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Revision B: June 7, 2016 Document No. 13-206CGW
PILOT’S OPERATING HANDBOOK and
FAA-Approved Airplane Flight Manual Supplement
for the
KING AIR MODEL C90/C90A
Equipped with Raisbeck Engineering: Swept Blade Turbofan Propellers - STC SA3593NM Dual Aft Body Strakes - STC SA4010NM Increased Gross Weight - STC SA3593NM Increased ITT and Cruise Speeds - STC SA3593NM Optional 1,600 Cruise RPM - STC SA3593NM
C90: LJ-527 thru LJ-1062 (including C90,C90-1) C90A: LJ-1063 thru LJ-1726, LJ-1728 thru LJ-1753,
LJ-1755 (including C90A,C90B,C90SE)
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Document No. 13-206CGW Increased Gross Weight
FAA-Approved: Revision B: June 7, 2016 i
PILOT’S OPERATING HANDBOOK AND FAA-APPROVED
AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECHCRAFT KING AIR MODELS
C90/C90A
Equipped with Raisbeck Engineering: Swept Blade Turbofan Propellers - STC SA3593NM Dual Aft Body Strakes - STC SA4010NM Increased Gross Weight - STC SA3593NM (for PT6A-21 powered aircraft) Increased ITT and Cruise Speeds - STC SA3593NM (for C90 and C90-1) Optional 1,600 Cruise RPM Minimum Cruise - STC SA3593NM
Reg. No._____________________
Ser. No._____________________
This Supplement must be attached to the Beechcraft Pilot’s Operating Handbook and FAA-approved Airplane Flight Manual when Raisbeck Swept Blade Turbofan Propellers and Raisbeck Dual Aft Body Strakes are installed in accordance with the STCs listed above. The information contained in this document supplements or supersedes the basic manual only in those areas listed. For limitations, procedures, and performance information not contained in this supplement, consult the Beechcraft Pilot’s Operating Handbook and FAA-approved Airplane Flight Manual. The increased gross weight capability applies to aircraft powered by Pratt & Whitney Canada PT6A-21 engines.
I. GENERAL II. LIMITATIONS III. EMERGENCY PROCEDURES IV. NORMAL PROCEDURES V. PERFORMANCE VI. WEIGHT AND BALANCE VII. SYSTEMS DESCRIPTION
FAA-Approved: for Manager, Seattle Aircraft Certification Office Federal Aviation Administration Seattle, Washington
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
ii FAA-Approved: Revision B: June 7, 2016
Document No. 13-206CGW
BEECHCRAFT KING AIR MODELS
C90/C90A
PILOT’S OPERATING HANDBOOK AND FAA-APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
Original Issue ................................................................................................................... December 12, 2013
Title Page
Pages i thru iii, 1-1, 2-1 thru 2-4, 3-1, 4-1, 4-2, 5-1 thru 5-55, 6-1, 6-2, and 7-1
LOG OF REVISIONS
REV PAGE(S) DESCRIPTION FAA-APPROVED DATE
IR All Initial Release
A 1-1, 2-1
2-4
2-4, 6-1, 6-2
6-1, 6-2
Changed propeller feather blade angle from 84.5° to 86.7°. Removed redundant reference to SL-08-BC-1. Expanded in-flight aft CG limit. Removed reference propeller weight and moment arm.
B Title, i, ii, 1-1 2-2
2-3, 2-4
5-5 thru 5-14, 5-54
5-53
Corrected title Deleted 10,350 lb from flight load factors. Revised weight limits and removed requirement for wing ballast weight. Calrified tire requirement. Replaced existing charts with revised performance charts Added max Landing Weight chart
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Document No. 13-206CGW Increased Gross Weight
FAA-Approved: Revision A: September 17, 2014 iii
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
SECTION VII ................................................................................... SYSTEMS DESCRIPTION
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA-Approved: Revision B: June 7, 2016 1-1
Document No. 13-206CGW Section I - General
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 King Air.
The information contained in this Pilot’s Operating Handbook and FAA-Approved Airplane Flight
Manual Supplement highlights the areas of performance improvement which can be expected from your Raisbeck-equipped King Air C90/C90A.
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 Beechcraft King Air C90/C90A 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
For current revision status visit www.raisbeck.com
FAA-Approved information, limitations, performance, and data are on pages marked at the bottom: “FAA-Approved: Revision Level and Date .”
PROPELLERS
No. of Propellers: 2 Propeller Manufacturer: Hartzell Propeller Inc. No. of Blades: 4 Propeller Diameter:
Maximum: 96 inches Minimum: 95 inches
Propeller Type: Constant-speed, Full-feathering, Reversing, Counter-weighted,
Hydraulically Actuated consisting of D9510SK blades and HC-D4N-3C hubs.
Pitch Range (30-inch station):
Reverse: -10.0° ± 0.5° Feathered: +86.7° ± 0.5°
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA-Approved: Revision A: September 17, 2014 2-1
Document No. 13-206CGW Section II - Limitations
SECTION II — LIMITATIONS
POWER PLANT LIMITATIONS Engine Model ............................................................................................................................... PT6A-21
ENGINE OPERATING LIMITS The following limitations shall be observed. Each column presents limitations. The limits presented do not necessarily occur simultaneously. Refer to Pratt & Whitney Canada Engine Maintenance Manual for specific actions required if limits are exceeded.
OPERATING CONDITION SHP TORQUE
MAXIMUM GENERATOR RPM N1
PROP OIL OIL
OBSERVED RPM PRESS TEMP
FT‐LBS (1) ITT °C RPM % N2 PSI (2) °C (3)
STARTING ‐‐‐ ‐‐‐ 1090 (4) ‐‐‐ ‐‐‐ ‐‐‐ ‐‐‐ ‐40 (min) LOW IDLE ‐‐‐ ‐‐‐ 660 (5) ‐‐‐ 51(min) 1100(min) 40(min) ‐40 to 99 HIGH IDLE ‐‐‐ ‐‐‐ ‐‐‐ ‐‐‐ 70 (approx) ‐‐‐ ‐‐‐ 0 to 99 TAKE‐OFF & MAX CONT 550 1315 695 38,100 101.5 2200 80 to 100 10 to 99 CRUISE CLIMB AND MAX CRUISE 538 1315 (6) 695 38,100 101.5 2200 80 to 100 0 to 99 MAX REVERSE (7) ‐‐‐ ‐‐‐ 695 ‐‐‐ 88 2100 80 to 100 0 to 99 TRANSIENT ‐‐‐ 1500 (4) 825 (4)(8) 38,500 102.6 2420 ‐‐‐ 0 to 99
(1) Maximum permissible sustained torque is 1315 ft/lbs. Propeller speeds (N2) must be set so at not to exceed power limitation.(2) When gas generator speeds are above 72% N1 and oil temperatures are between 60° C and 70° C, normal oil pressures is between 80 and 100 psi. Oil pressure between 40 and 80 psi is undesirable; it should be tolerated only for the completion of the flight, and then only at a reduced power setting. Oil pressure below 40 psi is unsafe; it requires that either the engine be shut down, or that a landing be made as soon as possible, using the minimum power required to sustain flight. (3) For increased service life of engine oil, an oil temperature of between 74° C and 80° C is recommended. A minimum oil temperature of 55° C is recommended for fuel heater operation at take‐off power. (4) These values are time‐limited to two seconds. (5) High ITT at ground idle may be corrected by reducing accessory load and/or increasing N1 RPM. (6) Cruise torque values vary with altitude and temperature. (7) Reverse power operation is limited to one minute. (8) Higher generator load at low N1 speeds may cause the ITT transient temperature limit to be exceeded. This does not apply during engine start. Observe generator load limits.
PROPELLER BLADE AND HUB NUMBERS
Two full-feathering, constant-speed, reversing, four-bladed propellers consisting of D9510SK blades and HC-D4N-3C hubs.
PROPELLER DIAMETER
Maximum diameter: 96.0 inches Minimum diameter: 95.0 inches
PROPELLER BLADE ANGLES AT 30-INCH STATION
Reverse: -10.0° ± 0.5° Feathered: +86.7° ± 0.5°
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
2-2 FAA-Approved: Revision B: June 7, 2016
Document No. 13-206CGW Section II - Limitations
PROPELLER REVERSE SPEED LIMITS
Do not select REVERSE until airspeed is below 95 KIAS.
WARNING PROPELLERS WILL NOT REVERSE AT AIRSPEEDS ABOVE 100 KIAS. BETWEEN 95 KIAS AND 100 KIAS, SIGNIFICANT THRUST ASYMMETRY MAY OCCUR IF REVERSE IS SELECTED.
PROPELLER ROTATIONAL SPEED LIMITS
CAUTION Stabilized ground operation between 400 and 1,100 RPM is prohibited. Operation between 0 and 400 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.
The maximum propeller overspeed limit is 2,420 RPM. Propeller speeds above 2,200 RPM indicate failure of the primary governor. Propeller speeds above 2,288 RPM indicate failure of both primary and overspeed governors.
POWERPLANT INSTRUMENT MARKINGS
Propeller Tachometer:
(LJ-527 thru LJ-1360, LJ-1362, and C90SE): Green Arc ................................................................................................. 1,600 to 2,200 RPM Red Radial .............................................................................................................. 2,200 RPM
(LJ-1361, LJ-1363 and After, excluding C90SE):
Green Arc ................................................................................................. 1,100 to 2,200 RPM Red Radial .............................................................................................................. 2,200 RPM
MISCELLANEOUS INSTRUMENT MARKINGS
Propeller De-ice Ammeter: Green Arc ....................................................................................................................... 18 to 24 amps
BEECH PROPELLER AUTOFEATHER SYSTEM INSTALLATION REQUIREMENTS
The optional Beech propeller autofeather system must be installed, operational, and armed prior to takeoff and landing.
CAUTION VMCA with one-engine inoperative, thrust lever at idle, and propeller windmilling is 99 KIAS (101 KCAS).
AIRSPEED LIMITATIONS
Air Minimum Control Speed, VMCA ................................................................................. 94 KCAS (93 KIAS)
Maximum Operating Speed, VMO, above 9,650 lbs (LJ-1063 thru LJ-1137, and LJ-1146) ......................................................................... 208 KCAS (208 KIAS)
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA-Approved: Revision B: June 7, 2016 2-3
Document No. 13-206CGW Section II - Limitations
AIRSPEED INDICATOR MARKINGS
C90/C90-1 (LJ-502 thru LJ-1062)
Red Radial (Air Minimum Control Speed, VMCA) ................................................................ 94 KCAS
C90A/C90B/C90SE (LJ-1063 thru LJ-1726, LJ-1728 thru LJ-1753, LJ-1755)
Red Radial (Air Minimum Control Speed, VMCA) ................................................................. 93 KIAS (LJ-1063 thru LJ-1137, and LJ-1146 only)
Red Line .......................................................................................................................... 208 KIAS*
Red and White Hash-Marked Pointer ............................................................................ 0.46 Mach* *Maximum speed for any operation is 208 KIAS or value equal to 0.46 Mach, whichever is lower.
AIRCRAFT EQUIPPED WITH GARMIN G1000
AIRSPEED INDICATOR DISPLAY (With Placard P/N REI-1001-14 installed)
Two (2) placards have been installed, one above each Primary Flight Display unit, to notify the pilot to disregard the VMC RED LINE displayed on the airspeed tape.
FLIGHT LOAD FACTORS At the design gross weight of 10,500 lbs ............................... Maneuver – positive 3.27G – negative 1.31G
MAXIMUM WEIGHT
Maximum Taxi Weight .................................................................................................................. 10,560 lbs Maximum Takeoff Weight ............................................................................................................. 10,500 lbs Maximum Landing Weight .............................................................................................................. 9,700 lbs Maximum Zero Fuel Weight:
For MTOW below 9,650 lbs .......................................................................................... No limitation For MTOW between 9,650 and 10,500 lbs ....................................................................... 9,000 lbs
NOTE
10-ply rated main tires required for operation above 10,100 lbs.
DISREGARD VMC MARKING VMC = 93 KIAS
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
2-4 FAA-Approved: Revision B: June 7, 2016
Document No. 13-206CGW Section II - Limitations
CENTER OF GRAVITY LIMITS (LANDING GEAR EXTENDED)
Aft Limit .......................................................................................... 160.0 inches aft of Datum at all weights (LJ-527 thru LJ-1137, and LJ-1146) Forward Limit at:
10,500 lbs ...................................................................................................... 154.8 inches aft of Datum 10,350 lbs ...................................................................................................... 154.5 inches aft of Datum 10,100 lbs ...................................................................................................... 154.0 inches aft of Datum 9,700 lbs ........................................................................................................ 154.0 inches aft of Datum 9,168 lbs ........................................................................................................ 151.4 inches aft of Datum 7,400 lbs or less ............................................................................................ 144.7 inches aft of Datum
(LJ-1138 thru LJ-1145, LJ-1147 and after) Forward Limit at:
10,500 lbs * ................................................................................................... 153.4 inches aft of Datum 10,350 lbs ...................................................................................................... 153.0 inches aft of Datum 10,100 lbs ...................................................................................................... 152.0 inches aft of Datum 7,850 lbs or less ............................................................................................ 144.7 inches aft of Datum
PLACARDS
C90/C90-1 (LJ-502 thru LJ-1062)
On Existing Overhead Panel in Pilot’s Compartment:
MIN SINGLE ENGINE CONTROL 94 KNOTS (108 MPH)
(LJ-1063 thru LJ-1137, and LJ-1146 only)
On Overhead Panel in Pilot’s Compartment:
AIRSPEED LIMITATIONS: MAX OPERATION 208 KIAS (SL TO 20,300 FT) DECREASE BY
4 KNOTS FOR EVERY 1,000 FT ABOVE 20,300 FT
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA-Approved: Revision A: September 17, 2014 3-1
Document No. 13-206CGW Section III – Emergency Procedures
SECTION III — EMERGENCY PROCEDURES
ELECTROTHERMAL PROPELLER DE-ICE Operation in icing conditions with abnormal readings on the de-ice ammeter are not recommended and ice removal cannot be assured. Normal Operation: 18 to 24 amps.
1. Zero Amps:
a. Breaker Switch - CHECK. b. If OFF, reposition to ON after 30 seconds. c. If ON with zero amps, system is inoperative. Position switch to OFF.
2. Zero to 18 Amps:
a. Continue operation. b. If propeller imbalance occurs, increase RPM briefly to aid in ice removal.
3. 24 to 29 Amps:
a. Continue operation. b. If propeller imbalance occurs, increase RPM briefly to aid in ice removal.
4. More than 29 Amps:
a. Avoid icing conditions, since continued operation of the system cannot be assured. b. Do not operate the system, except in emergencies. c. Restrict time of operation to a minimum.
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA-Approved: Revision A: September 17, 2014 4-1
Document No. 13-206CGW Section IV – Normal Procedures
SECTION IV — NORMAL PROCEDURES
AFTER STARTING ENGINES
CAUTION
Stabilized ground operation between 400 and 1,100 RPM is prohibited. Operation between 0 and 400 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.
ICING FLIGHT
Electrothermal Propeller De-ice:
CAUTION
Do not operate propeller de-ice when propellers are static.
a. Before Takeoff:
(1) Propeller Heat Switch - HEAT. (2) Propeller De-ice Ammeter - CHECK: 18 to 24 AMPERES. Monitor for 2 minutes
to assure automatic timer operation.
b. In Flight:
(1) Propeller Heat Switch - HEAT. The system may be operated continuously in flight and will function automatically until the switch is turned to OFF.
(2) Relieve propeller imbalance due to ice by increasing rpm briefly and returning to the desired setting. Repeat as necessary.
CAUTION
If the de-ice ammeter does not indicate 18 to 24 amperes, refer to the EMERGENCY PROCEDURES section.
LANDING
WARNING
PROPELLERS WILL NOT REVERSE AT AIRSPEEDS ABOVE 100 KIAS. BETWEEN 95 KIAS AND 100 KIAS, SIGNIFICANT THRUST ASYMMETRY MAY OCCUR IF REVERSE IS SELECTED.
SIMULATING ENGINE FAILURES
CAUTION
Using throttle cuts to simulate engine failures will result in the autofeather system being disarmed. In this configuration the VMCA is 99 KIAS (101 KCAS). Dynamic throttle cuts should only be attempted at airspeeds above 104 KIAS (105 KCAS).
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
4-2 FAA-Approved: Revision B: June 7, 2016
Document No. 13-206CGW Section IV – Normal Procedures
NOISE CHARACTERISTICS
Approach to and departure from an airport should be made so as to avoid prolonged flight at low altitude near noise-sensitive areas. Avoidance of noise-sensitive areas, if practical, is preferable to overflight 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 2,000 feet above the surface, weather permitting, even though flight at a 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 of less than 2,000 feet is necessary to adequately exercise his duty to see and avoid other airplanes.
The corrected takeoff noise level of this airplane, established in compliance with FAR Part 36, Appendix G (Amdt 36-28) and ICAO Annex 16, Chapter 10, is 84.4 dB as determined by flight tests. No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable for operation at, into, or out of any airport. The above statement notwithstanding, the noise level stated above has been verified by and approved by the Federal Aviation Administration in noise level test flights conducted in accordance with FAR Part 36, Appendix G, Amendment 28, Noise Standards: Airplane Type and Airworthiness Certification. The airplane noise is in compliance with all FAR Part 36 noise standards applicable to this type.
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA-Approved: Revision B: June 7, 2016 5-1
Document No. 13-206CGW Section V – Performance
SECTION V — PERFORMANCE
TABLE OF CONTENTS
INTRODUCTION
Introduction ........................................................................................................................................... 5-2
TAKEOFF AND CLIMB DATA
Stall Speeds - Zero Thrust .................................................................................................................... 5-3 Minimum Takeoff Power at 2200 RPM ................................................................................................. 5-4 Maximum Takeoff Weight to Achieve Positive One Engine Inoperative Climb at Lift-off ..................... 5-5 Maximum Allowable TOGW above 10,350 LBS ................................................................................... 5-6 Takeoff Distance – Flaps Up – Two Engines ....................................................................................... 5-7 Accelerate-Stop Distance – Flaps Up.................................................................................................... 5-8 Accelerate-Go Distance – Flaps Up ..................................................................................................... 5-9 Takeoff Climb Gradient – One-Engine-Inoperative ............................................................................. 5-10 Enroute Climb – All Engines Operating .............................................................................................. 5-11 Enroute Climb – One Engine Inoperative ........................................................................................... 5-12 Service Ceiling – One Engine Inoperative .......................................................................................... 5-13 Time, Fuel and Distance to Cruise Climb ........................................................................................... 5-14
CRUISE DATA
Normal Cruise Power Setting Tables:
ISA -30°C ..................................................................................................................................... 5-16 ISA -20°C ..................................................................................................................................... 5-17 ISA -10°C ..................................................................................................................................... 5-18 ISA ................................................................................................................................................ 5-19 ISA +10°C .................................................................................................................................... 5-20 ISA +20°C .................................................................................................................................... 5-21 ISA +30°C .................................................................................................................................... 5-22 ISA +37°C .................................................................................................................................... 5-23
Normal Cruise Power Setting Graphs: Normal Cruise Speeds ................................................................................................................. 5-24 Normal Cruise Power ................................................................................................................... 5-25 Fuel Flow at Normal Cruise Power .............................................................................................. 5-26
Maximum Cruise Power Setting Tables: ISA -30°C ..................................................................................................................................... 5-28 ISA -20°C ..................................................................................................................................... 5-29 ISA -10°C ..................................................................................................................................... 5-30 ISA ................................................................................................................................................ 5-31 ISA +10°C .................................................................................................................................... 5-32 ISA +20°C .................................................................................................................................... 5-33 ISA +30°C .................................................................................................................................... 5-34 ISA +37°C .................................................................................................................................... 5-35
Maximum Cruise Power Setting Graphs: Maximum Cruise Speeds ............................................................................................................. 5-36 Maximum Cruise Power ............................................................................................................... 5-37 Fuel Flow at Maximum Cruise Power .......................................................................................... 5-38
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-2 FAA-Approved: Revision B: June 7, 2016
Document No. 13-206CGW Section V – Performance
Maximum Range Power Setting Tables:
ISA -30°C ..................................................................................................................................... 5-40 ISA -20°C ..................................................................................................................................... 5-41 ISA -10°C ..................................................................................................................................... 5-42 ISA ................................................................................................................................................ 5-43 ISA +10°C .................................................................................................................................... 5-44 ISA +20°C .................................................................................................................................... 5-45 ISA +30°C .................................................................................................................................... 5-46 ISA +37°C .................................................................................................................................... 5-47
Range with 384 Gallons Usable Fuel ................................................................................................. 5-48 Endurance with 384 Gallons Usable Fuel .......................................................................................... 5-49
DESCENT AND LANDING DATA
Holding Time ....................................................................................................................................... 5-51 Time, Fuel, and Distance to Descend ................................................................................................ 5-52 Maximum Landing Weight – Flaps Down ........................................................................................... 5-53 Climb – Balked Landing ...................................................................................................................... 5-54 Landing Distance Without Propeller Reversing .................................................................................. 5-55 Landing Distance With Propeller Reversing ....................................................................................... 5-56
INTRODUCTION
The performance of all Beechcraft King Air C90/C90A airplanes equipped with the Raisbeck Increased Gross Weight System will perform to the graphs and charts in this section, up to a maximum takeoff gross weight of 10,500 lbs and a maximum landing weight of 9,700 lbs. Federal Aviation Regulations for this class aircraft require only that the all-engines operating distance over a 50 foot height be presented for take-off distance. We include for your information accelerate-go, accelerate-stop, climb-limited weight, net climb gradient, and other FAR 25 transport category information. For data not shown in this section, refer to Section V of the Beechcraft POH. Cruise performance is divided into three sections: NORMAL CRUISE, MAXIMUM CRUISE, and MAXIMUM RANGE. All sections recommend 1,750 propeller RPM for maximum quietness combined with excellent performance. Propeller RPM reduction in flight to 1,600 RPM is an option, requiring a rigging change to the propeller governors (see applicable Raisbeck Installation and Maintenance Manuals). Cruise at 1,750 RPM does not require this option. MAXIMUM CRUISE power settings reflect an increase in maximum allowable engine ITT to 695° C for C90 and C90-1 airplanes, per Raisbeck Engineering and FAA recertification of Pratt & Whitney Canada certified limits for the PT6A-21 engines. Slight variance in cruise speeds (±4 KTAS) may be evident between pitot inlet airplanes (C90A, C90B, C90SE) and chin inlet airplanes (C90 & C90-1).
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA-Approved: Revision A: September 17, 2014 5-3
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-4 FAA-Approved: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
OUTSIDE AIR TEMPERATURE ~ DEGREES C
-40 -30 -20 -10 0 10 20 30 40 50 60
MIN
IMU
M T
OR
QU
E S
ET
TIN
G (
220
0 R
PM
) ~
FT
-LB
S
700
800
900
1000
1100
1200
1300
NOTE:THE POWER (TORQUE) INDICATED IS THE MINIMUM VALUEFOR WHICH TAKE-OFF PERFORMANCE CAN BE OBTAINED.EXCESS POWER WHICH CAN BE DEVELOPED WITHOUT EXCEEDING ENGINE LIMITATIONS MAY BE UTILIZED.
OUTSIDE AIR TEMPERATURE ~ DEGREES C
-40 -30 -20 -10 0 10 20 30 40 50 60
MINIMUM TAKE-OFF POWER AT 2200 RPM (70 KNOTS)
TORQUE LIMIT: 1315 FT-LBS
PR
ES
SU
RE
ALTITU
DE
~ FEE
T
SL2000
40006000
8000
10,000
ISA +
37°
C
EXAMPLE:OAT AT TAKE-OFF ........................................AIRPORT PRESSURE ALTITUDE ................. MINIMUM TAKE-OFF POWER ......................
25° C3966 FT 1105 FT-LBS
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA-Approved: Revision B: June 7, 2016 5-5
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
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Document No. 13-206CGW Section V – Performance
M
AX
AL
LOW
AB
LE
T.O
.G.W
. ~
LB
S
10350
10400
10450
10500
OUTSIDE AIR TEMPERATURE ~ DEGREES C
-30 -20 -10 0 10 20 30 40
MAX ALLOWABLE TAKE-OFF GROSS WEIGHT ABOVE 10,350 LBS
IN ORDER TO ACHIEVE PART 25 APPROACH CLIMB & LANDING REQUIREMENTS
8,00
0 FT
EXAMPLE:OAT ..................................................................AIRPORT PRESSURE ALTITUDE ..................MAX ALLOWABLE T.O.G.W. ..........................
11° C4,000 FT 10,470 LBS
6,0
00 F
T
4,0
00 F
T
2,0
00 F
T
SE
A L
EV
EL
PRESSURE ALTITUDE ~ FEET
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
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Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-8 Reference Material: Revision B: June 7, 2016
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA-Approved: Revision B: June 7, 2016 5-9
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-10 FAA-Approved: Revision B: June 7, 2016
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA-Approved: Revision B: June 7, 2016 5-11
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-12 FAA-Approved: Revision B: June 7, 2016
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision B: June 7, 2016 5-13
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-14 Reference Material: Revision B: June 7, 2016
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-15
Document No. 13-206CGW Section V – Performance
C90 / C90-1 / C90A / C90B / C90SE
NORMAL CRUISE POWER SETTINGS
(LJ-527 and subsequent with PT6A-21 engines)
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-16 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
NO
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-17
Document No. 13-206CGW Section V – Performance
NO
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-18 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
NO
RM
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-19
Document No. 13-206CGW Section V – Performance
NO
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-20 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
NO
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-21
Document No. 13-206CGW Section V – Performance
NO
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-22 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
NO
RM
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CR
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ISA
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178
224
180
227
14,0
002
272
1061
238
476
168
219
171
223
174
227
16,0
001
864
1000
224
448
162
218
165
222
168
226
18,0
0014
5794
221
142
215
421
515
822
116
222
5
20,0
0010
5088
819
839
614
721
115
221
815
622
4
22,0
006
4383
218
637
213
920
714
521
514
922
2
24,0
002
3678
017
535
012
919
913
721
114
222
0
26,0
00-3
2772
616
332
611
718
812
820
613
521
6
28,0
00-7
1966
915
230
485
142
117
195
127
211
29,0
00-1
015
635
146
292
107
180
121
205
NO
TE
:1
. IO
AT
, T
OR
QU
E A
ND
FU
EL
FL
OW
BA
SE
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N 8
50
0 P
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SE
19
00
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HE
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QU
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3.
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E 1
75
0 R
PM
AT
HIG
HE
R A
LT
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DE
PR
OP
RP
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AIR
SP
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NO
TS
95
00
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50
0 L
BS
75
00
LB
SIO
AT
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-23
Document No. 13-206CGW Section V – Performance
NO
RM
AL
CR
UIS
E P
OW
ER
ISA
+3
7° C
PR
ES
SU
RE
TO
RQ
UE
FU
EL
F
LO
WT
OT
AL
AL
TIT
UD
EP
ER
E
NG
INE
PE
R
EN
GIN
EF
UE
L
FL
OW
FE
ET
CF
FT
-LB
SL
BS
/HR
LB
S/H
RC
AS
TA
SC
AS
TA
SC
AS
TA
S
175
0S
L56
133
131
532
66
522
002
1220
121
420
32
16
2,00
052
136
128
631
36
261
962
1419
821
619
92
18
4,00
048
118
125
630
06
001
922
1619
421
819
52
20
6,00
045
113
121
928
65
721
872
1818
922
019
12
22
8,00
041
106
117
127
25
441
822
1818
422
118
62
23
10,0
00
3799
111
325
75
141
762
1717
822
118
12
23
12,0
00
3391
105
524
34
861
692
1617
222
017
52
23
14,0
00
2984
999
229
458
163
215
166
219
169
223
16,0
00
2577
943
216
432
156
213
160
218
163
222
18,0
00
2170
889
203
406
149
210
153
216
157
221
20,0
00
1763
837
190
380
141
205
146
214
151
220
22,0
00
1355
784
179
358
132
199
139
210
144
218
24,0
00
846
733
168
338
121
190
131
205
137
215
26,0
00
639
683
157
314
103
168
122
198
130
211
28,0
00
032
633
146
292
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512
22
05
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00
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601
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280
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311
72
00
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TE
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OR
QU
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ND
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EL
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SE
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50
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SE
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00
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HE
N T
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QU
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3.
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E 1
75
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PM
AT
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HE
R A
LT
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DE
PR
OP
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SP
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NO
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95
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LB
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50
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BS
75
00
LB
SIO
AT
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-24 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
NORMAL CRUISE SPEEDSWEIGHT 8500 LBS
TRUE AIRSPEED ~ KNOTS
160 180 200 220 240 260
PR
ES
SU
RE
ALT
ITU
DE
~ F
EE
T
0
5000
10000
15000
20000
25000
30000
NORMAL CRUISE SPEEDSWEIGHT 8500 LBS
ISA
ISA -30° C
ISA
+30° C
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-25
Document No. 13-206CGW Section V – Performance
NORMAL CRUISE POWER
INDICATED OUTSIDE AIR TEMPERATURE ~ °C
-80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60
TO
RQ
UE
SE
TT
ING
~ F
T-L
BS
400
500
600
700
800
900
1000
1100
1200
1300
1400
PRESSURE ALTITUDE ~ FT
29,000
28,000
26,000
24,000
22,000
20,000
18,000
16,000
14,000
12,000
10,000
8,000
6,000
4,000
2,000
TORQUE LIMIT ~ 1315 FT-LBS
ISA
-30
° C
ISA
-20
° C
ISA
-10
° C
ISA
ISA
+10
° C
ISA
+20
° C
ISA
+30
° C
ISA
+37
° C
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-26 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
FUEL FLOW AT NORMAL CRUISE POWER
INDICATED OUTSIDE AIR TEMPERATURE ~ °C
-80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60
FU
EL
FLO
W ~
LB
S /
HR
/ E
NG
INE
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
310
320
330
340
350
PRESSURE ALTITUDE ~ FT29,000
26,000
24,000
22,000
20,000
18,000
16,000
14,000
12,000
10,000
8,000
6,000
4,000
2,000
SL
28,000
ISA
+30
° C
ISA
-20
° C
ISA
-30
° C
ISA
ISA
+20
° C
ISA
-10
° C
ISA
+37
° C
ISA
+10
° C
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-27
Document No. 13-206CGW Section V – Performance
C90 / C90-1 / C90A / C90B / C90SE
MAXIMUM CRUISE POWER SETTINGS
(LJ-527 and subsequent with PT6A-21 engines)
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-28 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
MA
XIM
UM
CR
UIS
E P
OW
ER
ISA
-3
0° C
PR
ES
SU
RE
TO
RQ
UE
FU
EL
F
LO
WT
OT
AL
AL
TIT
UD
EP
ER
E
NG
INE
PE
R
EN
GIN
EF
UE
L
FL
OW
FE
ET
CF
FT
-LB
SL
BS
/HR
LB
S/H
RC
AS
TA
SC
AS
TA
SC
AS
TA
S
190
0S
L-1
112
1315
335
670
218
207
220
208
221
209
2,00
0-1
55
1315
327
654
216
211
218
212
219
213
4,00
0-1
9-2
1315
320
640
214
215
216
216
217
217
6,00
0-2
2-8
1315
314
628
212
219
214
220
215
221
8,00
0-2
6-1
513
153
106
202
102
232
112
242
132
25
10,
000
-30
-22
1315
308
616
208
227
209
229
211
230
12,
000
-34
-29
1315
306
612
206
231
207
233
209
234
14,
000
-38
-36
1315
305
610
204
236
205
238
207
239
16,
000
-41
-42
1315
306
612
202
241
203
242
204
244
175
01
8,00
0-4
5-4
913
122
825
641
932
371
952
401
962
42
20,
000
-50
-58
1185
256
512
183
232
185
235
187
238
22,
000
-54
-65
1065
231
462
172
226
175
230
178
233
24,
000
-58
-72
958
209
418
162
219
165
224
168
228
26,
000
-62
-80
853
188
376
150
211
155
217
158
222
28,
000
-66
-87
758
168
336
137
200
144
209
149
216
29,
000
-69
-92
711
159
318
130
193
138
204
143
212
NO
TE
:1
. IO
AT
, T
OR
QU
E A
ND
FU
EL
FL
OW
BA
SE
D O
N 8
50
0 P
OU
ND
S2
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SE
19
00
RP
M W
HE
N T
OR
QU
E-L
IMIT
ED
3.
US
E 1
75
0 R
PM
AT
HIG
HE
R A
LT
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DE
4.
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SE
RV
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MO
/ M
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AT
ION
WH
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0 L
BS
85
00
LB
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50
0 L
BS
IOA
TA
IRS
PE
ED
KN
OT
S
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-29
Document No. 13-206CGW Section V – Performance
MA
XIM
UM
CR
UIS
E P
OW
ER
ISA
-2
0° C
PR
ES
SU
RE
TO
RQ
UE
FU
EL
F
LO
WT
OT
AL
AL
TIT
UD
EP
ER
E
NG
INE
PE
R
EN
GIN
EF
UE
L
FL
OW
FE
ET
CF
FT
-LB
SL
BS
/HR
LB
S/H
RC
AS
TA
SC
AS
TA
SC
AS
TA
S
190
0S
L-1
3013
1533
767
421
72
0921
821
021
92
11
2,0
00-5
2313
1532
865
621
52
1321
621
421
72
15
4,0
00-9
1613
1532
264
421
32
1721
421
821
52
20
6,0
00-1
210
1315
317
634
211
221
212
223
213
224
8,0
00-1
63
1315
313
326
209
226
210
227
211
228
10,0
00
-20
-413
1531
032
020
62
3020
823
120
92
33
12,0
00
-24
-11
1315
309
318
204
234
206
236
207
237
14,0
00
-27
-17
1315
308
316
202
239
204
241
205
242
16,0
00
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-24
1315
309
618
200
244
201
246
203
247
18,0
00
-35
-31
1248
294
588
193
243
195
246
197
248
175
020
,00
0-3
9-3
812
2426
653
218
32
3818
624
118
82
44
22,0
00
-43
-45
1106
241
482
173
232
176
236
178
239
24,0
00
-48
-54
991
218
436
162
226
166
231
169
234
26,0
00
-52
-62
885
196
392
151
217
156
224
159
229
28,0
00
-56
-69
786
176
352
138
206
145
215
149
222
29,0
00
-58
-72
739
166
332
131
199
139
211
144
219
NO
TE
:1
. IO
AT
, T
OR
QU
E A
ND
FU
EL
FL
OW
BA
SE
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N 8
50
0 P
OU
ND
S2
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SE
19
00
RP
M W
HE
N T
OR
QU
E-L
IMIT
ED
3.
US
E 1
75
0 R
PM
AT
HIG
HE
R A
LT
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DE
4.
OB
SE
RV
E V
MO
/ M
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IMIT
AT
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WH
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PP
LIC
AB
LE
PR
OP
RP
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50
0 L
BS
85
00
LB
S7
50
0 L
BS
IOA
TA
IRS
PE
ED
KN
OT
S
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-30 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
MA
XIM
UM
CR
UIS
E P
OW
ER
ISA
-1
0° C
PR
ES
SU
RE
TO
RQ
UE
FU
EL
F
LO
WT
OT
AL
AL
TIT
UD
EP
ER
E
NG
INE
PE
R
EN
GIN
EF
UE
L
FL
OW
FE
ET
CF
FT
-LB
SL
BS
/HR
LB
S/H
RC
AS
TA
SC
AS
TA
SC
AS
TA
S
190
0S
L9
481
315
339
678
216
212
217
213
218
214
2,0
005
411
315
331
662
213
216
215
217
216
218
4,0
002
361
315
323
646
211
220
213
221
214
222
6,0
00-2
281
315
317
634
209
224
210
225
212
227
8,0
00-6
211
315
314
628
207
228
208
230
210
231
10,
000
-10
141
315
313
626
205
233
206
234
207
236
12,
000
-13
91
315
311
622
203
237
204
239
205
240
14,
000
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11
315
311
622
200
242
202
244
203
245
16,
000
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315
3111
622
198
247
200
249
201
250
175
01
8,00
0-2
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31
315
292
584
191
245
193
248
194
250
20,
000
-29
-20
124
727
354
618
32
431
8524
618
724
9
22,
000
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-27
113
525
050
017
32
381
7624
217
924
5
24,
000
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-35
102
322
745
416
32
311
6623
616
924
0
26,
000
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-44
913
204
408
152
223
156
230
160
235
28,
000
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813
183
366
139
212
145
222
150
228
29,
000
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765
173
346
132
205
140
217
145
225
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TE
:1
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AT
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OR
QU
E A
ND
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EL
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OW
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SE
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50
0 P
OU
ND
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SE
19
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RP
M W
HE
N T
OR
QU
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ED
3.
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E 1
75
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PM
AT
HIG
HE
R A
LT
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DE
4.
OB
SE
RV
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MO
/ M
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AT
ION
WH
ER
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PP
LIC
AB
LE
PR
OP
RP
M
AIR
SP
EE
D K
NO
TS
95
00
LB
S8
50
0 L
BS
75
00
LB
SIO
AT
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-31
Document No. 13-206CGW Section V – Performance
MA
XIM
UM
CR
UIS
E P
OW
ER
ISA
PR
ES
SU
RE
TO
RQ
UE
FU
EL
F
LO
WT
OT
AL
AL
TIT
UD
EP
ER
E
NG
INE
PE
R
EN
GIN
EF
UE
L
FL
OW
FE
ET
CF
FT
-LB
SL
BS
/HR
LB
S/H
RC
AS
TA
SC
AS
TA
SC
AS
TA
S
190
0S
L19
6613
153
4268
421
42
142
1521
521
62
16
2,0
0015
5913
153
3466
821
22
182
1321
921
42
20
4,0
0012
5413
153
2665
221
02
222
1122
421
22
25
6,0
008
4613
153
2164
220
82
272
0922
821
02
29
8,0
004
3913
153
1663
220
62
312
0723
320
82
34
10,0
000
3213
153
1362
620
32
362
0523
720
62
39
12,0
00-3
2713
153
1162
220
12
402
0324
220
42
43
14,0
00-7
1913
153
1162
219
92
452
0024
720
22
48
16,0
00-1
112
1246
296
592
192
244
194
247
196
249
175
018
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512
642
7855
618
52
421
8724
518
92
48
20,0
00-1
9-2
1181
261
522
177
240
180
244
182
247
22,0
00-2
3-9
1100
245
490
170
238
173
242
175
245
24,0
00-2
7-1
710
232
2945
816
12
341
6523
916
82
43
26,0
00-3
1-2
49
362
1142
215
22
281
5623
516
02
40
28,0
00-3
6-3
38
391
9038
014
02
181
4622
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02
34
29,0
00-3
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67
891
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013
32
111
4022
214
52
30
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TE
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AT
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OR
QU
E A
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EL
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50
0 P
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ND
S2
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SE
19
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RP
M W
HE
N T
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QU
E-L
IMIT
ED
3.
US
E 1
75
0 R
PM
AT
HIG
HE
R A
LT
ITU
DE
4.
OB
SE
RV
E V
MO
/ M
MO L
IMIT
AT
ION
WH
ER
E A
PP
LIC
AB
LE
PR
OP
RP
M
AIR
SP
EE
D K
NO
TS
95
00
LB
S8
50
0 L
BS
75
00
LB
SIO
AT
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-32 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
MA
XIM
UM
CR
UIS
E P
OW
ER
ISA
+1
0° C
PR
ES
SU
RE
TO
RQ
UE
FU
EL
F
LO
WT
OT
AL
AL
TIT
UD
EP
ER
E
NG
INE
PE
R
EN
GIN
EF
UE
L
FL
OW
FE
ET
CF
FT
-LB
SL
BS
/HR
LB
S/H
RC
AS
TA
SC
AS
TA
SC
AS
TA
S
190
0S
L29
8413
153
466
922
132
162
142
182
152
19
2,00
026
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S
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-33
Document No. 13-206CGW Section V – Performance
MA
XIM
UM
CR
UIS
E P
OW
ER
ISA
+2
0° C
PR
ES
SU
RE
TO
RQ
UE
FU
EL
F
LO
WT
OT
AL
AL
TIT
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EP
ER
E
NG
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R
EN
GIN
EF
UE
L
FL
OW
FE
ET
CF
FT
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SL
BS
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LB
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RC
AS
TA
SC
AS
TA
SC
AS
TA
S
1900
SL
3910
213
153
49
698
211
219
213
220
214
221
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0036
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153
41
682
209
223
211
224
212
225
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33
666
207
227
208
229
210
230
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153
27
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205
232
206
233
208
234
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22
644
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236
204
238
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239
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220
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BS
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00
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S
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-34 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
MA
XIM
UM
CR
UIS
E P
OW
ER
ISA
+3
0° C
PR
ES
SU
RE
TO
RQ
UE
FU
EL
F
LO
WT
OT
AL
AL
TIT
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EP
ER
E
NG
INE
PE
R
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GIN
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UE
L
FL
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FE
ET
CF
FT
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SL
BS
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LB
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AS
TA
SC
AS
TA
SC
AS
TA
S
190
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122
131
535
270
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212
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3
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252
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BS
75
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LB
SIO
AT
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-35
Document No. 13-206CGW Section V – Performance
MA
XIM
UM
CR
UIS
E P
OW
ER
ISA
+3
7° C
PR
ES
SU
RE
TO
RQ
UE
FU
EL
F
LO
WT
OT
AL
AL
TIT
UD
EP
ER
E
NG
INE
PE
R
EN
GIN
EF
UE
L
FL
OW
FE
ET
CF
FT
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SL
BS
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LB
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RC
AS
TA
SC
AS
TA
SC
AS
TA
S
190
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BS
75
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S
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-36 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
MAXIMUM CRUISE SPEEDS
TRUE AIRSPEED ~ KNOTS
140 160 180 200 220 240 260
PR
ES
SU
RE
AL
TIT
UD
E ~
FE
ET
0
5000
10000
15000
20000
25000
30000
MAXIMUM CRUISE SPEEDS
ISA
-30°
CIS
AIS
A +
30°
C
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-37
Document No. 13-206CGW Section V – Performance
MAXIMUM CRUISE POWER
INDICATED OUTSIDE AIR TEMPERATURE ~ °C
-80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60
TO
RQ
UE
SE
TT
ING
~ F
T-L
BS
400
500
600
700
800
900
1000
1100
1200
1300
1400
PRESSURE ALTITUDE ~ FT
29,000
28,000
26,000
24,000
22,000
20,000
18,000
16,000
14,000
12,000
10,000
TORQUE LIMIT ~ 1315 FT-LBS
ISA
-30
° C
ISA
-20
° C
ISA
-10
° C
ISA
ISA
+10
° C
ISA
+20
° C
ISA
+30
° C
ISA
+37
° C
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-38 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
FUEL FLOW AT MAXIMUM CRUISE POWER
INDICATED OUTSIDE AIR TEMPERATURE ~ °C
-80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60
FU
EL
FLO
W ~
LB
S /
HR
/ E
NG
INE
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
310
320
330
340
350
360
PRESSURE ALTITUDE ~ FT
29,000
26,000
24,000
22,000
20,000
18,000
16,000
14,000
12,000
10,000
8,000
6,000
4,000
2,000
SL
28,000
ISA
+30
° C
ISA
-20
° C
ISA
-30
° C
ISA
ISA
+20
° C
ISA
-10
° C
ISA
+37
° C
ISA
+10
° C
ISA
-30
° C
ISA
-20
° C
ISA
-10
° C
ISA
ISA
+10
° C
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-39
Document No. 13-206CGW Section V – Performance
C90 / C90-1 / C90A / C90B / C90SE
MAXIMUM RANGE POWER SETTINGS AT
1750 RPM
(LJ-527 and subsequent with PT6A-21 engines)
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-40 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
FE
ET
°C°F
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
SL
-12
10
877
253
506
171
814
244
488
167
749
234
468
164
2,00
0-1
63
841
239
478
170
775
229
458
167
704
218
436
163
4,00
0-2
0-4
801
224
448
170
729
213
426
165
653
201
402
161
6,00
0-2
4-6
767
211
422
169
686
198
396
164
604
186
372
158
8,00
0-2
8-1
875
020
140
217
066
71
8837
616
557
717
43
4815
8
10,0
00-3
2-2
673
919
338
617
265
91
8136
216
757
016
73
3416
0
12,0
00-3
6-3
373
218
637
217
465
31
7434
816
956
516
03
2016
2
14,0
00-4
0-4
071
917
935
817
663
71
6633
217
055
315
23
0416
3
16,0
00-4
4-4
770
617
234
417
762
31
5831
617
153
914
42
8816
4
18,0
00-4
8-5
469
416
633
217
860
91
5130
217
252
513
72
7416
5
20,0
00-5
2-6
268
616
232
418
059
91
4629
217
351
513
12
6216
6
22,0
00-5
6-6
968
415
831
618
259
61
4328
617
550
812
72
5416
7
24,0
00-6
0-7
668
715
731
418
559
71
4028
017
850
612
42
4817
0
26,0
00-6
3-8
170
015
831
619
059
81
3927
818
150
812
22
4417
3
28,0
00-6
7-8
970
115
731
419
261
01
4028
018
551
412
12
4217
6
29,0
00-6
9-9
269
715
631
219
261
91
4128
218
851
812
12
4217
8
M
AX
IMU
M R
AN
GE
PO
WE
R
ISA
-30
°C
WE
IGH
T95
00 P
OU
ND
S85
00 P
OU
ND
S75
00 P
OU
ND
S
1750
RP
M
PR
ES
S
AL
TIT
UD
EIO
AT
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
FU
EL
F
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W
TO
TA
L
FU
EL
FL
OW
P
ER
EN
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TA
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UE
L
FL
OW
T
OT
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TA
ST
OR
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E
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UE
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LO
W
PE
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NG
.
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-41
Document No. 13-206CGW Section V – Performance
FE
ET
°C°F
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
SL
-22
89
0525
951
81
758
4525
050
01
7278
924
14
8216
9
2,0
00-6
21
866
244
488
175
803
234
468
171
746
226
452
168
4,0
00-1
01
48
4723
346
61
767
7722
344
61
7271
221
34
2616
8
6,0
00-1
47
823
222
444
177
750
211
422
173
683
201
402
168
8,0
00-1
80
800
211
422
178
725
200
400
173
655
189
378
168
10,
000
-22
-87
7820
240
41
796
9718
937
81
7362
017
73
5416
7
12,
000
-26
-15
769
194
388
181
682
181
362
174
603
168
336
168
14,
000
-30
-22
760
188
376
183
674
174
348
176
591
161
322
170
16,
000
-34
-29
727
181
362
185
667
168
336
179
583
155
310
172
18,
000
-38
-36
738
175
350
186
658
162
324
181
575
149
298
174
20,
000
-42
-44
730
170
340
188
648
157
314
182
565
143
286
175
22,
000
-45
-49
719
166
332
189
638
152
304
184
556
138
276
177
24,
000
-49
-56
708
162
324
190
633
148
296
186
548
133
266
179
26,
000
-53
-63
711
161
322
193
633
146
292
189
544
130
260
181
28,
000
-57
-71
719
162
324
197
631
145
290
191
543
128
256
183
29,
000
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-74
713
161
322
197
632
144
288
192
546
128
256
185
M
AX
IMU
M R
AN
GE
PO
WE
R
ISA
-2
0°C
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-42 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
FE
ET
°C°F
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
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FT
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846
864
255
510
173
801
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490
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745
236
472
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2,00
04
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780
323
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0
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745
417
673
621
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2
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0-4
2585
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177
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643
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770
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3
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1883
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375
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968
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539
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4
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184
740
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396
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666
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-43
Document No. 13-206CGW Section V – Performance
FE
ET
°C°F
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
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FT
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1864
879
260
520
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246
492
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2,00
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5786
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949
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977
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370
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8
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5085
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177
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1
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377
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5
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8
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366
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39
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378
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693
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608
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306
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567
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359
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729
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7
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558
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8
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065
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9
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264
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-44 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
FE
ET
°C°F
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
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NO
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FT
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2882
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259
518
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795
249
498
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734
239
478
170
2,00
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7586
525
150
218
079
323
947
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671
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1
4,00
020
6887
124
248
418
478
923
046
017
969
521
643
217
2
6,00
016
6186
923
446
818
778
622
144
218
268
920
741
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5
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5485
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444
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568
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8
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3981
320
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274
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438
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866
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3
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3479
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372
418
637
218
965
117
535
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4
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935
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163
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5
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570
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619
361
815
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6
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112
743
178
356
195
687
168
336
194
615
156
312
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22,0
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55
746
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352
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669
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324
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608
151
302
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744
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657
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603
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342
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660
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587
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865
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430
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057
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4
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---
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-65
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5
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-45
Document No. 13-206CGW Section V – Performance
FE
ET
°C°F
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
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BS
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3810
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2,00
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425
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670
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2
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970
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4
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8
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8
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---
---
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666
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314
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592
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284
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29,0
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80
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679
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585
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17
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-46 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
FE
ET
°C°F
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
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4811
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2
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702
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-69
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128
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9
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-47
Document No. 13-206CGW Section V – Performance
FE
ET
°C°F
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
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BS
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5513
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925
350
617
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4
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512
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782
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486
180
710
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6,00
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539
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2
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4
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870
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---
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---
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314
929
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858
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328
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8
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---
---
---
---
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014
328
620
2
29,0
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28--
---
---
---
---
---
---
---
-59
914
428
820
5
1750
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-48 Reference Material: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-49
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-50 FAA-Approved: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
C90 / C90-1 / C90A / C90B / C90SE
DESCENT AND LANDING DATA
(LJ-527 and subsequent with PT6A-21 engines)
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 5-51
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-52 FAA-Approved: Revision A: September 17, 2014
Document No. 13-206CGW Section V – Performance
TIME, FUEL, & DISTANCE TO DESCENDDESCEND SPEED: 169 KNOTS
TIME TO DESCEND ~ MINUTES
0 5 10 15 20
PR
ES
SU
RE
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TIT
UD
E ~
FE
ET
0
5000
10000
15000
20000
25000
30000
TIME, FUEL, & DISTANCE TO DESCENDDESCEND SPEED: 169 KNOTS
FUEL USED TO DESCEND ~ POUNDS
DESCENT DISTANCE ~ NAUTICAL MILES
0 20 40 60
0
80
10 20 30 40 50 60 70 80
EXAMPLE:INITIAL ALTITUDE ...................................FINAL ALTITUDE .................................... TIME TO DESCEND .................................FUEL TO DESCEND ................................DISTANCE TO DESCEND .......................
17,000 FT5651 FT (11.3 - 3.8) = 7.5 MIN(47 - 17) = 30 LBS(37 - 12) = 25 NM
ASSOCIATED CONDITIONS:POWER .....................................
LANDING GEAR ........................FLAPS .......................................PROPELLER SPEED ................
AS REQUIRED TO DESCEND AT1500 FT / MINUPUP1750 RPM
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision B: June 7, 2016 5-53
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-54 FAA-Approved: Revision B: June 7, 2016
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA-Approved: Revision B: June 7, 2016 5-55
Document No. 13-206CGW Section V – Performance
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
5-56 Reference Material: Revision B: June 7, 2016
Document No. 13-206CGW Section V – Performance
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BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
FAA Approved: Revision A: September 17, 2014 6-1
Document No. 13-206CGW Section VI – Weight and Balance
SECTION VI — WEIGHT AND BALANCE (LJ-527 thru LJ-1137, and LJ-1146)
CENTER-OF-GRAVITY LIMITS
CENTER OF GRAVITY ~ INCHES AFT OF DATUM
144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159 160 161
GR
OS
S W
EIG
HT
~ L
BS
7000
7500
8000
8500
9000
9500
10000
10500MAXIMUM TAKEOFF WEIGHT
MAXIMUM LANDING WEIGHT
MAXIMUM ZERO FUEL WEIGHT
NOTE: MAXIMUM RAMP WEIGHT 10,560 LBS
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
6-2 FAA Approved: Revision A: September 17, 2014
Document No. 13-206CGW Section VI – Weight and Balance
SECTION VI — WEIGHT AND BALANCE (LJ-1138 thru LJ-1145, LJ-1147 and after)
CENTER-OF-GRAVITY LIMITS
CENTER OF GRAVITY ~ INCHES AFT OF DATUM
144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159 160 161
GR
OS
S W
EIG
HT
~ L
BS
7000
7500
8000
8500
9000
9500
10000
10500MAXIMUM TAKEOFF WEIGHT
MAXIMUM LANDING WEIGHT
MAXIMUM ZERO FUEL WEIGHT
NOTE: MAXIMUM RAMP WEIGHT 10,560 LBS
BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight
Reference Material: Revision A: September 17, 2014 7-1
Document No. 13-206CGW Section VII – Systems Description
SECTION VII — SYSTEMS DESCRIPTION
HARTZELL/RAISBECK SWEPT BLADE TURBOFAN PROPELLER SYSTEM
Each engine is equipped with an advanced technology, lightweight, Hartzell/Raisbeck Swept Blade Turbofan propeller. Each propeller contains four blades, in full feathering, constant speed, counter-weighted, reversing, variable-pitch, and mounted on the output shaft of the reduction gearbox. The propeller pitch and speed are controlled by engine oil pressure, through single action engine-driven propeller governors. Centrifugal counter-weights, assisted by a feathering spring, move the blades toward the low RPM (high pitch) position and into the feathered position. Governor boosted engine oil pressure moves the propeller to the high RPM (low pitch) hydraulic stop and reverse position. The propellers have no low RPM (high pitch) stops; this allows the blades to feather after engine shut-down.
OPTIONAL 1,600 RPM MINIMUM CRUISE
For those wishing the absolute quietest cockpit and cabin in cruise, propeller cruise RPM as low as 1,600 RPM is available as an option. Resetting the propeller governor to Raisbeck specifications per Raisbeck Maintenance Manual (85-120) is required.
DUAL AFT BODY STRAKES The Raisbeck Dual Aft Body Strakes are mounted on the underside of the aft fuselage, and replace the single ventral fin. They are designed and engineered to attach and streamline the airflow over the aft body reducing drag, improving aircraft stability and VMC.
PROPELLER DE-ICE SYSTEM
The Hartzell propeller electric de-ice system includes an electronically heated boot for each propeller blade, brush assemblies, slip rings, an ammeter, a timer for automatic operation, and a manual control circuit for backup. The de-ice ammeter indicates the system amperage (normally 18 to 24 amperes). The timer directs current to the single-element boot on each blade in the following sequence: right propeller all elements; then left propeller all elements. Loss of one heating element circuit on one side does not mean that the entire system must be turned off. The timer switches every 90 seconds resulting in a complete cycle in approximately 3 minutes.