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)
71
Embed
KING AIR MODEL C90/C90A - aso.com · AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECHCRAFT KING AIR MODELS C90/C90A Equipped with Raisbeck Engineering: Swept Blade Turbofan Propellers
This document is posted to help you gain knowledge. Please leave a comment to let me know what you think about it! Share it to your friends and learn new things together.
Transcript
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
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:
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
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.
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
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
5-6 FAA-Approved: Revision A: September 17, 2014
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
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
LO
W
TO
TA
L
FU
EL
FL
OW
P
ER
EN
G.
TA
SF
UE
L
FL
OW
T
OT
AL
TA
ST
OR
QU
E
PE
R E
NG
.F
UE
L F
LO
W
PE
R E
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
-59
-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
WE
IGH
T95
00 P
OU
ND
S85
00 P
OU
ND
S7
500
PO
UN
DS
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
LO
W
TO
TA
LT
AS
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
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
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
SL
846
864
255
510
173
801
245
490
170
745
236
472
167
2,00
04
3986
924
749
417
780
323
747
417
374
522
845
617
0
4,00
00
3286
623
747
418
079
922
745
417
673
621
843
617
2
6,00
0-4
2585
022
745
418
177
421
643
217
770
720
541
017
3
8,00
0-8
1883
321
743
418
375
920
641
217
968
519
539
017
4
10,0
00-1
210
813
209
418
184
740
198
396
180
666
186
372
175
12,0
00-1
63
794
200
400
185
724
189
378
181
649
178
356
176
14,0
00-2
0-4
775
192
384
187
709
181
362
183
630
169
338
177
16,0
00-2
4-1
175
918
537
018
869
717
535
018
561
616
232
417
8
18,0
00-2
7-1
774
017
835
618
968
716
833
618
760
615
531
018
0
20,0
00-3
1-2
472
117
134
218
967
416
232
418
859
815
030
018
3
22,0
00-3
5-3
172
016
833
619
165
815
731
418
959
114
529
018
5
24,0
00-3
9-3
872
516
733
419
564
115
130
218
958
314
128
218
7
26,0
00-4
3-4
572
116
533
019
663
614
829
619
157
513
727
418
8
28,0
00-4
7-5
372
616
533
019
964
514
829
619
556
313
326
618
9
29,0
00-4
9-5
672
916
633
220
164
414
829
619
655
813
126
218
9
17
50 R
PM
TA
S
M
AX
IMU
M R
AN
GE
PO
WE
R
ISA
-1
0°C
WE
IGH
T95
00 P
OU
ND
S8
500
PO
UN
DS
7500
PO
UN
DS
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
LO
W
TO
TA
L
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
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 5-43
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
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
SL
1864
879
260
520
176
788
246
492
171
717
235
470
166
2,00
014
5786
724
949
817
977
623
547
017
370
722
444
816
8
4,00
010
5085
923
947
818
177
322
645
217
670
421
543
017
1
6,00
06
4384
622
945
818
377
321
843
617
970
620
741
417
5
8,00
02
3682
621
843
618
476
720
941
818
170
219
939
817
8
10,0
00-2
2880
520
841
618
575
020
040
018
369
219
138
218
0
12,0
00-6
2178
519
939
818
672
919
038
018
466
918
136
218
0
14,0
00-1
014
775
193
386
189
709
183
366
185
655
174
348
182
16,0
00-1
39
772
189
378
191
693
176
352
186
638
167
334
183
18,0
00-1
71
767
183
366
194
679
169
338
187
621
159
318
185
20,0
00-2
1-6
756
178
356
195
673
164
328
190
608
153
306
186
22,0
00-2
5-1
373
217
134
219
567
016
032
019
359
414
729
418
7
24,0
00-2
9-2
072
016
833
619
566
415
631
219
558
014
228
418
8
26,0
00-3
3-2
773
316
933
820
065
115
230
419
556
913
727
418
9
28,0
00-3
7-3
573
316
933
820
264
315
030
019
657
113
527
019
2
29,0
00-3
9-3
874
017
034
020
465
115
130
219
957
413
527
019
4
17
50 R
PM
TA
S
M
AX
IMU
M R
AN
GE
PO
WE
R
ISA
WE
IGH
T95
00 P
OU
ND
S8
500
PO
UN
DS
7500
PO
UN
DS
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
LO
W
TO
TA
L
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
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
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
SL
2882
861
259
518
177
795
249
498
173
734
239
478
170
2,00
024
7586
525
150
218
079
323
947
817
671
922
845
617
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
417
5
8,00
012
5485
222
444
818
977
721
342
618
568
519
939
817
8
10,0
008
4683
521
543
019
176
120
340
618
668
019
138
218
0
12,0
004
3981
320
641
219
274
219
438
818
866
918
336
618
3
14,0
001
3479
619
839
619
372
418
637
218
965
117
535
018
4
16,0
00-3
2777
819
038
019
471
017
935
819
163
416
733
418
5
18,0
00-7
1975
918
336
619
570
117
334
619
361
815
931
818
6
20,0
00-1
112
743
178
356
195
687
168
336
194
615
156
312
189
22,0
00-1
55
746
176
352
198
669
162
324
194
608
151
302
191
24,0
00-1
9-2
744
174
348
201
657
157
314
195
603
147
294
194
26,0
00-2
3-9
734
171
342
201
660
156
312
198
587
142
284
194
28,0
00-2
7-1
775
817
535
020
865
915
430
820
057
313
727
419
4
29,0
00-2
9-2
0--
---
---
---
-65
415
330
620
057
113
627
219
5
17
50 R
PM
TA
S
M
AX
IMU
M R
AN
GE
PO
WE
R
ISA
+1
0°C
WE
IGH
T95
00 P
OU
ND
S8
500
PO
UN
DS
7500
PO
UN
DS
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
LO
W
TO
TA
L
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
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 5-45
Document No. 13-206CGW Section V – Performance
FE
ET
°C°F
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
SL
3810
087
626
452
818
077
224
849
617
371
923
947
817
0
2,00
034
9386
425
350
618
276
923
847
617
670
822
845
617
2
4,00
030
8685
824
348
618
576
922
945
817
970
021
843
617
4
6,00
026
7984
923
446
818
777
422
244
418
370
021
042
017
8
8,00
022
7283
622
444
818
977
421
442
818
669
520
240
418
1
10,0
0018
6481
821
442
819
176
420
641
218
969
719
539
018
4
12,0
0015
5979
720
541
019
274
519
639
219
068
518
737
418
6
14,0
0011
5278
319
739
419
372
718
837
619
167
017
935
818
8
16,0
007
4577
819
238
419
670
918
036
019
265
617
134
319
0
18,0
003
3778
018
737
419
969
317
334
619
363
916
432
819
1
20,0
00-1
3077
218
336
620
168
216
733
419
562
315
731
419
2
22,0
00-5
2375
117
735
420
168
316
432
819
860
915
130
219
3
24,0
00-9
1673
617
434
820
168
016
232
420
059
414
629
219
4
26,0
00-1
39
764
178
356
208
656
156
312
199
591
144
288
196
28,0
00-1
71
---
---
---
---
666
157
314
203
592
142
284
200
29,0
00-1
80
---
---
---
---
679
160
320
207
585
140
280
200
17
50 R
PM
TA
S
M
AX
IMU
M R
AN
GE
PO
WE
R
ISA
+2
0°C
WE
IGH
T95
00 P
OU
ND
S8
500
PO
UN
DS
7500
PO
UN
DS
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
LO
W
TO
TA
L
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
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
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
SL
4811
887
226
553
018
179
325
250
417
672
424
148
217
2
2,00
044
111
888
258
516
186
793
244
488
180
702
229
458
173
4,00
040
104
894
250
590
190
793
235
470
183
681
218
436
174
6,00
036
9788
424
148
219
278
922
645
218
667
720
941
817
7
8,00
032
9086
523
046
019
478
321
843
618
967
920
240
418
1
10,0
0029
8485
022
144
219
676
720
841
619
168
219
539
018
4
12,0
0025
7783
321
242
419
874
919
939
819
267
418
737
418
7
14,0
0021
7081
320
440
819
973
519
138
219
465
917
935
818
9
16,0
0017
6378
919
539
019
972
618
537
019
664
317
134
219
0
18,0
0013
5576
718
737
419
971
917
835
619
962
816
432
819
1
20,0
009
4874
718
036
019
970
517
234
420
061
915
831
619
3
22,0
005
4174
717
835
620
168
516
633
220
062
115
430
819
7
24,0
001
3476
918
036
020
866
616
032
019
961
715
030
020
0
26,0
00-3
2779
118
336
621
466
715
831
620
260
114
529
020
0
28,0
00-6
21--
---
---
---
-69
216
332
621
058
314
128
219
9
29,0
00--
---
---
---
---
---
---
---
---
---
-58
114
028
020
0
17
50 R
PM
TA
S
M
AX
IMU
M R
AN
GE
PO
WE
R
ISA
+3
0°C
WE
IGH
T95
00 P
OU
ND
S8
500
PO
UN
DS
7500
PO
UN
DS
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
LO
W
TO
TA
L
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
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 5-47
Document No. 13-206CGW Section V – Performance
FE
ET
°C°F
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
FT
-LB
SL
BS
/HR
LB
S/H
RK
NO
TS
SL
5513
185
826
553
018
178
925
350
617
772
624
248
417
4
2,00
051
124
861
256
512
185
782
243
486
180
710
231
462
175
4,00
047
117
873
249
498
189
793
236
472
184
704
222
444
178
6,00
043
109
876
241
482
193
799
229
458
188
700
214
428
181
8,00
040
104
861
231
462
195
793
220
440
191
701
206
412
184
10,0
0036
9784
322
144
219
678
521
242
419
470
520
040
018
8
12,0
0032
9081
421
142
219
776
920
340
619
669
119
138
219
0
14,0
0028
8278
520
140
219
675
119
539
019
767
618
336
619
2
16,0
0024
7576
819
438
819
772
918
637
219
866
317
635
219
4
18,0
0020
6875
618
737
419
870
117
735
419
765
116
933
819
6
20,0
0016
6176
418
537
020
268
017
034
019
764
316
332
619
8
22,0
0012
5477
618
436
820
767
016
533
019
862
515
631
219
9
24,0
008
46--
---
---
---
-67
416
332
620
260
314
929
819
8
26,0
005
41--
---
---
---
-69
116
432
820
858
414
328
619
8
28,0
000
32--
---
---
---
---
---
---
---
-59
014
328
620
2
29,0
00-2
28--
---
---
---
---
---
---
---
-59
914
428
820
5
1750
RP
M
TA
S
M
AX
IMU
M R
AN
GE
PO
WE
R
ISA
+37
°C
WE
IGH
T95
00 P
OU
ND
S8
500
PO
UN
DS
7500
PO
UN
DS
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
LO
W
TO
TA
L
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
FU
EL
F
LO
W
TO
TA
LT
AS
TO
RQ
UE
P
ER
EN
G.
FU
EL
FL
OW
P
ER
EN
G.
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
AL
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 .......................
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.