Flight Test Performance Calculation Package - Beech BE76 Duchess

failure at 71 knots, rotate, lift off and climb to 50 ft above the runway elevation. It is not a legal requirement to calculate the Accelerate-Go Distance Required or that it should exceed the Accelerate-Go Distance Available. In fact, very few light twins other than the Beech Duchess publish this information in their handbooks. In many cases this class of aircraft is simply not able to continue accelerating, lift-off and climb away due to the very small performance margin when on one engine. Again, determine the required and available distances and use this to guide your decision making. Knowing for certain that you cannot clear obstacles is a good reason to abort the takeoff rather than attempting to continue if the engine fails before lift off. Don’t forget to include this information in your pre-takeoff briefing. Refer to the “Accelerate-Go Distance Required” graph and the local aerodrome information Accelerate-Go Distance Required: _____ ft Accelerate-Go Distance Available: _____ ft ©Sharper Edge Training Solutions Ltd Take-off Distance Required (TODR) The total take-off distance needed to clear a 50 ft tall obstacle. Where there are existing obstacles at your departure airport you should determine the distance required to clear these obstacles. Refer to the “Take-off Distance Required” chart and the local aerodrome data Take-off Distance Required: _____ ft Take-off Distance Available: _____ ft Time, Fuel and Distance to Climb This is the time, fuel and distance needed to climb from an initial altitude up to a specified altitude, usually the cruising altitude. For the flight test the initial altitude is usually the elevation of the departure airport and the final altitude is the altitude that you will use when manoeuvring or demonstrating your engine failure procedures. The chart is read by finding the time, fuel and distance to climb from sea level to the departure aerodrome altitude and then subtracting these from the time, fuel and distance to climb from sea level to the flight test altitude. Refer to the “Time, Fuel and Distance to Climb” chart = - Climb from sea level to flight test altitude Time __ minutes Fuel __ USG Distance __ nm Climb from sea level to aerodrome elevation Time __ minutes Fuel __ USG Distance __ nm Climb from aerodrome to flight test altitude Time __ minutes Fuel __ USG Distance __ nm ©Sharper Edge Training Solutions Ltd Single Engine Climb Rate The single engine rate of climb is usually determined for two situations – firstly following an engine failure after take-off and secondly at your cruising altitude. Refer to the “Climb – One Engine Inoperative” chart After liftoff Single engine rate of climb: _____ fpm (_____% gradient) At flight test altitude Single engine rate of climb: _____ fpm (_____% gradient) Single Engine Cruise Performance If you are above your single engine absolute ceiling when an engine fails then you will be unable to maintain altitude. You will gradually descend down to the single engine absolute ceiling even if you are at full power on the operating engine and are maintaining the best single engine rate of climb speed (blue line, VYSE ). You need to check that you still will be able to maintain an altitude above terrain. This is particularly important during instrument conditions when you can’t see the terrain, so you should always check that your single engine absolute ceiling is above the Minimum Obstacle Clearance Altitude (MOCA) if you are flying IFR. Refer to the “Service Ceiling – One Engine Inoperative” chart Single Engine Service Ceiling: _____ ft ©Sharper Edge Training Solutions Ltd Time, Fuel and Distance to Descend This chart enables you to determine the time, fuel and distance needed to descend from an initial altitude to some final altitude. The chart is similar in its form and usage to the one used to determine fuel, time and distance to climb. For the flight test the initial altitude is usually the altitude that you will use when manoeuvring or demonstrating your engine failure procedures and the final altitude is the altitude of the aerodrome that you will be landing at. The chart is used by finding the time, fuel and distance to descend from aerodrome elevation to sea level and then subtracting these from the time, fuel and distance to descend from flight test maneuvering altitude to sea level. Refer to the “Time, Fuel and Distance to Descend” chart = - Descend from flight test altitude to sea level Time __ minutes Fuel __ USG Distance __ nm Descend from aerodrome elevation to sea level Time __ minutes Fuel __ USG Distance __ nm Descend from flight test altitude to aerodrome elevation Time __ minutes Fuel __ USG Distance __ nm Landing Distance Required The total landing distance needed to clear a 50 ft tall obstacle situated at the threshold. Where there are existing obstacles at your arrival airport you should determine the distance required to clear these obstacles and land. The landing distance chart requires the pressure altitude and temperature (to take into account the effects of density altitude) and the wind component to calculate landing distance but do not usually take into account the effect of weight on landing distance. Refer to the “Landing Distance – Flaps Down” chart and the local aerodrome information Landing Distance Required: _____ ft Landing Distance Available: _____ ft ©Sharper Edge Training Solutions Ltd PERFORMANCE CALCULATIONS SUMMARY ___________________________________________________________________ WEIGHT AND BALANCE Estimated fuel required: ____ USG = _____ lbs Actual fuel on board: ____ USG = _____ lbs Take-off weight: _____ lbs, Center of Gravity: Within Limits / Outside Limits Landing weight: _____ lbs, Center of Gravity: Within Limits / Outside Limits ___________________________________________________________________ TAKE OFF Pressure Altitude: _____ ft Take-off Decision Speed: _____ KIAS Accelerate-Stop Distance Required: _____ ft, Distance Available: _____ ft Accelerate-Go Distance Required: _____ ft, Distance Available: _____ ft Take-off Distance Required: _____ ft, Distance Available: _____ ft ___________________________________________________________________ CRUISE Pressure Altitude: _____ ft Single Engine Service Ceiling: _____ ft Power Setting: _____ in. Hg, _____ RPM Performance: _____ KIAS, _____ KTAS, _____ GPH per Engine ___________________________________________________________________ CLIMB NORMAL Airspeed: _____ KIAS Time: _____ minutes Fuel: _____ USG Distance: _____ nm ___________________________________________________________________ DESCENT Airspeed: _____ KIAS Time: _____ minutes Fuel: _____ USG Distance: _____ nm ONE ENGINE INOPERATIVE Airspeed: _____ KIAS After Liftoff: Single Engine Rate of Climb: _____ fpm (_____% gradient) At Flight Test Altitude: Single Engine Rate of Climb: _____ fpm (_____% gradient) ___________________________________________________________________ LANDING Approach Airspeed: _____ KIAS Landing Distance Required: _____ ft, Distance Available: _____ ft ©Sharper Edge Training Solutions Ltd SL 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 12000 13000 14000 15000 16000 PRESS ALT. FEET NOTES: 1. FULL THROTTLE MANIFOLD PRESSURE SETTINGS ARE APPROXIMATE 2. SHADED AREA REPRESENTS OPERATION WITH FULL THROTTLE 3. LEAN TO 25°F – 50°F ON RICH SIDE OF PEAK EGT 4. CRUISE SPEEDS ARE PRESENTED AT AN AVERAGE WEIGHT OF 3600 LBS RECOMMENDED CRUISE POWER – 20.0 IN. HG @ 2300 RPM (OR FULL THROTTLE) (Chart extract) 16 14 13 11 9 7 5 3 1 -1 -3 -6 -7 -9 -11 -13 -15 61 57 55 52 48 45 41 37 34 30 27 23 19 16 12 9 5 20.0 20.0 20.0 20.0 20.0 20.0 20.0 20.0 20.0 20.0 20.0 19.5 18.8 18.0 17.3 16.7 16.0 40 41 42 42 43 44 45 46 47 48 49 49 47 46 44 42 40 6.7 6.8 7.0 7.0 7.2 7.3 7.5 7.7 7.8 8.0 8.2 8.2 7.8 7.7 7.3 7.0 6.7 123 124 125 126 127 127 128 128 129 129 130 129 125 122 119 115 111 123 126 129 132 135 137 140 143 145 148 151 152 151 149 147 145 143 STANDARD DAY (ISA) OAT MAN. PRESS. FUEL FLOW/ ENGINE IAS TAS °C °F IN. HG PPH GPH KTS KTS 36 34 33 31 29 27 25 23 21 19 17 15 13 11 9 7 5 97 93 91 88 84 81 77 73 70 66 63 59 55 52 48 45 41 20.0 20.0 20.0 20.0 20.0 20.0 20.0 20.0 20.0 20.0 20.0 19.5 18.8 18.0 17.3 16.7 16.0 38 39 40 41 42 43 44 45 46 47 48 47 46 44 42 41 39 6.3 6.5 6.7 6.8 7.0 7.2 7.3 7.5 7.7 7.8 8.0 7.8 7.7 7.3 7.0 6.8 6.5 119 120 121 122 122 123 124 124 125 125 125 124 121 117 114 110 106 123 126 129 132 135 137 140 143 146 149 151 152 151 149 147 144 142 ISA +20°C (+36°F) OAT MAN. PRESS. FUEL FLOW/ ENGINE IAS TAS °C °F IN. HG PPH GPH KTS KTS NOTE: Mark up these charts in red so that it is easy for the examiner to see how you came up with your performance figures ©Sharper Edge Training Solutions Ltd Weight Arm Moment (lbs) (inches) (inch-lbs / 100) Basic Empty Weight Pilot & Co-Pilot 108.0 Rear Passengers 144.0 Baggage (Max 200lb) 167.0 Zero Fuel Total (Max 3500lb) Fuel (6lb / USG) 117.0 Ramp Weight (Max 3916lb) Start & Taxi Fuel 16 117.0 1872 Take-Off Weight (Max 3900lb) Trip Fuel (6lb / USG) 117.0 Landing Weight (Max 3900lb) NOTE: Weight and CG location must be within limitations at all times during the flight. It is not sufficient to simply calculate the weight and balance at take-off ©Sharper Edge Training Solutions Ltd ISA PRESSURE ALTITUDE - FEET 6000 4000 2000 SL TAIL WIND HEAD WIND REFERENCE LINE REFERENCE LINE OUTSIDE AIR TEMPERATURE (°C) WEIGHT (LBS) WIND COMPONENT (KNOTS) -40 3800 0 6000 ACCELERATE – STOP DISTANCE REQUIRED 5000 1000 2000 3000 4000 -30 -20 -10 20 10 0 50 40 30 8000 10000 3600 3400 3200 10 20 30 7000 DISTANCE TO ACCELERATE TO DECISION SPEED AND STOP (FEET) ASSOCIATED CONDITIONS: POWER - 1) TAKE-OFF POWER AT 2700 RPM SET BEFORE BRAKE RELEASE - 2) ENGINE IDLE AT DECISION SPEED MIXTURE - FULL RICH (ABOVE 5000 FT LEAN TO 75°F TO 100°F ON RICH SIDE OF PEAK EGT) FLAPS - UP RUNWAY - PAVED, LEVEL, DRY SURFACE COWL FLAPS - OPEN DECISION SPEED (ALL WEIGHTS) 71 KNOTS 3000 2800 ©Sharper Edge Training Solutions Ltd ISA PRESSURE ALTITUDE - FEET 6000 4000 2000 SL TAIL WIND HEAD WIND REFERENCE LINE REFERENCE LINE OUTSIDE AIR TEMPERATURE (°C) WEIGHT (LBS) WIND COMPONENT (KNOTS) 60 3800 0 7000 6000 2000 3000 4000 5000 -30 -20 -10 20 10 0 50 40 30 3600 3400 3200 10 20 30 8000 TAKE-OFF DISTANCE OVER 50 FT OBSTACLE (FEET) 3000 ASSOCIATED CONDITIONS: POWER - TAKE-OFF POWER AT 2700 RPM SET BEFORE BRAKE RELEASE MIXTURE - FULL RICH (ABOVE 5000 FT LEAN TO 75°F TO 100°F ON RICH SIDE OF PEAK EGT) FLAPS - UP LANDING GEAR - RETRACT AFTER POSITIVE CLIMB ESTABLISHED RUNWAY - PAVED, LEVEL, DRY SURFACE COWL FLAPS - OPEN ACCELERATE – GO DISTANCE REQUIRED NOTES: 1. GROUND ROLL DISTANCE IS 20% OF TAKE-OFF DISTANCE OVER 50 FT OBSTACLE. 2. DISTANCES ASSUME AN ENGINE FAILURE AT LIFT-OFF AND PROPELLER IMMEDIATELY FEATHERED. 3. WEIGHTS IN SHADED AREA MAY NOT PROVIDE POSITIVE ONE-ENGINE INOPERATIVE CLIMB. REFER TO TAKE-OFF WEIGHT GRAPH FOR MAXIMUM WEIGHT AT WHICH THE ACCELERATE-GO PROCEDURE SHOULD BE ATTEMPTED. TAKE-OFF SPEEDS (ALL WEIGHTS) LIFT-OFF 71 KNOTS 50 FEET 80 KNOTS ©Sharper Edge Training Solutions Ltd ISA PRESSURE ALTITUDE - FEET 6000 4000 2000 SL TAIL WIND HEAD WIND REFERENCE LINE REFERENCE LINE OUTSIDE AIR TEMPERATURE (°C) WEIGHT (LBS) WIND COMPONENT (KNOTS) -40 3800 0 5000 TAKE-OFF DISTANCE REQUIRED 4000 0 1000 2000 3000 TAKE-OFF SPEEDS (ALL WEIGHTS) LIFT-OFF 71 KNOTS 50 FEET 80 KNOTS -30 -20 -10 20 10 0 50 40 30 8000 10000 3600 3400 3200 10 20 30 0 50 OBSTACLE HEIGHT (FEET) 6000 DISTANCE (FEET) REFERENCE LINE ASSOCIATED CONDITIONS: POWER - TAKE-OFF POWER AT 2700 RPM SET BEFORE BRAKE RELEASE MIXTURE - FULL RICH (ABOVE 5000 FT LEAN TO 75°F TO 100°F ON RICH SIDE OF PEAK EGT) FLAPS - UP LANDING GEAR - RETRACT AFTER POSITIVE CLIMB ESTABLISHED RUNWAY - PAVED, LEVEL, DRY SURFACE COWL FLAPS - OPEN ©Sharper Edge Training Solutions Ltd ISA PRESSURE ALTITUDE - FEET 18000 14000 12000 2000 OUTSIDE AIR TEMPERATURE (°C) -40 40 -30 -20 -10 20 10 0 50 40 30 30 20 10 0 ASSOCIATED CONDITIONS: POWER - FULL THROTTLE AT 2600 RPM MIXTURE - FULL RICH (ABOVE 5000 FT LEAN TO 75°F TO 100°F ON RICH SIDE OF PEAK EGT) COWL FLAPS - OPEN TIME, FUEL AND DISTANCE TO CLIMB CLIMB SPEED 100 KNOTS TIME TO CLIMB (MINUTES) 8 6 4 2 0 10 12 14 10 0 50 FUEL TO CLIMB (USG) 40 30 20 50 70 60 80 DISTANCE TO CLIMB (NM) -50 4000 6000 8000 10000 3800 3600 2800 WEIGHT (LBS) ©Sharper Edge Training Solutions Ltd ISA PRESSURE ALTITUDE - FEET 6000 4000 2000 SL REFERENCE LINE OUTSIDE AIR TEMPERATURE (°C) WEIGHT (LBS) -40 3800 500 CLIMB – ONE ENGINE INOPERATIVE 300 -500 -300 -100 100 -30 -20 -10 20 10 0 50 40 30 8000 10000 3600 3400 3200 RATE-OF-CLIMB (FPM) ASSOCIATED CONDITIONS: POWER - TAKE-OFF POWER AT 2700 RPM MIXTURE - FULL RICH (ABOVE 5000 FT LEAN TO 75°F TO 100°F ON RICH SIDE OF PEAK EGT) INOPERATIVE PROPELLER - FEATHERED FLAPS - UP LANDING GEAR - UP COWL FLAPS - OPEN CLIMB SPEED 85 KNOTS (ALL WEIGHTS) 3000 2800 -50 400 -400 -200 0 200 5 3 -5 -3 -1 1 CLIMB GRADIENT (%) 4 -4 -2 0 2 6 7 ©Sharper Edge Training Solutions Ltd NOTE: To use this chart, you have to estimate what the temperature will be at your single engine service ceiling before you have determined what that ceiling is. You will have to do this by trial and error but do not try to be too accurate because the graph itself is only an approximation of real world performance OUTSIDE AIR TEMPERATURE (°C) -40 SERVICE CEILING – ONE ENGINE INOPERATIVE -30 -20 -10 20 10 0 50 40 30 ASSOCIATED CONDITIONS: POWER - MAXIMUM CONTINUOUS AT 2700 RPM INOPERATIVE PROPELLER - FEATHERED FLAPS - UP LANDING GEAR - UP COWL FLAPS - OPEN CLIMB SPEED 85 KNOTS (ALL WEIGHTS) -50 NOTE: SERVICE CEILING IS THE ALTITUDE WHERE THE AIRPLANE HAS THE CAPABILITY OF CLIMBING AT 50 FPM WITH ONE PROPELLER FEATHERED. -60 60 SL 20,000 15,000 10,000 5,000 SERVICE CEILING (FEET) WEIGHT (LBS) 3000 3200 3400 3600 3800 3900 ©Sharper Edge Training Solutions Ltd TIME TO DESCEND (MINUTES) 4 TIME, FUEL AND DISTANCE TO DESCEND 6 8 10 16 14 12 ASSOCIATED CONDITIONS: POWER - AS REQUIRED TO MAINTAIN 1000 FPM RATE OF DESCENT FLAPS - UP LANDING GEAR - UP MIXTURE - FULL RICH (ABOVE 5000 FT LEAN TO 75°F TO 100°F ON RICH SIDE OF PEAK EGT) DESCENT SPEED – 170 KNOTS 2 0 SL 10000 1000 PRESSURE ALTITUDE (FEET) 2000 3000 4000 5000 6000 7000 8000 9000 11000 12000 13000 14000 15000 16000 FUEL TO DESCEND (USG) 2 3 4 1 0 DISTANCE TO DESCEND (NM) 20 30 40 10 0 5 50 ©Sharper Edge Training Solutions Ltd ISA PRESSURE ALTITUDE - FEET 6000 4000 2000 SL TAIL WIND HEAD WIND REFERENCE LINE OUTSIDE AIR TEMPERATURE (°C) WIND COMPONENT (KNOTS) -40 0 2500 LANDING DISTANCE – FLAPS DOWN 2000 0 500 1000 1500 APPROACH SPEED 76 KNOTS (ALL WEIGHTS) -30 -20 -10 20 10 0 50 40 30 8000 10000 10 20 30 0 50 OBSTACLE HEIGHT (FEET) DISTANCE (FEET) REFERENCE LINE ASSOCIATED CONDITIONS: POWER - RETARD TO MAINTAIN 600 FPM ON FINAL APPROACH FLAPS - DOWN (DN) LANDING GEAR - DOWN RUNWAY - PAVED, LEVEL, DRY SURFACE APPROACH SPEED - 76 KNOTS IAS BRAKING - MAXIMUM CANADIAN FLIGHT PLAN AND FLIGHT ITINERARY PLAN DE VOL ET ITINÉRAIRE DE VOL CANADIEN ICAO FLIGHT PLAN PLAN DE VOL OACI PRIORITY / PRIORITÉ ADDRESSEE(S) / DESTINATAIRE(S) <<<<<<<< ≡≡≡≡ FF → → → → <<<<<<<< ≡≡≡≡ FILING TIME / HEURE DE DÉPÔT ORIGINATOR / EXPÉDITEUR → → → → <<<<<<<< ≡≡≡≡ SPECIFIC IDENTIFICATION OF ADDRESSEE(S) AND/OR ORIGINATOR / IDENTIFICATION PRÉCISE DU(DES) DESTINATAIRE(S) ET/OU DE L’EXPÉDITEUR 3 MESSAGE TYPE TYPE DE MESSAGE 7 AIRCRAFT IDENTIFICATION / IDENTIFICATION DE L’AÉRONEF 8 FLIGHT RULES / RÈGLES DE VOL TYPE OF FLIGHT / TYPE DE VOL <<<<<<<< ≡≡≡≡ (FPL −−−− −−−− <<<<<<<< 9 NUMBER / NOMBRE TYPE OF AIRCRAFT / TYPE D’AÉRONEF WAKE TURBULENCE CAT. / CAT. DE TURBULENCE DE SILLAGE 10 EQUIPMENT / ÉQUIPEMENT −−−− / −−−− <<<<<<<< ≡≡≡≡ 13 DEPARTURE AERODROME / AÉRODROME DE DÉPART TIME / HEURE −−−− <<<<<<<< ≡≡≡≡ 15 CRUISING SPEED / VITESSE DE CROISIÈRE ALTITUDE / LEVEL / NIVEAU ROUTE / ROUTE −−−− 0 0 0 0 0 0 0 0 0 0 → → → → <<<<<<<< ≡≡≡≡ 16 DESTINATION AERODROME AÉRODROME DE DESTINATION TOTAL EET / DURÉE TOTALE ESTIMÉE DAYS/JOURS HRS MINS SAR HRS MINS ALTN AERODROME / AÉRODROME DE DÉGAGEMENT 2ND ALTN AERODROME / 2e AÉRODROME DE DÉGAGEMENT −−−− → → → → → → → → <<<<<<<< ≡≡≡≡ 18 OTHER INFORMATION / RENSEIGNEMENTS DIVERS −−−− )<<<<<<<< ≡≡≡≡ 19 ENDURANCE / AUTONOMIE EMERGENCY RADIO / RADIO DE SECOURS HRS MINS PERSONS ON BOARD / PERSONNES À BORD UHF VHF ELT ELT TYPE / TYPE D’ELT −−−− E / → → → → P / → → → → R / U V E SURVIVAL EQUIPMENT / ÉQUIPEMENT DE SURVIE JACKETS / GILETS DE SAUVETAGE POLAR POLAIRE DESERT DÉSERT MARITIME MARITIME JUNGLE JUNGLE LIGHT LAMPES FLUORES FLUORES UHF VHF → → → → S / P D M J → → → → J / L F U V DINGHIES / CANOTS NUMBER NOMBRE CAPACITY CAPACITÉ COVER COUVERTURE COLOUR COULEUR → → → → D / → → → → → → → → C → → → → <<<<<<<< ≡≡≡≡ AIRCRAFT COLOUR AND MARKINGS / COULEUR ET MARQUES DE L’AÉRONEF WHEELS ROUES SEAPLANE HYDRAVION SKIS AMPHIBIAN AMPHIBIE A / REMARKS / REMARQUES → → → → N / <<<<<<<< ≡≡≡≡ AN ARRIVAL REPORT WILL BE FILED WITH / UN COMPTE RENDU D’ARRIVÉE SERA NOTIFIÉ À : NAME AND PHONE NUMBER OR ADDRESS OF PERSONS(S) OR COMPANY TO BE NOTIFIED IF SEARCH AND RESCUE ACTION INITIATED / NOM ET NUMÉRO DE TÉLÉPHONE OU ADRESSE DE LA (DES) PERSONNE(S) OU COMPAGNIE À AVISER SI DES RECHERCHES SONT ENTREPRISES PILOT-IN-COMMAND / PILOTE COMMANDANT DE BORD PILOT’S LICENCE NO. / N° DE LICENCE DU PILOTE C / )<<<<<<<< ≡≡≡≡ FILED BY / DÉPOSÉ PAR SPACE RESERVED FOR ADDITIONAL REQUIREMENTS / ESPACE RÉSERVÉ À DES FINS SUPPLÉMENTAIRES NAVCAN26-0516 (2010-01)