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Premier Aircraft, LLC Doc. No. FTA-PA-001019 Rev I/R 18 Terminal Dr. East Alton, IL 62024

FAA APPROVED

AIRPLANE FLIGHT MANUAL SUPPLEMENT

For

Dassault Aviation

Mystere-Falcon 50

With

HONEYWELL TFE 731-4-1C TURBO FAN ENGINES

And

DIGITAL ELECTRONIC ENGINE CONTROL (N1 DEEC)

Serial No.________ Reg. No._________

This Supplement must be attached to the FAA Approved Airplane Flight Manual when the airplane is modified by the installation of Honeywell TFE 731-4-1C Turbo Fan Engines and Digital Electronic Engine Control (N1 DEEC) in accordance with technical data approved by STC ST01951LA.

The information contained herein supplements or supersedes the basic manual only in those areas listed herein. For Limitations, Procedures, and Performance information not contained in this Supplement, consult the basic Airplane Flight Manual.

FAA APPROVED ________________________________

Manager, Flight Test Branch, ANM-160L Federal Aviation Administration Los Angeles Aircraft Certification Office Transport Airplane Directorate

DATE:

Premier Aircraft, LLC Doc. No. FTA-PA-001019 Rev A 18 Terminal Dr. East Alton, IL 62024

AFM Supplement

FAA Approved Date: August 23, 2007 i

PAGE INTENTIONALLY LEFT BLANK

Premier Aircraft, LLC Doc. No. FTA-PA-001019 Rev B 18 Terminal Dr. East Alton, IL 62024

AFM Supplement

ii

LOG OF REVISIONS

REV. NO.

EFFECTED PAGES

DATE DESCRIPTION FAA APPROVAL

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1-1 to 1-5

2-1

3-1 to 3-3

4-1 to 4-7

5-1 to 5-11

6-1

A-1 to A-3

1/22/07 Initial Release

_________________________________ Manager, Flight Test Branch, ANM-160L Federal Aviation Administration Los Angeles Aircraft Certification Office Transport Airplane Directorate

Date:

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0-2

1-2

1-6

2-2

3-4

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8/23/07 Section repaginated, Log of Revisions Rev A

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TR Limitation added

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TR Operations revised

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FAR 36 Noise revised

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Date:

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10/03/07 Log of Revisions Rev B

Approved Fuels revised

Fuel Additives revised

Oil Temperature Limits revised

Anti-Icing Conditions revised


Date:

NOTE: All changes are indicated by a black vertical line along right margin.

Premier Aircraft, LLC Doc. No. FTA-PA-001019 Rev C 18 Terminal Dr. East Alton, IL 62024

AFM Supplement

iii

LOG OF REVISIONS (cont.)

REV. NO.

EFFECTED PAGES

DATE DESCRIPTION FAA APPROVAL

C iii

6-1

9/30/09 Log of Revisions Rev C

FAR 36 Noise revised


Date:


AFM Supplement

FAA Approved Date: August 23, 2007 iv

TABLE OF CONTENTS

SECTION DESCRIPTION PAGE

0 GENERAL 0-1

1 LIMITATIONS 1-1

2 EMERGENCY PROCEDURES 2-1

3 ABNORMAL PROCEDURES 3-1

4 NORMAL PROCEDURES 4-1

5 PERFORMANCE 5-1

6 NOISE 6-1

ANNEX LIST OF APPLICABLE ANNEXES

- ANNEX 3 - FERRY FLIGHT WITH ONE FUEL CONTROL COMPUTER INOPERATIVE

- ANNEX 5 - FLIGHT WITH ONE FUEL CONTROL COMPUTER IN MANUAL MODE

A-1


AFM Supplement

FAA Approved Date: August 23, 2007 v



AFM Supplement

FAA Approved Date: January 22, 2007 0-1

SECTION 0 - GENERAL

The Premier Aircraft, LLC Mystere-Falcon 50 Dash 4 engine upgrade converts the existing Honeywell TFE 731-3/3D-1C Turbo Fan Engines to TFE 731-4-1C Turbo Fan Engines. The TFE 731-4-1C is a front fan two spool (HP and LP) turbofan engine that is designed to provide increased performance, and improved durability/reliability and maintainability. The engine features a 3.3% reduction in thrust specific fuel consumption (TSFC) and a 13.7% increase in thrust at cruise altitude.

N1 DEECs, installed in accordance with STC ST01007CH-D, are required to accomplish the TFE 731-4-1C upgrade.

TFE 731-4-1C design improvements include:

• Aerodynamically Enhanced Fan

• Improved Fan Gearbox

• Improved 4th Stage LPC Seal

• High Technology HP Compressor

• Enhanced HP and LP Turbines

• New compound exhaust nozzles

Engine specifics:

• Engine weight, including the N1 DEEC, is increased by 68 lb

• Take-off thrust, flat rated by the N1 DEEC, is 3,700 lb (S.L., Static) up to 32.8ºC (i.e., ISA+17.8ºC)

• Maximum cruise thrust at 40,000 feet, M0.80 is 929 lb

• The TSFC is 0.518 lb/lb/hr (Takeoff, S.L., Static) and 0.796 lb/lb/hr (40,000 feet, M0.80)

• N1 DEECs are upgraded with TFE 731-4-1C power set tables


AFM Supplement

FAA Approved Date: August 23, 2007 0-2

SECTION 0 - GENERAL



AFM Supplement


SECTION 1 - LIMITATIONS

HONEYWELL TFE 731-4-1C ENGINE

THRUST RATING (UNINSTALLED, SEA LEVEL, ISA)

- TAKE-OFF............................................................................ 3,700 lb (1,649 daN)

- MAXIMUM CONTINUOUS.................................................... 3,700 lb (1,649 daN)

THRUST SETTING

The engine low pressure rotor speed (N1) is used as the thrust setting parameter.

The take-off and maximum continuous thrust must be based on the N1 values given in Section 5 of this AFM Supplement.

- Take-off thrust (5 minute time limit), refer to 5-2, 5-3, 5-4, 5-7, 5-8 and 5-9

- Maximum continuous thrust, refer to 5-5, 5-6, 5-10 and 5-11

MAXIMUM ENGINE ROTOR SPEEDS N1 AND N2

CONDITION OF USE N1 N2

Take-off – Maximum continuous 101.5% 100%

Transient (5 seconds max. allowable) 103% 103%

101.5% N1 = 21,000 RPM – 100% N2 = 29,989 RPM

MAXIMUM INTERSTAGE TURBINE TEMPERATURE (ITT)

Normal 952ºC Ground start Transient (10 seconds max.) 974ºC

Normal 952ºC Air Start Transient (10 seconds max.) 974ºC

Take-off 5 minutes max. 952ºC

Maximum continuous 924ºC

Maximum cruise 924ºC


AFM Supplement



HONEYWELL TFE 731-4-1C ENGINE

STARTING TIME

Ground start

From 10% N2 to light-off

From light-off to idle

10 seconds max.

60 seconds max.

Starter Assisted Air Start

From initial fuel flow to 60% N2

45 seconds max.

Windmilling Air Start

From initial fuel flow to 60% N2

45 seconds max.

FUEL CONTROL COMPUTERS (DEEC)

N1 DEECs must be installed in accordance with STC ST01007CH-D.

- Honeywell Digital Electronic Engine Controls (DEEC) AFM Supplement (Doc. No. AFMS220, Rev B or later approved revision) must be inserted in the Airplane Flight Manual.

Engine fuel control computers (N1 DEEC) must be operative for take-off.

Dispatch is not permitted with a rapidly flashing CMPTR 1, CMPTR 2 or CMPTR 3 annunciator (one flash per second).

THRUST REVERSER

- The thrust reverser is approved for ground operations only.

- The thrust reverser must not be used for taxiing in reverse.

- Limit maximum reverse thrust to 80% N1 when operating at airports between 7,000 feet and 10,000 feet airport elevation when the ambient temperature is less than -6.6ºC (20ºF).


AFM Supplement

FAA Approved Date: October 03, 2007 1-3


FUEL SYSTEM

Fuel used must conform to the following specification:

This table is representative of the fuel definition on October 1997.


AFM Supplement



FUEL SYSTEM

FUEL ADDITIVES

The following additives are authorized for use in the fuel:

- Anti-icing additive, conforming to AIR 3652 or MIL-I-27686D or E specifications (JP4/JP8), MIL-I-85470 (JP5) or equivalent at a concentration not in excess of 0.15% by volume.

- Approved C.I.S. Anti-icing additives (up to 0.3% by volume)

• I fluid GOST 8313-88

• I-M fluid TU6-10-1458-79 (I fluid mixed 1:1 with methanol (GOST 2222-78E)

• TGF-M fluid TU6-10-1457-79 (TGF fluid mixed 1:1 with methanol (GOST 2222-78E)

- Anti-static additive in amounts to bring the fuel up to 300 conductivity units providing the quantity added does not exceed:

• 1 ppm for SHELL ASA 3

• 3 ppm for STADIS 450

• 5 ppm for SIGBOL TU38-101741-78

- SOHIO Biobor JF biocide additive, or equivalent, is approved for use in the fuel at a concentration not to exceed 270 ppm (equivalent to 20 ppm of elemental boron).


AFM Supplement



LUBRICATION SYSTEM

APPROVED OILS

Approved Type II oils conforming to EMS 53110 specification.

OIL PRESSURE

Thrust setting Minimum pressure Maximum pressure

Take-off, climb, cruise or maximum continuous

38 psi 46 psi

Idle 25 psi 46 psi

Transient 55 psi less than 3 minutes

NOTE

The OIL 1, OIL 2 and OIL 3 annunciators illuminate for an oil pressure below 25 psi.

OIL TEMPERATURE

Operational limits

From sea level to 30,000 ft 127ºC maximum

Above 30,000 ft 140ºC maximum

Transient all altitudes 149ºC maximum less than 2 minutes

Minimum for ground start -54ºC

Minimum for initiating take-off, and continuous operation 30ºC


AFM Supplement





AFM Supplement


SECTION 2 - EMERGENCY PROCEDURES

No change to Airplane Flight Manual Procedures


AFM Supplement





AFM Supplement


SECTION 3 - ABNORMAL PROCEDURES

ENGINES - AIRSTART


IN FLIGHT RELIGHT ENVELOPE

No change to Airplane Flight Manual In Flight Relight Envelope

ENGINES - ABNORMAL AIRSTART

ABORT AIRSTART WHENEVER:

- Oil pressure does not rise within 10 seconds after light-off

- ITT does not rise within 10 seconds after light-off

- ITT is rapidly rising and approaching the 952ºC limit

- N1 remains close to zero when N2 = 20%

- N2 is not rising rapidly and smoothly after light-off

• Power lever ................................................................................ CUT-OFF

• Start Selector switch.............................................. MOTOR STOP START


AFM Supplement



FUEL CONTROL COMPUTER (N1 DEEC) FAULT (ON GROUND)

WARNING - CMPTR 1, CMPTR 2 or CMPTR 3 rapidly flashing (one flash per second)

- Dispatch is not permitted and the fault must be cleared prior to flight

OR

WARNING - CMPTR 1, CMPTR 2 or CMPTR 3 slowly flashing (one flash per 2 seconds)

- Dispatch is permitted. The DEEC should be interrogated and the fault identified at the next opportunity.

NOTES

A rapidly flashing CMPTR annunciator indicates the loss of an essential signal to or function of the DEEC. This warning will occur when the DEEC is powered and the airplane is on the ground with the engines not running.

A slowly flashing CMPTR annunciator indicates the loss of a non-essential signal to or function of the DEEC or the ECTM data buffer is full. This warning will occur when the DEEC is powered and the airplane is on the ground with the engines not running.


AFM Supplement



FUEL CONTROL COMPUTER (N1 DEEC) INOPERATIVE (IN FLIGHT)

WARNING - CMPTR 1, CMPTR 2 or CMPTR 3 illuminated (steady)

- Power lever of the affected engine ................................................................ IDLE

- Associated engine CMPTR switch ......................................................... OFF / ON

If the CMPTR annunciator remains illuminated and engine operational stability permits the DEEC switch to remain ON:

- ITT........................................................................................................MONITOR

- Avoid rapid power lever movements

If the CMPTR annunciator remains illuminated and engine operational stability does not permit the DEEC switch to remain ON:

- Associated engine CMPTR switch ..................................................................OFF

- Associated engine SPR switch ........................................... DEPRESS and HOLD

- Associated engine CMPTR switch ................................................................... ON

- Associated engine SPR switch ................... CONTINUE to HOLD (for 3 to 5 sec.) then RELEASE

- ITT........................................................................................................MONITOR

- Avoid rapid power lever movements

If engine operational stability still does not permit the DEEC switch to remain ON:

- Associated engine CMPTR switch ..................................................................OFF

CAUTION

- Maximum thrust may not be obtained

- Idle thrust may be higher than normal

- Acceleration time is longer in manual mode

- For any given N1, fuel flow is approximately 5% higher


AFM Supplement





AFM Supplement


SECTION 4 - NORMAL PROCEDURES

STARTING ENGINES


STARTING PROBLEMS

DISCONTINUE START WHENEVER:

- Oil pressure does not rise within 10 seconds after light-off

- ITT does not rise within 10 seconds after light-off

- ITT is rapidly rising and approaching the 952ºC limit

- N1 remains close to zero when N2 = 20%

- N2 is not rising rapidly and smoothly after light-off



- Perform a dry motoring whenever fuel is suspected to have accumulated in the tailpipe:



• Start button ............................................PUSH and HOLD for 15 seconds


AFM Supplement



OPERATION IN ICING CONDITIONS

- Engine and nacelle anti-ice systems (ENG ANTI-ICE) should be switched on in flight or on ground prior to entering visible moisture whenever the TAT is +10ºC or below.

- Airframe anti-ice system (AIRFRAME) should be switched on in flight prior to entering visible moisture whenever the TAT is +10ºC or below.

- Encounter with icing conditions is evidenced by the formation of ice on the non anti-iced area around the windshield panes. During night flight operations, a small spot light illuminates the lower RH corner of the LH windshield pane. The spot light is controlled by the NAV switch on the overhead panel.

- Do not exceed the operational engine nacelle, and airframe anti-ice system limitations (see Airplane Flight Manual Section 1, Systems – Anti-ice).

- If necessary during approach, extend airbrakes to help keep N1 speed to no less than the specified value, and increase approach speeds (see Airplane Flight Manual Section 3, Flight Controls – Airbrake System Malfunction).

- Satisfactory operation of the engine and nacelle, and airframe anti-ice systems requires that the engine N1 speed be not less than indicated below:

TAT -30º to -20ºC

-20º to -10ºC

-10º to 0ºC

0º to +10ºC

Minimum N1 speed in cruise condition

Minimum N1 speed in approach condition

84%

78%

81%

78%

78%

78%

73%

73%

One engine inoperative condition 91% 88% 84% 80%


AFM Supplement



THRUST REVERSER OPERATION

- Full reverse thrust is usable until the airplane comes to a complete stop. However, in cross-wind conditions, a 5% reduction in N1 is recommended shortly before the complete stop is reached.

- Fan stall may occur at full reverse thrust particularly when operating at colder ambient temperatures. If fan stall, characterized by an audible “chugging”, occurs reduce N1 by 5%.

- On landing, do not attempt a go-around after reverse thrust has been selected.

- Before using the thrust reverser ensure that the airplane is firmly on the ground, on all three landing gear, and that the airbrakes (if available) are extended.

- The thrust reverser control lever mechanical stop is set at 79º PLA.


AFM Supplement




DEEC SWITCHES

Each DEEC is controlled by a two position switch on the overhead panel. The ON position will provide normal DEEC operation. The OFF position will provide HMU overspeed protection (flyweight governor) only.

The pilot-operated Start Pressure Regulator (SPR) switch function has been deactivated with the N1 DEEC installation. Fuel enrichment during cold weather engine starts is now automatically controlled by the DEEC. The SPR switch now has two basic functions:

• Pilot Event Switch for the Engine Condition Trend Monitoring System (ECTM)

• Powered Manual Mode Enable Switch

DEEC ENGINE CONDITION TREND MONITORING SYSTEM (ECTM)

Using imbedded ECTM software, the DEEC continuously monitors the necessary engine parameters during engine operation and periodically stores those data in data buffers within the DEEC. At anytime following engine start, if the pilot observes abnormal engine operation, a momentary activation of the SPR switch for the corresponding engine will record pertinent data in the DEEC data buffer. Using a laptop with TFE-731 ECTM Data Downloader software, the data buffers can be downloaded for evaluation of engine usage and determination of required maintenance actions.

When an event occurs that requires an ECTM data download or when the ECTM data buffers are full a slowly flashing CMPTR 1, CMPTR 2 or CMPTR 3 annunciator will illuminate on the ground after engine shutdown.

Honeywell recommends downloading ECTM data every three flights for optimum performance trend data. Sufficient ECTM data buffer capacity exists to store data for 50 flights.

DEEC POWERED MANUAL MODE

When a fault transfers the DEEC to manual mode Ultimate Overspeed protection remains available as long as the DEEC switch remains ON. If engine operational stability does not permit the DEEC switch to remain ON only HMU overspeed protection (flyweight governor) will be available. It is possible to regain Ultimate Overspeed protection by accomplishing the following procedure:


AFM Supplement




DEEC POWERED MANUAL MODE (cont.)

• Place the DEEC switch in the OFF position

• Depress and hold the SPR switch

• Place the DEEC switch in the ON position

• Continue to hold the SPR switch for 3 to 5 seconds and then release. The CMPTR… annunciator will remain illuminated (in flight – steady, on ground – flashing then steady). The DEEC is now in powered manual mode.

To dispatch the airplane with one DEEC inoperative that DEEC must be placed in powered manual mode and then an automatic overspeed test must be successfully accomplished during the powered manual mode engine start. During the start, fuel is interrupted briefly at 40% N2 by automatic activation of the DEEC overspeed solenoid. A slight N2 RPM droop will be observed followed by normal engine acceleration. The slight N2 RPM droop must be confirmed visually on the engine instruments.

NOTES

A Ferry Permit is required to dispatch an airplane with one DEEC inoperative.

The airplane must be operated in accordance with ANNEX 3 or ANNEX 5 of the Honeywell Digital Electronic Engine Controls (DEEC) AFM Supplement, Doc. No. AFMS220, Rev. B (or later approved revision).

DEEC POWER LEVER ANGLE (PLA) FUNCTIONS

DEEC and rigging functions associated with power lever angle (PLA):

• PLA -2º to 5º: The HMU fuel cutoff and min travel hard stop

• PLA 20º: The HMU rigging pin location and idle hard stop

• PLA 20º to 26º Idle power range: The DEEC varies N1 to meet a thrust schedule based on ambient conditions. Idle thrust varies between approximately 210 and 310 lb. (corrected for Mach number and limited by the underspeed governor).

• PLA 64º to 66º: Bleed surge valve closes with increasing PLA and opens with decreasing PLA

• PLA 90º to 95º, Cruise power: The DEEC sets N1 for maximum cruise for the current ambient conditions (Pt2, Tt2, Ps0) corrected for Mach number


AFM Supplement




DEEC POWER LEVER ANGLE (PLA) FUNCTIONS (cont.)

• PLA 100º to 105º, Climb power: The DEEC sets N1 for climb based on ambient conditions (Pt2, Tt2, Ps0) corrected for Mach number

• PLA 107º, ITT (T5) limiter reset: When the power levers are ≤107º PLA the DEEC resets the ITT limiter 28ºC (952ºC to 924ºC). Regardless of power lever position, the DEEC ramps the ITT limiter 28ºC (952ºC to 924ºC) between 15,000 feet and 20,000 feet.

• PLA 117º to 122º: Take-off power range: The DEEC sets N1 for take-off based on ambient conditions (Pt2, Tt2, Ps0) corrected for Mach number. Since take-off N1 is a minimum N1 the DEEC will schedule N1 0.25% to 0.75% above take-off N1. This, to assure take-off performance is achieved.

• PLA 120º to 122º: The HMU max PLA hard stop

• Intermediate PLAs: At all other PLAs, thrust is set proportional to power lever position corrected for ambient conditions


AFM Supplement



INSTRUMENT MARKINGS

Instrument Graduation limits Range colors Operating ranges

POWER PLANT:

N1 indicator

ITT indicator

N2 indicator

Oil temperature/ pressure indicator

0/110%

0/960ºC

0/110%

0/150ºC

0/70 psi

Amber Green

Red radial

Green Amber

Red radial

Amber Green

Red radial

Green Amber

Red Red radial

Red radial Amber Green Amber

Red radial

25 to 35% 35 to 101.5%

101.5%

230 to 924ºC 924 to 952ºC

952ºC

52 to 61% 61 to 100%

100%

30 to 127ºC 127 to 140ºC 140 to 149ºC

149ºC

25 psi 25 to 38 psi 38 to 46 psi 46 to 55 psi

55 psi


AFM Supplement





AFM Supplement


SECTION 5 - PERFORMANCE

THRUST SETTING

• 5-2 Take-off N1 Without Ice Protection Take-off Run And First Segment Climb

• 5-5 Maximum Continuous N1 Without Ice Protection Final Take-off And Enroute Climbs

• 5-7 Take-off N1 With Engine Ice Protection Take-off Run And First Segment Climb

• 5-10 Maximum Continuous N1 With Engine And Airframe Ice Protection Final Take-off And Enroute Climbs


AFM Supplement



TAKE-OFF N1WITHOUT ICE PROTECTION

TAKE-OFF RUN AND FIRST SEGMENT CLIMBAltitude 0 ft / 5,000 ft

94.7 94.4

95.2 95.095.8 95.5

Side engine N1 Center engine N1

MAXIMUM ITT: 952ºC



94.7 94.4

95.2 95.095.8 95.5


MAXIMUM ITT: 952ºC SAT SAT(ºC) (ºC)50 92.2 91.9 92.0 91.7 50

48 92.9 92.6 92.7 92.4 92.4 92.1 48

46 93.5 93.2 93.3 93.0 93.1 92.8 92.9 92.6 46

44 94.1 93.9 93.9 93.7 93.7 93.5 93.5 93.3 93.4 93.1 4442 94.7 94.4 94.5 94.3 94.3 94.1 94.1 93.9 94.0 93.7 93.8 93.6 42

40 95.2 95.0 95.1 94.8 94.9 94.6 94.7 94.5 94.6 94.3 94.4 94.1 40

38 95.8 95.5 95.6 95.4 95.4 95.2 95.3 95.0 95.1 94.9 94.9 94.7 38

36 96.3 96.0 96.1 95.9 95.9 95.7 95.8 95.6 95.6 95.4 95.5 95.2 36

34 96.7 96.5 96.6 96.4 96.4 96.2 96.3 96.1 96.1 95.9 96.0 95.8 3432 97.2 97.0 97.0 96.8 96.9 96.7 96.7 96.5 96.6 96.4 96.4 96.2 32

30 97.0 97.1 97.4 97.2 97.3 97.1 97.1 96.9 97.0 96.8 96.9 96.6 30

28 96.7 96.8 97.8 97.6 97.7 97.5 97.6 97.3 97.4 97.2 97.3 97.0 28

26 96.4 96.5 97.6 97.6 98.1 97.9 97.9 97.7 97.8 97.6 97.6 97.4 26

24 96.1 96.1 97.3 97.3 98.4 98.2 98.3 98.1 98.2 97.9 98.0 97.8 2422 95.8 95.8 96.9 97.0 98.1 98.1 98.7 98.4 98.5 98.3 98.4 98.2 22

20 95.5 95.5 96.6 96.7 97.8 97.8 99.0 98.8 98.9 98.7 98.7 98.5 20

18 95.1 95.2 96.3 96.3 97.5 97.5 98.7 98.7 99.2 99.1 99.1 99.0 18

16 94.8 94.9 96.0 96.0 97.1 97.2 98.3 98.4 99.6 99.5 99.5 99.4 16

14 94.5 94.5 95.6 95.7 96.8 96.9 98.0 98.1 99.3 99.4 99.8 99.8 1412 94.1 94.2 95.3 95.4 96.5 96.5 97.7 97.8 99.0 99.1 100.2 100.2 12

10 93.8 93.9 95.0 95.0 96.1 96.2 97.4 97.4 98.6 98.8 100.0 100.3 10

8 93.5 93.6 94.6 94.7 95.8 95.9 97.0 97.1 98.3 98.4 99.6 99.9 8

6 93.2 93.2 94.3 94.4 95.5 95.5 96.7 96.8 97.9 98.1 99.3 99.6 6

4 92.8 92.9 94.0 94.0 95.1 95.2 96.3 96.4 97.6 97.7 99.0 99.3 42 92.5 92.6 93.6 93.7 94.8 94.8 96.0 96.1 97.2 97.4 98.6 98.9 2

0 92.2 92.2 93.3 93.3 94.4 94.5 95.6 95.7 96.9 97.0 98.3 98.6 0

-2 91.8 91.9 92.9 93.0 94.1 94.2 95.3 95.4 96.5 96.7 97.9 98.2 -2

-4 91.5 91.6 92.6 92.7 93.7 93.8 94.9 95.0 96.2 96.3 97.5 97.9 -4

-6 91.2 91.2 92.3 92.3 93.4 93.5 94.6 94.7 95.8 96.0 97.2 97.5 -6-8 90.8 90.9 91.9 92.0 93.1 93.1 94.2 94.3 95.5 95.6 96.8 97.1 -8

-10 90.5 90.5 91.6 91.6 92.7 92.8 93.9 94.0 95.1 95.3 96.5 96.8 -10

-12 90.1 90.2 91.2 91.3 92.4 92.4 93.5 93.6 94.8 94.9 96.1 96.4 -12

-14 89.8 89.9 90.9 90.9 92.0 92.1 93.2 93.3 94.4 94.5 95.7 96.1 -14

-16 89.4 89.5 90.5 90.6 91.7 91.7 92.8 92.9 94.0 94.2 95.4 95.7 -16-18 89.1 89.2 90.2 90.2 91.3 91.4 92.5 92.5 93.7 93.8 95.0 95.3 -18

-20 88.8 88.8 89.8 89.9 90.9 91.0 92.1 92.2 93.3 93.5 94.6 95.0 -20

-22 88.4 88.5 89.5 89.5 90.6 90.7 91.7 91.8 92.9 93.1 94.3 94.6 -22

-24 88.1 88.1 89.1 89.2 90.2 90.3 91.4 91.5 92.6 92.7 93.9 94.2 -24

-26 87.7 87.8 88.8 88.8 89.9 89.9 91.0 91.1 92.2 92.4 93.5 93.8 -26-28 87.4 87.4 88.4 88.5 89.5 89.6 90.7 90.7 91.8 92.0 93.1 93.5 -28

-30 87.0 87.1 88.1 88.1 89.2 89.2 90.3 90.4 91.5 91.6 92.8 93.1 -30

-32 86.6 86.7 87.7 87.8 88.8 88.8 89.9 90.0 91.1 91.3 92.4 92.7 -32

-34 86.3 86.4 87.3 87.4 88.4 88.5 89.6 89.6 90.7 90.9 92.0 92.3 -34

-36 85.9 86.0 87.0 87.0 88.1 88.1 89.2 89.3 90.3 90.5 91.6 92.0 -36-38 85.6 85.6 86.6 86.7 87.7 87.7 88.8 88.9 90.0 90.1 91.3 91.6 -38

-40 85.2 85.3 86.2 86.3 87.3 87.4 88.4 88.5 89.6 89.7 90.9 91.2 -40

-42 84.8 84.9 85.9 85.9 87.0 87.0 88.1 88.1 89.2 89.4 90.5 90.8 -42

-44 84.5 84.5 85.5 85.6 86.6 86.6 87.7 87.8 88.8 89.0 90.1 90.4 -44

-46 84.1 84.2 85.1 85.2 86.2 86.3 87.3 87.4 88.4 88.6 89.7 90.0 -46-48 83.7 83.8 84.8 84.8 85.8 85.9 86.9 87.0 88.1 88.2 89.3 89.6 -48

-50 83.4 83.4 84.4 84.5 85.4 85.5 86.5 86.6 87.7 87.8 88.9 89.3 -50

-52 83.0 83.1 84.0 84.1 85.1 85.1 86.2 86.2 87.3 87.4 88.5 88.9 -52-54 82.7 82.7 83.7 83.7 84.7 84.8 85.8 85.9 86.9 87.1 88.2 88.5 -54

(ºC) (ºC)SAT SAT

4,000 5,000Pressure altitude (ft)

0 1,000 2,000 3,000

Pressure altitude (ft)0 1,000 2,000 3,000 4,000 5,000


AFM Supplement




TAKE-OFF RUN AND FIRST SEGMENT CLIMBAltitude 5,000 ft / 10,000 ft

94.7 94.4

95.2 95.0

95.8 95.5


MAXIMUM ITT: 952ºC



94.7 94.4

95.2 95.0

95.8 95.5


MAXIMUM ITT: 952ºC SAT SAT(ºC) (ºC)50 50

48 48

46 46

44 4442 93.8 93.6 42

40 94.4 94.1 94.2 94.0 40

38 94.9 94.7 94.7 94.5 94.6 94.4 38

36 95.5 95.2 95.3 95.1 95.1 94.9 95.0 94.8 36

34 96.0 95.8 95.8 95.6 95.6 95.4 95.5 95.2 3432 96.4 96.2 96.3 96.1 96.1 95.9 96.0 95.8 95.8 95.6 32

30 96.9 96.6 96.7 96.5 96.6 96.4 96.4 96.2 96.3 96.0 96.1 95.8 30

28 97.3 97.0 97.1 96.9 97.0 96.8 96.9 96.6 96.7 96.5 96.5 96.3 28

26 97.6 97.4 97.5 97.3 97.4 97.2 97.3 97.0 97.1 96.9 96.9 96.7 26

24 98.0 97.8 97.9 97.7 97.8 97.5 97.6 97.4 97.5 97.3 97.3 97.1 2422 98.4 98.2 98.2 98.0 98.1 97.9 98.0 97.8 97.8 97.6 97.7 97.5 22

20 98.7 98.5 98.6 98.4 98.5 98.3 98.3 98.2 98.2 98.0 98.1 97.9 20

18 99.1 99.0 99.0 98.8 98.8 98.7 98.7 98.6 98.6 98.4 98.5 98.3 18

16 99.5 99.4 99.3 99.2 99.2 99.1 99.1 99.0 99.0 98.9 98.8 98.7 16

14 99.8 99.8 99.7 99.6 99.6 99.5 99.5 99.4 99.3 99.3 99.2 99.1 1412 100.2 100.2 100.1 100.0 99.9 99.9 99.8 99.8 99.7 99.7 99.6 99.5 12

10 100.0 100.3 100.4 100.4 100.3 100.3 100.2 100.2 100.1 100.1 99.9 99.9 10

8 99.6 99.9 100.8 100.8 100.6 100.7 100.5 100.6 100.4 100.4 100.3 100.3 8

6 99.3 99.6 100.8 101.2 101.0 101.1 100.9 100.9 100.8 100.8 100.7 100.7 6

4 99.0 99.3 100.5 101.0 101.3 101.4 101.2 101.3 101.1 101.2 101.0 101.1 42 98.6 98.9 100.1 100.7 101.5 101.5 101.5 101.5 101.5 101.5 101.4 101.5 2

0 98.3 98.6 99.8 100.3 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 0

-2 97.9 98.2 99.4 100.0 101.2 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -2

-4 97.5 97.9 99.1 99.6 100.8 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -4

-6 97.2 97.5 98.7 99.3 100.5 101.2 101.5 101.5 101.5 101.5 101.5 101.5 -6-8 96.8 97.1 98.4 98.9 100.1 100.8 101.5 101.5 101.5 101.5 101.5 101.5 -8

-10 96.5 96.8 98.0 98.5 99.7 100.5 101.5 101.5 101.5 101.5 101.5 101.5 -10

-12 96.1 96.4 97.6 98.2 99.4 100.1 101.3 101.5 101.5 101.5 101.5 101.5 -12

-14 95.7 96.1 97.3 97.8 99.0 99.7 101.0 101.5 101.5 101.5 101.5 101.5 -14

-16 95.4 95.7 96.9 97.4 98.6 99.4 100.6 101.4 101.5 101.5 101.5 101.5 -16-18 95.0 95.3 96.5 97.1 98.2 99.0 100.2 101.1 101.5 101.5 101.5 101.5 -18

-20 94.6 95.0 96.1 96.7 97.9 98.6 99.8 100.7 101.5 101.5 101.5 101.5 -20

-22 94.3 94.6 95.8 96.3 97.5 98.2 99.4 100.3 101.5 101.5 101.5 101.5 -22

-24 93.9 94.2 95.4 95.9 97.1 97.9 99.0 99.9 101.2 101.5 101.5 101.5 -24

-26 93.5 93.8 95.0 95.6 96.7 97.5 98.7 99.5 100.8 101.5 101.5 101.5 -26-28 93.1 93.5 94.6 95.2 96.3 97.1 98.3 99.1 100.4 101.2 101.5 101.5 -28

-30 92.8 93.1 94.2 94.8 95.9 96.7 97.9 98.7 100.0 100.8 101.5 101.5 -30

-32 92.4 92.7 93.9 94.4 95.6 96.3 97.5 98.3 99.6 100.4 101.5 101.5 -32

-34 92.0 92.3 93.5 94.0 95.2 95.9 97.1 97.9 99.2 100.1 101.5 101.5 -34

-36 91.6 92.0 93.1 93.6 94.8 95.5 96.7 97.5 98.8 99.7 101.1 101.5 -36-38 91.3 91.6 92.7 93.3 94.4 95.1 96.3 97.1 98.4 99.2 100.7 101.4 -38

-40 90.9 91.2 92.3 92.9 94.0 94.7 95.9 96.7 98.0 98.8 100.2 101.0 -40

-42 90.5 90.8 91.9 92.5 93.6 94.3 95.5 96.3 97.6 98.4 99.8 100.6 -42

-44 90.1 90.4 91.5 92.1 93.2 93.9 95.1 95.9 97.2 98.0 99.4 100.1 -44

-46 89.7 90.0 91.2 91.7 92.8 93.5 94.7 95.5 96.8 97.6 99.0 99.7 -46-48 89.3 89.6 90.8 91.3 92.4 93.1 94.3 95.1 96.3 97.2 98.5 99.3 -48

-50 88.9 89.3 90.4 90.9 92.0 92.7 93.8 94.7 95.9 96.7 98.1 98.9 -50

-52 88.5 88.9 90.0 90.5 91.6 92.3 93.4 94.3 95.5 96.3 97.7 98.4 -52-54 88.2 88.5 89.6 90.1 91.2 91.9 93.0 93.9 95.1 95.9 97.3 98.0 -54

(ºC) (ºC)SAT SATPressure altitude (ft)

5,000

5,000 6,000 7,000 8,000 9,000 10,000

Pressure altitude (ft)6,000 7,000 8,000 9,000 10,000


AFM Supplement





94.7 94.4

95.2 95.095.8 95.5


MAXIMUM ITT: 952ºC



94.7 94.4

95.2 95.095.8 95.5


MAXIMUM ITT: 952ºC SAT SAT(ºC) (ºC)50 50

48 48

46 46

44 4442 42

40 40

38 38

36 36

34 3432 32

30 96.1 95.8 30

28 96.5 96.3 96.3 96.1 28

26 96.9 96.7 96.7 96.5 96.5 96.3 26

24 97.3 97.1 97.1 96.9 96.9 96.7 96.7 96.5 2422 97.7 97.5 97.5 97.3 97.4 97.1 97.2 96.9 97.0 96.7 22

20 98.1 97.9 97.9 97.7 97.8 97.6 97.6 97.4 97.4 97.2 20

18 98.5 98.3 98.3 98.2 98.2 98.0 98.0 97.8 97.8 97.6 18

16 98.8 98.7 98.7 98.6 98.6 98.4 98.4 98.2 98.2 98.0 16

14 99.2 99.1 99.1 99.0 99.0 98.8 98.8 98.7 98.6 98.5 1412 99.6 99.5 99.5 99.4 99.3 99.2 99.2 99.1 99.0 98.9 12

10 99.9 99.9 99.8 99.8 99.7 99.7 99.6 99.5 99.4 99.3 10

8 100.3 100.3 100.2 100.2 100.1 100.1 100.0 99.9 99.8 99.8 8

6 100.7 100.7 100.6 100.6 100.5 100.5 100.4 100.4 100.2 100.2 6

4 101.0 101.1 100.9 101.0 100.8 100.9 100.7 100.8 100.6 100.6 42 101.4 101.5 101.3 101.4 101.2 101.3 101.1 101.2 101.0 101.0 2

0 101.5 101.5 101.5 101.5 101.5 101.5 101.4 101.5 101.3 101.4 0

-2 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -2

-4 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -4

-6 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -6-8 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -8

-10 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -10

-12 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -12

-14 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -14

-16 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -16-18 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -18

-20 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -20

-22 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -22

-24 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -24

-26 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -26-28 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -28

-30 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -30

-32 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -32

-34 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -34

-36 101.1 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -36-38 100.7 101.4 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -38

-40 100.2 101.0 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -40

-42 99.8 100.6 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -42

-44 99.4 100.1 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -44

-46 99.0 99.7 101.1 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -46-48 98.5 99.3 100.7 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -48

-50 98.1 98.9 100.3 101.0 101.5 101.5 101.5 101.5 101.5 101.5 -50

-52 97.7 98.4 99.8 100.6 101.5 101.5 101.5 101.5 101.5 101.5 -52-54 97.3 98.0 99.4 100.2 101.4 101.5 101.5 101.5 101.5 101.5 -54

(ºC) (ºC)SAT SAT

14,000Pressure altitude (ft)

10,000 11,000 12,000 13,000

Pressure altitude (ft)10,000 11,000 12,000 13,000 14,000


AFM Supplement



MAXIMUM CONTINUOUS N1WITHOUT ICE PROTECTION

FINAL TAKE-OFF AND ENROUTE CLIMBSAltitude 0 ft / 25,000 ft

94.7 94.4

95.2 95.095.8 95.5


MAXIMUM ITT: 924ºC



94.7 94.4

95.2 95.095.8 95.5


MAXIMUM ITT: 924ºC TAT TAT(ºC) (ºC)56 87.4 87.2 5654 88.1 87.9 5452 88.8 88.6 52

50 89.5 89.3 5048 90.2 90.0 4846 90.9 90.7 90.1 89.9 4644 91.5 91.3 90.7 90.6 4442 92.1 91.9 91.4 91.2 42

40 92.7 92.5 92.0 91.8 4038 93.3 93.1 92.6 92.4 91.8 91.6 3836 93.8 93.7 93.1 93.0 92.4 92.2 3634 94.4 94.2 93.7 93.5 93.0 92.8 3432 94.9 94.7 94.2 94.0 93.5 93.4 32

30 95.3 95.1 94.7 94.5 94.0 93.9 3028 95.5 95.5 95.1 94.9 94.5 94.4 93.7 93.5 2826 95.2 95.4 95.5 95.4 95.0 94.8 94.2 94.0 2624 94.9 95.0 95.9 95.8 95.4 95.2 94.7 94.5 2422 94.6 94.7 96.3 96.2 95.8 95.6 95.1 94.9 22

20 94.2 94.4 96.7 96.6 96.2 96.0 95.5 95.4 2018 93.9 94.1 97.1 97.0 96.5 96.4 95.9 95.8 95.1 94.9 1816 93.6 93.8 97.4 97.3 96.9 96.8 96.3 96.2 95.5 95.3 1614 93.3 93.4 97.8 97.7 97.2 97.2 96.6 96.6 95.8 95.7 1412 93.0 93.1 97.9 98.1 97.6 97.5 97.0 96.9 96.2 96.1 12

10 92.6 92.8 97.6 97.8 97.9 97.9 97.4 97.3 96.6 96.5 95.8 95.7 108 92.3 92.5 97.3 97.4 98.3 98.3 97.7 97.7 97.0 97.0 96.2 96.2 86 92.0 92.1 96.9 97.1 98.6 98.7 98.1 98.2 97.4 97.4 96.6 96.6 64 91.7 91.8 96.6 96.8 99.0 99.1 98.5 98.6 97.8 97.9 97.0 97.1 42 91.3 91.5 96.2 96.4 99.3 99.5 98.9 99.0 98.2 98.3 97.5 97.5 2

0 91.0 91.2 95.9 96.1 99.7 99.8 99.2 99.4 98.6 98.8 97.9 98.0 0-2 90.7 90.8 95.5 95.7 100.0 100.2 99.6 99.8 99.0 99.2 98.3 98.4 -2-4 90.4 90.5 95.2 95.4 100.3 100.5 99.9 100.1 99.4 99.6 98.7 98.9 -4-6 90.0 90.2 94.8 95.0 100.6 100.8 100.2 100.4 99.7 99.9 99.1 99.3 -6-8 89.7 89.8 94.5 94.7 100.9 101.1 100.5 100.7 100.1 100.3 99.5 99.7 -8

-10 89.4 89.5 94.1 94.3 100.6 101.3 100.8 101.0 100.4 100.6 99.9 100.1 -10-12 89.0 89.2 93.8 94.0 100.2 101.0 101.0 101.3 100.7 100.9 100.2 100.4 -12-14 88.7 88.8 93.4 93.6 99.8 100.6 101.3 101.5 100.9 101.1 100.5 100.7 -14-16 88.3 88.5 93.1 93.2 99.5 100.2 101.5 101.5 101.1 101.4 100.7 101.0 -16-18 88.0 88.1 92.7 92.9 99.1 99.8 101.5 101.5 101.3 101.5 101.0 101.2 -18

-20 87.7 87.8 92.4 92.5 98.7 99.5 101.5 101.5 101.5 101.5 101.2 101.4 -20-22 87.3 87.5 92.0 92.2 98.3 99.1 101.5 101.5 101.5 101.5 101.4 101.5 -22-24 87.0 87.1 91.6 91.8 97.9 98.7 101.5 101.5 101.5 101.5 101.5 101.5 -24-26 86.6 86.8 91.3 91.4 97.6 98.3 101.5 101.5 101.5 101.5 101.5 101.5 -26-28 86.3 86.4 90.9 91.1 97.2 97.9 101.5 101.5 101.5 101.5 101.5 101.5 -28

-30 85.9 86.1 90.5 90.7 96.8 97.5 101.5 101.5 101.5 101.5 101.5 101.5 -30-32 85.6 85.7 90.2 90.3 96.4 97.2 101.5 101.5 101.5 101.5 101.5 101.5 -32-34 85.2 85.4 89.8 90.0 96.0 96.8 101.5 101.5 101.5 101.5 101.5 101.5 -34-36 84.9 85.0 89.4 89.6 95.6 96.4 101.5 101.5 101.5 101.5 101.5 101.5 -36-38 84.5 84.7 89.1 89.2 95.2 96.0 101.5 101.5 101.5 101.5 -38

-40 84.2 84.3 88.7 88.9 94.8 95.6 101.5 101.5 101.5 101.5 -40-42 83.8 84.0 88.3 88.5 94.4 95.2 101.5 101.5 -42-44 83.4 83.6 87.9 88.1 94.0 94.8 -44-46 83.1 83.2 87.6 87.7 -46-48 -48

-50 -50-52 -52-54 -54-56 -56

(ºC) (ºC)TAT TAT


0 5,000 10,000 15,000



AFM Supplement




FINAL TAKE-OFF AND ENROUTE CLIMBSAltitude 25,000 ft / 50,000 ft

94.7 94.4

95.2 95.0

95.8 95.5


MAXIMUM ITT: 924ºC



94.7 94.4

95.2 95.0

95.8 95.5


MAXIMUM ITT: 924ºC TAT TAT(ºC) (ºC)56 5654 5452 52

50 5048 4846 4644 4442 42

40 4038 3836 3634 3432 32

30 3028 2826 2624 2422 22

20 2018 1816 1614 1412 12

10 95.8 95.7 108 96.2 96.2 86 96.6 96.6 64 97.0 97.1 42 97.5 97.5 96.2 96.2 2

0 97.9 98.0 96.6 96.6 0-2 98.3 98.4 97.0 97.1 -2-4 98.7 98.9 97.5 97.6 -4-6 99.1 99.3 98.0 98.1 96.4 96.4 93.6 93.6 -6-8 99.5 99.7 98.5 98.6 96.8 96.9 94.1 94.1 -8

-10 99.9 100.1 98.9 99.0 97.4 97.5 94.7 94.7 -10-12 100.2 100.4 99.3 99.5 97.9 98.0 96.5 96.7 95.2 95.3 -12-14 100.5 100.7 99.7 99.8 98.3 98.5 97.0 97.1 95.8 95.9 94.6 94.7 -14-16 100.7 101.0 100.0 100.2 98.7 98.9 97.5 97.6 96.3 96.4 95.1 95.2 -16-18 101.0 101.2 100.3 100.5 99.1 99.3 97.9 98.1 96.7 96.9 95.5 95.7 -18

-20 101.2 101.4 100.5 100.7 99.5 99.7 98.4 98.5 97.2 97.3 95.9 96.1 -20-22 101.4 101.5 100.8 101.0 99.9 100.1 98.7 98.9 97.6 97.8 96.3 96.5 -22-24 101.5 101.5 101.0 101.2 100.2 100.4 99.1 99.3 97.9 98.1 96.6 96.8 -24-26 101.5 101.5 101.2 101.4 100.4 100.6 99.4 99.6 98.2 98.4 96.9 97.1 -26-28 101.5 101.5 101.4 101.5 100.6 100.8 99.6 99.8 98.4 98.6 97.1 97.3 -28

-30 101.5 101.5 101.5 101.5 100.8 101.0 99.8 100.0 98.7 98.8 97.3 97.5 -30-32 101.5 101.5 101.5 101.5 101.0 101.1 100.0 100.2 98.9 99.0 97.6 97.6 -32-34 101.5 101.5 101.5 101.5 101.2 101.3 100.2 100.3 99.1 99.1 97.8 97.8 -34-36 101.5 101.5 101.5 101.5 101.4 101.3 100.4 100.4 99.3 99.3 98.1 98.1 -36-38 101.5 101.5 101.5 101.4 100.6 100.6 99.6 99.6 98.5 98.4 -38

-40 101.5 101.5 101.5 101.5 100.8 100.7 99.9 99.8 98.8 98.7 -40-42 101.5 101.5 101.5 101.5 101.0 100.8 100.1 100.0 99.2 99.1 -42-44 101.5 101.5 101.5 101.5 101.2 100.9 100.4 100.1 99.5 99.3 -44-46 101.5 101.5 101.5 101.5 101.4 101.0 100.6 100.3 99.8 99.6 -46-48 101.5 101.5 101.5 101.5 101.5 101.1 100.7 100.4 99.9 99.7 -48

-50 101.5 101.5 101.5 101.2 100.8 100.5 100.0 99.9 -50-52 101.5 101.5 101.5 101.3 100.9 100.7 100.1 100.0 -52-54 101.5 101.5 101.5 101.4 101.0 100.7 100.2 100.0 -54-56 101.5 101.5 101.5 101.5 101.1 100.8 100.3 100.1 -56

(ºC) (ºC)TAT TAT

Pressure altitude (ft)25,000 30,000 35,000 40,000 45,000 50,000


25,000 30,000 35,000 40,000


AFM Supplement



TAKE-OFF N1WITH ENGINE ICE PROTECTION


94.7 94.4

95.2 95.095.8 95.5


MAXIMUM ITT: 952ºC



94.7 94.4

95.2 95.095.8 95.5


MAXIMUM ITT: 952ºC SAT SAT(ºC) (ºC)10 93.8 93.9 95.0 95.0 96.1 96.2 97.4 97.4 98.0 97.8 97.9 97.7 10

8 93.5 93.6 94.6 94.7 95.8 95.9 97.0 97.1 98.3 98.2 98.2 98.0 8

6 93.2 93.2 94.3 94.4 95.5 95.5 96.7 96.8 98.0 98.1 98.5 98.4 6

4 92.8 92.9 94.0 94.0 95.1 95.2 96.3 96.4 97.6 97.7 98.8 98.7 42 92.5 92.6 93.6 93.7 94.8 94.8 96.0 96.1 97.3 97.4 98.6 98.9 2

0 92.2 92.2 93.3 93.3 94.4 94.5 95.7 95.7 96.9 97.0 98.3 98.6 0

-2 91.8 91.9 92.9 93.0 94.1 94.2 95.3 95.4 96.5 96.7 97.9 98.2 -2

-4 91.5 91.6 92.6 92.7 93.8 93.8 95.0 95.0 96.2 96.3 97.5 97.9 -4

-6 91.2 91.2 92.3 92.3 93.4 93.5 94.6 94.7 95.8 96.0 97.2 97.5 -6-8 90.8 90.9 91.9 92.0 93.1 93.1 94.3 94.3 95.5 95.6 96.8 97.1 -8

-10 90.5 90.5 91.6 91.6 92.7 92.8 93.9 94.0 95.1 95.3 96.5 96.8 -10

-12 90.1 90.2 91.2 91.3 92.4 92.4 93.5 93.6 94.8 94.9 96.1 96.4 -12

-14 89.8 89.9 90.9 90.9 92.0 92.1 93.2 93.3 94.4 94.5 95.7 96.1 -14

-16 89.5 89.5 90.5 90.6 91.7 91.7 92.8 92.9 94.0 94.2 95.4 95.7 -16-18 89.1 89.2 90.2 90.2 91.3 91.4 92.5 92.5 93.7 93.8 95.0 95.3 -18

-20 88.8 88.8 89.8 89.9 91.0 91.0 92.1 92.2 93.3 93.5 94.6 95.0 -20

-22 88.4 88.5 89.5 89.5 90.6 90.7 91.8 91.8 92.9 93.1 94.3 94.6 -22

-24 88.1 88.1 89.1 89.2 90.2 90.3 91.4 91.5 92.6 92.7 93.9 94.2 -24

-26 87.7 87.8 88.8 88.8 89.9 89.9 91.0 91.1 92.2 92.4 93.5 93.8 -26-28 87.4 87.4 88.4 88.5 89.5 89.6 90.7 90.7 91.8 92.0 93.1 93.5 -28

-30 87.0 87.1 88.1 88.1 89.2 89.2 90.3 90.4 91.5 91.6 92.8 93.1 -30

-32 86.7 86.7 87.7 87.8 88.8 88.9 89.9 90.0 91.1 91.3 92.4 92.7 -32

-34 86.3 86.4 87.3 87.4 88.4 88.5 89.6 89.6 90.7 90.9 92.0 92.3 -34

-36 85.9 86.0 87.0 87.0 88.1 88.1 89.2 89.3 90.4 90.5 91.6 92.0 -36-38 85.6 85.6 86.6 86.7 87.7 87.8 88.8 88.9 90.0 90.1 91.3 91.6 -38

-40 85.2 85.3 86.3 86.3 87.3 87.4 88.4 88.5 89.6 89.8 90.9 91.2 -40

-42 84.9 84.9 85.9 85.9 87.0 87.0 88.1 88.1 89.2 89.4 90.5 90.8 -42

-44 84.5 84.6 85.5 85.6 86.6 86.6 87.7 87.8 88.8 89.0 90.1 90.4 -44

-46 84.1 84.2 85.1 85.2 86.2 86.3 87.3 87.4 88.5 88.6 89.7 90.0 -46-48 83.8 83.8 84.8 84.8 85.8 85.9 86.9 87.0 88.1 88.2 89.3 89.6 -48

-50 83.4 83.5 84.4 84.5 85.5 85.5 86.5 86.6 87.7 87.8 88.9 89.3 -50

-52 83.0 83.1 84.0 84.1 85.1 85.1 86.2 86.2 87.3 87.4 88.5 88.9 -52-54 82.7 82.7 83.7 83.7 84.7 84.8 85.8 85.9 86.9 87.1 88.2 88.5 -54(ºC) (ºC)SAT SATPressure altitude (ft)

0 1,000 2,000 3,000 4,000 5,000



AFM Supplement





94.7 94.4

95.2 95.0

95.8 95.5


MAXIMUM ITT: 952ºC



94.7 94.4

95.2 95.0

95.8 95.5


MAXIMUM ITT: 952ºC SAT SAT(ºC) (ºC)10 97.9 97.7 97.7 97.6 97.6 97.5 97.5 97.3 97.4 97.2 97.3 97.1 10

8 98.2 98.0 98.1 97.9 97.9 97.8 97.8 97.7 97.7 97.6 97.6 97.4 8

6 98.5 98.4 98.4 98.3 98.2 98.1 98.1 98.0 98.0 97.9 97.9 97.8 6

4 98.8 98.7 98.6 98.6 98.5 98.5 98.4 98.4 98.3 98.3 98.2 98.1 42 98.6 98.9 98.9 98.9 98.8 98.8 98.7 98.7 98.6 98.6 98.5 98.5 2

0 98.3 98.6 99.2 99.3 99.1 99.2 99.0 99.0 98.9 98.9 98.8 98.8 0

-2 97.9 98.2 99.4 99.6 99.4 99.5 99.3 99.4 99.2 99.3 99.1 99.2 -2

-4 97.5 97.9 99.1 99.6 99.7 99.8 99.6 99.7 99.5 99.6 99.4 99.5 -4

-6 97.2 97.5 98.7 99.3 100.0 100.1 99.9 100.0 99.8 99.9 99.7 99.8 -6-8 96.8 97.1 98.4 98.9 100.1 100.4 100.2 100.3 100.1 100.2 100.0 100.1 -8

-10 96.5 96.8 98.0 98.5 99.7 100.5 100.5 100.6 100.4 100.5 100.3 100.4 -10

-12 96.1 96.4 97.6 98.2 99.4 100.1 100.8 100.8 100.7 100.7 100.6 100.6 -12

-14 95.7 96.1 97.3 97.8 99.0 99.8 101.0 101.1 100.9 101.0 100.8 100.9 -14

-16 95.4 95.7 96.9 97.4 98.6 99.4 100.6 101.3 101.2 101.2 101.1 101.1 -16-18 95.0 95.3 96.5 97.1 98.3 99.0 100.2 101.1 101.4 101.4 101.3 101.3 -18

-20 94.6 95.0 96.1 96.7 97.9 98.6 99.8 100.7 101.5 101.5 101.5 101.5 -20

-22 94.3 94.6 95.8 96.3 97.5 98.2 99.4 100.3 101.5 101.5 101.5 101.5 -22

-24 93.9 94.2 95.4 95.9 97.1 97.9 99.0 99.9 101.2 101.5 101.5 101.5 -24

-26 93.5 93.8 95.0 95.6 96.7 97.5 98.7 99.5 100.8 101.5 101.5 101.5 -26-28 93.1 93.5 94.6 95.2 96.3 97.1 98.3 99.1 100.4 101.2 101.5 101.5 -28

-30 92.8 93.1 94.3 94.8 96.0 96.7 97.9 98.7 100.0 100.8 101.5 101.5 -30

-32 92.4 92.7 93.9 94.4 95.6 96.3 97.5 98.3 99.6 100.4 101.5 101.5 -32

-34 92.0 92.3 93.5 94.0 95.2 95.9 97.1 97.9 99.2 100.1 101.5 101.5 -34

-36 91.6 92.0 93.1 93.7 94.8 95.5 96.7 97.5 98.8 99.7 101.1 101.5 -36-38 91.3 91.6 92.7 93.3 94.4 95.1 96.3 97.1 98.4 99.2 100.7 101.4 -38

-40 90.9 91.2 92.3 92.9 94.0 94.7 95.9 96.7 98.0 98.8 100.2 101.0 -40

-42 90.5 90.8 91.9 92.5 93.6 94.3 95.5 96.3 97.6 98.4 99.8 100.6 -42

-44 90.1 90.4 91.5 92.1 93.2 93.9 95.1 95.9 97.2 98.0 99.4 100.2 -44

-46 89.7 90.0 91.2 91.7 92.8 93.5 94.7 95.5 96.8 97.6 99.0 99.7 -46-48 89.3 89.6 90.8 91.3 92.4 93.1 94.3 95.1 96.3 97.2 98.5 99.3 -48

-50 88.9 89.3 90.4 90.9 92.0 92.7 93.8 94.7 95.9 96.7 98.1 98.9 -50

-52 88.5 88.9 90.0 90.5 91.6 92.3 93.4 94.3 95.5 96.3 97.7 98.4 -52-54 88.2 88.5 89.6 90.1 91.2 91.9 93.0 93.9 95.1 95.9 97.3 98.0 -54(ºC) (ºC)SAT SATPressure altitude (ft)

7,000 8,000 9,000 10,0005,000 6,000

10,0006,000 7,000 8,000 9,000Pressure altitude (ft)

5,000


AFM Supplement





94.7 94.4

95.2 95.095.8 95.5


MAXIMUM ITT: 952ºC



94.7 94.4

95.2 95.095.8 95.5


MAXIMUM ITT: 952ºC SAT SAT(ºC) (ºC)10 97.3 97.1 97.1 96.9 97.0 96.8 96.8 96.6 96.6 96.4 10

8 97.6 97.4 97.5 97.3 97.3 97.1 97.2 97.0 97.0 96.8 8

6 97.9 97.8 97.8 97.7 97.7 97.5 97.5 97.4 97.4 97.2 6

4 98.2 98.1 98.1 98.0 98.0 97.9 97.9 97.7 97.7 97.6 42 98.5 98.5 98.4 98.4 98.3 98.3 98.2 98.1 98.0 98.0 2

0 98.8 98.8 98.7 98.7 98.6 98.6 98.5 98.5 98.3 98.3 0

-2 99.1 99.2 99.0 99.1 98.9 99.0 98.8 98.8 98.7 98.7 -2

-4 99.4 99.5 99.3 99.4 99.2 99.3 99.1 99.2 99.0 99.1 -4

-6 99.7 99.8 99.6 99.7 99.5 99.6 99.4 99.5 99.3 99.4 -6-8 100.0 100.1 99.9 100.0 99.8 100.0 99.7 99.8 99.6 99.7 -8

-10 100.3 100.4 100.2 100.3 100.1 100.2 100.0 100.1 99.9 100.0 -10

-12 100.6 100.6 100.5 100.6 100.4 100.5 100.3 100.4 100.2 100.3 -12

-14 100.8 100.9 100.8 100.8 100.7 100.7 100.6 100.7 100.5 100.6 -14

-16 101.1 101.1 101.0 101.1 100.9 101.0 100.9 100.9 100.8 100.8 -16-18 101.3 101.3 101.2 101.3 101.2 101.2 101.1 101.1 101.0 101.1 -18

-20 101.5 101.5 101.5 101.5 101.4 101.4 101.3 101.3 101.2 101.3 -20

-22 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.4 101.5 -22

-24 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -24

-26 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -26-28 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -28

-30 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -30

-32 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -32

-34 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -34

-36 101.1 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -36-38 100.7 101.4 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -38

-40 100.2 101.0 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -40

-42 99.8 100.6 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -42

-44 99.4 100.2 101.5 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -44

-46 99.0 99.7 101.1 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -46-48 98.5 99.3 100.7 101.5 101.5 101.5 101.5 101.5 101.5 101.5 -48

-50 98.1 98.9 100.3 101.0 101.5 101.5 101.5 101.5 101.5 101.5 -50

-52 97.7 98.4 99.8 100.6 101.5 101.5 101.5 101.5 101.5 101.5 -52-54 97.3 98.0 99.4 100.2 101.4 101.5 101.5 101.5 101.5 101.5 -54(ºC) (ºC)SAT SAT

14,000Pressure altitude (ft)

10,000 11,000 12,000 13,000

13,000 14,00010,000 11,000 12,000Pressure altitude (ft)


AFM Supplement



MAXIMUM CONTINUOUS N1WITH ENGINE AND AIRFRAME ICE PROTECTION


94.7 94.4

95.2 95.095.8 95.5


MAXIMUM ITT: 924ºC



94.7 94.4

95.2 95.095.8 95.5


MAXIMUM ITT: 924ºC TAT TAT(ºC) (ºC)10 92.6 92.8 94.9 94.7 94.4 94.2 93.7 93.6 93.1 93.0 92.4 92.3 10

8 92.3 92.5 95.3 95.1 94.8 94.6 94.2 94.0 93.5 93.4 92.8 92.7 8

6 92.0 92.1 95.6 95.5 95.1 95.0 94.5 94.4 93.9 93.8 93.2 93.1 6

4 91.7 91.8 95.9 95.9 95.4 95.4 94.9 94.8 94.3 94.2 93.6 93.5 42 91.3 91.5 96.2 96.2 95.8 95.7 95.3 95.2 94.6 94.6 94.0 93.9 2

0 91.0 91.2 95.9 96.1 96.1 96.1 95.6 95.6 95.0 95.0 94.4 94.3 0

-2 90.7 90.8 95.5 95.7 96.4 96.4 96.0 96.0 95.4 95.4 94.7 94.7 -2

-4 90.4 90.5 95.2 95.4 96.6 96.7 96.3 96.3 95.7 95.7 95.1 95.1 -4

-6 90.0 90.2 94.8 95.0 96.9 97.0 96.6 96.6 96.0 96.0 95.4 95.4 -6-8 89.7 89.8 94.5 94.7 97.2 97.3 96.9 96.9 96.4 96.4 95.8 95.8 -8

-10 89.4 89.5 94.1 94.3 97.5 97.6 97.2 97.2 96.7 96.7 96.2 96.2 -10

-12 89.0 89.2 93.8 94.0 97.8 97.9 97.4 97.5 97.0 97.1 96.5 96.5 -12

-14 88.7 88.8 93.4 93.6 98.0 98.1 97.7 97.8 97.3 97.4 96.8 96.9 -14-16 88.3 88.5 93.1 93.2 98.3 98.4 98.0 98.1 97.6 97.7 97.2 97.2 -16-18 88.0 88.1 92.7 92.9 98.6 98.7 98.2 98.4 97.9 98.0 97.5 97.5 -18

-20 87.7 87.8 92.4 92.5 98.7 99.0 98.5 98.6 98.1 98.3 97.7 97.9 -20

-22 87.3 87.5 92.0 92.2 98.3 99.1 98.7 98.9 98.4 98.6 98.0 98.2 -22

-24 87.0 87.1 91.6 91.8 97.9 98.7 98.9 99.2 98.6 98.9 98.3 98.5 -24

-26 86.6 86.8 91.3 91.4 97.6 98.3 99.2 99.4 98.9 99.1 98.5 98.7 -26-28 86.3 86.4 90.9 91.1 97.2 97.9 99.3 99.6 99.1 99.3 98.7 99.0 -28

-30 85.9 86.1 90.5 90.7 96.8 97.5 99.5 99.8 99.3 99.5 98.9 99.2 -30

-32 85.6 85.7 90.2 90.3 96.4 97.2 99.7 99.9 99.5 99.7 99.1 99.4 -32

-34 85.2 85.4 89.8 90.0 96.0 96.8 99.9 100.1 99.6 99.9 99.3 99.5 -34

-36 84.9 85.0 89.4 89.6 95.6 96.4 100.0 100.2 99.8 100.0 99.5 99.7 -36-38 84.5 84.7 89.1 89.2 95.2 96.0 100.2 100.3 99.9 100.1 -38

-40 84.2 84.3 88.7 88.9 94.8 95.6 100.4 100.4 100.1 100.2 -40

-42 83.8 84.0 88.3 88.5 94.4 95.2 100.6 100.5 -42

-44 83.4 83.6 87.9 88.1 94.0 94.8 -44

-46 83.1 83.2 87.6 87.7 -46-48 -48

-50 -50

-52 -52

-54 -54-56 -56

(ºC) (ºC)TAT TATPressure altitude (ft)

20,000 25,0000 5,000 10,000 15,000



AFM Supplement





94.7 94.4

95.2 95.0

95.8 95.5


MAXIMUM ITT: 924ºC



94.7 94.4

95.2 95.0

95.8 95.5


MAXIMUM ITT: 924ºC TAT TAT(ºC) (ºC)10 92.4 92.3 10

8 92.8 92.7 8

6 93.2 93.1 6

4 93.6 93.5 42 94.0 93.9 93.3 93.3 2

0 94.4 94.3 93.6 93.6 0

-2 94.7 94.7 94.0 94.0 -2

-4 95.1 95.1 94.4 94.4 -4

-6 95.4 95.4 94.8 94.8 94.1 94.1 92.2 92.3 -6-8 95.8 95.8 95.2 95.1 94.5 94.4 92.5 92.6 -8

-10 96.2 96.2 95.5 95.5 94.9 94.8 92.9 93.0 -10

-12 96.5 96.5 95.9 95.9 95.3 95.2 94.5 94.5 93.4 93.4 -12

-14 96.8 96.9 96.3 96.3 95.7 95.7 94.9 94.9 93.9 93.8 92.4 92.4 -14

-16 97.2 97.2 96.6 96.6 96.0 96.1 95.3 95.3 94.4 94.3 92.9 92.8 -16-18 97.5 97.5 96.9 97.0 96.4 96.4 95.7 95.7 94.9 94.8 93.4 93.4 -18

-20 97.7 97.9 97.2 97.4 96.7 96.8 96.1 96.2 95.3 95.3 94.0 93.9 -20

-22 98.0 98.2 97.6 97.7 97.0 97.1 96.5 96.5 95.8 95.8 94.6 94.5 -22

-24 98.3 98.5 97.8 98.0 97.3 97.5 96.8 96.9 96.2 96.2 95.1 95.1 -24

-26 98.5 98.7 98.1 98.3 97.6 97.8 97.1 97.2 96.6 96.6 95.6 95.6 -26-28 98.7 99.0 98.3 98.6 97.9 98.1 97.4 97.6 96.9 96.9 96.1 96.0 -28

-30 98.9 99.2 98.5 98.8 98.1 98.4 97.7 97.9 97.2 97.3 96.4 96.4 -30

-32 99.1 99.4 98.7 99.0 98.3 98.6 97.9 98.1 97.4 97.6 96.8 96.8 -32

-34 99.3 99.5 98.9 99.2 98.5 98.8 98.1 98.4 97.7 97.9 97.0 97.2 -34

-36 99.5 99.7 99.1 99.4 98.7 99.0 98.3 98.6 97.9 98.1 97.3 97.5 -36-38 99.3 99.5 98.9 99.1 98.5 98.8 98.1 98.3 97.5 97.7 -38

-40 99.4 99.6 99.0 99.3 98.6 98.9 98.3 98.5 97.7 97.9 -40

-42 99.6 99.7 99.2 99.4 98.8 99.0 98.4 98.6 97.9 98.1 -42

-44 99.7 99.8 99.3 99.4 98.9 99.1 98.6 98.7 98.0 98.3 -44

-46 99.9 99.8 99.4 99.5 99.1 99.2 98.7 98.8 98.2 98.4 -46-48 100.1 99.9 99.6 99.6 99.2 99.2 98.8 98.9 98.3 98.5 -48

-50 99.8 99.6 99.3 99.3 98.9 98.9 98.4 98.5 -50

-52 99.9 99.7 99.5 99.3 99.1 99.0 98.6 98.6 -52

-54 100.1 99.8 99.7 99.4 99.2 99.0 98.7 98.6 -54-56 100.2 99.9 99.8 99.5 99.4 99.1 98.8 98.6 -56

(ºC) (ºC)TAT TATPressure altitude (ft)

35,000 40,000 45,000 50,00025,000 30,000

35,000 40,000 45,000 50,000Pressure altitude (ft)

25,000 30,000


AFM Supplement





AFM Supplement



S+FLAPS 20º TAKE-OFF

• 5-14 Accelerate Stop Distance S+Flaps 20º

• 5-15 Take-off Distance With Engine Failure S+Flaps 20º

• 5-16 Factored All Engine Take-off Distance S+Flaps 20º

• 5-17 Balanced Field Length S+Flaps 20º

• 5-18 Maximum Take-off Weight Limited By Climb Requirements S+Flaps 20º

• 5-19 Take-off Climb Second Segment S+Flaps 20º


AFM Supplement



ACCELERATE STOP DISTANCE

S+FLAPS 20°

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

6543

100

80

60

40

20

0

-20

-40

(x1,000 m)

(x1,000 ft)

°C °F

38

36

34

32

30

28

26

24 11

12

13

14

15

16

17

7 8

+2+1

0-1-2

50

0

-10

Tak

e-of

f Wei

ght (

x1,0

00 lb

)R

unw

ay S

lope

Win

d(%

)

(x1,

000

kg)

Headwind

Tailwind1 1.5 2 2.5Distance

NOTE: With anti-icing onuse dotted lines.

REF.

REF.

Field Pressure Altitude (ft

)

9

(kt)

V1/

VR 1

0.90

3

10

REF.

22 10

50 120

2

0.5

REF.

0

2,000

4,000

6,000

8,000

10,000

12,000

14,000

WEIGHT LIMITATIONSSee Airplane Flight Manual, Section 1

40 18


AFM Supplement



TAKE-OFF DISTANCEWITH ENGINE FAILURE

S+FLAPS 20°

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

654321

100

80

60

40

20

0

-20

-40

(x1,000 lb)

(x1,000 kg)

°C °F

40

38

36

34

32

30

28

26

24 11

12

13

14

15

16

17

18

7 8

+2+1

0-1-2

50

0

-101000 300

500 200

0

Tak

e-of

f Wei

ght (

x1,0

00 lb

)R

unw

ay S

lope

Win

dC

lear

way

Len

gth

(%)

(ft) 100

(x1,

000

kg)

Headwind

Tailwind(m)

1 1.5 2 2.50.5 Distance

Maximum Allowable Clearway


WEIGHTLIMITATIONSSee Airplane FlightManual, Section 1

REF.

REF.


)

REF.

9

(kt)

REF.

V1/

VR 1

0.90

02,000

4,000

6,0008,000

10,000

12,00014,000


AFM Supplement



FACTORED ALL ENGINETAKE-OFF DISTANCE

S+FLAPS 20°

0

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

6543210

100

80

60

40

20

0

-20

-40

(x1,000 m)

(x1,000 ft)

°C °F

40

38

36

34

32

30

28

26

24 11

12

13

14

15

16

17

18

7 8

+2+1

0-1-2

50

0

-10

1000 300

500200

0 0

Tak

e-of

f Wei

ght (

x1,0

00 lb

)R

unw

ay S

lope

Win

d (k

t)C

lear

way

Len

gth

(%)

(ft)

100

(x1,

000

kg)

Headwind

Tailwind

(m)

1 1.5 2 2.50.5 Distance


Factored Distance (115%)


WEIGHT LIMITATIONSSee Airplane Flight Manual,Section 1

REF.

REF.

REF.

Field Pressure Altit

ude (ft)

REF.

02000

4000

6000

8000

10000

1200014000


AFM Supplement



BALANCED FIELD LENGTH

S+FLAPS 20°

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

6543

100

80

60

40

20

0

-20

-40

(x1,000 m)

(x1,000 ft)

°C °F

38

36

34

32

30

28

26

24 11

12

13

14

15

16

17

7 8

+2+1

0-1-2

50

0

-10

Tak

e-of

f Wei

ght (

x1,0

00 lb

)R

unw

ay S

lope

Win

d(%

)

(x1,

000

kg)

Headwind



WEIGHT LIMITATIONSSee Airplane Flight Manual, Section 1

REF.

REF.


)

9

(kt)

50 120

2

0.5

40 18

22 10

0

2,000

4,000

6,0008,000

10,000

12,00014,000

REF.

1


AFM Supplement



MAXIMUM TAKE-OFF WEIGHT

LIMITED BY CLIMB REQUIREMENTSS+FLAPS 20°

-50

30 35 40

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

50

14,00012,000

10,000

8,000

6,000

4,000

2,000

8,000

10,000

12,000

14,000

- S+FLAPS: 20°- L/G: Up- 2 Engines at Take-off Thrust- Speed: V2- Required Gradient: 2.7%

18171615141312

120

100

80

60

40

20

0

-20

-40

(x1,000 lb)

(x1,000 kg)

Max. Allowable Take-off Gross Weight

Field Pressure Altitude (ft)



°C °F


AFM Supplement



TAKE-OFF CLIMB SECOND SEGMENT

S+FLAPS 20°

-50

5 10 15

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

500

- L/G: Up- Speed: V2- 2 Engines at Take-off Thrust


120

100

80

60

40

20

0

-20

-40

REF.

Tak

e-of

f Wei

ght (

x100

0 lb

)

40

38

36

34

32

30

28

26

24

22 10

11

12

13

14

15

16

17

18

5 10 150

0

Gross Climb Gradient (%)

Net Climb Gradient (%)



2,0004,0006,0008,00010,00012,00014,00014,00012,000

10,0008,000

6,0004,000

02,000

(x10

00 k

g)

°C °F


AFM Supplement





AFM Supplement



SLATS TAKE-OFF

• 5-22 Accelerate Stop Distance Slats

• 5-23 Take-off Distance With Engine Failure Slats

• 5-24 Factored All Engine Take-off Distance Slats

• 5-25 Balanced Field Length - Lower Weights Slats

• 5-26 Balanced Field Length – Higher Weights Slats

• 5-27 Maximum Take-off Weight Limited By Climb Requirements Slats

• 5-28 Take-off Climb Second Segment Slats


AFM Supplement



ACCELERATE STOPDISTANCE

SLATS

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

6543

100

80

60

40

20

0

-20

-40

(x1,000 m)

(x1,000 ft)

°C °F

40

38

36

34

32

30

28

26

24 11

12

13

14

15

16

17

18

7 8

+2+1

0-1-2

50

0

-10

Tak

e-of

f Wei

ght (

x1,0

00 lb

)R

unw

ay S

lope

Win

d(%

)

(x1,

000

kg)

Headwind




REF.

REF.


)

9

(kt)

V1/

VR 1

0.90

3

10

REF.

REF.

22 10

50 120

11

3.5

0

2,000

4,000

6,000

8,000

10,00012,000

14,000


AFM Supplement



TAKE-OFF DISTANCEWITH ENGINE FAILURE

SLATS

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

654321

100

80

60

40

20

0

-20

-40

(x1,000 m)

(x1,000 ft)

°C °F

40

38

36

34

32

30

28

26

24 11

12

13

14

15

16

17

18

7 8

+2+1

0-1-2

50

0

-10

500 200

0

Tak

e-of

f Wei

ght (

x1,0

00 lb

)R

unw

ay S

lope

Win

dC

lear

way

Len

gth

(%)

(ft) 100

(x1,

000

kg)

Headwind

Tailwind

(m)

1 1.5 2 2.50.5 Distance




REF.

REF.


9

(kt)

V1/

VR 1

0.90

3

10

0

REF.

REF.

02,000

4,000

6,000

8,00010,000

12,000

14,000


AFM Supplement



FACTORED ALL ENGINETAKE-OFF DISTANCE

SLATS

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

654321

100

80

60

40

20

0

-20

-40

(x1,000 m)

(x1,000 ft)

°C °F

40

38

36

34

32

30

28

26

24 11

12

13

14

15

16

17

18

7 8

+2+1

0-1-2

50

0

-10

1000 300

500200

0

Tak

e-of

f Wei

ght (

x1,0

00 lb

)R

unw

ay S

lope

Win

d (k

t)C

lear

way

Len

gth

(%)

(ft)

100

(x1,

000

kg)

Headwind

Tailwind

(m)

1 1.5 2 2.50.5 Distance


Factored Distance (115%)



REF.

REF.

REF.


REF.

3

9 10

02,000

4,000

6,000

8,000

10,000

12,00014,000


AFM Supplement




SLATS

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

6543

100

80

60

40

20

0

-20

-40

(x1,000 m)

(x1,000 ft)

°C °F

38

36

34

32

30

28

26

24 11

12

13

14

15

16

17

7 8

+2+1

0-1-2

50

0

-10

Tak

e-of

f Wei

ght (

x1,0

00 lb

)R

unw

ay S

lope

Win

d(%

)

(x1,

000

kg)

Headwind

Tailwind

1 1.5 2 2.5Distance


REF.

REF.


9

(kt)

3

10

120

2

0.5

22 10

REF.

02,000

4,000

6,0008,000

10,00012,000

14,000

50


40 18

LOWER WEIGHTS


AFM Supplement




SLATS

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

6

100

80

60

40

20

0

-20

-40

(x1,000 m)

(x1,000 ft)

°C °F

38

36

34

32

30

28

26

24 11

12

13

14

15

16

17

7 8

+2+1

0-1-2

50

0

-10

Tak

e-of

f Wei

ght (

x1,0

00 lb

)R

unw

ay S

lope

Win

d(%

)

(x1,

000

kg)

Headwind

Tailwind

2 2.5 Distance


REF.

REF.


9

(kt)

3

10

120

22 10

REF.

10,00012,000

14,000

50


11 12 13 14

3.5 4

40 18

HIGHER WEIGHTS


AFM Supplement



MAXIMUM TAKE-OFF WEIGHT

LIMITED BY CLIMB REQUIREMENTSSLATS

-50

30 35 40

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

50

18171615141312

120

100

80

60

40

20

0

-20

-40

(x1,000 lb)

(x1,000 kg)

- Slats- L/G: Up- 2 Engines at Take-off Thrust- Speed: V2- Required Gradient: 2.7%

Take-off Weight



4,0006,0008,00010,00012,00014,000

14,00012,000 10,000


°C °F


AFM Supplement



TAKE-OFF CLIMB SECOND SEGMENT

SLATS

-50

5 10 15

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

50

- L/G: Up- Speed: V2- 2 Engines at Take-off Thrust


120

100

80

60

40

20

0

-20

-40

REF.

Tak

e-of

f Wei

ght (

x100

0 lb

)

40

38

36

34

32

30

28

26

24

22 10

11

12

13

14

15

16

17

18

5 10 150

0


Net Climb Gradient (%)



(x10

00 k

g)

°C °F

02,0004,0006,0008,00010,00012,00014,000

14,00012,000

10,0008,000

6,0004,000

2,0000


AFM Supplement



ENROUTE

• 5-30 En Route And Final Take-off Climb Gradient One Engine Inoperative Clean


AFM Supplement



5 10 15

Gro

ss W

eigh

t (x1

000

lb)

40

38

36

34

32

30

28

26

24

22

0 Gross Climb Gradient (%)

10

11

12

13

14

15

16

17

18

(x10

00 k

g)

-50

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40100

80

60

40

20

0

-20

-40

°C °F

REF.

5 10 150

5 10 150

Net Final Take-off Climb Gradient (Gross Climb Gradient - 0.9%)

Net En Route Climb Gradient (Gross Climb Gradient - 1.4%)


05,000

10,000

15,00020,000

25,000

10,000

15,000

20,000

25,00030,000

5,000 0

30,000

EN ROUTE AND FINALTAKE-OFF CLIMB GRADIENTONE ENGINE INOPERATIVE

CLEAN


See Airplane FlightManual, Section 5 forindicated airspeedversus gross weight

- Flaps: 0°- L/G: Up- 2 Engines at Maximum

Continuous- Speed: 1.5Vs



AFM Supplement



S+FLAPS 48º APPROACH AND LANDING

• 5-32 Maximum Landing Weight Limited Approach And Landing Climb Gradient Requirements S+Flaps 48º

• 5-33 One Engine Inoperative Approach Climb Gradient S+Flaps 20º

• 5-34 All Engines Operating Landing Climb Gradient S+Flaps 48º


AFM Supplement



MAXIMUM LANDING WEIGHT LIMITED APPROACHAND LANDING CLIMB GRADIENT REQUIREMENTS

S+FLAPS 48°

-50

30 35 40

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

50

- S+FLAPS: 48°- L/G: Down- 3 Engines at Take-off Thrust- Speed: Vref - 5- Required Gradient: 3.2%

181716151413

120

100

80

60

40

20

0

-20

-40

(x1,000 lb)

(x1,000 kg)Landing Weight

°C °F


02,0004,0006,0008,00010,00012,000

8,00010,000

12,00014,000

14,000


Max

Lan

ding

Wei

ght


AFM Supplement



ONE ENGINE INOPERATIVE

APPROACH CLIMB GRADIENTS+FLAPS 20°

5 10 15

Gro

ss W

eigh

t (x1

000

lb)

40

38

36

34

32

30

28

26

24

22

0


10

11

12

13

14

15

16

17

18

(x10

00 k

g)

-50

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

50 120

100

80

60

40

20

0

-20

-40

°C °F

REF.


-Flaps: 20°- L/G: Up- 2 Engines at Take-off Thrust- Speed: V Ref + 5 kts


Max Landing Weight

02,0004,0006,0008,00010,00012,00014,000

14,00012,000

10,0008,000

6,0004,000

0



AFM Supplement



ALL ENGINES OPERATINGLANDING CLIMB GRADIENT

S+FLAPS 48°

-50

5 10 15

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

50

Max. Take-off Weight:See Airplane Flight Manual,Section 1

120

100

80

60

40

20

0

-20

-40

REF.

Gro

ss W

eigh

t (x1

000

lb)

40

38

36

34

32

30

28

26

24

22 10

11

12

13

14

15

16

17

18

0




(x10

00 k

g)

°C °F

- Flaps: 48°- L/G: Down- Thrust: Take-off- Speed: REF - 5kt

Max. Landing Weight

02,0004,0006,0008,00010,00012,00014,000

14,00012,000

10,0008,000

6,000 4,0002,000

0


AFM Supplement



S+FLAPS 20º APPROACH AND LANDING

• 5-36 Maximum Landing Weight Limited Approach And Landing Climb Gradient Requirements And Maximum Brake Energy Approach Slats / Landing S+Flaps 20º

• 5-37 One Engine Inoperative Approach Climb Gradient Slats

• 5-38 All Engines Operating Landing Climb Gradient S+Flaps 20º


AFM Supplement



30

Landing Weight

-50

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

50 120

100

80

60

40

20

0

-20

-40

°C °F

MAXIMUM LANDING WEIGHT LIMITED BY APPROACH AND LANDINGCLIMB GRADIENT REQUIREMENTS AND MAXIMUM BRAKE ENERGY

APPROACH SLATS / LANDING S+FLAPS 20°

35 40

13 14 15 16 17 18

2,0004,000

6,0008,00010,000

12,000

14,000


Max

Lan

ding

Wei

ght

Approach Climb GradientSlatsL/G: Up2 Engines at Take-off Thrust

1 Engine WindmillingSpeed: V Ref + 20 ktsRequired Gradient: 2.4%

(x1000 lb)

(x1000 kg)

Climb Gradient Limited

Brake Energy Limit


AFM Supplement



5 10 15

Gro

ss W

eigh

t (x1

000

lb)

40

38

36

34

32

30

28

26

24

22

0


10

11

12

13

14

15

16

17

18

(x10

00 k

g)

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

50 120

100

80

60

40

20

0

-20

-40

°C °F

REF.

ONE ENGINE INOPERATIVEAPPROACH CLIMB GRADIENT

SLATS



02,0004,0006,0008,00010,00012,00014,000

14,00012,000

10,0008,000

6,000 4,0002,000

0

Max Landing Weight

-Flaps: Slats- L/G: Up- 2 Engines at Take-off Thrust- Speed: V Ref + 20 kts



AFM Supplement



ALL ENGINE OPERATINGLANDING CLIMB GRADIENT

S+FLAPS 20°

0

Am

bien

t Tem

pera

ture

-40

-30

-20

-10

0

10

20

30

40

50 120

100

80

60

40

20

0

-20

-40

°C °F

40

38

36

34

32

30

28

26

24 11

12

13

14

15

16

17

18

Gro

ss W

eigh

t (x1

,000

lb)

(x1,

000

kg)

5





REF.

22 10

10 15 20

02,0004,0006,0008,00010,00012,00014,000

14,00012,000

10,000 8,000 6,000 4,000

Max Landing Weight

- Flaps: 20°-L/G: Down-Thrust: Take-off-Speed: V Ref + 5 kts

2,0000

Premier Aircraft, LLC Doc. No. FTA-PA-001019 Rev C 18 Terminal Dr. East Alton, IL 62024

AFM Supplement

FAA Approved Date: September 30, 2009 6-1

SECTION 6 - NOISE

NOISE LEVELS

14 CFR PART 36 REQUIREMENTS

No determination has been made by the Federal Aviation Administration that the noise procedures and levels in this AFM Supplement are, or should be, acceptable or unacceptable for operation at, into, or out of, any airport.

The following noise levels comply with 14 CFR Part 36, Appendix B, Stage 4 maximum noise level requirements and were obtained by analysis of approved data from noise tests conducted under the provisions of 14 CFR Part 36, Amendment 28. The noise measurement and evaluation procedures used to obtain these noise levels are considered by the FAA to be equivalent to the Chapter 4 noise level required by the International Civil Aviation Organization (ICAO) in Annex 16, Volume I, Appendix 2, Amendment 8.

ICAO Annex 16, Volume 1, Appendix 2, Amendment 8 approval is applicable only after endorsement by the Civil Aviation Authority of the country of airplane registration.

Noise reference point Noise levels (EPNdB)

Flyover: With cut-back power 84.8

Approach 95.3

Lateral 90.6

PERFORMANCE CONDITIONS FOR NOISE LEVELS

Compliance with 14 CFR Part 36, Amendment 28 was shown using the following configurations:

- Take-off configuration: S+FLAPS 20º at a weight of 40,780 lb (18,500 kg).

- Approach configuration: S+FLAPS 48º at a weight of 35,715 lb (16,200 kg).


AFM Supplement


SECTION 6 - NOISE



AFM Supplement

FAA Approved Date: January 22, 2007 A-1

ANNEX

LIST OF APPLICABLE ANNEXES

ANNEX 3 - FERRY FLIGHT WITH ONE FUEL CONTROL COMPUTER INOPERATIVE

Refer to Honeywell Digital Electronic Engine Controls (DEEC) AFM Supplement, Annex 3 (Doc. No. AFMS220, Rev B or later approved revision) in the Airplane Flight Manual.

ANNEX 5 - FLIGHT WITH ONE FUEL CONTROL COMPUTER IN MANUAL MODE

Refer to Honeywell Digital Electronic Engine Controls (DEEC) AFM Supplement, Annex 5 (Doc. No. AFMS220, Rev B or later approved revision) in the Airplane Flight Manual.


AFM Supplement

FAA Approved Date: August 23, 2007 A-2

ANNEX



AFM Supplement


ANNEX 3 - FERRY FLIGHT WITH ONE FUEL CONTROL COMPUTER INOPERATIVE


No change to Annex 3 Limitations


No change to Annex 3 Procedures




STARTING ENGINES

CAUTION

Since ITT cannot be monitored by the inoperative engine computer, the ITT limit of:

- 952°C for the TFE 731-4-1C engine

must under no circumstances be exceeded.


No change to Annex 3 Performance

SECTION 6 - NOISE

No change


AFM Supplement


ANNEX 5 - FLIGHT WITH ONE FUEL CONTROL COMPUTER IN MANUAL MODE


No change to Annex 5 Limitations






PREFLIGHT CHECKS

CAUTION

1. Starting using battery power only is not recommended.

2. As ITT monitoring is not ensured by the inoperative computer, the pilot must pay particular attention to the engine parameter indicator of the computer which is in manual mode to respect the maximum ITT values of:


STARTING ENGINES

CAUTION

Since ITT cannot be monitored by the inoperative engine computer, the ITT limit of:


must under no circumstances be exceeded.


No change to Annex 5 Performance

SECTION 6 - NOISE

No change

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Dassault Aviation Mystere-Falcon 50 - maistl.commaistl.com/sites/wsa/50dash4/wp-content/uploads/2012/01/wsa-falcon... · Dassault Aviation Mystere-Falcon 50 ... CONTROL COMPUTER IN

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