Piper PA28R 200 ARROW CHECKLIST

(b) Tx set on correct box (c) Volume control (d) Correct Freq. (e) Operate test switch (f) Check audio on phone / speaker (g) Check ammeter increase on Tx (h) Line of sight / out of range Out of hours? 2 ALTERNATIVES (a) Other box (b) Another freq. (c) Hand mic (select audio on speaker) 3 NO CONTACT (a)Transponder 7600 / ON (b)Follow Radio fail procedure for A/D Redhill Aviation Flight Centre PA28R Checklist 8 PRE-FLIGHT CHECKLIST NB: Before entering the cockpit ensure that the aircraft is free from slush, snow, ice & hoar frost. In particular check hinges & gaps of the flying controls, trim tabs & flaps. COCKPIT PREPARATION Aircraft documentation Stowed Parking brake ON IF screens Stowed (if used) First Aid kit Stowed Fire extinguisher Checked Magnetos switches OFF Gear selector DOWN Avionics Master switch OFF Circuit breakers Check IN Trim indicators Correct movement / set Flying controls Full, free & correct movement Battery Master switch ON Landing gear indicator 3 greens Pitot heater ON Fuel contents CHECK Fuel selector Emptier tank Low voltage light / Annunciator Panel Test / ON Recognition/Landing lights ON / CHECK / OFF Anti-collision light ON / CHECK / OFF Navigation lights (leave on at night) ON / CHECK / OFF Pitot heater OFF Panel lighting ON / CHECK / OFF Leave on at night (Only for night flying) Battery switch OFF Pitot static drains (if fitted) Operate Flaps FULLY DOWN / CHECK ALL STAGES Redhill Aviation Flight Centre PA28R Checklist 9 EXTERNAL: CABIN UPPER FUSELAGE 1 Door Closed / flush 2 Starboard windows Clean 3 Upper fuselage Check / undamaged 4 Tow bar (if carried) Stowed 5 Baggage door Secure STARBOARD WING: 1 Flap Check / Undamaged 2 Aileron Undamaged-check: surface, hinges, static wicks 3 Wing tip Undamaged 4 Strobe, Navigation & landing light Undamaged 5 Wing surface Undamaged 6 Fuel tank Check: contents, cap secure, sample, no seepage 7 Main gear Secure, oleo extension 4 ½ “ 8 Tyre Check: inflation, creep, no damage 9 Brakes Check: pads, no hydraulic leaks, undamaged 10 Wheel bay Check clear & door secure 11 Fresh air intake Unobstructed NOSE SECTION: 1 Windscreen Clean 2 OAT probe Check 3 Oil contents Check, cap secure 6-8 qts, 2 qts min, (Rec. min 5 qts.) 4 Starboard cowling Secure 5 Prop / spinner Secure & undamaged 6 Air intake Unobstructed 7 Alternator belt Check tension 8 Landing light Undamaged 9 Nose gear Check secure Oleo extension ¾” 10 Wheel bay Check clear, door secure 11 Tyre Inflation, creep, no damage 12 Port cowling Secure 13 Fuel drain Sample, no seepage 14 Port windows Clean Redhill Aviation Flight Centre PA28R Checklist 10 PORT WING: 1 Fresh air intake Unobstructed 2 Brakes Check: pads, no hydraulic leaks, undamaged 3 Tyre Check: inflation, creep, no damage 4 Main gear Secure, oleo extension 4½ “ 5 Wheel bay Check security & door 6 Fuel tank Check: contents, cap secure, sample, no seepage 7 Pitot head / Static vent Secure unobstructed 8 Stall warning vane Undamaged / free 9 Wing surface Undamaged 10 Wing tip Undamaged 11 Strobe, Navigation & landing light Undamaged 12 Aileron Undamaged-check: surface, hinges, static wicks 13 Flaps Check / undamaged REAR FUSELAGE, FIN & STABILATOR: 1 Radio aerials Secure / undamaged 2 Port fuselage & window Undamaged, clean 3 Fresh air intake Unobstructed 4 Fin surface Secure, undamaged 5 Rudder & Nav. light Undamaged 6 Stabilator Undamaged, free movement 7 Stabilator tab Undamaged 8 Air con scoop (if fitted) Flush / undamaged 9 Starboard fuselage & window Undamaged & clean Redhill Aviation Flight Centre PA28R Checklist 11 BEFORE ENGINE START CHECKS: 1 Flap UP 2 External checks Complete 3 Passenger brief Completed 4 Cabin door Closed & latched 5 Seats Adjusted & locked 6 Seat belts & shoulder straps Fitted / secure 7 Alternate static selector (if fitted) Check / Normal 8 Flight instruments & Check Standby compass & deviation card Check 9 Battery Master switch ON 10 Annunciator / Low voltage light Check / ON 11 Avionics Master switch ON 12 VHF radio check Request A/D data (or ATIS) Start request (OBTAIN if required) 13 Altimeter(s) Set QFE +50’ / -75’ QNH +50’ / -75’ (ELEV) 14 Avionics Master switch OFF STARTING ENGINE: 1 Anti collision lights ON 2 Fuel selector Least full tank 3 Mixture Exercise ICO 4 Throttle Exercise 1/2 “ OPEN 5 Fuel pump ON, check pressure in Green, OFF 6 Alternate Air Full & free movement, set OFF 7 COLD start only Mixture fully RICH until fuel flow Indicated, return to ICO HOT start only Leave mixture in ICO 8 Lookout PROP AREA CLEAR “CLEAR PROP” 9 Magnetos / starter Both & Operate 10 Mixture As engine starts ADVANCE to RICH 11 Starter warning light OUT 12 Oil Pressure Check rising within 30 sec 13 Throttle 1300 RPM 14 Alternator ON 15 Low Voltage light OUT 16 Suction Indicating 17 Magnetos Check Redhill Aviation Flight Centre PA28R Checklist 12 ENGINE START WHEN FLOODED: 1 Throttle Full open 2 Fuel pump OFF 3 Mixture control ICO 4 Starter Operate When engine fires: Retard throttle, mixture advance slowly to rich. AFTER START CHECKS: 1 Avionics switch ON Check: I/C ON, check VOL COMMS 1 & 2 ON NAV 1 & 2 ON ADF ON TRANSPONDER standby DME ON 2 Electric trim Check 3 Flight Instruments Check clock-UTC Wind stopwatch AI erect & set VSI ± 200’, ASI zero Turn coordinator ,”OFF” flag away HSI heading flag away Cross check HSI / RMI heading Standby compass Slaving meter control, slaving Deviation cards fitted 4 Avionics, Check as required: ADF function on 2 freq. Set for departure VOR ILS & DME if possible set for departure Transponder: Test, set Standby 5 Auto pilot OFF 6 Radios As required 7 Altimeter(s) Check set TAXI CHECKS: 1 Brakes & nose wheel steering CHECK (for both pilots) 2 Flight instruments HSI, RMI, standby compass Turn coordinator Attitude Indicator ADF needle tracking Redhill Aviation Flight Centre PA28R Checklist 13 POWER CHECKS: 1 Position INTO WIND Clear of obstructions & loose stones 2 Parking brake ON 3 Fuel selector Change tanks to fullest 4 Lookout Clear all round 5 Throttle 2000 rpm 6 Alternate air Select ON / OFF Negligible change in MP 7 Fuel pump Select OFF, check pressure Select ON 8 Magnetos Check, reset to both (Max drop 175 rpm, Max difference 50 rpm) 9 Alternator output Check 10 Suction 4.9 - 5.1 Ins Hg 11 T’s & P’s Check in normal limits 12 Propeller control Exercise (3 times if cold) Down to 1500 rpm & to MAX rpm 13 Throttle CLOSE, check idle 600 / 800 rpm Reset 1300 rpm Redhill Aviation Flight Centre PA28R Checklist 14 PRE TAKE OFF CHECKS: 1 IF screens As required 2 Trimmers SET 3 Throttle friction SET 4 Mixture RICH 5 Magnetos ON BOTH 6 Alternate air (if fitted) OFF 7 Fuel selector ON Fuller tank, check contents 8 Fuel pump ON 9 Flaps Set normal-UP, Short / soft field 25º 10 Engine instruments Check: OIL- T’s & P’s, Fuel pressure 11 Compasses Check 12 Seat belts / seat backs Secured / erect 13 Cabin door Latched & locked 14 Flying controls Full, free & correct movement 15 Departure clearance Obtain review 16 Avionics Confirm radio Nav set for departure 17 Flight instruments Check Altimeters set 18 Take-off brief Review: Take-off speeds Cross-wind component Emergency procedures WHEN GIVEN LINE-UP CLEARANCE: A Anti collision light ON T Transponder ON P Pitot heat ON L Lights, (landing & recognition) ON Redhill Aviation Flight Centre PA28R Checklist 15 AFTER TAKE-OFF / GO AROUND 1 Brakes ON / OFF 2 Gear UP after established in climb & insufficient runway left to land Max 125 mph 3 Flaps UP (above 200 feet aal) 4 Altimeters A/D QNH/QFE or QFE/QNH (ct) Cleared FL 1013 / Zone / Reg QNH 5 Icing CHECK 6 Radio Aids Ident if req. 7 Recognition / Landing lights OFF 8 Fuel pump OFF above 1000’ TOP OF CLIMB CHECKS: 1 Cruise power 24”/ 2400 RPM 2 Mixture Lean 3 Engine instruments CHECK: T’s & P’s, EGT, Fuel pressure CRUISE CHECKS (FREDAI): 1 Fuel Check: Quantity, balance 2 Radio / Nav Set / Identified 3 Engine Check: T’s & P’s, EGT, Fuel pressure Ammeter, Suction 4 DI Synchronise 5 Altimeter Check 6 Icing Check (OAT) DESCENT CHECKS (IFR): 1 MSA Check 2 Mixture As required (enrich during descent) 3 Altimeters Check: 4 WX Obtain, check minima 5 Icing Check (OAT) Redhill Aviation Flight Centre PA28R Checklist 16 INITIAL APC CHECKS (FFREHAI): 1 Fuel Check: Quantity, Balanced 2 Radio / Nav Set, Identified 3 Engine & associated instruments Check: T’s & P’s, Mixture, EGT, Suction Ammeter, Suction 4 DI / compass Cross check 5 Icing Check (OAT) 6 Altimeter Set PRE-LANDING CHECKS: 1 Brakes OFF 2 Undercarriage DOWN ( 3 greens ) 3 Mixture RICH 4 Propeller 2600 rpm 5 Fuel Contents, balance, sufficient Pump ON 6 Instruments T’s & P’s, QNH, DI 7 Hatch Closed & latched 8 Harness / seat Secure / erect 9 Landing light ON AFTER LANDING CHECKS (RWY VACATED): 1 Flaps UP 2 Fuel pump OFF 3 Recognition lights (strobe) OFF 4 Landing lights AS REQUIRED 5 Pitot heat OFF 6 Trimmers Neutral 7 Radio / Nav equipment As required 8 Transponder standby STANDBY Redhill Aviation Flight Centre PA28R Checklist 17 SHUT DOWN CHECKS: 1 Parking brake ON 2 Throttle 1300 rpm 3 Magnetos Check 4 Avionics master switch OFF 5 Mixture ICO 6 Throttle Closed When engine stops: 7 Magneto OFF, key removed 8 Exterior lights (inc. Anti-collision) OFF 9 Fuel selector OFF 10 Interior lights OFF 11 Battery & Alternator OFF 12 Control wheel Secure with seat straps if needed Note: Following G/A where the subsequent approach & landing is made at the same airfield Top of Climb, Cruise & Descent checks may at pilots discretion be omitted. NON NORMALS PRE-STALL CHECKS: 1 H Height Sufficient to recover by 2000’ AGL or 1000’ above cloud 2 A Airframe Flap as required 3 S Security Seat belts & shoulder straps tight, Loose articles stowed 4 E Engine Mixture RICH, fuel, contents sufficient, Pump ON Fuel pressure checked, T’s & P’s 5 L Location Clear of active A/D’s, built up areas, CAS, Danger areas & clouds 6 L Lookout Clearing turn Redhill Aviation Flight Centre PA28R Checklist 18 ALTIMETER SETTING PROCEDURES: No 1 No 2 PREFLIGHT Check within +50 ft / -75 ft of Airport QFE Airport QFE datum, 50 ft of each other Airport QNH Airport QNH DEPARTURE For take-off Airport QNH Airport/zone QNH Cleared to FL 1013 Airport/zone QNH CRUISE Above Transition Alt 1013 Regional QNH At or below Transition Alt Regional QNH Regional QNH Note: In or below TMA use TMA QNH, not regional QNH DESCENT Cleared to FL 1013 Zone/regional QNH Cleared to ALT Zone/ airport QNH Zone/regional QNH FIANL APC / CTS QFE Airport QNH MISSED APC Airport QNH Airport QNH Note: Airport QNH valid within 25 nm of airport RECOMMENDED OPERATING SPEEDS / LIMITATIONS: IAS (mph) TAKE-OFF* 0º FLAP 62-80 (See perf. Graph) CLIMB 0º flap / Best angle / gear up Vx 96 0º flap / Best rate / gear up Vy 100 Cruise climb 110 CRUISE Normal / 24” / 2400 rpm (75%) 150 Int Apc / 20” / 2400 rpm 120 GLIDE Power off, flaps up, gear up 105 APPROACH* Normal 40 ºflaps 70-90 See perf. Graph * Add 5 kts to T/O speeds & VAT in strong wind / turbulence, reducing flap as necessary Max airspeeds FLAP White arc 125 VNO Green arc 175 VNE Red line 214 VA (MAUW:2900 lbs) 132 VLE Gear lowering 153 VLO Gear raising 125 Max cross wind 17 (Kts) Redhill Aviation Flight Centre PA28R Checklist 19 Max AUW 2750 lbs CROSSWIND COMPONENT TABLE: WIND (Kts) Angle between wind direction & runway heading 10 20 30 40 50 60 70 80 90 5 1 2 2 3 4 4 4 5 5 10 2 3 5 6 7 8 9 9 10 15 3 5 7 9 11 13 14 14 15 20 3 7 10 13 15 17 18 19 20 25 4 8 13 16 19 22 23 24 25 30 5 10 15 19 23 26 28 29 30 35 6 12 17 22 26 30 32 34 3 40 7 14 20 25 30 35 37 39 40 45 8 15 22 29 34 39 42 44 45 50 9 17 25 32 38 43 47 49 50 PA28R-200 ARROW HANDLING NOTES PRINCIPAL DIMENTIONS: Span 32’ 2” Length 24’ 8” Height 8’00” Track 10’ 6” ENGINE: Avro Lycoming IO-369-cic, four cylinder horizontally opposed, developing 200BHP @ 2700 rpm at sea level. TACHOMETER: Normal operating range 500 to 2000rpm & 2350 to 2700 rpm (green arc). Avoid continuous operation from 2000 to 2350 rpm (red arc) PROPELLER: Two blade, Hartzell HC-C2YK-1 / 7666A-2 constant speed variable pitch. Diameter 74” OIL TEMPERATURE: Maximum Normal range 118ºC / 245 ºF ( red line) 75º to 245ºF (green arc) OIL PRESSURE (PSI) Maximum Normal range Red line Green arc 90 60-90 Redhill Aviation Flight Centre PA28R Checklist 20 Minimum (idling) Red line 25 FUEL PRESSURE (PSI): Maximum Normal range Minimum (idling) Red line Green arc Red line 45 14-45 14 SUCTION: Normal operating range 5.0 ± 0.1” FUEL GRADE: 100LL Grade aviation fuel OIL GRADE: Aeroshell W 15-W50 TYRES: 5.00 X 5 nose wheel 6.00 X 6 main wheel 30 PSI 27PSI LIMITATIONS: Maximum permissible all up weight: (Normal) 2650lbs / 1204 kgs Max baggage in baggage compartment 200lbs / 90 kgs Aircraft is not designed for aerobatics, spinning prohibited. C of G location: The C of G Reference Datum is 78.4 inches ahead of the wing leading edge at the intersection of the straight & tapered section. Normal category C of G limits are: Forward: Rear limits: +87.3” / 2650lbs +82.0” / 2300lbs +80.0” / 1800lbs 93.00” Straight line variation between points given. Basic empty mass of the aircraft is approximately 1668lbs which includes unusable fuel & full oil. However to obtain this weight for a particular aircraft, reference must be made to the aircrafts own weight schedule. Fuel is taken as 7.2lbs / gallon or 0.72 kg / litre. Redhill Aviation Flight Centre PA28R Checklist 21 SAMPLE LOADING PROBLEM: ITEM WEIGHT LBS LVER ARM (ins) MOMENT (lbs/ins) BEM USABLE FUEL (48.5usg max) Pilot & front seat passenger Rear seat passengers Baggage Ramp weight less fuel for start & taxi Moment due to gear retraction 1668 291 340 340 19 -8 85.6 95.0 80.5 118.1 142.8 95 142781 27645 27370 40154 2713 -760 819 TOTALS 2650 90.84 240722 NOTE: The max take off weight is 2650lbs, however a ramp mass of 2658 is allowed as it assumes that 8lbs of fuel will be used prior to departure. In the above sample loading problem the total moment is divided by the total weight, this gives a C of G of 90.84” aft of datum. This is within limits of 87.3” to 93” & weight is no more than allowable- so the loading is acceptable. Alternatively the totals can be entered on a Co G Moment Envelope. AIRSPEED LIMITATIONS (IAS in mph): VNE………………………………………………………214 VNO……………………………………………………...170 VA..……..……………………………………………….131 VFE……………………………………………..………..125 Redhill Aviation Flight Centre PA28R Checklist 22 ASI COLOUR MARKINGS (IAS in mph): Red Line …………………………………………………………………214 Yellow Arc (Caution Range) ………………………………………170-214 Green Arc (Normal operating Range) ……………………………71-170 White Arc (Flap Operating Range) ……………………………….64-125 MAXIMUM DEMONSTRATED CROSSWIND: For take-off & landing is 17 Kts. STALL SPEEDS: At gross weight, power off, speeds in mph: FLAP DEFLECTION ANGLE OF BANK GEAR DOWN 0º 20º 40º 60º GEAR UP 71 73 81 100 40º 64 66 73 90 STALL WARNING: The stall warning is by way of a stall warning horn which is activated by the airflow over the wing between 5 & 10 knots before the stall is reached 7 remains on up to the stall; it may be accompanied with mild airframe buffeting & gentle pitching. During pre-flight check, the stall warning horn should be checked. FLIGHT AT NIGHT: The aircraft is approved for night flying. FLIGHT IN ICING CONDITIONS: Flight in icing conditions is strictly prohibited. Redhill Aviation Flight Centre PA28R Checklist 23 FUEL SYSTEM: Fuel is supplied to the engine from two tanks, one in each wing; a tab in each tank aids determining quantity if not full. The fuel selector is located on the lower left side panel forward of the pilot’s seat. A metal bar stops accidental turning OFF the fuel supply. Fuel is supplied to the engine from the selected tank by means of an engine driven pump. An electric pump should be switched ON for take-off & landing & when switching between tanks. Each tank is equipped with a quick drain valve located under the inboard section of the wing. A fuel strainer is used to examine the fuel for water, dirt & correct colour. A fuel strainer on the left hand side of the fire wall also has a drain valve accessible via the left nose section. Ensure that the valves are closed after use. MIXTURE: The mixture should be leaned in level cruise, this is particularly important above 3000’. However, the mixture should not be leaned during climbs below 3000/. For economy cruise the mixture should be leaned to peak EGT in accordance with the aircraft manual. OIL SYSTEM: A wet sump lubricating system is employed. The oil capacity is 8 qts. Minimum safe quantity is 2 qts. Note: The oil level reading will not be accurate if the engine has been recently running. VACUUM SYSTEM: Suction to the DI & AI is provided by an engine driven vacuum pump. A suction gauge is fitted on the right hand side of the instrument panel & indicates the suction below ambient pressure. A vacuum regulator is provided in the system to protect the gyros, the valve is set to give a vacuum of 5.0” ±0.1” of mercury. An electrically operated auxiliary system is fitted to some aircraft for in flight back up only. Takeoff with the main engine driven pump unserviceable is not approved. If required in flight, all unnecessary electrical equipment should be turned off & when the AUX VAC switch is selected the AUX ON light should illuminate with an electrical load showing approximately 15 amps. If the vacuum falls below 4.8”, flight in IMC should be discontinued. Redhill Aviation Flight Centre PA28R Checklist 24 ELECTRICAL SYSTEM: Electrical energy is supplied by a 14V, direct current system powered by a belt driven alternator & a 12V battery placed in a plastic box immediately aft of the baggage compartment. A Master switch controls power to all circuits via a buss bar, except the ignition system. The MASTER switch is usually of the split-rocker type; & the left half is BAT the right half controls the ALT. Normally both sides of the master are used together. The BAT position could be used on its own to check equipment on the ground, however this places the entire electrical load on the battery & continued operation will reduce battery power sufficiently to open the battery contacter- removing power from the alternator field and preventing alternator start. The Ammeter displays in amps the load placed on the alternator; it does not indicate battery discharge. With all electrical equipment turned on (except the Master switch) the ammeter will show the amount of charging current demanded by the battery. As other equipment is turned on the reading will increase. The resulting load includes the battery and for night flying is in the region of 30 amps. Loss of alternator output is detected by zero reading on the ammeter. This zero reading should be confirmed by loading the electrical system: if there is no increase in the ammeter reading then an alternator failure may be assumed. In this case reduce electrical load as much as possible and then reset the CB (if available), after 2 to 5 minutes cooling off period, try a voltage regulator reset by turning the ALT switch OFF for one second and then to ON. If the ammeter continues to read zero, turn off the ALT switch, minimise the electrical oad and terminate flight as soon as practicable. “Push to reset” CB’s protect most of the electrical circuits. However a period of 2 to 5 minute cooling off period should be allowed. PITOT STATIC SYSTEM: Pitot head is located underneath the left wing, both pitot & static pressure are sensed there & fed to gauges on instrument panel. An alternate static source is available, the control valve being located underneath the left hand side of the instrument panel. When selected to “Alternate” feeds cabin pressure into the ASI, VSI & Altimeter. During operation of alternate static air, the cabin heater & defroster must be “ON”, the storm vent & cabin vents closed. Redhill Aviation Flight Centre PA28R Checklist 25 Altimeter error should be less than 50’. A drain valve for pitot & static lines is located on the left hand side of the pilot’s seat near the floor. LIGHTING SYSTEM: External lighting consists of, landings lights, anti-collision lights, strobes & navigation lights each selected by individual rocker switches on the instrument panel. Strobes should not be operated on the ground in close proximity with other aircraft as they maybe distracting to other pilots. In the air strobes can be disorientating when flying through fog or haze. IGNITION SYSTEM: The PA28 is equipped with a dual ignition system. There are four positions for the ignition switch: OFF, RIGHT, LEFT, BOTH, to start requires BOTH selected with an additional push & turn action. NB: If the starter warning light remains on, the starter is still engaged & the ignition switch must be immediately turned off. LANDING GEAR: The Arrow is equipped with a retractable tricycle landing gear, which is hydraulically actuated by an electrically powered reversible pump. The pump is controlled by a selector switch to the left of the control quadrant. Landing gear is retracted or extended in about seven seconds. The aircraft also incorporates a pressure sensing device in the system which lowers the gear regardless of gear selector position, depending on the airspeed & engine power (propeller slipstream). Gear extension is designed to occur, even when the selector is in the up position, at airspeeds below approximately 105 mph. The extension speed will vary between 85 & 105 mph depending on power settings & altitude. The device also prevents retraction at speeds below approx. 85 mph with full power even if selected up. The speed increases with reduced power &/or increased altitude. Manual override of the device is provided by an emergency gear lever located between the front seats & to the left of the flap handle. The sensing device operation is controlled by differential air pressure across a flexible diaphragm which is mechanically linked to a hydraulic valve & an electrical switch which activates the pump motor. A high pressure & static source for actuating the diaphragm is provided in a mast mounted on the left side of the fuselage above the wing. Any obstruction in the wholes in the mast will cause the gear to extend. An optional heated mast is available to alleviate obstruction caused by icing & is turned on when the pitot heat is selected on. Redhill Aviation Flight Centre PA28R Checklist 26 The emergency gear lever, when held in the raised position, can be used to override the system & gear position is then controlled by the selector switch regardless of power/airspeed settings. The emergency gear lever is provided with a latching device which may be used to lock the override lever in the up position. The latch is located on the left side panel of the console below the level of the manual override lever. To lock the override lever in the up position, raise the override lever to the full up position & push the latch in. A yellow warning light located below the gear selector switch flashes to warn the pilot that the automatic gear lowering system is disabled. The latch is spring loaded to the off position to aid disengagement. To disengage the latch, raise the override lever & release. The lever will return to its normal position & the yellow flag will extinguish. The lever must also be used in the raised (up) position when gear-up stalls are practised. When used for emergency extension of the gear, the emergency gear lever manually releases pressure to permit the gear to free fall with spring assistance on the nose gear. The lever must be held in the downward position for emergency extension. Gear down & locked positions are indicated by three green lights below the selector, a yellow in transit light is located at the top of the panel. An all lights out condition indicates the gear is up. The gear should not be retracted above 125 mph or lowered above 150 mph. Two micro switches in the throttle quadrant activate a warning horn & a red “Warning gear up” light under the following conditions: Gear up & power reduced below 14” MAP. On a/c equipped with backup gear extender, if the system has extended the gear with the selector in UP, except at full throttle. Gear selector switch UP while on the ground. The nose wheel is steerable through 60 degree arc via the rudder pedals. As the nose wheel retracts, the steering linkage disengages to reduce rudder pedal load in flight. The nose wheel is equipped with a hydraulic shimmy damper. The oleo struts are of the air-oil type, with normal extension of 2.75” for nose & 2” for main wheels under normal static load (empty weight of a/c plus full fuel & oil). The standard brake system includes toe brakes on the LHS rudder pedals & a handbrake located below & near the centre of the instrument panel. Toe brakes on the RHS are optional. Toe brakes & hand brake have individual brake cylinder fed from a common reservoir. Redhill Aviation Flight Centre PA28R Checklist 27 A single disc, single puck brake is mounted on the main gear. A brake disc is mounted on the inboard side of the wheels, the brake housing which incorporates the pucks is mounted to the inboard side of the wheel axle. FLIGHT CONTROLS: The metal control surfaces operate by cables between the flying controls & surfaces. The Stabilator is an all moving tail plane with a rear mounted trim tab controlled by a wheel between the front seats. Rudder trim is mounted centrally below the instrument panel. Simple flaps are manually operated & spring loaded to return to the up position. The three positions are: 10, 25 & 40 degrees. Externally the flaps may be used as a step only when fully retracted. CABIN HEATING & VENTILATION: Heat for the cabin is provided by a heater muff attached to the exhaust system. Heater controls are located on the far right hand side of the instrument panel. Fresh air inlets are situated in the leading edge of the wing near the routes. Fresh air controls are located on the side of the cabin near the floor on each side, air is exhausted through an outlet under the rear seat. Air flow can be regulated between front & rear seats by levers located on the side of a heat duct panel situated between the front seats. When cabin heat is operated this duct becomes very hot & could result in minor burns if legs are placed to close for too long a period.