURES INTENTIONALLY LEFT BLANK I 4 24 SOCATA MODEL TB 20 June 30 1988 Revision 11...

Page 87: ...4 STALLING SPEEDS 5 5 WIND COMPONENTS 5 6 NOTiCE 5 7 ALTERNATE AIR INFLUENCE 5 7 TAKE OFF PERFORMANCE 5 8 CLIMB PERFORMANCE 5 10 MAXIMUM PERFORMANCE ALTITUDE 5 14 ANTENNAS INFLUENCE ON PERFORMANCE 5 1...

Page 88: ...n the limit noise level of 4 4 d B A the TB 20 airplane complies with Chapter 10 appendix 6 annex 16 of the agreement relative to International Civil Aviation Organization ICAO The noise limit authori...

Page 89: ...ctor flow lever to open position Figure 5 2 June 30 1988 Revision 7 FLAPS TAKE OFF L Gear UP OR DOWN KIAS KCAS 60 56 70 69 5 75 75 85 85 5 100 101 MPH lAS MPH CAS 70 66 80 79 90 90 100 101 115 116 FLA...

Page 90: ...tic source utilization open air outlets and or actuate cabin air selector flow lever to open position AIRSPEED 80 KIAS 110 KIAS 140 KIAS 170 KIAS ALTITUDE 92 MPH lAS 127 MPH lAS 160 MPH lAS 195 MPH lA...

Page 91: ...ATION 0 30 45 KIAS MPH KIAS MPH KIAS MPH lAS lAS lAS FLAPS RETRACTED 70 80 75 86 83 95 L GEAR RETRACTED FLAPS TAKE OFF 65 75 70 80 77 89 L GEAR UP OR DOWN FLAPS LANDING 59 68 63 73 70 81 L GEAR DOWN N...

Page 92: ...d 20 kt Flight path 0 40 H e a 30 d w 0 d 20 c 0 m p 0 10 0 e 0 t 0 k o 5 6 la 10 Angle between wind dlrecllon and flight path 50 Headwind 13 kt Crosswind 15 kt 20 25 25 kl Demonstrated crosswind 30 4...

Page 93: ...tion Increase by 7 on hard sod 10 on short grass 25 on high grass Influence of wind Increase by 30 for each 10 kt rear wind Reduce by 10 for each 10 kt headwind ALTERNATE AIR INFLUENCE If flight condi...

Page 94: ...aph NOTICE for corrections due to wind and runway condition Tempe rature ISA 20 C 36 F ISA ISA 20 C 36 F 5 8 Pressure altitude tt Distance 0 2000 4000 6000 Roll tt 647 757 886 1042 Clear 50 ft ttl 100...

Page 95: ...NOTICE for corrections due to wind and runway condition Tempe Pressure altitude tt Distance rature 0 2000 4000 6000 8000 ISA Roll tt 1115 1305 1527 1795 2119 20 C 36 F Clear 50 ft ttl 1735 2036 2409...

Page 96: ...0 8500 10500 12500 5 10 Flaps retracted Power 2575 RPM full throttle CLIMB SPEED ISA 20 C 36 F ISA ISA 20 C 36U F m s ft min m s ftjmin m s ftjmin 8 94 1760 8 01 1576 7 22 1422 8 13 1601 7 24 1425 6 4...

Page 97: ...full throttle CLIMB SPEED PRESSURE ISA 20 C 36 F ISA ISA 20 C 36U F ALTITUDE 500 2500 4500 6500 8500 10500 12500 June 30 1988 Revision 7 m s ft min m s ftjmin 6 32 1244 5 59 1100 5 65 1112 4 94 972 4...

Page 98: ...F et TIME min s 500 0 17 2500 1 29 4500 2 48 6500 4 17 8500 5 58 10500 7 53 12500 10 9 5 12 FUEL DIST TIME FUEL DIST TIME FUEL DIST US Gal NM min s US Gal NM min s USGal NM 0 1 0 4 0 19 0 1 0 5 0 21 0...

Page 99: ...et TIME min s 500 0 24 2500 2 6 4500 4 2 6500 6 15 8500 8 51 10500 11 58 12500 15 53 June 30 1988 Revision 7 FUEL DIST TIME FUEL DIST TIME US Gal NM min s US Gal NM min s 0 2 0 6 0 27 0 2 0 7 0 30 0...

Page 100: ...ight ANTENNAS INFLUENCE ON PERFORMANCE Installation of radio antennas reduces cruise performance as follows CRUISE SPEED AERIAL RANGE KIAS MPH lAS VHF 0 48 0 56 0 30 VOR 0 59 0 68 0 37 Glide 0 32 0 37...

Page 101: ...E SPEED RANGE KIAS MPH lAS 2 5 2 9 0 8 Figure 5 12A FOOTSTEPS INFLUENCE ON PERFORMANCE NOTE The retractable footsteps are only installed when modification No MOD 151 is applied Thereby the 2 5 KfAS sp...

Page 102: ...SECTION 5 PERFORMANCE 5 14B INTENTIONALLY LEFT BLANK SOCATA MODEL TB 20 June 30 1988 Revision 8...

Page 103: ...condition and the atmospheric conditions wind moisture temperature and so on may noticeably vary the endurance and range Settings with EGT indicator Best economy mixture from full rich weaken slowly...

Page 104: ...7 2400 21 9 54 5 14 4 65 2300 22 6 163 142 165 143 53 6 14 2 2200 23 4 52 6 13 9 2500 20 1 52 5 13 9 2400 20 7 51 6 13 6 60 2300 21 3 158 137 159 13B 50 6 13 4 2200 22 1 49 7 13 1 2500 18 9 49 6 13 1...

Page 105: ...2 38 4 70 166 144 172 150 2300 23 3 56 5 14 9 37 7 2200 24 2 55 5 14 7 37 1 2500 20 7 55 4 14 6 38 1 2400 21 4 54 5 14 4 37 5 65 2300 22 1 161 140 167 145 53 6 14 2 36 8 2200 22 9 52 6 13 9 36 2 2500...

Page 106: ...4 7 2400 20 9 54 5 14 4 65 2300 21 6 160 139 170 148 53 6 14 1 2200 22 4 52 6 13 9 2500 19 2 52 5 13 9 2400 19 7 51 6 13 6 60 2300 20 4 154 134 165 143 50 6 13 4 2200 21 1 49 7 13 1 2500 18 0 49 6 13...

Page 107: ...8 155 57 4 15 2 37 0 2300 22 3 56 5 14 9 36 3 2500 19 8 55 4 14 6 36 8 2400 20 5 54 5 14 4 36 1 65 2300 21 1 157 137 173 151 53 6 14 1 35 5 2200 21 9 52 6 13 9 34 9 2500 18 7 52 5 13 9 36 0 2400 19 3...

Page 108: ...139 182 15B 58 4 15 4 2500 19 4 55 5 14 7 65 2400 20 0 155 135 176 154 54 5 14 4 2300 20 7 53 6 14 2 2500 18 3 52 5 13 9 2400 18 9 51 6 13 6 60 2300 19 5 150 130 170 14B 50 6 13 4 2200 20 2 49 7 13 1...

Page 109: ...E SPECIFIC N PA CAS TAS ADJUSTING CONSUMTION 8HP RPM in Hg MPH kt MPH kt 1 h U S 1 100 Gall hr NM 65 2500 19 0 153 133 180 156 55 5 14 7 35 5 2500 17 9 52 5 13 9 34 8 60 2400 18 5 148 129 173 151 51 6...

Page 110: ...represent recommended power N PA CAS TAS MIXTURE ADJUSTING 8HP RPM in Hg MPH kt MPH kt 1 h U S Gall hr 2500 17 5 52 5 13 9 60 2400 18 1 146 127 176 154 51 6 13 6 2500 16 5 49 6 13 1 55 2400 17 0 138 1...

Page 111: ...9 4 13 1 34 2 70 165 143 166 144 2300 23 9 48 5 12 8 33 6 2200 24 7 47 5 12 6 32 9 2500 21 2 47 9 12 7 34 2 2400 21 9 46 9 12 4 33 5 65 2300 22 6 160 139 161 140 46 0 12 1 32 8 2200 23 4 45 0 11 9 32...

Page 112: ...8 47 9 12 7 2400 21 4 46 9 12 4 65 2300 22 1 158 137 164 143 46 0 12 2 2200 22 9 45 1 11 9 2500 19 6 45 4 12 0 2400 20 2 44 5 11 8 60 2300 20 9 153 133 158 13B 43 5 11 5 2200 21 6 42 6 11 2 2500 18 5...

Page 113: ...3 0 70 161 140 172 150 2300 22 8 48 5 12 8 32 4 2200 23 6 47 5 12 6 31 8 2500 20 3 47 9 12 7 33 0 2400 20 9 46 9 12 4 32 3 65 2300 21 6 156 136 167 145 46 0 12 2 31 7 2200 22 4 45 0 11 9 31 0 2500 19...

Page 114: ...5 46 9 12 4 65 2300 21 1 154 134 170 14B 46 0 12 2 2200 21 9 45 0 11 9 2500 18 7 45 4 12 0 2400 19 3 44 5 11 8 60 2300 19 9 149 129 164 142 43 5 11 5 2200 20 6 42 6 11 2 2500 17 6 43 0 11 4 2400 18 2...

Page 115: ...t MPH kt 1 h U S 1 100 Gall hr NM 70 2500 20 5 157 136 178 155 50 3 13 3 32 5 2500 19 4 47 9 12 6 31 9 65 2400 20 0 152 132 173 150 46 9 12 4 31 2 2300 20 7 46 0 12 1 30 6 2500 18 3 45 4 12 0 31 3 240...

Page 116: ...USTING 8HP RPM in Hg MPH kt MPH kt 1 h U S Gall hr 65 2500 19 0 150 130 176 153 47 9 12 6 2500 17 9 45 4 12 0 60 2400 18 5 144 125 169 147 44 5 11 7 2300 19 1 43 5 11 5 2500 16 8 43 0 11 3 2400 17 4 4...

Page 117: ...SPECIFIC N PA CAS TAS ADJUSTING CONSUMTION 8HP RPM in Hg MPH kt MPH kt 1 h U S 1 100 Gall hr NM 2500 17 5 45 4 12 0 30 4 60 2400 18 1 142 123 171 149 44 5 11 7 29 8 2500 16 5 43 0 11 4 30 5 55 2400 1...

Page 118: ...d runway condition Tempe rature ISA 20 C 36 F ISA ISA 20 C 36 F 5 30 Pressure altitude tt Distance 0 2000 4000 6000 8000 10000 Roll ft 675 710 755 800 855 905 Clear 50 ft ttl 1420 1495 1570 1650 1740...

Page 119: ...unway condition Tempe Pressure altitude tt Distance rature 0 2000 4000 6000 8000 ISA Roll ft 770 815 865 915 980 20 C 36 F Clear 50 ft ttl 1713 1800 1895 1995 2110 Roll ft 825 875 930 985 1050 ISA Cle...

Page 120: ...SECTION 5 SOCATA PERFORMANCE MODEL TB 20 I INTENTIONALLY LEFT BLANK 5 32 June 30 1988 Revision 2...

Page 121: ...LE OF CONTENTS Page GENERAL 6 2 AIRPLANE WEIGHING PROCEDURES 6 2 BAGGAGE CARGO LOADING 6 2 BAGGAGE 6 2 CARGO 6 3 DETERMINING WEIGHT AND BALANCE 6 5 GENERAL 6 5 UTILIZATION OF WEIGHT MOMENT GRAPH 6 5 E...

Page 122: ...LANE WEIGHING PROCEDURES Refer to Maintenance Manual for the procedures to use NOTE Weighing carried out at the factory takes into accountall equipment installed on the airplane The fist ofthese equip...

Page 123: ...back Item 1 Unfasten attachments of sound proofing cloth on cross beam Item 2 Pushing unscrew turn both attaching pins of air regulation duct on rear floor Item 4 Pull both latches inwards Item 3 Lift...

Page 124: ...SECTION 6 WEIGHT AND BALANCE KEY REMOVAL INSTALLATION c to 2 SOCATA MODEL TB 20 3 A 5 4 Figure 6 1 REMOVAL AND INSTALLATION OF REAR BENCH OR Post MOD 151 REAR SEATS 6 4 June 30 1988 Revision 8...

Page 125: ...d to add them to empty airplane data These values carried forward on weight moment envelope must give a point within the limits drawn with continuous line If that is the case loading is acceptable NOT...

Page 126: ...w the baggage straight line to get point M Our sample loading 110 Ibs 50 kg baggage Since point M falls within weight moment envelope the loading is acceptable NOTE Option No oaOO OaM L H or R H front...

Page 127: ...installation for L H and or R H front seat s Weight Ib 600 500 400 300 200 100 A Weight Ib 600 June 30 1988 Revision 7 500 400 300 200 100 B PILOT FRONT REAR PASSENGER PASSENGERS 7i X3 2 I x V I x V...

Page 128: ...SECTION 6 WEIGHT AND BALANCE INTENTIONALLY LEFT BLANK 6 10 SOCATA MODEL TB 20 January 31 1988...

Page 129: ...2900 2800 2700 2600 2500 2400 2300 2200 2100 2000 1900 1800 June 30 1988 Revision 5 I II i A2 II I I Al I B 1 1 II SECTION 6 WEIGHT AND BALANCE Mxl B 2 II I II I II Moment with regard 10 firewall lb...

Page 130: ...n 8 standard equipment items Optional equipment not restrictive list A letter 0 or A allows classifying of the equipment 0 optional equipment items replacing required or standard items A optional equi...

Page 131: ...T10 OPTIONAL A or 0 EQUIPMENT a 01 SPECIFIC OPTIONAL EQUIPMENT A H61520M Additional equipment for IFR France Grey Up to SIN 1269 From SIN 1270 A H61620M Additional equipment for night VFR France Grey...

Page 132: ...ventilation blower KING KA 33 A F82200M Forced ventilation rear passengers VETUS A F82210M Forced ventilation rear passengers VETUS A F82220M Forced ventilation rear passengers VETUS 21 50 Air conditi...

Page 133: ...P 100 KING A G66810M NP MP 100 KING with electrical pitch trim A G66900M AlP KAP 150 KING A G67D OOM AlP KFC 150 KING A G81000M Remote AlP modes annunciator KA 185 03 for KAP 150 A G81010M Remote AlP...

Page 134: ...lity Loud speaker SONAVOX A J53920M VHF COM capability Loud speaker AUDAX A J68800M Boom microphone headset PELTOR A J82700M Intercommunication system SPA 400 ICS SIGTRONICS Front and rear seats A J82...

Page 135: ...rs receivers A K80910M Audio control box KMA 24H71 KING with audio selector threshold 5 transmitters receivers A K81500M Audio selection box KMA 24 02 KING A K81510M Audio selection box KMA 24 02 KING...

Page 136: ...A Ke05DOM VHF COM 2 KY 196 A 30 KING I A 054920 M VHF 2 faired antenna DMC 70 I A DORNE MARGOLIN 23 14 UHF installation I A K88010M UHF KTR909 KING 23 60 Static dischargers A J88400M ESD protection 6...

Page 137: ...3900M Converter 28 V 14 V LT 71A KGS a C861 DaM Battery G246 19AH GILL a C872 DaM Battery at the front A D68910M Ammeter 28 V with 60A shunt A D90700M Voltmeter ammeter indicator ELECTRONICS INTERNATI...

Page 138: ...on R Standard circuit breakers panel T820 61212 R Printed circuits assembly on firewall T820 6121 0 including fuses printed circuit lights warning printed circuit pilot and alternator output printed c...

Page 139: ...ar head rests Blue 95 Qly 2 PMV A F87945M Rear head rests Ficelle 95 Qty 2 PMV a 067800 M Leather seats assembly Grey PMV with head rests 067815 M Front seats Qty 2 PMV Rear seat PMV a 067810 M Leathe...

Page 140: ...lue 95 Qly 2 PMV A 067965 M Rear head rests Ficelle 95 Qly 2 PMV 25 11 Front seats R Front seats TB10 74030 R Front seats TB10 74095 R Front seats TB10 741 06xOO 01 R Front seats TB10 741 06x02 03 a F...

Page 141: ...QD 89 a 080010 M L H front seat back off installallon Post MOD 89 a 080020 M R H front seat back off installallon Post MOD 89 a 100140 M Tilting front seat Blue 95 a 100440 M Tilting front seat Ficell...

Page 142: ...est I 25 13 Safety and harnesses belts R Front seat belt TB10 79013 SECURAIGLON R Front seat belt TB10 79013 TRW REPA R Front seat belt TB10 79013 PIN 10 4022 000 002 ANJOU AERO R Rear seat belt TB1 0...

Page 143: ...91 SOCATA PIN ELT 91A 2560 000 000 TSO A J871 DaM Emergency locator transmitter POINTER A J90800M Three frequency emergency locator transmitter ELT 96 SOCATA EUROCAE A J90810M Three frequency emergen...

Page 144: ...OCATA T80 A 051700 M Emergency locator transmitter ELT 10 NARCO A 051710M Emergency locator transmitter JOLLIET aft baggage compartment A 051730 M Emergency locator transmitter JE2 NG JOLLIET forward...

Page 145: ...F82310M Cabin halon extinguisher H1 10 AIR MAIP A F82320M Cabin halon extinguisher Hl 10 AIR MAIP with special support A F82330M Cabin halon extinguisher L HOTELLIER A F88300M Cabin powder extinguishe...

Page 146: ...08 AVIAC R Flaps actuator TB20 61201 PIN 700 238 LPMI R Flaps control selector TB20 61234 R Flaps position indicator TB20 61232 R Flaps relay support TB20 61260 2 relays HG2 24 VDC MATSUSHITA 2 suppor...

Page 147: ...25 A 058040 M Ferry fuel lank TB20 52925 28 20 Fuel supply R Fuel electric pump TB20 61218 PIN 8120 H WELDON R Fuel electric pump TB20 61218 PIN B8120 H WELDON R Fuel seleclor fllter T820 52026 28 40...

Page 148: ...two blade propeller A C68710M TKS system empty tank Icing conditions not authorized with two blade propeller 30 60 Propeller deicing A C52220M Propeller deiCing two blade propeller TKS A C52230M Prope...

Page 149: ...60 minutes elapsed time indicator PIN QI8 945 22 28 1 KB or QI8 945 22 28 1 ME A 0680 10M Ouartz chronometer THOMMEN 60 minutes elapsed time indicator PIN Q18 945 22 28 1 KB or 018 945 22 28 1 ME R H...

Page 150: ...o ATA 77 31 50 Central warning systems R Advisory panel TB20 61222 if GPS installed refer to ATA 34 R LDG I stall warning unit TB30 69030 A C56100M Starter warning light A C85000M LDG GR hydraulic gen...

Page 151: ...nerator TB20 61263 PIN 1117 05 LHC R LOG hydraulic generator T820 61267 PIN 3939637177 COMMERCIAL HYDRAULICS R LOG hydraulic generator T820 61267 PIN MC108 BI 19 AL4VT 637177 OILDYNE R LOG hydraulic g...

Page 152: ...LOG lire 5 00 5 6 120TT MICHELIN R Nose LOG lire 5 00 5 6 120TT AVIATOR R Nose LOG lire 5 00 5 6 PR PIN 505C61 8 GOODYEJ R R Nose LDG tube 5 00 5 DUNLOP R Nose LDG tube TR67A PIN 092 308 0 MICHELIN R...

Page 153: ...light W1250 PR WHELEN 5 R H navigation light W1250 PG WHELEN 5 Rear navigation light 3175 LABINAL 5 Rear navigation light A555A V 28V WHELEN A E53700M Strobe light JPC on vertical stabilizer A E53710...

Page 154: ...A E82440M Anticollision lights WHELEN wing tips A490A T8 CF 14 28 Light A625 PIN 01 077058 15 a E82600M Strobe light WHELEN tail A490A T8 DF 14 28 Light A500 ASP a E82610M Strobe light WHELEN tall A4...

Page 155: ...UNITED INSTRUMENTS R Vertical speed indicator T820 76224 PIN 7000 Code C85 with light tray 28 VDC UNITED INSTRUMENTS R Vertical speed indicator TB20 76224 PIN 7000 Code C83 UNITED INSTRUMENTS a C51510...

Page 156: ...air temperature indicator water tight connector on sensor OPT10 080410M retrofit A 0910 OOM Outside air temperature indicator standard connector on sensor DAVTRON A 091010M Outside air temperature in...

Page 157: ...control at R H station A K66050M HSI assy KING with horizontal KA 51 B if GPS KLN 90B installed A K66060M HSI assy KING with vertical KA 51B if GPS KLN 90B installed A 067140 M Heading indicator KG 1...

Page 158: ...valid for U K aircraft A 068310M Attitude gyro and heading gyro Indicators AID Specific for UK aircraft A 068320M Attitude gyro indicator AID Not valid for UK aircraft A 080200M Electrical attitude gy...

Page 159: ...ttitude gyro indicator KG 258 for KAP 100 Not valid for UK aircraft A 067131 M Attitude gyro indicator KG 258 for KAP 100 Specific for UK aircraft A 067230 M Attitude gyro indicator KG 258 for KAP 150...

Page 160: ...s follows SG 465 symbol generator ED 461 EHSllndicator KN 40 adapter A K92300M Radio navigation assy KING with EHI40 EFIS system KING EHSI only KMA 24H70 audio control box VHF1 VOR ILS KX 165 25 VHF2V...

Page 161: ...5410M Receiver VOR KN 53 NAY 1 VOR LOC KING A K66200M NAY system KNS 81 10 KING A K66220M NAV system KNS 81 12 KING A K66300M VHF assy COM1 NAV1 VOR LOC KX 155 with audio amplifier with VHF capability...

Page 162: ...ty KING A K81300M VOR ILS Indicator K1206 04 KING A K81310M VOR ILS indicator K1206 05 KING A K81400M VOR ILS indicator KI204 KING A K84700M Converter VOR LOC KN 72 KING 34 52 NAV 2 installation A K65...

Page 163: ...C872 OOM Battery at the front Installed refer to ATA 24 A K65620M ATC KT 76 A KING on R H panel strip with support A K65630M ATC KT 76 A KING on R H panel strip with support EHSI version A K87600M Tra...

Page 164: ...WELL A K657DOM DME KN 62A KING A K65710M DME KN 64 KING A K664DOM DME KN 63 KING 34 57 Global Positioning System GPS A 34 500A Color Skymap capability CM 2000 SKYFORCE A J87000M GPS 100 AVD 140 GARMIN...

Page 165: ...gOA KING Stand alone with extended advisory panel A K86030M GPS KLN gOA KING interfaced with HSI with RMI A K86040M GPS KLN 90A KING interfaced with HSI and AlP without RMI For export only A K899 OOM...

Page 166: ...ith HSI KI525A KCS 55A compass system A K927 DaM GPS KLN 90B KING interfaced with HSI and NP without RMI KA92 antenna I 34 60 Flight management computing 34 62 Multifunction display A 34 304A MFD KMD...

Page 167: ...PMV A 062115 M Oxygen system equipment constant flow type PURITAN BENNETT A 062121 M Oxygen rear head rests Blue 90 Qty 2 PMV A 062122 M Oxygen rear head rests Blue 95 Qty 2 PMV A 062125 M Oxygen fro...

Page 168: ...Oxygen leather head rest Grey PMV A 062190 M Oxygen leather head rest Chanel PMV A 062200 M Oxygen pressure demand type mask with radio crew PURITAN BENNETT A 062300 M Oxygen constant flow mask withou...

Page 169: ...h AIRBORNE filter A A90400M Vacuum pump SIGMA TEK with filter A A90410M Vacuum pump SIGMA TEK with filter when stormscope Installed refer to ATA 34 A 067150 M Vacuum system without attitude gyro Indic...

Page 170: ...IONAL A or 0 EQUIPMENT a 52 DOORS 52 10 Access doors A H889 DaM Door slop system metallic doors 52 40 Inspection doors A H882 DaM Doors Qty 2 on lower engine cowl I 6 52 Pre MOD 151 SOCATA MODEL TB 20...

Page 171: ...ITEM REQUIRED R OR STANDARD S OR N OPT10 OPTIONAL A or 0 EQUIPMENT a 53 FUSELAGE A B896 DOM Tail cone protection A H885 DaM Centering cup jack rest convex contact area I June 30 1988 Revision 11 Pre M...

Page 172: ...1 Door windows T810 25030 Rear side windows T810 22030 A 056200 M L H little window A 056210 M R H little window A 056220 M L H tinted little window A 056230 M R H tinted little window A F86S OOM Vent...

Page 173: ...C3YR 1 RF F 7693F Not deiced propeller HARTZELL a 61 0018 Three blade propeller HC C3YR 1 RF F 7693F B Deiced propeller HARTZELL 61 20 Controls R Propeller governor M21 0 681 WOODWARD R Propeller gov...

Page 174: ...G with starter and magneto a A86500M Engine IO 540 C4B5D LYCOMING with starter magneto and vibrator Magneto selector PIN 10 357210 1 TeM Starting vibrator PIN 10 382808 24 TeM Dual magneto PIN 10 7851...

Page 175: ...wmeter FT 10 or Fe 10 Iilres ARNAV A 0821 10M Flowmeter FT 10 or Fe 10 gallons ARNAV A D83800M Fuel flow totalizer I h FT t01A HOSKINS A D83810M Fuel flow totalizer Gal h FT 101 A HOSKINS A D90500M Di...

Page 176: ...OR N OPT10 OPTIONAL A or 0 EQUIPMENT a I 74 IGNITION 74 10 Electric generation system R Dual magneto D6LN 3000 BENDIX R Dual magneto D6LN 2031 BENDIX 6 58 Pre MOD 151 SOCATA MODEL TB 20 WEIGHT ARM pe...

Page 177: ...MENTS R Manifold pressure fuel flow pressure T820 76220 PIN 6331 Code H139 UNITED INSTRUMENTS a D86200M Tachometer Hourmeter NRF 80 PIN LM 02 LMI 77 20 Temperature A D53600M Exhaust gas temperature EG...

Page 178: ...ALANCE S R ITEM REQUIRED R OR STANDARD S OR N OPT10 OPTIONAL A or 0 EQUIPMENT a I 78 EXHAUST A ABB8 DaM Low noise exhaust 6 60 Pre MOD 151 SOCATA MODEL TB 20 WEIGHT ARM per unit Ib kg m 19 841 15 75 J...

Page 179: ...UIRED R OR STANDARD S OR per unit N OPT10 OPTIONAL A or 0 EQUIPMENT a 79 LUBRICATION 79 10 Storage A 065820 M Oil drain door 79 20 Distribution R Oil cooler 20006A NOM A ABB600M 2nd 011 cooler June 30...

Page 180: ...rter PRESTOLlTEjELECTROSYSTEMS MHB 4016 or MHB 6016 or LYCOMING LW 15572 or 31822474 R Starter 318 21064 LYCOMING R Starter relay CE 1971 060 F PARIS RHONE 6 62 Pre MOD 151 SOCATA MODEL TB 20 WEIGHT A...

Page 181: ...UIRED R OR STANDARD S OR per unit N OPT10 OPTIONAL A or 0 EQUIPMENT Ib a kg m 01 SPECIFIC OPTIONAL EQUIPMENT A H61520M Additional equipment for IFR France Grey A H61620M Additional equipment for night...

Page 182: ...ced ventilation rear passengers VETUS 21 50 Air conditioning A F87400M Air conditioning system KEITH a with alternator 70A LW 14363 LYCOMING A F87410M Reinforced air conditioning system KEITH a with a...

Page 183: ...G EHSI version on radio console A G66800M NP MP 100 KING A G66810M NP MP 100 KING with electrical pitch trim A G66900M AlP KAP 150 KING A G67D OOM AlP KFC 150 KING A G81000M Remote AlP modes annunciat...

Page 184: ...t AHX 05 Sene X BOSE Pilot Front passenger IA J91200M Boom microphone headset HI 0 13 4 DAVID CLARK A J92800M Boom microphone headset HMEC 25 KA SENNHEISER Pilot and front passenger Rear passengers A...

Page 185: ...ONEYWELL KI 204 indicator A 23 006A COMI NAV1 GPSI GNS 430 1 GARMIN interfaced with HSI A 23 007A COM1 NAV1 GPS1 GNS 530 GARMIN interfaced with HSI A K805 VHF COM 1 KY 196 A 30 KING 23 13 COM 2 instal...

Page 186: ...NDARD 8 OR N OPT10 OPTIONAL A or 0 EQUIPMENT a 23 14 UHF installation I A K88010M UHF KTR909 KING 23 60 Static dischargers A J884 DaM ESD protection 6 18A Post MOD 151 SOCATA MODEL TB 20 WEIGHT ARM pe...

Page 187: ...A C83900M Converter 28 V 14 V LT 71A KGS a C86100M Battery G246 19AH GILL A 090700M Voltmeter ammeter indicator ELECTRONICS INTERNATIONAL 24 40 External power supply 5 Ground power receptacle TB20 618...

Page 188: ...harnesses belts R Front seat belt TB10 79013 PIN 10 4022 000 002 ANJOU AERO 5 Rear reel safely bell T810 79000 A 064000 M 3rd rear reel safety belt 25 14 Central pedestal 5 Lighter R V I Plug 5000 361...

Page 189: ...UROCAE A J90810M Three frequency emergency locator transmitter ELT 96 SOCATA EUROCAE A J924 DaM Emergency locator transmitter ELT 90 SOCATA EUROCAE A J931 OOM Emergency locator transmitter ELT 200 ART...

Page 190: ...A F82310M Cabin halon extinguisher H1 10 AIR MAIP A F82320M Cabin halon extinguisher Hl 10 AIR MAIP with special support I A F82330M Cabin halon extinguisher L HOTELLIER A F88300M Cabin powder extingu...

Page 191: ...IGHT CONTROLS 27 50 Wing flaps control R Flaps actuator TB20 61203 PIN 700 238 LPMI 5 203 85 04 R Flaps control selector TB20 61234 0 320 31 50 R Flaps position indicator TB20 61232 0 132 31 50 R Flap...

Page 192: ...ks A 058040 M Ferry fuel lank TB20 52925 28 20 Fuel supply R Fuel electric pump T820 61218 PIN B8120 H WELDON R Fuel seleclor fllter T820 52026 28 40 Fuel indication 5 Fuel low level warning 6 24A Pos...

Page 193: ...ade propeller A C68715M TKS system empty tank Icing conditions not authorized with two blade propeller A C68725M TKS ice protection systems empty tank Icing conditions authorized with three blade prop...

Page 194: ...DaM Quartz chronometer THOMMEN 60 minutes elapsed time indicator PIN Q18 945 22 28 1 KB or 018 945 22 28 1 ME A 0680 10M Ouartz chronometer THOMMEN 60 minutes elapsed time indicator PIN Q18 945 22 28...

Page 195: ...al clock chronometer LC2 ASTROTECH a D911 OOM Hourmeter Flight duration DATCON NOTE Tachometer Hourmeter refer to ATA 77 31 50 Central warning systems R Advisory panel TB20 61285 R LDG stall warning u...

Page 196: ...30 41 B CLEVELAND R Main LDG tire 2 15 6 00 6 6 PRTT DUNLOP R Main LDG tire 2 15 6 00 6 6 PR GOODYEAR R Main LDG tire 2 15 6 00 6 6 l60TI MICHELIN R Main LDG tube 2 15 6 00 6 DUNLOP R Main LDG tube 2...

Page 197: ...Nose LOG lire 5 00 5 6 PR PIN 505C61 8 GOODYEJ R R Nose LOG tube 5 00 5 DUNLOP R Nose LDG tube TR67A PIN 092 308 0 MICHELIN R Nose LDG tube 5 00 5 TR6 GOODYEAR 5 Braking control R H post TB20 45030 3...

Page 198: ...sion lights assy WHELEN TB2063212 A 33 001A Recognition lights WHELEN A E53700M Strobe light JPC on vertical stabilizer A E53710M Strobe lights JPC on vertical stabilizer and under fuselage A E53720M...

Page 199: ...itot 1 190 53 15 Alternate slatic source in cabin 0 331 23 62 A C63500M 2nd heated Pltot R H wing 1 190 47 24 A 0681 OOM 2nd altimeter 20000 ft 1 433 19 69 A 0803 DaM Installation of 2nd airspeed indi...

Page 200: ...yro indicator 205 1 BL BFG A K66020M HSI assy KING 30 400 Hz with heading recopy capability and vertical KA 51 B A K66030M HSI assy KING 30 400 Hz with heading recopy capability and hOrizontal KA 518...

Page 201: ...Specific for U K aircraft A 34 001C Electrical attitude gyro indicator 11 0O 28LS SF BFG on L H instrument panel Not valid for UK aircraft A 34 001D Electrical attitude gyro indicator 11 00 28LS 5F B...

Page 202: ...s are as follows SG 465 symbol generator ED 461 EHSllndicator KN 40 adapter 34 30 Landing and taxiing aids 34 31 Marker A K67600M Marker receiver Indicator KR 21 KING 34 40 Independent position determ...

Page 203: ...icator K1206 05 KING A K81400M VOR ILS indicator KI 204 KING A K84700M Converter VOR LOC KN 72 KING 34 52 NAV 2 installation A K663 21 M VHF assy COM2 NAV2 VOR LOC KX 155 KING A K663 31 M VHF assy COM...

Page 204: ...Finder ADF A 34 300A ADF assy KR 87 SC Indicator KI227 01 HONEYWELL A 34 300B ADF assy KR B7 SC Indicator KI227 00 HONEYWELL A 34 300C ADF assy KR B7 SC Indicator K1229 HONEYWELL A 34 300D ADF assy K...

Page 205: ...LN 94 HONEYWELL Stand alone A 34 500A Color Skymap capability eM 2000 SKYFORCE A K92010M GPS KLN 89B KING Stand alone A K92610M GPS KLN 89B KING interfaced with HSI KI 525A KCS 55A compass system A K9...

Page 206: ...ant flow masks with radio crew Qly 2 PURITAN BENNETT A 062105 M Oxygen system equipment constant flow type PURITAN BENNETT A 062300 M Oxygen constant flow mask without radio rear passenger PURITAN BEN...

Page 207: ...A TEK with filter or Vacuum pump CHAMPION or AERO ACCESSORIES with AIRBORNE filter TB2078817 A A90410M Vacuum pump SIGMA TEK with filter when stormscope Installed refer to ATA 34 37 12 Distribution em...

Page 208: ...UIRED R OR STANDARD S OR N OPT10 OPTIONAL A or 0 EQUIPMENT a 52 DOORS 52 40 Inspection doors A H882 DaM Doors Qty 2 on lower engine cowl I 6 40A Post MOD 151 SOCATA MODEL TB 20 WEIGHT ARM per unit Ib...

Page 209: ...TEM REQUIRED R OR STANDARD S OR N OPT10 OPTIONAL A or 0 EQUIPMENT a 53 FUSELAGE A B896 DOM Tail cone protection A H885 DaM Centering cup jack rest convex contact area I June 30 1988 Revision 11 Post M...

Page 210: ...L A or 0 EQUIPMENT a 56 WINDOWS 5 Colourless windows assy TB1 0 24000 Windshield Door window Rear side window I A F86800M Ventilation scoops 6 42A Post MOD 151 SOCATA MODEL TB 20 WEIGHT ARM per unit I...

Page 211: ...8477 4 HARTZELL a 61 D01A Three blade propeller HC C3YR 1 RF F 7693F Not deiced propeller HARTZELL a 61 0018 Three blade propeller HC C3YR 1 RF F 7693F B Deiced propeller HARTZELL 61 20 Controls R Pr...

Page 212: ...ith starter and magneto a A86500M Engine IO 540 C4B5D LYCOMING with starter magneto and vibrator Magneto selector PIN 10 357210 1 TeM Starting vibrator PIN 10 382808 24 TeM Dual magneto PIN 10 785146...

Page 213: ...r 0 EQUIPMENT a 73 FUEL SYSTEM AND CONTROLS 73 30 Indicating system A 73 001A Digital fuel management system MICROFLO LTM SHADIN A 0905 DaM Digital fuel management system SHADIN A 090530M Digital fuel...

Page 214: ...R N OPT10 OPTIONAL A or 0 EQUIPMENT a 74 IGNITION 74 10 Electric generation system R Dual magneto D6LN 3000 BENDIX R Dual magneto D6LN 2031 BENDIX I 6 46A Post MOD 151 SOCATA MODEL TB 20 WEIGHT ARM pe...

Page 215: ...77 10 Power R Manifold pressure fuel flow pressure TB20 76220 PIN 6331 Code H139 UNITED INSTRUMENTS R Tachometer Hourmeter NRF 80 PIN LM 021 022 023 024 LMI 77 20 Temperature 5 EGT CHT ALCOR TB20 762...

Page 216: ...IONAL A or 0 EQUIPMENT a 79 LUBRICATION 79 10 Storage A 065820 M Oil drain door 79 20 Distribution R Oil cooler 20006A NOM A ABB600M 2nd 011 cooler I 6 4BA Post MOD 151 SOCATA MODEL TB 20 WEIGHT ARM p...

Page 217: ...80 STARTING R Starter PRESTOLlTEjELECTROSYSTEMS MHB 4016 or MHB 6016 or LYCOMING LW 15572 or 31822474 R Starter 318 21064 LYCOMING R Starter relay CE 1971 060 F PARIS RHONE June 30 1988 Revision 11 P...

Page 218: ...SECTION 6 WEIGHT AND BALANCE INTENTIONALLY LEFT BLANK 6 50A Post MOD 151 SOCATA MODEL TB 20 June 30 1988 Revision 11...

Page 219: ...7 TRIM SYSTEMS 7 7 INSTRUMENT PANEL 7 9 ADVISORY PANEL SWITCH BREAKERS PANEL CIRCUIT BREAKERS PANEL GROUND CONTROL WING FLAPS LANDING GEAR LANDING GEAR CONTROL LANDING GEAR POSITION INDICATOR LIGHTS...

Page 220: ...HEAD RESTS 7 25 SEAT BELTS 7 27 DOORS AND EXITS 7 29 DOORS 7 29 EXITS 7 29 CONTROLS LOCK 7 29 ENGINE 7 30 ENGINE CONTROLS 7 31 ENGINE INSTRUMENTS 7 32 IGNITION STARTER SYSTEM 7 32 NEW ENGINE BREAK IN...

Page 221: ...LIGHTING SYSTEMS EXTERIOR LIGHTING INTERIOR LIGHTING DEMISTING AIR REGULATION VENTILATION FIRE CUT OFF DEMISTING AIR REGULATION VENTILATION FIRE CUT OFF AIR CONDITIONING OXYGEN SYSTEM AIRSPEED INDICA...

Page 222: ...56 HEADING INDICATOR 7 56 VACUUM GAGE 7 56 AUXILIARY DRY AIR PUMP 7 57 AUTOPILOT 7 57 STALL WARNING SYSTEM 7 57 STATIC DISCHARGERS 7 57 DE ICING SYSTEM 7 58 RADIO EOUIPMENT TURN AND BANK INDICATOR CL...

Page 223: ...on which firewall engine mount and nose gear mount are fixed Frame No 1 on which wing front attachments are fixed Frame No 2 double frame which allows crossing and attachment of the wing spar Frame N...

Page 224: ...d a controlled tab The horizontal stabilizer is of stabilator type with an automatic anti tab controlled in its stabilator tab function Both are of conventional metal structure type spar ribs and skin...

Page 225: ...wn 3 10 Thestabilator consists of an automatic anti tab which automaticity is 104 This anti tab can also be controlled through the pitch trim Each front seat is provided with a rudder pedal which cont...

Page 226: ...indicator if installed Radio call Airspeed indicator or true airspeed indicator ELT switch if installed Instruments and radio lighting control Bank indicator Magneto start selector Pilot s air oullet...

Page 227: ...trument panel see Figure 7 1 is designed around the basic T configuration The gyros if installed are located in front of the pilot and arranged vertically The airspeed indicator or the true airspeed i...

Page 228: ...er j Wing flap control Pitchlrim ___ d M 4 il Stabilator tab position indicator Engine controls friction adjustment Micro if installed 7 10 Mixture control Ashtray l _ _ _ _ I_ Fuel S I Oerr trim I Fr...

Page 229: ...ontrol Throttle control Lighter r iW P tch 1c m r Wing flap control Stabilator lab pOSition indicator A e J Engine i 7 L controls M friction If Installed K 0 adjustment Mixture control Q Fuel selector...

Page 230: ...SECTION 7 DESCRIPTION 7 10B INTENTIONALLY LEFT BLANK SOCATA MODEL TB 20 June 30 1988 Revision 11...

Page 231: ...al R H side engine controls friction device Pre MOD 151 The R H instrument panel see Figure 7 3 contains the tachometer or tachometer hourmeter and the manifold pressure fuel flow pressure dual indica...

Page 232: ...abin air selector SOCATA MODEL TB 20 Push to talk switch Handle Cootcol wheel Manifold pressure fuel flow I pressure Control wheel tube Front passenger s air outlet Figure 7 3 EXAMPLE OF INSTRUMENT PA...

Page 233: ...CTION 7 DESCRIPTION Push la talk switch i Handle Cootcol wheel Manifold pressure fuel flow I pressure EGT CHT OAT Control wheel tube Front passenger s air outlet Figure 7 3A EXAMPLE OF INSTRUMENT PANE...

Page 234: ...acard Instruction plate Front overhead lights Radio loud speaker if installed Oxygen control and pressure gage if installed Alarms loud speaker Blower switch if installed Autopilot alarm if installed...

Page 235: ...installed Alarms loudspeaker Altitude selector alarm If installed Autopilot alarm If installed Radio loudspeaker If installed Oxygen pressure gage If installed Blower switch If installed Rear overhea...

Page 236: ...d Oxygen pressure gage Front air outlets If Installed Oxygen control If installed Alarms loudspeaker Autopilot alarm and altitude selector alarm If installed R H aft air outlet If installed Blower swi...

Page 237: ...SOCATA MODEL TB 20 June 30 1988 Revision 11 INTENTIONALLY LEFT BLANK SECTION 7 DESCRIPTION 7 136...

Page 238: ...ing immediate corrective action a red light illuminates A day I night switch is installed in the centre of the advisory panel to control the intensity of the green indicator lights and of the GPS annu...

Page 239: ...TARTER MOTOR installed A LTERNATOR FU EL SELECTOR PARKING BRAKE oIL PRESSURE SECTION 7 DESCRIPTION DAY I NIGHT TOGGLE SWITCH AUXILI PUM ARY DRY AIR P if Installed UM SYSTEM orVACU if Installed LAN DI...

Page 240: ...GPS message an nun Clatarswitc hi 1annunCiators see Section 9 g light P FUEL cee 0 pur IIP LIGHT PITOT TAXI L L t t Vacuum system Starter motor Fuel low level LOG GR pump Day night Toggle switch Heate...

Page 241: ...SOCATA MODEL TB 20 FUEL TURN PU IP COORD M IN SWITCH STROBE LIGHT ALTr CO PITOT LIGHT HEAT SECTION 7 DESCRIPTION TAXI COG LIGHT LIGHT Figure 7 5B SWITCH BREAKERS 8B June 30 1988 Revision 6 7 158...

Page 242: ...Pull off type circuit breaker Opt 6 Switch Opt LDG FLAPS FAN 0 LIGHTER GEAR OAT 0 COM 0 COM 0 0 0 NAV 1 NAV 2 AUDIO AUDIO NAVO NAVO DME 0 XPDR 0 OSTROBES AIP TRIM OFF ON HFO R M SWITCH ALTr CO ALTr Al...

Page 243: ...cuit breaker Opt Pull off type circuit breaker Opt 6 Switch Opt WG GEAR i OAT COM 0 NAV 1 FLAPS FAN LIGHTER IT Of 0 00 P AUDIO 0 AUDIO 0 NAV 0 DME 0 XPDR 0 OSTROBES 6 AIP TRIM OFF ON HFO R M SWITCH AL...

Page 244: ...SECTION 7 DESCRIPTION 7 16B INTENTIONALLY LEFT BLANK SOCATA MODEL TB 20 June 30 1988 Revision 8...

Page 245: ...e center By applying either left or right brake the degree of turn may be increased The minimum turning radius of the airplane is obtained by using differential braking and nose gear steering see Figu...

Page 246: ...I SECTION 7 DESCRIPTION 7 18 6 075 m 20 Figure 7 7 MNIMUM TURNING RADIUS SOCATA MODEL TB 20 19 75 m 64 9 6 June 30 1988 Revision 9...

Page 247: ...and main gears are provided with oil air shock absorbers Each main gear wheel is equipped with a hydraulically actuated single disc brake on the inboard side of the wheel Landing gear extension or re...

Page 248: ...anding gear system will not begin until the lever has been repositioned Afterthe lever has been repositioned it directs hydraulic pressure within the system to actuate the gear to the selected positio...

Page 249: ...pressure in the system drops the pressure switch starts operation of the hydraulic generator which increases pressure During cruising flight with the landing gear retracted automatic cycling on the h...

Page 250: ...o retract the landing gear in a normal way LANDING GEAR WARNING SYSTEM The airplane is equipped with a landing gear warning system designed to help prevent the pilot from inadvertently making a wheels...

Page 251: ...s locked To open the access door proceed as follows POUSSER POUR TOURNER PUSH TO TURN DRUCKEN UM ZU DREHEN Figure 7 B WARNING ANY PARCEL OR BAGGAGE MUST BE FIXED WITH STRAPS IT IS FORBIDDEN TO TRANSPO...

Page 252: ...OD 151 LUXE AND EXECUTIVE VERSIONS Adjustment of the back at lurn bar level if installed SOCATA MODEL TB 20 Alternative procedure Oxygen masks If installed Alternative procedure Figure 7 9 FRONT SEATS...

Page 253: ...ess on the knob and moderately lean back to the desired position release the button the seat back should fit perfectly with your back Lift up adjustment bar or lever to unlock when in desired position...

Page 254: ...G PUSH BUTTON RIGID STRAP J ADJUSTMENT ADJUSTABLE STRAP SHOULDER HARNESS J UNLOCKING HANDLE REAR SEAT BELT UNLOCKING HANDLE ADJUSTMENT ADJUSTABLE S REAR SEAT REEL BELT Post MOD 151 PIN ADJUSTMENT L AD...

Page 255: ...occur during operation slightly ease back 5 in 10 em approximately then unwind strap again To unlock them Depress red unlocking push button to free movable strap Rear seat belts To lock them Engage bo...

Page 256: ...ON OUVERT Q OPEN AUF o J SOCATA MODEL TB 20 o Detail see FigLJre7 11A FERME CLOSED ZU Figure 7 11 DOORS OPENING AND CLOSING 7 28 IN EMERGENCY KICK OUT HERE Figure 7 11A EMERGENCY EXIT Pre MOD 151 June...

Page 257: ...windows kicking out at the location of the placard The placard see Figure 7 11A is located on both rear windows and is legible from the inside of the airplane CONTROLS LOCK A locking pin located in l...

Page 258: ...iring removal of the propeller The engine mount is made of steel tube rigidly attached on firewall Engine attachment is provided by dynafocal mounting brackets to attenuate vibrations Engine and acces...

Page 259: ...ull power in the aft position it is closed engine idling At approximately in 12 mm of its rear stop the throttle actuates on landing gear alarm microswitch The propeller governor is controlled by the...

Page 260: ...t IGNITION STARTER SYSTEM Engine ignition is provided by a dual magneto ontwo spark plugs per cylinder The R H part of the magneto fires the R H lower and L H upper spark plugs the L H part of the mag...

Page 261: ...SUMP r SECTION 7 DESCRIPTION SUMP STRAINER TEMPERATURE PROBE PRESSURE VALVE Calibrated ball COOLER THERMOSTATIC VALVE FILTER CARTRIDGE FIREWALL I I _______ J j cob C 0 PRESSURE eecee PANEL l PRESSURE...

Page 262: ...n l Yellow OIL OIL TEMPERATURE PRESSURE Red Yellow Green Yellow Red 12 9 6 3 SOCATA MODEL TB 20 FILLING PORT WITH GAGE GRADUATED IN US Qt GROOVE I 7 32B DRAINING I CLIP j PAUSE DRAINING UNION Figure 7...

Page 263: ...arkings Oil pressure PSI X 10 Sump Groove Draining union A tern perature 2 14 eX 10 Union Draining Clip Pause Key Red D Green D Yellow 12 9 6 3 Filling port with gage graduated in US Qt Figure 7 12B O...

Page 264: ...SECTION 7 DESCRIPTION 7 320 INTENTIONALLY LEFT BLANK SOCATA MODEL TB 20 June 30 1988 Revision 11...

Page 265: ...ing A sump located at the bottom of the engine allowing oil recovery a cartridge throw away type filter located on engine rear accessory housing and a strainer type filter located in the sump complete...

Page 266: ...pitch high RPM FUEL SYSTEM Thefuel system see Figures 7 13 and 7 14 7 14Aor7 14B 7 14C consists of two vented integral fuel tanks one in each wing a selector valve a filter an auxiliary fuel pump as w...

Page 267: ...er indicator L G i AL1 L H fuel quantity indicator if installed Boost pump indicator light I I R H Manifold pressure fuel flow I Pressure indicator Instrument panel Low level warning light if installe...

Page 268: ...ABLE USABLE PRESS TO CLOSE ICLOSEDI Y Manifold pressure L H fuel quantity Indicator I _4 4 _3 4 _1 2 _1 4 _0 US GAL r 43 _4 4 32 _3 4 21 5 _1 2 10 5 _1 4 _0 CD Fuel flow pressure R H fuel quantity ind...

Page 269: ...RESS TO CLOSE I CLOSED I Manifold pressure Fuel flow pressure MAN FUEL 0 0L y R H fuel L H fuel quantity indicator rquantity indicator LlTRES _4 4 163 _4 4 _3 4 121 _3 4 _1 2 81 _1 2 FUEL QTY _1 4 40...

Page 270: ...TO CLOSE I CLOSED I Manifold pressure 43 1 US GAL USABLE Fuel flow pressure L H fuel quantity indicator R H fuel quantity indicator 7 368 1 2 1 4 4 o 4 4 o 4 4 4 4 4 4 163 L 43 1 USG 163 L 43 1 USG o...

Page 271: ...USABLE TO CLOSE I CLOSED I Manifold pressure L H fuel quantity indicator o 4 4 4 4 163 L 43 1 USG 163 L USABLE Fuel flow I pressure R H fuel quantity indicator o 4 4 4 4 l 163 L 43 1 USG o TEST Figure...

Page 272: ...SECTION 7 DESCRIPTION I 7 360 INTENTIONALLY LEFT BLANK SOCATA MODEL TB 20 June 30 1988 Revision 11...

Page 273: ...ed on the upper portion of the central console Airplanes equipped with resistor float oaoes Thefloat type gages two on each wing are attached to the rear of the tanks Airplanes equipped with capacity...

Page 274: ...y fuel pump is controlled by a switch breaker located on front part of pedestal An indicator light located on the advisory panel shows operation of the auxiliary pump The fuel system is equipped with...

Page 275: ...als Differential braking helps to maneuver during taxiing L H pedal actuates the L H wheel brake R H pedal actuates the R H wheel brake PARKING BRAKE Parking brake is constituted with a knob located o...

Page 276: ...LINDER BRAKE PEDAL MICROSWITCH VALVE PARKING BRAKE CONTROL KNOB POWER PLANT BLEED DISK BRAKE UNIT SOCATA MODEL TB 20 r BRAKE FLUID RESERVOIR INDICATOR LIGHT Figure 7 15 BRAKE SYSTEM L H station only I...

Page 277: ...KE PEDAL MICROSWITCH VALVE PARKING BRAKE CONTROL KNOB POWER PLANT BLEED DISK BRAKE UNIT SECTION 7 DESCRIPTION r BRAKE FLUID RESERVOIR INDICATOR LIGHT Figure 7 15A BRAKE SYSTEM L H R H stations if inst...

Page 278: ...SECTION 7 DESCRIPTION I 7 40 INTENTIONALLY LEFT BLANK SOCATA MODEL TB 20 June 30 1988 Revision 11...

Page 279: ...limits the alternator electrical load to the battery and the networks ALTERNATOR CONTROL UNIT The alternator control unit located on the firewall on cabin side provides the alternator voltage regulati...

Page 280: ...TB 20 en J A n ATTERY RELAY 7 41A PULL OFF TYPE SWITCH I CIHCUIT lIREAKEH I CIRCUIT BREAKER C i A AKCR I IPCb SB STARTCR HUS 3 B U S 1 ALTERNATOR OUTPUT B U S 2 B U S 1 3 Figure 7 16 TYPICAL ELECTRIC...

Page 281: ...g Cabin blower To light Turn ond honk indlcotor Emergoncy lighting systom Rear overhead light lighting Intercom Clock Fro t o rh ad light lighting erTl rge GY Propeller de Icing Chronometer Statter re...

Page 282: ...er supply to avionics and enables automatic disconnection of avionics systems when the engine starts or manual disconnection during abnormal conditions When the switch is in OFF position no electrical...

Page 283: ...n may go down to the yellow sector If indication is within lower red sector remove and charge the battery If indication is within the upper red sector with the alternator operating the regulator has t...

Page 284: ...may decrease below 24 Volts Red LED VDC located on the indicator R H side illuminates for a voltage greater than 30 4 Volts or lower than 24 Volts Illuminated LED with displayed voltage lower than 24...

Page 285: ...SOCATA MODEL TB 20 June 30 1988 Revision 11 INTENTIONALLY LEFT BLANK SECTION 7 DESCRIPTION 7 436...

Page 286: ...70 A labelled BAT between battery and network 30 A labelled BUS 1 on bus bar 1 supply 30 A labelled BUS 2 on bus bar 2 supply 30 A labelled BUS 3 on bus bar 3 supply These five pull off type circuit...

Page 287: ...sic exterior lighting consists of conventional navigation lights located on the wing tips and tail cone a landing light and a taxi light mounted on the L H wing leading edge The airplane may be equipp...

Page 288: ...nticollision lights and strobe lights should not be used when flying through clouds or overcast the flashing light reflected from water droplets or particles in the atmosphere particularly at night ca...

Page 289: ...ion FULL INTENSITY turning counterclockwise A courtesy light is installed in the cabin headliner in front of the air outlets to facilitate boarding or deplaning the airplane during night operations Th...

Page 290: ...aft of the firewall in front of front passenger s feet The hot airflow supplying this mixer is regulated by a fire cut off shutter from the control panel located on R H portion of the instrument panel...

Page 291: ...I ii ii I I I I I I I I _ o _ _ o Clear vision window ___ c __ _ _1 if installed Rear passenger s feet F Scoop J_ l_ _ l_i_ if installed Blower if installed Rear air intake fin root r j j Rear top ven...

Page 292: ...vision window may be installed on the access doors to facilitate high ventilation for pilot and front passenger Rear passengers An air intake at outside temperature located at the bottom part of the f...

Page 293: ...installed is controlled by a switch breaker located on the central pedestal The alternate static source if installed is controlled by a knob located on the L H strip this knob controls a valve which s...

Page 294: ...lcato Airspeed indicator or true airspeed indicator I Airspeed ind icator or true airspeed indicator Vertical speed indicator I7 52 I Pitot J Drain Altimeter Static pori KEY Dynamic system Sialic syst...

Page 295: ...e airspeed indicator Alternate static source valve Airspeed indicator or true airspeed indicator Alternate slatic source valve Pitot Altimeter n 1 h Static port Vertical speed indicator Altimeiern 2 D...

Page 296: ...e to the current altimeter setting ALTERNATE STATIC SOURCE if installed A two position selector allows the normal static source system of the airplane to be isolated in case of clogging or icing of st...

Page 297: ...GAGE CC W ATTITUDE GYRO INDICATOR I I t I FILTER I if installed 0 0 0 j _ 000 _ 000 AIR FILTER HEADING INDICATOR I II VENT LINE LENGINE VACUUM PUMP KEY Vacuum _ _ _ _ Inlet air Discharge air Figure 7...

Page 298: ...r SOCATA MODEL TB 20 ATTITUDE GYRO INDICATOR t r L Q I t VACUUM GAGE I I I ODO _ 000 __ 0 00 AIR FILTER l II VENT LINE ENGINE VACUUM PUMP _________ KEY Vacuum Inlet air Discharge air Figure 7 20A VACU...

Page 299: ...I SOCATA MODEL TB 20 June 30 1988 Revision 5 INTENTIONALLY LEFT BLANK SECTION 7 DESCRIPTION 7 556...

Page 300: ...accurate flight attitude indication HEADING INDICATOR if installed The heading indicator displays airplane heading on a compass card in relation to a fixed simulated airplane image and index The head...

Page 301: ...d in IFR flights wick type static dischargers are installed to improve radio communications during flight through dust or various forms of precipitation rain snow or ice crystals Under these condition...

Page 302: ...ld turn both clear vision window attachment knobs upwards and tilt window downwards NOTE Close the clear vision window and lock it with both knobs prior to opening gulf wing access door SUN VISOR To r...

Page 303: ...integrated in the locator transmitter and allowing use of the latter outside the airplane and of a remote control located on the instrument panel Operation of the emergency locator transmitter is obta...

Page 304: ...ELT does not transmit control switch to AUTO emergency signal any longer ELT 96 EUROCAEI ELT 97 TSOI b On remote control the XMIT ALERT red warning light goes off c On ELT the red warning light goes...

Page 305: ...IDENTIFICATION PLATE PUBLICATIONS INSPECTION PERIODS ALTERATIONS OR REPAIRS GROUND HANDLING TOWING PARKING TIE DOWN JACKING LEVELING FLYABLE STORAGE STORAGE WITHOUT FLYING POSSIBILITY SERViCiNG MAINTE...

Page 306: ...TABLE OF CONTENTS Continued AIRPLANE CLEANING AND CARE WINDOWS AND WINDSHIELD SOCATA MODEL TB 20 PAINTED SURFACES 8 17 8 17 8 17 8 18 8 18 8 18 8 18 8 18 PROPELLER CARE ENGINE CARE INTERIOR CARE FRONT...

Page 307: ...ility It is recommended that a planned schedule of lubrication and preventive maintenance be followed and that this schedule be tailored to the climatic or flying conditions to which the airplane is s...

Page 308: ...ANE INSPECTION PERIODS Refer to regulations in force in the certification country for information concerning preventive maintenance which is to be carried out by pilots A maintenance Manual should be...

Page 309: ...steering device orexert excessive loads on the latter CAUTION WHEN TOWING WITH A VEHICLE DO NOT EXCEED THE NOSE GEAR TURNING ANGLE OR DAMAGE TO THE GEAR AND STEERING DEVICE WILL RESULT see Figure B 2...

Page 310: ...SECTION 8 AIRPLANE HANDLING SERVICING AND MANTENANCE IS030 18 30 I i i L H STOP i 0 I I SOCATA MODEL TB 20 R H STOP Figure 8 2 TURNING ANGLE LIMITS 8 6 June 30 1988 Revision 2...

Page 311: ...down hole located on flaps hinge arms and in rear tie down fitting located under horizontal stabilizer secure each rope to a ramp tie down Check that doors are closed and locked JACKING When it is nec...

Page 312: ...excessive accumulations of water in the fuel system and other air spaces in the engine Keep fuel tanks full to minimize condensation in the tanks Keep the battery fully charged to prevent the electro...

Page 313: ...2OWSO SAE 60 SAE 40 or SAE 50 SAE 40 SAE 30 SAE 40 or SAE 20W4Q SAE 20W50 or SAE 15W50 SAE 30 or SAE 20W30 This airplane was delivered from the factory with a corrosion preventive aircraft engine oil...

Page 314: ...ur airplane are detailed in the Maintenance Manual Engine oil is changed with the filter Drainthe engine oil sump and replace the filter at least every 4 months even though less than the recommended h...

Page 315: ...ph hereafter for additional information Capacity each tank 44 4 U S Gal 1681 NOTE Service the fuel system after each ffight and keep fuel tanks full to minimize condensation in the tanks respecting we...

Page 316: ...he engine fuel system While these conditions are quite rare and will not normally pose a problem to owners and operators they do exist in certain areas of the world and consequently must be dealt with...

Page 317: ...parate clean container approximately 2 to 3 U S Gal 7 to 11 litres and then transferring this mixture to the tank prior to the fueling operation Any high quality isopropyl alcohol may be used such as...

Page 318: ...NDED BY THE MANUFACTURER TO OBTAIN PROPER PROPORTIONING DO NOT ALLOW CONCENTRATED EGME COMPOUND TO COME IN CONTACT WITH THE AIRPLANE FINISH AS DAMAGE CAN RESULT Prolonged storage of the airplane will...

Page 319: ...ON 8 AIRPLANE HANDLING SERVICING AND MANTENANCE Lltres Fuel Litres 150 200 250 300 Add t e l 350 400 I 1 4 1 3 5 V I 3 ALCOHOL V 1 2 5 1 1 2 1 1 5 V EGME 0 5 o g g 0 10 20 30 40 50 60 70 80 90 100 110...

Page 320: ...that is 7 5 bars 0 3 Main gears shock absorbers Filling with hydraulic fluid MIL H 5606 inflate with pressurized dry air or nitrogen to 666 psi 15 0 that is 45 9 bars 1 0 Check every 100 hours and ser...

Page 321: ...TIC THESE MATERIALS WILL ATTACK THE PLASTIC AND MAY CAUSE IT TO CRAZE Follow by carefully washing with a mild detergent and plenty of water Rinse thoroughly then dry with a clean moist chamois Do not...

Page 322: ...ner on the blades remove grease and dirt ENGINE CARE Refer to Maintenance Manual for the procedures to follow INTERIOR CARE To remove dust and loose dirt from the upholstery and carpet clean the inter...

Page 323: ...ke it easier to locate a particular supplement Some installed items of optional equipment whose function and operational procedures do not require detailed instructions are discussed in Section 7 I Li...

Page 324: ......

Page 325: ...R equipment TB 9 From 5 I N1 to 878 except SIN 765 T8 10 FromS N 1 to 947 2A Night VFR equipment T8 20 From 5 I N 1 to 947 except S N 823 to 849 888 T8 20 From 5 I N 948 and 5 N 823 to 849 888 2B Nigh...

Page 326: ...1 to 947 except 5 N 823 to 849 888 10 Oxygen equipment PURITAN BENNETI Front seats pressure demand type masks T8 20 21 From S N 1 lOA Oxygen equipment PURITAN BENNETI Front seats constant flow type ma...

Page 327: ...N 948 and SIN 823 to 849 888 SECTION 9 SUPPLEMENT A 1 31 01 88 0 29 02 88 31 01 88 1 31 01 88 1 31 01 88 0 31 01 91 0 31 01 91 22 BFG WX 1000 1000 or WX 900 or WX 500 stormscope T89 10 200 20 21 From...

Page 328: ...48 and SIN 823 to 849 888 32 BENDIX I KING KLN90A GPS navigation system interfaced with EHI 40 EHSI TB20 21 From SIN 948 and SIN 823 to 849 888 33 BENDIX I KING KLN90B GPS navigation system interfaced...

Page 329: ...IX I KING KLN898 GPS navigation system interfaced with the HSt KI 52SA T89 10 200 20 21 From SIN 948 and SIN 823 to 849 888 41 TKS system T8 20 T8 21 From SIN 948 and SIN 823 to 849 888 42 Intentional...

Page 330: ...20 21 From SIN 948 and SIN 823 to 849 888 0 15 05 01 51 GARMIN GNS 430 GPS B RNAV navigation system interfaced with electromechanical instruments GPS 1 B RNAV GPS 2 IFR TB9 10 200 20 21 From SIN 2000...

Page 331: ...AND NIGHT IFR EQUIPMENT 2 SUPPLEMENT DAY AND NIGHT IFR EQUIPMENT TABLE OF CONTENTS GENERAL Page 9 1 3 LIMITATIONS 9 1 14 EMERGENCY PROCEDURES 9 1 14 NORMAL PROCEDURES 9 1 16 PERFORMANCE 9 1 20 June 3...

Page 332: ...SUPPLEMENT 1A SOCATA DAY AND NIGHT IFR EQUIPMENT INTENTIONALLY LEFT BLANK 9 1 2 January 31 1988...

Page 333: ...hereafter do not include specific flight I and radio navigation instruments required by decree concerning the civil airplanes operating general conditions or other foreign regulations for example FAR...

Page 334: ...T m BUS 1 J 7j BUS 2 r BATTERY BUS 3 ALTr ft ALTERNATOR ft i PUL TYPE i CIRCUIT BRE KER PCB Figure 9 1 1 BUS BARS POWER SUPPLY 9 1 4 SOCATA r B u I S 1 B u I S 2 B U I s 3 AIR GDND lif installed EVAP...

Page 335: ...t Turn and ban indicator Emergency lighting system ReO overhead light lighting Intercom Cloc Front overhead light lighting emergency Propeller de icing Chronometer Startcr relay Landing gear EHSI ADAP...

Page 336: ...PLEMENT 1A DAY AND NIGHT IFR EQUIPMENT 6 5 4 7 8 10 9 12 14 11 13 52 50 48 46 44 42 41 55 54 53__ 4 57 3 16 38 18 36 37 SOCATA 22 24 23 9 1 6 Figure 9 1 3 EXAMPLE OF INSTRUMENT PANEL IFR January 31 19...

Page 337: ...Engine monitoring cluster Std 15 Radio support visor lighting 16 Illuminated compass Std 17 Audio control panel 18 VHF1 19 VHF2 20 VOR I LOC indicator 21 R H instrument panel visor lighting I 22 Illum...

Page 338: ...lve 49 Emergency landing gear and circuit breakers panel post light 50 Emergency landing gear control Std 51 Magneto start selector Std 52 L H air outlet Std 53 Maps reading light 54 Push ta talk swit...

Page 339: ...e valve is pulled altitude compensation should be performed as per Section 5 Performance CLOCK I STOP WATCH The clock I stop watch and its post light are installed in the center of the pilot s control...

Page 340: ...SUPPLEMENT 1A SOCATA DAY AND NIGHT IFR EQUIPMENT 8 Figure 9 1 4 ANTENNAS 9 1 10 January 31 1988...

Page 341: ...1 antenna 2 VHF 2 antenna 3 VOR antenna 4 Glide ILS antenna 5 ATe transponder antenna SUPPLEMENT 1A DAY AND NIGHT IFR EQUIPMENT 6 Radio compass loop and sense antenna 7 Marker antenna 8 DME antenna J...

Page 342: ...IT BREAKER Facultative in IFR PULL OFF TYPE CIRCUIT BREAKER FacultatIVe in IFR lJ OPTIONAL SWITCH wo FLAPS LIGHTER GEAR 0 OA T COM COM AUDIO AUDIO 0 0 0 0 TRIM M SWITCH o 0 ON 0 ALT FLO 0 0 0 0 BUS BU...

Page 343: ...IRCUIT BREAKER PULL OFF TYPE CIRCUIT BREAKER o CIRCUIT BREAKER Facultative in IFR PULL OFF TYPE CIRCUIT BREAKER FacultatIVe in IFR lJ OPTIONAL SWITCH o OHSI HORO Figure 9 1 SA CIRCUIT BREAKERS ASSEMBL...

Page 344: ...SUPPLEMENT 1A DAY AND NIGHT IFR EQUIPMENT INTENTIONALLY LEFT BLANK 9 1 12B SOCATA June 30 1988 Revision 4...

Page 345: ...S ASSEMBLY 1 Alternator pull off type circuit breaker 60 A 2 Battery pull off type circuit breaker 70 A 3 BUS bar 1 pull off type circuit breaker 30 A 4 BUS bar 2 pull of type circuit breaker 30 A 5 B...

Page 346: ...in Section 3 Emergency procedures of the basic Pilot s Operating Handbook AIRSPEED INDICATING SYSTEM FAILURE Check the operation of the heated pitot green indicator light ON If the switch breaker is O...

Page 347: ...s 1 2 3 After a few moments reset pull off type circuit breakers in the numerical order with a delay between each operation for observation Disengage the faulty BUS bar and disconnect all the equipmen...

Page 348: ...fficient to comply with regulations BEFORE FLIGHT may be undertaken or continued at night Check the operation of anti collision light s of navigation lights of cabin and instrument panel lighting of l...

Page 349: ...to maximum demisting LINED UP ON RUNWAY Check heading indicator and attitude gyro indicator bar At night turn on landing lights as required TAKE OFF See Section 4 Normal procedures of the basic Pilot...

Page 350: ...g U S Gal Litres I hr I hr Up 0 120 137 2500 19 11 7 44 Down 0 120 137 2500 25 3 16 5 62 Level flight holding Up 0 100 112 2500 16 9 34 Down 0 100 112 2500 22 13 49 Up 0 100 112 2500 17 9 34 Approach...

Page 351: ...ecommended to use the headset VOR ADF MKR AND DME if installed They operate independently of VHF comm transceivers but at least one VHF comm transceiver must be turned on to provide an audio amplifier...

Page 352: ...ITY turning counterclockwise LANDING LIGHTS The lights are controlled by two switch breakers See Figure 7 5B of the basic Pilot s Operating Handbook The L H light has a wide beam which facilitates tax...

Page 353: ...A NIGHT VFR EQUIPMENT SUPPLEMENT NIGHT VFR EQUIPMENT TABLE OF CONTENTS GENERAL Page 9 2 3 2 LIMITATIONS 9 2 14 3 EMERGENCY PROCEDURES 9 2 14 4 NORMAL PROCEDURES 9 2 16 5 PERFORMANCE 9 2 20 June 30 198...

Page 354: ...SUPPLEMENT 2A SOCATA NIGHT VFR EOUIPMENT INTENTIONALLY LEFT BLANK 9 2 2 January 31 1988...

Page 355: ...LOC Category 2 NAV oc Radio compass Category 2 ADF NAVIGATION EQUIPMENT Attitude gyro indicator Turn and bank indicator Heading indicator Gyro ON indicator Vertical speed indicator Anti collision ligh...

Page 356: ...r l I B U S BUS 2 BATTERY J l I 1 B U S 2 ALTERNATOR BUS 3 L l I B U S 9 2 4 c _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 3 AIR eOND If Installed PULL OFF TYPE CIRCUIT BREAKER PCB I EVAP FAN If Installe...

Page 357: ...rn and ban indicator Emergency lighting system ReO overhead light lighting Intercom Cloc Front overhead light lighting emergency Propeller de icing Chronometer Startcr relay Landing gear EHSI ADAPT HO...

Page 358: ...VFR EQUIPMENT 6 8 10 12 7 9 11 o 0 41 13 14 C 0 0 16 42 40 38 36 34 33 T I 25 D 26 45 44 1 3 a I 27 3LilYo 43 3 t Y 28 29 SQCATA 17 19 21 18 20 24 23 22 Figure 9 2 3 EXAMPLE OF INSTRUMENT PANEL VFR 9...

Page 359: ...17 VOR I LOC indicator 18 R H instrument panel visor lighting I 19 Illuminated tachometer Std or Post MOD 151 illuminated tachometer hourmeter Std 20 Illuminated manifold pressure fuel flow pressure d...

Page 360: ...olled and regulated by Normal and Radio controls EMERGENCY LIGHTING Pre MOD 151 Front overhead lights controlled by turning post lights and regulated by the Emergency control See Figure 9 2 3 Post MOD...

Page 361: ...SOCATA June 30 1988 Revision 3 SUPPLEMENT 2A NIGHT VFR EQUIPMENT INTENTIONALLY LEFT BLANK 9 2 9...

Page 362: ...SUPPLEMENT 2A SQCATA NIGHT VFR EQUIPMENT 2_ o o Figure 9 2 4 ANTENNAS I 9 2 10 June 30 1988 Revision 3...

Page 363: ...SOCATA ANTENNAS 1 VHF antenna 2 VOR antenna SUPPLEMENT 2A NIGHT VFR EQUIPMENT 3 Radio compass loop and sense antenna I June 30 1988 Revision 3 9 2 11...

Page 364: ...aculta tlVe in VFR PULL OFF TYPE CIRCUIT BREAKER Facultative in VFR tJ OPTIONAL SWITCH ceG G 0 O AT 0 co COM AUDIO 0 0 Ai P TRIM LlGHTE AUDIO 0 SWITCH OOFFtJ ON 0 ALTr FLO 0 0 0 0 0 ALT BAT BUS BUS BU...

Page 365: ...CUIT BREAKER PULL OFF TYPE CIRCUIT BREAKER o CIRCUIT BREAKER Faculta tlVe in VFR PULL OFF TYPE CIRCUIT BREAKER Facultative in VFR tJ OPTIONAL SWITCH o OHSI HORO Figure 9 2 SA CIRCUIT BREAKERS ASSEMBLY...

Page 366: ...SUPPLEMENT 2A NIGHT VFR EOUIPMENT INTENTIONALLY LEFT BLANK 9 2 12B SOCATA June 30 1988 Revision 3...

Page 367: ...1 Alternator Pull off type circuit breaker 60 A 2 Battery Pull off type circuit breaker 70 A 3 BUS bar 1 Pull off type circuit breaker 30 A 4 BUS bar 2 Pull off type circuit breaker 30 A 5 BUS bar 3 P...

Page 368: ...These procedures supplement those of standard airplane described in Section 3 Emergency procedures of the basic Pilot s Operating Handbook NORMAL LIGHTING FAILURE Switch on emergency lighting system...

Page 369: ...pull ofF type circuit breaker and reconnect one after the other all the disconnected equipment until the faulty equipment is found and isolated Let the pull off type circuit breaker tripped for this i...

Page 370: ...ply with regulations BEFORE FLIGHT may be undertaken or continued at night Check the operation of anti collision light s of navigation lights of cabin and instrument panel lighting of landing lights o...

Page 371: ...ON RUNWAY Check heading indicator and attitude gyro indicator bar At night turn on landing lights as required TAKE OFF See Section 4 Normal procedures of the basic Pilot s Operating Handbook Always ma...

Page 372: ...Gal Litres I hr I hr Up 0 120 137 2500 19 11 7 44 Down 0 120 137 2500 25 3 16 5 62 Level flight holding Up 0 100 112 2500 16 9 34 Down 0 100 112 2500 22 13 49 Up 0 100 112 2500 17 9 34 Approach Desce...

Page 373: ...all receptions are simultaneous LIGHTING Three controls are located on the left side of the L H instrument panel See Figure 9 2 3 Lower control normal Controls and regulates lighting of L H and R H in...

Page 374: ...ers See Figure 7 5B of the basic Pilot s Operating Handbook The L H light has a wide beam which facilitates taxiing The R H light has a long range beam and should be used for take off and landing Simu...

Page 375: ...E ICING T K S SUPPLEMENT PROPELLER DE ICING T K S OPTIONAL EQUIPMENT W 522 TABLE OF CONTENTS Page GENERAL 9 5 3 2 LIMITATIONS _ 9 5 3 3 EMERGENCY PROCEDURES 9 5 4 4 NORMAL PROCEDURES _ 9 5 4 5 PERFORM...

Page 376: ...SUPPLEM ENT 5 SOCATA PROPELLER DE ICING T K S INTENTIONALLY LEFT BLANK 9 5 2 January 31 1988...

Page 377: ...tem control box is located on R H side of the lower panel strip on pilot sside 11 consists of a three position switch LO low flow maximum endurance 2 hr 10 OFF stop HI high flow maximum endurance 1 hr...

Page 378: ...ICING instructions given in Section 3 Emergency procedures as well as the procedure given hereafter Position the PROP DE ICING switch on LO or HI in case of severe icing Check the operation yelJow war...

Page 379: ...Litres 2 Liter 0 44 UK Gal 0 53 US Gal I TKS 80 I au or oder GlYCOLBO EAU WATER WASSER 20 SECTION 5 PERFORMANCE The installation and the operation of the propeller de icing system T K S do not change...

Page 380: ...SUPPLEMENT 5 SOCATA PROPELLER DE ICING T K S D G A C Approved INTENTIONALLY LEFT BLANK 9 5 6 January 31 1988...

Page 381: ...AP 100 SUPPLEMENT KING AUTOPILOT TYPE KAP 100 OPTIONAL EQUIPMENT N 668 TABLE OF CONTENTS Page GENERAL 9 7 3 2 LIMITATIONS 9 7 14 3 EMERGENCY PROCEDURES 9 7 15 4 NORMAL PROCEDURES _ 9 7 16 5 PERFORMANC...

Page 382: ...ENT 7 SOCATA KING AlP KAP 100 9 7 2 Figure 9 7 1 KC 190 AUTOPILOT COMPUTER 2 3 4 10 9 8 7 6 5 11 2 12 13 4 c NAV ARM AP HOG APR CPLD 2 2 14 3 Figure 9I2 KA 185 REMOTE MODE ANNUNCIATOR Option January 3...

Page 383: ...he figures of this supplement The KAP 100 Autopilot has an optional electric pitch trim system The trim system is designed to withstand any single inflight malfunction A trim fault is visually and aur...

Page 384: ...2 seconds AUTOPILOT ENGAGE AP ENG BUnON When pushed engages autopilot if all logic conditions are met When pushed again disengages autopilot PREFLIGHT TEST TESn BUnON When momentarily pushed initiates...

Page 385: ...until the automatic capture sequence is initiated On the KA 185 remote mode annun ciator NAV ARM will annunciate until the automatic capture sequence is initiated At beam capture NAV CPLD will annunc...

Page 386: ...LIGHTS Remote Airway Outer and Middle Marker Beacon lights driven by the Marker Beacon receiver MIC TRIM DN V __TRIM UP 16 APDtSC TRIM tNT Item 15 9 7 6 Figure 9 7 3 AUTOPILOT CONTROL WHEEL SWITCH CA...

Page 387: ...nual electric trim A split switch unit in which the left half provides power to engage the trim servo clutch and the right half to control the direction of motion of the trim servo motor Both halves o...

Page 388: ...ctorial presentation of airplane deviation relative to VOR radials or localizer beams It also displays Glide Slope deviations and gives heading reference with respect to magnetic north Item 27 NAV FLA...

Page 389: ...to selected course Item 32 DUAL GLIDE SLOPE POINTERS Indicate on Glide Slope scale Item 33 airplane displacement from Glide Slope beam center Glide Slope pointers in iew indicate a usable Glide Slope...

Page 390: ...SUPPLEMENT 7 KING AlP KAP 100 27 26 39 38 33 37 36 28 c N KI G Figure 9 7 5 KI 525 HSI 28 t Figure 9I6 KG 107 DG 9 7 10 SOCATA 29 30 31 32 33 34 35 39 35 34 January 31 1988...

Page 391: ...BUG Moved byQ knob Item 34 to select desired heading KG 107 NON SLAVED DIRECTIONAL GYRO DG Provides a stable visual indication of airplane heading to the pilot The gyro is air driven Item 41 GYRO ADJU...

Page 392: ...tion needle displace ment of 5 dots represents full scale o r deviation above or below Glide Slope beam centerline Item 47 RECIPROCAL COURSE INDEX Indicates reciprocal of selected VOR course Item 48 O...

Page 393: ...ASTER switch supplies power to the AUTOPILOT A I P circuit breaker The following circuit breakers are used to protect the following ele ments of the KING KAP 100Autopilot AlP TRIM HSI January 31 1988...

Page 394: ...off and landing and during approach under 200 ft height A Engagement height in climb and cruise 1000 ft B It is forbidden to operate TEST button in flight C Maximum fuel imbalance 20 U SGal T820 T821...

Page 395: ...8 10 and TB 200 airplanes PRESS to disengage autopilot B Systems with Autopilot and optional manual electric trim In case of Autopilot malfunction accomplish the two following items simultaneously Air...

Page 396: ...lectric trim did not pass preflight test The trim circuit breaker should be pulled The autopilot can still be used MANUAL ELECTRIC TRIM if installed TEST as follows a Actuate the left side of the spli...

Page 397: ...topilot engagement AP ENG button PRESS Note AP annunciator on If no other modes are selected the autopilot will operate in the wings level mode Heading changes aJ Manual heading changes with optional...

Page 398: ...KNOB SET BUG to provide desired inter cept angle NAV Mode Selector Button PRESS If the Course Deviation Bar is greater than 2 to 3 dots the airplane will continue in HDG mode or wings level if HDG no...

Page 399: ...ll be automatically captured and tracked If the D BAR is less than 2 to 3 dots the HDG mode will disen gage upon selecting NAV mode the NAV annunciator will illuminate steady and the capture I track s...

Page 400: ...el if HOG not selected with the APR annunciator flashing when the computed capture point is reached the HDG will disengage the APR annunciator will illuminate steady and the selected course will be au...

Page 401: ...front course inbound heading NOTE When equipped with NAV 1 NAV 2 switching and NAV 2 is selected set ass to the ILS front COUf5e inbound heading HEADING Selector Knob SET BUG to provide desired inter...

Page 402: ...point is reached the HDG annunciator will go out the Be and APR annuncia tors will illuminate steady and the selected course will be automatically captured and tracked If the D BAR is less than 2 to 3...

Page 403: ...MENT 7 KING AlP KAP 100 The installation and the operation of the autopilot do not change the basic performance ofthe airplane described in Section 5 Performance of the basic Pilot s Operating Handboo...

Page 404: ...SUPPLEMENT 7 KING AlP KAP 100 INTENTIONALLY LEFT BLANK 9 7 24 SOCATA January 31 1988 Revision 1...

Page 405: ...150 KAP 150 SUPPLEMENT KING AUTOPILOT TYPE KFC 150 AND KAP 150 TABLE OF CONTENTS Page 1 GENERAL 9 8 3 2 LIMITATIONS 9 8 17 3 EMERGENCY PROCEDURES 9 8 18 4 NORMAL PROCEDURES 9 8 19 5 PERFORMANCE 9 8 2...

Page 406: ...0 15 14 13 12 11 10 9 8 7 Figure 9 8 1 KC 192 AUTOPILOT FLIGHT DIRECTOR COMPUTER FOR KFC 150 16 3 4 3 5 6 1 k rr nI ALT HOG GS NAV APR Be T ij I f7 f I 15 13 12 11 10 9 8 7 Figure 9 8 2 KC 91 AUTOPILO...

Page 407: ...tch trim system which provides autotrim during autopilot operation and manual electric trim for the pilot The trim system is designed to withstand any single inflight malfunction Trim faults are visua...

Page 408: ...TOR Illuminates continuously whenever the autopilot is coupled to the Glide Slope signal The GS annunciator will flash ifthe Glide Slope signal is lost GS flag in CDr or absence of Glide Slope pointer...

Page 409: ...pilot is engaged Flashes approximately 12 times whenever the autopilot is disengaged an aural alert will also sound for 2 seconds Item 7 Item 8 AUTOPILOT ENGAGE AP ENG BUTTON When pushed engages autop...

Page 410: ...or APR ARM will annunciate until the automatic capture sequence is initiated At beam capture APR CPLD will annunciate 11em 11 NAVIGATION NAV MODE SELECTOR BUTTON When pushed will select the Navigation...

Page 411: ...er switch fitted with a return to neutral position through a spring allows nose down and nose up maneuvers adjusts in ALT altitude at a rate of about 500 ft I min adjusts when not in ALT pitch attitud...

Page 412: ...AUTOPILOT DISCONNECTITRIM INTERRUPT AP DISCTRM INT Switch When depressed will disengage the autopilot and cancel all operating Flight Director modes When depressed and held will interrupt all electri...

Page 413: ...half to control the direction of motion of the trim servo motor 80th halves of the split trim switch must be actuated in order for the manual trim to operate in the desired direction When the autopil...

Page 414: ...PLEMENT 8 SOCATA KING A I P KFC 150 KAP 150 28 26 27 U t 31 32 Figure 9 8 5 KI 256 FLIGHT COMMAND INDICATOR FOR KFC 150 33 27 35 INCi Figure 9 B 6 KG 258 VERTICAL GYRO FOR KAP 150 9 8 10 January 31 19...

Page 415: ...ATA 38 37 36 49 48 43 47 46 SUPPLEMENT 8 KING AI P KFC 150 KAP 150 39 OG 40 41 42 43 44 45 Figure 9 8 7 KI525A HSI FOR KFC 150 38 50 Figure 9 B 8 KG 107 DG FOR KAP 150 January 31 1988 Revision 5 45 9...

Page 416: ...SUPPLEMENT 8 KING AI P KFC 150 KAP 150 40 38 41 48 __I Figure 9 B SA EHSI 9 8 11A 49 SOCATA 36 43 42 45 44 January 31 1988 Revision 6...

Page 417: ...A 52 o 60 SUPPLEMENT 8 KING A P KFC 150 KAP 150 37 41 55 48 56 57 Figure 9 8 9 KI 204 206 VOR LOC GS INDICATOR 62 61 j 59 January 31 1988 Revision 6 53 o 37 56 Figure 9 8 SA Gl10SA COl 41 54 60 48 55...

Page 418: ...ll attitude is displayed by the relationship between the fixed symbolic airplane and the movable background During flight director operation the symbolic airplane is flown to align it with the command...

Page 419: ...ch would be used to manually maneuver the airplane laterally Item 40 COURSE BEARING POINTER Indicates selected VOR course or localizer course on compass card Item 45 The selected VOR radial or localiz...

Page 420: ...NM RNAVAPR 1 25 NM deviation from beam centerline I Item 49 HEADING BUG Moved by 9 or U knob Item 44 to select desired heading Item 50 KG 107 NON SLAVED DIRECTIONAL GYRO DG Provides a stable visual in...

Page 421: ...d VOR course Item 58 OMNI BEARING SELECTOR OBS KNOB Rotates course card to selected course Item 59 COURSE DEVIATION NEEDLE Indicatescoursedeviationfrom selected omni course or localizer centerline Ite...

Page 422: ...OT or NP circuit breaker The following circuit breakers are used to protect the following elements of the King 150 Series Autopilot LABEL FUNCTION AlP TRIM HSI I 9 8 16 Supplies power to the KC 192 or...

Page 423: ...t C Engagement height in climb and cruise 1000 ft o The system is approved for Category I operation only Approach mode selected E It is forbidden to operate TEST button in flight F Autopilot maximum a...

Page 424: ...itch trim wheel If pitch trim wheel is in motion follow the B procedure given hereafter B In case of manual electric trim malfunction AP DISC TRM INT switch PRESS and HOLD throughout recovery TRIM cir...

Page 425: ...remain off NOTE Iftrim warning light stays on then the autotrim did not pass preflight test The autopilot circuit breaker should be pulled Manual electric trim and autopilot will be inoperative MANUA...

Page 426: ...airplanes The minimum recommended airspeed for autopilot operauon is 8DK AS Before take off AP DISC TRM INT Switch PRESS Inflight Autopilot engagement a FD Mode Selector Button KFC 150 Only PRESS b AP...

Page 427: ...n the selected pressure attitude b Change selected altitude Using CWS recommended for altitude changes greater than 100 ft CWS Button PRESS and reach desired pressure altitude CWS Button RELEASE when...

Page 428: ...d heading HOG Mode Selector Button PRESS Note HDG mode annunciator ON Autopilot will automatically turn the airplane to the selected heading c Command Turns Heading Hold mode ON HEADING Selector Knob...

Page 429: ...G NOTE ass Knob SELECT desired course NAV Mode Selector Button PRESS Heading Selector Knob ROTATE BUG to agree with ass course When NAVis selected the lateral operating mode will change from HDG if se...

Page 430: ...om airplane heading AutopilotAPR mode operation should be discontinued whenever high engine power settings are anticipated This can be done by switching to HDG mode or CWS mode or by switching off the...

Page 431: ...n the position of the bug If the D Bar is greater than 2 to 3 dots the autopilot will annunciate HOG mode unless HOG not selected and APR flashing when the computed capture point is reached the HOG an...

Page 432: ...quipped with DG NOTE OSS Knob SELECT the ILS front course inbound heading Be mode Selector Button PRESS Heading Selector Knob ROTATE Bug to the lLS front course inbound heading When Be is selected the...

Page 433: ...SED APPROACH EXECUTE c CWS Button PRESS KFC 150 only as desired to activate FD mode during go around maneuver d AP ENG BUnON PRESS If A I P operation is desired Note M annunciator ON NOTE If it is des...

Page 434: ...TIONS PERFORMANCE SOCATA The installation and the operation of the autopilot do not change the basic performance of the airplane described in Section 5 Performance H of the basic Pilot s Operating Han...

Page 435: ...S SUPPLEMENT OXYGEN EQUIPMENT PURITAN BENN ETT I FRONT SEATS PRESSURE DEMAND TYPE MASKS OPTIONAL EQUIPMENT N 621 622 623 TABLE OF CONTENTS Page GENERAL 9 10 3 2 LIMITATIONS 9 10 3 3 EMERGENCY PROCEDUR...

Page 436: ...SUPPLEMENT 10 OXYGEN EQUIPMENT PURITAN BENNETT I FRONT SEATS PRESSURE DEMAND TYPE MASKS INTENTIONALLY LEFT BLANK 9 10 2 SOCATA January 31 1988 Revision 3...

Page 437: ...pressure demand type regulator and with a microphone The regulator possesses a two position selector Normal and 100 Pressure demand type masks have a pressure indicator The latter shows in case of nor...

Page 438: ...letely filled with a pressure of 126 bars approximately 1850 psi When pressure is different the endurance is proportional to the pressure in the cylinder For use limitations of oxygen equipment comply...

Page 439: ...rn on oxygen system valve on ON The flow must be established in constant flow masks at each inhaling in the mask the flow indicator is green Test the pressure demand type masks the pressure indicator...

Page 440: ...pressure indicators and the oxygen reserve WARNING SMOKING IS STRICTLY PROHIBITED ANY TIME OXYGEN IS IN USE lOlL FATTY OR GREASY SUBSTANCES INCLUDING SOAPS LIPSTICK AFTER SHAVE LOTION AND MAKE UP ARE...

Page 441: ...KS SUPPLEMENT OXYGEN EQUIPMENT PURITAN BENNETT FRONT SEATS CONSTANT FLOW TYPE MASKS TABLE OF CONTENTS Page 1 GENERAL 9 10A 3 2 LIMITATIONS 9 10A 3 3 EMERGENCY PROCEDURES 9 10A 4 4 NORMAL PROCEDURES 9...

Page 442: ...SUPPLEMENT lOA OXYGEN EQUIPMENT PURITAN BENNETT FRONT SEATS CONSTANT FLOW TYPE MASKS INTENTIONALLY LEFT BLANK 9 10A 2 SOCATA April 30 1997...

Page 443: ...cator giving the pressure in the cylinder Four quick disconnect connectors allow to connect four masks Two masks front are equipped with a microphone The four masks are of constant flow type Masks wit...

Page 444: ...mpletely filled with a pressure of 126 bars approximately 1850 psi When pressure is different the endurance is proportional to the pressure in the cylinder For use limitations of oxygen equipment comp...

Page 445: ...st mandatorily use a mask fitted with a mike Turn on oxygen system valve on ON The flow must be established in constant flow masks At each inhaling in the mask the flow indicator is green Turn off the...

Page 446: ...Handbook A OPTIONAL EQUIPMENT a 35 OXYGEN T820 T821 A Oxygen system equipment Pre MOD 15t OPT1Q 062115 M A Oxygen system equipment Post MOD 151 OPTIO 062105 M A Oxygen constant flow masks with radio...

Page 447: ...OUND POWER RECEPTACLE SUPPLEMENT GROUND POWER RECEPTACLE TABLE OF CONTENTS GENERAL Page 9 13 3 2 LIMITATIONS 9 13 3 3 EMERGENCY PROCEDURES 9 13 4 4 NORMAL PROCEDURES 9 13 4 5 PERFORMANCE 9 13 6 June 3...

Page 448: ...SUPPLEMENT 13 SOCATA GROUND POWER RECEPTACLE INTENTIONALLY LEFT BLANK 9 13 2 January 31 1988...

Page 449: ...ery catt external power source to prevent damage to the avionics equipment by transient voltage NOTE I The auxiliarypowersource relay disconnects batteryautomatically when the ground power receptacle...

Page 450: ...e starting using auxiliary power does not change the basic procedures however WARNING IF THE BATIERY HAS BEEN REMOVED BEFORE CONNECTING THE AUXILIARY POWER SOURCE ISOLATE ELECTRICAL HARNESS TERMINAL L...

Page 451: ...rrectly connected to the airplane If the plug is accidentally connected backwards no power will flow to the electrical system thereby preventing any damage to electrical equipment The following check...

Page 452: ...5 PERFORMANCE SOCATA The installation and the operation of the ground power receptacle do not change the basic performance of the airplane described in Section 5 Performance of the basic Pilot s Opera...

Page 453: ...SUPPLEMENT AUXILIARY DRY AIR PUMP OPTIONAL EQUIPMENT Nr 632 TABLE OF CONTENTS Page GENERAL 9 14 3 2 LIMITATIONS ___ _ ____ ___ ___ 9 14 4 3 EMERGENCY PROCEDURES __ 9 14 5 4 NQRMALPRQCEDURES 9 14 6 5 P...

Page 454: ...SUPPLEMENT 14 AUXILIARY DRY AIR PUMP INTENTIONALLY LEFT BLANK 9 14 2 SOCATA January 31 1988...

Page 455: ...circuit 1 a 10 amp circuit breaker for the power circuit At the head of the l H instrument panel 2 lights incorporating a press to test feature located on the alarms panel enable to check for conditi...

Page 456: ...on 2 Limitations of the basic Pilot s Operating Handbook These limits must be on a placard located at level with control switch of the auxiliary pump on L H instrument panel strip 9 14 4 AUX SUCT o ON...

Page 457: ...y procedures of the basic Pilot s Operating Handbook MAIN VACUUM PUMP FAILURE GYRO SUeT red light Suction gage Landing and taxiing lights Anticollision light if installed Strobe lights if installed AU...

Page 458: ...ch GYRO SUCT red light AUX SueT green light Main switch ON ON ILLUMINATED OFF GREEN SECTOR ON OFF ILLUMINATED OFF OFF DURING FLIGHT The auxiliary pump operation may lead to an electrical overload and...

Page 459: ...AL Page 9 15 2 2 LIMITATIONS 9 15 3 3 EMERGENCY PROCEDURES 9 15 6 4 NORMAL PROCEDURES 9 15 8 5 PERFORMANCE 9 15 13 6 WEIGHT AND BALANCE 9 15 15 7 DESCRIPTION 9 15 17 8 HANDLING SERVICING AND MAINTENAN...

Page 460: ...e Protection Systems are installed in accordance with the SOCATA I option No 687 or C6B OQM or C6B 05M or C68 25M refer to Section 6 of the present Supplement The information contained herein suppleme...

Page 461: ...d ALTERNATE AIR system must be applied On TB 21 SQCATA modification No 79 manually operated ALTERNATE AIR system is applied from SIN 1280 DE ICING FLUID CAUTION UNDER NO CIRCUMSTANCES ARE FLUIDS OTHER...

Page 462: ...r 40 minutes 2 minutes in every 30 minutes 5 seconds in every 10 minutes 2 hours 50 minutes With three blade propeller OPT10 61 001 version B Maximum system endurance With ANTI ICE selected 2 hours 50...

Page 463: ...EFER TO SECTION 8 OF T K S SUPPLEMENT TO PILOT S OPERATING HANDBOOK 3 Near the drain TKSSYSTEM Purge Drain Entleerung The following placard may be fitted 4 Near the instruction plate FLIGHT CONDITIONS...

Page 464: ...ntrol or prevent ice formation take immediate action to exit icing conditions in the most expedient manner Switch off TKS system and check fluid contents NOTE With the airplane in the climbing attitud...

Page 465: ...ct the airframe system and check operation If the low pressure warning is not cancelled within 30 seconds switch off and repeat priming sequence CAUTION THE WINDSCREEN PUMP IS INTERMITTENTLY RATED DO...

Page 466: ...GHT INSPECTIONS COCKPIT 1 Switches Prime and or inspect prior to flight Airframe propeller pump switch ANTI ICE I DE ICE Wing inspection light AIRFRAME INSPECTION 2 Fluid tank On ANTI ICE or DE ICE ON...

Page 467: ...TIALLY THEN CANCEL AS PRESSURE RISES WITH GREEN ANTI ICE ON NOTE REMAINING ILLUMINATED Select DE ICE CHECK THAT GREEN DE ICE ON IS ILLUMINATED If a delay occurs between the selection ofANTI ICE and DE...

Page 468: ...E If ice accreted before NOTE ice protection switched on DE ICE until ice cleared then ANTI ICE The time taken to remove established ice is variable and can be prolonged under certain circumstances es...

Page 469: ...ICING CONDITIONS CAUTION ON as required RETRACTION OF SEVERELY ICED LANDING GEAR MAY CAUSE DAMAGE The objective for holding in icing conditions is to use power and configuration settings which will pr...

Page 470: ...ended beyond the take off position If the windscreen is obscured by ice de ice in advance affinal approach and landing in order to allow sufficient time for ice removal and fluid dispersion ALTERNATE...

Page 471: ...On TB 21 A very severe icing of the engine air intake may cause a power drop which may bring about a loss of 5 kt on cruise speeds and 100 feet minute on rate of climb these alterations will be added...

Page 472: ...N ICEON UNPROTECTED REGIONS ONLY 2 knots per inch of ice thickness No significant change ICE ACCRETIONS OF A SIGNIFICANT SIZE CAN ACCUMULATE ON THE UNPROTECTED REGIONS OF THE AIRPLANE AFTER PROLONGED...

Page 473: ...craft OPT10 068700 M A Ice protection systems 28 VOC Pre MOD 151 Not valid for U S aircraft OPT10 C687 OOM A Ice protection systems 28 VDC Post MOD 1SI Not valid for U S aircraft OPT10 C687 05M A Ice...

Page 474: ...15 2 may be used Correction data is also shown in graphical form in Section 7 ofthis supplement Indicator True Weight Arm Moment contents reading U S Gal Ib in Ib in 1000 U S Gal Iitres kg m m kg 0 0...

Page 475: ...ccomplish filling Tank capacity is 7 8 U S Gal 29 6 litres The unusable volume is 0 1 U S Gal 0 4 litre with the airplane in the level attitude increasing to 1 45 U S Gal 5 5 litres in the climb attit...

Page 476: ...DE 10 5 0 NOSE UP 3 V 2 1 V n 0 1 I 2 3 4 o II 5 10 15 SOCATA FULL TO FILLER ORIFICE LEVEL 7 8 U S Gal 29 5 Litres Iii N V V 5 6 7 20 25 I I 4 I I I I i 8 I 30 TRUE TA CONTEN U SG NK TS allons Litres...

Page 477: ...LD NIGHT BRIGHTNESS LEVEL TRIMMER RECESSED RESET SWITCH Push button with ballpen pOint or similarto cancel high pressure warning DE_ICE FLUID nn LJ LJ o o DE_ICE FLASHING RED L Green Indicates DE_ICE...

Page 478: ...of the aitirame propeller ice protection system ANTI ICE or DE ICE in the event of low system pressure both lights flash red with the light appropriate to the current pump selection alternating red gr...

Page 479: ...PRESSURE WARNING SWITCH k_Lrr J DRAIN POROUS PANELS ON WING PROPORTIONING UNIT STRAINER TANK FILLING POINT VENTED POROUS P NELS ON VERTICAL STABILIZER FILTER J II II II II II CHECK VALVE QUANTITY TRA...

Page 480: ...HIGH PRESSURE II Jr rr Jr j WARNING SWITCH IT L L POROUS PANELS ON Q FILTER JL II II II II PROPORTIONING UNIT II 1 lF l I STRAINER TANK FILLING POINT VENTED POROUS PANELS ON VERTICAL STABILIZER CHECK...

Page 481: ...A system of plastic tubing carries the fluid to proportioning units located in rear fuselage The proportioning units divide the flow into the requirements of the individual regions fed from each propo...

Page 482: ...UMP I SOLENOiD VALVE _ _ 1 1 I _ WINDSCREEN PUMP HIGH PRESSURE WARNING r r I C3 CONNECTOR ON SUPPORT BAR V EAR H UDON EQUIPMENT PACK d77 WING INSPECTION LIGHT CONTENTS TRANSMITTER CONTROL PANEL SOCKET...

Page 483: ...o months for the first two years from new At the same time exercise the windshield pumps for several periods not exceeding 5 seconds each The two month interval between operation may be increased to a...

Page 484: ...ller is located on the left hand side of the fuselage just aft of the baggage compartment door To preclude the possibility of contamination always clean the top of fluid containers before dispensing I...

Page 485: ...priming The airframe propeller pump may not be self priming and is ground primed by first opening the drain valve to remove any air in the supply pipeline from the tank reference paragraph 1 of this...

Page 486: ...enance functions relating to the stall warning sensor are to be made as detailed in SOCATA Maintenance Manual Section X1 1 9 or Chapter 27 except that for access to and or removal of the unit it is fi...

Page 487: ...Water with soaps or detergents Approved de icing fluids Aviation gasoline Aviation turbine fuel Isopropyl alcohol Ethyl alcohol Industrial methylated spirit Cleaning of the porous panels will be great...

Page 488: ...cing severities for which the system is designed are based upon statistical data and more severe conditions may be encountered in nature It must therefore be emphasised that the pilot is an integral p...

Page 489: ...g or following icing conditions as the margin between operation ofthe wing mounted sensor and the aerodynamic stall may be affected by residual ice Depending upon circumstances it may be advisable to...

Page 490: ...POWER 100 90 ICE ON ENTIRE AIRPLANE CONFIGUR 1 H l STALLING SPEED TRENDS WITH ICE ON ENTIRE AIRPLANE lr C t b L CAUTION AT WITH LANDING FLAP EXTENDED AND ICE ot f t f ACCRETIONS ON THE STABILATOR PREM...

Page 491: ...EROS SUPPLEMENT OXYGEN EQUIPMENT EROS OPTIONAL EQUIPMENT N 617 618 619 TABLE OF CONTENTS Page GENERAL 9 18 3 2 LIMITATIONS __ 9 18 3 3 EMERGENCY PROCEDURES __ 9 18 4 4 NORMAL PROCEDURES 9 18 5 5 PERF...

Page 492: ...SUPPLEMENT 18 SOCATA OXYGEN EQUIPMENT EROS INTENTIONALLY LEFT BLANK 9 18 2 January31 1988...

Page 493: ...with self contained regulator and integral microphone The regulator can be set for either diluter demand or 100 oxygen operation The passenger masks are of constant flow type and can be set for two f...

Page 494: ...f 126 bar approximately 1850 psi When pressure is different the endurance is proportional to the pressure in the cylinder For use limitations of oxygen equipment comply with operational rules in force...

Page 495: ...fitted with a mike Turn on the oxygen system valve on uON The flow must be established in constant flow masks The flow indi cator moves towards the mask Test the pressure demand type masks the flow in...

Page 496: ...17 500 ft flow selection ring on HI NOTE In case of hypoxia or discomfort the HI position can be used at altitudes below 17500 ft Use of the 100 position on the regulators of the crew masks below20 0...

Page 497: ...CTION 5 PERFORMANCE The installation and the operation of the oxygen equipment EROS do Inot change the basic performance of the airplane described in Section 5 Performance ofthe basic Pilot s Operatin...

Page 498: ...SUPPLEMENT 18 SOCATA OXYGEN EQUIPMENT EROS INTENTIONALLY LEFT BLANK 9 18 8 January31 1988...

Page 499: ...ARNAV SUPPLEMENT FUEL FLOW TOTALIZER Fe I FT 10 ARNAV OPTIONAL EQUIPMENT N 821 and 0821 TABLE OF CONTENTS Page GENERAL 9 20 3 2 LIMITATIONS 9 20 8 3 EMERGENCY PROCEDURES 9 20 8 4 NORMAL PROCEDURES _ 9...

Page 500: ...SUPPLEMENT 20 FUEL FLOW TOTALIZER FC FT l0 ARNAV INTENTIONALLY LEFT BLANK 9 20 2 SOCATA January31 1991...

Page 501: ...procedure The FT 0 does not contain a memory retention battery However it is fitted with a RAM system which retains in memory the quantity of fuel burned during last flight B FUEL FLOW TOTALIZER FC 1...

Page 502: ...I SUPPLEMENT 20 FUEL FLOW TOTALIZER Fe I FT 10 ARNAV SOCATA PlACARD S 9 202 VARIANT O ILJ Y o I 1 2 4 Figure 9 20 1A 1 2 FT l0 fuel flow totalizer January 31 1991 Revision 3...

Page 503: ...RNAV BURN mode window fuel burned quantity mode 2 Fuel flow or fuel burned quantity display 3 CLR mode selection button dear 4 Button to zero the fuel quantity 5 Mode antral button Figure 9 20 lA 2 f...

Page 504: ...SUPPLEMENT 20 FUEL FLOW TOTALIZER Fe I FT l0 ARNAV SOCATA PLACARD See Figure 9 20 2 r F o W VARIANT 0 v I 2 3 1 4 6 Figure 9 20 1 B 1 12 FC l 0 fuel tlow totalizer 9 20 6 January 31 1991 Revision 3...

Page 505: ...entry 3 TIME mode window time remaining mode LOW mode window warning mode for time remaining 45 min 4 Fuel burned quantity or fuel remaining quantity display 5 Button for numberselection inside a colu...

Page 506: ...as a substitute to either the fuel gages or the analog fuel flow meter THE DIGITAL FUEL FLOW TOTALIZER SHALL SERVE AS SUBSTITUTE TO NEITHER THE FUEL GAUGES NOR THE ANALOG FUEL FLOW METER THE LATIER IN...

Page 507: ...BOARD IT IS ESSENTIAL THAT THE FUEL QUANTITY READING OF THE FUEL TOTALIZER IS PROGRAMMED TO READ THE SAME AS THE FUEL QUANTITY INDICATOR PRIOR TO FLIGHT GENERAL OPERATION PROCEDURES A FT 10 FUEL FLOW...

Page 508: ...ER PREFLIGHT o FLOW c b 9 20 10 o FLOW 1 When airplane electrical system is ON CHG IONBD appears NOTE It NWFL appears the flowmeter is not programmed refer to the Maintenance Manual 2 Since no fuel wa...

Page 509: ...d by the flowmeter use CLR IONBD mode by pressing MDE and REJ at the same time_ press OK to clear the amount recorded press R EJ to retu rn to CHG IONBD mode see Paragraphs 1 and 2 display FUL mode se...

Page 510: ...fuel burned since flight mode was entered_ The BURN light is ON whenever Fuel Burned is displayed CLR BURN DISPLAY Use the CLR BURN display to clear the fuel burned quantity CLR BURN is accessed from...

Page 511: ...ON whenever time remaining according to Fuel Flow I Fuel Remaining drops below45 min The lOW light can appear on any of the Flight Displays CAUTION REFER TO PARTICUlAR INSTRUCTIONS PROVIDED BY THE PLA...

Page 512: ...Return to factory and question whether transducer installed is correct for airplane E16 or E17 Indicates display malfunction Question validity of data and return to factory E18 E19 E 20 or E 21 Indica...

Page 513: ...FC FT l0 ARNAV SECTION 5 PERFORMANCE The installation and the operation of the fuel flow totalizer do not change the basic performance of the airplane described in Section 5 Performance of the basic...

Page 514: ...SUPPLEMENT 20 FUEL FLOW TOTALIZER FC FT 10 ARNAV INTENTIONALLY LEFT BLANK SOCATA january 31 1991...

Page 515: ...A HOSKINS SUPPLEMENT FU EL FLOW TOTALIZER FT 101 A HOSKINS OPTIONAL EQUIPMENT W 0838 TABLE OF CONTENTS Page GENERAL _ 9 21 3 2 LIMITATIONS 9 21 3 3 EMERGENCY PROCEDURES 9 21 3 4 NORMAL PROCEDURES 9 2...

Page 516: ...FUEL FLOW TOTALIZER FT 101 A HOSKINS FT 101 A SOCATA o oDDDD USED 0 o RESET TEST D S 9 9 212 00000 DO 00000_ 0 0 0 0 0 0 0 0 OOy 0 Cf g 0 0 Figure 9 21 1 FUEL FLOW TOTALIZER FT 101 A HOSKINS 9_21 2 Ja...

Page 517: ...ction 2 Limitations of the basic Pilot s Operating Handbook The fuel flow totalizer FT lOlA HOSKINS shall not be used as a substitute to either the fuel gages or the analog fuel flow meter THE DIGITAL...

Page 518: ...ET or USED I TEST button Once the RESET or USED TEST button is depressed the display will stop flashing and read fuel flow After starting the airplane engine the indicator will continuously display fu...

Page 519: ...999 pounds or 9999 litres depending on the mode Once this value is reached the next display will be that of a RESET function and the fuel used value will automatically begin at zero TEST FUNCTION A te...

Page 520: ...KINS SECTION 5 PERFORMANCE SOCATA The installation and the operation of the fuel flow totalizer do not change the basic performance of the airplane described in Section 5 Performance of the basic Pilo...

Page 521: ...EMENT I BFG WX 1000 1000 OR WX 900 OR WX 500 STORMSCOPE I TABLE OF CONTENTS Page 1 GENERAL 9 22 2 2 LIMITATIONS 9 22 2 3 EMERGENCY PROCEDURES 9 22 3 4 NORMAL PROCEDURES 9 22 3 5 PERFORMANCE 9 22 3 6 W...

Page 522: ...or areas of severe turbulence such intentional use is prohibited NOTE Range selector determines receiver sensitivity and therefore relative range Displayedrange is basedon signalstrength andis notto b...

Page 523: ...0 1 000 stormscopa Pilot s Handbook Range II No 75 0299 7690 1 at last revision Normal operating procedures are outlined in the BFG WX 900 stormscope Pilot s Guide Range II No 78 8060 6027 9 at last r...

Page 524: ...0 34 _ NAVIGATION A Stormscope WX l000 eFG on panel strip JB2000M A Stormscope WX l0DO eFG on R H instrument panel J820 10M A Stormscope WX 1000 eFG J82800M A Siormscope WX l000 eFG with converter as...

Page 525: ...to detect severe thunderstorm activity Stormscope information dots or strike points according to stormscope type will be displayed on the screen to indicate the electrical discharge areas Stormscope...

Page 526: ...SUPPLEMENT 22 SOCATA I BFG IX lOCO I IX I000 OR IX 900 OR IX SOO STORMSCOPE INTENTIONALLY LEFT BLANK 9 22 6 January 31 1991 Revision 5...

Page 527: ...ITIONING SYSTEM OPTIONAL EQUIPMENT N F845 TA8LE OF CONTENTS Page GENERAL _ 9 23 3 2 LIMITATIONS ___ _ 9 23 3 3 EMERGENCY PROCEDURES 9 23 3 4 NORMAL PROCEDURES _____ 9 23 4 5 PERFORMANCE 9 23 5 6 WEIGH...

Page 528: ...SUPPLEMENT 23 SOCATA AIR CONDITIONING SYSTEM INTENTIONALLY LEFT BLANK 9 23 1 January31 1991...

Page 529: ...ing engine starting The air conditioning system must be OFF for take off and landing The air conditioning system must be OFF when alternator is inoperative When air conditioning system is ON monitor a...

Page 530: ...ting air conditioning system Doors Pilot s front passenger vents Temperature rheostat Air conditioning switch Temperature rheostat Fan rheostat Engine RPM BEFORE TAKE OFF Air conditioning switch TAKE...

Page 531: ...ed next to the air conditioning control switch illuminates To reengage the air conditioning system turn the control switch to FAN I RESET the amber warning light switches off DO NOT TURN ON until the...

Page 532: ...ling may be selected During ground operation 1500 RPM should be maintained in order to assure an electrical flow sufficient forthe alternator The installation Figures 9 23 1 and 9 23 2 includes a cond...

Page 533: ...R BOTTLE fO d CONDENSER FAN EVAPORATOR AIR VENTS CONTROL OX See Figure 9 23 2 cr AMMETER r COMPRESSOR KEY CONDENSER COOLING AIR CONDITIONED AIR E s AIR TO BE REFRESHED _ HIGH PRESSURE SYSTEM z lOW PRE...

Page 534: ...IGHT M 0 0 0 0 0 0 RM snoaES SWITCH o Off 6 0N 0 ALT CO STORM Do ICE CONDo 0 0 0 0 0 BUS B S B S 8ATTERY 8 AMBER CA BIN CABIN CONTROL SWITCH TEMF ERATURE TEMPERATURE WARNING RHEOSTAT SWITCH LIGHT TOAI...

Page 535: ...3 4 SUPPLEMENT KEITH AIR CONDITIONING SYSTEM TABLE OF CONTENTS GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE DESCRiPTION September 30 1994 Revision 3 Page...

Page 536: ...SUPPLEMENT 2 SOCATA KEITH AIR CONDITIONING SYSTEM INTENTIONALLY LEFT BLANK September 30 1994...

Page 537: ...andbook The air conditioning system must be OFF during engine starting The air conditioning system must be OFF when alternator is inoperative SECTION 3 EMERGENCY PROCEDURES These procedures supplement...

Page 538: ...N With 70 amp alternator Day operation Air conditioning switch Night operation Air conditioning switch With 90 amp alternator Day or night operation Air conditioning switch BEFORE TAKE OFF Air conditi...

Page 539: ...selected and main gear strut extended In this case the warning light located next to the air conditioning control switch goes OFF To reset the air conditioning system turn the control switch to OFF T...

Page 540: ...supplement those given for the standard aircraft in Section 6 Weight and balance of the basic Pilot s Operating Handbook A OPTIONAL EQUIPMENT EQUIPMENT SUPPLIER 0 21 ENVIRONMENTAL SYSTEM A Air conditi...

Page 541: ...eat exchanger an evaporator blower a receiver drier a thermostatic expansion valve with remota bulb I a freeze switch if installed and wired an overpressure relief valve a binary pressure switch a sig...

Page 542: ...H side fuselage skin between the bulkhead C6 and the frame C5 The air outlet is located on the bulkhead C6 The condenser blower provides cooling airflow across the condenser heat exchanger The conden...

Page 543: ...te bulb sensing the evaporator outlet temperature The thermostatic expansion valve is screwed on the evaporator inlet The system lowside and high side service values are installed on a cross or a tee...

Page 544: ...mpurities particules and reaches the thermostatic expansion valve at the evaporator inlet The remote bulb senses the evaporator outlet temperature and throttles the thermostatic valve to modulate and...

Page 545: ...additional microswitch on the throttle in the pedestal To reengage the system set HAIR CONDITIONING switch to OFF and back to AIR CONon The electric protection of the air conditioning system is ensure...

Page 546: ...Evaporator heat exchanger 4 Evaporator blower 5 Condenser blower 6 Receiver drier 7 Condenser heat exchanger B Condenser airtight housing 9 Service valves 10 Overhead distribution duct SOCATA Figure...

Page 547: ...SOCATA N N SUPPLEMENT 24 KEITH AIR CONDITIONING SYSTEM l __ _ Figure 9 24 1 2 3 KEITW AIR CONDITIONING SYSTEM I September 30 1994 Revision 3 9 24 13...

Page 548: ...SUPPLEMENT 24 SOCATA KEITH AIR CONDITIONING SYSTEM o Figure 9 24 1 3 3 KEITW AIR CONDITIONING SYSTEM I 9 24 14 September 30 1994 Revision 3...

Page 549: ...NT 2 KEITH AIR CONDITIONING SYSTEM AIR CONDITIONING AIR COND HI FAN OFF FAN Lo FAN 1 Operation control switch 2 Speed control switch 3 Light 2 3 Ale Figure 9 24 2 CONTROL PANEL I September 30 1994 Rev...

Page 550: ...SUPPLEMENT 24 KEITH AIR CONDITIONING SYSTEM INTENTIONALLY LEFT BLANK I 9 24 16 SOCATA September 30 1994 Revision 3...

Page 551: ...NAVIGATION SYSTEM INTERFACED WITH HSI KI 525A OPTIONAL EQUIPMENT No J870 00 J870 30 J870 40 TABLE OF CONTENTS Page GENERAL 9 25 3 2 LIMITATIONS 9 25 4 3 EMERGENCY PROCEDURES 9 25 5 4 NORMAL PROCEDURES...

Page 552: ...SUPPLEMENT 25 GARMIN 100 AVD GPS NAVIGATION SYSTEM INTERFACED WITH HSI KI 525A SOCATA INTENTIONALLY LEFT BLANK 9 25 2 September 30 1994 Revision 2...

Page 553: ...aft is equipped with the option GARMIN 100 AVD GPS NAVIGATION SYSTEM INTERFACED WITH HSI K1525A Using information provided by satellites GARMIN 100 AVO is able to track up to 8 satellites at a time GP...

Page 554: ...ccordance with FAA notice 8110 47 dated 23 April 93 This equipment is approved for use as a VFR navigation system for en route and terminal area only Therefore GPS navigation must be crosschecked with...

Page 555: ...n Section 3 Emergency procedures of the basic Pilot s Operating Handbook when the aircraft is equipped with the option GARM1N 100 AVD GPS NAVIGATION SYSTEM INTERFACED WITH HSI KI S2SA If GARMIN 100 AV...

Page 556: ...are outlined in the GARMIN 100 AVD Owner s Manual at the latest revision However it is essential to precise the following points SET UP CONDITIONS Verify if the data base is current Check that COl se...

Page 557: ...hat require immediate attention such as an arrival alarm or a loss of GPS data generate a quick tone that will not stop until MSG key is pressed All other messages generate a slow tone that will cease...

Page 558: ...navigation parameters are presented on the Hsr as desired track DTK information cross track error XTK About one minute prior to reaching a waypoint MSG alarm lights on audio warning is on for 15 seco...

Page 559: ...INT WITH THE AUTOPILOT ENGAGED DN NAV MODE AND USING GPS DATA IF THE COURSE POINTER IS NDT ADJUSTED AT THE VALUE OF THE NEW DESIRED TRACK AND IF THE COURSE CHANGE IS MORE THAN So THE FLIGHT DIRECTDR A...

Page 560: ...not change the performance of the aircraft described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Weight and balance corresponding to the GARMIN 100 AV...

Page 561: ...m of the LCD Alphanumeric keys on the right of the LCD are used to enter data The rocker key activates a cursor that can be moved on the page to locations called fields This function is visible by an...

Page 562: ...SUPPLEMENT 25 GARMIN 100 AVD GPS NAVIGATION SYSTEM INTERFACED WITH HSI KI 525A CJ CJ POWER BRIGHTNESS NAVIGATION PAGES KEYS Figure 9 25 2 Controls 9 2S 12 SOCATA September 30 1994 Revision 2...

Page 563: ...ATA o SUPPLEMENT 25 GARMIN 100AVD GPS NAVIGATION SYSTEM INTERFACED WITH HSI KI525A MSG o GPS MESSAGE J WARNING LIGHT GPS BUTTON SWITCH Figure 9 25 3 GPS annunciators September 30 1994 Revision 2 9 25...

Page 564: ...SUPPLEMENT 25 GARMIN 100 AVD GPS NAVIGATION SYSTEM INTERFACED WITH HSI KI 525A SOCATA INTENTIONALLY LEFT BLANK 9 25 14 September 30 1994 Revision 2...

Page 565: ...NAVIGATION SYSTEM INTERFACED WITH HSI KI 525A OPTIONAL EQUIPMENT No K860 1OM K860 30M K86040M TABLE OF CONTENTS Page 1 GENERAL 9 26 3 2 LIMITATIONS 9 26 4 3 EMERGENCY PROCEDURES 9 26 5 4 NORMAL PROCE...

Page 566: ...SUPPLEMENT 26 BENDIX KING KLN90A GPS NAVIGATION SYSTEM INTERFACED WITH HSI KI525A INTENTIONALLY LEFT BLANK 9262 SOCATA January 15 1995...

Page 567: ...tes BENDIX I KING KLN90A is able to track up to 8 satellites at a time GPS is an automatic tridimensional latitude longitude altitude location and navigation means It also uses data recorded in a data...

Page 568: ...WGS 84 geodetic datum It the data base or chart are not referenced to WGS 84 or to NAD 83 geodetic datum in the absence of agreed operating procedure the GPS navigation must be disabled for terminal a...

Page 569: ...on 3 Emergency procedures of the basic Pilot s Operating Handbook when the aircraft is equipped with the option BENDIX I KING KLN90A GPS NAVIGATION SYSTEM INTERFACED WITH HSI KI525A If KLN90A GPS info...

Page 570: ...nticipation mode SET 6 to ENABLE turn anticipation ENABLED recommended mode DISABLE turn anticipation DISABLED not recommended mode Check that the proper criteria are used for nearest airport selectio...

Page 571: ...rn completion WARNING TURN ANTICIPATION IS AUTOMATICALLY DISABLED FOR WAVPOINTS USED EXCLUSIVELY IN SID I STARS WHERE OVERFLIGHT IS REQUIRED FOR WAYPOINTS SHARED BETWEEN SID I STARS AND PUBLISHED EN R...

Page 572: ...C Approved SYSTEM SWITCHES I NAV1 1 GPS This button switch is used for selecting data to be presented on the pilot s HSI either NAV data from the number one navigation receiver or GPS data from the K...

Page 573: ...age Page of the new desired track to select on the HSI This message will not be given if the course change is less than 5 CAUTION IT IS RECOMMENDED TO USE KLN90A WITH TURN ANTICIPATION ENABLED WHEN TU...

Page 574: ...in the case of the KFC 1SO autopilot When AP is engaged on the mode controller the autopilot is coupled to the HSI WARNING WHEN CROSSING A WAYPOINT WITH THE AUTOPILOT ENGAGED ON NAV MODE AND USING GPS...

Page 575: ...ot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement those given for the standard aircraft in Section 6 Weight and balance of the basic Pilot s Operating Handbook A TE...

Page 576: ...ered pages at once With a few exceptions each of these pages can be changed independently Generally the 2 concentric knobs and the cursor button to the left of the screen are used to select data on l...

Page 577: ...R JACK 1 LEFTCURSQR LEFT ourER RIGHT CURSOR KNOB BunON LEFT PAGE RIGHT PAGE n L__________ POWER BRIGHTN7 KNOB r mO USH o S UP AOV O ll1ER 1 1 ill 1m I IENTJ REf LEFT INNER KNOB MESSAGE BUnON January 1...

Page 578: ...NAVIGATION SYSTEM INTERFACED WITH HSI KI 525A LJ D I ANNUNCIATORS I GPS NOT APPROVED FOR NAVIGATION AS A PRIMARY SOURCE MSG NAV1 GPS BunON 5WlTCH AND LIGHTS SOCATA Figure 9 26 3 GPS placard and annunc...

Page 579: ...NOISE EXHAUST OPTIONAL EQUIPMENT N ABBB TABLE OF CONTENTS Page 1 GENERAL 9 29 3 2 liMITATIONS 9 29 3 3 EMERGENCY PROCEDURES 9 29 3 4 NORMAL PROCEDURES 9 29 4 S PERFORMANCE 9 29 5 6 WEIGHT AND BALANCE...

Page 580: ...SUPPLEMENT 29 SOCATA LOW NOISE EXHAUST INTENTIONALLY LEFT BLANK 9 29 2 October 31 1995...

Page 581: ...LIMITATIONS The installation and the operation of the option LOW NOISE EXHAUST do not change the basic limitations of the aircraft described in Section 2 Limitations ofthe basic Pilot s Operating Hand...

Page 582: ...the option LOW NOISE EXHAUST PREFLIGHT INSPECTIONS AIRFRAME 6 Forward fuse age Windshield and window panels Engine cowling attachment Clean Check Check level and absence of leak Clean good condition C...

Page 583: ...compiles with Chapter 10 appendix 6 annex 16 of the agreement relative to International Civil Aviation Organization ICAD The noise limit authorized in above mentioned ICAQ conditions is 88 0 dB A The...

Page 584: ...anding gear UP Flaps retracted Power 2575 RPM full throttle With option Nr ABBS LOW NOISE EXHAUST CLIMB SPEEDS ISA 20 C 15A ISA 20 C mi ft min mi ft min mi ft min B 22 1619 7 37 1450 6 64 130B 7 4B 14...

Page 585: ...anding gear UP Flaps retracted Power 2575 RPM full throttle With option Nr ABBS LOW NOISE EXHAUST CLIMB SPEED 15A 20 C 15A 15A 20 C m ft min m ft min m ft min 5 81 1144 5 14 1012 4 56 899 5 20 1023 4...

Page 586: ...LTllUDE 15A 20 C 15A ISA 20 C Feet TIME FUEL 015T TIME FUEL OIST TIME FUEL OIST min s USGal NM min s US Gal NM min s USGal NM 500 0 18 0 1 0 0 21 0 2 0 5 0 23 0 2 0 2500 36 0 2 3 47 0 7 2 58 0 7 3 0 5...

Page 587: ...ISA 200 ISA ISA 20 C Feet TIME FUEL 015T TIME FUEL DI5T TIME FUEL 015T min s USGal NM min s US Gal NM min s USGal NM 500 0 26 0 2 0 0 29 0 2 0 8 0 32 0 2 0 2500 2 16 0 3 2 34 0 4 t 2 54 1 0 4 8 4500 4...

Page 588: ...EMENT 29 SOCATA LOW NOISE EXHAUST LEVEL FLIGHT PERFORMANCE When aircraft is equipped with option Nr ABBS LOW NOISE EXHAUST level flight performance are reduced by 3 kt at ISO power 9 29 10 October 31...

Page 589: ...and balance hereafter complete those of the standard aircraft described in Section 6 Weight and balance of the basic Pilot s Operating Handbook A WEIGHT ARM ITEM 0 OPTIONAL EQUIPMENT N Ib io 0 A ENGIN...

Page 590: ...STEM see Figure 9 29 5 Exhaust gases from each cylinder are collected by pipes to be conducted in order to reduce their noise level to an exhaust duct which is located at the front crosswise under the...

Page 591: ...SOCATA SUPPLEMENT 29 LOW NOISE EXHAUST OWER PLANT FRONT FU S El A G __ _ _ _ _ _ _ _ _ _A RIGID PIPE EXHAUST DUCT Figure 9 29 5 EXHAUST SYSTEM PRINCIPLE October31 1995 9 29 13...

Page 592: ...SUPPLEMENT 29 SOCATA LOW NOISE EXHAUST INTENTIONALLY LEFT BLANK 9 29 14 October 31 1995...

Page 593: ...PEED AND ALTITUDE SELECTOR TYPE KAS 297B OPTIONAL EQUIPMENT N 0675 TABLE OF CONTENTS Page GENERAL 9 30 2 2 LIMITATIONS 9 30 2 3 EMERGENCY PROCEDURES 9 30 2 4 NORMAL PROCEDURES 9 30 3 S PERFORMANCE 9 3...

Page 594: ...pproaching the selected altitude automatically transfer into Altitude Hold altitude alerting as specified by the regulation SECTION 2 LIMITATIONS When the aircraft is equipped with the KAS 2978 in add...

Page 595: ...ND ALTITUDE SELECTOR 1 AP TEST k nob PRESS 2 Check All legends and digits are displayed on the KAS 2978 VERTICAL SPEED MODES MODE ENGAGEMENT 1 Select k nob PULL then ROTATE to display the desired vert...

Page 596: ...ft min The autopilot will maintain the desired vertical speed CAUTION VERTICAL SPEED HOLD MODE USE REQUIRES MONITORING OF THE INDICATED SPEED ESPECIALLY WHEN INDICATED SPEEDS ARE LOW CLIMB OR HIGH DE...

Page 597: ...e middle knob then ROTATE to display the desired altitude the larger outer knob for a 1000 foot increment the small inner knob for a 100 foot increment 2 ARM push button PRESS 3 Display an aircraft at...

Page 598: ...ft described in Section 5 Performance ofthe basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Weight and balance corresponding to the BENDIX I KING KAS 297B are given in the optional equip...

Page 599: ...N When pressed will engage the Vertical Speed Hold mode When pressed a second time will disengage the Vertical Speed Hold mode When pressed with altitude displayed will engage the Vertical Speed Hold...

Page 600: ...band has been exceeded and will remain on until 1000 ft from the selected altitude The alert light is accompanied by a 2 second pulsating aural tone anytime the light initially comes on VERTICAL SPEE...

Page 601: ...Indicates that the Altitude Select mode is armed to capture the selected altitude Item 11 ALTITUDE SELECT MODE ARM BUTTON When pressed and the selected altitude is displayed will arm the Altitude Sele...

Page 602: ...C 13 Figure 9 30 3 KC 191 CONTROL BOX KAP 150 Item 13 VERTICAL TRIM CONTROL 9 30 10 When in the Vertical Speed Hold mode this control can be used to slew the vertical speed up or down at 100 ft I min...

Page 603: ...es power to the KCP 220 the autopilot pitch roll and yaw servos and the PITCH TRIM AIL TRIM RUD TRIM and AP DISC circuit breakers Supplies power to the KAA 15 audible alarm Supplies power to the KAS 2...

Page 604: ...SUPPLEMENT 30 SOCATA BENDIX I KING KAS 297B INTENTIONALLY LEFT BLANK 9 30 12 December 31 1995...

Page 605: ...OM or K923 OOM BENDIX KING RadiolNavigation Assy with BENDIX KING EFIS EHI40 system EHSI only 1 GENERAL TABLE OF CONTENTS Page 9 31 3 1 LIMITATIONS 9 31 3 3 EMERGENCY PROCEDURES 9 31 5 4 NORMAL PROCED...

Page 606: ...SUPPLEMENT31 BENDIX I KING EHI40 INTENTIONALLY LEFT BLANK 9 31 2 SOCATA April 3D 1996...

Page 607: ...stalled on the airplane SECTION 2 LIMITATIONS These limitations supplement those of standard airplane described in Section 2 limitations of the basic Pilot s Operating Handbook To undertake an IFR fli...

Page 608: ...PG06 ITEM SG RK RK DISPLAYWIND VEe 7 DISPLAY DRIFT 9 DME DIST ONLY 0 VIEW I EDIT OPERATING PG08 ITEM SG RK RK 4 VERT PTR TYPE 5 DISPLAY FMS MSG 0 VIEW I EDIT OPERATlNG PG09 ITEM SG RK RK 4 HOG FAil A...

Page 609: ...lot s Operating Manual TABLE OF CONTENTS OF EMERGENCY PROCEDURES Page RED WARNING HDG I 9 31 6 EHSI FAILURE 9 31 6 YELLOWWARNING 1 DU I 9 31 6 YELLOW WARNING 1 SG I 9 31 7 RED WARNING I CP 9 31 7 SELF...

Page 610: ...id for the VOR EHSI FAILURE If EHSI symbols partially or completely disappear the display is out of order This involves the disconnection of the autopilot Control referring to the navigation instrumen...

Page 611: ...tes after annunciation RED WARNING CP This warning displayed on the L H of the EHSI indicates that a control panel switch of the EHSI has become stuck In this case ALL CURRENTLY SELECTED CONDITIONS AR...

Page 612: ...ROZEN SMALL RED WARNING I 5 I This warning displayed on EHSI upper part indicates that information present on the concerned display are no longer valid Use these information only after validation with...

Page 613: ...erating Handbook 4 2 LIST OF GROUND CHECKS BEFORE TAXIING 1 Check for no flags DU SG ep EHI40 SYSTEM AUTOTEST if desired 1 TST REF button 2 Check that the EHSI test pattern appears PRESS AND HOLD for...

Page 614: ...on will not show a system number Pressing 1PUSh button has no effect SELECTION OF THE PRIMARY NAVIGATION SENSOR 1 Push button 1 eI PRESS A press of the NAV push button sequentially selects the primary...

Page 615: ...OSE AND NAVIGATION MAP SELECTION OF BEARING POINTERS Push button EJor 0 PRESS The button EJ is paired with the white single bar pointer The button is paired with the magenta double bar pointer A press...

Page 616: ...ation in VOR function if a VOR DME frequence is selected n ADF function if a VOR OME frequence is selected and the OME positioned to HOLD The distance indication is displayed only if a valid DME signa...

Page 617: ...HSI or ARC formats The selectable ranges are 5 NM 10 NM 20 NM 40 NM 80 NM 160 NM 240 NM 320 NM 1000 NM COURSE SELECTION 1 knob ROTATE Pushing the center of the knob will cause the course pointer to s...

Page 618: ...the title of the navigation page When pressed twice consecutively the lST REF button allows the cyclic permutation of the navigation pages following the FPL ID AIRPORTINAVAlDS sequence CAUTION WHEN T...

Page 619: ...ance of the basic Pilot s Operating Handbook A ARM OPTION OPTIONAL EQUIPMENT WEIGHT 0 Ib in No 0 A K89100M R adio I Navigation any BENDIX I KING with 98 325 65 75 EHI40 EFISl Stem BENDIX f KING EHSI o...

Page 620: ...tion consists of the following elements KMA 24H70 audio control box VHF VORIILS KX 165 25 VHF2VORIlLS KX 165 25with KI20G indicator DMEKN63 ADFKRB7 MARKER KR 21 RMI KI229 GPS KLN 90B KCS 305 gyro unit...

Page 621: ...SOCATA April 30 1996 Revision 1 SUPPLEMENT 31 BENDIX KING EHI40 INTENTIONALLY LEFT BLANK 9 31 15B...

Page 622: ...mode 5 ARC symbologic mode selecting push button 6 Selected heading bug knob 7 ERMI dual pointer selecting push button 8 EHSI brightness setting knob 9 ERMI single pointer selecting push button 10 Nav...

Page 623: ...SOCATA 13 11 10 9 7 SUPPLEMENT 31 BENDIX I KING EHI40 HOLD NAVI NAV2 DME 2 a TS1 3 0 0 5 6 S4342S00AAAAWZMVOO Figure 9 31 2 2 2 CONTROLS AND DISPLAY April 30 1996 9 31 17...

Page 624: ...heading Item 7 PUSH BUn It allows to allocate the ERMI dual pointer to the different navigation sensors Item 8 BRT KNOB It allows to set the EHSI brightness Item 9 PUSH BUTION It allows to allocate th...

Page 625: ...SOCATA o SUPPLEMENT 31 BENDIX I KING EHI40 IC ff 3 4 lO If8io T L 9 8 7 Figure 9 31 3 2 2 EHSI CONTROLS April 30 1996 9 31 19...

Page 626: ...and NAV2 positions Furthermore when tuning is performed the rotary switch allows to memorize the selected frequency in the DME receiver HOLD position Item 14 EHSI MASTER SWITCH It controls the power...

Page 627: ...6 Glide Slope scale 7 Glide Slope pointer 8 Selected heading value 9 Heading rose 10 ERMI dual pointer 11 OME 2 distance 12 Navigation system allocated to ERMI dual pointer 13 DME 1 distance 14 Naviga...

Page 628: ...SUPPLEMENT 31 BENDIX f KING EHI40 16 4 SOCATA S4i42S00AAAEMAMVOO Figure 9 31 5 21 2 STANDARD EHSI SYMBOLOGY 9 31 22 April 30 1996...

Page 629: ...upply line of SG465 functions generator and the supply of portion B of KN40 adapter NAV I COM2 portion Protection of the supply line of portion A of KN4D adapter NAV I COM1 portion Controllable protec...

Page 630: ...IT BREAKER o CIRCUIT BREAKER Non EHI40 specific PULL OFF TYPE CIRCUIT BREAKER Non EHI4D specific CO G LIGHTER 0 0 0 OAT EHSI ADAf T 0 CO CO AUDIO AUDIO NAV 1 V 0 0 0 0 I XPDR 0 0 A I R M TRIM 0 S H AL...

Page 631: ...I40 EHSI This BENDIX KING KLN90A GPS is part ofthe Option No K891 OOM Radio Navigation assy BENDIX KING with EFIS EHI40 BENDIX KING system EHSI only TABLE OF CONTENTS Page 1 GENERAL 9 32 3 2 LIMITATIO...

Page 632: ...SUPPLEMENT 32 BENDIX I KING KLN90A GPS NAVIGATION SYSTEM INTERFACED WITH EHI40 EHSI INTENTIONALLY LEFT BLANK 9 32 2 SOCATA April 30 1996...

Page 633: ...y satellites BENDIX I KING KLN90A is able to track up to 8 satellites at a time GPS is an automatic tridimensional latitude longitude altitude location and navigation means It also uses data recorded...

Page 634: ...uine data base is referenced to WGS 84 geodetic datum If the data base or chart are not referenced to WGS 84 or to NAD 83 geodetic datum in the absence of agreed operating procedure the GPS navigation...

Page 635: ...ith the option BENDIX I KING KLN90A GPS NAVIGATION SYSTEM INTERFACED WITH THE EHI40 EHSI If KLN90A GPS information is flagged Flag NAV on HSI or GPS integrity RAIM capability is lost revert to remaini...

Page 636: ...icipation mode SET 16 to ENABLE turn anticipation ENABLED recommended mode I DISABLE turn anticipation DISABLED not recommended mode Check that the proper criteria are used for nearest airport selecti...

Page 637: ...DISABLED FOR WAYPOINTS USED EXCLUSIVELY IN SID I STARS WHERE OVERFLIGHT IS REQUIRED FOR WAYPOINTS SHARED BETWEEN SID I STARS AND PUBLISHED EN ROUTE SEGMENTS REQUIRING OVERFLIGHT IN THE SID I STARS PR...

Page 638: ...oint the track resetting on following navigation leg automatically occurs When turn anticipation is ENABLED the WPT annunciator will flash going solid upon initialization of the turn and extinguishing...

Page 639: ...ms the autopilot in navigation mode using selected course and left I right steering information presented on the EHSI It makes the FD appear in the case of the KFC 150 autopilot When AP is engaged on...

Page 640: ...YSTEM INTERFACED WITH THE EHI 40 EHSI do not change the performance of the aircraft described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE The weight a...

Page 641: ...each chapter having as many as 26 numbered pages at once With a few exceptions each of these pages can be changed independently Generally the 2 concentric knobs and the cursor button to the left of th...

Page 642: ...I 91 l DATALOADER JACK LEFT CURSOR BUnON MODE TRIP LEFT INNER KNOB 9 32 12 MESSAGE BUnON lEFT OUTER RIGHT CURSOR KNOB BUTTON LEFT PAGE RIGHT PAGE DIRECT TO BUTTON ENTER BUTTON Figure 9 32 2 Controls...

Page 643: ...NT 32 BENDIX I KING KLN90A GPS NAVIGATION SYSTEM INTERFACED WITH EHI40 EHSI LJ D I ANNUNCIATORS I GPS NOT APPROVED FOR NAVIGATION AS A PRIMARY SOURCE Figure 9 32 3 GPS placard and annunciators April 3...

Page 644: ...SUPPLEMENT 32 BENDIX I KING KLN90A GPS NAVIGATION SYSTEM INTERFACED WITH EHI40 EHSI INTENTIONALLY LEFT BLANK 9 32 14 SOCATA April 30 1996...

Page 645: ...GATION SYSTEM INTERFACED WITH THE HSI KI525A OPTIONAL EQUIPMENT No K899 OOM K89910M K899 20M K899 30M K927 OOM TABLE OF CONTENTS Page 1 GENERAL 9 33 3 2 LIMITATIONS 9 33 4 3 EMERGENCY PROCEDURES 9 33...

Page 646: ...SUPPLEMENT 33 BENDIX KING KLN90B GPS NAVIGATION SYSTEM INTERFACED WITH THE HSI KI525A INTENTIONALLY LEFT BLANK 9 33 2 SOCATA April 30 1996...

Page 647: ...automatic tridimensional latitude longitude altitude location and navigation means It also uses data recorded in a data base two different data bases are available North American one or International...

Page 648: ...h the WGS84 geodetic model If the data base or the cartridge are not in accordance with WGS84 or NAD 83 geodetic model and as there is no means of operation published GPS navigation system must be dis...

Page 649: ...9 33 2 GPS limitation placard IFR navigation is restricted as follows The system must utilize DRS level 20 or later IFR en route and terminal area navigation is prohibited unless the pilot verifies th...

Page 650: ...t the GPS signal integrity has been lost 1 NAV 11 GPS inverter PRESS Return to the NAVl navigation source and to remaining operational navigation equipment MSG ANNUNCIATOR ILLUMINATION MSG push Ic nob...

Page 651: ...tlined in the BENDIX I KING KLN90B Pilot s Guide at the latest revision and KLN90B Memory Jogger at the latest revision However it is important to precise the following points for the use of KLN90B on...

Page 652: ...n the first harmonic of the VHF frequencies 242 30 242 35 242 40 262 50 262 55 and 262 60 MHz SYSTEM ANNUNCIATORS I SWITCHES I CONTROLS NAV 1 GPS inverter It may be used to select data for presentatio...

Page 653: ...seconds prior to the beginning of the turn anticipation the WPT annunciator will flash going solid upon initiation of the turn and extinguishing upon turn completion WPT annunciator is amber GPS appro...

Page 654: ...TH TURN ANTICIPATION ENABLED WHEN TURN ANTICIPATION IS DISABLED WAYPOINT ALERTING OCCURS APPROXIMATELY 35 SECONDS PRIOR TO ACTUALLY REACHING THE WAYPOINT MSG ANNUNCIATOR REMAINS OFF THERE IS NO COURSE...

Page 655: ...D IF THE COURSE CHANGE IS MORE THAN S THE FLIGHT DIRECTOR AND AUTOPILOT WILL STEER A DIVERGENT ROUTE AFTER THE WAYPOINT EN ROUTE LEG MODE SELECTED _ NOTE When the HSI is selected on GPS navigation sou...

Page 656: ...riate STARn from the ACT 7 page NOTE 1 Using right hand outer knob select the ACT Active Flight Plan waypoints pages Pull right hand inner knob out and scroll to the destination airport then push the...

Page 657: ...nd balance of the basic Pilot s Operating Handbook A ITEM 0 0 No A K89900M A K89910M A K89920M A K89930M A K92700M April 30 1996 Revision 2 OPTIONAL EQUIPMENT GPS KlN 90B KING interfaced with HSI and...

Page 658: ...as chapters in a book each chapter having 26 pages With a few exceptions each of these pages can be changed independently Generally the 2 concentric knobs and the cursor button to the left of the scr...

Page 659: ...ALOADER JACK 1 LEFT CURSOR LEFT OUTE R RIGHT CURSOR BUTTON KNOB BUTTON LEFT PAGE RIGHT PAGE CALC STAT MODE SETUP TRIP OTHER MSG LEFT INNER KNOB MESSAGE DIRECTTO ENTER BUTTON BUTTON BUTTON Figure 9 33...

Page 660: ...ED FOR NAV AS PRIMARY SOURCE USE OF GPS APPROACH MODE S PROHIBITED NAV 1 MSG GPS APR ARM GPS WPT GPS APR ACTV MSGNlPT annunciator L Invert AV GPS er N 1 GPS CRS 08S GPS CRS LEG GPS approach Switch ann...

Page 661: ...witch annunciator USE OF GPS APPROACH MODE IS PROHIBITED NAV 1 MSG G S WPT SG W T annunciator L Inverter NAV1 GPS 8 I GPS APR ARM GPS APR ACTV L GPS CRS OBS GPS CRS LEG GPS app 0 ch Switch annunciator...

Page 662: ...SUPPLEMENT 33 BENDIX I KING KLN90B GPS NAVIGATION SYSTEM INTERFACED WITH THE HSI KI525A INTENTIONALLY LEFT BLANK 9 33 18 SOCATA April 30 1996 Revision 2...

Page 663: ...TABLE OF CONTENTS SUPPLEMENT 34 EDM 700 Page 1 GENERAL 9 34 3 2 LIMITATIONS 9 34 3 3 EMERGENCY PROCEDURES 9 34 3 4 NORMAL PROCEDURES 9 34 3 5 PERFORMANCE 9 34 4 6 WEIGHT AND BALANCE 9 34 4 7 DESCRIPTI...

Page 664: ...SUPPLEMENT 34 EDM 700 SOCATA INTENTIONALLY LEFT BLANK 9 34 2 November 15 1996...

Page 665: ...Section 2 Limitations of the basic Pilot s Operating Handbook SECTION 3 EMERGENCY PROCEDURES Installation and operation of the EDM 700 do not change the emergency procedures of the aircraft described...

Page 666: ...ibed in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement those given for the standard aircraft in Section 6 uW O ight and bal...

Page 667: ...t press on the STEP button In Manual Mode pressing STEP will display the engine parameters in the sequence BAT voltage DIF difference between hottest and coldest EGn EGT I CHT cylinders 1 to 6 CLD sho...

Page 668: ...4 Dot indicates which cylinder temperatures are shown in the digital display 5 Exhaust Gas Temperature EGD is the top of the column 6 Cylinder Head Temperature CHn trend is shown as a missing bar 7 LF...

Page 669: ...mber of LEANEST cylinder flashes 3 Dot indicates LEANEST cylinder 4 Column of LEANEST cylinderflashes 5 EGT of the LEANEST cylinder displayed with the word NSET I I l PER GT 2 N of 1 2 3 4 5 6 3 0 5o...

Page 670: ...SUPPLEMENT 34 EDM 700 SOCATA INTENTIONALLY LEFT BLANK 9 34 8 November 15 1996...

Page 671: ...EL MANAGEMENT SYSTEM OPTIONS No D905 OOM D905 10M D905 30M D90540M TABLE OF CONTENTS Page 1 GENERAL 9 35 3 2 LIMITATIONS 9 35 3 3 EMERGENCY PROCEDURES 9 35 4 4 NORMAL PROCEDURES 9 35 4 5 PERfORMANCE 9...

Page 672: ...SUPPLEMENT 35 SHADIN DIGITAL FUEL MANAGEMENT SYSTEM SOCATA INTENTIONALLY LEFT BLANK 9 35 2 November 15 1996...

Page 673: ...to transmit the fuel management data SECTION 2 LIMITATIONS Installation and operation of the SHADIN DIGITAL FUEL MANAGEMENT SYSTEM do not change the limitations of the aircraft described in Section 2...

Page 674: ...Handbook SECTION 4 NORMAL PROCEDURES I These procedures supplement those of standard aircraft described in Section 4 Normal Procedures of the basic Pilot s Operating Handbook BEFORE STARTING ENGINE Fu...

Page 675: ...basic Pilot s Operating Handbook A ITEM OPTIONAL EQUIPMENT 0 0 No A D90S00M Digital Fuel Management System fB 20 SHADIN A D90510M Digital Fuel Management System fBZ SHADIN A 090530M Digital Fuel Mana...

Page 676: ...BD switch while onboard fuel is being displayed until reaching the fuel onboard value This value will be saved automatically 3 seconds after the HONBD ONBD II or ONBD switch has been released The disp...

Page 677: ...L MANAGEMENT SYSTEM 2 To enter fuel onboard partial or full 3 Self test 4 Brightness control 5 Endurance hours and minutes 6 Fuel used o USEO ONBO 0 5 9L 00000000 1 8RT ONBD I I 0 T Figure 9 35 1 Digi...

Page 678: ...e the switch to USED The fuel used will be displayed for 3 seconds after releasing the switch ENOURANCE Move the switch to ENDURANCE The endurance in hours minutes will be displayed for 3 seconds afte...

Page 679: ...KLN89B GPS NAVIGATION SYSTEM STAND ALONE OPTIONAL EQUIPMENT No K920 OOM TABLE OF CONTENTS Page GENERAL 9 37 3 2 LIMITATIONS 9 37 4 3 EMERGENCY PROCEDURES 9 37 5 4 NORMAL PROCEDURES 9 37 6 S PERfORMANC...

Page 680: ...SUPPLEMENT 37 SOCATA BENDIX KING KLN89B GPS STANDALONE INTENTIONALLY LEFT BLANK 9 37 2 June 30 1997...

Page 681: ...up to 8 satellites at a time GPS is an automatic tridimensional latitude longitude altitude location and navigation means It also uses data recorded in a data base three different data bases are avail...

Page 682: ...base is in accordance with the WGS84 geodetic model If the data base or the cartridge are not in accordance with WGS84 or NAD 83 geodetic model and as there is no means of operation published GPS nav...

Page 683: ...KING KLN89B GPS NAVIGATION SYSTEM STANDALONE MSG ANNUNCIATOR ILLUMINATION 1 MSG push knob of KLN89B PRESS Check the message If the message mentions the loss of GPS system integrity RAIM NOT AVAILABLE...

Page 684: ...KING KLN898 Pilot s Guide at the latest revision and KLN89B Memory Jogger at the latest revision However it is important to precise the following points for the use of KLN898 on T8 SET UP CONDITIONS...

Page 685: ...ANNUNCIATORS SWITCHES CONTROLS MSG message annunciator CAUTION MSG ANNUNCIATOR MAY BE PERMANENTLY ILLUMINATED IF THERE EXISTS A PERMANENT MESSAGE WHEN A NEW MESSAGE APPEARS MSG ANNUNCIATOR ONLY FLASHE...

Page 686: ...ENABLED WHEN TURN ANTICIPATION IS DISABLED WAYPOINT ALERTING OCCURS APPROXIMATELY 3S SECONDS PRIOR TO ACTUALLY REACHING THE WAYPOINT MSG ANNUNCIATOR REMAINS OFF THERE IS NO COURSE CHANGE MESSAGE DISPL...

Page 687: ...he aircraft described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement those given forthe standard aircraft in Section 6 W...

Page 688: ...nt page formats The various display types can be considered as chapters in a book each chapter having some number of pages With a few exceptions each of these pages can be changed independently The la...

Page 689: ...D I INNER KNOB CURSOR BUTTON 0 r FF ON APT VOR NDB INT un ACT NP 9 L CAL 5ET OTH M5G G J INRST I D OUR OUTER ON OFF ALnruoE KNOB KNOB BUTTON MESSAGE BUTTON OBS BUTTON NEAREST BUTTON CLEAR BUTTON DIREC...

Page 690: ...SUPPLEMENT 37 BENDIX KING KLN89B GPS STANDALONE or o I I I GPS USED FOR NAVIGATION IN VFR ONLY MSG WPT MSGIWPT annunciator SOCATA Figure 9 37 3 GPS placard and annunciators 9 37 12 June 30 1997...

Page 691: ...This BENDIX KING KLN90B GPS is part of the Option No K923 OOM RadiolNavigation assy BENDIX KING with EFIS EHI40 BENDIX KING system EHSI only TABLE OF CONTENTS Page GENERAL 9 38 3 1 LIMITATIONS 9 38 4...

Page 692: ...SUPPLEMENT 38 BENDIX KING KLN90B GPS INTERFACED WITH EHI40 EHSI INTENTIONALLY LEFT BLANK 9 38 2 SOCATA June 30 1997...

Page 693: ...ude altitude location and navigation means It also uses data recorded in a data base two different data bases are available North American one or International one The data base is housed in a cartrid...

Page 694: ...dge are not in accordance with WGS84 or NAD 83 geodetic model and as there is no means of operation published GPS navigation system must be disengaged in terminal area GPS BENDIX I KING KLN90B is not...

Page 695: ...S limitation placard IFR navigation is restricted as follows The system must utilize DRS level 20 or later IFR en route and terminal area navigation is prohibited unless the pilot verifies the currenc...

Page 696: ...y has been lost 1 NAV push knob of EHSI PRESS ONCE or TWICE Return to VOR or ADF navigation source and to remaining operational navigation equipment MSG ANNUNCIATOR ILLUMINATION 1 MSG push knob of KLN...

Page 697: ...est revision However it is important to precise the following points for the use of KLN90B on TB SET UP CONDITIONS The system must utilize DRS level 20 or later in compliance with the Pilot s Guide Ve...

Page 698: ...AV push k nob It may be used to select data for presentation on the pilot s EHSI either NAV data from NAV 1 or NAV 2 navigation receiver or GPS data from the KLN90B GPS or ADF data NAV symbol is green...

Page 699: ...KLN90B GPS will provide navigation along a curved path segment to ensure a smooth transition between two adjacent legs in the flight plan This feature is called turn anticipation Approximately 20 seco...

Page 700: ...RC or HSI modes trace of the navigation in MMAP mode The active leg is blue the following legs are white When crossing a waypoint the track resetting on following navigation leg automatically occurs W...

Page 701: ...URE NOTE SID procedure can only be loaded in the Active Flight Plan FPL 0 Prior to take off Select an appropriate SID from the ACT 7 page If necessary select runway and transition point NOTE 7 Using r...

Page 702: ...estination airport then push the inner knob in and select the ACT 7 page To delete or rep ace a STAR select FPL 0 page Place the cursor over the name of the procedure press ENT to change it or CLR the...

Page 703: ...ERFACED WITH THE EHI 40 EHSI do not change the performance of the aircraft described in Section 5 II Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE The weight and bal...

Page 704: ...pter having as many as 26 numbered pages at once With a few exceptions each of these pages can be changed independently Generally the 2 concentric knobs and the cursor button to the left of the screen...

Page 705: ...v MODE J TRIP LEFT INNER KNOB MESSAGE BUTTON June 30 1997 LEFT OUTER RIGHT CURSOR KNOB BUTTON POWER I BRIGH NESS KNOB r IRT PUSH LEFT PAGE RIGHT PAGE AY __________________ on oN IAlT I I i J 10 11 I H...

Page 706: ...PROVED FOR NAY AS PRIMARY SOURCE USE OF BPS APPROACH MODE 18 PROHIBITED MSG GPS APR GPS CRS ARM OBS WPT GPS APR GPS CRS ACT LEG MSGIWPT GPS cou SOCATA I annunciator Switch annunciator i 9 38 16 L GPS...

Page 707: ...AVIGATION SYSTEM STAND ALONE OPTIONAL EQUIPMENT No J925 OOM TABLE OF CONTENTS Page 1 GENERAL 9 39 3 2 LIMITATIONS 9 39 4 3 EMERGENCY PROCEDURES 9 39 5 4 NORMAL PROCEDURES 9 39 6 5 PERFOR MANCE 9 39 B...

Page 708: ...SUPPLEMENT 39 SOCATA GARMIN 150 GPS STANDALONE INTENTIONALLY LEFT BLANK 9 39 2 August 31 1997...

Page 709: ...information provided by satellites GARMINN 150 GPS is able to track up to 8 satellites at a time GPS is an automatic tridimensional latitude longitude altitude location and navigation means It also u...

Page 710: ...ight uGARMIW 150 GPS can only be used as a navigation source in day VFR in sight of ground or water the instruments required for navigation in VFR must be available onboard GPS USED ONLY FOR NAVIGATIO...

Page 711: ...tion GARMIN 150 GP5 NAVIGATION SYSTEM STAND ALONE MSG ANNUNCIATOR ILLUMINATION 1 STAT button PRESS Check the message If the message mentions the loss of GPS system or part of the system 2 Continue the...

Page 712: ...he latest revision However it is important to precise the following points for the use of GARMIN 1S0GPSonTB SET UP CONDITIONS Verify if the data base is current Check that the proper criteria are used...

Page 713: ...ITCHES CONTROLS MSG message annunciator CAUTION MSG ANNUNCIATOR MAY BE PERMANENTLY ILLUMINATED IF THERE EXISTS A PERMANENT MESSAGE WHEN A NEW MESSAGE APPEARS MSG ANNUNCIATOR ONLY FLASHES It will flash...

Page 714: ...the aircraft described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement those given for the standard aircraft in Section...

Page 715: ...stination Item 3 NRST KEY The nearest key is used to obtain information on the 9 nearest airports VORs NDBs intersections user waypoints and 2 nearest FSSs This key also accesses any active SUA inform...

Page 716: ...operation or complete data entry It is also used to confirm information such as during power on Item 10 STAT KEY The status key is used to view receiver and satellite status as well as system messages...

Page 717: ...SOCATA SUPPLEMENT 39 GARMIN 150 GPS STANDALDNE DD I L NAVDATACARD GARMIN Figure 9 39 2 Controls August 31 1997 11 10 9 39 11...

Page 718: ...NCIATORS See Figure 9 39 3 The annunciators include 2 amber warning lights marked MSG and WPT I 9 39 12 GPS USED ONLY FOR NAVIGATION IN DAY VFR IN SIGHT OF GROUND OR WATER MSG WPT annunciator Figure 9...

Page 719: ...LN89B GPS NAVIGATION SYSTEM INTERFACED WITH THE HSI KI525A OPTIONAL EQUIPMENT No K926 OOM TABLE OF CONTENTS Page GENERAL 9 40 3 2 LIMITATIONS 9 40 4 3 EMERGENCY PROCEDURES 9 40 5 4 NORMAL PROCEDURES 9...

Page 720: ...SUPPLEMENT 40 BENDIX I KING KLN89B GPS INTERFACED WITH THE HSI KI525A SOCATA INTENTIONALLY LEFT BLANK 9 40 2 September 3D 1997...

Page 721: ...p to 8 satellites at a time GPS is an automatic tridimensional latitude longitude altitude location and navigation means It also uses data recorded in a data base three different data bases are availa...

Page 722: ...4 or NAD 83 geodetic model and as there is no means of operation published GPS navigation system must be disengaged in terminal area Navigation must be controlled using primary sources In any case GPS...

Page 723: ...PS signal integrity has been lost 1 NAV 11 GPS inverter PRESS Return to the NAVl navigation source and to remaining operational navigation equipment MSG ANNUNCIATOR ILLUMINATION 1 MSG U push knob of K...

Page 724: ...by BENDIX I KING manufacturer are outlined in the BENDIX I KING KLN89B Pilot s Guide at the latest revision and KLN898 Memory Jogger at the latest revision However it is important to precise the follo...

Page 725: ...armonic of the VHF frequencies 242 30 242 35 242 40 262 50 262 55 and 262 60 MHz SYSTEM ANNUNCIATORS I SWITCHES I CONTROLS NAV 1 GPS inverter It may be used to select data for presentation on the pilo...

Page 726: ...GPS will provide navigation along a curved path segment to ensure a smooth transition between two adjacent legs in the flight plan This feature is called turn anticipation Approximately 20 seconds pri...

Page 727: ...RS APPROXIMATELY 35 SECONDS PRIOR TO ACTUALLY REACHING THE WAYPOINT MSG ANNUNCIATOR REMAINS OFF THERE IS NO COURSE CHANGE MESSAGE DISPLAYED BY THE KLNB9B IT IS RECOMMENDED TO USE KLN89B WITH TURN ANTI...

Page 728: ...ILOT WILL STEER A DIVERGENT ROUTE AFTER THE WAYPOINT CROSSING EN ROUTE LEG MODE SELECTED NOTE When the NSf is selected on GPS navigation source the RMI if installed remains selected On NAV 1source VOR...

Page 729: ...TAR from the ACT 7 page NOTE 1 Using right hand outer knob select the ACT Active Flight Plan waypoints pages Pull right hand inner knob out and scroll to the destination airport then push the inner kn...

Page 730: ...rformance of the aircraft described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement those given for the standard aircraft...

Page 731: ...ber of different page formats The various display types can be considered as chapters in a book each chapter having some number of pages With a few exceptions each of these pages can be changed indepe...

Page 732: ...TACARD I INNER KNOB SOCATA CURSOR BunON rF ON APT VOR NOB IHT USR Acr NAV FPL CAL SET OTH MSG INRST I D CL 1 t OUTER ON OFF ALTITUDE KNOB KNOB BUnON MESSAGE BUnON OBS BUnON NEAREST BUnON CLEAR BUnON D...

Page 733: ...WITH THE HSI KI525A or o I I i I USE OF GPS APPROACH MODE IS PROHISrTeO NAV 1 MSG GPS APR ARM GPS WPT GPS APR ACTV MSGIWPT annunciator L Inverter NAV1 GPS GPS approach Switch annunciator Figure 9 40 3...

Page 734: ...SUPPLEMENT 40 BENDIX KING KLN89B GPS INTERFACED WITH THE HSI KIS25A SOCATA INTENTIONALLY LEFT BLANK 9 40 16 September 30 1997...

Page 735: ...TKS SYSTEM Page GENERAL 9 41 2 2 3 4 LIMITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES 9 41 2 9 41 5 9 41 6 5 PERFORMANCE 9 41 7 6 WEIGHT AND BALANCE 9 41 8 7 DESCRIPTION 9 41 10 8 HANDLING SERVICIN...

Page 736: ...R THAN THOSE LISTED BELOW TO BE USED IN THE T K S SYSTEM SOME FLUIDS CURRENTLY USED FOR GROUND DE ICING PURPOSES CONTAIN THICKENING AGENTS WHICH MAY BLOCK THE POROUS PANELS IF IT IS KNOWN OR SUSPECTED...

Page 737: ...URANCE 2 minutes in every 30 minutes 5 seconds in every 10 minutes 2 hours 50 minutes With three blade propeller OPT10 61 001 version 8 Maximum system endurance With ANTI ICE selected 2 hours 50 minut...

Page 738: ...TKS 80 AL 5 OTO 406B TKS R328 SOCATA 2 On the upper skin surface atthe root end of each wing and stabilator total 4 places TKS ICE PROTECTION CAUTION POROUS DE ICING PANELS MAY BE DAMAGED BY CERTAIN S...

Page 739: ...en hereafter ANTI ICE DE ICE aitirame propelier pump switch As required Wing inspection light ON as required ALTERNATE AIR if installed FULLY PULLED if IOAT below 39 3 F 4 C and WINDSHIELD visible moi...

Page 740: ...tank Quantity Filler cap Filler door Drain Checked Mini indicated 1 7 U S Gallons 6 41 SECURE CLOSED Check closed and not leaking 3 Porous panels Condition and security Evidence of fluid flow Wing in...

Page 741: ...riod until normal operating pressure is restored This is acceptable provided that the flashing red indication is replaced by a steady green light within 30 seconds Pump switches OFF IN FLIGHT GENERAL...

Page 742: ...UIPMENT m SUPPLIER 0 30 ICE AND RAIN PROTECTION A Ice protection systems 28 VOC TKS Pre MOD 1SI OPT10 C687 10M A Ice protection systems 28 VOC TKS Post MOD 1S1 OPT10 C687 15M A Ice protection systems...

Page 743: ...be used Correction data is also shown in graphical form in Section 7 ofthis supplement Indicator True Weight Arm Moment contents reading U S Gal Ib in Ib in 1000 U S Gal Iitres kg m m kg 0 0 7 2 7 6...

Page 744: ...ish filling Tank capacity is 7 8 U S Gal 29 6 litres The unusable volume is 0 1 U S Gal 0 4 litre with the airplane in the level attitude increasing to 1 45 U S Gal 5 5 litres in the climb attitude me...

Page 745: ...15 _A 3 10 2 5 1 o n IiI I I LEVEL _ ATTITUDE 4 0 o I I I I I I I CLIMB ATTITUDE _ V V 10 5 0 NOSE UP I I I V V I i 1 I 2 3 4 5 6 7 8 I II 5 10 15 20 25 30 1 1 45 U S Gal 5 5 Litres unusable In climb...

Page 746: ...CESSED RESET SWITCH Push buaon with ballpen pOint or similar to cancel high pressure warning LIGHT A OFF SHIELD nn LJ LJ o DE ICE z 0 CO o Green indicates DE_ICE selected flashing red indicates law pr...

Page 747: ...itirame propeller ice protection system ANTI ICE or DE ICE in the event of low system pressure both lights flash red with the light appropriate to the current pump selection alternating red green in c...

Page 748: ...E WARNING SWITCH k_Lrr J DRAIN POROUS PANELS ON WING PROPORTIONING UNIT STRAINER TANK FILLING POINT VENTED POROUS P NELS ON VERTICAL STABILIZER FILTER J II II II II II CHECK VALVE QUANTITY TRANS llITT...

Page 749: ...PRESSURE L rr j WARNING SWITCH L eo o l llF Crfcrr tt C NVALVE FILTER JL II II II II PROPORTIONING UNIT f II STRAINER __ 1 II TANK FILLING POINT VENTED POROUS PANELS ON VERTICAL STABILIZER ill QUANTI...

Page 750: ...plastic tubing carries the fluid to proportioning units located in rear fuselage The proportioning units divide the flow into the requirements of the individual regions fed from each proportioning uni...

Page 751: ...If WINDSCREEN PUMP HIGH PRESSURE WARNING _____ V r r I C3 CONNECTOR ON SUPPORT BAR y EAR UDON EQUIPMENT PACK WING INSPECTION LIGHT o o CONTENTS TRANSMITTER c f H J 0 _ _ ____ cItr_ 4 ___ f H H rn H H...

Page 752: ...for the first two years from new At the same time exercise the windshield pumps for several periods not exceeding 5 seconds each The two month interval between operation may be increased to a period n...

Page 753: ...located on the left hand side of the fuselage just aft of the baggage compartment door To preclude the possibility of contamination always clean the top of fluid containers before dispensing If fluid...

Page 754: ...priming The aitirame propeller pump may not be self priming and is ground primed by first opening the drain valve to remove any air in the supply pipeline from the tank reference paragraph 1 of this...

Page 755: ...ce functions relating to the stall warning sensor are to be made as detailed in SOCATA Maintenance Manual Chapter 27 except that for access to and I or removal of the unit it is first necessary to rem...

Page 756: ...urtaces Water with soaps or detergents Approved de icing fluids Aviation gasoline Aviation turbine fuel Isopropyl alcohol Ethyl alcohol Industrial methylated spirit Cleaning of the porous panels will...

Page 757: ...MENT GARMIN GNS 430 GPS NAVIGATION SYSTEM INTERFACED WITH GI 106A COl TABLE OF CONTENTS Page 1 GENERAL 9 43 3 2 LIMITATIONS 9 43 4 3 EMERGENCY PROCEDURES 9 43 6 4 NORMAL PROCEDURES 9 43 8 5 PERFORMANC...

Page 758: ...SUPPLEMENT43 GARMIN GNS 430 GPS NAVIGATION SYSTEM INTERFACED WITH GII06A COl INTENTIONALLY LEFT BLANK 9 43 2 SOCATA August 31 2000...

Page 759: ...N SYSTEM INTERFACED WITH GI106ACDI The GPS is an automatictridimsnsional latitude longitude altitude location and navigation means using information provided by satellites GARMIW GNS 430 is able to tr...

Page 760: ...NOTE The GNS 430 genuine data base is referenced to WGS 84 geodetic datum I GPS USED FOR NAVIGATION IN VFR ONLY Figure 9 43 1 GPS Iimi1ation placard I GARMIN GNS 430 Pilot s Guide PIN 190 00140 00 Rev...

Page 761: ...SYSTEM INTERFACED WITH Gll06A COl 2 2 COl coupled with KAP 150 autopilot The system must utifize the following software versions or more recent ones Subsystem MAIN GPS COM VOR LOC August 31 2000 Revis...

Page 762: ...ion GARMIN GNS 430 GPS NAVIGATION SYSTEM INTERFACED WITH GI106ACDI I COl NAV FLAG OR INTEG WARNING I Return to the VOR au ADF navigation source and to remaining operational navigation equipment mCDI p...

Page 763: ...error ofcourse deviation aBS set to OTK value Return to VOR or AOF navigation source and to remaining operational navigation equipment COl push button VLOC aBS not set to DTK value Set the COl to the...

Page 764: ...data on the self test page Verify that altitude data is valid for the GPS prior to flight SYSTEM ANNUNCIATORS I SWITCHES I CONTROLS COl push button This push button may be used to select data to be d...

Page 765: ...with KAP 150 autopilot The autopilot NAV mode uses left right course deviation information and the COl heading This information is related to the navigation source VLOC or GPS selected by the COl pus...

Page 766: ...d in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement those given for the standard aircraft in Section 6 Weight and balance o...

Page 767: ...the GARMIN GNS 430 GPS NAVIGATION SYSTEM INTERFACED WITH GI1 DBA COl are described in the GARMIW GNS 430 Pilot s Guide at the latest revision The option includes one GNS 430 GPS installed in radio rac...

Page 768: ...on of gcoop PUSH pages CRSR Group selection NAV WPT AUX NAST IMSGI WPT Map scae change ill 10BsI IMSGI IFPll rROC I I GO v RNG Al foo MENU Navigation source VLOC G PS selection OBS Leg mode selection...

Page 769: ...DE PROPELLER GENERAL LIMITATIONS TABLE OF CONTENTS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT AND BALANCE DESCRIPTION AIRPLANE HANDLING SERVICING AND MAINTENANCE October 28 2000 Revisio...

Page 770: ...hose of the standard airplane described in Section 2 Limitations of the basic Pilot s Operating Handbook when the TB airplane is equipped with the option THREE BLADE PROPELLER POWERPLANT LIMITATIONS N...

Page 771: ...the TB airplane is equipped with the option THREE BLADE PROPELLER ENGINE FAILURE IN FLIGHT MAXIMUM GLIDE Gliding distance is reduced by approximately 7 with the 3 blade propeller installed SECTION 4 N...

Page 772: ...with option OPT10 61001 Thee blade propeller at a maximum continuous power of 2575 RPM is 82 5 d B A for SOCATA Model TB 20 airplane 81 8 d B A for SOCATA Model TB 21 airplane FAR PART 36 requirements...

Page 773: ...PROPELLER Three blade propeller OPT10 61001 HARTZELL SECTION 7 DESCRIPTION WEIGHT ARM per unit in Ib kg 1m 14 550 4760 6 6 600 1 209 The propeller is a 78 inch diameter model which features three alum...

Page 774: ...SUPPLEMENT 45 THREE BLADE PROPELLER INTENTIONALLY LEFT BLANK 9 45 6 SOCATA October 28 2000 Revision 1...

Page 775: ...C 225 AUTOMATIC FLIGHT CONTROL SYSTEM GENERAL LIMITATIONS TABLE OF CONTENTS 3 EMERGENCY AND ABNORMAL PROCEDURES Page 9 47 2 9 47 5 Emergency procedures 9 47 7 Abnormal procedures 9 47 10 4 NORMAL PROC...

Page 776: ...7 1 The KFC 225 system provides the pilot with the following features pitch attitude hold PIT vertical speed hold VS altitude hold preselect ALT ARM altitude capture ALT CAP altitude hold ALT altitude...

Page 777: ...g AltimeW SUPPLEMENT 47 HONEYWELL KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM I 1 Audio Alan Ramoto Tormll1al r rI I F Connector AFCS I Jaln Flug KCM 100 Conl Q on Modulo KS 270C Pltoh Servo KS 272C Tn 8...

Page 778: ...SUPPLEMENT 47 HONEYWELL KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM INTENTIONALLY LEFT BLANK 9 47 26 SOCATA January 31 2001 Revision 1...

Page 779: ...clutches to disengage sustained accelerations will cause autopilot disengagement except when the CWS button is depressed The MAIN SWITCH supplies power to the aircraft bus bar From the aircraft bus ba...

Page 780: ...alerting to headphones and loud speakers An in line fuse located in the fuse panel provides circuit protection for the Altitude Encoder The following voice messages will be annunciated as conditions...

Page 781: ...utopilot operation 20 Gallons 76 Liters F Autopilot maximum airspeed limitation 175 KIAS G Autopilot coupled flap operation to and from the Landing 40 position is prohibited below 1000 feet AGL I H Al...

Page 782: ...EYWELL KFC 225 AUTOMATIC FLIGHT CONTROL SYSTEM L Required placard on pilot s instrument panel SOCATA AUTOPILOT AND ELECTRIC TRIM PREFLIGHT TESTS MUST BE CONDUCTED PRIOR TO EACH FLIGHT 9 47 6 January 3...

Page 783: ...lot Autopilot Trim or Manual Electric Trim malfunction accomplish Items 1 and 2 Simultaneously 1 Aircraft Control Wheel GRASP FIRMLY and regain aircraft control 2 AlP DISC TRM INTER Switch PRESS and H...

Page 784: ...f satisfied that the out of trim condition was temporary DISCONTINUE if evidence indicates a failure of the auto trim function C Aircraft Stall Autopilot coupled 1 AUTOPILOT DISENGAGE and perform stal...

Page 785: ...ectric trim malfunction is regaining control of the aircraft Grasp the control wheel firmly and press and hold down the AlP DISC TRM INTER switch Switch off the AP MASTER switch to remove all power fr...

Page 786: ...ch servo loading 1 FLASHING PT ANNUNCIATION OBSERVE aircraft pitch behavior If pitch behavior is satisfactory wait 5 1 0 seconds for the annunciation to stop 2 If annunciation continues aircraft Contr...

Page 787: ...caused by a failed heading or course datum input 3 Flashing GS Indication of a flagged glideslope or a fault in the KFC 225 pressure sensor GS will rearm automatically if a valid GS signal is received...

Page 788: ...impact autopilotoperation DO NOT ENGAGE autopilot into this situation 2 Loss of the turn coordinator no effect on the autopilot 3 Loss of the HSI Heading navigation and approach modes inoperative 4 L...

Page 789: ...Successful completion of self test is identified by all display segments being illuminated Display Test a momentary appearance of the flight director command bars and the disconnect tone sounding NOT...

Page 790: ...operations except that the autopilot is not engaged and the pilot must maneuver the aircraft to satisfy the flight director commands Note that the flight director will always be in view when the autop...

Page 791: ...gagement a Elevator Trim VERIFY or SET to place the aircraft in a trimmed condition prior to autopilot engagement b AP Button PRESS If no other modes have been selected on the flight director the auto...

Page 792: ...E MAXIMUM AUTOPILOT SPEED IT MAY BE NECESSARY TO REDUCE POWER IN ORDER TO MAINTAIN THE DESIRED RATE OF DESCENT AND NOT EXCEED THE MAXIMUM AUTOPILOT SPEED b Using CWS 1 CWS Button PRESS and DISPLAY des...

Page 793: ...altitude selection when the flight director is engaged 2 Aircraft ESTABLISH climb or descent necessary to intercept the selected altitude Note ALT CAP annunciated during level off at the preselected a...

Page 794: ...erence at the rate of 20 feet per button press 5 Heading Changes a Manual heading changes in ROL mode 1 CWS Button PRESS and MANEUVER aircraft to the desired heading 2 CWS Button RELEASE w bank angle...

Page 795: ...he selected course will be automatically captured and tracked NAV staying illuminated 2 If the O Bar is less than 2 to 3 dots from center the HOG mode will disengage upon selecting NAV mode the NAV an...

Page 796: ...ode with VOR as the selected navigation sensor changes in the selected course which result in a D Bar deviation of greater than 50 may result in the autopilot not tracking the signal It is recommended...

Page 797: ...cally begin 9 Glideslope Coupling NOTE G idesfope coupling is inhibited when operating in NAV or REV modes Glides ope arm and coupling occurs automatically in the APR mode when tracking a ocalizer a A...

Page 798: ...ing a AlP DISC TRM INTER Switch PRESS to disengage autopilot NOTE If the AP DISC Disengages FlO is not configured pitch and roll axis may be disengaged leaving only flight director at approach minimum...

Page 799: ...EM CONTROLS AND DISPLAYS TRIM FAIL 18 AP MASTER A Two axis FCC with altitude preselect and alerting B KFC 225 Front Panel C TRIM FAIL Annunciator D AP Master Switch located at the bottom of central co...

Page 800: ...When pressed will engage the flight director into the basic roll ROL mode which functions as a wing leveler and into the pitch attitude PIT hold mode The pitch attitude maintained will be the pitch at...

Page 801: ...he selected altitude If pressed when ALT hold mode is engaged will disengage the mode defaulting to PIT mode This button will engage the flight director Item 10 VERTICAL TRIM UP DN BUTTONS The respons...

Page 802: ...itude arming on or off When ALT ARM is annunciated the automatic flight control system will capture the altitude displayed in the Altitude AlerterNertical Speed Display provided the aircraft is climbi...

Page 803: ...the altitude and 200 feet from the selected altitude on leaving the altitude Item 17 PITCH AND ROLL MODE AND AUTOPILOT ANNUNCIATIONS Displays the active flight director pitch modes PIT VS ALT ARM ALT...

Page 804: ...how the system is configured Item 20 MANUAL ELECTRIC TRIM SWITCHES When both switches are pressed in the same direction will activate pitch trim in the selected direction If only one switch is moved t...

Page 805: ...O AROUND GA MODE BUTTON When pressed will engage the flight director in a pitch up attitude of 6 and wings level ROL mode GA will disengage the autopilot and cancel all armed modes including an armed...

Page 806: ...ting Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement those given for the standard aircraft in Section 6 Weight and balance of the basic Pilot s Operating Handbook A OPTIONAL EQU...

Page 807: ...PPLEMENT HONEYWELL KLN 94 GPS B RNAV NAVIGATION SYSTEM INTERFACED WITH ELECTROMECHANICAL INSTRUMENTS TABLE OF CONTENTS Page 1 GENERAL 9 48 2 2 LIMITATIONS 9 48 3 3 EMERGENCY PROCEDURES 9 48 5 4 NORMAL...

Page 808: ...ot s Operating Handbook when the TB airplane is equipped with the option HONE ANELL KLN 94 GPS B RNAV NAVIGATION SYSTEM INTERFACED WITH ELECTROMECHANICAL INSTRUMENTS This supplement does not constitut...

Page 809: ...anticipated flightshaJi be serviceable and allow an immediate crossed check on available ground aids or shall allow to return to primary navigation sources in case of GPS navigation 1055 Use of GPS as...

Page 810: ...CATA The use of SlOs and STARs stored in GPS data base is PROHIBITED The use of user waypoints on SID STAR is PROHIBITED 2 3 Instrument approach Non precision approach Use of the GPS is PROHIBITED 9 4...

Page 811: ...h the option HONEYWELL KLN 94 GPS B RNAV NAVIGATION SYSTEM INTERFACED WITH ELECTROMECHANICAL INSTRUMENTS HSI NAV FLAG Return to remaining operational navigation equipment NAV1 GPS1 push button NAV1 MS...

Page 812: ...t to DTK value Setthe OBS to the value of DTK Check the correct interception of the segment if the AP interface is used WHEN IN B RNAV VERIFY THE IFR PROCEDURE APPLICABLE TO EACH ONE OF THESE NEW SITU...

Page 813: ...ger at the latest revision However it is important to precise the following points for the GPS use on TB SET UP CONDITIONS Verify if the data base is current Verify data on the self test page Verify t...

Page 814: ...unciator amber CAUTION MSG ANNUNCIATOR MAY BE PERMANENTLY ILLUMINATED IF THERE EXISTS A PERMANENT MESSAGE WHEN A NEW MESSAGE APPEARS MSG ANNUNCIATOR JUST FLASHES MSG message annunciator will flash to...

Page 815: ...utopilot via the HSI which receives the information relative to the navigation source VORl or GPS selected by the NAV1 GPS1 push button When AP is engaged on the mode controller the autopilot is then...

Page 816: ...ance of the airplane described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airplane in...

Page 817: ...WELL KLN 94 Pilot s Guide at the latest revision GPS system consists of one KLN 94 GPS see Figure 9 48 2 This GPS may be a navigation source for the autopilot Course deviation information is then disp...

Page 818: ...D t a a card Map sea e change 0 PUSH ON 0 BFI S On I Off Brightness Message viewing DBS Leg mode selection Altitude functions W Q 0 PUll so Nearest VOR NOB Airports interceptions User defined waypoint...

Page 819: ...ED FOR B RNAV SID STAR AND APPROACH MODE PROHIBITED NAV1 MSG TERM GPSl WPT APR 8 _ NAV1 GPS1 push button Annunciators NAVl NAV1 navigation source GPS1 GP81 navigation source MSG WPT Repeater of GPS MS...

Page 820: ...SUPPLEMENT 48 HONEYWELL KLN 94 GPS B RNAV NAVIGATION SYSTEM INTERFACED WITH ELECTROMECHANICAL INSTRUMENTS INTENTIONALLY LEFT BLANK 9 48 14 SOCATA January 31 2001...

Page 821: ...SUPPLEMENT HONEYWELL KMD 550 MULTI FUNCTION DISPLAY TABLE OF CONTENTS Page GENERAL 9 49 2 2 LIMITATIONS 9 49 3 3 EMERGENCY PROCEDURES 9 49 3 4 NORMAL PROCEDURES 9 49 4 5 PERFORMANCE 9 49 5 6 WEIGHT A...

Page 822: ...escribed in Section 1 General of the basic Pilot s Operating Handbook when the T8 aircraft is equipped with the option HONEYWELL KMD 550 MULTI FUNCTION DISPLAY The KMD 550 is a multi function display...

Page 823: ...edition shall be readily available to the pilot The KMD 550 may be used only as an aid to navigation if navigation is based on other approved instruments the KMD 550 data base is current and compatibl...

Page 824: ...SPLAY KMO normal operating procedures recommended by the manufacturer are outlined in the KMD 550 850 Multi function Display Pilot s Guide PIN 006 18222 0000 Revision 0 dated Oct 20DO or any applicabl...

Page 825: ...ction 5 Pertormance H of the basic Pilot s Operating HandbOOK SECTION 6 WEIGHT AND BALANCE Information hereafter supplement those given for the standard aircraft in Section 6 Weight and balance of the...

Page 826: ...ction 5 ON OFF control 6 Selected indicators function 7 Function select keys 2 19 3 r 8 Control knobs inner and outer 9 Power key labels 10 Soft labels 11 Joystick 12 Power keys 13 Fault indicator o B...

Page 827: ...SUPPLEMENT SHADIN MICROFLO LTM DIGITAL FUEL MANAGEMENT SYSTEM TABLE OF CONTENTS Page 1 GENERAL 9 50 3 2 LIMITATIONS 9 50 3 3 EMERGENCY PROCEDURES 9 50 4 4 NORMAL PROCEDURES 9 50 4 5 PERFORMANCE 9 50...

Page 828: ...SUPPLEMENT 50 USHADtN MICRDFLD LTMDIGITAL FUEL MANAGEMENT SYSTEM INTENTIONALLY LEFT BLANK 9 50 2 SOCATA May 15 2001...

Page 829: ...o GPS receivers KLN 94 GNS 430 to transmit the fuel management data SECTION 2 LIMITATIONS Installation and operation oftha SHADIN MICROFLO LTM DIGITAL FUEL MANAGEMENT SYSTEM do not change the limitati...

Page 830: ...Handbook when the TB airplane is equipped with the option SHADIN MICROFLO LTM DIGITAL FUEL MANAGEMENT SYSTEM Normal operating procedures of the SHADIN MICROFLO LTM digital fuel management system reco...

Page 831: ...perating Handbook A WEIGHT ARM OPTIONAL EQUIPMENT EQUIPMENT per unit in oe SUPPLIER Ib a kg m 73 FUEL SYSTEM AND CONTROLS A Digital fuel management system 1 157 33 48 MICROFLO L SHADIN 0 525 0 850 OPT...

Page 832: ...ase the ADD FULL toggle switch so it returns to the center position To verify move the USED REMH toggle switch to the REM position Total usable fuel will be displayed 7 2 Partial fuel added Add the am...

Page 833: ...4 seconds Thefigure will decrement the longer you press the faster the decrementing When the correct figure is reached release both the USED REM toggle switch and the ENTER TEST button To avoid repeat...

Page 834: ...SUPPLEMENT 50 SHADIN MICROFLO L OIGITAL FUEL MANAGEMENT SYSTEM INTENTIONALLY LEFT BLANK 9 50 8 SOCATA May 15 2001...

Page 835: ...ENT GARMIN GNS 430 GPS B RNAV NAVIGATION SYSTEM INTERFACED WITH ELECTROMECHANICAL INSTRUMENTS GPS 1 B RNAV GPS 2 IFR TABLE OF CONTENTS GENERAL Page 9 51 2 LIMITATIONS 9 51 4 EMERGENCY PROCEDURES 9 51...

Page 836: ...led IFR in continental and Terminal Enroute areas as additional source I Conformity means ACJ 20X4 and ACJ 20X5 AC 20 138 The generalities hereafter supplement those of the standard airplane described...

Page 837: ...OMECHANICAL INSTRUMENTS Each data base contains information about airports communication frequencies VORs NDBs Intersections SIDs STARs instrument approaches flight service stations There is also room...

Page 838: ...dated 12 98 or any applicable following edition shall be readily available to the pilot each time the GPS navigation system is used The system must utilize the following software versions or more rec...

Page 839: ...Preflight procedures During preflight checks it is necessary to verify data base validity updating of the last AIRAC cycle The onboard equipment must be initialized in compliance with manufacturer pr...

Page 840: ...ved by the air navigation local authority for the approach in question Instrument approaches performed with the GPS must be achieved according to approved approach procedures given in the GPS data bas...

Page 841: ...GNS 430 GPS B RNAV NAVIGATION SYSTEM INTERFACED WITH ELECTROMECHANICAL INSTRUMENTS Use of the GPS approach mode is PROHIBITED GPS2 APPROACH MODE PROHIBITED Figure 9 51 1 GPS 2 if installed limitation...

Page 842: ...30 GPS B RNAV NAVIGATION SYSTEM INTERFACED WITH ELECTROMECHANICAL INSTRUMENTS GPS 1 B RNAV GPS 2 IFR 3 1 GPS 1 interfaced with HSI Option OPT10 23 006A HSI NAV FLAG OR INTEG WARNING Return to VOR or A...

Page 843: ...ckoning elements enable making sure that 8 RNAV accuracy criteria are observed When this condition is not met the Air Traffic Control must be contacted to return to conventional navigation If GPS navi...

Page 844: ...Searching the sky or RAIM position warning Return to VOR or ADF navigation source and to remaining operational navigation equipment CDI push button VLOC If the message mentions an error of course dev...

Page 845: ...s current Verify data on the self test page Verify that altitude data is valid for the GPS prior to flight In case of B RNAV use During the preflight planning phase the availability of GPS integrity R...

Page 846: ...tes GP CRS LEG green MSG message annunciator amber CAUTION MSG ANNUNCIATOR MAY BE PERMANENTLY ILLUMINATED IF THERE EXISTS A PERMANENT MESSAGE WHEN A NEW MESSAGE APPEARS MSG ANNUNCIATOR JUST FLASHES Th...

Page 847: ...S 2 When pressed once the push button illuminates VLOC white on the COl pressed one more time illuminates GPS green on the COl GPS mode of the GPS 2 if installed When using the GPS mode GPS 2 navigati...

Page 848: ...autopilot is then coupled with the HSI and uses displayed information track and course deviation Engaging the NAV mode on the autopilot mode controller will activate the FO on the AOI The FO uses sel...

Page 849: ...AV1 GPS1 push button I When crossing a waypoint the track resetting on the following navigation leg must be hand performed on the HSI When the AP NAV mode is engaged on the mode controller the autopil...

Page 850: ...ce of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airplane in Section 6 Weight and balance of the basic Pilot s Op...

Page 851: ...system consists of one GNS 430 GPS see Figure 9 51 2 This GPS may be a navigation source for the autopilot Course deviation information is then displayed on the HSI one repeater control unit see Figur...

Page 852: ...I Do ULI e j oc eN CRSR 0 D lOBS MSGI PROg 0 COM volume D NaVigation source VLOC GPS selection 8 VOR volume lOBS OBS Leg mode selection Selection of VOR VHF II sGl Message viewing eN frequencies Creat...

Page 853: ...MODE PROHIBITED NAV1 MSG TERM GPS CRS oes GPS1 WPT APR GPS eRS ceG NAV1 GPS1 push button GPS CRS OBS GPS CRS LEG push button Annunciators NAV1 NAV1 navigation source GPS1 GPS1 navigation source MSG WP...

Page 854: ...SUPPLEMENT 51 GARMIN GNS 430 GPS B RNAV NAVIGATION SYSTEM INTERFACED WITH ELECTROMECHANICAL INSTRUMENTS INTENTIONALLY LEFT BLANK 9 51 20 SOCATA May 15 2001 Revision 1...

Page 855: ...NE SUPPLEMENT HONEYWELL KLN 94 GPS NAVIGATION SYSTEM STAND ALONE TABLE OF CONTENTS Page GENERAL 9 52 3 2 LIMITATIONS 9 52 4 3 EMERGENCY PROCEDURES 9 52 5 4 NORMAL PROCEDURES 9 52 6 5 PERFORMANCE 9 52...

Page 856: ...SUPPLEMENT 52 HONEYWELL KLN 94 GPS NAVIGATION sYSTEM STAND ALONE INTENTIONALLY LEFT BLANK 9 52 2 SOCATA May 30 2001...

Page 857: ...the TB aircraft is equipped with the option HONEYWELL KLN 94 GPS NAVIGATION SYSTEM STAND ALONE The GPS is an automatic tridimensional latitude longitude altitude location and navigation means using in...

Page 858: ...E Data base updating must be verified before each flight NOTE The KLN 94 genuine data base is referenced to WGS 84 geodetic datum GPS USED ONLY FOR NAVIGATION IN DAYVFR IN SIGHT OF GROUND OR WATER Fig...

Page 859: ...4 GPS NAVIGATION SYSTEM STAND ALONE MSG ANNUNCIATOR ILLUMINATION MSG push button of GPS Check the message PRESS Bad Satellite Geometry Nay Super Flag Failure RAIM position error RAIM not available Sea...

Page 860: ...s far the GPS use on TB SET UP CONDITIONS Verify if the data base is current Verify data on the self test pags Verify that altitude data is valid for the GPS prior to flight SYSTEM ANNUNCIATORS MSG me...

Page 861: ...described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement those given for the standard aircraft in Section 6 Weight and...

Page 862: ...ormal operating procedures of the HONEYWELL KLN 94 GPS NAVIGATION SYSTEM STAND ALONE are described in the HONEYWELL KLN 94 Pilot s Guide at the latest revision The option includes one KLN 94 GPS insta...

Page 863: ...change 0 PUSH ON 0 TI cB3 On I Off Brightness Message viewing OBS leg mode selection Altitude functions IMSGI WPT IN 0 ICRSRI 0 PlJu Nearest VOR NOB Airports interceptions User defined waypoints g r w...

Page 864: ...SUPPLEMENT 52 HONEYWELL KLN 94 GPS NAVIGATION SYSTEM STAND ALONE INTENTIONALLY LEFT BLANK 9 52 10 SOCATA May 30 2001...

Page 865: ...NT GARMIN GNS 530 GPS B RNAV NAVIGATION SYSTEM INTERFACED WITH ELECTROMECHANICAL INSTRUMENTS GPS 1 B RNAV TABLE OF CONTENTS GENERAL Page 9 53 2 LIMITATIONS 9 53 3 EMERGENCY PROCEDURES 9 53 6 NORMAL PR...

Page 866: ...l of the basic Pilot s Operating Handbook when the TB airplane is equipped with the option GARMIN GNS 530 GPS B RNAV NAVIGATION SYSTEM INTERFACED WITH ELECTROMECHANICAL HSI GPS 1 B RNAV This supplemen...

Page 867: ...any applicable following edition shall be readily available to the pilot each time the GPS navigation system is used The system must utilize the following software versions or more recent ones Subsyst...

Page 868: ...Preflight procedures During preflight checks it is necessary to verify data base validity updating of the last AIRAC cycle The onboard equipment must be initialized in compliance with manufacturer pro...

Page 869: ...r navigation local authority for the approach in question Instrument approaches performed with the GPS must be achieved according to approved approach procedures given in the GPS data base The data ba...

Page 870: ...pped with the option GARMIN GNS 530 GPS B RNAV NAVIGATION SYSTEM INTERFACED WITH ELECTROMECHANICAL HSI GPS 1 B RNAV HSI NAV FLAG OR INTEG WARNING Return to VOR or ADF navigation source and to remainin...

Page 871: ...can be continued as long as cross checkings done with conventional means VOR DME NOB and dead reckoning elements enable making sure that 8 RNAV accuracy criteria are observed When this condition is no...

Page 872: ...Verify data on the self test page Verify that altitude data is valid for the GPS prior to flight In case of 8 RNAV use During the preflight planning phase the availability of GPS integrity RAIM shall...

Page 873: ...MAY BE PERMANENTLY ILLUMINATED IF THERE EXISTS A PERMANENT MESSAGE WHEN A NEW MESSAGE APPEARS MSG ANNUNCIATOR JUST FLASHES This annunciator is associated with the GPS 1 MSG message annunciator will f...

Page 874: ...ELECTROMECHANICAL HSI SOCATA I GPS flight plan In the active flight plan addition of a STAR or an approach is always made at the end of the flight plan In the scope of these additions the pilot must...

Page 875: ...ot is then coupled with the HSI and uses displayed information track and course deviation Engaging the NAV mode on the autopilot mode controller will activate the FO on the AOI The FO uses selected co...

Page 876: ...PS1 push button When crossing a waypoint the track resetting on the following navigation leg must be hand performed on the HSI When the AP NAV mode is engaged on the mode controller the autopilot is t...

Page 877: ...TB airplane described in Section 5 Performance of the basic Pilot s Operating Handbook SECTION 6 WEIGHT AND BALANCE Information hereafter supplement the one given for the standard airplane in Section...

Page 878: ...ot s Guide at the latest revision GPS 1 system consists of one GNS 530 GPS see Figure 9 53 1 This GPS may be a navigation source for the autopilot Course deviation information is then displayed on the...

Page 879: ...c 0 I I I y NavData card o COM volume 0 VOR volume Selectlo of VORNHF frequenCies Selection of group pages Group selection NAV WPT AUX QD Navigation source VLOC G PSI selection IOBsl DBS Leg mode sele...

Page 880: ...GPS1 push button GPS CRS OBS GPS CRS LEG GPS CRS Des GPS CRS leG GPS CRS OBS GPS CRS LEG push button Annunciators NAV1 NAV1 navigation source GPS1 GPS1 navigation source MSG WPT Repeater of GPS MSG W...

Page 881: ...Main switch 5B and BAT PCB FAILING Check ALTr FLO CB FAILING SUCCESS Check ALTr FLO CB I FAILING Close ALTr FLO 5B and ALTr PCB Close ALTr FLO 5B and ALTr PCB ALTERNATOR FAILURE BATTERY FAILURE R L R...

Page 882: ...see altimeter and airspeed indicator correction tables in Performance Section If erroneous indications persist carry out a precautionary approach maintaining an adequate airspeed margin above stall w...

Page 883: ...CTING WEIGHT AND BALANCE AIRPLJ NE MODEL ITEM No DATE OC As delivered DESCRIPTION OF EQUIPEMENT OR MODIFICATION Figure 6 2 SAMPLE WEIGHT AND BALANCE RECORD January 31 1986 SERIAL NUMBER PAGE NUMBER WE...

Page 884: ...SAMPLE AIRPLANE Weight Lever arm Ib 1866 170 45 38 I 47 44 170 45 38 I 47 44 340 80 00 397 42 70 110 102 54 3053 SECTION 6 WEIGHT AND BALANCE I YOUR AIRPLANE I I I Moment Weight Lever arm Moment Ib i...

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EADS Socata TB 20, Pilot'S Information Manual

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