Flight Test Performance Calculation Package – Piper PA44 Seminole

obstacles at your departure airport you should determine the distance required to clear these obstacles. Refer to the “Normal Procedure Take-off Distance Over 50 ft Barrier” chart and the local aerodrome data Take-off Distance Required: _____ ft Take-off Distance Available: _____ ft ©Sharper Edge Training Solutions Ltd 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 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 Performance – One Engine Operating” 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 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 “Climb Performance – One Engine Operating” chart to determine the single engine service ceiling, where climb rate is only 50 fpm Single Engine Service Ceiling: _____ ft 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 ©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 Barrier, Short Field Effort” 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 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 Press. Alt. Feet NOTES: 1. To maintain constant power, add approximately 1% manifold pressure for each 6°C above standard, subtract approximately 1% for each 6°C below standard. 2. Fuel flow provided for Best Power mixture FUEL AND POWER CHART – LYCOMING (L) O-360-E SEROES (PER ENGINE) 15 13 11 9 7 5 3 1 -1 -3 -5 -7 -9 -11 -13 22.2 21.9 21.6 21.3 21.0 20.8 20.5 20.2 19.9 19.6 19.3 FT - - - Std. Alt. Temp. °C 99 BHP – 55% Rated Power Approx Fuel Flow 9.3 Gal/hr RPM AND MAN. PRESS. 2100 117 BHP – 65% Rated Power Approx Fuel Flow 10.3 Gal/hr RPM AND MAN. PRESS. 135 BHP – 75% Rated Power Approx Fuel Flow 11.2 Gal/hr RPM AND MAN. PRESS. 21.7 21.4 21.1 20.8 20.6 20.3 20.2 19.7 19.5 19.2 18.9 18.6 FT - - 21.2 21.0 20.7 20.4 20.1 19.9 19.6 19.3 19.1 18.8 18.5 18.3 18.0 FT - 20.7 20.4 20.2 19.9 19.7 19.4 19.2 18.9 18.6 18.4 18.1 17.9 17.6 17.4 FT 24.5 24.2 23.9 23.6 23.2 22.9 22.6 FT - - - 24.0 23.7 23.4 23.1 22.7 22.4 22.1 21.8 FT - - 23.4 23.1 22.9 22.6 22.3 22.0 21.7 21.5 21.2 FT - 22.9 22.6 22.3 22.1 21.8 21.5 21.3 21.0 20.7 20.5 FT 26.4 26.1 25.8 25.4 FT - - 25.8 25.5 25.2 24.9 24.7 FT - 25.2 24.9 24.6 24.4 24.1 23.8 FT 2200 2300 2400 2100 2200 2300 2400 2200 2300 2400 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 STD. TEMP. OUTSIDE AIR TEMPERATURE (°C) WEIGHT (LBS) WIND COMPONENT (KNOTS) -40 3500 0 5000 1000 2000 3000 4000 -30 -20 -10 20 10 0 40 30 3000 2500 5 10 15 DISTANCE (FEET) ASSOCIATED CONDITIONS: POWER - BOTH ENGINES AT 2700 RPM AND FULL THROTTLE MIXTURE - FULL RICH FLAPS - 0° BRAKING - MAX COWL FLAPS - OPEN RUNWAY - PAVED, LEVEL, DRY SURFACE ABORT SPEED - 75 KIAS 7000 6000 PRESSURE ALTITUDE - FT 6000 4000 2000 SEA LEVEL 7000 REFERENCE LINE TAIL WIND HEAD WIND REFERENCE LINE *NOTE REDUCE ACCELERATE-STOP DISTANCE BY 10% IF HEAVY DUTY BRAKES ARE INSTALLED. NORMAL PROCEDURE ACCELERATE – STOP DISTANCE *STANDARD BRAKES ©Sharper Edge Training Solutions Ltd OUTSIDE AIR TEMPERATURE (°C) WEIGHT (LBS) WIND (KNOTS) -40 3500 0 5000 1000 2000 3000 4000 -30 -20 -10 20 10 0 40 30 3000 2500 5 10 15 DISTANCE (FEET) ASSOCIATED CONDITIONS: POWER - BOTH ENGINES AT 2700 RPM AND FULL THROTTLE BEFORE BRAKE RELEASE FLAPS - 0° RUNWAY - PAVED, LEVEL, DRY SURFACE NORMAL PROCEDURE TAKEOFF DISTANCE OVER 50 FT. BARRIER WEIGHT POUNDS 3800 3400 3000 2600 LIFT OFF SPEED KIAS 75 71 66 62 BARRIER SPEED KIAS 88 83 78 73 STD. TEMP. PRESSURE ALTITUDE - FT 6000 4000 2000 SEA LEVEL 7000 TAIL WIND HEAD WIND REFERENCE LINE (ZERO WIND) REF. LINE (3800 LBS) CAUTION Best one engine in- operative rate of climb is less than 50 FPM if T.O. wt. is in the shaded area ©Sharper Edge Training Solutions Ltd OUTSIDE AIR TEMPERATURE (°C) STD. TEMP. FT. PRESS. ALT 14000 12000 2000 -40 -30 -20 -10 20 10 0 40 30 4000 6000 8000 10000 40 30 20 10 0 TIME DISTANCE AND FUEL TO CLIMB DIST (NAUTICAL MILES) TIME (MIN) FUEL (GAL) ASSOCIATED CONDITIONS: POWER - FULL THROTTLE AT 2700 RPM WING FLAPS - 0° COWL FLAPS - OPEN LANDING GEAR - RETRACTED CLIMB SPEED - 88 KIAS NO WIND TIME, FUEL AND DISTANCE TO CLIMB ©Sharper Edge Training Solutions Ltd OUTSIDE AIR TEMPERATURE (°C) CLIMB PERFORMANCE – ONE ENGINE OPERATING ASSOCIATED CONDITIONS: POWER - FULL THROTTLE AND 2700 RPM MIXTURE - FULL RICH (ABOVE 75% POWER) - BEST POWER (BELOW 75% POWER) INOPERATIVE PROPELLER - FEATHERED FLAPS - 0° LANDING GEAR - UP COWL FLAPS - OPEN (OPERATING ENGINE) - CLOSED (INOPERATIVE ENGINE) AIRSPEED - 88 KIAS BANK ANGLE - 3° - 5° BANK TOWARD OPERATIVE ENGINE -40 -30 -20 -10 20 10 0 40 30 6000 RATE OF CLIMB (FEET / MINUTE) -200 0 200 400 600 14000 12000 PRESS. ALT. - FT SEA LEVEL STD. TEMP. 4000 2000 8000 10000 FULL RICH 2800 LBS 3000 LBS 3200 LBS 3400 LBS 3600 LBS 3800 LBS BEST POWER ©Sharper Edge Training Solutions Ltd OUTSIDE AIR TEMPERATURE (°C) STD. TEMP. FT. PRESS. ALT 14000 12000 2000 -40 -30 -20 -10 20 10 0 40 30 4000 6000 8000 10000 80 60 40 20 0 TIME DISTANCE AND FUEL TO CLIMB DISTANCE (NAUTICAL MILES) TIME (MIN) FUEL (GAL) TIME, FUEL AND DISTANCE TO DESCEND ASSOCIATED CONDITIONS: POWER - 2400 RPM & THROTTLE TO MAINTAIN 500 FPM DESCENT WING FLAPS - 0° COWL FLAPS - CLOSED LANDING GEAR - RETRACTED DESCENT SPEED - 165 KIAS NO WIND 100 ©Sharper Edge Training Solutions Ltd OUTSIDE AIR TEMPERATURE (°C) WEIGHT (LBS) WIND (KNOTS) -40 3500 0 -30 -20 -10 20 10 0 40 30 3000 2500 5 10 15 DISTANCE (FEET) LANDING DISTANCE OVER 50 FT. BARRIER SHORT FIELD EFFORT STANDARD BRAKES* STD. TEMP. PRESS ALT (FT) 6000 4000 2000 SEA LEVEL TAIL WIND HEAD WIND REFERENCE LINE (ZERO WIND) REF. LINE (3800 LBS) *NOTE Reduce total landing distance by 15% if optional landing gear heavy duty Group No. 1 is installed (See Equipment List) 1700 1300 1400 1500 1600 1200 ASSOCIATED CONDITIONS: POWER - OFF FLAPS - 40° FULL STALL TOUCHDOWN APPROACH SPEED AS SCHEDULED APPROACH SPEED - KIAS 75 72 67 61 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)