Flight Test Performance Calculation Package – Diamond DA42

chart, so you will have to use a rule of thumb to come up with this information. Rule-Of-Thumb #1: Average climb rate is approximately the climb rate at 2/3 your desired altitude Rule-Of-Thumb #2: Average TAS during climb is approximately the same as your TAS when at 2/3 your desired altitude Rule-Of-Thumb #3: Average fuel flow will be the fuel flow at 100 % load Example: Climbing from Sea Level to 10,000 ft so check climb rate and TAS at 7,000 ft. These values will be close to the average climb rate and average TAS for the climb. Since you now have the altitude to climb, average climb rate, average TAS and fuel flow you can now calculate the time, fuel and distance needed for the climb Time: _____ minutes Fuel: _____ USG Distance: _____ nm ©Sharper Edge Training Solutions Ltd 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 “One Engine Inoperative – Climb / Descent” chart Single Engine Service Ceiling: _____ ft 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 “One Engine Inoperative – Climb / Descent” chart After liftoff Single engine rate of climb: _____ fpm (_____% gradient) At flight test altitude Single engine rate of climb: _____ fpm (_____% gradient) ©Sharper Edge Training Solutions Ltd 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 Over 50 ft Obstacle” chart and the local aerodrome information Landing Distance Required: _____ ft Landing Distance Available: _____ ft Time, Fuel and Distance to Descend The Diamond DA42 Aircraft Flight Manual doesn’t provide a “Time, Fuel and Distance to Descend” chart, so you will have to pick an airspeed and descent rate for the descent, and use a rule of thumb to come up with this information. Descent Airspeed: A good airspeed to use for descent is the IAS used for cruise Rate of Descent: Since the DA42 is not pressurized a descent rate of 500 fpm will allow you to descend relatively quickly without being uncomfortable for your passengers Rule-Of-Thumb #1: Average TAS during descent is approximately the same as your TAS when at 2/3 of your cruising altitude Rule-Of-Thumb #2: Average fuel flow will be approximately the fuel flow at 50 % load Example: Descending from 10,000 ft to Sea Level so check TAS at 7,000 ft. This value will be close to the average TAS for the descent. Since you now have the altitude to descend, average descent rate, average TAS and fuel flow you can now calculate the time, fuel and distance needed for the descent Time: _____ minutes Fuel: _____ USG Distance: _____ nm ©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 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 FUEL FLOW (per engine) (Chart Extract) 30 100 90 80 70 60 50 40 LOAD (%) 4.5 1 1.5 2 2.5 3 3.5 4 7 5 5.5 6 6.5 7.5 8 8.5 FUEL FLOW (US GPH) 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 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 1500 TAKE-OFF DISTANCE Over 50 ft Obstacle 1300 700 900 1100 1700 DISTANCE OVER 50 ft OBSTACLE (FEET) 2700 2500 1900 2100 2300 2900 3300 3100 3500 OUTSIDE AIR TEMPERATURE (°C) WEIGHT (LBS) WIND COMPONENT (KNOTS) -20 3600 0 -15 -10 -5 10 5 0 25 20 15 3400 3200 3000 5 10 15 -35 -30 -25 30 45 40 35 20 0 ft Pressure Altitude 2000 ft 4000 ft 6000 ft 8000 ft 10,000 ft ASSOCIATED CONDITIONS: POWER - MAX POWER AT 2300 RPM FLAPS - UP ROTATE SPEED - 70 KIAS CLIMB SPEED - 77 KIAS RUNWAY - PAVED, LEVEL, DRY SURFACE ©Sharper Edge Training Solutions Ltd ASSOCIATED CONDITIONS: POWER - Both MAX at 2300 RPM FLAPS - UP LANDING GEAR - RETRACTED AIRSPEED - 77 KIAS CLIMB PERFORMANCE – TAKE-OFF CLIMB OUTSIDE AIR TEMPERATURE (°C) -20 -15 -10 -5 10 5 0 25 20 15 -25 30 45 40 35 3700 3600 3500 3400 3300 3200 3100 3000 2900 2800 WEIGHT (LBS) 1700 1600 1500 1400 1300 1200 1100 1000 900 800 700 600 500 400 300 200 100 0 ft (Sea Level) 2,000 ft 4,000 ft 6,000 ft 8,000 ft 10,000 ft 12,000 ft 14,000 ft 16,000 ft 18,000 ft RATE OF CLIMB (ft/min) ©Sharper Edge Training Solutions Ltd ASSOCIATED CONDITIONS: POWER - Both MAX at 2300 RPM FLAPS - UP LANDING GEAR - RETRACTED AIRSPEED - 85 KIAS CLIMB PERFORMANCE – CRUISE CLIMB OUTSIDE AIR TEMPERATURE (°C) -20 -15 -10 -5 10 5 0 25 20 15 -25 30 45 40 35 3700 3600 3500 3400 3300 3200 3100 3000 2900 2800 WEIGHT (LBS) 1700 1600 1500 1400 1300 1200 1100 1000 900 800 700 600 500 400 300 200 100 0 ft (Sea Level) 2,000 ft 4,000 ft 6,000 ft 8,000 ft 10,000 ft 12,000 ft 14,000 ft 16,000 ft 18,000 ft RATE OF CLIMB (ft/min) ©Sharper Edge Training Solutions Ltd OUTSIDE AIR TEMPERATURE (°C) -20 -15 -10 -5 10 5 0 25 20 15 -25 30 45 40 35 3700 3600 3500 3400 3300 3200 3100 3000 2900 2800 WEIGHT (LBS) 600 550 500 450 400 350 300 250 200 150 100 50 0 -50 -100 -150 -400 RATE OF CLIMB (ft/min) -200 -250 -300 -350 0 ft (Sea Level) 2,000 ft 4,000 ft 6,000 ft 8,000 ft 10,000 ft 12,000 ft 14,000 ft 16,000 ft 18,000 ft ASSOCIATED CONDITIONS: OPERATING ENGINE - MAX at 2300 RPM FAILED ENGINE - FEATHERED and SECURED FLAPS - UP LANDING GEAR - RETRACTED AIRSPEED - 82 KIAS ZERO SIDESLIP - ESTABLISHED ONE ENGINE INOPERATIVE – CLIMB / DESCENT ©Sharper Edge Training Solutions Ltd 1400 1300 1000 1100 1200 1500 DISTANCE OVER 50 ft OBSTACLE (FEET) 2000 1900 1600 1700 1800 2100 2300 2200 2400 OUTSIDE AIR TEMPERATURE (°C) WEIGHT (LBS) WIND COMPONENT (KNOTS) -20 3700 0 -15 -10 -5 10 5 0 25 20 15 3600 3500 3400 5 10 15 -35 -30 -25 30 45 40 35 20 3300 3200 3100 3000 2900 2500 2600 2800 2700 2900 ASSOCIATED CONDITIONS: POWER - IDLE FLAPS - LDG APPROACH SPEED - 76 KIAS RUNWAY - PAVED, LEVEL, DRY SURFACE 0 ft Pressure Altitude 2000 ft 4000 ft 6000 ft 8000 ft 10,000 ft LANDING DISTANCE Over 50 ft Obstacle 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)