Reims Aviation Cessna F172 N Flight Manual Download

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Summary of Contents for Cessna F172 N

Page 1: ... Sections 2 3 5 Pages 2 1 tltru i2 7 3 1 tlm1 3 8 5 1 tlrru S 3 ReQ istration Number This is the exact translation of the F 172 N French Flight Manual approved by DGAC on pctober 27 1976 This aircraft must be operated in accordance with the limite specified in this Flight Manual THIS DOCUMENT MUST BE CARRIED lN THE AIRCRAFT T LL TIMES lrcrafl S eda 1 No lSlS Qll 0 t ...

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Page 3: ...CTION 2 LIMITATIONS Certification Basis Indicated Airspeed Limitations Approved Maneuvers 0 1 0 2 al d 0 3 U 4 111d 0 5 1 1 1 2 1 3 thru 1 5 1 6 tnd 1 7 1 8 and 1 9 1 10 thru 1 15 1 15 1 16 1 16 1 16 2 1 2 1 and 2 2 2 3 Engine Operation Limitations tnd lnstnunent Markings 2 3 wd 2 4 Placards 2 5 thru 2 7 SECTION 3 ElvtERGENCY PROCEDURES Engine Failure Fires Electrical Power Supply System Ma lftmct...

Page 4: ...ication Demonstrated Crosswind Noise Level Airspeed Correction Table Stall Indicated Airspeeds Performance and Specifications Tal eoff Distance Maximum Rate of Climb Cruise Performance Range and Endurance Profile Landing Distance Jv1a xi murn Glide SECTION 6 APPENDIX Servicing Maintenance Optional Systems 0 3 4 7 thru 4 9 4 10 thru 4 14 4 15 thru 4 23 4 24 thru 4 25 4 25 thru 4 2 7 5 1 5 1 5 1A S ...

Page 5: ... 4 1 11 1 4 1 6 1 7 1 10 tluu 1 16 2 1 2 2 2 6 3 1 thru 3 8 4 1 4 6 4 8 4 10 thru 4 27 5 4 and 5 5 6 2 1 6 7 2 and6 7 3 0 2 0 4 and 0 5 1 6 thru 1 8 1 11 1 13 thru 1 16 2 1 and 2 2 2 4 thru 2 7 3 2 and 3 4 4 7 thru 4 10 4 13 and 4 18 5 2 6 1 0 6 2 1 and 6 2 2 6 7 2 and 6 7 3 6 7 6 and 6 7 7 6 17 1 6 18 1 and 6 18 2 1978 Model beginning with Serial Number 1640 1979 Model beginning with Serial Numbe...

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Page 7: ... 1 11 beginning with 1 14 1 16 Serial Number 2 1 2 4 thru 2 6 19 to 3 4 4 2 and 4 2 4 10 thm 4 13 4 18 4 20 thru 4 27 5 lA 5 18 S 2 thru S 4 S 6 thru 5 8 5 14 thru 5 18 6 0 6 6 1 0 1 2 and 2 2 6 1 1 6 1 2 6 2 1 6 2 2 Edition 1 Augmt 1976 Revis ion 4 rviay 1979 Approval Date Visa A LA o 11 r 0 nw r I I I I I l I I II I I i nl t 0 5 ...

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Page 9: ...erformance data of the Model REIMS C SSNA f172N DOCUMENTS AVAILABLE The following is a check list of the dnt inform tiotJ and liccllscs th 1r are part of the airc ra ft file 111d required b Regulations The sltould be made available at all times to relevant Authority 1 Airworthiness C ertific tte 2 Registration Certificate 3 Radio Installation License if rad io installed 4 Log Books 5 Flight Manual...

Page 10: ... 8 22m ___ ____ _ _ _ _ _ _ _ PRINCIPAL DIMENSIONS PIVOT POINT 1 10 97 m 1 91 m Figure 1 1 NOTES 1 Wmo uun t Mown wuh tHobf llohu inlUlle d 2 M1a1mvm hetQht how Wt1h n o 9t c Stpre u ed 111 tuf and no 1tru1 orOOHiy 1nfllted and flaUung beacon nualled PIVOT POINT ...

Page 11: ...e1 AILERONS Area Control Travel WING FLAPS Method of Actuation Area Control Travel Wing R oot Wing Tip Up Down HORJZONTAL STABILIZER AND ELEVA TOR Stabilizer Area Angle of Incidence Cable control systems 10 97 m With O ptiC n t l Strobe Light 8 22m 2 68 Ill With Fla hin Beacou m l Nose Strut Depresse cl NACA2412 1 lodi ic l 16 16m2 1 37 tt 25 chord 0 4 7 2 50 1 66 m2 wo lo 15 1 Electric C ble 1 97...

Page 12: ...ANDING GE t R Type Shod Absorber Nose Gear Main Gear Tread Nose Wheel Tire and Pressure 5 00 X 5 Main Wheel Tire and Pressure 6 00 X 6 Nose Gear Shock Strut Pressure 1 Cable control systems 1 4 Edition 1 August 197 6 Revision 2 June 197 7 1 35 m2 including tab J 10 280 I oo 10 23 oo 28 10 oo 130 10 oo 1 26 m2 0 69m2 16 1 1G0 1 Fixe Tric ycle Air Oil Tubular Spring 2 55 m 2 14 bars 31 psi 2 00 bars...

Page 13: ...ed Viscosity For Temperature Range MIL L 6082 Aviation Grade Straight Mineral Oil SAE SO above 16 C SAE 40 between 1 C and 32 C SAE 30 between l8 C and 21 C SAE 20 below 12 C MIL L 228S1 Ashless Dispersant Oil SAE 40 or SAE SO above 16 C SAE 40 between 1 C and 32 C SAE 30 or SAE 40 between 18 C and 21 C SAE 30 below 12 C Carburetor Heater PROPELLER Type Number of Blades Manually Operated vicCauley...

Page 14: ...flight M tntt 1l REIMS CESSN A f 172 N INSTRUMENT PANEL Figure 1 2 Sheet 1 of 2 l 6 Edition 1 Augnst 1976 Revision 3 September 1978 ...

Page 15: ... Space 2 0 ADF Radio 2 1 Flight Hour Recorder 2 2 Map Compartrne J t 2 3 _ C_ abin Heat and Air Control Knobs 24 Cigar Ughter 25 Wing Flaps Switch and Position Indicator 26 Mixture Contro l Knob 27 Throttle With Friction Lock 28 Static Pressure Alternate Source Valve 29 Instrument and Radio Dial Light Dimming Rheostat 30 Microphone 31 Air Conditioning Controls 32 Fuel Selector Valve Handle 33 Rudd...

Page 16: ...G E ELECTRICAL CONNECTION FUEL SYSTEM fUH OUANTI r y INDICATORS II DRAIN VALVE FUEL QUAN TI TY lkANSMITTE R SElECTOR VALVE ORAIN PLUG FUEl Sl f lAINE R FUEL STRAINER DRAIN CONTROL TO ENSURE MAXIMUM FUEL C PACITY WHEN REFUE liNG AND k INII OZE CROSS FEE OING WH N PA R 0 ON A SLOPINCi SUIIFACE PLACE THE FUEL SEL EClCl R A l V lr f iTHtR lH T OR IUGo iT OSITION 0 THIIOTTL E CONTROL CAriBURETDil r r l...

Page 17: ...OPTIONAL TWO LONG RANGE WING 102 litres 189 litres 15 litres 27 US Gal 50 US Gal 4 US Gal Figure 1 4 N 0 T E Fuel quantity i nd icators cannot be relied upon for accurate readings during skids 1 slips or unusual attitudes FUEL TANK SUMP QUICK DRJ IN VALVES TOTAL FUEL VOLUl 1E 163 lil res 43 US Gal 204 liti es 54 US Gal Each fuel tank sump is equipped with a fuel quicl cirain valve which extentls t...

Page 18: ...e on anytime the master and avionics power switches are turned on CAUTION Prior to turning the master switch on or off starting the engine or applying an external power source the avionics power switch labeled AVIONICS POWER should be turned off to prevent any hannful transient voltage from damaging the avionics equipment MASTER SWITCH The master switch is a split rocker type switch labeled 11 MAS...

Page 19: ...E T SV iTf A 0 QIGI TAL C Cr oc 10 OIL 1E 1 RA fUqE C t NO CYLIIIOER E 0 lE tr RAfUR G al e 1 TO IG711TIO I SWITCH TO LOW VOL UG R I IG I IG T GROUIIQ SERVICE PLUG FI CfPTACLf TO TOT 4 ot f CIRCUif 8R AIIEP 101011 l CLOCK ONl I I OIL PRES UR SW I I C I l iGHT 0Uq RECORDER AVIO tcs POwE SWilt H CIACUif SFIEAKER IOI f LEFT SlOE o sw1 TCH l fo rn CONTqOL PANELI Figure 1 4 TO FUEl OVANTITV INOICATOAS ...

Page 20: ...n the left side of the switch and control panel and is 11 0N11 in the up position and 110Ff 11 in the down position With the switch in the 0Ff11 position no electrical power will be applied to the avionics equipment regardless of the position of the master switch or the individual equipment switches The avionics power switch also functions as a circuit breaker If an electrical malfunction should o...

Page 21: ...system load the lo voltage warning light will illumin ate when system voltage drops below normal The altemator control tmit may be reset by turning the master switch off and back on again Ii t 1e warning light does not illuminate nonnal alternator charging has resumed bowever if the light does illuminate again a malfunction has occured and tl1e fl igbt should be tenninated as soon as practicable N...

Page 22: ... adjacent to the battery EXTERIOR LIGHTING Conventional navigation lights are located on the wing tips and top of the rudder A single landing light or dual landing taxi lights are installed in the cowl nose cap Optional flashing_ beacon is mounted on top of the vertical fin Additional lighting is available and includes a str be light on each wing tip and two courtesy lights one under each wing jus...

Page 23: ...equipment This is accomplished by rot lting the II RADIO LT knob full counterclokwise Check that the nood lights post llghts are tumed off for dnylight operation by rotating the PANEL LT 1 knob full counterclokwise A cabin dome llght is located in the aft part of the ov rhead console and is operated by a switch adjacent to the light A control wheel map light is available and is mounted on the bott...

Page 24: ... across a cabin manifold just forward of the pilot s and copilot s feet Rear cabin heat and air is supplied by two ducts frcm the manifold one extending down each side of tbe cabin to an outlet at the front doorpost at floor level Windshield defrost air is also supplied by two ducts leading from the cabin manifold to defroster outlets near the lower edge of the windshield Two knobs control sliding...

Page 25: ... Maximum Flaps Extended Speed 10 Flaps 10 40 Flaps V Maneuvering Speed A AIRSPEED INDICA TDR MARKINGS Red line km h 293 235 204 158 180 293 kts 158 127 110 85 97 158 mph 182 146 127 98 112 182 Yellow rc Caution Range 235 293 127 158 146 182 Green Arc Normal Operating Range 82 235 44 127 57 146 White Arc Flap Operating Range 6 1 158 33 85 38 98 FLIGHT MANEUVERING LOAD FACTORS AT GROSS WEIGHT Normal...

Page 26: ... 0 89 m Forward at 910 kg 0 98 m Straight line variation berween 885 and 910 kg LOADING LJlviiTS Number of Occupants Front Seats 2 Rear Seats 2 Minimum Crew 1 pilot Maximum Baggage in Baggage Compartment Area 1 Area 2 54 kg Occupied Optional Child s Seat Approved if Fitted With a Safety Belt NIGHT VFR AND IFR APPROVAL for night VFR and IFR approval the aircraft must carry the adJltion 1l equipment...

Page 27: ...on Use Slow Deceleration Intentional spins with fla 6 extended are not approved Inverted flight n1aneuvers are not recon1111e nded The Important thing to benr in mind ill flight m lllcnvers is that the airplane is clean in aerodynamic design and will build ttp speed quickly with the nose down Proper speed control is an essential requirement for execution of any maneuver and care should be exercise...

Page 28: ... arc Maximum 11 5 psi 7 93 bars red line FUEL QUANTITY INDICA TORS Empty E red line Total unusable fuel Standard tank Long range tank TACHOMETER 3 US Gal 11 4 1 4 US Gal 15 1 f Normal operating Range green arc Sea Level 2100 2450 RPM 5000 ft 1524m 2100 2575 RPM 10000 ft 3048m 2100 2700 RPM Maximum Limit red line 2700 RPM SUCTION GAGE Normal Operating Green Arc 4 5 to 5 4 in Hg 2 4 ...

Page 29: ... which must be complied with when operating this airplane in this category or in the Utility Category are contained in this Airplane Flight Manual Nonnal Category No acrob tic maneuvers including spins approved Utility Category No acrobatic maneuvers approved except those listed in this Airplane Flight Mauual Baggage compartment and rear seat must not be occupied Spins Recovery Opposite ntdcler fo...

Page 30: ...FF LANDING U FT 20 US CAL 76 1 LEVEL FLIGHT ONLY RIGHT 20 US GAL 76 1 LEVEL FLIGHT ONLY OFF Long range tanh BOTI I 50 US GAL 189 1 ALL FLIGHT ATTITIJ DES LEFT 25 US GAL RIGHT 25 US GAL OfF TAKEOFF LANDING 99 51 LEVEL FLIGHT ONLY 99 51 LEVEL FLIGHT ONLY 3 Near fuel tank filler cap t S tnndard tanl s 2 6 FUEL 1OOLL 100 MIN GRADE AVIATION GASOUNE CAP 21 5 US CAL 81 5 litres ...

Page 31: ...tent at 10 Indices at these positions lith white color code and 158 km h 85 kt 98 MPH callout i also mechanical detent at 10 and 20 6 In baggage compartment 120 lbs 54 kg maximum baggage and or au xiliary seat pns senger forw 1rd of bagg ge door latch 50 lbs 23 kg maximum baggage aft of baggage door latch Maximum combined 120 lbs 54 kg For additional loading instructions see weight o nd balance da...

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Page 33: ...ts 69 MPH Flaps DOWN 2 Mixture IDLE CUT OFF 3 Fuel Selector Valve OFF 1 Ignition Switch 1 0fF11 5 Wb1g Fb ps AS REQUIRED 40 recommended 6 Master Switch 11 0FF CAUTION Perform the landing straight ahead making only small changes in heading to a void obstructions Never attempt to turn back to the landing strip DUFUNG FLIGHT 1 Glide Speed lAS 121 km h 65 kts 75 MPH 2 Fuel Selector Valve B011 I11 3 Mi...

Page 34: ...If th start is successful 2 Run the engine at 1700 RPM for a few minutes 3 Engine SHUT DOWN and inspect the fire damage If engine start is unsuccessful 4 Throttle FULL OPEN 5 M b ture IDLE CUT OFF 6 Engine CONTINUE cranking for two or three minutes 7 Use fire e tinguisher if available 8 Engine SHUT DOWN a Master Switch OFF b Ignition Switch OFF c Fuel Selector Valve OFF 9 Flames SMOTHER with fire ...

Page 35: ... to inspect for damage VliNG FIRE 1 Navigation Light Switch OFF 2 Pitot Heat Switch if installed 11 0ffll 3 Strobe Light Switch if installed OFF NOTE Perionn a sideslip to keep the flames away from the fuel tank and cabin and land as soon as possible using flaps only as required for final approach and touchdown LECTRJCAL FlRE IN FLIGHT 1 Master Switch OFF 2 A vimJics Power Switch 110FF11 3 All Oth...

Page 36: ...f low voltage light illuminates again 7 Alternator Off 8 Nonessential Radio and Electrical Equirment OFF 9 Flight TERMINATE as soon as practical FLIGHT lN ICING CONDITIONS 1 lthough flying in known icing conditions is prohibited an unexpected icing encounter should be handled a follows 1 Tum pitot heat switch 11 0N11 if installed 2 Tum back or change altitude to obtain an outside air temperature t...

Page 37: ... 12 Pcr fonn fl lflndiug in level altitutle INADVERTENT SPlN NORivlAL CATEGORY To recover from an inadvertent spin use the iollowing standa rd procedure 1 Retard throttle to idle position and neutralize ailerons 2 Apply full rudder opposite to the direction of rotation 3 After one fourth tum move the control wheel forward of 11eutral in a brisk motion 4 As the rotation stops neutralize the rudder ...

Page 38: ...h an indicated air peed of a pproximately 111 l m h 60 l ts 69 MPH and flaps lowerer to 20 by using throttle and elevator trim_controls Then do not change this elevator trim setting control the glide angle by adjusting pc wer exclusively At flare out the nose down moment resulting from power reduction is an adverse factor and the aircraft may hit on the nose wheel Consequently at f1areout the cont...

Page 39: ... In dicated Airspeed 120 km h 65 kts 75 MPH flaps UP 111 km h 60 kts 69 MPH flaps DOWN 2 Seat Belts and Shoulder Harnesses SECURE 3 M ixture IDLE CUT OFF 4 Fuel Selector Valve OFF11 5 Ignition Switch OFF G Wing flaps AS REQUIRED 40 recommended 7 Master Switch OFF 8 Doors UNLATCH PPJOR TO TOUCHDOWN 9 Touchdown SLlGHTLY T IL LOW 10 Brakes APPLY HEAVILY PITCHING 1 Prepare for ditching by securing or ...

Page 40: ...tude 7 Place folded coat or cushion in front of face at time of touchdown 8 Evacuat airplane through cabin doors If necessary open window to fl ood cabin compartment for equalizing pressure so that door can be opened 9 Inflate life vests and raft ii available after evacuation of cabin The aircraft cannot be depended on for floatation for more than a few minutes 3 8 ...

Page 41: ... Flight Manual REIMS CESSNA F172N SECTION 4 Edition 1 August 1976 RevisiC1n 2 june 1977 NORMAL PROCEDURES 4 1 ...

Page 42: ...on 0 86 ro I 17 15 1 145 R r r sscnsors 77 IU f P A r I S l 1 t 1 x St 11 2 08 In 2 7 1 nl l o c ser 011 Child s s 53 1 8 fhs ge Are 2 t3 kg M x S t Jtion 2 74 to L6J rll TOT L WEIGIIT AND JQI IE NT 10 13 I175 l o a te this f Oinl 10 13 nd 175 011 the Celltcr nf gr rv ity n oment t oitll f tlls witlti11 the envclot c the lo fii R is ncccpt l lc 1 1 xi Cn111 l11 11cod Wc I Itt r n I 1 Arc 2 5 1 llj...

Page 43: ...kF Iitrl lOll 132 Fue l 1 111 Ho11r c 1l 2 lltrcs at n n 1 1 II ttc Pllr t 1 Ftc Pl r Hcu rr St llc n 0 l i l l 17 111 15 1 5 TOTAL WF I IIT AND 1 IOMC NT ll s Edition 1 August 197G I cv isil n 1 l 1ay 1 97 9 YOIH AIRPLANE Wei I 1 lomc nl kg m k l cx ote this polut JIO 2nd 90S 011 th Ct lllcr nf vlty lttetrnrnt envrlC J t sin t l ir r l nt h II wIt Itin Ihr r lr J r tltc lc ttfln i occc l l thlr F...

Page 44: ... 14 2 L 1 OPT I ONAL SEATING 3 0 61 Pilot or passenger center of gravity on adjustable seats positioned for average occupant Numbers in parentheses indicate fotward nd aft limits of occupant center of gravity range Arm measured to the center of the area shown NOTE The aft baggage wall approxim ne station l08 can be used as a convenient interior reference point for determ in ing the location o f ba...

Page 45: ...l Q 80 0 lOQ E CODE f 1 I 60 1 fuel 152 litres Standard Tanks and 189 litres Optional tanks 1 40 50 1 Rear Passengers t it ___ Baggage Area 1 or Passenger on t 20 Child s Seat 54 kg t l Baggage Area 2 2 3 kg t __ J r r r _ T r t t J r t 20 60 100 140 180 220 260 300 LOAD MOME t lT M KG N z TI Cl 0 1 c OQ c ...

Page 46: ...4 5 flight Manual REfMS CESSNA F172N 0 0 o I J 0 0 0 0 0 co Edition 1 August 197 0 tH f HI 0 0 0 N J H IJM l UIV 030V01 Figure 4 4 ...

Page 47: ...l9 J I l J_r I I 1 I 0 I I t_j w _ z w u 0 0 0 0 0 0 0 en co _I _ _r 0 0 r Edition 1 Augu t 1976 ll evisicn 2 June I l77 f t 0 0 c o 1 aU oO J J CJ Ck J 0 C 0 u 01 Z J UJ z J a a I w L U ZZw c iz J l4 O O s OOa ZZ4 4 I w J J j I I lI fi 1HD13M 3N v ld8 l v 0 30 v Ol fig11rc 4 t1J 1 G ...

Page 48: ...all accumulations of frost ice or snow from wing1 tail and control surfaces Also make sure that control surfaces contain no internal accumulations of ice or debris Prior to flight check that pitot heater if installed is wann to touc11 within 30 seconds with battexy and pitot heat switches on If a night flight is planned checl operation of all lights and mal c sure a fl lshlight is available F igur...

Page 49: ...l selector valve bnndlc on BOTI l h Check baggage door for security Lock with 1 c if chilclren nrc to occupy child1 s scat 0 a Remover ruoder gust loci i lllStallcd b Disconnect ta il tic dow11 c Check control surfaces fot freedom of movement and security D a Remove aileron gust lock if installed G a Check main wheel tire fo r proper inflation b Disconnect wing tie dovvn c Drain the wing tanks usi...

Page 50: ...r cleanliness f Check nose wheel stntt a nd tire for proper inflation g Disconnect nose tie down h Inspect flight instrument static source opening on left side of fuselage for stoppage Same as G a Remove pitot tube cover if installed and check pitot tube opening for stoppage b Check fuel tank vent opening for stoppage c C bee k stall warning vent opening for stoppage d Disconnect wing tie down Sam...

Page 51: ...e exposed horn bell inside the c J bin and over the left ing opening or by any other modification approved by the Rijksluchtvnartdienst Thereafter flight test tb 2 aircraft to assure that the stall warning horn sounds at 5 to l0 mph 1bove the stall warning speed and if not recalibrate in accordance with the provisions of the afore cite l paragraph of the Cessna l00 Series Service Manual or parngra...

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Page 53: ...lectrical Equip ment OFF CAUTION The avionics power switch must be 1 0Ff1 during engine st trt to prevent possible damage to avionics 4 Brakes TEST and SET 5 Circuit Breakers CHECK IN STARTI NG ENGINE 1 Mixture Rl CH 2 Carburetor Heat COLD 3 Master Switch ON 1 4 Prime AS REQUIRED 2 to 6 strokes none if engine is warm 5 Throttle OPEN 0 5 em G Propeller Area CLEAR 7 Ignition Switch START release whe...

Page 54: ... Throttle 1000 RPM or LESS 9 Radios SET 10 Autopilot if installed OFF 11 Air Conditioner if installed OFF 12 Flashing Beacon Navigation Lights and or Strobe Lights ON as required 13 Throttle Friction Lock ADJUST 14 Brakes RliEASE TAKE OFF NORlviAL TAKE OFF 1 Wing Flaps 0 10 refer top 4 18 Flap Settings 2 Carburetor Heat COLD 3 Throttle FULL OPEN 4 Elevator Control LIFT NOSE WHEEL AT 102 km h 55 kt...

Page 55: ...ain maximum RPM MAXJMUM PERFORMANCE CLIMB 1 Inclicated Airspeed 135 km h 73 kts 84 MPH at sea level 126 km h G8 kts 78 MPH at 3048 m 10 000 fl 2 Throttle FULL 3 Mixture RICH CRUISE 1 Power 2200 to 2700 RPM no more than 75 2 Elevator Trim and Rudder Trim if installed ADJUST 3 Mixture LEAN DESCENT NOTE If a loss of RPM is noted use the carburetor heat r refer to 1 CARBURETOR ICTNG11 on page 4 23 1 F...

Page 56: ...27 1 1PH 10 40 below 158 km h 85 l ts 98 MPH 3 Indicated Airspeed 102 to 121 l m h 55 to 65 kts 63 to 75 MPH flaps down 4 Touchdown lvf AIN WHEELS FIRST 5 Landing Roll LOWER NOSE WHEEL GENTLY 6 Braking MINIMUM REQUIRED htAXIMUM PERFORMANCE LANDING 1 Airspeed 111 to 130 km h 60 to 70 l ts 69 to 81 MPH flaps up 2 Wing Flaps FULL DOWN 40 3 Airspeed 109 krn h 59 kts 68 MP rl until flare 4 Powe r REDUC...

Page 57: ...ING RETRACT tfter reaching a safe altitude tnd 111 km h GO l ts 69 MPH 1 Wing Flaps UP 2 Carburetor H eat COLD SECUIUNG 111E IRCRJ FT 1 P rl ing Brak e SET 2 Avionics Power Switch Electrical Equipment Autopiiot if installed 11 0FF 3 Mixture IDLE CUT OfF pulled full out 4 Iguition OFF 5 Master Switch OFF 6 Control lock INSTALL 4 14 ...

Page 58: ...y the engine starts easily with one or t 1 0 strol es of primer in w3rm temperntttres to six stTokes in cold weathcr1 with the throttle open approxim3tcly 1 2 inch 1 em In extremely cold temperatures it may be necessary to continue priming while cranking Weal intermittent TAXIING DIAGRAM CODE WIND DIRECTION t Figure 4 G 4 15 l ...

Page 59: ...gine damage After starting1 avoid the use of carburetor heat unless icing conditions prevail TAXllNG When taxiing it is important that specc J tnd use of brakes l C l1eld to a minimum nnd that all controls be util l C c J see t txiing diagr m page 4 15 to maintain directio11al control tnd baJance T xiing over loo c gr Jvel or cinders shoulc J be done at low e11giJ1e speed The carburetor heat contr...

Page 60: ...t be engine runup Tbe ammeter will remain 1t zero if the altem ltor and volt ge reguhtor arc opcr 1ting properly TAI E OFJ7 POWER CllECI S Jt is important to check full throttle engine operation early in the tal c off run Any signs of rough engine operation or sluggish engine ace elera tion is good cause for discontinuing the take off If this occurs you are jt stificd in making a thorough full thr...

Page 61: ...al climb CROSSWIND TAKE OFFS Takeoffs into strong crosswinds lonnallr nre pedomtctl with lite lll H 1 mum flap setting necessilry for the field len th to nlinimizc the drift ilnglc immedi ttely niter trtltcoff With the ailerons p trti tlly deflec ted into the wind the 1irpl 1tJC is acccleralcd to 1 peed slightly hif ter thnn normnl nnd then ptdlcd off bruplly lo prevent possible scf tling back to ...

Page 62: ...211 l m h 4000 fl 11 B kts 14 0 NM Ill kts IS 3 N 1 I 03 kts 1220 m 219 km h 26 km 206 km h 28 km 191 krn h 8000 ft I 2 kts 14 S NM 115 lttj IS 8 NM IOG kts 2 l40 m 22 G km h 27 km 213km h 29 km 196km h St lnd nd Conditions NOTE Cntising should be done at a minimum of 75 power until a total of 25 hours bas accumulated or oil consumption has stabilized Operation at this higher power will ensure pro...

Page 63: ...t With aircraft weights lower than the full gross weight stall speeds are reduced_ The stall warning hom produces a steady signal 9 to 18 km h 5 to 10 ts G to 12 MPH before the actual stall is re tched and remains on tmtil the normal night attitude is resumed LANDINGS NORMAL LANDING Normal landing approaches can be made with power on or power off with any flap setting desired Surface winds and air...

Page 64: ...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 Maintain directional control by using the nose wheel steering system and the brakes NOTE If flap settings greater than 20 are used in sideslips with full n1dder deflection some elevator osdlhtjon may be felt at no nnal appro...

Page 65: ...sition 2 Propeller Are t Clear 3 Avionics Power Switch OFF 4 Master Switch ON 5 Mixture Rich 6 Throttle Open 1I 8 inch 1 2 em 7 Ignition Switch START 8 Release ignition switch to 0011 1 when engine starts 9 Oil Pressure Check Without Preheat 1 Prime the engine six to ten strokes while the propeller is beihg turned by hand with throttle closed Leave primer charged and ready for stroke 2 Propeller A...

Page 66: ...ressure remains norm al and steady the airplane is ready for take off ROUGH ENGINE OPERATION OR LOSS OF POWER CARBURETOR ICING A gradual loss of RPM and eventual engine roughness may result from the formation of carburetor ice To clear the ice apply full throttle and pu il the carburetor heat imob full out until the engine runs smoothly then remove carburetor heat nd re 1djust the throttle If cond...

Page 67: ...ttings and enrichen the mixture to determine if continued operation on BOTH magnetos is practicable If not1 switch to the good magneto and proceed to the nearest airport for repairs LOW OIL PRESSU1 tE If low oil pressure is accompanied by normal oil tempe nture there is a possibility the oil pressure gage or relief valve ls malfunctioning A leal in the line to the gage is not uecessarily cause for...

Page 68: ...n characteristics of the F172N Spins with baggage compartment and or child s seat occupied are prohibited The seat belts and shoulder harnesses should be adjusted to provide proper restraint during all anticipated flight conditions However care should be taken to ensure that the pilot can easily reach the flight controls and produce maximwn control travels 4 25 0 t AS TilE ROTATION STOI NEUTI ALI7...

Page 69: ...imum 1500 ft 460 m above ground level 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 Regardless of how many turns the spin is held or how it is entered the following recovery teclmique should be used 1 VERIFY 11 IAT THROTTLE IS IN IDLE POSITION_AND AILERONS A R E NEUTRAL 2 APPLY AND HOLD FU...

Page 70: ...xtended spins These differences are normal and will result in variations in the spin characteristics and in the spiraling tendencies for spins of more than 2 turns However the recovery technique 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 potential...

Page 71: ...it will be advis blc to plan on an ample safely mugin conceming the fuel reserve at arrival sb1ce the data given does not take into account the effects of wind navigational errors pilot teclmique nm up climb etc All these factors should be considered when estimating the reserve required by regulations Don t forget that maximum range increases by using a lower power setting DEMONSTRATED CROSSWlND T...

Page 72: ...level for the Reims Cessna Model F 172 N at 1043 l g certificated maximum weight is 73 9 d B A Tb e noise level detennincd according to tl1 e above shown regulation at maximum continuous power is 72 1 5 d B A The type certificate of noise limitation n N25 has been delivered to the Reims Cessna Model F 172 N Clll 12 October 1979 according to the regulation in force dated 30 July 1975 ...

Page 73: ...Flight Manual Edition 1 1 1 y 1977 REil S CESSNA F 172 N Rcvi i on 4 f 1 Y t 979 Page intentionally left blank 5 1 3 ...

Page 74: ...55 63 72 _ AIRSPEED CORRECTION TABLE f IAPS UP 130 148 167 185 204 131 148 165 183 202 70 80 90 100 110 71 80 89 99 109 81 92 104 115 127 82 92 102 114 125 FlAPS DOWN 10 130 148 167 185 204 131 148 167 183 200 70 80 90 100 110 71 80 90 99 108 81 92 104 115 127 82 92 104 114 124 FLAPS DOWN 40 130 148 158 133 152 161 70 80 85 72 82 87 81 92 98 83 94 100 222 241 259 278 296 220 239 258 276 313 120 13...

Page 75: ...OF BANK 0 300 82 km h 87 km h 44 kts 47 kts 5 1 M H 54 lvfPH 82 km h 87 km h 44 kts 47 kts 51 vfPH 54 f rPH 61 km h 65 lan h 33 kts 35 kts 38 lvfPH 4D tviPH 45 96 km h 115 52 kts 62 60 MPH 7 1 96 km h 115 52 kts 62 60 MPH 71 72 km h 87 39 kts 47 45tv PH 54 60 km h kts lvfPH km h kts lvfPH km h kts MPH 1 ro c rt c 0 l J ...

Page 76: ...ge at 3048 m 10 000 ft 40 US Gal 1S2 1 Usable Fuel Maximum Range at 3048 m 10 000 ft SO US Gal 189 1 Usable Fuel RATE OF CLIMB AT SEA LEVEL SERVICE CEiliNG STALL SPEED lAS Flaps Up Power Off flaps Down Power Off SPECIFICATIONS 1043 kg 910 kg 232 km h 125 kts 144 lvfPH 226 km b 122 kts 140 MPH Range 843 krn 4SS NM Time 3 8 hrs Range 1111 km 600 NM Time 5 0 Ius Range 1065 lun S75 NM Time 6 1 hrs Ran...

Page 77: ...ard Tanks 1 __ With Long Range Tanks 610 kg N z BAGGAGE 54 kg WING LOADrNG 64 kg m2 POWER LOADrNG 8 76 kg kW TOTAL FUEL CAPACITY tr1 ro 1 With Standard Tanks 163 litres 43 US Gal II 0 With Long Range Tanks 204 litres 54 US Gal 2 l OJ 1 N OIL TANK CAPACITY 6 qts 6 litres _ PROPEUER Fixed Pit ch Diameter 1 91 m 5 l ro 1 VI I 0 1 ENGINE Lycoming Engine 160 BHP 119 kW at 2700 RPM Type 0 320 H2AD 10 C ...

Page 78: ...0 509 302 549 326 591 351 639 376 689 55 61 4000 1219 308 564 332 610 360 660 387 713 416 773 MPH MPH 5000 1524 340 628 367 681 396 739 428 803 460 872 6000 1829 376 704 407 767 439 835 474 910 511 995 7000 2134 418 796 451 869 488 952 527 1045 568 1151 8000 2438 463 907 501 997 543 1100 587 1219 634 1361 NOTES 1 Short field technique as specified in Section 4 2 Prior to takeoff from fie lds above...

Page 79: ...6 410 244 440 262 474 282 509 303 547 l 914 z J 4000 1219 248 453 268 488 290 524 311 565 334 608 c 53 59 r MPH MPH 5000 1524 274 501 296 541 319 584 343 629 369 678 J N 6000 1829 302 556 326 602 352 651 379 704 408 764 z 7000 2134 334 622 361 674 390 732 421 794 453 864 8000 I 2438 370 700 401 760 433 829 466 904 503 989 j 11 0 Cll g NOTES 1 Short field technique as specified in Section 4 g 2 Pri...

Page 80: ...80 326 194 351 207 375 224 401 239 430 49 55 4000 1219 197 358 212 384 229 413 245 442 264 474 MPH MPH 5000 1524 216 395 233 424 251 456 271 489 291 526 6000 1829 239 436 258 469 277 504 299 544 322 585 7000 2134 264 483 285 527 306 562 331 607 355 654 8000 2438 291 538 314 581 340 628 366 680 393 735 NOTES 1 Short field technique as specified in Section 4 2 Prior to takeoff from fields above 3000...

Page 81: ...5 815 4 14 755 3 84 2000 610 133 72 83 765 3 89 705 3 58 650 3 30 4000 1219 131 71 82 655 3 33 600 3 05 545 2 77 6000 1829 130 70 81 545 2 77 495 2 52 440 2 24 8000 2438 128 69 79 440 2 24 390 1 99 335 1 70 10 000 3048 126 68 78 335 1 70 285 1 45 230 1 17 12 000 3658 124 67 77 230 1 17 180 0 91 NOTE Mixture leaned above 3000 ft 914 m for maximum RPM 40 C ft mn m s 695 3 53 590 3 485 2 46 385 1 96 ...

Page 82: ...9 3 4000 1219 7 131 71 580 2 9 6 1 2 4 5 B 14 B 5000 I 524 5 131 71 535 2 7 B 1 6 6 1 10 JB 5 6000 J829 3 130 70 485 2 5 10 1 9 7 2 12 22 2 7000 2134 I 128 69 440 2 2 12 2 3 B 7 15 27 8 8000 2438 I 128 69 390 2 15 2 7 10 2 19 35 2 9000 274 3 3 126 68 345 1 8 17 3 2 12 1 22 40 8 10 000 30i8 5 126 68 295 1 5 21 3 7 14 27 so II O Xl 3353 7 1 24 67 250 1 3 24 4 2 I 5 9 3 2 59 3 I 2 00 3658 9 124 67 20...

Page 83: ...Flight Manual REIMS CESSNA r172N Page intentionally left blank Edilion l 1 ugusl 1976 5 11 ...

Page 84: ...andard Temperature True Airspeed CoD um ption BHP us EHP kro h kt mph 1 h gal h 75 215 116 134 8 1 31 8 71 67 206 111 128 7 5 28 I 63 60 195 105 121 6 7 25 t 56 53 185 100 115 6 1 23 1 50 47 174 94 108 5 6 21 2 45 75 219 118 136 8 4 31 8 71 71 213 115 132 8 0 30 2 67 64 204 110 127 7 1 26 9 60 57 195 lOS 121 6 4 24 2 54 51 183 99 114 5 9 22 3 48 46 172 93 107 5 5 20 8 44 20 C Above Standard Temper...

Page 85: ...9 9 213 115 132 7 6 28 8 64 211 114 131 7 1 26 9 202 109 125 6 8 25 7 57 202 109 125 6 4 24 2 193 104 120 6 2 23 5 52 191 103 118 5 9 22 3 182 98 113 5 7 21 6 47 180 97 112 5 5 20 8 170 92 106 5 4 20 4 42 169 91 lOS 5 2 19 7 226 122 140 8 4 31 8 71 226 122 140 7 9 29 9 222 120 138 8 0 30 3 67 221 119 139 7 5 I 28 4 211 114 131 7 2 27 3 60 209 113 130 6 8 25 7 202 109 125 6 5 24 6 55 200 108 124 6 ...

Page 86: ...000 610 S L 400 711 I NOTE 111 I I 118 Q KTAS I I y A I 122 _KTAS 120 K TAS a l lJ 0 a_ t n 114 KTAS y I I 450 834 113 KTAS cr w 0 c t n D 107 KTAS I I 500 927 I I If i a a llJ __ __ w s s 0 0 CL c 1 LO 1 I I 100 KTAS I I 550 po19 _I I I 96 KTAS I I I 109 KTAS 93 I K1T S __f105 KTAS I 90 I gKTAS I I I 600 1112 RANGE NAUTICAL MILES l m This chart allows for the fuel used for engine start taxi tal e...

Page 87: ...ruise Standard Temperature 12000 3658 10000 3048 8000 2438 6000 1829 4000 1219 2000 610 S L NOTE I 3 1 L Q I I I C I 1 I I t JI I I I I I I I I I 0 0 0 0 UJ UJ I UJ UJ 3 s s I 0 0 0 0 a_ Q_ Q_ a cf LO c LO 1 0 lD 0 L I I I I I I 4 5 6 ENDURANCE HOUnS This chart allows for the fuel used for engine start taxi take off and climb and the time during climb as shown in figure page 5 10 I i I i I I I I 7...

Page 88: ... l t A 1 1 22 b KTAS r r t tl 6000 182 9 1 t 1 20 4 4 f j 11 3 1 05 1 93 1 KTAS KTAs KTA K1AS I 4000 f 4 1 t 1 4 E f t t 4 4 J j 4 5f J lf r 1 1219 6 6 5 I a_ j a_ CL CL f J Jf f 1 1 l t o 0 4 0 2000 f 1 L L t n f r t i co u 1 t 610 4 4 4 4 1 l 1 11 4 l l 107 1 100 90 JvKTAS VKTAS I VKTAS KTAS S L I_ I I I r 1 1 1 J 5 16 550 600 650 1019 1112 1204 700 12 97 750 1390 RANGE NAU TIC L MILES lon NOTE ...

Page 89: ...e 8 b 12000 3658 10000 3048 8000 2438 6000 I 1829 LLl Q s 4000 t 1219 2000 fi10 s L 1 0 I J 71 i Sf I J I I I I t 01 I I I I I l I I I a a a a w UJ UJ LU l s I s I s 0 0 0 0 a a 0 o e I 0 LP LP lD r 0 LO o t I I I i I i 4 5 6 7 8 ENDU TU NCE I IOU RS NOTE This chart allows for the fuel used for engine start taxi take0ff and climb and the time during climb as shown in figure page 5 10 I i I I l I 5...

Page 90: ... 168 396 174 407 180 418 186 428 WOO 1219 174 407 180 418 187 430 194 440 5000 1524 180 418 187 431 194 442 200 453 6000 1829 187 431 195 443 201 454 209 468 7000 2134 195 443 201 456 209 468 216 480 I 8000 2438 203 457 2 0 469 216 482 224 494 IDTES 1 Short field technique a s specified in Section 4 2 Decrease d istances 10 for each 9 knots headwind For operation with tailwinds up to 10 knots i Dc...

Page 91: ...38 UJ 1 w 6000 1829 0 co 4000 1 r 1219 t J w 2000 I 61 0 0 0 n I 0 MAXIMUM GL IDE 2 4 4 6 8 SPEED 121 km h 65 kts 75 MPH lAS PROPEllER W1ND l 1IWNG FLAPS UP ZERO WIND 10 12 14 16 8 12 16 20 24 28 32 18 36 GROUND DISTANCE NAUTICAL Ml LES km 20 40 ...

Page 92: ......

Page 93: ... must be attached to the approved Aircraft Flight Manual when the ProCom 4 PC 4 Intercom is installed in accordance with M O T FAA requirements The information contained herein supplements or supercedes the basic manual only in those areas listed herein For limitations procedures and performance information not contained in this supplement consult the basic aircraft flight manual Copyright 1989 by...

Page 94: ...ION II SECTION Ill SECTION IV SECTION V AIRCRAFT FLIGHT MANUAL SUPPLEMENT WITH PROCOM 4 INTERCOM TABLE OF CONTENTS Title LIMITATIONS OPERATION t t t EMERGENCY PROCEDURES PERFORMANCE INSTALLATION NOTES Page 3 3 6 6 6 ...

Page 95: ...NCTION Transmit function is available to the pilot in all modes of operation by keying the pilot PTT switch Transmit function is available to the copi lot when the mode selector switch is in either the ALL or CREW positions by keying the copilot PTT switch The pilot has transmit priority over the copilot Transmitter keying is indicated by an amber LED on the front panel of the intercom In the ALL ...

Page 96: ...s for pilot and copilot a master headphone volume control for passengers and a master squelch voice activation level control 1 3 Additional controls include squelch trimmers for pilot copilot and passengers a music input level trimmer and a headphone equalization trimmer to equalize radio and intercom volu me levels in headphones The squelch t rimmers are adjustable through access holes in the int...

Page 97: ...com does not affect the performance of the aircraft SECTON V INSTALLATION NOTES A This section is to be completed by the installing agency to note any special connections or procedures or to list any special options installed with the PC 4 Intercom B Special options or connections r v 1 _ l_ L _ t _ I t i 1 _ j l C Emergency Jack locations J l I _ 6 ...

Page 98: ...ot and copilot talk on a private channel without entertainment audio Passengers talk on a separate channel with entertainment audio Entertainment audio is muted during talk E TAPE RECORDER OPERATION If a tape recorder is connected as described in the intercom installation guide it will record all audio heard at the pilot s headphones F EMERGENCY OPERATION If power is lost to the PC 4 Intercom rota...

Page 99: ...pection and or testing at special u1tervals Since Dealers conduct all service inspection and test procedures in accordance with applicable Service Manuals it is recommended that you contact your Dealer concerning these requirements and begin scheduling your aircraft for service at the recommended intervals The manufactmer Progressive Care ensures that these requirements are accomplished at the req...

Page 100: ...l consumption has stabili7ed SAE 40 or SAE 50 above 16 C SAE 40 between 1 C and 32 C SAE 30 or SAE AO between 18 C and 21 oc SAE 30 below 12 C OIL SUMP CAPACITY 6 QTS 5 7 UTRES Do not operate on less than 4 qts 3 8 litres To minimize loss of oil through breather fiJI to 5 qts 4 7 litres for norm 1l flights of less than 3 hours For extended flight fill to 6 qts 5 7 litres Quantities shown above are...

Page 101: ...moulh period Reduce periods for prolonged operation in tlusty areas cold climates or when short flights anti long idle periods result in sludging conditions FUEL fUEL GRADE t vialion grade 100 LL BJue NOTE lOO Formerlyl00 130 Aviation Grade fuel Green with maximum lend con lent of 4 G cc per gal loll is also tpprovcu for usc I1efcr to VCO LYCOMI NG Sc rvice TI11l lctin N 1 070f fUEL TANK CAPACITY ...

Page 102: ...ar 1 79 bar MA lN WHEEL TIRE AND PRESSURE 31 psi 26 psi 6 00 x 6 4 PR 2 00 bar 29 psi NOSE GEAR SHOCK STRUT Edition 1 August 1 76 Check level fill as required with MIL H 5606 hydraulic nuid and inflate with air to 3 1 bars 45 psi 6 0 1 NOTE For complete servicing requirements refer to the aircraft Service Manual ...

Page 103: ...Tie sufficiently slrong ropes to wing and ta il tie down fittings1 md sec11re each rope to r un p Lie clown 4 Install a control surface Joel over Lh fin and rudc ler 5 Instrtll a pitot tube cover WINDSHIELD WINDOWS The windshield and windows should be kept clean at all times Wash them carefully with plenty of soap and water using palm of hand Chamois or sponge may be used but only to c u ry water ...

Page 104: ...owed by a rinse w tter and drying with chn111ois Do 110l ltSe polish or wnx 1nd void flying through rain hail or sleet during this period Once the finish has cured completely wnx or polish may be used p u licubrly on the leading edges engine nose cap and propeller spilmer to reduce the abrasion encountered in these areas PROPELLER CARE Preflight inspection of propeller blades for nicks and wiping ...

Page 105: ...bric with 1 voblilc solvent il m ty cl u11age the pauding and bacl ing mnlcrirlls The 11 roy dile11 trim instrument panel and control knobs need only be wiped off with t de1mp cloth Oil and grease on the control wheel lnd control lmobs can be removed with a cloth moistened with kerosene Volatile solvents such 1s mentioned in p uagraphs on c 1re of the windshield Jtlttsl never he used since they so...

Page 106: ......

Page 107: ... Indicator Instrument Flying IFR Glider Towing I look Femandcz Slds 1 it ARC 300 Automatic Pilot Sl ydiving J it Badin Crattzet RG 10 B Automatic Pilot Nav 0 Matic 200 A Automatic Pilot Nav 0 Matic 300 A Automatic Pilot Auxiliary Fuel System PAGE 6 1 1 and 6 1 2 6 2 1 and 6 2 2 6 3 1 6 4 1 6 4 1 6 5 1 6 6 1 6 7 1 thru 6 7 5 6 8 1 and 6 8 2 G 9 1 tln u 6 9 5 6 10 1 thru 6 10 4 6 11 1 tJ1nt G 11 6 6...

Page 108: ......

Page 109: ...st 1976 Revision 3 September 1978 OPTIONJ L EQUIP NIENT LIST DESCRIPTION PAGE 1 PPROVJ L Floatplane Option 6 1 6 1 tluu 6 16 36 r i f 1 r1 t I I Night VFR Opemtion 6 17 1j i I I Economy 1 v1ixture Indication 6 18 1 llld 6 18 2 0 t s o 1 1 l 6 1 0 2 2 ...

Page 110: ... ...

Page 111: ...the cowl nose cap openings One shield to partially cover the oil cooler air inlet at the RH rear side of the engine An insulation for the engine crankcase breather line NOTE Once installed the crankcase breather insulation is approved for pern1anent use in both cold and hot weather SECTION 2 LIMITATIONS The following information must be presented in the form of pl 1cards when the airplane is equip...

Page 112: ...ver and oil cooler cover plate must be removed when outside air temperal11re is above 7 C 3 On right hand nose cap cover plate Remove oil cooler cover plate from aft baffle when OAT exceeds 7 C Refer to Section 2 of the airplane night manual for the other limitations There is no change to Sections 3 through 5 of the airplane flight manual when this optional equipment is installed DGAC APPROVED ...

Page 113: ...IMITATIONS The following in fonnn tlon must be presented in the fonn of a rl tcard located on the inside of the ground service plug access d0or CAUTION 24 VOLTS D C This aircraft is equirped with alternator and a negative ground system Ol3SER VE PROPER POLl RITY Reverse polarity will damage electrical components Refer to Section 2 of the aircraft flight manual for the other limitati ons SECTION 4 ...

Page 114: ...ent by transient voltage Do not c1 1nl or start the engine with the l vionics power switch tnmed on This is especi llly important since it will enable the battery to absorb transient voltages which otherwise might damage the transistors in the electronic equipment The hattery and external power circuits have been designed to completely eliminate the need to jumper across the battery contactor to c...

Page 115: ...eaner method of draining engine oil To drain the oil with this valve installed slip a hose over the end of the valve rot1te the hose to a suitable container then push upward on the enJ of the valve unlil il snaps into the open position Spring clips will hold lhe valve open After draining tse a screwdriver or suitable tool to snap the valve inlo the extended closed position and remove the drain hos...

Page 116: ...I ...

Page 117: ...ilot d sires to use for transmission This is accomplished by placing the transmitter selector switch to the radio unit which is to be used 1 Spcnker Phone Switch The switch corresponding to the selected receiver is used to apply the output of that receiver either to the speaJ er through the audio amplifier in the up position or directly to the headphones in the down position ICOMBINATION HEADGEAR ...

Page 118: ... ...

Page 119: ...ions Under cruising conditions the fonn llion of ice is usu 1 lly slow providing lime lo clctccl the loss of RPM caused by the icc C ubmclOr icing dming t l c oH is r 1rc since the Iull open throttle conditio11 is less susceptible to ice obstrucl ion If the carburetor air temperature gage needle moves into the yellow arc during pol ential carburetor icing conditions or there is an unexplained drop...

Page 120: ......

Page 121: ... operation of a flight computer TO OBT A IN TRUE A IRSPEED rotate ring until pressure altitude is align ed with outside air temperature in degrees fahrenheit Then read true a irspeed on rotatable ring opposite airspeed needle NOTE Pressure tllitudc should not be confused with indic ted altitude To obtain pressme altitude set barometric seale on aHim eter to 1013 m b and read pressure altitude on l...

Page 122: ... ...

Page 123: ...and Stall Warning Heater System 0 One Altemate Static Pressure Source 0 One Rate of Climb Indicator 0 One Outside Air Tempcr ltut c Gage 0 One Electric Clocl with Second lland 0 One Flashing Beacon 0 Position Lights S Landing Lights on Left Wing 0 One Instrument Lighting System S One Pocket with Two Spare fuses Each Rating 0 Two Category 2 VHF Transmitter Receivers 0 One Category 2 VOR Receiver 0 ...

Page 124: ...1 2 3 4 5 t2 13 14 15 16 18 19 20 21 23 24 25 I I I I 1 l s I 1 0 z I t l oq I 0 I z c s 3 t j T1 z l 1 J J 0 z 0 r 48 47 46 45 26 0 tr1 1 c 39 til 9 0 38 0 OJ I I 1 JQ C c I 1 rt i c 0 1 J 0 _ I D J 00 ...

Page 125: ...35 Air Conditioning Controls z n C 7 V 11 Secondary Altimeter fuel Selector Valve Handle 36 J j 0 12 Vertical Speed Indicator 37 Rudder Trim Control Lever c j N 0 13 Encoding Altimeter 38 Elevator Trim Control Wheel z 14 ADF Bearing Indic ator 39 Carburetor Heat Control Knob 15 Course Deviation Indicators 40 Electrical Switches 16 Transponder 41 Circuit Breakers 1 1 tr1 17 Magnetic Compass Parking...

Page 126: ...ensation from the system lines If erroneous instrument readings are suspected due to water or ice in the st atic pressure lines the static pressure altemate source valve should he opened there by supplying static pressure from the cabin Ca bin pressures will vary however with open cabin ventilators or windows The most adverse combinations will result in airspeed and altimeter variati ons of no mor...

Page 127: ...RATION ALTERNATE STATIC SOURCE HEATER VENTS AND WINDOWS CLOSED 40 50 60 70 80 90 100 110 39 51 61 71 82 91 101 111 40 50 60 70 80 90 100 110 40 51 61 71 81 9l 99 108 40 50 60 70 80 85 38 50 60 70 79 83 120 121 HEATER VENTS OPEN AND WINDOWS CLOSED 40 50 60 70 80 90 100 110 120 36 48 59 70 80 89 99 108 118 40 50 60 70 80 90 100 110 38 49 59 69 79 88 97 106 40 50 60 70 80 85 34 47 57 67 77 81 WINDOWS...

Page 128: ... ...

Page 129: ... rear view mirrors on wing struts An operating instruction placard near the release control OPERATION REQUIREMENTS Maximum weight of towed glider Maximum weigltt of towing a ircraft i e pilot 80 litres fuel GLIDER TOWING PROCEDURE In addition to normal operating procetlures function llJy test aircraft nd glider hool s Wing flaps 15 full throttle power Lift off nose wheel at li S 96 hm h 52 l ts GO...

Page 130: ...t exceed 225 lun h 121 l ts Jtl 0 MPH lAS GLlDER TOWlNG INSTRUCTION PLACARD This placard which is located on the cabin LH side near the pilot shows the following indications Maximum weight of towed glider Maximum weight of towing aircraft Normal towing indicated airspeed v1inimum towing indicated airspeed G 8 2 DGAC APPROVED 500 l g 820 kg 101 l m h 55 kts 63 MPH 88 krn h 48 kts 55 fvi PH ...

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Reims Aviation Cessna F172 N, Flight Manual

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