ISSUED: April 29, 2009
PILOT’S OPERATING HANDBOOK
and
Airplane Flight Manual Supplement
for the
SUPER KING AIR
MODELS
200/200C/B200/B200C
Equipped with Enhanced Aero:
• PT6A-52 Engines – STC SA10842SC
-AND-
Equipped with Raisbeck Engineering:
• Quiet Turbofan Propellers – STC SA2698NM-S
• Ram Air Recovery System – STC SA3366NM
• Enhanced Performance Leading Edges – STC SA3831NM
• Dual Aft Body Strakes – STC SA3519NM
• Fully Enclosed MLG Doors (when HFG-Equipped) – STC
SA4175NM
OR
• Quiet Turbofan Propellers – STC SA2698NM-S
• MARK VI System – STC SA1783NM
• Fully Enclosed MLG Doors (when HFG Equipped) – STC
SA1668NM
TABLE OF DIVISIONS
SECTION I...GENERAL
SECTION II...LIMITATIONS
SECTION III...EMERGENCY PROCEDURES
SECTION IV...NORMAL PROCEDURES
SECTION V...PERFORMANCE
SECTION VI...WEIGHT AND BALANCE
•
Dual Aft Body Strakes•
Fully Enclosed MLG Doors (when HFG-equipped)SECTION I – GENERAL
INTRODUCTION
Thank you…
for displaying your confidence in selecting quality products from
Raisbeck Engineering Inc. Our design engineers, craftsmen, and
technicians have utilized their professional skills and years of experience
to provide you with state-of-the-art systems to enhance the performance,
safety, and productivity of your Super King Air.
The information contained in this FAA-approved Pilot’s Operating
Handbook and Airplane Flight Manual Supplement highlights the areas of
performance improvements to the propeller, air induction system, engine
compartment, wing, and external drag items that increase the
performance and productivity of your Beechcraft Super King Air200/ B200
across a broad spectrum of flight conditions. Your Raisbeck-equipped
Super King Air also has FAA-approved enhanced performance in those
flight regimes involving safety of flight such as take-off, flight in icing
conditions, flight with one engine inoperative, approach and landing.
This supplement is designed to facilitate maintaining the documents
necessary for the efficient operation of your airplane. It has been
prepared in loose-leaf form for ease in maintenance, and incorporates
quick reference tabs for each section.
After you have operated your Raisbeck-Equipped Super King Air 200/
B200 for a period of time, we would like to hear your comments regarding
our systems in service with your operation. Please feel free to contact us
at any time by mail or telephone.
Raisbeck Engineering Inc.
4411 South Ryan Way
Seattle, Washington 98178
U.S. 800-537-7277
Intl. 1-206-723-2000
FAX 206-723-2884
www.raisbeck.com
FAA-approved information, limitations, performance and data are on
pages marked at the bottom “FAA-Approved: Revision Level and Date”
SECTION II – LIMITATIONS
NOTE:
For aircraft with temporary repair installed per Beechcraft Service
Bulletin No. 2040, Beechcraft Pilot’s Operating Handbook must be
used for all performance data in Section V until the aircraft has
been permanently repaired per the Beech Service Bulletin.
AIRSPEED LIMITATIONS
Air Minimum Control Speed VMCA
FLAPS KIAS KCAS
Up 91 96
Approach 88
92
Down 78
83
This is the lowest airspeed at which the airplane is directionally
controllable when one engine suddenly becomes inoperative and the other
engine is at take-off power. VMCA was determined with a 5º bank into the
operating engine and the propeller feathered on the inoperative engine.
AIRSPEED INDICATOR MARKINGS:
200 series aircraft red radial at 96KCAS air minimum control speed (VMCA).
B200 series aircraft red radial at 91KCAS.
AIRSPEED INDICATOR DISPLAY
(Collins Pro Line 21 Equipped Aircraft Only):
DISPLAY
KIAS VALUE
OR RANGE
SIGNIFICANCE
Red Line
91
Air Minimum Control Speed (VMCA)
Solid Red Bar
(at bottom of
airspeed
scale)
ISS LSC
#Marker. The top of marker changes
with flap position to reflect the following stall
speeds.
71
Stalling Speed (VS0) at maximum weight with
flaps down.
83
Stalling Speed (VS1) at maximum weight with
flaps approach.
POWER PLANT LIMITATIONS
ENGINE OPERATING LIMITS:
Operating Conditions……….. Low Idle
Gas Generator RPM N1………... 22,500 RPM 60% (min.)
Prop RPM………..…… 1,150 (min.)
NUMBER OF PROPELLERS:
Two (2)
PROPELLER MANUFACTURER:
Hartzell Propeller Inc.
PROPELLER HUB AND BLADE MODEL NUMBERS:
Hub:
HC-D4N-3A
Blades:
D9383K
PROPELLER DIAMETER:
Maximum Diameter:
94.0 inches
Minimum Diameter:
93.0 inches
PROPELLER BLADE ANGLES AT 30-INCH STATION:
Feathered:
86º
±
2º
Reverse:
10.5º
±
1º
PROPELLER ROTATIONAL SPEED LIMITS:
Continuous Operation on Ground – 1150 RPM minimum
CAUTION
Stabilized ground operation between 400 and 1,150 propeller RPM is
prohibited. Operation between 0 and 400 propeller RPM is permissible only
with propeller feathered.
WARNING
STABILIZED GROUND OPERATION WITHIN THE PROPELLER
RESTRICTED RPM RANGE CAN GENERATE HIGH PROPELLER
STRESSES AND RESULT IN PROPELLER FAILURE AND LOSS OF
CONTROL OF THE AIRCRAFT.
PROPELLER DE-ICE AMMETER:
Green Arc (normal operating range) – 18 to 24 amperes.
AUTO FEATHERING SYSTEMS:
The Beech Propeller Autofeathering System must be installed,
operational, and armed for takeoff, climb and approach.
CAUTION
With one-engine either at idle or inoperative, flaps up and propeller
windmilling, VMCA may be as high as 108 KIAS.
MAXIMUM OPERATING PRESSURE – ALTITUDE LIMITS:
Yaw Damper Inoperative
The yaw damper is no longer a requirement for flight up to the ceiling capability of
the airplane when it is equipped with the Raisbeck Engineering Dual Aft Body
Strakes. Therefore, all altitude limitations presented in the basic Beechcraft Pilot’s
Operating Handbook and Flight Manual for yaw damper inoperative are removed.
ICE VANES (INERTIAL SEPERATOR SYSTEM) LIMITATIONS:
The aircraft can be operated with the inertial separator ice vanes deployed during
ground and flight operations, at ambient temperatures up to, and including ISA + 27
ºC, below 13,650 feet or + 15 ºC above 13,650 feet, provided:
1. All other engine limits are observed.
2. During ground operations, oil temperatures are monitored closely. If the oil
temperature limits are reached, the ice vanes must b
•
Fully Enclosed MLG Doors (when HFG-equipped)SECTION III – EMERGENCY PROCEDURES
EMERGENCY AIR SPEEDS:
Air Minimum Control Speeds (VMCA)
FLAPS KIAS
Up 91
Approach 88
Down 78
This is the lowest airspeed at which the airplane is directionally
controllable when one engine suddenly becomes inoperative and the
other is at takeoff power. VMCA was determined with a 5º bank into the
operating engine and the propeller feathered on the inoperative engine.
ENGINE FAILURE AFTER LIFT-OFF
1. The Autofeather system will be armed. Therefore, do not retard the
failed engine power lever until the Autofeather system has
completely feathered the affected propeller. To do so will
deactivate the autofeather circuit and prevent automatic feathering.
2. After Autofeather cycle is complete, failed engine power level–
IDLE.
3. Propeller lever (inoperative engine) – FEATHER
4. Other procedures as prescribed in the Airplane Flight Manual.
ICE PROTECTION SYSTEMS:
ELECTROTHERMAL PROPELLER DE-ICE
Auto System (Normal Operation: 18 to 24 amps)
Abnormal Readings on De-ice Ammeter
Zero-18 amps
A. Continue
Operation
B. If propeller imbalance occurs, increase RPM briefly to
aid in ice removal.
Manual Systems
To use Manual Systems, hold switch in MANUAL POSITION for
approximately 45 seconds. Repeat as required to avoid significant
build-up of ice which will result in loss of performance, vibration,
and ice impingement upon the fuselage.
Monitor manual system current requirement using the airplane’s
loadmeters when the switch is in the ON position. A small needle
deflection (approximately .05) indicates the system is functioning.
NOTE:
On aircraft originally equipped with the two-element propeller de-ice
system, holding the manual switch in either INNER or OUTER
position activates the manual propeller de-ice sys
SECTION IV – NORMAL PROCEDURES
AIRSPEEDS FOR SAFE OPERATION (12,500 LBS)
Air Minimum Control Speed: (VMCA) Flaps UP ... ..91KIAS
Take-off (Flaps UP)
Rotation ... 94 Knots
50 Ft. Speed ... 103 Knots
Take-off (Flaps APPROACH)
Rotation ... 96 Knots
50 Ft. Speed ... 105 Knots
Two-Engine Best Rate-of-Climb (Vy) ... 121 Knots
Landing Approach (Flaps DOWN) ... 97 Knots
Intentional One-engine Inoperative Speed (VSSE) ... 110 Knots
AFTER STARTING AND TAXING
CAUTION
Stabilized ground operation between 400 and 1,150 propeller RPM is
prohibited. Operation between 0 and 400 propeller RPM is permissible
only with propeller feathered.
WARNING
STABILIZED GROUND OPERATION WITHIN THE PROPELLER
RESTRICTED RPM RANGE CAN GENERATE HIGH PROPELLER
STRESSES AND RESULT IN PROPELLER FAILURE AND LOSS OF
CONTROL OF THE AIRCRAFT.
SIMULATING ONE-ENGINE-INOPERATIVE (ZERO THRUST)
When establishing zero thrust operation, use the power setting listed
below. By using this power setting to establish thrust, inherent delays of
restarting a shut-down engine are avoided and almost instant power is
available to counter any attendant hazard.
1. Propeller – 1600 RPM
2. Power Lever – Set 100 ft-lb torque
NOTE:
This setting will approximate Zero Thrust at low altitudes using
recommended One-Engine-Inoperative Climb speeds. Because the
SIMULATING ENGINE FAILURES
CAUTION
Using throttle cuts to simulate failures will result in the autofeather system
being disarmed. In this configuration the VMCA may be as high as 108
Knots. Dynamic throttle cuts should only be attempted at airspeeds above
110 Knots.
PRACTICE DEMONSTRATION OF V
MCAVMCA demonstration may be required for multi-engine pilot certification.
The following procedure may be used at a safe altitude of at least 5000
feet above the ground in clear air only.
VMCA demonstration may be required for multi-engine pilot certification.
The following procedure may be used at a safe altitude of at least 5000
feet above the ground in clear air only.
WARNING
IN-FLIGHT ENGINE OR THROTTLE CUTS BELOW VSSE SPEED OF 104
KNOTS ARE NOT RECOMMENDED.
1. Landing Gear – UP
2. Flaps – UP
3. Autofeather System – ARMED
4. Airspeed – ABOVE 104 KNOTS (VSSE)
5. Propeller Lever (Operative Engine) – HIGH RPM
6. Propeller Lever (Simulated Inoperative Engine) – 1600 RPM
7. Power Lever (Simulated Inoperative Engine) – SET 120 FT-LB
TORQUE
8. Power Lever (Operative Engine) – MAXIMUM ALLOWABLE
9. Airspeed – Reduce approximately one (1) knot per second until
either VMCA or stall warning is obtained.
CAUTION
Use rudder to maintain directional control (heading) and aileron to
maintain 5º bank towards the operative engine. At the first sign of either
VMCA or stall warning (which may be evidenced by: Inability to maintain
heading or bank angle, aerodynamic stall buffet, or stall warning horn
sound) initiate recovery by reducing power to idle on the operative engine,
and immediately lowering the nose to regain VSSE.
ICING FLIGHT
Electrothermal Propeller De-ice
Before Take-off:
1. Automatic Propeller De-ice Switch – AUTO
2. Propeller De-ice Ammeter – MONITOR for 2 minutes; normal operating
range is18 to 24 amperes. Indications above or below this range may
indicate system malfunction and should be thoroughly check before
beginning flight in icing conditions.
3. Manual Propeller De-ice Switch – MOMENTARILY HOLD MANUAL
POSITION. Check loadmeters for .05 increase.
CAUTION
If the de-ice ammeter does not indicate 18-24 amperes, refer to the
EMERGENCY PROCEDURES section.
NOISE CHARACTERISTICS
Approach to and departure from an airport should be made as to avoid
prolonged flight at low altitude near noise-sensitive areas. Avoidance of
noise-sensitive areas, if practical, is preferable to over flight at relatively
low altitudes.
For VFR operations over outdoor assemblies of persons, recreational and
park areas, and other noise-sensitive areas, pilots should make every
effort to fly not less than 2000 feet above the surface, weather permitting,
even though flight at lower level may be consistent with the provisions of
government regulations.
NOTE:
The preceding recommended procedures do not apply where they would
conflict with Air Traffic Control clearances or instructions, or where, in the
pilot’s judgment, an altitude less than 2000 feet is necessary to adequately
exercise his duty to see and avoid other airplanes.
The take-off noise level established in compliance with FAR 36, Appendix
G is 78.9 dB(A). The takeoff noise level established in compliance with
ICAO Annex 16, Chapter 10 is 79.8 dB(A). No determination has been
made by the Federal Aviation Administration that the noise level of this
airplane is or should be acceptable or unacceptable for operation at, into,
or out of any airport.
SECTION V – PERFORMANCE
NOTE:
For aircraft with temporary repair installed per Beechcraft Service Bulletin No.
2040, the Beechcraft Pilot’s Operating Handbook must be used for all
performance data in Section V until the aircraft has been permanently repaired
per the Beech Service Bulletin.
Comments Pertinent to the use of these
performance data ... 5-5
TAKE OFF AND CLIMB DATA
Fahrenheit to Celsius Temperature Conversion ... 5-7
Stall Speeds ... 5-8
Maximum Take-Off Weight Permitted by Enroute Climb
Requirement ... 5-9
Take-Off Weight to achieve Positive One-Engine-Inoperative
Climb at Lift-Off Flaps UP ... 5-10
Maximum Enroute Weight (FAR 135 Operations)... 5-11
Minimum Take-Off Power at 2000 RPM with RARS Ice Vanes
Extended
...
5-12
Take-Off Weight – Flaps UP – To Achieve a Gradient of 2.4% ... 5-13
Take-Off Distance – Flaps UP ... 5-14
Accelerate Stop – Flaps UP ... 5-15
Accelerate-Go – Flaps UP ... 5-16
Net Gradient of Climb – Flaps UP ... 5-17
Take-Off Distance – Flaps APPROACH ... 5-18
Accelerate Stop – Flaps APPROACH ... 5-19
Accelerate Go – Flaps APPROACH ... 5-20
Net Gradient of Climb – Flaps APPROACH ... 5-21
Climb – Two Engines – Flaps UP ... 5-22
Climb – Two Engines – Flaps APPROACH ... 5-23
Climb – One Engine Inoperative – Flaps UP ... 5-24
Service Ceiling – One Engine Inoperative ... 5-25
Time, Fuel, and Distance to Climb ... 5-26
1600 RPM CRUISE DATA
RECOMMENDED CRUISE POWER SETTING TABLES
ISA-30ºC ... 5-27
ISA-20ºC ... 5-28
ISA-10ºC ... 5-29
ISA ... 5-30
TORQUE ... 5-36
FUEL FLOW ... 5-37
RANGE ... 5-38
MAXIMUM CRUISE POWER SETTING TABLES
ISA-30ºC ... 5-39
ISA-20ºC ... 5-40
ISA-10ºC ... 5-41
ISA ... 5-42
ISA+10ºC ... 5-43
ISA+20ºC ... 5-44
ISA+30ºC ... 5-45
ISA+37ºC ... 5-46
MAXIMUM CRUISE POWER SETTING GRAPHS
SPEEDS ... 5-47
TORQUE ... 5-48
FUEL FLOW ... 5-49
RANGE ... 5-50
1700 RPM CRUISE DATA
RECOMMENDED CRUISE POWER SETTING TABLES
ISA-30ºC ... 5-51
ISA-20ºC ... 5-52
ISA-10ºC ... 5-53
ISA ... 5-54
ISA+10ºC ... 5-55
ISA+20ºC ... 5-56
ISA+30ºC ... 5-57
ISA+37ºC ... 5-58
RECOMMENDED CRUISE POWER SETTING GRAPHS
SPEEDS ... 5-59
TORQUE ... 5-60
FUEL FLOW ... 5-61
RANGE ... 5-62
MAXIMUM CRUISE POWER SETTING TABLES
ISA-30ºC ... 5-63
ISA-20ºC ... 5-64
ISA-10ºC ... 5-65
ISA ... 5-66
ISA+10ºC ... 5-67
ISA+20ºC ... 5-68
ISA+30ºC ... 5-69
ISA+37ºC ... 5-70
MAXIMUM CRUISE POWER SETTING GRAPHS
SPEEDS ... 5-71
TORQUE ... 5-72
FUEL FLOW ... 5-73
RANGE ... 5-74
1800 RPM CRUISE DATA
RECOMMENDED CRUISE POWER SETTING TABLES
ISA-30ºC ... 5-75
ISA-20ºC ... 5-76
ISA-10ºC ... 5-77
ISA ... 5-78
ISA+10ºC ... 5-79
ISA+20ºC ... 5-80
ISA+30ºC ... 5-81
ISA+37ºC ... 5-82
RECOMMENDED CRUISE POWER SETTING GRAPHS
SPEEDS ... 5-83
TORQUE ... 5-84
FUEL FLOW ... 5-85
RANGE ... 5-86
MAXIMUM CRUISE POWER SETTING TABLES
ISA-30ºC ... 5-87
ISA-20ºC ... 5-88
ISA-10ºC ... 5-89
ISA ... 5-90
ISA+10ºC ... 5-91
ISA+20ºC ... 5-92
ISA+30ºC ... 5-93
ISA+37ºC ... 5-94
MAXIMUM CRUISE POWER SETTING GRAPHS
SPEEDS ... 5-95
TORQUE ... 5-96
FUEL FLOW ... 5-97
RANGE ... 5-98
1600 RPM MAXIMUM RANGE DATA
POWER SETTING TABLES
ISA-30ºC ... 5-99
ISA-20ºC ... 5-100
ISA-10ºC ... 5-101
ISA ... 5-102
ISA+10ºC ... 5-103
ISA+20ºC ... 5-104
ISA+30ºC ... 5-105
ISA+37ºC ... 5-106
MAXIMUM RANGE PROFILE
ONE ENGINE-INOPERATIVE MAXIMUM POWER SETTING TABLES
NOTES ... 5-112
ISA-30ºC ... 5-113
ISA-20ºC ... 5-114
ISA-10ºC ... 5-115
ISA ... 5-116
ISA+10ºC ... 5-117
ISA+20ºC ... 5-117
ISA+30ºC ... 5-119
ISA+37ºC ... 5-120
DESCENT AND HOLDING GRAPHS
HOLDING TIME ... 5-121
TIME, FUEL, AND DISTANCE TO DESCEND ... 5-122
LANDING DATA
CLIMB – BALKED LANDING ... 5-123
LANDING APPROACH SPEEDS ... 5-124
LANDING DISTANCE – STANDARD GEAR
WITHOUT PROPELLER REVERSING – FLAPS DOWN ... 5-125
WITH PROPELLER REVERSING – FLAPS DOWN ... 5-126
WITHOUT PROPELLER REVERSING – FLAPS UP ... 5-127
WITH PROPELLER REVERSING – FLAPS UP ... 5-128
LANDING DISTANCE – HIGH FLOTATION GEAR
WITHOUT PROPELLER REVERSING – FLAPS DOWN ... 5-129
WITH PROPELLER REVERSING – FLAPS DOWN ... 5-130
WITHOUT PROPELLER REVERSING – FLAPS UP ... 5-131
WITH PROPELLER REVERSING – FLAPS UP ... 5-132
ALTERNATE BALANCED FIELD LENGTHS
FLAPS UP EQUIVALENT FAR PART 25 TAKEOFFS
BALANCED FIELD LENGTH ... 5-134
TAKEOFF DISTANCE ... 5-135
TAKEOFF AND BALANCED FIELD LENGTH SPEEDS ... 5-136
CLIMB – TWO ENGINES ... 5-137
CLIMB – NET GRADIENT ... 5-138
FLAPS APPROACH EQUIVALENT FAR PART 25 TAKEOFFS
BALANCED FIELD LENGTH ... 5-139
TAKEOFF DISTANCE ... 5-140
TAKEOFF AND BALANCED FIELD LENGTH SPEEDS ... 5-141
CLIMB – TWO ENGINES ... 5-142
CLIMB – NET GRADIENT ... 5-143
COMMENTS PERTINENT TO THE
USE OF THESE PERFORMANCE DATA
BASIC BEECHCRAFT POH/AFM PERFORMANCE
The performance of all the Beechcraft Super King Air airplanes equipped with the
above listed Raisbeck Performance Enhancement systems has been shown to
be equal to or better than the basic airplane performance presented in the
applicable Beechcraft POH/AFM. Therefore, the use of the basic POH/AFM
performance is approved in the areas not covered in this supplement.
ENHANCED RAISBECK TAKE-OFF AND LANDING PERFORMANCE
The aerodynamic improvements of the Raisbeck Enhanced Performance
Leading Edges make available improved take-off and landing performance.
Part 23 of the Federal Aviation Regulations require only the all engines operating
distance over a 50-ft. height be presented for take-off distance. Along with the
FAA-approved optional performance in this subsection, we include for your
information Accelerate-Go, Accelerate-Stop, Climb Limited Weight, Net Climb
Gradient, and other information generally tailored to FAR Part 25. For data not
shown in this section, refer to Section V of the Beechcraft POH.
ALTERNATE RAISBECK BALANCED FIELD LENGTHS
There is increasing world-wide acceptance of FAR Part 25 safety standards in
the smaller turboprop and turbojet Corporate and Airline fleet. Raisbeck
Engineering offers its fully Raisbeck-Equipped B200 aircraft with equivalent FAR
Part 25 Balanced Field Lengths, tailored to FAA Advisory Circular, AC25-7.
Take-off field length requirements for flaps up and approach may be drawn from
this subsection as an alternate to the standard enhanced Raisbeck takeoff
performance detailed in the previous subsection.
Some of the more important FAR Part 25 requirements utilized to calculate
performance in this subsection are as follows:
•
Decision speed (V1) is faster than engine failure speed (VEF) by the
demonstrated pilot engine-failure recognition time, plus one-second.
•
If continuing take-off:
-
Rotation speed (VR) must be faster than 1.05 VMCG
-
Speed at 35 feet altitude (V2) must be faster than 1.2 VS
The reference airspeeds for takeoff in this subsection, utilizing all the above
factors have naturally increased. To compensate for this, a new Flaps approach
takeoff procedure has been incorporated. Shorter take-off and Balanced Field
Lengths are the end results. This allows safe operation at heavy gross weights
out of previously inaccessible airports.
EFFECT OF ICE VANE DEPLOYMENT ON PERFORMANCE
The actual increase in engine flat rating due to the Raisbeck Ram Air Recovery
System has not been incorporated in the FAA-certified take-off and engine-out
performance. The engine produces as much torque at any given ITT with the
RARS ice vanes deployed as it did with the basic ice vanes retracted. Thus, no
performance penalties need be assessed to the performance parameters due to
RARS ice vane deployment. The use of ice vanes is covered in the limitations
section.
CLIMB AND CRUISE PERFORMANCE
The performance data in this subsection apply to all Raisbeck-equipped Super
King Air200/ B200 series aircraft and are also valid for airplanes with high
floatation gear, when equipped with the above listed Raisbeck Performance
Enhancement Systems.
Cruise performance data while not an FAA requirement, are based on actual
flight tests conducted on Beechcraft Super King Air B200/B200C airplanes
equipped with all Raisbeck Performance Enhancement Systems installed. These
data are intended to supplement or replace equivalent data in the basic B200
series Pilot’s Operating Handbook and Airplane Flight Manual.
For data on performance parameters not covered in this supplement, refer to the
performance data supplied by Hawker Beechcraft Corporation.
The actual performance attained will vary from airplane depending on the age
and condition of the airframe and powerplants, aircraft rigging and operator
technique.
FAHRENHEIT TO CELSIUS TEMPERATURE CONVERSION
DEGR
EE
S ~
°C
-40
-30
-20
-10
0
10
20
30
40
50
60
WEIGHT ~ POUNDS
9000 10000
11000 12000
ANGLE OF BANK ~ DEGREES
0 10 20 30 40 50 60 ST AL L SP EED S ~ KN OT S C A L IBR AT ED AIR SPEED 50 60 70 80 90 100 110 120 130
ZERO -THRUST STALL SPEEDS
FLAPS UP RE FE RE NCE L INE FLAPS LANDING EXAMPLE: WEIGHT... FLAPS... ANGLE OF BANK... STALL SPEED... 11,700 LBS APPROACH 30 DEG. 89 KTS CAS 84 KTS IAS NOTES: 1. 2. 3. 4. 5. 6.
LANDING GEAR POSITION HAS NO EFFECT ON STALL SPEED. INDICATED STALL SPEEDS ARE APPROXIMATELY 5 KTS BELOW CALIBRATED STALL SPEEDS.
POWER FOR ZERO THRUST (APPROXIMATELY 100 FT-LB TORQUE AND 1600 PROPELLER RPM.)
ALTITUDE LOSS EXPERIENCED WHILE CONDUCTING STALL IN ACCORDANCE WITH FAR 23.201 WAS 800 FEET.
MAXIMUM NOSE DOWN PITCH ATTITUDE AND ALTITUDE LOSS DURING RECOVERY FROM ONE-ENGINE-INOPERATIVE STALLS PER FAR 23.205 ARE APPROXIMATELY 8° AND 300 FEET RESPECTIVELY.
A NORMAL STALL RECOVERY TECHNIQUE MAY BE USED. THE BEST PROCEDURE IS A BRISK FORWARD WHEEL MOVEMENT TO A NOSE DOWN ATTITUDE. LEVEL THE AIRPLANE AFTER AIRSPEED HAS INCREASED APPROXIMATELY 25 KNOTS ABOVE STALL.
MAXIMUM TAKE-OFF WEIGHT
M
A
XIM
U
M
T
A
KE OF
F
W
E
IGH
T
~
POUND
S
9500
10000
10500
11000
11500
12000
12500
PERMITTED BY ENROUTE CLIMB REQUIREMENT
STRUCTURAL LIMIT
FOR OPERATION WITH ICE VANES EXTENDED,
NO OFF LOADING IS REQUIRED
NOTE:
NO OFF LOADING IS
REQUIRED TO MEET
ENROUTE CLIMB
REQUIREMENT
TAKE-OFF WEIGHT - FLAPS UP
WEIGHT ~ POUNDS 9000 9500 10000 10500 11000 11500 12000 12500 PR ESSU R E AL TIT U D E ~ F EET 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000TO ACHIEVE POSITIVE ONE-ENGINE-INOPERATIVE RATE-OF-CLIMB AT LIFT-OFF
M A X IM U M T A KE -O FF W E IG HT (12, 500 LB S ) O U T S IDE TE M P E R A TU R E ~ °C ISA + 37°C 35 °C 30° C 25 °C 20° C EXAMPLE: PRESSURE ALTITUDE... OAT... TAKE-OFF WEIGHT... 5,433 FT 28°C 12,500 LBS
NOTE: FOR OPERATION WITH ICE VANES EXTENDED, NO OFF-LOADING IS REQUIRED ASSOCIATED CONDITIONS: POWER... FLAPS... LANDING GEAR... INOPERATIVE PROPELLER... TAKE-OFF UP DOWN FEATHERED
MAXIMUM
ENRO
UT
E
W
E
IG
HT
~
PO
UND
S
9000
10000
11000
12000
13000
14000
MAXIMUM ENROUTE WEIGHT
(FAR PART 135 - OPERATIONS)
ASSOCIATED CONDITIONS:
POWER...
FLAPS...
LANDING GEAR...
INOPERATIVE PROPELLER...
MAX CONTINUOUS
UP
UP
FEATHERED
EXAMPLE:
OAT AT MEA...
MINIMUM ENROUTE ALTITUDE...
ALTIMETER SETTING...
MAXIMUM ALLOWABLE WEIGHT...
0°C
18,000 FT
29.75 IN. HG
12,500 LBS
NOTE:
PER FAR 135, OPERATIONS OVER THE TOP OR IN IFR CONDITIONS REQUIRE THAT
THE AIRPLANE BE CAPABLE OF CLIMBING 50 FT/MIN AT THE MEA'S OF THE
PROPOSED ROUTE OR 5000 FT MSL, WHICHEVER IS HIGHER.
22
,0
00
21
,0
00
20
,0
00
19
,0
00
18
,0
00
17
,0
00
16
,0
00
15
,0
00
13
,0
00
12
,0
00
STRUCTURAL LIMIT
M
IN
IM
U
M
E
N
R
O
U
TE
A
LT
IT
U
D
E
~
F
E
E
T
14
,0
00
NCE LI
NE
MI
N
IMU
M T
A
K
E
-O
F
F
P
O
W
E
R
OU
T
S
ID
E
T
E
M
PER
AT
U
R
E ~
°
C
-50
-40
-30
-20
-10
0
10
2
0
30
40
5
0
60
70
EN
GINE
TO
RQUE A
T 20
00 RP
M ~ F
T-LB
S
1000
1100
1200
1300
1400
1500
1600
1700
1800
1900
2000
2100
2200
2300
W
IT
H
ICE V
A
NE
S E
X
T
E
NDED
(6
5
K
N
OT
S
)
PR
ES
SU
RE
A
LT
ITU
DE
~
FE
ET
SL
20
00
40
00
60
00
80
00
10
00
0
IS
A
+2
7°C
IS
A
+3
7°C
T
O
R
Q
UE LI
M
IT
~
2230 FT
-LBS
N
O
T
ES:
1.
2.
3.
T
O
R
Q
U
E
IN
C
R
E
ASES
A
PPR
OX
IM
A
T
E
L
Y 2
0
F
T
-L
BS F
R
OM
0
T
O
6
5
KN
OT
S.
TH
E POW
E
R
(
T
OR
QU
E)
IN
D
IC
A
TE
D
IS
T
H
E M
IN
IM
U
M
VAL
U
E
AT
6
5
KN
OT
S F
O
R
W
H
IC
H
T
A
KE-OF
F
P
E
R
F
OR
M
A
N
C
EIN
T
H
IS SEC
T
ION
C
A
N
BE OBT
A
IN
ED
. T
O
R
Q
U
E
W
IL
L
C
O
N
T
IN
U
E
T
O
IN
C
R
EA
SE AB
OVE 6
5
KN
OT
S
.
T
AKE
-O
FF
W
IT
H
IC
E
V
A
N
ES EX
T
E
N
D
ED
IS R
EST
R
IC
T
ED
IN
SH
AD
ED
AR
EA
.
9000
10000
11000
12000
TAKE-OFF W
E
IGH
T
FLAPS U
P
W
E
IG
H
T
~ POUN
DS
T
O
ACH
IE
VE A
G
R
A
D
IE
NT
O
F
2.4%
O
ND
ITION
S
:
...
.
...
...
...
OPEL
LER
...
...
...
TA
K
E
-O
FF
UP
UP
FE
A
T
HE
RE
D
103 K
IAS
MA
XIM
UM
TA
KEOFF W
EIG
HT (1
2,50
0 LBS
)
O
UT
SI
DE
A
IR
T
EM
PE
RA
TU
RE
~
°C
10
15
20
25
30
35
40
ISA
+
37
°C
EX
AM
P
L
E:
PR
ESSU
R
E
ALT
IT
U
D
E
...
...
O
A
T
...
...
...
T
AKE-O
F
F
W
E
IG
H
T
...
...
5430 FEET
28°C
12,
500 LB
S
N
O
T
E
:
T
H
IS C
L
IM
B W
E
IGH
T
I
S
D
E
T
E
R
M
IN
ED
BY T
H
E SEC
O
N
D
SEG
M
EN
T
C
O
N
D
IT
IO
N
. G
R
AD
IEN
T
R
E
Q
U
IR
EM
EN
T
S
AT
LIFT
OF
F AN
D AT T
H
E END
OF T
H
E TAKE
-O
FF
PA
T
H
ARE
AU
T
O
M
A
T
IC
A
L
L
Y
C
O
M
P
ILED
W
IT
H
AT
T
H
IS W
E
IG
H
T
.
WEIGHT ~ POUNDS
9000
10000
11000
12000
WIND COMPONENT ~ KNOTS
0
10
20
30
0
50
DIST
ANCE ~
FEET
0
1000
2000
3000
4000
5000
6000
7000
OBSTACLE HEIGHT ~ FEET
OUTSIDE AIR TEMPERATURE ~ °C
-40
-30
-20
-10
0
10
20
30
40
50
TAKE-OFF DISTANCE - FLAPS UP
TAKE-OFF SPEEDS:
ALL WEIGHTS
ROTATION = 94 KIAS
50 FT = 103 KIAS
NOTE:
FOR OPERATION WITH ICE VANES EXTENDED, ADD
10°C TO THE ACTUAL OAT BEFORE ENTERING
GRAPH.
TAKE-OFF POWER SET
BEFORE BRAKE RELEASE
UP
RETRACT AFTER LIFT-OFF
PAVED, LEVEL, DRY SURFACE
ASSOCIATED CONDITIONS:
POWER...
FLAPS...
LANDING GEAR...
RUNWAY...
TA
IL
W
IN
D
HEA
DWIN
D
REFERENCE LINE
REFERENCE LINE
REFERENCE LINE
GROU
ND ROLL
PRESSURE ALTITUDE ~ FEET
ISA
10,000
8,000
6,000
4,000
2,000
SL
28°C
5,430 F
12,500 LBS
9.0 KTS
2670 FT
3370 FT
94 KIAS
103 KIAS
EXAMPLE:
OAT...
PRESSURE ALTITUDE...
TAKE-OFF WEIGHT...
HEADWIND COMPONENT...
GROUND ROLL...
TOTAL DISTANCE OVER
50 FT OBSTACLE...
TAKE-OFF SPEED AT ROTATION...
AT 50 FT...
GU IDE LIN ES N OT APP LIC ABLE FOR INTE RM EDIA TE OB STA CLE HEI GHTSV SPEED - 94 KIAS
FOR ALL WEIGHTS
1ACCELERATE STOP - FLAPS UP
ACC
E
LERAT
E
- ST
OP
FIELD
LENGT
H
~
FEET
2000
3000
4000
5000
6000
7000
8000
REFER
E
NCE LINE
REFER
E
NCE LINE
T
A
IL
W
IN
D
HEA
DW
IND
ISA
PRESSURE ALTITUDE ~ FEET
10,000
8,000
6,000
4,000
2,000
SL
TAKE-OFF POWER SET BEFORE
BRAKE RELEASE
BOTH ENGINES IDLE AT V
SPEED AND REVERSE OPERATING ENGINE
UP
ARMED
MAXIMUM
PAVED, LEVEL, DRY SURFACE
1
ASSOCIATED CONDITIONS:
POWER...
FLAPS...
AUTOFEATHER...
BRAKING...
RUNWAY...
1.
2.
EXAMPLE:
OAT...
PRESSURE ALTITUDE...
WEIGHT...
HEADWIND COMPONENT...
FIELD LENGTH...
V ...
28°C
5,430 FT
12,500 LBS
9.0 KTS
4450 FT
94 KIAS
1NOTE: FOR OPERATION WITH ICE VANES EXTENDED,
PERFORMANCE IS NOT AFFECTED.
OUTSIDE AIR TEMPERATURE ~ °C -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 WEIGHT ~ POUNDS 9000 10000 11000 12000 NOTE: 1. 2. 3.
V (ENGINE FAILURE SPEED) EQUALS V (ROTATION SPEED)
USABLE CLEARWAY CANNOT EXCEED 25% OF THE RUNWAY LENGTH FOR OPERATION WITH ICE VANES EXTENDED, ADD 6°C TO THE ACTUAL OAT BEFORE ENTERING THE GRAPH. R 1 ACCELERAT E - G O FIE L D LENG T H ~ FEET 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 12000 13000 14000
WIND COMPONENT ~ KNOTS
0 10 20 30
ACCELERATE-GO - FLAPS UP
(DISTANCE TO 35 FEET AGL)
EXAMPLE:
OAT... PRESSURE ALTITUDE... HEADWIND COMPONENT... WEIGHT... TAKE-OFF FIELD LENGTH...
28°C 5,430 FEET 9.0 KTS 12,500 LBS 6750 FEET TAKE-OFF SPEEDS: ALL WEIGHTS ROTATION = 94 KIAS V (35 FT) = 103 KIAS 2 ASSOCIATED CONDITIONS: POWER... FLAPS... AUTOFEATHER... LANDING GEAR... RUNWAY...
TAKE-OFF POWER SET BEFORE BRAKE RELEASE UP
ARMED
RETRACT AFTER LIFT-OFF PAVED, LEVEL, DRY SURFACE
ISA
PRESSURE ALTITUDE ~ FEET
10,000 8,000 6,000 4,000 2,000 SL REFE R E NC E LINE REFE R E NC E LINE TAIL WIN D HEADWIND
NET
GRADIENT
O
F
CLIM
B
~ %
0
1
2
3
4
5
6
7
8
9
10
11
12
NET GRADIENT OF CLIMB - FLAPS UP
ASSOCIATED CONDITIONS:
POWER...
FLAPS...
GEAR...
INOPERATIVE PROPELLER...
TAKE-OFF
UP
UP
FEATHERED
EXAMPLE:
OAT...
PRESSURE ALTITUDE...
WEIGHT...
NET GRADIENT OF CLIMB...
28°C
5430 FEET
12,500 LBS
2.4%
SINGLE ENGINE CLIMB SPEED - 103 KIAS
ALL WEIGHTS
NOTE:
FOR OPERATION WITH ICE VANES EXTENDED, ADD 10°C
TO THE ACTUAL OAT BEFORE ENTERING GRAPH.
REFERE
NCE LINE
ISA
PRESSURE ALTITUDE ~ FEET
SL
2,000
4,000
6,000
8,000
10,000
WEIGHT ~ LBS 12500 12000 11700 11550 11000 10000 9000 96 92 90 88 87 87 87 105 101 99 98 98 98 98 VR ~ KIAS V2 ~ KIAS
WIND COMPONENT ~ KNOTS
0 10 20 30 DI STAN CE ~ FEET 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000 5500 6000 6500 7000 WEIGHT ~ POUNDS 9000 10000 11000 12000
OUTSIDE AIR TEMPERATURE ~ °C
-40 -30 -20 -10 0 10 20 30 40 REF E RENC E L INE REF E RENC E L INE 8000 6000 4000 2000 0 ISA
TAKE-OFF DISTANCE - FLAPS APPROACH
(DISTANCE TO 50FT AGL)
HEAD WIND TA ILW INDNOTE: Takeoff with flaps APPROACH requiring more than 3150ft is not recommended. For these conditions use flaps UP.
FLAPS UP RECOMMENDED EXAMPLE: OAT... PRESSURE ALTITUDE... WEIGHT... HEADWIND COMPONENT... TAKE-OFF DISTANCE... 13°C 6,000 FT 10,000 LBS 20 KNOTS 2,000 FEET PRES SURE ALT ITUDE ~ FE ET ASSOCIATED CONDITIONS: POWER... FLAPS... LANDING GEAR... RUNWAY...
TAKE-OFF POWER SET PRIOR TO BRAKE RELEASE APPROACH
SELECTED "UP" AT 50 FT PAVED, LEVEL, DRY SURFACE
ACCEL E RAT E -S T O P F IEL D L E NGT H ~ F E E T 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 REF E RENCE L INE
ACCELERATE-STOP - FLAPS APPROACH
HEAD
WIND
NOTE: FOR OPERATION WITH ICE VANES EXTENDED, PERFORMANCE IS NOT AFFECTED
TA ILW IND ASSOCIATED CONDITIONS: POWER... FLAPS... AUTOFEATHER... BRAKING... RUNWAY...
1. TAKE-OFF POWER SET PRIOR TO BRAKE RELEASE
2. BOTH ENGINES IDLE AT V1
AND REVERSE OPERATING ENGINE APPROACH
ARMED MAXIMUM
PAVED, LEVEL, DRY SURFACE
EXAMPLE: OAT... PRESSURE ALTITUDE... WEIGHT... HEADWIND COMPONENT... ACCELERATE-STOP DISTANCE.. 13°C 6,000 FT 10,000 LBS 20 KNOTS 2,880 FEET PRES SURE ALTIT UDE ~ FEET 6000 4000 2000 0 8000 ISA REF E RENCE L INE WEIGHT ~ LBS 12500 12000 11700 11550 11000 10000 9000 96 92 90 88 87 87 87 V1 ~ KIAS
WEIGHT ~ POUNDS
9000 10000
11000 12000
WIND COMPONENT ~ KNOTS
0 10 20 30 ACC E LE RA T E -GO FI ELD LENG T H ~ FE ET 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 RE FE RE NC E LIN E
ACCELERATE-GO - FLAPS APPROACH
(DISTANCE TO 35 FEET AGL)
HEAD
WIND
TA
ILW
IND
WEIGHT ~ LBS VR ~ KIAS V2 ~ KIAS
12500 96 105 12000 92 101 11640 89 99 11550 88 98 11100 87 98 11000 87 98 10000 87 98 90000 87 98
NOTE: FOR OPERATION WITH ICE VANES EXTENDED, ADD 6°C TO THE ACTUAL OAT BEFORE ENTERING GRAPH
ASSOCIATED CONDITIONS: POWER... FLAPS... AUTOFEATHER... LANDING GEAR... RUNWAY...
TAKE-OFF POWER SET PRIOR TO BRAKE RELEASE APPROACH ARMED
RETRACT AFTER LIFT-OFF PAVED, LEVEL, DRY SURFACE
EXAMPLE: OAT... PRESSURE ALTITUDE... WEIGHT... HEADWIND COMPONENT... ACCELERATE-GO DISTANCE... 13°C 6,000 FT 10,000 LBS 20 KNOTS 2,600 FEET
OUTSIDE AIR TEMPERATURE ~ °C
-40 -30 -20 -10 0 10 20 30 40 50 RE FERE NC E LI NE 8000 6000 4000 PR ES SU RE AL TIT UD E ~ FE ET 2000 0 ISA
EXAMPLE: OAT... PRESSURE ALTITUDE... 28 ºC 5,430 FEET WEIGHT-POUNDS 11,700 9,250 10,625
NET GRADIENT OF CLIMB %
2.1 5.2 3.3
NET GRADIENT OF CLIMB - FLAPS APPROACH
NOTE: FOR OPERATION WITH ICE VANES EXTENDED, ADD 10 ºC TO THE ACTUAL OAT BEFORE ENTERING GRAPH
NET G R A D IE NT O F CL IM B ~ % -1 0 1 2 3 4 5 6 7 8 9 10 PRESSURE ALTITUDE ~ FT SL 2000 4000 6000 8000 10000 ISA RE F E RE NCE L INE ASSOCIATED CONDITIONS: POWER... FLAPS... LANDING GEAR... INOPERATIVE PROPELLER... TAKE-OFF APPROACH UP FEATHERED WEIGHT ~ LBS 12,500 12,000 11,000 10,000 9,000
CLIMB SPEED ~ KNOTS 106 105 103 101 99 CLIMB SPEED @ 10,625 LBS...102 KTS
-60
-50
-40
-30
-20
-10
0
10
20
30
40
50
60
ASSOCIATED CONDITIONS:
POWER... ...MAXIMUM CONTINUOUS FLAPS... UP
LANDING GEAR... UP
OUTSIDE AIR TEMPERATURE ~ °C
CLIMB - TWO ENGINES - FLAPS UP
9000
9500
10000 10500 11000 11500 12000 12500
-500
0
500
1000
1500
2000
2500
3000
3500
4000
125
124
121
118
115
12,500
12,000
11,000
10,000
9,000
CLIMB SPEED ~ KNOTS
WEIGHT ~ POUNDS
NOTE: DURING OPERATION WITH ICE VANES EXTENDED, RATE OF CLIMB WILL BE REDUCED APPROXIMATELY 635 FEET PER MINUTE
EXAMPLE:
OAT... 11°C PRESSURE ALTITTUDE.... 7,000 FT WEIGHT... 11,000 LBS RATE OF CLIMB ... 2,700 FT/MIN CLIMB GRADIENT... 15.0%
4,0
00
S
L
8,0
00
10
,00
0
12
,00
0
14
,00
0
16
,00
0
18
,0
00
20
,0
00
22
,00
0
24
,00
0
26
,0
00
30
,0
00
28
,0
00
32
,00
0
34
,00
0
35
,00
0
IS
A
PRESSURE ALTITUDE ~ FEET
RAT
E
OF
CL
IM
B
~
F
T
/M
IN
WEIGHT ~ POUNDS
RE F E RE NCE L INE-2
0
5
10
15
20
25
30
CL
IM
B G
R
ADI
E
N
T
~
%
CLIMB - TWO ENGINES - FLAPS APPROACH
1000
1500
2000
2500
3000
3500
20
,0
00
2,0
00
125
124
121
118
115
12,500
12,000
11,000
10,000
9,000
CLIMB SPEED ~ KNOTS
WEIGHT ~ POUNDS
NOTE: DURING OPERATION WITH ICE VANES EXTENDED, RATE OF CLIMB WILL BE REDUCED APPROXIMATELY 635 FEET PER MINUTE
ASSOCIATED CONDITIONS:
POWER... ...MAXIMUM CONTINUOUS FLAPS... APPROACH LANDING GEAR... UP EXAMPLE: OAT... 11°C PRESSURE ALTITTUDE.... 7,000 FT WEIGHT... 11,000 LBS RATE OF CLIMB ... 2,500 FT/MIN CLIMB GRADIENT... 14.2%
4,0
00
S
L
6,0
00
8,0
00
10
,0
00
12
,0
00
14
,0
00
16
,0
00
18
,0
00
IS
A
PRESSURE ALTITUDE ~ FEET
RA
T
E
O
F
CLIM
B
~
F
T
/M
IN
RE F E RE NCE L INE5
10
15
20
25
30
CL
IM
B G
R
AD
IE
NT
~
%
-60
-50
-40
-30
-20
-10
0
10
20
30
40
50
60
ASSOCIATED CONDITIONS:
POWER... ...MAXIMUM CONTINUOUS FLAPS... UP
LANDING GEAR... UP INOPERATIVE PROPELLER..FEATHERED
OUTSIDE AIR TEMPERATURE ~ °C
CLIMB - ONE ENGINE INOPERATIVE - FLAPS UP
9000
9500
10000 10500 11000 11500 12000 12500
-500
0
500
1000
1500
6,0
00
2,0
00
121
119
117
114
111
12,500
12,000
11,000
10,000
9,000
CLIMB SPEED ~ KNOTS
WEIGHT ~ POUNDS
NOTE: DURING OPERATION WITH ICE VANES EXTENDED, RATE OF CLIMB WILL BE REDUCED APPROXIMATELY 400 FEET PER MINUTE
EXAMPLE:
OAT... 11°C PRESSURE ALTITTUDE.... 7,000 FT WEIGHT... 11,000 LBS RATE OF CLIMB ... 760 FT/MIN CLIMB GRADIENT... 4.6%
4,0
00
S
L
8,0
00
10
,00
0
12
,00
0
14
,00
0
16
,00
0
18
,0
00
20
,0
00
22
,00
0
24
,00
0
26
,0
00
30
,0
00
28
,0
00
32
,0
00
IS
A
PRESSURE ALTITUDE ~ FEET
RATE
O
F
CL
IM
B
~
FT
/M
IN
WEIGHT ~ POUNDS
REF E REN C E L INE-2
0
2
4
6
8
10
12
14
C
L
IM
B GR
ADIE
N
T
~
%
-60
-50
-40
-30
-20
-10
0
10
20
30
40
50
2,000
OUTSIDE AIR TEMPERATURE ~ °C
TIME, FUEL, AND DISTANCE TO CLIMB
0
5
10
15
20
25
30
35
40
45
50
NOTE: 1. ADD 90 LBS FUEL FOR START, TAXI AND TAKEOFF 2. FOR OPERATION WITH ICE VANES EXTENDED, ADD 25°C TO THE ACTUAL OAT BEFORE ENTERING GRAPH. ASSOCIATED CONDITIONS: PROPELLER SPEED... 1800 RPM ITT... 820°C OR TORQUE... 2230 FT~LBS 160 140 130 120 SL TO 10,000 10,000 TO 20,000 20,000 TO 25,000 25,000 TO 35,000
CLIMB SPEED ~ KNOTS ALTITUDE ~ FEET
EXAMPLE:
OAT AT TAKEOFF... 28°C OAT AT CRUISE... -10°C AIRPORT PRESSURE ALTITTUDE.... 5433 FT CRUISE ALTITUDE... 26,000 FT INITIAL CLIMB WEIGHT... 12,500 LBS TIME TO CLIMB (16-2)... 14 MIN FUEL TO CLIMB (209-37)... 172 LB DISTANCE TO CLIMB (51-7)... 44 NM 4,000 6,000 8,000 10,000 12,000 14,000 16,000 18,000 20,000 22,000 24,000 26,000 29,000 28,000 31,000 33,000 35,000 ISA PRE SS URE AL TIT UD E ~ FE ET 12,500 12,000 11,0 00 10,0 00 9,0 00
TIME TO CLIMB ~ MINUTES
INIT IAL CL IM B W EIG HT ~ L BS
0
10
20
30
40
50
60
70
80
90 100 110 120 130 140 150 160 170
DISTANCE TO CLIMB ~ NAUTICAL MILES
0
50
100
150
200
250
300
350
400
NORMAL CRUISE POWER
1600 RPM
ISA -30ºC
NOTE:
1. IOAT, TORQUE AND FUEL FLOW BASED ON 11,000 POUNDS GROSS
WEIGHT.
2. DURING OPERATION WITH ICE VANES EXTENDED, TRUE AIRSPEED WILL
BE REDUCED IF ORIGINAL TORQUE IS NOT OR CANNOT BE RESET, BUT
WILL BE UNCHANGED IF ORIGINAL TORQUE IS RESET.
FEET °C °C FT-LBS LBS/HR LBS/HR IAS TAS IAS TAS IAS TAS
0 -10 -15 2230 442 883 238 226 240 227 240 227 2,000 -14 -19 2230 429 857 236 230 237 231 238 232 4,000 -18 -23 2230 416 832 233 234 234 235 236 236 6,000 -22 -27 2230 405 810 231 237 232 238 233 239 8,000 -25 -31 2230 394 788 230 244 232 246 232 246 10,000 -29 -35 2230 384 768 228 249 229 250 230 251 12,000 -33 -39 2230 376 753 226 253 227 254 228 255 14,000 -36 -43 2230 368 737 223 258 224 259 225 260 16,000 -40 -47 2230 361 721 221 263 222 264 224 266 18,000 -44 -51 2230 353 706 218 268 220 270 221 271 20,000 - - - -22,000 - - - -24,000 - - - -26,000 - - - -28,000 - - - -29,000 - - - -31,000 - - - -33,000 - - - -35,000 - - - -AIRSPEED - KNOTS 12,000 LBS 11,000 LBS 10,000 LBS PRESSURE
ALTITUDE IOAT OAT
TORQUE PER ENGINE FUEL FLOW PER ENGINE TOTAL FUEL FLOW
NORMAL CRUISE POWER
1600 RPM
ISA -20ºC
NOTE:
1. IOAT, TORQUE AND FUEL FLOW BASED ON 11,000 POUNDS GROSS
WEIGHT.
2. DURING OPERATION WITH ICE VANES EXTENDED, TRUE AIRSPEED WILL
BE REDUCED IF ORIGINAL TORQUE IS NOT OR CANNOT BE RESET, BUT
WILL BE UNCHANGED IF ORIGINAL TORQUE IS RESET.
FEET °C °C FT-LBS LBS/HR LBS/HR IAS TAS IAS TAS IAS TAS
0 0 -5 2230 446 893 236 228 237 229 238 230 2,000 -4 -9 2230 434 867 235 233 236 234 237 235 4,000 -8 -13 2230 421 842 233 238 234 239 235 240 6,000 -11 -17 2230 410 820 230 241 232 243 232 243 8,000 -15 -21 2230 399 798 228 246 229 247 230 248 10,000 -19 -25 2230 389 778 226 251 227 252 228 253 12,000 -23 -29 2230 380 760 223 256 224 257 225 258 14,000 -26 -33 2230 372 745 221 261 222 262 224 264 16,000 -30 -37 2230 365 731 218 266 220 268 221 269 18,000 -34 -41 2230 358 717 217 273 218 274 219 275 20,000 -37 -45 2230 352 704 214 277 215 279 217 281 22,000 -41 -49 2230 348 695 211 283 213 285 214 286 24,000 -45 -53 2230 344 688 208 288 210 290 211 292 26,000 - - - -28,000 - - - -29,000 - - - -31,000 - - - -33,000 - - - -35,000 - - - -AIRSPEED - KNOTS 12,000 LBS 11,000 LBS 10,000 LBS PRESSURE
ALTITUDE IOAT OAT
TORQUE PER ENGINE FUEL FLOW PER ENGINE TOTAL FUEL FLOW
NORMAL CRUISE POWER
1600 RPM
ISA -10ºC
NOTE:
1. IOAT, TORQUE AND FUEL FLOW BASED ON 11,000 POUNDS GROSS
WEIGHT.
2. DURING OPERATION WITH ICE VANES EXTENDED, TRUE AIRSPEED WILL
BE REDUCED IF ORIGINAL TORQUE IS NOT OR CANNOT BE RESET, BUT
WILL BE UNCHANGED IF ORIGINAL TORQUE IS RESET.
3. OBSERVE
MMO LIMITATION WHERE APPLICABLE.
FEET °C °C FT-LBS LBS/HR LBS/HR IAS TAS IAS TAS IAS TAS
0 10 5 2230 451 903 236 232 236 232 237 233 2,000 6 1 2230 438 877 233 236 234 237 235 238 4,000 2 -3 2230 427 853 230 239 231 240 232 241 6,000 -1 -7 2230 415 830 228 244 229 245 230 246 8,000 -5 -11 2230 404 808 226 249 227 250 228 251 10,000 -9 -15 2230 394 788 224 254 225 255 226 256 12,000 -12 -19 2230 385 770 221 259 222 260 223 261 14,000 -16 -23 2230 377 755 219 264 220 265 221 267 16,000 -20 -27 2230 370 741 217 270 219 272 220 273 18,000 -23 -31 2230 363 727 214 275 216 277 217 278 20,000 -27 -35 2230 357 714 211 280 213 282 214 284 22,000 -31 -39 2230 352 705 209 286 210 288 211 289 24,000 -34 -43 2230 349 698 206 292 208 295 209 296 26,000 -38 -47 2230 347 693 203 297 205 300 207 302 28,000 -42 -50 2230 350 701 199 301 201 304 202 306 29,000 -44 -52 2230 350 700 197 304 199 307 202 310 31,000 - - - -33,000 - - - -35,000 - - - -AIRSPEED - KNOTS 12,000 LBS 11,000 LBS 10,000 LBS PRESSURE
ALTITUDE IOAT OAT
TORQUE PER ENGINE FUEL FLOW PER ENGINE TOTAL FUEL FLOW
NORMAL CRUISE POWER
1600 RPM
ISA
NOTE:
1. IOAT, TORQUE AND FUEL FLOW BASED ON 11,000 POUNDS GROSS
WEIGHT.
2. DURING OPERATION WITH ICE VANES EXTENDED, TRUE AIRSPEED WILL
BE REDUCED IF ORIGINAL TORQUE IS NOT OR CANNOT BE RESET, BUT
WILL BE UNCHANGED IF ORIGINAL TORQUE IS RESET.
3. OBSERVE
MMO LIMITATION WHERE APPLICABLE.
FEET °C °C FT-LBS LBS/HR LBS/HR IAS TAS IAS TAS IAS TAS
0 20 15 2230 456 912 234 234 235 235 235 235 2,000 16 11 2230 442 885 231 238 232 239 233 240 4,000 13 7 2230 431 861 229 242 230 243 231 244 6,000 9 3 2230 419 838 227 247 228 248 229 249 8,000 5 -1 2230 409 818 224 251 225 253 226 254 10,000 1 -5 2230 398 796 221 256 223 258 224 259 12,000 -2 -9 2230 389 778 220 262 221 263 221 264 14,000 -6 -13 2230 382 764 218 268 219 270 220 271 16,000 -10 -17 2230 375 750 215 273 216 274 217 276 18,000 -13 -21 2230 368 736 212 278 214 280 214 281 20,000 -17 -25 2230 362 725 209 283 210 285 212 287 22,000 -21 -29 2230 358 717 207 290 209 292 210 294 24,000 -24 -33 2230 355 710 204 296 206 298 207 300 26,000 -28 -37 2230 356 711 201 301 203 304 205 306 28,000 -32 -40 2179 342 684 196 304 199 308 200 310 29,000 -34 -42 2108 331 662 192 303 194 307 197 310 31,000 -38 -46 1940 317 634 182 299 185 303 188 307 33,000 -42 -50 1750 278 556 170 291 174 297 177 302 35,000 -47 -54 1558 251 501 157 280 162 288 166 294 AIRSPEED - KNOTS 12,000 LBS 11,000 LBS 10,000 LBS PRESSURE
ALTITUDE IOAT OAT
TORQUE PER ENGINE FUEL FLOW PER ENGINE TOTAL FUEL FLOW
NORMAL CRUISE POWER
1600 RPM
ISA +10ºC
NOTE:
1. IOAT, TORQUE AND FUEL FLOW BASED ON 11,000 POUNDS GROSS
WEIGHT.
2. DURING OPERATION WITH ICE VANES EXTENDED, TRUE AIRSPEED WILL
BE REDUCED IF ORIGINAL TORQUE IS NOT OR CANNOT BE RESET, BUT
WILL BE UNCHANGED IF ORIGINAL TORQUE IS RESET.
FEET °C °C FT-LBS LBS/HR LBS/HR IAS TAS IAS TAS IAS TAS
0 30 25 2230 462 924 232 237 233 238 233 238 2,000 27 21 2230 447 895 230 240 231 241 232 242 4,000 23 17 2230 434 869 228 245 229 246 230 247 6,000 19 13 2230 424 847 225 250 226 251 227 252 8,000 15 9 2230 413 826 223 255 224 256 225 257 10,000 12 5 2230 402 804 221 260 221 261 222 262 12,000 8 1 2230 395 790 218 265 219 266 221 268 14,000 4 -3 2230 387 774 215 270 217 272 218 273 16,000 0 -7 2230 379 758 212 275 214 277 215 278 18,000 -3 -11 2230 372 744 210 281 211 283 213 285 20,000 -7 -15 2230 366 733 207 287 209 289 210 290 22,000 -10 -19 2230 368 736 204 291 205 293 207 295 24,000 -15 -23 2170 351 702 199 293 201 296 202 298 26,000 -19 -27 2016 328 656 190 291 192 294 194 297 28,000 -23 -30 1890 308 616 181 288 184 292 186 296 29,000 -25 -32 1822 298 595 177 287 179 291 182 295 31,000 -29 -36 1674 275 549 166 281 170 287 173 292 33,000 -33 -40 1504 251 501 154 270 159 278 163 284 35,000 -38 -44 1330 225 451 139 255 146 267 151 275 AIRSPEED - KNOTS 12,000 LBS 11,000 LBS 10,000 LBS PRESSURE
ALTITUDE IOAT OAT
TORQUE PER ENGINE FUEL FLOW PER ENGINE TOTAL FUEL FLOW
NORMAL CRUISE POWER
1600 RPM
ISA +20ºC
NOTE:
1. IOAT, TORQUE AND FUEL FLOW BASED ON 11,000 POUNDS GROSS
WEIGHT.
2. DURING OPERATION WITH ICE VANES EXTENDED, TRUE AIRSPEED WILL
BE REDUCED IF ORIGINAL TORQUE IS NOT OR CANNOT BE RESET, BUT
WILL BE UNCHANGED IF ORIGINAL TORQUE IS RESET.
FEET °C °C FT-LBS LBS/HR LBS/HR IAS TAS IAS TAS IAS TAS
0 40 35 2230 467 934 229 237 230 238 231 239 2,000 37 31 2230 453 906 228 242 229 243 230 244 4,000 33 27 2230 440 881 226 247 226 248 227 249 6,000 29 23 2230 429 857 223 252 224 253 225 254 8,000 25 19 2230 418 835 221 257 222 258 223 259 10,000 22 15 2230 407 813 218 262 219 263 221 265 12,000 18 11 2230 399 797 216 268 218 270 219 271 14,000 14 7 2230 391 782 214 273 215 275 216 276 16,000 11 3 2230 384 768 211 278 212 280 213 281 18,000 7 -1 2230 383 766 208 283 209 285 211 287 20,000 3 -5 2144 361 722 201 284 204 287 205 289 22,000 -1 -9 1968 334 668 192 281 194 284 196 286 24,000 -5 -13 1810 310 621 182 276 185 280 187 283 26,000 -9 -17 1664 288 576 173 271 176 276 178 279 28,000 -14 -20 1543 269 538 164 267 167 272 170 277 29,000 -16 -22 1483 259 519 159 265 163 271 166 276 31,000 -20 -26 1345 238 475 147 255 152 263 156 269 33,000 -25 -30 1191 215 429 131 237 139 251 144 260 35,000 -29 -34 1031 192 384 - - 121 228 131 247 AIRSPEED - KNOTS 12,000 LBS 11,000 LBS 10,000 LBS PRESSURE
ALTITUDE IOAT OAT
TORQUE PER ENGINE FUEL FLOW PER ENGINE TOTAL FUEL FLOW
NORMAL CRUISE POWER
1600 RPM
ISA +30ºC
NOTE:
1. IOAT, TORQUE AND FUEL FLOW BASED ON 11,000 POUNDS GROSS
WEIGHT.
2. DURING OPERATION WITH ICE VANES EXTENDED, TRUE AIRSPEED WILL
BE REDUCED IF ORIGINAL TORQUE IS NOT OR CANNOT BE RESET, BUT
WILL BE UNCHANGED IF ORIGINAL TORQUE IS RESET.
FEET °C °C FT-LBS LBS/HR LBS/HR IAS TAS IAS TAS IAS TAS
0 50 45 2230 474 947 230 241 231 242 232 243 2,000 47 41 2230 459 918 228 246 229 247 229 247 4,000 43 37 2230 446 892 224 250 225 251 226 252 6,000 39 33 2230 434 869 222 255 223 256 224 257 8,000 36 29 2230 423 845 220 260 220 261 222 263 10,000 32 25 2230 413 825 217 265 219 267 219 268 12,000 28 21 2230 407 813 214 270 216 272 216 273 14,000 24 17 2212 395 791 210 274 212 276 213 277 16,000 20 13 2078 371 742 203 273 204 275 206 277 18,000 16 9 1943 347 694 195 271 197 274 198 276 20,000 12 5 1819 326 652 187 269 189 272 190 274 22,000 8 1 1631 299 598 176 262 178 266 181 269 24,000 4 -3 1480 275 551 165 256 169 261 172 265 26,000 0 -7 1345 254 508 155 249 159 255 162 260 28,000 -5 -10 1223 234 468 142 239 148 249 152 255 29,000 -7 -12 1162 224 448 135 231 142 243 147 251 31,000 -11 -16 1030 203 407 111 200 127 227 136 241 33,000 - - - -35,000 - - - -AIRSPEED - KNOTS 12,000 LBS 11,000 LBS 10,000 LBS PRESSURE
ALTITUDE IOAT OAT
TORQUE PER ENGINE FUEL FLOW PER ENGINE TOTAL FUEL FLOW