Pilot's Operating Handbook & FAA Approved Airplane Flight Manual for Cessna Grand Caravan EX

CESSNA MODEL 208B867 SHP - GARMIN G1000 Serials 208B2197 and 208B5000 and On SUPPLEMENT 1 TKS ICE PROTECTION SYSTEM FOR CARGO POD EQUIPPED AIRPLANES SERIAL NO. REGISTRATION NO. This supplement must be inserted into Section 9 of the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual when the TKS Ice Protection System for Cargo Pod Equipped Airplanes is installed. COPYRIGHT © 2013 24 MAY 2013 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA REVISION 2 - 21 AUGUST 2014 208BPHCUS-S1-02 U.S. S1-1 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 SUPPLEMENT 1 TKS ICE PROTECTION SYSTEM FOR CARGO POD EQUIPPED AIRPLANES Use the Log of Effective Pages to determine the current status of this supplement. Pages affected by the current revision are indicated by an asterisk (*) preceding the page number. Supplement Status Date Original Issue 24 May 2013 Revision 1 16 May 2014 Revision 2 21 August 2014 LOG OF EFFECTIVE PAGES Page Page Revision Number Status Number * S1-1 thru S1-2 Revised 2 S1-3 thru S1-4 Original 0 * S1-5 Revised 2 S1-6 thru S1-8 Original 0 S1-9 Revised 1 S1-10 Original 0 * S1-11 Revised 2 S1-12 thru S1-16 Original 0 * S1-17 thru S1-76 Revised 2 * S1-77 thru S1-80 Added 2 FAA APPROVED S1-2 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 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 supplement. This list contains only those Service Bulletins that are currently active. Number Title Airplane Serial Revision Incorporated Effectivity Incorporated in Airplane FAA APPROVED 208BPHCUS-S1-00 U.S. S1-3 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 TKS ICE PROTECTION SYSTEM FOR CARGO POD EQUIPPED AIRPLANES GENERAL This supplement must be placed in Section 9 of the basic 208B 867 SHP Garmin G1000 Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual (POH/AFM), Revision 1, dated 22 May 2013 or later, when the TKS Ice Protection System is installed on Cargo Pod Equipped Airplanes. The information contained in this document supplements or supersedes the basic POH/AFM only in those areas listed. For limitations, procedures, performance, and loading information not contained in this supplement, consult the basic POH/ AFM. FAA APPROVED S1-4 U.S. 208BPHCUS-S1-00 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 LIMITATIONS The following Limitations supersede and/or are in addition to the Limitations set forth in the basic Pilot's Operating Handbook and FAA Approved Airplane Flight Manual: The airplane must be operated, and its ice protection systems must be used, as described in Normal, Abnormal and Emergency Procedures contained in this supplement. Specific operational speeds and performance information must be used where established for such conditions. REQUIRED TRAINING Specific training for flight into known or forecast icing conditions provided by Cessna Aircraft Company is required to be successfully completed by the pilot in command within the preceding 12 calendar months for any flight into known or forecast icing conditions. Operators conducting operations under 14 CFR 121 and 14 CFR 135 may apply the grace provisions of 121.401(b) or 135.323(b) to the crew member’s base month, as appropriate. Completion of either of the following courses will meet this training requirement: TKS-Equipped Caravan Cold Weather Ops Course (C14697, Onsite) TKS-Equipped Caravan Cold Weather Ops Course (C14698, Online) NOTE Pilots that have completed the Caravan Cold Wx Ops and Cold Wx Ops TKS training under any of the previous course numbers will still be shown in compliance for up to 12 calendar months from the last training completion date. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-5 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 LIMITATIONS (Continued) PREFLIGHT All checks and inspections as specified under Preflight Inspection, Before Starting Engine and Before Takeoff Check contained in the Normal Procedures section of this supplement must be satisfactorily completed prior to flight into known or forecast icing conditions. Takeoff is prohibited with any frost, ice, snow, or slush adhering to the wings, tail, control surfaces, propeller blades, or engine air inlets. WARNING • The TKS Ice Protection System is not approved for airplane deicing during ground operations. Use only approved deice/anti-icing fluids to make sure the critical surfaces are free of contamination before flight. • Even small amounts of frost, ice, snow, or slush on the wing may adversely change lift and drag. Failure to remove these contaminants will degrade airplane performance and will prevent a safe takeoff and climb. FAA APPROVED S1-6 U.S. 208BPHCUS-S1-00 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 LIMITATIONS (Continued) VISUAL AND TACTILE CHECK To assure the absence of frost, a tactile check of the wing leading edge and upper surface, as specified in Section 4, Normal Procedures of the basic POH/AFM, is required in addition to a visual inspection if the OAT is below 10°C (50°F). During ground icing conditions, takeoff must be accomplished within 5 minutes of completing the tactile check unless the airplane is operated 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 to active frost formation (e.g. clear night with a dew point temperature/OAT difference of 3°C (5°F) or less). The upper surface of each wing must be inspected for the condition and presence of Vortex Generators (VGs). Each wing must have all 10 VGs installed on the upper surface. All 10 VGs must be present on each wing or takeoff is prohibited for any flight regardless of planned flight into known or forecast icing. Takeoff is prohibited if frost, ice or snow may reasonably be expected to adhere to the airplane between the tactile check and takeoff (e.g. snow near freezing temperature with no ground deicing/anti-ice fluid application). FAA APPROVED 208BPHCUS-S1-00 U.S. S1-7 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 LIMITATIONS (Continued) WEIGHT LIMITS There are no additional limitations on the maximum allowable takeoff weight into known or forecast icing conditions for airplanes equipped with the TKS Ice Protection System. The maximum allowable operating weights for the airplane are: Maximum Ramp Weight . . . . . . . . . . . . . . . 8842 Pounds (4010 kg) Maximum Takeoff Weight. . . . . . . . . . . . . . . 8807 Pounds (3994 kg) Maximum Landing Weight . . . . . . . . . . . . . . 8500 Pounds (3855 kg) MINIMUM DISPATCH FLUID Minimum ice protection fluid for takeoff for flight into known or forecast icing conditions is 11.7 U.S. gallons (44.27 Liters) This minimum amount of fluid allows for 45 minutes of ice protection with the PRIMARY switch set to HIGH mode. The sight gage on the TKS Ice Protection System tank is the only means of making sure there is adequate fluid quantity onboard before each flight. Refer to Figure S1-8, System Endurance Characteristics, in the Airplane and Systems Descriptions section of this supplement to make sure proper fluid quantity is onboard prior to each flight into known or forecast icing conditions. FAA APPROVED S1-8 U.S. 208BPHCUS-S1-00 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 LIMITATIONS (Continued) APPROVED ICE PROTECTION FLUID The TKS Ice Protection System tank must be serviced with the following fluid: Specification DTD 406B Trade names for DTD 406B include: TKS Fluid (D.W. Davies) AVL-TKS (Aviation Laboratories) AeroShell Compound 07 (Shell) AL-5 Fluids conforming to this specification may be mixed in the TKS Ice Protection System tank in any proportions. WARNING Under no circumstances are fluids other than those listed above to be used in the TKS Ice Protection System. Some fluids currently used for ground deicing purposes contain thickening agents which may block the porous panels. If it is known or suspected that such a fluid has been placed in the tank, do not operate the system. POROUS PANEL CLEANING Only the following fluids are approved for cleaning the TKS leading edge porous panels: 1. Water (with soap or detergents) 2. Approved TKS Ice Protection System Fluids 3. Isopropyl Alcohol FAA APPROVED 208BPHCUS-S1-01 U.S. S1-9 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 LIMITATIONS (Continued) MINIMUM SPEEDS IN ICING CONDITIONS The minimum airspeeds for operations in icing conditions with a FULLY FUNCTIONAL TKS Ice Protection System operating are: WING FLAPS UP or TO/APR . . . . . . . . . . . . . . . . . . . . . . . 95 KIAS WARNING • These speeds do not apply to takeoff when using the published POH/AFM procedure for TYPE II, TYPE III OR TYPE IV ANTI-ICE FLUID TAKEOFF in Section 4, Normal Procedures of the POH/ AFM. • With a failed TKS Ice Protection System, maintain 120 KIAS with WING FLAPS UP (110 KIAS if climbing) and refer to the Emergency Procedure Section of this supplement. FLAP SETTING IN ICING CONDITIONS WING FLAPS must be UP when holding in icing conditions. WARNING • With ice suspected on the airframe, or operating with OAT at 5°C (41°F) or below in visible moisture, do not extend WING FLAPS beyond TO/APR for landing. • WING FLAPS must be extended to TO/APR during all phases of flight (takeoff and landing INCLUDED) when airspeed is below 95 KIAS. This does not apply to takeoff when using the published POH/AFM procedure for TYPE II, TYPE III OR TYPE IV ANTI-ICE FLUID TAKEOFF in Section 4, Normal Procedures of the POH/AFM. • The aural stall warning system does not provide adequate stall warning in all icing conditions. FAA APPROVED S1-10 U.S. 208BPHCUS-S1-00 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 LIMITATIONS (Continued) REQUIRED EQUIPMENT The following equipment must be installed and fully operational for flight into known or forecast icing conditions: 1. Wing and wing strut leading edge porous panels 2. Horizontal stabilizer leading edge porous panels 3. Vertical stabilizers leading edge porous panels 4. Propeller fluid slinger assembly 5. TKS Ice Protection System equipment pack (tank assembly, pumps, filter(s)) 6. Windshield spray bar 7. Heated lift detector (stall warning) vane 8. Alternate Static Source 9. Left and Right Pitot/Static Tube Heat System 10. Wing Ice Inspection Light 11. Engine Driven Generator 12. Standby Electrical System 13. Engine Inertial Separator 14. Heater and Defroster 15. Hartzell Propeller: HC-B3TN-3AF/T10890CNB-2 16. Cargo Pod 17. Low Airspeed Awareness System 18. Windshield Ice Detection Light 19. Vortex Generators (10 per wing) WINDSHIELD PUMP The windshield pump is rated for intermittent use only. Continuous operation may damage the pump. WARNING Do not operate the windshield pump continuously longer than 10 seconds. Allow at least 10 seconds between operations. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-11 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 LIMITATIONS (Continued) INERTIAL SEPARATOR If the INERTIAL SEPARATOR is set to BYPASS at any point due to suspected or actual icing conditions, do not return it to NORMAL until the inertial separator door has been visually inspected and verified free of ice and ice protection fluid. Comply with the SHUTDOWN AND SECURING AIRPLANE check of the Normal Procedures in this supplement. PROPELLER SPINNER Do not operate the airplane’s engine without the propeller spinner installed in accordance with the Cessna Model 208 Series Maintenance Manual. ENVIRONMENTAL CONDITIONS Icing conditions are defined as visually detected ice, or the presence of visible moisture in any form at an OAT of 5°C (41°F) or below. Known icing conditions are defined by 14 CFR Part 25, Appendix C. These conditions do not include, nor were tests conducted in, all icing conditions that may be encountered (e.g., freezing rain, freezing drizzle, mixed conditions or conditions defined as severe). WARNING • Flight in conditions outside of 14 CFR Part 25 Appendix C is prohibited. • The airplane must not depart or be flown into an airport where freezing rain or freezing drizzle conditions are being reported. (Continued Next Page) FAA APPROVED S1-12 U.S. 208BPHCUS-S1-00 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 LIMITATIONS (Continued) ENVIRONMENTAL CONDITIONS (Continued) Some icing conditions not defined in 14 CFR Part 25 Appendix C have the potential of producing hazardous ice accumulations, which (1) exceed the capabilities of the airplane’s ice protection equipment, and/ or (2) create unacceptable airplane performance and stall speed increase. Pilots must be prepared to divert the flight promptly if hazardous ice accumulations occur. Inadvertent operation in these conditions may be detected by: 1. Unusually extensive ice is accreted on the airframe in areas not normally observed to collect ice. 2. Accumulation of ice on the upper or lower surface of the wing aft of the protected area. 3. Heavy ice accumulations on the windshield, or when ice forms aft of the curved sections on the windshield. 4. Ice forms aft of the protected surfaces of the wing struts. If these conditions are encountered, the pilot must take immediate actions to exit these conditions. Continued flight in icing conditions is prohibited after encountering one or more of the following with the TKS Ice Protection System fully functional and operating: 1. Airspeed in level flight at constant power decreases by 10 KIAS using Maximum Cruise Power. 2. MEA or MOCA (if applicable) on current leg falls into Area “C” of Figure S1-1, Enroute Tool For Exiting Icing, located in the Performance section of this supplement. Exit strategies must be determined during preflight planning. FAA APPROVED 208BPHCUS-S1-00 U.S. S1-13 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 LIMITATIONS (Continued) AUTOPILOT OPERATION IN ICING CONDITIONS Autopilot operation is prohibited when operating in icing conditions which are outside the 14 CFR Part 25 Appendix C defined Environmental Conditions listed in the Limitations section of this supplement. The autopilot must be disengaged when the BELOW ICING MIN SPD flashing amber and white annunciation is activated. The airspeeds listed in the Minimum Speeds In Icing Conditions in the Limitations section of this supplement also apply to autopilot operations. MAXIMUM OPERATING ALTITUDES Certified Maximum Operating Altitudes: Icing Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20,000 Feet Any flight conditions with ice on the airplane . . . . . . . . . 20,000 Feet FAA APPROVED S1-14 U.S. 208BPHCUS-S1-00 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 LIMITATIONS (Continued) PLACARDS WARNING The following information must be displayed in the form of composite or individual placards. As a minimum, the exact wording of these placards is required as specified in this section. Placard wording can be from part numbered placards obtained from Cessna Aircraft Company or equivalent placards installed by an approved repair station in accordance with normal maintenance practices/procedures. INTERIOR PLACARDS FLIGHT CREW AREA In full view of the pilot on the sunvisor or windshield trim strip on airplanes equipped for flight into known icing: (Continued Next Page) FAA APPROVED 208BPHCUS-S1-00 U.S. S1-15 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 LIMITATIONS (Continued) PLACARDS (Continued) INTERIOR PLACARDS (Continued) FLIGHT CREW AREA (Continued) Adjacent to the TKS Ice Protection System controls: Above the Standby Airspeed Indicator: (Continued Next Page) FAA APPROVED S1-16 U.S. 208BPHCUS-S1-00 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 LIMITATIONS (Continued) PLACARDS (Continued) INTERIOR PLACARDS (Continued) FLIGHT CREW AREA (Continued) Above dimming switch panel.Location may vary depending on installed options (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-17 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 LIMITATIONS (Continued) PLACARDS (Continued) EXTERIOR PLACARDS Around the TKS Ice Protection Fluid Tank filler assembly: (Continued Next Page) FAA APPROVED S1-18 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 LIMITATIONS (Continued) PLACARDS (Continued) EXTERIOR PLACARDS (Continued) On the front of the TKS Ice Protection System Tank: (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-19 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 LIMITATIONS (Continued) PLACARDS (Continued) EXTERIOR PLACARDS (Continued) Adjacent to TKS Ice Protection Porous Panels: FAA APPROVED S1-20 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 EMERGENCY PROCEDURES RED A-ICE PRESS LOW ANNUNCIATOR COMES ON INTERMITTENTLY WITH PRIMARY SWITCH SELECTED TO NORM 1. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH IF A-ICE PRESS LOW ANNUNCIATOR REMAINS ON 2. BACKUP Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 3. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF NOTE The white A-ICE NORM annunciator will not be shown on PFD with the BACKUP switch selected to the ON position. 4. PRI ANTI-ICE Circuit Breaker . . . . . . . . . . . . . OPEN (pull out) (first row, fifth breaker from aft end) 5. TKS Ice Protection System . . . . . . . . . . . . . . . . . . . MONITOR 6. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 120 KIAS (or greater until final approach and landing) 7. Icing Conditions . . . . . . . . . . . EXIT AS SOON AS POSSIBLE IF A-ICE PRESS LOW ANNUNCIATOR GOES OFF 2. TKS Ice Protection System. . . . . . . . . . . . . . . . . . . . MONITOR 3. Icing Conditions . . . . . . . . . . . EXIT AS SOON AS POSSIBLE RED A-ICE PRESS LOW ANNUNCIATOR COMES ON WITH PRIMARY SWITCH SELECTED TO HIGH OR MAX FLOW SWITCH SELECTED TO AIRFRAME 1. BACKUP Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 2. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF NOTE The white A-ICE HIGH annunciator will not be shown on PFD with the BACKUP switch selected to the ON position. 3. PRI ANTI-ICE Circuit Breaker. . . . . . . . . . . . . . OPEN (pull out) (first row, fifth breaker from aft end) 4. TKS Ice Protection System. . . . . . . . . . . . . . . . . . . . MONITOR 5. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 120 KIAS (or greater until final approach and landing) 6. Icing Conditions . . . . . . . . . . . EXIT AS SOON AS POSSIBLE FAA APPROVED 208BPHCUS-S1-02 U.S. S1-21 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 EMERGENCY PROCEDURES (Continued) AMBER A-ICE PRESS HI OR A-ICE FLUID LO ANNUNCIATOR COMES ON 1. Icing Conditions. . . . . . . . . . . . EXIT AS SOON AS POSSIBLE 2. TKS Ice Protection System . . . . . . . . . . . . . . . . . . . . MONITOR FAILURE OF ICE PROTECTION SYSTEM OR EXCESSIVE ICE ACCUMULATION (OBSERVED OR SUSPECTED) ON PROTECTED AIRPLANE SURFACES 1. MAX FLOW Switch . . . . . . . . . . . . . . . . . . . . . . . . . AIRFRAME 2. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 120 KIAS (or greater until final approach and landing) 3. Icing Conditions. . . . . . . . . . . . EXIT AS SOON AS POSSIBLE 4. Landing Distance. . . . . . MULTIPLY POH/AFM DISTANCE BY: 2.2 - WING FLAPS UP 2.1 - WING FLAPS TO/APR 5. Minimum Approach Airspeed . . . . . . . . . . . . . . AT OR ABOVE: 120 KIAS - WING FLAPS UP 110 KIAS - WING FLAPS TO/APR WARNING • With an inoperative TKS Ice Protection System porous panel(s), increase power to Maximum Rated and exit icing conditions as soon as possible. In heavy icing conditions, it may not be possible to maintain altitude or proper glide path on approach. In this case, it is imperative that a safe airspeed be maintained. • Stall speeds will increase with ice accumulation on the wing and tail leading edges. Expect higher than normal rates of descent with power reduction. (Continued Next Page) FAA APPROVED S1-22 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 EMERGENCY PROCEDURES (Continued) FAILURE OF ICE PROTECTION SYSTEM OR EXCESSIVE ICE ACCUMULATION (OBSERVED OR SUSPECTED) ON PROTECTED AIRPLANE SURFACES (Continued) WARNING • With unshed ice accumulations on the horizontal stabilizer leading edge, do not extend flaps while enroute or holding. When preparing to land use the minimum flap setting required. Do not exceed WING FLAPS TO/APR and maintain extra airspeed consistent with available field length. Do not retract the flaps once they have been extended unless required for go-around. When executing a go-around, retract flaps while maintaining 5 to 10 knots extra airspeed. • Use of WING FLAPS LAND with an ice contaminated horizontal stabilizer leading edge can result in abnormal elevator control forces. The pilot should be prepared to apply the necessary elevator control inputs to maintain the desired pitch attitude while retracting the WING FLAPS to TO/APR. • The aural stall warning system does not provide adequate stall warning in all icing conditions. (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-23 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 EMERGENCY PROCEDURES (Continued) FAILURE OF ICE PROTECTION SYSTEM OR EXCESSIVE ICE ACCUMULATION (OBSERVED OR SUSPECTED) ON PROTECTED AIRPLANE SURFACES (Continued) NOTE • Maintain a minimum airspeed of 120 KIAS with WING FLAPS UP (110 KIAS minimum if climbing). If unable to maintain this airspeed in level flight, allow altitude to decease to maintain airspeed. • If there are unshed ice accumulations along the wing, wing strut, or stabilizer leading edges during approach and landing, follow the procedures listed under Inadvertent Icing Encounters in Section 3, Emergency Procedures, of the POH/AFM. • With an accumulation of 0.25 inch (6.35 mm) or more on the wing leading edges, be prepared for a significantly higher power requirement, approach speed, stall speed, and longer landing roll. • If necessary, set up a forward slip for visibility through the left portion of the windshield during the landing approach. • Select the minimum flap setting required for available field length. Use a minimum approach speed for the selected landing configuration. With ice suspected on the airframe, or operating at OAT 5°C (41°F) or less in visible moisture, do not extend WING FLAPS beyond TO/APR for landing. FAA APPROVED S1-24 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 EMERGENCY PROCEDURES (Continued) INADVERTENT ICING ENCOUNTER AT ALTITUDES ABOVE 20,000 FEET 1. IGNITION Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 2. TKS Ice Protection System. . . . . . . . . . . . . . . . . . . . . . . . . . ON a. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM (select HIGH if required) b. MAX FLOW Switch . . . . . . . . . . . . . . . . . . . WINDSHIELD (press momentarily and repeat if necessary to keep windshield free of ice) c. P/S HEAT/LOW A/S AWARE Switch . . . . . . . . . . . . . . . ON d. STALL HEAT Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . ON e. INERTIAL SEPARATOR. . . . . . . . . . . . . . . . . . . . . BYPASS (rotate counterclockwise and PULL out) CAUTION If the INERTIAL SEPARATOR is set to BYPASS at any point due to suspected or actual icing conditions, do not return it to NORMAL until the inertial separator door has been visually inspected and verified free of ice and ice protection fluid. 3. CABIN HEAT and DEFROST Controls. . . . . . . . . . . . . . . . . ON 4. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . 160 KIAS MAXIMUM 5. Altitude . . . . . . . . . . . . . . . . . . . . . DESCEND TO 20,000 FEET (or below as soon as practical) NOTE • Operate in accordance with the Normal Procedures contained in this supplement at altitudes of 20,000 feet or below. • Do not climb above 20,000 feet with any residual ice on the airplane, regardless of atmospheric conditions. • Turn IGNITION switch OFF after exiting icing conditions. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-25 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 EMERGENCY PROCEDURES (Continued) INERTIAL SEPARATOR MALFUNCTION 1. INERTIAL SEPARATOR . . . . . . . . . . . . . . . . . . . . . . . BYPASS (rotate counterclockwise and PULL out) CAUTION If the INERTIAL SEPARATOR is set to BYPASS at any point due to suspected or actual icing conditions, do not return it to NORMAL until the inertial separator door has been visually inspected and verified free of ice and ice protection fluid. 2. Engine TRQ Indicator . . . . . . . . . . . . . . . . . . . . . . . . MONITOR (torque redline and torque bug should drop approximately 100 to 200 foot-pounds) IF INERTIAL SEPARATOR FAILS TO MOVE TO BYPASS 3. IGNITION Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 4. Icing Conditions. . . . . . . . . . . . EXIT AS SOON AS POSSIBLE PROPELLER ANTI-ICE SYSTEM MALFUNCTION IF UNEVEN OR INADEQUATE ANTI-ICING OF THE PROPELLER BLADES IS INDICATED BY EXCESSIVE VIBRATION 1. A-ICE Annunciator. . . . . . . . . . . . . . . VERIFY NORM OR HIGH (PRIMARY switch in NORM or HIGH) 2. PROP RPM Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CYCLE (MAX to MIN and return to MAX) IF EXCESSIVE PROPELLER VIBRATION CONTINUES 3. MAX FLOW Switch . . . . . . . . . . . . . . . . . . . . . . . . . AIRFRAME 4. Icing Conditions. . . . . . . . . . . . EXIT AS SOON AS POSSIBLE FAA APPROVED S1-26 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 EMERGENCY PROCEDURES (Continued) WINDSHIELD ANTI-ICE SYSTEM MALFUNCTION IF WINDSHIELD ANTI-ICE SYSTEM DOES NOT DELIVER FLUID TO THE WINDSHIELD 1. W/S ANTI-ICE Circuit Breaker . . . . . . . . . . . . . . . . . . . CHECK (verify circuit breaker is IN) (second row, fifth breaker from forward end) 2. MAX FLOW Switch . . . . . . WINDSHIELD, HOLD 6 SECONDS (wait for total of 10 seconds) IF WINDSHIELD ANTI-ICE SYSTEM STILL DOES NOT DELIVER FLUID TO THE WINDSHIELD 3. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH 4. Icing Conditions . . . . . . . . . . EXIT AS SOON AS PRACTICAL NOTE • Plan a straight-in approach if possible. • Execute a forward slip as required for visibility through left portion of the windshield. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-27 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 EMERGENCY PROCEDURES (Continued) AMBER L P/S HEAT, R P/S HEAT OR L-R P/S HEAT ANNUNCIATOR COMES ON 1. PITOT HEAT Circuit Breakers (L and R). . . . . . . . . . . . CHECK (verify both circuit breakers are IN) (first and second row, third breaker from aft end) 2. Icing Conditions. . . . . . . . . . . . . . . . . . . . . EXIT IMMEDIATELY WARNING Do not rely on the Low Airspeed Awareness System if L P/S HEAT or L-R P/S HEAT annunciator comes on. IF AMBER L P/S HEAT OR R P/S HEAT ANNUNCIATOR SHOWN ON PFD 3. SENSOR Softkey . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PRESS 4. ADC 1/2 Softkey . . . . . . . . . . . . SELECT OPPOSITE SYSTEM 5. PFD ADI Displays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (amber BOTH ON ADC 1 or 2 shown on both PFDs) IF AMBER L-R P/S HEAT ANNUNCIATOR SHOWN ON PFD 3. Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE 4. ALT STATIC AIR Knob . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON (pull full out) NOTE The alternate static source is connected to the pilot side Air Data Computer (ADC1) and standby instruments only. Refer to POH/AFM, Section 5, Performance, Figure 5-1 (Sheet 2), Airspeed Calibration, and Figure 5-2, Altimeter Correction, for Alternate Static Source airspeed and altimeter corrections. 5. Airspeed . . . . . . . . . . . .EXPECT UNRELIABLE INDICATIONS 6. Fly the airplane using attitude, altitude, and power instruments. FAA APPROVED S1-28 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 EMERGENCY PROCEDURES (Continued) AMBER STALL HEAT ANNUNCIATOR COMES ON If ice is observed forming on the stall warning vane or its mounting plate. 1. STALL WARN Circuit Breaker . . . . . . . . . . . . . . . . . . . CHECK (verify circuit breaker is IN) (bottom row, third breaker from forward end) 2. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR NOTE • With continued ice buildup, expect no stall warning horn during slow speed operation. • Do not rely on the stall warning system. Maintain airspeed in accordance with the Minimum Speed In Icing Conditions in the Limitations section of this supplement. • LAA functionality is independent of stall warning. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-29 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 EMERGENCY PROCEDURES (Continued) INADVERTENT ENCOUNTER WITH FREEZING RAIN, FREEZING DRIZZLE, OR OTHER PERFORMANCE CRITICAL ICING SITUATION NOTE Refer to Environmental Conditions, Limitations, contained in this supplement for visual cues to identify severe icing conditions (freezing rain or freezing drizzle). ENROUTE 1. POWER Lever. . . . . . . . INCREASE TO MAXIMUM TAKEOFF (do not exceed 850° ITT or 103.7% Ng) 2. Minimum Airspeed. . . . . . . . . . . . . . . . . . . . . . . . . . . . 120 KIAS (110 KIAS if climbing to exit icing condition) 3. TKS Ice Protection System . . . . . . . . . . . . . . . . . . . . . . . . . . ON a. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH b. MAX FLOW Switch . . . . . . AIRFRAME then WINDSHIELD (press momentarily) c. P/S HEAT/LOW A/S AWARE Switch . . . . . . . . . . . . . . . ON d. STALL HEAT Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON e. LED PANELS/ANNUN Rheostat. . . . . . . . . . . . . . ADJUST (for ambient lighting conditions) f. IGNITION Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON g. INERTIAL SEPARATOR . . . . . . . . . . . . . . . . . . . . BYPASS (rotate counterclockwise and PULL out) CAUTION If the INERTIAL SEPARATOR is set to BYPASS at any point due to suspected or actual icing conditions, do not return it to NORMAL until the inertial separator door has been visually inspected and verified free of ice and ice protection fluid. 4. ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY (declare an emergency to exit icing conditions) 5. Icing Conditions. . . . . . . . . . . . . . . . . . . . . EXIT IMMEDIATELY (Continued Next Page) FAA APPROVED S1-30 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 EMERGENCY PROCEDURES (Continued) INADVERTENT ENCOUNTER WITH FREEZING RAIN, FREEZING DRIZZLE, OR OTHER PERFORMANCE CRITICAL ICING SITUATION (Continued) APPROACH 1. POWER Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE (as required to maintain airspeed and glidepath) Do not exceed 850° ITT or 103.7% Ng. 2. Recommended Airspeed . . . . . . . . . . . . . . . . . . . . . . 120 KIAS 3. WING FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO/APR 4. TKS Ice Protection System. . . . . . . . . . . . . . . . . . . . . . . . . . ON a. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH b. MAX FLOW Switch . . . . . AIRFRAME then WINDSHIELD (press momentarily) c. P/S HEAT/LOW A/S AWARE Switch . . . . . . . . . . . . . . . ON d. STALL HEAT Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . ON e. LED PANELS/ANNUN Rheostat . . . . . . . . . . . . . . ADJUST (for ambient lighting conditions) f. IGNITION Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON g. INERTIAL SEPARATOR. . . . . . . . . . . . . . . . . . . . . BYPASS (rotate counterclockwise and PULL out) CAUTION If the INERTIAL SEPARATOR is set to BYPASS at any point due to suspected or actual icing conditions, do not return it to NORMAL until the inertial separator door has been visually inspected and verified free of ice and ice protection fluid. 5. ATC. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY (declare an emergency and request straight-in approach) 6. Minimum Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . 110 KIAS FAA APPROVED 208BPHCUS-S1-02 U.S. S1-31 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 EMERGENCY PROCEDURES (Continued) AMBER BELOW ICING MIN SPD ANNUNCIATOR FLASHING AND AURAL WARNING HORN SOUNDS IF ENROUTE (FLAPS UP) 1. Autopilot . . . . . . . . . . . . . . . . . . . . . . . . VERIFY DISCONNECT 2. POWER Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE (airspeed above 95 KIAS) 3. Icing Conditions. . . . . . . . . . . . . . . . . . . . . EXIT IMMEDIATELY 4. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95 KIAS (minimum or greater during exit) 5. Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED WARNING WING Flaps must be extended to TO/APR anytime airspeed is below 95 KIAS. IF ON APPROACH (WING FLAPS - TO/APR) 1. Autopilot . . . . . . . . . . . . . . . . . . . . . . . . VERIFY DISCONNECT 2. POWER Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE 3. Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONTINUE 4. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR (observe minimum airspeed for icing with WING FLAPS TO/ APR) 5. Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS DESIRED NOTE When landing is assured the BELOW ICING MIN SPD annunciator can be pushed to silence the horn. FAA APPROVED S1-32 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 NORMAL PROCEDURES WARNING • Purge TKS panels after application of any type of deice fluid. Placing the BACKUP switch in the ON position for the recommended 4 minute interval will ensure that the TKS panels are clear of any residual deice fluid. Residual deice fluid may become trapped in the TKS panels and could potentially freeze and block or reduce TKS panel fluid flow. • Do not delay activation of the TKS Ice Protection System with ice forming on the airplane. • In order to minimize ice accumulations on unprotected lower surfaces, maintain a minimum speed of 95 KIAS with WING FLAPS UP during operations in icing conditions. If unable to maintain 95 KIAS at Maximum Rated Power, change altitude and/or course to exit conditions. NOTE Icing conditions are defined as visually detected ice, or the presence of visible moisture in any form at an OAT of 5°C (41°F) or below. If there is an inadvertent delay in activating the TKS Ice Protection System, select PRIMARY Switch to HIGH until all ice is removed, then select NORM or HIGH as required to prevent ice accumulation. (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-33 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 NORMAL PROCEDURES (Continued) WARNING The TKS Ice Protection System should not normally be activated in dry, cold air. The ice protection fluid is designed to mix with water impinging on the airplane surface in normal operation. If dispensed in dry, cold air, the fluid becomes a gel that takes considerable time to clear, particularly on the windshield. The windshield pump cycles for approximately 4 seconds each time it is activated. The windshield will take approximately 30 seconds to clear after the spray cycle has ended. Ice should not be allowed to accumulate on the windshield. Activate the windshield pump as necessary to maintain clear forward vision. Refer to Airplane and Systems Descriptions, TKS Ice Protection System Operation, Indication and Messaging in this supplement for description and operation of TKS indications. CAUTION • Other than the prescribed preflight steps outlined in this section, BACKUP mode should not be used during normal operations. It is intended for emergency use only (as detailed in the Emergency Procedures of this supplement). When operating the TKS Ice Protection System use Normal Procedures, and make sure that the BACKUP Switch is selected to OFF. • Simultaneous operations of the PRIMARY switch selected to either NORM or HIGH and the BACKUP switch selected to ON will increase fluid flow rates without making the appropriate adjustments to the time remaining function displayed on the MFD. There are no system annunciations for operating the system in BACKUP mode. The time remaining function of the system display will become unreliable; fluid quantity accuracy remains unchanged. FAA APPROVED S1-34 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 NORMAL PROCEDURES (Continued) PREFLIGHT INSPECTION  CABIN 1. BATTERY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 2. AVIONICS No. 1 Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON IF OAT IS BELOW 15°C (59°F) CAUTION With TKS Ice Protection System fluid temperatures at or above 15°C (59°F) the fluid viscosity will decrease, or become thinner, and may affect proper fluid flow to parts of individual panels. If OAT is above 15°C (59°F), refer to the procedure on the following pages. 3. BACKUP Switch . . . . . . . . . . ON FOR 4 MINUTES; THEN OFF NOTE Listen for pump operation, verify red A-ICE PRESS LOW annunciator initially comes ON then goes OFF as system flow and pressure build. 4. NAV Lights Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 5. Windshield Ice Detection Light . . CHECK FOR ILLUMINATION 6. WING LIGHT Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON (verify wing inspection light on) 7. LED PANELS/ANNUN Rheostat. . . . . . . . . . . . . . . . . . ADJUST (for ambient lighting conditions) 8. P/S HEAT/LOW A/S AWARE Switch . ON FOR 30 SECONDS; THEN OFF 9. BELOW ICING MIN SPD Light . . . . . . . . . . . . . . . . VERIFY ON (check light brightness for ambient conditions) 10. STALL HEAT Switch . . . . . ON FOR 30 SECONDS; THEN OFF 11. All Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-35 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 NORMAL PROCEDURES (Continued) PREFLIGHT INSPECTION (Continued)  CABIN (Continued) IF OAT IS AT OR ABOVE 15°C (59°F) CAUTION • With TKS Ice Protection System fluid temperatures at or above 15°C (59°F) the fluid viscosity will decrease, or become thinner, and may affect proper fluid flow to parts of individual panels. With lower fluid viscosity operating pressure may not be high enough to cancel the red A-ICE PRESS LOW annunciator. • It is extremely important to visually inspect each TKS panel for proper fluid flow across a portion of the active area of each panel prior to flight into known or forecast icing conditions. NOTE At these higher temperatures TKS panels may not “Wet Out or achieve 100% saturation” like they do at cooler temperatures. 3. BACKUP Switch . . . . . . . . . ON FOR 4 MINUTES; THEN OFF NOTE Listen for pump operation, verify red A-ICE PRESS LOW annunciator initially comes ON then goes OFF as system flow and pressure build. 4. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH (verify white A-ICE HIGH annunciator comes on) 5. MAX FLOW Switch . . . . . . . . . . . . . . . . . . . . . . . . . AIRFRAME (press momentarily and check operation) 6. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF (verify white A-ICE HIGH annunciator goes off) (Continued Next Page) FAA APPROVED S1-36 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 NORMAL PROCEDURES (Continued) PREFLIGHT INSPECTION (Continued)  CABIN (Continued) IF OAT IS AT OR ABOVE 15°C (59°F) (Continued) 7. NAV Lights Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON 8. Windshield Ice Detection Light . . CHECK FOR ILLUMINATION 9. WING LIGHT Switch. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON (verify wing inspection light on) 10. LED PANELS/ANNUN Rheostat. . . . . . . . . . . . . . . . . . ADJUST (for ambient lighting conditions) 11. P/S HEAT/LOW A/S AWARE Switch . ON FOR 30 SECONDS; THEN OFF 12. BELOW ICING MIN SPD Light . . . . . . . . . . . . . . . . VERIFY ON (check light brightness for ambient conditions) 13. STALL HEAT Switch . . . . . ON FOR 30 SECONDS; THEN OFF 14. All Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FAA APPROVED 208BPHCUS-S1-02 U.S. S1-37 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 NORMAL PROCEDURES (Continued) PREFLIGHT INSPECTION (Continued)  External Inspection (See Preflight Checks in Limitations) 1. Wings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK 2. Horizontal Stabilizer. . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK 3. Vertical Stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK 4. Windshield. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK WARNING Conduct a visual and tactile inspection of all critical surfaces in accordance with the Limitations Section of this supplement, to make sure complete removal of contamination. 5. TKS Ice Protection System Fluid Tank . . . CHECK QUANTITY and CAP SECURED (Min. 11.7 U.S. gallons) CAUTION The airplane must be level to assure accurate TKS Ice Protection System fluid quantity when using the fluid tank sight gage on the TKS Ice Protection System tank. 6. Porous Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (verify condition, security and even distribution of fluid flow from all panels) CAUTION Look for signs of TKS Ice Protection System fluid leakage through bonded area of the porous panels. If TKS Ice Protection System fluid is leaking through the bonded seam do not operate the TKS Ice Protection System. 7. Propeller . . . . . . . . . . . . . . . . . . . . CHECK FOR FLUID FLOW 8. Windshield Spray Bar . . . . . . . . . . . . . . . . CHECK CONDITION 9. Stall Warning Vane . . . . . . . . . . . . . . . . PERCEPTIBLY WARM 10. PITOT/STATIC Tubes . . . . . . . . . . CLEAR AND VERY WARM 11. Static Wicks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (verify condition and security) FAA APPROVED S1-38 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 NORMAL PROCEDURES (Continued) BEFORE STARTING ENGINE 1. TKS Ice Protection System: a. Windshield Pump . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK (1) MAX FLOW Switch . . . . . . . . . . . . . . . . WINDSHIELD (press momentarily and verify spray on pilot’s windshield) b. TKS Ice Protection System Pumps . . . . . . . . . . . . CHECK (1) PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . HIGH (verify white A-ICE HIGH annunciator comes ON, listen for pump operation) (2) PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . NORM (verify white A-ICE NORM annunciator comes ON) (3) MAX FLOW Switch . . . . . . . . . . . . . . . . . . AIRFRAME (press momentarily and check operation) (4) PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . OFF (verify white A-ICE NORM annunciator goes off) c. BACKUP Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON (verify pump is running; then OFF) d. A-ICE Annunciator . . . . . . . . . . . . . . . . . . . . . VERIFY OFF 2. INERTIAL SEPARATOR . . . . . . . . . . . . . . . . . . . . . . . . BYPASS (rotate counterclockwise and PULL out) (visible moisture and OAT 5°C (41°F) or below) CAUTION If the INERTIAL SEPARATOR is set to BYPASS at any point due to suspected or actual icing conditions, do not return it to NORMAL until the inertial separator door has been visually inspected and verified free of ice and ice protection fluid. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-39 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 NORMAL PROCEDURES (Continued) BEFORE TAKEOFF CHECK If icing conditions are anticipated or at the first indication of ice accretion after takeoff: 1. TKS Ice Protection System . . . . . . . . . . . . . . . . . . . . . . . . . . ON a. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM (select HIGH if required) NOTE In order to conserve fluid, the PRIMARY switch may be left OFF until actual ice can be seen accreting on the airplane. This is usually first noted on the lower portion of the windshield. However, to speed the ice shedding, the PRIMARY switch should then be set to HIGH flow until the ice has cleared from the wing leading edges. Usually this will take only three to five minutes. The PRIMARY switch may then be reset to NORM. b. MAX FLOW Switch . . . . . . . . . . . . . . . . . . . . WINDSHIELD (press momentarily and repeat if necessary to keep windshield free of ice) NOTE The ice that forms on the windshield can be cleared immediately by placing the MAX FLOW switch in the WINDSHIELD position momentarily. The spray from the propeller will generally also clear the windshield but will require a longer period of time. c. P/S HEAT/LOW A/S AWARE Switch . . . . . . . . . . . . . . . ON d. STALL HEAT Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON e. INERTIAL SEPARATOR . . . . . . . . . . . . . . . . . . . . BYPASS (rotate counterclockwise and PULL out) CAUTION If the INERTIAL SEPARATOR is set to BYPASS at any point due to suspected or actual icing conditions, do not return it to NORMAL until the inertial separator door has been visually inspected and verified free of ice and ice protection fluid. (Continued Next Page) FAA APPROVED S1-40 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 NORMAL PROCEDURES (Continued) BEFORE TAKEOFF CHECK (Continued) 2. LED PANELS/ANNUN Rheostat. . . . . . . . . . . . . . . . . . ADJUST (check BELOW ICING MIN SPD light brightness for ambient conditions) CAUTION Do not operate the P/S HEAT/LOW A/S AWARE switch or STALL HEAT switch for prolonged periods of time on the ground. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-41 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 NORMAL PROCEDURES (Continued) ALL FLIGHT CONDITIONS/PHASES WARNING • During flight in anticipated or actual icing conditions, the pilot must regularly monitor the performance of the TKS Ice Protection System. If ice is observed building on the leading edge of the wing with the PRIMARY switch in NORM, immediately select PRIMARY switch to HIGH. • If ice is observed building on the leading edge of the wing with PRIMARY switch in HIGH, immediately select MAX FLOW switch to AIRFRAME and execute the Emergency Procedure for Failure Of Ice Protection System Or Excessive Ice Accumulation (Observed Or Suspected) On Protected Airplane Surfaces. Exit icing conditions immediately. • P/S HEAT/LOW A/S AWARE switch must be turned ON when operating in visible moisture with an OAT of 5°C (41°F) or below. • LED PANELS/ANNUN rheostat must be adjusted for the ambient lighting conditions so the BELOW ICING MIN SPD light is visible. FAA APPROVED S1-42 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 NORMAL PROCEDURES (Continued) TAKEOFF 1. WING FLAPS Handle . . . . . . . . . . . . . . . . . . . . . UP or TO/APR (TO/APR recommended) (WING FLAPS UP if using Type II, III, or IV anti-ice fluid) 2. POWER Lever . . . . . . . . . . . . . . . . . . . . . SET FOR TAKEOFF (observe Takeoff ITT and Ng limits) 3. ANNUNCIATOR(s) . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK 4. Rotate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70 KIAS (83 KIAS Flaps UP) 5. WING FLAPS Handle . . . . . . . . . . . . . . . . . . . RETRACT to UP (after reaching 95 KIAS) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-43 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 NORMAL PROCEDURES (Continued) INFLIGHT (CLIMB, CRUISE, AND DESCENT) At the first indication of ice accretion: 1. TKS Ice Protection System . . . . . . . . . . . . . . . . . . . . . . . . . . ON a. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM (select HIGH if required) b. MAX FLOW Switch . . . . . . . . . . . . . . . . . . . . WINDSHIELD (press momentarily and repeat if necessary to keep windshield free of ice) c. P/S HEAT/LOW A/S AWARE Switch . . . . . . . . . . . . . . . ON d. STALL HEAT Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON e. BELOW ICING MIN SPD Switch Light . . PRESS TO TEST f. LED PANELS/ANNUN Rheostat. . . . . . . . . . . . . . ADJUST (for ambient lighting conditions) g. INERTIAL SEPARATOR . . . . . . . . . . . . . . . . . . . . BYPASS (rotate counterclockwise and PULL out) CAUTION If the INERTIAL SEPARATOR is set to BYPASS at any point due to suspected or actual icing conditions, do not return it to NORMAL until the inertial separator door has been visually inspected and verified free of ice and ice protection fluid. 2. CABIN HEAT and DEFROST Controls . . . . . . . . . . . . . . . . . ON 3. PROP RPM Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . 1900 RPM 4. POWER Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE (as required to maintain safe airspeed or to climb out of icing conditions, if possible) NOTE When climbing through icing conditions, it is recommended that the Maximum Climb Power rating be used (1900 RPM and 2397 ft-lb., not to exceed 825°C ITT or 103.7% Ng). Refer to POH/AFM, Section 5, Performance, Figure 5-9, Maximum Engine Torque for Climb for approved settings. (Continued Next Page) FAA APPROVED S1-44 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 NORMAL PROCEDURES (Continued) INFLIGHT (CLIMB, CRUISE, AND DESCENT) (Continued) 5. Minimum Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95 KIAS 6. WING LIGHT Switch. . . . . . . . . . . . . . . . . . . . . AS REQUIRED WARNING • When disengaging the autopilot with ice buildup on the airplane, the pilot should be alert for out of trim forces. Pilot control wheel input should be applied as required to prevent potential undesired flight path deviations. • Monitor airspeed in icing conditions with the autopilot engaged. The autopilot will maintain altitude or vertical speed at the expense of airspeed as drag increases due to ice accretion on the airplane. • If pre-stall buffet or uncommanded pitch oscillations are encountered, reduce pitch attitude while increasing power to Max Rated. Promptly extend WING FLAPS to TO/APR to help stabilize the airplane. If necessary, do not attempt to maintain altitude until positive recovery from buffet is achieved. Increase airspeed to 95 KIAS or greater before retracting flaps. If the flaps are subsequently retracted, maintain at least 10 KIAS above initial buffet airspeed. NOTE The autopilot may be used in icing conditions. However, every 10-15 minutes the autopilot should be disengaged to detect any out of trim conditions caused by ice buildup. If significant out of trim conditions are detected, the autopilot should remain off for the remainder of the icing encounter. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-45 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 NORMAL PROCEDURES (Continued) APPROACH If icing conditions exist, are anticipated, or at the first indication of ice accretion: 1. TKS Ice Protection System . . . . . . . . . . . . . . . . . . . . . . . . . . ON a. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM (select HIGH if required) b. MAX FLOW Switch . . . . . . . . . . . . . . . . . . . . WINDSHIELD (press momentarily) c. P/S HEAT/LOW A/S AWARE Switch . . . . . . . . . . . . . . . ON d. STALL HEAT Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON e. BELOW ICING MIN SPD Switch Light . . PRESS TO TEST f. LED PANELS/ANNUN Rheostat. . . . . . . . . . . . . . ADJUST (for ambient lighting conditions) g. INERTIAL SEPARATOR . . . . . . . . . . . . . . . . . . . . BYPASS (rotate counterclockwise and PULL out) CAUTION If the INERTIAL SEPARATOR is set to BYPASS at any point due to suspected or actual icing conditions, do not return it to NORMAL until the inertial separator door has been visually inspected and verified free of ice and ice protection fluid. 2. CABIN HEAT and DEFROST Controls . . . . . . . . . . . . . . . . . ON 3. WING LIGHT Switch . . . . . . . . . . . . . . . . . . . . . AS REQUIRED FAA APPROVED S1-46 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 NORMAL PROCEDURES (Continued) BEFORE LANDING At the first indication of ice accretion or if icing conditions exist or are anticipated or residual ice remains on the airframe: 1. WING FLAPS Handle . . . . . . . . . . . . . . . . . . . . AS REQUIRED (TO/APR MAX) 2. Recommended Airspeed . . . . . . . . . . . 105 KIAS - FLAPS UP 95 KIAS - FLAPS TO/APR 3. MAX FLOW Switch . . . . . . . . . . . . . . . . . . . . . . . WINDSHIELD (press momentarily as needed, minimum 30 seconds before landing to allow windshield to clear) NOTE • Multiply normal POH/AFM landing distance by 2.2 for WING FLAPS UP (120 KIAS maximum). • If the shortest landing distance is required due to field length, WING FLAPS TO/APR (maximum) may be used. Multiply normal POH/AFM landing distance by 2.1 (110 KIAS maximum). • When slowing for landing, expect the BELOW ICING MIN SPD annunciator to flash and aural warning to sound. • The pilot may fly a higher speed to avoid repeated LAA warnings. LANDING 1. WING FLAPS Handle . . . . . . . . . . . . . . . . . . . . AS REQUIRED (TO/APR MAX) 2. Recommended Airspeed . . . . . . . . . . . 105 KIAS - FLAPS UP 95 KIAS - FLAPS TO/APR 3. POWER Lever . . . . . . . . . . . . . REDUCE SLOWLY IN FLARE 4. Brakes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY FAA APPROVED 208BPHCUS-S1-02 U.S. S1-47 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 NORMAL PROCEDURES (Continued) BALKED LANDING 1. POWER Lever. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADVANCE (for takeoff power) 2. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95 KIAS (for climb) 3. WING FLAPS Handle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP AFTER LANDING 1. TKS Ice Protection System . . . . . . . . . . . . . . . . . . . . . . . . . OFF a. PRIMARY Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF b. BACKUP Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF c. P/S HEAT/LOW A/S AWARE Switch . . . . . . . . . . . . . . OFF d. STALL HEAT Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF 2. IGNITION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM SHUTDOWN AND SECURING AIRPLANE If the INERTIAL SEPARATOR was set to BYPASS during flight, perform the following after engine shutdown: 1. Inertial Separator Outlet . . . . . . . . . . . . . . . . . . . . . . . INSPECT (remove any ice and ice protection fluid if present) 2. Open Left Engine Cowl a. Inertial Separator Tunnel . . . . . . . . . . . . . . . . . . . INSPECT (remove any ice and ice protection fluid if present) b. Inertial Separator Door . . . . . . . . . . . . . . . . . . . . . INSPECT (remove any ice and ice protection fluid if present) 3. INERTIAL SEPARATOR . . . . . . . . . . . . . . . . . . . . . . . NORMAL (rotate clockwise and PUSH in) FAA APPROVED S1-48 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 PERFORMANCE Airplane performance and stall speeds without ice accretion are unchanged with installation of the TKS Ice Protection System. Use the performance charts located in the POH/AFM, Section 5, for performance calculations. NOTE If the TKS Ice Protection System is operating normally and preventing ice from accreting on the airframe protected areas and propeller, normal performance will only degrade slightly. If ice is allowed to accrete on the airframe protected areas, however, significant climb and cruise performance degradation, range reduction, as well as buffet and stall speed increase can be expected. Ice accretion on the airframe protected areas will cause noticeable performance losses. NORMAL AND BALKED LANDING RATE OF CLIMB Residual ice on unprotected airplane surfaces will cause a loss in rate of climb. Additional accumulation of ice on the airplane will result in significant loss in normal rate of climb. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-49 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 PERFORMANCE (Continued) STALL SPEED Stall speed is not significantly affected by residual ice on unprotected airplane surfaces. Stall speeds increase significantly with even small accumulations on the wing leading edge. The first 0.25 inch (6.35 mm) of ice accumulation on the wing leading edges causes the most rapid increase in stall speed. Additional ice accumulation on the wing leading edges results in a continued increase in stall speed, although at a less rapid rate. WARNING If pre-stall buffet or uncommanded pitch oscillations are encountered, disengage autopilot and reduce pitch attitude while increasing power to Maximum Rated Setting. Promptly extend the WING FLAPS to TO/APR to help stabilize the airplane. Increase airspeed to 95 KIAS or greater before retracting flaps. If the flaps are subsequently retracted, maintain at least 10 KIAS above initial buffet. PREFLIGHT PLANNING Figure S1-1 may be used for estimation of enroute altitude capability in icing conditions. After entering the chart with expected cruise weight and ambient temperature at altitude and cruise altitude, the pilot may plan the flight as follows: AREA A: These altitudes should be available under most icing conditions for prolonged periods of time. AREA C: These altitudes will probably not be available after ice begins to accrete on the airplane. Exiting the icing condition by climbing may not be possible. NOTE Exit strategies for icing conditions should be determined during preflight planning. FAA APPROVED S1-50 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 PERFORMANCE (Continued) ENROUTE TOOL FOR EXITING ICING Figure S1-1 must be used as one criteria for exiting icing conditions. Refer to Limitations, Environmental Conditions in this supplement for criteria for exiting icing conditions. Once enroute, if icing conditions are encountered such that ice begins to accrete on the airplane, the pilot MUST make their decision as follows: AREA A: If current route leg MEA or MOCA (if applicable) falls in this area, it is recommended that the pilot exit the icing conditions as soon as practical. AREA C: If current route leg MEA or MOCA (if applicable) falls in this area, the pilot must exit icing conditions immediately. CAUTION • Regardless of which area the airplane is operating, the pilot should continue to monitor ice buildup and airspeed decay and be prepared to exit icing immediately if icing conditions worsen. • Data on this chart is based on flight testing with critical ice shapes derived for 14 CFR Part 25, Appendix C icing envelope. While some icing conditions will produce ice accretions that result in performance better than shown here, some icing conditions (freezing drizzle or freezing rain) will result in considerably worse performance. (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-51 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 PERFORMANCE (Continued) ENROUTE TOOL FOR EXITING ICING (Continued) Figure S1-1* (Continued Next Page) FAA APPROVED S1-52 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 PERFORMANCE (Continued) ENROUTE TOOL FOR EXITING ICING (Continued) EXAMPLE USE OF ICING SERVICE CEILING CHART (Use Figure S1-1 for both examples) Direct Route: KSLC to KCPR (KSLC to OCS to DDY to KCPR) Takeoff Weight: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7850 Pounds MEA: . . . . . . . . . . . . . 18,000 Feet/19,000 Feet for direction of flight OAT at Altitude: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .-10°C Weight at Altitude: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7750 Pounds PREFLIGHT PLANNING Per Figure S1-1, initial operation is in Area C, indicating that prolonged exposure to icing conditions will not allow the airplane to climb to this altitude. ENROUTE LIMITATIONS If icing is encountered the pilot must exit icing immediately since enroute operation fell in Area C. Alternate Route: KSLC to KCPR (KSLC to FBR to OGD to DDY to KCPR) Takeoff Weight: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7850 Pounds MEA: . . . . . . . . . . . . . 16,000 Feet/17,000 Feet for direction of flight OAT at Altitude: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .-10°C Weight at Altitude: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7750 Feet PREFLIGHT PLANNING Per Figure S1-1, initial operation in Area A. Depending on severity of icing, the airplane should be able to reach this altitude in a climb. ENROUTE LIMITATIONS If icing conditions are encountered, it is recommended that the pilot exit the icing conditions as soon as practical. The pilot should monitor airspeed closely to assure compliance with other exit icing criteria. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-53 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 PERFORMANCE (Continued) LANDING When the airplane has encountered icing conditions, flap deflection is limited to a maximum deflection of TO/APR. An icing condition is defined as visually observing ice accumulation or flight in temperatures at 5°C (41°F) or below when any type of visible moisture is present. 1. Reference recommended 50 foot airspeed with ice on airframe in the Normal Procedures of this supplement; correct the applicable Short Field Landing Distance as follows for the appropriate flap setting: a. WING FLAPS UP LANDING - Multiply POH/AFM Total Landing Distance by 2.2. b. WING FLAPS TO/APR LANDING - Multiply POH/AFM Total Landing Distance by 2.1. CAUTION The notes found on the Short Field Landing Distance table in the POH/AFM are not applicable for airplanes with residual ice. FAA APPROVED S1-54 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 WEIGHT AND BALANCE CARGO POD LOADING ARRANGEMENTS TKS TANK INSTALLED NOTE The 195.77 inch station reference for TKS is for the fluid and tank installation and is not valid for computing the C.G. for the TKS Zone. Figure S1-2 FAA APPROVED 208BPHCUS-S1-02 U.S. S1-55 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 WEIGHT AND BALANCE (Continued) Figure S1-3 FAA APPROVED S1-56 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 WEIGHT AND BALANCE (Continued) WEIGHING PROCEDURES 1. In preparation to weighing and calculating the empty weight of the TKS Ice Protection System equipped Cessna Caravan; the TKS Ice Protection System must be drained of all fluid. Drain fluid from tank through the drain valve on the left side of the tank sump. When drained, no appreciable unusable fluid will remain in the tank. 2. After draining all appreciable fluid from the tank, follow the preparation and weighing instructions as specified in Section 6, Weight and Balance of the POH/AFM. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-57 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 WEIGHT AND BALANCE (Continued) Figure S1-4 (Sheet 1 of 2) FAA APPROVED S1-58 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 WEIGHT AND BALANCE (Continued) Figure S1-4 (Sheet 2) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-59 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS SYSTEM DESCRIPTION The TKS Ice Protection System includes laser-drilled titanium porous panels for the leading edges of the wings, horizontal and vertical stabilizers, lift struts, propeller fluid slinger ring and windshield fluid spray bar. Refer to Figures S1-5 and S1-6 for system installation and fluid schematic. The outer skin of the ice protection panels are manufactured with titanium, which provides excellent strength, durability, light weight, and corrosion resistance. The panel skin is perforated by laser drilling holes, 0.0025 inches in diameter, 800 per square inch. The porous areas of the titanium panels are designed to assure fluid coverage from best rate of climb speed to maximum operating speed. The back plates of the panels are also manufactured out of titanium and are formed to create reservoirs for the ice protection fluid, allowing fluid supply to the entire porous area. A porous membrane between the outer skin and the reservoir assure even flow and distribution through the entire porous area of the panel. The porous panels are bonded or attached as a cuff over a leading edge. Panels are bonded to the airframe with a two-part, flexible adhesive. Fluid is supplied to the panels and propeller by two positive displacement, constant volume metering pumps. The pumps provide various flow rates to the panels and propeller. Single pump operation, a combined mode, and timed pumping provide a range of flow rates for different icing conditions. Fluid for the windshield spray bar system is provided by an on-demand gear pump. The spray bar may be activated as needed to clear forward vision through the windshield. (Continued Next Page) FAA APPROVED S1-60 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) SYSTEM DESCRIPTION (Continued) TKS ICE PROTECTION SYSTEM INSTALLATION Figure S1-5 (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-61 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) TKS ICE PROTECTION SYSTEM FLUID SCHEMATIC Figure S1-6* FAA APPROVED S1-62 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) SYSTEM DESCRIPTION (Continued) The fluid passes through (a) microfilter(s) prior to distribution to the porous panels and propeller. The filter(s) assure(s) all contaminants are removed from the fluid and prevents panel blockage. A system of nylon tubing carries the fluid to proportioning units located in the wings and tail of the airplane. The proportioning units divide the flow into the volumetric requirements of each panel or device supplied through the unit. Each panel and device is fed again with nylon tubing. The TKS Ice Protection System tank is located in the cargo pod and serviced through a single filler located on the left side of the pod, near the left main landing gear. The tank has a maximum capacity of 20.8 gallons (78.7 Liters). It is the pilot’s responsibility to make sure that an adequate quantity of TKS fluid is carried for the planned mission. A minimum of 11.7 gallons (44.3 Liters) in the tank is required before takeoff if the system is to be considered operational for dispatch into known icing conditions. This minimum dispatch quantity must be determined by visual inspection of the sight gage located on the filler end of the TKS fluid tank, refer to Figure S1-10. CAUTION The sight gage is the only approved means of assuring adequate fluid quantity prior to flight into known or forecast icing conditions. The fluid level ball must be above the minimum dispatch quantity line, 11.7 U.S. Gallons, (44.3 Liters) with the airplane level to make sure proper indication. The TKS fluid quantity is also measured by a sensor which transmits an electrical signal to the level indicator. The fluid quantity indicator gage is displayed on the MFD, refer to Figure S1-9. (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-63 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) SYSTEM DESCRIPTION (Continued) The EIS strip on the MFD displays TKS (anti-ice) fluid quantity and time remaining feature to aid the pilot as to the amount of fluid/time available for ice protection. The system uses a series of colors to alert the pilot as to how much time is remaining based on fluid quantity and ANTI-ICE FLUID CONTROL switch position. Green readout informs the pilot of at least 20 minutes of ice protection with the PRIMARY switch in NORM; 8 minutes with the PRIMARY switch in HIGH. ANTI-ICE fluid quantity and time values displayed against an amber background with black text alerts the pilot of less than 20 minutes of ice protection with the PRIMARY switch in NORM; less than 8 minutes with the PRIMARY switch in HIGH. ANTI-ICE fluid quantity and time values displayed against a Red/White (reverse video) background alerts the pilot of less than 0.5 gallon of fluid. That equates to 5 minutes of ice protection with the PRIMARY switch in NORM; less than 2 minutes with the PRIMARY switch in HIGH. When BACKUP is selected, the time remaining function is unreliable and must not be used. A wing inspection light, controlled by the WING LIGHT switch, is provided to illuminate the leading edge of the left wing during night operation. FAA APPROVED S1-64 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) TKS ICE PROTECTION SYSTEM OPERATION, INDICATION AND MESSAGING The TKS Ice Protection system is operated with three toggle switches. These switches are located in the ANTI-ICE section of the lower left pilot’s instrument panel, refer to Figure S1-7. Control of the TKS Ice Protection System, ice detection light, pitot/static, Low Airspeed Awareness (LAA), and stall vane heat are included in this row of switches. Primary control of the system is accomplished through three switches labeled PRIMARY, MAX FLOW, and BACKUP. These switches activate the primary modes of ice protection, including Normal (NORM) and HIGH, Maximum (MAX FLOW AIRFRAME) and WINDSHIELD, and BACKUP, refer to Detail A of Figure S1-7. Normal mode is activated by selecting the NORM position (center) on the PRIMARY mode switch. NORM mode is the lowest fluid flow rate of the system. The flow rate is achieved by running both metering pumps of the system on a continuous repeat cycle of operation. The two pumps will run for approximately 20 seconds, then deactivate. After 100 seconds of inactivity, the pumps will again activate for the 20 second operation period. This on-off cycle of operation will continue until OFF is selected on the PRIMARY mode switch. HIGH mode is activated by selecting HIGH (up) on the PRIMARY mode switch. HIGH mode is achieved by running one metering pump continuously. Like NORM mode, the HIGH mode may be terminated by selecting OFF on the PRIMARY mode switch. Maximum flow (MAX FLOW) mode is provided for combating heavy or extreme icing conditions. For MAX FLOW mode to operate, the PRIMARY switch must be in either NORM or HIGH. With either of these modes operating, MAX FLOW mode may be activated by selecting the AIRFRAME position (spring-loaded up) on the MAX FLOW switch. The MAX FLOW switch is spring-loaded and will immediately return to the center position. (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-65 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) TKS ICE PROTECTION SYSTEM OPERATION, INDICATION AND MESSAGING (Continued) Activation of MAX FLOW AIRFRAME mode will run both metering pumps continuously for a period of two minutes. At the end of two minutes, the system will return to the mode of operation selected with the PRIMARY mode switch. MAX FLOW mode will terminate operation after: 1. The timer turns the mode OFF after two minutes, or 2. The PRIMARY mode switch is selected to OFF. CAUTION Each two minute use of MAX FLOW AIRFRAME mode consumes approximately one gallon of ice protection fluid, representing 5% of the total fluid capacity of the ice protection system. Use MAX FLOW AIRFRAME mode only when in heavy or extreme icing conditions. If conditions require MAX FLOW AIRFRAME use, exit the icing conditions immediately. The windshield system may be activated by selecting the WINDSHIELD position (spring-loaded down) on the MAX FLOW switch. The MAX FLOW switch is spring-loaded and will immediately return to the center position. The windshield pump will run for approximately four seconds after release of the switch. If the MAX FLOW switch is continuously held in the WINDSHIELD position, the windshield pump will continue to run when held down and four seconds after the switch is released. The windshield de-icing system is designed for intermittent operation to establish pilot's forward vision as conditions require. The timer interval is designed to provide an optimum burst of fluid for clearing the windshield of ice. Momentary selection and release of the WINDSHIELD switch will achieve the desired result. (Continued Next Page) FAA APPROVED S1-66 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 TKS ICE PROTECTION SYSTEM OPERATION, INDICATION AND MESSAGING Figure S1-7 FAA APPROVED 208BPHCUS-S1-02 U.S. S1-67 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) TKS ICE PROTECTION SYSTEM OPERATION, INDICATION AND MESSAGING (Continued) WARNING The windshield pump is rated for intermittent use only. Continuous operation may damage the pump. Do not operate the WINDSHIELD position of the MAX FLOW switch continuously longer than 6 seconds. Allow at least a total of 10 seconds between operations. The final operational mode of the system is the BACKUP mode. BACKUP mode is achieved by selecting the ON position (up) on the BACKUP switch. BACKUP mode activates the second metering pump (opposite of the pump used in HIGH mode) and runs continuously like HIGH mode. BACKUP mode is independent and isolated from the other ice protection operational modes. It is provided as a redundant capability in the event the normal operational modes are rendered inoperable. If BACKUP mode is selected in flight as prescribed in the Emergency Procedures of this supplement, then the PRIMARY Switch should be set to the OFF position, and the PRI ANTI-ICE circuit breaker pulled to deactivate the PRIMARY system. CAUTION Other than the prescribed preflight steps outlined in the Normal Procedures of this supplement, BACKUP mode should never be used during normal operations. It is intended for emergency use only (as detailed in the Emergency Procedures of this supplement). When operating the TKS Ice Protection System under normal procedures, make sure that the BACKUP Switch is selected to OFF. (Continued Next Page) FAA APPROVED S1-68 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) TKS ICE PROTECTION SYSTEM OPERATION, INDICATION AND MESSAGING (Continued) For the four modes of airframe ice protection operation, the resulting endurance with a full tank of fluid is: MAXIMUM FLUID ENDURANCE PRIMARY NORM selected . . . . . . . . . . . . . . . . 3 hours, 25 minutes PRIMARY HIGH selected . . . . . . . . . . . . . . . . . . 1 hour, 20 minutes BACKUP selected . . . . . . . . . . . . . . . . . . . . . . . . 1 hour, 20 minutes MAX FLOW AIRFRAME selected . . . . . . . . . . . . . . . . . . 40 minutes SYSTEMS ENDURANCE CHARACTERISTICS Figure S1-8 FAA APPROVED 208BPHCUS-S1-02 U.S. S1-69 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) TKS ICE PROTECTION SYSTEM OPERATION, INDICATION AND MESSAGING (Continued) SYSTEM FLUID QUANTITY INDICATIONS Figure S1-9 As stated earlier, the only approved means for determining the proper fluid quantity for dispatch into known icing conditions is the tank sight gage. The sight gage is located on the left side of the fluid tank, near the filler assembly. As illustrated in Figure S1-10, the sight gage may be viewed through the cargo pod door located ahead of the filler. To assure the minimum dispatch quantity is achieved, specific steps must be taken. First, the airplane must be sitting in a wings level attitude. If the airplane rests on a slope, the nose must be pointed up or down the slope. Second, the volume of fluid in the tank must be such that the bottom of the fluid ball is above the minimum dispatch line. When both conditions have been met, the tank contains the minimum quantity of fluid for flight into known icing. (Continued Next Page) FAA APPROVED S1-70 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTION (Continued) TKS ICE PROTECTION SYSTEM OPERATION, INDICATION AND MESSAGING (Continued) FLUID TANK SIGHT GAGE Figure S1-10 (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-71 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) TKS ICE PROTECTION SYSTEM OPERATION, INDICATION AND MESSAGING (Continued) The operational state of the TKS ice protection system may be monitored within the pilot’s and copilot’s PFD in the G1000 system. System status is constantly monitored and feedback is provided through various annunciations displayed in the annunciator window, located to the right of the vertical speed tape of each pilot’s PFD, refer to Figure S1-11. TKS SYSTEM ANNUNCIATIONS Figure S1-11 When the system is turned on using the PRIMARY mode switch, by selecting either NORM or HIGH the white A-ICE NORM or white A-ICE HIGH advisory message appears in the annunciation window. The appropriate white message, A-ICE NORM or A-ICE HIGH, will remain displayed independent of system operational conditions or status. The advisory message is not active in the BACKUP mode. The amber A-ICE PRESS HI annunciator is triggered by the high pressure sensor located on the system equipment/tank assembly. If the amber A-ICE PRESS HI annunciator is triggered, the system fluid filter(s) should be replaced. Activation of the amber A-ICE FLUID LO annunciator means a low fluid level condition exists and that at least 20 minutes of ice protection fluid endurance remains when the system is operated in NORM mode. (Continued Next Page) FAA APPROVED S1-72 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) TKS ICE PROTECTION SYSTEM OPERATION, INDICATION AND MESSAGING (Continued) NOTE When the amber A-ICE FLUID LO annunciator comes ON cross-check the anti-ice fluid quantity indication (A-ICE GAL) to verify a low fluid level condition exists. This system is designed to trigger the annunciator when anti-ice fluid quantity reaches 2 U.S. gallons (7.56 Liters). The red A-ICE PRESS LOW annunciator is tied to the two low pressure sensors in the tail of the airplane. A low pressure condition on either sensor will trigger the red A-ICE PRESS LOW annunciator, indicating that system pressure is too low for normal system operation and may be indicative of potential substandard ice protection performance. In BACKUP mode, the red A-ICE PRESS LOW annunciator is armed immediately upon selecting BACKUP ON. If a low pressure condition exists, the red A-ICE PRESS LOW annunciator will display immediately on both PFDs warning the crew to exit icing conditions immediately. NOTE With BACKUP selected ON, the red A-ICE PRESS LOW annunciator will momentarily appear and remain ON until system pressure is sufficient to inhibit the annunciator. The red A-ICE PRESS LOW annunciator is inhibited for a period of time in both PRIMARY modes of NORM and HIGH. When HIGH is selected, any red A-ICE PRESS LOW annunciator will be inhibited for 15 seconds. After the 15 second period, any low pressure condition will trigger the red A-ICE PRESS LOW annunciator. Selecting PRIMARY OFF will reset the CAS inhibiting functions. (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-73 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) TKS ICE PROTECTION SYSTEM OPERATION, INDICATION AND MESSAGING (Continued) Likewise, selecting NORM will also inhibit the red A-ICE PRESS LOW annunciator for a 15 second period, but the signal inhibiting will continue with the on-off cycling of the pump. When the pumps are activated for their 20 second cycle ON, the red A-ICE PRESS LOW annunciator will be inhibited. After 15 seconds of operation of both pumps, any low pressure condition will trigger the red A-ICE PRESS LOW annunciator. When the pumps turn off, the inhibiting circuit is reset for the next on-off pump cycle of the NORM mode. If a low pressure condition exists, the operator will see periodic triggering of the red A-ICE PRESS LOW annunciator for approximately 6 seconds every 2 minutes. Inhibiting the red A-ICE PRESS LOW annunciator in HIGH and NORM modes has been implemented to avoid nuisance CAS alerts. PITOT/STATIC HEAT SYSTEMS A left and right pitot-static heat system is installed to assure proper airspeed indications in the event icing conditions are encountered. The system is designed to prevent ice formation rather than remove it. The pitot-static heat system consists of a heating element in each pitot- static tube, a two-position toggle switch, labeled P/S HEAT/LOW A/S AWARE, on the ANTI-ICE switch panel, and two pull-off type circuit breakers, labeled LEFT PITOT HEAT and RIGHT PITOT HEAT, on the left sidewall switch and circuit breaker panel. When the P/S HEAT/LOW A/S AWARE switch is turned on, elements in both pitot-static tubes are heated electrically to maintain proper operation in icing conditions. Both pitot and static systems are monitored by the G1000 system for insufficient current and alerting is provided to the flight crew by a single chime and an amber L P/S HEAT, R P/S HEAT, or L-R P/S HEAT annunciation. (Continued Next Page) FAA APPROVED S1-74 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) LOW AIRSPEED AWARENESS SYSTEM The Low Airspeed Awareness (LAA) system is designed to warn the pilot when airspeed falls below 97.5 + 2.2 knots while operating in icing conditions. The system consists of an annunciator with a white or amber background and black letters, which reads BELOW ICING MIN SPD. LAA ANNUNCIATOR Figure S1-12 This annunciator is mounted in the instrument panel directly in front of the pilot, and is activated by an airspeed switch plumbed off the pilot’s pitot and static lines. A remote mounted relay box provides logic for the annunciator, and for the stall warning horn, which provides an aural alert. Power is supplied from the LEFT PITOT HEAT and RIGHT PITOT HEAT circuit breakers and through the P/S HEAT/LOW A/S AWARE switch. This switch has two positions, ON and OFF and the Low Airspeed Awareness System is powered only when the P/S HEAT/ LOW A/S AWARE switch is ON and at least one of the two circuit breakers is IN. (Continued Next Page) FAA APPROVED 208BPHCUS-S1-02 U.S. S1-75 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) LOW AIRSPEED AWARENESS SYSTEM (Continued) When the P/S HEAT/LOW A/S AWARE switch is turned ON prior to takeoff, the BELOW ICING MIN SPD annunciator will be illuminated white, indicating that the airspeed is below 97.5 + 2.2 knots. Once the airspeed exceeds 97.5 + 2.2 knots, the BELOW ICING MIN SPD annunciator will extinguish. If the airspeed falls back below 97.5 + 2.2 knots, the BELOW ICING MIN SPD annunciator will flash between amber and white and the stall warning horn will sound intermittently until the airspeed is increased above 97.5 + 2.2 knots. Pressing the flashing BELOW ICING MIN SPD annunciator, which incorporates a momentary switch, silences the stall warning horn and causes the annunciator to stop flashing. The annunciator will remain illuminated solid white as long as the airspeed is below 97.5 + 2.2 knots. The autopilot must be disengaged when the flashing amber and white annunciation is activated. The BELOW ICING MIN SPD annunciator brightness is controlled by the LED PANELS/ANNUN rheostat located on the lower part of the instrument panel to the left of the control pedestal. For daytime operations the rheostat should be rotated full counter-clockwise to the DAY position to make sure it is visible in bright light conditions. For all other lighting conditions, the LED PANELS/ANNUN rheostat can be adjusted clockwise to control lighting intensity. FAA APPROVED S1-76 U.S. 208BPHCUS-S1-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 AIRPLANE SYSTEMS AND DESCRIPTIONS (Continued) ICE DETECTION AND WING INSPECTION LIGHTS The windshield ice detection and wing inspection lights are used at night, or in conditions of poor visibility, to detect the presence of ice accumulating on the lower center portion of the windshield and leading edge of the left wing. The windshield ice detection light is located on the left side of the windshield center post. This light would typically be used first to visually detect the presence of ice accumulating on the windshield. The windshield ice detection light is activated anytime the NAV Switch is in the ON position. The wing inspection light is flush-mounted in the left wing leading edge- to-fuselage fairing to help detect ice on the wing at night by lighting the leading edge of the wing. The system consists of the wing inspection light, a two-position toggle switch located on the ANTI-ICE switch panel and a pull-off type circuit breaker, labeled WING ICE DET LIGHT, located on the left sidewall circuit breaker panel. The WING LIGHT switch is spring-loaded to the OFF, or down position, and must be held in the ON or up position to activate the light. ENGINE INERTIAL SEPARATOR, STANDBY ELECTRICAL, AND HEATED STALL WARNING SYSTEMS Refer to Section 7, Airplane and System Description of the POH/AFM for descriptions of these standard/required equipment items. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-77 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 HANDLING, SERVICING, AND MAINTENANCE PROLONGED OUT OF SERVICE CARE DURING FLYABLE STORAGE Make sure that the TKS fluid tank contains at least the minimum takeoff quantity of fluid and that all system components are filled with fluid. Refer to Limitations, Minimum Dispatch Fluid, of this supplement for minimum takeoff fluid quantity. Monthly, operate pump(s) until all air is purged from components and pipelines. Check and/or refill the TKS fluid tank to the minimum dispatch fluid level for takeoff. SERVICING ICE PROTECTION FLUID TANK Refer to Limitations, Approved Ice Protection Fluid, in this supplement for a list of approved TKS ice protection fluid type. The filler cap is located on the left side of the cargo pod. To prevent the possibility of contaminated fluid, always clean the top of fluid containers before dispensing, and if required maintain a clean measuring vessel solely for ice protection fluid. Secure the filler cap immediately after filling. Tank vents are included in the pallet. ICE PROTECTION FLUID STRAINER The ice protection fluid strainers of the metering pumps should not require cleaning unless there is a definite indication of foreign matter in the TKS fluid tank. ICE PROTECTION FLUID FILTER(S) An amber A-ICE HIGH PRESS annunciator in flight, or during ground testing, may indicate the need for filter element replacement. (Continued Next Page) FAA APPROVED S1-78 U.S. 208BPHCUS-02 CESSNA SECTION 9 - SUPPLEMENTS MODEL 208B 867 SHP SUPPLEMENT 1 GARMIN G1000 HANDLING, SERVICING, AND MAINTENANCE (Continued) SERVICING (Continued) POROUS LEADING EDGE PANEL CLEANING CAUTION Porous panels contain a plastic membrane which may be damaged by certain solvents, particularly Methyl Ethyl Ketone, Lacquer thinner and other types of thinners. Mask panels when painting airplane or when using solvents for other purposes in the proximity of the porous panels. Refer to the Maintenance Manual for detailed information on cleaning/painting interior and exterior painted surfaces on the airplane. Only the following fluids are approved for cleaning the TKS leading edge porous panels. 1. Water (with soap or detergents) 2. Approved TKS Ice Protection System Fluids 3. Isopropyl Alcohol The porous panels may be washed with mild soap and water using a brush or lint free cloth. Refer to the Maintenance Manual for more detailed information on handling, service, and maintenance. FAA APPROVED 208BPHCUS-S1-02 U.S. S1-79 SECTION 9 - SUPPLEMENTS CESSNA SUPPLEMENT 1 MODEL 208B 867 SHP GARMIN G1000 This Page Intentionally Left Blank. FAA APPROVED S1-80 U.S. 208BPHCUS-S1-02