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M20TN

1. CROSSWIND COMPONENT CHART EXAMPLE WIND SPEED ___________ 18 KNOTS ANGLE BETWEEN WIND DIRECTION AND FLIGHT PATH _ 35 HEADWIND COMPONENT 16 4 KNOTS 60 CROSSWIND COMPONENT 11 2 KNOTS 55 T 2 BO 109 20 9 45 309 a 40 400 A gt 035 500 Sm SS z e 600 e 225 lt SS z SN 6 20 22 SQ 700 ef O15 RS gt 10 lt 800 5 0 900 5 10 1000 180011600 15 1500 1700 1400 171300 1200 11100 20 0 5 10 15 20 25 30 35 40 45 50 55 60 CROSSWIND COMPONENT IN KNOTS ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL wd 5 5 SECTION V MOONEY PERFORMANCE M20TN AIRSPEED CALIBRATION PRIMARY STATIC SYSTEM POWER ON CLEAN CONFIGURATION Air Speed Calibration Primary Static System Power On Clean Configuration GIVEN IAS 129 KNOTS FIND CAS 130 KNOTS 0 lt 2 n lt tc m l lt x 100 110 120 130 140 150 160 170 KNOTS INDICATED AIRSPEED KIAS ERROR 5 5 130 131 135
2. EET HEEL 251 222088 e 22211202 2 pese ene repe pen 1 2 20608524 The minus sign indicates subtraction of the given numbers from the indicated pressure altitude to obtain correct altitude assuming zero instrument error CONDITIONS Power ON Vents amp Storm Window CLOSED Heater amp Defroster ON or OFF AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 14 Qo SECTION V PERFORMANCE STALL SPEED VS ANGLE OF BANK MOONEY M20TN Sdv 13 HV35 01 Sav 13 SOM 9221 NMOG Sg10042 o 08914 o HV35 01 64 14 SOM 1921 681 0008 o 05 o HV35 OF SOM 8261 681 8922 o 0 84 14 SVIM SVOM SVIA SVOJ SVOM SVDI SVOM NOILISOd dV 14 LHSISM 09 HV3O SSOHD MNVd 40 FTIONV Sv 0 22 SVOM 9 22 q33ds TLS STIVLS YNDDO Gp MNV8 dO AYN 6601 1334 008 01 310N Ol
3. Verify on BOTH After engine re start TAONE were dae iota dala a Seo qus ADJUST as required Propeller 2 24 ADJUST as required MIXIUEG bb Sade rae Rebus RELEAN as required for power setting Fact E Refer to power charts SECTION V LOW Boost PUMP b Rese Ciel eae te e IDE WESS OFF If engine does not re start after several attempts maintain best glide speed amp proceed to FORCED LANDING EMERGENCY TURBOCHARGER FAILURE WARNING If turbocharger failure is a result of a loose disconnected or burned through ex haust than a serious fire hazard exists If a failure in the exhaust system is sus pected in flight shut down the engine and LAND AS SOON AS POSSIBLE If a suspected exhaust system failure occurs before takeoff DO NOT FLY THE AIR CRAFT Turbocharger failure may be evidenced by the inability of the engine to develop manifold air pressure above the ambient pressure The engine will revert to normally aspirated mode and can be operated but will produce less than rated horsepower If turbocharger failure occurs be fore takeoff do not fly the aircraft If a failure occurs in flight readjust mixture as necessary to obtain fuel flow appropriate to manifold air pressure and RPM ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL
4. I 2 uz EE oe 3a 25 ae 55 6 onu gt 5 Zon 205 Ge Gz OA ke a a amp 5 2 zr Q Be 52 lt od gt lt ro nO zi 508 TVILN3SS3 SE o9 29 O guo 202 43 08 5219 lt SSE zoz amp 5 en 3 i lt m lt 2 gt 2 2 wo eye sy 8 2 9422 5 2 er 8 m 2 x 2 2 e C 508 1VILN3SS3 D 29 5 gt m lt z 88 2 B Q 22 A 5 S S 91 9 2 8 262 2 a 8 ord 2 86 2044 5 gt 50 gt 5 zm 9 5 9 4 e o SERE TEE 8 7 SHF 5 48 048 848 61 gt gt N 8 5 E 2 118 5 oe LL EE C sng TVLLN3SS3 NON 2 amp 4 E UE 5 m 53 E 5 5 O 8 5 5 5 mH S lt 0 2 m TU rr aS lt Y 1 lt m b E es 5 gt ell o o 25 54 ag 2 lt 26 m 41 ug t 5 tt B 2 OUR o 2 X nr o DEE S Figure 7 8 20 POWER SUMMARY AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006
5. IRURE AERE Full Flow Alternatot rra cec SOHO Ra C DO 28 Volt DC 100 AMPS Stater n estate ER e tea ne e IRR d ano Y antec sus 24 volt DC Intercooler sul RR Sek ea eme ARE a Ru ed Turbocharget eee TCM Kelly Aerospace Model 6 Turbocharger Controller System TCM Ratings Maximum Continuous Power 280 BHP at 2500 RPM Recommended Cruise Power 262 BHP at 2500 RPM ORIGINAL ISSUE 12 22 2006 4 1 5 SECTION I MOONEY GENERAL M20TN PROPELLER Hartzell DLE 1 MM Hartzell Model Number PHC J3YF 1RF F7693DF 2 Number or Blaos Ted as 3 Diameter hf ger ecu auc SX Matri 76 in 193 0 cm ab tti dec tuor prt de ERE dtt Ade 75 in 190 5 cm eere tage Sea Ue tag edm ML Eq EE Constant Speed Governor Hartzell Hydraulically controlled by engine oil Blade Angles 30 0 in Sta LOW staret beu deae RI vie 16 5 degrees 0 2 degrees att eua seite 38 0 degr
6. lx XE SHUTDOWN inspect for damage If engine does not start Magneto Starter Switch CONTINUE CRANKING MIXTE ees ai seed cae EC A top DOR RACE e Reb a epiac IDLE CUTOFF Low Fuel Boost Pump Switch OFF Throttle voce e FULL FORWARD Fuel Selector Valve s xeu coe ee De ce i et eg OFF Magneto Starter Switch OFF E MET cT su EXTINGUISH with Fire Extinguisher ENGINE FIRE IN FLIGHT F el Selector Valve 5 75 0 aer t ob hrs e ets ux OFF Throttle eter tte E eter E bee RE CLOSED CIT C PEDE IDLE CUT OFF Magneto Starter Switch OFF Cabin Ventilation amp Heating Controls CLOSED ELECTRICAL FIRE IN FLIGHT Smoke in Cabin If electrical power is essential for the flight attempt to isolate the faulty circuit Gabin Ventilation CDI SU HC ERE RECON das OPEN Heating Contool e euet ee na Pen fub Pele CLOSED Circuit Breakers CHECK to identify faulty circuit if possible LAND AS SOON AS POSSIBLE
7. eoe rcg 5 2 VARIABLE Shii EP 5 2 OPERATIONAL PROCEDURES FOR MAXIMUM FUEL EFFICIENCY BEST POWER 4 45 Raus Rd ea 5 2 BEST ECONOMY de 5 3 PERFORMANCE CONSIDERATIONS 5 4 LANDING QEAR DOORS 24425 54 eme 5 4 TABLES AND CHARTS TEMPERATURE CONVERSION 5 4 CROSSWIND COMPONENT CHART 5 5 AIRSPEED CALIBRATION PRIMARY STATIC SYS POWER ON CLEAN 5 6 AIRSPEED CALIBRATION PRIMARY STATIC SYS POWER OFF CLEAN 5 7 AIRSPEED CALIBRATION PRIMARY STATIC SYS POWER ON 10 GR DWN 5 8 AIRSPEED CALIBRATION PRIMARY STATIC SYS POWER OFF 10 GR DWN 5 9 AIRSPEED CALIBRATION PRIMARY STATIC SYS POWER ON 33 GR DWN 5 10 AIRSPEED CALIBRATION PRIMARY STATIC SYS POWER OFF 33 GR DWN 5 11 AIRSPEED CALIBRATION ALTERNATE STATIC SYSTEM 5 12 ALTIMETER CORRECTION PRIMARY STATIC SYSTEM 5 13 ALTIMETER CORRECTION ALTERNATE STATIC SYSTEM 5 14 STALL SPEED VS ANGLE OF BANK 5 15 TAKEOFF GROUND ROLL 2225244 26d etre ede dk bor at de 5 16 50 OBSTAG
8. INSPECT c CT ee oo ech PME Remove ice snow or frost 4 Left Fuselage Tailcone Cabin Fresh Air Vent Dorsal UNOBSTRUCTED Tailcone Empennage Access Panel SECURED Instrument Static Pressure Port UNOBSTRUCTED Avionics Battery 1 Access Panel SECURED Auxiliary Power Plug Access Door SECURED Static System PUSH Plunger UP Hold 3 5 Seconds General Skin 4 INSPECT 5 Left Wing General Skin Condition INSPECT Remove ice snow or frost Wing amp attach points INSPECT Aileron amp attach points INSPECT Control linkages ie Rer Eat M aee es INSPECT Wing Tip Lights and Lens INSPECT Fuel Tank Vent eee IAS LHP eun UNOBSTRUCTED Master ON reach through pilots window Pitot TUDE site oe Mae BERTA UE et RR bte UNOBSTRUCTED SECURED Heat element Operative Landing Taxi
9. 3 12 LOSS OF OIE PRESSURE e so ee t e ct ce 3 13 ENGINE DRIVEN FUEL PUMP FAILURE 3 13 FUEL VAPOR SUPPRESSION FLUCTUATING FUEL FLOW 3 13 FIRES Ebr 3 14 ENGINE FIRE ON GROUND DURING STARTUP 3 14 ENGINE FIRE IN FE IGEN ial Seen Gree outed 3 14 ELECTRICAL FIRE IN FLIGHT SMOKE IN CABIN 3 14 EMERGENCY DESCENT PROCEDURE 3 15 GUIDE eM 3 16 FORCED LANDING EMERGENCY 3 16 GEAR RETRACTED EXTENDED 3 16 OVERWEIGHT LANDING PROCEDURE 3 17 SYSTEMS EMERGENCIES 3 17 PROPELLER OVERSPEED ate eee fie s 3 17 ALTERNATOR OVERVOLTAGE 3 17 ALTERNATOR OUTPUT LOW 3 17 AETERNATOR FAIEURE 2 rer rre ete tem de cha 3 18 AVIONICS EMERGENCIES 3 19 PFD OR MFD DISPLAY FAILURE 3 19 AHRS FAILURE Rip eer Ro e epic ae ee
10. tutu E eie ELE UNOBSTRUCTED Left Side Engine Cowl Fasteners SECURED Exha st Pipes ees Rec Re ORAL INSPECT SECURED Engine Oil Filler Door OPEN amp INSPECT AREA NOTE The engine compartment must be free of foreign objects which could result in possible overheating and serious damage to the engine Engine Oil EE CIV LM EMI CHECK QUANTITY uester Teint tes cst gea Rode Ii M eA 8 7 57 L Engine Oil Filler DOOR gue CLOSE amp SECURE Cooling Air Inlet Verify UNOBSTRUCTED 7 Propeller Spinner amp Front Cowl Area INSPECT for nicks cracks asd retia taii eub pd tu oil leaks rotational movement Prop De Ice Boots if INSPECT condition Induction Air Inlet Filter I II UNOBSTRUCTED Nose Gear Shock Discs Tire amp Doors INSPECT Wheel pedes be t bc tue REMOVE 8 Right Cowl Area Right Side Engine Cowl Fasteners SECURED Cooling Air Inlet
11. AS DESIRED Landing Gear 2 2 Verena EXTEND below 140 KIAS Check Gear Down light ON Check visual indicator ts Dor GER rad tian v ad EQUI ase FULL RICH on final Propeller bb med RE HIGH RPM on final Fuel Boost Pump Switches OFF Fuel Selector 2 eb pac ge etri FULLEST TANK Wing Elaps TIRE DU a AER T O POSITION ct EA FULL DOWN below 110 KIAS CAUTION To minimize control wheel forces when entering landing configuration timely nose up trimming is recommended to counteract nose down pitching moment caused by reduction of power and or extension of flaps Elevator Trim cs Sot E yeaa ue d sae Bow ke NOE AS DESIRED Rudder i Stet ei sena AS DESIRED Parking Brake eode Ne PR we Ente ie Teo e a e HE a VERIFY OFF NOTE The parking brake should be rechecked to preclude partially applied brakes dur ing touchdown GO AROUND BALKED LANDING CAUTION To minimize control wheel forces during GO AROUND timely nose down trim ming is recommended to counteract nose up pitching moment as power is in creased and or flaps are retracted POWER 52225 seus iure Pu ee SE FULL FORWARD 2500 RPM pte pt ee REED eile bm epe eee
12. Se x Re e RI Ge INCREASE POWOb ed te te bee er d Eas er deni tele REDUCE PREPARE FOR POSSIBLE ENGINE FAILURE IF TEMPERATURE CONTINUES HIGH AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 3 12 x MOONEY SECTION III M20TN EMERGENCY PROCEDURES LOSS OF OIL PRESSURE Oil temperature 1709 to 2409 F 77910 1049 C If Oil Temperature Normal LAND AS SOON AS POSSIBLE If Oil Temperature Above Normal TAONE 5 REDUCE to Minimum Power Required n LAND AS SOON AS POSSIBLE BE PREPARED FOR LOSS OF ENGINE POWER AND PREPARE FOR AN EMERGENCY LANDING ENGINE DRIVEN FUEL PUMP FAILURE WARNING IF HIGH BOOST PUMP MUST BE LEFT ON TO ACHIEVE NORMAL FUEL FLOW LAND AS SOON AS PRACTICABLE WARNING When operating engine at moderate power with HIGH BOOST ON and engine driven fuel pump has failed engine may quit or run rough when manifold pressure is reduced unless manually leaned An engine driven fuel pump failure is probable when engine will only operate with HIGH BOOST pump ON Operation of engine with a failed engine driven fuel pump and auxiliary fuel pump HIGH BOOST ON will require smooth operation of engine controls and corresponding mixture change when throttle is repositioned or engine speed is changed When retarding throttle or reduc
13. ee e E ec eR eoe Sas tee 7 31 CABIN EIGEITING 7 31 EXTERIOR LIGHTING 7 31 CABIN ENVIRONMENT 2 7 32 HEATING amp VENTILATION SYSTEMS 7 32 PITOT PRESSURE amp STATIC SYSTEM 7 33 STALL WARNING SYSTEM 7 33 OXYGEN SYSTEM E RN enu pb oU E Sg wa e es 7 34 VAGUUM SYSTEM alb title sane 7 37 EMERGENCY LOCATOR TRANSMITTER 7 937 ELT REMOTE SWITCH OPERATION 7 38 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 2 VA SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION INTRODUCTION Acquiring a working knowledge of the aircraft s controls and equipment is one of your important first steps in developing a fully efficient operating technique This Airplane and Systems Section describes location function and operation of systems controls and equipment It is recom mended that you the pilot familiarize yourself with all controls and systems while sitting in the pilot s seat and rehearsing the systems operations and flight procedures port
14. 907 2000 LOADED 41 42 43 44 45 46 47 48 49 50 51 AIRCRAFT AIRCRAFT CG LOCATION Lc INCHES AFT OF DATUM STA 0 0 MRCG LIM WEGRIT 3368 Ibs ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 6 11 SECTION VI MOONEY WEIGHT AND BALANCE M20TN FIXED BALLAST The 20 has provisions for a fixed ballast located in the tailcone at Fuselage Station 209 5 Some aircraft with EFIS TKS amp other systems may require all or a portion ofthe fixed ballastto be removed in order to stay within the weight and balance center of gravity envelope EQUIPMENT LIST Thefollowing equipment list is a listing of items approved atthe time of publication ofthis manual for the Mooney M20TN Only those items having an X in the Mark If Installed column and dated were installed at Mooney Aircraft Company Inc at the time of manufacture If additional equipment is to be installed it must be done in accordance with the reference draw ing or a separate FAA approval NOTE Positive arms are distances aft of the airplane datum Negative arms are dis tances forward of the airplane datum Asterisks after the item weight and arm indicate complete assembly installations Some major components of the assembly are listed and indented on the lines following The summation of the major components will not necessarily equal the complete assembly installation AIRPLANE FLIGHT MANUAL 2 ORIGINAL ISSUE 12 22 2006 6 1
15. M20TN RATE OF CLIMB AT Vy 14 910110 30 31V SECTION V PERFORMANCE LH9I3M LVO OSZ 0061 0090 0971 0091 08102100 08 09 Op 02 0 OZ Ob 09 08 001 T I T T T T 1 I T 1 T 1 T T 1 T I T T I T N 81 LH9I3M 2 1 0 A 090012 0082 0060 0006 oore ooze 0066 09 07 02 0 09 0 d L 004 o 008 lt lt 9 tc AS s 0011 AAR DSS DOSE S i H mak am H 14 31 VH 0091 0091 Ft 0021 H 5 0081 H 0061 0002 NIW L4 068 gWI19 30 31V 64 14 5 97 0916 LH9IIM 1 1 ao 14 0002 11 IYNSSIYd SVIM POL 3345 Do Sb vo 111 450861 0082 7114 lt Q31VI2OSSV SECTION V PERFORMANCE RATE OF CLIMB at 120 KIAS CRUISE CLIMB 14 W179 ALVY MOONEY M20TN 93 LH9I3M LVO 0652 0061 0861 0091 0991 006 081001 08 09 02 0 02 09 08 00 5 21 97 LH9I3M 2 1 0 0 oy 002 0082 0060 0006 0016 0008 0066 09 0c 0 02 Or 09 08 009 009 002 AIRPLANE FLIGHT MANUAL 008 006 FH NIIN 13 SINITD 40 ALVA LL IA NIIW L3 072 HWI1O 30 31V dn SdV14 810916 Q312V3 l3 140002 11 3YNSSAYd SVIM 021 033
16. 1404 ISINYI Ava au vaNvis LIL 489d JO 06 H3A Od 1538 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 5 24 SECTION V PERFORMANCE CRUISE POWER SETTINGS amp FUEL FLOWS BEST ECONOMY MOONEY M20TN suonipuoo uo Buipuedep Io Aew 44186 6 21 9 0 9 81 51 any eui BHU 606 LYO 2 61 HY 00082 0082 10 ejduex3 15 9 01 uoee 10 9 0 eseoJou y OJON pJepuejs 5 0 uoeo 10 44 166 9 0 peniuued si 1104 02 z 30N 10 111 3 5491 16 eq 1 0022 199 000 22 sepninje 1y IION je6 q 079 1314 3singo Ava 5 LIL 428d 1 09 1538 5 25 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 SECTION V MOONEY PERFORMANCE M20TN SPEED and POWER SETTINGS vs ALTITUDE BEST POWER Conditions Example Mixture Pressure Altitude 16000 f
17. CHECK for proper indications Lift Off Climb Speed As specified in SECTION V Takeoff Distance Landing Gear RETRACT IN CLIMB after clearing obstacles Wing FIaps Jg bee eom pee leti quet mte eripe eget wat cite tout itg UP TAKEOFF SHORT FIELD Complete BEFORE TAKEOFF Checklist First Wing Flaps Ere DERE ae Rt PU ed beatae TAKEOFF POSITION Brakes ope ec meme me aditu emineat APPLY Throttle scd A EE Gea EAM CER Es FULL 2500 RPM hacac FULL RICH LOW Boost PUMP ire rep Re RE Rte a ds ON Brakes cipes bike expe pe oue EO pide RELEASE Lift Off Climb Speed As specified in SECTION V Takeoff Distance Landing Gear RETRACT IN CLIMB after clearing obstacles Wing Flaps vete eC RC RU A A NS Rs UP AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 4 12 4 SECTION IV M20TN NORMAL PROCEDURES CLIMB NOTE If applicable use noise abatement procedures as required See Section V for rate of climb graph CLIMB CRUISE et eeu te pee Ped trt nest 120 KIAS Throttle eL lE M P FULL esc ee oe cte evt see ea ee Dee RC ER a RR ERR a hi al 2500 RPM Mixture ade rate ix e ae FULL RICH 1350 to 1450 TIT LOW Boost P
18. eer vem E ae Ee E ah asa e OFF ccr CLOSED Magneto sc i oth eet uetus ae Sits OFF Wing Flaps IN THE LANDING POSITION If airspeed and height above ground permit full ex tension offlaps Otherwise use maximum flap extension practicable depending on airspeed and height above ground Obtain this airspeed if altitude permits otherwise lower the nose maintain current airspeed and land straight ahead WARNING If the LOW or HIGH boost pump is in use during an emergency proper leaning procedures are important During the descent and approach to landing phases of the flight DO NOT set the mixture too rich as prescribed in the normal landing procedures and avoid closing the throttle completely If a balked landing is nec essary coordinate the simultaneous application of throttle and mixture ENGINE POWER LOSS IN FLIGHT Above 400 Feet AGL AlrSpeed 5 vL 85 KIAS Flaps UP UI TEL ILLA Wes 80 KIAS Flaps DOWN Fuel Selector n 5i SELECT FULLEST TANK Magneto Switch Verify on BOTH LOW Boost Pump ON Throttle atento DER Ceo ec RD e enin SET TO HALF OPEN Propeller x xp rS Ue se DE FULL FORWARD Mixture PULL TO CUTOF
19. Dee ERES Dee as d aea qs COP EX Ere qa ON Propeller De Ice Secus e dL Deoa e Eo CORE ET Tx ON if installed Alternate Static Source ON if required Cabin Heat amp Defroster ON Engine Gauges MONITOR for any engine power reduction Turn back or change altitude to obtain an outside air temperature less conducive to icing Move propeller control to maximum RPM to minimize ice build up on propeller blades If ice builds up or sheds unevenly on propeller vibration will occur If excessive vibration is noted mo mentarily reduce engine speed with propeller control to bottom of GREEN ARC Lowest RPM then rapidly move control FULL FORWARD AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 a 4 SECTION III M20TN EMERGENCY PROCEDURES NOTE Cycling RPM flexes propeller blades and high RPM increases centrifugal force which improves propeller capability to shed ice As ice builds on the airframe move elevator control fore and aft slightly to break any ice buildup that may have bridged gap between elevator horn and horizontal stabilizer Watch for signs of induction air filter blockage due to ice build up increase throttle setting to maintain engine power NOTE If ice blocks induction air filter alternate air system will open automatically With ice accumul
20. SYSTEM esae E ext et e p tU RR RU ROCA C cac t 7 3 RUDDER SYSTEM one egeat ate oe e eee os afa 7 4 RUDDER TRIM SYSTEM 7 4 ELEVATOR SYSTEM n tee Ae Geach dee t bae uU A Seach 7 4 PITCH TRIM SYSTEM n eon ra e doa 7 4 WING FLAPS tete S Estee Cie Cast Beckie Gap 7 4 INSTRUMENT PANEL ERR aperte eic t o t CU Rc RR 7 4 GARMIN G1000 y AES eR BEES 7 5 FLIGHT PANEL amp INSTRUMENTS 7 8 SWITCHES amp CONTROLS 7 8 ANNUNCIATOR amp SWITCH PANEL 7 13 GROUND CONTROL nr tee nte ha ak ee eame e 7 15 NOSE GEAR STEERING ck CA RUN EE p 7 15 TAXIING AND GROUND HANDLING ee 7 15 LANDING GEAR e e nee d da ebd aces e woe tn ca 7 15 CONSTRUCTION 355 o ep t x tee Ue 7 15 RHETRACTION SYSTEM po 7 15 WHEEL BRAKES voucher reb rt cec e Re dd d 7 16 EMERGENCY EXTENSION SYSTEM 7 16 WARNING SYSTEM Pte EO ete 7 16 GABIN ete ean edu cci Rt e 7 16 BAGGAGE COMPARTMENT
21. H 03 NISHIN 151 LNAWdINOA ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 6 28 SECTION VI WEIGHT AND BALANCE MOONEY M20TN 061 8 011 LS N33AAL38 LN3IALHVdWWOO 39V99V8 NI GAMOLS ATIVINHON s NM 3 18I9r193N SMOIM 21 15 115 39HVHOSIG 211715 Tr S0 022066 20088 H3ldVQV 318V2 et L 991008 11SNI 650 SLLOZZ 7 LSNI NOISN3LX3 6 6008 YOLVNYALTV 15 66001 2 9 1and TANVd SS399V OGE RI 2 6 88 T 0060 1 114 e 61074 1558 G3TIVLSNI SSHONI 681 ONIMVYC NOILdIHOS3Q Jl LM 434 Lr O03 NLSYWN 151 LNAWdINOA 6 29 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 M20TN WEIGHT AND BALANCE SECTION VI CY 99 ws 069 09 TINA 6 aima SAL 99 200069 01114 ON 391 dOHd SDNIA J V SAL gen 200069 A1NO SONIM SAL _ 1V3S H39N3ssvd 16 LHOM 9 Gen
22. Verify UNOBSTRUCTED Windshield i bee Na NDA REY pd CLEAN Cabin C e UNOBSTRUCTED 9 Right Wing Fuel Tank Sump Drain DRAIN dea Use sampler cup to VERIFY fuel is free of water sediment amp other contamination Back e id ecce VERIFY proper fuel BLUE 100LL GREEN 100 octane SEE CAUTION on diesel fuel on previous dua erue adire VERIFY drain closes and does not leak Right Main Gear Shock Discs Tire amp Doors INSPECT Wheel Chocks mk REMOVE General Skin Condition INSPECT Remove ice snow and frost Fuel CHECK QUANTITY SECURE CAP NOTE The optional visual fuel quantity gauge is to be used for partial refueling pur poses only DO NOT use for preflight quantity check Tiedown Rope Chain REMOVE Fuel Tank Vent o serm DR nc ob e EOD RI RCNH ca UNOBSTRUCTED Landing Taxi Lights INSPECT Lens amp Bulbs Wing Tip Lights and Lens INSPECT and Attach Points INSPECT ORIGINAL I
23. 17 0 In 43 2 cm Ground to Bottom of Sill 46 0 In 116 8 cm ORIGINAL ISSUE 12 22 2006 d 1 7 SECTION I MOONEY GENERAL M20TN SPECIFIC LOADINGS Wing Loading Maximum Gross Weight 19 26 Ibs sq ft nias tL EE om 94 kg sq m Power Loading Maximum Gross 12 03 Ibs HP puc tu PORE EF ROT NO 5 46 kg HP IDENTIFICATION PLATE All correspondence regarding your airplane should include the Serial Number as depicted on the identification plate The identification plate is located on the left hand side aft end of the tailcone below the horizontal stabilizer leading edge The aircraft Serial Number and type certificate are shown GARMIN G1000 GENERAL The GARMIN G1000 Integrated Avionics System is a fully integrated flight engine communica tion navigation and surveillance instrumentation system The system consists of a Primary Flight Display PFD Multi Function Display MFD audio panel GMA Air Data Computer ADC Attitude and Heading Reference System AHRS engine airframe processing unit and integrated avionics GIA containing VHF communications VHS navigation and GPS navigation The primary function of the PFD is to provide attitude heading air data navigation and alerting information to the pilot The PFD may also be used for flight planning The primary
24. A ERE ORIGINAL ISSUE 9 9 etus tar epus be perte ipu pis fieret ORIGINAL ISSUE Qa EIU M ORIGINAL ISSUE Plus applicable supplements inserted ORIGINAL ISSUE 12 22 2006 wi POH AFM POH 003900 1V This POH AFM effective with S N 31 0001 THRU 31 TBA INTRODUCTION M20TN 10215 TLLA UE Ii TA ed Mea ORIGINAL ISSUE ER Re Et eei per ps ORIGINAL ISSUE 10 53 etr t lestie tds ORIGINAL ISSUE bis afe POUR UR ee It Bei e dus dE ORIGINAL ISSUE cL EI ORIGINAL ISSUE 1056 eeu EUR eed ee Eee ia Es pecia ORIGINAL ISSUE Deep ORIGINAL ISSUE 1028 wok eb neo ud Rls ORIGINAL ISSUE 10 08 ues E Leere E censes ORIGINAL ISSUE e buses a Me Rec rg ORIGINAL ISSUE 10211 ern RE ue ck gud Ear eR eae PRSE ORIGINAL ISSUE T0sd 2 LE ORIGINAL ISSUE ORIGINAL ISSUE 12 22 2006 A POH AFM POH 003900 This POH AFM effective with S N 31 0001 THRU 31 MOONEY INTRODUCTION M20TN LOG OF REVISIONS REVISION REVISED DESCRIPTION FAA DATE NUMBER PAGES OF REVISIONS APPROVED
25. ORIGINAL ISSUE ORIGINAL ISSUE eR ge pir Drei nA ald ORIGINAL ISSUE VA Lei e otto ossia dir ORIGINAL ISSUE iat tsa tat Eb tene ORIGINAL ISSUE dO i uctus feu ORIGINAL ISSUE epu ELS A raa udo e m ke eee reign i e a ORIGINAL ISSUE ASV uu veu mr eR ME PEDEM IE ES up Ed eek ORIGINAL ISSUE ELO reb A rie ORIGINAL ISSUE cocos or C URP Ud a e ORIGINAL ISSUE Vou PEDI MI ETIN ORIGINAL ISSUE mM ORIGINAL ISSUE VEHI ORIGINAL ISSUE Fd ice ats sene ORIGINAL ISSUE D PER ORIGINAL ISSUE Tee abut udo e e ie eee trees M e a ORIGINAL ISSUE p ORIGINAL ISSUE E EM ORIGINAL ISSUE d desta ORIGINAL ISSUE POS ALD Lote tr b esten ORIGINAL ISSUE POA s DOR Ls Tee qud ORIGINAL ISSUE Mem fel risa d Ste s insit A eee coins ORIGINAL ISSUE 926 ads cease edt s ebd ted us Ene aad ot ORIGINAL ISSUE VP EE PEE EE EE Mt ORIGINAL ISSUE bias SEE PEN ES ORIGI
26. OFF prior to landing e e Rand Sab E OUR nM ERU ae ie LEVEL Attitude AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 3 16 SECTION III M20TN EMERGENCY PROCEDURES OVERWEIGHT LANDING PROCEDURES In the event it is necessary to land with weight exceeding 3200 Lbs 1452 Kg max landing weight the following procedure is recommended in addition to normal APPROACH FOR LAND ING procedures Approach Airspeed isse Sees 80 KIAS Use aflatter approach angle than normal with power as necessary until a smooth touchdown is assured Expect landing distance over a 50 feet obstacle Ref SECTION V to increase at least 600 ft Conduct Gear and Tire Servicing inspection as required Ref SECTION VIII SYSTEMS EMERGENCIES PROPELLER OVERSPEED ne e xta ders E m de tO E RETARD OIl BreSSUrO 3 5 coste OI OP C CUR gii De em CHECK Propeller i etr mee DECREASE RPM re set if any control available a pede Ee NER UMS REDUCE Throttle eere AS REQUIRED to maintain RPM below 2500 RPM Record POWER settings MAX RPM and duration TIME of overspeed event NOTE Refer to Engine and Propeller operating manuals to determine continued airwor thiness requirements post flight ALTERNATOR OVER
27. Pa re Tea ee Verify red ALT VOLTS light extinguishes Stdby Alt Emerg Bus switch cece tenet eens OFF bote eue ate Hos Verify red ALT VOLTS light illuminates Alt Fed SWIER 2 2 ee vb a pr bte BO BER DIRAS Me Fede ON hubnut ete DUE late wate DOE RUD IHRER Verify red ALT VOLTS light extinguishes ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL SECTION IV MOONEY NORMAL PROCEDURES M20TN Standby Alternator Checks Complete AMME ce RE Due REG E e EE IE bs CHECK positive charge indication Main Battery Greater than 26 5VDC Lots hs ure eui LE roS ee Select the other battery using the BAT 1 2 selector eoe A eid ees CHECK Positive Charge Indication Main Battery Greater than 26 5VDC Sixt nt e Select desired Main Battery for use during flight using BAT 1 2 selector Elevator Trim dope pe EUR tp LES RE TAKEOFF SETTING Rudder TAM eer TAKEOFF SETTING Wing Flaps EIER ale Ta E CHECK operation DM M ace SET AT TAKEOFF POSITION 10 degrees Flight Controls CHECK free and correct movement Cabin CHECK SECURED Seats Seat Bel
28. ate TOUCHDOWN AT NORMAL LANDING SPEEDS SLOPDING acc etter tne AS REQUIRED STOP AIRCRAFT PRECAUTIONARY LANDING WITH ENGINE POWER Seat Belts Shoulder Harnesses FASTENED AND SECURE Loose Objects bere e een SECURE Wing Flaps asi ssi net s cst aie ap sc petis SET TO TAKEOFF POSITION ced dawn ae toi rat cal Eis 75 KIAS DEEP 80 KIAS Above 3200 Lbs Select a Landing area Wing Flaps SET TO LANDING POSITION On Final Approach US scii Spesa 75 KIAS 80 KIAS Above 3200 Lbs reete LAND AS SLOW AS PRACTICABLE NOSE UP ATTITUDE Magneto eee pq e op dise MR OP RATE Rn OFF LOW Boost PUMP trm eee im quee tenia vexare ee Verify OFF Stopping x res eb A d AS REQUIRED TO STOP AIRCRAFT NOTE If fire is not extinguished attempt to increase airflow over engine by increasing glide speed Proceed with FORCED LANDING EMERGENCY DO NOT attempt an engine restart If necessary use fire extinguisher to keep fire out of cabin area POWER LOSS PRIMARY ENGINE INDUCTION AIR SYSTEM BLOCKAGE Blockage of the primary engine induction air system may be a r
29. HV39 H3MOd SOM 1961 587 0006 LHDISM 00 3ldWvx3 5 Q31VIOOSSV 5 15 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 SECTION V PERFORMANCE ASSOCIATED CONDITIONS PAVED DRY SURFACE FULL PRIOR TO BRAKE RELEASE LANDING GEAR DOWN WING FLAPS EXTENDED 10 80 REL HUMIDITY RUNWAY POWER MOONEY M20TN TAKEOFF DISTANCE GROUND ROLL 39NVISIG 7108 ANNOYS 3303XV L 2 2 20 oo 5 gt x x o a w 2211 N 2 5 gt lt 8822 x Weegee x 17 4554 001 65588 5 N E E SE E EE lt 2 267625 IE EG 4 7 2o0o0ooo0 7 88588 o FERRE EERE EEG 9 39N3Y343 Y LHOI3M 1 81 8922 WEIGHT LB X 100 WEIGHT KG X 100 HUMIDITY IN EXCESS OF 80 CAN ADD UP 10 TO THE TAKEOFF DISTANCE OAT F 40 30 20 10 0 10 20 30 40 50 33 31 29 27 250 AIRPLANE FLIGHT MANUAL 5 16 40 20 0 20 40 60 80 100 120 15 14 13 12 ORIGINAL ISSUE 12 22 2006 SECTION V PERFORMANCE TAKEOFF DISTANCE OVER
30. taped wa e e s e e 6 4516 sq centimeters 1 5 TOOL cbe eb sup e erba ue edi eU erba 929 sq centimeters T square yard s LU REN EE DRE P DE RURSUS 0 836 sq meter VOLUME OR CAPACITY U S Customary eren dur he Ra de nce Metric Equivalents AS CUDIC NGH a eoe aste ue did delle Reb eT 16 39 cubic centimeters T cubic TOO 0 028 cubic meter T CUBIC e eee ees 0 765 cubic meter U S Customaty Metric Equivalents Liquid Measure 4 11 6 e ie aac AM ect tee eR Nu 29 573 milliliters A PING Oe 0 473 liter ee EE 0 946 liter Wake gto de Pere 3 785 liters US Customary biel ea nuca eel eM ea Metric Equivalents Dry Measure DDIM coss o teu tem ote te tine e o eui ed 0 551 liter IU PTT 1 101 liters British Imperial U S Metric Liquid and Dry Measure Equivalents Equivalents 1 fluid ounce 0 961 US 28 412 milliliters fluid OUNCE osse eset certet ed eas 1 734 cubic inches 109205 ats 568 26 milliliters dry pints 1 201 U S liquid pts 34 678 cubic inches T quart un rtis 1 082 U S LEE 1 1
31. 10 6 SPECIAL CONDITIONS CAUTIONARY NOTICE 10 6 WALK AROUND INSPECTIONS 10 7 COCKPIT GHEGCKS RE CREER 10 7 FLIGHT OPERATIONS iis met e c o i t a oer RE 10 7 GENERAL qos 10 7 TURBULENT WEATHER 10 7 FLIGHT IN TURBULENT AIR 10 8 MOUNTAIN EEYING act t ett e ot rep an HR spem te 10 8 VER EOW CEILINGS extre eb nt He EC CS RR 10 8 VERAT NIGHT E bte ROI RIO ER Ee 10 8 VERTIGO DISORIENTATION 10 9 STALLS SPINS AND SLOW FLIGHT 10 9 STANDARD PROCEDURE SPIN RECOVERY 10 10 VORTICES WAKE TURBULENCE 10 10 TAKE OFF AND LANDING CONDITIONS 10 10 MEDICAL FACTS FOR PILOTS 10 11 GENERAD nr deberse eS 10 11 FATIGUE 10 11 FY ROXIA edt et et gs em dese vp aider ets 10 11 HYPERVENTILATION het peo ticos e Sec e 10 11 eaae b ARA e A ee Gas Meee 10 11 DRUGS ccm 10 12 SCUBA DIVING tekst e PRA eR Ee dedi ek CI bti a 10
32. LM 3H WALI WALI 3 O3 NISHINN 151 LNAWdINOA 6 21 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 SECTION VI MOONEY WEIGHT AND BALANCE M20TN INCHES cm REF DRAWING o Lu Lu ITEM DESCRIPTION F MISCELLANEOUS SYSTEMS MRSTN EQ F1 AIRPLANE FLIGHT MANUAL 2 ORIGINAL ISSUE 12 22 2006 6 22 SECTION VI WEIGHT AND BALANCE MOONEY M20TN 119 22 991 147 26 6 82 7 147 evs 26 221 012 oe 2 081 9671 Oct 0S 8797 0S x v61 722 L 0 88 01 wea suosia nns Q3TIVISNI 34HVIN L9 O3 NISHIN 151 LNAWdINOA 6 23 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 M20TN WEIGHT AND BALANCE SECTION VI 28211 95 982 9 09 LONdOLNV 007245 NIINHVO 077921 00 28 122 96 006056 18 061 697 vt 002096 9 08 261 107086 82 1 002096 V69 69 135 00 28 6 28 82 802 80 82 002096 00019 Q3TIVLISNI e 5SNIAVHG NOILdIlHOS3q 03 15 151 LN3lWdinio3 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 6 24 SECTION VI WEIGHT AND BALANCE MOONEY M20TN Q3TIVISNI 151 LNAWdINOA
33. MEUSE ORIGINAL ISSUE GHI ci datis Led tc Ce idea eh ie ORIGINAL ISSUE pot t t Ett ORIGINAL ISSUE NCC e ORIGINAL ISSUE RT ETT ORIGINAL ISSUE P418 S uuo ceo Luo ORIGINAL ISSUE GAO M PSI ORIGINAL ISSUE DEDE Lise D E Ro ORIGINAL ISSUE TRU CEN MIND AR ORIGINAL ISSUE DU MERECE HMM HC A ORIGINAL ISSUE ORIGINAL ISSUE 27 E MU ORIGINAL ISSUE ERROR ORIGINAL ISSUE E ORIGINAL ISSUE TIR erp ORIGINAL ISSUE ORIGINAL ISSUE c P ORIGINAL ISSUE eei Moers emule iere ORIGINAL ISSUE Ld Jr TREO ORIGINAL ISSUE DAC MEHR RE CONDERE ORIGINAL ISSUE ORIGINAL ISSUE 12 22 2006 POH AFM 003900 iii This POH AFM effective with S N 31 0001 THRU 31 TBA INTRODUCTION M20TN de a reU ORIGINAL ISSUE UP ue DEL ORIGINAL ISSUE ye REDE A LEE MEME EIE ORIGINAL ISSUE RA e Ca
34. READJUST for smooth operation Magneto Starter Switch Select R or L or BOTH If roughness disappears on single magneto monitor power and continue on selected magneto WARNING The engine may quit completely when one magneto is switched off if the other magneto is faulty If this happens close throttle to idle and mixture to idle cutoff before turning magnetos ON to prevent a severe backfire When magnetos have been turned back ON proceed to POWER LOSS IN FLIGHT Severe roughness may be sufficient to cause propeller separation Do not continue to operate a rough engine unless there is no other alternative Asse NC A EM 3 MA aN REDUCE eosque tu Rep scr check for a throttle setting that may cause roughness to decrease If severe engine roughness cannot be eliminated LAND AS SOON AS PRACTICABLE HIGH CYLINDER HEAD TEMPERATURE bur ENRICH As Required RISE EPUM BE INCREASE As Required REDUCE if temperature cannot be maintained within limits HIGH OIL TEMPERATURE NOTE Prolonged high oil temperature indications will usually be accompanied by a drop in oil pressure If oil pressure remains normal then a high temperature indi cation may be caused by a faulty instrument display or thermocouple Airspeed
35. ence ebat ct Aat ea t od 1 5 ENGINE EE 1 5 PROPELLER e aw RCRUM 1 6 FUEL 1 6 PERRA tC ense o Ea 1 6 LANDING GEAR trm the ia qat 1 7 MAXIMUM CERTIFICATED WEIGHTS 1 7 STANDARD AIRPLANE WEIGHTS 1 7 CABIN amp ENTRY DIMENSIONS 1 7 BAGGAGE SPACE 8 ENTRY DIMENSIONS 1 7 SPECIFIC LOADINGS act p Re ede nena CR ea a as 1 8 IDENTIFICATION PEATE retener ei denter og at Ta 1 8 GARMIN G1000 eate eee hei ad ada Na exe euge 1 8 SYMBOLS ABBREVIATIONS amp TERMINOLOGY 1 9 GENERAL AIRSPEED TERMINOLOGY 4 SYMBOLS 1 9 ENGINE POWER TERMINOLOGY 1 9 AIRPLANE PERFORMANCE amp FLIGHT PLANNING TERMINOLOGY 1 10 ENGINE CONTROLS amp INSTRUMENTS TERMINOLOGY 1 10 METEOROLOGICAL TERMINOLOGY 1 10 WEIGHT amp BALANCE TERMINOLOGY 1 11 MEASUREMENT CONVERSION TABLES 1 12 USE OF THE TERMS WARNING CAUTION AND NOTE 1 13 ORIGINAL ISSUE 12 22 2006 4 1
36. qe ing Verify FULL RICH LOW Boost Pump RR LE P OFF Wing Flaps cet Rr pee RO Re RUD TAKEOFF POSITION 109 T EE After POSITIVE climb established Be E RE RD NET NOSE DOWN to reduce forces osuere etude sets ques 85 KIAS Landing Gear iis Rep Rete e e RETRACT Wing Flaps Ri epe es bx pce appen p eo RETRACT DANS E eed uo x ser cele d eat 105 KIAS LANDING LANDING NORMAL Approach for Landing Check 5 COMPLETED Approach Airspeed As specified in SECTION V Landing Distance Touchdown MAIN WHEELS FIRST aligned w runway Landing Holl cesis bab eae ely E ede LOWER nose wheel gently 5 curent ete ova E wath eR MINIMUM required AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 4 16 Qe SECTION IV M20TN NORMAL PROCEDURES NOTE Landing information for reduced flap settings is not available See SECTION V for Landing Distance tables NOTE If maximum performance landings are desired use above procedures except re duce approach airspeed to 70 KIAS flaps full down and apply maximum braking without skidding tires during rollout NOTE Crosswind landings should be accomplished by using abo
37. 1 58 Qe SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION 5 GEAR GEAR RELAY C PANEL DEFROST STARTER LIGHT BLOWERBLOWER SOLENOID ENGINE CDU AV FLAP PFS AHRS INST FAN FAN ACT ICE STBY RUDDER STBY PROTECT BUS TURN SPEED TRIM MED GYRO SYS COORD BRAKE 5 5 N T NAV1 NAV2 HEAD HEAD GPS1 RADIO 2 GPS2 SETI SET2 RADAR TRAFFIC DATA ALTIM DME WX ALERT LINK FIGURE 7 9 CIRCUIT BREAKER PANEL TYPICAL CIRCUIT BREAKER PANEL See FIGURES 7 9 Illustration depicts typical C B panel may vary from your aircraft The circuit breaker panel is located on the right side of the instrument panel Each breaker is clearly marked to show which circuit it protects Also circuit provisions are made to handle the addition of optional communications and navigation equipment ORIGINAL ISSUE 12 22 2006 8 AIRPLANE FLIGHT MANUAL 7 29 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN Push pull or rocker switch circuit breakers automatically break the electrical current flow if the system or unit receives current overload to prevent damage to electrical wiring Figure 7 9 illus trates atypical main circuit breaker panel with its push pull circuit breakers Rocker switch cir cuit breakers are at the bottom and left of the pilot s flight panel The alternator s push pull circuit breaker on the main breaker pan
38. 7 16 CARGO RESTRAINT 22525544 ek LEE pe Neda e RETE 7 17 SEATS 4 eet utei ime ae pi e Mer ba 7 18 SEAT BELTS SAFETY HARNESS 7 18 DOORS WINDOWS 8 EXITS 7 18 CABIN DOOR err ert e cba etai ete 7 18 PILOTS WINDQW evoteesrexran achete drea eed ate 7 18 poe Ra e DU te erc pite optas tere 7 18 ENGINE rismi tg Re ps ge Peace pw egg eru etta 7 19 GENERAL elatio er cie a 7 19 ENGINE CONTROLS x tava n cepa e 7 19 ENGINE INSTRUMENTS 7 19 ENGINE OPERATION AND CARE 7 20 OIL SYSTEM te prepa misc aee dete e fue tete 7 20 LUBRICATION SYSTEM Creer err ERR ERE ROC ER res 7 21 BREATHER FOR CRANKCASE 7 21 IGNITION SYSTEM sy t mee dp Wer E dag c 7 21 AIR INDUCTION SYSTEM lett ter neigt aca 7 22 PROTECTION wale ete ae RD 7 23 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 7 1 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN EXHAUST
39. 9 X 0079 ONILVH Ald 9 NIYIN ME EE E 509 527681 26 1 AIGINASSV 2610 86 69 OOF 16 291 ES v AIGWASSV 133HM vv9 28 91 97 9 SASSY 2518 33VH8 8 133HM NIYIN Ed ydg GSTIVLSNI 587 65 NAN La 03 NLSYN 151 LN3lWdinio3 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 6 18 SECTION VI M20TN WEIGHT AND BALANCE INCHES cm REF DRAWING H o Lu Lu ITEM DESCRIPTION D WHEELS TIRES amp BRAKES CONT MRSTN EQ D2 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL uli 6 19 M20TN WEIGHT AND BALANCE SECTION VI 881 81 19 866028 aaadsulv HO1VOIGNI 217 RD em mw FS BIB eee 892028 15 8 YOLVOIGNI 00 Q3TIVISNI SSHONI 587 ONIMVYC di IM WALI LH3 O3 NISHIN 151 LNAWdINOA ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 6 20 SECTION VI WEIGHT AND BALANCE MOONEY M20TN ez 20 1 9 028 39unoS HIV OILVLS 31VNH3lITV SSVdINOO T3NVd HOLVIONRnNNV 1 SLN3WRHLSNI 3 41 Q3TIVISNI 587 65 NOILdIHOS3Q
40. AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 M20TN SECTION V PERFORMANCE TIME FUEL DISTANCE to DESCEND Maintain 1000 fpm Rate of Descent 08 09 06 08 04 151 02 001 08 151 09 OS OF 09 06 91 79 IWI sn z20L v 0 05 0 6 14 0005 13 00061 VSI 0 AONVLSIC 5 1 9 sh aasn 1304 TIV 1H9I3M 4 14 8 49 SVIM 021 444 LIL 4V3d 4 00 409 32530 30 31V Wd 000 NIVLNIVIN OL aauinoaa sv 0022 SNOILIGNOD Q31VI2OSSV H3MOd 000 X 13 LIY 34155344 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 5 44 SECTION V PERFORMANCE LANDING GROUND ROLL 1514 9 M20TN 00 X 99 LH9I3M do LVO vL Oct 001 08 09 OF 02 0 Oc OF 59 AMY SLY ANIM 00 X 81 LH9I3M Do z L 002 9 0 9 0 92 82 06 26098 OF OZ 0 0 Ok Oc O OF 009 009 5 z 009 6 2 00L 5 o 5 gt 008 m 5 1 3 T 1510 006 2 OL 14 00 Gav 03345 031511 5 JHL LONM AN3A3 m SLO
41. FUEL 7 FLOORBOARD BETWEEN OXY OH OPTIONAL 4 S OFF FOR EMERG ve FLOORBOARD BETWEEN SEATS DOWN 150056 X 1015 Y FLOORBOARD FWD OF 150056 X 1036 Y CO PILOT SEAT AUXILIARY EXIT DO NOT OPEN IN FLIGHT TO OPEN PULL OFF COVER PULL CABLE EXTRACTING LOCK PI ACTUATE HANDLE TO CLOSE STORE HANDLE INSERT LOCK PIN INSTALL COVER CLOSE AND LATCH DOOR USING OUTSIDE HANDLE LOCK DOOR 150056 X 1045 Y AIRPLANE FLIGHT MANUAL FAA APPROVED 2 16 We ORIGINAL ISSUE 12 22 2006 M20TN 150056 X 2032 Y SECTION II LIMITATIONS UNDERSIDE OF FLOORBOARD ABOVE FUEL CHECK VALVE COMPASS CORRECTION CALIBRATE WITH 15 RADIO A COMPASS 150056 X 1016 Y CAUTION ABSENCE OF ELT LIGHT DURING FIRST 3 SECONDS OF TEST INDICATE 917033 11 POSSIBLE G SWITCH FAILURE ON RADIO PANEL 150056 X 1013 Y ADJACENT TO ELT SWITCH DO NOT OPEN WHEN APPLICABLE ELT ABOVE 132 KIAS 51019 UNIT IS INSTALLED 150056 X MUSIC IN L mm PUSH RELEASE 150056 3001 150056 1040 WARNING WARNING FAA APPROVED ORIGINAL ISSUE 12 22 2006 1031 Y WINDOW BETWEEN SEATS ON ON EMERGENCY GEAR RELEASE INSTRUMENT EXTENSION HANDLE PANE DO NOT EXCEED 10 LBS 4 5Kg IN THIS COMPARTMENT USE FOR STOWAGE OF LIGHT SOFT ARTICLES ONLY SEE AIRCRAFT LOADING SCHEDULE DATA FOR BAGGAGE COMPARTMENT ALL
42. HIV M HIV O M XSS WALSAS 10114 941 5 cH O3 N ISHMW 6 25 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 SECTION VI MOONEY WEIGHT AND BALANCE M20TN INCHES cm REF DRAWING H o Lu Lu ITEM DESCRIPTION H AVIONICS amp AUTOPILOTS CONT MRSTN EQ H3 AIRPLANE FLIGHT MANUAL 2 ORIGINAL ISSUE 12 22 2006 6 26 SECTION VI M20TN WEIGHT AND BALANCE cm INCHES NEGLIGIBLE REF DRAWING H o Lu Lu ITEM DESCRIPTION LOCATION WILL VARY MRSTN EQ H4 ORIGINAL ISSUE 12 22 2006 5 AIRPLANE FLIGHT MANUAL 6 27 M20TN WEIGHT AND BALANCE SECTION VI c z zee 20 20010 x 016 01 220010 5 61138 1NIVH1S3H 7 229 0181 9L 1 5 0181 S0 TUE mon 5 ux1dWvs 1403 x CIEL 60 160010 5 FIL 1709 7 229 w 220010 Q3MOLS SLNIOd 2 6701 92 6071 160010 16 HVE MOL ld 211 iv 1 Q311VLSNI 587 SNIAVHG NOILdIHOS3G 3I MYYN M
43. If filter Shows an accumulation of carbon soot or oil continue with cleaning steps 5 through 8 5 Soak filter in non sudsing detergent for 15 minutes then agitate filter back and forth for two to five minutes to free filter element of deposits NOTE A Donaldson D 1400 Filter Cleaner is also recommended Do not use solvents 6 Rinse filter element with a stream of clear water until rinse water is clear 7 Dry filter thoroughly Do not use a light bulb or air heated above 180 F for filter drying 8 Inspectfor damage and ruptures by holding light bulb inside filter If damage is evident replace filter with a new one GEAR amp TIRES Theaircraftis equipped with 6 ply Type Ill standard brandtires and tubes Keep main gear tires inflated at 42 PSI and the nose tire at 49 PSI for maximum service life Proper inflation will mini mize tire wear and impact damage Visually inspect tires during pre flight for cracks ruptures and worn spots Avoid taxi speeds that require heavy braking or fast turns Keep the gear and exposed gear retraction system components free of mud and ice to prevent retraction interfer ence and binding It is recommended that retraction extension cycles 5 minimum be done any time any tire is replaced to assure that no interference exists during the cycle CAUTION After any landing other than a smooth touchdown and rollout when aircraft is above 3200 Lbs 1 452 Kg the aircraft should under
44. OFF M ster Switch ai er eR er Riu duet OFF Magneto Starter Switch OFF CAUTION Allow the engine to idle at 900 RPM for 5 minutes before shutdown in order to cool the turbochargers Taxi time can be counted as cooling time SECURING AIRCRAFT Magneto Starter Switch VERIFY OFF key removed Master READER E RP VERIFY OFF Electrical Switches VERIFY OFF Interior Light Switches VERIFY OFF Emergency Bus VERIFY OFF Parking Brake Sad eee eee eer RELEASE Install wheel chocks Extended Parking Ae werte ree Ra RE Control Wheel Secured Cabin Windows and Doors Closed and Locked TIE DOWN AIRCRAFT at wing and tail points Refer to GROUND HANDLING POH Section VIII for proper procedure ORIGINAL ISSUE 12 22 2006 s AIRPLANE FLIGHT MANUAL 4 17 SECTION IV MOONEY NORMAL PROCEDURES M20TN BLANK AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 4 18 4 SECTION V M20TN PERFORMANCE TABLE OF CONTENTS nucis xa dus tabs tn ean a a erede duet SECTION INTRODUCTION s
45. SECTION IV M20TN NORMAL PROCEDURES POHR4 001 1 Cockpit Gear Swilchi cs e p CRIT aaa DOWN Magneto Starter Switch OFF All ROCKER Switches eben Ee CC leet eb ee EO OFF Master od ead mi ON All Circuit Breakers e p RE y Ic ied a wis OR CRI IN Battery Select Switch SELECT from 1 to 2 or 2 to 1 TB CHECK Voltmeter after each selection Leave on Battery with highest voltage Internal External Lights CHECK operation va DE a eer er APER acd Check for ammeter fluctuations as each light is checked Prot Heat SWIECIT qe eui sd tes prd cta Aad Gate ON UE eel Do Edo Check Pitot Heat annunciator light illuminated BLUE Fuel Quantity Gauges CHECK QTY Master Switch e e ek ce IUE OFF PilotWildOWedo tor Le LEE US Dd OPEN Fuel Selector It is recommended that wing tank sumps be drained prior to draining gascolator tye IA Rt Tank Pull Gascolator ring 5 seconds D cp Lt Tank Pull Gascolator ring 5 se
46. SECTION V MOONEY PERFORMANCE M20TN SPEED and POWER SETTINGS vs ALTITUDE BEST POWER 18000 Ft Pressure Altitude AISA 30 51 C 0 20 C 30 10 C OAT 54 59 F 0 5 F 54 49 F IL KTAS GPH KTAS GPH KTAS 16000 Ft Pressure Altitude AISA 30 47 C 0 16 C 30 14 C OAT 54 52 F 0 2 F 54 56 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Some low power settings may not be attainable due to low cylinder or oil temperatures depending on ambient conditions AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 28 SECTION V M20TN PERFORMANCE SPEED and POWER SETTINGS vs ALTITUDE BEST POWER 14000 Ft Pressure Altitude AISA 30 43 C 0 12 C 30 18 C OAT 54 45 F 0 9 F 54 63 F RPM MAP KTAS GPH KTAS GPH KTAS GPH 12000 Ft Pressure Altitude AISA 30 39 C 0 8 C 30 22 C OAT 54 38 F 0 16 F 54 70 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Some low power settings may not be attainable due to low cylinder or oil temperatures depending on ambient conditions ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL wd 5 29 SECTION V MOONEY PERFORMANCE M20TN SPEED and POWER SETTINGS vs ALTITUDE BEST POWER 10000 Ft Pressure Altitude AISA 30 359 0 4
47. When ordering replacement Decals and Placards refer to the Mooney Airplane Company M20TN IPC or call Mooney Service Parts Dept ON INBOARD END OF FLAP NO STEP WING LEADING EDGES AND WING AHEAD OF FLAPS 150056 2006 UNDERSIDE OF WINGS 2 PLCS amp AFT OF L H COWL FLAP 1 PLC HORIZ STAB L E DER T E BOTH SIDES DO NOT PUSH 150056 X 2019 Y UNDER LEFT WING L E NEAR FUSELAGE PITOT DRAIN 150056 2011 GASCOLATOR DRAIN 150056 X 2010 Y TIRE PRESSURE 42 PSI 2 95 Kg cm TIRE PRESSURE 49 PSI 3 44 Kg cm 150056 X 2004 Y ON NOSE LANDING GEAR LEG ASSEMBLY TOWING LIMITS 150056 X 2022 Y WARNING DO NOT EXCEED TOWING LIMITS 1 150056 X 2003 Y ON NOSE LANDING GEAR SPINDLE ASSEMBLY FAA APPROVED ORIGINAL ISSUE 12 22 2006 VA HOIST POINT 150056 X 2012 Y UNDER TAILCONE AFT OF WING T E STATIC DRAIN 150056 X 2014 Y UNDER WING NEAR SUMP DRAINS FUEL DRAIN 150056 X 2013 Y UNDER FUSELAGE RT SIDE AFT OF NOSE WHEEL WELL ON MAIN LANDING GEAR DOOR 150056 X 2005 Y ON NOSE LANDING GEAR DOOR ON BOTH FUEL FILLER CAPS FUEL 100 GREEN OR 100LL BLUE MIN OCT 51 0 U S GAL USABLE 193 0 LITERS USABLE 150056 X 4001 X AIRPLANE FLIGHT MANUAL 2 19 SECTION II MOONEY LIMITATIONS M20TN BOTTOM LEFT WING 150056 2025 TOP LEFT RIGHT WINGS AT FUEL FILLERS 150056 2007 AIRPLANE FLIGHT M
48. CONDITION RECOMMENDED SPEED ENGINE FAILURE AFTER TAKEOFF Wing Flaps UP 85 KIAS Wing Flaps DOWN 80 KIAS BEST GLIDE SPEED 3368 1528 kg 91 5 KIAS 3200 1452 kg 89 0 KIAS 2900 Ib 1315 kg 84 5 KIAS 2600 Ib 1179 kg 80 0 KIAS MANEUVERING SPEED 3368 1528 kg 127 KIAS 3300 Ib 1497 kg 126 KIAS 2430 Ib 1102 kg 108 KIAS 2232 1012 kg 103 KIAS PRECAUTIONARY LANDING WITH ENGINE POWER Flaps DOWN 75 KIAS PRECAUTIONARY LANDING ABOVE 3200 LBS Flaps DOWN 80 KIAS EMERGENCY DESCENT GEAR UP Smooth Air 194 KIAS Turbulent Air 3368 10 1528 kg 127 KIAS 3300 Ib 1497 kg 126 5 2430 Ib 1102 kg 108 KIAS 2232 10 1012 kg 103 KIAS EMERGENCY DESCENT GEAR DOWN Smooth Air 165 KIAS Turbulent Air 3368 10 1528 kg 127 KIAS 3300 Ib 1497 kg 126 KIAS 2430 Ib 1102 kg 108 KIAS 2232 10 1012 kg 103 KIAS AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 3 4 a SECTION III M20TN EMERGENCY PROCEDURES ANNUNCIATOR PANEL WARNING LIGHTS WARNING LIGHT FAULT amp REMEDY GEAR UNSAFE RED light indicates landing gear is not in fully extended or retracted position Refer to FAILURE OF LANDING GEAR TO EX TEND ELECTRICALLY procedure or FAIL URE OF LANDING GEAR TO RETRACT procedure LEFT or RIGHT FUEL RED light indicates 6 to 8 gals 23 to 30 3 liters of usable fuel remain in the respective tanks Switch to fuller tank SPEED BRAKE AMBER light indicates Speed Brakes are activated ALT AI
49. LOUIS SCHREINER FIELD KERRVILLE TEXAS 78028 SERIAL NUMBER REGISTRATON NUMBER FAA APPROVED A Michele M Owsley Manager Airplane Certification Office FEDERAL AVIATION ADMINISTRATION 2601 Meacham Boulevard Fort Worth Texas 76137 0150 DATE December 22 2006 FAA APPROVED in Normal Category based on CAR PART 3 applicable portions of FAR PART 23 and when applicable components are installed in accordance with Mooney Drawing 110080 applicable to Model M20TN S N listed above only This handbook meets GAMA Specification No 1 SPECIFICATION FOR PILOT S OPERATING HAND BOOK issued February 15 1975 revised October 18 1996 Revision No 2 Copyright 2006 All Rights Reserved Mooney Airplane Company Louis Schreiner Field Kerrville Texas 78028 ORIGINAL ISSUE 12 22 2006 POH AFM NUMBER POH 003900 M20TN BLANK INTRODUCTION M20TN CONGRATULATIONS WELCOME TO MOONEY S NEWEST DIMENSION IN SPEED QUALITY AND ECONOMY YOUR DECISION TO SELECT AMOONEY AIRCRAFT HAS PLACED YOU IN AN ELITE AND DISTINCTIVE CLASS OF AIRCRAFT OWNERS WE HOPE YOU FIND YOUR MOONEY A UNIQUE FLYING EXPERIENCE WHETHER FOR BUSINESS OR PLEASURE THE MOST PROFITABLE EVER NOTICE This manual is provided as an operating guide for the Mooney Model M20TN It is important that you regardless of your previous experience carefully read the handbook from cover to cover and review it frequently THIS AFM MUST BE CARRIE
50. The importance of keeping the induction air filter clean cannot be over emphasized A clean filter promotes fuel economy and longer engine life Challenger Aviation Products Re charging instructions must be followed carefully for maximum air filter life Air filter must be recharged every 100 hours or 12 months or sooner if operated in extreme dusty conditions Air AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 8 6 A MOONEY SECTION VIII M20TN HANDLING SERVICE AND MAINTENANCE filter assembly must be replaced after 25 cleanings or sooner if any deterioration or damage is found during pre flight post flight or any other aircraft inspections NOTE Air filter exposed to in flight rain encounter must be inspected before next flight If red oil color is missing clean and re oil per these instructions To clean the Challenger Aviation Products filter 1 Remove engine cowling 2 Remove the air filter assembly from the aircraft air box DO NOT REMOVE filter element from inside its frame Remove the old sealing gasket from filter assembly with frame 3 Begin re charging air filter by gently tapping the filter assembly on a hard surface to remove any loose dust that will easily fall off the filter Visually inspect the filter for any damage cracks broken wires or missing fibers If any of those conditions are visible the filter assem bly must be scrapped and replaced with a new filter assembly 4 Begin cleaning with C
51. lesus TOUCHDOWN AT NORMAL LANDING SPEEDS Stopping eie e iere AS REQUIRED TO STOP AIRCRAFT ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL uli 3 9 SECTION III MOONEY EMERGENCY PROCEDURES M20TN EMERGENCY LANDING WITH THROTTLE STUCK AT IDLE POWER GLIDE Airspeed BEST GLIDE SPEED See MAXIMUM GLIDE DISTANCE Chart 3968 Ib 1528 2255 hi ae DER I cep RN RETE E 91 5 KIAS 32001 1452 i 5 e itl ead e bbb dade e ep 89 0 KIAS 2900 Ib 1915 KQ Cs 2 Re he Dos cx 84 5 KIAS 2600 Ib H179 kg cue REFERRE Sek ee RR 80 0 KIAS Propeller gad Eo ta ME Dura I E PULL FULL AFT Wing custodes OI ERR no Oo Met ellen etis SET TO 85 KIAS Wing Elaps senectus pine Ore see cree e EE Ra A UP atop MAKE DISTRESS TRANSMISSION Seat Belts Shoulder Harnesses FASTENED AND SECURE Loose Objects nene cat eo ete SECURE EOW Boost PUMP etre tae eei dae OFF LANDING Wing Flaps AS REQUIRED Full Flaps Recommended Engine Shutdown DELAY AS LONG AS PRACTICABLE Landing Flare INITIATE AT APPROPRIATE POINT TO ARREST DESCENT RATE AND sends de veu tetur
52. C OAT 54 5 F 0 59 F 54 113 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Some low power settings may not be attainable due to low cylinder or oil temperatures depending on ambient conditions AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 32 MOONEY SECTION V M20TN PERFORMANCE SPEED and POWER SETTINGS vs ALTITUDE BEST ECONOMY Conditions Example Mixture Pressure Altitude 12000 ft Best Economy 50 F Rich of Peak TIT Propeller Speed 2300 RPM Manifold Pressure 28 0 in HG Cruise Weight 3300 LB Outside Air Temp 8 C Altimeter Set to 29 92 True Airspeed 192 KTAS Configuration Clean Fuel Flow 17 3 GPH 22000 Ft Pressure Altitude AISA 30 59 C 0 28 C 30 2 C OAT 54 73 0 19 F 54 35 F RPM MAP KTAS GPH KTAS GPH KTAS GPH 20000 Ft Pressure Altitude AISA 30 559 0 24 C 30 6 C OAT 54 66 F 0 12 54 42 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Some low power settings may not be attainable due to low cylinder or oil temperatures depending on ambient conditions ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL wd 5 33 SECTION V MOONEY PERFORMANCE M20TN SPEED and POWER SETTINGS vs ALTITUDE BEST ECONOMY 18000 Ft Pressure Altitude AISA 30 51 C 0 20 C 30 10 C OAT 54 59 0 5 F 54 49 F I
53. C 30 26 C OAT 54 31 F 0 23 F 54 77 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Ft Pressure Altitude AISA 30 31 C 0 0 C 30 30 C 54 24 F 0 30 F 54 84 RPM MAP KTAS GPH KTAS GPH KTAS GPH Some low power settings may not be attainable due to low cylinder or oil temperatures depending on ambient conditions AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 30 MOONEY SECTION V M20TN PERFORMANCE SPEED and POWER SETTINGS vs ALTITUDE BEST POWER Ft Pressure Altitude AISA 30 27 C 0 3 C 30 33 C OAT 54 16 F 0 38 F 54 92 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Ft Pressure Altitude AISA 30 23 C 0 7 C 30 37 C OAT 54 9 F 0 45 F 54 99 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Some low power settings may not be attainable due to low cylinder or oil temperatures depending on ambient conditions ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL wd 5 31 SECTION V MOONEY PERFORMANCE M20TN SPEED and POWER SETTINGS vs ALTITUDE BEST POWER Ft Pressure Altitude AISA 30 19 C 0 11 30 41 54 2 F 0 52 F 54 106 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Ft Pressure Altitude AISA 30 15 C 0 15 C 30 45
54. Handle after GEAR DOWN light ILLUMINATES may bind actuator electrical retraction MAY NOT be possible until binding is eliminated by ground maintenance Return lever to normal position and secure with latch Re set landing gear actuator circuit breaker WARNING Do not operate landing gear electrically with manual extension system engaged Do not fly aircraft until maintenance inspection is done on landing gear system AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 3 20 A SECTION III M20TN EMERGENCY PROCEDURES FAILURE OF LANDING GEAR TO RETRACT AIRSBEED ette dee etudes Below 106 KIAS rib se at REI Ib maU UP Position GEAR FAILS TO RETRACT GEAR WARNING VOICE ALERT SOUNDING GEAR ANNUNCIATOR LIGHT amp GEAR SAFETY BY PASS LIGHT ILLUMINATED GEAR SAFETY BY PASS SWITCH DEPRESS HOLD until landing gear is fully retracted GEAR UNSAFE and GEAR DOWN Lights EXTINGUISHED GEAR RELAY uos es en te eine Pee DUI PULL E Gear Warning VOICE ALERT and Gear By Pass light will go OFF Check Air speed Safety Switch or other malfunction as soon as practicable GEAR RELAY oue UELLE PUSH IN WHEN READY TO EXTEND LANDING GEAR esee ciet o Det ta inae
55. ORIGINAL HEEL p po poor NENNEN NENNEN ORIGINAL ISSUE 12 22 2006 003900 INTRODUCTION M20TN TABLE OF CONTENTS TITLE matr SECTION GENERAL tate qup dl e EE T ET n EIMITATIONS 275 eae 1 EMERGENCY PROCEDURES NORMAL PROCEDURES IV miran ee dec a SU RU e c UR Roc de V WEIGHT amp BALANCE e eese epe ea VI AIRPLANE amp SYSTEM DESCRIPTIONS VII HANDLING SERVICE amp MAINTENANCE VIII SUPPEEMENTAE BATA erat bt IX SAFELY amp OPERATIONAL TIPS Wena f X ORIGINAL ISSUE 12 22 2006 velie T INTRODUCTION MOONEY M20TN BLANK viii 4 ORIGINAL ISSUE 12 22 2006 SECTION I M20TN GENERAL TABLE OF CONTENTS t RM SECTION THREE VIEW esas tee ebbe nt HR Ree el nt t lade ate a 1 3 INTRODUCTION ette oet RR ad RR p dte t T Seah RR 1 4 DESCRIPTIVE DATA
56. after reaching a safe altitude by the following procedures Air spod oiea eaa ee pope ee IR OU 95 KIAS Pilot s Storm WirldOW a c acea AUR e OPEN RAW e MR ATO RIGHT SIDESLIP Right bank with left rudder DOO peur der PULL SHUT amp LATCH BAGGAGE DOOR If baggage door is not properly closed it may come unlatched in flight This may occur during or after take off The door may open to its full open position and then take an intermediate position depending upon speed of aircraft There will be considerable wind noise loose objects in the vicinity of the open door may exit the aircraft There is no way to shut and latch door from the inside Aircraft flight characteristics will not be affected fly aircraft in normal manner LAND AS SOON AS POSSIBLE and secure baggage door Baggage Door latching mechanism VERIFY MECHANISM PROPERLY ENGAGED He ieri i hag t inside latching mechanism then shut from outside aircraft ICING WARNING DO NOT OPERATE IN KNOWN ICING CONDITIONS The Model M20TN is NOT APPROVED for flight into known icing conditions and operation in that environment is prohibited However if those conditions are inadvertently encountered or flight into heavy snow is unavoidable the following procedures are recommended until further icing conditions can be avoided INADVERTENT ICING ENCOUNTER
57. edow wa ea PO ORIGINAL ISSUE AAE ER ORIGINAL ISSUE Ju ORIGINAL ISSUE END EE S IPS TEES E ORIGINAL ISSUE pO ye ORIGINAL ISSUE DO e ois bu pie aba tte el cive cbe ar ORIGINAL ISSUE Dien WD ORIGINAL ISSUE SRE REIT CRONE OR SES ORIGINAL ISSUE DUO usi lost ve a o ORIGINAL ISSUE haie base echa vc Rh ers ORIGINAL ISSUE 220 ue LED Ate CX T Cote t ORIGINAL ISSUE V TEE ORIGINAL ISSUE ORIGINAL ISSUE 2 11 e p AR ee ae one ER ORIGINAL ISSUE M pieta ahaa a qiiae he Ls ORIGINAL ISSUE o PE ORIGINAL ISSUE VAS I f eT E ORIGINAL ISSUE Db im ide acces t a a MT ORIGINAL ISSUE 25101455 eG fe tk o Reb e T ORIGINAL ISSUE Vh Ir dap ORIGINAL ISSUE 2518 tss dae uut e e ORIGINAL I
58. li 3 11 SECTION III MOONEY EMERGENCY PROCEDURES M20TN An interruption in fuel flow or manifold pressure to the engine will result in turbocharger run down At high altitude merely restoring fuel flow may not cause the engine to restart because without turbocharger boost the mixture will be excessively rich If the engine does not fire there will be insufficient mass flow through the exhaustto turn the turbine This condition may lead one to suspect a turbocharger failure Follow the procedures described in ENGINE POWER LOSS IN FLIGHT Above 400 Feel AGL Engine starting will be apparent by a surge of power As the turbocharger begins to operate manifold pressure will increase and mixture can be adjusted accordingly If manifold pressure does not increase then the turbocharger has failed If turbo charger failure is a result of a loose disconnected or burned through exhaust then a serious fire hazard exists TURBOCHARGER OVERBOOST If the turbocharger wastegate control fails in the CLOSED position an engine power overboost condition may occur The following procedure is recommended for an overboost condition Throttle REDUCE as required to keep manifold pressure within limits ENGINE ROUGHNESS Engine instruments CHECK Fuel Selector Lex RUD d gon OTHER TANK
59. smooth air and then only with caution Maneuvering Speed at Do not make full or Ibs Kg abrupt control move 2232 1012 104 103 ment above this 2430 1102 speed 3300 1497 3368 1528 128 127 Maximum Flap Ex 111 110 Do not exceed this tended Speed speed with flaps in full down position Maximum Landing 166 164 Maximum speed at Gear Extended which the aircraft Speed can be safely flown with the landing gear extended Max Speed for Gear 141 140 Max speed at which Extension the landing gear can be safely extended Max Speed for Gear 107 106 Maximum speed at Retraction which the landing gear can be safely retracted Maximum Pilot Win 133 132 Do not exceed this dow Open Speed speed with pilot win dow open Figure 2 1 AIRSPEED LIMITATIONS AIRPLANE FLIGHT MANUAL FAA APPROVED 2 4 We ORIGINAL ISSUE 12 22 2006 SECTION II M20TN LIMITATIONS AIRSPEED MARKINGS Airspeed indicator markings their color code and operational significance are shown in Figure 2 2 18 Low speed awareness White band 59 KIAS 110 KIAS __ Operating range with flaps fully extended _____ band 66 KIAS 173 KIAS Normal operating range Yellow band 174 KIAS 194 KIAS e Lower limit of 195 KIAS is Red band 194 KIAS and greater the maximum speed for all operations Figure 2 2 AIRSPEED INDICATOR MARKINGS The airspeed indicator is marked in IAS values
60. 0 0 C 30 30 C QAM LESA 24 F 0 30 F_ 54 84 RPM MAP KTAS GPH KTAS GPH KTAS GPH Some low power settings may not be attainable due to low cylinder or oil temperatures depending on ambient conditions AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 36 SECTION V M20TN PERFORMANCE SPEED and POWER SETTINGS vs ALTITUDE BEST ECONOMY Ft Pressure Altitude AISA 30 27 C 0 3 C 30 33 C OAT 54 16 F 0 38 F 54 92 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Ft Pressure Altitude AISA 30 23 C 0 7 C 30 37 C OAT 54 9 F 0 45 F 54 99 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Some low power settings may not be attainable due to low cylinder or oil temperatures depending on ambient conditions ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL wd 5 27 SECTION V MOONEY PERFORMANCE M20TN SPEED and POWER SETTINGS vs ALTITUDE BEST ECONOMY Ft Pressure Altitude AISA 30 19 C 0 1 30 41 C OAT 54 2 F 0 52 F 54 106 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Ft Pressure Altitude AISA 30 15 C 0 15 C 30 45 C OAT 54 5 F 0 59 F 54 113 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Some low power settings may not be
61. 02 87 0082 11014 5 14 9NIM 581 0082 1H9I3M SVIM 8S SVIA ZZ 87 0008 NV39 13 0001 SS33Hd SVIM 69 SVIA SZ 87 002 H3MOd d3adS 34V3H8 03345 dV L1H9I3M 3ovdauns ANG Q31VI2OSSV Do vC 1 0 ORIGINAL ISSUE 12 22 2006 SA AIRPLANE FLIGHT MANUAL 5 46 SECTION V M20TN PERFORMANCE LANDING GROUND ROLL ON GRASS PENDING DATA ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 7 SECTION V MOONEY PERFORMANCE M20TN LANDING OVER 50 15m OBSTACLE ON GRASS PENDING DATA AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 48 4 SECTION VI M20TN WEIGHT AND BALANCE TABLE OF CONTENTS TIGE M SECTION INTRODUCTION wei hee ette mh e aco e e eo ac et EDO RU A d 6 3 AIRPLANE WEIGHING PROCEDURE 6 4 WEIGHT 8 BALANCE CHART 6 5 OWNERS WEIGHT amp BALANCE RECORD 6 6 PILOTS LOADING GUIDE iiss empate etre Rs RR 6 7 PROBLEEM FORM Red 6 8 LOADING COMPUTATION GRAPH 6 9 CENTER OF GRAVITY MOMENT ENVELOPE 6 10 CENTER OF GRAVITY LIMITS
62. 1 SECTION I MOONEY GENERAL M20TN BLANK ORIGINAL ISSUE 12 22 2006 1 2 4 SECTION I M20TN GENERAL 26 8 812 8 cm 76 193 04 9 2 279 4 002 FIGURE 1 1 THREE VIEW ORIGINAL ISSUE 12 22 2006 4 1 3 SECTION I MOONEY GENERAL M20TN INTRODUCTION This Operators Manual conforms to GAMA Specification No 1 and includes both Manufacturer s material and FAA APPROVED material required to be furnished to the pilot by the applicable Federal Aviation Regulations Section IX contains supplemental data supplied by Mooney Air plane Company Inc Section contains information of general interest to the pilot It also contains definitions of the terminology used in this Operators Manual This Pilot s Operating Handbook is not designed as a substitute for adequate and competent flight instruction knowledge of current airworthiness directives applicable federal air regula tions or advisory circulars It is not intended to be a guide for basic flight instruction or a training manual and should not be used for operational purposes unless kept in an up to date status All limitations procedures safety practices servicing and maintenance requirements published this POH AFM are considered mandatory for the Continued Airworthiness of this airplane in a condition equal to that of its original manufacture
63. 1000 THOUSANDS OF INCH POUNDS 1000 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 6 9 SECTION VI MOONEY WEIGHT AND BALANCE M20TN CENTER OF GRAVITY MOMENT ENVELOPE 900 1100 1300 1500 1700 1900 WEIGHT 800 1000 1200 1400 1600 1800 2000 Kg LBS ig Lgs LOAD AIRCRAFT MOMENT 1000 Kg MM 1528 3368 1500 3300 1452 3200 1400 3100 3000 2900 1300 2800 2700 1200 2600 AREA ARE ABOVE NORMAL APPROVED LANDING WEIGHT FUEL MUST BE BURNED OFF PRIOR TO NORMAL LANDING o gt LL cc lt 2 LOADED WITHIN THIS RANGE 2500 1100 2400 2300 1000 2200 2100 907 2000 70 90 110 130 150 170 190 LOAD AIRCRAFT MOMENT 1000 POUND INCHES AIRPLANE FLIGHT MANUAL 2 ORIGINAL ISSUE 12 22 2006 6 10 SECTION VI M20TN WEIGHT AND BALANCE M20TN CENTER OF GRAVITY LIMITS ENVELOPE 5 5 WEIGHT 1050 1100 1150 1200 1250 1300 Kg Lbs AIRCRAFT CG LOCATION OF DATUM STA 0 0 1528 3368 1500 3300 1452 3200 3100 1400 3000 2700 1200 2600 2500 1100 2
64. 1750 degrees Fahrenheit A red Warning bar indicates 1750 degrees Fahrenheit The TIT gauge is used as the primary source to lean fuel mixture PROPELLER HARTZELL THREE BLADE PHC J3YF 1RF F7693DF 2 The propeller is a three blade 76 inch 193 cm diameter constant speed unit that features aluminum blades in an aluminum hub The spinner is fabricated from aluminum alloy Centrifugal twisting moment acting on the blades moves the blades to a low blade angle low pitch to increase RPM Since the centrifugal twisting momentis only present when the propeller is rotating a mechanical spring is installed within the propeller to assist movement of the blades to a lower pitch position as RPM decays and to reduce the propeller pitch to the low pitch stop when the propeller is static With the blades at low pitch the load onthe starter when starting the engine is reduced significantly Oil pressure opposes the spring and centrifugal twisting moment to move the blades to a high blade angle high pitch reducing engine RPM If oil pressure is lost at any time the propeller will move to low pitch This occurs because the spring and blade centrifugal twisting moment are no longer opposed by hydraulic oil pressure The propeller will then reduce blade pitch to the low pitch stop In cruise always use the power setting charts provided in SECTION V AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 24 4 SECTION VII AIRPLANE AND SYSTEM D
65. 2 Kg capacity scale under each of the three wheels 7 Level aircraft as previously described making certain nose wheel is centered 8 Weigh the aircraft and deduct any tare from each reading 9 Find reference point by dropping a plumb bob from center of nose gear trunnion retracting pivot axis to the floor Mark the point of intersection 10 Locate centerline of nose wheel axle and main wheel axles in the same manner 11 Measure the horizontal distance from the reference pointto main wheel axle center line Mea sure horizontal distance from centerline of nose wheel axle to center line of main wheel axles 12 Record weights and measurements and compute basic weight and CG as follows on next page NOTE Wing Jack Points are located at Fus Sta 56 658 in 143 91 cm Nose Jack Point is located at Fus Sta 5 51 in 14 0 cm Refer to SECTION VIII Jacking for procedures AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 8 4 SECTION VI M20TN WEIGHT AND BALANCE M20TN WEIGHT amp BALANCE CHART REF POINT REFERENCE LEVEL REF NOSE GEAR DATUM STA 0 LEVELING SCREWS TRUNNION STA 13 MEASUREMENTS INCHES CM INCHES CM SCALE POSITION AND SYMBOL SCALE READING TARE NET WEIGHT NOSE WHEEL RIGHT MAIN WHEEL LEFT MAIN WHEEL WL BASIC EMPTY WEIGHT WT of fuel has been drained AS WEIGHED W of fuel has not been drained a CG Forward of Main Wheels
66. 2 seconds will select the emergency frequency of 121 500 MHz and will show it in the Active frequency win dow The Attitude Heading and Reference System AHRS requires atleast one GPS or air data input to function properly In the unlikely event that both GPS position sources fail and the air data computer fails the AHRS will subsequently lose attitude and heading and the pilot will be re quired to use the standby instrumentation In this instance the PFD will not provide altitude airspeed attitude or navigation information AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 3 6 A SECTION III M20TN EMERGENCY PROCEDURES ENGINE ENGINE POWER LOSS DURING TAKE OFF ROLL Throttle puede adim du ara ien tie adeo de eee SET TO IDLE iod oce ee S ot AS REQUIRED TO STOP AIRCRAFT atti ch noted e E n ne SET TO IDLE CUTOFF Fuel is waste ta Ere xe C e eed ad OFF Magneto SWITCH rete nor eats RE DRE Dc d OFF ENGINE POWER LOSS IMMEDIATELY AFTER LIFTOFF Below 400 Feet AGL EE 85 KIAS Flaps UP M Odd cay dee ete lei 80 KIAS Flaps DOWN KEEP THE AIRCRAFT UNDER CONTROL THEN MIXIUFG OUR aS PR SET TO IDLE CUTOFF FUG Selector eti
67. 3 22 EMERGENCY EXIT OF AIRCRAFT 3 24 SPINS recie met met fes s ne eden aa tee ge rete t ek 3 24 OTHER 5 222 lt 5 ER DRUG 3 24 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 DQ SECTION III M20TN EMERGENCY PROCEDURES INTRODUCTION This section provides the recommended procedures to follow during adverse flight conditions The information is presented to enable you to form in advance a definite plan of action for coping with the most probable emergency situations which could occur in the operation of your airplane As it is not possible to have a procedure for all types of emergencies that may occur it is the pilot s responsibility to use sound judgement based on experience and knowledge of the aircraft to determine the best course of action Therefore it is considered mandatory that the pilot read the entire manual especially this section before flight When applicable emergency procedures associated with optional equipment such as Autopi lots are included in SECTION IX NOTE airspeeds in this section are indicated IAS and assume zero instrument error unless stated otherwise ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 3 3 SECTION III MOONEY EMERGENCY PROCEDURES M20TN AIRSPEEDS FOR EMERGENCY OPERATIONS
68. Company Inc Louis Schreiner Field Kerrville TX 78028 ORIGINAL ISSUE 12 22 2006 INTRODUCTION MOONEY M20TN BLANK INTRODUCTION M20TN LIST OF EFFECTIVE PAGES ORIGINAL ISSUE emere egre heme eget d ree 12 22 2006 Always destroy superseded pages when inserting revised pages HIME PAGE the e c ev ORIGINAL ISSUE CONGRATULATIONS ORIGINAL ISSUE Cera M E E DECR SISTERE UO LAT CIS EE ORIGINAL ISSUE TEN CST ep ORIGINAL ISSUE cc ORIGINAL ISSUE AMI wale Ss Se ee ead nad Satta ans ORIGINAL ISSUE ADORA eI ARE ORIGINAL ISSUE Ted Sai ie a karen ace Say ee aes ORIGINAL ISSUE ji CO ORIGINAL ISSUE E EE wa eda wens ORIGINAL ISSUE LS DERE EEUU er DRE ODER DERE OPE ORIGINAL ISSUE IN TTA XEM TRUE ORIGINAL ISSUE MEE ENNIUS ORIGINAL ISSUE x ORIGINAL ISSUE itj ORIGINAL ISSUE gi ORIGINAL ISSUE 1 s ecu MUI TURTLE PT ORIGINAL ISSUE 12514 RES PEE MEO ES P OL HE AT ORIGINAL ISSUE
69. Counterweights balance the elevators PITCH TRIM SYSTEM Pitch trim is electrically actuated with a split toggle switch on the control wheel for autopilot equipped aircraft The pitch trim may be manually actuated by a wheel located on the floor be tween the pilot and co pilot seat Trim actuation turns a ball screw that increases or decreases the pitch angle of the entire empennage The elevator trim position indicator located on the MFD depicts the position up down of the pitch trim setting Trim position is shown by a blue triangle A white block indicates take off pitch trim position WING FLAPS The wing flaps are electrically operated and interconnected through a torque tube and bellcranks Total flap area is 17 98 square feet Nominal travel is 0 to 33 Limit switches prevent travel beyond these limits Wing flap position is controlled by a pre select switch located on the lower center console The flap position indicator located on the MFD shows the current position of the flaps The three possible positions up take off and down are depicted in cyan as UP T O and DN respectively During flaps posi tion transition is displayed in the window Generally aircraft trim requirements will change with use of the flaps Lowering ofthe flaps will cause a nose down pitching condition which can be easily corrected by application of nose up trim Conversely retraction of the flaps from a trimmed flight
70. FAA regulations it must be replaced after two years of shelf life The battery should also be replaced ifthe transmitter has been used in an emergency situation or if accumulated test time exceeds one hour The battery replace ment date is marked on the transmitter label On the unit itself is a three position selector switch placarded ARM OFF The ARM position is provided to set the unit to the automatic position so that it will transmit only after impact and will continue to transmit until battery is drained to depletion or until the switch is manually moved to OFF ARM position is selected when the transmitter is installed at the factory and switch should remain in that position whenever unit is installed in the airplane The ON position is provided so unit can be used as a portable transmitter or in the event the automatic feature was not triggered by impact or to periodically test the function of the transmitter Select the OFF position when changing battery when rearming the unit if it has been activated for any reason or to discontinue transmission NOTE If the switch has been placed in the ON position for any reason the OFF position has to be selected before selecting ARM If ARM is selected directly from the ON position the unit will continue to transmit in the ARM position ORIGINAL ISSUE 12 22 2006 8 AIRPLANE FLIGHT MANUAL 7 37 SECTION VII MOONEY AIRPLA
71. Full Forward High RPM e e ELA UU b x a RR RR RUN Idle Cut OFF Brakes used oM ERE NU E RM NE EN duca Set Wing Flap Switch Re Rex CURAR or pe ae Rs Flaps Up cp Cabin Heat EROR RT RR Push OFF G nbucge bern As Desired Fugl Saleto r ioi ew INAAGHN AN NT PIN aT ER Fullest Tank Landing Gear Down Position Red Emergency Gear Extension Handle Down and Latched Internal Lights Passenger Briefing oos REG EE Completed Refer to SECTION IX Supplemental Data for other Optional Equipment Procedures and Checks WARNING IFR flight should not be initiated if the operation of the standby alternator and emergency bus is not in satisfactory condition prior to takeoff Obtain local airport information prior to engine start ENGINE START CAUTION When either battery voltage is low inspection should be conducted to determine condition of battery and or reason for battery being low Replacement or servic ing of batteries is essential and charging for at least one hour should be done before engine is started Batteries must be serviceable and IT IS RECOMMENDED TH
72. ISSUE ENTIER ORIGINAL ISSUE cp MERECE EE RO ORIGINAL ISSUE P ORIGINAL ISSUE aa i xo iG MUNITA AS e AD ORIGINAL ISSUE PPM E MITT E MEMOIRS ORIGINAL ISSUE dgio caua ME et O er ORIGINAL ISSUE Ader ORIGINAL ISSUE VE CSDL WA E ORIGINAL ISSUE NACER CE ORIGINAL ISSUE Men oec CPP ORIGINAL ISSUE TM MMC EU MP pe HIM ORIGINAL ISSUE D ORIGINAL ISSUE He ex Ri iS DIA OLX ORIGINAL ISSUE TE NIE OE nC HEEL ORIGINAL ISSUE ru MEE EE MN a ORIGINAL ISSUE I MM c ORIGINAL ISSUE TURNER Cp ORIGINAL ISSUE EM MERE REMO ORIGINAL ISSUE ORIGINAL ISSUE She CI D D S EAS E ICA UE EO A col ORIGINAL ISSUE PROCURE RECONNUE ORIGINAL ISSUE TC MEM REM Cnr NM RR ORIGINAL ISSUE cote ct es be E UE ORIGINAL ISSUE 20 ee d M Ri a ony o He ORIGINAL ISSUE ORIGINAL ISSUE c etc qr TE aide oes hah ORIGINAL ISSUE PECORE ND O totes dah ORIGINAL ISSUE o Con Meno oM ORIGINAL ISSUE com ORIGINAL ISSUE ORIGINAL ISSUE GE mee Tp ROMERO
73. If smoke in the cockpit continues press the EMERG BUS switch and Pull BATT C B to shed the non essential equipment NOTE If the autopilot is engaged the EMERG BUS is activated and the BATT C B is pulled it will disengage without annunciation If smoke in the cockpit continues then Alternator Field Switcli ccs esee beber ex epe RAG aaa ee es OFF eee PIER A The standby instrumentation will remain powered with the EMERG BUS switch ON AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 3 14 ae SECTION III M20TN EMERGENCY PROCEDURES If power must be re established to navigation equipment to continue flight If the faulty compo nent can be determined pull the associated circuit breaker if not tripped already Do not close the open breaker to re establish power to the failed circuit If the faulty component cannot be determined pull all essential circuit breakers switch the Mas ter switch ON and Alternator switch ON then close circuit breakers one at a time Permit a short time to elapse before closing the next circuit breaker EMERGENCY DESCENT PROCEDURE In the event an emergency descent from high altitude is required rates of descent of at least 3 000 feet per minute can be obtained in two different configurations 1 With landing gear and flaps retracted an airspeed of 196 KIAS will be required fo
74. LBS Kg x In cm mm LBS Kg In cm mm Distance Between Weight 2 Nose Main amp Nose Wheel Axle Centers Wn Wr Lu Total Weight of CG Forward of Aircraft Main Wheels b CG Aft of Datum Station 0 In cm mm 13 In 33 0 cm 330 mm In cm mm In cm mm Distance from Center Distance from Result of CG FUS STA Nose Gear Trunnion to Nose Gear Trun Computation Distance Aft of Center of Main Wheel nion to Datum Above a Datum Empty Axles Horizontal Weight CG CONSTANT Lu Leja WEIGHT LBS Kg C G In cm mm MOMENT Lb In Kg cm Kg mm 1000 AsWeighed Wry Usable Fuel 49 23 In 125 cm 1250 mm ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 Pd M20TN WEIGHT AND BALANCE SECTION VI 10 spunog 10 Aq seuouj un 10 Aq seuouj uni 11014 S3an19NI LM aauaAriaa SV LHDISM ALdW3 OISVa WIN IND WW W ININ IND 5 5 SSHONI WHY WHY WHY 1HOI3M _ ALdW3 ONINNNY 1H5I3M ON VV ON 1VIHAS 3NV IdHIV 4008 501 1 VLVd 39NVHO LHDISM 77 M07348 3ONV V8 LH9I3M S H3NMO ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 6 6 SECTION VI M20TN WEIGHT AND BALANCE PILOT S LOADING GUIDE LOADING CALCULATI
75. LOW CEILINGS If you are not instrument rated avoid VFR On Top and Special VFR Being caught above an undercast when an emergency descent is required or at destination is an extremely hazardous position for the VFR pilot Accepting a clearance out of certain airport control zones with no minimum ceiling and one mile visibility as permitted with Special VFR is not a recommended practice for VFR pilots Avoid areas of low ceilings and restricted visibility unless you are instrument proficient and have an instrument equipped airplane Then proceed with caution and have planned alternates VFR AT NIGHT When flying VFR at night in addition to the altitude appropriate for the direction of flight pilots should maintain a safe minimum altitude as dictated by terrain obstacles such as TV towers or communities in the area flown This is especially true in mountainous terrain where there is usu ally very little ground reference and absolute minimum clearance is 2 000 feet Don t depend on your being able to see obstacles in time to miss them Flight on dark nights over sparsely popu lated country can be almost the same as IFR and should be avoided by untrained pilots AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 10 8 MOONEY SECTION X M20TN SAFETY INFORMATION VERTIGO DISORIENTATION Disorientation can occur in a variety of ways During flight inner ear balancing mechanisms are subjected to varied forces not normally
76. ORIGINAL ISSUE 12 22 2006 SECTION I M20TN GENERAL DESCRIPTIVE DATA ENGINE Number of Engines 2 Erates pete Liebe e PER EC PER dads FE eda 1 Engine Manufacturer Teledyne Continental Motors TCM DTI TSIO 550 G 1 Recommended 2000 Hours sese yeh Reciprocating air cooled fuel injected turbocharged Number of Cylinders 6 Horizontally opposed Firing Order E be 1 6 3 2 5 4 Displacement Rp sate pente qx pue T 552 Cu In 9 05 Liters eee tdm 5 25 In 13 3 cm o 4 25 10 8 cm Compression Ratio 7 5 1 Fuel System sot arca E ORTU Fuel Injection Make ice Ree a Fuel Aviation Gasoline 100 octane 100LL Accessories M agnetoS RXGG P EUER EUER NO Bendix S6RSC 25P pressurized Ignition Harness dete DEP RE axe Shielded Braided Spark PIUJS AC 273 or equivalent 18 m m Oil COOLER saa hed
77. SYSTEM eme ette tr oboe se ede lee ede Gaede EO RR 7 23 FUEL INJECTION 7 23 ENGINE COQOLING AIR Ere ER 7 23 ENGINE STARTING 5 5 7 24 ACCESSORIES tee EPI Erde e EUER e nE 7 24 EXHAUST GAS TEMPERATURE PROBE 7 24 TURBINE INLET TEMPERATURE TIT 7 24 PROPELLER Eb EE oe bebe vb De a dedere eb ams 7 24 HARTZEEE THREE BLADE nett enn e m deu e Sede 7 24 FUEL SYSTEM ae Ree ciat aen a d 7 25 ELECTRICAL SYSTEM CU Reg uc 7 26 AETERNATOR amp BATTERY 2 Re bre ER Cn ERR trace 7 26 ESSENTIAL ree egeret qu eR ER a ad e aaa Ud 7 27 NON ESSENTIAL BUS 4420 LERRA 7 27 EQUIPMENT LOCATION 7 27 SCHEMATIC ett tt tee ql ac e 7 28 CIRCUIT BREAKER PANEL 7 29 ACCESSORIES iut eee etra utes 7 30 ANNUNCIATOR PANEL 7 30 LIGHTING SYSTEM 7 30 INSTRUMENT 4 PLACARD 7 30 LIGHT
78. Seats Folded Down 340 Lbs 154 2 Kg STANDARD AIRPLANE WEIGHTS Basic EMDI Weight See Page 1 11 Useful Load eomm ccm tae ene Varies with installed equipment See SECTION VI for specific airplane weight CABIN AND ENTRY DIMENSIONS Cabin Width Maximum 43 5 In 110 5 cm Cabin Length 126 In 315 cm Cabin Height Maximum 44 5 In 113 cm Entry Width Minimum 29 0 In 73 4 cm Entry Height Minimum 35 0 In 88 9 cm BAGGAGE SPACE AND ENTRY DIMENSIONS Compartment Width 24 In 60 9 cm Compartment Length 43 In 109 2 cm Compartment 35 In 88 9 cm Compartment Volume 22 6 cu ft ccn 0 63 cu m Cargo Area with rear seat folded down 38 6 cu ft 1 09 Entry Height Minimum 20 5 In 52 1 cm Entry Width
79. Section amp V ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 10 9 SECTION X MOONEY SAFETY INFORMATION M20TN STANDARD PROCEDURE FOR SPIN RECOVERY In the event of an inadvertent spin the following recovery procedure should be used Throttle er Eee ID INN RETARD to IDLE Allerons sous coser ied Uie ride eu icr ique NEUTRAL Rudder eR Apply FULL RUDDER opposite the direction of spin Control Wheel FORWARD of neutral in a brisk motion to break stall Saule terete Additional FORWARD elevator control may be required if rotation does not stop Flaps extended RETRACT as soon as possible Rudder teu oe rt ds NEUTRALIZE when spin stops Control Wheel Smoothly MOVE AFT to bring the nose up tee Su te m to a level flight attitude after spin has stopped VORTICES WAKE TURBULENCE Every airplane generates wakes of turbulence while in flight Part of this is from the propeller or jet engine and part from the wing tip vortices The larger and heavier the airplane the more pronounced wake turbulence will be Wing tip vortices from large heavy airplanes are very se vere at close range degenerating with time wind and space These are rolling in nature from each wingtip In test vortex velocities of 133 knots have been recorded Exhaust velocities from large airplanes at
80. accessories including the magnetos starter alter nator engine driven fuel and oil pumps oil cooler and propeller governor should be inspected for oil leaks and security Your Mooney Service Center will change engine oil in addition to performing all other service and inspection procedures needed when you bring your airplane in for its 50 hour 100 hour or annual inspections CAUTION Excessive oil sludge buildup indicates that the oil system needs servicing at less than 50 hour intervals When changing or adding oil the following grades of oil are recommended Oil Grades Recommended for Various Average Air Temperature Ranges Below 409 F 49 SAE 30 10W30 15W50 or 20W50 Above 409 F 490 SAE 50 15W50 or 20W50 Total Oil Capacity n ee ee a acs See ene ee ele 8 Qts 7 57 liters Oll Filter RE Rr eve RE Full Flow NOTE The first time the airplane is filled with oil additional oil is required for the filter oil cooler and propeller dome This oil is not drainable on subsequent oil changes Added oil is mixed with a few quarts of older oil in the system Refer to the latest edition of TCM Maintenance and Operators Manual for approved brands of oil Mooney Service Center s stock approved brands of lubricating oil and all consumable materials necessary to service your airplane INDUCTION AIR FILTER
81. attainable due to low cylinder or oil temperatures depending on ambient conditions AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 38 SECTION V M20TN PERFORMANCE RANGE BEST POWER PENDING DATA ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 9 SECTION V MOONEY PERFORMANCE M20TN RANGE BEST ECONOMY PENDING DATA AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 40 4 SECTION V M20TN PERFORMANCE ENDURANCE BEST POWER PENDING DATA ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 1 SECTION V MOONEY PERFORMANCE M20TN ENDURANCE BEST ECONOMY PENDING DATA AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 42 4 SECTION V PERFORMANCE MOONEY M20TN TIME FUEL DISTANCE to DESCEND Maintain 500 fpm Rate of Descent 6 00 052 002 1510 091 001 09 0 081 09 021 001 INN 2 26 62 121 WO 5001 12 16 SALNNIIW 0 82 00 0786 13 0009 13 00061 VSI 02 LTV LYVLS 1V9 sn 71313 tl 0 6 8 29 9 cC LH9I3M 4 13 8 Y9 SVIM 09 Q3adsuiv LIL 3001 42006 1N32S3Q 31V INdd 005 NIVLNIVIN 01 G3YINDAY SV 00 2 SNOILIQNOO Q31VI2OSSV H3MOd 000 X 13 LIV 334fnSS33d 5 43
82. e We e e cae ee RR et 5 45 OVER 50 OBSTACLE rema a eee ee 5 46 GRODNDBOLL GRASS LE E e bod bad 5 47 OVER 50 OBSTACLE ON GRASS j4324 bp ka eb a eiie OR Ee ER eode 5 48 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL gt 5 1 SECTION V MOONEY PERFORMANCE M20TN INTRODUCTION The purpose of this section is to present the owner or operator with information needed to facili tate planning of flights with reasonable accuracy The Performance Data and charts presented herein are calculated based on actual flight tests with the airplane and engine in good condition and the engine power control system properly adjusted The flight test data has been corrected to International Standard Atmosphere conditions and then expanded analytically to cover various airplane gross weights operating altitudes and out side air temperatures VARIABLES Itis not possible to make allowances inthe charts for varying levels of pilot technique proficiency or environmental conditions Mechanical or aerodynamic changes are not authorized because they can affect the performance or flight characteristics of the airplane The effect of such things as soft runways sloped runways winds aloft or airplane configuration changes must be evaluat ed by the pilot However the performance on the charts can be duplicated by following the stated
83. e creta BELOW 140 KIAS Gear Helay C B HOUR RESET Landing Gear a DOWN Gear Down aed ede eos ILLUMINATED NOTE If above procedures do not initiate retraction process check gear emergency manual extension lever on floor for proper position GEAR FAILS TO RETRACT GEAR WARNING VOICE ALERT DOES NOT SOUND GEAR ANNUNCIATOR LIGHTS amp GEAR BY PASS LIGHT NOT ILLUMINATED GEAR EMERGENCY EXTENSION LEVER on floor Verify LATCHED in proper position GEAR ACTUATOR G B nc RESET uta grece d bes t e eic a Gear should retract if C B was tripped ig Bislang CONTINUE if desired WHEN READY TO EXTEND LANDING GEAR AT NEXT LANDING AIRSPEED vgs eter opt eee Rh bat ei eias Below 140 KIAS GEAR SWITCH IR lade EAD RES DOWN Position If gear will not extend electrically at this time refer to FAILURE OF LANDING GEAR TO EX TEND ELECTRICALLY previous page OXYGEN In the event of oxygen loss above 12 500 ft return to 12 500 ft as soon as feasible Refer to SEC TION X for the physiological characteristics of high altitude flight ALTERNATE STATIC SOURCE The alternate static air source should be used whenever it is suspected that the normal static air sources are blocked Selecting the alternate static source c
84. enter the figures in the proper columns Step 6 Total the weight columns This total must be 3368 Pounds 1528 Kg or less Total the Moment 1000 column DO NOT FORGET TO SUBTRACT NEGATIVE NUMBERS Step 7 Refer to the Center of Gravity Moment Envelope page 6 10 Locate the loaded weight of your airplane on the left scale of the graph and trace a line horizontally to the right Locate the total moment 1000 value for your airplane on the bottom scale of the graph and trace a line vertically above this point until the horizontal line for weight is intersected If the point of intersection is within the shaded area your aircraft loading is acceptable If the point of intersec tion falls outside the shaded area you must rearrange the load before take off ORIGINAL ISSUE 12 22 2006 5 AIRPLANE FLIGHT MANUAL 6 7 SECTION VI MOONEY WEIGHT AND BALANCE M20TN PROBLEM FORM SAMPLE YOUR PROBLEM PROBLEM WEIGHT MOMENT WEIGHT MOMENT Kg Kg cm Ib in ee Ib in Lbs 1000 1000 Lbs 1000 1000 A C Basic Empty Wt W from page 6 5 includes Full Oil 1009 114 6 8 Qts 7 57 Li 1 875 Lbs Qt 80 Kg Li Sta 20 19 51 3 cm 2225 99 46 Oil sump assumed FULL for all flights 7 64 Pilot Seat 1 aft pos 6 63 7 25 Co Pilot Seat 2 2nd pos 6 29 14 3 Left Rear Seat 3 or Cargo Area 12 41 14 3 Right Rear Seat 4 or Cargo Area 12 41 Fuel Max Usable 164 7 20 59 102 0 G
85. of digits Reference An imaginary vertical plane from which all horizontal distances are mea Datum sured for balance purposes Station A location along the airplane fuselage usually given in terms of distance from the reference datum Tare The weight of chocks blocks stands etc used when weighing an air plane and is included in the scale readings Tare is deducted from the scale reading to obtain the actual net airplane weight Unusable Fuel remaining after a run out test has been completed in accordance Fuel with Federal regulations Usable Fuel available for aircraft engine combustion Fuel Useful The basic empty weight subtracted from the maximum weight of the air Load craft This load consists of the pilot crew if applicable useable fuel pas sengers and baggage ORIGINAL ISSUE 12 22 2006 d 1 11 SECTION I MOONEY GENERAL M20TN MEASUREMENT CONVERSION TABLES LENGTH U S Customary Metric Equivalents T 2 54 5 BICI EN 0 3048 meter TEE 0 9144 meter 1 mile statute land 1 609 meters 1 mile nautical international 1 852 meters AREA U S Customary Unit 2 riu Metric Equivalents 1 54 8
86. personal injury or death if not carefully followed CAUTION The use of the Caution symbol means information which follows is of significant importance and concerns procedures and techniques which could cause or re sult in damage to the airplane and or its equipment if not carefully followed NOTE The use of the term Note means the information that follows is essential to em phasize ORIGINAL ISSUE 12 22 2006 4 1 13 SECTION I MOONEY GENERAL M20TN BLANK RIGINAL I E 12 22 2 ORIG SSU 006 SECTION II M20TN LIMITATIONS TABLE OF CONTENTS RUE RM SECTION INTRODUCTION o uri tte ete He dil a t ide oe bbc RR e 2 3 NOISE LIMITS tte Ree te oet tee D Seah ve rs 2 3 AIRSPEED LIMITATIONS eben e eR e obra De 2 4 AIRSPEED MARKINGS te c De 2 5 POWER PLANT LIMITATIONS 2 6 POWER PLANT INSTRUMENT MARKINGS 2 7 FUEL LIMITATIONS ate con tte cet brat Me gcd be 2 8 WEIGHT LIMITS rh teer ad eee 2 8 CENTER OF GRAVITY LIMITS GEAR DOWN 2 8 MANEUVER LIMITS ce fe ate ta elena e ates 2 9 FLIGHT LOAD FACTOR LIMITS 2 9 FLIGHT CREW eser ih rie
87. procedures in a properly maintained MOONEY M20TN Examples are given to show how each chart is used The only charts with no example are those where such an example of use would be repetitive To obtain effect of altitude and OAT on aircraft performance 1 Set altimeter to 29 92 and read pressure altitude 2 Using the OAT grid for the applicable chart read the corresponding effect of OAT on perfor mance CAUTION Be sure to return to local altimeter setting in calculating aircraft elevation above sea level OPERATIONAL PROCEDURES FOR MAXIMUM FUEL EFFICIENCY Fuel efficiency best defined as nmi gal of fuel is dependent on the proper use of the mixture control There are two recommended cruise settings for the TSIO 550 G engine described in the following paragraphs At all times engine limitations need to be observed Best Power The Best Power setting will develop the maximum horsepower and speed for a particular manifold pressure and RPM setting Best Power mixture is desirable for minimizing flight time when fuel burn rate or range is not a primary concern When TIT limitations prevent attaining peak TIT then best power is obtained at 1650 F TIT Best Power Procedure Upon attaining level flight at cruise altitude set the manifold pressure and RPM as desired not exceeding 30 5 inHg Slowly move the mixture control toward lean while observing TIT indicator and maintaining TIT limits If manifold pressure changes while le
88. protects against inadvertent spins All airplanes are required to have flight characteristics that give adequate ad vance warning of an impending stall or they must be equipped with an artificial stall warning de vice Keepthe artificial system in good working order Do not operate the airplane with the device made inoperative by the use of circuit breakers or other means Stalls should be practiced at safe altitudes for ample recovery Should a spin be encountered inadvertently spin recovery should be initiated immediately As stall attitude is approached be alert Take prompt corrective action to avoid the stall or if you are practicing stalls react the moment the stall occurs The following is suggested 1 Do not carry passengers Be certain that the airplane s center of gravity is as far forward as possible Forward CG aids spin recovery 2 Be certain that both student pilot and instructor pilot have a full set of operable controls 3 Conduct such practice at altitudes in excess of 6 000 ft above ground level Remember that an airplane at or near traffic pattern altitude probably will not recover from a spin before impact with the ground When descending to traffic pattern altitude and during operation in the traffic pattern and approach maintain a safe margin above stall speed During takeoff or go around be especially careful to avoid departure stalls associated with turns at low speed Maintain speeds recommended in this handbook
89. sediment contamination or condensed water accumula tion The recessed three position handle aft of the console on the floor allows pilot to set selector valve to LEFT tank RIGHT tank or OFF position The gascolator located at right of selector valve in the floorboard is for draining condensed water and sediment from lowest point in fuel system before first flight of the day and after each refueling The gascolator sump can be used to drain the selected fuel tank Fuel is delivered by the engine driven pump to a throttle body fuel injector where pressure is regulated and the correct volume of fuel is metered to each cylinder ofthe engine Fuel not need ed by the engine is returned to the tank from which it is drawn The HIGH BOOST pump switch operates the fuel boost pump on high power The high boost setting is capable of operating the engine at reduced power in case of engine driven fuel pump failure or severe fuel filter blockage A guard onthe HIGH BOOST switch prevents inadvertent operation and must be lifted for switch operation High Boost may be used on the ground as an engine starting aid Continuous operation should be avoided except in an emergency Never run the boost pump without fuel in the system Refer to SECTIONS III and IV for proper use of the HIGH BOOST setting CAUTION Pushing HIGH BOOST pump switch ON when engine driven pump is operating prop erly will cause engine to quit due to excessive rich fuel mixtu
90. short occur combination switch circuit breaker will automatically trip to OFF position 19 TAXI LIGHT TAXI LITE SWITCHES L amp R 20 LANDING LIGHT LDG LITE SWITCHES L amp R Select and push split switches to turn desired set of lights ON Push switches OFF to turn desired setoflights off Lights should be operated only for shorttime periods while notinflightto preclude overheating of lamps Overload protection is achieved by circuit breakers in panel 21 GEAR SAFETY BY PASS SWITCH Gear Retraction Override Gear safety override switch is a manual means of electrically by passing the Air speed Safety Switch In the event the landing gear switch is placed in gear up position a properly operating ORIGINAL ISSUE 12 22 2006 5 AIRPLANE FLIGHT MANUAL 7 9 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN Airspeed Safety Switch prevents gear from being retracted before take off speed of approxi mately 60 5 KTS is reached To retract landing gear at a lower air speed the GR SAFETY BY PASS switch may be held de pressed until landing gear is completely retracted CAUTION Activation of landing gear safety override switch overrides the safety features of air speed safety switch and CAN cause landing gear to start retracting while aircraft is on ground 22 LANDING GEAR SWITCH Electric gear switch identified by its wheel shaped knob is a two position switch Pulling aft and lowering knob lowers landing gear while
91. takeoff have been measured at 25 MPH 2100 feet behind medium large air planes Encountering the rolling effect of wing tip vortices within two minutes or less after passage of large airplanes is hazardous to light airplanes This roll effect can exceed the maximum counter roll obtainable in an airplane The turbulent areas may remain for as long as three minutes or more depending on wind condi tions and may extend several miles behind the airplane Plan to fly slightly above or to the up wind side of the other airplane s flight path Because ofthe wide variety of conditions that can be encountered there is no set rule to follow to avoid wake turbulence in all situations However the Aeronautical Information Manual goes into considerable detail for a number of wake turbulence avoidance procedures Use prudent judg ment and allow ample clearance time and space following or crossing the wake turbulence of other airplanes in all takeoff climb out approach and landing operations Be observant of wake turbulence from all aircraft regardless of size The Aeronautical Information Manual contains a section on wake turbulence FAA Advisory Cir cular AC 90 23F is also recommended reading TAKE OFF AND LANDING CONDITIONS When taking off on runways covered with water or freezing slush the landing gear should remain extended for approximately ten seconds longer than normal allowing the wheels to spin and dissipate the freezing moisture The la
92. the currency ofthe database or verifies each selected way point for accuracy by reference to current approved data FAA APPROVED gt AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 2 11 SECTION II MOONEY LIMITATIONS M20TN 4 Instrument approach navigation predicated upon the G1000 GPS Receiver must be accom plished in accordance with approved instrument approach procedures that are retrieved fromthe GPS equipment database The GPS equipment database must incorporate the cur rent update cycle a Instrument approaches utilizing the GPS receiver must be conducted in the approach mode and Receiver Autonomous Integrity Monitoring RAIM must be available at the Final Ap proach Fix b Accomplishment of ILS LOC LOC BC LDA SDF MLS or any other type of approach not approved for GPS overlay with the G1000 GPS receiver is not authorized Use of the G1000 VOR ILS receiver to fly approaches not approved for GPS require VOR ILS navigation data to be valid on the PFD display d When an alternate airport is required by the applicable operating rules it must be served by an approach based on other than GPS navigation the aircraft must have the operational equipment capable of using that navigation aid and the required navigation aid must be op erational e VNAV information may be utilized for advisory information only Use of VNAV information for Instrument Approach Procedures does not guarantee step down fix altitude p
93. turning ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 9 SECTION IV MOONEY NORMAL PROCEDURES M20TN AFTER ENGINE START Throttle Gonttol opone aee ADJUST IDLE 900 to 1000 RPM Oil I C CHECK for 30 TO 100 PSI Alternator field ovens eo EUR edu NR exe ON Ammeter CHECK Verify annunciator alternator light is OFF and the system is charging Position and Anti collision Lights SET AS REQUIRED Radios and Required Avionics SET AS REQUIRED BEFORE TAXI Engine Start Checklist Completed Elevator Trim SWItCh 5 neta eMe RH os ON Internal External 1 As Desired PED MED cuneus OCURRE Check Normal Operation Comm Nav Radios Checked and Set Al meter hus Deae ie dU Meg tt axe e Set Fuel Selector Switch Tanks verify engine runs on other tank Cabin Heat osi eR EROR As Desired DONOSIO pecie a epe eumd As Desired Cabin Vent oven m LES bun As Desired Fl
94. um Goa den te RAE Apply FULL RUDDER opposite direction of spin Control Wheel FORWARD of neutral in a brisk motion ADDITIONAL FORWARD elevator control may be required if rotation does not stop HOLD ANTI SPIN CONTROLS UNTIL ROTATION STOPS Wing Flaps If extended RETRACT as soon as possible ael e NEUTRALIZE when spin stops Control Wheel ACCES 8 SMOOTHLY MOVE AFT TEE to bring the nose up to level flight attitude OTHER EMERGENCIES Refer to Section IX for Emergency Procedures of Optional Equipment AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 ey li SECTION IV M20TN NORMAL PROCEDURES TABLE OF CONTENTS CORPORE SECTION INTRODUCTION Mad tr 4 3 SPEEDS FOR NORMAL OPERATION 4 4 PRE FLIGHT INSPECTION 1 4 5 BEFORE STARTING CHECK 4 8 ENGINE START Roast Zl hes aud aan dub MI Red ol 4 8 NORMAL ENGINE START 4 9 HOT ENGINE START 2224 6534 0852 AAA 4 9 FLOODED ENGINE START 4 9 EXTREME COLD WEATHER ENGI
95. under 40 in height be restrained in an approved child restraint system appropriate to their height and weight The single diagonal type safety harness is designed so the chest strap crosses diagonally from the outboard shoulder to an attachment point as low on the inboard hip as possible Rear seat occupants should take care to conform with this procedure in adjusting chest strap and inboard belt length This diagonal configuration places body center of gravity inside the triangle formed by chest strap and lap belt The lap belt should be adjusted comfortably tight As a result the body is restricted from rolling out toward the unrestricted shoulder or open side of the harness upon forward impact Refer to Figure 7 4 for proper seat belt harness adjustment DOORS WINDOWS amp EXITS CABIN DOOR Access into cabin is provided by a door located on right side of fuselage This door has inside and outside operating handles The outside door handle can be locked with a key specifically pro vided for it The door hastwo latching mechanisms one located atthe top of door and one atthe aft center of door Should the door come openin flight flying qualities ofthe aircraft will not be affected Procedures for closing door in flight are contained in SECTION III PILOT S WINDOW pilot s storm window is located in the left main cabin window This window is generally used for fresh air for prolonged ground operations or as required during adv
96. wide and shallow as possible and be equally cautious in applying forward or back pressure to keep the nose level Maintain straight and level attitude in either up or down drafts Use trim sparingly to avoid being grossly mistrimmed as the vertical air columns change velocity and direction MOUNTAIN FLYING Avoid flight at low altitudes over mountainous terrain particularly near the lee slopes OBSERVE PUBLISHED MINIMUM ENROUTE ALTITUDES MEA Ifthe wind velocity near the level ofthe ridge is in excess of 25 knots and approximately perpen dicularto the ridge mountain wave conditions are likely over and near the lee slopes If the wind velocity at the level of the ridge exceeds 50 knots a strong mountain wave is probable with strong up and down drafts and severe or extreme turbulence The worst turbulence will be en countered in and below the rotor zone which is usually 8 to 10 miles down wind from the ridge This zone is characterized by the presence of roll clouds if sufficient moisture is present alto cumulus standing lenticular clouds are also visible signs that a mountain wave exists but their presence is likewise dependent on moisture Mountain wave turbulence can of course occur in dry air and the absence of such clouds should not be taken as any assurance that mountain wave turbulence will not be encountered A mountain wave down draft may exceed the climb capability of your airplane AVOID MOUNTAIN WAVE DOWN DRAFTS VFR
97. 0 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 6 3 SECTION VI MOONEY WEIGHT AND BALANCE M20TN AIRPLANE WEIGHING PROCEDURE LEVELING Place a spirit level on the leveling screws above the tailcone left access door when leveling the aircraft longitudinally Level the aircraft by increasing or decreasing air pressure in the nose wheel tire WEIGHING To weigh the aircraft select a level work area and 1 Check for installation of all equipment as listed in the Weight amp Balance Record Equipment List 2 Top off both wing tanks with full fuel Subtract usable fuel 102 0 U S gals 386 1 liters 5 82 Ib gal 100LL 69 593 6 Ibs 266 4 Kgs from total weight as weighed OPTIONAL METHOD Ground aircraft and defuel tanks as follows a Disconnect fuel line at fuel system union located forward of the firewall on the lower left hand side b Connect a flexible line to output fitting that will reach fuel receptacle c Turn fuel selector valve to tank to be drained remove filler cap from fuel filler port d Turn on fuel boost pump until tank is empty REPEAT STEPS C AND D TO DRAIN OTHER TANK e Replace 3 0 gallons 11 4 liters fuel into each tank unusable fuel Use 5 821b gal 69 Kg liter for 100LL fuel f Replace filler caps 3 Fill oil tank to capacity 8 qts 4 Position front seats in full forward position 5 Position flaps in full up position 6 Position a 2000 pound 907
98. 009H31NI ENGINE FIGURE 7 6 AIR INDUCTION SYSTEM SCHEMATIC A secondary or alternate air source for combustion air is provided It has a door which normally remains closed and is held by a magnetic catch If the air filter or induction air inlet is restricted beyond a minimum allowable inlet pressure the alternate air door will automatically open Warmer air will then be drawn from the engine compartment There will be a reduction of engine power when the alternate air door is open due to lower inlet air pressure and higher air tempera ture Whenever the alternate air door is open a switch will activate the ALT AIR annunciator light on the panel to alert the pilot AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 2222 Qe SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION ICING PROTECTION Continued operation of the induction system in the event of intake air being obstructed is pro vided by activation ofthe alternate air system The alternate air is automatically or manually con trolled When the door is opened unfiltered relatively warm air from engine compartment is admitted into the induction system EXHAUST SYSTEM Engine exhaust is collected by a system of headers The left side cylinder exhaust is routed through the left turbocharger The right side cylinder exhaust is routed through the right turbo charger Both the left and right side headers are connected to a single wastegate on the left side that e
99. 111 KIAS EMERGENCY MANUAL GEAR EXTENSION ON LEFT PULL LANDING GEAR ACTUATOR CIRCUIT BREAKER SIDE PUT GEAR SWITCH IN GEAR DOWN POSITION PANEL PUSH RELEASE TAB FORWARD AND LIFT UP RED HANDLE IN PULL T HANDLE STRAIGHT UP 12 TO 20 INCHES PILOT S ALLOW T HANDLE TO RETURN TO ORIGINAL POSITION VISION REPEAT UNTIL GEAR DOWN COMES ON 12 TO 20 PULLS IF TOTAL ELECTRICAL FAILURE SEE MECHANICAL INDICATOR CAUTION TURN OFF STROBE LITES WHEN TAXIING NEAR OTHER ACFT OR WHEN FLYING IN FOG OR IN CLOUDS STD POSITION LITES MUST BE USED FOR ALL NIGHT OPERATIONS IN CASE OF FIRE TURN OFF CABIN HEAT DO SCREW VERNIER CONTROLS CLOSER THAN 1 8 FROM NUT FACE 150056 X 1032 Y KNOWN ICING 150056 1032 NO ICING CHECK LIST CONTROLS RUN UP DOOR FUEL PROP WINDOW INSTRUMENTS WING FLAPS ALT AIR TRIM SEAT LATCH PARK BRAKE MIXTURE CONDUCT RUDDER AND ELEVATOR TRIM CHECK PRIOR ON TO FLIGHT SEE PILOT S OPERATING HANDBOOK CONSOLE BELT HARNESS GEAR MIXTURE FUEL WING FLAPS PROP PARK BRAKE 150056 X 1030 Y FLAP UP CONSOLE PILOT S L H ABOVE amp PANEL FWD BELOW SWITCH OF ARM REST FLAP DOWN 130336 5 OPTIONAL FAA APPROVED di AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 2 15 SECTION II MOONEY LIMITATIONS M20TN BAGGAGE DOOR WARNING FRAME FWD END OF DO NOT EXCEED 170 LBS BH SEA BOTTON AU 77 1 Kg ON THIS SEAT BACK STRUCTURE SEE AIRCRAFT LOADING SCHEDULE 150056 1043
100. 12 ADDITIONAL INFORMATION 10 12 MANUFACTURER S 10 12 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 10 1 SECTION X MOONEY SAFETY INFORMATION M20TN BLANK AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 10 2 e SECTION X M20TN SAFETY INFORMATION INTRODUCTION The best of engineering know how and manufacturing craftsmanship have gone into the design and building of your Mooney aircraft Like any high performance airplane it operates most effi ciently and safely in the hands of a skilled pilot We urge you to be thoroughly familiar with the contents of your operating manuals placards and check list to insure maximum utilization of your airplane When the airplane has changed owner ship some of these may have been misplaced If any are missing replacements should be ob tained from any Mooney Service Center as soon as possible For your added protection and safety we have added this special section to the Pilot s Operating Handbook to refresh your knowledge of a number of safety subjects You should review these subjects periodically Topics in this section are mostly excerpts from FAA Documents and other articles pertaining to the subject of safe flying They are not limited to any particular make or model airplane and not replace instructions for particular types of airplanes Your Mo
101. 12 Y SHELN f 5 A INTERMITTENT INSTRUMENT 150056 1056 ON INSTRUMENT INSTRUMENT LIGHTS PANEL 150056 1007 PUSHINCREASE ON INSTRUMENT GEAR NOT EXTENDED O GEAR UP 106 KIAS PUSH GEAR SAFETY BYP MIXTURE 150056 X 1010 Y PUSH RICH ON INSTRUMENT PANEL THROTTLE ON INSTRUMENT PUSH INCREASE PANEL ETA 222 LIGHTNING DETECTION EQUIPMENT NOT TO BE TE SENA USED FOR THUNDERSTORM on INSTRUMENT AREA PENETRATION PANEL ASS PULL FOR ALTERNATE 150056 X 1009 Y GEAR DOWN C UNDER PILOT S YOKE STATIC SOURCE ON CONTROL KNOB PANT 02 02 150056 X 3038 150085 038 OPTIONAL 150056 303 CWS A P DISC TRIM INTR ON INSTRUMENT ON CONTROL PANEL YOKE AIRPLANE FLIGHT MANUAL FAA APPROVED 2 14 We ORIGINAL ISSUE 12 22 2006 SECTION II M20TN LIMITATIONS OPERATING LIMITATIONS THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THE NORMAL CATEGORY THIS AIRPLANE IS CERTIFIED FOR DAY AND NIGHT VFR IFR OPERATION WHEN THE REQUIRED EQUIPMENT IS INSTALLED AND OPERATIONAL FLIGHT INTO KNOWN ICING CONDITIONS IS PROHIBITED NO AREOBATIC MANEUVERS INCLUDING SPINS ARE APPROVED OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THIS CATEGORY ARE CONTAINED IN THE AIRPLANE FLIGHT MANUAL MANEUVERING SPEED 3368 LBS 127 KIAS 2600 LBS
102. 136 140 141 145 146 150 152 155 157 160 162 165 167 170 172 175 177 180 182 185 187 190 192 197 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 6 A MOONEY SECTION V M20TN PERFORMANCE AIRSPEED CALIBRATION PRIMARY STATIC SYSTEM POWER OFF CLEAN CONFIGURATION Air Speed Calibration Primary Static System Power Off Clean Configuration GIVEN IAS 129 KNOTS FIND CAS 130 KNOTS a lt q a Lu Lu o m 120 lt tc m l lt O o x __ 00 110 120 130 140 150 160 170 190 200 KNOTS INDICATED AIRSPEED KIAS ERROR KIAS KCAS ERROR 130 131 135 136 140 141 145 146 150 151 155 156 160 162 165 167 170 172 175 177 180 182 185 187 190 192 197 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 5 7 SECTION V MOONEY PERFORMANCE M20TN AIRSPEED CALIBRATION PRIMARY STATIC SYSTEM POWER ON 10 FLAP GEAR DOWN Air Speed Calibration Primary Static System Power On 10 Flap Gear Down SPEED FOR SAFELY LOWERING FLAPS 0 lt q 2 E lt tc 8 l lt q H x 70 80 90 100 KNOTS INDI
103. 1NOHJ 115 15 7 156 21 11 11 11 1 07221 901 6 602 89 212086 5 14 NOISITIOO LLNV ER qp 1809 TWNOLLdO G3STIVLSNI sa NOILdIlHOS3q dau WALI e O3 NISHIN 151 LNAWdINOA ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 6 30 SECTION VI WEIGHT AND BALANCE MOONEY M20TN 012 ewn an osos 766 199 6161 0 02 000044 0 161 98 82 UM 86 272 621 6200 8 0161 620028 26101 pee 2 1 c 6v 0 lt 211 112012 GATIVLSNI 887 65 1M f O3 NISHIN 151 LN3lWdinio3 6 31 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 SECTION VI MOONEY WEIGHT AND BALANCE M20TN INCHES cm REF DRAWING H o Lu Lu ITEM DESCRIPTION J OPTIONAL EQUIPMENT CONT MRSTN EQ J4 AIRPLANE FLIGHT MANUAL 2 ORIGINAL ISSUE 12 22 2006 6 32 SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION TABLE OF CONTENTS LUE SECTION INTRODUCTION ie 7 3 AIRFRAME Pro RD Roo er Del RI ne RR RR Ie TR TER 7 3 FLIGHT CONTROLS DESCRIPTION 7 3
104. 2 SECTION VI M20TN WEIGHT AND BALANCE MARK IF INSTALLED cm INCHES T LBS EQUIPMENT LIST WEIGHT 501 INSTL WEIGHT 503 INSTL WEIGHT 505 INSTL MRSTN EQ A ITEM ITEM REF NO DESCRIPTION DRAWING 3 lt 2 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL uli 6 13 M20TN WEIGHT AND BALANCE SECTION VI uoneanByuoo 104 9 6 01 19J9H H3NNIdS M 62 92 160089 2 40669 4 4 4 TI3ZLHVH 03385 LNVLSNOO x H3 T13dOHd AOD dOHd 10 1104 62 22 678 0 009 LW LSAS LONGNI 91 66 2 YSLYVLS S3anoNI 4 99 088 0154 NOL 3NION3 5 554202 2 INV IdH3MOd G3TIVLSNI SSHONI 587 ONIMVYC NOILdIHOS3Qq WM di MYVIN IM WALI WALI 1 03 15 151 LNAWdINOA ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 6 14 SECTION VI M20TN WEIGHT AND BALANCE INCHES cm REF DRAWING H o Lu Lu ITEM DESCRIPTION MRSTN EQ B2 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL uli 6 15 M20TN WEIGHT AND BALANCE SECTION VI NOILVINHOHNI LN3NOdWOO DILVIN3HOS 1V9IHIO93 13 318VOrTddV 83338 1220 HOlVnlOV OH 9 Lt
105. 36 liters dry quarts 1 201 U S liquid qts 69 354 cubic inches 1 1 201 0 5 4 546 liters 277 420 cubic inches RIGINAL ISSUE 12 22 2006 1 12 4 MOONEY SECTION I M20TN GENERAL WEIGHT S Customary Unit Metric Equivalents Avoir du pois 1 gral terre aie Bec ne eta ane eae ewe caes 64 79891 milligrams DEEST 1 772 grams OUNCE deci ade te Rai da ced ert id 28 350 grams 1 oL ESPERE UN POLL PM EE DUAE 453 6 grams PRESSURE U S Customary Metric Equivalents AP SIGH Goo ote e re wea e Seg telis rea eue s 6 895 KPA 2 c M 3 388 KPA T Anci HG e c e Renee Ere e ee a ene 25 40 mm Hg COMMON CONVERSIONS 1 pound square foot 0 488 kg meter square 1 pound square inch reet Le e 2 036 inch Hg 1 pound FP est e et ea edat Gs ek 0 4538 kg HP USE OF THE TERMS WARNING CAUTION AND NOTE The following conventions will be used for the terms Warning Caution and Note WARNING The use of a Warning symbol means that information which follows is of critical importance and concerns procedures and techniques which could cause or re sult in
106. 4 5838 Je 8 4 8 4 T 4 m O 4 5 4 t 4 4 Ja HN 4 4 Zo 38 os ES 58 48 4 og d NL iN BE MATO gt aeoo 853 3 5 25 S zi NN P 4 O 0 0 16 a 8 o lt 1 gu X 1 jo 2045 LS 48 oui 4 4 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 5 23 M20TN CRUISE POWER SETTINGS amp FUEL FLOWS BEST POWER SECTION V PERFORMANCE suonipuoo uo Buipuedep Io 44186 5 61 9 0 FOZ 51 jon eui BHU 9706 LYO 2 92 HV H 00092 0082 10 ejduex3 15 9 01 uoee 10 9 0 eseoJou p OJON pJepuejs 2 01 uoeo 10 14 126 9 0 peniuued si 1104 02 z 30N 10 3 5491 16 eq 1 0022 199 000 22 sepninje 1y IION je6 q 079
107. 45 Do Sb LVO 40066 0052 1114 M3MOd Q31VI2OSSV ORIGINAL ISSUE 12 22 2006 SECTION V PERFORMANCE o 2 e 9 0 US GAL 39 0 NMI TIME 19 8 3 5 FUEL 11 0 2 0 DIST 42 5 3 5 EXAMPLE 3000 LBS ISA 15 C 24000 FT START ALT 5000 FT END ALT T O WT OAT FULL 1350 F TIT MINIMUM ASSOCIATED CONDITIONS UP UP POWER AIRSPEED 104 KIAS GEAR FLAPS AIRPLANE FLIGHT MANUAL 5 22 TIME FUEL DISTANCE to CLIMB at Vy 1 SN aasn 1313 q c VIA 1 20 DISTANCE WT LB x 100 40 60 80 100 DISTANCE 20 0 14 13 WT KG x 100 15 ORIGINAL ISSUE 12 22 2006 SECTION V M20TN PERFORMANCE TIME FUEL DISTANCE to CLIMB at 120 KIAS 1v9 sn 1903 N lt wo INIL 7169 o HN ul 5a 1 zoz 4s 502 1 Ng Yu 1 gt pu Od a ooo 106 SEJ led u 28 168 uic N 4 5 ll 48 o o 4 LITE tooo
108. 50 15m OBSTACLE 312 1580 SL 151 MOONEY M20TN 00 X 99 LH9I3M do LYO 6 vi SL OCL 00 08 09 02 0 00 OF IN3IQV39 AMY SLY ANIM 001 X 87 LH9I3M 2 2 002 St OL 6 092 12 66 OS Oc OL 0 Ok OZ O OF 002 002 009 1111 INS e e 1333 310V1S80 13 09 1510 1510 43O3 lv L IHL 9601 OL dN NVO 9608 SS3OX3 NI ALIGINNH 14 0022 71810 THHdN SVIM SZ SVIM S9 97 0022 9608 134 517 OL SVIM 84 SVIM 69 87 0062 20 5 14 587 001 1H9I3M SVIM 08 SVIM 22 97 0018 13 0001 Liv 553 SVIM v8 SVIM 22 818966 JAVY OL 1104 H3MOd 2 190 d3adS 1409 03345 5 ANG Q31VI2OSSV 5 17 AIRPLANE FLIGHT MANUAL Sess ORIGINAL ISSUE 12 22 2006 SECTION V MOONEY PERFORMANCE M20TN TAKEOFF DISTANCE GROUND ROLL ON GRASS PENDING DATA AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 18 4 SECTION V M20TN PERFORMANCE TAKEOFF DISTANCE OVER 50 15m OBSTACLE ON GRASS PENDING DATA ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 5 19
109. 88 S 9601 72 6145 IXVL ONIGNV1 201 OES os 2921 422 116 390915 9NIM 961 0L HOLVOIGNI HV35 061 61 f 555 85 15009 21910919 Tans 61 11 EE ES 1 21 514406 x 8819 2 901 ze ueni m9 7 x 0981 56 62 804 SLIOA vz 5 L Ed cd 3711 15 1 587 NOILdIHOS3G ON 12 03 15 EN o 0 06 0L 0 221 S HOLVOIGNI 9NINHVM 77715 39 per E EN 151 LNAWdINOA ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 6 16 SECTION VI WEIGHT AND BALANCE MOONEY M20TN Q3TIVISNI NOILVINYOSNI LN3NOdWOO 5 OL 83338 c9 O3 NISHMW 151 LNAWdINOA 6 17 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 M20TN WEIGHT AND BALANCE SECTION VI RE OON 34 vu8 H31S VW ES I 3dAL S X 00 S 9 ISON E ZI 0 iggy 900008 1 18 55 133HM ISON X 1599 09 Z
110. ANUAL FAA APPROVED 2 20 A ORIGINAL ISSUE 12 22 2006 SECTION III M20TN EMERGENCY PROCEDURES TABLE OF CONTENTS RUE MEA SECTION INTRODUCTION oiea ia ea ti RE e ae i uc e 0 3 3 AIRSPEEDS FOR EMERGENCY OPERATIONS 3 4 ANNUNCIATOR PANEL WARNING LIGHTS 3 5 GARMIN G1000 ANNUNCIATION 3 6 ENGINE i enaa E ra E 3 7 ENGINE POWER LOSS DURING TAKEOFF ROLL 3 7 ENGINE POWER LOSS IMMEDIATELY AFTER LIFTOFF Below 400 Ft AGL 3 7 ENGINE POWER LOSS DURING FLIGHT ABOVE 400 FEET AGL 3 7 ENGINE POWER LOSS SUSTAINED NEGATIVE g LOADING 3 8 AFTER ENGINE 5 3 9 EMERGENCY LANDING WITHOUT ENGINE POWER 3 9 EMERGENCY LANDING WITH THROTTLE STUCK AT IDLE POWER 3 10 PRECAUTIONARY LANDING WITH ENGINE POWER 3 10 POWER LOSS PRIMARY ENGINE INDUCTION AIR SYSTEM BLOCKAGE 3 10 TURBOCHARGER FAILURE 3 11 TURBOCHARGER 3 12 ENGINE ROUGHNESS 3 12 HIGH CYLINDER HEAD 3 12 HIGH OIL TEMPERATURE
111. AT BATTERIES BE FULLY CHARGED TO OPERATE AIRCRAFT Electrical com ponents may also be damaged if aircraft is operated when batteries are low AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 di SECTION IV M20TN NORMAL PROCEDURES NOTE When starting engine using the approved external power source no special start ing procedure is necessary Use normal starting procedures below DO NOT START ENGINE IF BOTH BATTERIES ARE INCAPABLE OF STARTING ENGINE Recharge dead batteries for at least one hour at 3 4 amps before starting en gine Only No 1 battery left side of tailcone is connected to the Auxiliary Power plug NORMAL ENGINE START Before Starting Check List COMPLETED T FULL RICH Throttle cov RR RR e FULL OPEN Prime the Engine SWITCH HIGH BOOST ON 2 SECONDS Throttle Control CLOSED THEN OPEN 1 8 TO 1 4 INCH Check Propeller Area CLEAR Ignition Switch TURN and PUSH TO START CAUTION If no oil pressure is noted within 30 seconds shut down the engine and investi gate the cause Operating the engine without oil pressure may result in engine damage or malfunction HOT ENGINE START Before Starting Check Li
112. ATOR The airspeed indicator registers air speed in knots The air pressure difference between the pitot tube and static ports on each side of the tailcone operates the air speed indicator 2 ATTITUDE INDICATOR Varies with installed equipment 3 ALTIMETER The altimeter operates by absolute pressure and converts barometric pressure to altitude reading in feet above mean sea level The altimeter has a fixed dial with three pointers to indicate hundreds thousands and tens of thousands of feet Barometric pressure is sensed through the static ports A knob adjusts a movable dial a small window on the face of the main dial to indicate local barometric pressure and to correct the altimeter reading for prevailing conditions 4 TURN INDICATOR The turn coordinator operates from an electric power source The turn coordinator is indepen dent of the flight reference gyros The turn coordinator displays variation in roll and yaw to the pilot by means of a damped miniature aircraft silhouette display this provides the pilot with es sential information to execute a proper turn 5 ANNUNCIATOR PANEL See description elsewhere in this SECTION 6 MAGNETIC COMPASS Magnetic compass dial is graduated in five degree increments and is encased in liquid filled glass and metal case It is equipped with compensating magnets adjustable from front of case Access to compass light and compensating magnets is provided by pivoted covers No mainte nance is
113. Alternator Emergency Checklist repeated below 1 Push Stdby Alt Emergency Bus switch ON This activates the emergency bus circuitry amp Standby Alternator system Verify The AMBER EMERG BUS annunciator illuminates and b The RED ALT VOLTS flashing annunciator extinguishes NOTE The most efficient operating RPM is 2500 RPM when operating on the Standby Alternator System 2 All electrical systems will remain powered and functional 3 If the RED ALT VOLTS annunciator remains flashing then CAUTION If the RED ALT VOLTS annunciation remains flashing then the standby alterna tor has failed and only main battery power remains 4 Reduce the electrical load by pulling the BAT circuit breaker This load sheds the non es sential bus The following systems remain powered by the essential bus CAUTION If the autopilot is engaged when the BAT circuit breaker is pulled the autopilot will disconnect without annunciation ALT SENSE ALT BUS ALT FIELD ALT FIELD ALT OUT e STBY ALT BAT e AUX PANEL e AUX OVHD e GLARESHIELD LIGHT PFD MFD e AHRS e ADC ENGINE INST STBY GYRO e ICE PROT SYS If Installed STBY BUS BAT COM 1 NAV1 GPS 1 AUDIO XPONDR e STALL WARN ICE LITE If Installed e PITOT HEAT AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 3 18 A MOONEY SECTION III M20TN EMERGENCY PROCEDURES Th
114. BLE OF CONTENTS eR EA SECTION INTRODUCTION etae eedem GAS ad dae e 8 3 GROUND HANDEING e ok atta eec 8 4 TOWING een RU e een n D e 8 4 TIEDOW N ec cr ene tat e 8 4 JACKING ced eer utt a eet tere CHE e ar ER ead 8 4 SERVICING pte te UE DI T uoa al dat cen e o de dete TAS 8 5 REFUELING iecore ete cte eet erar nte re eee idet 8 5 FUEL ADDITIVES eh Ead RUE Rn aa ead age 8 5 ENGINE EUBRIGATION etre met eec d o gl RR eta b 8 6 INDUCTION AIR FILTER 8 6 GEAR AND TIBES b E TENE Rede 8 8 BATTERIES IRURE ee edad eue as 8 8 HYDRAULIC BRAKE RESERVOIR SYSTEM 8 9 MAINTENANCE inte nti e Rn ere oa aea nd RR Oa ra Te aso 8 9 ENGINE PERFORMANCE CHECKS 8 9 CARE a tbt cocer eue dece dia bes e acted 8 9 eae ie Rc ute petas M oae te e Abe Cad desta 8 9 INTERIOR GARE ne meten eee aca e D ace C tts 8 10 AIRPEANE ette tein Rb tte a Ceo rece n 8 10 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 8 1 SECTION V
115. BUS The non essential bus powers the autopilot turn coordinator required for the autopilot the Stormscope and GIA 2 This bus is load shed manually by the pilot by pulling the BATT circuit breaker when the standby alternator and emergency bus switch are activated EQUIPMENT LOCATION The G1000 ADC and GEA LRU s are located behind the PFD and which may be removed using a hexagonal tool The magnetometer is located in the right wing outboard of the landing light The AHRS and remaining LRU s are located in the forward section of the tailcone near the main batteries ORIGINAL ISSUE 12 22 2006 8 AIRPLANE FLIGHT MANUAL 7 27 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN SCHEMATIC See FIGURE 7 8 The voltage regulator adjusts alternator output to current load while maintaining a constant volt age level It also prevents Overvoltage and Field Short conditions from damaging the electrical system A voltage warning light illuminates steadily when voltage limits are exceeded i e volt age spikes and flashes when the voltage is low
116. CATED AIRSPEED KIAS KCAS ERROR 0 2 EXAMPLE 0 1 GIVEN IAS 80 KNOTS 59 FIND CAS 80 KNOTS NOTE The minus sign indicates subtraction of the given numbers from KIAS to obtain the corrected airspeed AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 8 A SECTION V M20TN PERFORMANCE AIRSPEED CALIBRATION PRIMARY STATIC SYSTEM POWER OFF 10 FLAP GEAR DOWN Air Speed Calibration Primary Static System Power Off 10 Flap Gear Down SPEED FOR SAFELY LOWERING FLAPS 4 lt m o Y 70 80 90 100 KNOTS INDICATED AIRSPEED KIAS KCAS ERROR EXAMPLE 61 0 6 GIVEN IAS 80 KNOTS 66 0 6 FIND CAS 80 KNOTS 71 0 5 75 0 4 80 55 95 The minus sign indicates subtraction of the given numbers from KIAS to obtain the 100 corrected airspeed 105 110 115 120 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 5 9 SECTION V MOONEY PERFORMANCE M20TN AIRSPEED CALIBRATION PRIMARY STATIC SYSTEM POWER ON 33 FLAP GEAR DOWN Air Speed Calibration Primary Static System Power On 33 Flap Gear Down SPEED FOR SAFELY LOWERING FLAPS 0 lt q 2 lt tc m n x KNOTS INDICATED AI
117. CRAFT 2 4 4 4 17 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL me SECTION IV MOONEY NORMAL PROCEDURES M20TN BLANK AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 di SECTION IV M20TN NORMAL PROCEDURES INTRODUCTION This section describes the recommended procedures for the conduct of normal operations for the airplane All of the required FAA or ICAO regulations procedures and those necessary for operation of the airplane as determined by the operating and design features ofthe airplane are presented These procedures are provided to present a source of reference and review and to supply infor mation on procedures which are the same for all aircraft Pilots should familiarize themselves with the procedures given in this section in order to become proficient in the normal operations of the airplane Normal procedures associated with those optional systems and equipment which require hand book supplements are provided by SECTION IX Supplemental Data ORIGINAL ISSUE 12 22 2006 EV AIRPLANE FLIGHT MANUAL 4 3 SECTION IV MOONEY NORMAL PROCEDURES M20TN SPEEDS FOR NORMAL OPERATION Unless otherwise noted thefollowing speeds are based on a weight of 3368 pounds and may be used for any lesser weight However to achieve the performance specified in SECTION V for take off distance and climb performance the speed appropriate to the particular weig
118. D an Audio Panel and Attitude and Heading Reference System AHRS an Air Data Computer ADC and the sensors and computers to process flight and en gine information for display to the pilot The system contains dual GPS receivers dual VOR ILS receivers dual VHF communications transceivers a transponder and an integrated annunci ation system to alert the pilot of certain abnormal conditions The Primary Flight Display PFD typically displays airspeed attitude altitude and heading in formation in a traditional format Slip information is shown as a trapezoid under the bank pointer One width of the trapezoid is equal to a one ball width slip Rate of turn information is shown on the scale above the compass rose full scale deflection is equal to a standard rate turn The fol lowing controls are available on the PFD clockwise from top right e Communications frequency volume and squelch knob e Communications frequency set knobs e Communications frequency transfer button e Altimeter setting knob baro QNH set Course knob Maprange knob and cursor control FMS control buttons and knob PFD softkey buttons including master warning caution acknowledgement Altitude reference set knob Heading bug control e Navigation frequency transfer button e Navigation frequency set knobs Navigation frequency volume and Identifier knob The PFD displays the crew alerting annunciator system When an alert message is received
119. D IN THE AIRCRAFT AT ALL TIMES All information and illustrations in the manual are based on the latest product information avail able at the time of publication approval and all sections including attached supplements are mandatory for proper operation of the aircraft The right is reserved to make changes at anytime without notice Every effort has been made to present the material in a clear and convenient manner to enable you to use the manual as a reference Your cooperation in reporting presenta tion and content recommendations is solicited REVISING THE MANUAL The i pages of this manual contain a List of Effective Pages containing a complete current listing of all pages i e Original or Revised Also in the lower right corner of the outlined portion is a box which denotes the manual number and issue or revision of the manual It will be ad vanced one letter alphabetically per revision With each revision to the manual a new List of Effective Pages showing all applicable revisions with dates of approval and a Log of Revisions page s with only the latest Revision shown will be provided to replace the previous ones It is the operators responsibility to ensure that this manual is current through the latest published re vision This handbook will be kept current by Mooney Airplane Company Inc when the yellow information card in front of this handbook has been completed and mailed to Service Parts Department Mooney Airplane
120. Data Computer is indicated by a red X and yellow text over the airspeed altimeter vertical speed TAS and OAT displays Some FMS functions such as true airspeed and wind calculations will also be lost 1 Use Standby Airspeed Indicator and Altimeter 2 LAND AS SOON AS PRACTICABLE at a suitable airport ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 3 19 SECTION III MOONEY EMERGENCY PROCEDURES M20TN ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS NOTE Loss of an engine parameter is indicated by a red X through the data field Erro neous information may be identified by indications which do not agree with other system information Erroneous indications may be determined by comparing a display with other displays and other system information 1 Set power based on throttle lever position engine noise and speed 2 Monitor other indications to determine the health of the engine 3 Use known power settings in the POH Chapter V for approximate fuel flow values 4 Use other system information such as annunciator messages fuel quantity and flow to safely complete the flight ERRONEOUS OR LOSS OF WARNING CAUTION ANNUNCIATORS NOTE Loss of an annunciator may be indicated when engine or fuel displays show an abnormal or emergency situation and the annunciator is not present An erro neous annunciator may be identified when an annunciator appears which does not agree with other displays or system information 1 Ifan annunci
121. E AMBER when speed brakes are extended 8 ALT AIR AMBER when the alternate air door is opened either manually or automatically In this situation induction air for the engine is drawn from inside cowling rather than through the induction air intake The normal induction air system MUST be checked for proper operation prior to next flight NOTE Induction of alternate air warm air will result in loss of power 9 PROP DE ICE BLUE when Propeller De Ice has been selected ON 10 PITOT HEAT Illuminates BLUE when pilot has selected PITOT HEAT rocker switch ON Some exported air craft will Illuminate AMBER when switch is OFF or when there is any type of electrical failure in pitot heat system and WILL NOT BE illuminated when the switch is ON 11 SPARE 12 ALT VOLTS A RED light indicates improper voltage supply A FLASHING RED light indicates alternator volt age output is below load requirements or no voltage from alternator a STEADY RED light indi cates over voltage or tripped voltage relay 13 SPARE 14 START POWER RED when the starter switch or relay has malfunctioned and the starter is engaged while the engine is running Shut the engine off as soon as practicable 15 SPARE 16 SPARE AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 MD Qe SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION 17 EMERGENCY BUS A ste
122. EER Sas ct ce ORIGINAL ISSUE SENTI ORIGINAL ISSUE cr MMC EE TEE ORIGINAL ISSUE AMPIA ORIGINAL ISSUE Be exo Ur ORIGINAL ISSUE ORIGINAL ISSUE am CMM IM ORIGINAL ISSUE ee Ld En dE ORIGINAL ISSUE DE M aa ORIGINAL ISSUE MMC MOREM ORIGINAL ISSUE MINER MEUM CPP TOM ORIGINAL ISSUE MEE HH ORIGINAL ISSUE C sa Se cy lS ORIGINAL ISSUE 8511 uto Rito MU Ar INS PRS None ORIGINAL ISSUE ORIGINAL ISSUE EE ERUIT ORIGINAL ISSUE aces E ET CELO DD ORIGINAL ISSUE Ner MCI ND ORIGINAL ISSUE LOREM EMEN ORIGINAL ISSUE p MERERI M ace ee ORIGINAL ISSUE o MH ORIGINAL ISSUE OP TACEAM MUERE ORIGINAL ISSUE USC CH Ne EPFL ORIGINAL ISSUE MONI UMEN MUERE ORIGINAL ISSUE OU nee eR Uu ue rS ORIGINAL ISSUE E MM ORIGINAL ISSUE Cz RT JL ER ORIGINAL ISSUE RPM NM RP ER ECCE ERE ORIGINAL ISSUE C MPO Np ccn T oM ORIGINAL ISSUE peior uu eI r pM A ORIGINAL ISSUE
123. ENVELOPE 6 11 FIXED BALLAST vie nere eben e me eed PA mta ere eek nace a De 6 12 EQUIPMENT oci Se cc la eie P tete 6 12 NOTE The empty weight center of gravity and equipment list for the airplane as delivered from Mooney Airplane Company Inc is contained in this section The use of this section is valid for use with the airplane identified below when approved by Mooney Airplane Company Inc MOONEY M20TN AIRCRAFT SERIAL NO AIRCRAFT REGISTRATION NO Mooney Airplane Company Inc Approved Signature and Date ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL gt 6 1 SECTION VI MOONEY WEIGHT AND BALANCE M20TN BLANK AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 8 2 SECTION VI M20TN WEIGHT AND BALANCE INTRODUCTION This section describes the procedure for calculating loaded aircraft weight and moment for vari ous flight operations In addition procedures are provided for calculating the empty weight and moment of the aircraft when the removal or addition of equipment results in changes to the empty weight and center of gravity A comprehensive list of all Mooney equipment available for this airplane is included in this section Only those items checked X were installed at Mooney and are included in the empty weight and balance data The aircraft owner and or pilot has the responsibility of properly loading th
124. ESCRIPTION MOONEY M20TN 13371 YALLINSNVYL ASSV 3925 131110 AINO 39N3H3H3H H3LLINSNVH L SILVINSHOS WALSAS 1304 LINN TE 20 7 7 1904 p YAONGSNVYL 371113 1441 YOLVSIONI 2 3ATVA 194135 4 14 i C HOLVOIGNI HOlV1OOSV5 1905 2 YYZ 141100 7 AATVA NIVHG TIVA3ul3 4 X H3LLIINSNVH L cm 7303 le 1 31419474 13n3 W31SAS HOLVOIGONI NOILNGIYLSIC 71303 E 13n4 YALLINSNVYL Hari 7 25 AIRPLANE FLIGHT MANUAL FIGURE 7 7 FUEL SYSTEM SCHEMATIC ORIGINAL ISSUE 12 22 2006 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN FUEL SYSTEM Fuel is carried in two integrally sealed sections of the forward inboard area of wing Total usable fuel capacity is 102 U S gallons 386 1 liters There are sump drains at the lowest point in each tankfor taking fuel samples to check for
125. F THEN GRADUALLY RICHEN UNTIL ENGINE STARTS If engine does not restart Alternate Air Door UD tu E Rete e eue OR See PULL TO OPEN LOW Boost Purmp 5i severe EDO emt gti OFF HIGH Boost PUMP inm a EIE e ON Mixture PULL TO CUTOFF THEN GRADUALLY RICHEN UNTIL ENGINE STARTS If engine does not re start establish best glide speed Refer to Maximum Glide Distance Chart and proceed to FORCED LANDING EMERGENCY If engine starts Engine Temperatures CHECK OIL and CHT within GREEN arc PM EE warm engine at partial power if req d Altit de ew detis e bp BOR ATTAIN SAFE ALTITUDE After engine re start refer to AFTER ENGINE RE START procedure ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 3 7 SECTION III MOONEY EMERGENCY PROCEDURES M20TN WARNING At altitudes above 18 000 ft an overrich mixture may result if the turbocharger fails and the engine may stop firing NOTE Excessive engine cooling may be experienced during long descents resulting in low engine oil and cylinder head temperatures This may result in the engine not accelerating properly when power is reapplied If oil or cylinder head tempera tures are excessively low then the engine should be operated at partial power un til the temperatures are sufficient for full power operation ENGINE POWER LOSS SUSTAINED NEGATIVE g LOADIN
126. FAA APPROVED 4 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 2 5 SECTION II MOONEY LIMITATIONS M20TN POWER PLANT LIMITATIONS Number of Englries pu EXER EU E opere pue xU edt e aa 1 Engine Manufacturer Teledyne Continental Motors TCM Engine Model Number TSIO 550 G 1B Recommended Time Between 2000 Hours Time in Service Engine Operating Limits for Takeoff and Continuous Operations Maximum Recommended Cruise For Leaning 262 HP Maximum Continuous 280 BHP Maximum Continuous RPM 2500 RPM Maximum Recommended Continuous Cylinder Head Temperature rum Sr LI IUE 420 F 215 6 C Maximum Cylinder Head Temperature 460 F 237 79 C Maximum Turbine Inlet Temperature TIT 17509 F 954 C 1850 F 10109 C for 30 Sec Maximum Temperature 240 F 1169 C Minimum Oil Temperature 1009 F 389 C Recommended Cruising Oil Temperature 1709 F 220 F 76 79 C 104 4 Maximum Manifold 33 5 Inches of Hg Oil Pressure Normal Operating oce me oue
127. Fluid level should be no higher than two 2 inches 5 cm below filler cap Use only hydraulic fluid Red conforming to specification MIL H 5606 DO NOT FILL reser voir while parking brake is set MAINTENANCE ENGINE PERFORMANCE CHECKS When the aircraft leaves the factory the TSIO 550 G engine has been properly tuned and will perform at optimum efficiency To insure that the engine is continuing to perform properly certain maintenance action should be performed during the 100 HOUR or ANNUAL inspection or when ever it is suspected that engine performance is not correct Refer to 20 SERVICE AND MAINTENANCE MANUAL TCM maintenance manuals for specific maintenance actions to adjust engine if necessary PROPELLER CARE The high stresses to which propeller blades are subjected makes their careful inspection and maintenance vitally important Check blades for nicks cracks or indications of other damage before each flight Nicks tend to cause high stress concentrations in the blades which if ignored may result in cracks It is very important that all nicks and scratches be repaired prior to flight It is not unusual for propeller blades to have some end play or fore and aft movement as a result of manufacturing tolerances in the parts This has no adverse effect on propeller performance or operation With the first turn centrifugal force firmly seats the blades rigidly and positively against the retention bearing in the propeller hu
128. G WARNING DO NOT INTENTIONALLY OPERATE IN NEGATIVE g LOADING Per specifications the Model TSIO 550 series engine is NOT APPROVED for continuous negative or zero operation and operation in that environment is prohibited Depending on the loading and amount of time encountered more than normally encountered in gusts the engine may quit due to low oil pressure Upon return to positive loading the engine will normally restart on its own but may require some leaning of the mixture at very high altitudes for restart If nega tive load conditions are unavoidably encountered the following procedures are recommended s deat beste Epp benedi ele ote ete As required to RECOVER Attitude Ce AUR UT Wings LEVEL and UPRIGHT If engine restarts Throttle cerro REDUCE POWER to prevent propeller over speed Attitude e LAUR ep Rr teer Recover to LEVEL FLIGHT sure UC UR Lu pest Ns tree Resume NORMAL POWER setting If a propeller overspeed occurs follow PROPELLER OVERSPEED procedure If engine does not re start within ten 10 seconds follow ENGINE POWER LOSS IN FLIGHT procedure AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 3 8 A MOONEY SECTION III M20TN EMERGENCY PROCEDURES AFTER ENGINE RESTART HIGH Boost Pump Guarded If ON then turn OFF Alternate Alr DOOr austen nee BEN CLOSED If
129. Hg AlrSpeed 140 KIAS less Eandirig Gear SR ette ENORMES A A e DOWN cert cete qe opp EE eb idee ep metes 165 KIAS or less Power Settings Le ursi RE AS REQUIRED e AS REQUIRED LOW Boost Pump OFF Below 18 000 Ft Rudder euo e bns te AS DESIRED NOTE Using landing gear as a descent aid will result in a steeper descent rate for a giv en power setting and airspeed Alternatively for a fixed descent rate more power will be required This can be helpful for maintaining minimum oil and cylinder head temperatures Plan for additional fuel consumption accordingly ORIGINAL ISSUE 12 22 2006 2225 AIRPLANE FLIGHT MANUAL 4 15 SECTION IV MOONEY NORMAL PROCEDURES M20TN APPROACH FOR LANDING CAUTION The airplane must be within allowable weight and balance envelope for landing REF SECTION VI It will require a minimum of one hour of flight before a permis sible landing weight is attained when takeoffs are made at maximum gross weight If landing at a weight exceeding maximum landing weight 3200 Lbs 1452 Kgs is required see OVERWEIGHT LANDING PROCEDURE SECTION III Seats Seat Belts Shoulder Harness ADJUST AND SECURE Internal External lights
130. I KTAS GPH KTAS GPH KTAS 16000 Ft Pressure Altitude AISA 30 47 C 0 16 C 30 14 C OAT 54 52 0 2 F 54 56 F RPM MAP KTAS GPH KTAS GPH KTAS GPH 2200 21 0 168 12 6 168 11 7 167 10 7 Some low power settings may not be attainable due to low cylinder or oil temperatures depending on ambient conditions AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 34 4 SECTION V M20TN PERFORMANCE SPEED and POWER SETTINGS vs ALTITUDE BEST ECONOMY 14000 Ft Pressure Altitude AISA 30 43 C 0 12 C 30 18 C OAT 54 45 0 9 F 54 63 F RPM MAP KTAS GPH KTAS GPH KTAS GPH 12000 Ft Pressure Altitude AISA 30 39 C 0 8 C 30 22 C OAT 54 38 0 16 F 54 70 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Some low power settings may not be attainable due to low cylinder or oil temperatures depending on ambient conditions ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL wd 5 35 SECTION V MOONEY PERFORMANCE M20TN SPEED and POWER SETTINGS vs ALTITUDE BEST ECONOMY 10000 Ft Pressure Altitude AISA 30 359 0 4 C 30 26 C OAT 54 31 F 0 23 F 54 77 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Ft Pressure Altitude AISA 30 31 C
131. IGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 12 4 MOONEY SECTION V M20TN PERFORMANCE ALTIMETER CORRECTION PRIMARY STATIC SYSTEM SEA LEVEL 12 500 FT 25 000 FT Gear amp Gear Gear Gear amp Gear Gear Gear amp Gear Gear Flaps Dn 10 DN 33 Flaps Dn 10 DN 33 Flaps 109 DN 339 Flaps Flaps UP Flaps Flaps UP Flaps Flaps CEN REN The minus sign indicates subtraction of the given numbers from the indicated pressure altitude to obtain correct altitude assuming zero instrument error EXAMPLE KIAS 110 Ak eet oes e ALTIMETER CORRECTION 7 ft 109 aw ete ee Subtract from Indicated Altitude INDICATED PRESSURE ALTITUDE 12 500 ft PRESSURE ALTITUDE 12 493 ft ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL wd 5 13 SECTION V MOONEY PERFORMANCE M20TN ALTIMETER CORRECTION ALTERNATE STATIC SYSTEM SEA LEVEL 12 500 FT 25 000 FT ERN amp Gear Gear Gear amp Gear Gear Gear amp Gear Gear is Dn 10 DN 33 Flaps Dn 10 DN 33 Flaps Dn 10 DN 339 aps UP Flaps UP Flaps Flaps ER SZ ee 121005 6522 225 258 207126 aan ae se 219
132. III MOONEY HANDLING SERVICE AND MAINTENANCE M20TN BLANK AIRPLANE FLIGHT MANUAL 8 2 A ORIGINAL ISSUE 12 22 2006 SECTION VIII M20TN HANDLING SERVICE AND MAINTENANCE INTRODUCTION This section contains factory recommended procedures for proper ground handling routine care and servicing of your Mooney Itis recommended that all aircraft undergo a complete inspection ANNUAL each twelve calen dar months In addition to the recommended ANNUAL inspection aircraft operated commercial ly for hire should have a complete inspection every 100 hours of operation All inspections must be performed by a designated representative of the FAA or the Aviation Authority of the country in which the aircraft is licensed The FAA may require other inspections by the issuance of Airworthiness Directives applicable to the airplane engine propeller and other components It is the responsibility ofthe owner opera tor to ensure compliance with all applicable Airworthiness Directives and recommended MAN DATORY Mooney Aircraft Service Bulletins Instructions When inspections are repetitive the owner operator should take appropriate steps to prevent inadvertent non compliance Scheduling of ALL maintenance is the responsibility of the aircraft operator A general knowl edge of the aircraft is necessary to perform day to day service procedures and to determine when non routine or unusual service or shop maintenance is needed Ser
133. L HARNESS RETENTION ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 7 17 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN SEATS The front seats are individually mounted and may be adjusted fore and aft to fit individual comfort preferences The front seat back may be adjusted by turning left side hand crank knob until seat back 15 in desired position Both optional front seat configurations allow vertical seat height adjustment by turning right side hand crank to raise or lower the entire seat assembly The rear seat backs have four 4 adjustment positions Each seat can be adjusted independent of the other by pulling up on respective release handle located on left or right of aircraft centerline on forward spar This allows adjustments from approximately 10 to 40 recline position SEAT BELTS SAFETY HARNESS Safety restraints if worn properly 1 occupant per restraint keep occupants firmly in their seats during T O landing turbulent air and during maneuvers The belts harnesses are mechanically simple and comfortable to wear The front seat inertia belts harnesses are attached to hard points on side structure and seats The rear seat belts are attached to brackets firmly mounted to structural hard points Shoulder harnesses are provided for rear seat occupants Safety belts harnesses MUST be fastened for take off and landing operations It is recommended that all infants and small children below 40 Ibs weight and or
134. L nied by a red X through the airspeed dis play Display system is not receiving airspeed in put from the air data computer accompa RET TOCE FAI nied by a red X through the altimeter dis play Display system is not receiving vertical speed input from the air data computer ac companied by a red X through the vertical speed display VERT SPEED FAIL Display system is not receiving valid head ing input from the AHRS accompanied by a red X through the digital heading display A red X through any display field such as COM frequencies NAV frequencies or en gine data indicates that display field is not receiving valid data FAA APPROVED 4 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 2 13 SECTION II MOONEY LIMITATIONS M20TN DECALS AND PLACARDS CABIN INTERIOR The following placards are relevant to proper operation of the airplane and must be installed in side the cabin atthe locations specified When ordering replacement Decals and Placards refer to the Mooney Airplane Company M20TN IPC or call Mooney Service Parts Dept WHEN ORDERING DECALS amp PLACARDS CONTACT MOONEY SERVICE PARTS DEPT z MATERIAL Y COLOR OF INK 150056 0000 SPEEDBRAKE EQUIPPED FOR OPERATING INSTRUCTION 1500567900070 LIMITATIONS SEE FAA APPROVED AFM SUPPLEMENT ON INSTRUMENT OR PILOT S OPERATING HANDBOOK 14 VOLTS 150056 X 1004 Y ON INSTRUMENT PANEL GLARE PANE 3 AMPS MAX 150056 X40
135. LE ese epa hok Ra Rn ERR ae tee 5 17 GROUND ROLL ON GRASS ecco xk Ra epp ed 5 18 OVER 50 OBSTACLE ON GRASS 2235 ada E 5 19 CLIMB RATEAAT isis sio IRE DRE eb RE Rm E id c 5 20 CLIMB RATE 120 KIAS CRUISE CLIMB 5 21 TIME FUEL DISTANCE TO CLIMB 5 22 TIME FUEL DISTANCE TO CLIMB 120 KIAS 5 23 CRUISE POWER SETTINGS AND FUEL FLOWS BEST POWER sieved enya au quer a ec y qua 5 24 BEST ECONOMY DES ERR DR RR EAR ER 5 25 SPEED POWER VS ALTITUDE BEST POWER dp oe ee p eR adag nega 5 26 BEST ECONOMY pte Ron ote Rt ete DATED 5 33 RANGE BEST POWER gat dod ool dub obo deed e d db do 5 39 BEST ECONOMY AG odor Kl Ee ea Edd C dao Fe d 5 40 ENDURANCE BEST POWER 4 id taret Dad us iau dd die 5 41 BEST ECONOMY RE C ERE REED RE 5 42 TIME FUEL DISTANCE to DESCEND Maintain 500 fpm Rate of Descent 5 43 TIME FUEL DISTANCE to DESCEND Maintain 1000 fom Rate of 5 44 LANDING GROUND BOLNL inet sor eate
136. LECT setting Mixture LEAN AS REQUIRED observe limits see CAUTION below DDR p CU DOM NEU D RCM 50 F Rich of Peak for Best Power RAs Stank ERR Sete bee eec A P UE S 50 F Lean of Peak for Best Economy LOW Boost Pump OFF below 18 000 ft leave ON above 18 000 ft Temperatures CHECK within limits until stabilized dete xad hte RE ADJUST if required NOTE Refer to cruise performance charts in Section V for power settings CAUTION Above 30 5 inHg of manifold pressure only full rich mixture is permitted At alti tudes above 22 000 feet power settings above 2300 rpm must be operated at 1675 F TIT or richer ORIGINAL ISSUE 12 22 2006 EV AIRPLANE FLIGHT MANUAL 4 13 SECTION IV MOONEY NORMAL PROCEDURES M20TN CAUTION Above 12 000 ft the minimum manifold pressure is 15 in Hg and the minimum RPM is 2 000 Do not pull the throttle back to idle without leaning mixture appro priately above 12 000 ft The lack of manifold pressure at altitude without leaning will cause an over rich condition This condition may cause the engine to quit above 18 000 ft This condition may also cause the engine to quit when the throttle is suddenly increased If it does quit it is possible to re start the engine at any altitude by leaning the mixture CAUTION When changing power the sequence control usage i
137. Lights INSPECT Lens amp Bulbs Stall Switch CHECK operation Master ON reach through pilots window Fuel Tank nete e og acts CHECK QUANTITY SECURE CAP NOTE The optional visual fuel quantity gauge is to be used for partial refueling pur poses only DO NOT use for preflight quantity check Tiedown Rope Chain REMOVE Wheel Chock oui ntt ove as eges e iets aeo REMOVE Left Main Landing Gear Shock Discs Tire amp Doors INSPECT Fuel Tank Sump Drain DRAIN vada da Use sampler cup to VERIFY fuel is free of water sediment amp other contamination pas Rte aeo e BRE RO pect WAG VERIFY proper fuel BLUE 100LL GREEN 100 octane AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 un di SECTION IV M20TN NORMAL PROCEDURES CAUTION Some diesel may be BLUE Verify by smell and feel that 100LL is being used T H VERIFY drain closes and does not leak Pitot System PUSH plunger UP Hold for 3 5 seconds 6 Left Cowl Area Windshield iecur ater ere CLEAN
138. MANUAL ORIGINAL ISSUE 12 22 2006 8 10 SECTION VIII M20TN HANDLING SERVICE AND MAINTENANCE chased from Mooney Airplane Company Inc It is recommended that copies of SECTION VI be made and stored in a safe place 3 To be made available upon request a Airplane Log Book b Engine Log Book Since the regulations of other nations may require other documents and data owners of air planes not registered in the United States should check with their own aviation officials to deter mine their individual requirements ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL wd 8 11 SECTION VIII MOONEY HANDLING SERVICE AND MAINTENANCE M20TN BLANK AIRPLANE FLIGHT MANUAL A ORIGINAL ISSUE 12 22 2006 SECTION IX M20TN SUPPLEMENTAL DATA TABLE OF CONTENTS TITEE E ia cut suisse etta SECTION INTRODUCTION 555 E RUNS CER RUE DURER 9 3 THE SUPPLEMENTS INSERTED INTO THIS SECTION ARE FAA APPROVED SUPPLEMENT INSERTED DATE ORIGINAL ISSUE 12 22 2006 4 AIRPLANE FLIGHT MANUAL 9 1 SECTION IX MOONEY SUPPLEMENTAL DATA M20TN SUPPLEMENT INSERTED DATE AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 SECTION IX M20TN SUPPLEMENTAL DATA INTRODUCTION FAA approved
139. MOONEY PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL M20TN ORIGINAL ISSUE 12 22 2006 P N POH 003900 Copyright 2006 All Rights Reserved MOONEY AIRPLANE COMPANY INC Louis Schreiner Field Kerrville Texas 78028 tel 830 896 6000 www mooney com M20TN TWANVW LHN VV4 pue 3O008QNVH 9SNILVH3dO S LOTId ANVdWOO 3NV IdHIV lt POH 003900 CAUTION THIS AIRCRAFT IS CERTIFIED TO USE 100LL BLUE OR 100 130 GREEN AVIATION GASOLINE ONLY IT IS THE PILOT S RESPONSIBIITY TO INSURE THAT THE PROPER FUEL IS USED AT EACH REFUELING FILL IN FOR YOUR RECORDS DATE PURCHASED REVISION CARD MAILED TO MOONEY DATE IN ORDER TO KEEP THIS MANUAL UPDATED WITH THE LATEST REVISIONS FILL IN AND MAIL ATTACHED CARD MANUAL Please enter the following name to the mailing list for future revisions of this manual COMPANY DATE NAME ADDRESS CITY STATE ZIP CODE ATTN Service Parts MOONEY AIRPLANE COMPANY INC Louis Schreiner Field Kerrville Texas 78028 PILOT S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL MOONEY M20TN THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY THE FEDERAL AVIATION REGULATIONS AND CONSTITUTES THE FAA APPROVED AIRPLANE FLIGHT MANUAL THIS DOCUMENT MUST BE CARRIED IN THE AIRCRAFT AT ALL TIMES MOONEY AIRPLANE COMPANY INC
140. N 8L SI GQNIMSSONOD Q31VH ISNOWSQO WOIWIXVIN 14066 1510 1 THHdN 2 SVIM vS SVIM 49 81 0092 WNIWIXVIN SLY OL SVIM 99 SVIM 04 81 0082 off NMOG 11104 54 14 9NIM 587 0082 LHSISM SVIM 89 SVIA ZZ 87 0008 3NV39 13 0001 SS3ud SVIM 6S SVIM SZ 87 002 H3MOd 83345 JAVY 03395 HdV ANG Q31VI2OSSV Do 2 190 5 45 AIRPLANE FLIGHT MANUAL SA ORIGINAL ISSUE 12 22 2006 M20TN LANDING OVER 50 15m OBSTACLE SIOVLSEO SL 39NVISIG ONIGNVI SECTION V PERFORMANCE 00 X 9X LH9I3M do LVO Ek 00 00 08 09 02 0 Oc 12 9 AMY SLY GNIM 00 X 87 LH9I3M 20 002 St OL S 0 92 82 06 2606 OF 06 02 OL 0 OZ 06 009 009 009 004 008 006 0001 0011 0021 0086 0091 0091 0091 39NVISIG 0021 13 00 03345 031517 0084 3H1 H3AO LONY 1993 3712 1590 14 0S SDNVLSIC 9NIGNV T1 SLON 8I SI QNIMSSONO Q31VHISNONWA3QG WAWIXYIN 140992 1514 SNIQNV T1 TIIHNMOG 2 SVIM vS SVIM 49 87 0092 SLY Ob SVIM 99 SVIM
141. NAL ISSUE pad efe ep ER ORIGINAL ISSUE cec err E b d MS ORIGINAL ISSUE ORIGINAL ISSUE T O2 Libr Le tup TI ETE Lats tetti va dor Loo Ne ORIGINAL ISSUE pcc ORIGINAL ISSUE 7534 UE ORIGINAL ISSUE sii ere eats E ORIGINAL ISSUE 596 d e ORIGINAL ISSUE CSP ebbe pL oe ORIGINAL ISSUE ie ORIGINAL ISSUE up ORIGINAL ISSUE nta ORIGINAL ISSUE Ile EORUM MOM ue vuU Late vare E editos ORIGINAL ISSUE EE ORIGINAL ISSUE Bsb opos lE rs tta RU td RUE ORIGINAL ISSUE rp ORIGINAL ISSUE EON ERE EE ORIGINAL ISSUE 8 8 lis rei pr IC ERDUDO ne ORIGINAL ISSUE 80 tuu ORIGINAL ISSUE 8 10 noce teste LE Cab dd aay iere ORIGINAL ISSUE 8211 e states ORIGINAL ISSUE IRE ARR Side ORIGINAL ISSUE irda ORIGINAL ISSUE ou Das ceo ras c LE Mn
142. NE AND SYSTEM DESCRIPTION M20TN ELT REMOTE SWITCH OPERATION A pilot s remote ELT switch is located just below the bottom right corner ofthe co pilot MFD The remote ELT switch allows the transmitter to be controlled from inside cabin ELT is activated when the ON button is pushed ELT returns to armed condition when the RESET button is pushed ARTEX ELT optional If the ELT switch is labeled ARTEX ELT then operation is different from above ELT is activated when the switch is in the ON position ELT returns to armed the switch is in the ARMED position NOTE If for any reason a test transmission is necessary the operator must first obtain permission from a local FAA or FCC representative or other applicable Authority or in accordance with current regulations Test transmission should be kept to a minimal duration Testing of ELT should be conducted only during the first five 5b minutes after any hour and no longer than three 3 audible sweeps The ELT should be checked during the ground check to make certain the unit has not been acci dentally activated Check by tuning a radio receiver to 121 5 MHz If there is an oscillating war bling sound the locator may have been activated and should beturned off immediately Resetto ARM position and check again to insure against outside interference AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 38 Qe SECTION VIII M20TN HANDLING SERVICE AND MAINTENANCE TA
143. NE START 4 9 AFTER ENGINE STARTS 2 60 ato M As E he cu ad 4 9 BEFORE alu AS cte oi Aa 4 10 4 10 MINOR SPARK PLUG FOULING 4 11 BEFORE TAKEOFF ice t ban atte et 4 11 TAKEOFF euet eibi 4 12 CM tetra oe 4 13 CLIMB CRUISE eis 4 13 CLIMB BEST RATE Vy 126056 ocn ote 4 13 CLIMB BEST RATE 4 13 CRUISE o p RE EAD a E 4 13 FUEL TANK SELECTION deren 4 14 OXYGEN SYSTEM turks 4 14 eum rade 4 15 NORMAL DESCENT GEAR UP 4 15 NORMAL DESCENT GEAR 4 15 APPROACH FOR 4 16 GO AROUND BALKED LANDING 4 16 251 Gort are 4 16 TAXI AFTER LANDING uad gest Sane ed 4 17 SHUTDOWN 4 17 SECURING AIR
144. NS Landing Gear Retracted Wing Flaps Zero Degrees Propeller Windmilling Wind Zero Wind BEST GLIDE SPEED Weight IAS LBS Kg Kts 3368 1528 91 5 3200 1452 89 0 2900 1315 84 5 2600 1179 80 0 1 2 lt gt lt H I 5 20 25 30 35 40 45 50 55 60 GROUND DISTANCE NAUTICAL MILES 40 50 60 70 80 GROUND DISTANCE KILOMETERS NOTE Greater glide distances can be attained by moving the propeller control FULL AFT LOW RPM FORCED LANDING EMERGENCY GEAR RETRACTED OR EXTENDED Emergency Locator Transmitter ARMED Seat Belts Shoulder Harnesses SECURE Cabin UNLATCHED Fuel Selector corner br pee puer RUN Webs ue m OFF epum ted p EH meet pte IDLE CUTOFF Magneto Starter Switch OFF WING Flaps 2 eee toe Poe cale Noc a aaa Full DOWN Landing 2 vans ilg DOWN If conditions permit Approach p e RU E cR Dae 80 KIAS Master Switch yeas cae
145. O TO CRANKSHAFT PROP BEARNGS GOVERNOR CAMSHAFT CRANKSHAFT PISTON amp CONNECTING TAPPET ROD STARTER SHAFT GEAR TURBOCHARGER FIGURE 7 5 OIL SYSTEM SCHEMATIC AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 720 Qe MOONEY SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION LUBRICATION SYSTEM Filter Full flow oil filter is a throw away filter element with a bypass valve incorporated BREATHER FOR CRANKCASE The crankcase is vented overboard through an air oil separator to the left tailpipe The air oil separator condenses some ofthe oil vapor and returns the oil back to the crankcase The tailpipe slows the vaporization of oil by providing some pressure to the crankcase atmosphere Proper maintenance of this system is required to minimize oil consumption IGNITION SYSTEM The TSIO 550 G engine is equipped with pressurized magnetos with impulse couplings on each magneto Power from the engine crankshaft is transmitted through camshaft gear to the magneto drive gears which in turn drives the magneto drive couplings The left magneto incorporates an im pulse coupling As the rubber bushings in the drive gear turns the coupling drive lugs counter weighted latch pawls inside the coupling cover engage pins on the magneto case and hold back the latch plate until forced inward by the coupling cover When the latch plate is released the coupling spring spins the magneto shaft through its neutral position and the bre
146. ON PROCEDURE Proper loading of the aircraft is essential for maximum flight performance and safety This section will assist you in determining whether the aircraft loading schedule is within the approved weight and center of gravity limits To figure an actual loading problem for your aircraft proceed as follows Step 1 Refer to the latest entry on page 6 6 for the current empty weight and moment NOTE Since the engine oil is normally kept at the full level the oil weight and moment is included in basic empty weight and is constant in calculating all loading prob lems Step 2 Note the pilot s weight and the position his seat will occupy in flight Find this weight on the left scale of the Loading Computation Form page 6 9 and cross the graph horizontally to the graph for 1 and 2 seats When this point is located drop down to the bottom scale to find the value of the moment 1000 due to the pilot s weight and seat position Repeat procedure for co pilot and enter these weights and moment 1000 values in the proper sub columns in the Problem Form on page 6 8 9 Step 3 Proceed as in Step 2 to account for the passengers in seats 3 and 4 Enter the weight and value of moment 1000 in the proper columns Step 4 Again proceed as in Step 2 to account for the amount of fuel carried and enter the weight and moment 1000 values in the proper columns Step 5 Once more proceed as in Step 2 to account for the baggage to be carried and
147. ORIGINAL ISSUE ect ME ORIGINAL ISSUE occ apes eo emer ere ORIGINAL ISSUE E ORIGINAL ISSUE HT ORIGINAL ISSUE ake ORIGINAL ISSUE MAP M ORIGINAL ISSUE OC MM PER ORIGINAL ISSUE ORIGINAL ISSUE tas i e ORIGINAL ISSUE Bleed i taU ect E MU tn ORIGINAL ISSUE 17 Ne ll ener steel E ORIGINAL ISSUE ORIGINAL ISSUE D pM Tr ORIGINAL ISSUE PSU ORIGINAL ISSUE MC CT E ORIGINAL ISSUE co KOMMEN ORIGINAL ISSUE nhs a CER ORIGINAL ISSUE 297 MASON Me E CONDERE ORIGINAL ISSUE ORIGINAL ISSUE 12 22 2006 24 003900 This POH AFM effective with S N 31 0001 THRU 31 INTRODUCTION co ORIGINAL ISSUE SERERE ERE ER TERRENAE ORIGINAL ISSUE PRU ORIGINAL ISSUE e d LAU ER E En ORIGINAL ISSUE MEME RERO ET ORIGINAL ISSUE HM S CS ORIGINAL ISSUE CA CH
148. OWABLE 150056 X 1044 Y BAGGAGE COMPARTMENT ON HAT RACK SHELF DO NOT EXCEED 120 LBS 54 4 Kg IN THIS COMPARTMENT is SEE AIRCRAFT LOADING SCHEDULE DATA DOOR JAMB FOR BAGGAGE COMPARTMENT ALLOWABLI 150056 X 1046 Y 4 AIRPLANE FLIGHT MANUAL 2 17 SECTION II MOONEY LIMITATIONS M20TN FUSELAGE INTERIOR The following placards are relevant to proper operation of the airplane and must be installed in side the fuselage at the locations specified When ordering replacement Decals and Placards refer to the Mooney Airplane Company M20TN IPC or call Mooney Service Parts Dept MAINTAIN 1 HYDRAULIC OIL BACKSIDE OF 28 VOLTS LEVEL RESERVOIR AUX PWR RECEPTACLE ONLY 150056 X 2016 Y DOOR 150056 X 2023 Y ON BOTH BATTERY BATTERIES ACCESS MUST BE PANELS INSTALLED LH amp P H FLIGHT USE AVIATORS 150056 X 2015 Y OXYGEN ONLY SEE PILOT S OPERATING HANDBOOK FOR FILLING PRESSURES INSIDE OXYGEN FILLER DOOR 150056 X 2018 Y ENGINE OIL OIL INSTALLED IN THIS ENGINE IS INSIDE ENGINE HRS OIL FILLER NEXT OIL CHANGE DUE AT DOOR USE GREASE PENCIL TACH TIME 150056 X 2001 Y AIRPLANE FLIGHT MANUAL FAA APPROVED 2 18 We ORIGINAL ISSUE 12 22 2006 MOONEY M20TN EXTERIOR SECTION II LIMITATIONS The following placards are relevant to proper operation of the airplane and must be installed on the exterior of the aircraft at the locations specified
149. R AMBER light indicates alternate induction air door is open PITOT HEAT BLUE light indicates power is applied to heater Some Foreign A C AMBER light indicates power is NOT applied to heater ALT VOLTS RED light indicates alternator output low Flashing Refer to ALTERNATOR OUTPUT LOW ALT VOLTS RED light indicates over voltage and Alt Steady field C B tripped Refer to ALTERNATOR OVER VOLTAGE START POWER RED light indicates switch or relay is engaged and starter is energized Flight should be terminated as soon as practica ble Engine damage may result This is nor mal indication during engine start BOOST PUMP BLUE light indicates power to auxiliary fuel boost pump ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 3 5 SECTION III MOONEY EMERGENCY PROCEDURES M20TN GARMIN G1000 ANNUNCIATION If GARMIN 21000 GPS navigation information is not available or invalid utilize remaining op erational navigation equipment as required Ifthe POSN ERROR annunciation is displayed the system will flag and no longer provide GPS based navigational guidance The crew should revert to the G1000 VOR ILS receivers or an al ternate means of navigation other than the G1000 GPS receivers If the POSN ERROR annunciation is displayed in the enroute oceanic terminal or initial ap proach phase of flight continue to navigate using the GPS equipment or revert to an alternate means of navigatio
150. RE TAKEOFF Taxi Checklist CECI eMe RIS leet ae sabes Complete ob sent Set Fullest Tank Engine Runup OIL TEMPERATURE CHECK ABOVE 100 F Throttle Im EIE 1700 RPM Magneto Switch 2 9 UE uM NERA L POSITION DUC 25 RPM drop minimum 150 RPM drop max EGTs should rise Magneto Switch 2 22 exi d ipid eL LP eI R POSITION 25 RPM drop minimum 150 RPM drop max 50 RPM difference between and R RP Tue uat tUe CE LEE be AE EGTs will rise Magneto Switch euh EpL Ep ous dk pete enna aa BOTH EGTs should drop Propeller CHECK OPERATION Cycle from high to low RPM two to three times Erigirie Instr ments t ea tee poete DERE CHECK Annu nclator pe aceite leis ie eal eae TEST Throttle d nu oS RE ER RAE EOM C E PR ee e Ged SET TO IDLE Standby Alternator Preflight Check Will Not Show A Charge Until Approximately 2000 rpm Alt Field Switch EE CROIRE Tex ieri RHET OFF nr Verify red ALT VOLTS light illuminates Stdby Alt Emerg Bus ON d peu tentat Verify amber Emerg Bus light illuminates E Verify positive charge on battery ammeter
151. RI Y de 3 19 AIR DATA COMPUTER ADC FAILURE 3 19 ERRONEOUS OR LOSS OF ENGINE AND FUEL DISPLAYS 3 20 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL Qe 3 1 SECTION III MOONEY EMERGENCY PROCEDURES M20TN TABLE OF CONTENTS cont d TITLE SECTION ERRONEOUS OR LOSS OF WARNING CAUTION ANNUNCIATORS 3 20 LANDING GEAR WERE RAE TAa DR ree 3 20 FAILURE OF LANDING GEAR TO EXTEND ELECTRICALLY 3 20 FAILURE OF LANDING GEAR TO RETRACT 3 21 GEAR FAILS TO RETRACT GEAR WARNING VOICE ALERT SOUNDING 3 21 WHEN READY TO EXTEND LANDING GEAR 3 21 GEAR FAILS TO RETRACT GEAR WARNING VOICE ALERT DOES NOT SOUND 3 21 WHEN READY TO EXTEND LANDING GEAR AT NEXT LANDING 3 21 OXYGEN etit ete orat int ok fev oie Pelee d 3 21 ALTERNATE STATIC SOURCE 3 21 UNLATCHED DOORS IN FLIGHT 3 22 GABIN DOOR t beter DP E 3 22 BAGGAGE DOOR 3 22 T ot 3 22 INADVERTENT ICING ENCOUNTER
152. RPLANE FLIGHT MANUAL 4 10 5 SECTION X MOONEY SAFETY INFORMATION M20TN We urge all pilots to be thoroughly familiar with and use the information in this manual ADVISORY INFORMATION Airmen can subscribe to services to obtain FAA NOTAMS and Airman Advisories and these are also available at FAA Flight Service Stations NOTAMS are documents that have infomation of a time critical nature that would affect a pilot s decision to make a flight for example an airport closed terminal radar out of service enroute navigational aids out of service etc GENERAL INFORMATION ON SPECIFIC TOPICS FLIGHT PLANNING FAR Part 91 requires that each pilot in command before beginning a flight familiarize himself with all available information concerning that flight pilots are urged to obtain a complete preflight briefing This would consist of weather local enroute and destination plus alternates enroute navaid information Also airport runways ac tive length of runways takeoff and landing distances for the airplane for conditions expected should be known The prudent pilot will review his planned enroute track and stations and make a list for quick ref erence It is strongly recommended a flight plan be filed with Flight Service Stations even though the flight may be VFR Also advise Flight Service Stations of changes or delays of one hour or more and remember to close the flight plan at destination The pilot must be completely familiar w
153. RS 77 1 CUBIC FT CAPACITY FIGURE 7 13 OXYGEN DURATION CHART 77 1 CU FT The oxygen duration chart Fig 7 12 or Fig 7 13 should be used in determining the usable duration in hours of the oxygen supply in the airplane for the chosen cruising altitude The fol lowing procedure outlines the method of finding the duration from the chart 1 Note the available oxygen pressure shown on the pressure gauge 2 Locatethis pressure onthe scale onthe leftside ofthe chart Then go acrossthe charthorizon tally to the right until intersecting the diagonal line which represents the number of persons on board From that intersection drop vertically down to the heavy line marked 30 000 ft AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 86 Qe SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION 3 From this point on the heavy line follow the trend of the curved lines down to the horizontal line representing cruise altitude Then drop vertically downtothe bottom ofthe chart and read the duration in hours given on the scale 4 As an example ofthe above procedure referto Figure 7 12 1400 PSI of pressure will safely sustain the pilot and one passenger for 4 hours and 55 minutes at 28 000 ft however cruis ing at 20 000 ft would permit an oxygen duration of 7 hours and 55 minutes Light crew loads and relatively low altitudes will permit oxygen durations off the chart Such dura tions can be calculated by determini
154. RSPEED KIAS ERROR 0 4 EXAMPLE 20 5 GIVEN IAS 80 KNOTS As FIND CAS 79 KNOTS 0 7 0 8 04 The minus sign indicates subtraction of the given numbers from KIAS to obtain the 1 1 corrected airspeed 1 2 1 3 1 4 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 10 4 SECTION V M20TN PERFORMANCE AIRSPEED CALIBRATION PRIMARY STATIC SYSTEM POWER OFF 33 FLAP GEAR DOWN Air Speed Calibration Primary Static System Power Off 33 Flap Gear Down SPEED FOR SAFELY LOWERING FLAPS 0 x a 0 lt tc m l lt o x KNOTS INDICATED AIRSPEED KIAS KCAS ERROR 0 7 EXAMPLE 59 0 6 GIVEN IAS 80 KNOTS 64 0 5 FIND CAS 80 KNOTS 70 0 5 75 0 4 80 85 80 95 The minus sign indicates subtraction of the given numbers from KIAS to obtain the 100 corrected airspeed 105 110 115 120 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL wd 5 11 SECTION V MOONEY PERFORMANCE M20TN AIRSPEED CALIBRATION ALTERNATE STATIC SYSTEM GEAR amp FLAPS DN 339 KIAS NOTE The minus sign indicates subtraction of the given numbers from KIAS to obtain the corrected airspeed CONDITIONS Power ON Storm Window amp Vents CLOSED Heater amp Defroster ON or OFF AIRPLANE FL
155. SSUE 12 22 2006 AIRPLANE FLIGHT MANUAL SECTION IV MOONEY NORMAL PROCEDURES M20TN Wing Flap and Attach Points INSPECT Control Linkages eM ehe EG INSPECT 10 Baggage Door Area Baggage DOOF e a aa VERIFY SECURED DEUM ME pe LA VERIFY inside handle is properly secured Dido pet Eom termes teet Re quite CHECK outside handle operation 11 Return to Cockpit Master Rocker 5 BEFORE STARTING CHECK Prerlight Inspectlon xmi HERE Lu n RR Complete Seats Seat belts Shoulder Harness 1 occupant per restraint Adjust and Secured Magneto Starter Switch OFF Master SWILCEI e p Alternator Field Switch E DES Fuel Boost Pump Switches OFF Circuit Breaker Switches Check All In Rocker Switches eae ek eR Reve a e x E GU Ue a e Eel aes OFF Alternate Static Source isses ee a edd ead Push OFF Throttle Ren er e e RR Closed Propeller 2 nia
156. SSUE 2 9 Dua NM ORIGINAL ISSUE LP PPP ORIGINAL ISSUE I de ORIGINAL ISSUE E MEE e RI ORIGINAL ISSUE ORIGINAL ISSUE gud ut dure ci a wanes Mendon ae td rode tee Mr ORIGINAL ISSUE Oe ire fe IE ORIGINAL ISSUE ol See WE eae NE ORIGINAL ISSUE BUEN fh ORIGINAL ISSUE pes ORIGINAL ISSUE ac eme A Rate RO n prn A e Pre f a eoe ce fe d ORIGINAL ISSUE Oed uu E Acad EA rab S ORIGINAL ISSUE ORIGINAL ISSUE 12 22 2006 POH AFM POH 003900 4 This POH AFM effective with S N 31 0001 THRU 31 INTRODUCTION m ORIGINAL ISSUE AREE RE E A A ORIGINAL ISSUE c MH PLE PR ORIGINAL ISSUE RU UU RU E En ORIGINAL ISSUE MPO ER Rey ET ORIGINAL ISSUE nt cary ae cite at ORIGINAL ISSUE MEME E ORIGINAL
157. The MFD display must be operated in PFD reversionary mode by depressing the reversionary button on the Audio Panel When operating in reversionary mode the system is limited to DAY VFR operations only 3 f inoperative for unoccupied seat s seat s must be placarded DO NOT OCCUPY 4 Only required when the operating rules require use of oxygen 5 When required by the appropriate regulations a QI AIRPLANE FLIGHT MANUAL FAA APPROVED 2 10 A ORIGINAL ISSUE 12 22 2006 SECTION II M20TN LIMITATIONS TYPES OF OPERATION The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135 1 Day V F R 2 Night V F R 3 Day I F R 4 5 Non Icing GENERAL G1000 System 1 The GARMIN G1000 Cockpit Reference Guide for the M20TN Series aircraft P N 190 00450 01 Revision A or later approved revision must be immediately available to the flight crew 2 The GARMIN G1000 must utilize the following or later FAA approved software versions SYSTEM STATUS PAGE SOFTWARE PART NUM The database version is displayed on the MFD power up page immediately after system pow er up and must be acknowledged The remaining system software versions can be verified on the AUX group sub page 5 AUX SYSTEM STATUS 3 IFR enroute oceanic and terminal navigation predicated upon the G1000 GPS Receiver is prohibited unless the pilot verifies
158. The electrical extension or retraction system will not operate if the manual extension lever is not properly positioned down refer to Emergency Extension System section ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 24 7 15 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN CAUTION Never rely on airspeed safety switch to keep landing gear down during taxi take off or landing Always make certain that landing gear switch is in down position during these operations WHEEL BRAKES Main gear wheels incorporate self adjusting disc type dual puck hydraulic brakes The pilot s rudder pedals have individual toe actuated brake cylinders linked to the rudder pedals Depress ing both toe pedals and pulling parking brake control on console sets the brakes Push parking brake control forward to release brakes It is not advisable to set parking brake when brakes are overheated after heavy braking or when outside temperatures are unusually high Trapped hy draulic fluid may expand with heat and damage the system Wheel chocks and tie downs should be used for long term parking EMERGENCY EXTENSION SYSTEM A manual emergency gear extension mechanism is provided to allow emergency lowering of landing gear The control mechanism is located between and aft of pilot and co pilot seats The RED lever must be released and pulled up rotated aft to engage the manual emergency exten sion mechanism The mechanism has a spring retracted pul
159. VOLTAGE Alternator warning light illuminated steady and Alternator Field circuit breaker tripped Alternator Field Circuit Breaker RESET If circuit breaker will not reset the following procedures are required 1 Reduce electrical load as required to maintain essential systems 2 Continue flight and LAND when PRACTICABLE to correct malfunction NOTE The only source of electrical power is from the selected battery Monitor battery voltage min 18V and switch to other battery when necessary ALTERNATOR OUTPUT LOW Alternator annunciator warning light flashing Reduce electrical load If annunciator light still flashes Alternator Field Swit alot duals teeth eH e ete REG ANC OFF 1 Reduce electrical load as required to maintain essential systems 2 Continue flight and LAND when PRACTICABLE to correct malfunction NOTE The only source of electrical power is from the selected battery Monitor battery voltage min 18V and switch to other battery when necessary Battery endurance will depend upon battery condition and electrical load on battery If one bat tery becomes depleted switch to other battery ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 3 17 SECTION III MOONEY EMERGENCY PROCEDURES M20TN ALTERNATOR FAILURE If the Main Alternator fails indicated by the Master Warning ALT VOLTS flashing Perform the Standby
160. Velcro at tachment loose and slide seat cover UP and OFF frame Fold the seat backs the rest of the way down Store the cushions as desired Reverse the procedure to re install Seat back frames may also be removed for additional space To remove frame fold rear seat back forward pull Velcro attachment loose and slide seat cover UP and OFF frame the lock pin on the left side of each frame then pull seat frame from pivot rods Pull seat back release handle UP and push pivot rods forward amp down into seat cushion cavity Reverse the procedure to re install Both rear seats can be folded down and or removed together or independent of each other The storage area located aft of the top of the aft baggage compartment bulkhead hat rack is restricted to 10 pounds 4 5 Kg AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 16 4 SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION FIGURE 7 3 CARGO RETENTION TYPICAL CARGO RESTRAINT Cargo tie down rings clevis pins are to be inserted into holes provided in web of front seat rails The cargo belts attach to these rings and to standard seat belt harness to retain cargo Refer to Figure 7 3 for typical restraint CAUTION Proper loading and retention of cargo is mandatory See Loading Computation Graph SECTION VI SINGLE POINT ADJUSTMENT SEAT BELT STD SEAT BELT REEL FIGURE 7 4 INERTIAL REE
161. a and magnetic variation to determine pitch and roll attitude sideslip and heading Operation is pos sible in a degraded mode if the system loses any of these inputs but the AHRS must have at leastthe ADC or GPS inputto function Status messages alertthe crew oftheloss of any ofthese inputs The AHRS will align while the aircraft is in motion but will align quicker if the wings are kept level during the alignment process The Air Data Computer ADC provides airspeed altitude vertical speed and air temperature to the display system In addition to the primary displays this information is used by the FMS and TIS systems Engine instruments are displayed on the MFD Discrete engine sensor information is processed by the GARMIN Engine Airframe GEA sub system When an engine sensor indicates a value outside the normal operating range the legend will turn yellow for caution range and turn red and flash for warning range The G1000 also interfaces to the S TEC 55x autopilot and repeats the autopilot mode annuncia tors on the G1000 PFD This provides easy viewing of the autopilot operating mode and status but remains a supplemental display of autopilot operating modes The GDL 69 is remote sensor that receives broadcast weather data from a service of XM Satellite Radio and delivers the data to to the G 1000 MFD Highly reliable near real time weather information is transmitted to the aircraft via XM Satellite Radio XM WX Satellite Wea
162. able for download and printing from the Mooney Airplane Company website www mooney com Avionics and Navigation Systems information should be obtained from the applicable manufac turers Engine information should be obtained from Teledyne Continental Motors P O Box 90 Mobile AL 36601 USA Telephone 251 438 3411 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL di 8 3 SECTION VIII MOONEY HANDLING SERVICE AND MAINTENANCE M20TN GROUND HANDLING TOWING For maneuvering the aircraft in close quarters in the hangar or on the ramp use manual tow bar furnished with the aircraft loose equipment The tow bar attaches to the nose gear crossbar move the aircraft providing the ground surface is relatively smooth and the tires are properly inflated When no tow bar is available or when assistance in moving the aircraft is required push by hand 1 On wing leading edges and 2 On inboard portion of propeller blades adjacent to propeller hub Towing by tractor or other powered equipment is NOT RECOMMENDED CAUTION Exercise care not to turn the nose wheel past its normal swivel angle of 11 Left or 13 Right of center Exceeding the turn limits shown on the turn indicator may cause structural damage TIE DOWN As a precaution against wind damage always tie down the aircraft when parked outside Re movable wing tie down eye bolts supplied with the loose equipment screw into wing recep
163. ados destroy nearly everything in their path on the ground A roll cloud ahead of a squall line or thunderstorm is visible evidence of violent turbulence how ever the absence of a roll cloud should not be interpreted as denoting the lack of turbulence ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 10 7 SECTION X MOONEY SAFETY INFORMATION M20TN FLIGHT IN TURBULENT AIR Even though flight in severe turbulence is to be avoided flight in turbulent air may be encoun tered under certain conditions Flying through turbulent air presents two basic problems to both of which the answer is PROPER AIRSPEED On the one hand if you maintain an excessive airspeed yourun the risk of structural damage or failure on the other hand if your airspeed is too low you may stall If turbulence encountered in cruise or descent becomes uncomfortable to the pilot or passengers the best procedure is to reduce speed to the maneuvering speed which is listed inthe Limitations Section ofthe FAA Approved Airplane Flight Manual and Pilots Operating Handbook This speed gives the best assurance of avoiding excessive stress loads and atthe same time providing margin against inadvertent stalls due to gusts Beware of overcontrolling in attempting to correct for changes in altitude applying control pres sure abruptly will build up G forces rapidly and could cause damaging structural stress loads You should watch particularly your angle of bank making turns as
164. ady EMERG BUS light will illuminate AMBER when EMERG BUS is selected ON 18 BOOST PUMP BLUE when the Electric Fuel Boost Pump is selected ON SWITCH PANELS amp ANNUNCIATOR PANELS MAY VARY WITH AIRCRAFT GROUND CONTROL NOSE GEAR STEERING Nose gear steering system consists of a steering horn on the nose gear leg linked to the rudder pedals by push pull tubes Rudder pedal action steers the nose wheel Gear retraction relieves the rudder control system of its nose wheel steering and centers wheel to permit retraction into the nose wheelwell Minimum turning radius on the ground is 40 feet 12 0 m to the right and 48 feet 14 4 m to the left Adjustable steering stops have been incorporated on nose gear leg as sembly CAUTION The nose wheel must not be swivelled beyond 11 left or 13 right of center To exceed these limits may cause structural damage TAXIING AND GROUND HANDLING The aircraft can be easily taxied with minimum use of brakes Minimum turning radius is 40 ft 12 0 m right amp 48 ft 14 4 m left without use of brakes A MANUAL towbar is provided to ground handle aircraft Care must be used to not swivel nose wheel beyond 13 right or 11 left from center Adjustable steering stops are incorporated on nose gear leg assembly CAUTION Exceeding steering swivel angle limits may cause structural damage LANDING GEAR CONSTRUCTION Landing gear legs are constructed of chrome molybdenum tu
165. affected slightly when alternate static source is used See Charts in SECTION V 33 PARKING BRAKE CONTROL Depress brake pedals and pull parking brake control to set parking brake Push parking brake control in to release parking brake 34 CABIN VENT CONTROL Fresh Air Pull cabin vent control aftto open valve in mixing box connected to cabin air inlet vent located on the right side ofthe airplane Optimum use of cabin vent control is described in the Cabin Envi ronment Section 35 CABIN HEAT CONTROL Pull cabin heat control to turn cabin heat on To lower cabin temperature cabin heat control is pushed forward toward the OFF position Optimum use of cabin heat control is described in the Cabin Environment Section 36 DEFROST CONTROL Pull defrost control to decrease air flow to lower cabin area and increase air flow to windshield ducts in the front of glareshield area Optimum use ofthe defrost control is described in the Cabin Environment Section ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 7 11 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN 37 MIC JACK Hand Held Microphone If installed Plug hand held microphone jack into this plug and place microphone in holder located on front of lower console 38 TRIM CONTROL WHEEL Rotating trim control wheel forward lowers nose during flight rearward rotation raises nose of aircraft during flight If optional electric trim system is installed push
166. aker opens to produce a high voltage surge in the secondary coil The spring action permits the latch plate magnet and breaker to be delayed through a lag angle of 30 degrees of drive gear rotation during the engine cranking period Two lobes on the breaker cam produce two sparks per revolution of the drive shaft After engine is running counter weights hold the latch pawls away from the stop pins and the magneto shaft is driven at full advance The engine firing order is 1 6 3 2 5 4 Ignition harnesses are connected to the magnetos so right magneto fires the upper plugs on the right side and lower plugs on the left The left magneto fires the upper plugs on the left and lower plugs on the right The magneto cases spark plugs harnesses and connections are shielded to prevent radio interference ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 7 21 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN AIR INDUCTION SYSTEM The primary engine air induction system draws air from the upper cowling plenum through the engine cooling inlets The air passes through a filter and is split to provide air to the left and right turbo The standard air filter is cleanable and must be serviced at 100 hour intervals or if the air craft encounters rain in flight Refer the maintenance manual for instructions AIR INLET AIR INLET FRONT OF AIRCRAFT UPPER COWL PLENUM FUEL CONTROL UNIT ENGINE INDUCTION AIR SYSTEM INTERCOOLER HH H31
167. al 593 6 Lbs 386 1 Li 266 4 Kg Sta 49 23 363 17 87 125 cm Baggage Max 120 Lbs 54 4 Kg 11 70 9 Sta 101 5 257 8 cm 10 15 Obtain the moment 1000 value for each seat position FWD MID or AFT from loading computation graph CONTINUE PROBLEM FORM ON NEXT PAGE AIRPLANE FLIGHT MANUAL 2 ORIGINAL ISSUE 12 22 2006 6 8 Hat Rack Max 10 Lbs 4 54 Kg Sta 126 0 320 SECTION VI M20TN WEIGHT AND BALANCE PROBLEM FORM um A m E PROBLEM WEIGHT MOMENT WEIGHT MOMENT Kg Kg cm Ib in g cm 1 1 1000 1000 Lbs 1000 1000 Loaded A C Weight Takeoff at Max Weight A C will have to 1528 190 2 burn off 168 Lbs fuel before normal landing is accomplished 3368 165 0 Required Fuel Burn Off 84 3 32 Gals 121Li 5 82 Lbs Gal MAXIMUM LANDING WEIGHT 1452 180 6 of A C 3200 156 7 Refer to Center of Gravity Moment Envelope to determine whether your A C loading is acceptable CAUTION DO NOT LAND A C WHEN OVER 3200 LBS EXCEPT IN AN EMERGENCY SITUATION CAUTION Pilot is responsible for cargo loaded in rear seat area with seat backs folded down Cargo Center of Gravity location varies with total weight loaded Compute CG value when cargo is loaded LOADING COMPUTATION FORM LOAD MOMENT 1000 Kg cm mm Kg LBS 100 0 150 0 200 0 250 0 300 0 350 0 I S gt 15 20 25 30 MOMENT
168. al baffles to control air direction Hot air off the engine exits the cowl thru lower cowl openings located on either side of engine lower cowl immediately for ward of the firewall ORIGINAL ISSUE 12 22 2006 8 AIRPLANE FLIGHT MANUAL 7 23 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN ENGINE STARTING SYSTEM Engine starting is provided by a 24 volt starter The starter engages the drive shaft with a spring clutch Avoid manually turning the propeller backwards as it may damage the clutch A starter engaged warning light START POWER is incorporated in the annunciator panel Ignition is provided by an impulse coupled magneto The engine firing order is 1 6 3 2 5 4 The ignition harnesses are connectedto the magnetos so the right magneto fires the upper plugs onthe right side and lower plugs on the left The left magneto fires the upper plugs on the left and the lower plugs on the right ACCESSORIES EXHAUST GAS TEMPERATURE PROBE The exhaust gas temperature EGT probe measures exhaust gas temperature as it exits the exhaust valves into the exhaust manifold The EGT probe varies electrical current milliamps based on exhaust gas temperature and displays this data on the Garmin GDU 1040 Multi Func tion Display TURBINE INLET TEMPERATURE TIT The TIT Turbine Inlet Temperature indicator displays the temperature at the turbine inlet in de grees Fahrenheit A green bar indicates Normal operating range of 1000 to
169. an aural tone will be heard Selecting the Alert button will allow the flight crew to see additional information regarding the alert message Trend vectors are shown on the airspeed and altimeter displays as a magenta line predicting 6 seconds atthe current rate The turn rate indicator also functions as a trend indicator on the com pass scale The PFD can be displayed in a composite format for emergency use by pressing the DISPLAY BACKUP button on the audio panel In the composite mode the crew alerting function remains operative but no map functions are available The Multi Function Display MFD typically displays engine data maps terrain traffic and to pography displays and flight planning and progress information The display unit is identical to the PFD and contains the same controls as previously listed The audio panel contains traditional transmitter and receiver selectors as well as an integral intercom and marker beacon system The marker beacon lights appear on the PFD In addition a clearance recorder records the last 2 gt minutes of received audio Lights above the selections indicate what selections are active Pressing the red DISPLAY BACKUP button on the audio panel causes both the PFD and MFD to display a composite mode ORIGINAL ISSUE 12 22 2006 8 AIRPLANE FLIGHT MANUAL 7 5 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN The Attitude and Heading Reference System AHRS uses GPS rate sensors air dat
170. aning readjustthrottle and continue leaning until peak TIT is attained Note peak TIT and slow ly richen mixture until TIT indication is 50 F RICH OF PEAK Re adjust throttle or RPM as re quired AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 2 A MOONEY SECTION V M20TN PERFORMANCE Best Economy Best Economy mixture is desirable for maximizing range and minimizing fuel cost Best Economy is operated 50 F lean of peak TIT The engine may be leaned up to 100 F lean of peak however the fuel economy generally doesn t improve beyond 50 F lean of peak Lean of peak operation is dependenton all cylinders running at nearly equal EGT The first cylin der to reach an over lean condition will cause the engine to run rough If at anytime during lean of peak operation the engine begins to run rough the pilot should immediately richen the mixture If a smooth running engine cannot be attained at 50 F lean of peak maintenance action will be required to restore balanced fuel flow to the cylinders and the pilot should choose an alternate mixture setting and revise the flight plan accordingly The pilot must follow the proper order for changing the power settings noted below and in SECTION IV when transitioning back to rich operation or a higher power setting Best Economy Procedure Upon attaining level flight at cruise altitude set the manifold pres sure and RPM as desired not exceeding 30 5 inHg Slowly move the mixture control toward lean while
171. ase engine RPM Control is a vernier type and fine adjustments of RPM can be obtained by turning knob clockwise to increase RPM and counter clockwise to decrease RPM Knob should not be turned IN any closer than 030 to 060 to panel nut face 30 MIXTURE CONTROL Mixture control allows pilot to adjust the fuel air ratio mixture of the engine Push control for ward to enrich mixture Pull control full aftto close idle cut off shutting down engine Control is a vernier type and fine adjustments of mixture can be obtained by turning knob clockwise to enrich mixture and counterclockwise to lean Knob should not be turned IN any closer than 030 to 060 to panel nut face 31 WING FLAP SWITCH Flap switch on console operates the electrically actuated wing flaps The flap switch incorpo rates a pre select feature for TAKEOFF and FULL DOWN positions Move switch down to first detent position to obtain TAKE OFF flaps 109 Move switch to full down position to select FULL DOWN flaps 339 When flap switch is moved UP to either TAKEOFF position or FULL UP posi tion the flaps will retract to the selected position CAUTION Positioning Flap Switch to the UP position retracts the flaps completely 32 ALTERNATE STATIC SOURCE VALVE Pull alternate static source valve full aft to change source of static air for the altimeter airspeed and vertical speed indicator from outside of aircraft to cabin interior Air speed and altimeter readings are
172. ate of flow for the altitude without any manual adjustments Oxygen Supply Control Knob ON Face Mask Hose Flow Indicator CHECK D EN Oxygen is flowing if the indicator is being forced toward the mask Delivery Hose UNPLUG from outlet when discontinuing use of oxygen esc a Pe This automatically stops flow of oxygen from that outlet Oxygen Supply Control Knob OFF PITT When oxygen is no longer required AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 Pe di SECTION IV M20TN NORMAL PROCEDURES WARNING Proper oxygen flow is critical to pilot passenger safety especially at altitudes above 20 000 ft MSL It is important to closely monitor the face mask hose flow indicator to ensure oxygen is constantly flowing to the mask A GREEN indica tion on the flow indicator denotes proper oxygen flow Always place the flow indi cator in a position where it is in the normal scan area of the cockpit Refer to duration chart Fig 7 12 amp Fig 7 13 SECTION VII for safe operational quantities DESCENT CAUTION Above 12 000 ft the minimum manifold pressure is 15 in Hg and the minimum RPM is 2 200 Do not pull the throttle back to idle without leaning mixture appro priately above 12 000 ft The lack of manifold pressure at altitude with
173. ation of 1 4 inch or more on the airframe be prepared for a significant increase in aircraft weight and drag This will result in significantly reduced cruise and climb performance and higher stall speeds Plan for higher approach speeds requiring higher power settings and longer landing rolls CAUTION Stall warning system may be inoperative NOTE The defroster may not clear ice from windshield If necessary open pilot s storm window for visibility in landing approach and touchdown With ice accumulations of 1 inch or less use no morethan 10 wing flaps for approach and land ing For ice accumulation of 1 inch or more fly approaches and landing with flaps retracted to maintain better pitch control Fly approach speed at least 15 knots faster than normal expect a higher stall speed resulting in higher touchdown speed with longer landing roll Use normal flare and touchdown technique Missed approaches SHOULD BE AVOIDED whenever possible because of severely reduced climb performance If a go around is mandatory apply full power retract landing gear when ob stacles are cleared maintain 90 KIAS and retract wing flaps AVOID FURTHER ICING CONDITIONS ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 3 23 SECTION III MOONEY EMERGENCY PROCEDURES M20TN EMERGENCY EXIT OF AIRCRAFT CABIN DOOR PULL latch handle AFT OPEN door and exit aircraft BAGGAGE COMPARTMENT DOOR Auxiliary Exit Release Pull UP rear seat back la
174. ator appears treat itas if the condition exists Refer to the POH AFM Emergency or Abnormal procedures or the procedures contained in this AFMS 2 If a display indicates an abnormal condition but no annunciator is present use other system information such as engine displays fuel quantity and flow to determine if the condition ex ists If it cannot be determined that the condition does not exist treat the situation as if the condition exists Refer to the POH AFM Emergency or Abnormal procedures or the proce dures contained in this AFMS LANDING GEAR FAILURE OF LANDING GEAR TO EXTEND ELECTRICALLY pma e pu e a 140 KIAS or less Landing Gear Actuator Circuit Breaker PULL Landing Gear Switch DOWN Gear Manual Emergency Extension Mechanism LATCH FORWARD LEVER BACK va duisi mt oe wn dunt LE e to engage manual extension mechanism NOTE Slowly pull T handle 1 to 2 inches 2 5 to 5 1 cm to rotate clutch mechanism and allow it to engage drive shaft PULL 12 to 20 times cue te M race Loss DE OUR pe and RETURN until gear is down and locked A er eer GEAR DOWN light ILLUMINATED STOP when resistance is felt Visual Gear Down Indicator CHECK ALIGNMENT itae tate by viewing from directly above indicator CAUTION Continuing to pull on T
175. ator shutoff valve attached to the cylinder automatically reduces cylinder pressure to the delivery pressure required for operating altitude The oxygen cylinder filler valve is located under a spring loaded door aft ofthe baggage door A pilot s oxygen panel contains a cylinder pressure gauge on the pilot s arm rest effectively a quantity gauge control knob below arm rest which is mechanically connected to the shut off valve at the cylinder The supply of oxygen can thus be shut off from the cockpit when not required When the controlis inthe ON position sufficient oxygen flow is available at the maxi mum airplane operating altitude see Section Limitations while at lower altitudes the reducing valve automatically economizes the flow to conserve oxygen for longer duration or for future availability without requiring any action by the pilot See Fig 7 12 or Fig 7 13 Four oxygen outlets are provided in the overhead panel between the pilot s and co pilot s seat for the convenience of all occupants Oxygen flows from the outlets only when a mask hose is connected Four partial re breathing type masks are provided each with vinyl plastic hoses and flow indicators The three passenger masks are ofthe disposable type The pilot s maskis a per manenttype with a built in microphone for ease of radio communication while using oxygen To usethe mask microphone connect its lead to the microphone jack located left of the instru
176. b Pre flight inspection ofthe propeller blades should include in addition to the foregoing an occa sional wiping with an cloth soaked in kerosene NEVER USE AN ALKALINE CLEANER ON THE BLADES Your Mooney Service Center will answer any questions you may have concerning blade repair and inspection EXTERIOR CARE As with any paint applied to a metal surface an initial curing period is necessary for developing the desired qualities of durability and appearance Therefore DO NOT APPLY WAX TO THE NEW AIRCRAFT EXTERIOR UNTIL TWO OR THREE MONTHS AFTER DELIVERY Wax sub stances will seal paint from the air and prevent curing Wash the exterior to prevent dirt from working into the curing paint Hold buffing to a minimum until curing is complete and there is no danger of disturbing the undercoat CAUTION Before washing the exterior be certain the brake discs are covered a pitot cover is in place and all static air buttons are masked off ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL di 8 9 SECTION VIII MOONEY HANDLING SERVICE AND MAINTENANCE M20TN Remove grease or oil from the exterior by wiping with a cotton cloth saturated in kerosene Flush away loose dirt and mud deposits before washing the exterior with an aircraft type washing compound mixed in warm water Use soft cleaning cloths or a chamois and USE ONLY MILD LIQUID TYPE DETERGENTS avoid harsh or abrasive detergents that might scratch or corrode the surface It is esse
177. bee ee Rr C e RR RENE RE e 2 9 OPERATING LIMITATIONS 2 9 KINDS OF OPERATION 2 9 KINDS OF OPERATION EQUIPMENT LIST 2 10 TYPES OF OPERATION rari te e nt 2 11 GENERAL nre tex a a api ots 2 11 G1000 SYSTEM eera Rabe SE Tec dps 2 11 ADVISORY MESSAGES 2 13 DECAES amp PLACARDS attend Re eC Uere Ru ER 2 14 CABIN INTERIOR Roe eee ORBE ect s 2 14 FUSEEAGE INTERIOR Sb neo mx eg s 2 18 EXTERIOR 5 iie ree Ee ee i a t oce n tele le be b 2 19 FAA APPROVED wd AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 2 1 SECTION II MOONEY LIMITATIONS M20TN BLANK AIRPLANE FLIGHT MANUAL p 2 2 ORIGINAL ISSUE 12 22 2006 SECTION II M20TN LIMITATIONS INTRODUCTION SECTION II includes the mandatory operating limitations instrument markings and basic plac ards necessary for the safe operation ofthe airplane its engine standard systems and standard equipment The limitations included in this section have been approved by the Federal Aviation Administra tion When applicable limitations associated with optional systems or equipment suc
178. brated at 6 0 Ib gal 0 72 Kg liter AIRPLANE FLIGHT MANUAL FAA APPROVED 2 6 We ORIGINAL ISSUE 12 22 2006 SECTION II M20TN LIMITATIONS POWER PLANT INSTRUMENT MARKINGS Power plant instrument markings and their color code significance are shown inthe table below NOTE When an indication lies in the caution range the legend for that display will change to the color of the caution range When an indication lies in the upper or lower pro hibited range the legend for that display will change to the color of the prohibited range and will begin flashing as well Red Green Red Yellow Yellow arc bar arc bar arc bar arc bar arc bar Lower Caution Normal Caution Upper prohibited range operating range prohibited range range range Manifold 120281 Oil Temp F 100 240 Turbine Inlet Temp Oil Press PSI 10 Idle 10 30 30 100 rl 100 Cold To prevent nuisance alerts during normal takeoffs the RPM data will notturn red or flash until the RPM exceeds 2540 FAA APPROVED 4 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 2 7 SECTION II MOONEY LIMITATIONS M20TN FUEL LIMITATIONS WARNING Takeoff maneuvers when the selected fuel tank contains less than 12 gallons 45 4 liters of fuel have not been demonstrated NOTE Each fuel quantity gauge is calibrated to read zero only in coordinated level flight when remaini
179. bular steel heat treated for great er strength and wear resistance Main gear leg attaching points pivot in bearing surfaces on for ward and stub spars The nose gear mounts on cabin tubular steel frame Rubber discs in all gear leg assemblies absorb shock of taxiing and landing RETRACTION SYSTEM Landing gear is electrically retracted and extended The landing gear switch operates a landing gear actuator relay Pull wheel shaped knob out and move it to upper detent to raise landing gear An Airspeed Safety Switch located on leftfuselage side adjacentto the pilot s left knee and connected to the airspeed indicator is incorporated into the electrical system to prevent landing gear retraction while on the ground and until a safe takeoff speed approximately 60 5 KTS is reached A properly rigged up limit switch will stop landing gear in its retracted position Move control knob to its lower detent to lower landing gear A properly rigged down limit switch will stop landing gear actuating motor when proper force has been exerted to hold landing gear in the down and locked position Bungee springs pre load the retraction mechanism in an overcent er position to assistin holding landing gear down A landing gear safety by pass switch override is provided next to the gear switch to allow the landing gear to retract for maintenance pur poses Depress and hold this switch to manually by pass airspeed safety switch and allow land ing gear to retract
180. condition will cause a nose up pitching condition Use of flaps should always be within the operational limits established in SECTION II The flaps are very effective in lowering landing speed and can be used to slow the aircraft to approach speeds INSTRUMENT PANEL The instrument panel has been designed to incorporate the 91000 Integrated Cockpit All Com munications Navigation Engine Instruments and System annunciations have been integrated into a custom design package specifically for the M20TN series aircraft Engine and electrical switches are located onthe leftside ofthe switch panel Nav strobe recog nition landing and taxi light switches are located on the overhead switch panel AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 4 A SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION Instrument panel lighting is provided by post lights overhead panel lights and the internally lighted G1000 Integrated Cockpit System Optimum cockpit panel lighting for night flying is achieved by using a combination of panel lights and overhead map lights NOTE The illustrations depict a standard panel configuration The location of instru ments switches and avionics may be relocated in each aircraft dependant upon the optional equipment selected by the customer and available panel space GARMIN G1000 The GARMIN G1000 Integrated Avionics System consists of a Primary Flight Display PFD a Multi Function Display MF
181. conds Oxygen Supply Control Knob if installed OFF Oxygen Pressure Gauge CHECK ORIGINAL ISSUE 12 22 2006 dio AIRPLANE FLIGHT MANUAL 4 5 SECTION IV MOONEY NORMAL PROCEDURES M20TN Verify adequate oxygen supply for trip if use of oxygen is anticipated refer to oxygen duration chart Figures 7 12 amp 7 13 SECTION VII Also check that face masks and hoses are accessible and in good condition If TKS system is installed pitot heat annunciator will illuminate AMBER when switch is ON and Pitot Heat has failed Annunciator will not be illuminated when switch is ON and system is operat ing properly 2 Right Fuselage Tailcone Oxygen Filler Access Door and Filler SECURED Battery 2 Access Panel SECURED Instrument Static Pressure Port UNOBSTRUCTED General Skin INSPECT Tailcone Empennage Access Panel SECURED Tail Tiedown Rope Chain REMOVE 3 Empennage Elevator and rudder attach points and control linkage attachments INSPECT Empennage Freeplay Vertical Horizontal INSPECT General Skin
182. d be used by all occupants when cruising above 12 500 feet It is often advisable to use oxygen at altitudes lower than 12 500 feet under conditions of night flying fatigue or periods of physiological or emotional disturbances Also the habitual and excessive use of tobacco or alcohol will usually necessitate the use of oxygen at less than 10 000 feet GAUGE PRESSURE PSI 200 YELLOW gt gt gt PLAN TO DESCEND BELOW 14 000 FT ALTITUDE RED lt lt DESCEND IMMEDIATELY TO BELOW 14 000 FT ALTITUDE 30 000 28 000 27 500 25 000 24 000 22 000 20 000 17 500 DURATION MULTIPLIER 15 000 2 4 3 3 12 500 4 4 4 51 6 7 8 9 10 11 12 13 14 15 16 OXYGEN DURATION HOURS 115 7 CUBIC FT CAPACITY FIGURE 7 12 OXYGEN DURATION CHART 115 7 CU FT 10 000 0 ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 24 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN GAUGE PRESSURE PSI PLAN DESCEND BELOW 14 000 FT ALTITUDE DESCEND IMMEDIATELY TO BELOW 14 000 FT ALTITUDE 25 000 DURATION MULTIPLIER gt 4 5 6 7 8 9 OXYGEN DURATION HOU
183. d from within the cabin and will affect flight instrument readings Correction charts in SECTION V depictthe difference between indicated and calibrated instrument readings for both primary and alternate static systems as suming zero instrument error These corrections are required to determine true airspeed The true airspeed indicated on the MFD and the backup airspeed indicator doesn t include static er ror corrections STALL WARNING SYSTEM The electrical stall warning system uses a vane actuated switch installed in left wing leading edge to energize stall warning horn located in the cabin The stall warning switch is adjusted to provide aural warning VOICE ALERT at 5 to 10 KIAS before actual stall is reached and will remain on until aircraft flight attitude is changed toward a non stalled condition NOTE Do not attempt to adjust prestall warning speed by bending the vane This part has been heat treated and cannot be bent without damaging or breaking the vane ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 24 7 33 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN OXYGEN SYSTEM An optional four place oxygen system provides supplementary oxygen necessary for continu ous flight at high altitude An oxygen cylinder is located in the equipment bay accessible through aremovable panelonthe aft wall ofthe baggage compartment or through the standard external right side panel in the tailcone A combined pressure regul
184. d until the oper ator can set his own inspection periods based on experience NOTE The required periods do not constitute a guarantee that the item will reach the period without malfunction as the aforementioned factors cannot be controlled by the manufacturer Corrosion and its effects must be treated at the earliest possible opportunity A clean dry sur face is virtually immune to corrosion Make sure that all drain holes remain unobstructed Protec AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 10 6 MOONEY SECTION X M20TN SAFETY INFORMATION tive films and sealants help to keep corrosive agents from contacting metallic surfaces Corro sion inspections should be made most frequently under high corrosion risk operating conditions such as in regions of heavy airborne salt concentrations e g near the sea and high humidity areas e g tropical regions WALK AROUND INSPECTIONS All airplane surfaces free of ice frost or snow Tires properly inflated All external locks covers and tie downs removed Fuel sumps drained Fuel quantity adequate for trip plus reserve visually checked and access doors secured Oil quantity checked and access doors secured Check general condition of airplane engine propeller exhaust stacks etc All external doors secured COCKPIT CHECKS Flashlight available Required documents on board Use the check list All internal control locks removed If installed Chec
185. data pertaining to Limitations Normal Procedures Emergency Procedures and effects on performance for certain optional equipment installed in the airplane are con tained in this section Commonly installed items of optional equipment whose function and operation do not require detailed instructions are described by Section VII The supplements are Approved by the FAA prior to incorporation into the Airplane Flight Manual ORIGINAL ISSUE 12 22 2006 4 AIRPLANE FLIGHT MANUAL 9 3 SECTION IX MOONEY SUPPLEMENTAL DATA M20TN BLANK AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 SECTION X M20TN SAFETY INFORMATION TABLE OF CONTENTS num SECTION INTRODUCTION dE RE ee Rer Y med 10 3 GENERAL eae itd ad e due oda e edet 10 4 GENERAL SOURCES OF INFORMATION 10 5 RULES AND REGULATIONS 10 5 FAR PART 39 AIRWORTHINESS DIRECTIVES 10 5 AIRMAN INFORMATION ADVISORIES AND NOTICES FAA AERONAUTICAL INFORMATION MANUAL 10 5 ADVISORY INFORMATION 10 6 GENERAL INFORMATION ON SPECIFIC TOPICS 10 6 FLIGHT PEANNING Rr ete EIE x ER UR CR Ra en a e alae 10 6 INSPECTIONS MAINTENANCE
186. ded or retracted GS KCAS KIAS KTAS Va Vie Vie Vio Vne Vno Vs V Vx W sured in the exhaust pipe manifold Expressed in F MCP MAXIMUM CONTINUOUS POWER The maximum power for take off normal abnormal or emergency operations MANIFOLD PRESSURE Pressure measured in the engine s induction system and expressed in inches of mercury Hg REVOLUTIONS PER MINUTE Engine speed ORIGINAL ISSUE 12 22 2006 4 1 9 SECTION I MOONEY GENERAL M20TN AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demonstrated The velocity of the crosswind component for which adequate control of the Crosswind airplane during take off and landing test was actually demonstrated during Velocity certification The value shown is not considered to be limiting EN Acceleration due to gravity Service The maximum altitude at which aircraft at gross weight has the capability Ceiling of climbing at the rate of 100 ft min ENGINE CONTROLS amp INSTRUMENTS TERMINOLOGY Propeller The control used to select engine speed Control Throttle The control used to select engine power by controlling MP Control Provides a mechanical linkage to the fuel injector mixture control to control the size of the fuel feed aperture and therefore the air fuel mixture It is the primary method to shut the engine down CHT Cylinder head temperature indicator used to determine that engine operat Gauge ing temperature is within manufacturer
187. deep eee 30 100 PSI Minimum DLE ONG s ete ade Die eae ates 10 PSI Maximum Allowable Cold Oil 100 PSI Oil Grades Recommended for Various Average Air Temperature Ranges Below 40 F 490 SAE 30 10W30 15W50 or 20W50 Above 409 49 SAE 50 15W50 20W50 Fuel Grade Color 100LL Blue or 100 octane Green 1 Fuel Flow Normal Operations 7 to 32 GPH 27 to 121 LPH Maximum Allowable 32 GPH 121 LPH Number of Propellers 2 2004 1 Propeller Manufacture ae ee Hartzell Propeller Hub Blade Model Number PHC J3YF 1RF F7693DF 2 Number or Blades cdot chet atten sepe 3 Propeller Diameter pn 75 In 190 5 cm abana wb ee edd deben PEE RE MU decade 76 In 193 0 cm Propeller Blade Angles 30 0 In sta PT teat 16 5 Degrees 0 2 Degrees o et nea ncn de t eR 38 0 Degrees 1 0 Degrees Propeller Operating Limits 2500 RPM 1 100LL fuel is calibrated at 5 82 Ib gal 0 69 Kg liter 100 octane fuel is cali
188. e aircraft for safe flight Data presented inthis section will enable you to carry outthis responsibility and insure that your airplane is loadedto operate within the prescribed weight and center of gravity limitations Atthe time of delivery Mooney Aircraft Company Inc provides the empty weight and center of gravity data for the computation of individual loadings The empty weight and C G gear extended as delivered from the factory is tabulated on page 6 6 when this manual is supplied with the aircraft from the factory FAA regulations also require that any change in the original equipment affecting the empty weight and center of gravity be recorded in the Aircraft Log Book A convenientform for maintain ing a permanent record of all such changes is provided on page 6 6 This form if properly main tained will enable you to determine the current weight and balance status of the airplane for load scheduling The weight and balance data entered as your aircraft left the factory plus the record you maintain on page 6 6 is all of the data needed to compute loading schedules The maximum certificated gross weight for the TCM powered M20TN is 3368 Ibs 1528 Kg for Takeoff and 3200 pounds 1452 Kgs for Landing Maximum useful load is determined by sub tracting the corrected aircraft empty weight from its maximum gross weight The aircraft must be operated strictly within the limits of the Center of Gravity Moment Envelope shown on page 6 1
189. e following systems on the non essential bus will be unpowered e Com2 e Nav2 GPS2 e All lighting on the Overhead Panel e Fuel Pumps e Autopilot Electric Trim Landing Gear Motor and Indicators Defrost Blower e WX Stormscope ADF DME DATA LINK TRAFFIC ALERT e SKYWATCH 5 TERMINATE FLIGHT AS SOON AS PRACTICABLE 6 On approach the pilot may engage the BAT circuit breaker to reestablish power to all sys tems if necessary 7 If using battery power only and the primary battery has been depleted minimum of 18 VDC the pilot may select the alternate battery using the main battery selection switch There will be no change in available equipment when changing battery sources All equipment pow ered previously will remain powered AVIONICS EMERGENCIES PFD OR MFD DISPLAY FAILURE 1 DISPLAY BACKUP button on audio panel PUSH AHRS FAILURE NOTE Failure of the Attitude and Heading Reference System AHRS is indicated by a removal of the sky ground presentation and a red X and a yellow AHRS FAIL URE shown on the PFD The digital heading presentation will be replaced with a yellow HDG and the compass rose digits will be removed The course pointer will indicate straight up and course may be set using the digital window 1 Use Standby Attitude Indicator and Magnetic compass 2 Course Set using digital window 3 LAND AS SOON AS PRACTICABLE AIR DATA COMPUTER ADC FAILURE NOTE Complete loss of the Air
190. ees 1 0 degrees FUEL Minimum Fuel Grade Color 100 LL Blue or 100 Octane Green Total Fuel Useable 89 U S Gal 386 1 liters Unusable Fuel oen EVE UD ELE 6 U S Gal 22 7 liters OIL Oil Specification or Oil Grade First 25 Engine Hours Non dispersant mineral oil conforming to SAE J1966 shall be used during the first 25 hours of flight operations However if the engine is flown less than once a week a straight mineral oil with corrosion preventative MIL C 6529 for the first 25 hours is recommended Oil Specification or Oil Grade After 25 Engine Hours Teledyne Continental Motors Specifica tion MHS 24 An ashless dispersant oil shall be used after 25 hours Oil Grades Recommended for Various Average Air Temperature Ranges Below 409 49 SAE 30 10W30 15W50 20W50 Above 409 F A49 SAE 50 15W50 or 20W50 Total Oil Capacity neria eerte Det egeo vob Ege Euer 8 Qts 7 57 liters OIDEILOE hack cate ay Ro arent ERE Ria Full Flow Oil grades specifications and changing recommendations are contained in SECTION VIII NOTE The first time the airplane is filled with oil additional oil is required for the filter oil cooler and propeller dome This oil is not drainable on subsequent oil changes Add ed oil is mixed with a few qua
191. el furnish an emergency overload break between the alternators and the power bus Since the alternator is incapable of output in excess of circuit breaker capacity atripped breaker normally indicates afault within the alternator NOTE NEVER fly the aircraft with a severely discharged battery even if you do not plan to use it Selection of a severely discharged battery in flight can cause a current in rush from the alternator and may damage on board systems The alternator field has a push pull circuit breaker to furnish an emergency break in the alterna tor field excitation circuit in the event of alternator or voltage regulator malfunction If regulator output voltage exceeds limits the warning light illuminates steadily and the alternator field circuit breaker trips Resetting the alternator field circuit breaker should reset the alternator If the circuit breaker will not reset continue flight with minimum electrical load The flight will be continued using only bat tery power caution is advised to not drain both batteries if electrical power will be required before you are able to land Land when practical to correct the malfunction NOTE The circuit breakers installed in the panel may vary depending on installed equip ment ACCESSORIES Standard electrical accessories include the starter the electric fuel pump and the stall warning horn Electrical accessories include the navigation lights anti collision strobe lights i
192. ent from above ELT is activated when the switch is the ON position ELT returns to armed the switch is inthe ARMED position 48 ALTERNATE AIR ALT AIR The alternate air valve automatically opens when the primary induction air system becomes blocked for any reason The valve may be opened manually by pulling the ALT AIR knob aft An AMBER annunciator light will illuminate when alternate air door is open 49 BATTERY SELECT SWITCH BAT 1 BAT 2 This switch allows pilot to select either battery as primary for any flight Battery 1 is normally used for operations The battery not being used is recharged through a trickle charge system It is recommended to switch batteries occasionally AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 12 4 MOONEY SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION 50 EMERGENCY BUS SWITCH Optional when Stand by Alternator is installed When Low Voltage annunciator light illuminates steady or flashing pull 70A BAT circuit breaker and PUSH EMERG BUS switch ON to bring Stand by Alternator online 51 ACCESSORY SOCKET 14 volt Used for accessories that require 14 volts to operate Maximum of 3 AMPS continuous 5 AMPS intermittent requirements 52 OPTIONAL EQUIPMENT SWITCHES 53 ICE LIGHTS SWITCH 54 TKS CONTROL PANEL 55 S TEC AUTOPILOT 56 AUTOPILOT POWER SWITCH MAP LIGHT SWITCH RHEOSTAT MIKE SWITCH ELECTRIC TRIM SWITCH if installed amp OPTIONAL AUTO PILOT SWITCHES are
193. eptacle either or both batteries may be charged The External Power receptacle can also be used for maintenance activities or to start the engine In the event of an alternator failure selecting EMER BUS will e Power the standby alternator Shed unessential loads and power Essential systems consisting of 31000 system which is comprised of the PFD MFD AHRS ADC Com1 1 GPS1 transponder audio panel and Engine Instruments An independent standby attitude indicator artificial horizon Aux Overhead Equipment Aux Panel Equipment and Ice Protection Activating the EMER BUS switch bypasses the master switch and electrically feeds the standby attitude indicator and all standby lighting using both main batteries in the event that the Standby Alternator also fails NOTE In flight NEVER deselect the BATT MASTER switch unless the EMER BUS switch is energized ESSENTIAL BUS The Essential bus is tied directly to the main aircraft battery via the non essential bus When the master switch is turned on power is immediately supplied to the Essential and non Essential busses The Essential bus provides power to the G1000 equipment and to the backup instru ments When the Emergency Bus switch is activated by the pilot the standby alternator is brought online and two relays close to power the essential bus via a secondary path The se lected main battery two main batteries are available remains online NON ESSENTIAL
194. erse weather conditions The window should not be opened in flight above 132 KIAS EMERGENCY EXITS The CABIN DOOR is the primary emergency exit from the cabin If a situation exists where a probable off airport landing will occur the door should be unlatched to prevent jamming during landing The BAGGAGE compartment access DOOR can be used as an auxiliary exit The door can be opened from the inside even though locked To open pull off small ABS cover pull out latch pin and pull Red Handle To verify re engagement of latching mechanism open outside handle fully close inside handle to engage pin into cam slide of latch mechanism insert latch pin into shaft hole to hold Red Han dle down Replace ABS cover Operate outside handle in normal method AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 18 4 SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION ENGINE GENERAL The M20TN engine is a Teledyne Continental Motors Aircraft Engine Model TSIO 550 G twin turbocharged horizontally opposed six cylinder fuel injected air cooled engine that uses ahigh pressure wet sump style oil system for lubrication There is a full flow spin on disposable oil filter The engine utilizes top air induction engine mounted throttle body and a bottom exhaust system Engine front accessories include a hydraulically operated propeller governor and a gear driven alternator Rear engine accessories include a starter gear driven oi
195. es conducted with the autopilot coupled If the CDI navi gation source is changed when autopilot is engaged in GPSS mode the S Tec 55x autopilot lateral mode will revert to wings level mode and indicate GPSS FAIL NAV mode must be manually reselected by the pilot in order to track the ILS or Localizer 7 Display of autopilot operational mode on the PFD is supplemental to the data which is present ed on the display of the S Tec 55X autopilot control unit AIRPLANE FLIGHT MANUAL FAA APPROVED 2 12 We ORIGINAL ISSUE 12 22 2006 SECTION II M20TN LIMITATIONS ADVISORY MESSAGES The G1000 Cockpit Reference Guide and the G1000 Pilot s Guide contain detailed descriptions ofthe annunciator system and all advisory messages These messages appear on the PFD for flight crew awareness The following warnings and cautions may appear in various locations on the PFD or MFD Con sultthe G1000 Cockpit Reference Guide and the G1000 Pilot s Guide for detailed descriptions of each annunciation as necessary ANNUNCIATION CAUSE Attitude and Heading Reference System is AHRS Aligning Keep Wings Level aligning Keep wings level using standby attitude indicator Display system is not receiving attitude ref erence information from the AHRS accom pci panied by the removal of sky ground pre sentation and a red X over the attitude area Display system is not receiving airspeed in put from the air data computer accompa AIRSPEED FAI
196. esult of flying in cloud or heavy snow with cold outside air temperatures 0 C or below At these temperatures very small water droplets or solid ice crystals in the air may collect and freeze on the induction air filter causing partial or total blockage of the primary engine induction system If primary induction air system blockage occurs the alternate engine induction air system will automatically open supplying engine with an alternate air source drawn from inside the cowling rather than through the air filter The alternate air system can also be manually opened at any time by pulling the control labeled ALTERNATE AIR Automatic or manual activation of the alter nate induction system is displayed in the cockpit by the illumination of the ALT AIR light in the AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 3 10 A SECTION III M20TN EMERGENCY PROCEDURES main annunciator panel When operating on the alternate air system available engine power will be less for a given propeller RPM compared to the primary induction air system This is due to loss of ram effect and induction of warmer inlet air The following check list should be used if a partial power loss due to primary induction air sys tem blockage is experienced Alteriate AIE c wees bene bate Verify OPEN annunciator light ON Manifold Pressure 1 2 inches less than normal due to warm induction air NOTE The alternate air door s
197. evel as it is lowered NOTE Individual wheels may be raised without raising entire aircraft Wheels not being raised should be chocked fore and aft SERVICING REFUELING Integrally sealed tanks in forward inboard sections of wing LH amp RH carry the standard fuel quantity With aircraft positioned on level ground service each fuel tank after flight with 100 oc tane or 100LL aviation grade gasoline The fuel tank is considered full when fuel completely cov ers bottom of standpipe The optional fuel quantity sight indicators on top of each wing tank should be used as a refer ence for partial refueling only These gauges will not indicate the tank s total capacity above 30 gallons of fuel Before filling fuel tanks when planning a maximum weight flight configuration consult the Weight amp Balance Record SECTION VI for loading data CAUTION Never use aviation fuel of a lower grade than 100 octane or 100 LL avgas Fuel samples from the sump drain of each tank should always be taken before the first flight of the day to check for water sediment or other contamination It is recommended that fuel samples be taken prior to each flight Fuel samples taken immediately after refueling may not show water or sediment due to mixing action of refueling process WARNING Allow five minutes after refueling for water and sediment to settle in tank and fuel drain valve before taking fuel samples or draining gascolator Tank sum
198. experienced on the ground This combined with loss of outside visual reference can cause vertigo False interpretations illusions result and may con fuse the pilot s conception of the attitude and position of his airplane Under VFR conditions the visual sense using the horizon as a reference can override the illu sions Under low visibility conditions night fog clouds haze etc the illusions predominate Only through awareness of these illusions and proficiency in instrument flight procedures can an airplane be operated safely in a low visibility environment Flying in fog dense haze or dust cloud banks or very low visibility with strobe lights and partic ularly rotating beacons turned on frequently causes vertigo They should be turned off in these conditions particularly at night pilots should check the weather and use good judgment in planning flights The VFR pilot should use extra caution in avoiding low visibility conditions Motion sickness often precedes or accompanies disorientation and may further jeopardize the flight STALLS SPINS AND SLOW FLIGHT Stalls and slow flight should be practiced at safe altitudes to allow for recovery Any of these maneuvers should be performed at an altitude in excess of 6 000 feet above ground level Spins may be dangerous and should be avoided In fact most airplanes are placarded against inten tional spins Spins are preceded by stalls A prompt and decisive stall recovery
199. flet 2 Revision 1 and FAA Order 8110 60 for oceanic and remote airspace operations provided it is receiving usable navigation information from the GPS receiver A separate software application for prediction of GPS navigation availability may be required for oceanic and remote op erations Refer to appropriate limitations for the airspace you are operating in to deter mine if this GPS prediction software is required Navigation is accomplished using the WGS 84 NAD 83 coordinate reference datum GPS navigation data is based upon use of only the Global Positioning System GPS operated by the United States of America ORIGINAL ISSUE 12 22 2006 1 8 4 SECTION I M20TN GENERAL SYMBOLS ABBREVIATIONS amp TERMINOLOGY GENERAL AIR SPEED TERMINOLOGY amp SYMBOLS GROUND SPEED Speed of an airplane relative to the ground KNOTS CALIBRATED AIR SPEED The indicated speed of an aircraft corrected for position and instrument error Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level KNOTS INDICATED AIRSPEED The speed of an aircraft as shown on its airspeed indicator IAS values published in this handbook assume zero instrument error KNOTS TRUE AIRSPEED The airspeed of an airplane relative to undis turbed air which is the KCAS corrected for altitude and temperature MANEUVERING SPEED The maximum speed at which application of full available aerodynamic control will not overstress the a
200. function ofthe MFD is to provide engine information mapping terrain information and for flight planning The audio panel is used for selection of radios for transmitting and listening intercom functions and marker beacon functions The primary function ofthe VHF Communication portion of the G1000 is to enable external radio communication The primary function of the VOR ILS Receiver portion of the equipment is to receive and demodulate VOR localizer and Glide Slope signals The primary function of the GPS portion of the system is to acquire signals from the GPS satellites recover orbital data make range and Doppler measurements and process this information in real time to obtain the user s position velocity and time Provided the GARMIN 21000 GPS receivers are receiving adequate and usable GPS and or VHF navigation signals it has been demonstrated capable of and meets the accuracy specifica tions for the following types of flight operations VFR IFR en route oceanic andterminal operations as well as nonprecision instrument approach GPS Loran C VOR VOR DME TACAN NDB NDB DME RNAV opera tion within the U S National Airspace System in accordance with AC20 138A Navigation in the North Atlantic Minimum Navigation Performance Specification MNPS Airspace in accordance with AC91 49 and AC 120 33 The GARMIN G1000 system meets RNP5 airspace BRNAV requirements of AC 90 96 and in accordance with AC 20 138A JAA 20 2 Lea
201. ge of subjects in this section the National Transportation Safety Board and the FAA periodically issue general aviation pamphlets concerning aviation safety and in greater detail These can be obtained at FAA Offices Weather Stations Flight Service Stations or Airport Facilities These are very good sources of information and are highly recommended for study Some of these are titled Aeronautical Information Manual 12 Golden Rules for Pilots Weather or Not Disorientation Plane Sense Weather Info Guide for Pilots Wake Turbulence Don t Trust to Luck Trust to Safety Thunderstorm TRW IFR VFR Either Way Disorientation Can be Fatal MANUFACTURER S INFORMATION See following applicable pages of information that may have been inserted AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 10 12 e
202. go the Gear System Opera tional Inspection as outlined in M20TN Service and Maintenance Manual Chapter 32 The gear warning VOICE ALERT may be checked in flight by retarding throttle with the gear up The gear warning VOICE ALERT should sound when throttle is positioned 1 4 to 3 8 inch from idle while gear is up BATTERIES The two 24 volt 10 ampere hour electrical sealed storage batteries are located in the tailcone aft of baggage compartment bulkhead accessible through left and right side tailcone access panels To service batteries remove tailcone access cover s to gain access to battery ies Check ter minals and connectors for corrosion Keep battery at full charge to prevent freezing in cold weather and to prolong service life AIRPLANE FLIGHT MANUAL 8 8 ORIGINAL ISSUE 12 22 2006 SECTION VIII M20TN HANDLING SERVICE AND MAINTENANCE CAUTION Alternator and voltage regulator operate only as a one polarity system Be sure the polarity is correct when connecting a charger or booster battery If corrosion is present flush battery shelf and mounting area with a solution of baking soda and water Keep cable connections clean and tightly fastened HYDRAULIC BRAKE RESERVOIR SYSTEM The brake system hydraulic reservoir is located on the tailcone bulkhead forward of the avionics components To service remove the left side tailcone access panel and check fluid level every 50 HOURS of operation
203. h an electric rudder trim system which allows the pilot to trim out much of the rudder force required for take off climb cruise and descent The system is a bungee type spring assembly attached to the rudder control system and driven by an electric motor The trim system is operated by a split toggle switch located above the throttle on the pi lot s panel The split switch is a safety measure that greatly reduces the possibility of a runaway trim situation Rudder force varies from negligible with trim to the far right to mild with trim set to the third segment from right Cruise setting will result in the trim indicator being slightly left of neutral A high speed descent will result in an even more left of neutral position The Rudder Trim indicator is located on the Garmin GDU 1040 Mutli Function Flight Display MFD The indi cator depicts the position right left ofthe rudder trim setting Actual trim position is shown using a blue inverted triangle The takeoff rudder trim position is shown in white ELEVATOR SYSTEM Elevator construction is essentially the same as that of the rudder Both elevators attach to the horizontal stabilizer at four hinge points Push pull tubes and bellcranks link the elevators to the control wheel A down spring located in thetailcone and a bobweight located forward ofthe con trol column help create desirable stability characteristics A factory set fixed trim tab spans the length of the elevator
204. h as autopilots are included in SECTION IX NOTE The airspeeds listed in the Airspeed Limitations chart Figure 2 1 and the Air speed Indicator Markings chart Figure 2 2 are based on Airspeed Calibration data shown in SECTION V with the normal static source If the alternate static source is being used ample margins should be observed to allow for the air speed calibration variations between the normal and alternate static sources as shown in SECTION V Your Mooney is certificated under FAA Type Certificate No 2A3 as a Mooney M20TN NOISE LIMITS The certificated noise level per 14 CFR Part 36 Appendix G Amendment 36 22 of the Federal Aviation Regulations for the Mooney M20TN with the Hartzell 3 blade propeller installed at 3368 Ibs 1528 Kg maximum weight is 78 0 dB A No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or ceptable for operation at into or out of any airport FAA APPROVED 4 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 2 3 SECTION II MOONEY LIMITATIONS M20TN AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in Figure 2 1 This calibration assumes zero instrument error 2 VSPEED KCAS KIAS REMARKS 196 194 Do not exceed this Speed speed in any op eration Maximum Structural 175 173 Do not exceed this Cruising Speed speed except in
205. hallenger Re charger Kit P N CP 99 5050 the only FAA approved re charge kit Inside are two squeeze bottles one for cleaning and one red in color for re oiling the filter element Remove the bottle containing cleaning fluid and thoroughly saturate the filter Allow the filter to soak for approximately 15 minutes DO NOT USE ANY OTHER CLEANING FLUID 5 Flush the filter with low non pressurized warm water starting from inside out After flush gent ly shake the water out of the filter and allow to air dry only DO NOT USE ANY OTHER DRY ING METHOD 6 Remove the bottle from the Re charger Kit P N CP 99 5050 containing oil red in color Begin re oiling the dry filter by applying a bead or line of red oil along the top only of each pleat ofthe filter The oil will soak into the length of each pleat It may be necessary to apply oil on filter material that has not received oil from the wicking action The entire filter medium must be covered with red oil DO NOT OVER OIL If oil drips from the filter it has been over oiled Allow the filter to drain the excess oil onto a clean rag or paper towel until the red oil stops dripping Replace gasket with a new on the frame surface to be mounted to the air box assembly 7 Re install air filter Make sure the air filter assembly is properly seated and is mounted secure ly to the filter air box assembly 8 Re install engine cowling NOTE Do not use gasoline jet fuel or caustic cleaning solutions
206. hanges the source of static air forthe altimeter air speed indicator and rate of climb from outside of the aircraft to the cabin interior When alternate static source is in use adjust indicated airspeed and altimeter readings accord ing to the appropriate alternate static source airspeed and altimeter calibration tables in SEC TION V The alternate static air source valve is located on the instrument panel below pilot s con trol wheel shaft NOTE When using Alternate Static Source pilot s window and air vents MUST BE KEPT CLOSED ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 3 21 SECTION III MOONEY EMERGENCY PROCEDURES M20TN Alternate Static PULL ON Airspeed and Altimeter Readings CHECK Calibration Tables Ref SECTION V UNLATCHED DOORS IN FLIGHT CABIN DOOR If cabin door is not properly closed it may come unlatched in flight This may occur during or just after take off The door will trail in a position approximately 3 inches 7 6 cm open but the flight characteristics of the airplane will not be affected There will be considerable wind noise loose objects in the vicinity ofthe open door may exitthe aircraft Return to the field in a normal man ner If practicable secure the door in some manner to prevent it from swinging open during the landing If it is deemed impractical to return and land the door can be closed in flight
207. hould open automatically when primary induction system is restricted If alternate air door has not opened Annunciator light OFF it can be opened manually by pulling alternate air control op ace cep EUER cec es Glee atacand INCREASE as desired Propeller re eta ees INCREASE as required pen Ue n tado beam to maintain desired cruise power setting Ref SECTION V reete etes Met ed Set a E RELEAN to desired EGT Fliglit orc CONTINUE request altitude with warmer air if able In the unlikely event that a total power loss due to primary engine induction air blockage is experienced the following checklist should be used ive nu RUE HU LIU READER YR ERU SER e BEST GLIDE SPEED 23968 1D 1528 Kg eR ILE ete DERI WEN 91 5 KIAS 3200 lb H452 kgi eae Re 89 0 KIAS 2900 1b 915 Kg 2 ax che Sete 84 5 KIAS 2600 Ib 4179 eee te Furl e e ges 80 0 KIAS Alternate ete Aco Se Manually OPEN EOW Boost eap xe ON Throttle Em UC REND NIE SET TO HALF OPEN E Deal ERG ODE FULL FORWARD Mixture PULL TO CUTOFF THEN GRADUALLY RICHEN UNTIL ENGINE STARTS Magneto Starter Switch
208. ht must be used TAKEOFF Normal Climb QUI teh 80 90 KIAS Short Field Takeoff Speed At 50 75 5 ENROUTE CLIMB GEAR and FLAPS UP Best Hate of Climb iiu In RBS kh 104 KIAS Best Angle 85 KIAS LANDING APPROACH 3200 Ibs Normal Approach Flaps 10 degrees 80 KIAS Normal Approach Flaps 33 degrees 75 KIAS Short Field Approach Flaps 33 degrees 70 KIAS BALKED LANDING 3200 Ibs Maximum Power Flaps 10 degrees 85 KIAS MAXIMUM RECOMMENDED TURBULENT AIR PENETRATION SPEED 3968 bs 1528 Kg dla ten p tede ie t dia 127 KIAS 3200 1bs 1452 t em oett e emus 123 KIAS 2900 158 1315 o Deere ne be 117 KIAS 2600 Ibs 1179 io tu UE RR E E O 111 KIAS 2400 155 1089 Kg nce apte bbb MERE DERE DOE ERI Ce doe te 106 KIAS DEMONSTRATED CROSSWIND VELOCITY Takeott or Landing stre eee Ser id tas p 18 Knots This is NOT A LIMITATION only a demonstrated number See CROSSWIND COMPONENT CHART SECTION V AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 434 di
209. ich is mounted on the front of the engine It is driven by the engine crankshaft through a shear mecha nism and charges the main batteries The alternator is the primary source of aircraft power and is AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 Qe MOONEY SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION connected to the aircraft electrical system at the main bus In the event of an alternator failure a 20 Amp standby alternator actuated by the pilot using a manual switch in the cockpit labeled EMER BUS powers Essential systems as presented on the fascia ofthe Circuit Breaker Panel If the Primary and Standby charging systems fail the ship s battery s provide the system with electrical power The M20TN has 2 separate 11 ampere hour batteries which are mounted in the tail cone Either battery can be selected to powerthe electrical bus using the BATT 1 BATT 2 select rocker switch mounted on the LH side of the Pilot s Flight Panel Only one battery will power the bus at any time The unselected battery will be trickle charged by the ship s alternator when the engine is running and the ammeter shows a positive charge condition The selected battery is connected to the aircraft bus by the BATT MASTER rocker switch located on the LH side ofthe Pilot s Flight Panel The aircraft has an External Power receptacle located on the left side of the tailcone aft of the tailcone access panel When external power is connected to this rec
210. ight Plan As Desired Optional Equipment Checks Reference Section IX TAXI Before Taxi Checklist Completed CIM 3 i ien eer UR ace be x e S As Desired CAUTION With Rudder Trim in the full right position the aircraft will tend to steer to the right during taxi Parking Brakes ore e ER A We beet te am dele Release Biak6S ecw tet RUE Miu ese Ee a paler Check during taxi Heading Indicator Proper Indication During Turns PED ME Di erue Tm aues eI ELLE No Flags Red X s Thitottle bs Minimum Power Propeller AES Full Forward High RPM CAUTION To prevent battery depletion in prolonged taxi or holding position before takeoff increase RPM until the AMPS indication on the G1000 indicates a positive num ber WARNING The absence of RPM drop when checking magneto function may be an indication of a malfunction in the ignition circuit resulting in a hot magneto not grounding properly Should the propeller be moved by hand the engine may start and cause death or injury This type of malfunction must be corrected before operat ing the engine CAUTION Do not disregard the importance of pre takeoff magneto checks When operating on a single igni
211. ing both sides of split trim switch located on left hand portion of pilots control wheel will electrically trim aircraft 39 FUEL SELECTOR VALVE NOT SHOWN Fuel selector valve located on floorboard is a three position valve which allows pilot to select either left or right fuel tank Turning valve OFF shuts off ALL fuel to engine At full throttle engine will stop from fuel starvation in 2 to 3 seconds 40 GEAR DOWN POSITION INDICATOR NOT SHOWN The gear down position indicator located on floorboard near back of fuel selector valve pan aft of center console has two marks that align when landing gear is down and illuminates when GREEN GEAR DOWN light is ON red white striped decal shows when landing gear is NOT the down position 41 PANEL LIGHT SWITCH AND DIMMER Turning panel light switch knob clockwise turns instrument lights located in glareshield ON Con tinued turning clockwise increases light intensity 42 CIRCUIT BREAKER PANEL See details elsewhere in this Section 43 amp 44 CO PILOT S HEADSET JACKS 45 amp 46 PILOT S HEADSET JACKS See description elsewhere in this section 47 EMERGENCY LOCATOR TRANSMITTER ELT SWITCH ELT is activated when the ON button is pushed ELT returns to armed condition when the RE SET button is pushed Refer to ELT description elsewhere in this section on proper and lawful usage ARTEX ELT optional If the ELT switch is labeled ARTEX ELT then operation is differ
212. ing engine speed adjust mixture to prevent engine power loss from an overrich condition Enrich mixture when opening throttle or increasing engine speed to prevent engine power loss from a lean condition Always lean to obtain a smooth running engine The following procedure should be followed when a failed engine driven fuel pump is suspected HIGH BOOST Pump Guarded Switch ON oa D ero eA n CRUISE Position or as required for engine operation RAE S ADJUST for smooth engine operation LAND AS SOON AS PRACTICABLE amp CORRECT MALFUNCTION FUEL VAPOR SUPPRESSION Fluctuating Fuel Flow LOW Boost P mp bte prb ret ete Hg x deeds ON to clear vapors Engine operation em Re ER MOS RU RI RR Are MONITOR LOW Boost Pump OFF If condition still exists REPEAT PROCEDURE LEAVE PUMP ON ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 3 13 SECTION III MOONEY EMERGENCY PROCEDURES M20TN FIRES NOTE If necessary use fire extinguisher to keep fire out of cabin area ENGINE FIRE DURING START ON GROUND Magneto Starter Switch CONTINUE cranking or until fire is extinguished et lt qe E RC RUDI ane Ing iege at Sage If engine starts ra tata a RU rA P 1500 RPM for several minutes Engine
213. installed and operational as specified in the KINDS OF OPERATION EQUIPMENT LIST and the applicable operating rules Optional equipment installations may not be required to be operational The pilot must determine thatthe applicable operating rules requirements for each kind of opera tion are met OPERATIONS IN KNOWN ICING CONDITIONS ARE PROHIBITED FAA APPROVED 4 AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 2 9 SECTION II MOONEY LIMITATIONS M20TN KINDS OF OPERATION EQUIPMENT LIST The following equipment was approved during Type Certification and must be installed and op erable for each kind of operation as specified NOTE The KINDS OF OPERATION EQUIPMENT list may not include all the equipment as required by applicable operating rules KINDS OF OPERATION EQUIPMENT LIST VFR DAY VFR NIGHT IFR DAY IFR SYSTEM or COMPONENT NIGHT MULTI FUNCTION DISPLAY AUDIO PANEL AIR DATA COMPUTER ATTITUDE AND HEADING REFERENCE SYSTEM n SEAT BELT SHOULDER HARNESS 1 1 1 1 FOR EACH OCCUPANT 3 S MGE HD 4 perisse SsmosEuemmsawr consoy 3 wonen INSTRUMENT LIGHTS INTERNAL 1 GLARESHIELD NENNEN PILOT S OPERATING HANDBOOK amp 1 1 1 1 ALTERNATE STATICSOURCES 1 Equipment must be installed and operable for all operations 2 f the PFD is inoperative or removed for service the MFD may be used as the PFD
214. ions of this manual AIRFRAME The M20TN is an all metal low wing high performance airplane The fuselage has a welded tubular steel cabin frame covered with non structural aluminum skins Access to the cabin is provided by a door located on the right side of the fuselage A door is provided aft of the rear seat for access to the baggage compartment The aft fuselage tailcone is of semi monocoque construction Seating in the cabin is provided for the pilot and three passengers The M20TN has atapered full cantilever aluminum construction laminar flow type wing The airfoil varies from a NACA 635 215 atthe wing rootto a NACA 644 412 atthe wing tip modified by an inboard leading edge cuff Wrap around stretched formed skins cover the wing flush rivet ing is used on the forward top and bottom two thirds ofthe wing chord to provide benefit of lami nar flow aerodynamics The empennage consists of the vertical and horizontal stabilizer assembly and the rudder and elevator surfaces The entire empennage pivots around attaching points on the aft fuselage to provide pitch attitude trim The tricycle landing gear allows maximum vision and ground maneuvering Hydraulic disc brakes and a steerable nose wheel aid in directional control during taxiing and ground opera tions The landing gear is electrically retracted and extended A gear warning VOICE ALERT gear position indicator on the floorboard and a green GEAR DOWN light help p
215. irectly by outside ram air Twist vent to adjust flow Tilt vent to direct flow CABIN VENT The CABIN VENT handle on the center console opens a valve that will mix fresh outside air with the cabin heat or defrost system Pull CABIN VENT knob to open When cabin heat is on intermediate settings between full open and full closed provide continuously variable mixing ratios Cold and hot air mixing may be used to control the total cabin heat output AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 Qe SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION CABIN HEAT Sonic nozzles extract a constant mass flow of high temperature air immediately downstream from the turbo compressor and send it to the cabin heat valve assembly With the heat valve closed unused hot air is exhausted into the cowling Pulling the CABIN HEAT handle on the center console AFT opens the cabin heat valve and closes the overboard outflow vent to provide heated air to the cabin Intermediate settings will provide intermediate amounts of cabin heat and overboard outflow If exhaust or oil fumes are detected in the cockpit immediately shut the CABIN HEAT valve Oil fumes in particular may be a sign of impending turbo bearing failure and should be investigated post flight OVERHEAD VENTILATION Cabin overhead ventilating system works independently of cabin heating and ventilating system Fresh air enters a duct on dorsal fin and is controlled by individu al out
216. irplane MAXIMUM FLAP EXTENDED SPEED The highest speed permissible with wing flaps in a prescribed extended position NEVER EXCEED SPEED The speed limit that may not be exceeded at any time MAXIMUM STRUCTURAL CRUISING SPEED The speed that should not be exceeded except in smooth air and then only with caution STALLING SPEED The minimum steady flight speed at which the air plane is controllable 30 STALLING SPEED The minimum steady flight speed at which the air plane is controllable in the landing configuration BEST ANGLE OF CLIMB SPEED The airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance BEST RATE OF CLIMB SPEED The airspeed which delivers the great est gain in altitude in the shortest possible time with gear and flaps up ENGINE POWER TERMINOLOGY BRAKE HORSEPOWER Power developed by the engine CHT CYLINDER HEAD TEMPERATURE Operating temperature of engine cylinder s being monitored by sensor unit Expressed in TIT TURBINE INLET TEMPERATURE Temperature at turbine inlet used to identify the lean fuel flow mixtures for various power settings Expressed in EXHAUST GAS TEMPERATURE The exhaust gas temperature mea MAXIMUM LANDING GEAR EXTENDED SPEED The maximum speed at which an aircraft can be safely flown with the landing gear extended MAXIMUM LANDING GEAR OPERATING SPEED The maximum speed at which the landing gear can be safely exten
217. ith the performance of the airplane and performance data in the airplane manuals and placards The resultant effect of temperature and pressure altitude must be taken into account in determining performance if not accounted for on the charts Appli cable FAA manuals must be aboard the airplane at all times including the weight and balance forms and equipment lists The airplane must be loaded so as notto exceed the weight and the weight and balance loading center of gravity c g limitations Also that at least minimum fuel for takeoff is aboard and suffi cient for the trip plus reserves Oil in the engines should be checked and filled as required INSPECTIONS MAINTENANCE In addition to maintenance inspections and preflight information required by FAR Part 91 a com plete pre flight inspection is imperative It is the responsibility of the owner and operator to as sure that the airplane is maintained in an airworthy condition and proper maintenance records are kept While the following items can not substitute for the pre flight specified for each type of airplane they will serve as reminders of general items that should be checked SPECIAL CONDITIONS CAUTIONARY NOTICE Airplanes operated for Air Taxi or other than normal operation and airplanes operated in humid tropics or cold and damp climates etc may need more frequent inspections for wear corrosion andor lack of lubrication In these areas periodic inspections should be performe
218. k freedom of controls Cabin and baggage door properly closed Seat belts and shoulder harnesses fastened Passengers briefed Engine and propeller operating satisfactorily All engine gauges checked for proper readings Fuel selector in proper position Fuel quantity checked by gauges Altimeter setting checked FLIGHT OPERATIONS GENERAL The pilot should be thoroughly familiar with all information published by the manufacturer con cerning the airplane The pilot is required by FAA to operate in accordance with the FAR s and the FAA Approved Airplane Flight Manual and or placards installed TURBULENT WEATHER A complete weather briefing prior to beginning a flight is the start of assurance of a safe trip Up dating of weather information enroute is another assurance However the wise pilot also knows weather conditions change quickly at times and treats weather forecasting as professional ad vice rather than as absolute fact He obtains all the advice he can but still stays alert through knowledge of weather changes observations and conditions Plan the flight to avoid areas of severe turbulence and thunderstorms It is not always possible to detect individual storm areas or find the in between clear areas Thunderstorms squall lines and violent turbulence should be regarded as extremely dangerous and MUST be avoided Hail and tornadic wind velocities can be encountered in thunderstorms that can destroy any airplane just as torn
219. l cable which manually drives the gear actuator to extend landing gear 12 20 pulls are required to fully extend and lock landing gear down The electrical extension or retraction system will not operate if the manual extension lever is not properly positioned down WARNING SYSTEM The landing gear warning system consists of 1 landing gear condition lights GREEN for GEAR DOWN and RED for GEAR UNSAFE and 2 VOICE ALERT activated when landing gear is not down and locked and throttle is approxi mately 1 4 inch from idle position The green light shows continuously when landing gear is fully extended The red light shows when ever landing gear is in transit or not locked down but is OFF when landing gear is fully retracted A visual gear position indicator located on floorboard aft of the fuel selector shows that landing gear is down when indicator marks align The gear down light is dimmed when navigation lights are turned on CABIN BAGGAGE COMPARTMENT The baggage compartment is located aft of rear passenger seats The standard compartment has 20 9 cubic feet 0 59 cu m of baggage or cargo space A maximum of 120 pounds 54 may be loaded in this area There are floor tiedown straps provided Passengers should not be allowed to occupy this space Additional cargo space is available by folding rear seats down To fold seats down remove rear seat bottom cushion Pull seat back release handle and fold seat back forward pull
220. l pump gear driven fuel pump and dual gear driven magnetos The TSIO 550 G has twin turbochargers which use exhaust gas flow to boost induction air pressure for increased power There is one turbocharger on each side of the engine The turbo chargers compress and raise the temperature of the incoming air before going to the intercool ers The compressed air runs through the intercoolers where it is cooled down before entering the throttle body and cylinders The dual turbochargers are lubricated from external oil supply lines from a source at the bottom of the oil cooler There is one oil pressure actuated wastegate on the left side of the engine controlling the amount of exhaust gas used by the turbochargers Control is accomplished by a diaphragm actuated valve sensing differential pressure across the throttle plate and controlling the oil return flow rate from the wastegate An overboost valve in the induction system provides protection from too much pressure by actuating at 35 inHg of manifold pressure The engine operates with three standard engine controls The propeller turns clockwise as viewed from the cockpit ENGINE CONTROLS The engine controls are centrally located between the pilot and co pilot on the engine control console The BLACK throttle knob regulates manifold pressure push the knob forward to in crease the setting pull the knob aft to decrease the setting The propeller control with its crowned BLUE knob controls engi
221. left wing leading edge Split switches are used to control either the left or right taxi or landing lights All exterior light switches are located on overhead panel just behind top of windshield The high intensity wing tip and tail strobe lights are required for night operation but should be turned OFF when taxiing near other aircraft or flying in fog or clouds The conventional position lights must be used for all night operations ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 7 81 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN CABIN ENVIRONMENT RIGHT HOT AIR 5 221 COMPRESSOR OVERBOARD CABIN HEAT VALV OUTFLOW TO DEFROST VENTS FIREWALL OUTSIDE AIR div 3415110 DEFROST BLOWER TO ES amp CONSOL FRESH AIR VALVE gt DEFROST VALVE PILOT AIR CO PILOT AIR VALVE VALVE N 2 OVERHEAD AIR VALVES CABIN VENT DORSAL FIN INLET OVERHEAD MASTER FRESH AIR VALVE FIGURE 7 10 CABIN AIR FLOW CABIN ENVIRONMENT HEATING amp VENTILATION SYSTEMS Multiple controls are available to provide fresh air and or heated fresh air according to individual preferences PILOT CO PILOT AIR VALVE One adjustable swivel head valve is provided for each cockpit seat on the cabin walls at knee height just forward of the front seats These valves are supplied d
222. lets above and between each seat A master air vent control is located between the pilots amp co pilots seat on the overhead panel Rotating this control left or right will regulate the total air flow available to all four overhead vents DEFROST The windshield defrost system takes air from the cabin air distribution system and distributes this over the windshield interior surface any time the CABIN HEAT and or CABIN VENT valves are opened Pulling the DEFROST control full AFT decreases flow to the cabin turns the defroster blower ON and forces maximum air to flow through the defrost ducts PITOT PRESSURE amp STATIC SYSTEM A pitot tube mounted on lower surface of the left wing picks up ram air for air speed indication Two static ports one on each side of the tailcone supply static air pressure for the altimeter the airspeed indicator and vertical speed indicator A pitot heater prevents pitot tube icing when flying in moisture laden air A pitot system drain valve is located on the forward bottom skin ofthe left wing to fuselage fillet A static system drain valve is located on fuselage bottom skin below the left side tailcone access door and is used to drain moisture that might collect in static system lines Excessive moisture in the system can affect instrument readings An alternate static pressure source valve handle is installed in the instrument panel below the pilot s control wheel shaft Alternate static air pressure is sense
223. light Rules is a document of law governing operation of aircraft and the owner s and pilot s responsibilities This document covers such subjects as Responsibilities and authority of the pilot in command Certificates required Liquor and drugs Flight plans Pre flight action Fuel requirements Flight rules Maintenance preventative maintenance alterations inspections and maintenance records These are only some of the topics covered It is the owner s and pilot s responsibility to be thor oughly familiar with all items in FAR Part 91 and to follow them FEDERAL AVIATION REGULATIONS PART 39 AIRWORTHINESS DIRECTIVES This document specifies that no person may operate a productto which an airworthiness direc tive issued by the FAA applies except in accordance with the requirements ofthat airworthiness directive AIRMAN INFORMATION ADVISORIES AND NOTICES FAA AERONAUTICAL IN FORMATION MANUAL This document contains a wealth of pilot information for nearly all realms of flight navigation ground procedures and medical information Among the subjects are Controlled Air Space Services Available to Pilots Radio Phraseology and Technique Airport Operations Clearances and Separations Pre flight Departures IFR Enroute IFR Arrival IFR Emergency Procedures Weather Wake Turbulence Medical Facts for Pilots Bird Hazards Good Operating Practices Airport Location Directory ORIGINAL ISSUE 12 22 2006 AI
224. located in the pilot s control wheel FIGURE 7 2 ANNUNCIATOR amp SWITCH PANEL ANNUNCIATOR amp SWITCH PANEL ANNUNCIATOR 1 PRESS TO TEST SWITCH Press RED press to test switch 3 5 sec with Master Switch ON to illuminate light bulbs some annunciator legends may not be active see descriptions below Defective bulbs must be replaced prior to flight Includes MASTER WARN light on S N 29 0170 thru 29 2 DIM SWITCH The DIM switch may be activated after the low fuel lights come on bright The switch will dim both low fuel lights but will not turn them off To restore display to bright press TEST switch 3 GEAR SAFETY INDICATOR GEAR DOWN ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 24 7 13 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN 4 GEAR SAFETY INDICATOR GEAR UNSAFE A GEAR DOWN light GREEN a GEAR UNSAFE light RED and a gear warning VOICE AL ERT provide visual and audible gear position signals The green GEAR DOWN light shows continuously when gear is fully extended With navigation lights ON the GEAR DOWN light is dimmed for night operation All gear lights are OUT when landing gear is fully retracted Addition al verification is accomplished by checking floor board indicator window 5 LEFT FUEL 6 RIGHT FUEL Left and or right fuel annunciator light RED comes on when there is 6 to 8 gallons 23 to 30 3 liters of usable fuel remaining in the respective tank 7 SPEED BRAK
225. ltitude High altitude descent in lean condition with no corresponding throttle or mixture change EMERGENCY LANDING WITHOUT ENGINE POWER GLIDE Airspeed zorra dw ae ere ae T REDIT E BEST GLIDE SPEED 3368 1b 4528 kg A b RD eu oe M eu es 91 5 KIAS S200 ID 1452 ce epa EM E 89 0 KIAS 2900 ID 1315 Kg ore eee ER peter uti been ke ete ii D EET 84 5 KIAS 2600 Ib 1179 Kg cie Pte PENES 80 0 KIAS Propeller niue ue RE RED PR RE PULL FULL AFT Wing Flaps tthe SET 85 KIAS See Maximum Glide Distance Chart for best speed Radio ubt eeu MAKE DISTRESS TRANSMISSION Seat Belts Shoulder Harnesses FASTENED AND SECURE Loose Objects nd Rep US Re Re gana nde Rn ep e SECURE LOW three pto t ptite ib eU oot ede dise OFF LANDING baee d ewe eng ue e DUNT DIS SET TO IDLE CUTOFF Fuel Selector pce OFF Magneto Switch reto te need eere eer cgi evel en Up OFF Wing Flaps HERD AS REQUIRED Full Flaps Recommended SPEEDBRAKE Switch SET OFF DOWN POSITION Landing Flare INITIATE AT APPROPRIATE POINT TO ARREST DESCENT RATE AND
226. ment panel in place ofthe aircraft or headset microphone lead and key the switch on the control yoke The oxygen cylinder composite when fully charged contains either a 77 1 ft 9 or 115 7 1 3 of aviator s breathing oxygen Spec No MIL 0 27210 under a pressure of 1850 PSI at 219 C 709 F Filling pressures will vary however due to ambient temperature in filling area and the rise of temperature resulting from compression of the oxygen Because of this merely filling to 1850 PSI will not necessarily result in a properly filled cylinder Fill to pressures indicated on Fig 7 11 for ambient temperatures WARNING Oil grease or other lubricants in contact with oxygen create a serious fire hazard and such contact must be avoided when handling oxygen equipment Ambient Ambient Filling Pressure Filling Pressure Temperature PSIG Temperature PSIG 39 p 59 9 1 0 3 oom 29 6 1 89 FIGURE 7 11 OXYGEN FILLING PRESSURES NOTE The oxygen cylinder should not be run down to less than 100 PSI Below this pressure atmospheric contamination of the cylinder may occur requiring valve removal and cylinder cleaning and inspection at an FAA approved repair station AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 34 SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION For FAA requirements concerning supplemental oxygen refer to FAR 91 211 Supplemental ox ygen shoul
227. n of engine instru ment readings is essential for selecting optimum control settings and for maintaining maximum cruise fuel economy Refer to SECTION for Limitations ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL di 7 19 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN ENGINE OPERATION AND CARE Life of an engine is determined by the care it receives Maximum efficiency and engine service life can be expected when a good maintenance program is followed Poor maintenance results infaulty engine performance and reduced service life Efficient engine operation demands care ful attention to cleanliness of air fuel oil and maintaining operating temperatures within required limits Servicing of the engine should be accomplished only by qualified personnel The mini mum grade of fuel for this engine is 100 LL or 100 octane aviation gasoline Operational proce dures for adverse environmental conditions can be found in engine maintenance and operator s manual OIL SYSTEM The engine has a full pressure wet sump oil system with an 8 quart 7 57 liters capacity A con ventional dipstick is provided for determining oil quantity The oil system is depicted in Figure 7 5 The propeller governor boosts engine oil pressure for operation of the propeller It controls oil pressure going to the propeller hub to maintain or change propeller blade angles This oil flows through propeller shaft to reach the propeller TO PROPELLER T
228. n other than the G1000 GPS receiver appropriate to the route and phase of flight When continuing to use GPS navigation position must be verified every 15 minutes using the G1000 VOR ILS receiver or another IFR approved primary navigation system CAUTION If the POSN ERROR annunciation is displayed while on the final approach seg ment between the Final Approach Fix and the Missed Approach Point GPS based navigation will continue for up to 5 minutes with approach CDI sensitivity set at 0 3 nautical mile It is recommended that the pilot initiate the missed ap proach upon receipt of this message from the G1000 Navigation guidance will continue for 5 minutes allowing the pilot to initiate the missed approach while maintaining course guidance on the final approach course Then the system will flag and no longer provide course guidance with approach sensitivity Missed approach course guidance may still be available with 1 nautical mile CDI sensitiv ity by executing the missed approach This is typically caused by the GPS sen sor s inability to provide adequate horizontal position accuracy for the final ap proach segment It is possible however unlikely that the GPS position may degrade to the point where terminal operations cannot be supported for the missed approach segment Navigate using other primary navigation equipment VOR receivers etc if this occurs In an in flight emergency depressing and holding the Comm transfer button for
229. nding gear should then be cycled up then down wait approximately five seconds and then retract again Caution must be exercised to assure that the entire operation is performed below Maximum Landing Gear Operating Air speed Use caution when landing on runways that are covered by water or slush which cause hydro planing aquaplaning a phenomenon that renders braking and steering ineffective because of the lack of sufficient surface friction Snow and ice covered runways are also hazardous The pilot should be alert to the possibility of the brakes freezing Use caution when taking off or landing in gusty winds Be aware of special wind conditions caused by buildings or other obstructions located near runway in a crosswind pattern AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 10 10 SECTION X M20TN SAFETY INFORMATION MEDICAL FACTS FOR PILOTS GENERAL Modern industry s record in providing reliable equipment is very good When the pilot enters the airplane he becomes an integral part of the man machine system He is just as essential to a successful flight as the control surfaces To ignore the pilot in pre flight planning would be as senseless as failing to inspect the integrity of the control surfaces or any other vital part of the machine The pilot himself has the responsibility for determining his reliability prior to entering the airplane for flight While piloting an airplane an individual should be free
230. ne RPM through the propeller governor Push the knob forward to increase engine RPM pull the knob aft to decrease RPM The mixture control with its RED fluted knob establishes the fuel air ratio mixture Push the knob full forward to set the mixture to full rich pull the knob gradually aft to lean the mixture Pull the knob to its maximum aft travel position to close the idle cut off valve to completely shutdown the engine Precise mixture settings can be established by observing the TIT gauge on the pilot s instrument panel while adjusting the mixture control The throttle propeller and mixture controls are vernier type and fine adjustment can be made by turning knobs clockwise or counter clockwise The vernier controls should be rigged within 030 to 060 in from panel nut face Rapid movement or large adjustments can be made by pushing button on end of control and positioning control where desired The non vernier throttle has an integral friction device ENGINE INSTRUMENTS Engine instruments operate electrically except manifold pressure through variations in resist ance caused by pressure or temperature changes or by variations in current output caused by varying engine RPM or alternator output The tachometer receives its signal from the Hall effect sensor in magneto Engine operating instruments are displayed in the Garmin GDU 1040 Multi Function Display Colored bars on instrument faces mark operating ranges Proper interpretatio
231. ng quantity of fuel can no longer be safely used NOTE An optional visual fuel quantity gauge is installed on top of each tank and is to be used as a reference for refueling tanks only Standard Tanks 2 47 5 U S Gal each 179 8 liters Total Fuel Capacity Standard 95 U S Gal 359 6 liters Usable Fuel sedi got p RR RUP e ee 89 U S Gal 336 9 liters Unusable Fuel Rente eU RR ECHTE E eas 6 U S Gal 22 7 liters Fuel Grade and color 100LL low lead blue or 100 octane green is approved CAUTION Ethylene glycol monomethyl ether EGME or other additives are not recom mended due to potential deteriorating effects within the fuel system Under cer tain conditions of temperature and humidity water can be present in fuel in suffi cient quantities to create ice formations within the fuel system To prevent this add Anhydrous ISOPROPYL Alcohol to the fuel supply in quantities not to exceed 3 of total fuel volume per tank WEIGHT LIMITS Maximum Weight Takeoff 3368 Ib 1528 Kg Maximum Weight Landing 3200 Ib 1452 Kg Maximum Weight in Baggage Compartment 120 Ib Les Y Rio 54 4 Kg Fus Sta 101 5 253 7 cm Maximum Weight in Rear Storage A
232. ng the duration at 30 000 feet by steps 1 and 2 above and multiplying by the duration multiplier shown on the right of the appropriate cruising altitude Example Pilot only at 1600 PSI has 11 25 hours duration at 30 000 ft Duration Multiplier of 2 4 for 20 000 ft gives 26 hours and 54 minutes duration Oxygen durations off the chart obviously exceed the airplanes duration However judicious choices of altitude for the number of persons on board can permit flight planning for several fuel stops without need for recharging oxygen system at each stop CAUTION Facial hair beards and mustaches may prevent a proper seal between face and mask causing 16 67 leakage Duration chart be invalid VACUUM SYSTEM GX aircraft are all electric There is no Vacuum System in the standard aircraft EMERGENCY LOCATOR TRANSMITTER The Emergency Locator Transmitter ELT is located in the tailcone and is accessible from the battery access door on the right side of the tailcone The emergency locator transmitter meets the requirements of FAR 91 52 and is automatically activated by a longitudinal force of 5 to 7 g s The ELT transmits a distress signal on both 121 5 MHz and 243 0 MHz for a period of from 48 hours inlowtemperature areas and upto 100 hours in hightemperature areas Theunitoperates ona self contained battery The battery should be checked at each annual inspection The bat tery has a useful life of four years However to comply with
233. nhydrous ISO PROPYL Alcohol to the fuel supply in quantities not to exceed 3 of total fuel volume per tank ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 SECTION VIII MOONEY HANDLING SERVICE AND MAINTENANCE M20TN ENGINE LUBRICATION Operate and service new engine within limitations given in SECTION and per Mainte nance and Operators Manual Before every flight check engine oil level and replenish as necessary The oil filler cap access door is located in top cowling Any lubricating oil must conform with TCM Specification MHS24 to be acceptable for use in engine See TCM Maintenance and Operators Manual for specifically approved products During the engine break in period Nondispersant mineral oil conforming to SAE 51 966 shall be used However if the engine is flown less than once a week a straight mineral oil with corrosion preventative MIL C 6529 for the first 25 hours is recommended After the first 25 hours of the airplane s time in service the oil and oil filter must be changed and a new supply of Teledyne Continental Motors specification MHS 24 latest revision ashless dispersant oil must be used At 50 hours of time in service the oil and oil filter shall be changed Discard the old filter and replace with new Check discarded oil for evidence of metal particles Thereafter the oil and oil filter must be changed at every 50 hours of time in service At the first oil change the engine and related
234. nstrument panel lighting and cabin courtesy lights Make sure the lighting and Emergency Bus switch as well as the STBY GYRO circuit breaker are de energized when leaving the aircraft Leaving these systems energized for an extended period of time could cause depletion of the battery Two lights mounted in the overhead panel provide instrument and cockpit lighting for night fly ing A wing tip position light system consists of 2 lights on each wingtip and is operated by a rock ertype switch mounted in the overhead switch panel Landing and taxi lights are mounted on the wing leading edges on both wings Wing tip and tail mounted Strobe lights are controlled by a rocker type switch mounted in the overhead switch panel The M20TN electrical system is divided into two power buses A simplified schematic ofthe elec trical system is shown in the diagram which follows ANNUNCIATOR PANEL The landing gear low fuel speed brakes speed brake alternate air prop de ice and pitot heat lights are grouped in the upper annunciator panel The alternator fail start power emergency buss and boost pump are grouped in the lower annunciator panel Atest and dim switch are also found in the panel each of the lights and switches are discussed elsewhere in this Section LIGHTING SYSTEM INSTRUMENT amp PLACARD LIGHTS All placards are floodlighted by lights from the glareshield There are two rheostat knobs on the right hand radio panel The left cont
235. ntial that ALL CLEANING COMPOUNDS AND APPLICATION CLOTHS BE FREE OF ABRASIVES GRIT OR OTHER FOREIGN MATTER Use a pre wax cleaner to remove a heavy oxidation film For non oxidized or pre cleaned surfaces apply a good exterior finish wax recommended for protection of urethane enamel finishes Carefully follow the manufacturer s instructions A heavier coating of wax on the leading edge of the wings empen nage and nose section will help reduce drag and abrasion in these areas If fuel hydraulic fluid or any other dye containing substance is found on the exterior paint wash the area at once to prevent staining Before wiping windows or windshield flush exterior with clear water to remove particles of dirt Household window cleaning compounds should NOT be used some contain abrasives or sol vents which could harm Plexiglass Any commercial anti static Plexiglass cleaner is recom mended for cleaning and polishing the windshield and windows INTERIOR CARE Normal household cleaning practices are recommended for routine interior care Frequently vacuum clean seats carpets fabric side panels and headliner to remove as much surface dust and dirt as possible Spot clean Neather Leather with mild soap and water For stubborn stains use mild solvent such as 4097 Other type cleaners are not recommended at this time CAUTION Never use benzene carbon tetrachloride acetone or gasoline for cleaning Plexi glass or inte
236. observing TIT indicator and maintaining TIT limits If manifold pressure changes while leaning readjustthrottle and continue leaning until peak TIT is attained Note peak TIT and slow ly lean mixture until TIT indication is 50 F LEAN OF PEAK Re adjust throttle or RPM as re quired CAUTION Above 30 5 inHg of manifold pressure only full rich mixture is permitted At altitudes above 22 000 feet power settings above 2300 rpm must be operated at 1675 F TIT or richer CAUTION When changing power the sequence of control usage is important Monitor the TIT display to avoid exceeding 1750 F limit To increase power first increase the mixture not necessarily to FULL RICH then increase RPM with the propeller control and then increase manifold pressure with the throttle control To decrease power decrease manifold pressure first with the throttle control and then decrease RPM with the pro peller control When engine temperatures have stabilized lean mixture to desired TIT PERFORMANCE CONSIDERATIONS LANDING GEAR DOORS When snow and ice are likely to be present on taxi and runway surfaces inboard landing gear doors should be removed Accumulation of ice and snow could prevent landing gear operation If inboard landing gear doors are removed a decrease in cruise speed and range can be ex pected and should be considered in preflight planning To be conservative the following figures should be used Decrease of true airspeed at normal cr
237. of conditions which are harmful to alertness ability to make correct decisions and rapid reaction time FATIGUE Fatigue generally slows reaction times and causes foolish errors due to inattention In addition to the most common cause of fatigue insufficient rest and loss of sleep the pressure of business financial worries and family problems can be contributing factors If your fatigue is a factor prior to a given flight don t fly To prevent fatigue effects during long flights keep mentally active by making ground checks and radio navigation position plots HYPOXIA Hypoxia in simple terms is a lack of sufficient oxygen to keep the brain and other body tissues functioning properly There is wide individual variation in susceptibility to hypoxia In addition to progressively insufficient oxygen at higher altitudes anything interfering with the blood s ability to carry oxygen can contribute to hypoxia anemias carbon monoxide and certain drugs Also alcohol and various drugs decrease the brain s tolerance to hypoxia Your body has no built in alarm system to let you know when you are not getting enough oxygen It is impossible to predict when or where hypoxia will occur during a flight or how it will manifest itself A major early symp tom of hypoxia is an increased sense of well being referred to as euphoria This progresses to slow reactions impaired thinking ability unusual fatigue and dull headache feeling Symptoms are slow b
238. oney aircraft was designed and built to provide you with many years of safe and efficient transportation By maintaining it properly and flying it prudently you should realize its full poten tial ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 10 3 SECTION X MOONEY SAFETY INFORMATION M20TN GENERAL Flying is one of the safest modes of travel Remarkable safety records are being established each year As a pilot you are responsible to yourself your relatives to those who travel with you to other pilots and to ground personnel to fly wisely and safely The following materials in this Safety section covers several subjects in limited detail Here are some condensed DO s and Don t DO S 1 Be thoroughly familiar with your airplane and be current in it or get a check ride 2 Pre plan all aspects of your flight including weather FLY YOUR PLAN Use services available FSS Weather Bureau etc Pre flight you airplane thoroughly Use your checklists Have more than enough fuel for take off the planned trip and adequate reserve Be sure your weight loading and C G are within limits Be sure articles and baggage are secured ON Check freedom of all controls 10 Maintain appropriate airspeed in take off climb descent and landing 11 Avoid other aircraft wake turbulence 12 Switch fuel tanks before engine starvation occurs 13 Practice engine out emergency landing gear e
239. oodrich SKYWATCH Traffic Advisory Sys tem TAS if installed will appear on the MFD and traffic display pages of the Gi 1000 For de tailed operating instructions regarding the interface of the G 1000 with the SKYWATCH refer to the Pilot s Guide for the SKYWATCH and the Garmin G 1000 Cockpit Reference Guide for the Mooney M20TN Refer to the GARMIN G1000 Cockpit Reference Guide for the M20TN MODEL aircraft GARMIN P N 00 00450 01 Rev Aor later FAA approved for complete descriptions ofthe 21000 system and operating procedures AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 6 VA SECTION VII AIRPLANE AND SYSTEM DESCRIPTION MOONEY M20TN qi3iHS38V 19 3AO8V Q31V201 QNIH38 Q31V90 1 d 21 IG ad 7 7 FIGURE 7 1 FLIGHT PANEL 29 0333 THRU 29 TBD AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN FLIGHT PANEL amp INSTRUMENTS SWITCHES amp CONTROLS NOTE The illustration depicts a standard panel configuration The location of instru ments switches and avionics may be relocated in each aircraft dependant upon the optional equipment selected by the customer and available panel space 1 AIRSPEED INDIC
240. open T see Power Loss Primary Engine Induction Air System Blockage page 3 12 Piero ELEME ADJUST as required PATOS ove o ate MINIMUM FOR LEVEL FIGHT AT SAFE SPEED Failure Analysis oria db o a ced DETERMINE CAUSE Improper Fuel Management If the engine failure cause is determined to be improper fuel management set the HIGH boost pump to OFF and resume fight Engine Driven Fuel Pump Failure If fuel management is correct failure of the engine driven fuel pump or a clogged fuel filter is probable An engine driven fuel pump failure is probable when engine will only operate with HIGH BOOST pump ON If practicable reduce power to 7596 or less and land as soon as possible Do not set the mixture too rich for descent or lan ding Improper Mixture Setting If fuel management is correct and the engine driven fuel pump is functioning properly it is possible the mixture is either too lean or too rich Possible over rich conditions Very low power settings at high altitude and rich mixture Very low power settings with the fuel boost on and rich mixture Severe induction system blockage leakage or turbo failure and rich mixture Possible over lean conditions Advancing the throttle or prop from a lean condition before richening HIGH Fuel boost switched off from lean condition before richening Vapor in fuel likely to happen in very hot ambient conditions at a
241. or shop solvents Use only FAA approved Challenger cleaning solution in Challenger Re charger Kit P N CP 99 5050 Do not use steam cleaning equipment or any other cleaning devices When dry ing the filter after cleaning let the filter dry naturally Pressurized equipment will strip the cotton of critical microfilaments Do not use compressed air open flames or heating devices of any kind When recharging the filter with oil use only FAA approved Challenger Re charger Oil in Re charger Kit P N CP 99 5050 The oil is the same oil applied at the factory dur ing the manufacturing process Do not use transmission fluid motor oil or any other lightweight oil of any kind or any products containing petroleum products Dry Type Air Filters The dry type filter can usually be washed six to eight times before replacement is necessary Replace the paper induction air filter every 500 HOURS or at ONE YEAR intervals whichever occurs first ORIGINAL ISSUE 12 22 2006 8 AIRPLANE FLIGHT MANUAL 8 7 SECTION VIII MOONEY HANDLING SERVICE AND MAINTENANCE M20TN To clean the dry type induction air filter 1 Remove engine cowling 2 Remove filter element 3 Direct a jet of air from inside of filter out opposite normal airflow Cover entire filter area with air jet CAUTION Do not use a compressor unit with a nozzle pressure greater than 100 PSI 4 After cleaning inspect filter for damage Discard if filter or gasket is damaged NOTE
242. out leaning will cause an over rich condition This condition may cause the engine to quit above 18 000 ft This condition may also cause the engine to quit when the throttle is suddenly increased If it does quit it is possible to re start the engine at any altitude by leaning the mixture NOTE Avoid extended descents at low manifold pressure setting as engine can cool excessively and may not accelerate satisfactorily when power is re applied NORMAL DESCENT GEAR UP Seats Seat Belts Shoulder Harness ADJUST AND SECURE iens ER PUE IN ER Eee E Rb ERR S em Qe pb E ce UP Landing Gear X ae e e aedes qa UP Power Settings SEE ERU es AS REQUIRED eee EM MOVE TO RICHER SETTING AS REQUIRED LOW Boost PUND starten cette nee sea eed OFF Below 18 000 Ft AlfSpeed Dr etek AS DESIRED 196 KIAS max R dd r AS DESIRED NOTE Refer to descent planning charts in Section V for recommended power settings CAUTION DO NOT fly in YELLOW BAR speed range unless the air is smooth NORMAL DESCENT GEAR DOWN Seats Seat Belts Shoulder Harness ADJUST AND SECURE FIaps reme eee eet meer ee ERR LI ep etit cs UP Power Settings 2400 RPM and approximately 25 inches
243. p drains are near each wing root forward of the wheel wells A small plastic cup is sup plied as loose equipment for obtaining fuel samples To collect a fuel sample insert cup actuator prong into sump drain receptacle push upward to open valve momentarily and drain fuel into cup If water is in fuel a distinct separating water from gasoline will be seen through transpar ent cup wall Water being heavier will settle to bottom of cup while colored fuel will remain on top Continue taking fuel samples until all water is purged from tank Aircraft should be ina level position to prevent the possibility of any contamination not being at sump drain area The fuel system gascolator is on the cabin floor forward of co pilot s seat To flush system and lines leading from wing tanks to selector valve turn selector handle to the left tank position and pull fuel drain valve for about five seconds Repeat procedure for right tank Be sure fuel drain valve is returned to closed position and drain valve is not leaking NOTE Use recommended engine break in procedures as published by engine manufac turer FUEL ADDITIVES CAUTION Ethylene glycol monomethyl ether EGME or other additives are not recom mended due to potential deteriorating effects within the fuel system Under certain conditions of temperature and humidity water can be present in fuel in sufficient quantities to create ice formations within the fuel system To prevent this add A
244. pulling aft and raising knob raises landing gear NOTE Failure to Pull knob out prior to movement may result in a broken switch 23 RUDDER TRIM SWITCH Push split toggle switch to position rudder into trimmed condition to reduce rudder pedal forces during take off climbs or descents Right take off and climbs Left descents Pushing left side of spring loaded switch trims rudder left pushing right side of switch trims rudder right 24 HIGH BOOST FUEL BOOST PUMP SWITCH The High Fuel boost pump switch operates the fuel boost pump on high power The high boost setting is capable of operating engine at reduced power in case of engine driven fuel pump fail or severe fuel filter blockage A guard on the HIGH BOOST switch prevents inadvertent operation and must be lifted for switch operation Continuous operation should be avoided ex cept in an emergency Never run the boost pump without fuel in the system CAUTION Pushing HIGH BOOST pump switch ON when engine driven pump is operating prop erly will cause engine to quit due to excessive rich fuel mixture 25 BOOST PUMP SWITCH LOW BOOST The Low Fuel boost pump switch operates the fuel boost pump on low power to provide a means of suppressing fuel vapor from fuel system during hot day and high altitude conditions Low boost may also be used as an engine starting aid Continuous operation of the low boost is per mitted Never run the boost pump without fuel in
245. r maximum rate of descent 2 With the landing gear extended and flaps retracted an airspeed of 165 KIAS will also give approximately the same rate of descent At 165 KIAS and the gear extended the angle of descent will be greater thus resulting in less horizontal distance traveled than a descent at 196 KIAS Additionally descent at 165 KIAS will provide a smoother ride and less pilot work load THEREFORE The following procedure is recommended for an emergency descent aw EET RETARD INITIALLY teu tu t a 140 KIAS aet bene le pti ege doe deu o UV dies s EXTEND Airspeed INCREASE TO 165 KIAS after landing gear is extended Wing metu aS E E MBA UP hard E UE MAINTAIN 165 KIAS during descent Speedbrakes If installed EXTEND Pico d xm AS DESIRED Power During Descent AS REQUIRED TEE to Maintain CHT 250 F 121 C Minimum iss Ged Wan dee ee Maximum Continuous 460 F 215 69 C ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 3 15 SECTION III MOONEY EMERGENCY PROCEDURES M20TN MAXIMUM GLIDE DISTANCE MODEL M20TN ASSOCIATED CONDITIO
246. r the influence of alcohol Even small amounts of alcohol in the human system can adversely affect judgment and decision making abilities FAR 91 11 states a No person may act as a crew member 1 within 8 hours after the consumption of any alcoholic beverage Tests indicate that as a general rule 2 ounces 06 liters of alcohol at 15 000 feet produce the same adverse effects as 6 ounces 18 liters atsea level In other words the higher you get the higher you get ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL 4 10 11 SECTION X MOONEY SAFETY INFORMATION M20TN DRUGS Self medication ortaking medicine in any form when you areflying can be extremely hazardous Even simple home or over the counter remedies drugs such as aspirin antihistamines cold tab lets cough mixtures laxatives tranquilizers and appetite suppressors may seriously impairthe judgmentand coordination needed while flying The safest rule isto TAKE NO MEDICINE before or while flying except on the advice of your Aviation Medical Examiner SCUBA DIVING Flying shortly after any prolonged scuba diving could be dangerous Under the increased pres sure ofthe water excess nitrogen is absorbed into your system If sufficient time has not elapsed prior to take off for your system to rid itself of this excess gas you may experience the bends at altitudes even under 10 000 feet where most light planes fly ADDITIONAL INFORMATION In addition to the covera
247. re The BOOST PUMP Low Boost switch operates the fuel boost pump on low power to provide a means of suppressing fuel vapor from fuel system during hot day and high altitude conditions Low boost may also be used as an engine starting aid Continuous operation of the low boost is permitted Never runthe boost pump withoutfuel in the system Referto SECTIONS III and IV for proper use of the BOOST PUMP setting CAUTION Pushing LOW BOOST pump switch ON when engine is operating properly at idle con ditions will cause engine to run rough or quit due to excessive rich fuel mixture For this reason LOW BOOST should normally be turned off except where prescribed in the normal operating procedures Two electric fuel level transmitters working in series in each wing tank operate the appropriate left or right fuel quantity gauges The master switch actuates the fuel quantity indicator system to depict an indication of fuel remaining in each tank Vents in each fuel tank allow for overflow and pressure equalization The optional visual fuel quantity indicators in the top of each wing are to be used for PARTIAL FUELLOADING only and NOT for preflight inspection purpose The Fuel Flow indicating system indicates the volume of fuel being used total fuel used or fuel remaining or time remaining refer to GARMIN User Manual ELECTRICAL SYSTEM ALTERNATOR amp BATTERY The M20TN has a 28 Volt DC electrical system powered by a 100 amp alternator wh
248. re assumed to be zero Station Actual atmospheric pressure at field elevation Pressure RIGINAL I E 12 22 2 1 10 ORIG SSU 006 MOONEY SECTION I M20TN GENERAL WEIGHT AND BALANCE TERMINOLOGY The horizontal distance from the reference datum to the center of gravity C G of an item The actual weight of the airplane and includes all operating equipment in cluding optional equipment that has a fixed location and is actually installed in the aircraft It includes the weight of unusable fuel and full oil Center of The point at which an airplane would balance if suspended Its distance Gravity from the reference datum is found by dividing the total moment by the total weight of the airplane C G C G Arm The arm obtained by adding the airplane s individual moments and divid ing the sum by the total weight C G in Center of Gravity expressed in percent of mean aerodynamic chord 96 MAC MAC C G The extreme center of gravity locations within which the airplane must be Limits operated at a given weight Mean Aerodynamic Chord Maximum The maximum authorized weight of the aircraft and its contents as listed in Weight the aircraft specifications The maximum authorized weight of the aircraft and its contents when a normal landing is to be made Moment The product of the weight of an item multiplied by its arm Moment divided by a constant is used to simplify balance calculations by reducing the number
249. rea 10 eie diel et dele deberi 4 54 Kg Fus Sta 131 0 297 5 Maximum Weight in Cargo Area Rear seats folded down 340 Ibs OX 154 2 KG 9 Fus Sta 70 7 176 8 CENTER OF GRAVITY LIMITS GEAR DOWN Most Forward Fus Sta 41 0 IN 104 1 cm 2430 Ib 1102 Kg up 16 79 MAC Intermediate Forward Fus Sta 44 IN 111 7 cm 3300 Ib 1497 Kg Nr PUITS EH MT HERES 21 796 MAC Forward Gross Fus Sta 46 0 IN 116 8 cm 3368 Ib 1528 Kg cL Aa eI ite e xe icta cios 24 98 MAC Aft nct oleo iad Fus Sta 51 0 IN 129 5 3368 Ib 1528 Kg e DR Le E 33 18 at Wing Sta 94 85 241 61 00 In Datum station zero is 13 inches 32 5 cm aft of the centerline ofthe nose gear trunnion attach pivot bolts AIRPLANE FLIGHT MANUAL FAA APPROVED 2 8 We ORIGINAL ISSUE 12 22 2006 SECTION II M20TN LIMITATIONS MANEUVER LIMITS This airplane must be operated as a Normal Category airplane Aerobatic maneuvers including spins are prohibited NOTE Up to 500 foot altitude loss may occur during stall
250. required on magnetic compass except an occasional check on a compass rose adjust ment of the compensation screws if necessary and replacement of the lamp 7 HOUR METER NOT SHOWN Hour meter located on baggage compartment bulkhead indicates actual flight time and is trig gered by the airspeed switch Location may vary depending on installed systems 8 MASTER WARNING LIGHT When any RED warning light on the panel shows that a system or component is malfunctioning this MASTER light illuminates in approximately 15 20 seconds after any annunciator light begins to show a malfunction Pilot should identify the source system warning light on the annunciator then PUSH the MASTER WARN light it contains a PUSH switch under the light MASTER WARN light will extinguish for approximately 2 minutes or until the next system mal function warning light on the annunciator illuminates Repair inoperable system prior to next flight AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 8 VA SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION 9 GARMIN GDU 1040 PRIMARY FLIGHT DISPLAY PFD See description in Garmin G1000 earlier in this section 10 GARMIN GDU 1040 MULTI FUNCTION FLIGHT DISPLAY MFD See description in Garmin 21000 earlier in this section 11 GARMIN GMA 1347 AUDIO PANEL See description in Garmin G1000 earlier in this section 12 MAGNETO STARTER SWITCH Magneto Starter switch combine
251. revent in adver tent gear up landings A manual emergency gear extension system is provided in the event of electrical failure FLIGHT CONTROLS DESCRIPTION The aircraft has dual flight controls and can be flown from either the pilot or co pilot seat Dual pairs of foot pedals control rudder and nose wheel steering mechanisms Push pull tubes actu ate all metal flight control surfaces Rod end bearings are used through out the flight control systems These bearings are simple and require little maintenance other than occasional lu brication Longitudinal pitch trim is achieved through a trim control system that pivots the entire empennage around tailcone attachment points AILERON SYSTEM The ailerons are of all metal construction with beveled trailing edges Three hinges of machined extruded aluminum attach each aileron to aft wing spar outboard of wing flaps The ailerons link to the control wheel through push pull tubes and bellcranks Counterweights bal ancethe ailerons A spring loaded interconnect device indirectly joins aileron and rudder control systems to balance in lateral stability during flight maneuvers ORIGINAL ISSUE 12 22 2006 8 AIRPLANE FLIGHT MANUAL 7 3 SECTION VII MOONEY AIRPLANE AND SYSTEM DESCRIPTION M20TN RUDDER SYSTEM The rudder attaches to the aft vertical fin spar at four hinge points Push pull tubes and bellcranks link the rudder to the rudder pedals RUDDER TRIM SYSTEM The M20TN is equipped wit
252. rior panels Carefully follow the manufacturer s instructions when using commercial cleaning and finishing compounds Foam type shampoos may be used for routine cleaning of carpets To minimize carpet wetting keep foam type cleaners as dry as possible and gently rub in circles Use vacuum cleaner to remove foam and dry the materials Grease spots on carpet should be removed with jelly type spot lifter Do not saturate carpet with a solution which could damage backing materials Use a damp cloth to clean metal surfaces AIRPLANE FILE Certain miscellaneous data information and licenses are a part of the airplane file The following is a checklist of documents that must either be carried in the airplane or available on request of the proper authority 1 To be displayed in the airplane at all times a Aircraft Airworthiness Certificate FAA Form 8100 2 b Aircraft Registration Certificate FAA Form 8050 3 C Aircraft Radio Station License if transmitter installed FCC Form 556 2 To be carried in the airplane during all flight operations a Pilot s Operating Handbook including FAA Approved Flight Manual b Weight and Balance and associated papers latest copy ofthe Repair and Alteration Form FAA Form 337 if applicable C Equipment List NOTE The original weight and balance data and Equipment List are contained in SEC TION VI of this manual This manual is supplied with each new airplane pur AIRPLANE FLIGHT
253. rol regulates intensity ofthe placard lighting The right control provides avionics and instrument lighting Rotating the knobs clockwise turns ON and increases light intensity AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 30 Qe MOONEY SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION MAP LIGHT Map lights are installed on the bottom ofthe pilot and co pilot s wheel These lights are turned on when the INSTRUMENT light control on the panel is turned on The intensity ofthe map light may be adjusted with the MAP LITE knob located while facing the wheel on the right aft side of the pilot s and co pilot s control wheel CABIN LIGHTING Overhead lights illuminate the cabin All passenger overhead lights are controlled by POWER LITES switch located on the pilot s arm rest With Master Light Switch ON individual overhead cabin lights are controlled by rocker switches located on each passenger s arm rest excluding front seat passenger Front seat passenger s light switch is located forward of cabin door hinge on side panel CAUTION The Cabin Light rocker switches are connected directly to the battery Leaving the POWER LITES switch on indefinitely when the engine is shutdown will run down the batteries EXTERIOR LIGHTING Conventional navigation and high intensity strobe lights are installed on the wing tips and on the rudder trailing edge strobe light only Landing and Taxi lights are installed in the right and
254. rotection or arrival at approach minimums in a normal position to land VNAV also does not guarantee compliance with intermediate altitude constraints between the top of descent and the way point where the VNAV path terminates in terminal or enroute operations 5 If not previously defined the following default settings must be made in the SYSTEM SETUP menu of the G1000 prior to operation refer to Pilot s Guide for procedure if necessary a DIS SPD sets navigation units to nautical miles and knots b ALT VS fpm sets altitude units to feet and feet per minute DATUM WGS 84 sets map datum to WGS 84 see note below d POSITION deg min sets navigation grid units to decimal minutes example dd mm ss 45 30 30 in decimal minutes are 45 30 5 NOTE In some areas outside the United States datums other than WGS 84 or NAD 83 may be used If the G1000 is authorized for use by the appropriate Airworthiness author ity the required geodetic datum must be set in the G1000 prior to its use for naviga tion 6 Operation is prohibited north of 709 N and south of 709 S latitudes In addition operation is prohibited in the following two regions a North of 65 between 75 W and 120 W longitude and b South of 55 S between 1209 E and 1659 E longitude CAUTION CDI automatic source switching to the ILS on Nav 1 or 2 must be set to manual for instrument approach
255. rts of older oil in the system RIGINAL I E 12 22 2 1 6 ORIG SSU 006 MOONEY SECTION I M20TN GENERAL LANDING GEAR TYPE Electrically operated fully retractable tricycle gear with rubber shock discs The main wheels have hydraulically operated disc brakes The nose wheelis fully steerable 119 leftto 139 right of center Wheelbase gue se cp de Deua OU m UR DURER 6 7 1 2 201 9 cm Wheel Track c tete iE HE ter e babe 9 2 279 4 cm Tire Size eere ue iun 5 00 x 5 6 ply sabes n eee PANE du he eG ii 6 00 x 6 6 ply Tire Pressure pm DL wa x era Ub WI ER EX elite ete ey 49 PSI ate dee 42 PSI Minimum Turning Radius No brakes applied Highs D A DUE Eon ER ret Ken 40 ft 12 0 m Left Accent hrec eee S 48 ft 14 4 m MAXIMUM CERTIFICATED WEIGHTS Gross Weight coe SRI EDAD ON 3368 Lbs 1528 Kg Maximum Landing Weight 3200 Lbs 1452 Kg Useful Load No 5 1049 Lbs 475 8 Kg Baggage Area seas d Ce ME RR 120 Lbs 54 4 Kg Rear Storage Area 10 Lbs 4 5 Kg Cargo Rear
256. s at maximum weight FLIGHT LOAD FACTOR LIMITS Maximum Positive Load Factor Flaps Up e erp NU ERE ene 3 8 0 Flaps Down 33 Degrees ae xk hc t px da 2 0 4 Maximum Negative Load Factor Flaps Ups re n m ug ee de Ro 1 5 g Flaps DOWN em teo e bue quot cite 0 0 g FLIGHT CREW iom PH d Lm nd One Maximum passenger seating Three OPERATING LIMITATIONS When aircraft is not equipped with an approved oxygen system and flight operations above 12 000 ft are desired this airplane must be 1 Equipped with supplemental oxygen in accordance with FAR 23 1441 2 Operate in accordance with FAR 91 211 and 3 Equipped with avionics in accordance with FAR 91 or FAR 135 ALTERNATOR OPERATING LIMITATIONS IS 94 AMPS Above 30 5 inHg of manifold pressure only full rich mixture is permitted At altitudes above 22 000 feet power settings above 2300 RPM must be operated at 1675 F TIT or richer Above 12 000 ft the minimum manifold pressure is 15 inHg and the minimum RPM is 2 000 KINDS OF OPERATION LIMITS This is a Normal Category airplane certified for VFR IFR day or night operations when the re quired equipment is
257. s both ignition and starting functions Turning ignition key clock wise through L and BOTH to START position and then pushing forward on key and tacle engages starter Releasing key when engine starts allows switch to return by spring ac tion to BOTH position 13 ALTERNATOR FIELD SWITCH This switch cuts alternator field power from main buss to alternator 14 MASTER POWER SWITCH Master switch operates battery relay which controls battery power selected battery to main buss This switch cuts ALL ship power OFF except cabin overhead lights baggage compart ment light and electric clock 15 OPTIONAL Rotating Flashing Beacon etc 16 STROBE LIGHT SWITCH CIRCUIT BREAKER Strobe light combination switch circuit breaker turns wing tip and tail strobe lights ON Should a short occur the combination switch circuit breaker will automatically trip to the OFF position 17 NAVIGATION LIGHT NAV LITE SWITCH CIRCUIT BREAKER Navigation light combination switch circuit breaker turns wing tip and tail navigation lights ON Should a short occur the combination switch circuit breaker will automatically trip to the OFF position The glareshield and panel lights are also turned on when this switch is ON Control dim ming of either glareshield or panel lights with rotating switches on lower console 18 RECOGNITION LIGHT LITE If installed Recognition light combination switch circuit breaker turns recognition light ON Should a
258. s important Monitor the TIT display to avoid exceeding 1750 F limit To increase power first increase the mixture not necessarily to FULL RICH then increase RPM with the propeller control and then increase manifold pressure with the throttle control To de crease power decrease manifold pressure first with the throttle control and then decrease RPM with the propeller control When engine temperatures have stabi lized lean mixture to desired TIT FUEL TANK SELECTION 5 21522225 MADRE ESL a ate So sr Refs ON 14815 5 82 he EAR Lh deerat re i DE OPPOSITE TANK LOW bn ADEL ER OXYGEN SYSTEM OPTIONAL EQUIPMENT WARNING Greasy lipsticks and waxed mustaches have been known to ignite spontaneously inside oxygen masks Passengers should be suitably advised prior to flight For safely reasons NO SMOKING should be allowed in the airplane while oxygen is being used When ready to use the oxygen system proceed as follows Mask and HOSO EU SELECT either MIC or STD JEU biu ale Adjust mask to face and adjust metallic nose strap for snug mask fit Delivery PLUG INTO OUTLET assigned to that seat NOTE When the oxygen system is turned ON oxygen will flow continuously at the ap propriate r
259. s specifications Tachometer An instrument that indicates rotational speed of the engine The speed is shown as propeller revolutions per minute RPM Propeller The device that regulates RPM of the engine propeller by increasing or Governor decreasing the propeller pitch through a pitch change mechanism in the propeller hub METEOROLOGICAL TERMINOLOGY Above ground level Altitude as determined by pressure altitude and existing ambient tempera ture In standard atmosphere ISA density and pressure altitude are equal For a given pressure altitude the higher the temperature the higher the density altitude Indicated The altitude actually read from an altimeter when and only when baromet Altitude ric subscale Kollsman window has been set to Station Pressure ISA INTERNATIONAL STANDARD ATMOSPHERE assumes that 1 The air is a dry perfect gas 2 The temperature at sea level is 15 degrees Celsius 59 F 3 The pressure at sea level is 29 92 inches Hg 1013 2 MB 4 The temperature gradient from sea level to the altitude at which the temperature is 56 59C 69 7 F is 0 001989C 0 003564 F per foot OUTSIDE AIR TEMPERATURE The free air static temperature obtained either from in flight temperature indications or ground meteorological sources It is expressed in C Pressure The indicated altitude when Kollsman window is set to 29 92 In Hg or Altitude 1013 2 MB In this handbook altimeter instrument errors a
260. st COMPLETED MIX EFG Gs ttes AME as LOL IDE IDLE CUT OFF Propeller n Rer Re up hua ay FULL FWD High RPM Throttle Control ELSE Re SET TO CLOSED Fuel Boost Pump HIGH for 5 SEC or LOW for 25 SEC THEN SET TO OFF Engine Statt x ae ae ha RES follow NORMAL procedures FLOODED ENGINE START Before Starting Check List COMPLETED MIKUO IER EIE IDLE CUTOFF Throttle Control eee ten eb pere Ro 1 2 OPEN Ignition Switch TURN and PUSH TO START MIXt l e slowly advance toward RICH until engine starts EXTREME COLD WEATHER ENGINE START Refer to TCM Engine Operating Manual 01 18 for extreme cold weather starting procedures CAUTION For engine operation at outside air temperatures below 25 C 1392 the engine and engine oil should be preheated to at least 25 C 13 F before the engine is started NOTE START POWER warning light should illuminate when Magneto Starter switch is in START position NOTE Cranking should be limited to 30 seconds and several minutes allowed between cranking periods to permit the starter to cool Never engage starter while the pro peller is still
261. t Best Power 50 F Rich of Peak TIT Propeller Speed 2400 RPM Manifold Pressure 30 5 in HG Cruise Weight 3300 LB Outside Air Temp 16 C Altimeter Set to 29 92 True Airspeed 213 KTAS Configuration Clean Fuel Flow 20 7 GPH 25000 Ft Pressure Altitude AISA 30 65 0 34 C 30 4 C OAT 54 84 F 0 30 F 54 24 F RPM MAP KTAS GPH KTAS GPH KTAS GPH 24000 Ft Pressure Altitude AISA 30 63 C 0 32 C 30 2 C OAT 54 81 F 0 27 F 54 27 F RPM MAP KTAS GPH KTAS GPH KTAS GPH Some low power settings may not be attainable due to low cylinder or oil temperatures depending on ambient conditions AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 26 SECTION V M20TN PERFORMANCE SPEED and POWER SETTINGS vs ALTITUDE BEST POWER 22000 Ft Pressure Altitude AISA 30 59yC 0 28 C 30 2 C OAT 54 73 F 0 19 F 54 35 F RPM MAP KTAS GPH KTAS GPH KTAS GPH 20000 Ft Pressure Altitude AISA 30 55 0 24 C 30 6 C OAT 54 66 F 0 12 F 54 42 F KTAS GPH KTAS GPH KTAS Some low power settings not be attainable due to low cylinder or oil temperatures depending on ambient conditions ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL d 5 27
262. tacles marked HOIST POINT just outboard of each main gear Replace these eye bolts with jack point fixtures when itis necessary to liftthe aircraft with jacks The tail tie down point is part of the tail skid To Tie Down Aircraft 1 Park the airplane facing the wind 2 Fasten the co pilot seat belt through the flight control wheel Pull seat belt snug so flight con trols are immobilized 3 Fasten strong ground anchored chain or ropetothe installed wing tie down eye bolt and place wheel chocks fore and aft of each wheel 4 Fasten a strong ground anchored chain or rope through the tail skid JACKING When it is necessary to raise the aircraft off the ground 1 Install jack points in tie down mounting holes outboard of each main gear 2 Use standard aircraft jacks at both wing hoist points wing tie down eyebolt receptacles out board of the main gears While holding jack point in place raise jack to firmly contact jack point 3 Place a jack under front jack point Sta 5 51 to lift nose wheel 4 Raise aircraft keeping wings as nearly level as possible 5 Secure safety locks on each jack AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 8 4 A SECTION VIII M20TN HANDLING SERVICE AND MAINTENANCE CAUTION Do not raise the aircraft on jacks out of doors when wind velocity is over 8 KTS When lowering aircraft on jacks bleed off pressure on all jacks simultaneously and evenly to keep aircraft l
263. tches on spar Fold rear seat backs forward CLIMB OVER PULL off plastic cover from over inside latch PULL lock pin Pull red handle OPEN door and exit aircraft To VERIFY RE ENGAGEMENT of baggage door outside latch mechanism Open outside handle fully Close inside RED handle to engage pin into cam slide of latch mechanism Place lock pin in shaft hole to hold RED handle DOWN Replace cover CHECK amp operate outside handle in normal manner SPINS WARNING Up to 2 000 ft altitude may be lost in a one turn spin and recovery STALLS AT LOW ALTITUDE ARE EXTREMELY CRITICAL NOTE The best spin avoidance technique is to avoid flight conditions conducive to spin entry Low speed flight near stall should be approached with caution and exces sive flight control movements in this flight regime should be avoided Should an unintentional stall occur the aircraft should not be allowed to progress into a deep stall Fast but smooth stall recovery will minimize the risk of progressing into a spin If an unusual post stall attitude develops and results in a spin quick application of antispin procedures should shorten the recovery INTENTIONAL SPINS ARE PROHIBITED In the event of an inadvertent spin the following recovery procedure should be used les cres or ee Dar RETARD to IDLE AIMGFOLIS ou Ta a de C aces Ve ee Ea aar ove ees PA V NEUTRAL H dder iussu
264. th er service operate in the S band frequency to provide continuous uplink capabilities at any alti tude throughout North America Also available with the GDL 69A is XM s digital audio entertain ment which provides 130 plus channels of music news talk sports and information For detailed operating instructions see Garmin G 1000 Cockpit Reference Guide for the Mooney M20TN The TSO d KN 63 if installed is a complete 100 watt 200 channel remote DME system Dis tances up to 389 nm at line of sight altitude groundspeeds up to 999 knots and time to sta tion upto 99 minutes are computed digitally and displayed on the G 1000 PFD and controlled by the G 1000 interface controls Distance lock on is virtually instantaneous usually within one second with accurate groundspeed and time to station readouts following in less than a min ute For detailed operating instructions see Garmin G 1000 Cockpit Reference Guide for the Mooney M20TN The TSO d Becker ADF 3502 2 Automatic Direction Finder system if installed provides accu rate bearing to station in the 200 kHz to 1799 kHz frequency range complete with ADF ANT and BFO tuning modes plus audio output for station identification and monitoring AM broad casts It is displayed on the G 1000 PFD and controlled by the PFD interface controls For de tailed operating instructions see Garmin G 1000 Cockpit Reference Guide for the Mooney M20TN Traffic data detected by the L 3 Communications G
265. the system CAUTION Pushing LOW BOOST pump switch ON when engine is operating properly at idle con ditions will cause engine to run rough or quit due to excessive rich fuel mixture For this reason LOW BOOST should be turned off except where prescribed in the normal operating procedures 26 PITOT HEAT SWITCH CIRCUIT BREAKER Pitot heat combination switch circuit breaker turns heating elements within pitot tube on Should a short occur the combination switch circuit breaker will automatically trip to OFF position TOT HEAT annunciator light will illuminate BLUE when switch is ON and current is flowing through pitot heater On some export aircraft annunciator will illuminate AMBER when switch is OFF and will not be illuminated when ON and drawing current 27 ELEVATOR TRIM ELEC TRIM SWITCH Switch is normally left in ON position and serves as both a circuit protector and a master discon nect for the electric trim system in the event of a malfunction The Radio Master Switch must be ON before power is available to elevator trim system AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 7 10 4 SECTION VII M20TN AIRPLANE AND SYSTEM DESCRIPTION 28 THROTTLE CONTROL Push throttle control forward to increase engine power Pull throttle aft to decrease engine pow er Vernier control is optional 29 PROPELLER CONTROL Push propeller control forward to increase engine RPM pull control aftto decre
266. tion some RPM drop should always occur Normal indications are 25 to 75 RPM and a slight engine roughness as each magneto is switched OFF A drop in excess of 150 RPM may indicate a faulty magneto or fouled spark plugs AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 4 10 4 SECTION IV M20TN NORMAL PROCEDURES WARNING Continuous overboost operation may damage the engine and require engine in spection MINOR SPARK PLUG FOULING Minor spark plug fouling may be cleared by HOLD MANUALLY 2200 ADJUST FOR MAXIMUM PERFORMANCE wea th da RS Move Towards Idle Cutoff Until RPM Peaks DUI Hold For 10 Seconds ERE Return To Full Rich 1700 Magnetos RECHECK 50 RPM Difference With Max Drop Of 150 RPM Throttle urere ec bera CAU SERE SET TO IDLE 900 to 1000 RPM CAUTION Do not operate engine at a speed of more than 2000 RPM longer than necessary to test engine operations and observe engine instruments Proper engine cooling depends on forward speed Discontinue testing if temperature or pressure limits are approached WARNING Continuous overboost operation may damage the engine and require engine in spection BEFO
267. ts and Shoulder Harness SECURED Avionics and Autopilot CHECK Refer to Section IX Annunciator Lights CHECK Internal External 2 AS DESIRED Strobe Lights Rotating Beacon ON PilotSMIDdOW cues leider ae eret we e ERO b esset e HW Iba e e CLOSED Emergency Gear Extension RED Handle DOWN and LATCHED Parking Brake daca tes dae he eR ERN ERRARE DEO REP bb Ee EE ete HE nd bask RELEASE TAKEOFF Proper engine operation should be checked early in the takeoff roll Any significant indication of rough or sluggish engine response is reasonto discontinue takeoff When takeoff must be made over a gravel surface it is important that the throttle be applied SLOWLY This will allow the air craftto startrolling before high RPM is developed and gravel orloose material will be blown back from the propeller area instead of being pulled into it TAKEOFF NORMAL 2 Ur aut o ems me FULL RICH LER eal acute DLE RH ADVANCE SLOWLY TO FULL RPM 2500 RPM M MM E Watch manifold pressure adjust throttle as required to avoid overboost Annunclatot MeL S eoe tert de Be Bapt er p ee E CHECK Engine Instruments
268. turned to the tank selected The fuel injector pump forces liquid fuel into the metering unit assembly The fuel metering unit air throttle controls the amount of intake air admitted into the intake man ifold and meters the proportionate amount of fuel to the fuel manifold valve The assembly has three control units one for air in the air throttle assembly and two for the fuel control unit The manifold valve receives fuel from the metering unit When fuel pressure reaches approxi mately 3 5 PSI a check valve opens and admits fuel to six ports in the manifold valve one port for each fuel nozzle line The manifold valve also serves to provide a clean cut off of fuel to the cylinder when engine is shut down The injector nozzle lines connect the manifold valve to the six fuel injector nozzles The injector nozzles one per cylinder are air bleed type fuel nozzles which spray fuel directly into the intake port ofthe cylinder When engine is running flow through the nozzle is continuous and will enter the cylinder combustion chamber when the intake valve opens Since the size of the fuel nozzles are fixed the amount of fuel flowing through them is determined by the pressure applied For this reason fuel flow may be accurately determined by measuring fuel pressure at the manifold valve ENGINE COOLING AIR Ram air enters the forward part of upper cowl and flows through the cylinders intercoolers oil cooler and alternators using sever
269. uise power setting by approximately 5 KTAS An approximate adjustmentto range data shown in this manual can be made based on flight time planned with landing gear doors removed from aircraft For example using the above cruise speed decrease for a 5 hour flight will result in a decrease in range of approximately 25 N M SHRX SKTS va ne ERU 25 N M reduction in range CAUTION Zero wind conditions seldom occur In addition varying atmospheric conditions aircraft weight mechanical condition of the aircraft and piloting techniques all affect the actual flight time and fuel used during a flight It is the pilot s responsibility to determine the actual operating conditions and plan the flight accordingly ORIGINAL ISSUE 12 22 2006 AIRPLANE FLIGHT MANUAL li 5 3 SECTION V MOONEY PERFORMANCE M20TN TEMPERATURE CONVERSION 40 FAHRENHEIT 9 CELSIUS AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 5 4 A SECTION V M20TN PERFORMANCE CROSSWIND COMPONENT CHART DEMONSTRATED CROSS WIND IS 18 KNOTS THIS IS NOT A LIMITATION
270. ump ON for vapor suppression above 12 000 ft or if TIT is IET rising above 1450 F CLIMB BEST RATE Vy tas itum ewe ee 120 KIAS esce dicimur ben pd FULL Propeller es E eee derit Ye 2500 RPM Fuel Selector DELETE SET TO RIGHT OR LEFT TANK ree NI WEN ae FULL RICH 1350 F to 1450 TIT LOW Boost Pump ON for vapor suppression above 12 000 ft or if TIT is T rising above 1450 F CLIMB BEST ANGLE Vx 85 5 T REOR ione SEDIS Beene EQ FULL Propeller 2500 RPM Fuel Selector DELETE SET TO RIGHT OR LEFT TANK MIXU 5253 onere UE eor Dite FULL RICH 1350 F to 1450 TIT LOW Boost Pump ON for vapor suppression above 12 000 ft or if TIT is AU birgt cna edel dci rising above 1450 F NOTE Leaning may be required during CLIMB depending on atmospheric conditions CRUISE AIISDOGOG tea eiu e ares ACCELERATE to cruise airspeed TMOG 8 SP tore MATER EN UE SELECT setting Propeller er a eet eC ee SE
271. ut progressive insidious in onset and are most marked ataltitudes starting above 10 000 feet Night vision however can be impaired starting at altitudes lower than 10 000 feet Heavy smokers may experience early symptoms of hypoxia at altitudes lower than non smokers Use oxygen on flights above 10 000 feet and at anytime when symptoms appear HYPERVENTILATION Hyperventilation or over breathing is a disturbance of respiration that may occur in individuals as a result of emotional tension or anxiety Under conditions of emotional stress fright or pain breathing rate may increase causing increased lung ventilation although the carbon dioxide output of the body cells does not increase As a result carbon dioxide is washed out of the blood The most common symptoms of hyperventilation are dizziness hot and cold sensations tingling of the hands legs and feet tetany nausea sleepiness and finally unconsciousness Should symptoms occur that cannot definitely be identified as either hypoxia or hyperventilation try three orfour deep breaths of oxygen The symptoms should improve markedly ifthe condition was hypoxia recovery from hypoxia is rapid If the symptoms persist discontinue use of oxy gen consciously slow your breathing rate until symptoms clear then resume normal breathing rate Normal breathing can be aided by talking aloud ALCOHOL Common sense and scientific evidence dictate that you not fly as a crew member while unde
272. ve procedures except maintain approach speed appropriate for wind conditions Allow aircraft to crab until the landing flare Accomplish touchdown in a slight wing low sideslip low wing into wind and aircraft aligned with runway During landing roll position flight controls to counteract crosswind CAUTION Landing gear may retract during landing roll if landing gear switch is placed in the UP position TAXI AFTER LANDING tune bru belt AS REQUIRED Fuel Boost Pump Switches OFF Wing Flaps ze tal eek RU OR e Ad RETRACT Elevator Trim e DR EE TAKEOFF SETTING Avionics RadiOS Rev Eee eR RA UR AS REQUIRED Interior Exterior 8 AS DESIRED SHUTDOWN ee 1077 IDLE 900 RPM Interior Exterior OFF Pitot RIEN VENDI RO Er Lp ELT e OFF Magneto Starter Switch GROUNDING CHECK eoe e M IE LED LUE IDLE Cut OFF Alternator Field Switch
273. vice information in this section of the manual is limited to service procedures which the oper ator will normally perform or supervise Reference should be made to FAR Part 43 for informa tion regarding preventive maintenance which may be performed by a U S licensed pilot Itis wisetofollow a planned schedule of lubrication and preventive maintenance based on clima tic and flying conditions encountered in your locality Keep in touch with your Mooney Service Center and take advantage of his knowledge and expe rience He knows your airplane and how to maintain it Should an extraordinary or difficult prob lem arise concerning the repair or upkeep of your Mooney consult the Product Support Department Mooney Airplane Company Inc Louis Schreiner Field Kerrville TX 78028 Telephone 830 896 6000 or 800 331 3880 Email technicalsupport mooney com correspondence regarding your airplane should include the aircraft MODEL and SERIAL NUMBER These numbers can be found on an identification plate located on the lower aft por tion ofthe left side of the tailcone The aircraft Model and Serial Number must also be used when consulting either the Service amp Maintenance Manual or Illustrated Parts Catalog Service amp Maintenance Manuals and Illustrated Parts Catalogs for your airframe and sys tems excluding Avionics amp Navigation may be obtained from your Mooney Service Center Ser vice Bulletins and Service Instructions are avail
274. xhausts into the left tailpipe The left and right turbochargers exhaust out of the cowling through independenttailpipes The lefttailpipe also provides a ventforthe crankcase oil breath er system Inspections for cracking burn through etc is required during each maintenance activity and in spection of the tailpipes is recommended before each flight Particular attention should be paid to any crack burn through or loose tailpipe clamps that may allow exhaust to impinge on the firewall Do not attempt flight if the exhaust system is compromised FUEL INJECTION The fuel injection system is of the multi nozzle continuous flow type which controls fuel flow to match engine requirements Any change in air throttle position engine speed or a combination of these causes changes in fuel pressure in direct relation to engine requirements A manual mixture control is provided for precise leaning at any altitude and power setting A fuel flow sys temis installedfor digital read out offuel flow in gallons per hour However fuel flow is NOT to be used as reference for manual leaning Use the TIT gauge for this purpose The continuous flow system permits the use of a typical rotary vane pump with integral relief valve With this system there is no need for an intricate mechanism for timing fuel injection to the engine The fuel injector pump is equipped with a separator where vapor is separated by swirl ing augmenter system from the liquid fuel and re
275. xtension and other emergency procedures at safe altitude preferably with a check pilot 14 Use caution in mountainous terrain 15 Keep your airplane in good mechanical condition 16 Stay informed and alert fly in a sensible manner DON TS 1 Don t take off with frost ice or snow on the aircraft surfaces 2 Don t take off with less than minimum recommended fuel plus reserves 3 Don t fly in a reckless show off careless manner 4 Don t fly in thunderstorms or severe weather 5 Don t fly in possible icing conditions If you encounter icing conditions alter altitude or course to minimize exposure 6 Don t apply controls abruptly or with high forces that could exceed design loads of the airplane 7 Don t fly when physically or mentally exhausted 8 DON T TRUST TO LUCK AIRPLANE FLIGHT MANUAL ORIGINAL ISSUE 12 22 2006 10 4 SECTION X M20TN SAFETY INFORMATION GENERAL SOURCES OF INFORMATION There is a wealth of information available to the pilot created for the sole purpose of making your flying easier faster and safer Take advantage of this knowledge and be prepared for an emer gency in the remote event that one should occur You as a pilot also have certain responsibilities under government regulations These are designed for your own protection Compliance is not only beneficial but mandatory RULES AND REGULATIONS Federal Aviation Regulations Part 91 General Operating and F

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