SA227-CC
PART B STANDARD REFERENCE DATA
CONTENTS
ITEM PAGE
Takeoff Noise Levels...........................................................................................................................4B-1
Fuel Venting and Exhaust Emissions .................................................................................................4B-1
Wind Component Chart.......................................................................................................................4B-2
Compressibility and Position Error Correction to Indicated OAT (IOAT) ............................................ 4B-3
Relationship of Outside Air Temperature to ISA Temperature ........................................................... 4B-4
Airspeed Calibration Normal System
Gear Up, Flaps Up .....................................................................................................................4B-5
Gear Up, Flaps 1/4 .....................................................................................................................4B-6
Gear Down, Flaps 1/4 ................................................................................................................4B-7
Gear Down, Flaps 1/2 ................................................................................................................4B-8
Gear Down, Flaps Down ............................................................................................................4B-9
Ground Operation, Gear Down, Flaps 1/4 ............................................................................... 4B-10
Altimeter Correction Normal System
Gear Up or Down, Flaps Up ..................................................................................................... 4B-11
Gear Up or Down, Flaps 1/4 .................................................................................................... 4B-11
Gear Down, Flaps 1/2 ..............................................................................................................4B-11
Gear Down, Flaps Down ..........................................................................................................4B-11
Airspeed Calibration Alternate System
Gear Up, Flaps Up ................................................................................................................... 4B-12
Gear Down, Flaps 1/2 or Down ................................................................................................ 4B-13
Altimeter Correction Alternate System
Gear Up, Flaps Up ................................................................................................................... 4B-14
Gear Down, Flaps 1/2 ..............................................................................................................4B-15
Gear Down, Flaps Down ..........................................................................................................4B-15
Zero Thrust Stall Speeds ..................................................................................................................4B-16
FAA APPROVED: DEC 11/92 PERFORMANCE 4B-i
6CC
SA227-CC
THIS PAGE LEFT BLANK INTENTIONALLY
4B-ii PERFORMANCE MANUFACTURER'S DATA
6CC ISSUED: DEC 11/92
SA227-CC
TAKEOFF NOISE LEVELS
Takeoff noise level measured in accordance with FAR 36 subpart F is 80.4 dB(A).
NOTE
No determination has been made by the Federal Aviation
Administration that the noise levels of this aircraft are or should be
acceptable for operation at, into, or out of any airport.
FUEL VENTING AND EXHAUST EMISSIONS
This airplane complies with SFAR 27, "Fuel Venting and Exhaust Emissions Requirements for Turbine
Engine Powered Airplanes", which is equivalent to FAR PART 34, effective September 10, 1990.
FAA APPROVED: DEC 11/92 PERFORMANCE 4B-1
6CC
SA227-CC
WIND COMPONENT CHART
EXAMPLE:
GIVEN: WIND VELOCITY = 25 KNOTS
AT 40 OFF RUNWAY HEADING
OBTAIN: HEADWIND COMPONENT = 19 KNOTS
CROSSWIND COMPONENT = 16 KNOTS
NOTE
DEMONSTRATED CROSSWIND COMPONENT IS 20 KNOTS.
10 o
35
o
20
o
30
30
W EE TS)
SP NO
IN D
o
(K
D
40
LE Y
HEADWIND COMPONENT (KNOTS)
G A
25 35 AN NW )
D S
50
o IN RU E
W M RE
O G
FR (DE
30
20
60o
25
15
20
o
70
15
10
10
80o
5
5
0
0 5 10 15 20 25 30 35
CROSSWIND COMPONENT (KNOTS)
FIGURE 4B-1
4B-2 PERFORMANCE FAA APPROVED: DEC 11/92
6CC
SA227-CC
COMPRESSIBILITY AND POSITION ERROR CORRECTION TO INDICATED
OUTSIDE AIR TEMPERATURE (IOAT)
TEMPERATURE PROBE RECOVERY FACTOR .65
ASSUMES ZERO TEMPERATURE INDICATOR ERROR
EXAMPLE: I NOTE
l TEMPERATURE RISE IS SHOWN FOR STANDARD DAY
GIVEN: INDICATED AIRSPEED = 181 KIAS AMBIENT TEMPERATURES. FOR AMBIENT TEMPERA-
PRESSURE ALTITUDE = 15,000 FEET TURES WITHIN f40% OF STANDARD, THE TEMPERA-
IOAT = - 10C TURE RISE MAY VARY BY AS MUCH AS k2.5C FROM
OBTAIN: AT = - 4.5% THAT SHOWN.
OAT = IOAT + AT
E-10+(-4.5) l IOAT NOTED WHEN PARKED OR TAXIING MAY NOT BE
= - 14.5% ACCURATE.
-1
-2
-3
-4
-5
-6
-7
-8
-9
-100 120 140 160 180 200 220 240 260
INDICATED AIRSPEED (KNOTS)
(ASSUMES NO INSTRUMENTERROR)
FIGURE 4B-2
FAA APPROVED: DEC 1 l/92 PERFORMANCE 48-3
6CC
SA227-CC
RELATIONSHIP OF OUTSIDE AIR TEMPERATURE TO ISA TEMPERATURE
50
EXAMPLE: 120
GIVEN: OAT = 15oC
110
ALTITUDE = 10,000 FEET
40 OBTAIN: CONDITION = ISA +20oC
100
90
30
80
70
20
60
10 50
IS 40
A
+4
0 0o
IS C 30
A
OAT (oC)
OAT (oF)
+3
0o
IS C
A 20
+2
0o
10 IS C
A
+1 10
0o
C
IS
A 0
20 IS
A
1
0o 10
C
IS
A
2
20
0
30
oC
IS
A
3
0o 30
C
IS
A
4
40 40
0
oC
IS
A
5
0
oC
50
IS
A
6
0
50
oC
60
MINIMUM OPERATING TEMPERATURE
70
60
S.L. 5 10 15 20 25 30
PRESSURE ALTITUDE (THOUSANDS OF FEET)
FIGURE 4B-3
4B-4 PERFORMANCE FAA APPROVED: DEC 11/92
6CC
SA227-CC
AIRSPEED CALIBRATION - NORMAL SYSTEM
GEAR UP, FLAPS UP
EXAMPLE:
GIVEN: INDICATED AIRSPEED = 125 KIAS
GROSS WEIGHT = 16,000 POUNDS (7260 kg)
OBTAIN: CALIBRATED AIRSPEED = 126 KCAS
260
240
220
200
180
160
140
120
100
80
--80 120 140 160 180 200 220 240 260
INDICATED AIRSPEED (KNOTS)
(ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-4
FAA APPROVED: DEC 11/92 PERFORMANCE 4B-5
6CC
SA227-CC
AIRSPEED CALIBRATION - NORMAL SYSTEM
GEAR UP, FLAPS l/4
EXAMPLE:
GIVEN: INDICATED AIRSPEED = 145 KIAS
GROSS WEIGHT = ALL WEIGHTS
OBTAIN: CALIBRATED AIRSPEED = 146 KCAS
c? 180
5
G
E;
w 160
W
%
z
$ 140
2
ifi
i
4 120
80
80 100 120 140 160 180 200 220
INDICATED AIRSPEED (KNOTS)
(ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-5
4B-6 PERFORMANCE FAA APPROVED: DEC 1 l/92
6CC
SA227-CC
AIRSPEED CALIBRATION - NORMAL SYSTEM
GEAR DOWN, FLAPS l/4
EXAMPLE:
GIVEN: INDICATED AIRSPEED = 158 KIAS
GROSS WEIGHT = ALL WEIGHTS
OBTAIN: CALIBRATED AIRSPEED = 159 KCAS
180
80
I
INDICATED AIRSPEED (KNOTS)
(ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-6
FAA APPROVED: DEC 11/92 PERFORMANCE 4B-7
6CC
SA227-CC
AIRSPEED CALIBRATION - NORMAL SYSTEM
GEAR DOWN, FLAPS 112
EXAMPLE:
180
160
140
100
80
60
(
INDICATED AIRSPEED (KNOTS)
(ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-7
4B-8 PERFORMANCE FAA APPROVED: DEC 1l/92
6CC
SA227-CC
AIRSPEED CALIBRATION - NORMAL SYSTEM
GEAR DOWN, FLAPS DOWN
EXAMPLE:
GIVEN: INDICATED AIRSPEED = 108 KIAS
GROSS WEIGHT = 10,000 POUNDS (4540 kg)
OBTAIN: CALIBRATED AIRSPEED = 106 KCAS
180
160
80
60
60 80 100 120 140 160 180
INDICATED AIRSPEED (KNOTS)
(ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-8
FAA APPROVED: DEC 11/92 PERFORMANCE 4B-9
6CC
SA227-CC
AIRSPEED CALIBRATION - F,OR GROUND OPERATION - NORMAL SYSTEM
GEAR DOWN, FLAPS l/4
EXAMPLE:
GIVEN: INDICATED AIRSPEED = 80 KIAS
GROSS WEIGHT = ALL WEIGHTS
OBTAIN: CALIBRATED AIRSPEED = 79 KCAS
60
50 60 70 80 90 100 110 120 130 140
INDICATED AIRSPEED (KNOTS)
(ASSUMES NO INSTRUMENT ERROR)
FIGURE 48-9
4B-10 PERFORMANCE FAA APPROVED: DEC 11/92
6CC
SA227-CC
ALTIMETER CORRECTION - NORMAL SYSTEM
GEAR UP OR DOWN, FLAPS UP
The altimeter correction is less than minus 30 feet throughout the normal operating range of airspeeds
and altitudes.
GEAR UP OR DOWN, FLAPS l/4
The altimeter correction is less than minus 30 feet throughout the normal operating range of airspeeds
and for altitudes from sea level to 20,000 feet.
GEAR DOWN, FLAPS 112
The altimeter correction is less than minus 30 feet throughout the normal operating range of airspeeds
and for altitudes from sea level to 10,000 feet.
GEAR DOWN, FLAPS DOWN
FXAMPI F;
GIVEN: INDICATED AIRSPEED = 124 KNOTS
INDICATED ALTITUDE = 5,000 FEET
GROSS WEIGHT = 12,000 POUNDS (5440 kg)
OBTAIN: CORRECTED ALTITUDE =
(5,000 - 29) = 4,971 FEET
0
2
%
9 -10
z
P
5 -20
6
E
6
0 -30
b
t;
z
2
.-60 70 80 90 100 110 120 130 140 150 160
INDICATED AIRSPEED (KNOTS)
(INDICATED ALTITUDE AND AIRSPEED ASSUME NO INSTRUMENT ERROR)
FIGURE 4B-10
FAA APPROVED: DEC 11/92 PERFORMANCE 4B-11
6CC
SA227-CC
AIRSPEED CALIBRATION - ALTERNATE SYSTEM
GEAR UP, FLAPS UP
EXAMPLE: ----4
l DO NOT DUMP PRESSURIZATION WHEN USING THE
GIVEN: INDICATED AIRSPEED = 172 KIAS
ALTERNATE STATIC SOURCE.
0BTAIN:CALlBRATED AIRSPEED = 170 KCAS
. THEAIRSPEEDCORRECTION GIVEN IS NOTVALIDIFTHE
DUMP VALVE IS OPEN.
NOTE
THE COPILOTS STATIC PRESSURE INSTRUMENTS ARE
NOT CONNECTED TO THE ALTERNATE STATIC SOURCE.
260
240
Ef 160
k
E
i
4 140
120
100
80
80 100 120 140 160 180 200 220 240 260
INDICATED AIRSPEED (KNOTS)
(ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-11
4B-12 PERFORMANCE FAA APPROVED: DEC 1 l/92
6CC
SA227GC
AIRSPEED CALIBRATION - ALTERNATE SYSTEM
GEAR DOWN, FLAPS l/2 OR DOWN
EXAMPLE:
GIVEN: INDICATED AIRSPEED = 114 KIAS
OBTAIN: CALIBRATED AIRSPEED = 116 KCAS
*DO NOT DUMP PRESSURIZATION WHEN USING THE
. THE AIRSPEED CORRECTION GIVEN IS NOTVALID IF THE
NOTE
THE COPILOTS STATIC PRESSURE INSTRUMENTS ARE
NOT CONNECTED TO THE ALTERNATE STATIC SOURCE.
180
160
80
60
I 80 100 120 140 160 18
INDICATED AIRSPEED (KNOTS)
(ASSUMES NO INSTRUMENT ERROR)
FIGURE 4B-12
FAA APPROVED: DEC 1 l/92 PERFORMANCE 4B-13
6CC
ALTIMETER CORRECTION - ALTERNATE SYSTEM
GEAR UP, FLAPS UP
EXAMPLE:
GIVEN: INDICATED AIRSPEED = 165 KNOTS l DO NOT DUMP PRESSURIZATION WHEN USING
INDICATED ALTITUDE = 20,000 FEET
OBTAIN: CORRECTED ALTITUDE =
(20,000 - 120) = 19,880 FEET l THE AIRSPEED CORRECTION GIVEN IS NOT VALID
0
Liz-- NoTEl
THE COPILOTS STATIC PRESSURE INSTRUMENTS
ARE NOT CONNECTED TO THE ALTERNATE STATIC
-50
-100
-150
-200
-250
B
L
E
5-f 300
-350
400
80 90 100 110 120 130 140 150 160 170 180 190 200 210 220 230 240
INDICATED AIRSPEED (KNOTS)
(INDICATED ALTITUDE AND AIRSPEED ASSUME NO INSTRUMENT ERROR)
SA227-CC
ALTIMETER CORRECTION -ALTERNATE SYSTEM
CAUTION
l DO NOT DUMP PRESSURIZATION WHEN USING THE
ALTERNATE STATIC SOURCE.
l THE ALTIMETER CORRECTION GIVEN IS NOT VALID IF THE
DUMP VALVE IS OPEN.
NOTE
The copilots static pressure instruments are not connected to the
alternate static source.
GEAR DOWN, FLAPS l/2
The altimeter correction varies from plus 30 feet at 80 KIAS to minus 10 feet at 180 KIAS for altitudes
from sea level to 10,000 feet.
GEAR DOWN, FLAPS DOWN
EXAMPLE:
GIVEN: INDICATED AIRSPEED = 142 KNOTS
INDICATED ALTITUDE = 10,000 FEET
OBTAIN: CORRECTED ALTITUDE =
(10,000 - 35) = 9,965 FEET
50
-50
-100
-150
-200
I 70 80 90 100 110 120 130 140 150 160
INDICATED AIRSPEED (KNOTS)
(INDICATED ALTITUDE AND AIRSPEED ASSUME NO INSTRUMENT ERROR)
FIGURE 4B-14
A APPROVED: DEC 1l/92 PERFORMANCE 4B-15
6CC
SA227-CC
ZERO THRUST STALL SPEEDS
EXAMPLE: NOTE
l SPEEDS ARE BASED ON TESTS WITH BOTH PROPELLERS
GIVEN: GROSS WEIGHT = 14,000 POUNDS FEATHERED AND DEICE BOOTS DEFLATED.
(6350 kg)
FLAPS = 114 * SAS STALL BARRIER DEVICES (LIGHTS, HORNS, AND STICK
PUSHER) ARE SET TO ACTIVATE WITH FLIGHT IDLE POWER AT
BANK ANGLE = 20 THE ZERO THRUST STALL SPEEDS WITH A + 2 KIAS TOLERANCE.
OBTAIN: STALL SPEED = 96 KlAS
l PROPELLERS TURNING AERODYNAMIC STALL SPEEDS ARE A
MINIMUM OF 2 KIAS LESS THAN THE SAS STALL BARRIER
ACTIVATION SPEEDS FOR ALL FLIGHT CONDITIONS AND
CONFIGURATIONS.
l THE CENTER OF GRAVITY IS THE MOST FORWARD ALLOW-
ABLE AT EACH WEIGHT.
l THE GEAR IS UP OR DOWN FOR FLAPS UP AND l/4.
. THE GEAR IS DOWN FOR FLAPS l/2 AND DOWN.
l MAXIMUM ALTITUDE LOSS DURING RECOVERY FROM FLIGHT
IDLE POWER STALL PER FAR 23.201 IS APPROXIMATELY 500
FEET.
l MAXIMUM NOSE DOWN PITCH ATTITUDE CHANGE AND
ALTITUDE LOSS DURING RECOVERY FROM SINGLE ENGINE,
POWER ON STALLS PER FAR 23.205 ARE APPROXIMATELY
20 AND 200 FEET, RESPECTIVELY.
L
GROSS WEIGHT (KILOGRAMS)
7500 7000 65ofl 6000 5500 4500
150
140
16,000 15,ooO 14,ooo 13,ooo 12900 11,000 10,030 0 20 40
GROSS WEIGHT (POUNDS) BANK ANGLE (DEGREES)
FIGURE 4B-15
4B-16 PERFORMANCE FAA APPROVED: DEC 1 l/92
6CC
