CESSNA SECTION 2 MODEL 208B (867 SHP) … · model 208b (867 shp) operating limitations garmin...

CESSNA SECTION 2MODEL 208B (867 SHP) OPERATING LIMITATIONSGARMIN G1000

U.S.FAA APPROVED

OPERATING LIMITATIONS

TABLE OF CONTENTSPage

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-3Airspeed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-4Airspeed Indicator Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-5Powerplant Limitations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-6Powerplant Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . .2-10Miscellaneous Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . 2-11Preflight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-12Visual and Tactile Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-12Weight Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-13Center of Gravity Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-13Maneuver Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-14Flight Load Factor Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-14Flight Crew Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-14Kinds Of Operations Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-15Kinds of Operations Equipment List . . . . . . . . . . . . . . . . . . . . . . . .2-16Fuel Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-25Maximum Operating Altitude Limit . . . . . . . . . . . . . . . . . . . . . . . . . .2-28Outside Air Temperature Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-28Maximum Passenger Seating Limits . . . . . . . . . . . . . . . . . . . . . . . .2-28System and Equipment Limitations . . . . . . . . . . . . . . . . . . . . . . . . .2-29

Flap Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-29Standby Electric System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-29Aux Audio System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-2912V Power System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-29Generator Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-30G1000 Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-31Operational Approvals. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-33Garmin GFC-700 Automated Flight Control System (AFCS) . . .2-34L3 Communications WX 500 Stormscope. . . . . . . . . . . . . . . . . .2-35Sirius XM Weather . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2-35Traffic Advisory System (TAS). . . . . . . . . . . . . . . . . . . . . . . . . . .2-35Terrain Awareness and Warning System (TAWS-B) . . . . . . . . . .2-36

(Continued Next Page)

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SECTION 2 CESSNAOPERATING LIMITATIONS MODEL 208B (867 SHP)

GARMIN G1000

U.S.FAA APPROVED

TABLE OF CONTENTS (Continued)Page

Other Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-37Optional Equipment User’s Guide . . . . . . . . . . . . . . . . . . . . . . . 2-37Type II, Type III or Type IV Anti-ice Fluid Takeoff Limitations . . 2-37Flight in Known Icing Visual Cues . . . . . . . . . . . . . . . . . . . . . . . 2-38

Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-39Interior Placards. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-39Flight Crew Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-39Passenger Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-46Cargo Area . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-48Exterior Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-51Wings. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-54Engine Compartment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-56Forward Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-59Aft Fuselage. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-61

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U.S.FAA APPROVED

INTRODUCTIONSection 2 includes operating limitations, instrument markings, andbasic placards necessary for the safe operation of the airplane, itsengine, standard/non-standard systems and standard/non-standardequipment.

WARNING

The limitations included in this section and inSection 9 have been approved by the FederalAviation Administration. Observance of theseoperating limitations is required by FederalAviation Regulations.

NOTE• Operation in countries other than the United States may

require observance of other limitations, procedures orperformance data.

• Refer to Section 9, Supplements, of this POH/AFM foramended operating limitations, operating procedures,performance data and other necessary information forairplanes equipped with specific options.

• The airspeeds listed in Figure 2-1, Airspeed Limitations,and Figure 2-2, Airspeed Indicator Markings, are basedon Airspeed Calibration data shown in Section 5 with thenormal static source. If the alternate static source isbeing used, ample margins should be observed to allowfor the airspeed calibration variations between thenormal and alternate static sources as shown in Section5.

The Cessna Model No. 208B is certificated under FAA Type CertificateNo. A37CE.

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GARMIN G1000

U.S.FAA APPROVED

AIRSPEED LIMITATIONSThe airspeed limitations below are based on the maximum grosstakeoff weight of 8807 pounds (3994 kg). The maximum operatingmaneuvering speeds (VA) and applicable gross weight limitations areshown in Figure 2-1.

AIRSPEED LIMITATIONS

Figure 2-1

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U.S.FAA APPROVED

AIRSPEED INDICATOR MARKINGSThe airspeed on both the PFD and standby airspeed indicator isindicated with an airspeed tape with colored bands, refer to Section 7,Flight Instruments, for more information on airspeed indication. Theindicator markings and their color code significance are shown inFigure 2-2.

* G1000 airspeed indicator only.

Figure 2-2

AIRSPEED INDICATOR MARKINGS

208BPHCUS-00 2-5


GARMIN G1000

U.S.FAA APPROVED

POWERPLANT LIMITATIONS

ENGINEEngine Manufacturer . . . . . . . . . . . . . . Pratt & Whitney Canada Inc.

Engine Model Number . . . . . . . . . . . . . . . . . . . . . . . . . . . . PT6A-140

Engine Operating Limits . . . . . . . . . . . . . . . . . . Refer to Figure 2-3

Fuel Grade and Approved Fuel Additives . .Refer to Fuel Limitations

OIL SPECIFICATIONOil conforming to Pratt & Whitney Engine Service Bulletin No. 1001,and all revisions or supplements thereto, must be used. Refer toSection 8, Airplane Handling, Service and Maintenance, Servicing,Oil, for a listing of approved oils.When adding oil, service the engine with the type and viscositywhich is currently being used in the engine.

PROPELLERPropeller Manufacturer . . . . . . . . . . . . . . . . . . Hartzell Propeller Inc.Propeller Model Number . . . . . . . . . . . .HC-B3TN-3AF/T10890CN-2Propeller Diameter

Maximum. . . . . . . . . . . . . . . . . . . . . . . . . . . . 106 Inches (2.7 m)Minimum . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104 Inches (2.6 m)

Hartzell Propeller Blade Angle at 42-inch Station:Feathered . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78.0 + 1.0°Low Pitch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8.5 + 0.2°Maximum Reverse . . . . . . . . . . . . . . . . . . . . . . . . . . . -21 + 0.5°


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U.S.FAA APPROVED

POWERPLANT LIMITATIONS (Continued)

PROPELLER SYSTEM OPERATING LIMITSAn overspeed governor check shall be performed before the firstflight of the day, after engine control system maintenance, or ifadjustment has been made.

Propeller RPM must be set at 1900 during all instrumentapproaches.

ENGINE CONTROL OPERATING LIMITSFlight operation with the POWER Lever set below the IDLE positionis prohibited. Such positioning may lead to loss of airplane control ormay result in an engine overspeed condition and consequent loss ofengine power.

Operation of the EMERGENCY POWER Lever is prohibited with thePOWER Lever out of the IDLE position.

ENGINE STARTING CYCLE LIMITSUsing the airplane battery, the starting cycle shall be limited to thefollowing intervals and sequence:

30 seconds ON - 60 seconds OFF,30 seconds ON - 60 seconds OFF,30 seconds ON - 30 minutes OFF.

Repeat the above cycle as required.

Using external power, the starting cycle shall be limited to thefollowing intervals and sequence:

20 seconds ON - 120 seconds OFF,20 seconds ON - 120 seconds OFF,20 seconds ON - 60 minutes OFF.

Repeat the above cycle as required.


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GARMIN G1000

U.S.FAA APPROVED

POWERPLANT LIMITATIONS (Continued)

ENGINE OPERATING LIMITS

Figure 2-3 (Sheet 1 of 2)

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U.S.FAA APPROVED

POWER PLANT LIMITATIONS (Continued)

ENGINE OPERATING LIMITS (Continued)

NOTE1. Per Section 5, Performance, Figure 5-8, Maximum Engine

Torque for Takeoff. Anytime ITT exceeds 825°C, this powersetting is limited to 5 minutes.

2. For every 10°C (18°F) below -30°C (-22°F) ambienttemperature, reduce maximum allowable Ng by 2.2%.

3. Normal oil pressure is 85 to 105 PSI at Ng speeds above 72%with oil temperature between 60° and 70°C (140° and 158°F).Oil pressures below 80 PSI are undesirable and should betolerated only for the completion of the flight, preferably at areduced power setting. Oil pressures below normal should bereported as an engine discrepancy and should be correctedprior to next flight. Oil pressures below 40 PSI are unsafe andrequire that either the engine be shut down or a landing bemade as soon as possible using the minimum power requiredto maintain flight.

4. 2090 PROP RPM may be used in an emergency condition,to complete a flight, and may be utilized at all engine ratings.

5. Use of Maximum Rated Power Setting is intended forabnormal situations (e.g., maintain altitude or climb out ofsevere icing or windshear conditions).

6. Maximum transient oil temperature is 104°C for a maximum of10 minutes.

7. Per Section 5, Performance, Figures 5-9, Maximum EngineTorque for Climb.

8. Per Section 5, Performance, Figure 5-20, Cruise MaximumTorque with Cargo Pod Installed or Figure 5-37, CruiseMaximum Torque without Cargo Pod.

9. Increase Ng to keep idle ITT within limit.10. Torque must not exceed 2397 foot-pounds. Full 867 SHP

rating is available only at propeller RPM settings of 1900.11. A transient fluctuation of up to +40 PROP RPM is permitted to

account for power setting accuracy and steady statefluctuations. Note: Steady state Max Np setting is 1900 RPM.

Figure 2-3 (Sheet 2)

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GARMIN G1000

U.S.FAA APPROVED

POWERPLANT INSTRUMENT MARKINGSPowerplant instrument markings and their color code significance areshown in Figure 2-3. Operation with indications in the red range isprohibited. Avoid operating with indicators in the yellow range.

NOTE1. Incorporates dynamic redline that moves to display

maximum allowable torque as a function of OAT andpressure altitude. Takeoff torque is displayed up to 16,000 feetMSL, while maximum rated torque is displayed at 16,000 feetMSL and above.

2. Incorporates blue torque bug that moves to compensate forOAT, pressure altitude and propeller RPM variation.

3. Incorporates red line that moves to compensate for OAT.100% Ng is 37,468 RPM.

4. Start mode values also valid for OFF mode (red triangle at1090°C not shown in OFF mode).

5. Start mode is defined as the period between starterengagement and the point where idle Ng RPM reaches 55%.

6. Run mode is defined as anytime idle Ng RPM is above 55%.

Figure 2-4

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U.S.FAA APPROVED

MISCELLANEOUS INSTRUMENT MARKINGSPower plant instrument markings and their color significance are shownin Figure 2-5.

NOTE1. OFF mode is defined as anytime the engine is not running and

the starter has not transitioned to generator mode.

Figure 2-5

208BPHCUS-00 2-11


GARMIN G1000

U.S.FAA APPROVED

PREFLIGHTTakeoff is prohibited with any frost, ice, snow, or slush adhering to thewings, horizontal stabilizer, vertical stabilizer, control surfaces, propellerblades, and/or engine air inlets.

WARNING

Even small amounts of frost, ice, snow or slush onthe wing may adversely change lift and drag.Failure to remove these contaminants will degradeairplane performance and will prevent a safe takeoffand climb.

VISUAL AND TACTILE CHECKTo assure the absence of frost, a tactile check of the wing leading edgeand upper surface, as specified in Section 4, Normal Procedures, isrequired in addition to a visual inspection if the OAT is below 10°C(50°F). During ground icing conditions, takeoff must be accomplishedwithin 5 minutes of completing the tactile check unless the airplane isoperated per 14 CFR 135.227(b)(3).

Ground icing conditions are defined as:

1. The OAT is 2°C (36°F) or below and visible moisture is present(i.e. rain, drizzle, sleet, snow, fog, water is present on the wing,etc.), or,

2. The OAT is 5°C (41°F) or below and conditions are conducive toactive frost formation (e.g. clear night with a dew pointtemperature/OAT difference of 3°C (5°F) or less).

Takeoff is prohibited if frost, ice or snow may reasonably be expected toadhere to the airplane between the tactile check and takeoff (e.g. snownear freezing temperature with no deicing/anti-ice fluid application).

208BPHCUS-002-12


U.S.FAA APPROVED

WEIGHT LIMITSMaximum Ramp Weight . . . . . . . . . . . . . . . .8842 Pounds (4010 kg)Maximum Takeoff Weight . . . . . . . . . . . . . . .8807 Pounds (3994 kg)Maximum Landing Weight. . . . . . . . . . . . . . .8500 Pounds (3855 kg)

NOTERefer to Section 6, Weight and Balance, Figure 6-11, CabinInternal Loading Arrangements, for recommended loadingarrangements.

CENTER OF GRAVITY LIMITS

CENTER OF GRAVITY RANGE

FORWARD WITH OR WITHOUT CARGO POD185.00 inches (4699 mm) (11.19% MAC) aft of datum at 6500pounds (2948 kg) or less, with straight line variation to 193.37 inches(4912 mm) (23.80% MAC) aft of datum at 8000 pounds (3628 kg)and straight line variation to 199.15 inches (5059 mm) (32.50%MAC) aft of datum at 8807 pounds (3994 kg).

AFT WITH OR WITHOUT CARGO POD204.35 inches (5190 mm) (40.33% MAC) aft of datum at all weightsup to 8807 pounds (3994 kg).

REFERENCE DATUM100 inches (2540 mm) forward of front face of firewall.

MEAN AERODYNAMIC CHORD (MAC)The leading edge of the MAC is 177.57 inches (4510 mm) aft of thedatum. The MAC length is 66.40 inches (1686 mm).

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GARMIN G1000

U.S.FAA APPROVED

MANEUVER LIMITSThis airplane is certificated in the normal category. The normal categoryis applicable to aircraft intended for non-aerobatic operations. Theseinclude any maneuvers incidental to normal flying, stalls (except whipstalls), lazy eights, chandelles, and turns in which the angle of bank isnot more than 60°.

Aerobatic maneuvers, including spins, are not approved.

FLIGHT LOAD FACTOR LIMITSMaximum Takeoff Weight . . . . . . . . . . . . . . . . . 8807 Pounds (3994 kg)

*Flaps UP. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . +3.8g, -1.52g*Flaps LAND (All Settings). . . . . . . . . . . . . . . . . . . . . . . . . . . . +2.4g*The design load factors are 150% of the above, and in all cases,

the structure meets or exceeds design loads.

FLIGHT CREW LIMITSOne pilot required in left seat.

208BPHCUS-012-14


U.S.FAA APPROVED

KINDS OF OPERATIONS LIMITSThe Cessna 208B (867 SHP) equipped with the Garmin G1000 isapproved for day and night, VFR and IFR operations. The airplane maybe approved for flight into known icing conditions when appropriateequipment is installed. The operating limitation placard reflects thelimits applicable at the time of Airworthiness Certificate issuance.

The minimum equipment for approved operations required under theOperating Rules are defined by 14 CFR 91 and 14 CFR 135, asapplicable.

The following Kinds of Operations Equipment List (KOEL) identifies thesystems and equipment upon which type certification for each kind ofoperation was predicated.

These systems and equipment items must be installed and operableunless:

1. The airplane is approved to be operated in accordance with acurrent Minimum Equipment List (MEL) issued by the FAA.

Or;

2. An alternate procedure is provided in the basic FAA ApprovedAirplane Flight Manual for the inoperative state of the listedequipment and all limitations are complied with.

NOTEThe following systems and equipment list does not includedall equipment required by the 14 CFR Parts 91 and 135Operating Requirements. It also does not includecomponents obviously required for the airplane to beairworthy such as wings, primary flight controls,empennage, engine, etc.


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GARMIN G1000

U.S.FAA APPROVED

KINDS OF OPERATIONS EQUIPMENT LIST


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U.S.FAA APPROVED

KINDS OF OPERATIONS EQUIPMENT LIST (Continued)


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GARMIN G1000

U.S.FAA APPROVED



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GARMIN G1000

U.S.FAA APPROVED



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U.S.FAA APPROVED



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GARMIN G1000

U.S.FAA APPROVED



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GARMIN G1000

U.S.FAA APPROVED


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U.S.FAA APPROVED

FUEL LIMITATIONS

FUEL CAPACITYTOTAL FUEL

Both Tanks and Reservoir: . . . . . . . . . . .339.1 U.S. Gallons (1283 l)Both Tanks: . . . . . . . . . . . . . . . . . . . . . .335.6 U.S. Gallons (1270 l)Each Tank: . . . . . . . . . . . . . . . . . . . . . . . .167.8 U.S. Gallons (635 l)

TOTAL USABLE FUELBoth Tanks ON and Reservoir: . . . . . . . .335.3 U.S. Gallons (1268 l)Both Tanks ON: . . . . . . . . . . . . . . . . . . .332.0 U.S. Gallons (1256 l)Single Tank ON: . . . . . . . . . . . . . . . . . . . .165.0 U.S. Gallons (624 l)

TOTAL UNUSABLE FUELBoth Tanks ON: . . . . . . . . . . . . . . . . . . . . . . .3.6 U.S. Gallons (13 l)Single Tank ON: . . . . . . . . . . . . . . . . . . . . . . .2.8 U.S. Gallons (10 l)

Maximum Fuel Imbalance:. . . . . . . . . . . . . . . . . . . .200 Pounds (90 kg) NOTE

To achieve full fuel capacity, fill fuel tank to the top of thefiller neck. Filling fuel tanks to the bottom of the fuel fillercollar (level with flapper valve) allows space for thermalexpansion and results in a decrease in fuel capacity of 4.0U.S. gallons (15 l) per side (8.0 U.S. gallons (30 l) total).

The fuel quantity, fuel used and fuel remaining functions of the G1000are supplemental information only and must be verified by the pilot.

Continuous uncoordinated flight is prohibited if L FUEL LOW, R FUELLOW or L-R FUEL LOW annunciator is shown on PFD.

Unusable fuel quantity will continue to increase the longer a significantsideslip is maintained.

Due to possible fuel starvation, maximum full rudder sideslip duration islimited to a maximum of three minutes.

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GARMIN G1000

U.S.FAA APPROVED

FUEL LIMITATIONS

* It is assumed that fuel temperature is the same as Outside AirTemperature (OAT).

** AN8 is JP-8 fuel with a reduced freeze point specified forAntarctic operations.

Figure 2-6 (Sheet 1 of 2)

FUEL GRADE (SPECIFICATION) AND FUEL ADDITIVES

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U.S.FAA APPROVED

FUEL LIMITATIONS (Continued)

FUEL GRADE (SPECIFICATION) AND FUEL ADDITIVES(Continued)

APPROVED FUEL ADDITIVESOne of the following fuel system anti-ice additives must be added to thefuel as noted at the following concentrations. Use of fuel anti-iceadditives is required if freezing temperatures are expected during anypart of the flight. Refer to Section 8, Airplane Handling, Service andMaintenance, Servicing, Fuel, for additional information andrecommended blending instructions for approved fuel additives.

NOTE1. MIL-DTL-27686 (EGME) or MIL-DTL-85470 (DiEGME), Type:

Anti-Ice Additive, in a concentration of 0.10 to 0.15 percent byvolume.

2. MIL-DTL-27686 (EGME) or MIL-DTL-85470 (DiEGME), Type:Anti-Ice Additive, in a concentration of 0.10 to 0.20 percent byvolume.

3. GOST 8313 (Fluid I), Type: Anti-Ice Additive, in aconcentration of 0.10 to 0.30 percent by volume.

4. CIS TU6-10-1458 (Fluid I-M), Type: Anti-Ice Additive, in aconcentration of 0.10 to 0.30 percent by volume.

5. T1301 (SH0396-92), Type: Anti-Ice Additive, in aconcentration of 0.10 to 0.15 percent by volume.

6. DuPont Stadis 450, Type: Static Dissipator, in a concentrationas required to bring fuel up to 300 conductive units, not toexceed 1 Parts Per Million (PPM).

7. SOHIO Biobor JF, Type: Biocide, at a concentration not toexceed 20 PPM of elemental boron (270 PPM of totaladditive).

8. Kathon FP, Type: Biocide, at a concentration not to exceed100 PPM of total additive.

Figure 2-6 (Sheet 2)

208BPHCUS-01 2-27

TEMPORARY REVISION FOR CESSNA PILOT’S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL

208BPHCUS-01 TR01

Publication Affected: Model 208B (867 SHP) Garmin G1000, Serials 208B2197 and 208B5000 and On, basic Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual, Revision 1, dated 22 May 2013.

Airplane Serial Numbers Affected: Airplanes 208B2197 and 208B5000 and On. Description of Change: Section 2, Operating Limitations, page 2-28, Outside Air

Temperture Limits, Replace Outside Air Temperature Limits information.

Filing Instructions: Insert this temporary revision in the Model 208B (867

SHP) Garmin G1000, Serials 208B2197 and 208B5000 and On, basic Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual adjacent to page 2-28.

Removal Instructions: This temporary revision must be removed and

discarded when Revision 2 has been collated into the basic Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual.

In Section 2, Operating Limitations, page 2-28, Outside Air Temperature Limits, replace the information with the following: OUTSIDE AIR TEMPERATURE LIMITS

Cold Day.................................................. -54°C from Sea Level to 25,000 Feet

Hot Day: Ground Operations ................................. +47°C from Sea Level to 5000 Feet

ISA +39°C above 5000 Feet Flight Operations ...........................ISA +39°C from Sea Level to 25,000 Feet

Refer to Section 5, Performance, Figure 5-5, ISA Conversion and Operating Temperature Limits Chart, for a graphical presentation of the operating air temperature limits.

NOTE

• With both deck skin fans inoperative, ground operations are limited to +46°C for 30 minutes.

• Ground operations up to +38°C are not time limited with both deck skin fans inoperative.

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208BPHCUS-01 TR01

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GARMIN G1000

U.S.FAA APPROVED

MAXIMUM OPERATING ALTITUDE LIMITNon-Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . 25,000 FeetIcing Conditions (if equipped) . . . . . . . . . . . . . . . . . . . . 20,000 FeetAny conditions with any ice on the airplane. . . . . . . . . . 20,000 Feet

OUTSIDE AIR TEMPERATURE LIMITSCold Day . . . . . . . . . . . . . . . . . -54°C from Sea Level to 25,000 Feet

Hot Day:Ground Operations. . . . . . . . . +42°C from Sea Level to 5000 Feet

ISA +37°C above 5000 FeetFlight Operations . . . . . ISA +37°C from Sea Level to 25,000 Feet

Refer to Section 5, Performance, Figure 5-5, ISA Conversion andOperating Temperature Limits Chart, for a graphical presentation of theoperating air temperature limits.

NOTE• With both deck skin fans inoperative, ground operations

are limited to +42°C for 30 minutes.

• Ground operations up to +38°C are not time limited withboth deck skin fans inoperative.

MAXIMUM PASSENGER SEATING LIMITSIn the passenger version, up to 11 seats may be installed. The rightfront seat may be occupied by either a second crew member or apassenger. When the right front seat is occupied by a passenger, onlyeight seats in the aft cabin can be occupied.

In the cargo version, a maximum of one seat may be installed to theright of the pilot’s seat for a second crew member or a passenger.

Refer to Section 6, Weight and Balance, Figure 6-11, Cabin InternalLoading Arrangements, for approved seat locations.

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208BPHCUS-01 TR08

SEATING

WELDED TUBE FRAME

Individual and dual commuter seats equipped with the welded tube frame are approved for forward facing installation only.

MACHINED ALUMINUM FRAME

Individual commuter seats equipped with the machined aluminum frame are approved for forward or aft facing installation. The optional headrest must be installed when seat is installed facing in the aft position. The luggage restraint bar, located on the seat base, must be installed facing the forward side of the aircraft.

Dual commuter seats equipped with the machined aluminum frame are approved for forward facing installation only.

NOTE Mixing of seat types (Welded Tube and Machined Aluminum Frame Seats) is permissible. It is important to use the respective weight and moment table for a given seat type, seating configuration and location to ensure an accurate weight and balance.

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208BPHCUS-01 TR08

Publication Affected: Model 208B (867 SHP) Garmin G1000, Serials 208B2197 and 208B5000 and On, basic Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual, Revision 1, dated 22 May 2013.

Airplane Serial Numbers Affected: Airplanes 208B2197 and 208B5000 and On. Description of Change: Section 2, Limitations, Page 2-28, add new Seating,

limitations. Filing Instructions: Insert this temporary revision in the Model 208B (867

SHP) Garmin G1000, Serials 208B2197 and 208B5000 and On, basic Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual adjacent to page 2-29.

Removal Instructions: This temporary revision must be removed and

discarded when Revision 2 has been collated into the basic Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual.

In Section 2, Limitations, Page 2-28, add new Seating limitation with the information on the previous page:

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U.S.FAA APPROVED

SYSTEM AND EQUIPMENT LIMITATIONSFLAP LIMITATIONS

Approved Takeoff Range. . . . . . . . . . . . . . . . . . . . . . .UP to TO/APRApproved Landing Range . . . . . . . . . . . . . . . . . . . . . . . UP to LANDApproved Landing Range in Icing Conditions . . . . . . .UP to TO/APR

STANDBY ELECTRIC SYSTEMWhen operating the standby electrical system, the maximum electricalload is 75 amps from Sea Level to 21,000 feet. To ensure adequatealternator cooling at higher altitudes, reduce maximum standbyelectrical system load 5 amps per 1000 feet above 21,000 feet.

AUX AUDIO SYSTEMUse of the AUX AUDIO entertainment input is prohibited during takeoffand landing.

Use of the AUX AUDIO entertainment audio input and PortableElectronic Devices (PED), such as cellular telephones, games,cassette, CD or MP3 players, is prohibited under IFR unless theoperator of the airplane has determined that the use of the Aux AudioSystem and the connected PED(s) will not cause interference with thenavigation or communication system of the airplane.

12V POWER SYSTEMThe 12 Volt Power System is limited to a maximum combined currentdraw of 10 Amps (120 watts) all locations.

The 12 Volt Power System (12V POWER OUTLET) is not certified forsupplying power to flight-critical communications or navigation devices.

Use of the 12 Volt Power System is prohibited during takeoff andlanding.

Use of the 12 Volt Power System is prohibited under IFR unless theoperator of the airplane has determined that the use of the 12 VDCpower supply and connected PED(s) will not cause interference withthe navigation or communication systems of the airplane.

208BPHCUS-00 2-29


GARMIN G1000

U.S.FAA APPROVED

SYSTEM AND EQUIPMENT LIMITATIONS (Continued)

GENERATOR LIMITATIONSMaximum generator load limit is a function of Ng, air conditioning andbleed air heat position.

ON GROUND

IN FLIGHT

MAXIMUM GENERATOR LOAD - GROUND OPERATIONSAIR CONDITIONING - OFF,

BLEED AIR HEAT - ON or OFFAIR CONDITIONING - ON,BLEED AIR HEAT - OFF

Ng AMPS Ng AMPS55% 65 55% 3560% 100 60% 9065% 135 65% 155

MAXIMUM GENERATOR LOAD - FLIGHT OPERATIONSAIR CONDITIONING - OFF,

BLEED AIR HEAT - ON or OFFAIR CONDITIONING - ON,BLEED AIR HEAT - OFF

Ng AMPS Ng AMPS65% 125 65% 12572% 140 72% 170

>80% 200 >80% 200

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U.S.FAA APPROVED


G1000 LIMITATIONS

The current Garmin G1000 Cockpit Reference Guide (CRG) PartNumber and System Software Version that must be available to thepilot during flight are displayed on the MFD AUX group, SYSTEMSTATUS page.

GPS based IFR enroute, oceanic and terminal navigation is prohibitedunless the pilot verifies the currency of the database or verifies eachselected waypoint for accuracy by reference to current approved data.

RNAV/GPS instrument approaches must be accomplished inaccordance with approved instrument approach procedures that areretrieved from the G1000 navigation database. The G1000 databasemust incorporate the current update cycle.

Use of the NAVIGATION MAP page for pilotage navigation isprohibited. The Navigation Map is intended only to enhance situationalawareness. Navigation is to be conducted using only current charts,data and authorized navigation facilities.

Navigation using the G1000 is not authorized North of 72° Northlatitude or South of 70° South latitude due to unsuitability of themagnetic fields near the Earth's poles. In addition, operations are notauthorized in the following regions:

1. North of 65° North latitude between longitude 75° W and 120° W(Northern Canada).

2. North of 70° North latitude between longitude 70° W and 128° W(Northern Canada).

3. North of 70° North latitude between longitude 85° E and 114° E(Northern Russia).

4. South of 55° South latitude between longitude 120° E and 165°E (region south of Australia and New Zealand).


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GARMIN G1000

U.S.FAA APPROVED


G1000 LIMITATIONS (Continued)

Use of the TERRAIN PROXIMITY information for primary terrainavoidance is prohibited. The Terrain Proximity map is intended only toenhance situational awareness. It is the pilot’s responsibility to provideterrain clearance at all times. In addition, Terrain Proximity informationis not available in locations north of 75° North latitude or South of 60°South latitude due to the absence of terrain data in these geographicalareas.

The COM 1/2 (split COM) function of the Audio Panel is not approvedfor use. During COM 1/2 operation, transmission by one crew memberinhibits reception by the other crew member.

Dispatch with GIA1, GIA2, PFD, or MFD cooling advisory message isprohibited.

Verify the torque gage dynamic redline agrees with the values listed inFigure 5-8, Maximum Engine Torque For Takeoff, for current altitudeand temperature.

The dynamic redline is a graphical representation of takeoff powerbelow 16,000 feet MSL and Maximum Rated Power above 16,000 feetMSL as depicted in Section 5, Performance, Figure 5-8, MaximumEngine Torque For Takeoff chart and Figure 5-9 Maximum EngineTorque For Climb. The dynamic redline automatically compensates foraltitude and temperature changes and adjusts displayed takeoff torquefor inertial separator deployment and bleed air heat switch position.Failure to comply with the dynamic redline indication can result inaccelerated engine wear, unscheduled engine maintenance andincreased operating costs even though no other published enginelimitation has been exceeded.

The maximum cruise torque bug functions of the G1000 engine torqueindicator is advisory information only.

All power settings must be verified by the pilot, refer to Section 5,Performance, Figure 5-8, Maximum Engine Torque For Takeoff, Figure5-9, Maximum Engine Torque For Climb and Figure 5-19, CruisePerformance (with Cargo Pod) or Figure 5-36, Cruise Performance(without Cargo Pod) for the approved engine power settings.

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U.S.FAA APPROVED



OPERATIONAL APPROVALSThe Garmin G1000 GPS receivers are approved under TSO C145cClass 3. The Garmin G1000 system has been demonstrated capableof, and has been shown to meet the accuracy requirements for, thefollowing operations provided it is receiving usable navigation data.These do not constitute operational approvals.

1. Enroute, terminal, non-precision instrument approachoperations using GPS and WAAS (including GPS, or GPS, andRNAV approaches), and approach procedures with verticalguidance (including LNAV/VNAV, LNAV + V, and LPV) within theU.S. National Airspace System in accordance with AC 20-138C.

2. As a required Long Range Navigation (LRN) system for use inthe following types of airspace when used in conjunction withGarmin WAAS Fault Detection/Exclusion Prediction Program,part number 006-A0154-01 or later approved version:a. Oceanic/Remote - RNP-10 (per FAA AC 20-138C, FAA

Order 8400-12C, and FAA Order 8900.1). Both GPSreceivers are required to be operating and receiving usablesignals except for routes requiring only one Long RangeNavigation (LRN) sensor.

NOTEEach display computes an independent navigation solutionbased on the on-side GPS sensor. However, either displaywill automatically revert to the cross-side sensor if the on-side sensor fails or if the cross-side sensor is determined tobe more accurate. A BOTH ON GPS1 or BOTH ON GPS2message does not necessarily mean that one GPS hasfailed. Refer to the MFD AUX-GPS STATUS page todetermine the status of the unused GPS.

b. North Atlantic (NAT) Minimum Navigational PerformanceSpecifications (MNPS) Airspace per AC 91-49 Chg 1 andAC 120-33. Both GPS receivers are required to be operatingand receiving usable signals except for routes requiring onlyone Long Range Navigation sensor.

c. Enroute and Terminal including RNP5/BRNAV and PRNAV(RNP-1) - In accordance with JAA TGL-10, ACJ 20X4, AC90-96A, and AC 90-100A, provided the FMS is receivingusable navigation information from one or more GPSreceivers.

208BPHCUS-00 2-33


GARMIN G1000

U.S.FAA APPROVED



GARMIN GFC 700 AUTOMATED FLIGHT CONTROL SYSTEM(AFCS)

1. The GFC 700 AFCS preflight test must be successfullycompleted prior to use of the autopilot, flight director or manualelectric trim.

2. A pilot, with the seat belt fastened, must occupy the left pilot’sseat during all autopilot operations.

3. The autopilot and yaw damper must be off during all takeoff andlandings.

4. Autopilot maximum engagement speed . . . . . . . . . . . 175 KIASAutopilot minimum engagement speed . . . . . . . . . . . . . 80 KIASElectric Trim maximum operating speed . . . . . . . . . . . 175 KIAS

5. The autopilot must be disengaged below 200 feet AGL duringapproach operations and below 800 feet AGL during all otheroperations.

6. ILS approaches using the autopilot/flight director are limited toCategory I approaches only.

7. Raw data ILS approaches below 400 feet AGL are prohibited.8. Use of the autopilot is prohibited when the audio panel is

inoperative, since the aural alert will not be provided whenautopilot is disengaged.

9. When conducting a missed approach, use of the autopilot isprohibited until a rate of climb is established that will meet allaltitude requirements of the missed approach procedure.

208BPHCUS-002-34


U.S.FAA APPROVED



L3 COMMUNICATIONS WX 500 STORMSCOPE (if installed)

Use of the WEATHER MAP (WX-500 Stormscope) for hazardousweather (thunderstorm) penetration is prohibited. LTNG information onthe NAVIGATION MAP or WEATHER MAP is approved only as an aidto hazardous weather avoidance, not penetration. The WX-500Stormscope user’s guide should be available to the pilot during flight.

SIRIUS XM WEATHER (if installed)Use of the XM data link weather information for maneuvering in, near oraround areas of hazardous weather is prohibited. Informationcontained within XM data link weather products may not accuratelydepict current weather conditions.Do not use the indicated XM data link weather product age todetermine the age of the weather information shown by the XM datalink weather product. Due to time delays inherent in gathering andprocessing weather data for XM data link transmission, the weatherinformation shown by the XM data link weather product may besignificantly older than the indicated weather product age.

TRAFFIC ADVISORY SYSTEM (TAS) (if installed)

Use of the TRAFFIC MAP to maneuver the airplane to avoid traffic isprohibited. The Traffic Advisory System (TAS) is intended for advisoryuse only. TAS is intended only to help the pilot to visually locate traffic.It is the responsibility of the pilot to see and maneuver to avoid traffic.

TAS is unable to detect any intruding aircraft without an operatingtransponder. TAS can detect and track aircraft with either an ATCRBS(operating in Mode A or C) or Mode S transponders.

ATC procedures and the “see and avoid concept” will continue to be theprimary means of aircraft separation. However, if communication is lostwith ATC, TAS adds a significant backup for collision avoidance.

208BPHCUS-00 2-35


GARMIN G1000

U.S.FAA APPROVED



TERRAIN AWARENESS AND WARNING SYSTEM (TAWS-B) (ifinstalled)Use of the Terrain Awareness and Warning System (TAWS-B) tonavigate to avoid terrain or obstacles is prohibited. TAWS-B is onlyapproved as an aid to help the pilot to see-and-avoid terrain orobstacles.

TAWS-B must be inhibited when landing at a location not included inthe airport database.

Use of TAWS-B is prohibited when operating using the QFE altimetersetting (altimeter indicates 0 feet altitude when the airplane is on therunway).

The pilot is authorized to deviate from the current ATC clearance onlyto the extent necessary to comply with TAWS-B warnings.

The geographic area of the TAWS-B database must match thegeographic area in which the airplane is being operated.

TAWS-B is not available in locations north of 75° North latitude or southof 60° South latitude due to the absence of terrain data in thesegeographical areas.

208BPHCUS-002-36


U.S.FAA APPROVED

OTHER LIMITATIONS

OPTIONAL EQUIPMENT USER’S GUIDE

The pilot is responsible for ensuring the appropriate user’s guide(s) forall optional equipment installed in the airplane is accessible to the pilotin flight.

TYPE II, TYPE III OR TYPE IV ANTI-ICE FLUID TAKEOFFLIMITATIONS

FLAP LIMITATIONSTakeoff Flaps Setting. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP

AIRSPEED LIMITATIONSTakeoff Rotation Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . .83 KIAS

208BPHCUS-00 2-37


GARMIN G1000

U.S.FAA APPROVED

OTHER LIMITATIONS (Continued)

FLIGHT IN KNOWN ICING VISUAL CUESAs Required by AD 96-09-15, Paragraph (a) (1)

WARNING

Severe icing may result from environmentalconditions outside of those for which the airplaneis certificated. Flight in freezing rain, freezingdrizzle, or mixed icing conditions (supercooledliquid water and ice crystals) may result in icebuild-up on protected surfaces exceeding thecapability of the ice protection system, or mayresult in ice forming aft of the protected surfaces.This ice may not be shed using the ice protectionsystems, and may seriously degrade theperformance and controllability of the airplane.

During flight, severe icing conditions that exceed those for which theairplane is certificated shall be determined by the following visual cues.If one or more of these visual cues exists, immediately request priorityhandling from Air Traffic Control to facilitate a route or an altitudechange to exit the icing conditions.

1. Unusually extensive ice is accreted on the airframe in areas notnormally observed to collect ice.

2. Accumulation of ice on the upper or lower surface of the wing aftof the protected area.

3. Heavy ice accumulations on the windshield, or when ice forms aftof the curved sections on the windshield.

4. Ice forms aft of the protected surfaces of the wing struts.

Since the autopilot may mask tactile cues that indicate adversechanges in handling characteristics, use of the autopilot is prohibitedwhen any of the visual cues specified above exist, or when unusuallateral trim requirements or autopilot trim warnings are encounteredwhile the airplane is in icing conditions.

208BPHCUS-002-38


U.S.FAA APPROVED

PLACARDSWARNING

The following information must be displayed in theform of composite or individual placards. As aminimum, the exact wording of these placards isrequired as specified in this section. Placardwording can be from part numbered placardsobtained from Cessna Aircraft Company orequivalent placards installed by an approved repairstation in accordance with normal maintenancepractices/procedures.

INTERIOR PLACARDS

FLIGHT CREW AREAIn full view of the pilot on the sunvisor or windshield trim on airplanesnot equipped for flight into known icing:


208BPHCUS-00 2-39


GARMIN G1000

U.S.FAA APPROVED

PLACARDS (Continued)

INTERIOR PLACARDS (Continued)

FLIGHT CREW AREA (Continued)In full view of the pilot on the sunvisor or windshield trim:


208BPHCUS-002-40


U.S.FAA APPROVED



FLIGHT CREW AREA (Continued)On overhead panel adjacent to fuel tank selectors:

Located on magnetic compass:


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GARMIN G1000

U.S.FAA APPROVED



FLIGHT CREW AREA (Continued)Above left side PFD:

On instrument panel below standby instruments:


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U.S.FAA APPROVED



FLIGHT CREW AREA (Continued)On pedestal adjacent to wing flap position indicator:

On pedestal below the power lever:


208BPHCUS-00 2-43


GARMIN G1000

U.S.FAA APPROVED



FLIGHT CREW AREA (Continued)On left and right lower sidewall below and forward of instrumentpanel:

On the control lock:


208BPHCUS-002-44


U.S.FAA APPROVED



FLIGHT CREW AREA (Continued)Adjacent to left crew door inside door handle:


208BPHCUS-00 2-45


GARMIN G1000

U.S.FAA APPROVED


INTERIOR PLACARDS (Continued)PASSENGER AREA

Adjacent to upper passenger door inside door handle (Passengerversion only):

Adjacent to the interior door handle of lower passenger door(Passenger version only):


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U.S.FAA APPROVED



PASSENGER AREA (Continued)On right sidewall aft of lower passenger door below window trim(Passenger version only):

Adjacent to upper cargo door interior door handle (Passengerversion only):


208BPHCUS-00 2-47


GARMIN G1000

U.S.FAA APPROVED


INTERIOR PLACARDS (Continued)CARGO AREA

On left and right sides of the cargo barrier (Cargo version orPassenger version when cargo barrier is installed):

On right sidewall adjacent to Zone 5 (Cargo version only):


208BPHCUS-002-48


U.S.FAA APPROVED



CARGO AREA (Continued)On left and right sides of cabin in appropriate zones (Cargo versiononly):


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GARMIN G1000

U.S.FAA APPROVED

PLACARDS (Continued)INTERIOR PLACARDS (Continued)CARGO AREA (Continued)

On inside of lower cargo door (Cargo version only)

At each sidewall and ceiling anchor plate (except heavy duty anchorplates with additional structural support) and at anchor plate atcenter of lower cargo door (Cargo version only):


208BPHCUS-002-50


U.S.FAA APPROVED


EXTERIOR PLACARDSOn inside of cargo pod doors (if installed):


208BPHCUS-00 2-51


GARMIN G1000

U.S.FAA APPROVED


EXTERIOR PLACARDS (Continued)

Adjacent to upper cargo door outside pushbutton and door handle(Passenger version only):


208BPHCUS-002-52


U.S.FAA APPROVED




208BPHCUS-00 2-53


GARMIN G1000

U.S.FAA APPROVED

PLACARDS (Continued)EXTERIOR PLACARDS (Continued)WINGS


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U.S.FAA APPROVED



WINGS (Continued)On bottom of each wing just forward of aileron:


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GARMIN G1000

U.S.FAA APPROVED

PLACARDS (Continued)EXTERIOR PLACARDS (Continued)ENGINE COMPARTMENT

On the brake fluid reservoir:


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U.S.FAA APPROVED

PLACARDS (Continued)EXTERIOR PLACARDS (Continued)ENGINE COMPARTMENT (Continued)

Adjacent to oil dipstick/filler cap (on inertial separator duct):


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GARMIN G1000

U.S.FAA APPROVED



ENGINE COMPARTMENT (Continued)On firewall above battery tray:


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U.S.FAA APPROVED



FORWARD FUSELAGEAbove ground service plug receptacle:


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GARMIN G1000

U.S.FAA APPROVED



FORWARD FUSELAGE (Continued)On each side of nose strut fairing near tow limit marking:


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U.S.FAA APPROVED



AFT FUSELAGEOn the left side of the tailcone stinger, affixed to the rudder lock shaftcover plate:

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GARMIN G1000

U.S.FAA APPROVED

This Page Intentionally Left Blank

208BPHCUS-002-62

CESSNA SECTION 2 MODEL 208B (867 SHP) … · model 208b (867 shp) operating limitations garmin...

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