KING AIR MODEL C90/C90A

Transcription

1 PILOT S OPERATING HANDBOOK and FAA-Approved Airplane Flight Manual Supplement for the KING AIR MODEL C90/C90A Equipped with Raisbeck Engineering: - STC SA3593NM - STC SA4010NM - 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) Revision B: June 7, 2016

2 PILOT S OPERATING HANDBOOK AND FAA-APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECHCRAFT KING AIR MODELS C90/C90A Equipped with Raisbeck Engineering: - STC SA3593NM - STC SA4010NM - 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 FAA-Approved: Revision B: June 7, 2016 i

3 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, , 6-1, , 6-2 B Title, i, ii, , thru 5-14, Changed propeller feather blade angle from 84.5 to Removed redundant reference to SL-08-BC-1. Expanded in-flight aft CG limit. Removed reference propeller weight and moment arm. 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 ii FAA-Approved: Revision B: June 7, 2016

4 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 FAA-Approved: Revision A: September 17, 2014 iii

5 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 South Ryan Way Seattle, Washington U.S Intl FAX (206) For current revision status visit 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: Propeller Type: Maximum: Minimum: 96 inches 95 inches Constant-speed, Full-feathering, Reversing, Counter-weighted, Hydraulically Actuated consisting of D9510SK blades and HC-D4N-3C hubs. Pitch Range (30-inch station): Reverse: ± 0.5 Feathered: ± 0.5 FAA-Approved: Revision B: June 7,

6 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 N 1 PROP OIL OIL OBSERVED RPM PRESS TEMP FT LBS (1) ITT C RPM % N 2 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 , to to 99 CRUISE CLIMB AND MAX CRUISE (6) , to to 99 MAX REVERSE (7) to to 99 TRANSIENT 1500 (4) 825 (4)(8) 38, to 99 (1) Maximum permissible sustained torque is 1315 ft/lbs. Propeller speeds (N 2 ) must be set so at not to exceed power limitation. (2) When gas generator speeds are above 72% N 1 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 N 1 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 N 1 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: Minimum diameter: 96.0 inches 95.0 inches PROPELLER BLADE ANGLES AT 30-INCH STATION Reverse: ± 0.5 Feathered: ± 0.5 FAA-Approved: Revision A: September 17,

7 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 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 V MCA with one-engine inoperative, thrust lever at idle, and propeller windmilling is 99 KIAS (101 KCAS). AIRSPEED LIMITATIONS Air Minimum Control Speed, V MCA KCAS (93 KIAS) Maximum Operating Speed, V MO, above 9,650 lbs (LJ-1063 thru LJ-1137, and LJ-1146) KCAS (208 KIAS) 2-2 FAA-Approved: Revision B: June 7, 2016

8 Section II - Limitations AIRSPEED INDICATOR MARKINGS C90/C90-1 (LJ-502 thru LJ-1062) Red Radial (Air Minimum Control Speed, V MCA ) KCAS C90A/C90B/C90SE (LJ-1063 thru LJ-1726, LJ-1728 thru LJ-1753, LJ-1755) Red Radial (Air Minimum Control Speed, V MCA ) KIAS (LJ-1063 thru LJ-1137, and LJ-1146 only) Red Line KIAS* Red and White Hash-Marked Pointer 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 installed) Two (2) placards have been installed, one above each Primary Flight Display unit, to notify the pilot to disregard the V MC RED LINE displayed on the airspeed tape. DISREGARD V MC MARKING V MC = 93 KIAS 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. FAA-Approved: Revision B: June 7,

9 Section II - Limitations CENTER OF GRAVITY LIMITS (LANDING GEAR EXTENDED) Aft Limit inches aft of Datum at all weights (LJ-527 thru LJ-1137, and LJ-1146) Forward Limit at: 10,500 lbs inches aft of Datum 10,350 lbs inches aft of Datum 10,100 lbs inches aft of Datum 9,700 lbs inches aft of Datum 9,168 lbs inches aft of Datum 7,400 lbs or less inches aft of Datum (LJ-1138 thru LJ-1145, LJ-1147 and after) Forward Limit at: 10,500 lbs * inches aft of Datum 10,350 lbs inches aft of Datum 10,100 lbs inches aft of Datum 7,850 lbs or less 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 2-4 FAA-Approved: Revision B: June 7, 2016

10 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 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. FAA-Approved: Revision A: September 17,

11 Section IV Normal Procedures SECTION IV NORMAL PROCEDURES AFTER STARTING ENGINES ICING FLIGHT LANDING 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. 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. 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 V MCA is 99 KIAS (101 KCAS). Dynamic throttle cuts should only be attempted at airspeeds above 104 KIAS (105 KCAS). FAA-Approved: Revision A: September 17,

12 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. 4-2 FAA-Approved: Revision B: June 7, 2016

13 SECTION V PERFORMANCE TABLE OF CONTENTS INTRODUCTION Introduction TAKEOFF AND CLIMB DATA Stall Speeds - Zero Thrust Minimum Takeoff Power at 2200 RPM Maximum Takeoff Weight to Achieve Positive One Engine Inoperative Climb at Lift-off Maximum Allowable TOGW above 10,350 LBS Takeoff Distance Flaps Up Two Engines Accelerate-Stop Distance Flaps Up Accelerate-Go Distance Flaps Up Takeoff Climb Gradient One-Engine-Inoperative Enroute Climb All Engines Operating Enroute Climb One Engine Inoperative Service Ceiling One Engine Inoperative Time, Fuel and Distance to Cruise Climb CRUISE DATA Normal Cruise Power Setting Tables: ISA -30 C ISA -20 C ISA -10 C ISA ISA +10 C ISA +20 C ISA +30 C ISA +37 C Normal Cruise Power Setting Graphs: Normal Cruise Speeds Normal Cruise Power Fuel Flow at Normal Cruise Power Maximum Cruise Power Setting Tables: ISA -30 C ISA -20 C ISA -10 C ISA ISA +10 C ISA +20 C ISA +30 C ISA +37 C Maximum Cruise Power Setting Graphs: Maximum Cruise Speeds Maximum Cruise Power Fuel Flow at Maximum Cruise Power FAA-Approved: Revision B: June 7,

14 Maximum Range Power Setting Tables: ISA -30 C ISA -20 C ISA -10 C ISA ISA +10 C ISA +20 C ISA +30 C ISA +37 C Range with 384 Gallons Usable Fuel Endurance with 384 Gallons Usable Fuel DESCENT AND LANDING DATA Holding Time Time, Fuel, and Distance to Descend Maximum Landing Weight Flaps Down Climb Balked Landing Landing Distance Without Propeller Reversing Landing Distance With Propeller Reversing 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, acceleratestop, 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). 5-2 FAA-Approved: Revision B: June 7, 2016

15 FAA-Approved: Revision A: September 17,

16 MINIMUM TAKE-OFF POWER AT 2200 RPM (70 KNOTS) NOTE: THE POWER (TORQUE) INDICATED IS THE MINIMUM VALUE FOR WHICH TAKE-OFF PERFORMANCE CAN BE OBTAINED. EXCESS POWER WHICH CAN BE DEVELOPED WITHOUT EXCEEDING ENGINE LIMITATIONS MAY BE UTILIZED. EXAMPLE: OAT AT TAKE-OFF... AIRPORT PRESSURE ALTITUDE... MINIMUM TAKE-OFF POWER C 3966 FT 1105 FT-LBS TORQUE LIMIT: 1315 FT-LBS 1300 MINIMUM TORQUE SETTING (2200 RPM) ~ FT-LBS , SL PRESSURE ALTITUDE ~ FEET ISA + 37 C OUTSIDE AIR TEMPERATURE ~ DEGREES C 5-4 FAA-Approved: Revision A: September 17, 2014

17 FAA-Approved: Revision B: June 7,

18 MAX ALLOWABLE TAKE-OFF GROSS WEIGHT ABOVE 10,350 LBS IN ORDER TO ACHIEVE PART 25 APPROACH CLIMB & LANDING REQUIREMENTS EXAMPLE: OAT C AIRPORT PRESSURE ALTITUDE... 4,000 FT MAX ALLOWABLE T.O.G.W ,470 LBS PRESSURE ALTITUDE ~ FEET 8,000 FT 6,000 FT 4,000 FT 2,000 FT SEA LEVEL MAX ALLOWABLE T.O.G.W. ~ LBS OUTSIDE AIR TEMPERATURE ~ DEGREES C 5-6 FAA-Approved: Revision A: September 17, 2014

19 FAA-Approved: Revision B: June 7,

20 5-8 Reference Material: Revision B: June 7, 2016

21 FAA-Approved: Revision B: June 7,

22 5-10 FAA-Approved: Revision B: June 7, 2016

23 FAA-Approved: Revision B: June 7,

24 5-12 FAA-Approved: Revision B: June 7, 2016

25 Reference Material: Revision B: June 7,

26 5-14 Reference Material: Revision B: June 7, 2016

27 C90 / C90-1 / C90A / C90B / C90SE NORMAL CRUISE POWER SETTINGS (LJ-527 and subsequent with PT6A-21 engines) Reference Material: Revision A: September 17,

28 NORMAL CRUISE POWER ISA -30 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

29 NORMAL CRUISE POWER ISA -20 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

30 NORMAL CRUISE POWER ISA -10 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

31 NORMAL CRUISE POWER ISA NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

32 NORMAL CRUISE POWER ISA +10 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

33 NORMAL CRUISE POWER ISA +20 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

34 NORMAL CRUISE POWER ISA +30 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

35 NORMAL CRUISE POWER ISA +37 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1750 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

36 NORMAL CRUISE SPEEDS WEIGHT 8500 LBS ISA PRESSURE ALTITUDE ~ FEET ISA -30 C ISA +30 C TRUE AIRSPEED ~ KNOTS 5-24 Reference Material: Revision A: September 17, 2014

37 NORMAL CRUISE POWER 1400 TORQUE LIMIT ~ 1315 FT-LBS ,000 4, ,000 8, ,000 12,000 TORQUE SETTING ~ FT-LBS ,000 16,000 18,000 20,000 22,000 PRESSURE ALTITUDE ~ FT ISA -30 C ISA -20 C ISA -10 C ISA ISA +10 C ISA +20 C ISA +30 C ISA +37 C 24,000 26,000 28,000 29, INDICATED OUTSIDE AIR TEMPERATURE ~ C Reference Material: Revision A: September 17,

38 AT NORMAL CRUISE POWER ISA ISA +10 C ISA +20 C ISA +30 C ISA +37 C 320 SL ISA -30 C ISA -20 C ISA -10 C 4,000 2, , ,000 ~ LBS / HR / ENGINE ,000 12,000 10, , , , , ,000 PRESSURE ALTITUDE ~ FT , , , INDICATED OUTSIDE AIR TEMPERATURE ~ C 5-26 Reference Material: Revision A: September 17, 2014

39 C90 / C90-1 / C90A / C90B / C90SE MAXIMUM CRUISE POWER SETTINGS (LJ-527 and subsequent with PT6A-21 engines) Reference Material: Revision A: September 17,

40 MAXIMUM CRUISE POWER ISA -30 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

41 MAXIMUM CRUISE POWER ISA -20 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

42 MAXIMUM CRUISE POWER ISA -10 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

43 MAXIMUM CRUISE POWER ISA NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

44 MAXIMUM CRUISE POWER ISA +10 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

45 MAXIMUM CRUISE POWER ISA +20 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

46 MAXIMUM CRUISE POWER ISA +30 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

47 MAXIMUM CRUISE POWER ISA +37 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL , , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

48 MAXIMUM CRUISE SPEEDS PRESSURE ALTITUDE ~ FEET ISA ISA -30 C ISA +30 C TRUE AIRSPEED ~ KNOTS 5-36 Reference Material: Revision A: September 17, 2014

49 MAXIMUM CRUISE POWER 1400 TORQUE LIMIT ~ 1315 FT-LBS , , ,000 16,000 TORQUE SETTING ~ FT-LBS ,000 PRESSURE ALTITUDE ~ FT 22,000 24,000 18, ISA -30 C ISA -20 C ISA -10 C ISA ISA +10 C ISA +20 C ISA +30 C ISA +37 C 28,000 29,000 26, INDICATED OUTSIDE AIR TEMPERATURE ~ C Reference Material: Revision A: September 17,

50 AT MAXIMUM CRUISE POWER ~ LBS / HR / ENGINE ISA -30 C ISA -20 C ISA -10 C ISA ISA +10 C 28,000 29,000 26,000 24,000 ISA -30 C ISA -20 C ISA +20 C ISA -10 C 16,000 18,000 22,000 10,000 12,000 14,000 2,000 4,000 6,000 8,000 PRESSURE ALTITUDE ~ FT 20,000 ISA +30 C ISA ISA +37 C ISA +10 C SL INDICATED OUTSIDE AIR TEMPERATURE ~ C 5-38 Reference Material: Revision A: September 17, 2014

51 C90 / C90-1 / C90A / C90B / C90SE MAXIMUM RANGE POWER SETTINGS AT 1750 RPM (LJ-527 and subsequent with PT6A-21 engines) Reference Material: Revision A: September 17,

52 MAXIMUM RANGE POWER 1750 RPM ISA -30 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL TAS TORQUE TAS 2, , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

53 MAXIMUM RANGE POWER 1750 RPM ISA -20 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL TAS TORQUE TAS 2, , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

54 MAXIMUM RANGE POWER 1750 RPM ISA -10 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL TAS TORQUE TAS 2, , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

55 MAXIMUM RANGE POWER 1750 RPM ISA WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL TAS TORQUE TAS 2, , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

56 MAXIMUM RANGE POWER 1750 RPM ISA +10 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL TAS TORQUE TAS 2, , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

57 MAXIMUM RANGE POWER 1750 RPM ISA +20 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL TAS TORQUE TAS 2, , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

58 MAXIMUM RANGE POWER 1750 RPM ISA +30 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL TAS TORQUE TAS 2, , , , , , , , , , , , , , , Reference Material: Revision A: September 17, 2014

59 MAXIMUM RANGE POWER 1750 RPM ISA +37 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL TAS TORQUE TAS 2, , , , , , , , , , , , , , , Reference Material: Revision A: September 17,

60 5-48 Reference Material: Revision A: September 17, 2014

61 Reference Material: Revision A: September 17,

62 C90 / C90-1 / C90A / C90B / C90SE DESCENT AND LANDING DATA (LJ-527 and subsequent with PT6A-21 engines) 5-50 FAA-Approved: Revision A: September 17, 2014

63 Reference Material: Revision A: September 17,

64 TIME,, & DISTANCE TO DESCEND DESCEND SPEED: 169 KNOTS ASSOCIATED CONDITIONS: POWER... LANDING GEAR... FLAPS... PROPELLER SPEED... AS REQUIRED TO DESCEND AT 1500 FT / MIN UP UP 1750 RPM EXAMPLE: INITIAL ALTITUDE... FINAL ALTITUDE... TIME TO DESCEND... TO DESCEND... DISTANCE TO DESCEND... 17,000 FT 5651 FT ( ) = 7.5 MIN (47-17) = 30 LBS (37-12) = 25 NM PRESSURE ALTITUDE ~ FEET TIME TO DESCEND ~ MINUTES USED TO DESCEND ~ POUNDS DESCENT DISTANCE ~ NAUTICAL MILES 5-52 FAA-Approved: Revision A: September 17, 2014

65 Reference Material: Revision B: June 7,

66 5-54 FAA-Approved: Revision B: June 7, 2016