SECTION 5 PERFORMANCE - Beechcraftbeechcraft.com/customer_support/technical_publications/docs... · SECTION 5 PERFORMANCE ... The wings, stabilizers, and all control surfaces must

Model G58

5-1

SECTION 5PERFORMANCE

TABLE OF CONTENTS

SUBJECT PAGE

Introduction To Performance . . . . . . . . . . . . . . . . . . . . . 5-5Performance In Icing Conditions . . . . . . . . . . . . . . . . . . . 5-5How To Use The Graphs . . . . . . . . . . . . . . . . . . . . . . . . . 5-6

Example Calculations . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-7Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-7

Pressure Altitude . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-8Take-Off Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-8Take-Off Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-9Flight Time, Block Speed and Fuel Requirement. . . . . . 5-11

Cruise Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-11 . . . . . . . . . . . . . . . . . . . . . . . 5-12 . . . . . . . . . . . . . . . . . . . . . . . 5-14 . . . . . . . . . . . . . . . . . . . . . . . 5-14 . . . . . . . . . . . . . . . . . . . . . . . 5-15 . . . . . . . . . . . . . . . . . . . . . . . 5-15erformance . . . . . . . . . . . . . . 5-15

al System . . . . . . . . . . . . . . 5-17al System . . . . . . . . . . . . . . 5-18rgency System. . . . . . . . . . . 5-19rgency System . . . . . . . . . . . 5-20 . . . . . . . . . . . . . . . . . . . . . . . 5-21perature Conversion. . . . . . . 5-22 . . . . . . . . . . . . . . . . . . . . . . . 5-23. . . . . . . . . . . . . . . . . . . . . . . 5-24

. . . . . . . . . . . . . . . . . . . . . . . 5-25

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April, 2012

Cruise . . . . . . . . . . . . . .Descent . . . . . . . . . . . .Reserve Fuel . . . . . . . .Total Fuel Required . . .Landing. . . . . . . . . . . . .Balked Landing Climb P

Graphs:

Airspeed Calibration - NormAltimeter Correction - NormAirspeed Calibration - EmeAltimeter Correction - EmeISA Conversion . . . . . . . .Fahrenheit to Celsius TemStall Speeds - Power Idle .Manifold Pressure vs RPMTake-Off Weight . . . . . . . .

Model G58

April, 2012


TABLE OF CONTENTS (CONT’D)

SUBJECT PAGE

Wind Components. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-26Take-Off Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-27Accelerate-Stop Distance . . . . . . . . . . . . . . . . . . . . . . . 5-28Accelerate-Go Distance . . . . . . . . . . . . . . . . . . . . . . . . 5-29Take-Off Climb Gradient - One Engine Inoperative . . . 5-30Climb - Two Engine. . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-31Climb - One Engine Inoperative . . . . . . . . . . . . . . . . . . 5-32Service Ceiling - One-Engine-Inoperative. . . . . . . . . . . 5-33Time, Fuel, and Distance to Cruise Climb. . . . . . . . . . . 5-34

Tables:

Rich . . . . . . . . . . . . . . . . . . 5-36er

Lean . . . . . . . . . . . . . . . . . . 5-37Rich . . . . . . . . . . . . . . . . . . 5-38Lean . . . . . . . . . . . . . . . . . . 5-39

. . . . . . . . . . . . . . . . . . . . . . . 5-40

. . . . . . . . . . . . . . . . . . . . . . . 5-41s - Rich . . . . . . . . . . . . . . . . 5-42s - Lean. . . . . . . . . . . . . . . . 5-43llons - Rich. . . . . . . . . . . . . 5-44llons - Lean . . . . . . . . . . . . 5-45

s - Rich . . . . . . . . . . . . . . . . 5-46s - Lean. . . . . . . . . . . . . . . . 5-47


5-2

Maximum Cruise Power25 in. Hg @ 2500 RPM,

Recommended Cruise Pow25 in. Hg @ 2500 RPM, 23 in. Hg @ 2300 RPM, 23 in. Hg @ 2300 RPM,

Graphs:

Cruise Speeds - Rich . . . Cruise Speeds - Lean . . . Range Profile - 166 GallonRange Profile - 166 GallonEndurance Profile - 166 GaEndurance Profile - 166 GaRange Profile - 194 GallonRange Profile - 194 Gallon

Model G58

5-3


TABLE OF CONTENTS (CONT’D)

SUBJECT PAGE

Endurance Profile - 194 Gallons - Rich . . . . . . . . . . . . . 5-48Endurance Profile - 194 Gallons - Lean . . . . . . . . . . . . . 5-49Holding Time . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-50Time, Fuel, and Distance to Descend . . . . . . . . . . . . . . 5-51Climb - Balked Landing . . . . . . . . . . . . . . . . . . . . . . . . . 5-52Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-53


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Section 5

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Performance


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Section 5

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PerformanceModel G58

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.

5-5December, 2009

Section 5


Performance Model G58

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 December, 2009

Section 5



EXAMPLE CALCULATIONS

The calculations for flight time, block speed and fuel requiredfor a proposed flight are listed below:

CONDITIONS

At Departure: Outside Air Temperature . . . . . . . . . . . . . . . . . . . .15°C (59°F) Field Elevation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .5333 ft Altimeter Setting . . . . . . . . . . . . . . . . . . . . . . . . .29.60 in. Hg Runway 26L Length . . . . . . . . . . . . . . . . . . . . . . . . 10,004 ft Wind . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 300° at 13 kts

At Destination: Outside Air Temperature . . . . . . . . . . . . . . . . . . .25°C (77°F) Field Elevation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3605 ft Altimeter Setting . . . . . . . . . . . . . . . . . . . . . . . . .29.56 in. Hg Wind . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 190° at 12 kts Runway 22 Length . . . . . . . . . . . . . . . . . . . . . . . . . 13,502 ft

ROUTE SEGMENT

AVERAGE MAGNETIC COURSE

AVERAGE MAGNETIC VARIATION

DIST NM

WIND AT 11,500 FEET

DIR/KTS

OAT 11,500

FEET °C

LEG A 155° 12°E 51 010°/30 -5

LEG B 153° 12°E 40 010°/30 -5

LEG C 135° 12°E 74 100°/20 0

LEG D 132° 11°E 87 200°/20 9

LEG E 126° 10°E 70 200°/20 10

5-7December, 2009

Section 5



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 ft abovethe 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 December, 2009

Section 5



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: Ground Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2200 ft Total Distance over 50-ft Obstacle . . . . . . . . . . . . . .3775 ft

Enter the Accelerate-Stop graph at 15°C, 5653 ft pressure alti-tude, 5500 lbs, and 10 knots headwind component: Accelerate-Stop Distance . . . . . . . . . . . . . . . . . . . . .3960 ft

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.

5-9December, 2009

Section 5



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 Ground Roll Distance. . . . . . . . . . . . . . . . . . . . . . . . 3760 ft

Enter the graph for Take-Off Climb Gradient - One-Engine-Inoperative at 15°C, 5653 ft pressure altitude, and 4700 lbs: Climb Gradient . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.6%

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 December, 2009

Section 5

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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.

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Section 5

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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

Document Date

5-12

April, 2012

Section 5



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

5-13December, 2009


Section 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

December, 2009


PerformanceSection 5

Model G58

5-15

Total Fuel Flow . . . . . . . . . . . . . . . . . . . . . . . . . . . 17.4 gph

Reserve Fuel (45 minutes) (17.4 gph). . . . . . . . . . . 13.1 gal

TOTAL FUEL REQUIRED

Total Fuel Required = Calculated Fuel Usage + Reserve Fuel

Total Fuel Required

= 52.0 + 13.1 = 65.1 gal

LANDING

The estimated landing weight is determined by subtracting thefuel required for the trip from the ramp weight:

Assumed Ramp Weight. . . . . . . . . . . . . . . . . . . . . 5524 lbs

Estimated Fuel (52.0 gal at 6 lbs/gal) . . . . . . . . . . . 312 lbs

Estimated Landing Weight (5524 - 312) . . . . . . . . 5212 lbs

NOTEFor the Landing Distance example, a 5039lbs weight and a 9.5 kts headwind compo-nent were assumed.

Enter the LANDING DISTANCE graph at 25°C, 3965 ft pres-sure altitude, 5039 lbs landing weight an 9.5 kts headwindcomponent:

Ground Roll . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .1450 ft

Total Distance over 50 ft. Obstacle . . . . . . . . . . . . . .2500 ft

Approach Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91 kts

BALKED LANDING CLIMB PERFORMANCE

NOTEFor the Balked Landing Climb performanceexample, a weight of 5166 lbs wasassumed.

December, 2009



Section 5

5-16

Enter the CLIMB-BALKED LANDING graph at 25°C, 3965 ftpressure altitude and 5166 lbs:

Rate-of-Climb. . . . . . . . . . . . . . . . . . . . . . . . . . . . 765 ft/min

Climb Gradient . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.9%

December, 2009



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Performance Model G58Section 5

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Model G58

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Model G58

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5-32

Section 5



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 -2CWEIGHT 4700 LBSSERVICE CEILING 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 PRO-PELLER FEATHERED.

5-33December, 2009


5-34 December, 2009


Section 5



THIS PAGE INTENTIONALLY LEFT BLANK

5-35

Document Date

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December, 2009

Section 5



TH05C120028AA.AI

CRUISE POWER SETTINGS

MAXIMUM CRUISE POWER25 IN. HG (OR FULL THROTTLE)

@ 2500 RPM (5200 LBS.)

ISA

- 20°

C (I

SA -

36° F

)ST

AN

DA

RD

DAY

(ISA

)IS

A +

20° C

(ISA

+ 3

6° F

)

20°C RICH

SL2000400060008000

10,00012,00014,00016,000

SL2000400060008000

10,00012,00014,00016,000

SL2000400060008000

10,00012,00014,00016,000

187193199200198196194191187188195201202200198195192188

190196202203201199196193188

194195196191184177169162154189190191186179171162156148

184185185181173166159151143

101105109105

989286807498

101105102

9589837772

9598

101989286807570

252525242221191816252525242221191816

252525242221191816

2316

92

-6-13-20-27-3459524538302316

92

958881746659524538

-5-9

-13-17-21-25-29-33-37151173

-1-5-9

-13-17

3531272319151173

PRESS.ALT.

MAN.PRESS.OAT

FUEL FLOW/ENGINE

AIR-SPEED

OF PEAK EGT

FEET °C °F IN. HG PPH GPH KIAS KTAS

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.

16.817.518.217.516.315.314.313.312.316.316.817.517.015.814.813.812.812.0

15.816.316.816.315.314.313.312.511.7

5 - 36

Document Date

5-36

April, 2012

Section 5



TH05C120029AA.AI


RECOMMENDED CRUISE POWER25 IN. HG (OR FULL THROTTLE)

@ 2500 RPM (5200 LBS.)

ISA

- 20°

C (I

SA -

36° F

)ST

AN

DA

RD

DAY

(ISA

)IS

A +

20° C

(ISA

+ 3

6° F

)

20°C LEAN

SL2000400060008000

10,00012,00014,00016,000

SL2000400060008000

10,00012,00014,00016,000

SL2000400060008000

10,00012,00014,00016,000

182188194195193191188185181184190196197195193190186182

185191197198196192190187182

189191191186179172164157149184185186181174167159152143

179180181176169161154146138

879194918478726762848791888175706560

818487847872676258

252525242221191816252525242221191816

252525242221191816

2316

92

-6-13-20-27-3459524538302316

92

958881746659524538

-5-9

-13-17-21-25-29-33-37151173

-1-5-9

-13-17

3531272319151173

PRESS.ALT.

MAN.PRESS.OAT

FUEL FLOW/ENGINE

AIR-SPEED

OF PEAK EGT



14.515.215.715.214.013.012.011.210.314.014.515.214.713.512.511.710.810.0

13.514.014.514.013.012.011.210.3

9.7

5-37

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April, 2012


Section 5

5 - 38

Document Date

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TH05C120030AA.AI



@ 2300 RPM (5200 LBS.)

ISA

- 20°

C (I

SA -

36° F

)ST

AN

DA

RD

DAY

(ISA

)IS

A +

20° C

(ISA

+ 3

6° F

)

20°C RICH

SL2000400060008000

10,00012,00014,00016,000

SL2000400060008000

10,00012,00014,00016,000

SL2000400060008000

10,00012,00014,00016,000

170176182188190188185182178171177183190192189186183178

171178184191193190187182178

176178179180177169162154146171173174175171164156149140

166168169169166159151143135

818487918984787368787985888781767166

767982858478736864

232323232221191817232323232221191817

232323232221191817

2316

92

-6-13-20-27-3459524538302316

92

958881746659524538

-5-9

-13-17-21-25-29-33-37151173

-1-5-9

-13-17

3531272319151173

PRESS.ALT.

MAN.PRESS.OAT

FUEL FLOW/ENGINE

AIR-SPEED

OF PEAK EGT



13.514.014.515.214.814.013.012.211.313.013.514.214.714.513.512.711.811.0

12.713.213.714.214.013.012.211.310.7

April, 2012


Performance

Section 5

Model G58

5-39

Document Date

5-39

TH05C120031AA.AI



@ 2300 RPM (5200 LBS.)

ISA

- 20°

C (I

SA -

36° F

)ST

AN

DA

RD

DAY

(ISA

)IS

A +

20° C

(ISA

+ 3

6° F

)

20°C LEAN

SL2000400060008000

10,00012,00014,00016,000

SL2000400060008000

10,00012,00014,00016,000

SL2000400060008000

10,00012,00014,00016,000

164170176182184182179176171165171177184185183180176171

166172178184186182180175169

171172173174171164156149140166167168169166158151143135

161162163164160153145137128

677073767569646056646770737267625854

626568706964605652

232323232221191817232323232221191817

232323232221191817

2316

92

-6-13-20-27-3459524538302316

92

958881746659524538

-5-9

-13-17-21-25-29-33-37151173

-1-5-9

-13-17

3531272319151173

PRESS.ALT.

MAN.PRESS.OAT

FUEL FLOW/ENGINE

AIR-SPEED

OF PEAK 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

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Performance

Section 5

Model G58

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Section 5

Document Date

HOLDING TIME(APPLICABLE FOR ALL TEMPERATURES)

ASSOCIATED CONDITIONS:

POWER SETTINGS 21 IN. HGOR FULL THROTTLEAT 2100 RPM

MIXTURE 20C LEAN OF PEAK EGTWEIGHT 5200 LBS

EXAMPLE:

FUEL AVAILABLE FORHOLDING 50 GAL

PRESSURE ALTITUDE 11,500 FTHOLDING TIME 2.6 HRS

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Section 5

Model G58

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Document Date

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Section 5

Document Date

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Documents

SECTION 5 PERFORMANCE - Beechcraftbeechcraft.com/customer_support/technical_publications/docs... · SECTION 5 PERFORMANCE ... The wings, stabilizers, and all control surfaces must