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AFM - CAVOK Aviation Training

1. 62 0 EQUIPMENT LIST DESCRIPTION seromme wriss 0 2 0000 02 E 00 MO 000000 00010 2 010 O01 O amp I8 8 2 0102 00 OWOODOOMOPYON ABAOPARWNUMUND A LSIT JAONV IVE V LHOIM 9 NOILOAS WOST VNSSHO CESSNA SECTION 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS INTRODUCTION This section provides description and operation of the airplane and its systems Some equipment described herein is optional and may not be installed in the airplane Refer to Section 9 Supplements for details of other optional systems and equipment AIRFRAME The construction ofthe fuselage is a conventional formed sheet metal bulkhead stringer and skin design referred to as semi monocoque Major items of structure are the front and rear carry through spars to which the wings are attached a bulkhead and forgings for main landin gear attachment at the base ofthe rear door posts and a bulkhead wit attaching plates at the base ofthe forward door posts for the lower attach ment ofthe wing struts Four engine mount stringers are also attached to the forward door posts and extend forward to the firewall The externally braced wings containing the fuel tanks are construc ed of a front and rear spar with formed sheet metal ribs doublers and
2. SECTION 7 AIRPLANE amp SYSTEMS DESCRIPTIONS Q TO FUEL QUANTITY INDICATORS FUEL IND DL TO FLASHING BEACON TO PITOT HEAT PI TOT To srRosE LIGHTS STROBE LTS ot TO CIGAR LIGHTER WITH FUSE 55 TO LANDING AND TAXI LIGHTS LTS TO IGNITION SWITCH E O z WING FLAP SYSTEM Uu TO INSTRUMENT RADIO AND 5 COMPASS LIGHTS TO OIL TEMPERATURE GAGE TO TURN COORDINATOR TO AUDIO MUTING RELAY TO CONTROL WHEEL MAP LIGHT TO NAVIGATION LIGHTS TO DOME LIGHT TURN AND BANK INDICATOR 7 TO RADIO RADIO 1 Q TO RADIO RADIO 2 g TO RADIO OR TRANSPONDER AND ENCODING ALTIMETER TO RADIO RADIO 4 System 7 23 SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M system When the engine is operating and the master switch is turned on the ammeter indicates the charging rate applied to the battery In the event the alternator is not functioning or the electrical load exceeds the output of the alternator the ammeter indicates the battery discharge rate OVER VOLTAGE SENSOR AND WARNING LIGHT The airplane is equipped with an automatic over voltage protection system consisting of an over voltage sensor behind the instrument panel and a red warning light labeled HIGH VOLTAGE under the ammeter In the event an over voltage condition occurs the over voltage sen sor automatically removes alternator field current and shuts down the al ternator The red
3. Short Field Takeoff Enroute Climb Cruise Before Landing Landing Normal Landing Short Field Landing Balked Landing After Landing De Rt Securing Airplane AMPLIFIED Starting Engine Taxiing Page 4 3 CA CA CA CA CA OO pp pp pp PERE XO O0 1 1 1 1 OS OS BE 4 11 4 1 4 NORMAL PROCEDURES TABLE OF CONTENTS Continued Before Takeoff Warm Up Magneto Check Alternator Check Takeoff Power Check Flap Settings Short Field Takeoff Crosswind Takeoff Enroute Climb Normal Climb Best Rate of Climb Best of Climb Cruise Stalls Spins Landing Short Field Landing Crosswind Landing Balked Landing Cold Weather Operation Noise Abatement 4 2 CESSNA MODEL 150M Page 4 13 4 13 4 13 4 13 4 13 4 13 4 14 4 14 4 15 4 15 4 15 4 15 4 15 4 15 4 17 4 17 4 19 4 19 4 20 4 20 4 20 4 22 CESSNA SECTION 4 MODEL 150M NORMAL PROCEDURES INTRODUCTION Section 4 provides checklist and amplified procedures for the con duct of normal operation Normal procedures associated with Optional Systems can be found in Section 9 SPEEDS FOR NORMAL OPERATION Unless otherwise noted the pid speeds are based on a maxi mum weight of 726 KG and may be used for any lesser weight Takeoff Normal Climb Out 00 0 KIAS S
4. control lock is provided to lock the ailerons and elevator control surfaces in a neutral position and prevent damage to these systems by wind buffeting while the airplane is parked The lock consists of a shaped steel rod with a red metal flag attached to it The flag is labeled CON TROL LOCK REMOVE BEFORE STARTING ENGINE install the con trol lock align the hole in the top of the pilot s control wheel shaft with 7 14 CESSNA SECTION 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS the hole in the top of the shaft collar on the instrument panel and insert the rod into the aligned holes Proper installation of the lock will place the red flag over the ignition switch In areas where high or gusty winds Occur a control surface lock should be installed over the vertical stabi lizer and rudder The control lock and any other type of locking device should be removed prior to starting the engine ENGINE The airplane is powered by a horizontally opposed four cylinder overhead valve air cooled carbureted engine with a wet sump oil sys tem The engine is a Continental Model O 200 A and is rated at 100 horsepower at 2750 RPM Major engine accessories include a vacuum pump mounted at the front of the engine and a starter gear driven alternator and dual magnetos which are mounted on an accessory drive pad at the rear of the engine Provisions are also made for a full flow oil filter and an oil cooler ENGINE CONTROLS Engine
5. 2 Brakes APPLY AS REQUIRED 3 Ignition Switch OFF 4 Master Switch OFF Roll off the runway ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF 1 Airspeed 60 KIAS If time allows Q Throttle FULL 3 3 3 CESSNA EMERGENCY PROCEDURES MODEL 150M 3 Prop Pitch FINE full forward 4 Carb Heat OFF 5 Choke OFF 5 Ignition Switch BOTH 6 Electric Fuel Pump ON ENGINE FAILURE DURING FLIGHT PORPELLER WINDMILLING 1 Airspeed 60 KIAS 2 Prop Pitch FINE full forward 3 Electric Fuel Pump ON 4 Ignition Switch BOTH 5 Fuel Shutoff Valve ON 6 Throttle 2 CM IN 7 Choke OFF If engine fails to start in 10 seconds apply cold start procedure 8 Throttle IDLE 9 Choke ON ENGINE FAILURE DURING FLIGHT PORPELLER STOPPED 1 Electrical Equipment OFF 2 Master Switch ON 3 Prop Pitch FINE full forward 4 Electric Fuel Pump ON 5 Cold start Throttle IDLE Choke ON 6 Warm start Throttle 2 CM IN Choke OFF 7 Ignition Switch START POWER LOSS DURING FLIGHT 1 Throttle NOT TO BE MOVED 2 Choke OFF 3 Try to restore power with adjusting Electric Fuel Pump Ignition Switch Prop Pitch PROPER REACTIONS If engine power cannot be restored to normal apply minimum power setting to continue the flight and land on the nearest airfield 3 4 CESSNA SECTION 3 MODEL
6. 5 Touchdown MAIN WHEELS FIRST 6 Brakes APPLY HEAVILY 7 Flaps RETRACT BALKED LANDING 1 Throttle FULL OPEN 2 Carburetor Heat COLD 3 Wing Flaps RETRACT TO 20 4 Airspeed 55 KIAS 5 Wing Flaps RETRACT slowly AFTER LANDING 1 Wing Flaps UP 2 Carburetor Heat COLD 3 Fuel Pump OFF SECURING AIRPLANE 1 Parking Brake SET Q Radios Electrical Equipment OFF 3 Mixture IDLE CUT OFF pull full out 4 Ignition Switch OFF 5 Master Switch OFF 6 Control Lock INSTALL 4 9 4 10 blank CESSNA SECTION 4 MODEL 150M NORMAL PROCEDURES AMPLIFIED PROCEDURES STARTING ENGINE Ordinarily the engine starts easily with one or two strokes of primer in warm temperatures to six strokes cold weather with the throttle open approximately 1 4 inch In extremely cold temperatures it may be necessary to continue priming while cranking Weak intermittent firing followed by puffs of black smoke from the exhaust stack indicate overpriming or flooding Excess fuel can be cleared from the combustion chambers by the following procedure Set mixture control in the idle cut off position throttle full open and crank the engine through several revolutions with the starter Repeat the start ing procedure without any additional priming If the engine is underprimed most likely in cold weather with a cold engine it will not fire at all and additional pr
7. CESSNA 300 ADF PILOT S OPERATING HANDBOOK TYPE R 546E SUPPLEMENT SECTION 2 LIMITATIONS There is no to the airplane limitations when this avionic equipment is installed SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when this avionic equipment is installed SECTION 4 NORMAL PROCEDURES TO OPERATE AS A COMMUNICATIONS RECEIVER ONLY 1 OFF VOL Control ON 2 Function Selector Knob REC 3 Frequency Selector Knobs SELECT operating frequency 4 ADF SPEAKER PHONE Switch SELECT speaker or phone position desired 5 VOL Control ADJUST to desired listening level TO OPERATE AS AN AUTOMATIC DIRECTION FINDER 1 OFF VOL Control ON 2 Frequency Selector Knobs SELECT operating frequency 3 ADF SPEAKER PHONE Switch SELECT speaker or phone osition 4 Function Selector Knob ADF position and note relative bearing on indicator 5 VOL Control ADJUST to desired listening level TO TEST RELIABILITY OF AUTOMATIC DIRECTION FINDER 1 Function Selector Knob ADF position and note relative bearing on indicator 2 Function Selector Knob TEST position and observe that pointer moves away from relative bearing at least 10 to 20 degrees 3 Function Selector Knob ADF position and observe that pointer returns to same relative bearing as in step 1 CESSNA 300 ADF PILOTS OPERATING HANDBOOK R 546E SUPP
8. 4 Fuel Quantity Indicators CHECK QUANTITY 5 Master Switch OFF 6 Fuel Shutoff Valve ON EMPENNAGE 1 Rudder Gust Lock REMOVE 2 Tail Tie Down DISCONNECT 3 Control Surfaces CHECK freedom of movement and security RIGHT WINGTrailing Edge 1 Aileron CHECK freedom of movement and security RIGHT WING 1 Wing Tie Down DISCONNECT 2 Main Wheel Tire CHECK for proper inflation 3 Before first flight of the day and after each refueling use sampler cup and drain small quantity of fuel from fuel tank sump wan valve to check for water sediment and proper fuel ade 4 Fuel Quantity CHECK VISUALLY for desired level 5 Fuel Filler Cap SECURE NOSE 1 Engine Oil Level CHECK do not operate with less than 2 5 liters Fill to 3 5 liters for extended flight Before first flight of the day check the ignition switch and main switch are off and turn the propeller by hand several times in the direction of its rotation to pre lubricate the engine prior to start 2 Before first flight of the day and after each refueling pull out strainer drain knob for about four seconds to clear fuel strainer of possible water and sediment Check strainer drain closed If water is observed the fuel system may contain additional water and further draining of the system at the strainer fuel tank sumps and fuel line drain plug will be necessary 3 Check the engine coolant fluid level 4 5 S
9. 5 Tie a rope no chains or cables to an exposed portion of the engine mount and secure to a ramp tie down 6 Install a pitot tube cover JACKING When a requirement exists to jack the entire airplane offthe ground or when wing jack points are used in the jacking operation refer to the Service Manual for specific procedures and equipment required Individual main gear may be jacked by the jack pad which 1s incorporated in the main lan gear strut step bracket When using the individual gear strut jack pad flexibility of the gear strut will cause the main wheel to slide inboard as the wheel is raised tilting the jack The jack must then be lowered for a second jacking operation Do not jack oth main wheels simultaneously using the individual main gear jack pads If nose gear maintenance is required the nose wheel may be raised off the ground by pressing down on a tailcone bulkhead just forward of the horizontal stabilizer and allowing the tail to rest on the tail tie down ring NOTE Do not apply pressure on the elevator or outboard stabi lizer surfaces When Dunne on the tailcone always apply pressure at a bulkhead to avoid buckling the skin To assist in raising and holding the nose wheel offthe ground weight down the tail by placing sand bags or suitable weight on each side ofthe 8 8 CESSNA SECTION 8 MODEL 150M HANDLING SERVICE amp MAINTENANCE horizontal stabilizer next to the fuselage If ground anch
10. INTRODUCTION Performance data charts on the following pages are presented so that you may know what to expect from the airplane under various conditions and also to facilitate the planning of flights in detail and with reasonable accuracy The data 1n the charts has been computed from actual flight tests with the airplane and engine in good condition and using average piloting techniques It should be noted that the performance information presented in the range and endurance profile charts allows for 45 minutes reserve fuel based on 45 power Fuel flow data for cruise is based on the recommended lean mixture setting Some indeterminate variables such as mixture leaning technique fuel metering characteristics engine and propeller condition and air turbulence may account for variations of 10 or more in range and endurance herefore it is important to utilize all available information to estimate the fuel required for the particular flight USE OF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to illustrate the effect of different variables Sufficiently detailed information is provided in the tables so that conservative values can be selected and used to determine the particular performance figure with reasonable accuracy SAMPLE PROBLEM The following sample flight problem utilizes information from the various charts to determine the predicted performance data for a typical flight The following inf
11. THGHOIN VNSSHO CESSNA SECTION 6 MODEL 150M WEIGHT amp BALANCE EQUIPMENT LIST INCHES SEG LOADED AIRCRAFT MOMENT 1000 POUND Figure 6 8 Center of Gravity Moment Envelope EH t H H gt gt gt LL LLI 1 Op 1 2 ce N LHDIAM L3VHOMHIV SECTION 6 CESSNA WEIGHT amp BALANCE MODEL 150M EQUIPMENT LIST 1600 ood H LE MERE 1500 1400 CENTER OF GRAVITY LIMITS LOADED AIRCRAFT WEIGHT POUNDS Hhh HEHHEE ingi 3 4 22 1 14 ri 4 i HIPH f 1100 AIRCRAFT C G LOCATION INCHES DATUM Figure 6 9 Center of Gravity Limits CESSNA SECTION 6 MODEL 150M WEIGHT amp EQUIPMENT LIST EQUIPMENT LIST The following equipment list is a comprehensive list of all Cessna equipment available for this airplane A separate equipment list of items installed in your specific airplane is provided in your aircraft file The following list and the specific list for your airplane have a similar order of listing This equipment list provides th
12. This system provides visual and aural indications of 75 MHz ILS marker beacon signals as the marker is passed The following table lists the three most currently used marker facilities and their characteristics MARKER FACILITIES MARKER IDENTIFYING TONE LIGHT Inner Continuous 6 dots sec 3000 Hz White Middle Alternate dots and dashes 1300 Hz Amber Outer 2 dashes sec 400 Hz Blue When the identifying tone is keyed the respective indicating light will blink accordingly Operating controls and indicator lights are shown and described in Figure 1 of 4 CESSNA 400 MARKER PILOT S OPERATING HANDBOOK TYPE R 402A SUPPLEMENT TYPICAL INSTALLATION ON ALL 150 MODEL SERIES TYPICAL INSTALLATION ON ALL 172 177 177RG 180 amp 185 MODEL SERIES TYPICAL INSTALLATION ON ALL 182 206 207 amp 210 MODEL SERIES TYPICAL INSTALLATION ON ALL 337 MODEL SERIES Figure 1 Cessna 400 Marker Beacon Operating Controls and Indicator Lights Sheet 1 of 2 PILOT S OPERATING HANDBOOK CESSNA 400 MARKER BEACON SUPPLEMENT TYPE R 402A 1 OFF VOLUME CONTROL The small inner control turns the set on or off and adjusts the audio listening leveL Clock wise rotation turns the set on and increases the audio level 2 DIM BRT CONTROL The large outer control provides light dimming for the marker lights Clockwise rotation increases light intensity 3 TEST SWITCH 150 182 206
13. WING FLAP SYSTEM The wing flaps are ofthe single slot type see figure 7 3 and are extended or retracted by positioning the wing flap switch lever on the instrument panel to the desired flap deflection position The switch lever is moved up or down in a slot in the instrument panel that pro vides Stops atthe 10 and 20 positions or flap settings greater than 10 move the switch lever to the right to clear the stop and position it as desired scale and pointer on the left side of the switch lever indicates flap travel in degrees The wing flap system circuit is protected by 15 ampere circuit breaker labeled FLAP on the right side of the instrument panel LANDING GEAR SYSTEM The landing gear is of the tricycle t pe with a steerable nose wheel two main wheels and wheel fairings ock absorption is provided by the tubular spring steel main landing gear struts and the air oil nose gear shock strut Each main gear wheel is equipped with a hydraulic ally actu ated disc type brake on the inboard side of each wheel and an aerodyna mic fairing over each brake BAGGAGE COMPARTMENT The baggage compartment consists of the area from the back of the pilot and passenger s seats to the aft cabin bulkhead Access to the bag gage compartment is gained from within the airplane cabin baggage net with six tie down straps is provided for securing baggage and 1s at tached by tying the straps to tie down rings provided in the airp
14. tem consisting of an inlet in the leading edge of the left wing an air operated horn near the upper left corner of the windshield and asso ciated plumbing As the airplane approaches a stall the low pressure on the surface of wing moves forward around the leading edge of the wing This low pressure creates a differential pressure in the stall warning system which draws air through the warning horn in an audible warning at 5 to 10 knots above stall in all flight conditions The stall warning system should be checked during the preflight in spection by placing a clean handkerchief over the vent opening and apply ing suction sound from the warning horn will confirm that the system is operative AVIONICS SUPPORT EQUIPMENT The airplane may at the owner s discretion be equipped with vari ous types of avionics support equipment such as an audio control panel and static dischargers The following paragraphs discuss these items AUDIO CONTROL PANEL Operation of radio equipment is covered in Section 9 of this handbook When one or more radios 15 installed a transmitter audio switching sys tem is provided see figure 7 10 The operation of this switching system is described in the following paragraphs TRANS COM ADF SPEAKER 1 gm _ SPEAKER PHONE SWITCH TYPICAL Figure 7 10 Audio Control Panel TRANSMITTER SELECTOR SWITCH 7 31 SECTION 7 CESSNA AIRPLAN
15. 1 Function Switch SBY TO TRANSMIT MODE A AIRCRAFT IDENTIFICATION CODES IN FLIGHT 1 Offindicator Warning Flag VERIFY that flag is out of view on encoding altimeter PILOTS OPERATING HANDBOOK CESSNA 300 TRANSPONDER SUPPLEMENT AND ENCODING ALTIMETER 2 Reply Code Selector Knobs SELECT assigned code 3 Function Switch ON 4 DIM Control ADJUST light brilliance of reply lamp 5 During normal operation with function switch in 1 tion reply lamp flashes indicating transponder replies to interrogations ID Button DEPRESS momentarily when instructed by ground controller to squawk IDENT reply lamp will glow steadily in dicating IDENT operation TO TRANSMIT MODE C ALTITUDE REPORTING CODES IN FLIGHT D Off Indicator Warning Flag VERIFY that flag is out of view on encoding altimeter 2 Altitude Encoder Altimeter Setting Knob SET IN assigned local altimeter setting 3 4 5 Reply Code Selector Knobs SELECT assigned code Function Switch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode A operation only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated alti tude is done in ATC computers Altitude squawked will only agree with indicated altitude when the local altimeter setting in use by the ground controller is
16. 207 210 amp 337 Model Series Only When the press to test switch button is de pressed the marker beacon lights will illuminate indica ting the lights are operational the test position is a lamp test function only NOTE Turn the set on and rotate the DIM control clock wise fully on in order to view the marker beacon lights during test 4 LO HI SENS SWITCH 150 182 206 207 210 amp 337 Model Series Only In the LO position Up receiver sensi tivity is positioned for ILS approaches In the HI position Down receiver sensitivity is positioned for airway flying 5 SPEAKER PHONE SWITCH Selects speaker or phone for aural reception 6 MARKER BEACON INDICATOR LIGHTS Indicates passage of outer middle and inner marker beacons The OUTER light is blue the MIDDLE light is amber and the INNER light is white 7 HI LO TEST SWITCH 172 177 177RG 180 amp 185 Model Series Only In the HE position Up receiver sensitivity is positioned for airway flying In the LO position Center re ceiver sensitivity is positioned for ILS approaches In the TEST position Down the marker lights will illuminate in dicating the lights are operational the test position is a lamp test function only NOTE Turn the set on and rotate the BRIGHT control clockwise fully on in order to view the marker beacon lights during test The TEST position on the switch is spring loaded to return the switch to the LO SENS pos
17. 6 13 SECTION 6 CESSNA WEIGHT amp BALANCE MODEL 150M EQUIPMENT LIST X Oomunn 0000 NONGTON Qr eet t 5o c 5 1 1 1 1 1 stroooowvoor t 00 00Q r e WT LBS oT e 98552552 215552585 REF DRAWING RIO 1 E eR SES MORASS eases mos D 5 Oc nr n x TIR EL ASSY TPE TST in P WH 4 ea z EE ce rA 5i m ES e c3 FA Oo L oO a fr E E 2 r4 cc 2 Ca E s oo Ol 28 5 d lt Fa Ex er e E w E T PS CD m gt ca e e E 4 3 3 SES gt 29 Armes COL Hd om LAL Z x D 2 oa a YA m ne E lt E UE 55 mee d Ed am Er A gt C oS LLI yc me ITEM NO 6 14 EQUIPMENT LIST DESCRIPTION WHEEL FAIRINGS BRAKE FAIRINGS BATTERY 12 VOLT REGULATOR ALTERNATOR 60 GROUND SERVICE RECEPTACLE PITOT HEATER SET OF 3 NOSE WHEEL FAIRING MAIN WHEEL FAIRING WOST THGOIN VNSSHO C262023 0101 0541225 0054
18. SELECT 7700 operating code for 1 minute then SELECT 7600 operating code for 15 minutes and then REPEAT this procedure at same intervals for remainder of flight 3 ID Switch DEPRESS then RELEASE at intervals to effect immediate identification of aircraft on ground controller s display SECTION 4 NORMAL PROCEDURES BEFORE TAKEOFF 1 Function Switch SBY TO TRANSMIT MODE A AIRCRAFT IDENTIFICATION CODES IN FLIGHT 1 Reply Code Selector Switches SELECT assigned code PILOT S OPERATING HANDBOOK CESSNA 400 TRANSPONDER SUPPLEMENT AND ALTITUDE ENCODER BLIND 2 3 4 Function Switch ON DIM Control ADJUST light brilliance of reply lamp NOTE During normal operation with function switch in ON posi tion reply lamp flashes indicating transponder replies to interrogationso ID Button DEPRESS momentarily when instructed by ground controller to squawk IDENT reply lamp will glow steadily in dicating IDENT operation TO TRANSMIT MODE C ALTITUDE REPORTING CODES IN FLIGHT 1 2 3 Reply Code Selector Switches SELECT assigned code Function Switch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode A operation only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated alti tude is done in ATC computers Altitude squawked will only agree with indicated alti
19. When unavoid able small dents appear in the propeller blades they should be immediate ly corrected as described in Section 8 under Propeller Care Prior to takeoff from fields above 5000 feet elevation the mixture should be leaned to give maximum RPM in a full throttle static runup After full throttle is applied adjust the throttle friction lock clock wise to prevent the throttle from creeping back from a maximum power position Similar friction lock adjustment should be made as required other flight conditions to maintain a fixed throttle setting FLAP SETTINGS Normal and short field takeoffs are performed with flaps use of 10 flaps will shorten the ground run approximately 10 but this advantage is lost in the climb to a 50 foot obstacle Therefore the use of 10 flaps is reserved for minimum ground runs or for takeoff from soft or rough fields 10 of flaps are used on soft or rough fields with obstacles ahead it is preferable to leave them extended rather than retract them in the climb to the obstacle exception to this rule would be in a high alti tude takeoff in hot weather where climb would be marginal with flaps 10 Flap deflections greater than 10 are not approved for takeoff SHORT FIELD TAKEOFF If an obstruction dictates the use of a steep climb angle after liftoff 4 14 CESSNA SECTION 4 MODEL 150M NORMAL PROCEDURES accelerate to and climb out at an obstacle clear
20. Yellow Arc 107 141 Operations must be conducted with caution and only in smooth air Red Line 141 Maximum speed for all operations Figure 2 2 Airspeed Indicator Markings POWER PLANT LIMITATIONS Bombardier Rotax GmbH Engine Model Number 912 53 Engine Operating Limits for Takeoff and Continuous Operations Engine Manufacturer Maximum Power 100 BHP Maximum Engine Speed 5800 RPM 2385 prop RPM Maximum Oil Temperature Propeller Manufacturer Propeller Model Number Propeller Diameter 180 CM 2 4 135 Oil Pressure Minimum 2 bar Maximum 5 bar Hoffmann Propeller GmbH HO V352F 170FQ 10 CESSNA SECTION 2 MODEL 150M LIMITATIONS POWER PLANT INSTRUMENT MARKINGS Power plant instrument markings and their color code significance are shown in figure 2 3 Instrument Figure 2 3 Power Plant Instrument Markings WEIGHT LIMITS Maximum Takeoff Weight 726 kg Maximum Landing Weight 726kg Maximum Weight in Baggage Compartment Baggage Area 1 or passenger on child s seat Station 50 to 76 54 kg See note below Baggage Area 2 Station 76 to 94 18 kg See note below NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 54 kg CENTER OF GRAVITY LIMITS Center of Gravity Range Forward 0 8 M aft of datum at 581 kg or less with straight line variation to 0 835 M aft of datum at 726 kg Aft 0 95 M af
21. equipment is installed SECTION 3 EMERGENCY PROCEDURES TO TRANSMIT AN EMERGENCY SIGNAL 1 Function Switch ON 2 Reply Code Selector Switches SELECT 7700 operating code 3 ID Switch DEPRESS then RELEASE to effect immediate identi fication of aircraft on ground controller s display TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Function Switch ON Reply Code Selector Switches SELECT 7700 operating code or 1 minute then SELECT 7600 operating code for 15 minutes and den REPEAT this procedure at same intervals for remainder of t Gy ID Switch DEPRESS then RELEASE at intervals to effect immediate identification of aircraft on ground controller s display SECTION 4 NORMAL PROCEDURES BEFORE TAKEOFF 1 Function Switch SBY Don MODE A AIRCRAFT IDENTIFICATION CODES IN 1 Off Indicator Warning Flag VERIFY that flag is out of view on encoding altimeter PILOT S OPERATING HANDBOOK CESSNA 400 TRANSPONDER SUPPLEMENT AND ENCODING ALTIMETER Q Reply Code Selector Switches SELECT assigned code 3 Function Switch ON 4 DIM Control ADJUST light brilliance of reply lamp NOTE During normal operation with function switch in ON posi tion REPLY lamp flashes indicating transponder replies to interrogations 5 ID Button DEPRESS momentarily when instructed by ground controller to squawk IDENT REPLY lamp will glow st
22. if installed are attached to fittings on the floorboard The buckle half of the seat belt is inboard of each seat and has a fixed length the link half of the belt is outboard and is the adjustable part of the belt To use the seat belts for the pilot s and passenger s seats position seat as desired and then lengthen the link half of the belt as needed by grasping the sides ofthe link and pulling against the belt Insert 7 11 7 AIRPLANE amp SYSTEMS DESCRIPTIONS STANDARD SHOULDER HARNESS NARROW RELEASE STRAP Pull up when lengthening harness FREE END OF HARNESS Pull down to tighten SHOULDER HARNESS CONNECTING LINK Snap onto retaining stud on seat belt link to attach harness SEAT BELT BUCKLE HALF Non adjustable putes SEAT BELT LINK HALF AND SHOULDER HARNESS RETAINING STUD FREE END OF SEAT BELT Pull to tighten SEAT BELT BUCKLE Non adjustable SEAT BELT SHOULDER HARNESS ADJUSTABLE LINK Position link just below shoulder level pull link and harness down ward to connect to seat belt buckle CESSNA MODEL 150M PILOTS SEAT SHOWN SEAT BELT SHOULDER HARNESS WITH INERTIA REEL Figure 7 4 Seat Belts and Shoulder Harnesses CESSNA SECTION 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS and lock the belt link into the buckle Tighten the belt to a snug fit by pulling the free end of the belt The seat belt for the child s seat if installed is used in t
23. ing that the malfunction was only momentary an attempt should be made to reactivate the alternator system To do this turn both sides of the master switch off and then on again If the problem no longer exists normal alternator charging will resume and the warning light will go off If the light comes on again a malfunction is confirmed In this event the flight should be terminated and or the current drain on the battery minimized because the battery can supply the electrical system for only a limited period of time If the emergency occurs at night power must be conserved for later use of the landing light and flaps during landing INSUFFICIENT RATE OF CHARGE If the ammeter indicates a continuous discharge rate in flight the alternator is not supplying power to the system and should be shut down since the alternator field circuit may be placing an unnecessary load on the system All nonessential equipment should be turned off and the flight terminated as soon as practical 3 15 3 16 blank CESSNA SECTION 4 MODEL 150M NORMAL PROCEDURES SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS Introduction Speeds For Normal Operation CHECKLIST PROCEDURES Preflight rS Cabin Empennage M Right Wing Fdge Right Wing Nose Wing Left Wing Leading Edge Left Wing Trailing Edge Before Starting Engine Starting Engine Before Takeoff Takeoff Normal Takeoff
24. the surface weather pene even though flight at a lower level may be consistent with the provisions of government regulations 2 During departure from or approach to an airport climb after takeoff and descent for landing should be made so as to avoid pro longed flight at low altitude near noise sensitive areas 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 judgment an altitude of less than 2000 feet is necessary for him to exercise his duty to see and avoid other air craft 4 22 CESSNA MODEL 150M SECTION 5 PERFORMANCE TABLE OF CONTENTS Introduction Use of Performance Charts Sample Problem Takeoff Cruise Fuel Required Landing Figure 5 1 Airspeed Calibration Figure 5 2 Temperature Conversion Chart Figure 5 3 Stall Speeds Figure 5 4 Takeoff Distance Figure 5 5 Rate of Climb Figure 5 6 Time Fuel and Distance to Climb Figure 5 7 Cruise Performance Figure 5 8 Range Profile 85 liter Fuel Range Profile 132 liter Fuel Figure 5 9 Endurance Profile 85 liter Fuel Endurance Profile 132 liter Fuel Figure 5 10 Landing Distance SECTION 5 PERFORMANCE Page tata 4 GoGo 1 Re e e e e Un Cn LA CA tA NNN 4 5 1 5 2 blank CESSNA SECTION 5 MODEL 150M PERFORMANCE
25. 3 7 45 85 3 5 2200 45 82 3 5 42 81 3 3 40 80 3 2 6000 DD 77 107 5 8 71 105 5 3 2700 79 105 5 9 73 104 5 4 67 103 5 1 2600 70 100 5 2 64 99 4 8 60 98 4 5 2500 62 95 4 7 57 95 4 3 53 94 4 1 2400 54 91 4 2 51 90 3 9 48 89 3 7 2300 48 86 387 45 85 3 3 42 84 3 4 800 0 2700 74 104 5 5 68 103 5 1 63 102 4 8 2600 65 99 4 9 60 99 4 6 57 98 4 3 2500 58 95 4 4 54 94 4 1 51 93 3 9 2400 52 90 4 0 48 89 3 7 45 88 3 5 2300 46 85 3 6 43 84 3 4 40 82 3 2 10000 2700 69 103 5 2 64 102 4 8 59 102 4 5 2600 61 99 4 6 57 98 4 3 53 97 4 1 2500 55 94 4 2 51 93 3 9 48 92 3 7 2400 49 89 3 8 45 88 3 6 43 87 3 4 12000 2650 61 100 4 6 57 99 4 3 53 98 4 1 2600 58 98 4 4 54 97 4 1 50 96 3 9 2500 52 93 4 0 48 92 3 7 45 91 9 5 2400 46 89 3 6 43 87 3 4 41 84 3 3 Figure 5 7 Cruise Performance 5 14 CESSNA SECTION 5 MODEL 150M PERFORMANCE RANGE PROFILE 45 MINUTES RESERVE 22 5 GALLONS USABLE FUEL CONDITIONS 1600 Pounds Recommended Lean Mixture for Cruise Standard Temperature Zero Wind NOTES 1 This chart allows for the fuel used for engine start taxi takeoff and climb and the distance during climb as shown in figure 5 6 2 Reserve fuel is based on 45 minutes at 4596 BHP and is 2 6 gallons 12 000 10 000 8000 ALTITUDE FEET 4000 260 300 340 380 420 460 500 RANGE NAUTICAL MILES Figure 5 8 Range Profile Sheet 1 of 2 5 15 SECTION 5 CESSNA PERFORMANCE MODEL 150M RANGE
26. 3079 EACH EACH ELECTRICAL SYSTEM 24 AMP HOUR A Ou 14 VOLT 61 9 LIGHT INSTALLATION CONTROL WHEEL LIGHT INSTALLATION OMNIFLASH BEACON BEACON LIGHT FIN FLASHER POWER SUPPLY IN AFT TAILCONE RESISTER MEMCOR LIGHT INSTALLATION WING TIP STROBE STROBE LIGHTS IN WING TIP SET 2 FLASHER POWER SUPPLIES IN TIPS SET OF TALLATIO COWL MOUNTED LANDING TALLATION COWL MOUNTED DUAL 2 21 22 85 10 73 83 37 35 39 Me OK inno B Ol tu Wn gt D INSTRUMENTS C661064 0101 0513279 C661071 0101 C661025 0102 661071 0102 D RSPEED I E a FT MARKINGS 50 FT MARKINGS LUDES RELOCATION ETER MILLIBARS CONVENTIONAL LHOIHAA 1511 LNHINdIQOH 9 NOLLOAS 91 9 ALTIMETER ENCODING ALTIMETER USE WITH TRANSPOND CT REQUIRE ie ASIE DOES n AMMETER N CLOCK INSTALLATIO CLOC ELECTRIC COMPASS CLUSTER LH FUEL amp INSTRU RH UEL RES PT TRE DICATOR TOR v ON DIRE HEADING INDICATOR CATOR EWS TIONA EWS 05 0 E07 S E07 0 9 L INDICATOR I POINTER EQUIPMENT LIST DESCRIPTION _ wriss C669512 0103 0413466 1 661075 C661076
27. ALTITUDE ENCODER BLIND SUPPLEMENT SECTION 2 LIMITATIONS There is no change to the airplane limitations when this avionic equip ment is installed However a placard labeled ALTITUDE ENCODER EQUIPPED must be installed near the altimeter SECTION 3 EMERGENCY PROCEDURES TO TRANSMIT AN EMERGENCY SIGNAL 1 Function Switch ON Q Reply Code Selector Knobs SELECT 7700 operating code 3 ID Switch DEPRESS then RELEASE to effect immediate identi fication of aircraft ground controllers display TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Function Switch ON Q Reply Code Selector Knobs SELECT 7700 operating code for 1 minute then SELECT 7600 operating code for 15 minutes and then REPEAT this procedure at same intervals for remainder of flight 3 ID Switch DEPRESS then RELEASE at intervals to effect immediate identification of aircraft on ground controller s display SECTION 4 NORMAL PROCEDURES BEFORE TAKEOFF 1 Function Switch SBY TO TRANSMIT MODE A AIRCRAFT IDENTIFICATION CODES IN FLIGHT 1 Reply Code Selector Knobs SELECT assigned code PILOT S OPERATING HANDBOOK CESSNA 300 TRANSPONDER SUPPLEMENT AND ALTITUDE ENCODER BLIND 2 Function Switch ON 3 DIM Control ADJUST light brilliance of reply lamp NOTE During normal operation with function switch in ON posi tion reply lamp flashes indicating transponder re
28. Applica tion of recovery controls will produce prompt recoveries of from 1 4 to 1 2 of a turn Ifthe spin is continued beyond the 2 to 3 turn range some change in character of the spin may be noted Rotation rates may vary and some additional sideslip may be felt Normal recoveries from such extended spins may take up to a full turn or more Regardless of how many turns the spin is held or how it is entered the following recovery technique should be used 1 VERIFY THAT THROTTLE IS IN IDLE POSITION AND AILERONS ARE NEUTRAL 2 APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIREC TION OF ROTATION CESSNA SECTION 4 MODEL 150M NORMAL PROCEDURES 3 JUST AFTER THE RUDDER REACHES THE STOP MOVE THE CONTROL WHEEL BRISKLY FORWARD FAR ENOUGH TO BREAK THE STALL Full down elevator may be required at aft center of gravity loadings to assure optimum recoveries 4 HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS Premature relaxation of the control inputs may extend the recovery 5 AS ROTATION STOPS NEUTRALIZE RUDDER AND MAKE A SMOOTH RECOVERY FROM THE RESULTING DIVE NOTE If disorientation precludes a visual determination of the direction of rotation the symbolic airplane in the turn coordinator or the needle of the turn and bank indicator may be referred to for this information Variations in basic airplane rigging or in weight and balance due to installed equipment or cockpit occupancy can cause differences in behavior particu
29. CESSNA 400 TRANSPONDER AND ENCODING ALTIMETER PILOT S T Figure 1 Cessna 400 Transponder and Encoding Altimeter Operating Controls Sheet 1 of 2 PILOT S OPERATING HANDBOOK CESSNA 400 TRANSPONDER SUPPLEMENT AND ENCODING ALTIMETER 9 x 11 12 13 FUNCTION SWITCH Controls application of power and selects transponder operating mode as follows OFF Turns set off SBY Turns set on for equipment warm up or standby power ON Turns set on and enables transponder to transmit Mode A aircraft identification reply pulses ALT Turns set on and enables transponder to transmit either Mode A aircraft identification reply pulses or Mode C altitude reporting pulses selected automatically by the interrogating signal REPLY LAMP Lamp flashes to indicate transmission of reply pulses glows steadily to indicate transmission of IDENT pulse or satisfactory self test operation Reply Lamp will also glow steadily during initial warm up period IDENT JD SWITCH When depressed selects special pulse identifier to be transmitted with transponder reply to effect immediate identification of air craft on ground controller s display Reply Lamp will glow steadily during duration of IDENT pulse transmission DIMMER DIM CONTROL Allows pilot to control brilliance of Reply Lamp SELF TEST TST SWITCH When depressed causes transponder to gen erate a self interrogating signal to provide a check of transponder ope
30. Elevator Control LIFT NOSE WHEEL at 50 KIAS 5 Climb speed 60 70 KIAS SHORT FIELD TAKEOFF 1 Wing Flaps 0 2 Prop Lever FORWARD Above 300 ft AAL reduce RPM to 2260 3 Carburetor Heat COLD 4 Brakes APPLY 5 Throttle FULL OPEN 6 Brakes RELEASE 7 Elevator Control SLIGHTLY LOW 8 Climb Speed 60 KIAS With obstacles ahead ENROUTE CLIMB 1 Airspeed 65 75 KIAS NOTE If a maximum performance climb is necessary use speeds shown in the Rate Of Climb chart in Section 5 2 Throttle FULL OPEN 3 Fuel pump OFF CRUISE 1 Power 2000 RPM no more than 65 90 2 Manifold Pressure 24 65 3 Elevator Trim ADJUST BEFORE LANDING 1 Seats Belts Harnesses ADJUST and LOCK 2 Fuel Pump ON 3 Prop Lever Forward 4 Carburetor Heat ON apply full heat before closing throttle SECTION 4 NORMAL PROCEDURES LANDING NORMAL LANDING 1 Airspeed 60 70 KIAS flaps UP 2 Wing Flaps AS DESIRED below 85 KIAS 3 Airspeed 50 60 KIAS flaps DOWN 4 8 CESSNA MODEL 150M CESSNA SECTION 4 MODEL 150M NORMAL PROCEDURES 4 Touchdown MAIN WHEELS FIRST 5 Landing Roll LOWER NOSE WHEEL GENTLY 6 Braking MINIMUM REQUIRED SHORT FIELD LANDING 1 Airspeed 60 70 KIAS flaps UP 2 Wing Flaps 40 below 85 KIAS 3 Airspeed MAINTAIN 52 KIAS 4 Power REDUCE to idle as obstacle is cleared
31. Integrated seat belt shoulder harnesses with inertia reels are avail able for the pilot and front seat passenger The seat belt shoulder har nesses extend from inertia reels located in the upper cabin sidewall just aft of each cabin door to attach points outboard of the front seats separate seat belt half and buckle is located inboard of the seats Inertia reels allow complete freedom of body movement However in the event of a sudden deceleration they will lock automatically to protect the occupants To use the seat belt shoulder harness position the adjustable metal link on the harness at about shoulder level pull the link and harness downward and insert the link in the seat belt buckle Adjust belt tension across the lap by pulling upward on the shoulder harness Removal is ac complished by releasing the seat belt buckle which will allow the inertia reel to pull the harness outboard of the seat 7 13 SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M ENTRANCE DOORS AND CABIN WINDOWS Entry to and exit from the airplane is accomplished through either of two entry doors one on each side of the cabin refer to Section 6 for cabin and cabin door dimensions The doors incorporate a recessed ex terior and interior door handle a key operated door lock left door only a door stop mechanism and an openable window To open the doors from outside the airplane utilize the recessed door handle near the aft edge of ea
32. MEGA HERTZ SELECTOR Selects communication receiver transmitter frac tional frequency in 05 MHz steps between 000 and 950 MHz or be Mcd and 975 MHz depending on position of 50 25 MHz selector switc Figure 1 Cessna 300 Nav Com RT 328T Sheet 1 of2 PILOT S OPERATING HANDBOOK CESSNA 300 NAV COM SUPPLEMENT TYPE RT 328T 10 11 12 13 14 15 16 17 18 19 20 50 25 FRACTIONAL MHz SELECTOR SWITCH In 50 position enables communication whole MHz frequency readout to display and communication fractional MHz control to select fractional part of frequency in 05 MHz steps between 000 and 950 MHz In 25 position frequency display and coverage is in 05 MHz steps between 025 and 975 NOTE The third decimal place digit is not shown on the receiver transmitter frequency readout NAVIGATION RECEIVER MEGAHERTZ SELECTOR Selects navigation receiver frequency in 1 MHz steps between 108 and 117 MHz simultaneously selects paired glide slope frequency or DME channel NAVIGATION RECEIVER VOLUME CONTROL Controls volume of audio from navigation receiver only Clockwise rotation increases audio level NAVIGATION RECEIVER FRACTIONAL MEGAHERTZ SELECTOR Selects navigation receiver frequency in 05 MHz steps between 00 and 95 MHz simultaneously paired glide slope frequency or DME channel COMBINED IDENTIFIER SIGNAL SELECTOR AND VOR SELF TEST SELECTOR SWITCH ID T SWI
33. MODEL 150M amp MAINTENANCE CLEANING AND CARE WINDSHIELD WINDOWS The plastic windshield and windows should be cleaned with an aircraft windshield cleaner Apply the cleaner sparingly with soft cloths and rub with moderate pressure until all dirt oil scum and bug stains are re moved Allow the cleaner to dry then wipe it off with soft flannel cloths If a windshield cleaner is not available the plastic can be cleaned with soft cloths moistened with Stoddard solvent to remove oil and grease 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 ma terials will attack the plastic and may cause it to craze Follow by carefully washing with a mild detergent and plenty of water Rinse thoroughly then dry with a clean moist chamois Do not rub the plastic with a dry cloth since this builds up an electrostatic charge which attracts dust Waxing with a good commercial wax will finish the clean ing job A thin even coat of wax polished out by hand with clean soft flannel cloths will fill in minor scratches and help prevent further scratching Do not use a canvas cover on the windshield unless freezing rain or sleet is anticipated since the cover may scratch the plastic surface PAINTED SURFACES The painted exterior surfaces of your new Cessna have a durable long lasting finish and under normal conditions requir
34. RECEPTACLE Connection to antenna mounted on top of the tailcone Figure 1 ELT Control Panel SECTION 3 EMERGENCY PROCEDURES Immediately after a forced landing where emergency assistance is re quired the ELT should be utilized as follows 1 ENSURE ELT ACTIVATION Turn a radio transceiver and select 121 5 MHz Ifthe ELT can be heard transmitting it was ac tivated by g switch and is functioning properly If no emergen cy tone is audible gain access to the ELT and place the function se PILOT S OPERATING HANDBOOK EMERGENCY LOCATOR SUPPLEMENT TRANSMITTER ELT lector switch in the ON position 2 PRIOR TO SIGHTING RESCUE AIRCRAFT Conserve airplane battery Do not activate radio transceiver 3 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 a frequency of 121 5 MHz If no contact is established return the function selector switch to ON immediately 4 FOLLOWING RESCUE Place ELT function selector switch in the OFF position terminating emergency transmissions SECTION 4 NORMAL PROCEDURES As long as the function selector switch remains in the ARM position the ELT automatically activates following an impact of 5g or more over a short period of time Following a lightning strike or an exceptionally hard landing the ELT may activate although no emergency exi
35. T Switch a Identify Station SET to ID to hear navigation station identifier Morse Code signal b Filter Out Station Identifier Signal SET to CENTER unmarked position to include filter in audio circuit 60 OBS Knob SELECT desired course TO SELF TEST VOR NAVIGATION CIRCUITS 1 COM OFF VOL Control TURN ON 2 Frequency Selector Switches SELECT usable VOR station signal 3 OBS Knob SET for 0 course at index CDI pointer centers or deflects left or right depending on bearing of signal OFF TO FROM indicator shows TO or FROM 4 ID T Switch PRESS to T and HOLD at T CDI pointer should center and OFF TO FROM indicator should show FROM 5 OBS Knob TURN to displace course approximately 10 to either side of 0 while holding ID T switch at T CDI pointer should deflect full scale in direction corresponding to course dis placement OFF TO FROM indicator should still show FROM NOTE This test does not fulfill the requirements of FAR 91 25 SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mount ed antenna or several related external antennas will result in a minor reduction in cruise performance 5 6 blank OPERATING HANDBOOK CESSNA 300 ADF TYPE R 546E SUPPLEMENT CESSNA 300 ADF Type R 546E SECTION 1 GENERAL The Cessna 300 ADF is a panel mou
36. are also provided A comprehensive list of all Cessna equipment available for this airplane is included at the back of this section It should be noted that specific information regarding the weight arm moment and installed equipment list for this airplane can only be found in the appropriate weight and balance records carried in the airplane AIRPLANE WEIGHING PROCEDURES 1 Preparation a Inflate tires to recommended operating pressures b Remove the fuel tank sump quick drain fittings and fuel line drain plug to drain all fuel c Remove oil sump drain plug to drain all oil d Move sliding seats to the most forward position e Raise flaps to the fully retracted position 2 Leveling a Place scales under each wheel 5008 minimum capacity for scales b Deflate nose tire and or lower or raise the nose strut to center bubble on level see Figure 6 1 3 Weighing a With the airplane level and brakes released record the weight shown on each scale Deduct the tare if any from each reading 4 Measuring a Obtain measurement by measuring horizontally along the airplane center line from a line stretched between the main wheel centers to a plumb bob dropped from the firewall b Obtain measurement B by measuring horizontally and par allel to the airplane center line from center of nose wheel axle left side to a plumb bob dropped from the line between the main wheel centers Repeat on right side and average t
37. are listed below CUSTOMER CARE PROGRAM BOOK PILOT S OPERATING HANDBOOK SUPPLEMENTS FOR YOUR AIRPLANE AVIONICS PILOT S CHECKLISTS POWER COMPUTER SALES AND SERVICE DEALER DIRECTORY DO S AND DON TS ENGINE BOOKLET The following additional publications plus many other supplies that are applicable to your airplane are available from your Cessna Dealer SERVICE MANUALS AND PARTS CATALOGS FOR YOUR AIRPLANE ENGINE AND ACCESSORIES AVIONICS Your Cessna Dealer has a Customer Care Supplies Catalog covering all available items many of which he keeps on hand will be happy to place an order for any item which is not in stock AIRPLANE FILE There are miscellaneous data information and licenses that are a part of the airplane file The following is a checklist for that file In addition a periodic check should be made of the latest Federal Aviation Regulations to ensure that all data requirements are met A To be displayed in the airplane at all times 1 Aircraft Airworthiness Certificate FAA Form 8100 2 2 Aircraft Registration Certificate FAA Form 8050 3 3 Aircraft Radio Station License if transmitter installed FCC Form 556 B To be carried in the airplane at all times d Weight and Balance and associated papers latest copy of the Repair and Alteration Form FAA Form 337 if applicable 2 Equipment List 8 4 CESSNA SECTION 8 MODEL 150M HANDLING SERVICE amp MAINTENANCE C To be made available u
38. at 4596 BHP and is 2 6 gallons 12 000 10 000 s000 E E FH HHE HHHH HHHH peg Hirn HH 6000 ALTITUDE FEET 4000 2000 HH ENDURANCE HOURS o Figure 5 9 Endurance Profile Sheet 2 of 2 5 18 Ouemq 05 6 6 6 LANDING DISTANCE SHORT FIELD CONDITIONS Flaps 40 Power Off Maximum Braking Paved Level Dry Runway ZeroWind NOTES 1 Short field technique as specified in Section 4 2 Decrease distances 10 for each 9 knots headwind For operation with tailwinds up to 10 knots increase distances by 1096 for each 2 knots 3 For operation on a dry grass runway increase distances by 45 of the ground roll figure Figure 5 10 Landing Distance WOST THGOIN VNSSHO NOLLOHS CESSNA SECTION 6 MODEL 150M WEIGHT amp BALANCE SECTION 6 WEIGHT amp BALANCE EQUIPMENT LIST EQUIPMENT LIST TABLE OF CONTENTS Page Wn METTE 6 3 Airplane Weighing Procedures 6 3 Weight and Balance 4 6 6 Equipment List 2 4 6 13 6 1 6 2 blank CESSNA SECTION 6 MODEL 150M WEIGHT amp EQUIPMENT LIST INTRODUCTION This section describes the procedure for establishing the basic empty weight and moment of the airplane Sample forms are provided for refer ence Procedures for calculating the weight and moment for various oper ations
39. attached to the nose wheel When towing with a vehicle do not exceed the nose gear turning angle of 30 either side of center or damage to the gear will result If the airplane is towed or pushed over a rough surface during hangaring watch that the normal cushioning action of the nose strut does not cause excessive vertical movement of the tail and the resulting contact with low hangar doors or structure flat nose tire or deflated strut will also increase tail height PARKING When parking the airplane head into the wind and set the parking brakes o not set the parking brakes during cold weather when accumu 8 7 8 CESSNA HANDLING SERVICE MODEL 150M amp MAINTENANCE lated moisture may freeze the brakes or when the brakes are overheated install the control wheel lock and chock the wheels In severe weather and high wind conditions tie the airplane down as outlined in the follow ing paragraph TIE DOWN Proper tie down procedure is the best precaution against damage to the parked airplane by gusty or strong winds tie down the airplane securely proceed as follows 1 Setthe parking brake and install the control wheel lock 2 Install a surface control lock between each aileron and flap 3 Tie sufficiently strong ropes chains 700 pounds tensile strength to the wing and tail tie down fittings and secure each rope to a ramp tie down 4 Install a surface control lock over the fin and rudder
40. ground roll 990 feet x 13 129 Corrected ground roll 861 Feet Total distance to clear a 50 foot obstacle zero wind 1865 Decrease in total distance 1865 feet 13 242 Corrected total distance to clear 50 foot obstacle 1623 Feet 5 4 CESSNA SECTION 5 MODEL 150M PERFORMANCE CRUISE The cruising altitude should be selected based on a consideration of trip length winds aloft and the airplane s performance A typical cruising altitude and the expected wind enroute have been given for this sample problem However the power setting selection for cruise must be determined based on several considerations These include the cruise performance characteristics presented in figure 5 7 the range profile chart presented in figure 5 8 and the endurance profile chart presented in figure 5 9 The relationship between power and range is illustrated by the range profile chart Considerable fuel savings and longer range result when lower power settings are used The range profile chart indicates that use of 6096 power at 5500 feet yields a predicted range of 385 nautical miles under no wind condi tions The endurance profile chart figure 5 9 shows a corresponding 4 hours The range figure of 385 nautical miles is corrected to account for the expected 10 knot headwind at 5500 feet Range zero wind 385 Decrease in range due to wind 4 1 hours x 10 knot headwind 41 Corrected range 344 Nautical Miles This indicates that the tr
41. is changed Stall speeds for various combinations of flap setting and bank angle are summarized in Section 5 SPINS Intentional spins are approved in this airplane see Section 2 Before attempting to perform spins however several items should be carefully considered to assure a Safe flight No spins should be attempted without first having received dual instruction in both spin entries and spin recov eries from a qualified instructor who is familiar with the spin character istics of the Cessna 150M The cabin should be clean and all loose equipment including the micro phone should be stowed For a solo flight in which spins will be conducted the copilot s seat belt and shoulder harness should be secured Spins with baggage loadings or occupied child s seat are not approved The seat belts and shoulder harnesses should be adjusted to provide proper restraint during all anticipated flight conditions However care 4 17 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 150M should be taken to ensure that the pilot can easily reach the flight controls and produce maximum control travels It is recommended that where feasible entries be accomplished at high enough altitude that recoveries are completed 4000 feet or more above ground level At least 1000 feet of altitude loss should be allowed for a l turn spin and recovery while a 6 turn spin and recovery may re quire somewhat more than twice that amount For example the recom mend
42. 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 Total the weights and moments 1000 and plot these values on the Center of Gravity Moment Envelope to determine whether the point falls within the envelope and if the loading is acceptable 6 6 CESSNA SECTION 6 MODEL 150M WEIGHT amp EQUIPMENT LIST LOADING ARRANGEMENTS STATION Pilot or passenger center of STATION gravity on adjustable seats ARM positioned for average occu ant Numbers in parentheses indicate forward and ait limits of occupant center of gravity range 39 33 41 Arms measured to the center of the areas shown 64 AREA NOTE The aft baggage wall approx imate station 94 can be used 84 AREA 2 as convenient interior refer IO poini tpr determining thg lt 94 stations RENS E STANDARD OPTIONAL SEATING SEATING Figure 6 3 Loading Arrangements BAGGAGE LOADING AND TIE DOWN UTILITY SHELF BAGGAGE AREA MAXIMUM ALLOWABLE LOADS Wn dieu AREA 1 120 POUNDS AREA 2 40 POUNDS MEL do mer AREAS 1 0 120 POUNDS TIE DOWN NET ATTACH POINTS A tie down net is provided to secure baggage in the baggage area The net attaches to six tie d
43. of primer for best atomization of fuel After priming push primer all the way in and turn to locked position to avoid possibility of engine drawing fuel through the primer Q Propeller Area CLEAR 3 Master Switch ON 4 Prop Lever Forward 5 Throttle OPEN 1 4 INCH 6 Ignition Switch START 7 Release ignition switch to BOTH when engine starts 8 Pressure CHECK Without Preheat 1 Prime the engine eight to ten strokes while the propeller is being turned by hand with the throttle closed Leave the primer and ready for a stroke 2 Propeller Area CLEAR 3 Master Switch ON 4 Fuel Pump ON 5 Prop Lever Forward 6 Ignition Switch START 7 Pump throttle rapidly to full open twice Return to 1 4 inch open osition 8 Release ignition switch to BOTH when engine starts 9 Continue to prime engine until it is running smoothly or alter nately pun throttle over first 1 4 of total travel 10 Oil Pressure CHECK 11 Pull carburetor heat knob full on after engine has started Leave on until engine is running smoothly 12 Primer LOCK NOTE 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 been frosted over Preheat must be used before another start is attempted CAUTION Pumping the throttle may cause raw fuel to accumulate in the intake air duct creat
44. power is controlled by a throttle located on the lower center portion of the instrument panel The throttle operates in a convention al manner in the full forward position the throttle is open and in the full aft position it is closed friction lock which is a round knurled disk is located at the base of the throttle and is operated by rotating the lock clockwise to increase friction or counterclockwise to decrease it The mixture control mounted above the right corner of the control pedestal is a red knob with raised points around the circumference and is equipped with a lock button in the end of the knob The rich position is full forward and full aft is the idle cut off position For small ad justments the control may be moved forward by rotating the knob clockwise and aft by rotating the knob counterclockwise For rapid or large adjustments the knob may be moved forward or aft by depressing the lock button in the end of the control and then positioning the con trol as desired ENGINE INSTRUMENTS Engine operation is monitored by the following instruments oil pres sure gage oil temperature gage and a tachometer The oil pressure gage located on subpanel is operated by oil pressure A direct pressure oil line from the engine delivers oil at en gine operating pressure to the oil pressure gage Gage markings indicate 7 15 SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M that minimum idling
45. released it will automatically return to the B position AIR INDUCTION SYSTEM The engine air induction system receives ram air through an intake in the lower front portion ofthe engine cowling The intake is covered by an air filter which removes dust and other foreign matter from the induction air Airflow passing through the filter enters an airbox After passing through the airbox induction air enters the inlet in the carburetor which is under the engine and is then ducted to the engine cylinders through intake manifold tubes In the event carburetor 1ce is encountered or the intake filter becomes blocked alternate heated air can be obtained from the right muffler shroud through a duct to a valve in the airbox operated by the carburetor heat control on the SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M instrument panel Heated air from the muffler shroud is obtained from an unfiltered outside source Use of full carburetor heat at full throttle wilFresult in a loss of approximately 200 to 250 RPM EXHAUST SYSTEM Exhaust gas from each cylinder passes through riser assemblies to a muffler and tailpipe on each side of the engine Each muffler is con structed with a shroud around the outside which forms a heating chamber for carburetor heat and cabin heater air CARBURETOR AND PRIMING SYSTEM The engine is equipped with an up draft float type fixed jet carbu retor mounted on the bottom of the engine The car
46. sea level pressure altitude and decreases by 2 C for each 1000 feet of altitude Pressure Altitude is the altitude read from an altimeter when the altimeter s barometric scale has been set to 29 92 inches of mercury 1013 mb CESSNA SECTION 1 MODEL 150M GENERAL ENGINE POWER TERMINOLOGY BHP Brake Horsepower is the power developed by the engine RPM Revolutions Per Minute is engine speed Static Static RPM is engine speed attained during a full throttle en RPM gine runup when the airplane is on the ground and stationary AIRPLANE PERFORMANCE AND FLIGHT PLANNING TERMINOLOGY Demon Demonstrated Crosswind Velocity is the velocity of the cross strated wind component for which adequate control of the airplane Crosswind during takeoff and landing was actually demonstrated during Velocity certification tests The value shown is not considered to be limiting Usable Fuel Usable Fuel is the fuel available for flight planning Unusable Unusable Fuel is the quantity of fuel that can not be safely Fuel used in flight GPH Gallons Per Hour is the amount of fuel in gallons consumed per hour NMPG Nautical Miles Per Gallon is the distance in nautical miles which can be expected per gallon of fuel consumed at a spe cifie engine power setting and or flight configuration g gis acceleration due to gravity WEIGHT AND BALANCE TERMINOLOGY Reference Reference Datum is an imaginary vertical plane from which Datum
47. wing tip is 24 8 Figure 1 1 Three View 1 2 CESSNA SECTION 1 MODEL 150M GENERAL INTRODUCTION This handbook contains 9 sections and includes the material required to be furnished to the pilot by CAR Part 3 It also contains supplemental data supplied by Cessna Aircraft Company Section 1 provides basic data and information of general interest It also contains d finitions or explanations of symbols abbreviations and terminology commonly used DESCRIPTIVE DATA ENGINE Number of Engines 1 Engine Manufacturer Bombardier Rotax Model Number 912S3 Engine Type Normally aspirated gearbox driven combined air and liquid cooled horizontally opposed carburetor equipped four cylinder engine with 1 3 L displacement Horsepower Rating and Engine Speed 100 rated BHP at 5800 RPM 2385 prop RPM PROPELLER Propeller Manufacturer Hoffmann Propeller GmbH Propeller Model Number HO V352F 170FQ 10 Number of Blades 2 Propeller Diameter 180 CM Propeller Type Constant speed FUEL Approved Fuel Grades and Colors 95 Grade Automotive Fuel EN 228 Green 100LL Grade Aviation Fuel Blue SECTION 1 CESSNA GENERAL MODEL 150M Fuel Capacity Long Range Tanks Total Capacity 144 liters Total Capacity Each Tank 72 liters Total Usable 132 liters NOTE Due to cross feeding between fuel tanks the tanks should be re topped after each refueling to assure maximum capacity OIL Oil Grade Spe
48. 0413466 1201126 C661076 401019 C668507 0101 _ eo ococmw hN S NNNNN OUM N SRNO LSIT LNHWdIQOH X 1 WOSI IHGOIN VNSSHO 9 NOLLOHS xz S 1413N2 661080 0101 BLY N ASSEMBLY LAP BELT 551 uh AT ini B ACCOMMCOATIII NS 51 AANAND LOLOLOLOCOQI SE CO e no dq e Io La Oooo Too DESANN 5939520 eooooooo0 S Sa 2 EU m 2 mc a AW LLO aa m On EA gt H EXEA gt H HOE i OFF AE DO POF OgErDOAgETDmWmmonmcxDOUHZz dsgp Ue Ou 4 Q HALOL ato no H HHH gt 11 9 EQUIPMENTLISTDESCRIPTION wres aruns lt 20000 OT INSTL PILOT amp ASSY CO PILOT TOP INCREASE E OF 2 15 SET OF 4 NET CHANGE LF N UTILITY BAGGAGE NET DUAL CONTROLS WHEEL PEDALS TOE BRAKES HEATING SYSTEM CABIN CARBURETOR AIR INCLUDES EXHAUST SYSTEM 20020 EU Mot gt niri OOMOMATWHN OONCC ooo Dan F PLACARDS 6 WARNING OPERATIONAL LIMITATIONS PLACARD VFR 1FR INDICATOR STALL WARNING AUDIBLE G AUXILIARY EQUIPMENT N I OOD e Oo OOOoooo TS KHEE
49. 150M EMERGENCY PROCEDURES FORCED LANDINGS EMERGENCY LANDING WITH ENGINE RUNNING Before touchdown when field identified 1 Airspeed 65 KIAS flaps UP 55 KIAS flaps DOWN 2 Throttle AS REQUIRED 3 Prop Pitch FINE full forward 4 Wing Flaps AS REQUIRED 5 Cabin Doors UNLATCH PRIOR TO TOUCHDOWN 6 Safety Harness TIGHTEN When landing is safe 7 Touchdown SLIGHTLY TAIL LOW 8 Brakes APPLY HEAVILY 9 Throttle IDLE 10 Fuel Shutoff Valve OFF 11 Master Switch OFF 12 Ignition Switch OFF EMERGENCY LANDING WITHOUT ENGINE POWER 1 Airspeed 65 KIAS flaps UP 55 KIAS flaps DOWN 2 Cabin Doors UNLATCH PRIOR TO TOUCHDOWN 3 Safety Harness TIGHTEN 4 Wing Flaps AS REQUIRED 5 Master Switch OFF 6 Fuel Shutoff Valve OFF 7 Ignition Switch OFF PRECAUTIONARY LANDING WITH ENGINE POWER Before landing off an airfield slowly fly over the selected field and check the obstructions and the texture If the field is suitable land following the given procedure CESSNA SECTION 3 MODEL 150M EMERGENCY PROCEDURES 1 Airspeed 65 KIAS flaps UP 55 KIAS flaps DOWN 2 Throttle AS REQUIRED 3 Prop Pitch FINE full forward 4 Wing Flaps AS REQUIRED 5 Cabin Doors UNLATCH PRIOR TO TOUCHDOWN 6 Safety Harness TIGHTEN 7 Fuel Shutoff Valve OFF 8 Master Switch OFF 9 Ignition Switch OFF 3 6 CESS
50. 96 alcohol is harmful and should be avoided While applying the de icing solution keep it away from the windshield and cabin windows since the alcohol will attack the plastic and may cause it to craze PROPELLER CARE Preflight inspection of propeller blades for nicks and wiping them occasionally with an oily cloth to clean off grass and bug stains will as sure long trouble free service Small nicks on the propeller particu larly near the tips and on the leading edges should be dressed out as soon as possible since these nicks produce stress concentrations and if ignored may result in cracks Never use an alkaline cleaner on the blades remove grease and dirt with carbon tetrachloride or Stoddard solvent ENGINE CARE The engine may be cleaned with Stoddard solvent or equivalent then dried thoroughly CAUTION Particular care should be given to electrical equipment before cleaning Cleaning fluids should not be allowed to enter magnetos starter alternator and the like Protect these components before saturating the engine with solvents other openings should also be covered before cleaning the engine assembly Caustic cleaning solutions should be used cautiously and should always be properly neutralized after their use INTERIOR CARE To remove dust and loose dirt from the upholstery and carpet clean the interior regularly with a vacuum cleaner 8 13 SECTION 8 CESSNA HANDLING SERVICE MODEL 150M amp MAINTENAN
51. CAVOK CAVOK Aviation Training Ltd Pilot Operating Book Cessna C150M HA VOF PILOTS OPERATING HANDBOOK Cem 1976 SPECIFICATIONS CESSNA MODEL 150M PERFORMANCE SPECIFICATIONS SPEED Maximum 2000 Ft Cruise 7596 Power at 6000 Ft CRUISE Recommended cruise settings 7596 Power at 2000 Ft Range 35 Gallons Usable Fuel Time Maximum Range at 6 000 Ft Range 35 Gallons Usable Fuel Time RATE OF CLIMB AT SEA LEVEL SERVICE CEILING TAKEOFF PERFORMANCE Ground Roll Total Distance Over 15 M Obstacle LANDING PERFORMANCE Ground Roll Total Distance Over 15 M Obstacle STALL SPEED CAS Flaps Up Power Off Flaps Down Power Off MAXIMUM WEIGHT STANDARD EMPTY WEIGHT Commuter MAXIMUM USEFUL LOAD Commuter BAGGAGE ALLOWANCE aua WING LOADING Pounds Sq Ft POWER LOADING Pounds HP FUEL CAPACITY Total Long Range Tanks OIL CAPACITY ENGINE Bombardier Rotax 100 at 2385 prop RPM PROPELLER Constant Speed Diameter D1080 13 RPC 6 000 12 77 98 KNOTS 95 KNOTS 658 NM 7 2 HRS 657 NM 7 9 HRS 720 FPM 15 000 FT 158 314M 136M 328 47 KNOTS 42 KNOTS 726 KG 515 5 KG 210 5 KG 54 KG 10 0 16 0 1441 3 51 912 53 180 PILOTS OPERATING HANDBOOK Cessna 150 COMMUTER 1976 MODEL 150M Serial No Registration No THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PIL
52. CE Blot up any spilled liquid promptly with cleansing tissue or rags Don t pat the spot press the blotting material firmly and hold it for sev eral seconds Continue blotting until no more liquid is taken up Scrape off stickly materials with a dull knife then spot clean the area Oily spots may be cleaned with household spot removers used spar ingly Before using any solvent read the instructions on the container and test it on an obscure place on the fabric to be cleaned Never satu rate the fabric with a volatile solvent it may damage the padding and backing materials Soiled upholstery and carpet may be cleaned with foam type detergent used according to the manufacturer s instructions To minimize wetting the fabric keep the foam as dry as possible and remove it with a vacuum cleaner The plastic trim headliner instrument panel and control knobs need only be wiped off with a damp cloth Oil and grease on the control wheel and control knobs can be removed with a cloth moistened withStoddard solvent Volatile solvents such as mentioned in paragraphs care of the windshield must be never be used since they soften and craze the plastic CESSNA SECTION 9 MODEL 150M SUPPLEMENTS SECTION 9 SUPPLEMENTS Optional Systems Description amp Operating Procedures TABLE OF CONTENTS Introduction Supplements Emergency Locator Transmitted ELT Cessna 300 Nav Com Type RT 308C Cessna 300 Nav Com Type RT 328
53. E amp SYSTEMS DESCRIPTIONS MODEL 150M The transmitter selector switch is labeled TRANS and has two posi tions When two transmitters are installed it is necessary to switch the microphone to the radio unit the pilot desires to use for transmission This is accomplished by placing the transmitter selector switch in the position corresponding to the radio unit which is to be used The up posi tion selects the upper transmitter and the down position selects the lower transmitter The installation of Cessna radio equipment provides certain audio back up capabilities and transmitter selector switch functions that the pilot should be familiar with When the transmitter selector switch is placed in the No 1 or No 2 position the audio amplifier of the corres ponding transceiver is utilized to provide the speaker audio for all radios If the audio amplifier in the selected transceiver fails as evidenced by loss of speaker audio for all radios place the transmitter selector switch in the other transceiver position Since an audio amplifier is not utilized for headphones malfunctioning amplifier will not affect headphone oper ation The speaker phone switches determine whether the output of the re ceiver in use is fed to the headphones or through the audio amplifier to the speaker Place the switch for the desired receiving system either in the up position for speaker operation or in the down position for head phones The center OFF posit
54. ECTION 4 CESSNA NORMAL PROCEDURES MODEL 150M 3 Propeller and Spinner CHECK for nicks and security 4 Carburetor Air Filter CHECK for restrictions by dust or other foreign matter 5 Landing Light s CHECK for condition and cleanliness 6 Nose heel Strut and Tire CHECK for proper inflation 7 Nose Tie Down DISCONNECT 8 Static Source Opening left side of fuselage CHECK for stoppage 6 LEFT WING 1 Main Wheel Tire CHECK for proper inflation 2 Before first flight of day and after each refueling use sampler cup and drain small quantity of fuel from fuel tank sump quick drain valve to check for water sediment and proper fuel grade 3 Fuel Quantity CHECK VISUALLY for desired level 4 Fuel Filler Cap SECURE 7 LEFT WING Leading Edge 1 Pitot Tube Cover REMOVE and check opening for stoppage 2 Stall Warning Opening CHECK for stoppage To check the system place a clean handkerchief over the vent opening and apply suction a sound from the warning horn will confirm sys tem operation 3 Fuel Tank Vent Opening CHECK for stoppage 4 Wing Tie Down DISCONNECT 8 LEFT WING Trailing Edge 1 Aileron CHECK freedom of movement and security BEFORE STARTING ENGINE 4 6 1 Preflight Inspection COMPLETE 2 Seats Belts Shoulder Harnesses ADJUST and LOCK 3 Fuel Shutoff Valve ON 4 Radios Electrical Equipment OFF 5 Brakes TE
55. F CONTENTS Page Introduction 6 3353 Airspeeds For Emergency Operation 3 3 OPERATIONAL CHECKLISTS Engine Failures 3 3 Engine Failure During Takeoff 3 3 Engine Failure Immediately After Takeoff 3 3 Engine Failure During Flight 3 4 Forced Landings 34 Emergency Landing Without Engine Power 3 4 Precautionary Landing With Engine Power 3 4 Ditching NE 3 4 Fires 3 5 During Start On Ground 3 5 Engine Fire in Flight M 3 5 Electrical Fire In Flight 3 6 Cabin Fire 3 6 Wing Fire 3 7 Icing 3 7 Inadvertent Icing Encounter 3 7 Landing With a Flat Main Tire 3 8 Electrical Power Supply System Malfunctions 3 8 Over Voltage Light Illuminates 3 8 Ammeter Shows Discharge 3 8 AMPLIFIED PROCEDURES Engine Failure 2 2 2 2 2 2 39 Forced Landings oh ah ROL Landing Without Elevator Control 3 0 n ge hee Atala Weed 3 1 SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS Continued Emergency Operation In Clouds Vacuum System Failure Executing A 180 Turn In Clouds Emergency Descent Through Clouds Recovery From a Spiral Dive Flight In Icing Conditions Spins o L Rough Engine Operation Or Loss Of Power Carburetor Icing uon cp Spark Plug Fouling Magneto Malfunction Low Oil Pressure Electrical Power Supply System Malfunction
56. HINdIQOH 9 NOILOHS SECTION 6 CESSNA WEIGHT amp BALANCE MODEL 150M EQUIPMENT LIST 6 Basic Empty Weight may be determined by completing Figure 6 1 WEIGHT AND BALANCE The following information will enable you to operate your Cessna within the prescribed weight and center of gravity limitations To figure weight and balance use the Sample Problem Loading Graph and Center of Gravity Moment Envelope as follows Take the basic empty weight and moment from appropriate weight and balance records carried 1n your airplane and enter them in the column titled YOUR AIRPLANE on the Sample Loading Problem NOTE In addition to the basic 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 1000 and this value used as the moment 1000 on the loading problem Use the Loading Graph to determine the moment 1000 for each addi tional item to be carried then list these on the loading problem NOTE Loading Graph information for the pilot passengers and baggage is based on seats positioned for average occu pants and baggage loaded in the center of the baggage 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 area
57. II S TAKEOFF DISTANCE 5 iv SHORT FIELD tr CONDITIONS T Flaps Up Full Throttle Prior to Brake Release gt Paved Level Dry Runway lt Zero Wind NOTES 1 Short field technique as specified in Section 4 2 Prior to takeoff from fields above 5000 feet elevation the mixture should be leaned to give maximum RPM ina full throttle static runup 3 Decrease distances 10 for each 9 knots headwind For operation with tailwinds up to 10 knots increase distances by 10 foreach 2 knots 4 Where distance value has been deleted climb performance after lift off is less than 150fpm at takeoff speed 5 For operation ona dry grass runway increase distances by 15 of the ground roll figure TAKEOFF SPEED ete KIAS LIFT AT rt 50 FT 1600 53 tri Z gt 2 Figure 5 4 Takeoff Distance VNSSHO NOILOHS SECTION 5 CESSNA PERFORMANCE MODEL 150M RATE OF CLIMB maximum CONDITIONS Flaps Up Full Throttle WEIGHT PRESS CLIMB SPEED RATE OF CLIMB FPM LBS ALT KIAS FT 20 C 09C 209C 40 1600 SL 68 770 710 655 595 2000 67 675 615 560 500 4000 65 580 520 465 105 6000 64 485 430 375 310 8000 63 390 335 280 215 10 000 62 295 240 185 12 000 61 200 150 Figure 5 5 Rate of Climb 5 12 CESSNA MODEL 150M TIME FUEL AND DISTANCE TO CLIMB CONDITIONS Flaps Up Full Throttle Standard Temperature NOTES SECTION 5 PERFORMA
58. INED PERSONNEL to provide you with courteous expert service FACTORY APPROVED SERVICE EQUIPMENT to provide you efficient and accurate workmanship A STOCK OF GENUINE CESSNA SERVICE PARTS on hand when you need them THE LATEST AUTHORITATIVE INFORMATION FOR SERVICING CESSNA AIRPLANES since Cessna Dealers have all of the Service Manuals and Parts Catalogs kept current by Service Letters and Service News Letters published by Cessna Aircraft Company We urge all Cessna owners to use the Cessna Dealer Organization to the fullest A current Cessna Dealer Directory accompanies your new airplane The Directory is revised frequently and a current copy can be obtained from your Cessna Dealer Make your Directory one of your cross country flight planning aids a warm welcome awaits you at every Cessna Dealer CESSNA TABLE OF CONTENTS MODEL 150M TABLE OF CONTENTS SECTION GENERAL LIMITATIONS 402 EMERGENCY PROCEDURES 3 NORMAL PROCEDURES 4 PERFORMANCE 5 WEIGHT amp BALANCE EQUIPMENT UST 4 6 AIRPLANE amp SYSTEMS DESCRIPTIONS 7 AIRPLANE HANDLING SERVICE amp MAINTENANCE 8 SUPPLEMENTS Optional Systems Description amp Operating Procedures 9 This handbook will be kept current by Service Letters published by Cessna Aircraft Company These are distributed to Cessna Dealers and to those who subscribe through the Owner Follow Up System If you are
59. ING SELECTOR OBS Selects desired course to or from a VOR station BACK COURSE BC INDICATOR LIGHT On IN 514B Only Not used with this radio BEARING DIAL Rotated by OBS to select course at index COURSE INDEX Indicates selected VOR course Figure 1 Cessna 300 Nav Com Type RT 308C VOR only Sheet 2 of 2 CESSNA 300 NAV COM PILOT S OPERATING HANDBOOK TYPE RT 308C SUPPLEMENT SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when this avionic equipment is installed SECTION 4 NORMAL PROCEDURES COMMUNICATIONS TRANSCEIVER OPERATION D OFF VOL Control TURN ON and adjust to desired listening evel XMTR SEL Switch SET to desired transceiver 3 SPEAKER PHONE or AUTO Switch SET to desired mode 9 COM Frequency Selector Knobs SELECT desired operating requency 5 SQ Control ROTATE counterclockwise to decrease background noise as required 6 Mike Button a Transmit DEPRESS and SPEAK into microphone b Receive RELEASE NAVIGATION RECEIVER OPERATION 1 COM OFF VOL Control TURN ON 2 SPEAKER PHONE or AUTO Switch SET to desired mode 3 Frequency Selector Knobs SELECT desired operating frequency 4 4 VOL Control ADJUST to desired listening level 5 OBS Knob SELECT desired course SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipmen
60. JUST to desired listening level to confirm proper localizer station When glide slope OFF flag is visible glide slope in dications are unusable SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed 3 4 blank Cessna i TAKE YOUR HOME FOR SERVICE AT THE SIGN OF THE CESSNA SHIELD CESSNA AIRCRAFT COMPANY WICHITA KANSAS
61. L STOWED XTERIOR E PASE ON RESISTANT CONTROL NET gt 0513052 16 ER HAND TYPE 0401001 gt CO NOJSNOO e CR DERE WOST THGOIN VNSSHO HONV IV8 X LHOIHA 1511 LNHINdIQOH 9 NOLLOHS 81 9 STEPS S HANDLES REFUELING ASSIST WINTERIZATION KIT INSTALLATION ENGINE COVER PLATESt FWO COWL SET OF 2 INSTALLED COVER PLATES FORWARD COWL STOWE CRANKCASE BREATHER TUBE IN RANGE FUEL TANKS SET OF 2 NET CHANGE H AVIONICS AUTOPILOTS CESSNA 300 ADF RECEIVER WITH PN IR 546E INDICATOR UN 346A ANTENNA INSTALLATION LOOP ANTENNA INSTALLATION CABLE INSTALLATION MISC INSTALLATION COMPONENTS CESSNA 400 GLIDESLOPE RECEIVER R 443B MOUNTING RIGID ANTENNA CESSNA 400 MARKER BEACON RECEIVER R 402A ANTENNA L SHAPED ROO BENDIX MARKER BEACON EXPORT USE RECEIVER ANTENNA L SHAPED ROD CESSNA 300 TRANSPONDER TRANSCEIVER RT 359A ANTENNA A 109B CESSNA 400 TR NSPONDER a UA USE N CESSNA 300 LEER ER 1ST UNIT TRANSCEIVER 524 NOTE INSTALLATION COMPONENTS ARE AS LISTED VHF ANTENNA CABLE INSTALLATION 0413456 2 0450105 2 0450409 0450409 0456004 0426008 3910159 11 3950104 14 3910157 10 42100 0000 36450 0000 1200098 2 3910142 1 42410 5114 0770681 1 3910174 1 GM 247A 077 0681 1 3910127 1 41420 1114 41530 0001 3910128 20 41470 1114 41530 0001 3910155 13 31390 1814 3960113 1
62. LEMENT TO OPERATE BFO 1 OFF VOL Control ON 2 Function Selector Knob BFO 3 Frequency Selector Knobs SELECT operating frequency 4 ADF SPEAKER PHONE Switch SELECT speaker or phone position 5 VOL Control ADJUST to desired listening level NOTE A 1000 Hz tone is heard in the audio output when a CW signal Morse Code is tuned in properly SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mount ed antenna or several related external antennas will result in a minor reduction in cruise performance 5 6 blank PILOT S OPERATING HANDBOOK CESSNA 300 TRANSPONDER SUPPLEMENT AND ENCODING ALTIMETER SUPPLEMENT CESSNA 300 TRANSPONDER Type RT 359A AND OPTIONAL ENCODING Type EA 401A SECTION 1 GENERAL The Cessna 300 Transponder Type RT 359A shown in Figure 1 is the airborne component of an Air Traffic Control Radar Beacon System ATCRBS The transponder enables the ATC ground controller to see and identify the aircraft while in flight on the control center s radar scope more readily The Cessna 300 Transponder consists of a panel mounted unit and an externally mounted antenna The transponder receives interrogating pulse signals on 1030 MHz and transmits coded pulse train reply signals on 1090 MHz It is capable of replying to Mode A aircraft identification and Mode C alti
63. MPG KTAS NMPG KTAS NMPG Sea Level 100 17 9 94 19 2 88 21 0 3500 Feet 103 18 4 97 19 8 91 21 7 7000 Feet 106 18 9 100 20 4 94 22 4 Standard Conditions Zero Wind Figure 4 3 Cruise Performance Table 4 16 CESSNA SECTION 4 MODEL 150M NORMAL PROCEDURES For best fuel economy at 65 power or less operate at the leanest mixture that results in smooth engine operation or at 50 RPM on the lean side of the peak RPM whichever occurs first This will result in approxi mately 596 greater range than shown in this handbook Carburetor ice as evidenced by an unexplained drop in RPM can be removed by application of full carburetor heat regaining the origi nal RPM with heat off use the minimum amount of heat by trial and error to prevent ice from forming Since the heated air causes a richer mixture readjust the mixture setting when carburetor heat is to be used continuously in cruise flight The use of full carburetor heat is recommended during flight in very heavy rain to avoid the possibility of engine stoppage due to excessive water ingestion The mixture setting should be readjusted for smoothest operation STALLS The stall characteristics are conventional for the flaps up and flaps down condition Slight elevator buffeting may occur just before the stall with flaps down The stall warning horn produces a steady signal 5 to 10 knots before the actual stall is reached and remains on until the airplane flight attitude
64. MS MANEUVERING SPEED IAS 97 knots GROSS WEIGHT 726kg FLIGHT LOAD FACTOR Flaps Up 44 1 76 Flaps Down 3 5 NO ACROBATIC MANEUVERS APPROVED EXCEPT THOSE LISTED BELOW Maneuver Recm Entry Speed Maneuver Recm Entry Speed Chandelles 95 knots Spins Slow Deceleration Lazy Hights 95 knots Stalls except Steep Turns 95 knots whip stalls Slow Deceleration Abrupt use of controls prohibited above 97 knots Spin Recovery opposite rudder forward elevator neutralize controls Intentional spins with flaps extended are prohibited Flight into known icing conditions prohibited This airplane is certified for the following flight operations as of date of original airworthiness certificate DAY NIGHT VFR In the baggage compartment 54kg maximum baggage and or auxiliary seat passenger For additional loading instructions see Weight and Balance Data 2 8 CESSNA SECTION 2 MODEL 150M LIMITATIONS 3 Near fuel shut off valve long range tanks FUEL 35 0 GALS ON OFF 4 Near fuel tank filler cap long range tanks FUEL 95 MIN GRADE AUTOMOTIVE FUEL AVGAS 100LL 144 liters 5 On the instrument panel near over voltage light HIGH VOLTAGE 2 9 2 10 blank CESSNA SECTION 3 MODEL 150M EMERGENCY PROCEDURES CESSNA SECTION 3 MODEL 150M EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES TABLE O
65. Mixture Control Knob Throttle With Friction Lock Microphone Elevator Trim Control Wheel Carburetor Heat Control Knob Electrical Switches Oil Pressure Gage Oil Temperature Gage Cigar Lighter Instrument Panel and Radio Dial Lights Rheostat Right Tank Fuel Quantity Indicator Ignition Switch Left Tank Fuel Quantity Indicator Master Switch Primer Parking Brake Knob WOST THHOIN VNSSHO SNOLLIdTWOSHG SWALSAS 29 HNV Id IV L NOLLOS SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M ing edge of the right half is hinged and forms the elevator trim tab The leading edge of both left and right elevator tips incorporate extensions which contain balance weights FLIGHT CONTROLS The airplane s flight control system consists of conventional aileron rudder and elevator control surfaces see figure 7 1 The control sur faces are manually operated through mechanical linkage using a control wheel for the ailerons and elevator and rudder brake pedals for the rudder TRIM SYSTEM A manually operated elevator trim tab is provided Elevator trim ming is accomplished through the elevator trim tab by utilizing the vertically mounted trim control wheel Forward rotation of the trim wheel will trim nose down conversely aft rotation will trim nose up INSTRUMENT PANEL The instrument panel see figure 7 2 15 designed to place the prim ary flight instruments directly in front of the pilot The gyro operated fli
66. N 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS GROUND CONTROL Effective ground control while is accomplished through nose wheel steering by using the rudder pedals left rudder pedal to steer left and right rudder pedal to steer right When a rudder pedal is depressed a spring loaded steering bungee which is connected to the nose gear an to the rudder bars will turn the nose wheel through an arc of approximate ly 8 5 each side of center By applying either left or right brake the de gree Of turn may be increased up to 30 each side of center Moving the airplane by hand is most easily accomplished by attaching a tow bar to the nose gear strut If a tow bar is not available or pushing is required use the wing struts as push points Do not use the vertical or horizontal surfaces to move the airplane airplane is to be towed by vehicle never turn the nose wheel more than 30 either side of center or structural damage to the nose gear could result The minimum turning radius of the airplane using differential braking and nose wheel steering during taxi is approximately 24 feet 8 inches To obtain a minimum radius turn during ground handling the airplane may be rotated around either main landing gear by pressin down on the tail conejust forward of the vertical stabilizer to raise the nose wheel offthe ground Figure 7 3 Wing Flap System 7 9 SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M
67. NA SECTION 3 MODEL 150M EMERGENCY PROCEDURES DITCHING 1 Radio TRANSMIT MAYDAY on 121 5 MHz giving location and intentions 2 Heavy Objects in baggage area SECURE or JETTISON 3 Approach High Winds Heavy Seas INTO THE WIND Light Winds Heavy Swells PARALLEL TO SWELLS 4 Wing Flaps 40 5 Power ESTABLISH 300 FT MIN DESCENT at 55 KIAS 6 Cabin Doors UNLATCH 7 Touchdown LEVEL ATTITUDE AT 300 FT MIN DESCENT 8 Face CUSHION at touchdown with folded coat 9 Airplane EVACUATE through cabin doors If necessary open window and flood cabin to equalize pressure so doors can be opened 10 Life Vests and Raft INFLATE FIRES DURING START ON GROUND 1 Cranking CONTINUE to get a start which would suck the flames and accumulated fuel through the carburetor and into the engine If engine starts 2 Power FULL for a few minutes 3 Engine SHUTDOWN and inspect for damage If engine fails to start 4 Cranking CONTINUE in an effort to obtain a start 5 Fire Extinguisher OBTAIN have ground attendants obtain if not installed 6 Engine SECURE a Master Switch OFF b Ignition Switch OFF c Fuel Shutoff Valve OFF 7 Fire EXTINGUISH using fire extinguisher wool blanket or dirt 8 Fire Damage INSPECT repair damage or replace damaged components or wiring before conducting another flight ENGINE FIRE IN FLIGHT 1 Mixtu
68. NCE MAXIMUM RATE OF CLIMB 1 Add 0 8 of a gallon of fuel for engine start taxi and takeoff allowance 2 Increase time fuel and distance by 1096 for each 8 above standard temperature 3 Distances shown are based on zero wind FROM SEA LEVEL weer Sab We LBS FT C kias FPM TIME FUEL USED DISTANCE MIN GALLONS NM 1600 S L 15 68 670 0 0 0 1000 13 68 630 2 0 2 2 2000 11 67 590 3 0 5 4 3000 9 66 550 5 0 7 6 4000 7 65 510 7 1 0 8 5000 5 65 470 9 13 10 6000 3 64 425 11 1 6 13 7000 1 64 385 14 19 16 8000 1 63 345 17 2 3 19 9000 3 63 305 20 2 7 23 10 000 5 62 265 23 3 2 27 11 000 7 62 220 27 87 32 12 000 9 61 180 33 4 3 38 Figure 5 6 Time Fuel and Distance to Climb 5 13 SECTION 5 CESSNA PERFORMANCE MODEL 150M CRUISE PERFORMANCE CONDITIONS 1600 Pounds Recommended Lean Mixture 20 C BELOW STANDARD 20 C ABOVE PRESSURE RDM STANDARD tEMP TEMPERATURE STANDARD TEMP ALTITUDE BHP KTAS GPH BH KTAS GPH BHP KTAS GPH 2000 2650 em 78 103 5 9 72 102 5 4 2600 80 102 6 0 73 101 3 3 68 100 5 1 2500 70 97 5 3 65 96 4 9 60 95 4 6 2400 62 92 4 7 57 91 4 3 53 91 4 1 2300 54 87 4 1 50 87 3 9 47 86 3 7 2200 47 83 3 7 44 82 3 5 42 81 3 3 4000 2700 sem 78 105 5 8 72 104 54 2600 75 101 5 6 69 100 5 2 64 99 4 8 2500 66 96 5 0 61 95 4 6 57 95 4 3 2400 58 91 4 4 54 91 4 1 50 90 3 9 2300 51 87 3 9 48 86
69. OT BY CAR PART 3 CESSNA AIRCRAFT COMPANY WICHITA KANSAS USA CONGRATULATIONS CESSNA MODEL 150M CONGRATULATIONS Welcome to the ranks of Cessna owners Your Cessna has been designed and constructed to give you the most in performance economy and comfort It is our desire that you will find flying it either for business or pleasure a pleasant and profitable experience This Pilot s Operating Handbook has been prepared as a guide to help you get the most pleasure and utility from your airplane It contains information about your Cessna s equip ment operating procedures and performance and suggestions for its servicing and care We urge you to read it from cover to cover and to refer to it frequently Our interest in your flying pleasure has not ceased with your purchase of a Cessna World wide the Cessna Dealer Organization backed by the Cessna Customer Services Department stands ready to serve you The following services are offered by most Cessna Dealers e THE CESSNA WARRANTY which provides coverage for parts and labor is available at Cessna Dealers worldwide Specific benefits and provisions of warranty plus other important benefits for you are contained in your Customer Care Program book sup plied with your airplane Warranty service is available to you at authorized Cessna Dealers throughout the world upon presentation of your Customer Care Card which establishes your eligibility under the warranty FACTORY TRA
70. PROFILE 45 MINUTES RESERVE 35 0 GALLONS USABLE FUEL CONDITIONS 1600 Pounds Recommended Lean Mixture for Cruise Standard Temperature Zero Wind NOTES 1 This chart allows for the fuel used for engine start taxi takeoff and climb and the distance during climb as shown in figure 5 6 2 Reserve fuel is based on 45 minutes at 45 BHP and is 2 6 gallons 12 000 T seem 10 000 6000 ALTITUDE FEET 4000 2000 520 560 600 640 680 720 760 800 RANGE NAUTICAL MILES Figure 5 8 Range Profile Sheet 2 of 2 5 16 CESSNA SECTION 5 MODEL 150M PERFORMANCE ENDURANCE PROFILE 45 MINUTES RESERVE 22 5 GALLONS USABLE FUEL CONDITIONS 1600 Pounds Recommended Lean Mixture for Cruise Standard Temperature NOTES 1 This chart allows for the fuel used for engine start taxi takeoff and climb and the time during climb as shown in figure 5 6 2 Reserve fuel is based on 45 minutes at 4596 BHP and is 2 6 gallons ALTITUDE FEET ENDURANCE HOURS Figure 5 9 Endurance Profile Sheet 1 of 2 5 17 5 CESSNA PERFORMANCE MODEL 150M ENDURANCE PROFILE 45 MINUTES RESERVE 35 0 GALLONS USABLE FUEL CONDITIONS 1600 Pounds Recommended Lean Mixture for Cruise Standard Temperature NOTES 1 This chart allows for the fuel used for engine start taxi takeoff and climb and the time during climb as shown in figure 5 6 2 Reserve fuel is based on 45 minutes
71. RANGE 19 Gal Each 35 0 3 0 38 0 Figure 7 5 Fuel Quantity Data SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M VENIED HIFR CAP FILLER CAP THROTTLE CARBURETOR TO ENGINE MIXTURE DE CYLINDERS co E CONTROL FUEL SUPPLY KNOB L 3 VENT Due to crossfeeding between fuel MECHANICAI tanks the tanks should be re im topped after each refueling to assure maximum capacity Fuel System Standard and Long Range Figure 7 6 7 20 CESSNA SECTION 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS Fuel system venting is essential to system operation Blockage of the venting system will result in a decreasing fuel flow and eventual engine stoppage Venting is accomplished by an interconnecting line from the right fuel tank to the left tank The left tank is vented overboard through a vent line which is equipped with a check valve and protrudes from the bottom surface of the left wing near the wing strut attach point The right fuel tank filler cap is also vented Fuel quantity is measured by two float type fuel quantity transmit ters one each tank and indicated by two electrically operated fuel quantity indicators on the lower left portion of the instrument panel An empty tank is indicated by a red line and the letter E When an indicator shows an empty tank approximately 1 75 gallons remain in a standard tank or 15 gallons remain in a long range tank as unusable fuel The
72. ST and SET 6 Circuit Breakers CHECK IN CESSNA MODEL SECTION 4 150M NORMAL PROCEDURES STARTING ENGINE 6 7 8 Prop Lever FORWARD Carburetor Heat OFF Master Switch ON Electric Fuel Pump ON for 3 seconds then OFF For a cold start e Choke ON e Throttle IDLE For a warm start e Choke OFF Throttle 2 CM IN Propeller Area CLEAR Ignition Switch START release when engine starts Oil Pressure CHECK BEFORE TAKEOFF Cabin Doors CLOSED and LATCHED Parking Brake SET Flight Controls FREE and CORRECT Flight Instruments SET Fuel Shutoff Valve ON Prop Lever FORWARD Above 300 ft AAL reduce RPM to 2260 Elevator Trim TAKEOFF Throttle 1700 RPM a Magnetos CHECK RPM should not exceed 150 RPM on either magneto or 75 RPM differential between magnetos b Carburetor Heat CHECK for RPM c Engine Instruments Ammeter CHECK d Suction Gage CHECK 9 Throttle 1800 RPM a Prop Lever 1700 RPM b Throttle INCREASE slightly c RPM Should not rise d Prop Lever FORWARD 10 Radios SET Flashing Beacon Navigation Lights and or Strobe Lights N as required 12 Throttle Friction Lock ADJUST 4 7 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 150M TAKEOFF NORMAL TAKEOFF Wing Flaps 0 2 Carburetor Heat COLD 3 Throttle FULL OPEN 4
73. T Cessna 300 ADF Type R 546E Cessna 300 Transponder Type RT 359A and Optional Encoding Altimeter EA 401A Cessna 300 Transponder Type RT 359A and Optional Altitude Encoder Blind Cessna 400 Transponder Type RT 459A and Optional Encoding Altimeter Type EA 401A Cessna 400 Transponder Type RT 459A and Optional Altitude Encoder Blind Cessna 400 Marker Beacon Type R 402A Cessna 400 Glide Slope Type R 443B 4 pages 4 pages 6 pages 6 pages 6 pages 6 pages 6 pages 6 pages 4 pages 4 pages 9 CESSNA SUPPLEMENTS MODEL 150M INTRODUCTION This section consists of a series of Supple mens each covering a single optional system which may be installed in the airplane Each sup lement contains a brief description and when applicable operating lim itations emergency and normal procedures and performance ther routinely installed items of optional equi ment whose function and opera procedures do not require detailed instructions are discussed in ection PILOT S OPERATING HANDBOOK EMERGENCY LOCATOR SUPPLEMENT TRANSMITTER ELT SUPPLEMENT EMERGENCY LOCATOR TRANSMITTER ELT SECTION 1 GENERAL The ELT consists of a self contained dual frequency radio transmit ter and battery power supply and is activated by an impact of 5g or more as may be experienced in a crash landing ELT emits an omnidirec tional on i
74. TCH With VOR or LOC station selected in ED position sta tion identifier is audible in center unmarked position identifier is off in momentary on position tests VOR navigation circuits COURSE DEVIATION POINTER Indicates deviation from selected omni bearing or localizer centerline OFF TO FROM OMNI INDICATOR Operates only with VOR or localizer signal OFF position flag indicates unreliable signal When OFF position disappears indicator shows whether selected VOR course is TO or FROM the station if LOC frequency is selected indicator will only show TO RECIPROCAL COURSE INDEX Indicates reciprocal of selected VOR course OMNI BEARING SELECTOR OBS Selects desired course to or from a VOR station BC During LOC operation when optional Back Course operation is selected amber lamp illuminates to alert the pilot that CDI indication is reversed BEARING DIAL Rotated by OBS to select course at index COURSE INDEX Indicates selected VOR course GLIDE SLOPE OFF FLAG When visible indicates unreliable glide slope signal or no glide slope signal The flag disappears when a reliable glide slope signal is being received GLIDE SLOPE DEVIATION POINTER Indicates deviation from normal glide slope Figure 1 Cessna 300 Nav Com Type RT 328T Sheet 2 of 2 CESSNA 300 NAV COM PILOT S OPERATING HANDBOOK TYPE RT 328T SUPPLEMENT SECTION 2 LIMITATIONS There is no change to the airplane lim
75. VNE Vs Vs Vx Vy CESSNA MODEL 150M Knots Indicated Airspeed is the speed shown on the airspeed indicator and expressed in knots Knots True Airspeed is the airspeed expressed in knots rel ative to undisturbed air which is KCAS corrected for altitude and temp rature Maneuvering Speed is the maximum speed at which you may use abrupt control travel Maximum Flap Extended Speed is the highest speed permis sible with flaps in a prescribed extended position Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air then only with caution Never Exceed Speed is the speed limit that may not be ex ceeded at any time Stalling Speed or the minimum steady flight speed at which the airplane is controllable Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration at the most forward center of gravity Best Angle of Climb Speed is the speed which results in the greatest gain of altitude in a given horizontal distance Best Rate of Climb Speed is the speed which results in the greatest gain in altitude in a given time METEOROLOGICAL TERMINOLOGY OAT Standard Tempera ture Pressure Altitude 1 6 Outside Air Temperature is the free air static temperature It is expressed in either degrees Celsius formerly Centi grade or degrees Fahrenheit Standard Temperature is 15 C at
76. a door on the left side of the fuselage near the aft 7 24 CESSNA SECTION 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS edge of the cowling Just before connecting an external power source generator type or battery cart the master switch should be turned ON Tnis is especially important since it will enable the battery to absorb transient voltages which otherwise might damage the transistor in the electronic equipment The battery and external power circuits have been designed to com pletely eliminate the need to jumper across the battery contactor to close it for charging a completely dead battery special fused cir cuit in the external power system supplies the needed jumper across the contacts so that with a dead battery and an external power source applied turning the master switch ON will close the battery contactor LIGHTING SYSTEMS EXTERIOR LIGHTING Conventional navigation lights are located on the wing tips and top of the rudder a single landing light is installed in the cowl nose cap and a flashing beacon is mounted on top ofthe vertical fin Additional lightin is available and includes dual landing Le lights in the cowl nose cap an a strobe light on each wing tip exterior lights are controlled by rock er type switches on the lower left side of the instrument panel The switches are ON in the up position and OFF in the down position The flashing beacon should not be used when flying through clouds o
77. all horizontal distances are measured for balance purposes Station Station is a location along the airplane fuselage given in terms ofthe distance from the reference datum Arm Arm is the horizontal distance from the reference datum to the center of gravity C G of an item Moment Moment is the product of the weight of an item multiplied by its arm Moment divided by the constant 1000 is used in this handbook to simplify balance calculations by reducing the number of digits 1 7 SECTION 1 CESSNA GENERAL MODEL 150M Center of Center of Gravity is the point at which an airplane or equip Gravity ment would balance if suspended Its distance from the C G reference datum is found by dividing the total moment by the total weight of the airplane C G Center of Gravity Arm is the arm obtained by adding the Arm airplane s individual moments and dividing the sum by the total weight C G Center of Gravity Limits are the extr me center of gravity Limits locations within which the airplane must be operated at a given weight Standard Standard Empty Weight is the weight of a standard airplane Empty including unusable fuel full operating fluids and full engine Weight oil Basic Empty Basic Empty Weight is the standard empty weight plus the Weight weight of optional equipment Useful Useful Load is the difference between takeoff weight and the Load basic empty weight Gross Gross Loaded Weight i
78. ance speed of 60 KIAS with flaps retracted This speed provides the best overall climb speed to clear obstacles when taking into account the turbulence often found near ground level CROSSWIND TAKEOFF Takeoffs into strong crosswinds normally are performed with the minimum flap setting necessary for the field length to minimize the drift angle immediately after takeoff The airplane is accelerated to a speed slightly higher than normal then pulled off abruptly to prevent possible settling back to the runway while drifting When clear of the ground make a coordinated turn into the wind to correct for drift ENROUTE CLIMB When conducting the following climbs the mixture should be full rich below 5000 feet and may be leaned if necessary above 5000 feet for smoother engine operation NORMAL CLIMB Normal climbs are conducted at 65 to 75 KIAS with flaps up and full throttle for best engine cooling BEST RATE OF CLIMB The best rate of climb speeds range from 68 KIAS at sea level to 62 KIAS at 10 000 feet with flaps up and full throttle BEST ANGLE OF CLIMB If enroute terrain dictates the use of a steep climb angle climb at the best angle of climb speed of 56 KIAS with flaps up and full throttle NOTE Steep climbs at low airspeeds should be of short duration to allow improved engine cooling CRUISE Normal cruising is performed between 55 and 75 power The en 4 15 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 150M
79. ased Instru ment Landing System ILS It is used with the localizer function of a VHF navigation system when making instrument approa lies to an airport The puse slope provides vertical path guidance while the localizer provides orizontal track guidance The Cessna 400 Glide Slope system consists of a remote mounted receiver coupled to an existing navigation Dem a panel mounted indi cator and an externally mounted antenna e glide slope receiver is designed to receive ILS glide slope on any of 40 channels The channels are spaced 150 apart and cover a frequency range of 329 15 MEZ through 335 0 MHz When a localizer frequency is selected on the NAV receiver the associated glide slope frequency is selected automati cally Operation of the Cessna 400 Glide Slope system is controlled by the associated navigation system The functions and indications of a typical 300 series glide slope indicator are pictured and described in Figure 1 For functions and indications of the optional 400 series indicator or HSI indicator refer to the 400 NAV COM Type RT 428A or HSI Type IG 832A write ups if they are listed in this section as options SECTION 2 LIMITATIONS There is no change to the airplane limitations when this avionic equip mentis installed However the pilot should be aware that on many Cessna airplanes equipped with the windshield mounted glide slope antenna pilots Should avoid use of 2700 100 RPM with a two bladed prop
80. avigation Light Switch OFF 2 Strobe Light Switch OFF 3 Pitot Heat Switch OFF NOTE Perform a side slip to keep the flames away from the fuel tank and cabin and land as soon as possible with flaps retracted ICING INADVERTENT ICING ENCOUNTER 1 Turn pitot heat switch ON if installed 2 Turn back or change altitude to obtain an outside air temperature that is less conducive to icing 3 Pull cabin heat control full out to obtain maximum defroster air temperature For air flow at reduced temperatures adjust the cabin air control as required 4 Open the throttle to increase engine speed and minimize ice build up on propeller blades 5 Watch for signs of carburetor air filter ice and apply carburetor heat as required An unexpected loss in engine speed could be caused by carburetor ice or air intake filter ice ean the mixture for maximum RPM if carburetor heat is used continuously 6 Plan a landing at the nearest airport With an extremely rapid ice build up select a suitable off airport landing site 7 With an ice accumulation of 1 4 inch or more on the wing leading edges be prepared for significantly higher stall speed 8 Leave wing flaps retracted With a severe ice build up on the horizontal tail the change in wing wake airflow direction caused by wing flap extension could result in a loss of elevator effec tiveness 9 Open left window and if practical scrape ice from a portion of t
81. buretor is equipped with an enclosed accelerator pump simplified fuel passages to prevent vapor locking an idle cut off mechanism and a manual mixture control Fuel is delivered to the carburetor by gravity flow from the fuel system In the carburetor fuel is atomized proportionally mixed with intake air and delivered to the cylinders through intake manifold tubes The propor tion of atomized fuel to air is controlled within limits by the mixture control on the instrument panel For easy starting in cold weather the engine is equipped with a man ual primer The primer is actually a small pump which draws fuel from the fuel strainer when the plunger is pulled out and injects it into the in take manifold when the plunger is pushed back in The plunger knob on the instrument panel is equipped with a lock and after being pushed full in must be rotated either left or right until the knob cannot be pulled out COOLING SYSTEM Ram air for engine cooling enters through two intake openings in the front of the engine cowling The cooling air is directed around the cylin ders and other areas of the engine by baffling and is then exhausted through an opening at the bottom aft edge of the cowling No manual cool ing system control is provided A winterization kit is available for the airplane The kit consists of two shields to partially cover the cowl nose cap opening the addition of heat ducting from the right exhaust manifold for additi
82. calculated as follows Fuel to climb standard temperature 1 1 Increase due to non standard temperature 1 1 x 2096 0 2 Corrected fuel to climb 1 3 Gallons Using a similar procedure for the distance to climb results in 11 nautical miles The resultant cruise distance is Total distance 330 Climb distance 11 Cruise distance 319 Nautical Miles With an expected 10 knot headwind the ground speed for cruise is predicted to be 98 10 88 Knots Therefore the time required for the cruise portion of the trip is 319 Nautical Miles 3 6 Hours 88 Knots The fuel required for cruise is 3 6 hours x 4 5 gallons hour 16 2 Gallons 5 6 CESSNA SECTION 5 MODEL 150M PERFORMANCE The total estimated fuel required is as follows Engine start taxi and takeoff 0 8 Climb 13 Cruise 16 2 Total fuel required 18 3 Gallons This will leave a fuel reserve of 22 5 18 3 4 2 Gallons Once the flight is underway ground speed checks will provide a more accurate basis for estimating the time enroute and the correspon ding fuel required to complete the trip with ample reserve LANDING A procedure similar to takeoff should be used for estimating the landing distance at the destination airport Figure 5 10 presents land ing distances for various airport altitude and temperature combina tions using the short field technique The distances corresponding to 2000 feet and 30 C are as follows Ground roll 505 Feet Total di
83. ch door Grasp the forward edge of the handle and pull out close or open the doors from inside the airplane use the recessed door handle and arm rest Both cabin doors should be checked for security prior to flight and should not be opened intentionally during flight NOTE Accidental opening of a cabin door in flight due to im proper closing does not constitute a need to land the air plane The best procedure is to set up the airplane in a trimmed condition at approximately 65 knots momentar ily shove the door outward slightly and forcefully close the door Exit from the airplane is accomplished by grasping the forward edge of the door handle and pulling To lock the airplane lock the right cabin door from the inside by lifting up on the lever near the aft edge of the door close the left cabin door and using the ignition key lock the door Both cabin doors are equipped with openable windows The windows are held in the closed position by a lock button equipped over center latch on the lower edge of the window frame To open either window depress the lock button and rotate the latch upward The windows are equipped with a spring loaded retaining arm which will help rotate the window outward and hold it there If required the windows may be opened at any speed up to 141 knots other cabin windows are of the fixed type and cannot be opened Two additional fixed windows may be installed in the cabin top CONTROL LOCKS
84. ciated glide slope frequency will be selected automatically controls of the Cessna 300 Nav Com except the omni bearing selector knob OBS which is located on the course indicator are mount ed on the front panel of the receiver transmitter course indicator includes either a single pointer and related OFF flag for VOR LOC indi cation only or dual pointers and related OFF flags for both VOR LOC and glide slope indications course indicator also incorporates a back course lamp BC which lights when optional back course operation is selected In addition when two or more radios are installed a trans mitter selector switch and a speaker phone selector switch are provided Each control function is described in Figure 1 of 6 CESSNA 300 NAV COM PIIXDT S OPERATING HANDBOOK TYPE RT 328T SUPPUEMENT 1 RECEIVER TRANSMITTER FREQUENCY INDICATOR 2 NAVIGATION RECEIVER FREQUENCY INDICATOR 3 SQUELCH CONTROL Used to adjust signal threshold necessary to activate communication receiver audio lockwise rotation increases background noise decreases squelch action counterclockwise rotation decreases background noise 4 COMMUNICATION RECEIVER TRANSMITTER MEGAHERTZ SELECTOR Selects communication receiver transmitter frequency in 1 MHz steps be tween 118 and 135 MHz 5 OFF ON VOLUME CONTROL Turns set on and controls volume of audio from communications receiver 6 COMMUNICATION RECEIVER TRANSMITTER FRACTIONAL
85. cification API SG or higher Due to the high stresses in the reduction gear oils with gear additives such as high performance heavy duty motor cycle oils are required NOTE SAE 10W50 or SAE 10W60 oils are suitable for operation at ambient temperatures as low as 20 Oil Capacity Sump 3 5 liters CESSNA SECTION 1 MODEL 150M GENERAL MAXIMUM CERTIFICATED WEIGHTS Takeoff 726 kg Landing 726 kg Weight in Baggage Compartment Baggage Area 1 or passenger on child s seat Station 50 to 76 54 kg See note below Baggage Area 2 Station 76 to 94 18 kg See note below NOTE The maximum combined weight capacity for baggage areas 1 and 2 is 54 kg STANDARD AIRPLANE WEIGHTS Standard Empty Weight Commuter 515 5 kg Maximum Useful Load Commuter 210 5 kg CABIN AND ENTRY DIMENSIONS A Detailed dimensions of the cabin interior and entry door openings are illustrated in Section 6 BAGGAGE SPACE DIMENSIONS Dimensions of the baggage area are illustrated in detail in Section 6 SPECIFIC LOADINGS Wing Loading 10 0 165 sq ft Power Loading 16 0 165 SYMBOLS ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS Knots Calibrated Airspeed is indicated airspeed corrected for position and instrument error and expressed in knots Knots calibrated airspeed is equal to KTAS in standard at mosphere at sea level 1 5 1 GENERAL KIAS KTAS
86. clude the SERIAL NUMBER The Serial Number Model Number Production Cer tificate Number PC and Type Certificate Number TC can be found on the Identification Plate located on the cabin floor below the left rear cor ner of the pilot s seat The plate is accessible by sliding the seat for ward and lifting the carpet in this area Located adjacent to the Identifi cation Plate is a Finish and Trim Plate which contains a code describing the interior color scheme and exterior paint combination of the airplane The code may be used in conjunction with an applicable Parts Catalog if finish and trim information is needed OWNER FOLLOW UP SYSTEM Your Cessna Dealer has an Owner Follow Up System to pour you when he receives information that applies to your Cessna In addition if ou wish you may choose to receive similar notification in the form of ervice Letters directly from the Cessna Customer Services Department A subscription form is supplied in your Customer Care Program book for our use should you choose to request this service Your Cessna Dealer will be glad to supply you with details concerning these follow up programs and stands ready through his Service Department to supply you with fast efficient low cost service PUBLICATIONS Various publications and flight operation aids are furnished in the 8 3 SECTION 8 CESSNA HANDLING SERVICE MODEL 150M amp MAINTENANCE airplane when delivered from the factory These items
87. d bank indicator may be referred to for this information For additional information on spins and spin recovery see the dis cussion under SPINS in Normal Procedures Section 4 ROUGH ENGINE OPERATION OR LOSS OF POWER CARBURETOR ICING A gradual loss of RPM and eventual roughness may result from the formation of carburetor ice To clear the ice apply full throttle and pull the carburetor heat knob full out until the engine runs smoothly then remove carburetor heat and readjust the throttle If conditions require the continued use of carburetor heat 11 cruise flight use the minimum amount of heat necessary to prevent ice from forming and lean the mixture slightly for smoothest engine operation SPARK PLUG FOULING A slight engine roughness in flight may be caused by one or more spark plugs becoming fouled by carbon or lead deposits This may be verified by turning the ignition switch momentarily from BOTH to either L or R position An obvious power loss in single ignition operation is evidence of spark plug or magneto trouble Assuming that spark plugs are the more likely cause lean the mixture to the recommended lean set ting for cruising ffight Ifthe problem does not clear up in several min utes determine ifa richer mixture setting will produce smoother opera tion Ifnot proceed to the nearest airport for repairs using the SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 150M position of the ignition switch unless extreme r
88. e following information An item number gives the identification number for the item Each number is prefixed with a letter which identifies the descriptive grouping example A Powerplant amp Accessories under which it is listed Suffix letters identify the equipment as a required item a standard item or an optional item Suffix letters are as follows R required items of equipment for FAA certification 8 standard equipment items O optional equipment items replacing required or standard items optional equipment items which are in addition to required or standard items A reference drawing column provides the drawing number for the item NOTE If additional equipment is to be installed it must be done in accord ance with the reference drawing accessory kit instructions or a separate FAA approval Columns showing weight in pounds and arm in inches provide the weight and center of gravity location for the equipment NOTE Unless otherwise indicated true values not net change values for the weight and arm are shown Positive arms are distances aft of the airplane datum negative arms are distances forward of the datum NOTE Asterisks after the item weight and arm indicate complete assem bly installations Some major components of the assembly are listed on the lines immediately following The summation of these major components does not necessarily equal the complete assembly instal lation
89. e lower portion of the cabin just forward of the pilot and is helpful when checking maps and other flight data during night operations To operate the light first turn on the NAV LIGHTS switch then adjust the map light s intensity with the knurled disk type rheostat control located at the bottom of the control wheel The most probable cause of a light failure is a burned out bulb how ever in the event any of the lighting systems fail to illuminate when turn ed on check the appropriate circuit breaker If the circuit breaker has opened white button popped out and there is no obvious indication of a short circuit smoke or odor turn off the light switch of the affected lights reset the breaker and turn the switch on again If the breaker opens again do not reset it CABIN HEATING VENTILATING AND DEFROSTING SYSTEM The temperature and volume of airflow into the cabin can be regulated to any degree desired by manipulation of the push pull CABIN HT and CABIN AIR control knobs see figure 7 8 Heated fresh air and outside air are blended in a cabin manifold just aft of the firewall by adjustment of the heat and air controls this air is then vented into the cabin from outlets in the cabin manifold near the pilots and passenger s feet Windshield defrost air is also supplied by a duct leading from the manifold Full ventilation air may be obtained by utilization of the adjustable ventilators near the upper left and right corners of t
90. e no polishing or buffing Approximately 15 days are required for the paint to cure com pletely in most cases the curing period will have been completed prior to delivery of the airplane the event that polishing or buffing 15 re quired within the curing period it is recommended that the work be done by someone experienced in handling uncured paint Any Cessna Dealer can accomplish this work Generally the painted surfaces can be kept bright by washing with water and mild soap followed by a rinse with water and drying with cloths or a chamois Harsh or abrasive soaps or detergents which cause corrosion or scratches should never be used Remove stubborn oil and grease with a cloth moistened with Stoddard solvent 8 12 CESSNA SECTION 8 MODEL 150M HANDLING SERVICE amp MAINTENANCE Waxing is unnecessary to keep the painted surfaces bright However if desired the airplane be waxed with a good automotive wax A heavier coating of wax on the leading edges of the wings and tail and on the engine nose cap and propeller spinner will help reduce the abrasion encountered in these areas When the airplane is parked outside in cold climates and it is neces sary to remove ice before flight care should be taken to protect the paint ed surfaces during ice removal with chemical liquids 50 50 solution of isopropyl alcohol and water will satisfactorily remove ice accumulations without damaging the paint A solution with more than 50
91. e up elevator and apply maximum brake pres sure without sliding the tires Slightly higher approach speeds should be used under turbulent air conditions CROSSWIND LANDING When landing in a strong crosswind use the minimum flap setting required for the field length Use a wing low crab or a combination method of drift correction and land in a nearly level attitude BALKED LANDING In a balked landing go around climb the wing flap setting should be reduced to 20 immediately after full power is applied reaching safe airspeed the flaps should be slowly retracted to the full up position COLD WEATHER OPERATION Prior to starting on cold mornings it is advisable ull the pro peller through several times by hand to break loose or limber the oil thus conserving battery energy NOTE When pulling the propeller through by hand treat it as ifthe ignition switch is turned A loose or broken ground wire on either magneto could cause the engine to fire In extremely cold 18 and lower weather the use of an external preheater is recommended whenever possible to reduce wear and abuse to the engine and electrical system Cold weather starting procedures are as follows With Preheat 1 With ignition switch OFF and throttle closed prime the engine four to ten strokes as the propeller is being turned over by hand 4 20 CESSNA SECTION 4 MODEL 150M NORMAL PROCEDURES NOTE Use heavy strokes
92. eadily indi cating IDENT operation TO TRANSMIT MODE C ALTITUDE REPORTING CODES IN FLIGHT 1 Off Indicator Warning Flag VERIFY that flag is out of view encoding altimeter 2 Altitude Encoder Altimeter Setting Knob SET IN assigned local altimeter setting 3 Reply Code Selector Switches SELECT assigned code 4 Function Switch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode A operation only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated alti tude is done in ATC computers Altitude squawked will only agree with indicated altitude when the local altimeter setting in use by the ground controller is set in the encoding altimeter 5 DIM Control ADJUST light brilliance of reply lamp SELF TEST TRANSPONDER OPERATION 1 Function Switch SBY and wait 30 seconds for equipment to warm up CESSNA 400 TRANSPONDER PILOT S OPERATING HANDBOOK AND ENCODING ALTIMETER SUPPLEMENT 2 Function Switch ON or ALT 3 TST Button DEPRESS and HOLD Reply lamp should light with full brilliance regardless of DIM contol setting 4 TST Button Release for normal operation SECTION 5 PERFORMANCE _There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mount sd antenna or several related external antenna
93. ects communication receiver transmitter frequency in 1 MHz steps between 118 and 135 MHz Figure 1 Cessna 300 Nav Com Type RT 308C VOR only Sheet 1 of 2 PILOT S OPERATING HANDBOOK CESSNA 300 NAV COM SUPPLEMENT TYPE RT 308C 5 10 11 12 13 14 15 16 OFF ON VOLUME CONTROL Turns complete set on and controls volume of audio from communication re ceiver Clockwise rotation increases audio level COMMUNICATION RECEIVER TRANSMITTER FRAC TIONAL MEGAHERTZ SELECTOR Selects communi cation receiver transmitter fractional frequency in 0 05 MHz steps between 00 and 0 95 MHz NAVIGATION RECEIVER MEGAHERTZ SELECTOR Selects navigation receiver frequency in 1 MHz steps between 108 and 117 MHz NAVIGATION RECEIVER VOLUME CONTROL Con trols volume of audio from navigation receiver only Clockwise rotation increases audio level NAVIGATION RECEIVER FRACTIONAL MEGAHERTZ SELECTOR Selects navigation receiver frequency in 0 05 MHz steps between 0 00 and 0 95 MHz COURSE DEVIATION POINTER Indicates deviation from selected omni bearing OFF TO FROM OMNI INDICATOR Operates only with VOR signal OFF position flag indicates unreliable signal or no signal shows OFF when localizer frequency is selected When OFF position disappears indicator shows whether selected course is TO or FROM VOR station RECIPROCAL COURSE INDEX Indicates reciprocal of selected VOR course OMNI BEAR
94. ed entry altitude for a 6 turn spin would be 6000 feet above ground level In any case entries should be planned so that recoveries are com pleted well above the minimum 1500 feet above ground level required by FAR 91 71 Another reason for using high altitudes for practicing spins is that a greater field of view is provided which will assist in maintaining pilot orientation The normal entry is made from a power off stall As the stall is approached the elevator control should be smoothly pulled to the full aft position Just prior to reaching the stall break rudder control in the desired direction ofthe spin rotation should be applied so that full rudder deflection is reached almost simultaneously with reaching full aft elevator A slightly greater rate of deceleration than for normal stall entries or the use of partial power at the entry will assure more consistent and positive entries to the spin Care should be taken to avoid using aileron control since its application can increase the rotation rate and cause erratic rota tion Both elevator and rudder controls should be held full with the spin until the spin recovery is initiated inadvertent relaxation of either of these controls could result in the development of a nose down spiral For the purpose oftraining in spins and spin recoveries a 1 to 2 turn spin is adequate and should be used Up to 2 turns the spin will progress to a fairly rapid rate of rotation and a steep attitude
95. eerable nose wheel and rudder to maintain direction Figure 4 2 Diagram 4 12 CESSNA SECTION 4 MODEL 150M NORMAL PROCEDURES inflated and the airplane is loaded to a rearward center of gravity posi tion it may be necessary to partially compress the strut to permit steer ing This can be accomplished prior to taxiing by depressing the airplane nose by hand or during taxi by sharply applying brakes BEFORE TAKEOFF WARM UP Most of the warm up will have been conducted during taxi and addi tional warm up before takeoff should be restricted to the checklist proce dures Since the engine is closely cowled for efficient in flight cooling precautions should be taken to avoid overheating on the ground MAGNETO CHECK The magneto check should be made at 1700 RPM as follows Move ignition switch first to R position and note RPM Next move switch back to BOTH to clear the other set of plugs Then move switch to the L posi tion note RPM and return the switch to the BOTH position RPM drop should not exceed 150 RPM on either magneto or show greater than 75 RPM differential between magnetos If there is a doubt concerning opera tion of the ignition system RPM checks at higher engine speeds will usually confirm whether a deficiency exists An absence of RPM drop may be an indication of faulty grounding of one side of the ignition system or should be cause for suspicion that the magneto timing is set in advance of the sett
96. eller or 1800 100 RPM with a three bladed propeller during ILS paas to avoid oscil lations of the glide slope deviation pointer caused by propeller interference 1 of 4 CESSNA 400 GLIDE SLOPE PILOT S OPERATING HANDBOOK TYPE R 443B SUPPLEMENT 1 GLIDE SLOPE DEVIATION POINTER Indicates devia tion from normal glide slope PA GLIDE SLOPE OFF FLAG When visible indicates unreliable glide slope signal or improperly operating equipment The flag disappears when a reliable glide slope signal is being received caution Spurious glide slope signals may exist in the area of the localizer back course approach which can cause the glide slope OFF flag to disappear and present unreliable glide slope information Disregard all glide slope signal indications when making a localizer back course approach unless a glide slope ILS BC is specified on the approach and landing chart Figure 1 Typical 300 Series VOR LOC ILS Indicator PILOT S OPERATING HANDBOOK CESSNA 400 GLIDE SLOPE SUPPLEMENT TYPE R 443B SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when this avionic equipment is installed SECTION 4 NORMAL PROCEDURES TO RECEIVE GLIDE SLOPE SIGNALS 1 NAV Frequency Select Knobs SELECT desired localizer frequency glide slope frequency is automatically selected 2 NAV COM ID T Switch SELECT ID position to disconnect filter from audio circuit 3 NAV VOL Control AD
97. eporting capabilities are available in 100 foot increments between 1000 feet and the airplane s Maximum service ceiling All Cessna 400 Transponder operating controls are located on the front panel of the unit Functions of the operating controls are described in Figure 1 1 of 6 CESSNA 400 TRANSPONDER PILOT S OPERATING HANDBOOK AND ALTITUDE ENCODER BLIND SUPPLEMENT 1 FUNCTION SWITCH Controls application of power and selects transponder operating mode as follows OFF Turns set SBY Turns set on for equipment warm up or standby power ON Turns set on and enables transponder to transmit ode A aircraft identification reply pulses ALT Turns set on and enables transponder to transmit either Mode A aircraft identification reply pulses or Mode C altitude reporting pulses selected auto matically by the interrogating signal 2 REPLY LAMP Lamp flashes to indicate transmission of pulses glows steadily to indicate transmission of IDENT pulse or satisfactory self test operation Reply lamp will also glow steadily during initial warm up period Figure 1 Cessna 400 Transponder and Altitude Encoder Blind Sheet 1 of 2 PILOTS OPERATING HANDBOOK CESSNA 400 TRANSPONDER SUPPLEMENT AND ALTITUDE ENCODER BLIND 3 IDENT ID SWITCH When depressed selects special pulse iden tifier to be transmitted with transponder reply to effect immediate identification of aircraft on ground controller s disp
98. es soft or spongy pedals and excessive travel and weak braking action If any of these symptoms appear the brake system is in need of immediate attention If during taxi or landing roll braking action decreases let up on the pedals and then re apply the brakes with heavy pressure Ifthe brakes become spongy or pedal travel increases pumping the pedals should build braking pressure If one brake be comes weak or fails use the other brake sparingly while using oppo site rudder as required to offset the good brake ELECTRICAL SYSTEM Electrical energy see figure 7 7 is supplied by a 14 volt direct current system powered by an engine driven 60 alternator The 12 volt 25 amp hour battery is located on the right forward side of the firewall Power is supplied through a single bus bar a master switch controls this power to all circuits except the engine ignition system clock or flight hour recorder if installed The flight hour recorder re ceives power through activation of an oil pressure switch whenever the engine is operating the clock is supplied with current at all times All avionics equipment should be turned off prior to starting the engine or using an external power source to prevent harmful transient voltages from damaging the transistors in this equipment MASTER SWITCH The master switch is a split rocker type switch labeled MASTER and and is ON in the up position and OFF in the down position The right half o
99. f the switch labeled BAT controls all electrical power to the airplane The left half labeled ALT controls the alternator Normally both sides of the master switch should be used simulta neously however the BAT side of the switch could be turned ON separate ly to check equipment while on the ground The ALT side of the switch when placed in the OFF position removes the alternator from the electri cal system With this switch in the OFF position the entire electrical load is placed on the battery Continued operation with the alternator switch in the OFF position will reduce battery power low enough to open the battery contactor remove power from the alternator field and pre vent alternator restart AMMETER The ammeter indicates the flow of current in amperes from the alternator to the battery or from the battery to the airplane electrical 7 22 CESSNA MODEL 150M REGULATOR ALTERNATOR ev OVER VOLTAGE WARNING LIGHT ALTERNATOR FIELD CIRCUIT T BREAKER MASTER SWITCH AMMETER CLOCK Ie d amp STARTER OIL PRESSURE SWITCH STARTER FLIGHT HOUR CONTACTOR RECORDER BATTERY contactor X amp 9 GROUNDSERVICE PLUG RECEPTACLE Nes BATTERY IGNITION SWITCH CODE CIRCUIT BREAKER AUTO RESET CIRCUIT BREAKER FUSH TO RESET FUSE 44 DIODE ANY RESISTOR MAGNETOS CAPACITOR NOISE FILTER Figure 7 7 Electrical
100. ght Use the data pertaining to your airplane as it is presently equipped Includes unusable fuel and full oil Usable Fuel At 6 Lbs Gal Standard Tanks 22 5 Gal Maximum LongRange Tanks 35 Gai Maximum Reduced Fuel As limited by maximum weight Pilot and Passenger Station 33 to 41 Baggage Area 1 Or passenger on child s seat Station 50 to 76 120 Lbs Max Locate this point 1600 at 55 6 on the Center of Gravity Moment Envelope and since this point falls within the envelope the loading is acceptable Figure 6 6 Sample Loading Problem WOST THGOIN VNSSHO HONV IVGH X LSIT LNHINdIQOH 9 NOILOHS 01 9 a 2 2 E T lt d PILOT PASSENGER AND FUEL LONG RANGE TANKS GHIGAL FUEL STANDARD TANKS 6H GAL BAGGAGEIN AREA 1 OR PASSENGER ON CHILD S SEAT 120 MAX E BAGGAGE IN AREA 2 0 MAX TTT ni i cu LOADING GRAPH ETHIC Ls HE LOAD MOMENT 1000 POUND INCHES NOTES Line representing adjustable seats shows the pilot or passenger center of gravity on adjustable seats positioned for an average occupant Refer to the Loading Arrangements Diagram for for ward and aft limits of occupant e g range Figure 6 7 Loading Graph 1511 LNHINdIQOH 7 LHOIHA 9 NOLLOHS
101. ght instruments are arranged one above the other slightly to the left of the control column To the left of these instruments are the airspeed indicator turn coordinator and suction gage On the right side are the clock altimeter rate of climb indicator and navigation instruments Avionics equipment is stacked approximately on the centerline of the panel with space for additonal equipment on the lower right side of the instrument panel The right side of the panel also contains the ta chometer ammeter over voltage light and additional instruments such as a flight hour recorder subpanel under the primary instrument panel contains the fuel quantity indicators cigar lighter and engine instruments positioned below the pilot s control wheel The electrical switches panel and radio light rheostat knob ignition and master switches primer and parking brake control are located around these instruments The engine controls wing flap switch and cabin air and heat control knobs are to the right of the pilot along the upper edge of the subpanel Directly below these controls are the elevator trim con trol wheel trim position indicator microphone and circuit breakers A map compartment is on the extreme right side of the subpanel For details concerning the instruments switches circuit breakers and controls on this panel refer in this section to the description of the systems to which these items are related 7 8 CESSNA SECTIO
102. gine RPM and corresponding fuel consumption for various altitudes can be determined by using your Cessna Power Computer or the data in Section 5 NOTE Cruising should be done at 65 to 75 power until a total of 50 hours has accumulated or oil consumption has sta bilized This is to ensure proper seating of the rings and is applicable to new engines and engines in service following cylinder replacement or top overhaul of one or more cylinders The data in Section 5 shows the increased range and improved fuel economy that is obtainable when operating at lower power settings and higher altitudes The use of lower power settings and the selection of cruise altitude on the basis of the most favorable wind conditions are significant factors that should be considered on every trip to reduce fuel consumption The Cruise Performance Table Figure 4 3 shows the true airspeed and nautical miles per gallon during cruise for various altitudes and per cent powers This table should be used as a guide along with the avail able winds aloft information to determine the most favorable altitude and power setting for a given trip To achieve the recommended lean mixture fuel consumption figures shown in Section 5 the mixture should be leaned as follows 1 Pull the mixture control out until engine RPM peaks and begins to fall off 2 Enrichen slightly back to peak RPM 75 POWER 65 POWER 55 POWER ALTITUDE KTAS N
103. he measure ments 5 Using weights from 3 and measurements from 4 the airplane weight and C G can be determined SECTION 6 CESSNA WEIGHT amp BALANCE MODEL 150M EQUIPMENT LIST Datum Firewall Front Face Sta 0 0 C Level on Leveling Screws amp Left Side of Tailcone B N L amp R Scale Position Scale Reading Tare Symbol Net Weight Left Wheel L Right Wheel R Nose Wheel N Sum of Net Weights As Weighed X ARM A X IN Moment 1000 Item Weight Lbs X C G Arm In Lbs In Airplane Weight From ltem 5 page 6 3 Add Oil No Oil Filter 6 Qts at 7 5 Lbs Gal 13 5 With Oil Filter 7 Qts at 7 5 Lbs Gal 13 5 Add Unusable Fuel Std Tanks 3 5 Gal at 6 Lbs Gal 40 0 L R Tanks 3 0 Gal at 6 Lbs Gal 40 0 Equipment Changes Airplane Basic Empty Weight Figure 6 1 Sample Airplane Weighing 6 4 9 SAMPLE WEIGHT AND BALANCE RECORD Continuous History of Changes in Structure or Equipment Affecting Weight and Balance AIRPLANE MODEL SERIAL NUMBER PAGE NUMBER WEIGHT CHANGE RUNNING BASIC pp EMPTY WEIGHT DESCRIPTION ADDED REMOVED OFARTICLE QR MODIFICATION Wt Arm Moment Wt Arm Moment Wt Moment Ib In 1000 Ib 1000 Ib 1000 Figure 6 2 Sample Weight and Balance Record WOST IHGOIN VNSSHO HONV IVG8 X LHOTHAA ISIT LN
104. he same manner as the belts for the pilot s and passenger s seats To release the seat belts grasp the top of the buckle opposite the link and pull upward SHOULDER HARNESSES Each shoulder harness is attached to a rear doorpost above the window line and is stowed behind a stowage sheath above the cabin door To stow the harness fold it and place it behind the sheath No harness is available for the child s seat The shoulder harnesses are used by fastening and adjusting the seat belt first Then lengthen the harness as required by pulling on the connecting link on the end of the harness and the narrow release strap Snap the connecting link firmly onto the retaining stud on the seat belt link half Then adjust to length Removing the harness is accomplished by pulling upward on the narrow release strap and re moving the harness connecting link from the stud on the seat belt link In an emergency the shoulder harness may be removed by releasing the seat belt first and allowing the harness still attached to the link half of the seat belt to drop to the side of the seat Adjustment of the shoulder harness is important properly ad justed harness will permit the occupant to lean forward enough to sit completely erect but prevent excessive forward movement and contact with objects during sudden deceleration Also the pilot will want the freedom to reach all controls easily INTEGRATED SEAT BELT SHOULDER HARNESSES WITH INERTIA REELS
105. he windshield and by pulling the CABIN AIR control knob out The CABIN HT control knob must be pushed full in 7 26 CESSNA SECTION 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS EXHAUST MUFFLER 22 SHROUD A HEATER VALVE VENTILATING gt Pad AIR DOOR S 4 5 DEFROSTER E A pa CABINAIR OUTLET Xx 1 t gt 4 gt 1 1 ADJUSTABLE k ADJUSTABLE VENTILATOR VENTILATOR CODE C RAM AIR FLOW VENTILATING AIR HEATED AIR BLENDED AIR MECHANICAL CONNECTION Figure 7 8 Cabin Heating Ventilating and Defrosting System SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M PITOT STATIC SYSTEM AND INSTRUMENTS The pitot static system supplies ram air pressure to the airspeed indicator and static pressure to the airspeed indicator rate of climb indicator and altimeter The system is composed of a heated pitot tube mounted on the lower surface of the left wing an external static port on the lower left side of the forward fuselage and the associated plumb ing necessary to connect the instruments to the sources The heated pitot system consists of a heating element in the pitot tube a rocker type switch labeled PITOT HT on the lower left side of the instru ment panel a 10 amp circuit breaker under the engine controls on the in strument panel and associated wiring When the pitot heat switch is turned on the element in the pitot tube is heated electrically to maintain proper o
106. he windshield for visibility in the landing approach 10 Perform a landing approach using a forward slip if necessary for improved visibility 11 Approach at 65 to 75 KIAS depending upon the amount of ice accumulation 12 Perform a landing in level attitude 3 7 3 CESSNA EMERGENCY PROCEDURES MODEL 150M LANDING WITH A FLAT MAIN TIRE 1 Wing Flaps AS DESIRED 2 Approach NORMAL 3 Touchdown GOOD TIRE FIRST hold airplane off flat tire as long as possible with aileron control ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS OVER VOLTAGE LIGHT ILLUMINATES 1 Master Switch OFF both sides 2 Master Switch ON 3 Over Voltage Light OFF If over voltage light illuminates again 4 Hlight TERMINATE as soon as practical AMMETER SHOWS DISCHARGE 1 Alternator OFF 2 Nonessential Electrical Equipment OFF 3 Flight TERMINATE as soon as practical 3 8 CESSNA SECTION 3 MODEL 150M EMERGENCY PROCEDURES AMPLIFIED PROCEDURES ENGINE FAILURE If an engine failure occurs during the takeoff run the most important thing to do is stop the airplane on the remaining runway Those extra items on the checklist will provide added safety during a failure of this type Prompt lowering of the nose to maintain airspeed and establish a glide attitude is the first response to an engine failure after takeoff most cases the landing should be planned straight ahead with only s
107. hort Field Takeoff Flaps Up Speed at 50 60 KIAS Climb Flaps Up 65 75 KIAS Best Rate of Climb Sea Level 68 KIAS Best Rate of Climb 10000 Feet 7 6 KIAS Best Angle of Climb Sea Level thru 10000 Feet 202022222 26 KIAS Landing Approach Normal Approach Flaps Up 8 60 70 KIAS Normal Approach Flaps 40 50 60 KIAS short Field Approach Flaps 40 22 KIAS Balked Landing Maximum Power Flaps 20 55 KIAS Maximum Recommended Turbulent Air Penetration Speed tN ee ee 97 KIAS 93 KIAS 589 1 1 88 KIAS Maximum Demonstrated Crosswind Velocity 13 KNOTS 4 3 SECTION 4 CESSN NORMAL PROCEDURES js ao NOTE Visually check airplane for general condition during walk around inspection In cold weather remove even small accumulations of frost ice or snow from wing tail and control surfaces Also make sure that control surfaces contain no internal accumula tions of ice or debris night flight is planned check operation of all lights and make sure a flash light is available Figure 4 1 Preflight Inspection 4 4 CESSNA SECTION 4 MODEL 150M NORMAL PROCEDURES CHECKLIST PROCEDURES PREFLIGHT INSPECTION 1 2 3 4 5 CABIN 1 Control Wheel Lock REMOVE 2 Ignition Switch OFF 3 Master Switch ON
108. iming will be necessary As soon as the cylinders begin to fire open the throttle slightly to keep it running After starting if the oil gage does not begin to show pressure within 30 seconds in the summertime and about twice that long in very cold weather stop engine and investigate Lack of oil pressure can cause serious engine damage After starting avoid the use of carburetor heat unless icing conditions prevail TAXIING When taxiing it is important that speed and use of brakes be held to a minimum and that all controls be utilized see Taxiing Diagram Figure 4 2 to maintain directional control and balance The carburetor heat control knob should be pushed full in during all ground operations unless heat is absolutely necessary the knob is pulled out to the heat position air entering the engine is not filtered Taxiing over loose gravel or cinders should be done at low engine speed to avoid abrasion and stone damage to the propeller tips The nose wheel is designed to automatically center straight ahead when the nose strut is fully extended In the event the nose strut is over 4 11 4 CESSNA NORMAL PROCEDURES MODEL 150M USE DOWN AILERON USE DOWN AILERON ON LH WING AND ON RH WING AND DOWN ELEVATOR DOWN ELEVATOR CODE NOTE WIND Strong quartering tail winds require caution DIRECTION Avoid sudden bursts of the throttle and sharp braking when the airplane is in this attitude Use the st
109. in feet per minute The pointer is actuated by atmospheric pressure changes resulting from changes of altitude as supplied by the static source 7 28 CESSNA SECTION 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS ALTIMETER Airplane altitude is depicted by a barometric type altimeter A knob near the lower left portion of the indicator provides adjustment of the instrument s barometric scale to the current altimeter setting VACUUM SYSTEM AND INSTRUMENTS An engine driven vacuum system see figure 7 9 provides the suction necessary to operate the attitude indicator and directional indicator The system consists of a vacuum pump mounted on the engine a vacuum re lief valve and vacuum system air filter on the aft side of the firewall be low the instrument panel and instruments including a suction gage on the left side of the instrument panel ATTITUDE INDICATOR An attitude indicator 15 available and gives a visual indication of flight attitude Bank attitude is presented by a pointer at the top of the indicator relative to the bank scale which has index marks at 10 20 30 60 and 90 either side of the center mark Pitch and roll attitudes are presented by a miniature airplane in relation to the horizon bar A knob at the bottom of the instrument is provided for in flight adjust ment of the miniature airplane to the horizon bar for a more accurate flight attitude indication DIRECTIONAL INDICATOR directional i
110. indicators cannot be relied upon for accurate readings during skids slips or unusual attitudes The fuel system is equipped with drain valves to provide a means for the examination of fuel in the system for contamination and grade The system should be examined before the first flight of every day ana after each refueling by using the sampler cup grovided to drain fuel from the wing tank sumps and by utilizing the fuel strainer drain under an access panel on the right side of the engine cowling The fuel tank should be filled after each flight to prevent condensation BRAKE SYSTEM The airplane has a single disc hydraulically actuated brake on each main landing gear wheel Each brake is connected by a hydraulic line to a master cylinder attached to each of the pilot s rudder pedals The brakes are operated by applying pressure to the top of either the left pilot s or right copilot s set of rudder pedals which are interconnected When the airplane is parked both main wheel brakes may be set by utiliz ing the parking brake which is operated by a knob on the lower left side of the instrument panel For maximum brake life keep the brake system properly maintained and minimize brake usage during taxi operations and landings Some of the symptoms of impending brake failure are gradual decrease in braking action after brake application noisy or dragging 7 21 SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M brak
111. ine Broken or loose alternator wiring is most likely the cause of alternator failures although other factors could cause the problem A damaged or improperly adjusted voltage regulator can also cause malfunctions Problems of this nature constitute an electrical emergency and should be dealt with immediately Electrical power malfunctions usually fall into two categories excessive rate of charge and insufficient rate of charge The paragraphs below describe the recommended remedy for each situation EXCESSIVE RATE OF CHARGE After engine starting and heavy electrical usage at low engine speeds such as extended taxiing the battery condition will be low enough to ac 3 14 CESSNA SECTION 3 MODEL 150M EMERGENCY PROCEDURES cept above normal charging during the initial part of a flight However after thirty minutes of cruising flight the ammeter should be indicating less than two needle widths of charging current If the charging rate were to remain above this value on a long flight the battery would overheat and evaporate the electrolyte at an excessive rate Electronic components in the electrical system could be adversely affected by higher than normal voltage if a faulty voltage regulator setting is causing the overcharging To preclude these possibilities an over voltage sensor will automati cally shut down the alternator and the over voltage warning light will illuminate if the charge voltage reaches approximately 16 volts Assum
112. ing a fire hazard in the event 4 CESSNA NORMAL PROCEDURES MODEL 150M of a backfire Ifthis occurs maintain a cranking action to suck flames into the engine outside attendant with fire extinguisher is advised for cold starts without pre eat During cold weather operations no indication will be apparent on the oil temperature gage prior to takeoff if outside air temperatures are very cold After a suitable warm up period 2 to 5 minutes at 1000 RPM ac celerate the engine several times to higher engine RPM Ifthe engine ac celerates smoothly and the oil pressure remains normal and steady the airplane is ready for takeoff When operating in temperatures below 18 C avoid using partial car buretor heat Partial heat may increase the carburetor air temperature to the 0 to 21 range where icing is critical under certain atmospheric conditions NOISE ABATEMENT _ Increased emphasis on the quality of our environment quires renewed effort on the part of all pilots to minimize the effect of airplane noise on the public We as pilots can demonstrate our concern for environmental im provement by application ofthe following suggested procedures and thereby tend to build public support for aviation 1 Pilots operating aircraft under VFR over outdoor assemblies of persons recreational and park areas and other noise sensitive areas should make every effort to fly not less than 2000 feet above
113. ing specified ALTERNATOR CHECK Prior to flights where verification of proper alternator and voltage regulator operation is essential such as night or instrument flights a positive verification can be made by loading the electrical system mo mentarily 3 to 5 seconds with the landing light or by operating the wing flaps during the engine runup 1700 RPM The ammeter will remain within a needle width of its initial position if the alternator and voltage regulator are operating properly TAKEOFF POWER CHECK It is important to check full throttle engine operation early in the 4 13 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 150M takeoff run sign of rough engine operation or acceleration is 2900 cause for discontinuing the takeoff If this occurs you are justified in aD a thorough full throttle static runup before another takeoff is attempted engine should run smoothly and turn appro imately 2460 to 2560 RPM with carburetor heat off and mix ture rich NOTE At higher airport altitudes this check should be made e mixture leaned to provide maximum engine Full throttle runups over loose gravel are especially harmful to pro peller tips When takeoffs must be made over a gravel surface itis very important that the throttle be advanced slowly This allows the air pene to start rolling before high RPM is developed and the gravel will e blown back of the propeller rather than pulled into it
114. ion will remove receiver output to either headphones or the speaker STATIC DISCHARGERS If frequent IFR flights are planned installation of wick type static dischargers is recommended to improve radio communications during flight through dust or various forms of precipitation rain snow or ice crystals Under these conditions the build up and discharge of static electricity from the trailing edges ofthe wings rudder elevator pro peller tips and radio antennas can result in loss of usable radio signals on all communications and navigation radio equipment Usually the ADF is first to be affected and VHF communication equipment is the last to be affected Installation of static dischargers reduces interference from precipi tation static but it is possible to encounter severe precipitation static conditions which might cause the loss of radio signals even with static dischargers installed Whenever possible avoid known severe precipita tion areas to prevent loss of dependable radio signals If avoidance is impractical minimize airspeed and anticipate temporary loss of radio signals while in these areas 7 32 CESSNA MODEL150M SECTION 8 SECTIONS HANDLING SERVICE amp MAINTENANCE AIRPLANE HANDLING SERVICE amp MAINTENANCE TABLE OF CONTENTS Introduction Identification Plate Owner Follow Up System Publications Airplane File Airplane Inspection Periods FAA Required Inspections Cessna Progress
115. ip can be made without a fuel stop using approximately 60 power The cruise performance chart figure 5 7 is entered at 6000 feet altitude and 20 C above standard temperature These values most nearly correspond to the planned altitude and expected temperature conditions The engine speed chosen is 2600 RPM which results in the following Power 60 True airspeed 98 Knots Cruise fuel flow 4 5 GPH The power computer may be used to determine power and fuel consumption more accurately during the flight FUEL REQUIRED The total fuel requirement for the flight may be estimated using the 5 5 SECTION 5 CESSNA PERFORMANCE MODEL 150M performance information in figures 5 6 and 5 7 For this sample prob lem figure 5 6 shows that a climb from 2000 feet to 6000 feet requires 1 1 gallons of fuel The corresponding distance during the climb is 9 nautical miles These values are for a standard temperature as shown on the climb chart and are sufficiently accurate for most flight plan ning purposes However a further correction for the effect of tempera ture may be made as noted on the climb chart The approximate effect of a non standard temperature is to increase the time fuel and distance by 10 for each 8 C above standard temperature due to the lower rate of climb In this case assuming a temperature 16 C above standard the correction would be x 10 20 Increase With this factor included the fuel estimate would be
116. itations when this avionic equipment is installed However the pilot should be aware that on many Cessna airplanes equipped with the windshield mounted glide slope antenna pts should avoid use of 2700 100 RPM or 1800 100 RPM with a three laded during ILS to avoid oscillations of the glide evia y propeller interference slope tion pointer caused SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when this avionic equipment is installed SECTION 4 NORMAL PROCEDURES COMMUNICATIONS TRANSCEIVER OPERATION 1 OFF VOL Control TURN ON and adjust to desired listening level XMTR SEL Switch SET to desired transceiver 3 SPEAKER PHONE or AUTO Switch SET to desired mode 4 50 25 Fractional MHz Selector Switch SELECT desired frequency does not affect navigation 5 COM Frequency Selector Knobs SELECT desired operating frequency 6 SQ Control ROTATE counterclockwise to decrease background noise as required 7 Mike Button a To Transmit DEPRESS and SPEAK into microphone b Receive RELEASE NAVIGATION RECEIVER OPERATION 1 COM OFF VOL Control TURN ON 2 SPEAKER PHONE or AUTO Switch SET to desired mode Frequency Selector Knobs SELECT desired operating requency PILOT S OPERATING HANDBOOK CESSNA 300 NAV COM SUPPLEMENT TYPE RT 328T 4 NAV VOL Control ADJUST to desired audio level 5 ID
117. ition when TEST position is released Figure 1 Cessna 400 Marker Beacon Operating Controls and Indicator Lights Sheet 2 of 2 CESSNA 400 MARKER BEACON PILOT S OPERATING HANDBOOK TYPE R 402A SUPPLEMENT SECTION 2 LIMITATIONS There is no change to the airplane limitations when this avionic equip ment is installed SECTION 3 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when this avionic equipment is installed SECTION 4 NORMAL PROCEDURES TO OPERATE 1 OFF VOL Control VOL position and adjust to desired listening level 2 LO HI SENS Switch SELECT HI position for airway flying or LO position for ILS approaches 3 SPKR PHONE Switch SELECT speaker or phone audio 4 TEST Switch PRESS and ensure that marker beacon indicator lights are operative NOTE Ensure that BRT control is on enough to view the marker beacon during this test SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic is installed However the installation of an externally mount ed antenna or several related external antennas will result in a minor reduction in cruise performance PILOT S OPERATING HANDBOOK CESSNA 400 GLIDE SLOPE SUPPLEMENT TYPE R 443B SUPPLEMENT CESSNA 400 GLIDE SLOPE Type R 443B SECTION 1 GENERAL The Cessna 400 Glide Slope is an airborne navigation receiver which receives and interprets glide slope pan from a ground b
118. ive Care 1 Cessna Customer Care Program Pilot Conducted Preventive Maintenance Alterations or Repairs Ground Handling Towing Parking Tie Down Jacking Leveling Flyable Storage Servicing Engine Oil Fuel Landing Gear Cleaning and Care Windshield Windows Painted Surfaces Propeller Care Engine Care Interior Care Page KW amp WW M NN Qo 00 Qo 00 00 00 Qo 00 Qo bo N Qo 0 Qo 00 00 See ee eRe eee WWWNNNRRFOO 8 1 8 2 blank CESSNA SECTION 8 MODEL 150M HANDLING SERVICE amp MAINTENANCE INTRODUCTION This section contains factory recommended ground handling and routine care and servicing of your Cessna It also identifies certain inspection and maintenance requirements which must be followed if your airplane is to retain that new plane performance and dependability It is wise to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encoun tered in your locality Keep in touch with your Cessna Dealer and take advantage of his knowledge and experience knows your airplane and how to maintain it He will remind you when lubrications and oil changes are necessary and about other seasonal and periodic services IDENTIFICATION PLATE correspondence regarding your airplane should in
119. lane When loading the airplane children should not be placed or permitted in the baggage compartment unless a child s seat is installed and any ma terial that might be hazardous to the airplane or occupants should not be anywhere in the airplane For baggage area dimensions refer to ection 6 SEATS The seating arrangement consists of two separate adjustable seats for the pilot and passenger and if installed a child s seat in the rear cabin area The pilot s and passenger s seats are available in two designs four way and six way adjustable Four way seats may be moved forward or aft and the seat back angle 7 10 CESSNA SECTION 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS changed To position either seat lift the lever under the inboard corner ofthe seat slide the seat into position release the lever and check that the seat is loccked in place To adjust the seat back pull forward on the knob under the center of the seat and apply pressure to the back To re turn the seat back to the upright position pull forward on the exposed portion of the seat back frame Both seat backs will also fold full forward The six way seats may be moved forward or aft adjusted for height and the seat back angle changed Position either seat by lifting the tubular handle under the inboard front corner ofthe seat bottom and slide the seat to the desired position Release the lever and check that the seat is lock ed in place The seat
120. larly in extended spins These differences are normal and will re sult in variations in the spin characteristics and in the recovery lengths for spins of more than 3 turns However the above recovery procedure should always be used and will result in the most expeditious recovery from any spin Intentional spins with flaps extended are prohibited since the high speeds which may occur during recovery are potentially damaging to the flap wing structure LANDING Normal landing approaches can be made with power on or power off at speeds of 60 to 70 KIAS with flaps up and 50 to 60 KIAS with flaps down Surface winds and air turbulence are usually the primary factors in deter mining the most comfortable approach speeds Actual touchdown should be made with power off and on the main wheels first nose wheel should be lowered smoothly to the runway as speed is diminished SHORT FIELD LANDING For a short field landing in smooth air conditions make an ap proach at 52 KIAS with 40 flaps using enough power to control the glide path After all approach obstacles are cleared progressively re 4 19 SECTION 4 CESSNA NORMAL PROCEDURES MODEL 150M duce power and maintain 52 KIAS by lowering the nose of the airplane Touchdown should be made with power off and on the main wheels first Immediately after touchdown lower the nose wheel and apply heavy braking as required For maximum brake effectiveness retract the flaps hold full nos
121. lay lamp glow steadily during duration of IDENT pulse trans mission DIMMER DIM CONTROL Allows pilot to control brilliance of reply lamp SELF TEST TST SWITCH When depressed causes transponder to generate a self interrogating signal to provide a check of trans ponder operation Reply lamp will glow steadily to verify self test operation REPLY CODE SELECTOR SWITCHES 4 Select assigned Mode A reply code REPLY CODE INDICATORS 4 Display selected Mode A reply code REMOTE MOUNTED DIGITIZER Provides an altitude reporting range of 1000 feet up to the airplane s maximum service ceiling Figure 1 Cessna 400 Transponder and Altitude Encoder Blind Sheet2 of 2 CESSNA 400 TRANSPONDER PILOT S OPERATING HANDBOOK AND ALTITUDE ENCODER BLIND SUPPLEMENT SECTION 2 LIMITATIONS There is no change to the airplane limitations when this avionic equip ment is installed However a placard labeled ALTITUDE ENCODER EQUIPPED must be installed near the altimeter SECTION 3 EMERGENCY PROCEDURES TO TRANSMIT AN EMERGENCY SIGNAL 1 Function Switch ON 2 Reply Code Selector Switches SELECT 7700 operating code 3 ID Switch DEPRESS then RELEASE to effect immediate identi fication of aircraft on ground controller s display TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Function Switch ON 2 Reply Code Selector Switches
122. mall changes in direction to avoid obstructions Altitude and airspeed are seldom suf ficient to execute a 180 gliding turn necessary to return to the runway The checklist procedures assume that adequate time exists to secure the fuel and ignition systems prior to touchdown After an engine failure in flight the best glide speed as shown in Fig ure 3 1 should be established as quickly as possible While gliding to ward a suitable landing area an effort should be made to identify the cause of the failure If time permits an engine restart should be attempted as shown in the checklist If the engine cannot be restarted a forced landing without power must be completed SPEED 60 KIAS PROPELLER WIND WILLING FLAPS UP ZERO WIND HEIGHT ABOVE TERRAIN FT 0 2 4 6 8 10 12 14 16 18 20 GROUND DISTANCE NAUTICAL MILES Figure 3 1 Maximum Glide 3 9 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 150M FORCED LANDINGS If all attempts to restart the engine fail and a forced landing 1 imminent select a suitable field and prepare for the landing as dis cussed in the checklist for engine off emergency landings Before attempting an off airport landing with engine power avail able one should drag the landing area at a safe but low altitude to inspect the terrain for obstructions and surface conditions proceeding as dis cussed under the Precautionary Landing With Engine Power checklist Prepare for ditching by securing o
123. nd 1000 feet ALTIMETER SETTING SCALE DRUM TYPE Indicates se lected altimeter setting in the range of 27 9 to 3 1 O inches of mercury on the standard altimeter or 950 to 1050 millibars on the optional altimeter ALTIMETER SETTING KNOB Dials in desired altimeter setting in the range of 27 9 to 31 0 inches of mercury on the standard altimeter or 950 to 1050 millibars on the optional altimeter Figure 1 Cessna 300 Transponder and Encoding Altimeter Sheet 2 of 2 CESSNA 300 TRANSPONDER PILOT S OPERATING HANDBOOK AND ENCODING ALTIMETER SUPPLEMENT SECTION 2 LIMITATIONS There is no change to the airplane limitations when this avionic equip ment is installed SECTION 3 EMERGENCY PROCEDURES TO TRANSMIT AN EMERGENCY SIGNAL 1 Function Switch ON Q Reply Code Selector Knobs SELECT 7700 operating code 3 ID Switch DEPRESS then RELEASE to effect immediate identi fication of aircraft on ground controller s display TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL COMMUNICATIONS WHEN IN A CONTROLLED ENVIRONMENT 1 Function Switch ON Q Reply Code Selector Knobs SELECT 7700 operating code for 1 minute then SELECT 7600 operating code for 15 minutes and then REPEAT this procedure at same intervals for remainder of flight 3 ID Switch DEPRESS then RELEASE at intervals to effect immediate identification of aircraft on ground controller s display SECTION 4 NORMAL PROCEDURES BEFORE TAKEOFF
124. ndicator is available and displays airplane heading on a compass card in relation to a fixed simulated airplane image and index The directional indicator will precess slightly over a period of time Therefore the compass card should be set in accordance with the mag netic compass just prior to takeoff and occasionally re adjusted on ex tended flights knob on the lower left edge of the instrument is used to adjust the compass card to correct for any precession SUCTION GAGE A suction gage 1 located on the left side of the instrument panel and indicates in inches of mercury the amount of suction available for opera ion of the attitude indicator and directional indicator The desired suc tion range is 4 6 to 5 4 inches of mercury A suction reading below this range may indicate a system malfunction or improper adjustment and in this case the indicators should not be considered reliable 7 29 SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M CODE REEL AIR 2 OVERBOARD Z VENT LINE VACUUM IN LLL DISCHARGE AIR VACUUM RELIEF VALVE ATTITUDE INDICATOR SUCTION DIRECTIONAL INDICATOR N 3 wr NN 5 7 3 NS DES VACUUM SYSTEM FILTER t SN 1 Figure 7 9 Vacuum System CESSNA SECTION 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS STALL WARNING SYSTEM The airplane is equipped with a stall warning sys
125. nding on which program you choose to establish for your airplane ile these important inspections will be you by any Cessna Dealer in most cases you will prefer to have the Dealer from whom you purchased the airplane accomplish this work 8 6 CESSNA SECTION 8 MODEL 150M HANDLING SERVICE amp MAINTENANCE PILOT CONDUCTED PREVENTIVE MAINTENANCE A certified pilot who owns or operates an airplane not used as an air carrier is authorized by FAR Part 43 to perform limited maintenance on his airplane Refer to FAR Part 43 for a list of the specific maintenance operations which are allowed NOTE Pilots operating airplanes of other than U S registry should refer to the regulations of the country of certi fication for information on preventive maintenance that may be performed by pilots A Service Manual should be obtained prior to performing any preven tive maintenance to ensure that proper procedures are followed our Cessna Dealer should be contacted for further information or for required maintenance which must be accomplished by appropriately licensed per sonnel ALTERATIONS OR REPAIRS It is essential that the FAA be contacted prior to any alterations on the airplane to ensure that airworthiness ofthe airplane is not violated Alterations or repairs to the airplane must be accomplished by licensed personnel GROUND HANDLING TOWING The airplane is most easily and safely maneuvered by hand with the tow bar
126. not receiving subscription service you will want to keep in touch with your Cessna Dealer for information concerning the change status of the handbook Subsequent changes will be made in the form of stickers These should be examined and attached to the appropriate page in the handbook immediately after receipt the handbook should not be used for opera tional purposes until it has been updated to a current status iii Gv blank CESSNA MODEL 150M SECTION 1 GENERAL TABLE OF CONTENTS Three View Introduction Descriptive Data Engine Propeller Fuel Oil Maximum Certificated Weights Standard Airplane Weights Cabin and Entry Dimensions Baggage Space Dimensions Specific Loadings Symbols Abbreviations and Terminology General Airspeed Terminology and Sabo Meteorological Terminology Engine Power Terminology Airplane Performance and Flight Planning Weight and Balance Terminology sus SECTION 1 GENERAL 9 2 ga e Pip pipipip CR 6 bo do bo bo bo d dA CA DONO E T RR SECTION 1 CESSNA GENERAL MODEL 150M NOTES 1 Wing span shown with strobe lights installed 2 Maximum height shown with nose gear de pressed ail tires and nose strut properly in flated and flashing beacon installed Wheel base length is 58 Propeller ground clearance is 12 Wing area is 160 square feet on e Minimum turning radius pivot point to outboard
127. nted digitally tuned automatic direction finder It is designed to provide continuous 1 kHz digital tuning in the frequency range of 200 kHz to 1 699 kHz and eliminates the need for mechanical band switching The system is comprised of a receiver loop antenna bearing indicator and a sense antenna In addition when two or more radios are installed speaker phone selector switches are provided Each control function is described in Figure 1 The Cessna 300 ADF can be used for position plotting and homing procedures and for aural reception of amplitude modulated AM signals With the function selector knob at ADF the Cessna 300 ADF provides a visual indication on the bearing indicator ofthe bearing to the trans mitting station relative to the nose ofthe airplane This is done by com bining signals from the sense antenna with signals from the loop antenna With the function selector knob at REC the Cessna 300 ADF uses only the sense antenna and operates as a conventional low frequency receiver The Cessna 300 ADF is designed to receive transmission from the following radio facilities commercial broadcast stations low frequency range stations FAA radio beacons and ILS compass locatorSc lof6 CESSNA 300 ADF PILOT S OPERATING HANDBOOK TYPE R 546E SUPPLEMENT OFF VOL CONTROL Controls primary power and audio output level Clockwise rotation from OFF position applies primary power to receiver further clockwise rotation inc
128. nternational distress frequencies of 121 5 and 243 0 MHz Some ELT units in export aircraft transmit only on 121 5 MHz General aviation and commercial aircraft the FAA and CAP monitor 121 5 MEZ and 243 0 MHz is monitored by the military Following a crash landing the ELT will provide line of sight transmission up to 1 miles at 10 000 feet The duration of ELT transmissions is affected by ambient temperature At temperatures of 421 to 54 C 70 to 130 F continuous transmission for 115 hours can be expected a temperature of 40 C 40 F will shorten the duration to 70 hours The ELT is readily identified as a bright orange unit mounted behind the baggage compartment wall in the tailcone To gain success to the unit remove the baggage compartment wall The ELT is operated by a control panel at the forward facing end ofthe unit see figure 1 SECTION 2 LIMITATIONS There is no change to the airplane limitations when this equipment is installed 1 of4 EMERGENCY LOCATOR PILOT S OPERATING HANDBOOK TRANSMITTER ELT SUPPLEMENT TO TRANSMIT se COVER Removable for access to battery FUNCTION SELECTOR SWITCH 3 position toggle switch ON Activates transmitter instantly Used for test purposes and if g switch is inoperative OFF Deactivates transmitter Used during shipping storage and following rescue ARM Activates transmitter only when g switch receives 5g or more impact ANTENNA
129. o maintain a 70 KIAS glide 5 Keep hands off the control wheel using rudder control to hold a straight heading 6 Apply carburetor heat 7 Clear engine occasionally but avoid using enough power to disturb the trimmed glide 8 Upon breaking out of clouds resume normal cruising flight FLIGHT IN ICING CONDITIONS Flight into icing conditions is prohibited An inadvertent encounter with these conditions can best be handled using the checklist procedures The best procedure of course is to turn back or change altitude to es cape icing conditions SPINS Should an inadvertent spin occur the following recovery procedure should be used 1 RETARD THROTTLE TO IDLE POSITION 2 PLACE AILERONS IN NEUTRAL POSITION 3 12 CESSNA SECTION 3 MODEL 150M EMERGENCY PROCEDURES 3 APPLY AND HOLD FULL RUDDER OPPOSITE TO THE DIREC TION OF ROTATION 4 JUST AFTER THE RUDDER REACHES THE STOP MOVE THE CONTROL WHEEL BRISKLY FORWARD FAR ENOUGH TO BREAK THE STALL Full down elevator may be required at aft center of gravity loadings to assure optimum recoveries 5 HOLD THESE CONTROL INPUTS UNTIL ROTATION STOPS Premature relaxation ofthe control inputs may extend the recovery 6 AS ROTATION STOPS NEUTRALIZE RUDDER AND MAKE SMOOTH RECOVERY FROM THE RESULTING DIVE NOTE If disorientation precludes a visual determination of the direction of rotation the symbolic airplane in the turn coordinator or the needle ofthe turn an
130. onal cabin heat a carburetor airbox heat outlet cap insulation for the engine crankcase breather line and a placard to be installed on the map com partment door This equipment should be installed for operations in temperatures consistently below 7 C 20 F Once installed the crank 7 18 CESSNA SECTION 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS case breather insulation is approved for permanent use regardless of temperature PROPELLER The airplane is equipped with a two bladed fixed pitch one piece forged aluminum alloy propeller which is anodized to retard corrosion The propeller is 69 inches in diameter FUEL SYSTEM The airplane may be with either a standard fuel system a long range system see figure 7 6 Both systems consist of two vented fuel tanks one in each fuel shutoff valve fuel strainer manual primer and carburetor efer to figure 7 5 for fuel quantity data for oth systems Fuel flows by gravity from the two wing tanks to a fuel shutoff valve With the valve in the ON position fuel flows through a strainer to the car buretor From the carburetor mixed fuel and air flows to the cylinders through intake manifold tubes The manual primer draws its fuel from the fuel strainer and injects it into the intake manifold FUEL QUANTITY DATA U S GALLONS TOTAL TOTAL TANKS UNUSABLE FUEL MESE FUEL VOLUME CONDITIONS STANDARD 13 Gal Each 22 5 3 5 26 0 LONG
131. ormance PILOT S OPERATING HANDBOOK CESSNA 400 TRANSPONDER SUPPLEMENT AND ENCODING ALTIMETER SUPPLEMENT CESSNA 400 TRANSPONDER RT 459A AND OPTIONAL ENCODING ALTIMETER EA 401A SECTION 1 GENERAL The Cessna 400 Transponder Type 459A shown in Figure 1 is the airborne component of an Air Traffic Control Radar Beacon System ATCRBS he transponder enables the ATC ground controller to see and identify the aircraft while in flight on the control center s radar Scope more readily The 400 Transponder consists of a panel mounted unit and an exter nally mounted antenna The transponder receives interrogating pulse signals on 1030 MHz and transmits coded pulse train reply signals on 1090 MHz It is capable of replying to Mode A aircraft identification and Mode C altitude reporting interrogations on a selective reply basis any of 4 096 information code selections When an optional panel mounted EA 401A Encoding Altimeter not part of 400 Transponder System is included in the avionic configuration the transponder can provide alti tude reporting in 100 foot increments between 1000 and 35 000 feet All Cessna 400 Transponder operating controls with the exception of the optional altitude encoder s altimeter setting knob are located on the front panel of the unit The altimeter setting knob is located on the en coding altimeter Functions of the operating controls are described in figure 1 lof6
132. ormation is known AIRPLANE CONFIGURATION Takeoff weight 691 kg Usable fuel 85 liter TAKEOFF CONDITIONS Field pressure altitude 1500 Feet Temperature 28 C 16 C above standard Wind component along runway 12 Knot Headwind Field length 3500 Feet 5 3 SECTION 5 CESSNA PERFORMANCE MODEL 150M CRUISE CONDITIONS Total distance 330 Nautical Miles Pressure altitude 5500 Feet Temperature 20 C 16 C above standard Expected wind enroute 10 Knot Headwind LANDING CONDITIONS Field pressure altitude 2000 Feet Temperature 25 Field length 3000 Feet TAKEOFF The takeoff distance chart figure 5 4 should be consulted keeping in mind that the distances shown are based on the short field tech nique Conservative distances can be established by reading the chart at the next higher value of altitude and temperature For example in this particular sample problem the takeoff distance information pres ented for a pressure altitude of 2000 feet and a temperature of 30 should be used and results in the following Ground roll 990 Feet Total distance to clear a 50 foot obstacle 1865 Feet These distances are well within the available takeoff field length However a correction for the effect of wind may be made based on Note 3 of the takeoff chart The correction for a 12 knot headwind is 12 Knots 9 Knots 10 13 Decrease This results in the following distances corrected for wind Ground roll zero wind 990 Decrease in
133. ors are avail able the tail should be securely tied down NOTE Ensure that the nose will be held off the ground under all conditions by means of suitable stands or supports under weight supporting bulkheads near the nose of the airplane LEVELING Longitudinal leveling of the airplane 1s accomplished by placing a level on leveling screws located at stations 94 63 and 132 94 on the left side of the tailcone Deflate the nose tire and or lower or raise the nose strut to properly center the bubble in the level Corresponding points on both upper door sills may be used to level the airplane laterally FLYABLE STORAGE Airplanes placed in non operational storage for a maximum of 30 days or those which receive only intermittent operational use for the first 25 hours are considered in flyable storage status Every seventh day during these periods the propeller should be rotated by hand through five revolu tions This action limbers the oil and prevents any accumulation of cor rosion on engine cylinder walls WARNING 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 After 30 days the airplane should be flown for 30 minutes or a ground runup should be made just long enough to produce an oil temperature
134. oud deck to VFR conditions may be appropriate possible obtain radio clearance for an emergency descent through clouds To guard against a spiral dive choose an easterly or westerly heading to minimize compass card swings due to changing bank angles In addition keep hands off the control wheel and steer a straight course with rudder control by monitoring the turn coordinator Occasionally check the com pass heading and make minor corrections to hold an approximate course Before descending into the clouds set up a stabilized let down condition as follows SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 150M 1 Apply full rich mixture 2 Use full carburetor heat 3 Reduce power to set up a 500 to 800 ft min rate of descent 4 Adjust the elevator trim for a stabilized descent at 70 KIAS 5 Keep hands off control wheel 6 Monitor turn coordinator and make corrections by rudder alone 7 Check trend of compass card movement and make cautious cor rections with rudder to stop turn 8 Upon breaking out of clouds resume normal cruising flight RECOVERY FROM A SPIRAL DIVE If a spiral is encountered proceed as follows 1 Close the throttle 2 Stop the turn by using coordinated aileron and rudder control to align the symbolic airplane in the turn coordinator with the horizon reference line 3 Cautiously apply elevator back pressure to slowly reduce the air speed to 70 KIAS hy Adjust the elevator trim control t
135. oughness dictates the use of a single ignition position MAGNETO MALFUNCTION A sudden engine roughness or misfiring is usually evidence of mag neto problems Switching from BOTH to either L or R ignition switch position will identify which magneto is malfunctioning Select different power settings and enrichen the mixture to determine if continued opera tion on BOTH magnetos is practicable If not switch to the good magneto and proceed to the nearest airport for repairs LOW OIL PRESSURE If low oil pressure is accompanied by normal oil temperature there is a possibility the oil pressure gage or relief valve is malfunctioning A leak in the line to the gage is not necessarily cause for an immediate precautionary landing because an orifice in this line will prevent a sudden loss of oil from the engine sump However a landing at the nearest air port would be advisable to inspect the source of trouble If a total loss of oil pressure is accompanied by a rise in oil tempera ture there is good reason to suspect an engine failure is imminent Re duce engine power immediately and select a suitable forced landing field Use only the minimum power required to reach the desired touchdown spot ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS Malfunctions in the electrical power supply system can be detected by periodic monitoring of the ammeter and over voltage warning light however the cause of these malfunctions is usually difficult to determ
136. own rings Two rings are located on the floor just aft of the seat backs and one ring is located two inches above the floor on each cabin wall at the aft end of area Two additional rings are located at the top aft end of area least four rings should be used to restrain the maximum baggage load of 1208 Ifthe airplane is equipped with utility shelf it should be re moved prior to loading and tying down large baggage items Slide the tab of the locking clips on each end of the shelf to disengage the shelf from the aircraft structure After baggage is loaded and secured either stow the shelf or if space permits install it for storing small articles Figure 6 4 Baggage Loading and Tie Down SECTION 6 CESSNA WEIGHT amp BALANCE MODEL 150M EQUIPMENT LIST CABIN HEIGHT MEASUREMENTS FIREWALL 56 0 FACE OF INSTRUMENT PANEL DOOR OPENING DIMENSIONS WIDTH WIDTH HEIGHT HEIGHT WIDTH TOP BOTTOM FRONT REAR LWR WINDOW LINE 314 334 4 31 31 CABIN FLOOR REAR WALL OF CABIN CABIN WIDTH MEASUREMENTS TIE DOWN RINGS 6 CABIN l 1 STATIONS 0 0 10 20 30 40 50 60 70 80 9094 C G ARMS 56 0 Figure 6 5 Internal Cabin Dimensions 6 9 SAMPLE AIRPLANE YOUR AIRPLANE Momenft Moment Ib ins Weight Ib ins 1000 Ibs 1000 SAMPLE LOADING PROBLEM Weight Ibs Basic Empty Wei
137. peration in possible icing conditions Pitot heat should be used only as required AIRSPEED INDICATOR The airspeed indicator is calibrated in knots and miles per hour Limitation and range markings include the white arc 42 to 85 knots green arc 47 to 107 knots yellow arc 107 to 141 knots and a red line 141 knots If a true airspeed indicator is installed it is equipped with a rotatable ring which works in conjunction with the airspeed indicator dial in a man ner similar to the operation of a flight computer To operate the indicator first rotate the ring until pressure altitude is aligned with outside air tem perature in degrees Fahrenheit Pressure altitude should not be confused with indicated altitude To obtain pressure altitude momentarily set the barometric scale on the altimeter to 29 92 and read pressure altitude on the altimeter Be sure to return the altimeter barometric scale to the original barometric setting after pressure altitude has been obtained Having set the ring to correct for altitude and temperature then read the airspeed shown on the rotatable ring by the indicator pointer For best accuracy this indication should be corrected to calibrated airspeed by referring to the Airspeed Calibration chart in Section 5 Knowing the cali brated airspeed read true airspeed on the ring opposite the calibrated air speed RATE OF CLIMB INDICATOR The rate of climb indicator depicts airplane rate of climb or descent
138. plies to interrogations 4 ID Button DEPRESS momentarily when instructed by ground controller to squawk IDENT reply lamp will glow steadily in dicating IDENT operation TO TRANSMIT MODE C ALTITUDE REPORTING CODES IN FLIGHT 1 Reply Code Selector Knobs SELECT assigned code 2 Function Switch ALT NOTE When directed by ground controller to stop altitude squawk turn Function Switch to ON for Mode operation only NOTE Pressure altitude is transmitted by the transponder for altitude squawk and conversion to indicated alti tude is done in ATC computers Altitude squawked will only agree with indicated altitude when the local altimeter setting in use by the ground controller is set in the aircraft altimeter 3 DIM Control ADJUST light brilliance of reply lamp TO SELF TEST TRANSPONDER OPERATION 1 Function Switch SBY and wait 30 seconds for equipment to warm up 2 Function Switch ON or ALT 3 TST Button DEPRESS reply lamp should light brightly regardless of DIM control setting 4 TST Button Release for normal operation CESSNA 300 TRANSPONDER PILOT S OPERATING HANDBOOK AND ALTITUDE ENCODER BLIND SUPPLEMENT SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mounted antenna or several related external antennas will result in a minor re duction in cruise perf
139. pon request 1 Airplane Log Book 2 Engine Log Book Most of the items listed are required by the United States Federal Aviation Regulations Since the Regulations of other nations may require other documents and data owners of airplanes not registered in the United States should check with their own aviation officials to determine their in dividual requirements Cessna recommends that these items plus the Pilot s Operating Handbook Pilot s Checklists Power Computer Customer Care Pro gram book and Customer Care Card be carried in the airplane at all times AIRPLANE INSPECTION PERIODS FAA REQUIRED INSPECTIONS As required by Federal Aviation Regulations all civil aircraft of U S registry must undergo a complete inspection annual each twelve calendar months In addition to the required ANNUAL inspection air craft operated commercially for hire must have a complete inspection every 100 hours of operation The FAA may require other inspections by the issuance of airworthi ness directives applicable to the airplane engine propeller and compo nents It is the responsibility of the owner operator to ensure compliance with all applicable airworthiness directives and when the inspections are repetitive to take appropriate steps to prevent inadvertent noncompliance In lieu of the 100 HOUR and ANNUAL inspection requirements an airplane may be inspected in accordance with a progressive inspection schedule which allows the
140. pressure is 10 PSI red line the normal operating range is 30 to 60 PSI green arc and maximum pressure is lOO PSI red line Oil temperature is indicated by a gage located on the subpanel The gage is operated by an electrical resistance type temperature sensor which receives power from the airplane electrical system temperature lim itations are the normal operating range green arc which is 38 100 F to 116 C 240 F and the maximum red line which is 116 C 240 F The engine driven mechanical tachometer is located near the upper center portion of the instrument panel The instrument is calibrated in increments of 100 RPM and indicates both engine and propeller speed An hour meter below the center of the tachometer dial records elapsed engine time in hours and tenths Instrument markings include a normal operating range green arc of 2000 to 2750 RPM and a maximum allow able red line of 2750 RPM NEW ENGINE BREAK IN AND OPERATION The engine underwent a run in at the factory and is ready for the full range of use It is however suggested that cruising be accomplished at 65 to 75 power until a total of 50 hours has accumulated or oil consump tion has stabilized This will ensure proper seating of the rings The airplane is delivered from the factory with corrosion preventive oil in the engine If during the first 25 hours oil must be added use only aviation grade straight mineral oil conforming to Specifica
141. r element at this time Refill sump with straight mineral oil and use until a total of 50 hours has accumulated or oil consumption has sta bilized then change to dispersant oil airplanes not equipped with an oil filter drain the engine oil sump and clean the oil pressure screen each 50 hours thereafter On airplanes which have an oil fil ter the oil change interval may be extended to 100 hour intervals providing the oil filter element is changed at 50 hour intervals Change engine oil at least every 6 months even though less than the recommended hours have accumulated Reduce intervals for pro longed operation in dusty areas cold climates or when short flights and long idle periods result in sludging conditions FUEL APPROVED FUEL GRADES AND COLORS 80 Formerly 80 87 Grade Aviation Fuel Red 10011 Grade Aviation Fuel Blue 100 formely 100 130 Grade Aviation Fuel Green CAPACITY EACH STANDARD TANK 13 Gallons CAPACITY EACH LONG RANGE TANK 19 Gallons NOTE Due to cross feeding between fuel tanks the tanks should be re topped after each refueling to assure maximum capacity LANDING GEAR NOSE WHEEL TIRE PRESSURE 30 PSI on 5 00 5 4 Ply Rated Tire MAIN WHEEL TIRE PRESSURE 21 PSI on 6 00 6 4 Ply Rated Tires NOSE GEAR SHOCK STRUT Keep filled with MIL H 5606 hydraulic fluid and inflated with air to 20 PSI Do not over inflate SECTION 8 CESSNA HANDLING SERVICE
142. r overcast the flashing light reflected from water droplets or particles in the atmosphere particularly at night can produce vertigo and loss of orientation The two high intensity strobe lights will enhance anti collision protec tion However the lights should be turned off when taxiing in the vicinity of other airplanes or during night flight through clouds fog or haze INTERIOR LIGHTING Instrument and control panel lighting is provided by flood lighting and integral lighting Two concentric rheostat control knobs on the lower left side of the instrument panel labeled PANEL LT RADIO LT control the intensity of both flood and integral lighting Instrument and control panel flood lighting consists of a single red 7 25 SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M flood light in the forward part of the overhead console To use the flood lighting rotate the PANEL LT rheostat control knob clockwise to the de sired intensity The radio equipment and magnetic compass have integral lighting The light intensity of all integral lighting is controlled by the RADIO LT rheostat control knob A cabin dome light is located in the aft part of the overhead console and is operated by a switch on the lower portion of the instrument panel To turn the light on place the switch in the ON position control wheel map light is available and is mounted on the bottom of the pilot s control wheel The light illuminates th
143. r Mode C altitude reporting pulses selected auto matically by the interrogating signal 2 REPLY LAMP Lamp flashes to indicate transmission of pulses glows steadily to indicate transmission of IDENT pulse or satisfactory self test operation Reply lamp will also glow steadily during initial warm up period Cessna 300 Transponder and Altitude Encoder Blind Figure 1 Sheet 1 of 2 PILOT S HANDBOOK CESSNA 300 TRANSPONDER SUPPLEMENT AND ALTITUDE ENCODER BLIND 3 IDENT ID SWITCH When depressed selects special pulse identifier to be transmitted with transponder reply to effect immediate identification of aircraft on ground controllers dis play Reply lamp will glow steadily during duration of IDENT pulse transmission 4 DIMMER DIM CONTROL Allows pilot to control brilliance of reply lamp 5 SELF TEST TST SWITCH When depressed causes trans ponder to generate a self interrogating signal to provide a check of transponder operation Reply lamp will glow steadily to verify self test operation 6 REPLY CODE SELECTOR KNOBS 4 Select assigned Mode reply code 7 REPLY CODE INDICATORS 4 Display selected Mode reply code 8 REMOTE MOUNTED DIGITIZER Provides an altitude reporting code range of 1000 feet up to the airplane s maximum service ceiling Figure 1 Cessna 300 Transponder and Altitude Encoder Blind Sheet 2 of 2 CESSNA 300 TRANSPONDER PILOT S OPERATING HANDBOOK AND
144. r and attitude indicator will be disabled and the pilot will have to rely on the turn coordinator or the turn and bank indicator if he inadvertently flies into clouds The following instructions assume that only the electrically powered turn coordinator or the turn and bank indicator is operative and that the pilot is not completely pro ficient in instrument flying EXECUTING A 180 TURN IN CLOUDS Upon inadvertently entering the clouds an immediate plan should be made to turn back as follows 1 Note the time of the minute hand and observe the position of the sweep second hand on the clock 2 When the sweep second hand indicates the nearest half minute initiate a standard rate left turn holding the turn coordinator sym bolic airplane wing opposite the lower left index mark for 60 seconds Then roll back to level flight by leveling the miniature airplane 3 Check accuracy of the turn by observing the compass heading which should be the reciprocal of the original heading 4 If necessary adjust heading primarily with skidding motions rather than rolling motions so that the compass will read more ac curately 5 Maintain altitude and airspeed by cautious application of elevator control Avoid over controlling by keeping the hands off the control wheel as much as possible and steering only with rudder EMERGENCY DESCENT THROUGH CLOUDS If conditions preclude reestablishment of VFR flight by a 180 turn a descent through a cl
145. r jettisoning heavy objects located in the baggage area and collect folded coats for protection of occupants face at touchdown Transmit Mayday message on 121 5 MHz giving loca tion and intentions LANDING WITHOUT ELEVATOR CONTROL Trim for horizontal flight with an airspeed of approximately 55 KIAS and flaps lowered to 20 by using throttle and elevator trim controls Then do not change the elevator trim control setting control the glide angle by adjusting power exclusively At flareout the nose down moment resulting from power reduction is an adverse factor and the airplane may hit on the nose wheel Conse quently at flareout the trim control should be set at the full nose up position and the power adjusted so that the airplane will rotate to the hor izontal attitude for touchdown Close the throttle at touchdown FIRES Although engine fires are extremely rare in flight the steps of the appropriate checklist should be followed if one is encountered After completion of this procedure execute a forced landing Do not attempt to restart the engine The initial indication of an electrical fire is usually the odor of burn ing insulation The checklist for this problem should result in elimination of the fire 3 10 CESSNA SECTION 3 MODEL 150M EMERGENCY PROCEDURES EMERGENCY OPERATION IN CLOUDS Vacuum System Failure In the event of a vacuum system failure during flight in marginal weather the directional indicato
146. ration Reply Lamp will glow steadily to verify self test operation REPLY CODE SELECTOR SWITCHES 4 Select assigned Mode A Reply Code REPL Y CODE INDICATORS 4 Display selected Mode A Reply Code 1000 DRUM TYPE INDICATOR Provides digital altitude readout in 1000 foot increments between 1000 feet and 435 000 feet When alti tude is below 10 000 feet a diagonally striped flag appears in the 10 000 foot window OFF INDICATOR WARNING FLAG Flag appears across altitude readout when power is removed from altimeter to indicate that readout is not reliable 100 FOOT DRUM TYPE INDICATOR Provides digital altitude readout in 100 foot increments between O feet and 1000 feet 20 FOOT INDICATOR NEEDLE Indicates altitude in 20 foot increments between 0 feet and 1000 feet ALTIMETER SETTING SCALE DRUM TYPE Indicates selected alti meter setting in the range of 28 1 to 30 99 inches of mercury on the stan dard altimeter or 946 to 1049 millibars on the optional altimeter ALTIMETER SETTING KNOB Dials in desired altimeter setting in the range of 28 1 to 30 99 inches of mercury on standard altimeter or 946 to 1049 millibars on the optional altimeter Figure 1 Cessna 400 Transponder and Encoding Altimeter Operating Controls Sheet 2 of 2 CESSNA 400 TRANSPONDER PILOT S OPERATING HANDBOOK AND ENCODING ALTIMETER SUPPLEMENT SECTION 2 LIMITATIONS _There is no to the airplane limitations when this avionic
147. re IDLE CUT OFF 3 5 SECTION 3 CESSNA EMERGENCY PROCEDURES MODEL 150M 2 Fuel Shutoff Valve OFF 3 Master Switch OFF 4 Cabin Heat and Air OFF except wing root vents 5 Airspeed 85 KIAS fire is not extinguished increase glide speed to find an airspeed which will provide an incombustible mix ture 6 Forced Landing EXECUTE as described in Emergency Land ing Without Engine Power ELECTRICAL FIRE IN FLIGHT 1 Master Switch OFF 2 Other Switches except ignition switch OFF 3 Vents Cabin Air Heat CLOSED 4 Fire Extinguisher ACTIVATE f available After discharging an extinguisher within a closed cabin ventilate the cabin If fire appears out and electrical power is necessary for continuance of flight 5 Master Switch 6 Circuit Breakers CHECK for faulty circuit do not reset 7 Radio Electrical Switches ON one at atime with delay after each until short circuit is localized 8 Vents Cabin Air Heat OPEN when it is ascertained that fire is completely extinguished CABIN FIRE 1 Master Switch OFF 2 Wents Cabin Air Heat CLOSED to avoid drafts 3 Fire Extinguisher ACTIVATE f available After discharging an extinguisher within a closed cabin ventilate the cabin 4 Land the airplane as soon as possible to inspect for damage 3 6 CESSNA SECTION 3 MODEL 150M EMERGENCY PROCEDURES WING FIRE 1 N
148. re additional service inspections or tests For these regulatory requirements owners should check with local aviation officials where the airplane is being operated For quick and ready reference quantities materials and specifica tions for frequently used service items are as follows ENGINE OIL GRADE Aviation Grade SAE 40 Above 4 402 Aviation Grade SAE 10W30 or SAE 20 Below 4 C 40 F Multi viscosity oil with a range of SAE 10W30 is recommended for improved starting in cold weather Ashless dispersant oil conform ing to Continental Motors Specification MHS 24A must be used NOTE Your Cessna was delivered from the factory with a corro sion preventive aircraft engine oil If oil must be added during the first 25 hours use only aviation grade straight mineral oil conforming to Specification No MIL L 6082 CAPACITY OF ENGINE SUMP 6 Quarts Do not operate on less than 4 quarts To minimize loss of oil through breather fill to 5 quart level for normal flights of less than 3 hours For extended flight fill to 6 quarts These quantities refer to oil dipstick level readings During oil and oil filter changes one addi tional quart is required when the filter element is changed CESSNA SECTION 8 MODEL 150M HANDLING SERVICE amp MAINTENANCE OIL AND OIL FILTER CHANGE After the first 25 hours of operation drain engine oil sump and clean the oil pressure screen If an oil filter is installed change the filte
149. reases audio level FREQUENCY SELECTORS Knob A selects 100 kHz incre ments of receiver frequency knob B selects 10 kHz incre ments and knob C selects 1 kHz increments Figure 1 Cessna 300 ADF Operating Controls and Indicators Sheet 1 of 2 PILOT S OPERATING HANDBOOK CESSNA 300 ADF SUPPLEMENT TYPE R 546E 3 FUNCTION SWITCH BFO Selects operation as communication receiver using only sense antenna and activates 1000 Hz tone beat frequency oscillator to permit coded identifier of stations transmitting keyed CW signals Morse Code to be heard REC Selects operation as standard communication re ceiver using only sense antenna ADF Set operates as automatic direction finder using loop and sense antennas TEST Momentary on position used during ADF operation to test bearing reliability When held in TEST position slews indicator pointer clockwise when released if bearing is reliable pointer returns to original bearing position 4 INDEX ROTATABLE CARD Indicates relative magnetic or true heading of aircraft as selected by HDG control 5 POINTER Indicates station bearing in degrees of azimuth relative to the nose of the aircraft When heading control is adjusted indicates relative magnetic or true bearing of radio signal 6 HEADING CONTROL Rotates card to set in relative magnetic or true bearing information 1 Cessna 300 ADF Operating Controls and Indicators Sheet 2 of 2 3
150. rs are 15096 of the above and in all cases the structure meets or exceeds design loads KINDS OF OPERATION LIMITS The airplane is equipped for day VFR and may be equipped for night and or operations FAR Part 91 establishes the minimum re quired instrumentation and equipment for these operations The refer ence to types of flight operations on the operating limitations placard re 2 6 CESSNA SECTION 2 MODEL 150M LIMITATIONS fleets equipment installed at the time of Airworthiness Certificate issu ance Flight into known icing conditions is prohibited FUEL LIMITATIONS 2 Long Range Tanks 72 liters each Total Fuel 144liters gallons Usable Fuel all flight conditions 132 liters Unusable Fuel 12 liters NOTE Due to cross feeding between fuel tanks the tanks should be re topped after each refueling to assure maximum capacity Approved Fuel Grades and Colors 95 Grade Automotive Fuel EN 228 Green 100LL Grade Aviation Fuel Blue 2 7 SECTION 2 CESSNA LIMITATIONS MODEL 150M PLACARDS The following information is displayed in the form of composite or individual placards 1 In full view of the pilot The DAY NIGHT VFR IFR entry shown on the example below will vary as the airplane is equipped This airplane is approved in the utility category and must be operated in compliance with the operating limitations as stated in the form of placards markings and manuals MAXIMU
151. s Excessive Rate Of Charge Insufficient Rate Of Charge 3 2 CESSNA MODEL 150M Page 3 1 3 11 3 11 3 12 3 12 3 12 3 13 3 13 3 13 3 14 3 14 3 14 3 14 3 15 CESSNA SECTION 3 MODEL 150M EMERGENCY PROCEDURES INTRODUCTION Section 3 provides checklist and amplified procedures for coping with emergencies that may occur Emergencies caused by airplane or engine malfunctions are ven rare if proper preflight inspections and main tenance are practiced Enroute weather emergencies can be minimized or eliminated by careful heht planning and good judgement when unexpect ed weather is encountered However should an emergency arise the basic guidelines described in this section should be considered and applied as necessary to correct the problem procedures associated with the ELT and other optional systems can be found in Section 9 AIRSPEEDS FOR EMERGENCY OPERATION Engine Failure After Takeoff 60 KIAS Maneuvering Speed TORB g 2 2 s 97 KIAS 657 Kg 2 2 2 2 2 s 903 KIAS 589 kg 2 s s s 88 KTAS Maximum Glide 60 KTAS Precautionary Landing With Engine Power 55 KIAS Landing Without Engine Power Wing Flaps Up 65 KIAS Wing Flaps Down 99 KTAS OPERATIONAL CHECKLISTS ENGINE FAILURES ENGINE FAILURE DURING TAKEOFF RUN 1 Throttle IDLE
152. s will result in a minor reduction in cruise performance OPERATING HANDBOOK CESSNA 400 TRANSPONDER AND ALTITUDE ENCODER BLIND SUPPLEMENT CESSNA 400 TRANSPONDER Type 459 AND OPTIONAL ALTITUDE ENCODER BLIND SECTION 1 GENERAL The Cessna 400 Transponder Type RT 459A shown in Figure 1 is che airborne component of an Air Traffic Control Radar Beacon System ATCRBS The transponder enables the ATC ground controller to see and identify the aircraft while in flight on the control center s radar scope more readily The Cessna 400 Transponder system consists of a panel mounted unit and an externally mounted antenna The transponder receives interroga ting pulse signals 1030 MHz and transmits pulse train reply signals on 1090 MHz The transponder is capable of replying to Mode A air craft identification and also to Mode C altitude reporting when coupled to an optional altitude encoder system The transponder is capable of re plying on both modes of interrogation on a selective reply basis on any of 4 096 information code selections The optional altitude encoder system not part of a standard 400 Transponder system required for Mode C altitude reporting operation consists of a completely independent remote mounted digitizer that is connected to the static system and supplies encoded altitude information to the transponder When the altitude encoder system is coupled to the 400 Transponder system altitude r
153. s may be raised or lowered two inches in one inch steps and should be adjusted prior to flight raise or lower either seat pull forward on a T handle under the seat near the inboard corner force the seat down against spring tension or allow spring tension to raise it to the desired position release the T handle and then allow the seat to move until it locks in place Seat back angle is adjustable by rotating a lever on the rear inboard corner of each seat To adjust either seat back rotate the lever aft and apply pressure against the back until it stops moving then release the lever The seat back may be returned to the up right position by pulling forward on the exposed portion of the lower seat back frame Check that the release lever has returned to its vertical po sition Both seat backs will fold full forward A child s seat is available for installation in the rear of the cabin The seat back is secured to the cabin sidewalls and the seat bottom is attached to brackets on the floor This seat is non adjustable SEAT BELTS AND SHOULDER HARNESSES All seat positions are equipped with seat belts see figure 7 4 pilots and passenger s seats are also equipped with separate shoulder harnesses Integrated seat belt shoulder harnesses with inertia reels can be furnished for the pilot s and passenger s seat positions if desired SEAT BELTS The seat belts used with the pilot s seat passenger s seat and the child s seat
154. s the loaded weight of the airplane Loaded Weight Maximum Maximum Takeoff Weight is the maximum weight approved Takeoff for the start of the takeoff run Weight Maximum Maximum Landing Weight is the maximum weight approved Landing for the landing touchdown Weight Tare Tare is the weight of chocks blocks stands etc used when weighing an airplane and is included in the scale readings Tare is deducted from the scale reading to obtain the actual net airplane weight 1 8 CESSNA MODEL 150M SECTION 2 LIMITATIONS TABLE OF CONTENTS Introduction Airspeed Limitations Airspeed Indicator Markings Power Plant Limitations Power Plant Instrument Markings Weight Limits 4 Center of Gravity Limits Maneuver Limits Flight Load Factor Limits Kinds of Operation Limits t ori eco pe Fon en aped c Placards SECTION 2 LIMITATIONS 24 EO EO 2 1 2 2 blank CESSNA SECTION 2 MODEL 150M LIMITATIONS INTRODUCTION Section 2 includes operating limitations instrument markings and basic placards necessary for the safe operation ofthe airplane its engine standard Systems and standard equipment The limitations included in this section have been approved by the Federal Aviation Administration When applicable limitations associated with optional Systems or equip ment are included in Section 9 Your Cessna is certificated under FAA Type Certifica
155. set in the encoding altimeter DIM Control ADJUST light brilliance of reply lamp TO SELF TEST TRANSPONDER OPERATION CO Function Switch SBY and wait 30 seconds for equipment to warm up 2 Function Switch ON or ALT CESSNA 300 TRANSPONDER PILOT S OPERATING HANDBOOK AND ENCODING ALTIMETER SUPPLEMENT 3 TST Button DEPRESS and HOLD reply lamp should light with full brilliance regardless of DIM control setting 4 TST Button Release for normal operation SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic equipment is installed However the installation of an externally mount ed antenna or several related external antennas will result in a minor reduction in cruise performance PILOT S OPERATING HANDBOOK CESSNA 300 TRANSPONDER SUPPLEMENT AND ALTITUDE ENCODER BLIND SUPPLEMENT CESSNA 300 TRANSPONDER Type RT 359A AND OPTIONAL ALTITUDE ENCODER BLIND SECTION 1 GENERAL The Cessna 300 Transponder Type RT 359A shown in Figure 1 is the airborne component of an Air Traffic Control Radar Beacon System ATCRBS The transponder enables the ATC ground controller to see and identify the aircraft while in flight on the control center s radar scope more readily The Cessna 300 Transponder system consists of a panel mounted unit and an externally mounted antenna The transponder receives interroga tion pulse signals on 1030 MHz and transmits pulse train reply
156. signals for localizer indications However the audio portion of the localizer is audible so that flight information such as that broadcast in certain areas on selected localizer frequencies by the Automatic Terminal Information Service ATIS may be heard controls for the Cessna 300 Nav Com Type RT 308C except the omni bearing selector OBS are mounted on the front panel of the receiver transmitter The course selector and the navigation indicators are in cluded in the course deviation indicator communication transmitter and the navigation receiver are synthesizer controlled and are tuned automatically when the frequency is selected In addition when two or more radios are installed a transmitter selector switch and a speaker phone selector switch are provided Each control function is described in Figure 1 SECTION 2 LIMITATIONS There is no change to the airplane limitations when this avionic equip ment is installed 1 of 4 CESSNA 300 PILOT S OPERATING HANDBOOK TYPE RT 308C SUPPLEMENT 1 RECHIVER TRANSMITTER FREQUENCY INDICATOR 2 NAVIGATION RECEIVER FREQUENCY INDICATOR 3 SQUELCH CONTROL Used to adjust signal threshold necessary to activate communication receiver audio Clockwise rotation increases background noise decreases squelch action counterclockwise rotation decreases background noise 4 COMMUNICATION RECEIVER TRANSMITTER MEGA HERTZ SELECTOR Sel
157. signals on 1090 MHz The transponder is capable of replying to Mode A aircraft identification and also Mode C altitude reporting when coupled to an op tional altitude encoder system The transponder is capable of replying on both modes of interrogation on a selective reply basis on any of 4 096 in formation code selections The optional altitude encoder system not part of a standard 300 Transponder system required for Mode C altitude re porting operation consists of a completely independent remote mounted digitizer that is connected to the static system and supplies encoded al titude information to the transponder When the altitude encoder system is coupled to the 300 Transponder system altitude reporting capabilities are available in 100 foot increments between 1000 and 20 feet All Cessna 300 Transponder operating controls are located on the front anel of the unit Functions of the operating controls are described in igure 1 1 of 6 CESSNA 300 TRANSPONDER PILOT S OPERATING HANDBOOK AND ALTITUDE ENCODER BLIND SUPPLEMENT 1 FUNCTION SWITCH Controls of power and selects transponder operating mode as follows OFF Turns set off SBY Turns set on for warm up or standby power ON Turns set on and enables transponder to transmit Mode A aircraft identification reply pulses ALT Turns set on and enables transponder to transmit either Mode A aircraft identification reply pulses o
158. sna 300 Transponder and Encoding Altimeter Sheet 1 of 2 PILOT S OPERATING HANDBOOK CESSNA 300 TRANSPONDER SUPPLEMENT AND ENCODING ALTIMETER 10 11 12 13 IDENT ID SWITCH When depressed selects special pulse identifier to be transmitted with transponder reply to effect immediate identification of aircraft ground con trollers display Reply Lamp will glow steadily during duration of IDENT pulse transmission DIMMER DIM CONTROL Allows pilot to control brilliance of reply lamp SELF TEST TST SWITCH When depressed causes trans ponder to generate a self interrogating signal to provide a check oftransponder operation Reply Lamp will glow steadily to verify self test operation REPLY CODE SELECTOR KNOBS 4 Select assigned Mode A reply code REPLY CODE INDICATORS 4 Display selected Mode A reply code 1000 FOOT DRUM TYPE INDICATOR Provides digital alti tude readout in 1000 foot increments between 1000 feet and 35 feet When altitude is below 10 feet a diagonally striped flag appears in the 10 foot window OFF INDICATOR WARNING FLAG Flag appears across alti tude readout when power is removed from the altimeter to indi cate that readout is not reliable 100 FOOT DRUM TYPE INDICATOR Provides digital alti tude readout in 100 foot increments between feet and 1000 feet 20 FOOT INDICATOR NEEDLE Indicates altitude in 20 foot increments between O feet a
159. stance to clear a 50 foot obstacle 1165 Feet A correction for the effect of wind may be made based on Note 2 of the landing chart using the same procedure as outlined for takeoff 5 7 SECTION 5 CESSNA PERFORMANCE MODEL 150M AIRSPEED CALIBRATION FLAPS UP KIAS 40 50 60 70 80 90 100 110 120 130 140 KCAS 43 51 59 68 77 87 98 108 118 129 140 FLAPS 10 KIAS 40 50 60 70 80 85 KCAS 42 50 60 69 78 82 FLAPS 40 40 50 60 70 80 85 KCAS 40 50 61 72 83 89 Figure 5 1 Airspeed Calibration 5 8 5 CESSNA MODEL 150M TEMPERATURE CONVERSION CHART CELSIUS DEGREES Temperature Conversion Chart Figure 5 2 5 9 SECTION 5 CESSNA PERFORMANCE MODEL 150M STALL SPEEDS CONDITION Power Off NOTE KIAS values are approximate MOST REARWARD CENTER OF GRAVITY ANGLE OF BANK WEIGHT FLAP o 5 LBS DEFLECTION 0 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 46 48 49 52 55 57 65 68 1600 10 44 45 41 48 52 54 62 64 40 42 42 45 45 50 50 59 59 MOST FORWARD CENTER OF GRAVITY ANGLE OF BANK WEIGHT FLAP 5 LBS DEFLECTION 0 30 45 60 KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 47 49 51 53 56 58 66 69 1600 10 45 46 48 49 54 55 64 65 40 42 42 45 45 50 50 59 59 Figure 5 3 Stall Speeds
160. stringers The entire structure is covered with aluminum skin The front spars are equipped with wing to fuselage and wing to strut attach fittings The aft spars are equipped with wing to fuselage attach fittings and are partial span spars Conventional hinged ailerons and single slot ted flaps are attached to the trailing edge of the wings The ailerons are constructed of a forward spar containing a balance weight formed sheet metal ribs and V type corrugated aluminum skin joined together at the trailing edge The flaps are constructed basically the same as the aile rons with the exception of balance weight and the addition of a formed sheet metal leading edge section The empennage tail consists of a conventional vertical stabilizer rudder horizontal stabilizer and elevator The vertical stabilizer consists of a spar formed sheet metal ribs and reinforcements a wrap around skin panei formed leading edge skin and a dorsal The rudder is constructed of a formed leading edge skin containing hinge halves a wrap around skin panel and ribs and a formed trailing edge skin with a ground adjustable trim tab at its base The top of the rudder a leading edge extension which contains a balance weight The horizontal stabilizer is constructed of a forward spar main spar formed sheet metal ribs and stiffeners a wrap around skin panel and formed leading edge skins The horizontal stabilizer also contains the elevator trim tab ac
161. sts o check your ELT for inadvertent activation select 121 5 MHz on your radio transceiver and listen for an emergency tone transmission the ELT can be heard trans mitting place the function selector switch in the OFF position and the tone should cease Immediately place the function selector switch in the ARM Position to re set the ELT for normal operation SECTION 5 PERFORMANCE There is no change to the airplane performance data when this equip ment is installed 3 4 blank PILOTS OPERATING HANDBOOK CESSNA 300 NAV COM SUPPLEMENT TYPE RT 308C SUPPLEMENT CESSNA 300 NAV COM COM VOR No LOC Type RT 308C SECTION 1 GENERAL The Cessna 300 Nav Com Type RT 308C shown in Figure 1 con sists of a panel mounted receiver transmitter RT 308C and a single needle course deviation indicator IN 514R or IN 514B The RT 308C Receiver Transmitter includes a 360 channel VHF communication receiver transmitter and a 160 channel navigation receiver both of which may be operated simultaneously The communication receiver transmitter receives and transmits sig nals between 118 00 and 135 95 MHz in 50 KHz steps The navigation re ceiver receives and interprets VHF omnidirectional range VOR signals between 108 00 and 117 95 MHz Although localizer signals all odd tenth frequencies between 108 1 and 111 9 MHz can also be received the navigation receiver does not include the necessary circuits to interpret the
162. t is installed However the installation of an externally mount ed antenna or several related external antennas will result in a minor reduction in cruise performance 4 PILOT S OPERATING HANDBOOK CESSNA 300 NAV COM SUPPLEMENT TYPE RT 328T SUPPLEMENT CESSNA 300 NAV COM 720 Channel Type 328 SECTION 1 GENERAL The Cessna 300 Nav Com Type RT 328T shown in Figure 1 con sists of a panel mounted receiver transmitter and a single or dual pointer remote course deviation indicator CDI The set includes a 720 channel VHF communication receiver transmitter and a 200 channel VHF navigation receiver both of which may be operated simultaneously The communication receiver transmitter receives and transmits sig nals between 118 000 and 135 975 MHz in 25 kHz steps navigation receiver receives and interprets omnidirectional and localizer sig nals between 108 00 and 117 95 MHz in 50 kHz steps The communication receiver transmitter and the navigation receiver are synthesizer control led and are tuned automatically when the frequency is selected A DME receiver transmitter or a glide slope receiver or both may be interconnected with the Cessna 300 Nav Com set for automatic selec tion of the associated DME or GS ie When a VOR frequency is selected on the Nav Com the associated VORTAC or VOR D station frequency will also be selected automatically likewise if a localizer fre quency is selected the asso
163. t of datum at all weights Reference Datum Front face of firewall 2 5 SECTION 2 CESSNA LIMITATIONS MODEL 150M MANEUVER LIMITS This airplane is certificated in the utility category and is designed for limited aerobatic flight In the acquisition of various certificates such as commercial pilot instrument pilot and flight instructor certain maneuvers are required All of these maneuvers are permitted in this airplane No aerobatic maneuvers are approved except those listed below MANEUVER MAXIMUM ENTRY SPEED Chandelles 95 knots Lazy Eights 455006 de opo 95 knots Steep Turns 95 knots Spins Use Slow Deceleration Stalls Except Whip Stalls Use Slow Deceleration Higher speeds can be used if abrupt use of the controls is avoided Aerobatics that may impose high loads should not be attempted The important thing to bear in mind in flight maneuvers is that the airplane is clean in aerodynamic design and will build up speed quickly with the nose down Proper speed control is an essential requirement for execution of any maneuver and care should always be exercised to avoid excessive speed which in turn can impose excessive loads the execution of all maneuvers avoid abrupt use of controls FLIGHT LOAD FACTOR LIMITS Flight Load Factors Flaps Up 4 4 1 76g Flaps Down 3 5g The design load facto
164. te No 3A19 as Cessna Model No 150M This airplane is modified by EASA STC no 10015134 to run on a Rotax 912 53 engine The changes regarding to the STC are incorporated in this Manual AIRSPEED LIMITATIONS Airspeed limitations and their operational significance are shown in figure 2 SPEED KCAS KIAS REMARKS Never Exceed Speed 141 141 Do not exceed this speed in any operation VNO Maximum Structural 104 107 Do not exceed this speed Cruising Speed except in smooth air and then only with caution VA Maneuvering Speed 726 kg 95 97 Do not make full or abrupt 656 kg 90 93 control movements above 590 kg 85 88 this speed VE Maximum Flap Extended Do not exceed this speed Speed 89 85 with flaps down Maximum Window Open Do not exceed this speed with Speed 141 141 Windows open Figure 2 1 Airspeed Limitations 2 3 SECTION 2 LIMITATIONS AIRSPEED CESSNA MODEL 150M INDICATOR MARKINGS Airspeed indicator markings and their color code significance are shown in figure 2 2 MARKING KIAS VALUE OR RANGE SIGNIFICANCE White Arc 42 85 Full Flap Operating Range Lower limit is maximum weight Vso in landing configuration Upper limit is maximum speed permissible with flaps extended Green Arc 47 110 Normal Operating Range Lower limit is maximum weight Vg at most forward C G with flaps retracted Upper limit is maximum structural cruising speed
165. tick indication only For engine oil grade and specifications refer to Section 8 of this handbook An oil quick drain valve is available to replace the drain plug in the oil sump drain port and provides quicker cleaner draining of the engine oil To drain the oil with this valve installed slip a hose over the end of the valve and push upward on the end of the valve until it snaps into the open position Spring clips will hold the valve open After draining use a suitable tool to snap the valve into the extended closed position and re move the drain hose IGNITION STARTER SYSTEM Engine ignition is provided by two engine driven magnetos and two spark plugs in each cylinder The right magneto fires both left and right upper spark plugs and the left magneto fires both left and right lower spark plugs Normal operation is conducted with both magnetos due to the more complete burning of the fuel air mixture with dual ignition Ignition and starter operation is controlled by a rotary type switch located on the left subpanel The switch is labeled clockwise OFF BOTH and START The engine should be operated on both magnetos OTH position except for magneto checks The and L positions are or checking purposes and emergency use only When the switch is ro tated to the spring loaded ST position with the master switch in the ON position the starter contactor is energized and the starter will crank the engine When the switch is
166. tion L 6082 ENGINE OIL SYSTEM An oil sump on the bottom of the engine supplies a total capacity of six quarts to the engine for lubrication one additional quart is re quired if a full flow oil filter is installed The oil is drawn from the sump through a filter screen on the end of a pick up tube to the engine driven oil pump The pump feeds the oil under pressure through a filter screen full flow oil filter and or oil cooler if installed and is then circulated to the left and right oil galleries The engine parts are then lubricated under pressure from the galleries pressure to the galleries is regulated by a pressure relief valve at the rear of the right oil gallery After lubricating the engine the oil returns to the sump by gravity If a full flow oil filter is installed the filter adapter is equipped with a bypass valve which will cause lubricating oil to by pass the filter in the event the filter becomes plugged or the oil temperature is extremely cold CESSNA SECTION 7 MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS An oil filler cap oil dipstick is located at the rear of the engine on the right side filler cap dipstick is accessible through an access door in the engine cowling The engine should not be operated on less than four quarts of oil minimize loss of oil through the breather fill to five quarts for normal flights of less than three hours For extended flightfill to six quarts dips
167. tuator Construction of the elevator consists of a main spar and bellcrank left and right wrap around skin panels and a formed trailing edge skin on the left half of the elevator the entire trail 7 3 SECTION 7 CESSNA AIRPLANE amp SYSTEMS DESCRIPTIONS MODEL 150M AILERON CONTROL SYSTEM RUDDER CONTROL SYSTEM Figure 7 1 Flight Control and Trim Systems Sheet 1 of 2 7 4 CESSNA SECTIONS MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS ELEVATOR TRIM CONRTROL SYSTEM Figure 7 1 Flight Control and Trim Systems Sheet 2 of 2 7 5 CESSNA MODEL 150M AIRPLANE amp SYSTEMS DESCRIPTIONS SECTION 7 1 1 l A a t be SE I LE 8 6 OF T Instrument Panel Sheet 1 of 2 Figure 7 2 7 6 L L CL ems c JO PAS eueq juoummrjsu Ne Turn Coordinator Airspeed Indicator Suction Gage Directional Indicator Attitude Indicator Airplane Registration Number Clock Rate of Climb Indicator Encoding Altimeter Marker Beacon Indicator Lights and Switches Omni Course Indicator ADF Bearing Indicator Rear View Mirror and Control Radios Transponder Audio Control Panel Flight Hour Recorder Tachometer Secondary Altimeter Additional Instrument and Radio Space Over Voltage Warning Light Ammeter 38 39 40 41 43 Map Compartment Cabin Heat Control Knob Cabin Air Control Knob Circuit Breakers Wing Flap Switch and Position Indicator
168. tude reporting interrogations on a selective reply basis on any of 4 096 information code selections When an optional panel mounted EA 401A Encoding Altimeter not part of a standard 300 Transponder sys tem is included in the avionic configuration the transponder can provide altitude reporting in 100 foot increments between 1000 and 35 000 feet Cessna 300 Transponder operating controls with the exception of the optional altitude encoder s altimeter setting knob are located on the front panel of the unit The altimeter setting knob is located on the encoding altimeter Functions of the operating controls are described in Figure 1 1 of 6 CESSNA 300 TRANSPONDER PILOT S OPERATING HANDBOOK AND ENCODING ALTIMETER SUPPLEMENT l FUNCTION SWITCH Controls application of power and selects transponder operating mode as follows Turns set off SBY Turns set on for equipment warm up ON Turns set on and enables transponder to transmit Mode A aircraft identification reply pulses ALT Turns set on and enables transponder to transmit either Mode A aircraft identification reply ulses or Mode C altitude reporting pulses se ected automatically by the interrogating signal REPLY LAMP Lamp flashes to indicate transmission of reply pulses glows steadily to indicate transmission of IDENT pulse or satisfactory self test operation Reply Lamp will also glow steadily during initial warm up period Figure 1 Ces
169. tude when the local altimeter setting in use by the ground controller is set in the aircraft altimeter DIM Control ADJUST light brilliance of reply lamp TO SELF TEST TRANSPONDER OPERATION 1 Function Switch SBY and wait 30 seconds for equipment to warm up 2 Function Switch ON 3 Button DEPRESS reply lamp should light brightly regardless of DIM control setting Button RELEASE for normal operation CESSNA 400 TRANSPONDER PILOT S OPERATING HANDBOOK AND ALTITUDE ENCODER BLIND SUPPLEMENT SECTION 5 PERFORMANCE There is no change to the airplane performance when this avionic is installed However the installation of an externally mount ed antenna or several related external antennas will result in a minor reduction in cruise performance PILOT S OPERATING HANDBOOK CESSNA 400 MARKER BEACON SUPPLEMENT TYPE R 402A SUPPLEMENT CESSNA 400 MARKER BEACON 402 1 GENERAL The system consists of a 75 MHz marker beacon receiver three in dicator lights one speaker phone switch a light dimming control an ON OFF VOLUME control and a 75 MHz marker beacon antenna In addition on 150 182 206 207 210 and 337 series models a HI LO sensitivity selector switch and a press to test button are provided On all 172 177 177RG 180 and 185 series models a single three position switch is provided for HI LO sensitivity selection or test selection
170. warning light will then turn on indicating to the pilot that the alternator is not operating and the battery is supplying all electri cal power The over voltage sensor may be reset by turning the master switch off and back on again If the warning light does not illuminate normal alternator charging has resumed however if the light does illuminate again a malfunction has occurred and the flight should be terminated as soon as practical The warning light may be tested by momentarily turning off the ALT portion of the master switch and leaving the BAT portion turned on CIRCUIT BREAKERS AND FUSES Most of the electrical circuits in the airplane are protected by push to reset circuit breakers mounted under the engine controls on the in strument panel Exceptions to this are the battery contactor closing exter nal power circuit clock and flight hour recorder circuits which have fuses mounted near the battery Also the cigar lighter and control wheel map light are both protected by circuit breakers on the instrument panel and fuses behind the panel An automatic reset type circuit breaker be hind the instrument panel protects the alternator field and circuitry GROUND SERVICE PLUG RECEPTACLE A ground service plug receptacle may be installed to permit the use of an external power source for cold weather starting and during lengthy maintenance work on the electrical and electronic equipment The recep tacle is located behind
171. with in the lower green arc range Excessive ground runup should be avoided Engine runup also helps to eliminate excessive accumulations of water in the fuel system and other air spaces in the engine Keep fuel tanks full to minimize condensation in the tanks Keep the battery fully charged to Prevent the electrolyte from freezing in cold weather If the airplane is to be stored temporarily or indefinitely refer to the Service Manual for Proper storage procedures 8 9 SECTION 8 CESSNA HANDLING SERVICE MODEL 150M amp MAINTENANCE SERVICING In addition to the PREFLIGHT INSPECTION covered in Section 4 COMPLETE servicing inspection and test requirements for your air plane are detailed in the Service Manual The Service Manual outlines all items which require attention at 50 100 and 200 hour intervals plus those items which require servicing inspection and or testing at special intervals Since Cessna Dealers conduct all service inspection and test proce dures in accordance with applicable Service Manuals it is recommended that you contact your Cessna Dealer concerning these requirements and begin scheduling your airplane for service at the recommended intervals Cessna Progressive Care ensures that these requirements are accom plished at the required intervals to comply with the 100 hour or ANNUAL inspection as previously covered Depending on various flight operations your local Government Avia tion Agency may requi
172. with Cessna equipment and factory approved procedures provides the highest level of service possible at lower cost to Cessna owners Regardless ofthe inspection method selected by the owner he should keep in mind that FAR Part 43 and FAR Part 91 establishes the require ment that properly certified agencies or personnel all required FAA inspections and most of the manufacturer recommended inspections CESSNA CUSTOMER CARE PROGRAM Specific benefits and provisions of the CESSNA WARRANTY plus other important benefits for you are contained in your CUSTOMER CA PROGRAM book supplied with your airplane You will want to thoroughly INIM your Customer Care Program book and keep it in your airplane at all times Coupons attached to the Program book entitle you to an initial inspec tion and either a Progressive Care Operation No 1 or the first 100 hour inspection within the first 6 months of ownership at no charge to you If you take delivery from your Dealer the initial inspection will have been performed before delivery of the airplane to you If you pick up your air plane at the factory plan to take it to your Dealer reasonably soon after 1n take delivery so the initial inspection may be performed allowing the ealer to make any minor adjustments which may be necessary You will also want to return to your Dealer either at 50 hours for your first Progressive Care Operation or at 100 hours for your first 100 hour inspection depe
173. work load to be divided into smaller operations what can be accomplished in The CESSNA PROGRESSIVE CARE PROGRAM has been developed to Provide a modern progressive inspection schedule that satisfies the com plete airplane inspection requirements of both the 100 HOUR and ANNUAL inspections as applicable to Cessna airplanes The program assists the owner in his responsibility to comply with all FAA inspection requirements while ensuring timely replacement of life limited parts and adherence to factory recommended inspection intervals and maintenance procedures 8 5 SECTION 8 CESSNA HANDLING SERVICE MODEL 150M amp MAINTENANCE CESSNA PROGRESSIVE CARE The Cessna Progressive Care Program has been designed to help you realize maximum utilization of your airplane at a minimum cost and down time Under this pora your airplane is inspected and maintained in four operations at 50 hourintervals during a 200 hour period The oper ations are recycled each 200 hours and are recorded in a Spectat pro vided Aircraft Inspection Log as each operation is conducted The Cessna Aircraft Company recommends Progressive Care for air planes that are being flown 200 hours or more per year and the 100 hour inspection for all other airplanes The procedures for the Progressive Care Program and the 100 hour inspection have been carefully worked out by the factory and are followed by the Cessna Dealer Organization _ The complete familiarity of Cessna Dealers

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