16 f 11 performance standard reference parte j

METRO III – ICAO ANNEX 8 PART J – REDUCED POWER TAKEOFF OPERATIONS CONTENTS ITEM

PAGE

Introduction ......................................................................................................................................... 4J-1 Worksheet – Reduced Power Takeoff ................................................................................................ 4J-3 Example 1 .................................................................................................................................. 4J-4 Example 2 .................................................................................................................................. 4J-6 Example 3 .................................................................................................................................. 4J-8

FAA APPROVED: APR 17/97 REVISED: NOV 18/97

PERFORMANCE

4J-i 8AC

METRO III – ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4J-ii 8AC

PERFORMANCE

MANUFACTURER'S DATA ISSUED: APR 17/97

METRO III – ICAO ANNEX 8 INTRODUCTION Part J provides for the use of reduced engine power for takeoff by employing the Assumed Temperature Method (ATM). This technique allows takeoff with less than the maximum available engine power in those cases where excess climb performance and runway length are available.

The amount of power to be set for the reduced power takeoff is determined by assuming an air temperature, higher than the actual temperature, at which adequate performance is available.

The limitations applicable to reduced power operations are repeated below from Section 1.

1. The engine torque used for a takeoff may not be less than 90% of the torque shown by the appropriate power setting chart for the actual ambient conditions.

2. The use of reduced power for takeoff is not permitted on a wet runway or when the runway is contaminated with ice, slush or snow.

3. As a condition to the use of reduced power procedures, operators must establish a periodic check system or engine condition monitoring system to ensure that the engines are capable of producing normal takeoff thrust for the actual ambient temperature.

4. Minimum crew during reduced power takeoff operations is two pilots.

5. Air Carrier or Air Taxi commercial operators must have prior approval of the cognizant FAA inspector prior to conducting reduced power takeoff operations.

6. The use of reduced power for takeoff is not permitted if the Anti-skid System, if installed, is inoperative.

The correct engine torque to be set for reduced power takeoff is determined from the performance section using the technique illustrated by the filled-in work sheets on Figures 4J-2, 4J-3, and 4J-4.

For any given set of conditions, the procedure involves: 1. Determination of the highest OAT at which the performance requirements will allow takeoff; this becomes the assumed temperature.

2. Finding the torque to be used. This is the higher of the torque for a 10% power reduction at the actual OAT or the torque for the assumed temperature.

NOTE Determine both computed reduced power and maximum takeoff power torques. Set computed reduced power torque for takeoff.

If more power is required during takeoff (engine failure, windshear encounter, etc.), torque can be increased to maximum takeoff power torque.

3. Selection of the takeoff speeds for the actual OAT and takeoff weight conditions.

Use the procedure outlined by the form presented on Figure 4J-1 of this part, together with the performance data listed below, to establish the minimum safe power setting for takeoff and the associated scheduled speeds. The procedure is illustrated by three examples on pages 4J-4, 4J-6, and 4J-8.

FAA APPROVED: APR 17/97 REVISED: JUN 05/98

PERFORMANCE

4J-1 8AC

METRO III – ICAO ANNEX 8 INTRODUCTION (continued) Applicable Performance Data Takeoff Power Check Chart Dry, Bleed Air On .................................................................................................. Figure 4C-1 Dry, Bleed Air Off .................................................................................................. Figure 4D-1 Wet ........................................................................................................................ Figure 4E-1

Takeoff Speeds V1, VR, V2, and V50 Dry, Bleed Air On .................................................................................................. Figure 4C-3 Dry, Bleed Air Off ....................................................................................... Figure 4D-3 or 4I-2 Wet ............................................................................................................. Figure 4E-3 or 4I-7

Maximum Takeoff Weight Limitation Chart Dry, Bleed Air On .................................................................................................. Figure 4C-2 Dry, Bleed Air Off ....................................................................................... Figure 4D-2 or 4I-1 Wet ............................................................................................................. Figure 4E-2 or 4I-6

Distance to Accelerate to V1 and Stop Dry, Bleed Air On .................................................................................................. Figure 4C-4 Dry, Bleed Air Off ....................................................................................... Figure 4D-4 or 4I-3 Wet ............................................................................................................. Figure 4E-4 or 4I-8

Single Engine Takeoff Distance to 35 Foot Height Dry, Bleed Air On .................................................................................................. Figure 4C-5 Dry, Bleed Air Off ....................................................................................... Figure 4D-5 or 4I-4 Wet ............................................................................................................. Figure 4E-5 or 4I-9

4J-2 8AC

PERFORMANCE

FAA AAPPROVED: APR 17/97

METRO III – ICAO ANNEX 8 WORKSHEET REDUCED POWER TAKEOFF ASSUMED TEMPERATURE METHOD (ATM) (1)

ACTUAL PRESSURE ALTITUDE ....................................................................................................

FT.

(2)

ACTUAL OAT...................................................................................................................................

oC

(3)

RUNWAY LENGTH, SLOPE, AND WIND ...........................

(4)

GROSS WEIGHT .............................................................................................................................

(5)

MAX. OAT FOR GROSS WEIGHT (4),

FT.

%

KTS. LBS.

POWER

(a)

MAXIMUM TAKEOFF WEIGHT LIMITATION CHART ................................ FIG.

oC

(b)

DISTANCE TO ACCEL TO V1 AND STOP CHART ................................... FIG.

oC

(c)

SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT CHART .. FIG.

oC

NOTE WHEN (5a), (5b), AND (5c) RESULT IN MAX. OAT's WARMER THAN THE ISA +40 BOUNDARY IN THE FIGURES, THE ASSUME TEMPERATURE IS THE MAXIMUM TEMPERATURE APPROVED FOR THE ALTITUDE (ISA +40oC).

IF EITHER (5a), (5b), OR (5c) IS LOWER THAN ACTUAL OAT (2), THE GROSS WEIGHT MUST BE REDUCED OR A DIFFERENT POWER CONDITION USED.

(6)

ASSUMED TEMPERATURE [LOWER OF (5a), (5b), OR (5c)] , OR MAXIMUM ALLOWABLE ......................................................................................................................

(7)

(8)

oC

TORQUE, FROM TAKEOFF POWER CHECK CHART, FIGURE: (a)

FOR OAT (2) ................................................................................................................................

%

(b)

TORQUE FOR (a) – [(a) DIVIDED BY 10] ...................................................................................

%

(c)

FOR ASSUMED TEMPERATURE (6) .........................................................................................

%

(d)

COMPUTED TORQUE, USE HIGHER OF (b) OR (c) .................................................................

%

TAKEOFF SPEEDS, FIGURE: (a)

V1 FOR ALTITUDE (1), OAT (2), WEIGHT (4) ...........................................................................

KIAS

(b)

VR FOR ALTITUDE (1), OAT (2), WEIGHT (4) ..........................................................................

KIAS

(c)

V2 FOR ALTITUDE (1), OAT (2), WEIGHT (4) ...........................................................................

KIAS

(d)

V50 FOR ALTITUDE (1), OAT (2), WEIGHT (4) .........................................................................

KIAS

FIGURE 4J-1 FAA APPROVED: APR 17/97

PERFORMANCE

4J-3 8AC

METRO III – ICAO ANNEX 8 REDUCED POWER TAKEOFF (continued) EXAMPLE 1 Given Conditions: Engine Power Setting for Takeoff – Dry, Bleed Air Off Airport Altitude: 1,000 Feet Press. Alt. Airport OAT: 10oC Runway Length: 5,500 Feet Runway Slope: Level Airport Wind: No Wind Desired Takeoff Weight: 14,000 Lbs. • Supplemental Takeoff Performance in PART I is used for this example.

• Dry takeoff power with bleed air off is desired, so Figure 4I-2, Maximum Takeoff Weight Limitation Chart, is used to determine (5a).

• Figure 4I-3, Distance to Accelerate to V1 and Stop, is used with given runway length to determine (5b).

• Figure 4I-4, Single Engine Takeoff Distance to 35 Foot Height, is used with given runway length to determine (5c).

• Figure 4D-1, Takeoff Power Check Chart – Dry, Bleed Air Off, is used to determine (7a) and (7c).

• The torque for the actual OAT, when reduced by 10% (7b) is higher than that for the assumed temperature (7c), so the higher torque is used for the Computed Torque, (7d).

• Takeoff speeds are determined from Figure 4I-2.

4J-4 8AC

PERFORMANCE

FAA AAPPROVED: APR 17/97

METRO III – ICAO ANNEX 8 EXAMPLE 1 (continued)

WORKSHEET REDUCED POWER TAKEOFF ASSUMED TEMPERATURE METHOD (ATM)

(1)

ACTUAL PRESSURE ALTITUDE ....................................................................................................

1,000

FT.

(2)

ACTUAL OAT...................................................................................................................................

10

oC

(3)

RUNWAY LENGTH, SLOPE, AND WIND ...........................

0

(4)

GROSS WEIGHT .............................................................................................................................

(5)

MAX. OAT FOR GROSS WEIGHT (4),

DRY, BLEED AIR OFF

5,500

FT.

0

%

KTS.

14,000 LBS.

POWER

(a)

MAXIMUM TAKEOFF WEIGHT LIMITATION CHART ................................ FIG. 4I-1

34.5 oC

(b)

DISTANCE TO ACCEL TO V1 AND STOP CHART ................................... FIG. 4I-3

35.0 oC

(c)

SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT CHART .. FIG. 4I-4

28 oC

NOTE WHEN (5a), (5b), AND (5c) RESULT IN MAX. OAT's WARMER THAN THE ISA +40 BOUNDARY IN THE FIGURES, THE ASSUME TEMPERATURE IS THE MAXIMUM TEMPERATURE APPROVED FOR THE ALTITUDE (ISA +40oC).

IF EITHER (5a), (5b), OR (5c) IS LOWER THAN ACTUAL OAT (2), THE GROSS WEIGHT MUST BE REDUCED OR A DIFFERENT POWER CONDITION USED.

(6)

ASSUMED TEMPERATURE [LOWER OF (5a), (5b), OR (5c)] , OR MAXIMUM ALLOWABLE ......................................................................................................................

(7)

(8)

TORQUE, FROM TAKEOFF POWER CHECK CHART, FIGURE:

28 oC

4D-1

(a)

FOR OAT (2) ................................................................................................................................

95.8

%

(b)

TORQUE FOR (a) – [ (a) DIVIDED BY 10] ..................................................................................

86.2

%

(c)

FOR ASSUMED TEMPERATURE (6) .........................................................................................

80.5

%

(d)

COMPUTED TORQUE, USE HIGHER OF (b) OR (c) .................................................................

86.2

%

TAKEOFF SPEEDS, FIGURE:

4I-2

(a)

V1 FOR ALTITUDE (1), OAT (2), WEIGHT (4) ...........................................................................

107 KIAS

(b)

VR FOR ALTITUDE (1), OAT (2), WEIGHT (4) ..........................................................................

107 KIAS

(c)

V2 FOR ALTITUDE (1), OAT (2), WEIGHT (4) ...........................................................................

113 KIAS

(d)

V50 FOR ALTITUDE (1), OAT (2), WEIGHT (4) .........................................................................

123 KIAS

FIGURE 4J-2 FAA APPROVED: APR 17/97

PERFORMANCE

4J-5 8AC

METRO III – ICAO ANNEX 8 REDUCED POWER TAKEOFF (continued) EXAMPLE 2 Given Conditions: Engine Power Setting for Takeoff – Dry, Bleed Air Off Airport Altitude: 2,000 Feet Press. Alt. Airport OAT: 10oC Runway Length: 8,000 Feet Runway Slope: Level Airport Wind: 5 Knots Headwind Desired Takeoff Weight: 15,000 Lbs. • Takeoff Performance in PART D is used for this example.

• (5b) results in a Max. OAT greater than ISA +40oC, so the maximum allowable temperature of ISA +40oC is entered. The lower temperature of 21oC from (5a) is entered in (6).

• The Computed Torque, (7d) is limited by the assumed temperature (7c).

4J-6 8AC

PERFORMANCE

FAA AAPPROVED: APR 17/97

METRO III – ICAO ANNEX 8 EXAMPLE 2 (continued)

WORKSHEET REDUCED POWER TAKEOFF ASSUMED TEMPERATURE METHOD (ATM)

(1)

ACTUAL PRESSURE ALTITUDE ....................................................................................................

2,000

FT.

(2)

ACTUAL OAT...................................................................................................................................

10

oC

(3)

RUNWAY LENGTH, SLOPE, AND WIND ...........................

5

(4)

GROSS WEIGHT .............................................................................................................................

(5)

MAX. OAT FOR GROSS WEIGHT (4),

DRY, BLEED AIR OFF

8,000

FT.

0

%

KTS.

15,000 LBS.

POWER

(a)

MAXIMUM TAKEOFF WEIGHT LIMITATION CHART ................................ FIG. 4D-2

21 oC

(b)

DISTANCE TO ACCEL TO V1 AND STOP CHART ................................... FIG. 4D-4

ISA +40 oC

(c)

SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT CHART .. FIG. 4D-5

26 oC

NOTE WHEN (5a), (5b), AND (5c) RESULT IN MAX. OAT's WARMER THAN THE ISA +40 BOUNDARY IN THE FIGURES, THE ASSUME TEMPERATURE IS THE MAXIMUM TEMPERATURE APPROVED FOR THE ALTITUDE (ISA +40oC).

IF EITHER (5a), (5b), OR (5c) IS LOWER THAN ACTUAL OAT (2), THE GROSS WEIGHT MUST BE REDUCED OR A DIFFERENT POWER CONDITION USED.

(6)

ASSUMED TEMPERATURE [LOWER OF (5a), (5b), OR (5c)] , OR MAXIMUM ALLOWABLE ......................................................................................................................

(7)

(8)

TORQUE, FROM TAKEOFF POWER CHECK CHART, FIGURE:

21 oC

4D-1

(a)

FOR OAT (2) ................................................................................................................................

92.1

%

(b)

TORQUE FOR (a) – [ (a) DIVIDED BY 10] ..................................................................................

82.9

%

(c)

FOR ASSUMED TEMPERATURE (6) .........................................................................................

83.8

%

(d)

COMPUTED TORQUE, USE HIGHER OF (b) OR (c) .................................................................

83.8

%

TAKEOFF SPEEDS, FIGURE:

4D-3

(a)

V1 FOR ALTITUDE (1), OAT (2), WEIGHT (4) ...........................................................................

107 KIAS

(b)

VR FOR ALTITUDE (1), OAT (2), WEIGHT (4) ..........................................................................

113 KIAS

(c)

V2 FOR ALTITUDE (1), OAT (2), WEIGHT (4) ...........................................................................

116 KIAS

(d)

V50 FOR ALTITUDE (1), OAT (2), WEIGHT (4) .........................................................................

126 KIAS

FIGURE 4J-3 FAA APPROVED: APR 17/97

PERFORMANCE

4J-7 8AC

METRO III – ICAO ANNEX 8 REDUCED POWER TAKEOFF (continued) EXAMPLE 3 Given Conditions: Engine Power Setting for Takeoff – Dry, Bleed Air Off Airport Altitude: 2,000 Feet Press. Alt. Airport OAT: 25oC Runway Length: 10,000 Feet Runway Slope: Level Airport Wind: No Wind Desired Takeoff Weight: 15,000 Lbs. • Supplemental Takeoff Performance in PART I is used for this example.

• In this example (5a) results in a Max. OAT less than the actual airport OAT. • Gross weight must be reduced.

4J-8 8AC

PERFORMANCE

FAA AAPPROVED: APR 17/97

METRO III – ICAO ANNEX 8 EXAMPLE 3 (continued)

WORKSHEET REDUCED POWER TAKEOFF ASSUMED TEMPERATURE METHOD (ATM)

(1)

ACTUAL PRESSURE ALTITUDE ....................................................................................................

2,000

FT.

(2)

ACTUAL OAT...................................................................................................................................

25

oC

(3)

RUNWAY LENGTH, SLOPE, AND WIND ...........................

0

(4)

GROSS WEIGHT .............................................................................................................................

(5)

MAX. OAT FOR GROSS WEIGHT (4),

DRY, BLEED AIR OFF

10,000

FT.

0

%

KTS.

15,000 LBS.

POWER

(a)

MAXIMUM TAKEOFF WEIGHT LIMITATION CHART ................................ FIG. 4I-1

22.1 oC

(b)

DISTANCE TO ACCEL TO V1 AND STOP CHART ................................... FIG. 4I-3

ISA +40 oC

(c)

SINGLE ENGINE TAKEOFF DISTANCE TO 35 FOOT HEIGHT CHART .. FIG. 4I-4

46.1 oC

NOTE WHEN (5a), (5b), AND (5c) RESULT IN MAX. OAT's WARMER THAN THE ISA +40 BOUNDARY IN THE FIGURES, THE ASSUME TEMPERATURE IS THE MAXIMUM TEMPERATURE APPROVED FOR THE ALTITUDE (ISA +40oC).

➨ (6)

IF EITHER (5a), (5b), OR (5c) IS LOWER THAN ACTUAL OAT (2), THE GROSS WEIGHT MUST BE REDUCED OR A DIFFERENT POWER CONDITION USED.

ASSUMED TEMPERATURE [LOWER OF (5a), (5b), OR (5c)] , OR MAXIMUM ALLOWABLE ......................................................................................................................

(7)

(8)

oC

TORQUE, FROM TAKEOFF POWER CHECK CHART, FIGURE: (a)

FOR OAT (2) ................................................................................................................................

%

(b)

TORQUE FOR (a) – [ (a) DIVIDED BY 10] ..................................................................................

%

(c)

FOR ASSUMED TEMPERATURE (6) .........................................................................................

%

(d)

COMPUTED TORQUE, USE HIGHER OF (b) OR (c) .................................................................

%

TAKEOFF SPEEDS, FIGURE: (a)

V1 FOR ALTITUDE (1), OAT (2), WEIGHT (4) ...........................................................................

KIAS

(b)

VR FOR ALTITUDE (1), OAT (2), WEIGHT (4) ..........................................................................

KIAS

(c)

V2 FOR ALTITUDE (1), OAT (2), WEIGHT (4) ...........................................................................

KIAS

(d)

V50 FOR ALTITUDE (1), OAT (2), WEIGHT (4) .........................................................................

KIAS

FIGURE 4J-4 FAA APPROVED: APR 17/97

PERFORMANCE

4J-9 8AC

METRO III – ICAO ANNEX 8

THIS PAGE LEFT BLANK INTENTIONALLY

4J-10 8AC

PERFORMANCE

FAA MANUFACTURER'S AAPPROVED: APR DATA 17/97 ISSUED: APR 17/97