This document is posted to help you gain knowledge. Please leave a comment to let me know what you think about it! Share it to your friends and learn new things together.
58-590000-67A11_sec05toc.fm Page 3 Friday, August 1, 2014 11:10 AM
July, 2014
Model G58
July, 2014
Section 5
IONALLY LEFT BLANK
Performance
58-590000-67A11_sec05toc.fm Page 4 Tuesday, July 29, 2014 8:37 AM
5-4
THIS PAGE INTENT
PerformanceSection 5
Model G58
58-590000-67A11_sec05.fm Page 5 Tuesday, July 29, 2014 8:32 AM
Except as noted, all airspeeds quoted in this section are indi-cated airspeeds (IAS) and assume zero instrument error.
INTRODUCTION TO PERFORMANCE
The graphs and tables in this section present performanceinformation for flight planning at various parameters of weight,power, altitude and temperature. Examples have been pre-sented on all performance graphs.
PERFORMANCE IN ICING CONDITIONS 1. On a clean airplane (no ice build-up) stall speeds are
increased 4 knots in all configurations when surfacedeice boots are inflated.
2. Residual ice on the airplane can disrupt the airflow overlifting surfaces and may cause an increase in the stallspeeds and a change in the amount of warning providedby the stall warning vane.
3. The wings, stabilizers, and all control surfaces must becleared of frost, ice or snow prior to takeoff.
4. Ice accumulations on unprotected surfaces will decreaseclimb rates, cruise speeds, and range. Therefore, flightplanning should be accomplished for altitudes whereadequate performance margins exist.
5. Two-engine climb performance at maximum continuouspower will be reduced due to the 130 KIAS minimumclimb speed.
6. The minimum recommended holding speed in icing con-ditions is 140 KIAS.
5-5July, 2014
Performance Model G58Section 5
58-590000-67A11_sec05.fm Page 6 Tuesday, July 29, 2014 8:32 AM
HOW TO USE THE GRAPHS1. In addition to presenting the answer for a particular set of
conditions, the example on the graph also presents theorder in which the various scales on the graph should beused. For instance, if the first item in the example isOAT, then enter the graph at the known OAT and pro-ceed to the remaining item(s) in the order given in theexample.
2. The reference lines indicate where to begin following theguidelines. Always project to the reference line first, thenfollow the guidelines to the next known item by maintain-ing the same PROPORTIONAL DISTANCE between theguideline above and guideline below the projected line.For instance, if the projected line intersects the referenceline in the ratio of 30% down/70% up between the guide-lines, then maintain this same 30%/70% relationshipbetween the guidelines all the way to the next knownitem or answer.
3. The associated conditions define the specific conditionsfrom which performance parameters have been deter-mined. They are not intended to be used as instructions;however, performance values determined from chartscan only be achieved if the specified conditions exist.
4. Indicated airspeeds (IAS) were obtained by using theAIRSPEED CALIBRATION-NORMAL SYSTEM graph.
5. The full amount of usable fuel is available for allapproved flight conditions.
5-6
July, 2014
PerformanceSection 5
Model G58
58-590000-67A11_sec05.fm Page 7 Tuesday, July 29, 2014 8:32 AM
EXAMPLE CALCULATIONS
The calculations for flight time, block speed and fuel requiredfor a proposed flight are listed below:
58-590000-67A11_sec05.fm Page 8 Tuesday, July 29, 2014 8:32 AM
PRESSURE ALTITUDE
To determine pressure altitude at departure and destinationairports, add 1000 ft to field elevation for each 1.00 in. Hgbelow 29.92, and subtract 1000 ft from field elevation for each1.00 in. Hg above 29.92.
Pressure Altitude at Departure:
29.92 - 29.60 = 0.32 in. Hg 0.32 x 1000 = 320 ft
The Pressure Altitude at the departure airport is 320 ftabove the field elevation.
5333 + 320 = 5653 ft
Pressure Altitude at Destination:
29.92 - 29.56 = 0.36 in. Hg
0.36 x 1000 = 360 ft
The Pressure Altitude at the destination airport is 360 ftabove the field elevation.
3605 + 360 = 3965 ft
NOTEFor flight planning, the difference betweencruise altitude and cruise pressure altitudehas been ignored.
TAKE-OFF WEIGHT
Maximum Allowable Take-off Weight = 5500 lbs
Ramp Weight = 5500 + 24 = 5524 lbs
NOTEFuel for start, taxi and run-up is normally 24lbs.
5-8
July, 2014
PerformanceSection 5
Model G58
58-590000-67A11_sec05.fm Page 9 Tuesday, July 29, 2014 8:32 AM
Enter the Take-Off Weight graph at 5653 ft pressure altitudeand 15°C, to determine the maximum take-off weight toachieve a positive one-engine-inoperative rate-of-climb at lift-off.
Take-off Weight = 4870 lbs
TAKE-OFF DISTANCE
Enter the Take-Off Distance graph at 15°C, 5653 ft pressurealtitude, 5500 lbs, and 10 knots headwind component:
NOTESince 3960 ft is less than the available fieldlength of 10,004 ft, the accelerate-stop pro-cedure can be performed at any weight.
Take-off at 5500 lbs can be accomplished. However, if anengine failure occurs before becoming airborne, the acceler-ate-stop procedure must be performed.
The following example assumes the airplane is loaded so thatthe take-off weight is 4700 lbs.
Although not required by regulations, information has beenpresented to determine the take-off weight, field requirementsand take-off flight path assuming an engine failure occurs dur-ing the take-off procedure. The following illustrates the use ofthese graphs.
5-9July, 2014
Performance Model G58Section 5
58-590000-67A11_sec05.fm Page 10 Tuesday, July 29, 2014 8:32 AM
Enter the Accelerate-Go graph at 15°C, 5653 ft pressure alti-tude, 4700 lbs, and 10 knots headwind component:
Total Distance Over 50-ft Obstacle . . . . . . . . . . . . . 9400 ft
A 2.6% climb gradient is 26 ft of vertical height per 1000 ft ofhorizontal distance.
NOTEThe Take-off Climb Gradient - One-Engine-Inoperative graph assumes zero wind con-ditions. Climbing into a headwind will resultin higher angles of climb, and hence, betterobstacle clearance capabilities.
Calculation of horizontal distance to clear an obstacle 90 ftabove the runway surface:
Horizontal distance used to climb from 50 ft to 90 ft = (90-50) X (1000 ÷ 26) = 1539 ft
Total Distance = 9400 + 1539 = 10,939 ft
5-10
July, 2014
PerformanceSection 5
Model G58
58-590000-67A11_sec05.fm Page 11 Tuesday, July 29, 2014 8:32 AM
The results are illustrated as follows:
FLIGHT TIME, BLOCK SPEED AND FUELREQUIREMENT
CRUISE CLIMB
Enter the TIME, FUEL AND DISTANCE TO CRUISE CLIMBGraph at the takeoff temperature of 15°C and trace up to 5653ft pressure altitude. Then trace right to 5500 lbs. and thendown to obtain the time, fuel, and distance to climb from S.L to5653 ft. Repeat the process starting with the cruise tempera-ture of -5°C, cruise altitude of 11,500 ft, and initial cruiseweight of 5500 lbs. to obtain the time, fuel and distance toclimb from S.L. to 11,500 ft. Subtract the former values fromthe latter values to obtain the time, fuel and distance to climbfrom 5653 ft to 11,500 ft.
5-11July, 2014
Performance Model G58Section 5
58-590000-67A11_sec05.fm Page 12 Tuesday, July 29, 2014 8:32 AM
Time to Climb = (13 - 5) = 8 min
Fuel Used to Climb = (9.5 - 3.9) = 5.6 gal
Distance Traveled = (32 - 11.5) = 20.5 nm
CRUISE
The air temperatures for cruise are presented for 20°C below aStandard Day (ISA -20°C), for a Standard Day (ISA) and for20°C above a Standard Day (ISA +20°C). OAT is used to enterthe Cruise Power Setting tables to determine the enroutecruise power setting. OAT is displayed in the OAT Box locatedin the lower left corner of the PFD. For temperature valuesbetween ISA and ISA ±20°C, interpolate to determine thecruise power setting.
Enter the ISA CONVERSION Graph at 11,500 ft and the truetemperature for the route segment:
Enter the MAXIMUM CRUISE POWER table at 10,000 ft andat 12,000 ft at ISA and ISA + 20°C:
ROUTE SEGMENT OAT ISA CONDITION
LEG A-B -5°C ISA + 3°C
LEG C 0°C ISA + 8°C
LEG D 9°C ISA + 17°C
LEG E 10°C ISA + 18°C
ALTITUDE FEET
TEMPERATURE
ISA ISA + 20°C
FUEL FLOW PER ENG GAL/HR
TASKNOTS
FUEL FLOW PER ENG GAL/HR
TASKNOTS
10,000 14.8 198 14.3 199
12,000 13.8 195 13.3 196
5-12
July, 2014
PerformanceSection 5
Model G58
58-590000-67A11_sec05.fm Page 13 Tuesday, July 29, 2014 8:32 AM
Interpolate for 11,500 ft and the temperature for the appropri-ate route segment. Results of the interpolations are:
Time and fuel used are calculated as follows:
Time = Distance ÷ Ground Speed
Fuel Used = (Distance ÷ Ground Speed) x Fuel Flow
Results are:
* Distance required to climb or descend has been subtractedfrom segment distance.
ROUTESEGMENT
ISA CONDITION FUEL FLOW PER ENG GAL/HR
TASKNOTS
LEG A-B ISA + 3°C 14.0 196
LEG C ISA + 8°C 13.9 196
LEG D ISA + 17°C 13.6 197
LEG E ISA + 18°C 13.6 197
ROUTE SEGMENT
DISTANCENM
EST GROUND SPEEDKNOTS
TIME AT CRUISE
ALTITUDEHRS:MIN
FUEL USED
CRUISEGAL
LEG A *30.5 224 :08.2 3.8
LEG B 40.0 223 :10.8 5.0
LEG C 74.0 182 :24.4 11.3
LEG D 87.0 186 :28.1 12.7
LEG E *22.0 188 :07.0 3.2
TOTAL 253.5 1:19 36.0
5-13July, 2014
Performance Model G58Section 5
5-14
DESCENT
Enter the TIME, FUEL, and DISTANCE TO DESCEND Graphat the cruise pressure altitude of 11,500 ft and trace right to thereference line. Then trace down to obtain the time, fuel, anddistance to descend to S.L. Repeat the process starting withdestination field pressure altitude of 3965 ft. to obtain the time,fuel and distance to descend from 3965 ft to S.L. Subtract theformer values from the latter values to obtain the time, fuel anddistance to descend from 11,500 ft. to 3695 ft.
Time to Descend = (23 - 7.8) = 15.2 min
Fuel Used to Descend = (8.7 - 2.8) = 5.9 gal
Descent Distance = (70 - 22) = 48 NM
TIME - FUEL - DISTANCE SUMMARY
Total Flight Time: 1 hour, 42.2 min
Block Speed: 322 NM ÷ 1 hour, 42.2 min = 189 kts
RESERVE FUEL
Enter the ECONOMY CRUISE POWER table at ISA and ISA +20°C at 10,000 ft and 12,000 ft. Interpolate to find the FuelFlow at 11,500 ft at ISA + 18°C:
ITEM TIMEHRS:MINS
FUELGAL
DISTANCENM
Start, Runup, Taxi, and Take-off acceleration
0:00 4.5 0
Climb 0:08.0 5.6 20.5
Cruise 1:19.0 36.0 253.5
Descent 0:15.2 5.9 48.0
Total 1:42.2 52.0 322.0
July, 2014
58-590000-67A11_sec05.fm Page 14 Tuesday, July 29, 2014 8:32 AM
58-590000-67A11_sec05.fm Page 16 Tuesday, July 29, 2014 8:32 AM
PerformanceSection 5
Model G58
5-17July, 2014
58-590000-67A11_sec05fo.fm Page 1 Tuesday, July 29, 2014 8:36 AM
Performance Model G58Section 5
5-18 July, 2014
58-590000-67A11_sec05fo.fm Page 2 Tuesday, July 29, 2014 8:36 AM
PerformanceSection 5
Model G58
5-19July, 2014
58-590000-67A11_sec05fo.fm Page 3 Tuesday, July 29, 2014 8:36 AM
Performance Model G58Section 5
5-20 July, 2014
58-590000-67A11_sec05fo.fm Page 4 Tuesday, July 29, 2014 8:36 AM
PerformanceSection 5
Model G58
5-21July, 2014
58-590000-67A11_sec05fo.fm Page 5 Tuesday, July 29, 2014 8:36 AM
Performance Model G58Section 5
July, 2014
58-590000-67A11_sec05fo.fm Page 6 Tuesday, July 29, 2014 8:36 AM
5-22
PerformanceSection 5
Model G58
58-590000-67A11_sec05.fm Page 23 Tuesday, July 29, 2014 8:32 AM
5-23July, 2014
Performance Model G58Section 5
5-24 July, 2014
58-590000-67A11_sec05fo.fm Page 7 Tuesday, July 29, 2014 8:36 AM
PerformanceSection 5
Model G58
5-25
July, 2014
58-590000-67A11_sec05.fm Page 25 Tuesday, July 29, 2014 8:32 AM
Performance Model G58Section 5
5-26
July, 2014
58-590000-67A11_sec05.fm Page 26 Tuesday, July 29, 2014 8:32 AM
PerformanceSection 5
Model G58
5-27July, 2014
58-590000-67A11_sec05fo.fm Page 8 Tuesday, July 29, 2014 8:36 AM
Performance Model G58Section 5
July, 2014
58-590000-67A11_sec05fo.fm Page 9 Tuesday, July 29, 2014 8:36 AM
5-28
PerformanceSection 5
Model G58
5-29July, 2014
58-590000-67A11_sec05fo.fm Page 10 Tuesday, July 29, 2014 8:36 AM
Performance Model G58Section 5
July, 2014
58-590000-67A11_sec05fo.fm Page 11 Tuesday, July 29, 2014 8:36 AM
5-30
PerformanceSection 5
Model G58
5-31July, 2014
58-590000-67A11_sec05fo.fm Page 12 Tuesday, July 29, 2014 8:36 AM
Performance Model G58Section 5
July, 2014
58-590000-67A11_sec05fo.fm Page 13 Tuesday, July 29, 2014 8:36 AM
5-32
PerformanceSection 5
Model G58
58-590000-67A11_sec05.fm Page 33 Tuesday, July 29, 2014 8:32 AM
SERVICE CEILING - ONE-ENGINE-INOPERATIVECLIMB SPEED: 101 KNOTS (ALL WEIGHTS)
ASSOCIATED CONDITIONS:
POWER MAXIMUM CONTINUOUSLANDING GEAR UPINOPERATIVE PROPELLER FEATHEREDFLAPS UPMIXTURE AS REQUIRED BY ALTITUDE
EXAMPLE:
OAT -20°CWEIGHT 4700 LBSSERVICE CEILIN 12,015 FT
NOTE: ONE-ENGINE-INOPERATIVE SERVICE CEILING IS THE MAXIMUM PRESSURE ALTITUDE AT WHICH THE AIRPLANE HAS THE CAPABILITY OF CLIMBING AT 50 FT/MINUTE WITH ONE PROPELLER FEATHERED.
5-33July, 2014
Performance Model G58Section 5
5-34 July, 2014
58-590000-67A11_sec05fo.fm Page 14 Tuesday, July 29, 2014 8:36 AM
PerformanceSection 5
Model G58
58-590000-67A11_sec05.fm Page 35 Tuesday, July 29, 2014 8:32 AM
THIS PAGE INTENTIONALLY LEFT BLANK
5-35July, 2014
Performance Model G58Section 5
58-590000-67A11_sec05.fm Page 36 Tuesday, July 29, 2014 8:32 AM
NOTES: 1. Full throttle manifold pressure settings are approximate.2. Shaded area represents operation with full throttle.3. Fuel flows are to be used for flight planning only and will vary from airplane to airplane. Lean using the EGT.
NOTES: 1. Full throttle manifold pressure settings are approximate.2. Shaded area represents operation with full throttle.3. Fuel flows are to be used for flight planning only and will vary from airplane to airplane. Lean using the EGT.
NOTES: 1. Full throttle manifold pressure settings are approximate.2. Shaded area represents operation with full throttle.3. Fuel flows are to be used for flight planning only and will vary from airplane to airplane. Lean using the EGT.
NOTES: 1. Full throttle manifold pressure settings are approximate.2. Shaded area represents operation with full throttle.3. Fuel flows are to be used for flight planning only and will vary from airplane to airplane. Lean using the EGT.
11.211.712.212.712.511.510.710.0
9.310.711.211.712.212.011.210.3
9.79.0
10.310.811.311.711.510.710.0
9.38.7
July, 2014
58-590000-67A11_sec05.fm Page 39 Tuesday, July 29, 2014 8:32 AM
Performance Model G58Section 5
5-40
July, 2014
58-590000-67A11_sec05.fm Page 40 Tuesday, July 29, 2014 8:32 AM
PerformanceSection 5
Model G58
5-41
July, 2014
58-590000-67A11_sec05.fm Page 41 Tuesday, July 29, 2014 8:32 AM
Performance Model G58Section 5
5-42 July, 2014
58-590000-67A11_sec05fo.fm Page 15 Tuesday, July 29, 2014 8:36 AM
PerformanceSection 5
Model G58
5-43
58-590000-67A11_sec05fo.fm Page 16 Tuesday, July 29, 2014 8:36 AM
July, 2014
Performance Model G58Section 5
5-44 July, 2014
58-590000-67A11_sec05fo.fm Page 17 Tuesday, July 29, 2014 8:36 AM
PerformanceSection 5
Model G58
5-45
58-590000-67A11_sec05fo.fm Page 18 Tuesday, July 29, 2014 8:36 AM
July, 2014
Performance Model G58Section 5
5-46 July, 2014
58-590000-67A11_sec05fo.fm Page 19 Tuesday, July 29, 2014 8:36 AM
PerformanceSection 5
Model G58
5-47
58-590000-67A11_sec05fo.fm Page 20 Tuesday, July 29, 2014 8:36 AM
July, 2014
Performance Model G58Section 5
5-48 July, 2014
58-590000-67A11_sec05fo.fm Page 21 Tuesday, July 29, 2014 8:36 AM
PerformanceSection 5
Model G58
5-49
58-590000-67A11_sec05fo.fm Page 22 Tuesday, July 29, 2014 8:36 AM
July, 2014
Performance Model G58Section 5
HOLDING TIME(APPLICABLE FOR ALL TEMPERATURES)
ASSOCIATED CONDITIONS:
POWER SETTINGS 21 IN. HG OR FULL THROTTLE AT 2100 RPM
MIXTURE 20°C LEAN OF PEAK EGTWEIGHT 5200 LBS
EXAMPLE:
FUEL AVAILABLE FORHOLDING 50 GAL
PRESSURE ALTITUDE 11,500 FTHOLDING TIME 2.6 HRS
July, 2014
58-590000-67A11_sec05.fm Page 50 Tuesday, July 29, 2014 8:32 AM
5-50
PerformanceSection 5
Model G58
5-51
58-590000-67A11_sec05.fm Page 51 Tuesday, July 29, 2014 8:32 AM
July, 2014
Performance Model G58Section 5
July, 2014
58-590000-67A11_sec05fo.fm Page 23 Tuesday, July 29, 2014 8:36 AM
5-52
PerformanceSection 5
Model G58
5-53
58-590000-67A11_sec05fo.fm Page 24 Friday, August 1, 2014 11:06 AM
July, 2014
Performance Model G58Section 5
THIS PAGE INTENTIONALLY LEFT BLANK
July, 2014
58-590000-67A11_sec05.fm Page 54 Tuesday, July 29, 2014 8:32 AM