Service Bulletin Sb560-34-121

Citation SERVICE BULLETIN SB560-34-121

TITLE

NAVIGATION - SANDELST3400TAWSINSTALLATION

EFFECTIVITY

MODEL SERIAL NUMBERS

560 -0001 thru -0259

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) 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 syncro 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 addedto 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 V.

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 pilots or copilots instrument panel. This option is at the discretion of the airplane owner.

Dec 1/2004 560-34-121 Page 1 of 19

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 Citation Service Center.

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

WORK PHASE MAN-HOURS Modiﬁcation *

MATERIAL - Cost and Availability

PART NUMBER AVAILABILITY COST SB560-34-121-0 ** SB560-34-121-1 * * SB560-34-121-2 * * SB560-34-121-3 * * SB560-34-121-4 * * SB560-34-121-5 * *

* Refer to the attached Service Bulletin Supplemental Data sheet for man-hours, material cost and availability, and warranty information.

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CONSUMABLE MATERIAL

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 Alodine 1201 Henkel Surface Technologies To treat bare aluminum. Treatment 32100 Stephenson Highway Madison Heights, MI 48071 Corrosion Resistant 513 x 419/910 x PRC-DeSoto Inc. To treat bare aluminum. Primer 942 1608 Fourth St. Berkeley, CA 94710 Sealant Type 1, Class Cessna Citation Parts Distribution For pressure and fay seal B-1/2 (CMNP021 7121 Southwest Boulevard applications. CLASSB1/2) Wichita, KS 67215

TOOLING

NAME NUMBER MANUFACTURER USE Nav Test Set NAV-402AP IFR Systems Incorporated To test the glideslope and 10200 West York Street nav receivers. Wichita, KS 67215 Pitot-Static Test Set 6520-10 or Equiv- Laversab Incorporated To test the pitot-static alent 10435 Greenbough Suite 300 systems. Stafford, TX 77477

CHANGE IN WEIGHT AND BALANCE

Weigh the airplane after modiﬁcation to calculate weight and balance information.

REFERENCES

Cessna Model 560 Maintenance Manual

Cessna Model 500 Series Structural Repair Manual

Instructions for Continued Airworthiness (document number CMR-550-246)

Order the applicable Cessna Engineering Drawings that follow. The drawings necessary 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.

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DOCUMENT NUMBER TITLE CA16163 SANDEL ST3400 TAWS/RMI WBA CA16173 SANDEL ST300 ANNUNCIATOR INTERFACE WBA CA16174 SANDEL ST3400 AUDIO INTERFACE WBA CA16175 SANDEL ST3400 FLAPS INTERFACE WBA CA16176 SANDEL ST3400 SYSTEMS INTERFACE CA16177 SANDEL ST3400 COLLINS RMI-36 INTERFACE CA16182 SANDEL ST3400 COLLINS RMI-30/332C-10 INTERFACE CI90629 SANDEL ST3400 TAWS INSTRUMENT PANEL MODS CI90630 RIGHT CIRCUIT PANEL MOD CI54293 SANDEL TAWS INSTL OVERVIEW CI54294 SANDEL TAWS WIRE ROUTING CI19012 TEMPERATURE PROBE INSTALLATION - RIGHT NOSE S2811 CUTOUT INSTRUMENT PANEL

PUBLICATIONS AFFECTED

Cessna Model 560 Citation V Approved Airplane Flight Manuals

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. 2. (Airplanes that are not originally equipped with an AZ-242 Air Data Computer with a temperature probe.) Install one 05257 Temperature Probe. (Refer to Cessna Engineering Drawing CI19012.) NOTE: Make sure that the 05257 Temperature Probe extends 0.66-inch +0.03 -0.01-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 Drawing CI90629 and S2811 and the 500 Series Structural Repair Manual.) 4. Install the applicable wire bundle assemblies. (Refer to Cessna Engineering Drawings CA16163, CA16173, CA16174, CA16175, CA16176, CA16177 and CA16182 as necessary.) 5. Install one 7277-5-5 Circuit Breaker in the right circuit breaker panel. (Refer to Cessna Engineering Drawing CI90630.) 6. Install the new Sandel TAWS/RMI. (Refer to Cessna Engineering Drawing CI90629.) A. Remove the RMI. (Refer to the Maintenance Manual, Chapter 34, Radio Magnetic Indicators - Maintenance Practices.)

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B. Return the RMI to Cessna for credit. C. (Airplanes that will install Class A TAWS.) Install one ST3400-001 Sandel TAWS/RMI. (1) Make sure that the ST3400-001 Sandel TAWS/RMI is mod 2A or later. D. (Airplanes that will install Class B TAWS.) Install one ST3400-102 Sandel TAWS/RMI. (1) Make sure that the ST3400-102 Sandel TAWS/RMI is mod 2A or later. 7. Remove the warning tags and connect external power to the airplane. 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 WWW.SANDEL.COM, 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. The airplane must be in full view of the GPS satellites. 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 ST3400 - 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.

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

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PAGE EQUIPMENT FUNCTION DATA TYPE 8VALID 8RA-2 8VALID 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. Doacheckoftheﬂap override switch. (1) Press the FLAP OVRD annunicator switch. (2) Make sure that the ACTIVE portion of the switch comes on and the ST3400 indicated FLAPS OVRD. (3) Press the FLAP OVRD annunicator 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 annunicator 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 annunicator 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.

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RECORD SIGNAL FUNCTION TOLERANCE PASS FAIL VALUE Field Elevation CBA 1 Make sure that the altitude between the Pilot's Altimeter and TAWS is within ± 75 feet. Adjust the CBA 1 Make sure that Pitot/Static Test the altitude box to 1000 between the feet over ﬁeld pilot's altimeter elevation 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).

RECORD SIGNAL FUNCTION TOLERANCE PASS FAIL VALUE Adjust the BR 1 Make sure that pitot/static test the vertical box to 1,000, speed readings 2,000 and 4,000 between the fpm climb pilot's VSI and TAWS is within ±200fpm. Adjust the BR 1 Make sure that pitot/static test the vertical box to 1,000, speed readings 2,000 and 4,000 between the fpm descent. pilot's VSI and TAWS is within ±200fpm.

NOTE: If using analog baro rate input this tolerance is increased + or - 400 fpm. (6) Adjust the pitot static box to ﬁeld elevation.

RECORD SIGNAL FUNCTION TOLERANCE PASS FAIL VALUE Adjust the TA 1 Make sure that pitot/static test the airspeed box to 120, 160 readings and 220 knots. between the pilot's airspeed and TAWS is within ± 25 knots. Field Temp IAT or OAT Make sure that the temperature is with ± 5 degrees of ambient.

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P. Do an ADF input test.

(1) Select the ST3400 to maintenance page 5, ADF and HDG.

SIGNAL FUNCTION RESULT PASS FAIL Tunethe#1ADFto ADF 1 Make sure that the a station and select #1 ADF bearing the ADF mode. value matches the bearing to the station within ± 5 degrees. #1 ADF Valid ADF 1 VALID Make sure that the value of #1 ADF valid indicates VALID. Tunethe#1ADFto ADF 1 VALID Make sure that the a station and select value of the #1 the ANT mode 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 HDG 1 Make sure that use the manual the#1heading mode and slew value matches the the heading 360 airplane heading degrees displayedintheHSI within ± 2 degrees. #1 heading valid HDG 1 VALID Make sure that the disengage the value of the #1 HDG circuit breaker to valid show VALID. go invalid #1 heading valid HDG 1 VALID Make sure the engage the circuit #2 mag heading breaker value the airplane displayedonthe HSI within ± 2 degrees. #2 heading system HDG 2 Make sure that the use the manual value of the #2 mode and slew mag heading valid the heading 360 shows INVALID degrees. DATA. HDG 2 VALID Make sure that the value of the #2 HDG valid shows VALID.

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R. Do a discrete inputs test. (1) Check all discrete inputs are interfaced to the SANDEL ST3400 TAWS/RMI. (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.

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SIGNAL FUNCTION RESULT PASS FAIL Engage Autopilot AP ENGAGE Make sure that the value ENGAGED is shown when the autopilots is engaged. Disengage AP ENGAGE Make sure Autopilot that the value DISENGAGED shows when AP is disengaged. Alert Inhibit ALERT Activate the remote switch if installed. Makes sure that ALERTS DISABLED is shown, release the switch and 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 TST DISABLED is shown. Cycle the flaps FLAPS Make sure that through all the with the flaps in settings 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.

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SIGNAL FUNCTION RESULT PASS FAIL #1 VOR/ILS NAV 1 Nav 1 value VOR receiver generate BEARING should external VOR signal read 0 degrees TO. at 0 degrees TO. Calibrate BRGas necessary. Make sure that ILS NOT TUNED is shown, #1 VOR/ILS GS 1 TheNAV1value receiver, generate should indicate external localizer ILS TUNED and signal, vary the LOC DEV DDM input deviation. deviation should Test at 0, ±0.046 match generated and ± 0.093 DDM signal. #1 VOR/ILS GS 1 the GS1 value receiver, generate for GS DEV DDM external glidslope deviation should signal, vary the match generated input deviation. signal. Test at 0, ±0.046 and ± 0.093 DDM #2 VOR/ILS NAV 2 Nav 2 value VOR receiver, generate bearing should the external VOR read 0 degrees TO. signal at 0 degrees Calibrate BRG as TO. necessary. Make sure the value ILS NOT TUNED is shown. #2 VOR/ILS NAV 2 Nav 2 value should receiver, generate indicate ILS TUNED the external and LOC DEV localizer signal, DDM deviation vary the input should match the deviation. Test generated signal. at 0, ± 0.046 and ± 0.093 DDM. #2 VOR/ILS GS 2 The GS2 value receiver, generate for GS DEV DDM the external deviation should glideslope signal, match generated vary the input signal. deviation. Test at 0, ± 0.046 and ± 0.093 DDM

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.

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SIGNAL FUNCTION RESULT PASS FAIL #1 Radar RA 1 #1 radar altimeter Altimeter Receiver/ value should shown Transmitter Activate with ± 5 feet of Rad Rad Alt self test Alt test output. #1 Radar Altimeter RA 1 FAIL INPUT Make sure that Fail, disengage the J2-13 the value of circuit breaker to go the#1Radar invalid. Altimeter Fail shows J2-13<+14VDC. #1 Radar Altimeter RA 1 FAIL INPUT Make sure that Fail, engage the J2-13 the value of circuit breaker the#1Radar Altimeter Fail shows J2-13>+14VDC. #1 Radar Altimeter RA 1 VALID Make sure that the valid, disengage the value of the#1 circuit breaker to go Radar Altimeter invalid. Valid shows INVALID DATA. #1 Radar Altimeter RA 1 VALID Make sure that valid, engage the the value of the circuit breaker. #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 #1 GPS POSITION #1 GPS latitude locked on with the and longitude value invalid signal. displayed should match the position onthe#1GPS. Turn off the #1 GPS #1 GPS POSITION #1 GPS latitude and receiver. 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.

PASS/FAIL REMARKS

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(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 TERRFAILisshownandthe#1ST3400showsTAWSINH.

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 annunicator 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 annunicator 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

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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) All of the airplane systems are to be installed and in working condition. 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.

EMI EMITTER EMI RECEPTOR EMI RECEPTOR/EMITTER ST3400TAWS/RMI & DISPLAY ST3400TAWS/RMI & DISPLAY PASS/FAIL PASS/FAIL PILOT'S PRIMARY ATTITUDE DISPLAY COPILOT'S PRIMARY ATTITUDE DISPLAY STANDBY ATTITUDE INDICATOR (IF INSTALLED)

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EMI EMITTER EMI RECEPTOR EMI RECEPTOR/EMITTER ST3400TAWS/RMI & DISPLAY ST3400TAWS/RMI & DISPLAY PASS/FAIL PASS/FAIL 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 #2 RATE GYRO ENGINE INSTRUMENTS (at ground idle only) RAT INDICATOR HF RADIO (if installed) AIR CONDITIONER (if installed)

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EMI EMITTER EMI RECEPTOR EMI RECEPTOR/EMITTER ST3400TAWS/RMI & DISPLAY ST3400TAWS/RMI & DISPLAY PASS/FAIL PASS/FAIL FUEL BOOST PUMPS INFLIGHT ENTERTAINMENT

ADDITIONAL SYSTEMS INSTALLED ON THE AIRPLANE (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-550-246) 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, PO Box 7706, Wichita, KS 67277.

MATERIAL INFORMATION

The parts included in this service bulletin cover installation for one airplane.

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NEW P/N QUAN- KEY WORD OLD P/N INSTRUCTIONS/ TITY DISPOSITION SB560-34-121-0 1 Kit, consisting of the following parts: CA16163-1 1 Sandel ST3400 Annuncator InterfaceWireBundle Assembly CA16173-1 1 Sandel ST3400 Annunciator InterfaceWireBundle Assembly CA16174-1 1 Sandel ST3400 Audio Interface CA16175-1 1 Sandel ST3400 Flaps Interface Wire Bundle Assembly CA16176-1 1 Sandel ST3400 Systems InterfaceWireBundle Assembly 7277-5-5 1 Circuit Breaker S2899L2.0 Discard SB560-34-121 1 Instructions

Airplanes that were not originally equipped with an AZ-242 Air Data Computer, order the kit that follows in addition to the SB560-34-121-0 Kit.

NEW P/N QUAN- KEY WORD OLD P/N INSTRUCTIONS/ TITY DISPOSITION SB560-34-121-1 1 Kit, consisting of the following parts: CM3827AD4-4.5 4Rivet CM3827AD4-5 4Rivet NAS1149F0763P 3 Washer (AN960-716) 05257 1 Temperature Probe 05592 1 Temperature Probe Mounting Plate CI19012-2 1 Doubler

Airplanes that have a Collins RMI-36 RMI installed, order the kit that follows in addition to a combination of the above kits.

NEW P/N QUAN- KEY WORD OLD P/N INSTRUCTIONS/ TITY DISPOSITION SB560-34-121-2 1 Kit, consisting of the following parts: CA16177-1 1 RMI-36 Interface Wire Bundle Assembly

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Airplanes that have a Collins RMI-30/332C-10 RMI installed, order the kit that follows in addition to a combination of the above kits.

NEW P/N QUAN- KEY WORD OLD P/N INSTRUCTIONS/ TITY DISPOSITION SB560-34-121-3 1 Kit, consisting of the following parts: CA16182-1 1 RMI-30/332C-10 Interface Wire Bundle Assembly

Airplanes that will install Class B TAWS, order the kit that follows.

NEW P/N QUAN- KEY WORD OLD P/N INSTRUCTIONS/ TITY DISPOSITION SB560-34-121-4 1 Kit, consisting of the following parts: 90136 1 Sandel ST3400 TAWS/RMI Kit

Airplanes that will install Class A TAWS, order the kit that follows.

NEW P/N QUAN- KEY WORD OLD P/N INSTRUCTIONS/ TITY DISPOSITION SB560-34-121-5 1 Kit, consisting of the following parts: 90135 1 Sandel ST3400 TAWS/RMI Kit

NOTE: The 9013X Sandel ST3400 TAWS/RMI Kit contains the parts that follow: • 90130-PG Pilots Guide • 90130-ADB-WW Airport Database • 90130-TDB-XX Terrain/Obstacle Database • 88114 USB Serial Cable • ST3400-XXX TAWS/RMI Display unit.

Dec 1/2004 560-34-121 Page 19

Citation ATTACHMENT SB560-34-121

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.

Citation ATTACHMENT SB560-34-121

INSTALLATION INFORMATION

Aircraft Conﬁguration Airplane Serial Number Airplane Registration Airplane Make Airplane Model

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 Citation ATTACHMENT SB560-34-121

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. Citation ATTACHMENT SB560-34-121

CONFIGURATION TABLES

NOTE: Use the tables that follow as necessary to conﬁgure the Sandel ST3400 TAWS.

GPS/FMS

MANUFACTURER MODEL INTERFACETYPE Free Flight 1201 RS232 Garmin GPS 165 429 Garmin GNS 4XX 429 *RS232 Garmin GNS5XX 429 *RS232 Honeywell KLN90B-0200 429 Honeywell KLN900 429 Honeywell KLN94 429 Honeywell GNS-XLs 429 Low Speed Honeywell GNS-XLs 429 High Speed II Morrow 2100 429 II Morrow 2101 429 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 Citation ATTACHMENT SB560-34-121

ARINC 429 LABELS FOR GPS/FMS

LABEL DATA 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

310 Present Position Latitude

311 Present Position Longitude 312 Ground Speed 313 Ground Track 315 Wind Speed 316 Wind Direction Citation ATTACHMENT SB560-34-121

RADIO 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 RADIO ALTIMETER

LABEL DATA 164 Radio Altitude

HEADING

MANUFACTURER MODEL INTERFACE TYPE Bendix/King KCS 55A (KI525A) XYZ Bendix/King KCS 305XYZ Collins MCS 65 (DGS 55) XYZ Sperry C14A XYZ

ARINC 429 LABELS FOR HEADING

LABEL DATA 320 Magnetic Heading Citation ATTACHMENT SB560-34-121

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 DATA 162 ADF Heading

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 DATA 173 Localizer Deviation 174 Glideslope Deviation Label 222 VOR Citation ATTACHMENT SB560-34-121

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 90004-() ARINC 429 Shadin ADC 2000 ARINC 429

ARINC 429 LABELS FOR AIR DATA

LABEL DATA 203 Uncorrected Altitude 204 CorrectedBaroAltitude 210 True Airspeed 211 Total Air Temperature 212 Baro Rate 213 Static Air Temperature Citation ATTACHMENT SB560-34-121

TRAFFIC

MANUFACTURER MODEL INTERFACE TYPE Goodrich TCAS 791/A 429 Goodrich Skywatch HP 429 Ryan 9900BX 429 Citation ATTACHMENT SB560-34-121

POWER CONSUMPTION

UNIT Part Number DISPOSITION POWER (AMPS) RMI 622-4938-004 Remove 0.60 Sandel TAWS/RMI ST3400-001 or Install 1.60 ST3400-102

SERVICE BULLETIN Citation SUPPLEMENTAL DATA SB560-34-121

TITLE

NAVIGATION - SANDELST3400TAWSINSTALLATION

EFFECTIVITY

MODEL SERIAL NUMBERS

560 -0001 thru -0259

MANPOWER

WORK PHASE MAN-HOURS Modiﬁcation As Required

MATERIAL - Cost and Availability

PART NUMBER AVAILABILITY COST SB560-34-121-0 * * SB560-34-121-1 * * SB560-34-121-2 ** SB560-34-121-3 * * SB560-34-121-4 * * SB560-34-121-5 * *

* Please contact Citation Parts Distribution for current cost and availability of parts listed in this service bulletin. Phone at 1-800-835-4000 (Domestic) or 1-316-517-7542 (International). Send Email to: [email protected] or telefax at 1-316-517-7711.

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.

Dec 1/2004 560-34-121 Page 1 of 1