1975 CESSNA 177 AND CARDINAL OWNER’S MANUAL

3. Tie Down ..................... DISCONNECT 4. Pitot Tube Cover .................. REMOVE 5. Stall Warning Opening ............ CHECK 6. Wing Tips................................ CHECK 7. Aileron .......................... CHECK FREE 8. Aileron ..................... CHECK HINGES 9. Aileron ................ CHECK PUSH BAR 10. Flap Guides ............................. CHECK 11. Flap Connection ...................... CHECK 12. Fuel Tank Sump .................... SAMPLE 13. Main Wheel Tire ..................... CHECK 14. Fuel Vent Opening .....CHECK CLEAR PREFLIGHT – EMPENNAGE 1. Antennas ................................... CHECK 2. Baggage Door ........... CHECK SECURE 3. Stabilator .................................. CHECK 4. Trim Taps ................................. CHECK 5. Tail Tie-Down ............... DISCONNECT 6. Rudder ...................................... CHECK PREFLIGHT – RIGHT WING 1. Fuel Vent Opening .......CHECK CLEAR 2. Main Wheel Tire....................... CHECK 3. Fuel Tank Sump ..................... SAMPLE 4. Flap Connection ........................ CHECK 5. Flap Guides .............................. CHECK 6. Aileron............................ CHECK FREE 7. Aileron.................. CHECK PUSH BAR 8. Aileron....................... CHECK HINGES 9. Wing Tips ................................. CHECK 10. Tie Down ....................... DISCONNECT 11. Fuel Quantity ............................ CHECK 12. Fuel Filler Cap ........................ SECURE PREFLIGHT – NOSE 1. Engine Oil Level ..................... CHECK 2. Fuel Strainer ............................. DRAIN 3. Hobbs Time ...........................RECORD 4. Owl ...................................... REMOVE 5. Propeller & Spinner ................. CHECK 6. Blades...................................... CHECK 7. Cowl Plugs ........................... REMOVE 8. Alternator Belt ......................... CHECK 9. Landing Light .......................... CHECK 10. Carburetor Air Filter ................ CHECK 11. Nose Strut ......................... COMPRESS 12. Tire .......................................... CHECK 13. Static Source Opening ............. CHECK 14. OAT ...........................CHECK CLEAR As of 1/15/20 C-177B – N35031 CHECKLISTS BEFORE STARTING ENGINE . 1. Preflight Inspection .......... COMPLETE 2. Seats Belts ............ ADJUST & LATCH 3. Cabin Doors ......CLOSED & LOCKED 4. Passengers ............................ BRIEFED 5. Fuel Selector Valve ................... BOTH 6. Fuel Shutoff Valve ......... IN & WIRED 7. Electrical Equipment / Avionics .... OFF 8. Brakes ............................. TEST & SET 9. Circuit Breakers ................. CHECK IN STARTING THE ENGINE . 1. Cowl Flaps ................................. OPEN 2. Mixture........................................ RICH 3. Propeller .............................HIGH RPM 4. Carburetor Heat .......................... COLD 5. Beacon ............................................ ON 6. Prime ........................... AS REQUIRED 7. Throttle....................... OPEN 1/2 INCH 8. Propeller Area .......................... CLEAR 9. Master Switch ................................. ON 10. Auxiliary Fuel Pump ............... CHECK 11. Ignition Switch ......................... START 12. Oil Pressure ............................. CHECK 13. Throttle.................................1000 RPM BEFORE TAXI . 1. Flaps ................................................ UP 2. Electronics....................................... ON 3. Radios / Navigation ........................SET 4. Transponder ....................... STANDBY 5. Intercom ...... ON & CHECK VOLUME 6. Taxi Area .................. VERIFY CLEAR 7. Mixture.................... LEAN FOR TAXI 8. Parking Brake ...................... RELEASE 9. Brakes ......................................... TEST 10. Flight Controls ...... POSITIONED FOR ................................................... WIND BEFORE TAKE-OFF . 1. Nose Wheel ....................... STRAIGHT 2. Parking Brake ................................ SET 3. Flight Controls ..... FREE & CORRECT 4. Fuel Shutoff Valve ..........IN & WIRED 5. Fuel Selector Valve ............ ON BOTH 6. Mixture ................ RICH (below 3,000’) 7. Stabilator Trim ...................TAKE-OFF 8. Rudder Trim .......................TAKE-OFF 9. Primer...........................IN & LOCKED 10. Oil Temperature ................. IN GREEN 11. Throttle Setting .................... 1800 RPM a) Engine Instruments .................. CHECK b) Ammeter ................................. CHECK c) Propeller .............................. CYCLE 3x a. Check RPM Drop b. Check Oil Pressure Drop c. Check MP Drop d) Carburetor Heat ....................... CHECK e) Magnetos ......... CHECK, Max drop 150 RPM; Max differential 50 RPM f) Aux Fuel Pump........................ CHECK g) Suction Gage .......... CHECK 4.6”– 5.4” 12. Throttle ............................... 1,000 RPM 13. Flight Instruments.......................... SET a. Heading b. Altimeter c. Transponder Code d. Navigation 14. Radios ........................................... SET 15. Throttle Friction Lock ............ ADJUST 16. Cabin Doors & Windows ...... CLOSED 17. NAV/Strobe Lights...... AS REQUIRED 18. Transponder ........................... ON ALT 19. Parking Brake ...................... RELEASE As of 1/15/20 C-177B – N35031 CHECKLISTS PASSENGER BRIEFING . 1. Expected WX and Flight Conditions 2. Seatbelt Operations – WEAR AT ALL TIMES 3. Headset Operation 4. What NOT TO TOUCH 5. Sterile Cockpit until after Takeoff 6. Sick Sacks 7. Ventilation 8. How to Radio for Help (PTT Button on panel) 9. Emergency Situations 10. Foreflight Passenger App on iPhone As of 1/15/20 C-177B – N35031 CHECKLISTS NORMAL TAKE-OFF . 1. Wing Flaps .......... 0°-10° (10° preferred) 2. Carburetor Heat ........................... COLD 3. Throttle .............................. FULL OPEN 4. Propeller ...............................2,700 RPM 5. Elevator Control ...... LIFT NOSE AT 60 6. Climb Speed ................ BEST RATE: 92 7. Flaps ..................................... RETRACT 8. Power/Prop ..................... 2500 RPM/25” SHORT FIELD TAKE-OFF . 1. Wing Flaps ...................................... 15° 2. Carburetor Heat .......................... COLD 3. Brakes ...................... APPLY & HOLD 4. Throttle.............................FULL OPEN 5. Propeller ..............................2,700 RPM 6. Mixture.............. LEAN ABOVE 3,000’ 7. Brakes ................................. RELEASE 8. Elevator Control ..... LIFT NOSE AT 60 9. Climb Speed ............ BEST ANGLE: 69 10. Flaps .................................... RETRACT 11. Power/Prop .................... 2500 RPM/25” 12. Climb Speed ............... BEST RATE: 92 ENROUTE CLIMB . 1. Landing Light ................................. OFF 2. Airspeed .................................. 90 to 100 3. Power .................. 24”; 2500-2700 RPM 4. Mixture .............. LEAN ABOVE 3,000’ 5. Cowl Flaps......... OPEN AS REQUIRED CRUISE . 1. Power ............................. 75% OR LESS 2. Stabilator Trim......................... ADJUST 3. Rudder Trim ............................ ADJUST 4. Mixture ........................................ LEAN 5. Cowl Flaps............................... ADJUST .............................. FOR 350° OR LESS DECENT . 1. Fuel Selector Valve ....................... BOTH 2. Mixture .......................................... RICH 3. Power ................................ AS DESIRED 4. Carb Heat .......... FULL BELOW GREEN 5. Landing Lights ................................... ON 6. Airspeed ......................................... 80-90 7. Flaps ................................. AS DESIRED BEFORE LANDING . 1. Seats Belts – ADJUST and LATCH 2. Fuel Selector – BOTH 3. Mixture – RICH 4. Propeller – HIGH RPM 5. Carburetor Heat – ON 6. Airspeed – 70-80 MPH (FLAPS DOWN) As of 1/15/20 C-177B – N35031 CHECKLISTS BALKED LANDING . 1. Power .. FULL THROTTLE; 2700 RPM 2. Carburetor Heat ........................... COLD 3. Wing Flaps ................ (immediately) 20° 4. Climb ........................ BEST ANGLE: 69 5. Wing Flaps (after safe alt & 75) .............................. RETACT SLOWLY 6. Climb Speed ................. BEST RATE: 92 7. Cowl Flaps................................... OPEN NORMAL LANDING . 1. Airspeed................ 80-75 MPH (flaps up) 2. Wing Flaps............ 10° (below 130 MPH) 3. Wing Flaps.... AS DESIRED (below 105) 4. Airspeed........... 70-80 MPH (flaps down) 5. Touchdown ....... MAIN WHEELS FIRST 6. Landing Roll .. LOWER NOSE GENTLY 7. Braking ............ MINIMUM REQUIRED AFTER LANDING . 1. Wing Flaps......................................... UP 2. Carburetor Heat ............................ COLD CLEAR OF RUNWAY . 1. Transponder .......................... STANDBY 2. Strobe / Nav / Landing Lights .......... OFF PRIOR TO PARKING . 1. Fuel – TOP OFF 2. Purchase – RECORD SECURING AIRCRAFT . 1. Parking Brake ................................. SET 2. Tach Time ............ RECORD FROM JPI 3. Radios & Electrical Equipment ....... OFF 4. Ignition Switch ........GROUND CHECK 5. Mixture ......................... IDLE CUT OFF 6. Ignition Switch ............................... OFF 7. Master/Battery Switch’s ................. OFF 8. Control Lock.......................... INSTALL 9. Fuel Selector Valve.....................RIGHT 10. Airplane ............... CHOCK, TIE DOWN 11. Cowl Plugs ............................ INSTALL 12. Owl ........................................ INSTALL 13. Pitot Tube Cover.................... INSTALL 14. Squawks .................................RECORD 15. Cabin Doors ................................. LOCK 16. Baggage Door .............................. LOCK 17. Cabin Cover ........................... INSTALL 18. Hobbs ...... RECORD (next to fuel drain) 19. Keys .................. RETURN TO OFFICE As of 1/15/20 C-177B – N35031 CHECKLISTS ENGINE FAILURE DURING TAKEOFF 1. Throttle ........................................ IDLE 2. Brakes ....................................... APPLY 3. Wing Flaps.......................... RETRACT 4. Mixture ....................... IDLE CUT-OFF 5. Ignition Switch............................... OFF 6. Master/Battery Switch.................... OFF ENGINE FAILURE AFTER TAKEOFF 1. Airspeed................................... 80 MPH 2. Mixture ....................... IDLE CUT-OFF 3. Fuel Selector Valve ........................ OFF 4. Fuel Shutoff Valve ................................ ...................... OUT (Break Safety Wire) 5. Ignition Switch............................... OFF 6. Wing Flaps.................. AS REQUIRED 7. Master Switch ................................ OFF ENGINE FAILURE DURING FLIGHT 1. Airspeed................................... 85 MPH 2. Carburetor Heat .............................. ON 3. Fuel Selector Valve .................... BOTH 4. Mixture ........................................ RICH 5. Ignition Switch.......... BOTH or START 6. Primer .......................... IN & LOCKED 7. Airspeed................................... 80 MPH ENGINE FIRE DURING FLIGHT 1. Mixture ....................... IDLE CUT-OFF 2. Fuel Shutoff Valve ................................ ...................... OUT (Break Safety Wire) 3. Master Switch ................................ OFF 4. Cabin Heat ..................................... OFF 5. Airspeed.......................................... 100 ELECTRICAL FIRE DURING FLIGHT 1. Master Switch ................................ OFF 2. All other Switches (except Ignition) ...... ....................................................... OFF 3. Vents / Cabin Air / Heat ......... CLOSED 4. Fire Extinguisher............... ACTIVATE (if fire appears out) a. Master Switch ............................ ON b. Circuit Breakers .................. CHECK ............(Do NOT reset faulty circuit) c. Electrical/Radios ........................ ON . One at a time, with delay after each EMERGENCY LANDING 1. Mixture ...................... IDLE CUT-OFF 2. Fuel Selector Valve....................... OFF 3. Fuel Shutoff Valve ............................... .................... OUT (Break Safety Wire) 4. Select Field ....................... SUITABLE 5. Electrical Switches ....................... OFF 6. Wing Flaps (on final) . AS REQUIRED 7. Airspeed ................................. 75 MPH 8. Master/Battery Switch .................. OFF 9. Doors ................................ UNLATCH 10. Touchdown ........ SLIGHT TAIL LOW 11. Ignition ......................................... OFF 12. Brakes................... APPLY HEAVILY PRECAUTIONARY LANDING 1. Wing Flaps .................................... 15° 2. Airspeed ................................. 75 MPH 3. Select Field ....................... SUITABLE 4. Electronics .................................... OFF 5. Wing Flaps (on Final) .................... 30° 6. Airspeed ................................. 60 MPH 7. Master/Battery Switch .................. OFF 8. Doors ................................ UNLATCH 9. Touchdown ... SLIGHTLY TAIL LOW 10. Ignition Switch ............................. OFF 11. Brakes................... APPLY HEAVILY As of 1/15/20 FUEL SYSTEM DESCRIPTION AND OPERATING DETAILS NOTE With full cabin loading with either standard or long range tanks, it will be necessary to reduce the fuel load to keep the aircraft within approved weight limits. Refer to Section IV for weight and balance control procedures. NOTE Take off with the fuel selector valve handle in the BOTH ON position to prevent inadvertent take-off on an empty tank. However, during long range flight with the selector valve handle in the BOTH ON position, unequal fuel flow from each tank may occur if the wings are not maintained exactly level. Resulting wing heaviness can be alleviated gradually by turning the selector valve handle to the fuel tank in the “heavy wing”. The recommended cruise fuel management procedure for extended flight is to use the left and right tank alternately. With low fuel (1/16th tank or less) a prolonged powered steep descent (1,000’ or more) should be avoided with more than 10° flaps to prevent the possibility of fuel starvation resulting from uncovering the fuel tank outlets. If starvation should occur, leveling the nose and turning on the auxiliary fuel pump should restore engine power within 30 seconds. NOTE FUEL SYSTEM QUICK-DRAIN VALVES ELECTRICAL SYSTEM MASTER SWITCH AMMETER OVER-VOLTAGE SENSOR AND WARNING LIGHT ELECTRICAL SYSTEM LIGHTING EQUIPMENT CIRCUIT BREAKERS AND FUSES EXTERIOR LIGHTING INTERIOR LIGHTING CABIN HEATING, VENTILATING AND DEFROSTING SYSTEM SHOULDER HARNESSES INTEGRATED SEAT BELT / SHOULDER HARNESSES WITH INERTIA REEL STARTING ENGINE NOTE The inertia reels are located for the maximum shoulder harness comfort and safe retention of the seat occupants. This location requires that the shoulder harnesses cross near the top so that the right hand inertia reel serves the pilot and the left hand reel serves the front passenger. When fastening the harness, check to ensure the proper harness is being used. TAXIING BEFORE TAKE-OFF NOTE WARM-UP Additional details concerning cold weather starting and operation may be found under “Cold Weather Operation” paragraphs in this seciton. TAXIING DIAGRAM TAKE-OFF MAGNETO CHECK ALTERNATOR CHECK POWER CHECK WING FLAP SETTINGS PERFORMANCE CHARTS CROSSWIND TAKE-OFFS E N R O U T E C L I M B . C L I M B D A T A . For detailed data, refer to the Maximum Rate-Of-Climb Data chart i n S e c t i o n V I . C L I M B S P E E D S . Normal climbs are performed at 90 to 100 MPH with flaps up and reduced power (down to 24 inches of manifold pressure and 2500 RPM) for increased passenger comfort due to lower noise level. The mixture should be full rich below 3000 feet and may be leaned above 3000 feet for s m o o t h e r e n g i n e o p e r a t i o n . T h e m a x i m u m r a t e - o f - c l i m b s p e e d s r a n g e from 92 MPH at sea level to 83 MPH at 10, 000 feet. If an obstacle dic¬ tates the use of asteep climb angle, an obstacle clearance speed of 77/ MPH should be used with flaps up and full throttle at all altitudes. _ . < U I S E . Normal cruising is performed between 55% and 75% power. The cor¬ responding power settings and fuel consumption for various altitudes can be determined by using your Cessna Power Computer or the Operational D a t a i n S e c t i o n V I . The Cruise Performance table shown on the following page iliustrates the time airspeed and miles per gallon during cruise for various altitudes and percent powers. This table should be used as aguide, along with the available winds aloft information, to determine the most favorable altitude and power setting for agiven trip. TJie selection of cruise altitude on the basis of the most favorable wind conditions and the use of low power set¬ tings are significant factors that should be considered on every trip to reduce fuel consumption. The tachometer is marked with agreen arc from 2100 to 2700 RPM with astep at 2500 RPM. The use of 2500 RPM will allow 75% power at altitudes up to 8000 feet on astandard day. For hot day or high altitude conditions, the cruise RPM may be increased to 2700 RPM. Cruise at 2700 RPM permits the use of 75% power at altitudes up to 10, 000 feet on a standard day. However, for reduced noise levels it is desirable to select lowest RPM in the green arc range for agiven percent power that will I )vide smooth engine operation. 2 - 1 5 CRUISE PERFORMANCE LEANING WITH A CESSNA ECONOMY MIXTURE INDICATOR (EGT) SPINS STALLS LANDING SHORT FIELD LANDINGS COLD WEATHER OPERATION NOTE CROSSWIND LANDINGS BALKED LANDING STARTING When pulling the propeller through by hand, treat it as if the ignition switch is turned on. A loose or broken ground wire on either magneto could cause the engine to fire. 2.1 NOTE Use heavy strokes of primer for best atomization of fuel. After priming, push primer all the way in and turn to the locked position to avoid the possibility of the engine drawing fuel through the primer. NOTE IMPORTANT FLIGHT OPERATIONS Pumping the throttle may cause a raw fuel to accumulate in the intake air duct, creating a fire hazard in the event of a backfire. If this occurs, maintain a cranking action to suck the flames the engine. An outside attendant with a fire extinguisher is advised for cold starts without preheat. If the engine does not start during the first few attempts, or if engine firing diminishes in strength, it is probable that the spark plugs have frosted over. Preheat must be used before another start is attempted. HOT WEATHER OPERATION NOISE ABATEMENT NOTE The above recommended procedures do not apply where they would conflict with Air Traffic Control clearances or instructions, or where, in the pilot’s judgement, an altitude of less than 2,000 feet is necessary for him ti adequately exercise his duty to see and avoid other aircraft. EMERGENCY PROCEDURES ENGINE FAILURE ENGINE FAILURE AFTER TAKE-OFF ENGINE FAILURE AFTER DURING FLIGHT FORCED LANDINGS PRECAUTIONARY LANDING WITH ENGINE POWER EMERGENCY LANDING WITHOUT POWER FIRES DITCHING ENGINE FIRE DURING START ON GROUND ENGINE FIRE IN FLIGHT ELECTRICAL FIRE IN FLIGHT EXECUTING A 180° TURN IN CLOUDS EMERGENCY LET-DOWNS THROUGH CLOUDS DISORIENTATION IN CLOUDS .Before descending into the clouds, set up astabilized let-dov, c o u r s e c o n d i t i o n a s f o l l o w s ; ( 1 ) A p p l y f u l l r i c h m i x t u r e . (2) Use full carburetor heat. (3) Reduce power to set up a500 to 800 ft./min. rate of descent. (4) Adjust the stabilator trim tab for astabilized descent at 90 MPH. (5) Keep hands off the control wheel. (6) Monitor turn coordinator and make corrections by rudder alone. (7) Adjust rudder trim to relieve unbalanced rudder force if present. (8) Check trend of compass card movement and make cautious cor¬ rections with rudder to stop the turn. (9) Upon breaking out of clouds resume normal cruising flight. R E C O V E R Y F R O M A S P I R A L D I V E . If aspiral is encountered, proceed as follows: ( 1 ) C l o s e t h e t h r o t t l e . (2) Stop the turn by using coordinated aileron and rudder control to align the symbolic airplane in the turn coordinator with the horizon r e f e r e n c e l i n e . (3) Cautiously apply control wheel back pressure to slowly reduce the indicated airspeed to 90 MPH. ~ (4) Adjust the stabilator trim control to maintain a90 MPH glide (5) Keep hands off the control wheel, using rudder control to hole astraight heading. Adjust rudder trim to relieve unbalanced rudder force, if present. (6) Apply carburetor heat. (7) Clear engine occasionally, but avoid using enough power to dis¬ turb the trimmed glide. (8) Upon breaking out of clouds apply normal cruising power and re¬ s u m e fl i g h t . F L I G H T I N I C I N G C O N D I T I O N S . Although flying in known icing conditions is prohibited, an unexpected icing encounter should be handled as follows: (1) Turn pitot heat switch ON (if installed). (2) Turn bade or change altitude to obtain an outside air temperature tha.t is less conducive to icing. 3 - 6 ROUGH ENGINE OR LOSS OF POWER CARBURETOR ICING SPARK PLUG FOULING ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS MAGNETO MALFUNCTION LOW OIL PRESSURE INSUFFICIENT RATE OF CHARGE EXCESSIVE RATE OF CHARGE C-177B – N35031 CHECKLISTS ENGINE FAILURE DURING TAKEOFF 1. Throttle ........................................ IDLE 2. Brakes ....................................... APPLY 3. Wing Flaps.......................... RETRACT 4. Mixture ....................... IDLE CUT-OFF 5. Ignition Switch............................... OFF 6. Master/Battery Switch.................... OFF ENGINE FAILURE AFTER TAKEOFF 1. Airspeed................................... 80 MPH 2. Mixture ....................... IDLE CUT-OFF 3. Fuel Selector Valve ........................ OFF 4. Fuel Shutoff Valve ................................ ...................... OUT (Break Safety Wire) 5. Ignition Switch............................... OFF 6. Wing Flaps.................. AS REQUIRED 7. Master Switch ................................ OFF ENGINE FAILURE DURING FLIGHT 1. Airspeed................................... 85 MPH 2. Carburetor Heat .............................. ON 3. Fuel Selector Valve .................... BOTH 4. Mixture ........................................ RICH 5. Ignition Switch.......... BOTH or START 6. Primer .......................... IN & LOCKED 7. Airspeed................................... 80 MPH ENGINE FIRE DURING FLIGHT 1. Mixture ....................... IDLE CUT-OFF 2. Fuel Shutoff Valve ................................ ...................... OUT (Break Safety Wire) 3. Master Switch ................................ OFF 4. Cabin Heat ..................................... OFF 5. Airspeed.......................................... 100 ELECTRICAL FIRE DURING FLIGHT 1. Master Switch ................................ OFF 2. All other Switches (except Ignition) ...... ....................................................... OFF 3. Vents / Cabin Air / Heat ......... CLOSED 4. Fire Extinguisher............... ACTIVATE (if fire appears out) a. Master Switch ............................ ON b. Circuit Breakers .................. CHECK ............(Do NOT reset faulty circuit) c. Electrical/Radios ........................ ON . One at a time, with delay after each EMERGENCY LANDING 1. Mixture ...................... IDLE CUT-OFF 2. Fuel Selector Valve....................... OFF 3. Fuel Shutoff Valve ............................... .................... OUT (Break Safety Wire) 4. Select Field ....................... SUITABLE 5. Electrical Switches ....................... OFF 6. Wing Flaps (on final) . AS REQUIRED 7. Airspeed ................................. 75 MPH 8. Master/Battery Switch .................. OFF 9. Doors ................................ UNLATCH 10. Touchdown ........ SLIGHT TAIL LOW 11. Ignition ......................................... OFF 12. Brakes................... APPLY HEAVILY PRECAUTIONARY LANDING 1. Wing Flaps .................................... 15° 2. Airspeed ................................. 75 MPH 3. Select Field ....................... SUITABLE 4. Electronics .................................... OFF 5. Wing Flaps (on Final) .................... 30° 6. Airspeed ................................. 60 MPH 7. Master/Battery Switch .................. OFF 8. Doors ................................ UNLATCH 9. Touchdown ... SLIGHTLY TAIL LOW 10. Ignition Switch ............................. OFF 11. Brakes................... APPLY HEAVILY As of 1/9/20 C-177B – N35031 CHECKLISTS ENGINE FAILURE DURING TAKEOFF 1. Throttle ........................................ IDLE 2. Brakes ....................................... APPLY 3. Wing Flaps.......................... RETRACT 4. Mixture ....................... IDLE CUT-OFF 5. Ignition Switch............................... OFF 6. Master/Battery Switch.................... OFF ENGINE FAILURE AFTER TAKEOFF 1. Airspeed................................... 80 MPH 2. Mixture ....................... IDLE CUT-OFF 3. Fuel Selector Valve ........................ OFF 4. Fuel Shutoff Valve ................................ ...................... OUT (Break Safety Wire) 5. Ignition Switch............................... OFF 6. Wing Flaps.................. AS REQUIRED 7. Master Switch ................................ OFF ENGINE FAILURE DURING FLIGHT 1. Airspeed................................... 85 MPH 2. Carburetor Heat .............................. ON 3. Fuel Selector Valve .................... BOTH 4. Mixture ........................................ RICH 5. Ignition Switch.......... BOTH or START 6. Primer .......................... IN & LOCKED 7. Airspeed................................... 80 MPH ENGINE FIRE DURING FLIGHT 1. Mixture ....................... IDLE CUT-OFF 2. Fuel Shutoff Valve ................................ ...................... OUT (Break Safety Wire) 3. Master Switch ................................ OFF 4. Cabin Heat ..................................... OFF 5. Airspeed.......................................... 100 ELECTRICAL FIRE DURING FLIGHT 1. Master Switch ................................ OFF 2. All other Switches (except Ignition) ...... ....................................................... OFF 3. Vents / Cabin Air / Heat ......... CLOSED 4. Fire Extinguisher............... ACTIVATE (if fire appears out) a. Master Switch ............................ ON b. Circuit Breakers .................. CHECK ............(Do NOT reset faulty circuit) c. Electrical/Radios ........................ ON . One at a time, with delay after each EMERGENCY LANDING 1. Mixture ...................... IDLE CUT-OFF 2. Fuel Selector Valve....................... OFF 3. Fuel Shutoff Valve ............................... .................... OUT (Break Safety Wire) 4. Select Field ....................... SUITABLE 5. Electrical Switches ....................... OFF 6. Wing Flaps (on final) . AS REQUIRED 7. Airspeed ................................. 75 MPH 8. Master/Battery Switch .................. OFF 9. Doors ................................ UNLATCH 10. Touchdown ........ SLIGHT TAIL LOW 11. Ignition ......................................... OFF 12. Brakes................... APPLY HEAVILY PRECAUTIONARY LANDING 1. Wing Flaps .................................... 15° 2. Airspeed ................................. 75 MPH 3. Select Field ....................... SUITABLE 4. Electronics .................................... OFF 5. Wing Flaps (on Final) .................... 30° 6. Airspeed ................................. 60 MPH 7. Master/Battery Switch .................. OFF 8. Doors ................................ UNLATCH 9. Touchdown ... SLIGHTLY TAIL LOW 10. Ignition Switch ............................. OFF 11. Brakes................... APPLY HEAVILY As of 1/9/20 C-177B – N35031 CHECKLISTS ENGINE FAILURE DURING TAKEOFF 1. Throttle ........................................ IDLE 2. Brakes ....................................... APPLY 3. Wing Flaps.......................... RETRACT 4. Mixture ....................... IDLE CUT-OFF 5. Ignition Switch............................... OFF 6. Master/Battery Switch.................... OFF ENGINE FAILURE AFTER TAKEOFF 1. Airspeed................................... 80 MPH 2. Mixture ....................... IDLE CUT-OFF 3. Fuel Selector Valve ........................ OFF 4. Ignition Switch............................... OFF 5. Wing Flaps.................. AS REQUIRED 6. Master Switch ................................ OFF ENGINE FAILURE DURING FLIGHT 1. Airspeed................................... 85 MPH 2. Carburetor Heat .............................. ON 3. Fuel Selector Valve .................... BOTH 4. Mixture ........................................ RICH 5. Ignition Switch.......... BOTH or START 6. Primer .......................... IN & LOCKED 7. Airspeed................................... 80 MPH EMERGENCY LANDING 1. Mixture ...................... IDLE CUT-OFF 2. Fuel Selector Valve ...................... OFF 3. Select Field ....................... SUITABLE 4. Electrical Switches ....................... OFF 5. Wing Flaps (on final) ......................30° 6. Airspeed ................................. 75 MPH 7. Master/Battery Switch .................. OFF 8. Doors .............. UNLATCH PRIOR TO TOUCHDOWN 9. Touchdown .........SLIGHT TAIL LOW 10. Ignition ......................................... OFF 11. Brakes................... APPLY HEAVILY PRECAUTIONARY LANDING 1. Wing Flaps .....................................15° 2. Airspeed ................................. 75 MPH 3. Select Field ....................... SUITABLE 4. Electronics .................................... OFF 5. Wing Flaps (on Final) .....................30° 6. Airspeed ................................. 60 MPH 7. Master/Battery Switch .................. OFF 8. Doors ................................ UNLATCH 9. Touchdown ... SLIGHTLY TAIL LOW 10. Ignition Switch ............................. OFF 11. Brakes................... APPLY HEAVILY LOSS OF INDIVIDUAL DISPLAY ELEMENT 1. Continue normal engine operation by referring to the remaining parameters displayed. 1. Avoid high engine power settings and rapid power changes; 2. Enrichen Mixture to maintain smooth engine operation; 3. Arrange to terminate the flight safely and as soon as practicable. 4. Refer to your origional airplane AFM for possible additional engine instrument failure information EDM-900 EMERGENCY PROCEDURES LOSS OF ALL DISPLAYS (Electrical Failure). The RAL will indicate limits even if the display fails and the rest of the unit is functional. NOTE EMERGENCY LOCATOR TRANSMITTER (ELT). T h e E LT c o n s i s t s o f a s e l f - c o n t a i n e d d u a l - f r e q u e n c y r a d i o t r a n s m i t ¬ ter and battery power supply, and is activated by an impact of 5g or more as may be experienced in acrash landing. The ELT emits an omni¬ directional signal on the international distress frequencies of 121. 5and 243.0 MHz. General aviation and commercial aircraft, the FAA, and CAP monitor 121. 5MHz, and 243.0 MHz is monitored by the military. F o l l o w i n g a c r a s h l a n d i n g , t h e E LT w i l l p r o v i d e l i n e - o f - s i g h t t r a n s m i s ¬ sion up to 100 miles at 10,000 feet. The duration of ELT transmissions is affected by ambient temperature. At temperatures of +70° to +130°F, continuous transmission for 115 hours can be expected; atemperature of - 4 0 ° F w i l l s h o r t e n t h e d u r a t i o n t o 7 0 h o u r s . Tlie ELT is readily identified as abright orange unit mounted behind the baggage compartment wall on the right side of the fuselage. To gain access to the unit, grasp the edge of the baggage wall and pull. The ELT is operated by acontrol panel at the forward facing end of the unit (see fi g u r e 3 - 1 ) . E L T O P E R A T I O N . (1) NORMAL OPERATION: As long as the function selector switch remains in the ARM position, the ELT automatically activates fol-'^ l o w i n g a n i m p a c t o f 5 g o r m o r e o v e r a s h o r t t i m e p e r i o d . ( 2 ) E LT FA I L U R E : I f " g " s w i t c h a c t u a t i o n i s q u e s t i o n e d f o l l o w i n g aminor crash landing, gain access to the ELT and place the function selector switch in the ON position. ( 3 ) P R I O R TO S I G H T I N G R E S C U E A I R C R A F T: C o n s e r v e a i r c r a f t b a t t e r y. D o n o t a c t i v a t e r a d i o t r a n s c e i v e r. (4) AFTER SIGHTING RESCUE AIRCRAFT: Place ELT function selector switch in the OFF position, preventing radio interference. Attempt contact with rescue aircraft with the radio transceiver set to afrequency of 121. 5MHz. If no contact is established, return t h e f u n c t i o n s e l e c t o r s w i t c h t o O N i m m e d i a t e l y . ( 5 ) F O L L O W I N G R E S C U E : P l a c e E LT f u n c t i o n s e l e c t o r s w i t c h i n t h e O F F p o s i t i o n , t e r m i n a t i n g e m e r g e n c y t r a n s m i s s i o n s . 3 - 1 0 OPERATIONS AUTHORIZED MANEUVERS - NORMAL CATEGORY OPERATING LIMITATIONS MANEUVERS - UTILITY CATEGORY AIRSPEED LIMITATIONS (CAS) AIRSPEED INDICATOR MARKINGS ENGINE OPERATION LIMITATIONS ENGINE INSTRUMENT MARKINGS OIL TEMPERATURE GAGE CYLINDER HEAD TEMPERATURE GAGE WEIGHT AND BALANCE NOTE OIL PRESSURE GAGE FUEL PRESSURE GAGE FUEL QUANTITY INDICATORS TACHOMETER MANIFOLD PRESSURE GAGE CARBURETOR AIR TEMPERATURE GAGE (optional) The licensed empty weight and moment are recorded on the Weight and Balancer and Installed Equipment Data sheet, or on revised weight and NOTE BAGGAGE AND CARGO TIE-DOWN Loading Graph information for the pilot, passengers, baggage, cargo, and hatshelf is based on seats positioned for average occupants and baggage / cargo or hatshelf items loaded in the center of these areas as shown on the Loading Arrangements diagram. For loadings which may differ from these, the Sample Loading Problem lists fuselage stations for these items to indicate their forward and aft c.g. range limitation (seat travel and baggage / cargo or hatshelf area limitation. Additional moment calculations, based on the actual weight and c.g. arm (fuselage station) of the item being loaded, must be made if the position of the load is different from that shown on the Loading Graph. A reduced fuel weight may be measured for use with heavy cabin loadings by filling both tanks to the 22 gallon marker for 43 gallons (258 pounds) usable. Both tanks may be filled for maximum range, provided gross weight is not exceeded. balance records, and are included in the aircraft file. In addition to the licensed empty weight and moment noted on these records, the c.g. arm (fuselage station) is also shown, but need not be used on the Sample loading Problem. The moment which is shown must be divided by 1,000 and this value used as the moment/1000 on the loading problem. EDM-930 Operating Limitations A. The EDM-930 may replace any existing RPM, MAP, EGT, CHG, CDT, TIT, O-T O-P, F-P, FF, and Fuel Quantity indicators required by the aircraft type design. B. The EDM=930 cannot be used as primary if the RAD is not working. C. This Pilots Guide must be available to the pilot for all flight operations. LOADING ARRANGEMENTS STANDARD SEATING 2ND ROW SEAT REMOVED 1,426 148.3 33.0 294.0 450.0 41.7 10.0 2.0 2197 225.8 SAMPLE LOADING PROBLEM N35031 17 0.8 Weight (lbs.) Moment (lb. -ins. /1000) . LOADING GRAPH . CENTER OF GRAVITY MOMENT ENVELOPE . GROUND HANDLING MOORING YOUR AIRPLANE CARE OF THE AIRPLANE WINDSHIELD - WINDOWS PAINTED SURFACES NOTE Never use gasoline, benzine, alcohol, acetone, carbon tetrachloride, fire extinguisher, or anti-ice fluid, lacquer thinner or glass cleaner to clean the plastic. These materials will attack the plastic and may cause it to craze. ALUMINUM SURFACES PROPELLER CARE INTERIOR CARE MAA PLATE / FINISH AND TRIM PLATE AIRCRAFT FILE FLYABLE STORAGE INSPECTION REQUIREMENTS IMPORTANT For maximum safety, check that the ignition switch is OFF, the throttle is closed, the mixture control is in the idle cut-off position and the airplane is secured before rotating the propeller by hand. Do not stand within the arc of the propeller blades while turning the propeller. CESSNA PROGRESSIVE CARE CESSNA CUSTOMER CARE PROGRAM SERVICING REQUIREMENTS OWNER FOLLOW-UP SYSTEM PUBLICATIONS OPERATIONAL DATA 2500 2200 1900 2500 2200 1900 ( ) 2500 2400 2300 2200 2100 2,500 FEET ( ) 2500 2400 2300 2200 2100 5,000 FEET ( ) 2500 2400 2300 2200 2100 7,500 FEET ( ) 2500 2400 2300 2200 2100 2600 2700 10,000 FEET ) ( 2500 2400 2300 2200 2100 2600 2700 12,500 FEET 2500 Horton: 540 Horton:50 WINTERIZATION KIT GROUND SERVICE PLUG RECEPTICLE OPTIONAL SYSTEMS COLD WEATHER EQUIPMENT Electrical power for the aircraft electrical circuits is provided through a split bus bar having all electronic circuits on one side of the bus and the other electrical circuits on the other side of NOTE STATIC PRESSURE ALTERNATE SOURCE VALVE the bus. When an external power source is connected, a contractor automatically opens the circuit to the electronic portion of the split bus bar as a protection against damage to the transistors in the electronic equipment by transient voltages from the power source. Therefore the external power source can not be used as a source of power when checking electronic components. an 4MPH and 50 feet, respectively. However, opening the vent win- ivs results in large errors which increase with increasing airspeed, xor example, at the placarded maximum window open speed of 120 MPH, the airspeed indicator and altimeter will read low by as much as 12 MPH and 90 feet, respectively. To avoid these large errors the windows should not be open when using the alternate static source. M I C R O P H O N E - H E A D S E T Amicrophone-headset combination is offered as optional equipment. Using the microphone-headset and amicrophone keying switch on the left side of the pilot's control wheel, the pilot can conduct radio communica¬ tions without interrupting other control operations to handle ahand-held microphone. Also, passengers need not listen to all communications. The microphone and headset jacks are located near the lower left corner the instrument panel. 7 - 3 N35031 17702167 N35031 17702167 Cessna 177B 190-00734-15 Rev. 3 AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B Page 2 of 17 FAA APPROVED LOG OF REVISIONS Page Revision Number Date Number Description FAA Approved 1 05/01/2013 All Complete Supplement Robert Murray Robert Murray ODA STC Unit Administrator Garmin International, Inc. ODA-240087-CE Date: 05/01/2013 2 03/08/2016 All New supplement format with GTX 3X5 added. Michael Warren Michael Warren ODA STC Unit Administrator Garmin International, Inc. ODA-240087-CE Date: 03/08/2016 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. See cover page AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B 190-00734-15 Rev. 3 FAA APPROVED Page 3 of 17 Table of Contents SECTION PAGE Section 1. GENERAL 4 1.1 GTX 33X 4 1.2 GTX 3X5 6 1.3 Capabilities 8 1.4 Installation Configuration 8 1.5 Definitions 11 Section 2. LIMITATIONS 12 2.1 Minimum Equipment 12 2.2 ADS-B Out 12 2.3 TIS Traffic Display with User Navigation Angle 12 2.4 Applicable System Software 13 2.5 Pressure Altitude Broadcast Inhibit (PABI) 13 2.6 Datalinked Weather Display (GTX 345 Only) 13 2.7 Portable Electronic Devices 13 Section 3. EMERGENCY PROCEDURES 14 3.1 Emergency Procedures 14 3.2 Abnormal Procedures 14 Section 4. NORMAL PROCEDURES 15 4.1 Unit Power On 15 4.2 Before Takeoff 16 Section 5. PERFORMANCE 16 Section 6. WEIGHT AND BALANCE 16 Section 7. SYSTEM DESCRIPTION 17 7.1 GTX TIS Behavior 17 7.2 GTX 345R and G950/1000 No Bearing Traffic Alerts 17 190-00734-15 Rev. 3 AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B Page 4 of 17 FAA APPROVED Section 1. GENERAL 1.1 GTX 33X The Garmin GTX 33X family consists of the GTX 330 ES and GTX 33 ES (Non- Diversity Mode S Transponders) and the GTX 330D ES and GTX 33D ES (Diversity Mode S Transponders). The ES option of any of the transponders provides ADS-B extended squitter functionality. All Garmin GTX 33X transponders are a radio transmitter/receiver that operates on radar frequencies, receiving ground radar 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 position identification) pulse for 18 seconds and will reply to ATCRBS Mode A, Mode C and Mode S All-Call interrogation. Interfaces to the GTX 33X are shown in the following block diagrams. GTX 330 or GTX 330D Bottom Antenna GTX 330D Installs only GPS Traffic System Audio Panel Optional Interfaces Heading Source Secondary GPS Display External Ident Temperature Squat Switch External STBY Required Interfaces Altitude Source Power/Ground Top Antenna Figure 1 – GTX 330 or GTX 33D Interface Summary AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B 190-00734-15 Rev. 3 FAA APPROVED Page 5 of 17 GTX 33 or GTX 33D Bottom Antenna GTX 33D Installs only Garmin GTN 6XX/7XX Traffic System Audio Panel Optional Interfaces Heading Source Secondary GPS Temperature Squat Switch Required Interfaces Altitude Source Power/Ground Top Antenna External Ident External Standby Garmin GNS 480 OR Figure 2 – GTX 33 or GTX 33D Interface Summary The GTX 33X performs the following functions: x Transmission 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: ƒ GPS Position, Altitude, and Position Integrity ƒ Ground Track and/or Heading, Ground Speed, and Velocity Integrity ƒ Air Ground Status ƒ Flight ID, Call Sign, ICAO Registration Number ƒ Capability and Status Information ƒ Transponder Squawk Codes between 0000-7777. ƒ Emergency Status ƒ IDENT - initiates SPI (special position identification) pulse for 18 seconds o Pressure Altitude Broadcast Inhibit x Reception of TIS-A traffic data from a ground station x Provides TIS-A traffic alerting to the pilot via interfaced display and audio output 190-00734-15 Rev. 3 AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B Page 6 of 17 FAA APPROVED 1.2 GTX 3X5 The Garmin GTX 3X5 family consists of the GTX 335, 335R, 345, and 345R transponders. The functional differences between each of these transponders are described in Table 1. Function GTX 335 GTX 335 w/GPS GTX 335R GTX 335R w/GPS GTX 345 GTX 345 w/GPS GTX 345R GTX 345R w/GPS Panel mount x x x x Remote mount x x x x Mode S x x x x x x x x ADS-B (out) x x x x x x x x ADS-B Traffic x x x x FIS-B x x x x Internal GPS x x x x Bluetooth x x x x Optional Garmin Altitude Encoder x x x x x x x x Table 1 – GTX 3X5 Unit Configurations Interfaces to the GTX 3X5 are shown in Figure 3. TAS/TCAS I Traffic Sensor ADS-B Traffic FIS-B Display Bluetooth Device GTX 3X5 GPS Antenna External GPS Source Audio Panel Bottom Antenna GTX 3X5 with GPS only OR GTX 335R/345R Control Power/Ground Altitude Source Heading Source Air Data Source Secondary GPS Radio Altitude Source Optional Interfaces Required Interfaces WOW Switch Bluetooth GTX 345 / 345R only External Traffic Annunciator For NO display Install Flight Stream OR Keep Alive Input Figure 3 – GTX 3X5 Interface Summary AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B 190-00734-15 Rev. 3 FAA APPROVED Page 7 of 17 The GTX 3X5 performs the following functions: x Transmission 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: ƒ GPS Position, Altitude, and Position Integrity ƒ Ground Track and/or Heading, Ground Speed, and Velocity Integrity ƒ Air Ground Status ƒ Flight ID, Call Sign, ICAO Registration Number ƒ Capability and Status Information ƒ Transponder Squawk Codes between 0000-7777. ƒ Emergency Status ƒ IDENT - initiates SPI (special position identification) pulse for 18 seconds o Pressure Altitude Broadcast Inhibit The GTX 335 performs the following additional functions: x Reception of TIS-A traffic data from a ground station x Provide TIS-A traffic alerting to the pilot via interfaced display and audio output. The GTX 345 performs the following additional functions: x Reception of ADS-B In data on 1090 MHz o ADS-B (Data directly from another transmitting aircraft) o ADS-R (Rebroadcast of ADS-B data from a ground station) x Reception 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 radar) (SSR) derived traffic information from a ground station. o FIS-B (Broadcast of aviation data from a ground station) x Provide ADS-B traffic information and alerting to the pilot via an interfaced display 190-00734-15 Rev. 3 AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B Page 8 of 17 FAA APPROVED o Correlation and consolidation of traffic data from multiple traffic sources o Aural and visual traffic alerting x Provide FIS-B data to the pilot via an interfaced display o Graphical and textual weather products ƒ NEXRAD ƒ PIREPs ƒ AIRMET/SIGMETs ƒ METARs ƒ TAFs ƒ Winds Aloft o Aviation Data ƒ TFRs ƒ NOTAMs 1.3 Capabilities The Garmin GTX 33X and GTX 3X5 as installed in this aircraft have been shown to meet the equipment requirements of 14 CFR § 91.227 when operating in 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: AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B 190-00734-15 Rev. 3 FAA APPROVED Page 9 of 17 Equipment Installed: Transponder #1 … GTX 330 … GTX 330D … GTX 33 … GTX 33D … GTX 335 … GTX 335R … GTX 345 … GTX 345R Transponder #2 (if installed) … GTX 330 … GTX 330D … GTX 33 … GTX 33D … GTX 335 … GTX 335R … GTX 345 … GTX 345R Interfaced GPS/SBAS Position Source(s): GPS #1 GPS #2 (if installed) … Internal … Internal … GTN 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) … GIA 63W … GDL 88 (GTX 330 only) Interfaced Pressure Altitude Source: Pressure Altitude Source #1 …_____________________ … Garmin Altitude Encoder Pressure Altitude Source #2 (if installed) …_____________________ … Garmin Altitude Encoder x x x 190-00734-15 Rev. 3 AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B Page 10 of 17 FAA APPROVED Interfaced Remote Control Display (Required for remotely mounted GTX variants): Transponder #1 Remote Control Display … GTN 6XX/7XX … GNS 480 … G950/1000 Display … Gables 7534 Controller Transponder #2 Remote Control Display (if installed) … GTN 6XX/7XX … GNS 480 … G950/1000 Display … Gables 7534 Controller Interfaced Active Traffic System: … None … TCAD … TAS/TCAS NOTE If the system includes all of the following components: x GTX 345R, x G950/1000 Display, and x TCAD or TAS/TCAS Then the aircraft is no longer equipped with a TSO compliant active TCAD, TAS or TCAS system. Any operational requirement to be equipped with such system is no longer met. x AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B 190-00734-15 Rev. 3 FAA APPROVED Page 11 of 17 1.5 Definitions The following terminology is used within this document: ADS-B: Automatic Dependent Surveillance-Broadcast AFM: Airplane Flight Manual AFMS: Airplane Flight Manual Supplement ATCRBS: Air Traffic Control Radar 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: Garmin Touchscreen Navigator ICAO: International Civil Aviation Organization LRU: Line Replaceable Unit PABI: Pressure Altitude Broadcast Inhibit POH: Pilot Operating Handbook SBAS: Satellite-Based Augmentation System SW: Software TCAS: Traffic Collision Avoidance System TIS: Traffic Information Service TX: Transmit 190-00734-15 Rev. 3 AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B Page 12 of 17 FAA APPROVED Section 2. LIMITATIONS 2.1 Minimum Equipment The GTX 33X and GTX 3X5 must have the following system interfaces fully functional in order to be compliant with the requirements for 14 CFR 91.227 ADS- B Out operations: Interfaced Equipment Number Installed Number Required Uncorrected Pressure Altitude Source 1 1 GPS SBAS Position Source 1 or more 1 Remote Control Display (for remotely mounted transponders) 1 or more 1 Table 2 – Required Equipment 2.2 ADS-B Out The GTX 33X 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 remote control display interface, or the GTX 330 or GTX 3X5 panel display. If a Gables 7534 controller is being used the ADS-B equipment failure condition will be annunciated on the Gables disSOa\ ³TUaQVSRQdeU FaiO´ ZhiOe Whe ADS-B Out Position failure will be aQQXQciaWed b\ Whe UePRWeO\ iQVWaOOed ³ADS-B POSN FAIL´ AQQXQciaWRU. 2.3 TIS Traffic Display with User Navigation Angle Display of TIS traffic from a GTX 33/330 or GTX 335 is not permitted with an iQWeUfaciQg diVSOa\ cRQfigXUed fRU a QaYigaWiRQ aQgOe Rf ³XVeU´. AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B 190-00734-15 Rev. 3 FAA APPROVED Page 13 of 17 2.4 Applicable System Software This AFMS/AFM is applicable to the software versions shown in Table 3. The Main GTX software version is displayed on the splash screen during start up for the GTX 330 and GTX 3X5 panel mounted units, and the External LRU or System page on the interfaced remote control display for remotely mounted GTX transponders. Software Item Software Version (or later FAA Approved versions for this STC) GTX 33X Main SW Version 8.04 GTX 3X5 Main SW Version 2.12 Table 3 - Software Versions 2.5 Pressure Altitude Broadcast Inhibit (PABI) Pressure Altitude Broadcast Inhibit shall only be enabled when requested by Air Traffic Control while operating within airspace requiring an ADS-B Out compliant 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 hazardous weather. Information provided by datalink weather products may not accurately depict current weather conditions. Do not use the indicated datalink weather product age to determine the age of the weather information shown by the datalink weather product. Due to time delays inherent in gathering and processing weather data for datalink transmission, the weather information shown by the datalink weather product may be significantly older than the indicated weather product age. Do not rely solely upon datalink services to provide Temporary Flight Restriction (TFR) or Notice to Airmen (NOTAM) information. 2.7 Portable Electronic Devices This STC does not relieve the operator from complying with the requirements of 91.21 or any other operational regulation regarding portable electronic devices. 190-00734-15 Rev. 3 AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B Page 14 of 17 FAA APPROVED Section 3. EMERGENCY PROCEDURES 3.1 Emergency Procedures No Change. 3.2 Abnormal Procedures 3.2.1 LOSS OF AIRCRAFT ELECTRICAL POWER GENERATION XPDR Circuit Breaker ................................................................................. PULL Transponder and ADS-B Out functions will no longer be available. NOTE This guidance is supplementary to any guidance provided in the POH or AFM for the installed 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 transmitting ADS-B Out data. For GTX 330 installations: NO ADSB annunciator illuminated: Interfaced GPS position sources ........................... VERIFY VALID POSITION For GTX 3X5 installations: NO 1090ES TX annunciator illuminated: Interfaced GPS position sources ........................... VERIFY VALID POSITION For GTX 33 and GTX 3X5R installations: Reference Display Device documentation for applicable annunciation: Interfaced GPS position sources ........................... VERIFY VALID POSITION AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B 190-00734-15 Rev. 3 FAA APPROVED Page 15 of 17 Section 4. NORMAL PROCEDURES The procedures described below are specific only to the panel mounted GTX 330 or GTX 3X5 transponders. Cockpit Reference Guides and Pilot Guides for interfaced remote control displays will provide additional operating information specific to the displays or other traffic systems. ADS-B Out functionality resides within the GTX transponders thereby 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 these procedures are located in the GTX 330/330D PLORW¶V GXLGH DQG GTX 3X5 SHULHV TUDQVSRQGHU PLORW¶V GXLGH. 4.1 Unit Power On For GTX 330 installations: GTX Mode .................................................................................... VERIFY ALT NO ADSB .................................................................................. CONSIDERED For GTX 3X5 installations: GTX Mode .................................................................................... VERIFY ALT NO 1090ES TX .......................................................................... CONSIDERED NOTE The NO ADS-B or NO 1090ES TX Annunciation (or associated display annunciations) may illuminate as the unit powers on and begins to receive input from external systems, to include the SBAS position source. 190-00734-15 Rev. 3 AFMS, Garmin GTX 33X and 3X5 XPDR with ADS-B Page 16 of 17 FAA APPROVED 4.2 Before Takeoff For GTX 330 installations: ADS-B TX ....................................................................................... VERIFY ON NO ADSB ............................................................................... EXTINGUISHED For GTX 3X5 installations: 1090ES TX CTL .............................................................................. VERIFY ON NO 1090ES TX ...................................................................... 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 requirements specified in 14 CFR 91.227. This system must be operational in certain airspaces after January 1, 2020 as specified by 14 CFR 91.225. Section 5. PERFORMANCE No change. Section 6. WEIGHT AND BALANCE See current weight and balance data. AFMS, Garmin GTN GPS/SBAS System 190-00734-15 Rev. 3 Page 17 of 17 Section 7. SYSTEM DESCRIPTION The Garmin GTX 330 and GTX 3X5 PLORW¶V GXLGHs, part numbers, and revisions listed below contain additional information regarding GTX system description, control, and function. Title Part Number Revision GTX 330 PLORW¶V GXLGH GTX 3X5 PLORW¶V GXLGH 190-00207-00 190-01499-00 Rev. G (or later) Rev. A (or later) Pilot¶V Guides for interfaced displays, part numbers and revisions listed below, provide additional operating information for the Garmin GTX 33 and GTX 3X5R. Title Part Number Revision Garmin GTN 725/750 PLORW¶V GXLGH 190-01007-03 Rev. E (or later) Garmin GTN 625/635/650 PLORW¶V GXLGH 190-01004-03 Rev. E (or later) GNS 480 PLORW¶V GXLGH 190-00502-00 Rev. D (or later) GTX 3X5 Series TUDQVSRQGHU G1000 PLORW¶V Guide 190-01499-01 Rev. A (or later) 7.1 GTX TIS Behavior The TIS Standby/Operate controls for GTX 33/330 and GTX 335 units only function when the aircraft is airborne. 7.2 GTX 345R and G950/1000 No Bearing Traffic Alerts No visual indication is provided for no bearing traffic alerts. Only an aural indication of the no bearing traffic alert is provided. If an aural alert for no bearing WUDIILF KDV EHHQ SUHYLRXVO\ LVVXHG, D ³QR EHDULQJ WUDIILF FOHDU´ DXUDO LQGLFDWLRQ ZLOO be provided once all traffic alerts are resolved. AOO DXUDO DOHUWV DUH LQKLELWHG EHORZ 500¶ AGL, WKHUHIRUH D ³QR EHDULQJ WUDIILF FOHDU´ aural may not be heard in a landing or touch and go flight scenario. CESSNA AIRCRAFT COMPANY WICHITA, KANSAS “TAKE YOUR CESSNA HOME FOR SERVICE AT THE SIGN OF THE CESSNA SHIELD” Fuel sampling: Fuel strainer, wing tank and reservoir quick drains. 1. Place a suitable container under the fuel strainer drain outlet prior to operating the strainer drain control for at least 4 seconds. Check strainer drain closed. 2. Inspect the fluid drained from the fuel strainer and each wing tank quick drain for evidence of fuel contamination in the form of water, rust, sludge, ice or any other substance not compatible with fuel. Also check for proper fuel grade before the first flight of each day and after each refueling. If any contamination is detected, comply with 4 below. 3. Repeat Steps 1 and 2 on each wing tank quick drain. 4. If the airplane has been exposed to rain, sleet or snow, or if the wing fuel tanks or fuel strainer drains produce water, the fuel reservoir(s) must be checked for the presence of water by operating the fuel reservoir quick drains. The airplane fuel system must be purged to the extent necessary to insure that there is no water, ice or other fuel contamination. APPENDIX 86-19-11 PILOT OPERATING PROCEDURES PREFLIGHT FUEL SYSTEM CHECK NOTE 1: The fuel reservoir(s) are located under the fuselage between the firewall and forward door post on all airplane models. Consult the pilots Operating Handbook or Owners Manual in order to determine if one or two reservoir(s) are installed. NOTE 2: A check for the presence of water using the fuel reservoir quick drains prior to the first flight of each day is considered good operating practice. A L P H A B E T I C A L I N D E X A oil, inside back cover C a r b u r e t o r A i r Te m p e r a t u r e G a g e , 4 - 4 , 7 - 5 Carburetor Icing, 3-7 C a r e , A f t e r L a n d i n g , 1 - 7 A i r c r a f t , fi l e , 5 - 5 ground handling, 5-1 mooring, 5-1 s e c u r i n g , 1 - 7 A i r s p e e d C o r r e c t i o n Ta b l e , 6 - 2 Airspeed Indicator, True, 7-6 A i r s p e e d I n d i c a t o r M a r k i n g s , 4 - 3 A i r s p e e d L i m i t a t i o n s , 4 - 3 Alternate Source Valve, Static P r e s s u r e , 7 - 2 Aluminum ^rfaces, 5-3 A m m e t e r , 2 - 4 Authorized Operations, 4-1 i n t e r i o r , 5 - 4 p r o p e l l e r, 5 - 3 Center of Gravity Moment Envelope, 4-10 Cessna Customer Care Program, 5 - 7 Cessna Progressive Care, 5-7 Circuit Breakers and Fuses, 2-6 C l i m b , data, 2-15 e n r o u t e , 1 - 5 , 2 - 1 5 maximum performance, 1-6 m a x i m u m r a t e - o f - c l i m b data chart, 6-3 n o r m a l , 1 - 5 speeds, 2-15 Cold Weather Equipment, 7-1 ground service plug receptacle, 7-1 s t a t i c p r e s s u r e a l t e r n a t e source valve, 7-2 w i n t e r i z a t i o n k i t , 7 - 1 Cold Weather Operation, 2-20 flight operations, 2-22 s t a r t i n g , 2 - 2 0 C o r r e c t i o n Ta b l e , A i r s p e e d , 6 - 2 Crosswind Landings, 2-19 C r o s s w i n d Ta k e - O ff , 2 - 1 4 C r u i s e , 2 - 1 5 leaning with EGT, 2-17 Cruise Performance Chart, 2-16, 6-4, 6-5, 6-6, 6-7, 6-8 C r u i s i n g , 1 - 6 Cylinder Head Temperature Gage, B Baggage and Cargo Tie-Down, 4-5 Balked Landing, 1-7, 2-19 B e f o r e L a n d i n g , 1 - 6 Before Starting Engine, 1-4 B e f o r e Ta k e - O f f , 1 - 4 , 2 - 11 a l t e r n a t o r c h e c k , 2 - 1 3 magneto check, 2-13 w a r m - u p , 2 - 11 c Cabin Heating, Ventilating and Defrosting System, 2-8 C a p a c i t y, fuel, inside back cover 4 - 3 I n d e x - 1 D E m e r g e n c y L o c a t o r Tr a n s m i t t e r (ELT), 3-10 ELT operation, 3-10 Empty Weight, inside front cover Engine, D i a g r a m , electrical system, 2-5 ELT control panel, 3-11 exterior inspection, 1-2 fuel system, 2-2 instrument panel, 1-8 loading arrangements, 4-7 maximum glide, 6-10 principal dimensions, ii radio selector switches, 7-4 taxiing, 2-12 Dimensions, Principal, ii Disorientation In Clouds, 3-5 emergency let-downs through clouds, 3-5 executing 180° turn in clouds, 3-5 recovery from spiral dive, 3-6 etching, 3-3 before starting, 1-4 instrument markii^s, 4-3 magneto check, 2-13 oil, inside back cover operation limitations, 4-3 rough operation or loss of p o w e r, 3 - 7 starting, 1-4, 2-10, 2-20 w a r m - u p , 2 - 11 Engine Failure, 3-1 a f t e r t a k e - o ff , 3 - 1 d u r i n g fl i g h t , 3 - 1 Enroute Climb, 2-15 maximum performance, 1-6 n o r m a l , 1 - 5 Equipment, Cold Weather, 7-1 E x c e s s i v e R a t e o f E l e c t r i c a l Charge, 3-9 Executing 180° Turn in Clouds, E 3 - 5 Economy Mixture Indicator, 7-7 operating instructions, 2-17 Electrical Power Supply System M a l f u n c t i o n s , 3 - 8 excessive rate of charge, 3-9 insufficient rate of charge, 3-9 Electrical System, 2-4 a m m e t e r, 2 - 4 circuit breakers and fuses, 2-6 ground service plug receptacle, 7 - 1 m a s t e r s w i t c h , 2 - 4 over-voltage sensor and w a r n i n g l i g h t , 2 - 4 s c h e m a t i c , 2 - 5 Emergency Landing Without Engine Power, 3-2 'mergency Let-Downs Through C l o u d s , 3 - 5 Exterior Inspection Diagram, 1-2 Exterior Lighting, 2-6 F Flap Settings, Wing, 2-14 File, Aircraft, 5-5 F i r e s , 3 - 3 electrical fire in flight, 3-4 engine fire during start on ground, 3-3 engine fire in flight, 3-4 Flight in Icing Conditions, 3-6 Flyable Storage, 5-6 F o r c e d L a n d i n g s , 3 - 2 d i t c h i n g , 3 - 3 emergency landing without engine power, 3-2 I n d e x - 2 Interior Care, 5-4 Interior Lighting, 2-7 precautionary landing Avith engine power, 3-2 Fuel System, 2-1 capacity, inside back cover fuel grade, inside back cover fuel pressure gage, 4-4 fuel quantity indicators, 4-4 quick-drain valves, 2-3 s c h e m a t i c , 2 - 2 Fuses and Circuit Breakers, 2-6 L L a n d i n g , 2 - 1 8 after, 1-7 balked, 1-7, 2-19 before, 1-6 crosswind, 2-19 distance table, 6-9 f o r c e d , 3 - 2 normal, 1-7 precautionary with power, 3-2 short field, 2-19 Landing Gear Servicing, inside b a c k c o v e r main/nose wheel tire pressure, i n s i d e b a c k c o v e r nose gear shock strut servicing, i n s i d e b a c k c o v e r Leaning With Cessna Economy Mixture Indicator (EGT), 2-17 Let-Down, 1-6 Lighting Equipment, 2-6 exterior lighting, 2-6 interior lighting, 2-7 Limitations, Airspeed, 4-3 Limitations, Engine Operation, G Graph, Loading, 4-9 Gross Weight, inside front cover Ground Handling, 5-1 Ground Service Plug Receptacle, 7 - 1 H —Handling Airplane on Ground, 5-1 \rnesses. Shoulder, 2-9 jadset-Microphone, 7-3 Heating, Ventilating and Defrosting S y s t e m , C a b i n , 2 - 8 Hot Weather Operation, 2-22 4 - 3 I L o a d i n g A r r a n g e m e n t s D i a g r a m , 4 - 7 I n d i c a t o r, E c o n o m y M i x t u r e , 7 - 7 o p e r a t i n g i n s t r u c t i o n s , 2 - 1 7 I n d i c a t o r, F u e l Q u a n t i t y, 4 - 4 I n d i c a t o r, Tr u e A i r s p e e d , 7 - 6 I n s p e c t i o n R e q u i r e m e n t s , 5 - 6 I n s t r u m e n t M a r k i n g s , E n g i n e , 4 - 3 Instrument Panel Diagram, 1-8 I n s u f fi c i e n t R a t e o f E l e c t r i c a l C h a r g e , 3 - 9 Integrated Seat Belt/Shoulder Har¬ nesses with Inertia Reel, 2-10 Loading Graph, 4-9 Loading Problem, Sample, 4-8 L o w O i l P r e s s u r e , 3 - 8 M MAA Plate/Finish Trim Plate, 5-5 Magneto Check, 2-13 Magneto Malfunction, 3-8 M a n e u v e r s - N o r m a l C a t e g o r y, 4 - 1 I n d e x - 3 Owner Follow-Up System, 5-9 publications, 5-9 ^ers -Utility Category, 4-2 !Pressure Gage, 4-4 ..gs, Airspeed Indicator, 4-3 M r > M M a . Markings, Engine Instrument, 4-3 M a s t e r S w i t c h , 2 - 4 M a x i m u m G l i d e D i a g r a m , 6 - 1 0 M a x i m u m P e r f o r m a n c e C l i m b , 1 - 6 M a x i m u m P e r f o r m a n c e Ta k e - O f f , P Painted Surfaces, 5-2 Performance Charts, 2-14 P e r f o r m a n c e - S p e c i fi c a t i o n s , i n s i d e f r o n t c o v e r Power Check, 2-13 Precautionary Landing with Ei^ine P o w e r, 3 - 2 Principal Dimensions Diagram, ii Progressive Care, Cessna, 5-7 P r o p e l l e r, c a r e , 5 - 3 Publications, 5-9 1 - 5 M a x i m u m R a t e - O f - C l i m b D a t a Chart, 6-3 Microphone-Headset, 7-3 Moment Envelope, Center of G r a v i t y, 4 - 1 0 Mooring Your Airplane, 5-1 N Noise Abatement, 2-22 Normal Category Maneuvers, 4-1 N o r m a l C l i m b , 1 - 5 Normal Landing, 1-7 Normal Take-OH, 1-5 Nose Gear Shock Strut, inside back Q Quick-Drain Valve, Oil, 7-7 Quick-Drain Valves, Fuel, 2-3 c r o R Oil System, capacity, inside back cover oil/filter change, inside back c o v e r oil grade, inside back cover pressure gage, 4-4 quick-drain valve, 7-7 temperature gage, 4-3 Operation, Cold Weather, 2-20 C^eration, Hot Weather, 2-22 Operation Limitations, Engine, 4 - 3 Operations Authorized, 4-1 Over-Voltage Sensor and Warning Light, 2-4 Radio Selector Switches, 7-4 diagram, 7-4 operation, 7-4 speaker-phone switches, 7-5 t r a n s m i t t e r s e l e c t o r s w i t c h , 7 - 4 Recovery From Spiral Dive, 3-6 Rough Engine Operation Or Loss of P o w e r, 3 - 7 c a r b u r e t o r i c i n g , 3 - 7 low oil pressure, 3-8 magneto malfunction, 3-8 spark plug fouling, 3-7 I n d e x - 4 s b e f o r e , 1 - 4 , 2 - 11 crosswind, 2-14 data chart, 6-3 m a x i m u m p e r f o r m a n c e , 1 - 5 n o r m a l , 1 - 5 performance charts, 2-14 power check, 2-13 wing flap setting, 2-14 Sample Loading Problem, 4-8 Securing Aircraft, 1-7 S e r v i c i n g R e q u i r e m e n t s , 5 - 8 i n s i d e b a c k c o v e r engine oil, inside back cover fuel, inside back cover landing gear, inside back cover Taxiing, 2-11 Short Field Landings, 2-19 d i a g r a m , 2 - 1 2 Shoulder Harnesses, 2-9 T i r e P r e s s u r e , i n s i d e b a c k c o v e r Shoulder Harnesses/Integrated Seat Transmitter Selector Switch, 7-4 Belt with Inertia Reel, 2-10 Spark Plug Fouling, 3-7 Speaker-Phone Switches, 7-5 Spins, 2-18 S t a l l s , 2 - 1 8 speed chart, 6-2 Starting Engine, 1-4, 2-10, 2-20 Static Pressure Alternate Source Va l v e , 7 - 2 Storage, Flyable, 5-6 Surfaces, a l u m i n u m , 5 - 3 p a i n t e d , 5 - 2 True Airspeed Indicator, 7-6 u utility Category Maneuvers, 4-2 w Wa r m - U p , 2 - 11 We i g h t , e m p t y, i n s i d e f r o n t c o v e r g r o s s , i n s i d e f r o n t c o v e r Weight and Balance, 4-4 baggage and cargo tie-down. lystem. cabin heating, ventilating and defrosting, 2-8 electrical, 2-4 fuel, 2-1 o w n e r f o l l o w - u p , 5 - 9 4 - 5 center of gravity moment envelope, 4-10 loadii^ arrangements diagram. 4 - 7 T loading graph, 4-9 sample loading problem, 4-8 W i n d s h i e l d - V ^ n d o w s , 5 - 2 Wing Flap Settings, 2-14 Winterization Kit, 7-1 Table of Contents, iii Ta c h o m e t e r, 4 - 4 Ta k e - O f f , 1 - 5 , 2 - 1 3 I n d e x - 5 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS “TAKE YOUR CESSNA HOME FOR SERVICE AT THE SIGN OF THE CESSNA SHIELD”