PA-28R Arrow III – Operations Manual

Taxi ........................................................................................................................51 Take-off .................................................................................................................53 Climb.....................................................................................................................54 Cruise....................................................................................................................55 Descent .................................................................................................................58 PA-28R Arrow III – Operations Manual 5 Approach and landing ..........................................................................................59 Shutdown..............................................................................................................62 NORMAL PROCEDURES.........................................................................................63 Airspeed (IAS) for safe operations ........................................................................63 Pre-flight ...............................................................................................................63 Before starting engine ..........................................................................................64 Engine starting ......................................................................................................64 Taxiing ...................................................................................................................65 Ground check .......................................................................................................65 Before take-off ......................................................................................................66 Take-off .................................................................................................................66 Climb.....................................................................................................................67 Cruise....................................................................................................................67 Descent .................................................................................................................67 Approach and landing ..........................................................................................67 Shutdown..............................................................................................................68 Stalls .....................................................................................................................68 EMERGENCY PROCEDURES .................................................................................69 Airspeed (IAS) for safe operations ........................................................................69 Engine failures ......................................................................................................69 Power off landing..................................................................................................70 Fires ......................................................................................................................71 Low oil pressure ...................................................................................................71 Low fuel flow/pressure .........................................................................................72 Propeller governor failure .....................................................................................72 Electrical failures ...................................................................................................72 Icing ......................................................................................................................72 Emergency landing gear extension ......................................................................73 Spin recovery ........................................................................................................73 Airspeed indicating system failure........................................................................73 CREDITS ...................................................................................................................74 COPYRIGHT..............................................................................................................74 PA-28R Arrow III – Operations Manual 6 INTRODUCTION The PA-28R Arrow III is a four-seat, piston-engine aircraft equipped with retractable tricycle landing gear and a constant-speed propeller – an ideal aircraft for touring and instrument training. The origins of the Arrow start with the Piper Cherokee, which began production in 1961. The Cherokee was introduced as a more affordable alternative to Piper’s Comanche and to compete with the popular Cessna 172. Piper introduced the original Cherokee Arrow in 1967 and it was the first of the Cherokee family to feature retractable landing gear. The Arrow II followed in 1972 with a stretched fuselage to provide increased leg room for the rear passengers, and the Arrow III arrived in 1977 with larger fuel tanks for improved range and a semi- tapered wing and longer stabilator for improved low-speed handling. Over 6,000 PA-28Rs have been built and the Arrow III continues to be flown all around the world. Aircraft specifications Dimensions Length 7.5 m (24.7 ft) Wingspan 10.8 m (35.4 ft) Height (to top of tail) 2.4 m (7.9 ft) Wing area 15.8 m2 (170 ft2) Engine Type Lycoming IO-360 four cylinder, horizontally opposed piston Power 200 horsepower Propeller Three-blade, constant-speed, hydraulically actuated Weights Empty weight 1,612 lb (731 kg) Maximum take-off/landing weight 2,750 lb (1,247 kg) Maximum baggage weight 200 lb (91 kg) Maximum useful load 1,148 lb (521 kg) Fuel and oil Fuel capacity 77 US gallons Usable fuel 72 US gallons Oil capacity 8 US quarts PA-28R Arrow III – Operations Manual 7 Performance VNE (never exceed speed) 183 KIAS VNO (max. cruising speed) 146 KIAS VA (manoeuvring speed) 118 KIAS (at 2,750 lb) 96 KIAS (at 1,865 lb) VFE (max. flap speeds) 103 KIAS VLE (max. gear extension speed) 129 KIAS VSO (stall speed) 55 KIAS (landing configuration) Service ceiling 15,000 ft Range (max. payload) 697 nautical miles Paint schemes The Arrow III is supplied in the following seven 8K resolution paint schemes: • D-ENOX (Germany) • G-CBPI (UK) • N38273 (USA) • PH-MJB (Netherlands) • SP-TUT (Poland) • ZK-EIF (New Zealand) • White (Default) PA-28R Arrow III – Operations Manual 8 INSTALLATION, UPDATES AND SUPPORT You can install this Arrow III software as often as you like on the same computer system: 1. Click on the ‘Account’ tab on the Just Flight website. 2. Log in to your account. 3. Select the ‘Your Orders’ button. 4. A list of your purchases will appear and you can then download the software you require. Windows users should ensure they have the 2010 Microsoft Visual C++ redistributable package installed. It is available to download from the Microsoft website. To install the aircraft into X-Plane 12: 1. Download the PA-28R Arrow III from your Just Flight account. 2. Unzip the downloaded .zip file. The resulting folder will be named ‘JF12_PA28_Arrow’. 3. Copy the ‘JF12_PA28_Arrow’ folder into your ‘X-Plane 12/Aircraft’ folder. Accessing the aircraft To access the aircraft in X-Plane 12: 1. From the main menu, click ‘New Flight’ or go to the Flight Configuration window. 2. Click on ‘PA28 Arrow For XP12’ in the aircraft selection screen. 3. Click ‘Customize’ and choose a livery from the drop-down menu in the top right. 4. Click ‘Start Flight’. Uninstalling To uninstall this software from your system: 1. Open your X-Plane 12 folder. 2. Open the ‘Aircraft’ folder. 3. Delete the ‘JF12_PA28_Arrow’ folder. Updates and Technical Support For technical support (in English) please visit the Support pages on the Just Flight website. As a Just Flight customer you can obtain free technical support for any Just Flight product. If an update becomes available for this aircraft, we will post details on the Support page and we will also send a notification email about the update to all buyers who are currently subscribed to our emails. PA-28R Arrow III – Operations Manual 9 Regular News To get all the latest news about Just Flight products, special offers and projects in development, subscribe to our regular emails. We can assure you that none of your details will ever be sold or passed on to any third party and you can, of course, unsubscribe from this service at any time. You can also keep up to date with Just Flight via Facebook and X (formerly Twitter). PA-28R Arrow III – Operations Manual 10 SYSTEMS GUIDE Airframe The PA-28R-201 Arrow III is a single-engine, all-metal aircraft with retractable landing gear. It has seating for up to four occupants, a 200-pound luggage compartment and a 200 HP engine. The basic airframe is constructed out of aluminium alloy. Aerobatics are prohibited in this aircraft since the structure is not designed for aerobatic loads. The fuselage is a semi-monocoque structure. There is a front door on the right side and a cargo door is installed aft of the rear seat. The wing is of conventional semi-tapered design and employs a laminar flow NACA 652-415 airfoil section. The main spar is located at approximately 40% of the chord aft of the leading edge. The rear spar, in addition to taking torque and drag loads, provides a mount for flaps and ailerons. The four-position wing flaps are mechanically controlled by a handle located between the front seats. When fully retracted, the right flap locks into place to provide a step for cabin entry. Each wing contains one fuel tank. A vertical stabiliser, an all-movable horizontal stabilator and a rudder make up the empennage. The stabilator incorporates an anti-servo tab which improves longitudinal stability and provides longitudinal trim. This tab moves in the same direction as the stabilator but with increased travel. Fuel system The fuel system was designed with simplicity in mind. Fuel is contained in two 38.5 US gallon tanks, one in each wing. Of the total 77-gallon capacity, only 72 gallons are usable. The tanks are attached to the leading edge of the wing with screws and are an integral part of the wing structure. A fuel tank selector allows the pilot to control the flow of fuel to the engine and is located on the left sidewall below the instrument panel. It has three positions: OFF, LEFT TANK and RIGHT TANK. The arrow on the handle of the selector points to the tank which is supplying fuel to the engine. Normally fuel is supplied to the engine through an engine-driven fuel pump. An electric fuel pump serves as a back-up feature. The electric fuel pump is controlled by a rocker switch on the switch panel above the engine control quadrant. The electric fuel pump should be ON when switching fuel tanks and during take-offs and landings. Fuel quantity and flow/pressure are indicated on gauges on the instrument panel. There is a separate fuel quantity gauge for each tank. Electrical system All switches are grouped in a switch panel above the throttle quadrant. The circuit breaker panel is located on the lower right side of the instrument panel. Each breaker is clearly marked to show which circuit it protects. The circuit breaker implementation in X-Plane is linked to X-Plane’s internal failure logic. This means that if you manually pull out a circuit breaker, the associated failure in the sim logic will be immediately triggered. Conversely, if you have set up X-Plane failures for random or pre-determined failure events, each of these failures will cause the corresponding circuit breaker to pop out. Standard electrical accessories include alternator, starter, electric fuel pump, stall warning horn, ammeter and annunciator panel. The annunciator panel includes alternator, low oil pressure and low vacuum indicator lights. The annunciator panel lights are provided only as a warning to the pilot that a system may not be operating properly and that they should check and monitor the applicable system gauge to determine when or if action is required. PA-28R Arrow III – Operations Manual 11 The primary electrical power source is a 14-volt, 60-amp alternator which is protected by an alternator control unit that incorporates a voltage regulator and an over-voltage relay. The alternator provides full electrical power output even at low engine RPM. This provides improved radio and electrical equipment operation and increases battery life by reducing battery load. Secondary power is provided by a 12-volt, 35-ampere-hour battery. The ammeter as installed does not show battery discharge; rather, it shows the electrical load placed on the system. With all the electrical equipment off, and the battery master (BATT MASTR) and alternator (ALT.R) switches on, the ammeter will indicate the charging rate of the battery. As each electrical unit is switched on, the ammeter will indicate the total ampere draw of all the units, including the battery. For example, the average continuous load for night flying with radios on is about 30 amperes. The 30-ampere value plus 2 amperes for charging the battery will then show on the ammeter, indicating the alternator is functioning properly. Vacuum system The vacuum system is designed to operate the air-driven gyro instruments. This includes the directional and attitude gyros when installed. The system consists of an engine vacuum pump, a vacuum regulator, a filter and the necessary plumbing. The vacuum gauge, mounted on the right instrument panel, provides valuable information to the pilot about the operation of the vacuum system. A decrease in pressure, or zero pressure, over an extended period may indicate a problem with the vacuum system. A vacuum regulator is provided in the system to protect the gyros. The valve is set so the normal vacuum reads 4.8-5.1 inches of mercury, a setting which provides sufficient vacuum to operate all the gyros at their rated RPM. Pitot-static system The system supplies both pitot and static pressure for the airspeed indicator, altimeter and vertical speed indicator. Pitot pressure is picked up by the pitot head on the bottom of the left wing. The switch for pitot heat is located on the switch panel. Static pressure is sensed by button-type vents on each side of the aft fuselage. Push- button-type pitot and static drains are located on the lower left sidewall of the cockpit. Lighting system Lights fitted to the aircraft include navigation, anti-collision, landing, instrument panel and cabin dome lights. The navigation lights are controlled by a rheostat switch on the main switch panel. This same rheostat switch controls the radio lights and landing gear indicator lights. When the switch is in the fully down position, the navigation lights are off and the radio and gear lights are on full brightness. As soon as the switch is rotated up past the click, the navigation lights turn on and the radio and gear lights are dimmed. The radio and gear indicator light brightness can be increased by moving the switch further upwards. Note that the gear lights are not visible in daylight when dimmed. Be sure to check the position of this switch if the landing gear lights don’t illuminate after gear extension. Radio, panel and switch lights are controlled by rheostat switches located below and to the right of the pilot’s yoke, adjacent to the engine instruments. A light mounted in the overhead panel provides instrument and cockpit lighting for night flying. The light is controlled by a rheostat switch adjacent to the light. PA-28R Arrow III – Operations Manual 12 The Arrow III’s main pop-up window (accessible via the Arrow tab on the left side of the X-Plane window) has a button that turns the overhead light on or off. This is to help you orient yourself in a dark cockpit at night. In that situation in real life you would most likely make use of tactile feedback and ambient light from the airport to find the light switch. If the plane’s batteries are off and the dome light is not available, the pop-up light button will actually turn on a hand-held flashlight which you can use to find your way around the dark panel until the battery switch is found and turned on. This is helpful for those ‘cold and dark’ starts at night. The anti-collision and landing lights are controlled by rocker switches on the main switch panel. Instrument markings Airspeed indicator markings MARKING KIAS VALUE OR RANGE SIGNIFICANCE White arc 55-103 Full flap operating range. Lower limit is maximum weight VSO in landing configuration. Upper limit is maximum speed permissible with flaps extended. Green arc 60-146 Normal operating range. Lower limit is maximum weight VS1 with flaps retracted. Upper limit is maximum structural cruising speed. Yellow arc 146-183 Operations must be conducted with caution and only in smooth air. Red line 183 Maximum speed for all operations. Engine indicator markings INSTRUMENT Red line or arc Minimum limit Yellow arc Caution range Green arc Normal operating Red line Maximum limit Tachometer ---------- ---------- 500-2,700 RPM 2,700 RPM Oil temperature ---------- ---------- 75-245°F (24-118°C) 245°F (118°C) Fuel pressure Fuel flow ---------- ---------- 0.05-12 PSI 2-21.4 gal/hr 12 PSI 21.4 gal/hr Oil pressure 25 PSI 25-60 PSI (idle) and 90-100 PSI (start/warm-up) 60-90 PSI 100 PSI Vacuum gauge ---------- ---------- 4.8-5.1 inHG 6.0 inHG PA-28R Arrow III – Operations Manual 13 Limits Weight limits Maximum weight: 2,750 lb (1,247 kg) Maximum weight in baggage compartment: 200 lb (91 kg) Centre of gravity limits Weight (lb) Forward limit Inches aft of datum Rearward limit Inches aft of datum 2,750 88.9 91.5 2,375 and below 82.0 91.5 The datum used is 78.4 inches ahead of the wing leading edge at the intersection of the straight and tapered section. Manoeuvre limits This aircraft is certificated in the normal category. The normal category is applicable to aircraft intended for non- aerobatic operations. These include any manoeuvres incidental to normal flying, stalls (except whip stalls), lazy eights, chandelles and steep turns in which the angle of bank is no more than 60° and pitch is no more than 30°. Aerobatic manoeuvres, including spins, are not approved. Flight load factor limits Positive load factor (maximum): + 3.8 G Negative load factor (maximum): No inverted manoeuvres approved Types of operation The aircraft is approved for the following operations: • Day VFR • Night VFR • Day IFR • Night IFR • Non-icing Fuel limitations Total capacity: 77 US gallons Unusable fuel: 5 US gallons (2.5 gallons per wing tank) Usable fuel: 72 US gallons (36 gallons per wing tank) PA-28R Arrow III – Operations Manual 14 Landing gear The Arrow is equipped with retractable tricycle landing gear which is hydraulically actuated by an electrically powered reversible pump. The pump is controlled by a selector switch on the instrument panel, to the left of the control quadrant. The landing gear is retracted or extended in about seven seconds. For emergency gear extension, the emergency gear lever, located between the front seats to the left of the flap handle, must be in the down position to manually release hydraulic pressure and permit the gear to freefall. The nose gear is spring-assisted. The aircraft is fitted with an automatic gear extension system. The system automatically extends the landing gear when engine power is reduced with the airspeed at or below approximately 87 KIAS. The system is triggered by differential air pressure sensed by a static source mast on the left side of the fuselage. The emergency gear lever can also be used to override the automatic gear extension system. The lever has three positions: • UP – automatic extension system overridden. Used for situations such as take-off, practising stalls and low speed handling, and for maximising glide ratio. The AUTO EXT OFF light flashes in conditions where the gear would normally automatically extend. • MID – automatic extension system enabled. Landing gear will automatically extend when power is reduced below 14 inches of manifold pressure and airspeed drops below 87 KIAS. • DOWN – push down for manual emergency gear extension when below 87 KIAS. Gear down and locked positions are indicated by three green lights located to the left of the selector. A red WARNING GEAR UNSAFE light, at the top of the panel, illuminates while the gear is in transit, or not in the fully up or locked down position. An all lights out condition indicates that the gear is up. The landing gear should not be retracted above a speed of 107 KIAS and should not be extended above a speed of 129 KIAS. A microswitch in the throttle quadrant activates a warning horn and red WARNING GEAR UNSAFE light under the following conditions: a. Gear up and power reduced below approximately 14 inches of manifold pressure, or automatic extension triggered and gear handle in UP position. b. Gear selector switch UP while on the ground and throttle in retarded position. c. Whenever the flaps are extended beyond the approach position (10°) and the landing gear is not down and locked. The gear warning horn emits a 90Hz beeping sound, in contrast to the stall warning horn which emits a continuous sound. The nose gear is steerable through a 30-degree arc each side of centre by use of the rudder pedals. As the nose wheel retracts, the steering linkage disengages to reduce rudder pedal loads in flight. The nose wheel is equipped with a hydraulic shimmy damper to reduce nose wheel shimmy. A bungee assembly is also included to reduce ground steering effort and to dampen shocks and bumps during taxiing. The standard brake system includes toe brakes on the left and right set of rudder pedals and a hand brake located below and near the centre of the instrument panel. The toe brakes and the hand brake have individual brake cylinders, but all cylinders use a common reservoir. The parking brake is incorporated in the lever brake and is operated by pulling back on the lever and depressing the knob attached to the top of the handle. To release the parking brake, pull back on the brake lever and then allow the handle to swing forward. Doors and exits The aircraft is fitted with a passenger door and a baggage door. The passenger door can be opened from within the virtual cockpit by clicking on the two door latches to rotate them to the OPEN position and then clicking and dragging on the door handle to push it open. It can be closed by pulling on the door handle to pull it closed and then clicking on the two door latches to rotate them to the LATCH position. PA-28R Arrow III – Operations Manual 15 The Arrow III’s passenger door is programmed in X-Plane to react to environmental forces such as oncoming air (when trying to open the window while flying) and G-forces (when yawing the plane on the ground or in flight). If it is not closed and latched properly, this can result in some interesting movement, as it would in real life. Flight controls Dual flight controls are provided as standard equipment. A cable system provides actuation of the control surfaces when the flight controls are moved. The horizontal surface (stabilator) features a trim tab/servo mounted on the trailing edge. This tab serves the dual function of providing trim control and pitch control forces. The trim function is controlled by a trim control wheel located on the control console between the two front seats. Rotating the wheel forward gives nose-down trim and rotation aft gives nose-up trim. The rudder is conventional in design and incorporates a rudder trim. The trim mechanism is a spring-loaded recentring device. The trim control is located on the right side of the pedestal below the throttle quadrant. Turning the trim control clockwise results in nose-right trim and anti-clockwise rotation results in nose-left trim. Manually controlled flaps are provided. They are extended by a control cable and are spring-loaded to the retracted (up) position. The control is located between the two front seats on the control console. To extend the flaps, pull the handle up to the desired flap setting of 10, 25 or 40 degrees. To retract, depress the button on the end of the handle and lower the control. The aircraft will experience a pitch change during flap extension or retraction. This pitch change can be corrected by either stabilator trim or increased control wheel force. When the flaps are in the retracted position the right flap, provided with an over-centre lock mechanism, acts as a step. Engine The Arrow is powered by a Lycoming I0-360 four-cylinder, direct drive, horizontally opposed fuel-injected engine, rated at 200 horsepower at 2,700 RPM. It is fitted with a starter, 60-ampere 14-volt alternator, ignition, vacuum pump drive, fuel pump, propeller governor and an induction air filter. The aircraft is equipped with a constant speed, controllable-pitch propeller. The propeller control is located on the throttle quadrant between the throttle and mixture controls. A mixture control lock is provided to prevent activation of the mixture control instead of the pitch control. Left-click on the lock to disengage or engage it. With the lock engaged, the mixture lever cannot be moved below approximately 40%. An oil cooler is located on the forward lower right side of the firewall, with the air inlet for the cooler located on the right side of the bottom cowling. Engine controls The engine controls consist of a throttle control, a propeller control and a mixture control lever. These controls are located on the control quadrant on the lower centre of the instrument panel, where they are accessible to both the pilot and the co-pilot. The throttle lever is used to adjust the manifold pressure. It incorporates a gear-up warning horn switch which is activated during the last portion of travel of the throttle lever to the low power position. If the landing gear is not locked down, the horn will sound until the gear is down and locked or until the power setting is increased. This is a safety feature to warn of an inadvertent gear-up landing. The propeller control lever is used to adjust the propeller speed from high RPM to low RPM. The mixture control lever is used to adjust the air-to-fuel ratio. The engine is shut down by placing the mixture control lever in the fully lean position. In addition, the mixture control has a lock to prevent activation of mixture control instead of pitch control. The alternate air control is located to the right of the control quadrant. When the alternate air lever is in the up (closed) position, the engine is operating on filtered air. When the lever is in the down (open) position, the engine is operating on unfiltered, heated air. PA-28R Arrow III – Operations Manual 16 Engine instruments Indicators enable the pilot to check oil pressure, oil temperature, tachometer, manifold pressure, fuel flow and EGT. The engine instruments are located on the mid and lower portions of the left panel and the lower portion of the right panel. Ignition and starter system Engine ignition is provided by a dual magneto on two spark plugs per cylinder. Ignition is controlled by a key- operated rotating selector on the lower left portion of the left panel. The selector operates clockwise, with right, left, left/right and start positions. Induction system The induction system incorporates a fuel injector. The injector is based on the principle of differential pressure, which balances air pressure against fuel pressure. The regulated fuel pressure established by the servo valve when applied across a fuel control makes the fuel flow proportional to air flow. The fuel flow portion of the manifold pressure/fuel flow gauge is connected to a flow divider and monitors fuel pressure. This instrument converts fuel pressure to an indication of fuel flow in gallons per hour and percentage of rated horsepower. The alternate air source of the induction system contains a door that functions automatically or manually. If the primary source is obstructed, the door will open automatically. It may be opened manually by moving the selector on the right side of the quadrant. The primary source should always be used for take-off. Stall warning system An approaching stall is indicated by a stall warning horn which is activated between 5-10 knots above stall speed. Mild airframe buffeting and gentle pitching may also precede the stall. Stall speeds are shown on graphs in the OPERATING DATA MANUAL included with this software. The stall warning horn emits a continuous sound, in contrast to the gear warning horn which emits a 90Hz beeping sound. The stall warning horn is activated by a lift detector installed on the leading edge of the left wing. The battery master (BATT MASTR) switch must be ON for the stall warning system to function. Propeller The aircraft is fitted with an all-metal, three-blade, constant-speed, governor-regulated propeller. The propeller control actuates on the governor. According to the control position, the governor determines propeller rotation speed and thus the engine speed to be maintained. The governor controls the flow of engine oil, boosted to high pressure by the governing pump, onto a piston located in the propeller hub. Oil pressure twists the blades toward high pitch (low RPM). When oil pressure to the piston is relieved, the blades twist to low pitch (high RPM). PA-28R Arrow III – Operations Manual 17 PANEL GUIDE The instrument panel is designed to accommodate the customary advanced flight instruments and the normally required power plant instruments. The altitude and directional gyros, located in the centre of the left-hand instrument panel, are vacuum-operated. The vacuum gauge is located on the right-hand instrument panel. The turn indicator on the left side is electrically operated. The radios are located in the centre section of the panel and the circuit breakers are in the lower right corner of the panel. An annunciator panel is mounted in the upper instrument panel to warn the pilot of a possible malfunction in the alternator, oil pressure or vacuum systems. Additional features include a pilot storm window and two sun visors. The cabin door is double-locked. To close the cabin door, hold the door closed with the armrest while moving the side door latch to the LATCHED position, then engage the top latch. Both latches must be secured before flight. A large baggage area, located behind the rear seats, is accessible either from the cabin or through a large outside baggage door on the right side of the aircraft. It is the pilot’s responsibility when baggage is loaded to be sure that the aircraft’s centre of gravity falls within the allowable CG range. EFB 2D pop-out The EFB 2D pop-out arrow appears in the top left corner of the screen every time you load the Arrow III: Left-click on this arrow to open the 2D EFB pop-out. This icon can easily be faded out and hidden completely by hovering your mouse over it and moving the scroll wheel. It will reappear for the next flight. Please see the separate EFB manual for further details of EFB operation. PA-28R Arrow III – Operations Manual 18 Left main panel 1. Vacuum gauge 2. Airspeed indicator (ASI) – a true airspeed indicator is incorporated into the airspeed indicator. The true airspeed indicator consists of a rotatable ring which is controlled using the knob located below the ASI. To set the indicator, rotate the ring until the pressure altitude is aligned with the outside air temperature (OAT). To obtain the pressure altitude, set the barometric scale of the altimeter to 29.92 inHG / 1013.2 hPa and then read the pressure altitude. With the ring set, the true airspeed can be read along the bottom scale. 3. Attitude indicator (AI) – a pitch reference knob allows for the pitch bars (aircraft symbol) position to be adjusted nose-up or nose-down. 4. Gear unsafe warning light – illuminates while the gear is in transit, or not in the fully up or locked down position. Refer to the Landing gear section of this manual for more information. 5. Starter engaged light 6. Altimeter – a barometric pressure scale is provided for hPa/mb 7. Annunciator press-to-test button – press to test annunciator lights 8. Annunciator lights 9. VOR 1 / ILS indicator – driven by the GNS 530 10. Low voltage warning light 11. ADF indicator – driven by KR 85 ADF system. HDG knob controls rotation of the compass card. 12. Turn and bank indicator 13. Direction indicator – caging knob (bottom left) controls rotation of the compass card. HDG knob (bottom right) controls the heading bug. 14. Vertical speed indicator (VSI) 15. VOR 2 indicator – driven by KX 175B PA-28R Arrow III – Operations Manual 19 Left mid panel 1. Oil pressure indicator 2. Oil temperature indicator 3. Ammeter 4. Yoke toggle click-spot (same location on right yoke) 5. Left fuel tank quantity indicator 6. Fuel pressure indicator 7. Right fuel tank quantity indicator Left lower panel 1. Autopilot controls – refer to the AUTOPILOT section for more information. 2. Electric pitch trim push-button – push in to enable the electric pitch trim (rocker switch located on yoke). 3. Magneto/start selector 4. Manifold pressure (inHG) and fuel flow (gallons per hour) 5. Tachometer (RPM) 6. Landing gear lever 7. Automatic gear extension warning light 8. Gear position lights PA-28R Arrow III – Operations Manual 20 Left sidewall 1. Fuel tank selector 2. Emergency locator transmitter switch – this is normally in the AUTO/ARM position. If the ELT is inadvertently activated you will hear the characteristic siren tone. It can be reset by moving the switch to OFF, then back to AUTO/ARM. 3. Storm window – click on the latch to open or close the window. Throttle quadrant 1. Throttle lever 2. Propeller control lever 3. Mixture lever – the mixture lever is fitted with a lock. Left-click on the lock to disengage or engage it. The lock must be disengaged before the lever can be moved below 40%. 4. Friction control PA-28R Arrow III – Operations Manual 21 Right panel 1. Intercom switch 2. DME selector switch – selects whether the GNS 530 or KX 175B is used as the input to the KN 62. 3. KX 175B – COM 2 / NAV 2 radio 4. KN 62A DME 5. KR 85 ADF 6. Standby altimeter – a barometric pressure scale is provided for hPa/mb. 7. DATCON hour meter 8. Heating control levers 9. Fan control switch 10. Circuit breaker panel PA-28R Arrow III – Operations Manual 22 Centre panel 1. KMA 20 audio selector 2. GNS 530 GPS 3. KT 76A transponder 4. Navigation and radio light switch 5. Battery master and alternator switches 6. Fuel pump switch 7. Landing light switch 8. Rotating beacon and anti-collision lights switches 9. Pitot heat switch 10. Panel lights switch 11. Alternate air control lever 12. Exhaust gas temperature (EGT) indicator – rotate screw to control the position of the red (maximum value) needle. PA-28R Arrow III – Operations Manual 23 Upper cockpit 1. Outside air temperature indicator 2. Sun visors 3. Whiskey compass Lower cockpit 1. Parking brake handle 2. Rudder trim knob and indicator – turning the trim control clockwise results in nose-right trim and anti- clockwise rotation results in nose-left trim. 3. Flap lever 4. Emergency gear lever – refer to the Landing gear section for more information. 5. Elevator trim wheel and indicator – rotating the wheel forward gives nose-down trim and rotation aft gives nose-up trim. PA-28R Arrow III – Operations Manual 24 Yoke timer 1. Timer display 2. Reset button 3. Mode button 4. Start/stop button The yoke is fitted with a digital chronometer. The mode button allows you to toggle between either clock mode or timer mode. With timer mode selected, the start/stop and reset buttons can be used to control the timer. Press the reset (RST) button so that the time reads zero and then press the start/stop (ST-SP) button to start and stop the timer. The timer will count in minutes and seconds until 59 minutes and 59 seconds, at which point the timer will change to count in hours and minutes. With clock mode selected, the current local time will be shown in hours and minutes. PA-28R Arrow III – Operations Manual 25 KMA 20 – audio selector 1. Microphone selector switch 2. AUTO switch 3. Receiver selector switches 4. Marker beacon sensitivity and lamp test switch 5. Marker beacon lights The KMA 20 is an audio control system which provides control over transceiver and receiver outputs through the use of selector switches. The simulator doesn’t allow for separate speaker and headphone outputs so both buttons perform the same function. The COM 1 and COM 2 switches are used to toggle the COM 1 and COM 2 transceiver audio, allowing you to select COM 1 and/or COM 2 as the audio sources to monitor. The NAV, DME, MKR and ADF switches are used to toggle the associated audio sources. When the AUTO switch is placed in either the SPEAKER or PHONE position, the unit will automatically match the corresponding receiver audio with the selected transmitter. For example, with COM 1 selected on the microphone selector knob, the COM 1 audio source will be automatically enabled. The microphone selector knob connects the microphone to the selected output. PA-28R Arrow III – Operations Manual 26 GNS 530 – COM 1 / NAV 1 GPS unit 1. Swap standby and active NAV 1 frequencies 2. ON/OFF key – controls power to the unit 3. Swap standby and active COM 1 frequencies 4. Range key – zooms the map view in and out 5. Direct-To key – selects a waypoint to proceed directly to 6. Menu key – brings up the context-sensitive menu 7. Clear key – clears the last data entry. Press and hold to return to the main navigation view. 8. ENT key – acknowledge or confirm a data entry 9. GPS knob – used for data entry and to move among pages and page groups 10. Procedures key – allows the selection of instrument arrival, departure, and approach procedures 11. VNAV key – this is an optional feature that is not implemented in this version of the GNS 530 12. Flight Plan key – brings up the Flight Plan page group 13. Message key – view the Messages page 14. OBS key – used to suspend and unsuspend automatic waypoint sequencing during an instrument approach 15. CDI key – toggle between NAV 1 and GPS as the active navigation source 16. Frequency knob – tunes the COM 1 or NAV 1 frequency. Press in to switch between COM 1 and NAV 1 Detailed instructions can be found in ‘X-Plane 12/Instructions/X-Plane G530 Manual.pdf’. PA-28R Arrow III – Operations Manual 27 KX 175B – COM 2 / NAV 2 radio 1. COM 2 frequency display 2. COM 2 power/test switch 3. COM 2 frequency selector knobs 4. COM 2 volume knob 5. NAV 2 frequency display 6. NAV 2 power/mode switch 7. NAV 2 frequency selector knobs 8. NAV 2 volume knob The KX 175B is a very simple COM/NAV radio and acts as COM 2 / NAV 2 in the Arrow. COM controls Turn up the volume with the volume knob and then rotate the concentric selector knobs to tune in a COM frequency. NAV controls Turn up the volume with the volume knob and then rotate the concentric selector knobs to tune in a NAV frequency. Activate the NAV 2 switch on the audio selector panel to hear the Morse identifier. PA-28R Arrow III – Operations Manual 28 KT 76A – transponder 1. Function selector knob 2. Reply light 3. Identification push-button 4. Code windows 5. Code knobs Operating the KT 76A The function selector knob should be in the OFF position before starting the aircraft’s engine. Select the required reply code by rotating the four code knobs (one per code digit). The code will be displayed in the four code windows. After starting the engine, turn the function selector to standby (SBY). Once airborne, turn the function selector to ON, enabling normal Mode A operation. Turn the function selector to the altitude (ALT) position for altitude reporting (Mode C) to ATC. Important codes 7700: Emergency 7600: Communications failure 7500: Hijacking 0000: Reserved for military aircraft Squawk ident When you are asked to ident by ATC, press and release the ident push-button. Your aircraft will be positively identified to the air traffic controller. Reply light During normal operation, the reply light will flash to indicate that the KT 76A is functioning properly and replying to interrogations from ground radar. Interrogations occur at 10-15 second intervals, corresponding to each radar sweep. PA-28R Arrow III – Operations Manual 29 KN 62A – DME 1. Three-position function switch – determines the information that is displayed and the channelling source. On the Frequency (FREQ) setting, the unit can be channelled internally. On the Groundspeed/Time-to-Station (GS/T) setting, the unit holds the internally selected frequency and also displays distance, groundspeed and time-to-station information. On the Remote (RMT) setting, the DME is channelled when you select your NAV frequency on the NAV 1 receiver (GNS 530) and displays distance, groundspeed and time-to-station. 2. ON/OFF switch – controls power to the unit. The KN 62A should be powered on only after engine start-up and should be turned off prior to engine shutdown. 3. Frequency selector knobs – used to alter the internally selected frequency. The inner knob adds 0.05 MHz to the frequency and tunes the frequency in 0.1 MHz steps (0.05, 0.15, 0.25 etc.). Turning the outer knob changes the larger digits (1 MHz, 10 MHz etc.). The KN 62A is a Distance Measuring Equipment (DME) system. It can be channelled remotely through the NAV 1 receiver (GNS 530) or the NAV 2 receiver (KX 175B), depending on the position of the DME selector switch, or tuned directly with its own frequency selection knobs. This dual channelling compatibility makes two DME frequencies available to you at all times, allowing for DME holds. Frequency mode In this mode the DME displays distance and the internally selected frequency. You can alter the frequency using the frequency knobs. PA-28R Arrow III – Operations Manual 30 Groundspeed/Time-to-Station mode In this position the DME holds the internally selected frequency while displaying distance, groundspeed and time- to-station. A ‘frequency hold’ feature prevents you from accidentally altering the frequency when it isn’t displayed. Remote mode With remote mode selected, the DME uses the frequency that is selected on the NAV 1 receiver (GNS 530) or the NAV 2 receiver (KX 175), depending on the position of the DME selector switch. Distance, groundspeed and time-to-station is shown. Dashes will be displayed when there is no valid signal. KR 85 – ADF 1. Power/mode selector knob – selects ADF, ANT or BFO mode 2. Volume knob 3. Frequency display 4. Frequency select knobs – tune the ADF frequency Frequency selection The ADF frequency is displayed on three counters. The frequency is selected using the frequency select knobs which are rotated either clockwise or anti-clockwise. The right inner knob tunes the 1s and the right outer knob tunes the 10s. Since X-Plane’s internal ADF logic doesn’t support frequencies in the 1000s, the left knob is a single knob that only controls 100s. PA-28R Arrow III – Operations Manual 31 Operating modes ANT mode provides improved audio reception from the station tuned and is usually used for identification. The bearing pointer on the ADF indicator will be deactivated and immediately turn to the 90° relative position and remain there during ANT reception. Due to limitations in the simulator, this mode does not provide the audio Morse identification. ADF mode activates the bearing pointer on the ADF indicator, causing it to point in the direction of the station relative to the aircraft heading. BFO mode permits the carrier wave and the associated Morse code identifier broadcast on the carrier wave to be heard, as long as the ADF switch on the KMA 20 audio selector panel has been turned on. ADF test Select ANT mode and confirm that the bearing pointer moves directly to the parked 90° position. Make sure that the unit is tuned to a usable frequency and then select ADF mode. Confirm that the needle moves to the station bearing. Reality XP GTN 750 If you have purchased Reality XP’s GTN 750 and have it installed in X-Plane 12, you can use the unit in the Arrow cockpit. Due to limited panel space in the aircraft, the GTN 750 replaces the GNS 530 and KMA 20 when enabled, seeing as those units serve a similar purpose (COM 1 / NAV 1 / GPS). The GTN 750 will automatically replace the GNS 530 and KMA 20 when enabled via the Reality XP menu bar entry. Note: The Reality XP GTN 750 is not included in this product. It is available as a separate purchase from the Reality XP website. PA-28R Arrow III – Operations Manual 32 AUTOPILOT 1. Autopilot engage switch 2. Roll command knob 3. Heading switch 4. Navigation/approach coupler knob – click on the PIPER logo to toggle the hidden altitude hold mode on and off. 5. Coupler radio selector switch – click on the switch to toggle the autopilot’s NAV source between NAV 1 and NAV 2. By modern standards the AutoControl III B is quite a primitive autopilot. It controls the roll axis of the aircraft but is not equipped to control the pitch axis. Controls The controls for the system consist of: • Console with engage and heading switches, and a roll command knob • Navigation/approach coupler knob • Coupler radio selector switch • Heading bug on the direction indicator gauge • A hidden toggle for the altitude hold mode, which is activated by clicking on the PIPER logo above the navigation/approach coupler knob. Navigation/approach coupler The coupler has five modes: • Heading (HDG) mode – the autopilot operates without coupling (refer to the Use of heading hold and preselect section). • OMNI mode – the coupler will automatically intercept, track and make crosswind corrections on any desired VOR radial the pilot selects. • Navigation (NAV) mode – the coupler will automatically intercept, capture, track and correct for crosswind on any desired VOR radial the pilot selects. It is recommended procedure to use only the OMNI mode for VOR approach work. PA-28R Arrow III – Operations Manual 33 • LOC NORM (localiser normal) – the coupler will automatically intercept, capture, track and correct for crosswind conditions during ILS approach work. This mode automatically adjusts for the increased sensitivity that accompanies the ILS system. • LOC REV (localiser reverse) – the coupler will automatically intercept, capture, track and correct for crosswind conditions during ILS approach work, when it is necessary to correct away from the course deviation indicator. This mode automatically adjusts for the increased sensitivity that accompanies the ILS system. Coupler radio selector switch This switch connects the coupler to either the NAV 1 or the NAV 2 radio. Heading bug When the autopilot is engaged, the heading bug becomes the primary control of the aircraft around the roll axis. When the heading of the aircraft matches the heading bug, the autopilot will maintain the heading. To turn to a new heading, rotate the heading bug to the desired heading and the aircraft will turn to the newly selected heading. Operation Pre-flight ground check To ground check the autopilot: 1. Move heading switch to OFF. 2. Centre roll command knob. 3. Engage ON/OFF switch. 4. Rotate the bank command knob right and left. 5. Return the bank command knob to the centre position. Preselect 1. Set the heading bug to align with the current heading. 2. Rotate the coupler knob to the heading (HDG) position. 3. Engage the heading switch. 4. Rotate the heading bug to the right. 5. Rotate the heading bug to the left. 6. Centre the heading bug. Coupler 1. Tune in an available VOR station on the NAV 1 radio. 2. Centre the VOR 1 CDI needle with a ‘TO’ flag using the OBS knob. 3. Set the heading bug to match the selected OBS value. 4. Place the coupler selector switch in the NAV 1 position. 5. Rotate the coupler knob to the OMNI position. PA-28R Arrow III – Operations Manual 34 6. Rotate the OBS knob to swing the CDI needle to full right deflection. 7. Rotate the OBS knob to swing the CDI needle to full left deflection. 8. Disengage the autopilot – this completes the ground check. Engaging in flight Before engaging the autopilot, make certain the aircraft is trimmed for hands-off level flight with the slip-ball centred. Use of heading hold and preselect 1. Rotate the coupler knob to the heading (HDG) position. 2. Set the heading bug to align with the current heading. 3. Engage the ON/OFF switch. 4. Centre the bank command knob. 5. Engage heading switch. Heading changes are now made by setting the heading bug to the desired heading. With the heading switch engaged, the roll command knob is inoperative. Use of roll command function To employ this function the heading switch must be OFF. Bank angles of approximately 30 degrees can be achieved with the roll command knob in the maximum left or right position. Clicking at the top of the switch will command the centred position. Override Applying a large control input will override the autopilot when engaged. The override should be checked prior to each flight: 1. Rotate the coupler knob to the heading (HDG) position. 2. While the heading bug is set for a left turn, apply a large right input to the yoke. 3. While the heading bug is set for a right turn, apply a large left input to the yoke. Operation of coupler Intercepting VOR radials 1. While flying with the autopilot engaged and operating in the heading (HDG) mode, tune in a VOR and set the OBS to the desired radial. 2. Rotate the heading bug to align with the selected OBS. 3. Rotate the coupler from heading (HDG) mode to either navigation (NAV) or OMNI mode. 4. The aircraft will turn to intercept the desired radial at an angle not exceeding 45°. 5. The coupler will roll the aircraft onto the selected radial and will establish a crosswind corrected heading. Note: When flying with a crosswind, the heading bug will not align with the course flown by the autopilot. The difference between the two is the wind correction (crab) angle. PA-28R Arrow III – Operations Manual 35 VOR navigation 1. The aircraft is inbound and coupled to the 045° radial to VOR ‘A’. 2. When flying over VOR ‘A’, the autopilot will bank the aircraft left and right to indicate passage over the station. At this point, select the desired outbound radial (140° in this example) using the OBS knob and align the heading bug to the same course. 3. The autopilot will bank the aircraft left to intercept the 140° radial of VOR ‘A’, compensating for any crosswind. 4. As the aircraft moves out of range of VOR ‘A’, tune VOR ‘B’ into the KX 175B (NAV 2) radio and rotate the OBS knob to select the desired inbound radial. 5. Move the coupler radio selector switch to the NAV 2 position. 6. The autopilot will continue to bank the aircraft to maintain the radial to VOR ‘B’. 7. This procedure is repeated, as described, from VOR to VOR as the aircraft progresses along its route. Note: If you wish to use the same VOR receiver for navigating to VOR ‘B’, the coupler should be placed in heading (HDG) mode while VOR ‘B’ is tuned in. VOR approach 1. The aircraft is inbound on the 032° radial with compass, direction indictor, heading bug and OBS reading 212°. The coupler is tracking the radial with navigation (NAV) mode selected. 2. When passing overhead the VOR, select the 140° radial in the OBS, set the heading bug to 140° and rotate the coupler mode selector to the OMNI position. 3. The coupler will automatically intercept the 140° radial outbound. 4. When reaching the time for the procedure turn, select the heading (HDG) mode on the coupler and rotate the heading bug to the left to agree with the published outbound heading of the procedure turn (095°). Note: You must compensate for winds while in HDG mode. 5. At the end of the first leg of the procedure turn, rotate the heading bug to the right to the reciprocal heading (275°). 6. It is recommended that the OBS be set to the inbound course (320°) while flying the outbound leg of the procedure turn. 7. With the aircraft turning right, set the heading bug further right to the inbound radial of 320° to match the OBS. Rotate the coupler mode selector to the OMNI position. 8. The coupler will now intercept the 140° radial inbound. ILS approach 1. When receiving vectors to the localiser, set the coupler to heading (HDG) mode and use the heading bug to maintain the provided headings. 2. When the aircraft is in a position for the localiser intercept, select the inbound heading of the localiser using the heading bug before rotating the coupler mode selector to the LOC NORM position. 3. The coupler will intercept the localiser and correct for crosswinds. 4. It is important to note that the coupler only controls the heading of the aircraft and cannot adjust the rate of descent for the glideslope. You must make pitch changes to maintain the glideslope. 5. When passing over the middle marker, disengage the autopilot and take over control of the aircraft. Select heading (HDG) mode on the coupler in case of a go-around. Note: The heading bug must be set to the inbound heading of the localiser. PA-28R Arrow III – Operations Manual 36 ILS back course approach 1. When receiving vectors to the back course of the localiser, set the coupler to heading (HDG) mode and use the heading bug to maintain the provided headings. 2. Set the inbound heading of the back course using the heading bug and switch to LOC REV mode on the coupler. 3. The coupler will intercept the back course and track inbound on the localiser, correcting for crosswinds. Checklist Engaging roll command All switches OFF Direction indicator and compass ALIGNED Coupler HDG Engage switch ON Roll command knob Rotate left/right for up to 30° bank Engaging heading preselect Heading bug Aligned with current heading Heading switch ENGAGED Heading bug Rotate to select heading Engaging radio coupling NAV 1 / NAV 2 Valid VOR tuned in Coupler radio selector switch NAV 1 or NAV 2 Roll command knob CENTRED Heading switch DISENGAGED OBS Centre CDI needle Heading bug Rotate to selected OBS Coupler NAV Heading switch ENGAGED PA-28R Arrow III – Operations Manual 37 GROUND EQUIPMENT The aircraft can be fitted with chocks and tie-downs whilst on the ground. The chocks and tie-downs can be fitted to the aircraft by toggling the ground equipment sliders in the AIRCRAFT OPTIONS app of the tablet EFB. The aircraft’s pilot, co-pilot and baggage doors can also be opened by enabling the relevant options. PA-28R Arrow III – Operations Manual 38 FLYING THE ARROW In this tutorial flight we will be departing from Compton-Abbas airfield, 85 nautical miles south-west of London and 35 nautical miles south-east of Bristol. We will be heading east, passing north of Bournemouth Airport and over the top of Southampton Airport before approaching Shoreham Airport from the west. Covering a distance of approximately 72 nautical miles, this short flight is the ideal length for learning about the essential systems on board the PA-28R Arrow III. Here are the details for today’s flight: EGHA – SAM (113.35) – GWC (114.75) – SHM (332.0) – EGKA Estimated time en route: 40 minutes Route distance: 72 nautical miles Departure time: 1200 (local time) Weather: Clear Now that we are prepared for the flight we can proceed to the cockpit to begin our pre-flight checks. To load up the PA-28R Arrow III tutorial flight, follow these steps: 1. Start X-Plane 12. 2. From the Main Menu, click New Flight or go to the Flight Configuration window. 3. Click on PA28 Arrow in the Aircraft Selection screen. 4. Click Customize, choose a livery from the drop-down menu in the top right and untick the box labelled ‘Start with engines running’. 5. Under the Location box, type EGHA and select Compton Abbas. Click the Customize button. 6. Under ‘Starts’, select Ramp and choose a ramp start location. Press Confirm when done. 7. Click Start Flight. PA-28R Arrow III – Operations Manual 39 This tutorial will cover the necessary steps for you to get from point A to point B, but it will not explore each system in depth. Please refer to the rest of this manual for details of each system. Getting started The first step is to open the door to allow entry into the cockpit. In the virtual cockpit, click on the upper and lower door latches to rotate them to the OPEN position and then click and drag on the door handle to push it open. PA-28R Arrow III – Operations Manual 40 Switch to the exterior (chase) view and use the on-screen menu to open the baggage door. Confirm that the baggage door has opened and then return to the cockpit. We can now start working through the pre-flight inspections. To enable easier access to the controls, you may want to hide the yoke using the clickspot at the base of the yoke, where it is mounted to the panel. Check that the magneto selector is set to OFF (rotated fully anti-clockwise). PA-28R Arrow III – Operations Manual 41 Confirm that the landing gear lever is in the DOWN position and that the parking brake handle is set ON. Check that all avionics are OFF and the mixture lever is set to IDLE CUT-OFF and then switch ON the battery master. Check the left and right fuel quantity gauges to confirm that we have full tanks (36 gallons per tank). PA-28R Arrow III – Operations Manual 42 Confirm that the three green landing gear lights are illuminated. Switch ON the navigation, rotating beacon, anti-collision and landing lights. Switch to the exterior (chase) view and confirm that all the lights are illuminated before returning to the cockpit and switching them all OFF. PA-28R Arrow III – Operations Manual 43 Confirm that all annunciator lights and the low voltage light are illuminated. Check that you have full and free movement of the flying controls and that the flaps extend and retract fully, then switch OFF the BATT MASTR. Move the elevator and rudder trims to the centre/neutral position. PA-28R Arrow III – Operations Manual 44 Switch to the external (chase) view and carry out a visual inspection of the aircraft. The wheel chocks and tie- downs should be visible. Open the Refill menu on the EFB. This menu allows you to refill the fuel, recharge the aircraft battery and check the engine stats. Use the menu to recharge the battery in case it has discharged while you’ve been finding your way around the cockpit. PA-28R Arrow III – Operations Manual 45 Starting the engine To avoid draining the battery we will start the engine before configuring the avionics for our departure. Close the baggage door via the on-screen pop-up and then close the passenger door by first clicking on the door to pull it shut and then clicking on the door latches to rotate them to the LATCH position. Check that the parking brake is set and that all circuit breakers are pushed in. PA-28R Arrow III – Operations Manual 46 On the left sidewall, right-click on the fuel selector to rotate it to the LEFT position. On the throttle quadrant, move the propellor lever to the FULL FORWARD position and advance the throttle lever to approximately 1/4 open. Confirm that the alternate air is set to CLOSE and that all avionics are still OFF. PA-28R Arrow III – Operations Manual 47 Switch ON the battery master to provide electrical power to the aircraft. Turn ON the navigation and rotating beacon lights, warning anyone in the area that we are about to start the engine. Switch ON the fuel pump and then move the mixture lever to the FULL RICH (forward) position until fuel flow is displayed. PA-28R Arrow III – Operations Manual 48 Check that the area surrounding the aircraft is clear of obstructions and then rotate the magneto/start selector to the START (fully clockwise) position. When the engine starts, release the magneto/start selector and it will return to the BOTH position. Check that the oil pressure and temperature are rising. Switch ON the ALT (alternator) switch breaker and confirm that the associated warning light on the annunciator panel extinguishes. Adjust the throttle to maintain 1,400-1,500 RPM and check that the vacuum gauge shows suction within the given limits. Lean the mixture to avoid fouling the spark plugs. PA-28R Arrow III – Operations Manual 49 With the engine running and the alternator charging the battery, we can now switch on the avionics. Starting at the top of the centre panel and working down, switch on the GNS 530, KT 76A, KX 175B, KN 62A, and KR 85 units. We will leave the autopilot unit switched off for now. Finally, rotate the fuel selector switch to the RIGHT and then the LEFT position, checking that the engine operates correctly on both tanks before selecting the fullest tank. Configuring the avionics We now need to configure the avionics for our departure. For the initial climb we are going to maintain the runway heading, so rotate the heading bug on the direction indicator to 080 degrees. PA-28R Arrow III – Operations Manual 50 Once we are settled into our climb to the east, we will make a turn to fly towards the first waypoint on the route, Southampton (SAM) VOR. In preparation, tune the VOR frequency (113.35) into the GNS 530 (NAV 1) unit. Tune the second waypoint on our route, Goodwood VOR (114.75), into the KX 175B (NAV 2) unit. Check that the function switch on the KN 62A is set to the RMT (remote) position and that the DME selector switch, located above the KX 175B unit, is set to NAV 1. Selecting the remote function allows the KN 62A to display DME information from either NAV 1 (the GNS 530) or NAV 2 (the KX 175B), rather than its own internal NAV receiver. The DME selector switch controls which of the two radio units the KN 62A receives its DME information from – in this case the GNS 530, which we have just tuned to the Southampton VOR. PA-28R Arrow III – Operations Manual 51 Taxi We can now taxi to the runway. Check that the area around the aircraft is clear of obstacles and then release the parking brake. Apply power slowly to get the aircraft rolling and then start your taxi to the threshold of runway 08. Steering the aircraft with the rudder pedals only is generally sufficient. The combined use of the rudder pedals and the brakes permits, if necessary, tight turns. Check the operation of gyroscopic instruments (horizontal attitude, heading and turn and bank indicators) by means of alternate turns. Stop at the holding point just short of runway 08. We can carry out the power (ground) check here. Set the parking brake and confirm that the propeller lever is in the FULL FORWARD position. To carry out a magneto check, enrichen the mixture, advance the throttle lever to obtain 2,000 RPM and then rotate the magneto selector to the LEFT position, note the RPM drop and then rotate it back to the BOTH position. Repeat the process for the right magneto. Check that the vacuum, oil temperature, oil pressure and ammeter readings are within limits. Use the PRESS-TO-TEST button to confirm that all the annunciator lights illuminate. Make sure that the mixture lever is set to FULL RICH (fully forward) and the fuel selector is set to the fullest tank. PA-28R Arrow III – Operations Manual 52 To carry out a propeller check, advance the throttle lever to obtain 2,000 RPM and then cycle the propeller lever twice, moving it aft towards the high pitch/low RPM position and then forwards towards the low pitch/high RPM position. Note the RPM drop on the tachometer. Reset the lever to the FULL FORWARD position. To carry out an alternate air check, pull the alternate air knob and check that the manifold pressure doesn’t drop, then push the alternate air knob in again. Check the operation of the fuel system by switching the fuel pump OFF and confirming that the fuel pressure is still within the green sector. Finally, reduce the throttle to idle and check for rough running. We can now run through the before take-off checks. Confirm that the battery master and alternator switches are both set to ON. Rotate the fuel selector to the fullest tank and switch ON the fuel pump. Check that the alternate air lever is set to CLOSE, and that the mixture and propeller levers are in the FULL FORWARD position. Lower the flaps to the 10° (first stage) position. PA-28R Arrow III – Operations Manual 53 Confirm the magneto selector is in the BOTH position and switch ON the landing and anti-collision lights. Rotate the pitch trim wheel until the indicator sits in the neutral/centre position. Confirm that both doors are LOCKED and that you have full and free movement of the flying controls. Finally, switch ON the PITOT HEAT switch. With the before take-off checks complete, have a look left and right, verify that nothing is on approach and that the runway is clear, and then taxi onto the runway. Take-off Line up with the runway centre line and then come to a stop. Smoothly apply full power, and as the aircraft starts to gather speed, keep it running down the centre line with rudder inputs. As you approach 65 knots start to raise the nose of the aircraft. The aircraft will begin to climb away from the runway. Once you are safely airborne, tap the brakes and then raise the landing gear using the [G] key. Make elevator inputs as required to maintain a climb speed of approximately 90 knots, holding the runway heading (080 degrees) and retracting the flaps as you pass through 300ft AGL. PA-28R Arrow III – Operations Manual 54 Climb Once stable in the climb, adjust your pitch to maintain the 90 knots climb speed and maintain your heading. Switch OFF the fuel pump and landing light on reaching 1,000 feet. As you climb through 2,000 feet, the Southampton VOR should be within range of the aircraft. The NAV flag on the VOR 1 indicator will disappear to indicate that a valid signal is being received and the KN 62A will display the DME distance (nautical miles), groundspeed (knots) and time-to-station (minutes). Rotate the OBS knob on the VOR 1 indicator until the CDI needle centres with a TO flag visible – approximately 095 degrees. Bank the aircraft to the right to bring it onto the OBS course, so that you are tracking inbound to the VOR. To reduce your workload we will now engage the autopilot and command it to maintain the course to the VOR. Move the autopilot engage switch to the A/P ON position to engage the autopilot, and move the heading switch to the HDG ON position to enable the autopilot to take control of the aircraft’s heading. Check that the coupler radio selector switch is set to NAV 1. This switch connects the coupler to either the NAV 1 or the NAV 2 radio and, as we’ve tuned the Southampton VOR into the NAV radio, we need to couple the autopilot to that same radio. PA-28R Arrow III – Operations Manual 55 Finally, make sure that the navigation/approach coupler knob is set to NAV. This selects navigation hold mode. The autopilot will now control the heading and maintain our course to the VOR. Note that the autopilot is not controlling the aircraft’s pitch, so continue to adjust your pitch to maintain the climb. Cruise As you approach 4,000ft, place your mouse cursor over the PIPER logo above the navigation/approach coupler knob and press the left button on your mouse. This toggles altitude hold mode. The autopilot will capture and hold the current altitude (rounded to the nearest hundred feet). The real-life Piper AutoControl IIIB doesn’t feature altitude hold mode but it has been included for convenience. As the aircraft levels out and begins to accelerate, reduce the throttle to obtain 23 inHG on the manifold pressure gauge and then reduce the propeller lever to obtain 2,200 RPM on the tachometer. This is a typical cruise power setting. It is important to remember that the engine is only being fed with fuel from a single tank at any given time, and therefore the quantity of each tank should be carefully monitored. It is recommended that you change fuel tanks every half hour and do not exceed a fuel imbalance of 10 US gallons. If you want to avoid worrying about switching fuel tanks, enable the automatic fuel selector from the Panel Selector menu. You can now relax for a while as the autopilot takes care of controlling the aircraft. The leg to the Southampton VOR should take approximately 10 minutes, as displayed on the KN 62A. This is the ideal opportunity to take a closer look at some of the features of the aircraft. The Arrow III has a very capable IFR-capable avionics fit. We’ll take a quick look at some of the features of those avionics. Make sure you keep an eye on the distance remaining to the Southampton VOR, as we’ll need to return to navigating the aircraft once we are five miles from the VOR. PA-28R Arrow III – Operations Manual 56 Sliding over to the KN 62A unit, move the function switch to the FREQ (frequency) position. With this function selected we can tune the KN 62A’s internal receiver (NAV 3). Rotate the frequency selector knobs to tune in 114.35, the frequency for the Compton VOR/DME which is commonly used by airliners transiting the London airspace. The DME distance (nautical miles) to the VOR will be shown on the left of the display. Move the function switch to the GS/T (groundspeed/time) position to show the DME distance (nautical miles), groundspeed (knots) and time-to-station (minutes) to the London VOR. Note that the display is identical to that shown with RMT (remote) selected, but this display shows the information for the internally tuned frequency rather than the remote frequency (NAV 1 – GNS 530 or NAV 2 – KX 175). Return the function switch to the RMT (remote) position so we can continue to monitor the distance to the next waypoint. Another useful feature for navigation is the Flight Computer which can be found on the EFB and shows a variety of real-time information related to everything from speed to fuel burn/flow and range/endurance. Take the opportunity to explore the cockpit using the PANEL GUIDE for reference. PA-28R Arrow III – Operations Manual 57 With five miles to run to the Southampton VOR, rotate the OBS knob on the VOR 2 indicator until the CDI needle centres with a TO flag visible – approximately 105 degrees – and then move the autopilot coupler radio selector switch to NAV 2. The autopilot will now bank the aircraft to maintain the selected course to the VOR tuned into the KX 175 (NAV 2) – Goodwood VOR. Set the DME selector switch to NAV 2 so that we can monitor the distance to the Goodwood VOR on the KN 62. We can now tune in the Shoreham (SHM) NDB, which is situated on the airfield. Using the selector knobs on the KR 85, tune in 0332 (332 kHz) and make sure that the mode knob is set to ADF. The needle on the ADF indicator will point towards the Shoreham NDB when it comes within range (approximately 10 miles out from the Goodwood VOR), which should be ahead of the aircraft and on a similar heading to the VOR which is located close by. PA-28R Arrow III – Operations Manual 58 When the KN 62 shows that we are three miles from the Goodwood VOR, rotate the heading bug on the direction indicator to match up with your current heading and then rotate the navigation/approach coupler knob to the HDG position. The autopilot will now maintain our current heading. Now use the heading bug to track towards the NDB, using the ADF indicator to estimate what heading is required for a direct routing to the NDB. Descent We need to begin our descent when we are approximately seven miles past the Goodwood VOR. The distance from the VOR is still available on the KN 62 although we are now using the ADF indicator for navigation. Move the propeller lever forward to the fully forward (high RPM) position and then reduce the throttle to obtain 15 inHG on the manifold pressure gauge. The airspeed will start to decrease. PA-28R Arrow III – Operations Manual 59 Once the airspeed has reduced to 110 knots, start the descent by disengaging altitude hold mode and then pitching down to obtain a -500ft/min descent rate. As the aircraft stabilises in its descent, adjust the throttle to maintain 110 knots. Approach and landing As Shoreham Airport comes into view, position the aircraft to join the base leg for runway 02, using the heading bug to turn the aircraft right, towards the coastline. Continue to follow the coastline east towards the airport. As you approach 1,000ft, reduce your vertical speed to enter level flight and increase the throttle as the aircraft levels out to maintain your airspeed. Disengage the autopilot by moving the heading switch to HDG OFF and the engage switch to A/P OFF. PA-28R Arrow III – Operations Manual 60 Switch ON the landing light and fuel pump. Confirm that the propeller and mixture levers are fully forward and that the fuel selector is set to the fullest tank. Once established on the base leg for runway 02, reduce your airspeed to 100 knots and extend the flaps to the 10° position. With the airfield in the 10 o’clock position, extend the landing gear and confirm that you see three greens. PA-28R Arrow III – Operations Manual 61 Reduce your airspeed further to 85 knots and extend the flaps to the 25° position. Begin a descending turn to position yourself on final for runway 02. Once established on final, extend the flaps to the 40° (fully down) position. Reduce power to begin slowing to a touchdown speed of approximately 75 knots. As the aircraft arrives over the runway, start to bring the aircraft into a flare, gently raising the nose just above the horizon. Reduce the throttles to idle and the aircraft should touch down smoothly. PA-28R Arrow III – Operations Manual 62 Apply gentle braking and once the aircraft has slowed to a fast walking pace, turn right off the runway. When you are safely off the runway, raise the flaps and switch OFF the landing and anti-collision lights. You can also switch OFF the fuel pump and pitot heat. Shutdown Begin your taxi to the nearest available parking spot. Once you have come to a stop at your chosen parking spot, engage the parking brake and switch OFF the avionics. Bring the throttle lever back to IDLE and then bring the mixture lever back to IDLE CUT-OFF to shut down the engine (remember to disengage the mixture lock!). Once the engine comes to a stop, rotate the magneto selector to the OFF position. Switch OFF the navigation and rotating beacon lights, and then switch OFF the alternator and battery to disconnect the electrical power. Rotate the fuel selector to the FUEL OFF position and and open the passenger and baggage doors. Congratulations – you have completed the Arrow III tutorial flight! PA-28R Arrow III – Operations Manual 63 NORMAL PROCEDURES Airspeed (IAS) for safe operations Best rate of climb (gear up, flaps up) 90 KIAS Best rate of climb (gear down, flaps up) 78 KIAS Best angle of climb (gear up, flaps up) 78 KIAS Best angle of climb (gear down, flaps up) 72 KIAS Operating speed in turbulent air 118 KIAS Maximum flap speed 103 KIAS Final approach speed (flaps 40) 75 KIAS Maximum demonstrated crosswind 17 KIAS Pre-flight Cockpit Landing gear lever DOWN Parking brake SET Avionics OFF Mixture IDLE CUT-OFF Magneto switch OFF BATT MASTR switch ON Fuel gauges CHECK QUANTITY Annunciator panel CHECK BATT MASTR switch OFF Primary flight controls CHECK OPERATION Flaps CHECK OPERATION Trim NEUTRAL Baggage door CLOSED Left/right wing Flap and aileron CHECK Wing tip and lights UNDAMAGED Tie-down REMOVED Fuel tank CHECK LEVEL PA-28R Arrow III – Operations Manual 64 Nose section Chocks REMOVED Towbar REMOVED (NOSE GEAR) Engine inspection door CLOSED Oil CHECK LEVEL Propeller GOOD CONDITION Air inlets CLEAR Landing light CHECK Tail section Fin CHECK CONDITION Rudder CHECK CONTROLS Stabilator and trim tab CHECK CONTROLS Tail cone CHECK CONDITION Before starting engine Brakes SET Circuit breakers IN Alternate air OFF Propeller FULL FORWARD Avionics OFF Fuel selector DESIRED TANK Engine starting Caution: If a positive oil pressure is not indicated within 30 seconds after an engine start, stop the engine and determine the trouble. In cold weather it will take a few seconds longer to get a positive oil pressure indication. Cold engine Throttle ½ INCH OPEN ALTR switch ON BATT MASTR switch ON Fuel pump ON Mixture RICH then IDLE CUT-OFF Propeller CLEAR Starter ENGAGE Mixture FULL RICH PA-28R Arrow III – Operations Manual 65 When the engine starts: Magneto selector BOTH Throttle ADJUST Oil pressure CHECK Throttle 1,400-1,500 RPM Hot engine Throttle ½ INCH OPEN ALTR switch ON BATT MASTR switch ON Fuel pump ON Mixture IDLE CUT-OFF Propeller CLEAR Starter ENGAGE Mixture ADVANCE When the engine starts: Magneto selector BOTH Throttle ADJUST Oil pressure CHECK Throttle 1,400-1,500 RPM Taxiing Taxi area CLEAR Parking brake RELEASE Throttle APPLY SLOWLY Brakes CHECK Steering CHECK Steering the aircraft with the rudder pedals only is generally sufficient. The combined use of the rudder pedals and the brakes permits, if necessary, tight turns. Check the operation of gyroscopic instruments (horizontal attitude, heading and turn and bank indicators) by means of alternate turns. Ground check Parking brake SET Propeller FULL FORWARD Throttle 2,000 RPM Magnetos CHECK (max. drop 175 RPM) Vacuum 4.8-5.1 inHG Oil temperature CHECK Oil pressure CHECK PA-28R Arrow III – Operations Manual 66 Ammeter CHECK Annunciator panel PRESS-TO-TEST Propeller EXERCISE then FULL FORWARD Alternate air CHECK Fuel pump OFF Fuel pressure CHECK Throttle RETARD Before take-off BATT MASTR switch ON ALTR switch ON Flight instruments CHECK Fuel selector AS REQUIRED Fuel pump ON Engine checks CHECK Alternate air CLOSED Mixture SET Propeller SET Flaps SET Trim SET Controls FREE Doors LATCHED Take-off Lined up on runway CHECK COMPASS Normal technique Flaps SET Trim SET Accelerate to 65-75 KIAS. Yoke Back pressure to rotate smoothly to climb attitude Short field/obstacle clearance technique Flaps 25° (second notch) Accelerate to 50-60 KIAS depending on aircraft weight. Yoke Back pressure to rotate smoothly to climb attitude After clearing the ground, accelerate to 55-65 KIAS depending on aircraft weight. Gear UP PA-28R Arrow III – Operations Manual 67 Accelerate to best gear-up angle-of-climb speed 78 KIAS, slowly retract the flaps and climb past the obstacle. Accelerate to best gear-up rate-of-climb speed 90 KIAS. Climb Best rate (2,750 lb, gear up, flaps up) 90 KIAS Best rate (2,750 lb, gear down, flaps up) 78 KIAS Best angle (2,750 lb, gear up, flaps up) 78 KIAS Best angle (2,750 lb, gear down, flaps up) 72 KIAS En route 104 KIAS Fuel pump OFF Cruise Refer to the OPERATING DATA MANUAL for cruise power settings. The normal maximum cruising power is 75% of the rated horsepower of the engine. Use of the mixture control in cruising flight reduces fuel consumption significantly, especially at higher altitudes. The mixture should be leaned during cruising operation when 75% power or less is being used. If any doubt exists as to the amount of power being used, the mixture should be in the full RICH position for all operations. The pilot should monitor weather conditions while flying and should be alert to conditions which might lead to icing. If induction system icing is expected, place the alternate air control in the ON position. To keep the aircraft in the best lateral trim during cruise flight, fuel should be used alternately from each tank at 15-minute intervals. Always remember that the electric fuel pump should be turned ON before switching tanks and should be left on for a short period thereafter. Descent Set the required power for descent. Apply engine power every 1,500ft to prevent excess engine cooling and spark plug fouling. Avoid prolonged descents with a manifold pressure lower than 14 inHG. Approach and landing Fuel selector FULLEST TANK Fuel pump ON Mixture SET Propeller FULL FORWARD Gear DOWN (129 KIAS max.) Flaps SET (103 KIAS max.) Trim to 75 KIAS. PA-28R Arrow III – Operations Manual 68 Shutdown Flaps RETRACT Fuel pump OFF Avionics OFF Electrical switches OFF Propeller FULL FORWARD Throttle CLOSED Mixture IDLE CUT-OFF Magnetos OFF ALTR switch OFF BATT MASTR switch OFF Stalls The stall characteristics of the Arrow are conventional. An approaching stall is indicated by a stall warning horn which is activated between 5-10 knots above stall speed. Mild airframe buffeting and gentle pitching may also precede the stall. The gross weight stalling speed of the Arrow with power off and full flaps is 55 KIAS. With the flaps up, this speed is increased by 5 knots. Loss of altitude during stalls can be as great as 400 feet, depending on configuration and power. Note: The stall warning system is inoperative with the battery master switch OFF. PA-28R Arrow III – Operations Manual 69 EMERGENCY PROCEDURES Airspeed (IAS) for safe operations Stall speed (2,750 lb, gear up, flaps 0) 60 KIAS Stall speed (2,750 lb, gear down, flaps 40) 55 KIAS Manoeuvring speed (2,750 lb) 118 KIAS Manoeuvring speed (1,865 lb) 96 KIAS Never exceed speed 183 KIAS Power off glide speed (2,750 lb, gear up, flaps 0) 79 KIAS Engine failures Engine fire during start Starter CRANK ENGINE Mixture IDLE CUT-OFF Throttle OPEN Fuel pump OFF Fuel selector OFF Engine failure during take-off If sufficient runway remains for a normal landing, leave gear down and land straight ahead. If area ahead is rough or if it is necessary to clear obstructions: Landing gear lever UP If sufficient attitude has been gained to attempt a restart: Fuel selector SET TO FULLEST TANK Fuel pump CHECK ON Mixture CHECK RICH Alternate air OPEN If power is not regained, proceed with power off landing. PA-28R Arrow III – Operations Manual 70 Engine failure in flight If at low altitude: Airspeed 79 KIAS minimum Prepare for power off landing. If altitude permits: Fuel selector SWITCH TO FULLEST TANK Fuel pump ON Mixture RICH Alternate air OPEN Engine gauges Check for indication of cause If no fuel flow/pressure is indicated, check tank selector position to be sure it is on a tank containing fuel. When power is restored: Alternate air CLOSE Fuel pump OFF If power is not restored, prepare for power off landing. Trim for 79 KIAS. Power off landing Trim for 79 KIAS. Locate suitable field and establish spiral pattern 1,000ft above field at downwind position for normal landing approach. When field can be easily reached, slow to 72 KIAS for shortest landing. Gear down emergency landing Touchdowns should normally be made at the lowest possible airspeed with full flaps. When committed to landing: Landing gear lever AS REQUIRED Flaps AS DESIRED Throttle CLOSE Mixture IDLE CUT-OFF Ignition OFF BATT MASTR switch OFF ALTR switch OFF Fuel selector OFF Note: If battery master switch is OFF, the landing gear cannot be retracted. PA-28R Arrow III – Operations Manual 71 Gear up emergency landing If a gear up landing is required, proceed as follows: Flaps AS DESIRED Throttle CLOSE Mixture IDLE CUT-OFF Ignition OFF BATT MASTR switch OFF ALTR switch OFF Fuel selector OFF Contact surface at minimum possible airspeed. Fires Engine fire in flight Fuel selector OFF Throttle CLOSED Mixture IDLE CUT-OFF Fuel pump OFF Cabin heat OFF Proceed with power off landing procedure. Electrical fire BATT MASTR switch OFF ALTR switch OFF Cabin heat OFF Land as soon as possible. Low oil pressure Oil annunciator light ON Pressure indicator IN LOW SECTOR Throttle REDUCE AS FAR AS POSSIBLE Oil temperature CHECKED If oil temperature in red sector REDUCE THROTTLE Prepare for a forced landing and land as soon as possible. PA-28R Arrow III – Operations Manual 72 Low fuel flow/pressure Fuel pump ON Fuel quantity CHECKED Fuel selector SWITCH TANKS Propeller governor failure In case of oil pressure drop in the governor system or pitch control failure, the propeller moves to low pitch. Oil pressure CHECKED Oil temperature CHECKED Throttle AS REQUIRED Airspeed REDUCED Avoid rapid application of power – maximum RPM is 2,700. Electrical failures Check the circuit breakers panel. If the circuit breaker is open, close it only once. If it opens again do not try to close the circuit breaker as the equipment has failed. ALT annunciator light illuminated: Ammeter Check to verify inoperative alternator If ammeter shows zero: ALTR switch OFF Reduce electrical loads to minimum: ALNTR. FIELD circuit breaker Check and reset as required ALTR switch ON If power is not restored: ALTR switch OFF If alternator output cannot be restored, reduce electrical loads and land as soon as practical. The battery is the only remaining source of electrical power. Icing IMPORTANT! Flight into known icing conditions is prohibited. Alternate air OPEN Cabin heat FULL HOT Pitot heat ON Engine MAX. POWER/RPM Adjust course and/or altitude to obtain best outside air conditions. Divert to nearest airport. PA-28R Arrow III – Operations Manual 73 Emergency landing gear extension Prior to emergency extension: BATT MASTR switch ON ALTR switch ON Circuit breakers Check NAV LIGHT switch OFF If landing gear fails to extend: Airspeed Reduce below 87 KIAS Landing gear lever DOWN If gear has still failed to lock down, move and hold the emergency lever down to the Emergency Down position. If gear has still failed to lock down, yaw the aircraft abruptly from side to side with the rudder. Spin recovery Intentional spins are prohibited, but if an inadvertent spin does occur, the following recovery procedure is recommended: Rudder HOLD OPPOSITE DIRECTION OF ROTATION Yoke FULL FORWARD, AILERONS NEUTRAL Throttle IDLE When spinning stops, centralise rudder, level the wings and ease out of the dive. Airspeed indicating system failure In case of erroneous indications in flight: Pitot heat ON If erroneous indications persist, carry out a precautionary approach, maintaining an adequate airspeed margin above stall warning activation speed. PA-28R Arrow III – Operations Manual 74 CREDITS Just Flight Project management Martyn Northall Aircraft modelling and design Mark Griffiths Sounds Turbine Sound Studios Manual Martyn Northall, John Hodgson Installer Martin Wright Design Fink Creative Thranda Design Project management, animation, UI, PBR, lighting, special effects Daniel Klaue Sound design (FMOD multi-track audio engineering), flight dynamics Daniel Klaue, Erick Stromback Manual Joseph Noe Programming Daniel Klaue, Erick Stromback, Joseph Noe 3D mesh and animation Daniel Klaue Testing and logic Erick Stromback, Joseph Noe Special thanks to all the testers COPYRIGHT ©2024 Just Flight. All rights reserved. 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