Airplane Flight Manual

Original Revised Revised Revised Revised Added Revised Added Revised Revised Revised Revised Revised Revised Revised Added Original Revised Revised Revised Revised Revised Revised Added Revised Added Revised Revised Revised Revised Added Added Revision Number 5 3 5 6 6 0 5 0 5 6 5 6 6 6 6 5 6 5 6 5 6 5 5 0 6 6 4 3 5 6 6 6 6 6 5 6 5 5 6 AA AA AA AA AA AA AH AI AH AI AA AA AA AA AA AA Iiv U.S. Configuration AA TEMPORARY CHANGES MODEL 510 FAA Approved U.S. Airplane Flight Manual Model 510 Citation Mustang Airplanes 510-0001 and On THIS IS A LIST OF ALL CURRENT FAA APPROVED TEMPORARY CHANGES. The following list of temporary changes must be incorporated into this basic FAA Approved Airplane Flight Manual untilthe removal instructions have been complied with. Insert this page opposite the Log of Effective Pages in the front of this basic FAA Approved Airplane Flight Manual. TEMPORARY CHANGE NUMBER PAGE NUMBER ISSUE DATE SERVICE BULLETIN (IF APPLICABLE) OR SERIAL EFFECTIVITY 51oFM TC-R06-01 2-29 04/30/08 Airplanes 510-0001 thru -0065 incorporating SB51 0-34-02 and Airplanes 510-0066 and On. 51oFM TC-R06-02 3-90 5t29t0B Airplanes 510-0001 and On. 510FM TC-R06-03 2-29 5/8/08 Airplanes 510-0001 and On not incorporating SL51 0-34-04. 29 May 2008 51OFM U.S. MODEL 5{O SECTION I . INTRODUCTION INTRODUCTION The information in this publication is based on data available at the time of publication and is updated, supplemented, and automatically amended by Service Letters, Service Bulletins, Supplier Service Notices, Publications Changes, Revisions, Reissues, Temporary Revisions, and Temporary Changes, that are issued through subscriptions service available from Citation Service Information. All such amendments become parts of, and are specifically incorporated within this publication. Users are urged to stay current with the latest amendments to this publication through Citation Service Information subscription services and/or Citation Service Centers and Citation Service Stations. COVERAGE The Flight Manual, including supplements in the airplane at the time of delivery from Cessna Aircraft Company contains information applicable only to that particular airplane. The basic manual is applicable to airplane serial 510-0001 thru -0004 incorporating SL510-99-01 and 510-0005 and On. UNIT AND SERIAL NUMBER On all Citation Model 510 airplanes, both the serial and unit numbers are stamped into the airplane identification nameplate. This manual uses serial numbers to describe airplane effectivity. FLIGHT MANUAL PART NUMBER Each page in the basic FAA Approved Airplane Flight Manual contains the part number of the manual and the page status of each page. Refer to the following example: Basic FAA Approved Airplane Flight Manual: 510 FM - 06 lr_ Page Status (Revision 6) Manual (Flight Manual) Airplane Model (510) FAA Approved Airplane Flight Manual Supplements: 510 FM - S02 - 01 1-3 NOTICE SUPPLEMENTS IN SECTION V OF THIS FL]GHT MANUAL CONTAIN AMEND NG LIMITATIONS. OPERATING PROCEDURES. PERFORMANCE DATA. R NECESSARY INFORMATION FOR AIRPLANES CONDUCTING OPERATIONS AND FOR AIRPLANES EQUIPPED WITH SPECIFIC OPTIONS. OPERATORS SHOULD REFER TO SECTION V TO MAKE SURE THAT ALL LIMITATIO AND PROCEDURES APPROPRIATE FOR THEIR AIRPLANE ARE OBSERVED. | | l- Page Status (Revision 1) I l- Supplement Number (Supplement 2) l- Manual (Flight Manual) Airplane Model (510) FAAAPPROVED 510FM-06 Configuration AA U.S. SECTION I . INTRODUCTION MODEL 510 REVISIONS As new information becomes available for your airplane, revisions will be issued to all registered owners. lt is the pilot's responsibility to make sure that this FAA Approved Airplane Flight Manual is complete and current at all times. REVISED MATERIAL INDICATORS A bar will extend the full length of deleted, new or revised text added on new or previously existing pages. This bar will be located adjacent to the applicable text in the margin on the left side of the page. A bar in the footer will indicate a revision to the footer, a new page, format or spelling/grammar changes and/or that information has slipped to or from that page. A bar located adjacent to tne figure number in the margin on the left side of the page will be used to indicate that the figure number only has changed. An asterisk located at the end of a figure number will be used to indicate that an illustration has been revised or is all new material (Ex: Figure 3-4*). All revised pages will carry the revision number opposite the page number on the applicable page. A list of revisions is located at the beginning of the Log of Effective Pages. SYMBOLS USED FOR PROCEDURE DIVISION Symbgls are used to mark different parts of procedures. A decision must be made by the pilot to identify the applicable part of the procedure. After the initial choice has been made, a further division of the procedure is possible. In that case, a second choice must be made, etc. When a choice has been made, all remaining actions, consequences, and references are listed. When the procedure is no longer required, this will be indicated by "Procedure Completed". The division symbols are identified as follows: I First Division O Second Division Elrniro Division O Fourth Division DEFINITIONS Performance definitions are available in Section lV; the remaining definitions are listed as follows: WARNING OPERATING PROCEDURES, TECHNIQUES, ETC., THAT WILL RESULT IN PERSONAL INJURY OR LOSS OF LIFE IF NOT CAREFULLY FOLLOWED. CAUTION OPERATING PROCEDURES, TECHNIQUES, ETC., THAT WILL RESULT IN DAMAGE TO EQUIPMENT IF NOT CAREFULLY FOLLOWED. (Continued Next Page) U.S. Configuration AA FAA APPROVED 510FM-00 14 MODEL 510 DEFI N ITIONS (continued) SECNON I.INTRODUCTION NOTE An operating procedure, technique, etc., that is considered essentialto emphasize. LAND AS SOON AS POSSIBLE Land at the nearest suitable airport. Unless reference to alternate Abnormal Before Landing procedures is made, use of Normal Approach and Before Landing procedures is assumed. Extreme situations can require an off airport landing. Primary consideration is safety of occupants. LAND AS SOON AS PRACTICAL Land at a suitable airport. Unless reference to alternate Abnormal Before Landing procedures is made, use of Normal Approach and Before Landing procedures is assumed. The primary consideration is the urgency of the emergency or abnormal situation. Continuing to the destination or an alternate with appropriate service facilities may be an option. EMERGENGY PROCEDURES An emergency procedure is one requiring the use of special systems and/or regular systems in order to protect the occupants and the airplane from serious or critical harm. These procedures usually require immediate action. ABNORMAL PROCEDURES An abnormal procedure is one requiring the use of special systems and/or the alternate use of regular systems that, if followed, will maintain an acceptable level of airworthiness or reduce operational risk resulting from a failure condition. NORMAL PROCEDURES A normal procedure is one that may be thought of as routine in day-to-day flying. CIRCUIT BREAKERS CHECK Make sure the circuit breaker has remained in the normal position or, if it has opened the circuit, push back in to the normal position. RESET Place the circuit breaker in the normal position. lf the circuit breaker is currently normal, pull to open the circuit then push to reset. FAAAPPROVED 510FM-06 1-5 Configuration AA u.s. SECTION I . INTRODUCTION MODEL 510 SERVICE BULLETIN CONFIGURATION LIST The following is a list of Service Bulletins that are applicable to the operation of the airplane, and have been incorporated into this manual. This list contains only those Service Bulletins that are currently active. Number Title Airplane Serial Effectivity 58510-03-01 Certification Requirements - 510-0001 thru -0020 FAA to EASA Registration Gonversion 58510-34-02 Garmin c1000 2008 Q1 510-0001 thru -0065 Software/Hardware u pdate Revision Incorporated Incorporated in Airolane 4 6 1-6 FAA APPROVED 510FM-06 U.S. Configuration AA MODEL 510 SECTION I . INTRODUCTION AIRPLANE CONFIGURATION GODES The following is a list of airplane configuration codes that appear at the bottom of each page of the basic FAA Approved Airplane Flight Manual and indicate page effectivity by serial number. This list contains only the configurations that have been incorporated into the basic FAA Approved Airplane Flight Manual. From each grouping, identify and record the configuration code that applies to your airplane, then select and insert the correct pages into this FAA Approved Airplane Flight Manual. Configuration Code Effectivity by Serial Number Applicable Configuration Code AA Airplanes 510-0001 and On AB AC Airplanes 510-0001 and On with NiCad battery option Airplanes 510-0001 and On without NiCad battery option AD AE Airplanes 510-0001 thru -0020 incorporating SB510-03-01 (Certification Requirements - FAA to EASA Registration Conversion) and airplanes 510-0021 and On Airplanes 510-0001 thru -0020 not incorporating S8510-03-01 (Certification Requirements - FAA to EASA Registration Conversion) AF AG Airplanes 510-0041 and On (Airplanes with Multi-Function Change and Cabin Altitude Module lmprovement) Airplanes 510-0001 thru -0040 (Airplanes without Multi- Function Change and Cabin Altitude Module lmprovement) AH AI Airplanes 510-0001 thru -0065 incorporating S8510-34-02 (Garmin G1000 2008 Q1 Software/Hardware update) and Airplanes 510-0066 and On. Airplanes 510-0001 thru -0065 not incorporating S8510-34-02 (Garmin G1000 2008 Q1 Software/Hardware update) FAA APPROVED 510FM-06 Configuration AA U.S. 1-7t1-B I T MODEL 510 SECTION II- OPERATING LIMITATIONS OPERATING LIMITATIONS TABLE OF CONTENTS PAGE CertificationStatus .......2-3 OperationsAuthorized ....2-3 Weightlimitations. .......2-3 Center-of-Gravitylimitations. ....2-4 Weight and Balance Data . . 2-4 Powerplantlimitations ....2-4 EngineStartlimitations. ..2-4 FADEC (FullAuthorityDigital EngineComputers).... ..2-11 EngineFanlnspection.. .2-11 EngineStartlimitations(Air) ....2-12 Starter Cycle Limitations . . 2-12 Ground PowerUnit LimitationsforStarting ......2-12 BatteryLimitations ......2-12 Electrical Power System . . 2-13 Hydraulic Power System. . 2-13 LandingGearandTirelimitations. .....2-13 Ground Operation .2-14 Fuel Limitations.. .2-14 Unusable Fuel.. ..2-14 ApprovedOils.. ..2-15 Speed Limitations . 2-16 Takeoff andLandingOperational Limitations.... ......2-18 Enroute Operational Limitations . . 2-19 Minimum Crew . ..2-21 LoadFactor..... .2-21 Cabin PressurizationLimitations.... ....2-22 Maneuverlimitations ....2-22 PassengerCompartment... ....2-22 BaggageCompartments... .....2-22 VortexGeneratorsand StaticWicks .....2-22 ElCASand lnstrumentMarkings..... ...2-23 SupplementalOxygen System . ..2-28 StallWarning and Low Speed Awareness Systems . . . . . 2-28 Garmin G1000System ...2-29 GarminGl000GPSNavigationSystem.... ....2-30 Standbylnstruments .....2-32 AHRSAreasof Operation.... ...2-32 lce and Rain Protection. . . 2-32 Operations in Severe lcing Conditions . . .2-33 Kindsof OperationsEquipmentlist.. ...2-34 FAA APPROVED 510FM-06 I I Configuration AB U.S. 2-1t2-2 J SECTION II . OPERATING LIMITATIONS OPERATING LIMITATIONS TABLE OF CONTENTS PAGE Certification Status .......2-3 OperationsAuthorized ....2-3 Weightlimitations. .......2-3 Center-of-Gravitylimitations. ...2-4.1 Weight and Balance Data .2-4.1 Powerplantlimitations ...2-4.1 Engine Start Limitations . .2-4.1 FADEC(FullAuthorityDigital EngineComputers).... ..2-11 EngineFanlnspection.. .2-11 Engine Start Limitations (Air) . . .2-12.1 Starter Cycle Limitations .2-12.1 Ground Power Unit Limitations for Starting . . . . .2-12.1 BatteryLimitations .....2-12.1 Electrical Power System . . 2-13 Hydraulic Power System. . 2-13 LandingGearandTireLimitations.. ....2-13 I Ground Operation .2-14 Fuel Limitations. . .2-14 Unusable Fuel.. ..2-14 ApprovedOils.. ..2-15 Speed Limitations . 2-16 Takeoff andLandingOperational Limitations.... ......2-18 Enroute Operational Limitations . .2-19 Minimum Crew . ..2-21 LoadFactor..... .2-21 I Cabin PressurizationLimitations.... ....2-22 Maneuverlimitations ....2-22 PassengerCompartment... ....2-22 BaggageCompartments... .....2-22 VortexGeneratorsand StaticWicks .....2-22 ElCASand InstrumentMarkings..... ...2-23 SupplementalOxygen System ...2-28 Stall Warning and Low Speed Awareness Systems . . . . . 2-28 Garmin G1000System ...2-29 Garmin G1000GPS Navigation System.... ....2-30 Standby lnstruments .....2-32 AHRSAreasof Operation.... ...2-32 lceand Rain Protection... ......2-32 Operations in Severe lcing Conditions . . .2-33 Kindsof Operations Equipmentlist.. ...2-34 I T I MODEL 510 FAA APPROVED 510FM-06 Configuration AC U.S. 2-1.1t2-2 MODEL 510 SECTION II, OPERATING LIMITATIONS OPERATING LIMITATIONS NOTICE CERTIFICATION AND OPERATIONAL LIMITATIONS ARE CONDITIONS OF THE TYPE AND IRWORTHINESS CERTIFICATES AND MUST BE COMPLIED WITH AT ALL TIMES REQUIRED BY LAW. CERTIFICATION STATUS This airplane is certified in accordance with 14 CFR, Part23 Normal Category Part 34 (FuelVenting and Exhaust Emissions), Part 36 (Noise Requirements) and Special Conditions as prescribed by the Administrator. OPERATIONS AUTHORIZED This airplane is approved for day and night, VFR and IFR operations and flight into known icing conditions when the required equipment is installed as defined within the Kinds of Operations Equipment List. This airplane is approved for operations in Reduced Vertical Separation Minimum (RVSM) airspace when required equipment is maintained in accordance with the airplane Maintenance Manual. This does not constitute operational approval. Operational approval must be obtained in accordance with applicable operating rules. Acrobatic maneuvers, including spins, are prohibited. Intentional stalls are prohibited above 18,000 feet. WEIGHT LIMITATIONS Maximum Design Ramp Weight . . . . 8730 Pounds Maximum Design Takeoff Weight . . . 8645 Pounds Maximum Design Landing Weight . . 8000 Pounds Maximum Design ZeroFuel Weight . 6750 Pounds Minimum Weight in RVSM Airspace . 6300 Pounds Takeoff weight is limited by the most restrictive of the following requirements: Maximum Certified Takeoff Weight (Flaps - TAKEOFF/APPROACH). . . . . . 8645 Pounds Maximum Takeoff Weight Permitted by Climb Requirements . . . . . . Refer to Section lV, Performance, TAKEOFF Takeoff Field Length . . . . . . Refer to Section lV, Performance, TAKEOFF Landing weight is limited by the most restrictive of the following requirements: Maximum Certified Landing Weight . 8000 Pounds Maximum Landing Weight Permitted by Climb Requirements or Brake Energy Limits . . Refer to Section lV, Performance, APPROACH AND LANDING Landing Distance Refer to Section lV, Performance, APPROACH AND LANDING FAAAPPROVED 510FM-03 Configuration AA U.S. 2-3 SECTION II . OPERATING LIMITATIONS MODEL 510 C E N TE R.O F.GRAVITY LI M ITATIONS center-of-Gravity Moment Envelope . . Refer to Figure 2-1 WEIGHT AND BALANCE DATA The airplane must be operated in accordance with the approved loading schedule. Refer to the Model 510 Weight and Balance Manual (510WB-00 or latest revision). POWERPLANT LI M ITATIONS Engine Type . . . . . . .Pratt and Whitney Canada Inc. PW615F-A Turbofan Engine Operating Limits . . . . . Refer to Figures 2-2 Engine Inter-Turbine Temperature (lTT) Limits. . . . . Refer to Figures 2-3 and 2-4 Engine overspeed Limits . . . Refer to Figures 2-s and 2-6 Engine Oil Pressure Limits . . . . Refer to Figure 2-7 Takeoff/Go-AroundThrust(TODetent)..... .... RefertoFigures 4-13and4-14 Maximum Continuous Thrust, Single-Engine (CLB Detent) . . . . . Refer to Figures 4-15 and 4-16 Maximum Continuous Thrust, Multi-Engine (CLB Detent) Refer to Figures 4-17 and 4-18 ENGIN E START LIMITATIONS Inter-Turbine Temperature (lrr) Limits . Refer to Figure 2-3 Maximum Tailwind Component . . .10 Knots Maximum Quartering Tailwind (within Tailwind component limits) 15 Knots Maximum Crosswind Component .25 Knots Maximum Time to Light-off . . . 10 Seconds Maximum Time to Stabilized ldle (Ground or lnflighVStarter Assist). . 45 Seconds Maximum Time to stabilized ldle (lnflightAlVindmilling). . . . . . g0 Seconds NOTE Time to light-off is defined as the time after the throttle lever is moved from CUTOFF to IDLE position and an increase in ITT is observed. Minimum Engine OilTemperature (as indicated on EICAS) . -40'C NOTE ' lf engine oil temperature is below -40'C (-40'F), the engine must be preheated prior to conducting a start. ' lf the battery has been cold soaked for 2 hours or longer at an ambient surface temperature of -10"C (14"F) or lower, it must be preheated to above -10"C (14'F) prior to start. r The Engine Indicating System may take up to 10 minutes to become usable after power is applied when cold soaked below -40"C (-40'F). Maximum Temperature For Engine start . . . . Refer to Figure 2-13 Maximum Airport Elevation For Ground Battery Start. . . . . . . 10,000 Feet Maximum Airport Elevation For Ground Power Unit Start. . . . 14.000 Feet Minimum Battery Voltage For Battery Start. . . . . . .22 Volts FAA APPROVED 510FM-06 2-4 u.s. Configuration AB MODEL 5{O SECTION II. OPERATING LIMITATIONS OPERATING LIMITATIONS NOTICE RTIFICATION AND OPERATIONAL LIMITATIONS ARE CONDITIONS OF THE TYPE AN RWORTHINESS CERTIFICATES AND MUST BE COMPLIED WITH AT ALL TIMES A QUIRED BY LAW. CERTIFICATION STATUS This airplane is certified in accordance with 14 CFR, Par123 Normal Category Part 34 (Fuel Venting and Exhaust Emissions), Part 36 (Noise Requirements) and Special Conditions as prescribed by the Administrator. OPERATIONS AUTHORIZED This airplane is approved for day and night, VFR and IFR operations and flight into known icing conditions when the required equipment is installed as defined within the Kinds of Operations Equipment List. This airplane is approved for operations in Reduced Vertical Separation Minimum (RVSM) airspace when required equipment is maintained in accordance with the airplane Maintenance Manual. This does not constitute operational approval. Operational approval must be obtained in accordance with applicable operating rules. Acrobatic maneuvers, including spins, are prohibited. Intentional stalls are prohibited above 18,000 feet. WEIGHT LIMITATIONS Maximum Design Ramp Weight . . . . 8730 Pounds Maximum Design Takeoff Weight . . . 8645 Pounds Maximum Design Landing Weight . . 8000 Pounds Maximum Design ZeroFuel Weight . 6750 Pounds Minimum Weight in RVSM Airspace . 6300 Pounds Takeoff weight is limited by the most restrictive of the following requirements: Maximum Certified Takeoff Weight (Flaps - TAKEOFF/APPROACH). . . . . . 8645 Pounds Maximum Takeoff Weight Permitted by Climb Requirements . . . . . . Refer to Section lV Performance, TAKEOFF Takeoff Field Length . . . . . . Refer to Section lV Performance, TAKEOFF Landing weight is limited by the most restrictive of the following requirements: Maximum Gertified Landing Weight . 8000 Pounds Maximum Landing Weight Permitted by Climb Requirements or Brake Energy Limits . . Refer to Section lV, Performance, APPROACH AND LANDING Landing Distance Refer to Section lV Performance, APPROACH AND LANDING FAAAPPROVED 510FM-03 Configuration AA U.S. 2-3 SECTION II. OPERATING LIM]TATIONS MODEL 510 C E NTER-OF.G RAVITY LI M ITATIONS center-of-Gravity Moment Envelope . . Refer to Figure 2-1 WEIGHT AND BALANCE DATA The airplane must be operated in accordance with the approved loading schedule. Refer to the Model 510 Weight and Balance Manual (510WB-00 or latest revision). POWE RP LANT LI M ITATIO N S Engine Type . . . . . . .Pratt and Whitney Canada Inc. PW615F-A Turbofan Engine Operating Limits . . . . . Refer to Figures 2-2 Engine Inter-Turbine Temperature (lTT) Limits . . . . . Refer to Figures 2-3 and 2-4 Engine overspeed Limits . . . Refer to Figures 2-s and 2-6 Engine Oil Pressure Limits . . . . iefer to Figure 2-7 Takeoff/Go-AroundThrust(TODetent)..... .... RefertoFigures 4-13and4-14 Maximum Continuous Thrust, Single-Engine (CLB Detent) . . . . . Refer to Figures 4-15 and 4-16 Maximum Continuous Thrust, Multi-Engine (CLB Detent) Refer to Figures 4-17 and 4-18 ENGIN E START LIMITATIONS Inter-Turbine Temperature (lTT) Limits . Refer to Figure 2-3 Maximum Tailwind Component . . . 10 Knots Maximum Quartering Tailwind (within Tailwind component limits) 15 Knots Maximum Crosswind Component .25 Knots Maximum Time to Light-off . . . 10 Seconds Maximum Time to Stabilized ldle (Ground or InflighVstarter Assist) . . 45 Seconds Maximum Time to stabilized ldle (lnflightMindmilling). . . . . . g0 seconds NOTE Time to light-ofi is defined as the time after the throttle lever is moved from CUTOFF to IDLE position and an increase in ITT is observed. Minimum Engine OilTemperature (as indicated on EICAS) . -40.C NOTE ' lf engine oil temperature is below -40'C (40'F), the engine must be preheated prior to conducting a start. o lf the battery has been cold soaked for 2 hours or longer at ambient surface temperature of -18'C (0'F) or lower, it must be preheated to above -18'C (0'F) prior to start. o The Engine lndicating System may take up to 10 minutes to become usable after power is applied when cold soaked below -40'C (-40"F). Maximum Temperature For Engine Start . . . . Refer to Figure 2-13 Maximum Airport Elevation For Ground Battery start. . . . . . . 10,000 Feet Maximum Airport Elevation For Ground Power Unit Start. . . . 14,000 Feet Minimum Battery Voltage For Battery Start. . . . . . .24 Volts FAA APPROVED 510FM-06 2-4.',| U.S. Configuration AC MODEL 510 90m 8Sm 8000 6000 5500 FAAAPPROVED 510FM-06 e, g i'0g m00 {l[ '6 3 SECTION II. OPERATING LIMITATIONS G E NTE R.OF-G RAVIry LI M ITATIO N S foruf,rd CG FS t87.04, er k$t 3i!!6 I \'\- ,t Maxlmum trtlamp Welgil 8?S0 pounds 1-f-{.-.{--+- Me*mom Taksott $faight 8g4S po$nda / / Ml xrnllrn Lan dhgl,VsQn 8000 Fouf {b I Fon rard OG Llfit0varpo J!td* fJ .q *' .g iN JO ?E :6 s$ bo Lq Maxirnur nzero F0s l!ryoight Ei '59 pound€ (J = et -t? x,e{9 3q s$c() { lr" J as4 ?8$ es6 287 2&A e$g 2CS 2St ASe 2$3 254 gsnter ot Grsrily {lnchec} f 7"5 18% 1*/o Zff/a 21l*, *Vo 23% 24?r 25% 26% 27".{ 28o/o 29% 30% 31% 3E% Senter ot Gravity {percenl MAC} Fgnr,l NUtiSSfi g'34,24AI{{|3t 2fi8 Figure 2-1 Configuration AA u.s. 2-5 SECTION II . OPERATING LII'ITATIONS MODEL 510 ENGINE OPERATING LIMITS Figure 2-2 NOTE The total time during which takeoff thrust may be used is limited to five minutes per flight. The five minute time limit commences when the throttle is first advanced to the TO detent. This time may be extended to 10 minutes for one engine inoperative operation. The takeoff thrust (N1) for the airplane is defined in Figures 4-13 and 4-14 and is more limiting than engine rotational limits and must be observed. Performance data including Vnacn and VMg6 in Section lV, is based on use of the appropriate Takeoff Thrust setting. Maximum continuous thrust (CLB Detent) for the airplane is defined by Figures 4- 15 and 4-16 (single-engine) and Figures 4-17 and 4-18 (multi-engine). These thrust settings (N1) are more limiting than engine rotational limits and must be observed. Performance data in Section lV is based on the use of the appropriate maximum continuous thrust setting. Oil temperature must be above 22"C for at least 5 minutes before takeoff. Once oil temperature is +10'C or warmer, it is acceptable to increase power up to the CRU detent to decrease the time required to warm the oil to 22'C. ldle speed is a function of ambient pressure and temperature. After initiation of the start cycle, oil pressure should indicate a steady increase within 20 seconds of the start of N2 rotation. 1. 2. 4. 5. FAA APPROVED 510FM-00 OPERATING CONDITION OPERATING LIMITS THRUST SETTING TIME LIMlT (MTNUTES) ITT TEMPERATURE "C Nz% Nr% OIL PRESSURE PSI OILTEMPERATURE START 862 SEE FIGURE 2-3 0 To 250 (NOrE 5) -40 MINIMUM GND IDLE CONTINUOUS 48.6 24 MINIMUM -40 TO 135 (NorE 3) FLT IDLE CONTINUOUS 56.8 (r\4rNtMUM) (NorE 4) SEE FIGURE 2.7 22TO 135 TAKEOFF fiO DETENT) c (NorE 1) 830 100.0 100.0 (NOrE 1) SEE FIGURE 2-7 22TO 135 (NorE 3) MAXIMUM CONTINUOUS (CLB DETENT) CONTINUOUS 830 100.0 100.0 (NorE 2) SEE FIGURE 2-7 22rO 135 MMIMUM CRUISE (CRU DETENT) CONTINUOUS 830 100.0 100.0 SEE FIGURE 2.7 22TO'135 TRANSIENT 20 SECONDS 862 SEE FIGURE 2.4 102.0 SEE FIGURE 2-5 101.0 SEE FIGURE 2€ 90 SECONDS SEE FIGURE 2-7 135 TO 141 15 / 500 SECONDS SEE FIGURE 2-7 2-6 U.S. Configuration AA MODEL 5IO SECTION II. OPERATING LIMITATIONS t#t*76 FAA APPROVED 510FM-02 o E ocr- E .o O .E 830 gl c OVER TEMPERATURE LIMITS . STARTING s 2 45678 10 1e U 16 18 2A 22 24 36 Tims {$econds} &raa A - No Action Requlrad AreaB-{1} Determin* Oause and Correcl {?} lnspecl Hot gectiCIn Using Borescope {3} nepo* Incidsnl in Engino Log Eook Arca C - Ratorto Pratt andwhitney PW61SF-A Mainlenance Manual Figure 2-3* Configuration M SECTION II. OPERATING LIMITATIONS MODEL 510 OVER TEMPERATURE LIMITS - EXCEPT STARTING 020't2345678910 {Sec} (Min} Time {$aconds} Area A - No Actior Required Area B - {'l} Oetern'lina Cau** snd Cofisct (2) Inspect Hol $ection Using Bor*scope (3) Repod Incident in Engine Log Book Area C - Re,f*r to Pratt and Whitney PWS15F-A Malntenance irlanual Figure 24* (J a o 5 o CL tr .it {u c E 8{n : o FAAAPPROVED 51oFM-02 2-B U.S. Configuration AA MODEL 510 sEcnoN il - oPERATNG LrMrrAToNs N2 ENGTNE OVERSPEED LtMtTS Time {$econds} Area A- No Action Rquirad Area B - Refer to Pratt and Whitney PW61sf-A Malntenance Manual Figure 2-5* ID t) b'l 1gt $o CL u) bt{l E, .E .gr Ito 3 oJ FAA APPROVED 510FM-02 U.S. 0r02Q304050 Configuration AA 2-9 SECTION II . OPERATING LIMITATIONS MODEL 510 FAA APPROVED 510FM-02 N1 ENGTNE OVERSPEED LtMtTS 101 o eqt {L €o scL t'l o o(f 3 100 oJ Area A - No Action Roquircd Area B - Refarlo Prafi and Whitney pW615F-A Maintsnanca Manual Figure 2-6* 0 'r0 20 30 40 Tlnw {Saconds} 2-10 U.S. Configuration AA MODEL 510 SECTION II. OPERATING LIMITATIONS ENGINE OIL PRESSURE LIMITS rrsat0 40150 45"44/a N2 f6) Figure 2-7 FADEC (FULL AUTHORITY DIGITAL ENGINE GOMPUTERS) Dispatch with an engine FADEC fault (ENG CTRL SYS L or R message displayed) is prohibited. ENGINE FAN INSPECTION Prior to engine start, the Engine Fan Duct and Fan inspection in Section lll, Normal Procedures, must be satisfactorily completed. 200 170 t; 1$0 tt l:- ro E 100 FAA APPROVED 510FM-05 Configuration AA U.S. 2-11 SECNON II . OPERATING LIIUITATIONS MODEL 510 ENGINE START LIMITATIONS (Air) Inter-Turbine Temperature (lTT) Limits . Refer to Figure 2-3 Airspeed/Altitude Limits Refer to Figure 3-1 Minimum Temperature for Windmill Start . . . . . -10.C RAT STARTER CYCLE LIMITATIONS Starter Cycle Limitation . . . Three engine starts per 30 minutes. Three cycles of operation with a 60-second rest period between cycles is permitted. NOTE This limitation is independent of starter power source (i.e. baftery generator assisted cross start, or ground power unit) and applies to both starting and dry motoring of the engine. GROUND POWER UNIT LIMITATIONS FOR STARTING Minimum/Maximum Current . . .900/1100 Amperes Maximum Voltage . .29 VDC CAUTION NORMAL STARTER CURRENT DRAW IS APPROXIMATELY l OOO AMPERES PEAK. GROUND POWER UNITS WITH VARIABLE MAXIMUM CURRENT SHUTOFF SHOULD BE SET TO 11OO AMPERES. USE OF AN GROUND POWER SOURCE WITH VOLTAGE IN EXCESS OF 29 VDC OR CURRENT IN EXCESS OF 11OO AMPS MAY DAMAGE THE STARTER. BATTERY LIMITATIONS Battery Start Limitation . . . . . Three engine starts per hour Minimum Voltage for Start. ,22Volts CAUTION BATTERY STARTS ARE PROHIBITED AT AIRPORT ELEVAT]ONS ABOVE 1O,OOO FEET. ABOVE 1O,OOO FEET, ENGINES MUST BE STARTED USING A GROUND POWER UNIT OR USING A GENERATOR ASSISTED CROSS START. lf the BATTERY O'TEMP message displays during ground operations, dispatch is prohibited until after the proper maintenance procedures have been accomplished. NOTE !! b-attery^limitation is exceeded, ground maintenance procedures are required. Refer to Chapter 24 of the Maintenance Manual for procedure. Three generator assisted cross starts are equal to one battery start. lf a ground power unit is used for start, no battery cycle is counted. FAAAPPROVED 510FM-05 I 2-12 U.S. Configuration AB MODEL 510 SEcroN il - oPERATNG LIM|TATONS ENGINE OIL PRESSURE LIMITS mo 1?0 6 1$0 ut .g IL o = 100 4At50 45.4Y<r N2 t%) Figure 2-7 FADEC (FULL AUTHOR|TY DtctTAL ENGINE COMPUTERS) Dispatch with an engine FADEC fault (ENG CTRL SYS L or R message displayed) is prohibited. ENGINE FAN INSPECTION Prior to engine start, the Engine Fan Duct and Fan inspection in Section lll, Normal Procedures, must be satisfactorily completed. FAA APPROVED 510FM-05 U.S. Configuration M 2-11 SECTION II. OPERATING LIMITATIONS MODEL 510 ENGINE START LIMITATIONS (Air) Inter-Turbine Temperature (lTT) Limits . Refer to Figure 2-3 Airspeed/Altitude Limits Refer to Figure 3-1 Minimum Temperature for Windmill Start . . . . . -10"C RAT STARTER GYCLE LIMITATIONS Starter Cycle Limitation . . . Three engine starts per 30 minutes. Three cycles of operation with a 60-second rest period between cycles is permitted. NOTE This limitation is independent of starter power source (i.e. battery generator assisted cross start, or ground power unit) and applies to both starting and dry motoring of the engine. GROUND POWER UNIT LIMITATIONS FOR STARTING Minimum/Maximum Current . . .800/1100 Amperes Maximum Voltage . .29 VDC CAUTION NORMAL STARTER CURRENT DRAW IS APPROXIMATELY l OOO AMPERES PEAK. GROUND POWER UNITS WITH VARIABLE MAXIMUM CURRENT SHUTOFF SHOULD BE SET TO 11OO AMPERES. USE OF AN GROUND POWER SOURCE WITH VOLTAGE IN EXCESS OF 29 VDC OR CURRENT IN EXCESS OF 11OO AMPS MAY DAMAGE THE STARTER. BATTERY LIMITATIONS Battery start Limitation . . . . . Three engine starts per hour Minimum Voltage for Start. .24 Volts CAUTION BATTERY STARTS ARE PROHIBITED AT AIRPORT ELEVATIONS ABOVE 1O,OOO FEET. ABOVE 1O,OOO FEET, ENGINES MUST BE STARTED USING A GROUND POWER UNIT OR USING A GENERATOR ASSISTED CROSS START. NOTE lf battery limitation is exceeded, ground maintenance procedures are required. Refer to Chapter 24 of the Maintenance Manual for procedure. Three generator assisted cross starts are equal to one battery start. lf a ground power unit is used for start, no battery cycle is counted. O o I 2-12.1 FAAAPPROVED 510FM-05 U.S. Configuration AC MODEL 510 ELECTRICAL POWER SYSTEM Generator limits are as listed in Figure 2-8. SECTION II . OPERATING LIMITATIONS STATUS LIMIT On Ground, ldle 150 Amps On Ground, Above ldle 300 Amps Air < 30,000 Feet 300 Amps Air > 30,000 Feet 280 Amps Figure 2-8 NOTE The above limits are steady state limits. Following an engine battery start, generator current may exceed 150A at ground idle for up to 5 minutes while the battery is recharging. Above idle or during flight, transients up to 4504 are permitted for up to 2 minutes. HYDRAULIG POWER SYSTEM The only approved hydraulic fluid for the hydraulic power system is MIL-PRF-87257. LANDING GEAR AND TIRE LIMITATIONS The only approved hydraulic fluid for the landing gear struts is MIL-PRF-87257. The tires listed in Figure 2-9 are the only tires approved. Tires must be inflated to the pressure shown. POStTtON VENDOR PART NUMBER UNLOADED PRESSURE LOADED PRESSURE Nose Tire Michelin 079-606-0 12015 PSIG 12515 PSIG Dunlop DR170267 12015 PSIG 12515 PSIG Main Tires Michelin 021-523-0 8515 PS|G 8815 PSIG Dunlop DR255267 B5t5 PSIG 8Bt5 PSIG NOTE lf the ground operating temperature is expected to drop more than 28'C (50"F) or the arrival airfield is expected to be more than 28'C (50"F) colder than the departure airfield, refer to the Airplane Maintenance Manual for tire servicing. Figure 2-9 FAA APPROVED 510FM-05 Configuration AA U.S. 2-13 SECTION II . OPERATING LIMITATIONS MODEL 510 GROUND OPERATION Continuous engine ground static operation up to and including five minutes at takeoff thrust is limited to ambient temperatures defined in Figure 2-13. Limit ground operation of pitoUstatic heat to two minutes to preclude damage to the pitot tubes and stallwarning vane. Movement of the flaps is prohibited at temperatures colder than -40'C. FUEL LIMITATIONS The corresponding electric fuel boost pump must be turned ON when the FUEL LO L-R CAS message is displayed or at 170 pounds or less of indicated fuel in either tank. Maximum approved fuel imbalance is 200 lbs. A emergency fuel imbalance of 600 pounds has been demonstrated for safe return and landing. Minimum fuel quantity for takeoff is 200 lbs. per wing. Figure 2-10 lists the fuel temperature limitations for each approved fuel. GRADE (TYPE) SPECIFIGATION MINIMUM FUEL TEMPERATURE 'c ('F) JET A, JET A.1 ASTM.DI655 €5 (-31) JP.8 MtL-T-83133 -35 (-31) NOTE o The fuel tank temperature indication on EICAS does not monitor for fuel temperature out of limits. o Dupont Stadis 450 antistatic additive or equivalent is permitted to bring fuel up to 300 conductive units, but not to exceed 3 ppm (parts per million) by weight. o SOHIO Biobor JF biocide additive is approved at a concentration not to exceed 270 ppm by weight. ' EGME/DIEGME anti-icing additive is approved for use, but not required, at a concentration not to exceed 0.15To by volume. Refer to Normal Procedures, ANTI-lCE ADDITIVES for blending instructions. Figure 2-10 UNUSABLE FUEL Unusable fuel is the fuel remaining in the fuel tanks when the fuel quantity indicator reads zero. This fuel is not usable in flight. FAA APPROVED 510FM-05 I 2-14 U.S. Configuration AA MOBIL JET OIL II AIR BP / EXXON 2380 MOBIL JET OlL 254- AIR BP / EXXON 2197" ROYCO TURBINE OIL 5OO AEROSHELL TURBINE OIL 5OO ROYCO TURBINE OIL 560- AEROSHELL TURBINE OIL 560- TurboNycoilTN 600 CASTROL 5OOO * Oils denoted with an asterisk are "THIRD GENERATION" lubricants. In addition, oils listed forthe engine in the latest revision to PW615F Maintenance Manual (P/N 3059712) are approved. CAUTION WHEN CHANGING FROM AN EXISTING LUBRICANT FORMULATION TO A ''THIRD GENERATION'' LUBRICANT FORMULATION, THE ENGINE MANUFACTURER STRONGLY RECOMMENDS THAT SUCH A CHANGE SHOULD ONLY BE MADE WHEN AN ENGINE IS NEW OR FRESHLY OVERHAULED. FOR ADDITIONAL INFORMATION ON USE OF THIRD GENERATION OILS. REFER TO ENGINE MANUFACTURER'S PERTINENT OIL SERVICE BULLETINS. Figure 2-11 Maximum oil consumption is 1 U.S. quart per 13.5 hour period. lf oil consumption exceeds this amount, refer to the Pratt and Whitney PW61SF-A Maintenance manual. The oil level must be serviced to the MAX indication on the sight glass for any flight planned to exceed 5 hours in duration. Should it be necessary to replenish oil consumption losses when oil of the same brand (as tank contents) is unavailable, then the following requirements apply: For contingency purposes, oil replenishment using any other approved oil brand listed is acceptable provided: 1. The total quantity of added oil does not exceed two U.S. quarts in any 400-hour period. 2. lf it is required to add more than two U.S. quarts of dissimilar oil brands, drain and flush complete oil system and refill with an approved oil in accordance with Engine Maintenance Manual instructions. Should oils of non-approved brands or of different viscosities become intermixed, drain and flush complete oil system and refill with an approved oil in accordance with Engine Maintenance Manual instructions. MODEL 510 APPROVED OILS The following oils are approved for use: FAA APPROVED 510FM-00 SECTION II. OPERATING LIMITATIONS Configuration AA U.S. 2-15 SECTION II. OPERANNG LIMITANONS MODEL 510 SPEED LIMITATIONS Maximum Operating Limit Speeds V"o (Between Sea Level and 27,120 Feet) . . . . 250 KIAS Mys (Above 27,120 Feet) . . .0.63 Mach (tndicated) NOTE The maximum operating limit speeds may not be deliberately exceeded in any regime of flight (climb, cruise or descent) unless a higher speed is authorized for flight test or pilot training. Maximum operating Maneuvering Speeds - Vo. . Refer to Figure 2-12 WARNING AVOID RAPID AND LARGE ALTERNATING CONTROL INPUTS, ESPECIALLY IN COMBINATION WITH LARGE CHANGES IN PITCH, ROLL, OR YAW (t.E., LARGE StDESLtp ANGLES) AS THEY MAy RESULT tN STRUCTURAL FATLURES AT ANy SPEED, |NCLUD|NG BELOW Vo. NOTE Full application of rudder and aileron controls, as well as maneuvers that involve angle-of-attack near the stall, should be confined to speeds below maximum maneuvering speed. EXAMPLE PROBLEM: Refer to Figure 2-12 PRESSURE ALTITUDE - 35,OOO FEET WEIGHT - B,OOO POUNDS MAXIMUM MANEUVERING SPEED - 158 KNOTS Maximum Flap Extended Speed - Vpg TAKEOFF / APPROACH Position (15") . 185 KIAS LANDPosition(30"). ...150K1AS Maximum Landing Gear Extended Speed - Vle. . . . 250 KIAS Maximum Landing Gear Operating Speed - V1e (Extending). . . . . . 250 KIAS Maximum Landing Gear Operating Speed - Vse (Retracting) . . . . . 185 KIAS Maximum Speed Brake Operation Speed - Vse. . . . . No Limit Maximum Autopilot Operation Speed . 250 KIAS or 0.63 Mach Maximum Tire Ground Speed 160 Knots Minimum Speed in RVSM Airspace . 110 KIAS Minimum Speed For Sustained Flight In lcing Conditions (except takeoff, approach and landing). . . . . 160 KIAS Minimum Control Speeds (Vnrcn and Vy66) . . Refer to Section lV Performance, GENERAL FAA APPROVED 510FM-06 2-16 U.S. Configuration AA MODEL 510 SECTION II. OPERATING LIMITATIONS MAXIMUM OPERATING MANEUVERING AIRSPEEDS t8*{{8 190 14S rsCI 160 Operating M*neuvering Spoeds {Vo} - K}AS FAA APPROVED 510FM-04 Figure2-12* Configuration AA U.S. 2-17 SECTION II . OPERATING LIMITATIONS TAKEOFF AND LANDING OPERATIONAL LIMITS MODEL 510 Maximum Altitude Limit. . . 14.000 Feet Maximum Tailwind Component 't0 Knots Maximum/Minimum Ambient Temperature Refer to Figure 2-13 Maximum Demonstrated Crosswind Component (Not Limiting). . . . .25 Knots Minimum Fuel Quantity per Wing for Takeoff . . 200 lbs The maximum approved fuel imbalance is 200 pounds; however, controllability for safe return and landing has been demonstrated with an emergency fuel imbalance of 600 pounds. A satisfactory preflight check of each of the following systems must be accomplished in accordance with Section lll, Normal Procedures, prior to takeoff: 1. StallWarning 2. Flight Controls 3. Flaps 4. Standby Instruments Electric elevator trim system preflight test must be accomplished in accordance with Section lll, Normal Procedures prior to takeoff. The autopilot and yaw damper must be disengaged for takeoff and landing. Dispatch with a ENG CTRL SYS L-R message displayed is prohibited. Takeoff and landings are limited to paved runway surfaces. Refer to Section Vll for takeoff and landing distance corrections applicable to runway surfaces other than dry. Dispatch with antiskid inoperative is prohibited if the forecast conditions for the destination approach and landing will require the use of STALL WARNING-HIGH (Flap TO/APR) landing data. Use of flaps in the LAND position is prohibited with ice adhering anywhere on the outside of the airplane. STALL WARNING-HIGH landing performance data in Section lV is predicated on the use of Flaps TO/APR for landing. Speed brakes must be retracted prior to 50 feet AGL before landing (unless required by AFM procedure). Cabin must be depressurized for landing. Takeoff is prohibited with the following forms of contamination: 1. With frost adhering to the following critical areas: a. Wing Leading Edge b. Upper Wing Surface c. Windshield (Continued Next Page) t 2-18 FAA APPROVED 510FM-05 U.S. Configuration AA MODEL 510 SECTION II. OPERATING LIMITATIONS TAKEOFF AND LANDING OPERATIONAL LIMITS (continued) 2. With ice, snow or slush adhering to the following critical areas: a. Wing Leading Edge and Upper Wing Surface b. Flight Control Surfaces including all hinge gaps c. Horizontal Stabilizer d. Vertical Stabilizer e. Engine Inlets f. Top of Engine Pylons g. Top of Fuselage h. Windshield i. All Static Ports j. Stall Warning Vane k. Upper surface of nose forward of the windshield 3. A visual and tactile (hand on surface) check of the wing leading edge and the wing upper surface must be performed to ensure the wing is free from frost, ice, snow, or slush when the outside air temperature is less than 10'C (50'F) or if it cannot be determined that the wing fueltemperature is above 0'C (32"F)and: a. There is visible moisture present (rain, drizzle, sleet, snow, fog, etc.); or b. Water is present on the wing upper surface; or c. The difference between the dew point and the outside temperature is 3'G (5'F) or less; or d. The atmospheric conditions have been conducive to frost formation. ENROUTE OPERATIONAL LIMITS GENERAL Maximum OperatingAltitude. ....41,000Feet Maximum Ambient Temperature . . Refer to Figure 2-13 MinimumAmbientTemperature.... ....RefertoFigure2-13 Maximum Altitude for Extension of Flaps . 18,000 Feet t Minimum Temperature for Operation of Flaps . . . . -40'C RAT Yaw Damper must be engaged above FL300. FAA APPROVED 510FM-06 Configuration AA U.S. 2-19 sEcToNil.oPERAflNGLtMffAnoNs MODEL 510 TAKEOFF ILANDING / ENROUTE TEMPERATURE LIMITS -20 0 Ambient Air T€npsratur€' oC Figure 2-13 NOTE Ambient Air Temperature is ISA Temperature corrected for Indicated ISA Deviation (reference Figures 4-2 and 4-3). For operations below -10"C (+14'F), refer to Section lll, Normal Procedures, COLD WEATHER OPERATIONS. Long term operation (>30 minutes) is limited to a maximum of ISA+31'C if the air- conditioner is inoperative or turned OFF. 630 TL o It €eo d g :9)gl o i10 I | 2-20 FAA APPROVED 510FM-05 U.S. Configuration AA o MODEL 5{O SECTION II. OPERATING LIMITATIONS ENROUTE OPERATIONAL LIMITS lcontinued) RVSM OPERATIONS Minimum Speed in RVSM Airspace . 110 KIAS Minimum Weight in RVSM Airspace . . . . 6300 Pounds The following equipment must be installed and operating normally upon entering RVSM airspace: 1. Pilot and copilot primary altimeters. 2. Autopilot. 3. Altitude Alerter. 4. ATCRBS Transponder. NOTE t Any changes to the pitoUstatic, air data computer, autopilot, altitude alerting and/ or transponder systems, or other changes that affect operation of these systems must be evaluated for impact on the RVSM approval. o The standby altimeter is not approved for RVSM operations. Each operator must ensure compliance with required crew training and operating practices and procedures. Individual airplane and operational approval must be obtained in accordance with applicable operating rules. MINIMUM CREW Except where otherwise prescribed by applicable operating limitations, Minimum Crew for all operations: 1 Pilot, provided: a. The pilot holds a CE510(S), single pilot type rating. b. The airplane is equipped for single pilot operation as specified in the Kinds of Operations Equipment List. c. The pilot must occupy the left pilot's seat. Or 1 Pilot and 1 Copilot provided: a. The pilot holds a CE510(S) or CE510 (second-in-command required) pilot type rating. LOAD FACTOR Flaps - UP (0o) . . . -1 .44to+3.6c at 8645 lbs. Flaps - TAKEOFF / APPROACH or LAND (15o or 30o). . . . . 0.0 to +2.0G at 8645 lbs. NOTE These accelerations limit the angle-of-bank in turns and limit the severity of pull-up maneuvers. (Continued Next Page) FAAAPPROVED 510FM-05 Configuration AA U.S. 2-21 SECTION II . OPERATING LIMITATIONS MODEL 510 CABIN PRESSURIZATION LIMITATIONS NormalCabin Pressurization Limitations . . . MANEUVER LIMITATIONS Acrobatic maneuvers, including spins, are prohibited. Intentional stalls are prohibited above 18,000 feet. Refer to Figure 2-12for maximum maneuvering speeds. PASSENGER COMPARTMENT For taxi, takeoff, and landing, adjustable passenger seats must be positioned with seatbacks upright. Passenger seat belts must be properly fastened. The maximum passenger seating, not including 2 crew seats, is four. The use of the lavatory is prohibited for taxi, takeoff, and landing and is limited to one occupant in flight. BAGGAGE COMPARTMENTS Nose Baggage Compartment (L-R) . . . . . .320 pounds maximum (combined) I TailconeBaggageCompartment ... .....300poundsmaximum(combined) VORTEX GENERATORS AND STATIC WICKS The following lists the number of vortex generators required for dispatch: 1. Wing - 16 installed (B per side), 16 required. The following lists the number of static wicks that may be missing or broken, but no more than two total: 1. Right-hand wingtip and aileron - 3 installed, 2 required. 2. Left-hand wingtip and aileron - 3 installed, 2 required. 3. Rudder and Tailcone - 4 installed, 3 required. 4. Elevators - 6 installed (3 per side), 5 required. FAA APPROVED 51oFM-06 2-22 U.S. Configuration AA MODEL 5IO SECTION II . OPERATING LIMITATIONS EICAS AND INSTRUMENT MARKINGS ENGINE INDICATING SYSTEM FAN (N1) RPM |ND|CATORS Scale markings . .Red Line. . . .100% RpM Tape Pointer/ Digital Readout ..Red >101% RpM Red. . . . 100 to 101% RPM for > 20 Sec Tape Pointer . .. . . .. .. .White . .. . StOOy" npU Digital Readout . .Green <100% RPM NOTE o Tape Pointer and Digital Readout will turn red if outside normal operating limits. Digits will appear in inverse video. White Tape Pointer represents Green band. Tape Pointer is removed when N1 is less than 20o/o. Digital readout will still be displayed. a O I I INTER-TURB|N E TEMpERATURE (tTT) TNDTCATORS FAA APPROVED 510FM-02 Scale markings . .Red Line. . AmberBand. ...> 830to862"C Tape Pointer / Digital Readout (Engine Start) . . .Red . .> 830 to 862"C for > 5 Sec Amber. Tape Pointer/ Digital Readout (Engine Running)Red.... .. > B30to 862'Cfor> 20 Sec Amber. TapePointer.... ......White.... S830'C Digital Readout ..Green ..<830"C NOTE The Tape Pointer and Digital Readout will tum red or amber if outside normal operating limits. Digits will appear in inverse video. White Tape Pointer represents green band. ' Digits will only appear during engine start, limit exceedance, or when below 200"c. TURBTNE (N2) RPM TNDTCATORS Digital Readout ..Red > 102% RPM Red. . > 100 to 102o/o RPM for > 20 Sec Amber. ffiJ : : : : : : : : : : il;,?,iJi"liJ NOTE Digital Readout will turn red if outside normal operating limits. Digits will appear in inverse video. (Continued Next Page) Configuration M U.S. 2-23 SECTION II . OPERATING LIMITAT]ONS EICAS AND INSTRUMENT MARKINGS (continued) OIL TEMPERATURE INDICATORS MODEL 510 FAAAPPROVED 510FM-05 I ScaleMarkings ..RedBand(High).... .>141'C Amber Band (High) . . . >135 to 141"C Green Band . ..... 22 to 135'C Amber Band (Low) -40 to 22"C Red Band (Low) . . . -50 to -40"C Pointer / Digital Readout. Red (High) Red (High) . . . . .135 to 141'C > 90 Sec Amber (High) . . . 135 to 141"C < 90 Sec Green(PointerOnly) . .... 22to135"C Amber (Low). 40to 22"C Red (Low). NOTE The Pointer and Digital Readout will turn red or amber if outside normal operating limits. Digits will appear in inverse video. Digitalvalues are not shown when oiltemperatures are in the green band. OIL PRESSURE INDICATORS ScaleMarkings ..RedBand(High).... >250PSl Amber Band (High) . . . . 170 to 250 PSI Green Band . ......Variableto 170 PSI AmberBand(Low) .... Variable Red Band (Low) Variable Pointer/Digital Readout. ......Red (High) ... >275 PSI Red (High) 170 to 250 PSI for > 500 Sec Amber (High) . . .170 to 250 PSI (> 440 Sec and < 500 Sec) Green. . . .170 to 250 PSlfor < 440 Sec Green ......Variableto 170 PSI Amber(Low). .. Variable Red(Low). ..... InAmberfor>90Sec Red (Low). . Below Variable Limit (Continued Next Page) a 2-24 U.S. Configuration AA MODEL 510 SECTION II . OPERATING LIMITATIONS EICAS AND INSTRUMENT MARKINGS (continued) NOTE o The Pointer and Digital Readout will turn red or amber if outside normal operating limits. Digits will appear in inverse video. ' Low oil pressure limits vary with engine N2. Refer to Figure 2-7. Values may be different for the left and right engines. o Digital values are not shown when oil pressures are in the green band or in the high amber band for less than 440 seconds. DC VOLTAGE INDICATORS Pointer / Digital ReadouV Scale Markings . .Red (High) 37 to 40 VDC Amber (High) . . . . 33 to 36 VDC Green . . . .22 to 32 VDC Amber(Low). ....111o21 VDC Red (Low). . 0 to 10 VDC NOTE The Pointer and Digital Readout will turn red or amber if outside normal operating limits. Digits will appear in inverse video. DG CURRENT INDICATORS ENGINE AT GROUND IDLE Pointer / Digital ReadouV Scale Markings . .Red . . .180 to 995 AMPS Red (Pointer/Digits Only) . . . . 150 to 175 AMPS for > 2 Minutes Amber. 150 to 175 AMPS Green -995 to 145 AMPS NOTE The Pointer and Digital Readout will turn red or amber if outside normal operating limits. Digits will appear in inverse video. ENGINE ABOVE GROUND IDLE OR IN.AIR AT FL3OO OR BELOW Pointer / Digital ReadouV Scale Markings . .Red . . .450 to 995 AMPS Red (Pointer/Digits Only) . . . .300 to 445 AMPS for > 2 Minutes Amber. 300 to 445 AMPS Green -995 to 295 AMPS (Continued Next Page) Configuration AA U.S. 2-25 SECTION II. OPERATING LIM]TATIONS MODEL 510 EICAS AND INSTRUMENT MARKINGS (continued) NOTE The Pointer and Digital Readout will turn red or amber if outside normal operating limits. Digits will appear in inverse video. IN . AIR ABOVE FL3OO Pointer / Digital ReadouU Scale Markings . .Red. . .450 to 995 AMPS Red (Pointer/Digits Only) . . . .280 to 445 AMPS for > 2 Minutes Amber. 280 to 445 AMPS Green -995 to 275 AMPS NOTE The Pointer and Digital Readout will turn red or amber if outside normal operating limits. Digits will appear in inverse video. BATTERY VOLTAG E INDICATOR Digital Readout . .Red (High) 37 to 40 VDC Amber (High) . . . . 33 to 36 VDC Green . . . .22 to 32 VDC Amber(Low). ....111o21 VDC Red (Low). . 0 to 10 VDC NOTE The Pointer and Digital Readout will turn red or amber if outside normal operating limits. Digits will appear in inverse video. BATTERY CU RRENT INDICATOR Digital Readout . .Red. . .500 to 995 AMPS Amber. 300 to 495 AMPS Green -995 to 295 AMPS NOTE The Pointer and Digital Readout will turn red or amber if outside normal operating limits. Digits will appear in inverse video. (Continued Next Page) FAA APPROVED 510FM-05 | 2-26 U.S. Configuration AA MODEL 510 SECTION II . OPERATING LIMITATIONS EICAS AND INSTRUMENT MARKINGS (continued) CABIN PRESSURIZATION INSTRUMENTATION CABIN ALTITUDE Pointer / Digital ReadouU Scale Marking (Normal Mode) . .Red Band . AmberBand. .....8500to10,000Feet Green Band . Pointer / Digital ReadouU Sca|eMarking(HighA|titudeMode)....RedBand.....'.> Amber Band . . . . 14,000 to 14,600 Feet Green Band . Pointer/ScaleMarking(Ground) ......GreenBand ..... EntireRange NOTE o The Pointer and Digital Readout will turn red or amber if outside normal operating limits. Digits will appear in inverse video. r The Pressurization system will be in high altitude mode if Takeoff or Destination Elevation > 8000 feet and airplane is below 24,500 feet. o Cabin Altitude may not be displayed when the airplane is on the ground. CABIN ALTITUDE RATE Scale Markings Digital Readout ..Green ....EntireRange CABIN DIFFERENTIAL PRESSURE Pointer / Digital ReadouV ScaleMarkings ..RedBand. .....8.6T010PS1 GreenBand. . <B.SPSI NOTE The Pointer and Digital Readout will turn red or amber if outside normal operating limits. Digits will appear in inverse video. OTHER INSTRUMENTS StandbyAirspeed Indicator .....Red Line.. .....250 KIAS (0.63 Mach) Hydraulic Accumulator Pressure Indicator Per Placard According to Temperature Emergency Brake Pneumatic Pressure Indicator . Per Placard According to Temperature Emergency Gear Pneumatic Pressure lndicator . . Per Placard According to Temperature Fire Bottle Pressure lndicator . . . . Per Placard According to Temperature Oxygen Pressure Indicator .. ...Red Line. . . . . 2000 PSI AmberArc.. .....0to400PS| FAA APPROVED 510FM-05 Configuration AA U.S. 2-27 SECTION II . OPERATING LIMITATIONS SUPPLEMENTAL OXYGEN SYSTEM MODEL 510 Service the oxygen system with Aviator's Breathing Oxygen (M\L-O-27210). The use of medical oxygen is prohibited. For single pilot operations, a crew oxygen mask must be available for a passenger occupying the right crew seat. The mask must be checked during preflight and passenger briefed on its use. The following aircraft certification requirements are in addition to the requirements of applicable operating rules. The most restrictive requirements (certification or operating) must be observed: 1. Crew and passenger oxygen masks are not approved for use above 4O,OO0 feet cabin altitude. Prolonged use of passenger masks above 25,000 feet cabin altitude is not approved. 2. The pressure demand crew oxygen masks must be properly stowed in their containers to qualify as a quick-donning oxygen mask. WARNING O SOME LARGE EYEGLASSES, HEADSETS, HATS AND HAIRSTYLES MAY INTERFERE WITH THE QUICK DONNING CAPABILITY OF THE MASK. IT IS THE CREW MEMBERS RESPONSIBILITY TO ENSURE THE MASK CAN BE DONNED QUICKLY. . PASSENGER MASKS ARE INTENDED FOR USE DURING AN EMERGENCY DESCENT TO AN ALTITUDE NOT REQUIRING SUPPLEMENTAL OXYGEN. STALL WARNING AND LOW SPEED AWARENESS SYSTEMS The low airspeed awareness system can be used as a reference for approach speed (Vpgp) at all airplane weights, CG locations, anti-ice/deice system settings and flap positions. Vpgp is indicated by a green circle on the pilot and copilot airspeed indicators. The low speed awareness system may be used as a reference, but does not replace the airspeed display in the PFD as a primary instrument. FM APPROVED 510FM-05 I 2-28 U.S. Configuration AA TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE Publication Affected: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 6, dated 29 February 2008. Airplane Serial Numbers Affected: Description of Change: Filing Instructions: Removal Instructions: Airplanes 510-0001 thru -0065 incorporating S8510-34-02 and Airplanes 510-0066 and On. Section ll, Operating Limitations, Garmin G1000 Avionics System, change reference to software load. Insert this temporary change in the Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 2-29. This temporary change must be removed and discarded when Revision 7 has been collated into the basic FAA Approved Airplane Flight Manual. ln Section ll, Operating Limitations, page 2-29, Garmin G1000 Avionics System, change ltem 2 to read as follows: GARMIN GlOOO AVIOINICS SYSTEM 2. These limitations apply to Garmin system software version 0435.10, which includes GPS software version 2.4. and GPS Antenna Model's GA36/37 or GA56A/57. APPROVED BY bd*rd rndAacsilrt CffiAltrdCorpryry DOA#0604€E 5.*-*G,4- Ac(DOAAffiSST & DATE OF APPROVAL 3o Apptt- zs>B 51oFM TC-R06-01 TEMPORARY FAA APPROVED AIRPLANE FLIGHT MANUAL CHANGE Publication Affected: Airplane Serial Numbers Affected: Description of Change: Filing Instructions: Removal Instructions: Model 510 Citation Mustang (510-0001 and On) basic FAA Approved Airplane Flight Manual, Revision 6, dated 29 February 2008. Airplanes 510-0001 and On not incorporating SL510-34- 04. Section ll, Operating Limitations, Garmin G1000 Avionics System, add a limitation. Insert this temporary change in the Model 510 (510-0001 and On) basic FAA Approved Airplane Flight Manual adjacent to page 2-29. This temporary change must be removed and discarded when SL510-34-04 has been complied with or when Revision 7 has been collated into the basic FAA Approved Airplane Flight Manual. ln Section ll, Operating Limitations, page 2-29,Garmin G1000Avionics System, and a new ltem 15 to the list of limitations as shown below: GARMIN GlOOO AVIONICS SYSTEM 15. Flight operations are prohibited over large bodies of sea level water if that flight is conducted under operating regulations that require a functioning TAWS. CAUTION TAWS-B Forward Looking Terrain Avoidance (FLTA) is not available when flying over the open ocean/sea (specifically any body of water at sea level, more than 6 NM from any terrain features) until terrain database 08T2 or later is installed. Do not use TAWS-B information for primary terrain avoidance. TAWS-B is intended only to enhance situational awareness. APPROVED BY HASX}E UTN fl CR Nf,T 2I SHf,rJ OnH& o-tsrortoaffirmfll{E 4.d*A6**A-.mrhrt* sf DATE OF APPROVAL oB 4t{ ztloa 51OFM TC-R06-03 MODEL 5{O SECTION II . OPERATING LIMITATIONS GARMIN G1OOO AVIONICS SYSTEM 1. The Garmin G1000 Cockpit Reference Guide for the Cessna Citation MUSTANG, 190-00600-01, Rev B, dated April 2007, or later applicable revision, must be immediately available to the flight crew. 2. These limitations apply to Garmin system software version 0435.09, which includes GPS software version 2.4, and GPS Antenna Model's GA36/37 or GA56A/57. 3. Category ll approaches are prohibited. 4. Dispatch is prohibited following a flight where either a PFD/MFD COOLING or GIA 1-2 COOLING Garmin System Message was displayed, until the condition is identified and corrected. 5. Dispatch is prohibited with a PFD/MFD SERVICE, GIA 1-2 SERVICE, or GMA 1-2 SERVICE Garmin System Message displayed, until the condition is identified and corrected. All display units must be installed and operational. Dispatch with a display in reversionary mode is prohibited. Autopilot: a. One pilot must remain seated, with the seatbelt fastened, during all autopilot operations. b. Autopilot operation is prohibited if either PFD is in AHRS reversion. c. AutopilotMinimum-Use-Height: (1) Takeoff, and Climb ...700feetAGL (2) Enroute and Descent................ 1000 feet AGL (3) Approach (GP or GS Mode).. .....200 feet AGL (4) Approach (FLC, VS, PIT or ALT Mode) Higher of 400 feet AGL or Approach MDA Use of VNAV is prohibited during an approach with a teardrop course reversal. VNAV will fail at the beginning of the teardrop. Use of the NAVIGATION MAP page for pilotage navigation is prohibited unless required by AFM procedure. The NAVIGATION MAP is intended only to enhance situational awareness. Navigation is to be conducted using only current charts, data, and authorized navigation facilities. Use of the TMFFIC MAP to maneuver the airplane to avoid trafric is prohibited. The TRAFFIC INFORMATION SYSTEM (TlS) is intended for advisory use only. TIS is intended only to help the pilot to visually locate traffic. lt is the responsibility of the pilot to see and maneuver to avoid traffic. Use of the TERRAIN information for primary terrain avoidance is prohibited. The TERRAIN information is intended only to enhance situational awareness. lt is the pilot's responsibility to provide terrain clearance at all times. Use of the WEATHER MAP (XM Weather) for hazardous weather (thunderstorm) penetration is prohibited. LTNG information on the NAVIGATION MAP or WEATHER MAP is approved only as an aid to hazardous weather avoidance, not penetration. The fuel quantity, fuel required, fuel remaining, and gross weight estimate functions of the G1000 are supplemental information only and must be verified by the flight crew. 6. 7. 8. 9. 10. FAA APPROVED 510FM-05 11. 12. 13. 14. Configuration AA U.S. 2-29 SECTION II . OPERATING LIMTTATIONS GARMIN GIOOO GPS NAVIGATION SYSTEM MODEL 510 OPERATIONAL APPROVALS The Garmin G1000 GPS receivers are approved underTSO C145a Class 3. The Garmin G1000 system has been demonstrated capable of, and has been shown to meet the accuracy requirements for, the following operations provided it is receiving usable navigation data. These do not constitute operational approvals. 1. Enroute, terminal, non-precision instrument approach operations using GPS and WAAS (including "GPS', "or GPS", and "RNAV" approaches), and approach procedures with vertical guidance (including "LNAVA/NAV", "LNAV + V", and 'LPV.) within the U.S. National Airspace System in accordance with AC 20-138A. 2. As a required Long Range Navigation (LRN) system for use in the following types of airspace when used in conjunction with Garmin WMS Fault Detection/Exclusion Prediction Program, part number 006-40154-01 or later approved version: a. Oceanic/Remote - RNP-10 (per FAA AC 20-138A, FAA Notice 8110-60, FAA Order 8400-12A, and FAA Order 8700-1). Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range vigation (LRN) sensor. NOTE Each display computes an independent navigation solution based on the on-side GPS sensor. However, either display will automatically revert to the cross-side sensor if the on-side sensor fails or if the cross-side sensor is determined to be more accurate. A'BOTH ON GPSI" or "BOTH ON GPS2" message does not necessarily mean that one GPS has failed. Refer to the MFD AUX-GPS STATUS page to determine the status of the unused GPS. b. North Atlantic (NAT) Minimum Navigational Performance Specifications (MNPS) Airspace per AC 91-49 and AC 120-33. Both GPS receivers are required to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor. c. Enroute and Terminal including RNPS/BRNAV and PRNAV (RNP-1) - In accordance with JAA TGL-10, ACJ 20X4, AC 90-96A, and AC 90-100A, provided the FMS is receiving usable navigation information from one or more GPS receivers. LIMITATIONS 1. GPS based IFR enroute, oceanic, and terminal navigation is prohibited unless the pilot verifies the currency of the database or verifies each selected waypoint for accuracy by reference to current approved data. 2. RNAV/GPS instrument approaches must be accomplished in accordance with approved instrument approach procedures that are retrieved from the G1000 navigation database. The G1000 database must incorporate the current update cycle. NOTE Not all published approaches are in the navigation database. The flight crew must ensure that the planned approach is in the database. (Continued Next Page) Configuration AA FAA APPROVED 510FM-05 I 2-30 U.S. MODEL 510 SECTION II . OPERATING LIMITATIONS GARMIN G1000 GPS NAVIGATION SYSTEM (continued) a. Receiver Autonomous lntegrity Monitoring (RAIM) must be available when conducting instrument approaches utilizing the GPS receiver. b. IFR non-precision approach approval is limited to published approaches within the U.S. National Airspace System. Approaches to airports in other airspace are not approved unless authorized by the appropriate governing authority. c. Use of the Garmin G1000 GPS receiver to accomplish lLS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for GPS overlay is not authorized. 3. Operation in airspace referenced to a datum other than WGS-84 or NAD-83 is prohibited. 4. RNP operations are not authorized except as noted in the Operational Approvals section. 5. The installed Garmin GTX-33D Mode-S transponder system satisfies the data requirements of ICAO Document 703014, Regional Supplementary Procedures for SSR Mode S Enhanced Surveillance in designated European airspace. The capability of the GTX-33D to transmit specific Mode-S, Level 2 data parameters is shown in column 2 of the following table (marked as applicable): PARAMETER AVAILABLE / NOT AVAILABLE Magnetic Heading Available Indicated Airspeed Available Mach Number Available Vertical Rate Available RollAngle Available Track Angle Rate Not Available True Track Angle Available Ground Speed Available Selected Altitude Available True Airspeed Available FAA APPROVED 510FM-06 Configuration AH U.S. 2-31 SECTION II . OPERANNG LIMITATIONS STANDBY INSTRUMENTS MODEL 5{O FAA APPROVED 510FM-06 The standby flight instruments (including ATT, ALT and ASI) must successfully complete the preflight test defined in the Normal Procedures section and be functioning prior to takeoff. AHRS AREAS OF OPERATION Navigation using the G1000 is not authorized north of 70o North latitude or south of 70o South Latitude due to unsuitability of the magnetic fields near the Earth's poles. In addition, operations are not authorized in the following two regions: 1. North of 65' North latitude between longitude 75o W and 120o W (Northern Canada). 2. South of 55' South latitude between longitude 120" E and 165' E (region south of Australia and New Zealand). Dispatch is prohibited with the GEo LlMlrs Garmin system message displayed. ICE AND RAIN PROTECTION ln icing conditions, the airplane must be operated, and its ice protection systems must be used, as described in Section lll, Normal Procedures, ICE PROTECTION SYSTEMS. Specific operational speeds and performance information must be used where established for such conditions. The ENGINE ANTI-ICE switches must be selected ON at a RAT of +10"C (50.F) or colder when in visible moisture. WING/STAB deice must be selected to AUTO at the first sign of ice accretion anywhere on the airplane. Except for the ground preflight check, maximum RAT for operation of engine anti-ice with the throttles above idle is +20"C (+68'F). Limit the ground operation of the pitot-static heat to two minutes to preclude damage to the pitot tubes and stallwarning vane. The airplane must be free of ice prior to takeoff. Anti-ice systems must not be used to deice engine inlets prior to takeoff. Dispatch with polished frost is prohibited. CAUTION TO PREVENT POSSIBLE ENGINE DAMAGE FROM INGESTION OF ICE, DO NOT CHIP OR SCRAPE ICE OR SNOW FROM THE ENGINE AIR INLET. DEICE THESE AREAS PRIOR TO START. Minimum airspeed for sustained flight in icing conditions (except takeoff, approach and landing) is 160 K|AS. In icing conditions, operation at other than flaps UP and landing gear retracted is prohibited except during approach and landing. The use of wing or tail de-ice boots is prohibited below -30'C RAT. | 2-32 U.S. Configuration AA MODEL 510 SECTION II. OPERATING LIMITATIONS GARMIN G1000 GPS NAVIGATION SYSTEM (continued) a. Receiver Autonomous Integri$ Monitoring (RAIM) must be available when conducting instrument approaches utilizing the GPS receiver. b. IFR non-precision approach approval is limited to published approaches within the U.S. National Airspace System. Approaches to airports in other airspace are not approved unless authorized by the appropriate governing authority. c. Use of the Garmin G1000 GPS receiver to accomplish lLS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for GPS overlay is not authorized. 3. Operation in airspace referenced to a datum other than WGS-84 or NAD-83 is prohibited. 4. RNP operations are not authorized except as noted in the OperationalApprovals section. 5. Use of the Garmin G1000 system for GPS or WAAS navigation under Instrument Flight Rules (lFR) requires that: a. The airplane must be equipped with an approved and operational alternate means of navigation appropriate to the route being flown (NAV receiver, DME or ADF). b. For flight planning purposes, if an alternate airport is required, it must have an approved instrument approach procedure, other then GPS or RNAV that is anticipated to be operational and available at the estimated time of arrival. All equipment required for this procedure must be installed and operational. c. For procedures requiring a prediction of GPS integrity monitoring (RAIM) capability for TSO-C129a (non-WAAS) equipment (e.g. oceanic operations, U.S. RNAV routes, European BRNAV and PRNAV etc.), the Garmin WAAS Fault Detection/Exclusion Prediction program (006-A0154-01 or later approved version) should be used to confirm the availability of RAIM for the intended route and time of flight. Generic prediction tools do not provide an accurate indication of RAIM availability for the Garmin G1000 system. d. When flight planning an LNAVA/NAV or LPV approach, the Garmin WAAS Fault Detection/Exclusion Prediction program (006-40154-01 or later approved version) should be used in addition to any NOTAMS issued from the approach. 6. The installed Garmin GTX-33D Mode-S transponder system satisfies the data requirements of ICAO Document 703014, Regional Supplementary Procedures for SSR Mode S Enhanced Surveillance in designated European airspace. The capability of the GTX-33D to transmit specific Mode-S, Level 2 data parameters is shown in column 2 of the following table (marked as applicable): PARAMETER AVAILABLE / NOT AVAILABLE Magnetic Heading Available Indicated Airspeed Available Mach Number Available Vertical Rate Available RollAngle Available Track Angle Rate Not Available True Track Angle Available Ground Speed Available Selected Altitude Available True Airspeed Available FAA APPROVED 510FM-06 Configuration Al U.S. 2-31.1 SECTION II . OPERATING LIMITATIONS MODEL 510 STANDBY INSTRUMENTS The standby flight instruments (including ATT, ALT and ASI) must successfully complete the preflight test defined in the Normal Procedures section and be functioning prior to takeoff. AHRS AREAS OF OPERATION Navigation using the G1OO0 is not authorized north of 70o North latitude or south of 70' South Latitude due to unsuitability of the magnetic fields near the Earth's poles. In addition, operations are not authorized in the following two regions: 1. North of 65" North latitude between longitude 75" W and 12Oo W (Northern Canada). 2. South of 55o South latitude between longitude 120" E and 165o E (region south of Australia and New Zealand). Dispatch is prohibited with the GEO LIMITS Garmin System message displayed. ICE AND RAIN PROTECTION In icing conditions, the airplane must be operated, and its ice protection systems must be used, as described in Section lll, Normal Procedures, ICE PROTECTION SYSTEMS. Specific operational speeds and performance information must be used where established for such conditions. The ENGINE ANTI-ICE switches must be selected ON at a RAT of +10'C (50'F) or colder when in visible moisture. WING/STAB deice must be selected to AUTO at the first sign of ice accretion anywhere on the airplane. Except for the ground preflight check, maximum RAT for operation of engine anti-ice with the throttles above idle is +20"C (+68'F). Limit the ground operation of the pitot-static heat to two minutes to preclude damage to the pitot tubes and stallwarning vane. The airplane must be free of ice prior to takeoff. Anti-ice systems must not be used to deice engine inlets prior to takeoff. Dispatch with polished frost is prohibited. CAUTION TO PREVENT POSSIBLE ENGINE DAMAGE FROM INGESTION OF ICE, DO NOT CHIP OR SCRAPE ICE OR SNOW FROM THE ENGINE AIR INLET. DEICE THESE AREAS PRIOR TO START. Minimum airspeed for sustained flight in icing conditions (except takeoff, approach and landing) is 160 K|AS. In icing conditions, operation at other than flaps UP and landing gear retracted is prohibited except during approach and landing. The use of wing or tail de-ice boots is prohibited below -30'C RAT. FAA APPROVED 510FM-06 I 2-32 U.S. Configuration AA MODEL 510 SECTION II. OPERATING LIMITATIONS OPERATIONS IN SEVERE ICING GONDITIONS WARNING SEVERE ICING MAY RESULT FROM ENVIRONMENTAL CONDITIONS OUTSIDE OF THOSE FOR WHICH THE AIRPLANE IS CERTIFIED. FLIGHTIN FREEZING RAIN, FREEZING DRIZZLE, OR MIXED ICING coNDrTtoNS (SUPERCOOLED LIQUID WATER AND ICE CRYSTALS) MAY RESULT IN ICE BUILD.UP ON PROTECTED SURFACES EXCEEDING THE CAPABILITY OF THE ICE PROTECTION SYSTEM, OR MAY RESULT IN ICE FORMING AFT OF THE PROTECTED SURFACES. THIS ICE MAY NOT BE SHED WHEN USING THE ICE PROTECTION SYSTEMS, AND MAY SERIOUSLY DEGRADE THE PERFORMANCE AND CONTROLLABILITY OF THE AIRPLANE. During flight, severe icing conditions shall be determined by the following visual cues: 1. Unusually extensive ice accumulation on the airframe and windshield in areas not normally observed to collect ice. 2. Accumulation of ice on the upper surface of the wing aft of the edge of the boot. lf one or more of these visual cues exist: Use of the autopilot is prohibited. lmmediately request priority handling from Air Traffic Control to facilitate a route or altitude change to exit the icing conditions. Leave flaps in current position, do not extend or retract. Avoid abrupt and excessive maneuvering that may exacerbate control difficulties. lf unusual or uncommanded roll control movement is observed, reduce angle-of attack. Since the autopilot, when installed and operating, can mask tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when: 1. Unusual lateral trim is required while the airplane is in icing conditions. 2. Autopilot trim warnings are encountered while the airplane is in icing conditions. 1. 2. 3. 4. 5. FAAAPPROVED 510FM-06 Configuration AA U.S. 2-33 SECTION II . OPERATING LIMITATIONS MODEL 510 KINDS OF OPERATIONS EQUIPMENT LIST This airplane may be operated in day or night VFR or IFR and flight into known icing conditions when the appropriate equipment is installed. The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated. The systems and items of equipment listed must be installed and operable unless: 1. The airplane is approved to be operated in accordance with a current Minimum Equipment List (MEL) issued by the FAA. Or; 2. An alternate procedure is provided in the basic FAA Approved Airplane Flight Manual for the inoperative state of the listed equipment and all limitations are complied with. NOTE The following systems and equipment list does not include all equipment required by the 14 CFR Parts 91 and 135 Operating Requirements. lt also does not include components obviously required for the airplane to be airworthy such as wings, primary flight controls, empennage, engine, etc. (Continued Next Page) FAAAPPROVED 510FM-04 System and/or Component KIND OF OPERATION COMMENTS V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I c I N G AUTO FLIGHT Autopilot (1) Yaw Damper (1) 3 - Electric Elevator Trim (1) 4 - Yoke Autopilot Disconnect Switches (2) 0* 0* 0 1* 0" 0* 0 1* 0* 0* 0 1* 0* 0* 0 1* 0* 0* 0 1* " Required for single pilot operation and in RVSM airspace. * Required above FL300. Autopilot will be inoperative with inoperative yaw damper. Manual elevator trim must be operational. * Left side is required for single pilot operations. Both sides required for two crew operation. ** These items are part of the Engine Indicating and Crew Alerting System (EICAS) displayed on the MFD. 2-34 U.S. Configuration M MODEL 510 KINDS OF OPERATIONS SECTION II. OPERATING LIMITATIONS EQUIPMENT LIST (continued) System and/or Component KIND OF OPERATION COMMENTS V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I c I N G AIR CONDITIONING / PRESSURIZA 'loN 1 - Flow ControlValves (2) 2 - Pressure Regulating Shutoff Valves (2) 3 - Cabin Outflow Valves (2) 4 - Cabin Differential Pressure Gauge ** (1) 5 - Cabin Altitude Warning System (1) 6 - Cabin Altitude Display ** (1) 7 - Cabin Differential Pressure Display *. (1) I - Cockpit Temperature Control System (except Air Conditioner) (1) 9 - Cabin Temperature Control System (except Air Conditioner (1) 10 - Air conditioning System (1) 11 - Pressurization Control System (1) 12 - Cockpit Fan (1) 13 - Cabin Fan (1) 14 - Fresh Air Fan (1) 15 - Glareshield Avionics Fans (3) 16 - Emergency Pressurization Dump System (1) 2 2 2 1 1 1 1 I 1 0* 1 1 ', 1 3 1 2 2 2 1 1 1 1 1 1 0* 1 1 1 1 3 1 2 2 2 1 ,l 1 1 1 1 0* 1 1 1 1 3 1 2 2 2 1 1 1 1 1 1 0* 1 1 1 1 3 1 2 2 2 1 'l 1 1 1 ,l 0* 1 1 1 1 3 1 *Temperature limits reduced with inoperative air conditioner. Refer to Figure 2-13. These items are part of the Engine Indicating and Crew Alerting System (EICAS) displayed on the MFD. FAA APPROVED 510FM-03 (Continued Next Page) Configuration AA U.S. 2-35 MODEL 510 SECTION II . OPERATING LIMITATIONS KINDS oF OPERATIONS EQUIPMENT LIST (continued) System and/or Component KIND OF OPERATION COMMENTS V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I c I N G COMMUNICATIONS Communication Systems (vHF)(2) Audio Control Panels (Pilot and Copilot)(2) Static Wicks (16) 3- 4 - Hand Microphone (1) * 1* 14* 1 * 'l* 14* 1 1* 'l* 14* 1 1* 1* '14* 1 1* 1* 14* 1 " Or as required by operating regulation * Left side is required for single pilot operations. Both sides required for two crew operation. * One may be missing from any control surface. No more than 2 total may be missing. -LECTRICAL POWER 1 - DC Generator (2) 2 - DC Generator VOLTS Display.* (2) 3 - DC Generator AMPS Display." (AMPS) (2) 4 - Main Battery (1) 5 - Battery VOLTS Display ** (1) 6 - Battery AMPS Display ** (1) 7 - Battery Temperature Monitoring System (1) I - Standby Instrument Battery (1) 2 2 2 1 1 ,l 1* 1 2 2 2 1 1 1 1* 1 2 2 2 1 1 1 1* ,l 2 2 2 1 1 1 1* 1 2 2 2 1 1 1 1* ,l * Required only with NiCad battery option. EQUIPMENT / FURNISHINGS 1 - Passenger Seat Belts (4) 2 - Crewmember Seat Belts (2) 3 - Aircraft Emergency Locator Transmitter (ELT) (1) 't* * * 1* * 1* * 1* * 1* * * One per occupied seat * Left side required. Right side may be inoperative if seat is not occupied. * These items are part of the Engine Indicating and Crew Alerting System (EICAS) OisptayeO on tne tvtfO. (Continued Next Page) I 2-36 FAA APPROVED 510FM-03 U.S. Configuration AA MODEL 510 KINDS OF OPERATIONS SECTION II . OPERATING LIMITATIONS EQUIPMENT LIST (continued) System and/or Component KIND OF OPERATION COMMENTS V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I c I N G IRE PROTECTION 1- Engine Fire Detection System (2) 2 - Engine Fire Extinguishing System (1) 3 - Portable Fire Extinguisher (1) 2 1 1 2 1 'l 2 1 1 2 I I 2 1 1 FLIGHT CONTROLS 1 - Flap System (1) 2- Flap Position Indicator ** (1) 3 - Trim Systems - Elevator, Aileron, Rudder (3) 4 - Trim Position Indicator Systems - Elevator, Aileron **, Rudder ** 5 - Speed Brake System (1) 1 1 3 3 1 1 1 3 3 ,l ,| 1 3 3 1 1 1 3 3 I 1 1 3 3 1 IncludesLandRsides. ICE AND RAIN PROTECTION I - Engine Anti-lce Systems (2) 2 - Engine T2 Heaters (2) 3 - Tail De-lce Boot System (3) 4 - Wing De-lce Boot System (2) 5 - Windshield Anti-lce Systems (2) 6 - Pitot Probe Heaters (2) 7 - Static Port Heaters (4) I - Stall Warning Heater (1) 2 2 0 2 1* 2 4 1 2 2 0 2 1" 2 4 1 2 2 0 2 1* 2 4 1 2 2 0 2 1" 2 4 1 2 2 3 2 2 2 4 1 lncludes L and R horizontal tail and verticaltail boots. Includes L and R wing boots. *Left side required for ground defog. '* These items are part of the Engine Indicating and Crew Alerting System (EICAS) displayed on the MFD. I FAA APPROVED 510FM-05 (Continued Next Page) Configuration AA u.s. 2-37 sEcToN il - opERAnNG LtMtTAflONS MODEL 510 KINDS OF OPERATIONS EQUIPMENT LIST (continued) (Continued Next Page) FAA APPROVED 510FM-03 System and/or Component KIND OF OPERATION COMMENTS V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I c I N G NDICATING / RECORDING SYSTEMS 1 - MASTER WARNING Switch/ Lights (2) 2 - MASTER CAUTION Switch/ Lights (2) 3 - StallWarning System (1) + - AuralWarning Systems 1* 1* 1 * 1* 1* 1 * 1* 1* 1 * 1* 1* 1 1* 1* 1 * *Left side is required for single-pilo1 operations. Both sides required for two. crew operation. *Left side is required for single-pilo1 operations. Both sides required for two. crew operation. AllAudio warnings must be operational. -ANDING GEAR / BRAKES 2- Landing Gear Position Indicators (3) Landing Gear UNSAFE lndicator (1) Landing Gear Warning System (1) Emergency Landing Gear Extension System (1) Power Brake System (1) Antiskid System (1) Emergency Brake System (1) Hydraulic Power System* 3- 4- 5- 6- 7- 8- 3 1 1 'l 1 0* 1 1 3 1 1 1 1 0* 1 1 3 1 1 1 1 0* 1 1 3 1 1 1 1 0* 'l 1 3 ,l 1 1 1 0* 1 1 * For inoperative antiskid, refer to Abnormal Procedures, DISPATCH WITH ANTISKID INOPERATIVE * Includes pump, indications accumulator. and | 2-38 U.S. Configuration AA MODEL 510 SECTION II. OPERATING LIMITATIONS KINDS OF OPERATIONS EQUIPMENT LIST (continued) I FAA APPROVED I 510FM-05 (Continued Next Page) Configuration AA System and/or Component KIND OF OPERATION COMMENTS V F R D A Y V F R N I G H T I F R D A Y I F R N I G H T I c I N G IGHTS 1- Anti-Collision Light System (Wing Strobes) (2) 2 - Flashing Beacon Light (1) 3 - Position Light System (2) 4 - Landing/Recognition Lights (2) 5 - Fasten Seat Belt Sign (1) 6 - Cabin Emergency Lights (2) 7 - Cockpit and Instrument Lighting Sytems (1) B - Windshield lce Detection Lishts (2) I - Wing lce Detection Light (1) 0 0" 0 0 1* 0 0 0 0 2 0 2* 2 1* 2 1 0 0 0 0* 0 0 1* 0 0 0 0 2 0 2* 2 1* 2 1 2* 1* 0 0 0 0 1* 0 0 2 1 * May be inoperative only if Anti-Collision Light System is operational. " All red, green, & white segments as appropriate must be operational. * May be inoperative only if no passengers carried in cabin. One light each by cabin door and emergency exit. Required for night ice detection Required for night ice detection \AVIGATION 1 - Primary Flight Display (PFD) (2) 2 - Multi-Function display (MFD) (1) 3 - Air Data Computers (ADC) (2) 4 - AttitudeiHeading Reference System (AHRS) (2) 5 - Standby Airspeed Indicator (1) 6 - Standby Attitude Indicator (1) 2 1 2 2 I 1 2 1 2 2 I 1 2 1 2 2 1 I 2 1 2 2 1 1 2 1 2 2 1 1 U.S. 2-39 SECTION II . OPERATING LIMITATIONS KINDS OF OPERATIONS EQUIPMENT LIST (continued) MODEL 510 FAAAPPROVED 510FM-03 a 2-40 System and/or Component KIND OF OPERATION COMMENTS V F R D A Y N I G H T V F R D A Y I F R I F R N I G H T I c I N G NAVIGATION (Continued) 7 - Standby Altimeter (1) 8 - Magnetic Compass (1) 9 - ATC Transponder (2) 10 - VHF Nav Receiver (2) 11 - GPS Receivers (2) 12 - Automatic Direction Finder (ADF)(Optional) 13 - Distance Measuring Equipment (DME) (1) 14 - Marker Beacon Receiver (2) 15 - TAWS (1) 16 - Weather Radar (1) 17 - XM Datalink Weather (1) 1 1 0* 0 0 0* 0* 0* 0* 0 0 1 1 0* 0 0 0* 0* 0* 0* 0 0 1 1 1* 1" 1* 0* 0* 0* 0* 0 0 1 1 1* 1* 1* 0* 0* 0* 0" 0 0 1 1 1" 1* 1* 0* 0* 0* 0* 0 0 * Or as required by operating regulation " Or as required by operating regulation * Or as required by operating regulation * Or as required by operating regulation " Or as required by operating regulation * Or as required by operating regulation * Or as required by operating regulation XYGEN 1 - Oxygen System including Pressure Gauge (1) 2- Passenger Oxygen System (4) 3 - Crew Oxygen Masks (2) 1 * 1* 1 * 1* I * 'l* 1 * 1* 1 * 1* Required if unpressurized or for flight above FL240. * lf any passenger seat is occupied, the number of installed masks must equal the number of passenger seats plus one. * Left side required. Right side required only if seat is occupied. DOORS 1- Cabin DoorSeal (1) I 1 1 1 1 (Continued Next Page) U.S. Configuration AA MODEL 510 KINDS OF OPERATIONS EQUIPMENT SECTION II. OPERATING LIMITATIONS LIST (continued) :NGINE FUEL AND CONTROL 1 - Fuel Boost Pumps (2) 2 - Fuel Quantity Indications** (2) 3 - Fuel Flow Indications.. (2) 4 - Fuel Temperature System ** (1) 5 - Fuel Transfer System (1) 6 - Firewall Shutoff System (2) 7 - Engine Driven Fuel Pump (2) I - Engine FADEC. (2) 9 - Dual lgniter System Indications ** (2) 10 - Engine Indications (Nl, N2, Oil Pressure, and Temperature) ** 11 - Engine Synchronizer System (1) and ITT, oil 2 2 2 I I 2 2 2 2 2 0 2 2 2 1 I 2 2 2 2 2 0 2 2 2 1 1 2 2 2 2 2 0 2 2 2 1 1 2 2 2 2 2 0 2 2 2 1 1 2 2 2 2 2 0 " Both channels of each FADEC must be operational. One dual ignitor system per engine. MISCELLANEOUS EQUIPMENT 1- FAA Approved Airplane Flight Manual 2 - Garmin G1000 Cockpit Reference Guide 3 - Passenger Briefing Cards 4 - Weight and Balance Manual 1 1 * 1 1 1 * 1 1 ,| 1 1 1 * 1 1 1 * 1 Accessible to pilot in flight Accessible to pilot in flight * One for each occupied passenger seat SINGLE PILOT The following are required when the airplane is operated with a crew of one pilot; per applicable operating rules: 1 - Operable GFC-700 Autopilot. 2 - Headset with microphone (must be worn). 3 - FAA Approved Pilots'Abbreviated Normal Procedures Checklist, Cessna PN 510CLNP-03 or later approved revision. 4 - FAA Approved Pilots' Abbreviated Emergency and Abnormal Procedures Checklist, Cessna PN 510CLEAP-03 or later approved revision. 5 - Provisions for storage and retention of navigation charts, accessible to the pilot from the pilol station. These items are part of the Engine Indicating and Crew Alerting System (EICAS) displayed on the MFD. FAA APPROVED 510FM-06 Configuration AA U.S. 2-41t2-42 t MODEL 510 SECTION III . OPERATING PROCEDURES GENERAL GENERAL OPERATING PROCEDURES . GENERAL The operating procedures contained in this manual have been developed and recommended by Cessna Aircraft Company and are approved for use in the operation of this airplane. This section contains the emergency, abnormal, and normal procedures for your airplane. For your convenience, definitions of these terms are listed in Section l. Operating procedures in this airplane flight manual are organized into EMERGENCY ABNORMAL, and NORMAL PROCEDURES. Normal procedures are those recommended for routine day-to-day preflight, flight, and postflight operation and include expanded systems information and procedures. Some checks, as noted in the Limitations Section of this airplane flight manual, are required to assure proper system integrity. The Garmin G1000 Integrated Avionics System monitors most of the airplane systems for faults or failures and displays this information to the crew as messages in the Crew Alerting System (CAS) portion of the Engine Indicating and Crew Alerting System (EICAS) in the center cockpit display. Some Garmin G1000 faults are also displayed as messages in the Primary Flight Display (PFD) or Multi Function Display (MFD). These messages are listed within the appropriate portion of the Emergency and Abnormal procedures sections, according to the color of each message. The engine fire detection system has separate panel annunciators. Emergency procedures are generallyassociated with red CAS messages, red Garmin G1000 messages, or separate red annunciators. Some procedures, such as Maximum Glide/Emergency Landing, are not associated with any particular message, but may involve one or more messages. All emergency procedures are organized by appropriate systems and include each red CAS or Garmin message if applicable exactly as it appears in the CAS, PFD, or MFD. Emergency procedures require immediate pilot recognition and corrective or compensatory action by the crew. Red CAS messages will flash and are accompanied by illumination of the MASTER WARNING lights. Pressing either MASTER WARNING light will reset the MASTER WARNING and change the CAS message to steady. Some emergency situations require immediate memorized corrective action. These numbered steps are printed in boxes within the emergency procedures and should be accomplished without the aid of the checklist. Abnormal procedures are general procedures that may be associated with one or more Amber CAS, or Garmin G1000 messages. Some procedures are not associated with any particular CAS or Garmin G1000 message but may involve one or more messages. These procedures are organized by related systems. An abnormal procedure is one requiring the use of special systems and/or the alternate use of regular systems that will maintain an acceptable level of airworthiness. These procedures require immediate crew awareness, and subsequent crew action will be required. Amber CAS messages will initially flash and are accompanied by illumination of the MASTER CAUTION lights. Pressing either MASTER CAUTION light will reset the MASTER CAUTION and change the CAS message to steady. (Continued Next Page) FAA APPROVED 510FM-00 Configuration AA U.S. 3-3 SECTION III . OPERATING PROCEDURES GENERAL OPERATING PROCEDURES - GENERAL (continued) o a MODEL 510 NOTE White CAS messages indicate an awareness and possible future pilot action. In order to avoid confusion due to multiple messages, redundant messages, and non-critical messages at criticaltimes, some CAS messages are inhibited during engine shutdown, during takeoff, landing, on the ground or in flight when that message would not be critical or would not be needed. Generally, the following Emergency and Abnormal procedures do not direct the pilot to checl</reset circuit breakers. This is considered basic airmanship and may be accomplished at the pilot's discretion. Except where specific action is required, these procedures do not specify action when "on the ground." Conditions resulting in a red or amber message should be corrected prior to flight. Reasons for white CAS messages should be determined prior to flight. lf a red or amber message occurs in flight, consideration should be given to landing at an airfield where corrective maintenance can be performed. FAA APPROVED 51oFM-00 3-4 U.S. Configuration AA I MODEL 510 sEcroN 'r .oPERArrtg il38E3ulE: EMERGENCY PROCEDURES TABLE OF CONTENTS PAGE ENGINE Engine Failure or Fire or Master Warning or Any Other Non-Normal Event During Takeoff . . . 3-7 Engine Failure During Approach (Possible ENGINE FAIL L-R CAS Message) . . . . . . 3-8 ENGFIRELoTR(ENGINEF|REWarningLightllluminated) .......3-9 EmergencyRestart-TwoEngines... ......3-11 AirstartEnvelope. ....3-13 MaximumGlide-Emergencylanding ......3-15 EngineSurgesorUnstableEngineOperation ......3-19 OIL PRESS LO L-R(LowOil Pressure, Red Pointerand Digits).... ......3-20 COCKPIT / CABIN / BAGGAGE FIRE Electrical FireorSmoke .....3-21 SmokeRemoval .....3-27 Environmental System SmokeorOdor. .....3-28 PRESSU RIZATION / ENVIRON M ENTAL Loss of Cabin Pressure (Red CABIN ALT CAS Message) . . . 3-29 Emergency Descent ..3-29 Tailcone Bleed Leak (Red TAIL CONE BLD LK CAS Message). . . . . 3-31 ELECTRICAL Battery Over-Temperature (Red BATTERY O'TEMP CAS Message). . . . . . . 3-32 DualGeneratorFailure(GENOFFL-RRedCASMessage).. .....3-35 FLIGHT CONTROLS Autopilot Malfunction (Possible Red AFCS on PFD) . 3-39 Pitch Trim Failure (Red PTRM on PFD) . . . . . 3-39 RollAxis Autopilot Failure (Red ROLL on PFD) . . . . . 3-39 Pitch Axis Autopilot Failure (Red PTCH on PFD) . . . . 3-39 Yaw Axis Autopilot Failure (Red YAW on PFD). . . . . . 3-39 AileronTrimRunaway... ....340 RudderTrimRunaway... ...3-40 Pitch Trim Runaway . . 3-40 HydraulicWheel BrakeFailure ......3-40 MISCELLANEOUS EmergencyEvacuation ......3-4'l Ditching ......342 InadvertentStall (Buffetand/orRoll-Off) .....343 FAAAPPROVED 510FM-05 U.S. Configuration AB 3-5/3-6 I MODEL 510 sEcroN ilr. oPERATNG FI3:EBUIES EMERGENCY PROCEDURES TABLE OF CONTENTS PAGE ENGINE Engine Failure or Fire or Master Warning or Any Other Non-Normal Event During Takeoff . . . 3-7 Engine Failure During Approach (Possible ENGINE FAIL L-R CAS Message) . . . . . . 3-8 ENG FIRELoTR(ENGINE F|REWarningLightllluminated) .......3-9 EmergencyRestart-TwoEngines ...3-11 AirstartEnvelope. ....3-13 MaximumGlide-Emergencylanding ......3-15 EngineSurgesorUnstableEngineOperation ......3-19 OIL PRESS LO L-R(LowOil Pressure, Red Pointerand Digits).... ......3-20 COCKPIT / CABIN / BAGGAGE FIRE Electrical FireorSmoke .....3-21 Smoke Removal . . .. .3-27 Environmental System SmokeorOdor. .....3-28 PRESSU RIZATION / ENVI RONMENTAL Loss of Cabin Pressure (Red CABIN ALT CAS Message) . . . 3-29 EmergencyDescent ..3-29 Tailcone Bleed Leak (Red TAIL CONE BLD LK CAS Message). . . . . 3-31 ELECTRICAL Battery Over-Temperature (Red BATTERY O'TEMP CAS Message). . . . . .3-33.1 DualGeneratorFailure(GENOFFL-RRedCASMessage).. .....3-35 FLIGHT CONTROLS Autopilot Malfunction (Possible Red AFCS on PFD) . 3-39 Pitch Trim Failure (Red PTRM on PFD) . . . . . 3-39 RollAxis Autopilot Failure (Red ROLL on PFD) . . . . . 3-39 Pitch Axis Autopilot Failure (Red PTCH on PFD) . . . . 3-39 Yaw Axis Autopilot Failure (Red YAW on PFD). . . . . . 3-39 AileronTrimRunaway... ....3-40 RudderTrimRunaway... ...340 Pitch Trim Runaway . . 3-40 HydraulicWheel BrakeFailure ......3-40 MISCELLANEOUS EmergencyEvacuation ......341 Ditching ,.....342 lnadvertentStall (Buffetand/orRoll-Off) .....3-43 FAAAPPROVED 510FM-05 Configuration AC U.S. 3-5.1/3-6 I I SECTION III . OPERATING PROCEDURES MODEL 5{o EMERGENcypRocEDUREs EMERGENGY PROCEDURES r ENGINE FAILURE OR FIRE OR MASTER WARNING OR ANY OTHER NON.NORMAL EVENT DURING TAKEOFF o SPEED BELOW Vl - TAKEOFF REJECTED 1. Takeoff - ABORT. a. Brakes - MAXIMUM PILOT EFFORT. b. Throttles - IDLE. c. Speed Brakes - EXTEND. d. Throttles - CUTOFF (if runway departure is imminent). tr IF ENGINE FIRE 2. Refer to Emergency Procedures, L or R ENGINE FIRE (Engine Fire Warning Light llluminated). Procedure Completed tr lF ENGTNE FATLURE (POSS|BLE ENGTNE FA|L L-R CAS MESSAGE) 2. Refer to Abnormal Procedures, ENGINE FAILURE / PRECAUTIONARY SHUTDOWN. NOTE ' To obtain maximum braking performance from the antiskid system, the pilot must apply continuous maximum effort (no modulation)to the brake pedals. ' The Takeoff Field Lengths assume that the pilot has applied maximum effort to the brakes at the scheduled V., speed during the aborted takeoff. Procedure Completed O SPEED ABOVE VT 'TAKEOFF CONTINUED 1. Climb to a safe altitude. a. Maintain directional control. b. ROTATE at Vp to +10' initial pitch attitude (use flight director TO mode). c. IANDING GEAR - UP (after positive rate-of-climb). d. Airspeed - V2 (single-engine) or AS REQUIRED (multi-engine). e. At 1500 feet AGL (minimum) and clear of obstacles - Retract flaps at Vz +10 and accelerate to Vr**. ! IF ENGINE FIRE INDICATIONS ARE PRE