Pitot-Static System - Inspection/Check ICA Supplement

AIRCRAFT DIVISION WICHITA, KANSAS 67277 Pitot-Static System - Inspection/Check ICA Supplement MODEL NO: 680A SUPPLEMENT NO: ICA-680A-34-00001 SUPPLEMENT DATE: 1/22/2016 Cessna Aircraft Company Form 2261 Rev 1

AIRCRAFT DIVISION WICHITA, KANSAS 67277 REVISIONS ICA-680A-34-00001 Rev: - Date: Jan 22/2016 ICA Summary Pages 1-6 Manuals Affected Description Title Maintenance Manual 34-10-00 pages 601-617 Adds Calibrated Airspeed and Altitude charts. Appendix A: Illustrated Parts Catalog Appendix B: Wiring Diagram Manual 1. Export Compliance Not Used Not Used Pitot-Static System - Inspection/Check A. This publication contains technical data and is subject to U.S. export regulations. This information has been exported from the United States in accordance with export administration regulations. Diversion contrary to U.S. law is prohibited. ECCN: 9E991 2. Revision Bars A. Revision bars in this ICA supplement identify new ICAs and/or changes to the current ICAs in the released maintenance manual. New ICAs that are not in the current maintenance manual will have a revision bar from top to bottom along the left margin. ICAs that are in the current maintenance manual and have information added, deleted or revised will have a revision bar(s) in the left margin adjacent to the added, deleted or revised information. New or changed illustrations will have a change bar for the entire length of the page. 3. Page Numbering A. The page number system for ICA included in this supplement have three-element numbers that are separated by dashes. The three-element number is found at the bottom right corner of the page, left of the page number. The date is found below the page number. B. When the chapter/system element number is followed with zeros in the section/subsystem and subject/unit element number (28-00-00), the information is applicable to the entire system. C. When the section/subsystem element number is followed with zeros in the subject/unit element number (281-00), the information is applicable to the subsystems in the system. Page 1 of 6 Jan 22/2016 Cessna Aircraft Company

AIRCRAFT DIVISION WICHITA, KANSAS 67277 D. The subject/unit element number is used to identify information applicable to units in the subsystems. The subject/unit element number continues in sequence from the number -01- with the number of subsystem units in which maintenance information is necessary. E. All system/subsystem/unit (chapter/section/subject) maintenance data is separated into speciied types of information: Description and Operation, Troubleshooting, Maintenance Practices, etc. Blocks of page numbers that are in sequence are used to identify the type of information: (1) Description and Operation or Troubleshooting information may not be included if the procedure is easy. When subtopics are short, they may be put together into the Maintenance Practices section. Maintenance Practices can have a mix of subtopics that includes information to service, remove, install, adjust, test, clean, paint or do approved repairs. (2) Longer procedures that are not as easy to do may be included in a speciied section. Page 1 through 99 - Description and Operation Page 101 through 199 - Troubleshooting Page 201 through 299 - Maintenance Practices Page 301 through 399 - Servicing Page 401 through 499 - Removal/Installation Page 501 through 599 - Adjustment/Test Page 601 through 699 - Inspection/Check Page 701 through 799 - Cleaning/Painting Page 801 through 899 - Approved Repairs F. A typical page number: G. Illustrations use the same igure numbers as the page block in which they appear. For example, Figure 202 would be the second igure in a Maintenance Practices section. 4. Supplement Revisions A. Revisions to this supplement may be accomplished if changes to this supplement are required after release of the original issue and prior to incorporation into the manuals listed in the REVISIONS table. B. All revisions to this supplement will have changes identiied in detail in the revision block(s) above. C. All pages in this ICA supplement will have the same date and are valid as of the date shown. 5. ICA Incorporation into Applicable Manuals Most ICA supplements will be incorporated in the next available revision to the manuals listed above and should be used in conjunction with those manuals until the next available revision is released. A. The ICA Supplement List located in the Introduction section of each manual listed in the REVISIONS table will indicate the incorporation status as of the release date of the published revision. Page 2 of 6 Jan 22/2016 Cessna Aircraft Company

AIRCRAFT DIVISION WICHITA, KANSAS 67277 B. The manual revision level of the supplement incorporation will be listed in the "Manual Incorporation Status" column in the ICA Supplement List, when those ICAs associated with that manual have been incorporated. After ICAs are incorporated, the manual that they are incorporated in must now be used for those ICAs instead of the supplement. Based on revision cycle times for the affected manuals, MM ICAs, WDM ICAs, etc. in this supplement may be incorporated in the manuals at different times. There will not be a revision to this supplement to indicate incorporation in the manuals. Users are required to check the ICA Supplement List for each manual affected to determine incorporation status. C. This supplement will be completely superseded by the manuals listed in the REVISIONS table when it has been incorporated in all of the manuals. Page 3 of 6 Jan 22/2016 Cessna Aircraft Company

AIRCRAFT DIVISION WICHITA, KANSAS 67277 1. Purpose INTRODUCTION A. The purpose of this Supplement is to provide the maintenance technician with the information necessary to ensure the correct functionality and performance of the Pitot-Static System - Inspection/Check on the Cessna Model 680A until this information gets incorporated into the next revision to the manuals listed in the "REVISIONS" section of this supplement. B. This ICA supplement is designed to satisfy the requirements of 14 CFR 25.1529 "Instructions for Continued Airworthiness" associated with this installation. This document is a supplement to the Model 680A Maintenance Manual and will be incorporated in the next revision to the manual. C. When this information is incorporated in the next revision to the manuals listed in the "REVISIONS" section, those manuals shall take precedence over this supplemental document. Refer to the "ICA Supplement List" in the "Introduction" section of the respective manual for the status of all applicable ICA Supplements. D. Revisions to this supplement may occur if there is a change to any of the ICAs in this supplement prior to incorporation into all of the affected manuals. This document must be placed with the aircraft operator's Technical Library CD-ROM or Model 680A Maintenance Manual and incorporated into the operator's scheduled maintenance program. 2. Effectivity A. These Instructions for Continued Airworthiness (ICA) are effective for the following aircraft model and serialization. Model Beginning Effectivity Ending Effectivity 680A 000001 and On 3. Complete ICA Documents A. The following document(s), in conjunction with this supplement, constitute the Instructions for Continued Airworthiness for the Pitot-Static System - Inspection/Check on the Cessna Model 680A. All items must be available to the operator at initial delivery. (1) Model 680A Maintenance Manual Page 4 of 6 Jan 22/2016 Cessna Aircraft Company

AIRCRAFT DIVISION WICHITA, KANSAS 67277 1. Model 680A Maintenance Manual LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS A. Chapter 34, Navigation (1) Refer to 34-10-00 Pitot-Static System - Inspection/Check Page 5 of 6 Jan 22/2016 Cessna Aircraft Company

AIRCRAFT DIVISION WICHITA, KANSAS 67277 1. Continuous Inspection Program INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS A. This ICA Supplement does not affect the current inspection program. 2. Airworthiness Limitations A. Cessna Aircraft Company Model 680A Maintenance Manual, Chapter 4, Airworthiness Limitations, contains the system and airframe limitations for the Model 680A. The Airworthiness Limitations section is FAA-approved and speciies maintenance required under Section 43.16 and 91.403 of Title 14 Code of Federal Regulations, unless an alternative program has been FAA approved. (1) There are no new (or additional) airworthiness limitations associated with this equipment and/or installation. Page 6 of 6 Jan 22/2016 Cessna Aircraft Company

1. General PITOT-STATIC SYSTEM - INSPECTION/CHECK A. This section gives the inspections and checks necessary to keep the pitot-static system in a serviceable condition. For a general description of the pitot-static system refer to Chapter 34, Pitot-Static System - Description and Operation Task 34-10-00-720 2. Pitot-Static System Functional Check These tests are designed to allow performance of tests and recertiication of air data related instruments to satisfy all of the requirements of 14 CFR 91.411 without the removal of components from the airplane. This procedure is Cessna-approved as meeting the intent of the regulations. Certain additional tests not necessary by the regulations are also included in the inspection task to reduce manpower requirements and multiple cycling of test equipment. Individual components that do not meet the tolerances necessary in this procedure must be removed from the airplane and recertiied by an authorized facility. It is important to attach a placard onto all altimeters that shows the test date and maximum test altitude. All tests must be done with a ground power unit (GPU) with the output voltage adjusted to 28.5 Vdc, +0.5 or -0.5 Vdc and with a current capability of 200 Amperes. A. Tools and Equipment For the tool, equipment, and special consumable part numbers and the manufacturer data, refer to Chapter 34, Navigation - General. For the supplier publication part number and manufacturer data, refer to the Introduction - Supplier Publication List. (1) Tools and Equipment Air Data Test Set Ground Power Unit Pitot Adapters Static Adapters Straightedge, six inches long Feeler Gages 0.5 inches wide. (2) Special Consumables Red Vinyl Pressure Tape. (3) Reference Material Chapter 7, Lifting - Maintenance Practices Chapter 24, External Electrical Power - Maintenance Practices Chapter 32, Landing Gear - Maintenance Practices Model 680A Structural Repair Manual, Chapter 51, Structures Model 680A Structural Repair Manual, Chapter 51, Aerodynamic Surfaces. B. Safety Precautions and Preparations 34-10-00 Page 601

WARNING: Do not apply electrical power to the anti-icing system when the pitot and the static adapters are installed or injury to personnel can result. CAUTION: Make sure that you apply warning tags/signs as applicable. Make sure that the pitot-static systems anti-ice is off during the functional check. You can damage components and/or equipment. CAUTION: Paper masking tape or adhesive tape is not an equivalent for red vinyl pressure tape. Do not use transparent tape or the test will not be accurate. CAUTION: Do not apply electrical power to the anti-icing system when the pitot and the static adapters are installed or damage to the equipment can result. CAUTION: Do not let the airspeed indication go less than 80 knots or more than 350 knots unless it is speciied during the functional check. CAUTION: Do not let the altimeter indication go less than 1000 feet (304.8 m) below sea level or more than 45,000 feet (13,716 m) above sea level or damage to the equipment can result. CAUTION: Do not let the rate of climb increase or decrease more than 6,000 feet-per-minute (1828.8 meters-per-minute) or damage to the equipment can result. CAUTION: Do not bleed the systems faster than 6,000 feet-per-minute (1828 m) vertical speed or damage to the equipment can result. (1) Slowly bleed the input pressures to ambient before you disconnect the lines. (2) Do not use soap and water or any liquid to do a leak test on the pitot and static system. Each static line ends at two static port outlets, found on the left and right side of the forward lower fuselage. When you do a check of the static system, use red vinyl pressure tape to seal the opposite static port surface(s). If not, it will vent to the atmosphere and cause invalid test results. C. Prepare the Airplane for the Pitot-Static System Functional Check. (1) Do the air data test set self-test. (a) Make sure the test set passes the self-test before you do the functional tests that follow. (2) Disengage the circuit breakers given in Table 601. Table 601. Circuit Breakers Circuit Breaker Name L PITOT HEAT L STATIC HEAT R PITOT HEAT Circuit Breaker Location Left Circuit Breaker Panel Left Circuit Breaker Panel Right Circuit Breaker Panel 34-10-00 Page 602

Table 601. Circuit Breakers (continued) Circuit Breaker Name R STATIC HEAT STBY PITOT HEAT STBY STATIC HEAT Circuit Breaker Location Right Circuit Breaker Panel Right Circuit Breaker Panel Right Circuit Breaker Panel D. Do the RVSM Skin Waviness Inspection (Refer to Figure 601). This procedure must be done at the intervals given in Chapter 5, and after painting or any maintenance that is done which could cause unwanted waviness in the inspection area. This inspection is only applicable to airplanes certiied for RVSM (Reduced Vertical Separation Minimums). (1) Clean and remove all debris (bug remnants and dirt) from the areas around each static port. (2) Visually inspect the areas (right and left) for waviness, scratches and prior repairs. (3) Make sure that the entire inspection area meets the criteria of local contour. Refer to Model 680A Structural Repair Manual, Chapter 51, Aerodynamic Surfaces. (4) Repair any discrepancies. Use the standard procedures found in the Model 680A Structural Repair Manual, Chapter 51, Structures. (5) Visually inspect a 3-inch (76.2 mm) radius area around each static port for paint stripes, stencils or placards. (a) For location of placards or stencils, refer to Figure 601. (b) Visually inspect the static port openings to make sure the static ports are clean and clear and the edges of the port openings are undamaged. Static port openings which have paint ridges or chipped edges must be repaired to a smooth condition. (c) Make sure the static ports are clean and clear, edge of port openings are undamaged and otherwise in good condition. 1 Blocked, dirty, corroded, or otherwise irregular ports should be cleaned, repaired and/ or replaced, as necessary. (6) Do the static port depression check. (a) Use a six-inch (152.4 mm) straightedge and a set of 0.50 inch (12.7 mm) wide feeler gages to inspect and determine if the static port depression is acceptable as shown in Figure 601. (b) Center the straightedge at the center of the static port opening. (c) Align the straightedge parallel to the approximate airplane waterline as shown in Figure 601, View A-A. (d) Insert a 0.002 inch (0.051 mm) feeler gage between the airplane skin and the center of the straightedge. 1 If you cannot insert the feeler gage, do the static port bulge check in this section. (e) Measure the depression depth at the approximate center of the static port opening. 1 If the measurement is 0.015 inch (0.381 mm) or less, the static port depression is acceptable. 2 If the measurement is more than 0.015 inch (0.381 mm), the static port depression is unacceptable and must be repaired. Refer to the Model 680A Structural Repair Manual, Chapter 51, Structures. (7) Do the static port bulge check. (a) (b) (c) (d) Push the forward edge of the straightedge irmly against the airplane skin. Insert the feeler gage(s) between the airplane skin and the aft 0.50 inch (12.7 mm) of the straightedge end. 1 If the measurement is 0.030 inch (0.762 mm) or less the static port is acceptable. 2 If the measurement is more than 0.030 inch (0.762 mm) the static port is unacceptable and must be repaired. Refer to the Model 680A Structural Repair Manual, Chapter 51, Structures. Remove the feeler gage(s). Push the aft edge of the straightedge irmly against the airplane skin. 34-10-00 Page 603

Skin Contour Inspection Figure 601 (Sheet 1) 34-10-00 Page 604

Skin Contour Inspection Figure 601 (Sheet 2) 34-10-00 Page 605

(e) Insert the feeler gage(s) between the airplane skin and the forward 0.50 inch (12.7 mm) of the straightedge end. 1 If the measurement is 0.030 inch (0.762 mm) or less the static port is acceptable. 2 If the measurement is more than 0.030 inch (0.762 mm) the static port is unacceptable and must be repaired. Refer to the Model 680A Structural Repair Manual, Chapter 51, Structures. E. Do the Pitot-Static System Leak Check. CAUTION: Paper masking tape or adhesive tape is not an equivalent for red vinyl pressure tape. Do not use transparent tape or the test will not be accurate. CAUTION: Do not apply electrical power to the anti-icing system when the pitot and the static adapters are installed or damage to the equipment can result. WARNING: Do not apply electrical power to the anti-icing system when the pitot and the static adapters are installed or injury to personnel can result. CAUTION: Do not let the airspeed indication go less than 80 knots or more than 350 knots unless it is speciied during the functional check. CAUTION: Do not let the altimeter indication go less than 1000 feet (304.8 m) below sea level or more than 45,000 feet (13,716 m) above sea level or damage to the equipment can result. CAUTION: Do not let the rate of climb increase or decrease more than 6,000 feetper-minute (1828.8 meters-per-minute) or damage to the equipment can result. CAUTION: Do not bleed the systems faster than 6,000 feet-per-minute (1828 m) vertical speed or damage to the equipment can result. (1) Make sure that the static ports and the pitot probes do not have blockage. (2) Complete all data on the Component Recording and Reporting Form. (3) Make sure that the L and the R PITOT/STATIC ANTI-ICE switch/lights on the right switch panel are in the OFF position. CAUTION: Make sure that the static ports and the pitot probes are at the ambient temperature or damage to equipment can occur. (4) Do the Pilot's Pitot System Leak Check. Each static line stops at two static port outlets, one is found on the left side and one on the right side of the forward lower fuselage. When you do a static system check, use red vinyl pressure tape to seal the opposite static port that would otherwise be vented to the atmosphere. That will result in invalid test results. (a) Connect the static adapter and the air data test set static source (vacuum) to one of the pilot's static ports. 34-10-00 Page 606

CAUTION: Do not cover the copilot's or the standby static ports. Only cover the remaining pilot's static port or the test results will be inaccurate. 1 Cover the remaining pilot's static port with red vinyl pressure tape. (b) Cover the drain holes on the pilot's pitot probe with red vinyl pressure tape. (c) Connect the pitot adapter and the air data test set to the pilot's pitot probe. (d) Connect the external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. 1 Adjust the ground power unit (GPU) to 28 Vdc +0.5 and -0.5 Vdc. (e) Use the air data test set to apply pressure to the pitot system to get an airspeed indication of 250 knots. With the static system at ambient pressure, a pitot system leak will cause the airspeed to decrease. (f) Put the air data test set in leak detect mode. (g) Make sure that the indicated airspeed decreases no more than 2 knots in one minute. (h) Record the PFD indicated airspeed after one minute. (i) Bleed the applicable pitot and static systems to the ambient pressure. 1 Do not exceed the altitude rate of change of 6,000 feet-per-minute (1828.8 metersper-minute). (5) Do the Pilot's Static System Leak Check. (a) Apply pressure to the pitot system to get an airspeed indication of 250 knots. (b) Apply a vacuum to the static system to get and altitude of 31,420 feet (9577 m). As the altitude increases, monitor the airplane altimeter. If the increase of the airplane altimeter is less than the air data test set, examine the static port and the static tube for blockage. (c) As the altitude increases, monitor the airplane's altitude indicator for a parallel indication with the test set altimeter. (d) Put the air data test set in leak detect mode. (e) Make sure that the PFD indicated altitude does not decrease below 31,320 feet (9546 m) in one minute. If leakage is more than allowed the airspeed will increase. (f) Record the PFD indicated altitude after one minute. CAUTION: Do not let the rate of climb increase or decrease more than 6,000 feet-per-minute (1828.8 meters-per-minute) or damage to the equipment can result. (g) Bleed the pitot and static systems to the ambient pressure. (h) Remove the pitot adapter and the air data test set from the pilot's pitot probe. (i) Remove the static adapter and the air data test set from the applicable static port. (j) Remove and discard all the red vinyl pressure tape from the remaining static port and the pitot probe drain holes. (6) Do the Copilot's Pitot System Leak Check. (a) Connect the static adapter and the air data test set static source (vacuum) to one of the copilot's static ports. 34-10-00 Page 607

CAUTION: Do not cover the pilot's or the standby static ports. Only cover the remaining copilot's static port or the test results can be inaccurate. (b) (c) (d) 1 Cover the remaining copilot's static port with red vinyl pressure tape. Cover the drain holes on the copilot's pitot probe with red vinyl pressure tape. Connect the pitot adapter and the air data test set to the copilot's pitot probe. With the static system at ambient pressure, apply pressure to the pitot system to get an airspeed indication of 250 knots. With the static system at ambient pressure, a pitot system leak will cause the airspeed to decrease. (e) (f) (g) (h) Put the air data test set in leak detect mode. Make sure that the PFD indicated airspeed decreases no more than 2 knots in one minute. Record the PFD indicated airspeed after one minute. Bleed the applicable pitot and static systems to the ambient pressure. 1 Do not exceed the altitude rate of change of 6,000 feet-per-minute (1828.8 metersper-minute). (7) Do the Copilot's Static System Leak Check. (a) Apply pressure to the pitot system to get an airspeed indication of 250 knots, +50 or -50 knots. (b) Apply a vacuum to the static system to get and altitude of 31,420 feet (9577 m). As the altitude increases, monitor the airplane altimeter. If the increase of the airplane altimeter is less than the air data test set, examine the static port and the static tube for blockage. (c) As the altitude increases, monitor the airplane's altitude indicator for a parallel indication with the test set altimeter. (d) Put the air data test set in leak detect mode. (e) Make sure that the altitude indication does not decrease below 31,320 feet (9546 m) in one minute. (f) Record the PFD indicated altitude after one minute. (g) Bleed the pitot and static systems to the ambient pressure. 1 Do not exceed the altitude rate of change of 6,000 feet-per-minute (1828.8 metersper-minute). (h) Remove the pitot adapter and the air data test set from the copilot's pitot probe. (i) Remove the static adapter and the air data test set from the applicable static port. (j) Remove and discard all the red vinyl pressure tape from the remaining static port and the pitot probe drain holes. (8) Do the Standby Pitot-Static System Leak Check. (a) Connect the static adapter and the air data test set static source (vacuum) to one of the standby static ports. CAUTION: Do not cover the pilot's or the copilot's static ports. Only cover the remaining standby static port or the test results can be inaccurate. (b) (c) (d) 1 Cover the remaining standby static port with red vinyl pressure tape. Cover the drain holes on the standby pitot probe with red vinyl pressure tape. Connect the pitot adapter and the air data test set to the standby pitot probe. Apply pressure to the pitot system to get an airspeed indication of 250 knots. 34-10-00 Page 608

(e) Apply a vacuum to the static system to get and altitude of 31,420 feet (9577 m). As the altitude increases, monitor the airplane altimeter. If the increase of the airplane altimeter is less than the air data test set, examine the static port and the static tube for blockage. (f) Put the air data test set in leak detect mode. (g) Make sure that the indicated altitude shown does not decrease below 31,320 feet (9546 m) in one minute. (h) Record the secondary light display indicated altitude after one minute. (i) Bleed the standby pitot and static systems to the ambient pressure. 1 Do not exceed the altitude rate of change of 6,000 feet-per-minute (1828.8 metersper-minute). (j) Remove the pitot adapter and the air data test set from the standby pitot probe. (k) Remove the static adapter and the air data test set from the standby static port. (l) Remove and discard all the red vinyl pressure tape from the remaining standby static port and the standby pitot probe drain holes. F. Primary and Standby Air Data Computer Check. WARNING: Do not apply electrical power to the anti-icing system when the pitot and the static adapters are installed or injury to personnel can result. CAUTION: Paper masking tape or adhesive tape is not an equivalent for red vinyl pressure tape. Do not use transparent tape or the test will not be accurate. CAUTION: Do not apply electrical power to the anti-icing system when the pitot and the static adapters are installed or damage to the equipment can result. CAUTION: Do not let the airspeed indication go less than 80 knots or more than 350 knots unless it is speciied during the functional check. CAUTION: Do not let the altimeter indication go less than 1000 feet (304.8 m) below sea level or more than 45,000 feet (13,716 m) above sea level or damage to the equipment can result. CAUTION: Do not let the rate of climb increase or decrease more than 6,000 feetper-minute (1828.8 meters-per-minute) or damage to the equipment can result. (1) Make sure that the L and the R PITOT/STATIC ANTI-ICE switch/lights on the right switch panel are in the OFF position. (2) Make sure that the circuit breakers given in Table 601 are disengaged. (3) Make sure all three pitot and static systems are connected to the air data test set. (a) Connect the air data test set to the left or right pilot's, copilot's, and standby static ports. (b) Make sure that all of the static ports that are not used have red vinyl pressure tape on them. (c) Connect the air data test set to the pilot's, copilot's, and standby pitot probes. (d) Put red vinyl pressure tape on the drain holes on the pilot's, copilot's, and standby pitot probes. (4) Set the air data test set to apply the ambient pressure to the static system. (5) Do the Overspeed Check. (a) On the pilot's right Garmin GTC 570 Touchscreen Control Units, do as follows: 1 Select the Aircraft Systems page. 2 Select the System Test page. 34-10-00 Page 609

3 Push the Overspeed button to start the check. a Make sure that the check is in progress and the button shows the blue In Progress message. 4 Make sure that you hear the Overspeed aural message. 5 Make sure that the blue Done message shows on the button when the check is done. (6) Do the Barometric Control Check. (a) Make sure that the pilot's PFD, copilot's PFD, and SFD show the correct airspeed, altitude, and no red X. (b) Make sure that the pilot's and the copilot's PFD's show the barometric correction in inches of Mercury (inhg). (c) If the one or the two PFD's shows the barometric correction in hectopascals (hpa), do as follows: 1 Use the pilot's right Garmin GTC 570 Touchscreen Control Unit and select the Home page. 2 Select PFD Settings. 3 Select Altitude Units. 4 Select IN to show the barometric pressure in inhg. When you use one GTC to change the barometric setting the both PFD's setting will change. (d) (e) (f) (g) If the SFD shows the barometric correction in hpa, do as follows: 1 Push the M button on the SFD to show the Menu. 2 Turn the knob and select BARO TYPE. 3 Select IN to show the barometric pressure in inhg. Turn the BARO knob on the pilot's Garmin GCU 275 Display Controller clockwise to increase and counterclockwise to decrease the barometric setting on the pilot's PFD. 1 Push the BARO knob to show STD BARO on the pilot's PFD. Turn the BARO knob on the copilot's Garmin GCU 275 Display Controller clockwise to increase and counterclockwise to decrease the barometric setting on the copilot's PFD. 1 Push the BARO knob to show STD BARO on the copilot's PFD. Turn the knob on the SFD clockwise to increase and counterclockwise to decrease the barometric setting. 1 Push the knob to show 29.92 IN HG on the standby light display. (7) (Airplanes -0001 thru -0016 not incorporating SB680A-34-01) Do the Airspeed/Altimeter/Mach Display Check. (a) Make sure that the air data test set, pilot's PFD, copilot's PFD, and SFD are set to 29.92 inhg (1013 millibars). Because of Static Source Error Correction (SSEC) in the air data computers (ADC's), the tester inputs will correlate to the altitude and airspeed values given in Table 602 and Table 603. Table 602. (Airplanes -0001 thru -0016 not incorporating SB680A-34-01) Calibrated Airspeed and Altitude (RVSM and SSEC Corrected with Gear Down) Air Data Tester Input Pilot's PFD, Copilot's PFD, and SFD (SSEC Corrected) Altitude Airspeed Altitude Airspeed Feet Meters Knots Feet Meters Knots Mach -1400-426 20-1400, +15 or -15-426, +4.5 or -4.5, +10 or - 10 0 0 35 0, +15 or -15 +4.5 or -4.5, +5 or -5 1000 304 50 1000, +17 or -17 305, +5 or -5 50, +5 or -5 34-10-00 Page 610

Table 602. (Airplanes -0001 thru -0016 not incorporating SB680A-34-01) Calibrated Airspeed and Altitude (RVSM and SSEC Corrected with Gear Down) (continued) Air Data Tester Input Pilot's PFD, Copilot's PFD, and SFD (SSEC Corrected) Altitude Airspeed Altitude Airspeed Feet Meters Knots Feet Meters Knots Mach 2000 609 80 2000, +18 or -18 3000 914 100 3000, +19 or -19 4000 1219 120 3998 +20 or 0 5000 1524 150 4992, +25 or 5 8,000 2438 200 7972, +25 or 5 11,000 3352 250 10,952, +35 or -35 14,000 4267 300 13,923, +31 or -31 17,000 5181 300 16,915, +45 or -45 20,000 6096 300 19,906, +50 or -50 28,400 8656 200 28,345, +37 or -37 28,600 8717 200 28,610, +37 or -37 30,000 9144 200 30,007, +37 or -37 609, +5.5 or -5.5 914, +5.7 or -5.7 80, +3 or -3 100, +2 or 1218, +6 or -6 120, +2 or 1521, +7.6 or -7.6 2430, +7.6 or -7.6 3338, +10.7 or -10.7 150, +2 or 199, +2 or 249, +2.4 or.4 4243, +9 or -9 298, +2.8 5155, +13.7 or -13.7 6067, +15.2 or -15.2 8639, +11 or -11 8720, +11 or -11 9146, +11 or -11 298, +2.8 298, +2.8 199, +2.0 or -3.0 200, +2.0 or.0 200, +2.0 or.0 0.458, +0.011 or -0.011 0.578, +0.008 or -0.008 0.611, +0.007 or -0.007 0.647, +0.006 or -0.006 0.520, +0.010 or -0.010 0.526, +0.009 or -0.009 0.542, +0.009 or -0.009 Table 603. (Airplanes -0001 thru -0016 not incorporating SB680A-34-01) Calibrated Airspeed and Altitude (RVSM and SSEC Corrected with Gear Up) Air Data Tester Input Pilot's PFD, Copilot's PFD, and SFD (SSEC Corrected) Altitude Airspeed Altitude Airspeed Feet Meters Knots Feet Meters Knots Mach -1400-426 20-1400, +15 or -15-426, +4.5 or -4.5, +10 or -10 0 0 35 0, +15 or -15 +4.5 or -4.5, +5 or -5 1000 304 50 1000, +17 or -17 2000 609 80 2000, +18 or -18 304, +5 or -5 50 +5 or -5 6609, +5 or - 5 80, +3 or -3 34-10-00 Page 611

Table 603. (Airplanes -0001 thru -0016 not incorporating SB680A-34-01) Calibrated Airspeed and Altitude (RVSM and SSEC Corrected with Gear Up) (continued) Air Data Tester Input Pilot's PFD, Copilot's PFD, and SFD (SSEC Corrected) Altitude Airspeed Altitude Airspeed Feet Meters Knots Feet Meters Knots Mach 3000 914 100 3,001, +19 or -19 4000 1219 120 4002, +20 or 0 5000 1524 150 5005, +25 or 5 8000 2438 200 8018, +25 or 5 11000 3352 250 11,019, +35 or -35 14,000 4267 300 13,996, +31 or -31 17,000 5181 300 16,983, +45 or -45 20,000 6096 300 19,964, +50 or -50 28,400 8656 300 28,266, +36 or -36 28,600 8717 300 28,463, +36 or -36 30,000 9144 300 29,836, +37 or -37 41,000 12,496 208 40,928, +46 or -46 43,000 13,106 208 42,900, +71 or -71 45,000 13,716 208 44,865, +86 or -86 47,000 14,325 208 46,821, +102 or -102 (b) 914, +5.7 or -5.7 100, +2 or 1219, +6 or -6 120, +2 or 1525, +7.6 or -7.6 2443, +7.6 or -7.6 3358, +10.6 or -10.6 150,+2 or 201, +2 or 251, +2.4 or.4 4265, +9 or -9 300, +2.8 5176, +13.7 or -13.7 6085, +15.2 or -15.2 8615, +10.9 or -10.9 8675, +10.9 or -10.9 9094, +11 or -11 12474, +14 or -14 13075, +21.6 or 1.6 13674, +26 or 26 14,271, +31 or -31 300, +2.8 299, +2.8 298, +2.8 298, +2.8 298, +2.8 207, +2.1 or.1 207, +2.1 or.1 207, +2.1 or.1 206, +2 or 0.462 +0.011 or -0.011 0.582 +0.008 or -0.008 0.615, +0.007 or -0.007 0.650, +0.006 or -0.006 0.760, +0.005 or -0.005 0.763, +0.005 or -0.005 0.783 +0.005 or -0.005 0.708, +0.005 or -0.005 0.738, +0.005 or -0.005 0.768, +0.005 or -0.005 0.799, +0.005 or -0.005 Adjust the altitude and airspeed settings on the air data test set. 1 Do a check of all the displayed Airspeed/Altitude/Mach values given in Table 602 on the pilot's PFD, copilot's PFD, and SFD. The Mach display numbers will not show until 0.45 Mach and above ascending. The Mach display numbers will not show below 0.40 Mach during descent. (c) 2 Make sure that the error is not more than limits given in Table 602. 3 Make sure that you record the Airspeed/Altitude/Mach values from the pilot's PFD, copilot's PFD, and SFD, not from the air data test set. Lift the airplane on jacks. Refer to Chapter 7, Lifting - Maintenance Practices. 34-10-00 Page 612

(d) Connect the nose gear and the main gear simulator test boxes. Refer to Chapter 32, Landing Gear - Maintenance Practices. 1 Set the gear simulator test boxes to the Up and Locked coniguration. (e) (f) Set the landing gear handle to the GEAR UP position. Adjust the altitude and airspeed settings on the air data test set. 1 Do a check of all the displayed Airspeed/Altitude/Mach values given in Table 603 on the pilot's PFD, copilot's PFD, and SFD. The Mach display numbers will not show until 0.45 Mach and above ascending. The Mach display numbers will not show below 0.40 Mach during descent. 2 Make sure that the error is not more than limits given in Table 603. 3 Make sure that you record the Airspeed/Altitude/Mach values from the pilot's PFD, copilot's PFD, and SFD, not from the air data test set. (g) Bleed the pilot's pitot and static systems to ambient pressure. 1 Do not bleed the systems faster than 6,000 feet-per-minute (1828 m) vertical speed. (h) Set the landing gear handle to the GEAR DOWN position. (i) Set the gear simulator test boxes to the Down and Locked coniguration. (j) Disconnect the nose gear and the main gear simulator test boxes. Refer to Chapter 32, Landing Gear - Maintenance Practices. (k) Lower the airplane and remove the jacks. Refer to Chapter 7, Lifting - Maintenance Practices. (8) (Airplanes -0017 and On and -0001 thru -0016 incorporating SB680A-34-01) Do the Airspeed/ Altimeter/Mach Display Check. (a) Make sure that the air data test set, pilot's PFD, copilot's PFD, and SFD are set to 29.92 inhg (1013 millibars). Because of Static Source Error Correction (SSEC) in the air data computers (ADC's), the tester inputs will correlate to the altitude and airspeed values given in Table 604 and Table 605. Table 604. (Airplanes -0017 and On and -0001 thru -0016 incorporating SB680A-34-01) Calibrated Airspeed and Altitude (RVSM and SSEC Corrected with Gear Down) Air Data Tester Input Pilot's PFD, Copilot's PFD, and SFD (SSEC Corrected) Altitude Airspeed Altitude Airspeed Feet Meters Knots Feet Meters Knots Mach -1400-426 20-1400, +12 or -12-426, +3.6 or -3.6, +10 or - 10 0 0 35 0, +12 or -12 +3.6 or -3.6, +5 or -5 1000 304 50 1000, +14 or -14 2000 609 80 2000, +15 or -15 3000 914 100 3000, +16 or -16 4000 1219 120 3998 +17 or -17 5000 1524 150 4992, +18 or -18 305, +4.2 or -4.2 609, +4.5 or -4.5 914, +4.8 or -4.8 1218, +5.1 or -5.1 1521, +5.4 or -5.4 50, +5 or -5 80, +3 or -3 100, +2 or 120, +2 or 149, +2 or 34-10-00 Page 613

Table 604. (Airplanes -0017 and On and -0001 thru -0016 incorporating SB680A-34-01) Calibrated Airspeed and Altitude (RVSM and SSEC Corrected with Gear Down) (continued) Air Data Tester Input Pilot's PFD, Copilot's PFD, and SFD (SSEC Corrected) Altitude Airspeed Altitude Airspeed Feet Meters Knots Feet Meters Knots Mach 8,000 2438 200 7972, +21 or 1 11,000 3352 250 10,952, +24 or 4 14,000 4267 300 13,923, +27 or 7 17,000 5181 300 16,915, +45 or -45 20,000 6096 300 19,906, +50 or -50 28,400 8656 200 28,345, +25 or 5 28,600 8717 200 28,586, +24 or 4 30,000 9144 200 29,981, +23 or 3 2430, +6.4 or -6.4 3338, +7.3 or -7.3 4243, +8.2 or -8.2 5155, +13.7 or -13.7 6067, +15.2 or -15.2 8639, +7.6 or -7.6 8713, +7.3 or -7.3 199, +2 or 249, +2.4 or.4 298, +2.8 298, +2.8 298, +2.8 199, +2.0 or.0 200, +2.0 or.0 9138, +7 or -7 200, +2.0 or.0 0.458, +0.011 or -0.011 0.578, +0.008 or -0.008 0.611, +0.007 or -0.007 0.647, +0.006 or -0.006 0.520, +0.010 or -0.010 0.525, +0.009 or -0.009 0.540, +0.009 or -0.009 Table 605. (Airplanes -0017 and On and -0001 thru -0016 incorporating SB680A-34-01) Calibrated Airspeed and Altitude (RVSM and SSEC Corrected with Gear Up) Air Data Tester Input Pilot's PFD, Copilot's PFD, and SFD (SSEC Corrected) Altitude Airspeed Altitude Airspeed Feet Meters Knots Feet Meters Knots Mach -1400-426 20-1400, +12 or -12-426, +3.6 or -3.6, +10 or -10 0 0 35 0, +12 or -12 +3.6 or -3.6, +5 or -5 1000 304 50 1000, +14 or -14 2000 609 80 2000, +15 or -15 3000 914 100 3,001, +16 or -16 4000 1219 120 4002, +17 or -17 5000 1524 150 5005, +18 or -18 8000 2438 200 8018, +21 or 1 304, +4.2 or -4.2 6609, +4.5 or - 4.5 914, +4.8 or -4.8 1219, +5.1 or -5.1 1525, +5.4 or -5.4 2443, +6.4 or -6.4 50 +5 or -5 80, +3 or -3 100, +2 or 120, +2 or 150,+2 or 201, +2 or 34-10-00 Page 614

Table 605. (Airplanes -0017 and On and -0001 thru -0016 incorporating SB680A-34-01) Calibrated Airspeed and Altitude (RVSM and SSEC Corrected with Gear Up) (continued) Air Data Tester Input Pilot's PFD, Copilot's PFD, and SFD (SSEC Corrected) Altitude Airspeed Altitude Airspeed Feet Meters Knots Feet Meters Knots Mach 11000 3352 250 11,009, +27 or 7 14,000 4267 300 13,959, +27 or 7 17,000 5181 300 16,940, +45 or -45 20,000 6096 300 19,916, +50 or -50 28,400 8656 300 28,208, +25 or 5 28,600 8717 300 28,404, +24 or 4 30,000 9144 300 29,779, +23 or 3 41,000 12,496 208 40,879, +35 or -35 43,000 13,106 208 42,847, +55 or -55 45,000 13,716 208 44,810, +75 or -75 47,000 14,325 208 46,770, +95 or -95 (b) 3355, +8.2 or -8.2 4254, +8.2 or -8.2 5163, +13.7 or -13.7 6070, +15.2 or -15.2 8597, +7.6 or -7.6 8657, +7.3 or -7.3 250, +2.4 or.4 299, +2.8 299, +2.8 298, +2.8 297, +2.8 297, +2.8 9076, +7 or -7 297, +2.8 12459, +10.6 or -10.6 13059, +16.7 or -16.7 13658, +22.8 or 2.8 14,255, +28.9 or 8.9 207, +2.1 or.1 206, +2.1 or.1 206, +2.1 or.1 206, +2 or 0.461 +0.011 or -0.011 0.580 +0.008 or -0.008 0.612, +0.007 or -0.007 0.647, +0.006 or -0.006 0.757, +0.005 or -0.005 0.760, +0.005 or -0.005 0.780 +0.005 or -0.005 0.706, +0.005 or -0.005 0.735, +0.005 or -0.005 0.765, +0.005 or - 0.005 0.797, +0.005 or -0.005 Adjust the altitude and airspeed settings on the air data test set. 1 Do a check of all the displayed Airspeed/Altitude/Mach values given in Table 604 on the pilot's PFD, copilot's PFD, and SFD. The Mach display numbers will not show until 0.45 Mach and above ascending. The Mach display numbers will not show below 0.40 Mach during descent. 2 Make sure that the error is not more than limits given in Table 604. 3 Make sure that you record the Airspeed/Altitude/Mach values from the pilot's PFD, copilot's PFD, and SFD, not from the air data test set. (c) Lift the airplane on jacks. Refer to Chapter 7, Lifting - Maintenance Practices. (d) Connect the nose gear and the main gear simulator test boxes. Refer to Chapter 32, Landing Gear - Maintenance Practices. 1 Set the gear simulator test boxes to the Up and Locked coniguration. (e) (f) Set the landing gear handle to the GEAR UP position. Adjust the altitude and airspeed settings on the air data test set. 1 Do a check of all the displayed Airspeed/Altitude/Mach values given in Table 605 on the pilot's PFD, copilot's PFD, and SFD. The Mach display numbers will not show until 0.45 Mach and above ascending. The Mach display numbers will not show below 0.40 Mach during descent. 34-10-00 Page 615

2 Make sure that the error is not more than limits given in Table 605. 3 Make sure that you record the Airspeed/Altitude/Mach values from the pilot's PFD, copilot's PFD, and SFD, not from the air data test set. (g) Bleed the pilot's pitot and static systems to ambient pressure. 1 Do not bleed the systems faster than 6,000 feet-per-minute (1828 m) vertical speed. (h) Set the landing gear handle to the GEAR DOWN position. (i) Set the gear simulator test boxes to the Down and Locked coniguration. (j) Disconnect the nose gear and the main gear simulator test boxes. Refer to Chapter 32, Landing Gear - Maintenance Practices. (k) Lower the airplane and remove the jacks. Refer to Chapter 7, Lifting - Maintenance Practices. (9) Disconnect the air data test set from the static ports and the pitot tubes. (10) Remove the red vinyl pressure tape from the static ports and the pitot probe drain holes. (11) Record and put the dates and the maximum altitude on the placard on the air data units only for the systems that were tested. (12) Record the necessary data in the Component Recording and Reporting Form. The person who approves the airplane for return to service must enter the same data in the airplane logbook (records and entries in accordance to FAR Part 43 paragraph 43.11). (13) Disengage the ADC 1 circuit breaker on the left circuit breaker panel. (a) Make sure that the pilot's PFD airspeed and altitude displays show a red X. (14) Engage the ADC 1 circuit breaker on the left circuit breaker panel. (15) Disengage the ADC 2 circuit breaker on the right circuit breaker panel. (a) Make sure that the copilot's PFD airspeed and altitude displays show a red X. (16) Engage the ADC 2 circuit breaker on the right circuit breaker panel. (17) Disengage the STBY ADC circuit breaker on the left circuit breaker panel. (a) Make sure that the standby airspeed and altitude displays show a red X. (18) Engage the STBY ADC circuit breaker on the left circuit breaker panel. G. Put the Airplane Back to its Initial Condition. (1) Engage the circuit breakers given in Table 601. (2) Disconnect the external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. H. Ensure that Task Findings are entered into Cescom/Camp Systems at http://www.campsystems.com/ or provided to Cessna, Maintenance Engineering, Department 753, 2121 South Hoover Road, Wichita, Kansas 67209, Phone: 316-517-9370, E-mail: maintenanceengineering@txtav.com if other maintenance tracking system is used. Task Findings (Check All That Apply) [ ] No Fault Found [ ] Fails Skin Waviness [ ] Failed Static System Check [ ] Failed Leak Check [ ] Failed Pitot System Check [ ] Failed Anti-Icing System Check [ ] Failed Functional Check [ ] Failed Air Data Computer Check [ ] Other 34-10-00 Page 616

End of task 34-10-00 Page 617

AIRCRAFT DIVISION WICHITA, KANSAS 67277 SUPPLEMENT NO: ICA-680A-34-00001 APPENDIX A: ILLUSTRATED PARTS CATALOG NOT APPLICABLE Cessna Aircraft Company Form 2261 Rev 1

AIRCRAFT DIVISION WICHITA, KANSAS 67277 SUPPLEMENT NO: ICA-680A-34-00001 APPENDIX B: WIRING DIAGRAM MANUAL NOT APPLICABLE Cessna Aircraft Company Form 2261 Rev 1