euops gulfstream 200, pw 306a

7/24/2019 EUOPS Gulfstream 200, PW 306A

1/10

Aircraft Performance Group, Inc

April 29, 20131

GULFSTREAM 200

PW 306A

INTRODUCTION

Runway Analysis provides the means to determine maximum allowable takeoff and landing

weights based upon:

Airport characteristics consisting of airport elevation, runway gradient and length,

runway contaminants, and the obstructions within the takeoff flight path,

Environmental conditions consisting of temperature, wind, and pressure altitude.

Aircraft Configurations consisting of power settings, flap settings, bleed configurations,

and Minimum Equipment List (MEL) inoperative components.

The performance and limitations are as outlined in the approved Airplane Flight Manual (AFM)

for the specific aircraft considered. All takeoff and landing airport analysis data provided byAircraft Performance Group complies with EU-OPS regulations.

TAKEOFF

The maximum allowable takeoff weight is obtained by selecting the most limiting of thefollowing:

1. Maximum certified takeoff structural weight.

2.

Climb limited weight the maximum weight at which the appropriate airworthiness

climb gradients, for each takeoff segment, are attained for airport elevation and

temperature.

3. Runway field length limit weight the maximum weight at which the aircraft

complies with the appropriate airworthiness rules governing runway length, runwaygradient (slope), airport elevation, temperature, wind, pressure altitude, and runway

contamination.

4. Obstruction limited weight the maximum weight at which obstruction clearance

required by the appropriate airworthiness rules can be attained. The obstruction limit

weight is a function of aircraft configuration, obstacle height and distance, airportelevation, temperature, and wind. Unless otherwise stated, all takeoffs assume a

straight out takeoff flight path along the extended runway centerline.

5. Brake energy the maximum weight at which the aircraft brakes can absorb theamount of energy required to stop the aircraft.


2/10


3/10


April 29, 20133

TAKEOFF PERFORMANCE CHART

DESCRIPTION / DEFINITIONS

GULFSTREAM 200 PW 306A

1. Chart Heading

The chart heading specifies the performance outlined (takeoff or landing), the airport byIdentifier, City/State, and Airport Name, the airport elevation, and the Aircraft type and Engine.

2. Aircraft Configuration

Aircraft configurations upon which the attached data is based on are presented in this block.Aircraft configurations consist of the following:

Takeoff flaps settings:0 Degrees, 12 Degrees and 20 Degrees

0 Degrees, 12 Degrees and 20 Degrees WET

0 Degrees, 12 Degrees and 20 Degrees Contaminated runway and

Compact snow

3. Special Departure Procedure

Some runways/airports require a Special Departure Procedure in order to optimize takeoff

weight in terrain sensitive areas. The specific description of the Special Departure Procedure is

outlined on a separate page attached to the takeoff airport analysis. These procedures describethe non-standard, one engine inoperative, departure flight path. The maximum allowable takeoff

weights, presented in the subsequent analysis, are based upon the specific procedure(s) outlined.

If there is no DP attached to the runway identifier, the takeoff weights are predicated upon a

STRAIGHT OUT departure.

4. Runway Identifier

The runway identifier is specified as follows:

Full length runways indicated by basic identifier i.e. 34L

Intersection takeoffs include hyphen - i.e. 34L-A takeoff from intersection A Temporary runway lengths / closures include TMP, i.e. 34LTMP

Special Departure Procedures include DP i.e. 34LDP

Declared distances used:

Takeoff Run Available (TORA)

Takeoff Distance Available (TODA) Accelerate Stop Distance Available (ASDA)

Associated runway slope/gradient (percent)


4/10


April 29, 20134

5. OAT

This is the surface temperature, in degrees Celsius, upon which the performance data is based.

The maximum temperature shown on the chart corresponds to the maximum operational

temperature for airport elevation.

6. Takeoff Thrust Setting

Engine Power (N1) settings for airport surface temperature and airport altitude are displayed for

both Engine Anti-ice ON and OFF.

7. Zero Wind Runway Limit Weight, Limit Code

The zero wind runway limit weight displayed is the lowest of the following:

1. One Engine Inoperative Accelerate / Stop Limitations.

2.

One Engine Inoperative Accelerate / GO limitations.3. All Engine Operating Field limitations.4. Minimum Control limitations.

5. Brake Energy limitations.

6. Tire Speed limitations.

7. Obstacle Clearance limitations.8. Flight Path / Level-off Altitude limitations.

The limit codes associated with the zero wind runway limits are as follows:

ST = Structural LimitFL = Field Length Limit

-O = Obstacle Limit

TS = Tire Speed LimitBE = Brake Energy Limit

MC = Minimum Control Speed Limit

FP = Flight Path / Level-Off Altitude Limit

8. Climb Limit Weight

The climb limit is a weight that meets the minimum climb gradients required for each takeoffflight path segment as defined in the certification regulations. The climb limit is determined from

the applicable TAKEOFF WEIGHT LIMITED BY CLIMB REQUIREMENTS chart within

the AFM. The climb limit is dependent upon reported surface temperature and airport altitudeonly.

THE LIMITING TAKEOFF WEIGHT IS THE LOWER OF THE RUNWAY LIMIT

WEIGHT, THE CLIMB LIMIT WEIGHT, OR THE MAXIMUM CERTIFIED

STRUCTURAL LIMIT WEIGHT.


5/10


April 29, 20135

CORRECTIONS

Corrections may be available to the zero wind runway limit weight and/or the Climb limit

weight. A zero (0) may appear as a correction, which indicates that the adjustment item requires

no correction. An NA may appear as a correction, which indicates that the adjustment item is

NOT AUTHORIZED for operations.

9. Wind Corrections

Corrections to the runway limit weight may be made for Headwind and must be made for

Tailwind. Multiply the associated figure (HW+LBS/KT or TWLBS/KT) or (HW+KGS/KT or

TWKGS/KT) by the number of knots of steady state Headwind or number of knots of steadystate plus gusts of Tailwind. The resulting figure should be added/subtracted to/from the zero

wind runway limit weight.

10. QNH / Non-Standard Altimeter Corrections

Corrections to the runway limit weight may be made for high QNH (pressure) and must be made

for low QNH (pressure). Multiply the associated correction factor for high pressure(QNH+LBS/.1 or QNH+KGS/mb) or for low pressure (QNH-LBS/.1 or QNH-KGS/mb) by the

difference in the altimeter setting from the standard (29.92 or 1013). The resulting amount

should be added (high pressure) or subtracted (low pressure) from the zero wind runway limitweight to correct for non-standard pressure.

11. Anti-ice ON Corrections

If the Anti-ice system is to be selected ON for takeoff, a weight penalty must be applied.

Subtract the associated figure (ANTIICE ON-LBS or ANTIICE ON-KGS) from the runwaylimit/climb limit weight after considering wind and temperature as described above. The

resulting figure is the runway limit/climb limit weight with Anti-ice ON.

12. Thrust Reverser Inoperative Corrections (Wet Runway Only)

If the Thrust Reverser is inoperative, a weight penalty must be applied. Subtract the associatedfigure (THRST REV INOP-LBS or THRST REV INOP-KGS) from the runway limit weight

after considering wind and temperature as described above. The resulting figure is the runway

limit weight with Thrust Reverser inoperative.

13. Acceleration Altitude (MSL)

The standard level-off height for flap retraction and acceleration to final climb speed is 1500 feetabove ground level (AGL). In some cases, it may be necessary to extend the second segment

climb to a nonstandard altitude in order to achieve obstacle clearance prior to level-off

/acceleration. The required Acceleration Altitude, in feet MSL, is indicated below the specificrunway limit weights.


6/10


April 29, 20136

14. Structural Limits Note

The maximum takeoff weight for runway limits and climb limits may exceed the Maximum

Structural weight of the aircraft up to the limits provided by AFM charts. This is in order to

apply penalty items without impacting maximum allowable takeoff weight in some cases. The

note at the bottom of the page is a reminder to indicate that:

THE LIMITING TAKEOFF WEIGHT IS THE LOWER OF THE RUNWAY LIMIT

WEIGHT, THE CLIMB LIMIT WEIGHT, OR THE MAXIMUM CERTIFIED

STRUCTURAL LIMIT WEIGHT.

15. Date

Indicates the date the performance chart was prepared.


7/10

-- THF -EDDI -- TAKEOFF PERFORMANCE -- THF -EDDI --

GULFSTREAM 200 BERLIN, DEU

ELEVATION 167 PW 306A ENG TEMPELHOF

TAKEOFF FLAPS 0.0 DEGREES

RUNWAY 09L 27R

TORA(FT) 5118 5577

TODA(FT) 5118 5577 CLIMB

ASDA(FT) 6870 6870

SLOPE(%) 0.25 -0.34 LIMIT

TMP N1%RPM

DEG C A/I A/I RUNWAY-OBSTACLE LIMIT WEIGHT/LIMIT CODE

OFF ON

-20 93.1/ 93.1 31386 FL 33199 -O 35450.

-15 94.0/ 94.0 31137 FL 32951 FL 35450.

-10 94.9/ 95.0 30888 FL 32693 FL 35450.

-5 95.8/ 95.9 30554 FL 32363 FL 35450.

0 96.7/ 96.8 30392 FL 32188 FL 35450.

2 97.1/ 97.1 30293 FL 32086 FL 35450.

4 97.4/ 97.4 30193 FL 31984 FL 35450.

6 97.8/ 97.6 30091 FL 31880 FL 35450.

8 98.1/ 97.9 29988 FL 31774 FL 35450.

10 98.5/ 97.9 29884 FL 31669 FL 35450.

12 98.8 29770 FL 31556 FL 35450.

14 99.2 29656 FL 31442 FL 35450.

16 99.5 29538 FL 31322 FL 35450.

18 99.7 29415 FL 31195 FL 35450.

20 99.9 29293 FL 31067 FL 35450.

22 99.7 29019 FL 30772 FL 35450.

24 99.4 28745 FL 30477 FL 35450.

26 99.1 28430 FL 30137 FL 35450.

28 98.7 28072 FL 29752 FL 35450.

30 98.3 27715 FL 29367 FL 35450.

32 98.0 27360 FL 28986 FL 35450.

34 97.6 27004 FL 28604 FL 35450.

36 97.3 26670 FL 28250 FL 35450. 38 97.1 26358 FL 27924 FL 35450.

40 96.8 26045 FL 27598 FL 35450.

45 96.2 25274 FL 26816 FL 34458.

49 95.6 NA NA NA NA 33238.

HW +LBS/KT 55 53

TW -LBS/KT 153 133

QNH +LBS/.1 21 22

QNH -LBS/.1 91 96

ANTI ICE ON-LBS 1430 1760 0

ACCEL ALT (MSL) 1670 1670

*** INCLUDES AFM REVISION 15 - EXTENDED SECOND SEGMENT CLIMB CAPABILITY ***

*** OBSERVE STRUCTURAL LIMITS *** 29Apr13


8/10


April 29, 20138

LANDING PERFORMANCE CHART

DESCRIPTION / DEFINITIONS

GULFSTREAM 200 PW 306A

1. Chart Heading

The chart heading specifies the performance outlined (takeoff or landing), the airport by

Identifier, City/State, and Airport Name, the airport elevation, and the Aircraft type andEngine.

2. Approach Climb Limits

The approach climb limit weights meet the minimum climb gradients required for the

approach climb (go-around) phase of landing as defined in the certification regulations.The approach climb limit weights are determined from the applicable Landing Weight

Permitted by Climb Requirements Charts within the AFM. The approach climb limit is

dependent upon reported surface temperature and airport altitude only. Corrections aredisplayed for Anti-ice ON.

3. Aircraft/Runway Configuration for Landing

Landing data is provided for the following aircraft/runway configurations:

Landing Flaps 40

Anti Skid Operative and InoperativeLanding Distance factors 60% and Unfactored

Dry and Wet runways.

4. Runway Identifier

The runway identifier is specified as follows:

Full length runways indicated by basic identifier i.e. 34L

Temporary runway lengths / closures include TMP, i.e. 34LTMP

Declared Distances used:

Landing Distance Available (LDA)

Associated effective runway slope/gradient.

5. Landing Runway Limit Weight

The runway limit weight for landing distance available is displayed corresponding to

given wind component and aircraft/runway configuration.

THE LIMITING LANDING WEIGHT IS THE LOWER OF THE RUNWAY

LIMIT WEIGHT, THE APPROACH CLIMB LIMIT WEIGHT, OR THE

MAXIMUM CERTIFIED STRUCTURAL LIMIT WEIGHT.


9/10


April 29, 20139

6. Quick Turnaround Information

The critical temperature (CRTP) is the highest temperature that the aircraft can be landed

at maximum landing weight andmake a quick turnaround. At temperatures above the

CRTP the weight must be reduced by the amount (SUB LB or SUB KG)for each degree

Cabove the critical temperature, for the given wind component. After landing at weightsin excess of the Quick Turnaround landing weight, perform a visual inspection and wait

the manufacturers required time before making a subsequent takeoff.

7. Temperature Correction

The landing field length data is calculated at 15 degrees Centigrade. For temperaturesless than () 15C, a

penalty must be applied. Multiply the associated figure (15C-

LBS/DEGC) or (15C-KGS/DEGC) by the number of degrees Cbelow 15C or above 15C. The resulting figure should be added to or subtracted from the

runway limit weight.

8. Date

Indicates the date the performance chart was prepared.


10/10

-- THF -EDDI -- LANDING PERFORMANCE -- THF -EDDI --

GULFSTREAM 200 BERLIN, DEU

ELEVATION 167 PW 306A ENG TEMPELHOF

*** APPROACH CLIMB LIMITS - APPROACH FLAPS 20 ***

CLIMB PERFORMANCE NOT LIMITING BELOW 49 (C)

TEMP(C) -20 0 10 20 25 30 35 40 45 49

CLMB WT 30000. 30000. 30000. 30000. 30000. 30000. 30000. 30000. 30000. 30000.

ENG A/I 30000. 30000. 30000. NA NA NA NA NA NA NA

*** LANDING FIELD LENGTH LIMITS ***

*** ENGINE ANTI-ICE AND SURFACE DE-ICE OFF ***

______________________________________________________________________________

RUNWAY | *** LANDING FLAPS - 40 *** | QUICK |

LENGTH WIND| ANTI SKID OPERATIVE | ANTI SKID INOPERATIVE | TURN |

SLOPE | JAR 60% FCTR| UNFACTORED | JAR 60% FCTR| UNFACTORED | CRTP SUB |

| DRY WET | DRY WET | DRY WET | DRY WET | DEGC LBS |

______________________________________________________________________________

-10| 25251 20863 | 30000 30000 | NA NA | 30000 30000 | 21 55 |

-5| 27828 23161 | 30000 30000 | 22007 NA | 30000 30000 | 45 7 |

09L | | | | | |

5466FT 0| 30000 25484 | 30000 30000 | 24269 20215 | 30000 30000 | 49 0 |

0.25 | | | | | |

10| 30000 27349 | 30000 30000 | 26070 21815 | 30000 30000 | 49 0 |

20| 30000 29265 | 30000 30000 | 27908 23513 | 30000 30000 | 49 0 |

15C-LB/DEGC| 84 70 | 0 0 | 66 55 | 0 0 | |

______________________________________________________________________________

-10| 22214 NA | 30000 30000 | NA NA | 30000 28203 | 17 54 |

-5| 24513 20426 | 30000 30000 | NA NA | 30000 30000 | 43 49 |

27R | | | | | |

5180FT 0| 26824 22493 | 30000 30000 | 21445 NA | 30000 30000 | 49 0 |

-0.34 | | | | | |

10| 28720 24160 | 30000 30000 | 23047 NA | 30000 30000 | 49 0 |

20| 30000 25840 | 30000 30000 | 24695 20855 | 30000 30000 | 49 0 |

15C-LB/DEGC| 73 62 | 0 0 | 59 48 | 0 94 | |

______________________________________________________________________________

29Apr13

euops gulfstream 200, pw 306a

Documents