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Mooney M20M, Pilot Operating Handbook

The Mooney M20M Pilot Operating Handbook is a comprehensive manual that provides essential information for operating this aircraft. You can download the manual for free from 88.208.23.73:8080. Access detailed procedures, checklists, and technical specifications to ensure safe and efficient flights for your Mooney M20M.

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190-02291-18 Rev. 5 

AFMS – GFC 500 Mooney M20M/M20R/M20S Series 

Page 4–5 

LATERAL MODES 

HEADING MODE (HDG) 

1.  HDG/TRK Knob ......................................................... Rotate to set heading bug to desired heading. 

2.  HDG Key ................................................................................................................................ PRESS 

 

The autopilot will turn the airplane in the direction of the heading bug. 

TRACK MODE (TRK) 

1.  HDG/TRK Knob ................................................................... Rotate to set track bug to desired track. 

2.  TRK Key ................................................................................................................................. PRESS 

 

The autopilot will turn the airplane in the direction of the track bug. 

NAVIGATION (VOR) 

This mode will only be available if the optional VHF navigator is installed. 

1. 

Navigation Source.   ................................................................................. SELECT CDI to VHF NAV

 

 

Tune and identify the station frequency.

 

2.  Course Pointer   ............................................................................... SET CDI to the Desired Course 

3.  Intercept Heading   ............................................................ ESTABLISH in HDG, TRK or ROL mode 

4.  NAV Key ................................................................................................................................. PRESS 

NOTE 

If the Course Deviation Indicator (CDI) is greater than one dot from center, the autopilot 
will arm the VOR mode when the NAV key is pressed. The pilot must ensure that the 
current heading will result in a capture of the selected course. If the CDI is one dot or less 
from center, the autopilot will enter the capture mode when the NAV key is pressed. 

NAVIGATION (GPS) 

This mode will only be available if the optional GPS navigator is installed. 

1.  Navigation Source ............................................................................................ SELECT CDI to GPS 

2.  Waypoint .......................................................................................... SELECT on Navigation Source 

3.  Course Pointer ..................................................................... VERIFY CDI set to the Desired Course 

4.  Intercept Heading ........................................................................ ESTABLISH in HDG or ROL mode 

5.  NAV Key ................................................................................................................................. PRESS 

NOTE 

If the Course Deviation Indicator (CDI) is greater than one dot from center, the autopilot 
will arm the GPS mode. The pilot must ensure that the current heading will result in a 
capture of the selected course. If the CDI is one dot or less from center, the autopilot will 
enter the capture mode when the NAV key is pressed. 

 

 

Summary of Contents for M20M

Page 1: ...MBER REGISTRATIONNUMBER FAAAPPROVED 3 16 a HenryA Arrnstrong Manager Airplane CertificationOftice FEDERALAMATION ADMINISTRATION FortWith Texas 76193 0150 FAAAPPROVED in Normal Category based on CAR PA...

Page 2: ......

Page 3: ...onvenient manner to enable you to use the manual as a reference Your cooperation in reporting presentationand contentrecommendationsissolicited REVISING THE MANUAL The i pages of this manual contain a...

Page 4: ......

Page 5: ...inal 2 3 thru 2 6 A 2 7 thru 2 10 original 2 11 2 12 A 2 13 original 2 14 A 2 15 thh 2 20 original 3 1 A 3 2 thru 3 5 original 3 6 A 3 7 8 original 3 9 3 10 A 3 11 thru 3 14 original 3 15thru3 18 A 4...

Page 6: ...nal 6 6 6 7 A 6 8 thru 12 original 6 13 A 6 14thru i 28 original 7 1 7 2 A 7 3 thru 7 7 0igina1 7 8 7 9 A 7 10t t h 7 15 Original 7 16 thru 7 23 A 7 24 thru 7 30 original 8 1 thru 810 Original 9 1 thr...

Page 7: ...ion o f Revisions Revision N u m b e r Revision Pages A T P Congrat ithnr iv 1 5 2 3 2 4 245 2 11 2 12 2 14 3 1 3 10 4 8 4 10 7 8 7 9 7 16 7 17 1 3 1 7 2 5 2 6 3 63 9 4 14 6 13 7 1 1 6 3 17 3 18 53 7...

Page 8: ...C O R P O R A T I O N LOUIS SCHREINER FIELD KERRVILLE TEXAS 78028 LOG OF REVISIONS ISSUED 3 90 Date black lines in the narsin POHIAPM NO 3501 FAA Approved indicated by vertical Description o f Revisio...

Page 9: ...UCTION TITLE CONTENTS SECTION GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMALPROCEDURES PERFORMANCE WElGHT BALANCE AIRPLANE SYSTEM DESCRIPTIONS HANDLING SERVICE MAINTENANCE SUPPLEMENTALDATA SAFETY OPE...

Page 10: ...INTRODUCTION MOONEY MODEL M20M BLANK ISSUED 3 90...

Page 11: ...WEIGHTS 1 5 CABIN ENTRY DIMENSIONS 1 5 BAGGAGE SPACE AND ENTRY DIMENSIONS 1 5 SPECIFICLOADINGS 1 6 IDENTIFICATIONPLATE 1 5 SYMBOLS ABBREVIATIONS TERMINOLOGY 1 6 GENERAL AIRSPEED TERMINOLOGY SYMBOLS 1...

Page 12: ...SECTION I GENERAL MOONEY MODEL M20M FIGURE 1 1 THREE VIEW ISSUED 3 90...

Page 13: ...safety practices servicing and maintenancerequirementspub lished in this POHIAFM are considered mandatoryfor the ContinuedAirworthiness of this airplane in a condlion equalto that of its original manu...

Page 14: ...eratorsManual Above 3 0 F lo C Ambient Air S L SAE40 or SAE 15W50 Below 30 F lo C Ambient Air S L SAE 30 or 20W30 Total Oil Capacity I 0Qts 9 5 liters Minimumfor Flight 6 Qts 5 7 liters 0 1 1 Filter F...

Page 15: ...AGGAGE SPACEAND ENTRY DIMENSIONS Compartment Wdth 24 In 60 9 cm CompartmentLength 43 In 109 2 cm Compartment Height 35 In 88 9 cm Compartment Volume 20 9 Cu Ft 2 cubic meters Cargo Area with rear seat...

Page 16: ...highest speed permissiblewith wing flaps in a prescribed extended posilon W e MAXIMUM LANDINGGEAR EXTENDEDSPEED The maximum speed at which an aircraflcan besafely flown with the landing gear extended...

Page 17: ...be limiting 9 Accelerationdue to gravity Service The maximum atiude at which aircraft at gross weight hasthe Ceiling capability of climbing at the rateof 100ftlmin ENGINECONTROLS8 INSTRUMENTSTERMINOL...

Page 18: ...TERMINOLOGY Arm The horizontaldistancefrom the referencedatumto the center of gravity C G of an item Basic The actual weight of the airplane and includes all operating Empty equipment includingoption...

Page 19: ...stion Useful Load The basic empty weight subtracted from the maximum weight of the aircraft This load consists of the pilot crew if applicable fuel passengers and baggage MEASUREMENTCONVERSION TABLES...

Page 20: ...s 1 pint 1 032 U S dry pints 1 201 U S liquid pts 34 678 cubic inches 1 quart 1 032 U S dry quarts 1 201 U S liquid qts 69 354 cubic inches 1 gallon 1 201 U S 277 420 cubic inches 568 26 milliliters 1...

Page 21: ...TATIONS 2 7 WEIGHT LIMITS 2 8 CENTER OF GRAVITY GEAR DOWN 2 8 MANEUVER LIMITS 2 8 FLIGHT LOAD FACTOR LIMITS 2 8 FLIGHT CREW 2 8 OPERATING LIMITATIONS 2 9 OXYGEN SYSTEM LIMITATIONS 2 9 KINDS OF OPERATI...

Page 22: ...Indicator Marklngs chart F gure 2 2 are bas on Alrspeed Calibration data shown in Section V with the normal statlc source If the alternate static source is being used ample margins should be observed...

Page 23: ...91140 Gear Extension Max Speed for 1041106 Gear Retraction Do not exceed this speed ex cept in smooth air and then only with cau tion Do not make full or abrupt control move ment above this speed Do n...

Page 24: ...Range Radial Red Line 59110 WAS 66 174 WAS 174 195 KlAS 195WAS Lower limit is maximum weight VW in landing configu ration Upper limit is maxi mum speed permissable with flaps ex tended Lower limit is...

Page 25: ...l Pressure NormalOperating 55 95 PSI Minimum IDLE ONLY 25 PSI Maximum cold oil 115 PSI Oil Specification MlL L 22851 and TEXlRON LycomingApproved oils Fuel Grade Color IOOLL Blue or 100octane Green Nu...

Page 26: ...F 500 F Head 121 260 260 Temperature Oil No Redline 100 245 F 245 F Temperature 37 1 8 118 Oil 25 0 PSI 55 95 PSI 25 55 PSI 115 PSI Pressure IDLE ONLY 95 115 PSI Fuel Pressure 15 PSI 24 55 PSI 15 24 P...

Page 27: ...2 7 liters Fuel Grade and color 100LL low lead blue or 100 green is approved N N N N N N N CAUTION N N N N N N N To reduce the possibility of ice formation within the aircraft or engine fuel system it...

Page 28: ...cluding spins are prohibited I NOTE I Up to 500 foot altitude loss may occur during stalls at maximum weight Maximum Positive Load Factor Flaps Up 3 8g FlapsDown 33 e rees 2 0 g Maximum Neaative Load...

Page 29: ...e pilot must determine that the applicable operating rules requirementsfor each kind of operation are met I OPERATIONSIN KNOWN ICING CONDITIONSARE PROHIBITED l v Autopilot Limitations See Section IX K...

Page 30: ...TURE INDICATOR ALTERNATOR LOAD METER ALTERNATOR LANDING GEAR POSITION INDICATOR SEAT BELT SHOULDER HARNESS FOR EACH OCCUPANT OXYGEN MASK FOR EACH OCCUPANT I POSITIONS LIGHTS I 3 I STROBE LIGHTS ANTI C...

Page 31: ...GLARESHIELD CLOCK WlHSVMEPSECOND HAND or DIGITAL NAVIGATIONSYSTEM APPROPRIATE TO FACILITIESBEING USED BAllERY VACUUM SYSEM INDICATOR FUELBOOST PUMP PILOTSOPERATINGHANDBOOK AIRPLANEFLIGHTMANUAL PITOT H...

Page 32: ...m IS ILmMlED AH OPERA110W FURn INTO KNOW EIffi J C N S IS PROHIBIIED NO MROBME WNNYERS INCLUDNG SPNS ARE 0 OTHER 0F ERP llNG UUilAllONS W H MJS BE COUPFLEDmM YMM O P E B W 4 G l H S A R F V X N l H S...

Page 33: ...UH PANEL FWD OF ARM REST WARNING DO NOT EXCEED 170 LBS 77 1 Kg ON THIS SEAT BACK SEE AIRCRAFT LOADINGSCHEDULE DATA FOR BAGGAGE COMPARTMENTALLOWABLE FWD END OF REAR SEAT BOTTOM STRUCTURE TOP RT RADIO...

Page 34: ...c m P I G LOCK PIN I GEAR UP 106 KlAS ABOVE INSIDE BAGGAGE DOOR HANDLE I TO CLOSE I I SORE HAIlaE 2 BGERT L O C 1 PIN LHnKLCDYER 5 LOCK WOR 1 L W INSTRPNL BELOW CONTFOLWEEL SHAFT OPEN BELOWPILOTS 32KI...

Page 35: ...N HAT RACK SHELF AROUND EACH OXYGEN OUTLET ON OVERHEAD PANEL CONSOLE ON CONTROL KNOB PULL ON TOP OF BAGGAGE DOOR JAMB FLOORBOARD BETWEEN SEATS ON UPPER GLARESHIELD BETWEEN SEATS ON 4 PUSH TO RELEASE E...

Page 36: ...ed I I I LEVEL HERE I MAINTAIN I ONLY I HYDRAULIC OIL RESERVOIR USE AVIATORS OXYGEN ONLY SEE PILOT S OPERATING HANDBOOK FOR FILLING PRESSURES INSIDE OXYGEN FILLER DOOR ENGINE OIL OIL INSTALLED IN THIS...

Page 37: ...PS UNDERSIDE OF WlNG 2 PLCS AFT OF UH COWL FLAP 1PLC UNDER TAILCONE AFT OF WlNG TIE PITUT DRAIN n HORIZ STAB LIE RUDDERTIE BOTH SIDES UNDER LEFT WlNG LIE NEAR FUSELAGE UNDER WING NEAR SUMP DRAINS 183...

Page 38: ...ADD ACID I NEVER FILL OVER BAFFLE NOR MORETHAN 114 OVER THE TOPS OF SEPARATORS FULLY CHARGEDSPECIFIC GRAVITY 1 275 RECHARGEREQUIRED WHEN SP GR REACHES 1 225 CHARGING RATES START4 AMPERES FINISH 2AMPE...

Page 39: ...PULL KNOB PULL ON P T CONSOLE ON PULL KNOB CONSOLE ON PULL KNOB PHONE i PARK BRAKE LWR UH INSTR AND OR LWR R H C B PANEL SLAM DOOR ABOVE INSIDE DOOR HANDLE OVERHEAD BETWEEN PILOT CO PILOT CABIN LTS AF...

Page 40: ...SECTION II MOONEY LIMITATIONS MODEL M20M OPTIONAL See Section IX Supplementsfor Optional System s Placards Required...

Page 41: ...N FLAPSFAILURE FULL CLOSED POSITION 3 9 HIGH CYLINDERHEADTEMPERATURE 3 9 HIGH OILTEMPERATURE 3 10 LOWOIL PRESSURE 3 10 LOWFUELPRESSURE 3 10 ENGINE DRIVEN FUEL PUMP FAILURE 3 10 FUELVAPOR SUPPRESSION...

Page 42: ...ECTION Ill MOONEY EMERGENCY PROCEDURES MODEL M20M UNLATCHED DOORS IN FLIGHT 3 15 CABIN 3 15 BAGGAGE 3 16 ICEPROTECTION 3 16 EMERGENCY EXIT OF AIRCRAFT 3 17 SPINS 3 17 OTHEREMERGENCIES 3 18 ISSUED 3 90...

Page 43: ...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 determinethe best course of a...

Page 44: ...52 kg I23 KlAS 2900 Ibl 1315 kg 117 KlAS 2600 lbl1179 kg 111 KlAS Precautionary Landing with Engine Power Flaps DOWN 75 KlAS recautionary anding above 3200 Lbs 80 KlAS Emergency Descent Gear UP Smooth...

Page 45: ...enchAIC ONLY AMBER light indicates power is NOT applied to heater Suction is below 4 25 in Hg RED Suction is above 5 2 in Hg RED I NOTE 1 When either a steady HI or flashing LO VAC light is illuminate...

Page 46: ...FUGHT RESTART PROCEDURES Airspeed 85 KlAS minimum u e l elecior S T OTHERTANK FuelPressure Verify in GreenArc Fuel Boost Pump ONto start lkgi e diive fuel pump may have failed Fuel Boost Pump O f f if...

Page 47: ...ine 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 OUT the control labeled AL...

Page 48: ...If a turbocharger failure is a result of a loose disconnected or burned through exhaust then a serious fire hazard exists If a failure in the exhaust system is suspected in flight shut down the engine...

Page 49: ...Ror L or BOW If roughness disappearson singie magneto monitor power and continue on selected magneto I IMTARNlNGll I II IIII1111111 The engine may quit completely when one magneto is switched off if...

Page 50: ...Repeat above procedures until uel re ure stabilizes LANDAS SOONAS POSSIBLE ENGINE DRIVEN FUEL PUMP FAILURE IAn engine driven fuel pump failure is probable when low fuel pressure is indicated and when...

Page 51: ...If fire is not extinguished attempt to increaseairflow over the engine by increasing glide speed and open cowl flap Proceed with FORCED LANDING EMERGENCY as descrrbed on page 3 13 DO NOT attempt an en...

Page 52: ...resulting in less horizontal distance traveled than a descent at 195 KIAS Additionally a descent at 165 KlAS will provide a smoother ride and less pilot work load THEREFORE The following procedureis...

Page 53: ...nding procedures Approach Airspeed 80 KlAS Use a flatter approach angle than normal with power as necessaryuntil a smooth touchdown is assured Expect landing distance over a 50 feet obstacle Ref Secti...

Page 54: ...ALTERNATOR FAILURE If alternators will not reset Non esentialelectrical equipment OFF to conserve battery power LAND AS SOON AS PRACTICABLE Battery endurancewill depend upon battery condition and the...

Page 55: ...icall referto F A I L U OFL NG G TO EXTEND ELECTRICALLY If above procedures do not initiate retraction process check emergency manual extension lever on floor for proper position VACUUM en HVLO VAC an...

Page 56: ...intermediate position depending upon speed of aircraft There will be considerable wlnd noise loose objects inthe vicinity of the open door may exit the aircraft There is no way to shut and latchthe do...

Page 57: ...dtouchdown W h ice accumulationsof 1 inch or less use no more than 15 wing flaps for approach and landing Foriceaccumulationof 1inch or more fly approachesand landingwith flaps retractedto maintainbet...

Page 58: ...izethe risk of progressing into a spin If an unusual post stall attitude develops and results in a spin quick applicationof antispin procedures should shortenthe recovery INTENTIONALSPINS ARE PROHIBIT...

Page 59: ...EFORETAXI 4 10 TAXI 4 11 BEFORE TAKEOFF 4 11 TAKEOFF PROCEDURES 4 12 CLIMB PROCEDURES 4 12 CLIMB CRUISE CLIMB 4 12 CLIMB BEST RATE 4 13 CLIMB BEST ANGLE 4 13 CRUISE PROCEDURES 4 13 FUELTANK SELECTION...

Page 60: ...SECTION IV NORMAL PROCEDURES MOONEY MODEL M20M ISSUED 3 90...

Page 61: ...res of the airplane are presented These procedures are provided to present a source of reference and review and to supply information on procedures which are the same for all aircraft Pilots should fa...

Page 62: ...S ENROUTE CLIMB GEAR and FLAPS UP Best Rate of Climb 105KlAS Best Angle of Climb 85 KlAS LANDING APPROACH 3200 Ibs NormalApproach Flaps 10 degrees 80 KlAS NormalApproach Flaps 33 degrees 75 KlAS Short...

Page 63: ...ng Gascolator I W Tank Pull Gascolator ring 5 seconds Lt Tank PullGascolator ring 5 seconds Oxygen Supply Control Knob OFF Oxygen Pressure Gauge CHECK Verify adequate oxygen supiy f trip iiuse of oxyg...

Page 64: ...P I NOTE I The optional visual fuel quantity gauge is to be use for partial refueling purposes only DO NOT use for preflight quantity check Tiedown REMOVE Wheel chock REMOVE Main Landing Gear shock di...

Page 65: ...free of water sediment other contamination VERIFY proper fuel BLUE 100LL GREEN lOO VERIFY drain closes and does not leak Right main ear shock discs tire doors CHECK Wheel choc REMOVE General Skin Cond...

Page 66: ...general informkon briefing Referto SECTION IXfor Optional Equipment Procedures and Checks Obtain local information prior to engine start IENGINESTART I l hIoTE l When starting engine using the approve...

Page 67: ...tteries be fully chargedto operate aircraft Electrical componentsmay also be damaged if aircraft is operated when batteries are low Fuel Boost Pump OFF PropellerArea CLEAR Magneto Starter Sw iich TbRN...

Page 68: ...IME IF ENGINE IS HEAT SOAKED MagnetoIStarterSwitch TURN PUSHto START releaseto BOTH when engine staffs IDLE700 750 RPM SEE EMAINING ENGINE ST WT PROCEDURES ABOVE I I BEFORE TAXI I Engine Start Checkli...

Page 69: ...othly each magneto 50 ninimum 3ED 3PM ITH on each magneto separately 150 RPM RPM MAX difference I NOTE I An absence of RPM drop may be an indication of faulty magneto grounding or improper timing If t...

Page 70: ...ttle to lower manifold pressure below 38 in Hg and continue flight As the oil warms above 100 F throttle can be moved to full throttle position and controller will maintain proper manifold pressurefor...

Page 71: ...ations may result in some fuel pressure fluctuations when the throttle is reduced If fluctuationsoccur turn Boost PumpSvvltch ON until cooling has alleviated fluctuations Propeller Set RPMto selecteds...

Page 72: ...fects on cruise speedwll result Cowl Flaps 112Open Approx loss in TAS 2 5 KTS Enginetemperatures STABILIZEat cruise condition RudderTrim As Desired VUlen ncreasingpowerakvaysreturnmixluretoMIrich then...

Page 73: ...ing the mixture to peak TIT during descent will save fuel and will eliminate any engine roughness associated with an overly rich mixture setting During descent engine MP will tend to increaseas the ai...

Page 74: ...isual indicator Boost Pump ON Fuel Selector FULLEST TANK Wing flaps AS DESIRED FULLdown below 110 KIAS ElevatorTrim AS DESIRED Rudder Trim AS DESIRED N N N N N N N CAUTION N N N N N N N To minimize co...

Page 75: ...in approach speed appropriate for the wind conditions Allow aircraft to crab until the landing flare Accomplish the touchdown in a slight wing low sideslip low wing into the wind and the aircraft alig...

Page 76: ...RING THE AIRCRAF 1 MagnetoIStarterSwitch VERIFY OFF Key removed Master Switch VERIFY OFF Radio Master Switch Verify OFF Rocker Switches Verify OFF Interior Light Switches VERIFY OFF Parking Brake RELE...

Page 77: ...ALTERNATE STATICSYSTEM 5 10 ALTIMETER CORRECTION PRIMARY STATIC SYSTEM 5 11 ALTIMETER CORRECTION ALTERNATE STATIC SYSTEM 5 12 STALLSPEEDVSANGLE OFBANK 5 13 TAKEOFF DISTANCE HARD SURFACE 5 14 TAKEOFF...

Page 78: ...SECTION V PERFORMANCE MOONEY MODEL M20M ISSUED 3 90...

Page 79: ...mental conditions Mechanical or aerodynamic changes are not authorized because they can affect the performance or tight characteristics of the air plane The effect of such things as soft runways slope...

Page 80: ...in TIT or until best power TIT is obtained whatever is desired Severalthrottle and mixtureadjustments may be required before peakTITandthe desired cruise manifoldpressureare obtained 3 Under condition...

Page 81: ...r example using the above speed decrement for the cowl flap 112 open for a 5 hour flight w ll result in the following decrease in range 5HRX2 5KTS 12 5 N M reduction in range The Mission Profile Chart...

Page 82: ...SECTION V PERFORMANCE MOONEY MODEL M20M 5 6 ISSUED 3 90...

Page 83: ...ONENT CHART SECTION V PERFORMANCE MAXIMUM DEMONSTRATED CROSSWIND I S 1 3 KNOTS EXAMPLE1 WIND SPEED 10 KNOTS ANGLE BETWEEN WIND DIRECTION AND FLIG T PATH 20 HEADWIND COMPONENT 9 5 KNOTS CROSSWIND COMPO...

Page 84: ...GEAR UP FLAPS UP 200 190 180 170 I 160 I R 150 a V o 2 140 R W 130 o I 5 120 I 5 110 u 100 90 80 70 60 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200 IAS INDICATED AIRSPEED KNOTS NOTE WlICAl...

Page 85: ...YSTEM GEAR AND FLAPS DOWN EXAMPLE GIVEN IAS 80 KTS FLAPS 10 POWER OFF FINDt CAS 79 KTS NOTE INDICATED AIRSPEED ASSUMES ZERO INSTRUMENT ERROR 140 130 V I 120 Y t 1 1 0 W w ERING a 2 100 H 6 90 I 6 i z...

Page 86: ...AR KlAS FLAPS FLAPS FLAPS UP DN DN KlAS 1oO 33O KlAS KtAS NOTE The minus sign indicates subtraction of the given numbers from KlAS to obtain the corrected airspeed CONDITIONS Power ON Storm Window Ven...

Page 87: ...0 12 N0TE The minus sign indicates subtraction of the given numbersfrom the indicated pressureto obtain altitude assuming zero instrument error Gear Gear Gear Flaps Dnl10 Dn133 UP Flaps Flaps 4 7 4 4...

Page 88: ...R UP FLAPS FLAPS DN UP lo033O 20 0 7 12 9 16 0 20 29 19 34 47 33 47 71 39 62 97 43 78 127 48 77 84 102 128 139 158 185 215 GEAR GEAR UP FLAPS FLAPS UP lo03 3 30 0 10 18 14 24 0 31 45 29 51 72 50 72 10...

Page 89: ...SECTION V PERFORMANCE ISSUED 3 90 5 13...

Page 90: ...SECTION V PERFORMANCE MOONEY MODEL M20M 5 14 ISSUED 3 90...

Page 91: ...MOONEY MODEL M20M SECTION V PERFORMANCE ISSUED 3 90 5 1 5...

Page 92: ...aenR U P FLAPS UP 1500 1400 RATE OP CLIMB 1300 lgoo 1100 1000 900 m o P 9 0 b j so0 400 300 eoo i w 0 00 70 60 so 40 30 40 10 o 10 eo 30 40 ao 60 3368 ww 3eoo 3100 3000 P O O esaa eroo WElGHTiaS OUTSI...

Page 93: ......

Page 94: ...MOONEY MODEL M20M 5 1 8 ISSUED 3 90...

Page 95: ......

Page 96: ...1 7 20000 25 20 6 17 6 16 6 13 3 12 O 25000 35 20 5 16 6 13 3 12 l NOTE1 1 PEAK T I T INDICATES PEAK TIT OR 1750 DEGREES F TIT 2 BEST POWER AT 34 In Hg 2400 RPM I S 1650 DEGREES F TIT 3 WHEN OPERATING...

Page 97: ...RPM PEAK T I T...

Page 98: ...s Closed Range Includes Warmup Taxl Takeoff R A N G E Max Power C L l m b Descent Plus 4 5 Mlnutes Reserve a t Cruise Power 3368 LBS 1528 KGS 80 60 40 20 0 2 0 4 0 60 600 ZtfiGE _ B O A U T I MItgp 11...

Page 99: ...MOONEY SECTION V MODEL M20M PERFORMANCE ISSUED 3 90 5 23...

Page 100: ...TIAL PRESSURE ALT 18000 FINAL PRESSURE ALTl TIME TO DESCEND1 24 0 5 0 19 MINUTES FUEL TO DESCEND1 3 8 0 8 3 0 GALLONSC14 39 3 03 11 36 Li DISTANCE TO DESCEND 69 0 13 0 56 0 NAUTICAL MILES 25000 t20000...

Page 101: ...PAVED LEVEL DRY BRAKING MAXIMUM EXAMPLE8 OAT 150 C PRESSURE 6000 FT ALTITUDE WEIGHT 2800 LBS 1270 KGS HEADWIND 4 KTS COMPONENT GROUND ROLL 1350 FT 411 M TOTAL LANDING 2800 FT 853 M eOOo 600 DISTANCE 5...

Page 102: ...SECTION V PERFORMANCE MOONEY MODEL M20M 5 26 ISSUED 3 90...

Page 103: ...e Fuel Zero Wind Cowl Flaps Closed Mlsslon Proflles Allow For Warmup TaxL TakeoQf MISSION PROFILE 200 N M Max Power Cllmb Crulse and Descent 3368 LBS 1598 KGS OUTSIDE AIR TEMPERATURE OC TOTAL MISSION...

Page 104: ...SECTION V PERFORMANCE MOONEY MODEL M20M 5 28 ISSUED 3 90...

Page 105: ...AIIow For Warmup TaxC Takeoff MISSION PROFILE 600 NtM Max Power Cllnb Crulse and Descent 3369 LBS 1Se8 KGS 80 60 40 90 0 20 40 60 3 2 3 4 3 6 3 8 4 0 4 9 4 4 4 6 4 8 S O 55 60 70 75 TOTAL MISSION TIME...

Page 106: ...ProFlles Allow For Warmup Taxb Takeoff MISSION PROFILE 800 N M Max Power Cllmb Crulse and Descent 3368 LBS 1520 KGS 80 60 40 20 0 20 40 60 4 4 4 6 4 8 3 O Ssp 5 4 5 6 S 0 6 O 00 OUTS ID AIR TEMPERATUR...

Page 107: ...OF GRAVIN LIMITS 6 8 FIXED BALLAST 6 9 PILOTS LOADING GUIDE 6 10 EQUIPMENT LIST 6 11 NOTE The empty weight center of gravity and equipment list for the airplane as delivered from Mooney Aircraft Corp...

Page 108: ...all such changes is provided on page 6 5 This form if properly maintained will enable you to determinethe current weight and balance status of the airplane for load scheduling The weight and balance...

Page 109: ...ee 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...

Page 110: ...ED WT a CG Fonord of M n Vheelsl J S X J d n n 2 s m c n l n n V e c g h t p f W I M M c e B r h r m Totatmelght CG Formrd of h M d N o s e v h F d of Allxt aft Ham Vheels M e centers VT am WH Lvn b C...

Page 111: ...MOONEY MODEL M20M SECTION VI WEIGHT AND BALANCE M2OM WT BAL RECORD ISSUED 3 90 6 5...

Page 112: ...SECTION VI WEIGHT AND BALANCE MOONEY M20M Cargo loaded in rear seat area with seat backsfolded down should have center of gravity over fuselage station 70 7 6 6 R R l A 1 96 ISSUED 3 90...

Page 113: ......

Page 114: ...SECTION VI WEIGHT AND BALANCE MOONEY MODEL M20M 6 8 ISSUED 3 90...

Page 115: ...ainthe center of gravity enevelope The aircraft should be weighed and a new center of gravity established as defined in the airplane weighing computationon page 6 4 Check the weight and C G on the Fix...

Page 116: ...nd enter these weights and moment11000values in the proper sub columns in the Problem Form on page 6 6 Step 3 Proceed as in Step 2 to account for the passengers in seats 3 and 4 Enter the weight and v...

Page 117: ...re If additional equipment is to be installed it must be done in accordance with the referencedrawingor a separate FAA approval I NOTE I Positive arms are distances aft of the airplane datum Negative...

Page 118: ...DAY M EQ A YEAR ITEM N 0 I 1 A 2 A 3 A WEIGHT KQ POUNDS C 2 81 612 6 08 13 4 8 94 19 7 ITEM DESCRIPTION A FIXED BALLAST WEIGHT 501 INSTL WEIGHT 503 INSTL WEIGHT 505 INSTL ARM 53241 209 SO C532 l 209 S...

Page 119: ...600417 6 0 0 4 2 3 ITEM N O 1 2 3 B 4 B 5 ITEM D E S C R I P T I O N B POWERPLANT ACCESSORIES ENGINE LYCOMING TIO 540 AFlA INCLUDES STARTER ALTERNATORS 2 O I L FILTER O I L RADIATOR PROP GOV TURBOCHAR...

Page 120: ......

Page 121: ...13C 14C 15C 16C 17C 18C 19C 20C 21C ITEM DESCRIPTION C ELECTRICAL SYSTEM CON T E L T D M ELT 8 HOURMETER INSTALLATION E L T ARNAV ELT 100 REF D R A W I N G 810152 950241 810152 WEIGHT KQ POUNDS 1 63...

Page 122: ...N 2 6 PLY RATING 6 00 X 6 TYPE I11 W TUBES NOSE WHEEL ASSEMBLY 1 TIRE NOSE 1 6 PLY RATING 5 00 X 5 TYPE I11 W TUBE MASTER CYLINDER BRAKE 2 VALVE PARKING BRAKE REF D R A W I N G 520029 520029 520029 52...

Page 123: ...E 2E 3E 4E 5E 6E 7E 8E 9E 1 O E 1 1 E 12E REF I l R A W I N G 820336 I 820336 ITEM DESCRIPTION E INSTRUMENTS G Y R O HORIZON DIRECTIONAL GYRO CLOCK PANEL MOUNTED OAT GAUGE INDICATOR VERTICAL SPEED IND...

Page 124: ...TALLED X X MU DAY M E Q 2 YEAR ITEM NO 13E 14E 15E 16E 17E 18E 19E 20E ITEM DESCRIPTIUN E INSTRUMENTS CON T ANNUNCIATUR PANEL MAGNETIC DIRECTION INDICATOR REFl D R A W I N G 820336 130323 WEIGHT C K 5...

Page 125: ...POUNDS 2 58 5 68 Clm54 3 4 2 45 5 41 14 16 31 21 5 59 1232 C2 69 5 9 3 25 3 5 ITEM N u I 1F 2F 3F 4F 57 6F 7F ITEM DESCRIPTION F MISCELLANEOUS SYSTEMS VACUUM SYSTEM INSTALLATION VACUUM PUMP STAND BY...

Page 126: ...I S AT FWD SEAT POSITION ITEM NU 1G 2G 3G 4G 5G 6G 7G 8 G 9 G 10G 1lG REF D R A W I N G 130303 140214 140262 140295 130331 130331 ITEM DESCRIPTION G CABIN ACCOMODATIONS SUN VISORS 2 SHOULDER HARNESS...

Page 127: ...a 3 11 fj 1 s N 3 IdvW S3H3NI W t l d H V 3 A IH U3 W Ava OW SfINnOd c6 1 lH313M E N 1 M tJ a d 3 a SLOlIdOlnV 8 S3INDIAV H NOIldItl3S3tI 1 1 3 1 1 HZ1 H T T HOT H6 H8 HL H9 HS HP HE HZ H I ON w 131I...

Page 128: ...K IF CINCHES INSTALLED EQUIPMENT L I S T M o I D A Y M E Q 2 YEAR ARM ITEM NO 13H 14H 15H 16H 17H 18H 19H 20H 21H 22H 23H 24H REF D R A W I N G I T E M DESCRIPTION H AVIONICS AUTOPILOTS WEIGHT KQ POUN...

Page 129: ...PMENT L I S T MARK I F INCHES INSTALLED M 0 D A Y M E Q 3 YEAR ITEM NO 25H 26H 27H 28H 29H 30H 31H 32H 33H 34H 35H 36H WEIGHT KQ P O U N D S ARM I T E M DESCRIPTION H AVIONICS AUTOPILOTS CON T REF DRA...

Page 130: ...C04 05 C04 16 C 27 1 O 03 0 3 84 1 5 C35 5 07 2 063 2 ITEM NO 1 1 2 1 31 41 51 61 71 8 1 9 1 101 111 121 I T E M DESCRIPTION I AUXILIARY EQUIPMENT FLY AWAY TOW BAR FOLDING STOWED JACK POINTS 2 STOWED...

Page 131: ...INSTL U M M M NORMALLY STOWED I N BAGGAGE COMPARTMENT BETWEEN STA 1 1 0 130 Iz rnS 7J 8J 9J 10J 11J 12 J 140295 140300 210099 210413 720115 800166 AUX POWER CABLE ADAPTER DUAL BRAKE INSTL STATIC DISC...

Page 132: ...QUIPMENT L I S T MU DAY M E Q 2 YEAR ITEM N 0 13J 14J 15J 16J 17J 18J 19J 20J 21J 22J 23J 24J ITEM DESCRIPTION J OPTIONAL EQUIPMENT CONIT ANTI COLLISION BEACON RED REF DRAWING 800311 WEIGHT KQ CPOUNDS...

Page 133: ...EQUIPMENT L I S T M A R K IF INS T A L L ED MU DAY M E Q 3 YEAR ITEM N 0 ITEM DESCRIPTION J OPTIONAL EQUIPMENT CON T REF D R A W I N G WEIGHT KQ POUNDS ARM ccm CINCHES...

Page 134: ...EQUIPMENT L I S T MU D A Y M EQ J3 YEAR REF WEIGHT ARM MARK I F D R A W I N G KQ POUNDS ccm INCHES INSTALL ED ITEM N O n ITEM DESCRIPTION J CIPTIONAL EQUIPMENT CON T...

Page 135: ...7 12 GROUND CONTROL 7 14 NOSEGEAR STEERING 7 14 TAXIINGAND GROUND HANDLING 7 14 LANDINGGEAR 7 14 CONSTRUCTION 7 14 RRRACTIONSYSTEM 7 14 WEEL BRAKES 7 14 EMERGENCYEXENSIONSYSTEM 7 15 WINGSYSTEM 7 15 ST...

Page 136: ...GAIR 7 21 ENGINESTARTlNGSYSTEM 7 21 ACCESSORIES 7 21 PROPELLER 7 22 FUEL SYSTEM 7 22 ELECTRICALSYSTEM 7 23 ALTERNATOR BAllERY 7 24 SCHEMATIC 7 24 CIRCUIT BREAKERPANEL 7 24 ANNUNCIATOR PANEL 7 26 ELT P...

Page 137: ...eerable nose wheel aid in directionalcontrol during taxiing and ground operations The landing gear is electrically retracted and extended A warning horn a gear position indicator on the floorboard and...

Page 138: ...r right to mild with trim set to the third segment from the right Cruise will result in the trim indicator being slightly left of neutral and even more left of neutral during a high speed descent Wing...

Page 139: ...seconds when in elapsed time mode CLEAR Pushto reset elapsed time to Zero Set Hours Minutes or 24 vs 12 hour time Push and Hold both STARTISTOP and CLEAR buttonsfor 4 5 seconds to enter clock set mod...

Page 140: ...l speed indicator converts barometric pressure changes in the static lines to aircraft ascent or descent rate readings in feet per minute This indicator has a single needle and two adjoining scales th...

Page 141: ...e type temperature robe installed in cylinder number 5 The indicator receives power from the aircraft ekctrical system The instrument is calibrated in O F A 6 position switch with probes installed in...

Page 142: ...y relay which controls battery power selected battery to main buss This switch cuts ALL ship power OFF except forward and aft cabin overhead lightsandthe electric clock 5 OPTIONAL RotatinglFlashingBea...

Page 143: ...movement may result in a broken switch 13 STABILIZER TRlM POSITIONINDICATOR Stabilizertrim positionindicator LED is e ectrically actiied by a potentiometerattached to trimwheel mechanism The position...

Page 144: ...adjustments of the mixture can be obtained by turning the knob clockwise to enrichen the mixture and counterclockwise to lean The knob should not be turned IN any closer than 118 to the panel nut fac...

Page 145: ...nto this plug and place in mike holder located on storage compartment door on front of lower console 33 Trim ControlWheel Manually rotating the trim control wheel forward lowers the aircraft nose duri...

Page 146: ...e operation Refer to ELT description elsewhere in this section on proper and lawiul usage 47 Alternate Air Automatically opens when Induction air becomes blocked for any reason May be opened manually...

Page 147: ...insidethe cowling ratherthan through the NACA air intakevent Normal induc tion air system MUST be checked for proper operation prior to next flight I NOTE I Use of alternate air will result in loss of...

Page 148: ...re constructed of chrome molybdenumtubular steel heat treated for greater strength and wear resistance Main gear attaching points have metal backings imbedded in the gear mounting box attached to the...

Page 149: ...r retracting system will not operate if the manual extension lever is not properly positioned WARNING SYSTEM The landing gear warnin system consists of 1 the landing gear condition lights GREEN for GE...

Page 150: ...aft to fit individual comfort pref erences The front seat back may be adjusted by turning hand crank until seat back is in desired po sition Both optional front seat configurations allow verti cal se...

Page 151: ...sms one located at the top ofdoor and one at the aft center ofdoor Should the door come open in flight flying qualities of the aircraft will not be affected Proceduresfor closingdoor intight are conta...

Page 152: ...nier 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 wheredesired Thenon...

Page 153: ......

Page 154: ...ith the left collector then this exhaust manifold joins to the turbocharger crossover A shorttailpipe is attachedto the end oftheturbochargerand exitsthroughthe leftcowlflap The crossoverpipehas a hea...

Page 155: ...i h e magnetosarepressurizedfromturbocharged tnduction systembleedatr ACCESSORIES ALTERNATOR Electricalpowerissupplied bytwo beltdriven 28 Volt 70amperealternators VACUUM PUMP A full time engine driv...

Page 156: ...or where pressure is regulatedand the correct volume offuel is meteredto each cylinderofthe engine The electric boost pump located under the floor board below the passenger s feet is cable of supplyin...

Page 157: ...MOONEY M20M SECTION VII AIRPLANE AND SYSTEM DESCRIPTION ISSUED3 90 REV A 1 96 7 23...

Page 158: ...typical C B panel may vary from your aircraft Push pull or rocker switch circuit breakersautomatically break the electrical current flow if the system or unit receives an overload to Drevent damaae to...

Page 159: ...AR GEAR ACT m y WARN A H HSI 00000 RAP S T m STAU EFmST iWFI ACT IGN WARN aDWER aMRD 00000 MRE T M sHmD PAIlEL Ll5 L E Ll5 a G LTR m u 1 NAVl m o 000 MU 2 NAY 2 FliDNE 000 RAM XPCNDER ENC a o m 00600...

Page 160: ...e controlled by a BRIGHT OFF DIMswitch located in headliner between pilot and co pilot and a switch in the cabin door frame The rear cabin lights are controlled by another BRIGHT OFF DIMswitch located...

Page 161: ...preferences FRESH AIR One source of outside air enters the cabin through airscoops on the both sides of the fuselage This outside air is always available through the adjus table outlets Wemacs near th...

Page 162: ...indicator and vertical speed indicator A static system drain valve is located on the fuselage bottom skin below the left side tailcone access door and is used to drain moisture that might collect in t...

Page 163: ...due to ambient temperature in the filling area and the rise of temperature resulting from compression of the oxygen Because of this merely filling to 1850 PSI will not result in a properly filled cyii...

Page 164: ...SECTION VII AIRPLANE AND SYSTEMS DESCRIPTION MOONEY MODEL M20M FIGURE 7 13 OXYGEN DURATION CHART 115 7 Cu Ft CAPACITY ISSUED 3 90...

Page 165: ...beforethe pump ison line A vacuum system malfunction is shown to the pilot by a RED HllLO VAC annunciator light A flashing annunciatorlight indicates low vacuum and a steady light indicates high vacu...

Page 166: ...ARM positionduringcockpitcheckout lNOTE l If for any reason a test transmissionis necessary the operator must first obtain permission from a local FAA or FCC representative or other applicable Authori...

Page 167: ...3 TOWING 8 3 TIEDOWN 8 3 JACKING 8 3 SERVlClNG 8 4 REFUELING 8 4 ENGINELUBRICATION 8 4 INDUCTION AIR FILTER SERVICING 8 5 GEAR AND TIRE SERVICING 8 6 BAlTERY SERVICE 8 6 HYDRAULICBRAKERESERVOIRSYSTEM...

Page 168: ...manual is limited to service procedures which the operator will normally perform or supervise Reference should be made to FAR Part 43 for information regarding preventive maintenance which may be per...

Page 169: ...with jacks The tail tiedown point is part of the tail skid TO TIE DOWN THE AIRCRAFT a Park the airplane facing the wind b Fastenthe co pilot seat belt through the flight control wheel Pull seat belt...

Page 170: ...are near each wing root forward of the wheel wells A small plastic cup is supplied in the loose equipment kit for obtaining fuel samples To collect a fuel sample insert the cup actuator prong into th...

Page 171: ...itive oil b DO NOT operate engine longerthan FIVE HOURS before again changing oil c Check oil filter for evidence of sludge or plugging CHANGE oil and REPLACE oil filter element every 10 HOURS if slud...

Page 172: ...ted at 42 PSI and the nose tire at 49 PSI for maximum service life Proper inflation will minimize tire wear and impact damage Visually inspect the tires at preflight for cracks and ruptures and avoid...

Page 173: ...nforming to specification MIL H 5606 DO NOT FILL reservoir wh le park ng brake IS set ENGINE PERFORMANCE CHECKS When the aircraft leaves the factory the TEXTRON Lycoming TIO 540 AF1Aengine has been pr...

Page 174: ...c fluid or any other dye containing substance is found on the ex terior paint wash the area at once to prevent staining Immediately flush away spilled battery acid and treat the area with a baking sod...

Page 175: ...n the air lane durin all flight operations a Pilot s Operating handbook Including FAA Approved Flight Manual b Weight and Balance and associated papers latest copy of the e a i r and Alteration Form F...

Page 176: ...SECTION Vlll HANDLING SERVICE AND MAINTENANCE MOONEY MODEL M20M BLANK ISSUED 3 90...

Page 177: ...MOONEY MODEL M20M SECTION lX SUPPLEMENTAL DATA TITLE PAGE INTRODUCTION 9 3 1 THE SUPPLEMENTS INSERTEDINTO THIS SECTIONARE FAA APPROVED SUPPLEMENT INSERTED DATE ISSUED 3 90 9 1...

Page 178: ...SECTION IX SUPPLEMENTAL DATA SUPPLEMENT INSERTED MOONEY MODEL M20M DATE ISSUED 3 90...

Page 179: ...erformancefor certain optional equipment installed in the airplane are contained in this section Commonly installed items of optional equipment whose function and operation do not require detailed ins...

Page 180: ...SECTION IX SUPPLEMENTAL DATA MOONEY MODEL M20M BLANK ISSUED 3 90...

Page 181: ...NSPECTIONS MAINTENANCE 10 5 SPECIAL CONDITIONS CAUTIONARYNOTICE 10 5 WALKAROUND INSPECTIONS 10 6 COCKPIT CHECKS 10 6 FLIGHT OPERATIONS 10 6 GENERAL 10 6 TURBULENT WEATHER 10 6 FLIGHT IN TURBULENT AIR...

Page 182: ...RE_FAA APPROVED l SUPPLEMENT INSERTED Precise Speedbrake Svs eri BS King KLN88 Loran C Nav Sys EHI 40 E ISI Propeller De Ice System King KNS 81 King KFC150 King KAS297B WX 1000 Storm scope AA80 InterV...

Page 183: ...ts on performance for certain optional equipment installed in the airplane are contained in this section Commonly installed items of optional equipment whose function and operation do not require deta...

Page 184: ...when the Precise Speedbrake System SBS with control horn switch I operation is installed in accordance with Mooney Aircraft Corporation Drawing Number 950155 The information contained herein suppleme...

Page 185: ...t of an electrical malfunction the SBS circuit breaker may be pulled to remove electrical power from the heavily spring loaded solenoid SECTION 11 _OPERATING __ LIMITATIONS 1 Airspeeds Same limitation...

Page 186: ...lide path Maintainan 85 knot approachspeedby establishinga moderatelysteep nosedown attitude NOTE Lowerthe nose In anticipationof Increaseddragas the SBSIs actuated Landing Initiatethe landingflareat...

Page 187: ...ndbook and Airplane Flight Manual POH AFM when the 8 F Goodrich Propeller De IceSystem Is InstalledInaccordancewith MooneyDrawing690003 The information containedhereinsupplementsor supersedes the basi...

Page 188: ...VISIONS Revlslor Revision Description of FAA Nuriber Po ges Revisions Approved A Title Page Added REY Ato page 1 1lma 3 of 3 RevisedData M20M Do te 1 19o The revised portions of o ffected po ges o re...

Page 189: ...er Indicatingwhen currentIs being applied to heatingI elements SECTION II LIMITATIONS ThereIsno changeto the airplanelimitationswhenthe propeller de IcesystemIn Installed FlightIntoknownIcingcondition...

Page 190: ...dbook and AirplaneFlightManual POH AFM when the AA80lnterVOXIn tercom Sy stem is installed In accordancewith Mooney Drawing number 810417 M20J M20K 810202 M20L M20M The informationcontainedhereinsuppl...

Page 191: ...AIRCRAFT CORPORATION P B X 72 Kerrville TeXQS 78029 0072 Rev1s10r Revision Nul lber Po ges L G F REVISI NS Description of Revisions FAA Do te Approved u 1 The revised portlOns of o f f ected po ges o...

Page 192: ...the following for emergencyproceduresfor the AASO Intercomsystem EMERGENCYOPERATION If power ls lost to the AASO for any reason It will drop Intothe power fallmode and the pilot will be connected dir...

Page 193: ...t audio tapes etc with a separate level adjustment This llne Is mutedduring transmitfunctions and when the Inter com Is active If the ISO function Is selected the pilot will be connecteddlrectly to th...

Page 194: ...en Lons Range Fue1 Tanks are installed in accordance with Supplemental Type Certificate STC No SA1913S0 The information contained herein supplements or supersedes he information presented in the basic...

Page 195: ...FUELCAPACITY 59 GAL OCTANE 100 130 FILL BOTHWINGSEVENLY 1 Check the left and right tank for fuel level and drain the inboard drain sump for clear fuel the original drain on each tank 2 Drain the outb...

Page 196: ...posite one 5 Ensure that both wings are filled to the same level til2ll Fuel level may drop approximately 1 0 inch after refueling five minutes due to fuel level equalization in the aux tank Just fill...

Page 197: ...meswhentheGannin 500WSeriesunitis installedin accordancewith STCSA0l933LA Theinformationcontainedhereinsupplementsor supersedesthe information madeavailableto the operatorbythe manufacturerin the form...

Page 198: ...00WSeries NavigationSystem LOGOF REVISIONS Page No Date Des tion FAAA111 roved All 1l Ofi 06 Complete IX JltH Supplement Mgr Pit TestBr ANM 160L PAA LosAngelesACO TransportAirplaneDirectorate Date l i...

Page 199: ...FROperational Limitation 2 7 Approaches 2 8 Autopilot Coupling 2 9 TerrainDisplay UnitswithoutTAWS 2 10 TAWS Function UnitswithTAWS 2 11 WeatherDisplay 2 12 Traffic Display Section3 EMERGENCYPROCEDURE...

Page 200: ...in some installations The navigation functions are operated by dedicated keys and graphical menus which are controlled by the buttons and the dual concentric rotary knob along the bottom and right sid...

Page 201: ...space whenusedin conjunctionwithGarminPredictionProgram partnumber006 A01 3 Oceanicoperationsaresupportedwhenthe 500WSeriesunitmmunciates OCN Thisprovidesan alarmlimitof fournmi andamaskangleof fivede...

Page 202: ...laircraftsystemsmaybe requiredfor IFR operationalapproval Systemslimitedto VFRshallbe placardedin closeproximityto the SOOW Seriesunit GPSLIMITED TO VFR USE ONLY 2 2 System Software Thesystemmustutili...

Page 203: ...ataCard WAAS IPR Americas 010 10S46 02 Borlater DataCard WAAS IFR International 2 4 Tenain Database The SOOW SeriesunitsupportsTerrainorTAWS optional andrequiresa Terraindatabasecardto beinstalledin o...

Page 204: ...edureotherthan OPSor RNAVthat isanticipated to be operationaland availableat the estimated time of arrival AHequipmentrequiredfor thisproceduremustbe installedandoperationaJ c For flightplanningpurpos...

Page 205: ...slimitationdoesnot prohibitthe conductof an IFR approachif therequiredremoteannunciationfailsduringflight The indicationsprovidedon the 500WSeriesunit displaymaybe usedas a backup t Exceptin emergency...

Page 206: ...entATC clearanceto the extentnecessaryto complywith TAWSwarnings Navigationmustnot be predicateduponthe useof TAWS To avoidunwantedalerts TAWSshouldbe inhibitedwhenlandingat an aiTport thatis not incl...

Page 207: ...odesdonotsupportDR b If a Lossof Integrity QNTEG messageis displayedduring Enroute Terminal continueto navigateusingOPSequipmentand periodicallycross checkthe OPSguidanceto otherapproved meansof navig...

Page 208: ...nitin an IFRenvironment particularlywithoutthe autopilotengaged Ganninprovidesexcellenttrainingtoolswiththe Pilot s GuideandPC basedsimulator Pilotsshouldtake full advantageof these trainingtoolsto en...

Page 209: ...ata becomesunavailableoris inhibited TheCDIselectionofVLOC should inhibitthedigitalcontrolinterface WhenswitchingbetweenOPSand VLOCthepilotshouldbe awarethatthe autopilotmayneedto be re engagedintoAPR...

Page 210: ...versarereconunended m1lessvisualmeteorologicalconditions VMC existor the pilot can determinethatturningin additionto the climbingmaneuveris the safest courseof action 4 S WFDEPredictionProgram TheGarm...

Page 211: ...PLEMENTAL AIRPLANEFLIGHTMANUAL for a Gannin 500WSeriesNavigationSystem SectionS PERFORMANCE No change Seetlon6 WEIGHTANDBALANCE Seecurrentweightandbalancedata Section7 SYSTEMDESCRIPTIONS SeeGarminSOOW...

Page 212: ...TX 3X5withADS B is installedinaccordancewithSupplemental Type CertificateSA0l714WI This V documentmustbe incorporatedintotheFAAApprovedAirplaneFlightManualor providedasan FAAApprovedSupplementalAirpla...

Page 213: ...Michael Warren 3X5 added ODASTCUnitAdministrator Garmin International Inc ODA 240087 CE Date t 3 Jcf tl 6 All UpdatedSW btiliffwli versionsand ErikFrisk removedsection ODASTCUnitAdministrator 3 2 3 U...

Page 214: ...Broadcast Inhibit PABI 14 2 6 Datalinked Weather Display GTX 345 Only 14 2 7 Portable Electronic Devices 14 Section 3 EMERGENCY PROCEDURES 15 3 1 Emergency Procedures 15 3 2 Abnormal Procedures 15 Sec...

Page 215: ...ased radar on a frequency of I090 MHz Each unit is equipped with IDENT capability to initiate the SPI special position identification pulse for 18 seconds and will reply to ATCRBS Mode A Mode C and Mo...

Page 216: ...to transmit the followingdataper 14CFR 91 227 GPS Position Altitude and PositionIntegrity GroundTrackand orHeading GroundSpeed and VelocityIntegrity Air GroundStatus Flight ID Call Sign ICAO Registra...

Page 217: ...antenna 1 GTX GTX GTX GTX GTX GTX GTX GTX Function 335 335 335R 335R 345 345 345R 345R 335D w GPS 335DR w GPS 345D w GPS 345DR w GPS Panelmount X X X X Remotemount X X X X ModeS X X X X X X X X ADS B...

Page 218: ...ion of data from internal and external sources to transmit the following data per 14 CFR 91 227 OPS Position Altitude and Position Integrity Ground Track and or Heading Ground Speed and Velocity Integ...

Page 219: ...ADS R Rebroadcast of ADS B data from a ground station o TIS B Broadcast of secondary surveillance radar SSR derived traffic information from a ground station o FIS B Broadcast of aviation data from a...

Page 220: ...r 2 if installed GTX330 GTX330 GTX330D GTX330D GTX33 GTX33 GTX33D GTX33D IY 6TX33S GTX335 GTX33SD GTX335D GTX33SR GTX335R GTX335DR GTX335DR u GTX345 GTX345 GTX345D GTX345D GTX345R GTX34SR GTX34SDR GTX...

Page 221: ...essureAltitudeSource 1 PressureAltitudeSource 2 if installed G Jt e v GarminAltitudeEncoder GarminAltitudeEncoder 190 00734 15Rev 4 Page 10of 18 AFMS GarininGTX 33X and 3XSXPDRwith ADS 8 FAAAPPROVE_D...

Page 222: ...InterfacedActiveTrafficSystem El None TCAD TAS TCAS D 0950 1000 Display D Gables7534 Controller Gables7614 Controller CTL 92Controller CTL 92EController NOTE If the systemincludesall ofthe followingco...

Page 223: ...vigationSatelliteSystem GNS GarminNavigationSystem GPS GlobalPositioningSystem GTX GarminTransponder GTN GarminTouchscreenNavigator ICAO InternationalCivilAviationOrganization LRU LineReplaceableUnit...

Page 224: ...dfunctionsareoperational Whenthe systemis notoperational VADS B Outtransmitfailuremessageswillbe presentonthe remotecontroldisplay interface or theGTX330 or GTX3X5paneldisplay fa Gables7534controllero...

Page 225: ...ather Display GTX 345 Only n Do notusedatalinkweatherinformationformaneuvering in near or aroundareas of hazardousweather Informationprovidedbydatalinkweatherproductsmaynot accuratelydepictcurrentweat...

Page 226: ...henthe GPS SBASreceiveris inoperativeor GPSpositioninformationis not availableor invalid the GTXwillno longerbe transmittingADS BOutdata V ForGTX330 installations NOADSBannunciatorilluminated Interfac...

Page 227: ...ity and activatingor deactivatingemergencystatusforbothtransponderandADS 8 Out functions Detailson performingtheseproceduresare locatedintheGTX330 330D Pilot s GuideandGTX3XSSeriesTransponderPilot sGu...

Page 228: ...ADS Bor NO 1090ESTX Annunciation or associateddisplayannunciations mustbe EXTINGUISHED for the systemto meetthe requirementsspecifiedin 14CFR 91 227 This systemmustbe operationalincertainairspacesafte...

Page 229: ...Pilot s Guide 190 00502 00 Rev D or later GTX 3X5 Series Transponder GI 000 Pilot s 190 01499 0I Rev A or later Guide 7 1 GTXTIS Behavior The TIS Standby Operate controls for GTX 33 330 and GTX 335 33...

Page 230: ...CE 10 5 SPECIALCONDITIONSCAUTIONARYNOTICE 10 5 WALKAROUND INSPECTIONS 10 6 COCKPITCHECKS 10 6 FLIGHT OPERATIONS 10 6 GENERAL 10 6 TURBULENTWEATHER 10 6 FLIGHT IN TURBULENTAIR 10 7 MOUNTAIN FLYING 10 7...

Page 231: ...ed from any Mooney Marketing or Ser vice 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...

Page 232: ...curs 13 Practice engine out emergency landing gear extension and other emergency procedures at safe altitude preferably with a check pilot 14 Use caution in mountainous terrain 15 Keepyour airplane in...

Page 233: ...IONREGULATIONS PART 39 AIRWORTHINESS DIRECTIVES This document specifies that no person may operate a product to which an airwor thiness directive issued by the FAA applies except in accordance with th...

Page 234: ...ith the performanceof the airplaneand per formance data In the airplane manuals and placards The resultant effect of temperatureand pressurealtitude must be taken Into account In determiningper forman...

Page 235: ...shlight available Required documents on board Use the check list All internal control locks removed If installed Check freedom of controls Cabin and baggage door property closed Seat belts and shoulde...

Page 236: ...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 f...

Page 237: ...in avoiding low visibility conditions Motion sickness often precedes or accompanies disorientation and jeopardize the flight STALLS SPINS AND SLOWFLIGHT further Stalls and slow flight should be practi...

Page 238: ...an airplane The turbulent areas may remain for as tong as three minutes or more depending on wind conditions and may extend several miles behind the airplane Plan to fly slightly above or to the upwi...

Page 239: ...e is wide individual variation in susceptibility to hypoxia In addition to progressivelyinsufficient oxygen at higher altitudes any thing interfering with the blood s ability to carry oxygen can contr...

Page 240: ...the counter remedies drugs such as aspirin antihistamines cold tablets cough mixtures laxatives tranquilizers and ap petite suppressors may seriously impair the judgment and coordination needed while...

Page 241: ...ust be catTied in the airplane at all times The information contained herein supplements or supersedes the information made available to the operator by the aircraft manufacturer in the form of clearl...

Page 242: ...ughout document 24 Changed amber to yellow for consistency throughout document 29 Corrected AHRS ADC annunciation figures 31 Changed amber to yellow for consistency throughout document 32 Added Note t...

Page 243: ...y heading source 17 Added GPS aiding system message description Clarified limitations of aerobatic maneuvers for primary and standby ADI configurations Added clarifications for battery capacity requir...

Page 244: ...Added images for ALT and IAS advisories 40 Added steps to test any installed external annunciators and verify the Magnetic angle units to match across interfaced systems Added clarification of 60 min...

Page 245: ...6 Clarified that barometric altitude is required when interfaced with GTN to provide VNAV functionality 60 Removed typo 61 Added a note to clarify traffic data availability based on services provided...

Page 246: ...T INSTRUMENTS 18 SENSOR SELECTION 19 SYNTHETIC VISION 19 MOVING MAPS 19 AUTOPILOT DISCONNECT 19 TERRAIN DISPLAY 19 TERRAIN TAWS ALERTS 19 DATALINK PRODUCTS SIRIUSXM AND FIS B 20 TRAFFIC DISPLAY 20 STO...

Page 247: ...POWER SOURCES 47 SYSTEM STATUS 48 DATABASES 49 CREW PROFILES 49 INTEGRATED STANDBY SYSTEM 50 GPS APPROACH MODE ANNUNCIATIONS 51 VFR GPS 51 AIRCRAFT AUDIO INTERFACE 52 MESSAGES 52 SYSTEM SETTINGS 52 S...

Page 248: ...I can be installed as stand alone primary flight instruments as long as there are other equivalent source s of primary flight information that are independently powered The ADI or HSI can also be inst...

Page 249: ...ing indication and compass card There are navigation annunciations and distance time fields The HSI MAP Page includes a top down view inset map hazard awareness overlays traffic terrain topo along wit...

Page 250: ...ht data in the event the primary ADI fails or the pilot reverts the display either through the rotation of the outer knob counter clockwise or engages the reversionary switch An ADI page will be avail...

Page 251: ...icable on the upper portion of the screen Five configurable pages are available on the EIS unit Main o Contains all gauges with red yellow markings Aux EGT CHT Fuel Available gauges are as follows Eng...

Page 252: ...nna Table 3 GI 275 System Components MFD functions are supported by GPS navigator interfaces and a variety of other optional interfaces such as traffic systems Stormscope and satellite and ADS weather...

Page 253: ...me dedicated ADI GI 275 system has a configuration for redundancy which is satisfied by using a GI 275 MFD or HSI that is configured as a standby instrument This configuration is only possible when th...

Page 254: ...ector FLTA Forward looking Terrain Alerting GPSS GPS Steering HDG Heading HSI Horizontal Situation Indicator IFR Instrument Flight Rules IMC Instrument Meteorological Conditions LOI Loss of Integrity...

Page 255: ...purpose of navigating the AFMS and to assist with identification of important system functions included with this installation Section Heading Title Tick Box Marked Section 2 2 Heading operation Sect...

Page 256: ...ss than that shown in the table above Heading Operational Area This installation uses GI 275 as the primary heading source If the GI 275 is used as the primary heading source IFR Operations are prohib...

Page 257: ...will advise the pilot if the GPS and or air data is lost or invalid NOTE In dual GPS installations only one GPS needs to be available to the ADAHRS or AHRS for IFR flight Aerobatic Maneuvers Do not c...

Page 258: ...n Section 2 7 is completed successfully to verify the following The backup battery is operational and sufficiently charged Refer to Section 2 7 Attitude heading altitude and airspeed from AHRS ADC 1 a...

Page 259: ...ts The synthetic vision presentation must not be used as the sole reference for navigation or obstacle terrain traffic avoidance If the installed TAWS or Terrain Alerting system is inoperative the syn...

Page 260: ...e Display Stormscope lightning information displayed is limited to supplemental use only The use of the Stormscope lightning data on the display for hazardous weather thunderstorm penetration is prohi...

Page 261: ...o initiate flight when a Service Required advisory is present on the ADI or EIS display Portable Electronic Devices This STC does not relieve the operator from complying with the requirements of 91 21...

Page 262: ...GI 275 Standby ADI Either the original flight instruments with a turn rate indicator or the original flight instruments with a third attitude source must be installed as standbys for IFR flight Figure...

Page 263: ...ny additional engine instruments required by the aircraft Kinds of Equipment list as listed in the Aircraft Flight Manual If the GI 275 EIS is installed outside of the pilot s primary field of view an...

Page 264: ...Switch Adjacent to the GI 275 Reversion Backup Switch On Auto 2 28 3 Installations Limited to VFR This installation is not limited to VFR This installation is limited to VFR and the following placard...

Page 265: ...flight instruments for attitude airspeed altitude and heading reference 2 If GI 275 reversionary capability is available the standby GI 275 should automatically change to the ADI page and promptly res...

Page 266: ...k button to return to the ADI page NOTE If airborne AHRS alignment is necessary minimize maneuvering and turbulence during and after the restart process Excessive maneuvering or turbulence may prevent...

Page 267: ...conditions or land as soon as practical if there are no other reliable ADC sensors capable of providing accurate data If multiple ADC sources are installed 3 Select the operative ADC i e ADC 1 2 or 3...

Page 268: ...ease to operate except for displays which are equipped with an internal backup battery Refer to procedures for failure of affected equipment and operation on backup battery 3 1 6 Operation on Backup B...

Page 269: ...g on how these were installed and configured to the GI 275 some information from these configured systems will not be available when the GI 275 is operating on its backup battery 3 1 7 Display Backup...

Page 270: ...f climb airspeed NOTE Only the climb maneuver is recommended unless operating in VMC or it is determined based on all available information that turning in addition climbing is the safest course of ac...

Page 271: ...heading failure The heading bug and course pointer will continue to function normally using GPS ground track as a reference instead of magnetic heading Figure 4 Bottom of the ADI when HDG failed with...

Page 272: ...ture If the display is in an overheating condition the system will alert the pilot with a system message The system message will read Display Overtemperature 1 Prepare for loss of the affected display...

Page 273: ...r malfunctioning 1 Turn off synthetic terrain using the Menu Options Terrain SVT menu on the ADI 3 2 6 Electrical Load Shedding The following equipment is considered non essential If it becomes necess...

Page 274: ...AA APPROVED 3 2 8 EIS Display Parameter Failure Indicated by individual parameters having a red or yellow X drawn through the gauge and data removed see EIS failure procedure for loss of entire EIS fu...

Page 275: ...X through the digital heading display Red X Reference the data source or alternate equipment A red X through any display field indicates that display field is not receiving data or is corrupted Red EI...

Page 276: ...navigator does not have sufficient GPS position LOI Loss of Integrity Monitoring GPS integrity is insufficient for the current phase of flight No GPS Position Use alternate information for positional...

Page 277: ...Yellow Alert Banner on EIS Observe the caution indication on the EIS display and take appropriate action One or more engine parameters have exceeded a caution threshold Yellow EIS Parameter Take appr...

Page 278: ...etails Seek VFR flight conditions or land as practical The Internal battery has detected an issue which may not allow the battery to charge or discharge properly Such as Charge Inhibited unable to cha...

Page 279: ...ng the cross side ADC sensor multiple ADI and ADC installations only Messages Icon View and consider advisory messages Refer to the GI 275 Pilot Guide for appropriate pilot or service action Typically...

Page 280: ...roper function 5 Verify that the MAG TRUE navigation angle selection on the GI 275 and any interfaced navigators match 4 1 1 ADI System Check 1 For IFR aircraft verify that no yellow or red battery ic...

Page 281: ...Rev 4 Airplane Flight Manual Supplement Page 41 of 70 FAA APPROVED 4 Select the Reversion Backup Switch to the AUTO position and verify that the display return to their normal state and other configu...

Page 282: ...pilot is interfaced NOTE Garmin GFC 500 GFC 600 installations will not have an AP DISC button present in the Menu Options menu even though the GI 275 ADI is providing attitude 1 While on the ground en...

Page 283: ...ot s ADI 2 Enable GPSS emulation on the ADI using the AP REF button in the Menu Options NAV Options HDG Options menu 3 Engage the autopilot in HDG mode NOTE When GPSS emulation is enabled the GI 275 A...

Page 284: ...functionality requires barometric altitude This installation is equipped and configured to provide EDO VNAV display and autopilot coupling This installation is equipped and configured to provide EDO V...

Page 285: ...GI 275 Part 23 AML STC 190 02246 12 Rev 4 Airplane Flight Manual Supplement Page 45 of 70 FAA APPROVED PERFORMANCE No change WEIGHT AND BALANCE See current weight and balance data Section 5 Section 6...

Page 286: ...tabase updates Database updates cannot be performed in flight Additionally the GI 275 supports a Bluetooth connection to personal electronic devices running Garmin Pilot for the supplemental display o...

Page 287: ...nu press and hold the inner knob To access the Menu via touchscreen swipe up from the bottom of the GI 275 display Display Brightness Display brightness is controlled automatically based on input to a...

Page 288: ...Stand alone USB GSB 15 USB Interface System Status The GI 275 status can be viewed via the Menu System Info menu This includes the serial number and system ID of the unit the software version loaded...

Page 289: ...spaces and other data This database is updated on a 28 day cycle The obstacle database contains data for obstacles and wires that pose a potential hazard to aircraft Obstacles 200 feet and higher are...

Page 290: ...is installed which will force the standby ADI into the display backup mode of operation when moved to the ON position A backup battery will provide power to the ADI MFD HSI or standby ADI in the event...

Page 291: ...uidance LP V Lateral and vertical navigation approach L VNAV Lateral navigation approach with advisory vertical guidance LNAV V VFR GPS A Garmin GI 275 may be interfaced with its own optional VFR GPS...

Page 292: ...ed GI 275s A Message annunciation flashes in the upper left corner of each display to notify the pilot when a new advisory is available The pilot may select Messages in the Menu to display a list of a...

Page 293: ...and selected airspeed bugs with the TXi It is required that BARO SYNC be enabled when using VNAV functionality as the GTN will only use the pilot side BARO unless there is a failure 7 14 1 Primary Fli...

Page 294: ...nstallations when both ADIs are displaying the same sensor source A no compare monitor is used to determine when data between GI 275s cannot be compared No compares are annunciated the same as miscomp...

Page 295: ...ical path of the aircraft The FPM is always displayed when SVT is enabled The FPM will be dashed when it hits the vertical or lateral display limit Traffic a display on the ADI indicating the position...

Page 296: ...d by touching the field and rotating the inner knob or simply rotating the knob when the active field reverts to the Baro field home state Altitude airspeed and heading bugs may be configured and sync...

Page 297: ...Options HSI Map Options Map Options menu 7 14 8 Lateral Deviation Indicator LDI A Lateral Deviation Indicator LDI is displayed on the ADI above the heading display when selected in the Menu This LDI...

Page 298: ...de descends through minimums and the minimums bug will change to yellow As the aircraft altitude climbs back above minimums the minimums bug will change to white 50 ft above minimums and cyan 150 ft a...

Page 299: ...GPS In dual GPS installations the HSI sends Roll Steering information from the selected GPS source For autopilots which are not GPSS Roll Steering capable the GI 275 can convert GPSS turn commands in...

Page 300: ...from the standby or a remote gyro and the autopilot attitude input is independent of the attitude displayed on the GI 275 ADI It is recommended that pilots thoroughly familiarize themselves with the...

Page 301: ...cts the traffic displayed on the Traffic HSI Map and Map Pages When interfaced to a TIS A traffic system altitude filtering is not available The center of the traffic target icon serves as the reporte...

Page 302: ...AWS B then the GI 275 will display TAWS B parameters provided by the GNS or GTN The Terrain or TAWS function provided by the GI 275 system is indicated by a text box on the bottom of the Terrain Page...

Page 303: ...rea of color corresponding to the alert severity and encircling the obstruction o If Synthetic Vision depiction is turned on an area corresponding to the alert area on the map terrain page is shaded i...

Page 304: ...eather pages The products available on the map page and HSI are different for each weather receiver The map page and HSI provide controls to select the desired weather receiver only one weather receiv...

Page 305: ...table engine advisories The layout of EIS gauges is dependent on the GI 275 display type and number of engines The determination of which data is presented in which slot is set by the installer in con...

Page 306: ...where carburetor icing is possible humid air or visible moisture 7 18 3 CHT CHT is displayed on a graph on the CHT page Each cylinder will numerically display it s respective CHT below the indicated b...

Page 307: ...ndicates the last engine cylinder to peak during the leaning process Once the last cylinder peak EGT is detected the system will display the temperature differential from the recorded maximum EGT of t...

Page 308: ...initial estimated fuel quantity value is accurate The fuel computer calculates the remaining fuel based on the initial fuel value entered by the pilot The estimated fuel remaining is derived by the f...

Page 309: ...to an analog HOBBS meter that increments in tenths of an hour whenever one engine is registering 5 PSI of engine oil pressure TACH Similar to analog tachometers such that the timer increments in tenth...

Page 310: ...sent from the GI 275 to the PED Limitations regarding database operations are found in Section 2 25 Garmin provides a list of tested and compatible devices that can be used with the Connext platform C...

Page 311: ...0 Autopilot system is installed in accordance with STC SA01866WI The information contained herein supplements the information of the basic Airplane Flight Manual For Limitations Procedures and Perform...

Page 312: ...ission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revi...

Page 313: ...ON DATE OF APPROVAL FAA APPROVED 1 ALL Original Issue 01 18 19 Robert G Murray Garmin ODA STC Unit Administrator 2 ALL Add G3X Information 3 15 19 Robert G Murray Garmin ODA STC Unit Administrator 3 A...

Page 314: ...AFMS GFC 500 Mooney M20M M20R M20S Series 190 02291 18 Rev 5 Page ii This page intentionally left blank...

Page 315: ...PROTECTION MAXSPD 3 3 UNDERSPEED PROTECTION MINSPD 3 4 Section 3A Abnormal Procedures 3 5 AUTOPILOT PRE FLIGHT TEST FAIL 3 5 LOSS OF NAVIGATION INFORMATION 3 5 LOSS OF AIRSPEED DATA 3 6 LOSS OF ALTIT...

Page 316: ...ACH 4 6 LOC APPROACH GS out 4 7 GPS APPROACH LPV LNAV VNAV LP V or LNAV V 4 8 GPS APPROACH LP LNAV 4 8 LOC BC APPROACH 4 9 VOR APPROACH 4 10 DISABLING ESP 4 11 Section 5 Performance 5 1 Section 6 Weig...

Page 317: ...or adds to the basic POH AFM only as set forth below Users of the manual are advised to always refer to the supplement for possibly superseding information and placarding applicable to operation of t...

Page 318: ...500 Garmin Autopilot GMC 507 Autopilot Mode Control Panel GNSS Global Navigation Satellite System GPS Global Positioning System GS Glideslope GSA Garmin Servo Actuator HDG AFCS heading mode IAS Indica...

Page 319: ...ssociated with the GFC 500 Autopilot installation in this airplane Table 1 1 Table of Installed Equipment Interfaces DEVICE TYPE Manufacturer Model If not installed note N A Additional Information GPS...

Page 320: ...tion Vertical Autopilot Modes Pitch PIT Level Zero vertical speed Go Around GA Altitude Hold ALT Vertical Speed VS Altitude Capture via Altitude Preselect Indicated Airspeed IAS Vertical Navigation VN...

Page 321: ...cable to the software versions shown below Software Item Software Version or later FAA Approved version for this STC G5 Software Version 6 40 G3X Software Version 8 30 GI275 Software Version 2 11 A pi...

Page 322: ...AFMS GFC 500 Mooney M20M M20R M20S Series 190 02291 18 Rev 5 Page 2 2 This page intentionally left blank...

Page 323: ...r control forces 3 Aircraft Attitude MAINTAIN REGAIN AIRCRAFT CONTROL 4 Elevator Trim RE TRIM if necessary using Elevator Trim Control Wheel 5 Autopilot Circuit Breaker PULL NOTE Do not release the AP...

Page 324: ...amber AP with a red X the autopilot will not be available However the flight director will still be functional In the event of a GMC failure pressing the G5 knob GI 275 knob or autopilot status button...

Page 325: ...active for approximately 10 seconds the autopilot will automatically engage in LVL mode an aural ENGAGING AUTOPILOT will be played or a Sonalert tone will sound for installations without a supported...

Page 326: ...IRSPEED Aural sounds 1 Throttle INCREASE POWER AS REQUIRED TO CORRECT UNDERSPEED 2 Aircraft Attitude and Altitude MONITOR After underspeed condition is corrected 3 Autopilot RESELECT VERTICAL AND LATE...

Page 327: ...OF NAVIGATION INFORMATION This procedure applies only if the optional GPS and or VHF navigator is installed Amber GPS VOR LOC or BC flashes for 10 seconds on G5 GI 275 or G3X NOTE If a navigation sign...

Page 328: ...vo is installed LOSS OF ALTITUDE DATA Red X through altitude tape on the G5 GI 275 or G3X display NOTE If altitude data is lost while the autopilot is tracking altitude the autopilot will default to p...

Page 329: ...possible If the optional pitch trim servo is NOT installed 1 Refer to the Normal Procedures section of this AFMS MANUAL PITCH TRIM WITH AUTOPILOT ENGAGED If the optional pitch trim servo is installed...

Page 330: ...aw servo is installed 1 YD Button on GMC or G5 Knob PRESS AND RELEASE to cancel disconnect tone 2 Aircraft Attitude MAINTAIN REGAIN AIRCRAFT CONTROL NOTE A flashing amber YD in the autopilot status bo...

Page 331: ...ane to capture the FD command bars The prior flight director modes remain unchanged Autopilot Disengagement The most common way to disconnect the autopilot is to press and release the AP DISC TRIM INT...

Page 332: ...n Altitude Capture INDICATED AIRSPEED IAS MODE 1 Altitude Preselect SET to Desired Altitude 2 Press IAS Key autopilot synchronizes to the airplane s current indicated airspeed 3 AIRSPEED Reference ADJ...

Page 333: ...rrent aircraft altitude No waypoints with altitude constraints in the flight plan Glideslope or Glidepath is the active flight director pitch mode OBS mode is active Dead Reckoning mode is active Para...

Page 334: ...is pressed the Flight Director command bars will command go around pitch attitude and wings level The pilot must set Go Around power then select the CDI to the appropriate navigation source and selec...

Page 335: ...dicator CDI is greater than one dot from center the autopilot will arm the VOR mode when the NAV key is pressed The pilot must ensure that the current heading will result in a capture of the selected...

Page 336: ...Continue visually for a normal landing Or 7 GO AROUND GA button PRESS Execute Missed Approach Procedure 8 Apply GA power NOTE Pressing the GA button will not disconnect the autopilot Select NAV or HD...

Page 337: ...n a capture of the selected course 3 NAV Key PRESS verify LOC ARMED 4 LOC Mode VERIFY airplane Captures and Tracks LOC Course 5 Altitude Preselect SET to next required step down altitude 6 Missed Appr...

Page 338: ...ESS Execute Missed Approach Procedure 9 Apply GA power NOTE Pressing the GA button will not disconnect the autopilot Select NAV or HDG mode to fly the missed approach procedure GPS APPROACH LP LNAV Th...

Page 339: ...ted course 3 NAV Key PRESS verify BC ARMED when heading is within 75 degrees of Back Course 4 BC Mode VERIFY airplane Captures and Tracks Back Course 5 Altitude Preselect SET to next required step dow...

Page 340: ...pture of the selected course 3 NAV Key PRESS verify VOR ARMED 4 VOR Mode VERIFY airplane Captures and Tracks VOR Course 5 Altitude Preselect SET to next required step down altitude 6 Missed Approach A...

Page 341: ...PRESS 2 ESP SELECT 3 G5 Knob PRESS ESP can be disabled on the G3X with the following procedure ESP will default to Enabled on the next power cycle 1 Autopilot Status Box TOUCH 2 ESP Button TOUCH 3 Bac...

Page 342: ...190 02291 18 Rev 5 AFMS GFC 500 Mooney M20M M20R M20S Series Page 5 1 SECTION 5 PERFORMANCE No Change...

Page 343: ...C 500 Mooney M20M M20R M20S Series Page 6 1 SECTION 6 WEIGHT AND BALANCE No change to loading information Refer to current weight and balance report and equipment list for changes to empty weight mome...

Page 344: ...speed Optional Electric Pitch Trim The pitch trim servo provides manual electric pitch trim capability when the autopilot is not engaged The trim servo provides automatic pitch trim when the autopilot...

Page 345: ...normal flight below 65 KIAS The conditions that are required for ESP to be available are Pitch and Roll servos available Autopilot not engaged The GPS altitude above ground is more than 200 feet for l...

Page 346: ...e following figures Figure 7 1 Nominal Roll Attitude ESP Engagement Limit Indications Once ESP becomes active in roll the engagement limit indication that was crossed either Left or Right will move to...

Page 347: ...following pilot actions will cause the autopilot to disconnect Pressing the red AP DISC TRIM INT button on the pilot s control wheel Actuating the manual electric trim switch if installed Pushing the...

Page 348: ...0 to 2000 FPM 100 FPM IAS Hold IAS Key IAS nnn 69 to 185 KIAS 1 KT Vertical Path Tracking VNAV VNAV Key VNAV VNAV Target Altitude Capture ALTV Glidepath APR Key GP Glideslope GS Takeoff or Go Around G...

Page 349: ...R Key GPS 30 Approach ILS Arm Capture Track Glideslope Mode Automatically Armed LOC 30 Takeoff or Go Around GA Button TO or GA Wings Level LVL Level LVL Key LVL Wings Level ESP Roll Attitude Engagemen...

Page 350: ...e inputs to the trim system are invalid The trim system needs service Autopilot Annunciations Autopilot has failed Autopilot is inoperative and flight director is not available Autopilot normal discon...

Page 351: ...noperative LIGHTING When the aircraft s dimming bus is selected off or full dim GMC 507 mode control panel lighting is controlled by integrated photocells which sense the ambient cockpit lighting When...

Page 352: ...ed from any Mooney arteting or Ser vice 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 o...

Page 353: ...ne statvation occurs 13 Practice engine out emergency landing gear extension and other emergency proceduresat safe altitude preferablywith a check pilot 14 Use caution in mountainousterrain 15 Keep yo...

Page 354: ...PART 39 AIRWORTHINESS DIRECTIVES This document specifies that no person may operate a product to which an airwor thiness directive issued by the FAA applies except in accordance with the require ment...

Page 355: ...irplane and per formance data in the airplane manuals and placards The resultant effect of temperature and pressure altitude must be taken into account in determining per formance if not accounted for...

Page 356: ...S flashlight available Requireddocuments on board Use the check list All internal control locks removed If installed Check freedom of controls Cabin and baggage door properlyclosed Seat belts and shou...

Page 357: ...intain straight and leve atfitude in either up or down drafts Use trim sparingly to avo dbelng grossly m str mmed as the verticalair columns change velocity and direction MOUNTAIN FLYING Avoid flight...

Page 358: ...a caution in avoiding low visibility conditions Motion sickness often precedes or accompanies disorientation and may further jeopardizethe flight STALLS SPINS AND SLOW FLIGHT Stalls and slow flight sh...

Page 359: ...an airplane The turbulent areas may remain for as long as three minutes or more depending on wind conditions and may extend several miles behind the airplane Plan to fly slightly above or to the upwin...

Page 360: ......

Page 361: ...8 2016 3 12 07 2017 All Updated SW versions and removed section 3 2 3 Updated section 2 2 Corrected PED FAR reference and additional minor corrections Erik Frisk Erik Frisk ODA STC Unit Administrator...

Page 362: ...y with User Navigation Angle 13 2 4 Applicable System Software 14 2 5 Pressure Altitude Broadcast Inhibit PABI 14 2 6 Datalinked Weather Display GTX 345 Only 14 2 7 Portable Electronic Devices 14 Sect...

Page 363: ...or TCAS interrogations at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz Each unit is equipped with IDENT capability to initiate the SPI special...

Page 364: ...n of ADS B out data on 1090 extended squitter 1090 MHz o Integration of data from internal and external sources to transmit the following data per 14 CFR 91 227 GPS Position Altitude and Position Inte...

Page 365: ...D designation are diversity capable and support both a top fuselage and bottom fuselage antenna Function GTX 335 335D GTX 335 w GPS GTX 335R 335DR GTX 335R w GPS GTX 345 345D GTX 345 w GPS GTX 345R 34...

Page 366: ...Input Bottom Antenna GTX 3X5D 3X5DR Installs only Top Antenna GTX 345D 345DR only Time Mark Figure 3 GTX 3X5 Interface Summary The GTX 3X5 performs the following functions Transmission of ADS B out da...

Page 367: ...ception of ADS B In data on UAT 978 MHz o ADS B Data directly from another transmitting aircraft o ADS R Rebroadcast of ADS B data from a ground station o TIS B Broadcast of secondary surveillance rad...

Page 368: ...accordance with sections 2 1 and 2 2 of this supplement 1 4 Installation Configuration This aircraft is equipped with a GTX 33X and or GTX 3X5 with the following interfaces features Equipment Install...

Page 369: ...6XX 7XX Series GTN 6XX 7XX Series GNS 400W 500W Series GNS 400W 500W Series GNS 480 GNS 480 GIA 63W GDL 88 GTX 330 only GPS 175 GNC 355 GIA 63W GDL 88 GTX 330 only GPS 175 GNC 355 Interfaced Pressure...

Page 370: ...oller Transponder 2 Remote Control Display if installed GTN 6XX 7XX GNS 480 G950 1000 Display GI 275 Gables 7534 Controller Gables 7614 Controller CTL 92 Controller CTL 92E Controller Interfaced Activ...

Page 371: ...dar Beacon System CFR Code of Federal Regulations ES Extended Squitter GNSS Global Navigation Satellite System GNS Garmin Navigation System GPS Global Positioning System GTX Garmin Transponder GTN Gar...

Page 372: ...3X and GTX 3X5 only comply with 14 CFR 91 227 for ADS B Out when all required functions are operational When the system is not operational ADS B Out transmit failure messages will be present on the re...

Page 373: ...pliant transmitter PABI is enabled by selecting the GTX to ON mode 2 6 Datalinked Weather Display GTX 345 Only Do not use datalink weather information for maneuvering in near or around areas of hazard...

Page 374: ...d aircraft for loss of power generation 3 2 2 LOSS OF GPS SBAS POSITION DATA When the GPS SBAS receiver is inoperative or GPS position information is not available or invalid the GTX will no longer be...

Page 375: ...providing a single point of entry for Mode 3 A code Flight ID IDENT functionality and activating or deactivating emergency status for both transponder and ADS B Out functions Details on performing th...

Page 376: ...EXTINGUISHED NOTE The ADS B TX or 1090ES TX CTL must be turned on and the NO ADS B or NO 1090ES TX Annunciation or associated display annunciations must be EXTINGUISHED for the system to meet the req...

Page 377: ...ev E or later GNS 480 Pilot s Guide 190 00502 00 Rev D or later GTX 3X5 Series Transponder G1000 Pilot s Guide 190 01499 01 Rev A or later Garmin GI 275 Pilots s Guide 190 02246 01 Rev F or later Garm...

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