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SUPPLEMENTS 8AIRWORTHINESS FLIGHT TEST DATA

Table of contents Issue 1

DTM537

UK registered A/C

EASA APPROVED

SUPPLEMENT No 8 TO THE EASA APPROVED AIRPLANE FLIGHT MANUAL

CONCERNING

AIRWORTHINESS FLIGHT TEST DATA

FOR UK REGISTERED A/C

This supplement gives information on rate of climb, stalling speeds, and flight at airspeed in excess ofVMO for test purposes or crew training.

Serial No :

Registration No :

This supplement must be attached to the DTM537 Airplane Flight Manual approved by the DGAC onNovember 30, 1994.

The information contained herein supplements the information of the basic Airplane Flight Manual.

For limitations, procedures and performance information not contained in this supplement, consult thebasic Airplane Flight Manual.

SECTIONS OF AIRPLANE FLIGHT MANUAL PARTS OF SUPPLEMENT

- Section 1 : LIMITATIONS..........................................................................................................Part 1

- Section 2 : EMERGENCY PROCEDURES ....................................................................... No change- Section 3 : ABNORMAL PROCEDURES.......................................................................... No change

- Section 4 : NORMAL PROCEDURES............................................................................... No change

- Section 5 : PERFORMANCE ....................................................................................................Part 2

- Annexes :......................................................................................................................... No change

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Issue 1

SUPPLEMENTS 8AIRWORTHINESS FLIGHT TEST DATA

Table of contents

F2000Airplane

Flight Manual

DTM537

EASA APPROVED

UK registered A/C

p

y

LIST OF REVISIONS

Parts changesRevisionand Date

Titleand

Approval reference Added Revised Removed

Original

12-may-1995

Airworthiness Flight Test Data(UK registered A/C)

Approved by DGAC.

First Issue of supplement 8.

Revision 1

12-jul-2010

New page layout.

Approved under DOA EASA.21.J.051authority under change referenceM3346.

Part 0 Issue 1

Part 1 Issue 1

Part 2 Issue 1

All pages.

LIST OF EFFECTIVE PARTS

Reference Issue Special applicability

Part 0 Issue 1 UK registered A/C

Part 1 Issue 1 UK registered A/C

Part 2 Issue 1 UK registered A/C

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F2000Airplane

Flight Manual

SUPPLEMENTS 8AIRWORTHINESS FLIGHT TEST DATA

Limitations Issue 1

DTM537

UK registered A/C

EASA APPROVED

FLIGHT IN EXCESS OF VMO / MMO

VMO / MMO may be exceeded when authorized for the purpose of pilot training or flight test, provided

the following conditions are observed:- Passengers are not carried.

- Altitude shall be at least 10,000 ft.

- There is no significant turbulence.

The increase in speed allowed is 20 kts above VMO or 0.02 above MMO.

If a higher speed than that stated above is inadvertently achieved, or if a severe buffet isencountered, take recovery action immediately by retarding the thrust levers, extending the airbrakesand making a gentle pull-up.

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SUPPLEMENTS 8AIRWORTHINESS FLIGHT TEST DATA

Limitations

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EASA APPROVED

UK registered A/C

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F2000Airplane

Flight Manual

SUPPLEMENTS 8AIRWORTHINESS FLIGHT TEST DATA

Performance Issue 1

DTM537

UK registered A/C

EASA APPROVED

STALL IDENTIFICATION

STALLING SPEEDS

Stall warning and stall recognition speeds are given page 2. Decrease speeds by 0.2 kt per 1 % aft offorward limit C.G. (see AFM 1-050-05).

STALLING TECHNIQUE

Intentional stalls may be attempted as follows:

- Center of gravity of the airplane within limitations.

- Altitude below 15,000 ft.

- Power levers set at idle.

- Airplane trimmed at an airspeed approximately 1.3 times the stall speed in the appropriateconfiguration.

- Airspeed shall be reduced at approximately one knot per second, avoiding rapid or violent

movements of the controls.As soon as the stall is recognized, prompt recovery action must be taken by forward movement ofthe control column until normal flight is resumed, any rolling tendancy being corrected by use ofailerons.

NOTE

Stall is preceded by stall warning, aerodynamic buffet and is defined by a nose-down pitch or fullback control column position.An occasional tendancy to roll would be easily corrected.

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SUPPLEMENTS 8AIRWORTHINESS FLIGHT TEST DATA

Performance

F2000Airplane

Flight Manual

DTM537

EASA APPROVED

UK registered A/C

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STALL WARNING SYSTEM CHECK

Indicated Airspeed:

CLEAN 10 FLAPS + SLATS - L/G UPWeight

lb/kg Stall warning (kt) Stall speed (kt) Stall warning (kt) Stall speed (kt)

20,000 / 9,072 103 90 92 83

22,000 / 9,979 108 94 97 87

24,000 / 10,886 113 98 101 91

26,000 / 11,794 117 102 105 94

28,000 / 12,700 122 106 109 98

30,000 / 13,608 126 110 113 101

32,000 / 14,515 130 113 116 104

34,000 / 15,422 134 117 120 108

36,000 / 16,330 138 120 123 111

20 FLAPS + SLATS - L/G UP 40 FLAPS + SLATS - L/G DOWNWeight

lb/kg Stall warning (kt) Stall speed (kt) Stall warning (kt) Stall speed (kt)

20,000 / 9,072 87 80 85 78

22,000 / 9,979 91 84 89 82

24,000 / 10,886 95 87 93 86

26,000 / 11,794 99 91 97 89

28,000 / 12,700 103 94 100 92

30,000 / 13,608 106 98 104 96

32,000 / 14,515 110 101 107 99

34,000 / 15,422 113 104 110 102

36,000 / 16,330 116 107 114 105

NOTE

Accuracy: Airspeeds 4 ktDeceleration rate: 1 kt/sec.

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SUPPLEMENTS 8AIRWORTHINESS FLIGHT TEST DATA

Performance Issue 1

DTM537

UK registered A/C

EASA APPROVED

GROSS PRESSURE RATE OF CLIMB

SECOND SEGMENT CLIMB

This chart gives the gross pressure rate of climb at the second segment as a function of pressurealtitude, ambient temperature and gross weight assuming the following configuration:

- Gear up, 20 flaps + slats.

- One engine at take-off thrust (Power lever in TAKE-OFF position ).

- Engine and wing anti-icing off.

- One engine windmilling.*

- Take-off safety speed V2.

* For engine running at idle thrust, increase gross pressure rate of climb by 90 ft/min for 36,000 lb A/Cweight and 150 ft/min for 20,000 lb.

EN ROUTE CLIMB

This chart gives the gross pressure rate of climb for en route condition as a function of pressurealtitude, ambient temperature and gross weight assuming the following configuration:

- Clean airplane.

- One engine at maximum continuous thrust (Power lever in MAX CLIMB position).

- Engine and wing anti-icing off.

- One engine windmilling.*

- En route climb speed.

* For engine running at idle thrust, increase gross pressure rate of climb by 130 ft/min for 36,000 lbA/C weight and 170 ft/min for 20,000 lb.

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SUPPLEMENTS 8AIRWORTHINESS FLIGHT TEST DATA

Performance

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DTM537

EASA APPROVED

UK registered A/C

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y

WEIGHT LIMITATIONSsee 1-050-05

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F2000Airplane

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SUPPLEMENTS 8AIRWORTHINESS FLIGHT TEST DATA

Performance Issue 1

DTM537

UK registered A/C

EASA APPROVED

See 5-600-05 forindicated airspeedversus gross weight

WEIGHT LIMITATIONS

see 1-050-05

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SUPPLEMENTS 8AIRWORTHINESS FLIGHT TEST DATA

Performance

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DTM537

EASA APPROVED

UK registered A/C

p

y

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