SERVICE BULLETIN REVISION

Transcription

1 Revision 1 REVISION TRANSMITTAL SHEET This sheet transmits Revision 1 to. A. Changed the drawing number in the REFERENCES table from C to CI B. Changed the drawing number in the REFERENCES table from C to CI C. Changed the drawing number in Step 3 and Step 6 of the instructions from C to CI D. Changed the drawing number in Step 5 of the instructions from C to CI E. Minor editorial changes throughout document. NOTE: This revision replaces the original issue of in its entirety. NOTE: Change bars and pointing hands are not used in this publication to denote revised material. This transmittal sheet provides a complete description of the changes made by this revision, except for editorial changes. REVISION COMPLIANCE NO EFFECT. Airplanes previously modified by this service bulletin are not effected by this revision. SUMMARY OF REVISIONS Original Issue Dec 1/2004 Revision 1 May 3/2005

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3 TITLE NAVIGATION - SANDELST3400TAWSINSTALLATION EFFECTIVITY MODEL UNIT NUMBERS thru NOTE: This service bulletin does not apply to Model 551 airplanes. NOTE: Limitations and Conditions: This Service Bulletin should not be extended to other specific airplanes of these models on which other previously approved modifications are incorporated, unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of that airplane. NOTE: Airplane Flight Manual Supplement FM90505 will be required to complete this service bulletin. NOTE: An electrical loads analysis (ELA) must be conducted to make sure that this service bulletin is compatible with the existing electrical loads. The installer should make sure that adequate capacity exists for the loads being added to the circuit breaker panel and distribution system electrical loads prior to modification of the power distribution system. Refer to the Maintenance Manual, Chapter 24, Electrical Load Analysis - Description and Operation for the aircraft base load report. Additional electrical system changes may have occurred since the airplane left the factory and will need to be accounted for in the electrical loads review conducted during this modification. If the installer determines that additional electrical loads have been added and are not assessed in the base ELA, please contact Cessna ACMT (Mod Engineering) at Telephone Number (316) for assistance if further analysis is necessary. NOTE: The Sandel TAWS/RMI can be installed in either the pilots or copilots instrument panel. NOTE: If the airplane has an RMI-30, RMI-36 or RMI332C-10 indicator, additional FAA approval may be required. The RMI-30, RMI-36 or RMI332C-10 have an auxiliary compass synchro output (bootstrap) that supplies an auxiliary heading source to systems added after the airplane was delivered to the original customer. The Sandel TAWS/RMI does not have this output. If a system has been added to the airplane that uses this RMI output, they will need to be connected to an alternate source and the installation must be FAA approved. REASON Gives a Class A or a Class B TAWS installation for the Cessna Citation Model 550. DESCRIPTION This service bulletin provides parts and instructions to install a Sandel ST3400 TAWS system with software A3.06 or later approved version. NOTE: Only one TAWS RMI will be installed in either the pilot's or copilot's instrument panel. This option is at the discretion of the airplane owner. Revision 1 - May 3/2005 Page 1 of 21 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A , Fax COPYRIGHT 2004

4 COMPLIANCE OPTIONAL. This service bulletin may be accomplished at the discretion of the owner. A service bulletin published by Cessna Aircraft Company may be recorded as completed in an aircraft log only when the following requirements are satisfied: 1) The mechanic must complete all of the instructions in the service bulletin, including the intent therein. 2) The mechanic must correctly use and install all applicable parts supplied with the service bulletin kit. Only with written authorization from Cessna Aircraft Company can substitute parts or rebuilt parts be used to replace new parts. 3) The mechanic or airplane owner must use the technical data in the service bulletin only as approved and published. 4) The mechanic or airplane owner must apply the information in the service bulletin only to aircraft serial numbers identified in the Effectivity section of the bulletin. 5) The mechanic or airplane owner must use maintenance practices that are identified as acceptable standard practices in the aviation industry and governmental regulations. No individual or corporate organization other than Cessna Aircraft Company is authorized to make or apply any changes to a Cessna-issued service bulletin, service letter, or flight manual supplement without prior written consent from Cessna Aircraft Company. Cessna Aircraft Company is not responsible for the quality of maintenance performed to comply with this document, unless the maintenance is accomplished at a Cessna-owned of Cessna authorized Citation Service Center facility. FLIGHT CREW OPERATIONS Refer to the attached Flight Crew Operations Summary. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. This information shall be considered an amendment to the Cessna Manufacturer's Maintenance Manual. MANPOWER MATERIAL - Cost and Availability WORK PHASE MAN-HOURS Modification * PART NUMBER AVAILABILITY COST -0 * * -1 * * -2 * * -3 * * -4 * * * Refer to the attached Service Bulletin Supplemental Data sheet for man-hours, material cost and availability, and warranty information. Revision 1 - May 3/2005 Page 2

5 CONSUMABLE MATERIAL Sealant In addition to the above kit(s), the following materials, or equivalent, are required for the accomplishment of this service bulletin. NAME NUMBER MANUFACTURER USE Color Chem Film Treatment Corrosion Resistant Primer CMNP021 Class B1/2 Alodine x 419/910 x 942 Cessna Citation Parts Distribution 7121 Southwest Boulevard Wichita, KS Henkel Surface Technologies Stephenson Highway Madison Heights, MI PRC-DeSoto Inc Fourth St. Berkeley, CA To seal the antenna installations. To treat bare aluminum. To treat bare aluminum. TOOLING NAME NUMBER MANUFACTURER USE Nav Test Set NAV-402AP IFR Systems Incorporated West York Street Wichita, KS Pitot-Static Test Set or Equivalent Laversab Incorporated Greenbough Suite 300 Stafford, TX To test the glideslope and nav receivers. To test the pitot-static systems. CHANGE IN WEIGHT AND BALANCE Weigh the airplane or calculate the weight and balance change after modification to determine weight and balance information. Revision 1 - May 3/2005 Page 3

6 REFERENCES Cessna Model 550 Maintenance Manual Cessna Model 500 Series Structural Repair Manual Instructions for Continued Airworthiness (document number CMR ) Order the applicable Cessna Engineering Drawings that follow. The drawings required to complete this modification will depend on the configuration of the airplane. The latest revision and all applicable DCN's for each document must be used. DOCUMENT NUMBER CA16163 TITLE SANDEL ST3400 TAWS/RMI WBA CA16173 SANDEL ST3400 ANNUNCIATOR INTERFACE WBA CA16174 CA16175 CA16176 CA16177 CA16182 CI90629 CI90630 CI54293 CI54294 CI19012 S2811 SANDEL ST3400 AUDIO INTERFACE WBA SANDEL ST3400 FLAPS INTERFACE WBA SANDEL ST3400 SYSTEMS INTERFACE SANDEL ST3400 COLLINS RMI-35 INTERFACE SANDEL ST3400 COLLINS RMI-30/332C-10 INTERFACE SANDEL ST3400 TAWS INSTRUMENT PANEL MODS RIGHT CIRCUIT PANEL MOD SANDEL TAWS INSTALLATION OVERVIEW SANDEL TAWS WIRE ROUTING TEMPERATURE PROBE INSTALLATION - RIGHT NOSE CUTOUT INSTRUMENT PANEL PUBLICATIONS AFFECTED Cessna Model 550 Airplane Flight Manual ACCOMPLISHMENT INSTRUCTIONS 1. Prepare the airplane for maintenance. A. Make sure that all switches are in the OFF/NORM position. B. Disconnect electrical power from the airplane. (1) Disconnect the airplane battery. (2) Disconnect external electrical power. C. Attach maintenance warning tags to the battery and external power receptacle that have "DO NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" writtenonthem. Revision 1 - May 3/2005 Page 4

7 2. (Airplanes that are not originally equipped with an AZ-242 Air Data Computer with a temperature probe.) Install one Temperature Probe. (Refer to Cessna Engineering Drawing CI19012.) NOTE: Make sure that the Temperature Probe extends 0.66-inch inch from the skin surface. NOTE: Use the color chem film treatment and corrosion resistant primer as necessary to complete this service bulletin. 3. Do a modification of the instrument panels. (Refer to Cessna Engineering Drawings CI90629 and S2811 and the Structural Repair Manual.) 4. Modify the wiring. (Refer to the Wiring Diagram Manual, Chapter 20, Standard Practices - Airframe.) NOTE: Route the wiring as shown in Cessna Engineering Drawing CI A. Install the CA TAWS Wire Bundle Assembly. (Refer to Cessna Engineering Drawing CA16163.) B. Install the CA Annunciator Interface Wire Bundle Assembly. (Refer to Cessna Engineering Drawing CA16173.) C. Install the CA Audio Interface Wire Bundle Assembly. (Refer to Cessna Engineering Drawing CA16174.) D. Install the CA Flaps Interface Wire Bundle Assembly. (Refer to Cessna Engineering Drawing CA16175.) E. Install the CA Systems Interface Wire Bundle Assembly. (Refer to Cessna Engineering Drawing CA16176.) F. (Airplanes equipped with a Collins RMI-36 indicator) Install the CA Collins RMI-36 Interface Wire Bundle Assembly. (Refer to Cessna Engineering Drawing CA16177.) G. (Airplanes equipped with a Collins RMI-30 or RMI-332C-10 indicator) Install the CA Collins RMI-30/ Interface Wire Bundle Assembly. (Refer to Cessna Engineering Drawing CA16182.) 5. Do a modification of the right circuit breaker panel. A. (Airplanes thru -0533) Install two Circuit Breakers as shown in Cessna Engineering Drawing CI and CI B. (Airplanes thru ) Install two Circuit Breakers as shown in Cessna Engineering Drawing CI and CI Install the new ST3400 Sandel TAWS/RMI. (Refer to Cessna Engineering Drawing CI90629.) NOTE: The Sandel TAWS/RMI can be located in the left or right instrument panel depending on the configuration of the airplane. A. Remove the existing RMI. (Refer to the Maintenance Manual, Chapter 34, Radio Magnetic Indicators - Maintenance Practices.) B. Return the RMI to Cessna for credit. C. (Airplanes that install Class A TAWS.) Install one ST Sandel TAWS/RMI's. (1) Make sure that the Sandel TAWS/RMI is mod 2A or later. D. (Airplanes that install Class B TAWS) Install one ST Sandel TAWS/RMI. (1) Make sure that the Sandel TAWS/RMI is mod 2A or later. 7. Remove the warning tags and connect external power to the airplane. Revision 1 - May 3/2005 Page 5

8 8. Do a test of the Sandel TAWS/RMI installation. NOTE: The Sandel TAWS needs to have a valid GPS satellite signal. NOTE: An installation manual is available at which provides detailed configuration instructions. A. Use the tables that are attached to this service bulletin to determine what data type and other inputs to the ST3400 TAWS/RMI. B. TheairplanemustbeinfullviewoftheGPSsatellites. C. Press and hold the BRG1 and BRG2 buttons. D. Turn avionics power ON. E. Wait until the MAINTENANCE PAGE INDEX is displayed. NOTE: When the MAINTENANCE PAGE INDEX is displayed it will automatically enter "READ"' mode. To enter "EDIT" mode press and hold the M button for three seconds. To exit "EDIT" mode press and hold the M button for three seconds. This can be done at any time while in the maintenance mode. F. Release the BRG1 and BRG2 buttons. NOTE: The CONFIG MODULE STATUS page may appear with initial power up and configuration of the unit. This page will be displayed again only if there is a mismatch in information between the configuration module and the ST3400. The mismatched information will be displayed at the top of this page with the necessary actions to be taken. G. Make sure that the CM is not displayed. NOTE: If CM is displayed in the upper right corner, no stored data can be read from or written to the configuration module. If CM is displayed after the initial configuration, it could indicate that the configuration module is not operating correctly. NOTE: Additional configuration information: ST3400 TO CM - if this option is selected it will allow data that is stored in the ST3400 to be written to the configuration module. When this option is selected it will OVERWRITE all information stored in the configuration module. CM TO ST if this option is selected it will allow data that is stored in the configuration module to be transferred to the ST3400. When this option is selected it will OVERWRITE all information stored in the ST3400. The airplane tail number should be entered on the systems settings page. H. Select the ST3400 to maintenance page 2, SYSTEM. (1) Make sure that the Software Rev is A3.06 or later. I. Select the ST3400 to maintenance page 3, AIRDATA. (1) Make sure that ADC1/BR1 is 429-B. J. Configure and record the configuration information from the ST3400 TAWS/RMIs. NOTE: Use the tables in the attachment to determine the data type. PAGE EQUIPMENT FUNCTION DATA TYPE AIR DATA ADC-1 3 CBA1 3 BR1 3 TA1 Revision 1 - May 3/2005 Page 6

9 PAGE EQUIPMENT FUNCTION DATA TYPE 3 OAT AIR DATA ADC-2 (if installed) 4 CBA1 4 BR1 4 TA1 4 OAT ADF & HEADING 5 ADF-1 5 VALID 5 ADF-2 5 VALID 5 HDG-1 5 VALID 5 HDG-2 5 VALID DISCRETE 6 AP 6 ALERT 6 TEST 6 FLAPS 6 GEAR 6 WHEELS 6 WINDSHIELD WIPERS NAV & ILS 7 NAV-1 7 CALIBRATE 7 NAV-2 7 CALIBRATE 7 GS #1 7 GS #2 RADIO ALTIMETER 8 RA-1 8 VALID 8 RA-2 8 VALID Revision 1 - May 3/2005 Page 7

10 PAGE EQUIPMENT FUNCTION DATA TYPE GPS/FMS-1 9 SELECTION GPS/FMS-1 10 SELECTION K. Turn avionics power OFF and wait a minimum of 20 seconds. L. Turn avionics power ON and wait for the avionics to initialize. M. Do a check of the flap override switch. (1) Press the FLAP OVRD annunciator switch. (2) Make sure that the ACTIVE portion of the switch comes on and the ST3400 indicated FLAPS OVRD. (3) Press the FLAP OVRD annunciator switch. (4) Make sure that the ACTIVE portion of the switch goes out and the ST3400 does not indicate FLAPS OVRD. N. Do a check of the G/S override switch. (1) Press the G/S OVRD annunciator switch. (2) Make sure that the ACTIVE portion of the switch comes on and the ST3400 indicated G/S OVRD. (3) Press the G/S OVRD annunciator switch. (4) Make sure that the ACTIVE portion of the switch goes out and the ST3400 does not indicate G/S OVRD. O. Do an air data test. (1) Connect a pitot static test box to the airplane. (2) Set the ST3400 to maintenance page three and four. (3) Set the pilot's altimeter to field elevation. (4) Do the air data test. SIGNAL FUNCTION TOLERANCE RECORD VALUE PASS FAIL Field Elevation CBA 1 Make sure that the altitude between the pilot's altimeter and TAWS is within ± 75 feet. Adjust the Pitot/Static Test box to 1000 feet over field elevation CBA 1 Make sure that the altitude between the pilot's altimeter and TAWS is within ± 75 feet. (5) Adjust the pitot/static box for a climb and descent as necessary (do not exceed the airplane's VSI rate). Revision 1 - May 3/2005 Page 8

11 SIGNAL FUNCTION TOLERANCE RECORD VALUE PASS FAIL Adjust the pitot/static test box to 1,000, 2,000 and 4,000 fpm climb BR 1 Make sure that the vertical speed readings between the pilot's VSI and TAWS is within ±200fpm. Adjust the pitot/static test box to 1,000, 2,000 and 4,000 fpm descent. BR 1 Make sure that the vertical speed readings between the pilot's VSI and TAWS is within ±200fpm. NOTE: If using analog baro rate input this tolerance is increased ± 400 fpm. (6) Adjust the pitot static box to field elevation. SIGNAL FUNCTION TOLERANCE RECORD VALUE PASS FAIL Adjust the pitot/static test box to 120, 160 and 220 knots. TA 1 Make sure that the airspeed readings between the pilot's airspeed and TAWS is within ± 25 knots. Field Temp IAT or OAT Make sure that the temperature is within ± 5 degrees of ambient. P. Do an ADF input test. (1) Select the ST3400 to maintenance page 5, ADF and HDG. Revision 1 - May 3/2005 Page 9

12 SIGNAL FUNCTION RESULT PASS FAIL Tunethe#1ADFto a station and select the ADF mode. ADF 1 Make sure that the #1 ADF bearing value matches thebearingtothe station within ± 5 degrees. #1 ADF Valid ADF 1 VALID Make sure that the value of #1 ADF valid indicates VALID. Tunethe#1ADF to a station and select the ANT mode ADF 1 VALID Make sure that the value of the #1 ADF valid shows INVALID DATA. Q. Do a heading input test. (1) Select the ST3400 to maintenance page 5, ADF and HDG. NOTE: If the Sandel TAWS/RMI indicator is installed in the pilots instrument panel then complete the table that follows for HDG 2. If the Sandel TAWS/RMI indicator is installed in the copilots instrument panel then complete the table that follows for HDG 1. SIGNAL FUNCTION RESULT PASS FAIL #1 heading system use the manual mode and slew the heading 360 degrees #1 heading valid disengage the circuit breaker to go invalid #1 heading valid engage the circuit breaker #2 heading system use the manual mode and slew the heading 360 degrees. HDG 1 HDG 1 VALID HDG 1 VALID HDG 2 HDG 2 VALID Make sure that the #1 heading value matches the airplane heading displayedinthehsi within ± 2 degrees. Make sure that the value of the #1 HDG valid show VALID. Make sure the #2 mag heading value the airplane displayedonthe HSI within ± 2 degrees. Make sure that the value of the #2 mag heading valid shows INVALID DATA. Make sure that the value of the #2 HDG valid shows VALID. R. Do a discrete inputs test. (1) Check all discrete inputs are interfaced to the SANDEL ST3400 TAWS/RMI. Revision 1 - May 3/2005 Page 10

13 (2) Select the ST3400 to maintenance page 6, DISCRETES. NOTE: The airplane will need to be placed on jacks or a landing gear breakout boxes will be needed to simulate retracted landing gear. Revision 1 - May 3/2005 Page 11

14 SIGNAL FUNCTION RESULT PASS FAIL Engage Autopilot AP ENGAGE Make sure that the value ENGAGED is shown when the autopilot is engaged. Disengage Autopilot AP ENGAGE Make sure that the value DISENGAGED shows when the autpilot is disengaged. Alert Inhibit ALERT Activate the remote switch if installed. Make sure that ALERTS DISABLED is shown, release theswitchand make sure ALERTS ENABLED is shown. Self Test TEST Press the remote switch if installed. Make sure that ALERTS TEST ENABLED is shown, release the switch and make sure that ALERTS TEST DISABLED is shown. Cycle the flaps through allthe settings FLAPS Make sure that with the flaps in the landing setting that FLAPS DOWN is shown and in all other positions (including takeoff) is shown as FLAPS UP. Landing Gear GEAR Make sure that the value shows GEAR DOWN on the ground. Retract the landing gear to make sure the value shows GEAR UP. N/A WIPERS S. Do a Nav and ILS Input Test. (1) Set the ST3400 to maintenance page 6, NAV and ILS. Revision 1 - May 3/2005 Page 12

15 SIGNAL FUNCTION RESULT PASS FAIL #1 VOR/ILS receiver generate external VOR signal at 0 degrees TO. #1 VOR/ILS receiver, generate external localizer signal, vary the input deviation. Test at 0, ±0.046 and ± DDM #1 VOR/ILS receiver, generate external glideslope signal, vary the input deviation. Test at 0, ±0.046 and ± DDM #2 VOR/ILS receiver, generate the external VOR signal at 0 degrees TO. #2 VOR/ILS receiver, generate the external localizer signal, vary the input deviation. Test at 0, ± and ± DDM. #2 VOR/ILS receiver, generate the external glideslope signal, vary the input deviation. Test at 0, ± and ± DDM NAV 1 GS 1 GS 1 NAV 2 NAV 2 GS 2 NAV 1 value VOR BEARING should read 0 degrees TO. Calibrate BRG as necessary. Make sure that ILS NOT TUNED is shown. The NAV 1 value should indicate ILS TUNED and LOC DEV DDM deviation should match generated signal. The GS1 value for GS DEV DDM deviation should match generated signal. NAV 2 value VOR bearing should read 0 degrees TO. Calibrate BRG as necessary. Make sure the value ILS NOT TUNED is shown. NAV 2 value should indicate ILS TUNED and LOC DEV DDM deviation should match the generated signal. The GS2 value for GS DEV DDM deviation should match generated signal. T. Do a radar altimeter test. NOTE: The radar altimeter test may be done by pressing the radar altimeter self test button, or by using a radar altimeter test set. This test procedure references the use of the radar altimeter self test button and does not provide the information to setup and test the radar altimeter with a test set. The test that will be performed to validated the ST3400 TAWS/RMI operation with the radar altimeter will be the tests that follow. Revision 1 - May 3/2005 Page 13

16 SIGNAL FUNCTION RESULT PASS FAIL #1 Radar Altimeter Receiver/ Transmitter Activate Rad Alt self test #1 Radar Altimeter Fail, disengage the circuit breaker to go invalid. #1 Radar Altimeter Fail, engage the circuit breaker. #1 Radar Altimeter valid, disengage the circuit breaker to go invalid. #1 Radar Altimeter valid, engage the circuit breaker. RA 1 RA1FAILINPUT J2-13 RA1FAILINPUT J2-13 RA 1 VALID RA 1 VALID #1 radar altimeter value should show with ± 5 feet of Rad Alt test output. Make sure that the value of the#1radar Altimeter Fail shows J2-13<+14VDC. Make sure that the value of the#1radar Altimeter Fail shows J2-13>+14VDC. Make sure that the value of the #1 Radar Altimeter Valid shows INVALID DATA. Make sure that the value of the #1 Radar Altimeter Valid shows VALID. U. Do a GPS/FMS Test. (1) Set the ST3400 to Maintenance Page 9, GPS/FMS1. SIGNAL FUNCTION RESULT PASS FAIL #1 GPS receiver lockedonwiththe invalid signal. Turn off the #1 GPS receiver. PASS/FAIL REMARKS #1 GPS POSITION #1 GPS latitude and longitude value displayed should match the position onthe#1gps. #1 GPS POSITION #1 GPS latitude and longitude value will not be displayed. NOTE: Press the VUE button and UP/DOWN buttons for access to additional parameters and GPS Altitude. (a) Activate the TAWS inhibit. Make sure that this inhibit annunciates on screen TAWS inhibited when selected and does not annunciate on screen TAWS Inhibited when deselected. Revision 1 - May 3/2005 Page 14

17 (b) Power up the GPS/FMS but do not initialize, do not accept/acknowledge latitude or longitude position, or enter and activate a flight plan. Make sure that the ST3400 flags the terrain display (GPS/FMS not active and GPS/FMS data output is not valid). PASS/FAIL REMARKS (c) Initialize the GPS/FMS and activate a valid flight plan. Make sure that the ST3400 shows correct terrain and works correctly. Disable the GPS signal, by either disengaging the circuit breaker for the GPS/FMS or covering the antenna with a piece of sheet metal. Make sure that the GPS/FMS position solution is no longer valid and that the flight plan is no longer active. Make sure that the ST3400 flags the terrain display. NOTE: Some GPS/FMS receivers such as the KLN 90B only provide a valid output after developing a ground track. PASS/FAIL REMARKS (d) Fail the GPSs/FMSs that the Sandel TAWS/RMI is connected to and make sure that the TERR FAIL is shown and the #1 ST3400 shows TAWS INH. PASS/FAIL REMARKS (e) Run a #1 TAWS self test and make sure that aural annunciations are acceptable in clarity and volume (both loudspeaker and headphone aural annunciations). PASS/FAIL REMARKS (f) Make sure the ST3400 display and annunciator switch lights can be seen under all expected cockpit ambient light conditions (this test should be done in bright daylight and again at night or in a simulated dark cockpit). PASS/FAIL REMARKS (g) Make sure that the ST3400 manual display and annunciator switch lights brightness lighting control is working and provides display brightness over the full range of control for all normal cockpit lighting conditions. PASS/FAIL REMARKS (h) Make sure that the annunicator switch lights can be seen from both pilots and copilots seats. View the display from normal, expected viewing angles. This should include viewing the annunicator switch lights from all viewing angles that might be encountered during normal cockpit operations PASS/FAIL REMARKS Revision 1 - May 3/2005 Page 15

18 9. Do the Electro-Magnetic Interference (EMI) and Radio Frequency Interference (RFI) tests. A. Make sure that the airplane is correctly configured. (1) Successful completion of the Sandel TAWS/RMI test procedures as outlined in Step 8. (2) All access panels, radomes, doors and hatches must be installed as they would be for flight. (3) Alloftheairplanesystemsaretobeinstalledandinworkingcondition. NOTE: The airplane engines should be operated at ground idle to accomplish the EMI/RMI checks. B. Described below are the operating observations: (1) Flight Director (FD), Navigation (NAV) (short range navigation (SRN) signal strength VOR, ADF, Localizer and Glideslope), GPS signal strength and Attitude (ATT) indicators, shall be selected and during the test procedures. Observe the FD, NAV and ATT indicators for any abnormal operation, instability, intermittent warning flags and other malfunctions. (2) Air Data Systems - Observe the altimeters, vertical speed and airspeed indicators for any abnormal operations, movement, or flags coming into view while operating the TAWS/RMI. (3) Attitude System - observe the attitude direction indicator (ADI). The ADI should not show signs of abnormal operations or instability while operating the TAWS/RMI. (4) Compass System - Observe the horizontal situation indicator (HSI) and RMI systems. The compass cards should not show signs of abnormal operations or instability while operating the TAWS/RMI. (5) Compass System (Standby) - Observe the standby compass. The standby compass should not show any signs of abnormal operations or instability while operating the TAWS/RMI. (6) Flight Guidance System (Autopilot) - Observe the flight controls with the autopilot engaged. The autopilot system should not show any signs of abnormal operations or instability while operating the TAWS/RMI. (7) Communication/Navigation - The COMM and NAV systems should not show any signs of abnormal operations or instability while operating the TAWS/RMI. NOTE: Operate the COMM and NAV systems on at least one low frequency, high frequency and mid-band frequency. (8) Radio Altimeter System - Observe the RA system. The RA system should not show any signs of abnormal operations or instability while operating the TAWS/RMI. (9) Optional Systems - Monitor all other optional systems. All of the optional systems should not show any signs of abnormal operations or instability while operating the TAWS/RMI. C. Complete the table that follows. NOTE: PASS: no significant conducted or radiated interference is present. FAIL: significant interference exists and corrective action is necessary. Revision 1 - May 3/2005 Page 16

19 EMI RECEPTOR/EMITTER PILOT'S PRIMARY ATTITUDE DISPLAY COPILOT'S PRIMARY ATTITUDE DISPLAY STANDBY ATTITUDE INDICATOR (IF INSTALLED) DG 1 (AHRS1)/EHSI 1 DG 2 (AHRS2)/EHSI 2 AUTOPILOT COMPUTER #1 FLIGHT DIRECTOR * #2 FLIGHT DIRECTOR * MAGNETIC COMPASS STANDBY HSI (IF INSTALLED) TCAS LEFT ALTIMETER/ADC RIGHT ALTIMETER/ADC VHF COMM 1 VHF COMM 2 VHF NAV 1 VHF NAV 1 XPDR 1 XPDR 2 DME 1 DME 2 ADF 1 ADF 2 RAD ALT FMS 1 (Nav display on the HSI) FMS 2 (Nav display on the HSI) MFD/RADAR VNAV AUDIO 1 AUDIO 2 #1 RATE GYRO EMI EMITTER ST3400TAWS/RMI & DISPLAY PASS/FAIL EMI RECEPTOR ST3400TAWS/RMI & DISPLAY PASS/FAIL Revision 1 - May 3/2005 Page 17

20 EMI RECEPTOR/EMITTER #2 RATE GYRO ENGINE INSTRUMENTS (at ground idle only) RAT INDICATOR HF RADIO (if installed) AIR CONDITIONER (if installed) FUEL BOOST PUMPS INFLIGHT ENTERTAINMENT EMI EMITTER ST3400TAWS/RMI & DISPLAY PASS/FAIL EMI RECEPTOR ST3400TAWS/RMI & DISPLAY PASS/FAIL ADDITIONAL SYSTEMS INSTALLEDONTHEAIRPLANE (Examples: AC Inverter, Aircell, Flight Phone, RS Data Port) * Test at least two vertical and two lateral modes. 10. Make sure that the Flight Crew Operations Summary included with this service bulletin is given to the crew to inform them of the operational changes resulting from incorporation of this service bulletin. 11. Make sure that Airplane Flight Manual Supplement FM90505 is inserted in the flight manual. 12. Insert the Instructions for Continued Airworthiness (document number CMR ) into the Maintenance Manual. 13. Record that this service bulletin has been completed. A. Complete a Maintenance Transaction Report. B. Put a copy of the completed Maintenance Transaction Report in the airplane logbook. C. Send a copy of the completed Maintenance Transaction Report to: CESCOM, P.O. Box 7706, Wichita, KS MATERIAL INFORMATION Airplanes that are equipped with a pilot and copilot Class A Installation must order the following kit. Revision 1 - May 3/2005 Page 18

21 NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION -0 1 Kit, consisting of the following parts: CA TAWS ST3400 WBA None CA Annunciator Interface Wire None Bundle Assembly CA Audio Interface Wire Bundle None Assembly CA Flaps Interface Wire Bundle None Assembly CA Systems Interface Wire None Bundle Assembly Sandel TAWS/RMI - Class A or Instructions NOTE: The 9013X Sandel ST3400 TAWS/RMI Kit contains the parts that follow: PG Pilots Guide ADB-WW Airport Database TDB-XX Terrain/Obstacle Database USB Serial Cable ST3400-XXX TAWS/RMI Display unit. Return to Cessna Airplanes that are equipped with a pilot and copilot Class B Installation must order the following kit. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION -1 1 Kit, consisting of the following parts: CA TAWS ST3400 WBA None CA Annunciator Interface Wire None Bundle Assembly CA Audio Interface Wire Bundle None Assembly CA Flaps Interface Wire Bundle None Assembly CA Systems Interface Wire Bundle Assembly None Revision 1 - May 3/2005 Page 19

22 NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION Sandel TAWS/RMI - Class B or Instructions NOTE: The 9013X Sandel ST3400 TAWS/RMI Kit contains the parts that follow: PG Pilots Guide ADB-WW Airport Database TDB-XX Terrain/Obstacle Database USB Serial Cable ST3400-XXX TAWS/RMI Display unit. Return to Cessna. In addition to the applicable above kit, airplanes that are not originally equipped with a AZ-242 Air Data Computer with a temperature probe must order the following kit. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION -2 1 Kit, consisting of the following parts: CM3827AD4-3 4 Rivet None CM3827AD4-4 4 Rivet None Temperature Probe Temperature Probe Mounting Plate CI Doubler In addition to the applicable above kit, airplanes equipped with a Collins RMI-30 or RMI-332C-10 indicator must order the following kit. NEW P/N QUAN- TITY -3 1 Kit, consisting of the following parts: CA RMI-30/332C-10 Interface Wire Bundle Assembly KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION None In addition to the applicable above kit, airplanes equipped with a Collins RMI-36 indicator must order the following kit. Revision 1 - May 3/2005 Page 20

23 NEW P/N QUAN- TITY -4 1 Kit, consisting of the following parts: CA RMI-36 Interface Wire Bundle Assembly KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION In addition to the applicable above kit, it will be necessary to order some of the following parts depending on the configuration of the airplane. NEW P/N QUAN- TITY None KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION Circuit Breaker S2899L2.0 Discard Circuit Breaker S2899L5.0 Discard NAS1149F0763P As Required Washer None Revision 1 - May 3/2005 Page 21

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25 ATTACHMENT FLIGHT CREW OPERATIONS SUMMARY This summary provides additional information for the flight crew regarding operational changes as a result of accomplishment of this service bulletin. Please remove this summary from the service bulletin and give it to the flight crew. This summary is informational only and does not supersede any information in the FAA Approved Airplane Flight Manual. Refer to Airplane Flight Manual Supplement FM90505.

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27 ATTACHMENT INSTALLATION INFORMATION Airplane Serial Number Airplane Registration Airplane Make Airplane Model Aircraft Configuration Ground Test Personnel Airplane Operator System Installer System Information Date ST3400 Serial Number Pilot's ST3400 Part Number Pilot's ST3400 Software Revision (Must be A3.06 or later.) Pilot's ST3400 Terrain Revision Pilot's ST3400 Map Data Revision Pilot's

28 ATTACHMENT AIRPLANE CONFIGURATION Installed Equipment Interface Type ARNIC 429 Label GPS/FMS Radio Altimeter Heading ADF NAV Air Data Traffic The above table should be completed and stored in the airplane log book for future reference.

29 ATTACHMENT CONFIGURATION TABLES NOTE: Use the tables that follow as necessary to configure the Sandel ST3400 TAWS. GPS/FMS MANUFACTURER MODEL INTERFACE TYPE Free Flight 1201 RS232 Garmin GPS Garmin GNS 4XX 429 *RS232 Garmin GNS5XX 429 *RS232 Honeywell KLN90B Honeywell KLN Honeywell KLN Honeywell GNS-XLs 429 Low Speed Honeywell GNS-XLs 429 High Speed II Morrow II Morrow Trimble 2000/3000 RS422 Trimble 2101 RS422 Trimble 2101 I/O 429 Low Speed Trimble 2101 I/O 429 High Speed Universal UNS-1X 429 Low Speed

30 ATTACHMENT ARINC 429 LABELS FOR GPS/FMS LABEL 074 Flight Plan 075 Waypoint HDR 076 GPS Altitude 101 HDOP 102 VDOP 113 Waypoint Checksum 115 WPT Bearing 136 VFOM 147 MAG VAR 150 Time (HH:MM:SS) 165 GPS Vertical Speed 167 ANP 247 HFOM 260 Date 261 GPS Discrete 275 LRN Integrity 303 Waypoint Type 304 Waypoint ID LSB 305 Waypoint ID MSB 306 Waypoint Latitude 307 Waypoint Longitude DATA 310 Present Position Latitude 311 Present Position Longitude 312 Ground Speed 313 Ground Track 315 Wind Speed 316 Wind Direction

31 ATTACHMENT RADAR ALTIMETER MANUFACTURER MODEL INTERFACE TYPE Bendix/King KRA405 Analog Bendix/King KRA405B ARNIC 429 Collins ALT50 Analog Collins ALT50A Analog Collins ALT55 Analog Collins RAC870 ARNIC 429 Sperry RT-220 Analog Sperry RT-300 Analog ARINC 429 LABELS FOR RADAR ALTIMETER LABEL 164 Radio Altitude DATA HEADING MANUFACTURER MODEL INTERFACE TYPE Bendix/King KCS 55A (KI525A) XYZ Bendix/King KCS 305 XYZ Collins MCS 65 (DGS 55) XYZ Sperry C14A XYZ ARINC 429 LABELS FOR HEADING LABEL 320 Magnetic Heading DATA

32 ATTACHMENT ADF MANUFACTURER MODEL INTERFACE TYPE Bendix/King KR-87 SIN/COS Bendix/King KDF806 SIN/COS & XYZ Collins ADF-60A SIN/COS & XYZ Collins ADF-60B SIN/COS Collins ADF-462 ARINC 429 ARINC 429 LABELS FOR ADF LABEL 162 ADF Heading DATA NAV MANUFACTURER MODEL INTERFACE TYPE Bendix/King KN-40 ARINC 429 Bendix/King KX165 Analog Bendix/King KNR634 Analog Collins VIR30/31/32 Analog Collins VIR432 ARINC 429 Garmin GNS430/530 ARINC 429 ARINC 429 LABELS FOR NAV LABEL 173 Localizer Deviation 174 Glideslope Deviation Label 222 VOR DATA

33 ATTACHMENT AIR DATA MANUFACTURER MODEL INTERFACE TYPE Collins ADC-80 F/H/N Manchester Buss Collins ADC-80-G/J/K/L/M/Q/R ARINC 575-3/ARINC 419 Collins ADC-82 () ARINC 575-3/ARINC 419 Collins ADC-85 () ARINC 575-3/ARINC 419 Honeywell AZ-241 Analog Honeywell AM-250 ARINC 429 Honeywell AZ-252 ARINC 429 Honeywell AZ-600 Analog Honeywell AZ-810 ARINC 429 IS & S ADDU ARINC 429 Penny & Giles D60286 Analog Penny & Giles () ARINC 429 Shadin ADC 2000 ARINC 429 ARINC 429 LABELS FOR AIR DATA LABEL 203 Uncorrected Altitude 204 CorrectedBaroAltitude 210 True Airspeed 211 Total Air Temperature 212 Baro Rate 213 Static Air Temperature DATA

34 ATTACHMENT TRAFFIC MANUFACTURER MODEL INTERFACE TYPE Goodrich TCAS 791/A 429 Goodrich Skywatch HP 429 Ryan 9900BX 429

35 ATTACHMENT POWER CONSUMPTION UNIT Part Number DISPOSITION POWER (AMPS) RMI Remove 0.60 Sandel TAWS/RMI ST or ST Install 1.60

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37 TITLE SUPPLEMENTAL DATA NAVIGATION - SANDELST3400TAWSINSTALLATION EFFECTIVITY MODEL SERIAL NUMBERS thru NOTE: This service bulletin does not apply to Model 551 airplanes. MANPOWER WORK PHASE Modification MAN-HOURS As Required MATERIAL - Cost and Availability PART NUMBER AVAILABILITY COST -0 * * -1 * * -2 * * -3 * * -4 * * * Please contact Citation Parts Distribution for current cost and availability of parts listed in this service bulletin. Phone at (Domestic) or (International). Send to: citationparts@cessna.textron.com or telefax at Based on availability and lead times, parts may require advanced scheduling. In cases where the required part(s) are available as exchange, order the exchange part and, upon completion, expedite the return of the removed core to avoid return penalties. Contact the Citation Parts Distribution Sales Desk for availability of exchange parts. Page 1 of 1 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A , Fax COPYRIGHT 2004

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