Cessna 182 Operating Instructions Manual Download | Manualshive

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1-46

Vacuum System

86.

An engine driven vacuum pump provides the suction necessary to operate the attitude

indicator and directional indicator. The system incorporates a vacuum relief valve and air filter.
A suction gauge located to the left of the flight instruments is calibrated in inches of mercury
and indicates the suction currently available. A suction range of 4.5 to 5.5 in-Hg is desired for
reliable operation of the attitude indicator and directional indicator.

Figure 1-55 Vacuum System

Stall Warning System

87.

A vane type stall warning unit is located in the left wing leading edge which electrically

activates an audible stall warning horn located under the instrument panel.

The horn is not

connected to the intercom system

. The horn is activated at speeds approximately 5-10 mph

above the stall in all configurations.

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Summary of Contents for 182

Page 1: ... Force under the authority of the Chief of Defense Staff OPI 2 Canadian Air Division Director Air Force Training 2017 01 31 NOTICE This document has been reviewed by the technical authority and does not contain controlled goods Disclosure notices and handling instructions originally received with the document shall continue to apply This document is electronically controlled and should not be cons...

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Page 3: ...rried on board the aircraft during flight There is no need to carry the AOIs in the aircraft For the list of documents used to compile these AOIs refer to LIST OF REFERENCES 5 All speeds are IAS unless indicated otherwise 6 Note Caution and Warning headings in this manual are defined as follows NOTE To point out a procedure event or practice which it is desired or essential to highlight CAUTION To...

Page 4: ... A 2 0 01 Feb 10 Revised Draft for review only N A N A 3 0 01 Mar 10 Revised Draft for review only N A N A 4 0 02 Jun 10 Initial Release Operational Airworthiness Clearance OAC N A N A 5 0 17 Nov 10 Update and Complete Document Re Issue N A N A 5 1 09 Feb 11 Update and Complete Document Re Issue N A N A 6 0 27 Jan 12 Update and Complete Document Re Issue N A N A 7 0 22 April 15 Update and Complete...

Page 5: ...iii TEMPORARY REVISIONS INDEX Temporary Revision No Date Inserted Date Removed Part Page Paragraph Affected ...

Page 6: ...imensions and Weights 1 2 Fuel Tank Capacities 1 2 Oil Capacities 1 2 AIRFRAME 1 3 Fuselage 1 3 Wings 1 4 Empennage 1 5 Windshield and Windows 1 6 Cabin Doors 1 7 Front Seats 1 9 Rear Seats 1 10 Seat Harnesses 1 10 Baggage Compartment 1 10 Removable Ballast 1 10 FLIGHT CONTROLS 1 11 Primary Flight Controls 1 11 Control Lock 1 12 Trim 1 12 Wing Flaps 1 13 UNDERCARRIAGE 1 14 Landing Gear 1 14 Wheels...

Page 7: ... 1 28 Fuel Strainer 1 28 Fuel Vent System 1 28 Fuel Quantity Indicators 1 29 Rotary Fuel Selector Valve 1 29 Fuel Header Tank 1 30 Fuel Shutoff Valve 1 31 Auxiliary Fuel Pump 1 32 ENGINE DATA MANAGEMENT SYSTEM 1 33 General 1 33 Main Display 1 34 Scanner Display 1 35 Remote Auxiliary Display RAD 1 35 Alerts 1 36 Responses to Alerts 1 36 Low Fuel Pressure Alerts 1 37 Shock Cooling Alerts 1 37 Mandat...

Page 8: ...der 1 54 Emergency Locator Transmitter ELT 1 55 GLIDER TOWING EQUIPMENT 1 56 Glider Tow Hook 1 56 Tow Mirrors 1 56 Gravel Deflectors 1 56 SAFETY EQUIPMENT 1 57 Fire Extinguisher 1 57 Life Preservers 1 57 First Aid Kit 1 57 Carbon Monoxide Detector 1 57 PART 2 NORMAL OPERATING PROCEDURES 2 1 GENERAL 2 1 GROUND HANDLING 2 1 General Ground Handling 2 1 Fuel and Oil Replenishment 2 2 DAILY INSPECTION ...

Page 9: ...FF 2 18 Normal Takeoff 2 18 Short Field Takeoff 2 18 Soft Rough Field Takeoff 2 19 Crosswind Takeoff 2 20 Post Takeoff 2 20 CLIMB PROFILES 2 21 CRUISE 2 22 Cruise Profiles 2 22 Level Off Cruise 2 23 FLIGHT MANOEUVRES FLIGHT CHARACTERISTICS 2 24 Turns 2 24 Slow Flight 2 24 Stalls 2 24 Spins 2 25 Spiral Dives 2 25 PRE STALL CHECK ASCOT 2 26 DESCENT 2 26 TRAFFIC PATTERN 2 27 FINAL APPROACH 2 28 ...

Page 10: ...rol 2 35 Mixture Control 2 35 FUEL MANAGEMENT 2 36 Pre Flight Planning 2 36 En Route Fuel Management 2 37 GLIDER TOWING OPERATIONS 2 38 General 2 38 Aircraft Performance on Tow 2 38 Prior to First Tow 2 38 Continuous Towing Operations 2 38 Takeoff with Glider on Tow 2 39 Glider Tow 2 40 Glider Release 2 40 Descent after Release 2 41 Approach and Landing 2 43 Cross Country Towing Operations 2 43 SE...

Page 11: ...ITICAL EMERGENCIES 3 10 Engine Shutdown FMS Check 3 10 Engine Restart FMS Check 3 10 Engine Fire on Start on Ground 3 11 In Flight Fires 3 12 Engine Failures 3 13 Forced Landing Ditching 3 15 PART 4 OPERATING DATA AND LIMITATIONS 4 1 GENERAL 4 1 GENERAL DATA 4 1 FLIGHT RESTRICTIONS 4 2 General 4 2 Flight Rules 4 2 Flight Load Factors 4 2 ENGINE LIMITATIONS 4 3 AIRSPEED LIMITATIONS 4 4 Airspeed Cor...

Page 12: ...Cruise Performance 6 000 ft MSL 4 12 Cruise Performance 8 000 ft MSL 4 13 Cruise Performance 10 000 ft MSL 4 14 Cross Country Glider Towing 4 15 Approach and Landing Speeds 4 16 Landing Performance Data 4 17 WEIGHT AND BALANCE 4 18 Weight Limitations 4 18 Centre of Gravity Limitations 4 18 Calculation of Operational Weight and Balance 4 19 ...

Page 13: ...t s Guide EDM 930 Engine Data Management System ANNEX B Pilot s Guide Garmin SL40 VHF Radio ANNEX C Pilot s Guide Garmin AERA 500 VFR GPS ANNEX D Pilot s Guide Garmin GMA340 Audio Panel ANNEX E Pilot s Guide Garmin GTX327 Transponder ...

Page 14: ... Atlee Dodge Dual Calliper Brakes STC No SA02331AK Flight Manual Supplement I Heavy Duty Engine Mount STC No SA01573NY Installation Instructions J Sportsman STOL Kit STC No SA4303WE Installation Instructions K ART Wing Extensions STC No SA00276NY Flight Manual Supplement L MicroAir Vortex Generators STC No SA00834SE Flight Manual Supplement M Rosen Sun Visors STC No SA00871SE Installation Instruct...

Page 15: ...er Towing Package STC O LSA12 028D Flight Manual Supplement Y Pacific Region Maintenance Policy Manual Chapter 10 Maintenance Standards Z RCA Ops Pac Orders and Instructions Volume 4 Aircraft Maintenance AA C182 C FCGS Evaluation Plan Results RCA Ops Pac BB C182 C FTUG Evaluation Plan Results RCA Ops Pac CC Aero Twin MLG Gravel Deflectors STC SA02312AK Installation Instructions ...

Page 16: ...or pressure and temperature variations Demonstrated Crosswind Maximum crosswind for which adequate control on takeoff and landing was demonstrated during certification tests EGT Exhaust Gas Temperature the measured temperature of the exhaust gas normally at the cylinder exhaust manifold FACU Fuel Air Control Unit GPH Gallons Per Hour fuel consumption rate Gross Weight The loaded weight of the airc...

Page 17: ...nifold Pressure alternate abbreviation for MAP MSL Mean Sea Level OAT Outside Air Temperature free static air temperature PA Pressure Altitude the altitude displayed when the altimeter subscale is set to 29 92 in Hg RAD Remote Auxiliary Display a secondary display of the EDM930 engine monitoring system RPM Revolutions Per Minute rotational speed of the propeller SHP Shaft Horsepower the power deli...

Page 18: ...ld not be exceeded except in smooth air VA Manoeuvring Speed the maximum speed at which you may use full abrupt control deflection VFE Maximum Speed with Flaps Extended maximum permissible speed at the prescribed flap position VS Stalling Speed Flaps Up the airspeed at which the airplane stalls or minimum controllable airspeed VSO Stalling Speed in Landing Configuration the stalling airspeed in th...

Page 19: ...Technology Inc SA00276NY Vortex Generator Kit Micro AeroDynamics SA00834SE Heavy Duty Nose Landing Gear Airglas Inc SA02069AK Sun Visors Rosen Sunvisor Systems SA00871SE Brackett Air Filter Brackett SA71GL EDM 930 Engine Management System JP Instrument SA01435SE Flap Roller Kit McFarlane Aviation SA01074WI RMD HID Pulse Lights for Modified Wingtip RMD SA4337NM Bubble Door Windows Great Lakes Aero ...

Page 20: ...g Weight 2950 lbs Basic Empty Weight Approximately 1850 lbs Useful Load Approximately 1250 lbs Figure 1 2 Dimensions and Weight Fuel Tank Capacities Total Fuel Useable Fuel USG Litres Pounds USG Litres Pounds Left Tank 40 151 240 37 5 142 225 Right Tank 40 151 240 37 5 142 225 TOTAL 80 303 480 75 284 450 Figure 1 3 Fuel Tank Capacities CAUTION Only 100LL AVGAS shall be used Oil Capacity US Quarts ...

Page 21: ...s which includes forgings at the base of the rear door posts for attachment of the main landing gear c a bulkhead incorporating the front door posts which includes fittings for attachment of the wing struts d four engine mount stringers connecting the forward door posts bulkhead to the engine firewall and e a stainless steel engine firewall which provides a fire barrier between the engine compartm...

Page 22: ...rut which enhances bending strength stiffness and d conventional ailerons and single slotted flaps attached to the training edge of the wings 6 The wings have been extensively modified to enhance performance at the reduced airspeeds associated with glider towing operations These modifications reduce stalling speed increase lift coefficient improve slow speed aileron response and reduce takeoff rol...

Page 23: ...er trim which adjusts the neutral position of the rudder c vortex generators applied to the lower trailing edge of the horizontal stabilizer to enhance low speed pitch control d vortex generators applied to the trailing edge of the vertical stabilizer to enhance low speed directional control and e horn style balance weights on both the rudder and elevator Figure 1 7 Tail Vortex Generators ...

Page 24: ... and never hang headsets from the V brace CAUTION To avoid scratching and or crazing the windshield and windows use only cleaning products certified for use on acrylic plastic Apply lightly with a micro fibre or flannel cloth Never use paper towels 9 The forward windshield is equipped with a fully articulating glare shield at both the pilot and co pilot positions to enhance pilot visibility when c...

Page 25: ...quipped with a a recessed exterior door handle to open the door from the outside a an interior door handle used to pull the door closed from the inside b an interior latch handle to lock and unlock the door from the inside and c a bubble window Figure 1 9 Door Exterior and Interior ...

Page 26: ...d with a paddle style latch handle shown below Figure 1 11 Paddle Latch Handle CAUTION Both cabin doors must be locked prior to takeoff Doors shall be pulled closed only using the D shaped door handle Latch handles shall not be used for pulling doors closed as they are not designed to withstand the required force The latch handle shall not be moved until after the door has been pulled closed Doing...

Page 27: ...ner of the seat If additional upward adjustment is required for proper visibility over the nose an approved and properly secured seat cushion may be used c the seat back angle is adjusted with the small crank handle on the outboard lower corner of the seat The seat bottom angle changes with the back angle d both seat backs may be folded forward for easier access to the rear cabin and e a safety st...

Page 28: ...artment Refer to Part 4 Figure 4 19 for specific weight limits in the baggage compartment The baggage compartment is accessible either over the rear seat or through an external door on the left hand side of the fuselage The baggage door is fitted with a locking latch mechanism WARNING Ensure that all items carried in the baggage compartment are properly secured prior to flight CAUTION To prevent i...

Page 29: ...ither front seat a control yokes provide aileron and elevator control through a combination of push pull rods cables pulleys and bell cranks and Figure 1 13 Aileron Controls Figure 1 14 Elevator Controls b rudder pedals provide both rudder and nose wheel steering control and incorporate conventional toe brakes Figure 1 15 Rudder Controls ...

Page 30: ...l and insert the rod into the aligned holes Figure 1 16 Control Locks Trim 19 Elevator and rudder trim tabs are cable actuated from control wheels located on the centre console These control wheels are labelled NOSE UP NOSE DOWN NOSE LEFT and NOSE RIGHT A tab position indicator is adjacent to each wheel to indicate the neutral centred trim position Figure 1 17 Trim Controls CAUTION Once at the tra...

Page 31: ...right to clear the detent and then position as required A scale and pointer to the left of the switch lever indicates flap travel in degrees The wing flap system circuit is protected by a 15 amp circuit breaker on the left instrument sub panel Figure 1 18 Flap Controls Figure 1 19 Flap Selector NOTE Flaps are limited to 35 degrees of travel in compliance with STC SA00152WI Continental IO520D Engin...

Page 32: ...n the nose wheel through an arc of 11º of centre By applying brake the degree of turn may be increased to a maximum of 29º of centre Through the use of brakes the aircraft can be pivoted about the outer wing strut fitting achieving a turn radius of approximately 27 feet Figure 1 20 Side View CAUTION The extended nose fork assembly increases the potential for wheel barrowing compared to a standard ...

Page 33: ...e and rotating the handle to a vertical orientation to lock in position and b the parking brake is released by pulling slightly on the handle to relieve tension rotating the handle to the horizontal position and then pushing the handle fully in Figure 1 21 Parking Brake Handle CAUTION Reliance on the parking brake when the aircraft is unattended could result in aircraft movement in the event that ...

Page 34: ...n EDM 930 engine data management system in the main RH panel d a lower sub panel that incorporates engine controls electrical switches controls and circuit breakers e a bin for storing publications maps charts on the far right hand side of the main panel and f a glove compartment for storing aircraft documents in lower right hand sub panel Figure 1 22 Instrument Panel ...

Page 35: ...0 RPM and b Maximum Continuous Power 285 BHP at 2700 RPM Figure 1 23 IO 520 Engine Propeller 27 The aircraft is equipped with a Hartzell PHC L3YF 1RF F7691 three blade metal constant speed propeller Propeller pitch is controlled by an engine mounted propeller governor which uses engine oil as a hydraulic medium The propeller has a low fine pitch setting of 11 1 degrees and a high coarse pitch sett...

Page 36: ...and excess fuel from the engine driven pump and the FACU are returned to the RH fuel tank by a vapour return line d air is delivered to the cylinders through intake manifold tubes and metered fuel is delivered by the FACU to the fuel manifold on the top of the engine e the fuel manifold evenly distributes the fuel to an air bleed type injector nozzle in the intake valve of each cylinder and f a pr...

Page 37: ... angles are established using mechanical stops b the governor uses an internal oil pump driven by the engine This pump increases engine oil pressure for supply to the propeller as a control medium c propeller blade angle change is accomplished via a hydraulic piston cylinder mounted on the forward end of the propeller hub One end of the cylinder holds a sealed air charge the other side reacts to c...

Page 38: ...ogressively leans the mixture until the IDLE CUTOFF position is reached 35 The Mixture Control incorporates a vernier control feature which provides slow and or fine adjustments Rotate the control clockwise to enrich the mixture and vice versa Rapid or large adjustments can be made by depressing the button on the end of the control knob and reposition control as required Detailed instructions on c...

Page 39: ...t II These are established based on the following considerations a Takeoff during takeoff and initial climb aircraft performance is optimized with the blade angles at fine pitch high RPM b Climb after takeoff the propeller speed can be decreased for noise abatement reasons c Cruise during cruise performance is optimized by selecting coarser pitch and thus reducing propeller RPM and d Landing durin...

Page 40: ...ine a an oil filler cap is located on the top of the crankcase accessed through a door in the front of the upper engine cowling and Figure 1 26 Oil Filler Cap Location b an oil dip stick is located on the left side of the crankcase accessed through a door in the left side of the upper engine cowling Figure 1 27 Oil Dip Stick Location ...

Page 41: ...ystem capacity is 12 US quarts 11 4 litres and minimum operating level is 9 US quarts 8 5 litres For normal operations maintain the oil level between 10 and 11 quarts and top up if the level drops below 10 quarts CAUTION Failure to ensure the dipstick locking clip is engaged may result in the dipstick coming loose with a significant loss of engine oil through the open tube end Prior to adding oil ...

Page 42: ...er is engaged a properly functioning adapter will immediately begin turning the propeller A starter adapter that slips slowly or intermittently turns the propeller indicates a serious malfunction which immediately renders the aircraft unserviceable until assessed by an RCA Ops Pac AME These conditions can result in metal flakes entering the engine oil system They are not indicators of a minor prog...

Page 43: ...e throttle a should the primary air intake be blocked by snow impact ice or other contaminants the alternate air control should be selected FULL ON by pulling it all the way OUT This will open the alternate air valve and draw unfiltered air from inside the engine compartment and b at all other times the alternate air should be OFF Figure 1 30 Alternate Air Control CAUTION Other than when required ...

Page 44: ... controlled by cowl flaps mechanically operated by the Cowl Flap Lever on the right side of the centre control pedestal The lever is raised to open the cowl flaps for takeoff and high power operations and lowered to close the cowl flaps for cruise and descent Intermediate positions can be used to maintain optimum engine operating temperatures The lever must be moved to the right to clear detents b...

Page 45: ...dder style vented fuel tanks b vent system check valve c fuel quantity indicators for each tank d rotary fuel selector valve e fuel header tank f fuel shutoff valve g fuel strainer h electric auxiliary fuel pump i engine driven fuel pump j fuel injection system and k vapour return line Figure 1 32 Fuel System Components ...

Page 46: ...fore it reaches the fuel injection system The fuel strainer drain valve is adjacent to the oil dip stick and is accessed through a door on the left side of the engine cowling During the pre flight inspection the strainer should be opened to drain for approximate 4 seconds to clear any water or sediment Figure 1 34 Oil Dip Stick and Fuel Strainer Drain Fuel Vent System 52 The left tank is fitted wi...

Page 47: ...tored fuel flow the EDM 930 calculates the useable fuel remaining This system has been proven to be accurate to within 5 if the starting fuel quantity is entered correctly Rotary Fuel Selector Valve 55 Fuel is fed from the wing fuel tanks by gravity through a three position rotary selector valve and strainer Fuel is then collected in the header tank from where it is fed through the firewall to the...

Page 48: ...g through the fuel selector valve and provides a steady uninterrupted flow of fuel to the fuel injection system on the engine Figure 1 36 Header Tank 57 A fuel drain for the header tank is installed in the aircraft belly aft of the firewall just behind the nose gear scissors This allows water and contaminants to be drained from the header tank during the pre flight inspection Figure 1 37 Header Ta...

Page 49: ...e control is located on the centre pedestal When the control is a pushed FULLY IN the valve is OPEN and permits the normal flow of fuel and b pulled FULLY OUT the valve is CLOSED and shuts off all fuel flow to the engine Figure 1 38 Fuel Shutoff Valve NOTE The fuel shutoff valve is only used during a critical emergency The NORMAL position for the valve control is OPEN or pushed FULLY IN ...

Page 50: ...educed preventing an excessively rich mixture when the engine is operated at low power settings a 60 The pump is controlled by a switch located on the left hand side of the pilot s lower sub panel immediately below the Master Switch 61 The auxiliary fuel pump switch is a three position switch operated as follows a Switch Up PRIME spring loaded back to OFF b Switch Centred OFF c Switch Down ON Figu...

Page 51: ...nstrument indications including 1 propeller RPM 2 manifold pressure 3 fuel pressure 4 oil temperature 5 oil pressure 6 cylinder head temperature 7 exhaust gas temperature and 8 voltmeter ammeter b fuel tank quantity indication fuel flow and fuel totalizer functions c EGT and CHT bar graph display of individual cylinders d Percentage of maximum rated horsepower HP e LeanFind function for precise le...

Page 52: ...Identifier Notes Propeller RPM RPM Manifold Pressure MANIFOLD PRESSURE Exhaust Gas Temperature EGT Cylinder Head Temperature CHT Oil Temperature OIL T Oil Pressure OIL P Fuel Pressure FUEL P Fuel Remaining FUEL REM Calculated parameter Ammeter AMPS Voltmeter VOLTS Fuel Flow Rate FUEL FLW Fuel Quantity FUEL QTY Outside Air Temperature OAT Percent Brake Horsepower HP Figure 1 41 Display Parameters ...

Page 53: ...ime to Empty 02 45 H M Rate of Shock Cooling 30 CLD Max Difference between EGTs 80 DIF Figure 1 42 Scanner Display Parameters Remote Auxiliary Display RAD 65 A Remote Auxiliary Display RAD using LEDs is mounted on the upper left hand side of the instrument panel During normal operations the RAD will display a secondary indication of Propeller RPM and Manifold Pressure When an alert is triggered th...

Page 54: ... These are Alerts that indicate important operational information not related to a published engine or system limitation When a measurement falls outside a programmed caution point the main display will blink ALERT in amber and the measurement will appear in the scanner display Alert Display Alert Description Notes TK LOW Fuel Tank Low Quantity MIN Low Fuel Endurance Remaining REM Low Fuel Quantit...

Page 55: ...lowing a during towing operations during post release descent increase power and or reduce airspeed if safe and practical to do so b during routine descents increase power and or reduce airspeed if safe and practical to do so c during practice forced landings smoothly apply mid range power for 2 3 seconds every 1000 feet to minimize shock cooling effects and d during circuits approach and landing ...

Page 56: ...g electronic circuits and components and the other side serving general electrical system components d electrical circuits and equipment are protected by push to reset type circuit breakers e a split rocker style Master Switch is used to connect the alternator and the battery to the electrical system f a Radio Master Switch is used to isolate the electronic circuits from transient voltage spikes d...

Page 57: ...1 39 Figure 1 47 Electrical Schematic ...

Page 58: ...round The ALT side of the switch when selected OFF removes the alternator from the system CAUTION Continued operation with the alternator OFF will eventually reduce battery power resulting in loss of power to the alternator field precluding a restart CAUTION Do not turn off the alternator in flight except in an emergency Other Electrical Switches and Controls 74 All electrical switches and control...

Page 59: ...ertical stabilizer High intensity LED anti collision pulse lights are mounted in the wing leading edges at the tips and dual high intensity LED taxi landing lights are mounted in the lower nose cowling All are controlled by switches on the pilot s lower instrument panel High Intensity LED Taxi Landing Lights High Intensity LED Pulse Light Navigation Light Strobe Light High Intensity LED Strobe Lig...

Page 60: ...PPM f B44 both lights flash at 44 PPM g A88 lights alternate at 88 PPM preferred daytime setting h A120 lights alternate at 120 PPM Interior Lighting 77 Flight instruments are continuously illuminated by adjacent post lights controlled by a dimmer switch on the lower instrument panel The avionics and EDM 930 both have self adjusting internal lighting Adjustable LED map cabin lights with red filter...

Page 61: ...1 43 HEATING AND VENTILATION SYSTEM General 79 The heating and ventilation system is depicted in the schematic below Figure 1 51 Heating and Ventilation Schematic ...

Page 62: ...n Figure 1 52 Heat and Air Controls 81 Windshield defrost air is ducted from the cabin heat manifold to an outlet on the pilot s side of the glare shield and is controlled by a rotary knob labelled DEFROST on the right hand subpanel NOTE The CABIN HEAT must be ON to get warm defrost air Ventilation 82 Ventilating cool air is supplied through the heating manifold by pulling out the CABIN AIR knob o...

Page 63: ...c pressure to the altimeter ASI and VSI Figure 1 53 OAT Probe and Pitot Tube 85 Alternate Static Air An alternate static air valve is located adjacent to the parking brake handle Actuation of this valve pull out supplies static pressure from the cabin and should be selected when erroneous instrument reading are suspected due to icing clogging of the static ports or water in the system Figure 1 54 ...

Page 64: ...s the suction currently available A suction range of 4 5 to 5 5 in Hg is desired for reliable operation of the attitude indicator and directional indicator Figure 1 55 Vacuum System Stall Warning System 87 A vane type stall warning unit is located in the left wing leading edge which electrically activates an audible stall warning horn located under the instrument panel The horn is not connected to...

Page 65: ... Range limitation markings are in satisfaction of STC SA00152WI ref D and are as follows 1 white arc 47 110 mph 2 green arc 55 165 mph 3 yellow arc 165 206 mph 4 red line 206 mph WARNING A placard located immediately above ASI limits VNE to 180 MPH This limitation is associated with the wing extensions installed under STC SA00276NY b Attitude Indicator AI Vacuum operated with an adjustable split b...

Page 66: ...cation of slip or skid L and R turn indices indicate a standard rate one turn 3º sec e Directional Indicator DI Vacuum operated with rotating compass card f Vertical Speed Indicator VSI Instrument is actuated by static pressure changes and depicts rate of climb or descent in feet per min g Magnetic Compass A rotating card magnetic compass is mounted to the centre of the front windscreen Figure 1 5...

Page 67: ...0 VFR GPS d Garmin GTX 327 Transponder and e Artex ME 406 MHz ELT mounted in the aft baggage compartment Audio Panel GPS VHF COMM Transponder Figure 1 58 Avionics Suite 90 All avionics except the ELT are controlled through the RADIO MASTER switch on the left subpanel To prevent voltage spikes from damaging the avionics the RADIO MASTER switch must be selected OFF prior to engine start and prior to...

Page 68: ...rating instructions Figure 1 59 Audio Panel 92 Normal operation is achieved by selecting COM 1 MIC and setting pilot co pilot volumes squelch levels as required All other buttons can be deselected LEDs OFF A fail safe circuit connects the pilot s headset and microphone directly to the radio if the audio panel fails or is turned off The LED lighting intensity is controlled by the photocell on the p...

Page 69: ...pressure The screen is cleaned using a soft clean lint free cloth with water isopropyl alcohol or eyeglass cleaner b navigational database including data for airports aerodromes and navigation aids and controlled restricted airspace boundaries c point to point navigation d route navigation e HSI navigation display and f color map navigational displays capable of 1 topographical colour coding 2 haz...

Page 70: ...rated into the Pilots Checklist Emergency Procedures and Operating Data Refer to Annex C for more detailed operating instructions WARNING This GPS is for VFR navigation only CAUTION The GPS database is only updated periodically Information on airspace boundaries and aerodrome facilities may not be accurate Such information shall be obtained from current VFR charts and the Canada Flight Supplement ...

Page 71: ... dual concentric knobs on the right side of the SL40 are used to select frequencies or to view the features available within a function c Flip Flop Button Press the Flip Flop button to switch between the active left most and standby rightmost frequency on the display Switching between frequencies is disabled when transmitting d EC Button Press the EC button to load the Emergency Channel 121 500 MH...

Page 72: ... d ALT selects Mode A and C interrogation replies include altitude output from encoding altimeter ALT appears in the display e Code Selection Keys 0 7 provide 4096 identification codes Pressing any one begins the code selection process and the new code is active as soon as the fourth digit is entered f IDENT activates special position identifier SPI pulse for 18 sec IDENT will appear in the displa...

Page 73: ...urst contains aircraft identification data programmed into the beacon and provides location accuracy of approximately 3 km 100 The ELT is activated either automatically during a crash a change in velocity or deceleration greater than 4 5 fps 0 5 or manually by selecting the instrument panel remote switch to ON Once activated the ELT may be switched off by selecting either the remote switch or the ...

Page 74: ...tow rope tension or angle 104 The release mechanism is actuated from the cockpit via a conduit style cable The release handle is a red D Ring mounted centrally on the instrument panel immediately below the avionics stack Figure 1 65 Tost Release Handle Tow Mirrors 105 A ground adjustable mirror is mounted at the mid point of each strut These mirrors allow the pilot to observe the glider during nor...

Page 75: ...loor mounted between the front seats Figure 1 66 Fire Extinguisher First Aid Kit 108 A first aid kit is mounted below the rear seat Carbon Monoxide Detector 109 An adhesive card type Carbon Monoxide CO detector is mounted on the instrument panel The spot turns gray black in the presence of CO ...

Page 76: ...1 58 This page intentionally left blank ...

Page 77: ... of the horizontal stabilizer to raise the nose wheel off the ground WARNING Prior to moving the propeller or moving to a position inside the propeller plane of rotation visually confirm that the Ignition Switch is in the OFF position and the keys are removed CAUTION When manually moving the propeller blades is necessary such as repositioning to use a tow bar the propeller shall only be moved in i...

Page 78: ... 4 Fuel Replenishment When replenishing fuel ensure that the aircraft is properly grounded and that the correct type of fuel is available before commencing the pumping of fuel A ladder is required for refuelling and a light weight folding ladder is carried in the baggage compartment for use during deployed operations NOTE To ensure maximum fuel capacity during refuelling place the fuel selector to...

Page 79: ...10 Elevator and rudder trim Confirm functional Verification of full travel is not required 11 Cowl flaps Set to full open 12 Fire Extinguisher Secure and charged 13 Pubs documents maps Present Pubs and navigational materials must be current 14 Battery Master Select ON Combine steps 16 through 15 Flaps Set Full Flaps 16 Interior exterior lights Confirm functioning a Interior and taxi landing light ...

Page 80: ...cap is on and secure Min oil quantity for flight 9 US quarts indicated on the dipstick Add oil if quantity is less than 10 US quarts Figure 2 1 Pre External Inspection External Inspection 6 Perform the external pre flight inspection by starting at the left main landing gear and proceeding clockwise around the aircraft as follows EXTERNAL INSPECTION ACTION CHECK NOTES LEFT MAIN GEAR 1 Brake line Co...

Page 81: ...heck inside the cowl flaps 12 Cowling right side Secure 13 Right static port Clear RIGHT MAIN GEAR 14 Brake line Condition Check for security wear chafing or leaking 15 Brake rotor and pads Condition and wear Check for unusual wear 16 Tire Inflation and wear RIGHT WING 17 Strut and tow mirror Condition and security 18 Leading edge vortex generators fresh air vents Condition Aircraft is U S if more...

Page 82: ...ection 29 Tail cone Condition 30 Tow hook Condition and security TOST release mechanism for function FUSELAGE LEFT REAR 31 Fuselage skin Condition 32 Belly Check for oil 33 Battery vent and drain Condition and clear 34 Baggage compartment door Closed latched and locked Door must be locked to ensure it cannot be opened by slipstream LEFT WING 35 Fuel filler cap Secure and in line 36 Aileron and fla...

Page 83: ...TION CHECK NOTES 1 Engine Fuel and Oil Leaks If checking engine oil shortly after within 1 hr shutdown oil level may appear low as oil has not fully drained into the sump Do not over fill 2 Oil Check Qty Cap Secure Doors Secure 3 Fuel Check Qty Caps Secure and In Line 4 Main Wheels Check Condition 5 Nose Wheel Assembly Check Condition 6 If Night Flying Check all lights Figure 2 3 Between Flight In...

Page 84: ...imeter Set Set to altimeter setting or field elevation Figure 2 4 Pre Start Check START CLEARANCE 9 For engine starts conducted at military aerodromes pilots must obtain start clearance from ATC START CLEARANCE If Required ACTION CHECK NOTES 1 Master Switch On 2 Radio Master Switch On 3 Radio On Set Set to ground frequency 4 Start Clearance Obtain Provide ATC with Tug number location fuel on board...

Page 85: ...are on 2 Anti collision lights On 3 Brakes Apply Do not rely on parking brake 4 Prop area All clear 5 Throttle SET 1 4 INCH 6 Propeller FULL FINE 7 Mixture FULL RICH 8 Aux Fuel Pump PRIME for approximately 3 seconds then promptly OFF If engine is COLD more prime may be required If engine is WARM little or no prime is required If engine is HOT and will not start use HOT START procedure 9 Starter En...

Page 86: ...onounced 15 30 minutes after engine shutdown 13 If significant fuel vapour is present in the fuel injection system it can be advantageous to pressurize the fuel system for a short period of time to circulate cooler fuel into the fuel system and force any fuel vapour back to the RH fuel tank through the vapour return line This process is accomplished by setting the throttle FULL OPEN setting the mi...

Page 87: ...1000 rpm Engine will start at approximately 1400 RPM Smoothly retard throttle to set approximately 1000 RPM 13 Oil pressure Normal Indication If no indication within 30 sec shutdown immediately Figure 2 7 Hot Engine Start FLOODED ENGINE START 14 Should it become evident that the engine is flooded the engine start should be conducted using the Flooded Engine Start procedure detailed below FLOODED E...

Page 88: ...r does not immediately turn upon engaging the starter the aircraft is U S 10 Throttle Reduce to 1000 rpm The engine will start at very high RPM Smoothly retard throttle to set approximately 1000 RPM 11 Mixture Slowly advance to FULL RICH 12 Oil pressure Normal Indication If no indication within 30 sec shutdown immediately Figure 2 8 Flooded Engine Start CAUTION There is an elevated risk of a fire ...

Page 89: ...ct Select UP or as required for takeoff 5 Audio Panel Set 6 Radio On and Set 7 GPS Confirm Initializing 8 Transponder Standby 9 Landing Nav Lights ON for night operations Figure 2 9 Pre Taxi Taxi 16 While taxiing perform the following actions TAXI ACTION CHECK NOTES 1 Brakes Ensure functional 2 Nose wheel steering Ensure functional 3 Flight instruments Ensure functional In turns ensure that turn c...

Page 90: ... have ground crew verify clearances or shut down and manoeuvre by hand c avoid taxiing with flaps down especially in high winds d avoid excessive use of brake during taxiing Use power settings that do not require continuous use of brake to control speed Note that when taxiing in very strong crosswinds some brake may be required to maintain directional control e when taxing over soft rough surfaces...

Page 91: ... and 200º CHT 5 Throttle Set 1700 rpm 6 EDM 930 Select NORMALIZE Hold LF button for 3 seconds or until NRM appears on display 7 Magnetos Select LEFT BOTH RIGHT BOTH a Check EGT rise all cylinders b Check normal RPM drop CAUTION RPM drop 150 or an RPM differential 50 may indicate plug fouling or a faulty magneto NOTE Clear minor plug fouling as follows a throttle 2200 RPM b mixture lean until RPM p...

Page 92: ... not exceeded 11 Suction Confirm 4 5 5 5 in HG 12 Alternator Confirm charging 13 Idle Check Confirm IDLE at 650 750 RPM 14 Throttle Set 1000 RPM 15 Mixture Function Lean gradually until engine falters then IMMEDIATELY reset to full rich to prevent engine shutdown Very little movement of the mixture control is required Figure 2 12 Run up ...

Page 93: ...llision and for night ops 9 Pitot heat OFF Takeoff shall not be attempted in conditions requiring pitot heat 10 Pulse Lights ON for daytime ops Optimum setting for daytime visibility is A88 11 Gyro instruments Set 12 Altimeter Set 13 Radio Set as required 14 GPS Set as required CAUTION Do not enter data into GPS while taxiing or during critical regimes of flight 15 Transponder Code Set ALT ON 16 A...

Page 94: ...ff roll d ensure full power is achieved by confirming approximately 2850 RPM and approximately 28 MAP and that EGTs increase on all six cylinders e maintain directional control with nose wheel steering and rudder f apply gentle back pressure on the yoke so that the aircraft becomes airborne at approximately 60 mph g adjust yoke position to set required climb attitude and h complete the post takeof...

Page 95: ...ble and accelerating to safe climb speed in ground effect A soft rough field takeoff is accomplished as follows a while taxiing on soft rough surfaces hold the yoke fully aft to keep weight off the nose gear to the greatest extent possible b set trim for takeoff and set flaps to 10º NOTE The C182 POH specifies 20º of flap for a soft field takeoff However the aerodynamic enhancements on this aircra...

Page 96: ...roll progressively reducing aileron deflection as the aircraft accelerates c allow the aircraft to accelerate to a slightly higher speed before rotating to ensure a positive lift off With proper aileron position for the crosswind the downwind wheel should lift off slightly before the upwind wheel and d once airborne make a coordinated turn into wind to correct for drift Post Takeoff 24 The Post Ta...

Page 97: ...irspeed for Max Rate Climb decreases by approximately 2 MPH every 5 000 feet to 86 mph 10 000 ft ASL Max Angle Climb 20º flap 2700 FT 63 Used for obstacle clearance takeoffs and climbs Max Angle Climb no flap 2700 FT 73 May be used for terrain clearance climbs during cruise phase when flaps have not been selected Normal Climb 2700 FT 110 Standard default climb profile The normal climb allows for t...

Page 98: ...tween 55 and 75 BHP Continuous cruise power settings shall not exceed 75 BHP Select a cruising speed appropriate to the in flight conditions i e turbulence and desired range and economy Refer to the Cruise Performance Charts in Part 4 for detailed cruise settings or use one of the following generic settings 2 000 MSL RPM MAP Typical Performance at 2 000 ft MSL IAS MPH TAS KTS Fuel Flow GPH Range1 ...

Page 99: ...e and Prop Refer to performance data chart for cruise power settings Trim As required Cowl flaps CLOSE Maintain appropriate CHTs and minimize cooling drag Mixture Lean to 50 ºF Rich of Peak Refer to EDM 930 manual for LeanFind procedure Cowl flaps As required to manage CHT After leaning cowl flaps may be opened as required to maintain desired CHT Figure 2 17 Level Off Cruise Check ...

Page 100: ...gn Due to the aerodynamic modifications to the aircraft aileron effectiveness is maintained well into the stall and the aircraft does not exhibit noteworthy wing drop tendencies The Stall Speed Chart is provided in Part IV of this manual 31 Stall recoveries are emergencies demanding prompt action and a minimum loss of altitude While just lowering the nose will recover the aircraft from a stall the...

Page 101: ...and establish a climb to a safe altitude NOTE Spin recoveries are a critical emergency procedure and shall be committed to memory Spiral Dives 35 Spiral dives are steep descending turns characterized by rapidly increasing airspeed and rate of descent in a spin the airspeed and rate of descent remain relatively low and constant Left uncorrected a spiral dive usually leads to structural failure Atte...

Page 102: ...f Doors SECURE O Objects Secure loose objects T Traffic Terrain Clear Check for conflicting traffic and ensure clear of obstructions Figure 2 18 ASCOT Check PRE DESCENT 38 Prior to commencing a descent perform descent check as follows PRE DESCENT ACTION CHECK NOTES 1 Mixture Enrich as required May be done progressively in extended descents to ensure continued smooth running of the engine 2 Cowl fl...

Page 103: ... to prevent an excessive nose up attitude in the circuit and c if desired higher throttle settings higher airspeeds may be used but will require careful circuit planning to permit deceleration to Vfe without creating an unusually high fast final approach 40 Perform the pre landing check as follows PRE LANDING ACTION CHECK NOTES 1 Mixture Full RICH Depending on density altitude leaning may be requi...

Page 104: ...re accomplished by flaring the aircraft to a slightly nose high attitude and progressively easing back on the control column to delay touchdown so as to accomplish a two point landing on the main wheels followed by gently lowering the nose wheel 43 The C182 is a slightly nose heavy aircraft and the aircraft operated in the ACGP are also equipped with an extended nose fork and oversize tire which r...

Page 105: ...ances exist A normal landing is accomplished as follows a establish a final approach with 20º flaps and IAS of 75 85 MPH If desired to achieve a steeper approach angle the approach may be flown with 35º flaps and IAS of 70 80 MPH b as the aircraft is flared for landing smoothly reduce power to idle A small amount of power may be retained to assist in achieving a nose up attitude at touchdown but w...

Page 106: ... of 70 MPH b conduct the final approach with an aim point just prior to the threshold so as to touch down close to the threshold of the usable landing surface c as the aircraft is flared for landing smoothly reduce power to idle d smoothly increase backpressure on the yoke to hold off the landing establish a nose high landing attitude e touch down on the main landing gear f after touchdown hold th...

Page 107: ...he yoke aft slowly reduce power to idle and raise flaps and f use only minimum required braking If safe to do so delay the use of brakes until ground speed is as slow as possible CAUTION Landing flat or prematurely lowering the nose after landing on a soft or rough surface may result in damage to the nose landing gear or supporting structure Crosswind Landing 48 When landing in a strong crosswind ...

Page 108: ...and a positive rate of climb has been established slowly retract the flaps WARNING Premature retraction of the last 20º of flaps can result in the aircraft settling and a loss of altitude CONTINUOUS CIRCUIT OPERATIONS Stop and Go Landings 51 When conducting multiple circuits use the Stop and Go check as follows STOP AND GO ACTION CHECK NOTES 1 Prop FULL FINE When extended ground wait is anticipate...

Page 109: ...emaining when the go is initiated CAUTION Performing continuous circuits on runways less than 3000 requires a high level of landing accuracy Pilots must be prepared to abort a planned Stop Go or Touch Go landing by either over shooting or fully stopping and taxiing back to the normal take off point POST LANDING CHECK 53 Upon termination of a flight and when clear of the runway complete the post la...

Page 110: ...inder of shutdown checklist 6 Magnetos OFF Remove keys from ignition 7 All switches OFF 8 Master switch OFF 9 Fuel Selector Either Left or Right To prevent cross feeding during fuelling or when parked on a sloped surface 10 Control lock Install 11 Secure Aircraft Keys Secure as req d Cowl Flaps Open Fresh Air Vent Close Chocks In Tie downs Secure Plugs Install Covers Install as req d CAUTION Durin...

Page 111: ...or high power settings to prevent engine overheating and e Descent and Landing CLOSED to minimize shock cooling of engine When conducting continuous circuits the cowl flaps may be left OPEN Mixture Control 56 To prevent fouled plugs rough running and or engine damage correct leaning procedures must be followed during all phases of flight Proceed as follows a Ground Handling full rich unless operat...

Page 112: ...onably foreseeable contingencies such as airport departure and arrival procedures en route altitude changes en route course variations for weather routing changes directed by ATC etc e incorporate an appropriate VFR fuel reserve Canadian Aviation Regulations require that pre flight planning allows for a minimum fuel reserve of 1 30 minutes for daytime operations and 2 45 minutes for night operatio...

Page 113: ...mption rate d EDM 930 Low Fuel Alerting The EDM 930 will provide fuel alerts 1 Low Fuel Flow Low fuel flow rate will trigger an alert as low fuel flow in flight may indicate imminent engine failure With the throttle closed on the ground a low fuel flow alert may be triggered 2 Low Fuel Quantity Fuel Tanks If the fuel quantity in either tank drops below 9 USG a low fuel alert for the specific tank ...

Page 114: ...n of the TOST release mechanism and ensure the mirrors are properly adjusted Perform a tow rope release check prior to the first tow Normal pre takeoff checks are performed prior to the first tow Continuous Towing Operation 62 The Stop and Go Check is performed prior to each subsequent tow STOP AND GO ACTION CHECK NOTES 1 Prop FULL FINE 2 Mixture FULL RICH When extended ground wait is anticipated ...

Page 115: ...ck pressure to maintain a slightly nose high attitude f due to the high angle of attack the aircraft will become airborne in ground effect at between 50 60 MPH As the aircraft becomes airborne smoothly lower the pitch attitude so that the aircraft accelerates in ground effect g smoothly adjust pitch attitude to establish a 70 MPH climb Once safety established in a stable climb reduce propeller RPM...

Page 116: ...thly maintaining rudder co ordination throughout and d plan your pattern to arrive at the designated release point at the same time you reach release altitude Glider Release 65 Glider release is performed using the following procedure a approaching the planned release altitude gradually reduce MAP to approximately 16 while maintaining 70 MPH This will result in the tow aircraft levelling off or ma...

Page 117: ... flaps to 0 c ensure the cowl flaps are closed d reduce propeller speed to 2300 RPM for noise abatement e increase IAS to approximately 130 MPH f initial cooling rate should be approximately 40 to 60 minute g monitor the cooling rate and maintain at less than 60 minute h as the cooling rate decreases to about 40 minute reduce power to 18 MAP i cooling rate will increase and then begin to decrease ...

Page 118: ... places unusual strain on the flap system Using flaps at the higher end of the certified speed range has been associated with stress cracking in the flap track brackets To reduce the risk of stress cracking pilots should not normally extend the first 10 of flaps above 110 MPH and any further flaps above 90 MPH Flaps may be lowered at speeds up to the certified limits on an exceptional basis or whe...

Page 119: ...n not to over speed the glider during the cruise phase of cross country towing operations 70 To provide an acceptable pitch attitude and to optimize aircraft performance and control during the cruise phase of the cross country tow the aircraft should be configured as follows a When towing in smooth atmospheric conditions the aircraft should normally be configured as follows 1 flaps set to 10 degre...

Page 120: ...rass surfaces Both take off and landing should be flown with a nose high attitude on grass surfaces as unseen heavy wet grass or deep puddles could cause wheel barrowing Icing Conditions WARNING Flights into conditions where icing should reasonably be expected are prohibited This specifically includes flight in freezing rain or freezing drizzle flight in wet snow or flight in clouds 72 This aircra...

Page 121: ...d set airspeed as close to manoeuvring speed as practical and fly a constant pitch attitude This technique combats the tendency to chase wildly fluctuating airspeeds and altitudes caused by differential barometric pressures in the storm WARNING Flights into thunderstorms are prohibited Cold Weather Operations 74 Operating the Cessna 182 in cold weather involves greater than normal care of the airf...

Page 122: ...ter WARNING Prior to moving the propeller or moving to a position inside the propeller plane of rotation visually confirm that the ignition switch is in the OFF position and the keys are removed d perform a Normal Start in accordance with the checklist e after start monitor oil pressure temperature and cylinder heat temperatures closely to ensure operating minimums and maximums are maintained Warm...

Page 123: ...ing landings make allowances for reduced braking effectiveness on snow or ice covered runways and k when securing the aircraft take steps to ensure that snow and ice will be prevented from entering critical areas ...

Page 124: ...2 48 This page intentionally left blank ...

Page 125: ...situational awareness and to draw his her attention to specific aircraft parameters that may be of concern Non Critical Emergencies 5 Non critical emergencies are those that do not pose an immediate threat to the safety of the aircraft or the personnel on board These are circumstances where there is sufficient time available to assess the situation consider available options and determine a suitab...

Page 126: ...nce with the procedures detailed in Figure 3 1 EDM 930 SECONDARY ALERTS ALERT DISPLAY INDICATION OF ACTION TK LOW Fuel tank low quantity Confirm that sufficient fuel is available to complete the planned flight MIN Low Fuel Endurance Remaining Confirm that sufficient fuel is available to complete the planned flight REM Low Fuel Quantity Remaining Confirm that sufficient fuel is available to complet...

Page 127: ...if necessary O P Low Oil Pressure Execute Low Fluctuating Oil Pressure Checklist F P Low Fuel Pressure Execute Low Fuel Pressure Checklist EGT High EGT Reduce power and or increase airspeed for better cooling Monitor and land if necessary MAP Over Boost Manifold Pressure Reduce throttle if safe to do so RPM High RPM over Red Line Reduce propeller RPM if safe to do so BUS An under voltage or over v...

Page 128: ...wn the alternator when the charging voltage reaches approximately 30 volts Note that no specific current flow has been specified as the threshold for excessive rate of charge However in general terms once the battery charge has been restored after starting normal current flow would typically be less than 5 amps 12 If the ammeter indicates a continuous discharge rate in flight the alternator is not...

Page 129: ...ble power highly dependent on battery condition charge and electrical services selected 4 Land As soon as practicable Reduce all available electrical load in order to conserve power for EDM930 operation circuit and landing Figure 3 4 Battery Discharge Alerts NOTE Battery power is sufficient for normal VFR operations for a minimum of 30 minutes CAUTION Total electrical failure will result in the lo...

Page 130: ...re 16 Low fuel pressure or loss of fuel pressure indication may signify the failure of the engine driven fuel pump This may also indicate a malfunction of the fuel pressure sensor or a problem with the EDM930 To determine if the problem is instrumentation related determine whether fuel flow is normal or whether there are secondary indications such as a rough running engine or loss of power Selecti...

Page 131: ...cation refer to Low Oil Pressure Figure 3 5 or i major mechanical failure 18 The actions to be taken in response to a rough running engine should consider a while attempting to identify and correct the problem it may be appropriate to manoeuvre the aircraft so as to optimize the position for a forced landing should the situation deteriorate b immediate actions should be taken appropriate to the sy...

Page 132: ...el quantity indications 1 Select Aux Fuel Pump ON 2 Land as soon as practicable Fuel Exhaustion Sudden reduction in fuel pressure and or fuel flow rate with low fuel quantity indications 1 Select fullest fuel tank 2 Land as soon as practicable Air Induction Icing Reduced Manifold Pressure 1 Select alternate air to ON 2 Land as soon as practicable Fouled Plugs High EGT on one or more cylinders 1 Le...

Page 133: ...0 RPM Minimizes ice buildup on propeller blades MAP Monitor for decrease MAP decrease may indicate air induction filter icing Alternate air Use as required Lean mixture if used continuously Land As soon as practicable If ice buildup is extremely rapid land as soon as possible Flaps Leave Retracted Ice on the horizontal tail and the change in airflow from flap extension may result in a loss of elev...

Page 134: ... case of a critical emergency the FUEL SHUTOFF VALVE must be selected OFF to prevent fuel from the fuel header tank from continuing to be delivered to the engine Engine Restart FMS Check 21 In cases of an engine failure in flight if time permits conduct a restart using the FMS Restart Check detailed below FMS SHUTDOWN ACTION CHECK NOTES F Fuel Fuel Selector BOTH Fuel Shutoff Valve OPEN Confirm shu...

Page 135: ... as possible ENGINE FIRE ON START ACTION CHECK NOTES 1 Starter Continue cranking Sucks flames and accumulated fuel into engine 2 Throttle OPEN full 3 Mixture Idle cut off CAUTION As fuel is sucked in the engine may start and run at high RPM briefly If no further evidence of fire Complete normal shutdown and investigate If fire continues Perform engine fire on ground check Figure 3 11 Engine Fire o...

Page 136: ...to extinguish fire 4 Carry out a forced landing Do not attempt to restart engine Figure 3 13 Engine Fire in Flight WING FIRE ACTION CHECK NOTES 1 Slip away from burning wing Keep flames away from fuel tank and cabin 2 All lights OFF Anti collision navigation and pulse lights 3 Pitot heat OFF 4 Land As soon as possible Figure 3 14 Wing Fire CABIN FIRE ACTION CHECK NOTES 1 Cabin Heat Air all vents C...

Page 137: ...nt characterized by a total or near total loss of engine power where altitude cannot be maintained Engine failures may occur at any point during the flight and with little or no warning An appropriate emergency response must consider the altitude airspeed and location where the engine failure occurs Prior to initiating take off pilots should have established a course of action to deal with time cr...

Page 138: ...landing area Fly to it 5 Forced Landing CARRY OUT Figure 3 18 Engine Failure after Takeoff ENGINE FAILURE IN FLIGHT ACTION CHECK NOTES 1 Establish glide 80 MPH Retract flaps if required 2 If towing Release glider 3 Throttle CLOSE 4 Select landing area Fly to it 5 FMS Restart CARRY OUT If no indication of restart 6 Forced Landing CARRY OUT Figure 3 19 Engine Failure in Flight ...

Page 139: ...nder Set 7700 5 Landing area Recheck Re assess for suitability approach obstacles MSL altitude and wind direction and speed 6 FMS Shutdown CARRY OUT 7 Harness Ensure tight 8 Brakes Check 9 Cabin doors and windows Unlatch 10 Flaps Select as required Land with full flap if practicable 11 Master switch OFF After final flap selection DITCHING In light winds land parallel to swells In strong winds land...

Page 140: ...3 16 This page intentionally left blank ...

Page 141: ...otalizer 15 USG Fuel Tank Gauges Total 20 USG Oil Acceptable Grades Journey Log Max Capacity 12 US Qts Top Up if below 10 US Qts Min Level for Take Off 9 US Qts Tire Pressures Main Wheel 30 psi Nose Wheel 30 psi Allowable Flap Settings Take Off 0 20º Landing 0 35º Nose Oleo Normal Extension 2 4 inches Vortex Generators Maximum Number Missing 5 Shock Cooling Threshold CHT Cooling Rate 60º min Fly O...

Page 142: ...ircraft is certified for a maximum of four occupants c aerobatic manoeuvres as defined by the Canadian Aviation Regulations are prohibited and d deliberate spins or incipient spins are prohibited Flight Rules 4 The aircraft is equipped and certified for flight in day and night VFR conditions only Flight in Instrument Meteorological Conditions IMC and flight in known icing conditions are both prohi...

Page 143: ...ty Cycle Cooling Period 30 secs 3 mins Oil Pressure Minimum at idle 10 psi Normal operating range 30 60 psi Maximum cold oil 100 psi Oil Temperature Minimum for run up 75º F Minimum for takeoff 75º F Normal operating range 100 240º F Maximum 240º F Fuel Pressure Minimum 3 5 psi Maximum 19 5 psi Fuel Flow Rate Normal Operating Range 7 17 GPH Maximum 25 2 GPH Cylinder Head Temp CHT Minimum for run u...

Page 144: ...4 Maximum structural cruising speed Do not exceed this speed except in smooth air VA 2950 lbs 126 Manoeuvring speed Do not make full or abrupt control movements above this speed 2450 lbs 116 1950 lbs 105 VFE 0 10º flap 160 Maximum flap speed Do not exceed these speeds with the given flap settings 11 35º flap 110 Maximum window open speed 120 Do not exceed this speed with bubble window open Maximum...

Page 145: ...Tow 70 Traffic Pattern Normal Downwind 0º flap 125 2400 RPM 20 MAP Slow Downwind 10º flap 115 2400 RPM 18 MAP Final Approach Final Approach 0º flap 80 90 In gusty winds add half the gust spread to the FAS Final Approach 20º flap 75 85 Final Approach 35º flap 70 80 Gliding Optimum glide zero wind prop wind milling flaps up 80 Figure 4 6 Normal Operating Speeds Stalling Speeds 10 The following stall...

Page 146: ... 2250 1400 2950 10 550 1150 650 1400 800 1750 1000 2300 20 350 850 450 1050 550 1300 700 1750 Governing Conditions 1 200 flaps 2 Hard surface runway 3 Increase distances 10 for each 250 F above ISA 4 For dry grass runway increase distances by 10 of total to clear 50 ft obstacle 5 For glider towing increase both ground roll and total takeoff distances by 25 of total to clear 50 ft obstacle Figure 4...

Page 147: ...ft 86 800 750 700 650 2 500 lbs SL 90 1 750 1 700 1 550 1 500 2 000 ft 90 1 600 1 500 1 400 1 350 4 000 ft 89 1 500 1 350 1 300 1 200 6 000 ft 87 1 300 1 200 1 150 1 100 8 000 ft 87 1 150 1 100 1 000 950 10 000 ft 86 1 000 950 900 850 Governing Conditions 1 Aircraft weight as shown 2 Flaps UP 3 Power Set 2700 RPM Full Throttle 4 Cowl Flaps OPEN 5 For 3 100 lbs reduce published climb rate for 2 950...

Page 148: ...87 900 6 2 0 8 8 000 ft 87 800 8 2 8 11 10 000 ft 86 700 11 3 6 14 Governing Conditions 1 Flaps UP 2 Power Set 2700 RPM Full Throttle 3 Cowl Flaps OPEN 4 ISA Conditions 5 Aircraft Weight 2 950 lbs 6 Add 2 USG of fuel for start taxi run up and takeoff allowance 7 Increase time fuel and distance by 10 for each 10º C above ISA conditions 8 Increase time fuel and distance by 10 for aircraft weight of ...

Page 149: ...eaned to 50ºF Rich of Peak ROP CAUTION Do not adjust the mixture to Lean of Peak as significant engine damage may result b standard atmospheric conditions ISA c aircraft weight of 3 100 lbs d range estimates are based on full fuel tanks e range estimates are based on still air and f range estimates are based on a 30 minute fuel reserve NOTE Maximum continuous cruise power is 75 of maximum continuo...

Page 150: ... 515 22 68 134 140 121 15 8 515 21 65 132 138 120 15 3 530 20 62 130 136 118 14 5 550 19 59 126 132 114 13 9 560 2400 25 74 140 146 127 17 5 480 Normal Cruise 24 71 138 144 125 16 6 500 23 68 143 140 121 15 9 510 22 66 128 134 116 15 2 515 21 62 124 129 113 14 4 530 20 60 122 126 110 13 9 540 19 57 121 125 109 13 3 560 2300 26 74 139 145 126 17 3 480 25 71 137 143 124 16 3 510 24 68 135 141 122 15...

Page 151: ... 149 129 16 1 535 21 67 133 143 125 15 2 550 20 64 126 136 118 14 7 555 19 61 123 133 115 14 2 550 2400 25 75 142 153 133 17 8 495 Normal Cruise 24 73 139 150 130 16 7 520 23 70 136 147 127 16 0 535 22 68 134 145 126 15 4 550 21 65 130 140 122 14 6 565 20 62 127 137 119 14 0 580 19 59 123 133 115 13 4 590 2300 26 75 142 153 133 18 2 480 25 73 140 151 131 16 8 520 24 70 137 148 128 15 7 550 23 67 1...

Page 152: ...131 17 0 510 22 70 132 148 128 16 0 535 21 67 129 144 125 15 2 555 20 63 126 141 123 14 5 575 19 61 124 139 121 13 8 595 2400 Full Throttle at approximately 24 MAP 24 72 138 154 134 17 6 505 Normal Cruise 23 70 135 151 131 16 3 540 22 67 131 147 127 15 6 550 21 64 129 144 125 14 7 570 20 62 126 141 123 14 1 590 19 59 123 138 120 13 4 610 2300 Full Throttle at approximately 24 MAP 24 69 135 151 131...

Page 153: ... 2 610 Max Speed Cruise 22 69 135 157 136 15 1 610 21 66 133 154 134 14 3 635 20 63 130 151 131 13 7 650 19 60 127 148 128 13 2 660 2400 Full Throttle at approximately 22 5 MAP 22 5 68 131 152 132 14 8 605 Normal Cruise 22 66 130 151 131 14 4 620 21 64 124 144 125 13 7 625 20 61 120 140 121 13 0 640 19 58 117 135 117 12 5 645 2300 Full Throttle at approximately 22 6 MAP 22 6 65 131 152 132 14 3 62...

Page 154: ...ange NM Comments 2500 Full Throttle at approximately 21 0 MAP 21 66 130 157 136 15 3 595 Max Speed Cruise 20 63 127 153 133 14 5 620 19 60 122 147 128 13 8 630 2400 Full Throttle at approximately 21 0 MAP 21 64 127 153 133 14 7 610 Normal Cruise 20 61 125 150 131 13 9 640 19 58 119 143 125 13 2 645 2300 Full Throttle at approximately 21 0 MAP 21 61 120 145 126 14 1 605 20 59 116 139 120 13 1 630 1...

Page 155: ...0 20 80 72 13 0 360 NM 4 000 ft 10 o 2300 18 90 84 11 8 465 NM 20 o 2300 20 80 75 12 8 375 NM 6 000 ft 10 o 2300 18 90 87 11 6 485 NM 20 o 2300 20 80 78 12 6 395 NM 8 000 ft 10 o 2300 18 90 90 11 4 505 NM 20 o 2300 20 80 80 12 4 405 NM 10 000 ft 10 o 2300 18 90 94 11 2 525 NM 20 o 2300 20 80 83 12 2 420 NM Governing Conditions 1 Mixture leaned to 50 degrees ROP 2 Standard Atmospheric Conditions 3 ...

Page 156: ...irspeed it is recommended to select flaps to 10 degrees to prevent an excessive nose up attitude in the circuit and c if desired a slower airspeed of approximately 115 MPH can be achieved with power setting of 2400 RPM and 18 MAP At this airspeed it is recommended to select flaps to 10 degrees to prevent an excessive nose up attitude in the circuit 19 Approach Speeds Normal approach and landing sp...

Page 157: ...ions 1 Flaps 35 degrees 2 Power IDLE Propeller FULL FINE 3 Final Approach Speed 70 MPH IAS 4 Maximum Braking after flaps raised on touchdown 5 Paved level dry runway 6 Zero Wind 7 Aircraft Weight 2950 lbs maximum landing weight 8 Decrease both distances by 10 for every 10 kts of headwind 9 Increase both distances by 10 for every 2 kts of tailwind up to 10 kts 10 For operations from dry grass incre...

Page 158: ...ight 3 100 lbs Maximum landing weight 2 950 lbs Full fuel weight 75 USG useable 15º C 480 lbs Max weight Fwd Baggage Compartment 120 lbs Max weight Aft Baggage Compartment 80 lbs Figure 4 19 Weight Limitations Center of Gravity Limits 22 Figure 4 20 details the weight and centre of gravity limits Figure 4 20 Centre of Gravity Limits ...

Page 159: ...aircraft outside of published weight and balance limits will adversely affect the stability and control characteristics of the aircraft and will invalidate the Certificate of Airworthiness NOTE Aircraft Empty Weight as shown on the Aircraft Weight Balance report includes the following 10qts Oil 5 USG Unusable Fuel Life Jackets Charts Fire Extinguisher and First Aid Kit NOTE As flights planned with...

Page 160: ...cupants 37 00 37 00 Rear Seat Occupants 74 00 74 00 Forward Baggage Area max 120 lbs 97 00 97 00 Tie Down Box 20 lbs if carried 97 00 97 00 Step Ladder 6 lbs if carried 97 00 97 00 Rear Baggage Area max 80 lbs 115 00 115 00 Removable Ballast 20 lbs if carried 115 00 115 00 Tow Bar 2 lbs if carried 124 00 124 00 Total Weight Moment Figure 4 21 Weight and Balance Worksheet ...

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