Revision 1 REVISION TRANSMITTAL SHEET This sheet transmits Revision 1 to. A. Removed the 4890307-2 Carpet from the -2 Kit and added the requirement to order it separately based on airplane color scheme. B. Removed the 4811983-37 Carpet from the -3 Kit and added the requirement to order it separately based on airplane color scheme. C. Added Steps 4B(1)(a) and 4B(2)(a) to give instructions for ordering the correct carpet. D. Updated the information listed in the CHANGE IN WEIGHT AND BALANCE section. 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. The original issue of this service bulletin was never released to the field. SUMMARY OF REVISIONS Original Issue Nov 11/2003 Revision 1 Jan 16/2004
TITLE NAVIGATION - MARK VIII TERRAIN AWARENESS & WARNING SYSTEM (TAWS) INSTALLATION EFFECTIVITY MODEL UNIT NUMBERS 550-0801 thru -1016 NOTE: This service bulletin may only be accomplished at a Cessna owned or authorized Citation Service Center. NOTE: SB550-34-71, Navigation - Honeywell Primus 1000 Phase II Software Upgrade, should be accomplished prior to or in conjunction with this service bulletin. The equivalent of this service bulletin has been incorporated on production airplanes -1017 and On. REASON To install the Mark VIII TAWS system. DESCRIPTION This service bulletin provides parts and instructions to install the Mark VIII TAWS system. 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. Revision 1 - Jan 16/2004 Page 1 of 25 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-6000, Fax 1-316-517-8500 COPYRIGHT 2003
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 * * -5 * * -6 * * -7 * * -8 * * -9 * * -10 * * -11 * * -12 * * -13 * * -14 * * * Refer to the attached Service Bulletin Supplemental Data sheet for man-hours, material cost and availability, and warranty information. Revision 1 - Jan 16/2004 Page 2
TOOLING NAME NUMBER MANUFACTURER USE Personal Computer Requires 386 or better processor, Windows and Winviews software Commercially Available To do a function test of the system. Pitot-Static Test Set VOR/Localizer Simulator Test Set Squat Switch Breakout Box Vertical Gyro Extender Cable 6520-10 or Equivalent Nav 401/402 or Equivalent Laversab Incorporated 10435 Greenbough Suite 300 Stafford, TX 77477 IFR Systems 10200 West York Wichita, KS 67277 6588006-1 Cessna Aircraft Company Citation Marketing Division 7121 Southwest Boulevard Wichita, KS 67215 CJMD834-006 Cessna Aircraft Company Citation Marketing Division 7121 Southwest Boulevard Wichita, KS 67215 Hydraulic Mule CJMD129-002 Cessna Aircraft Company Citation Marketing Division 7121 Southwest Boulevard Wichita, KS 67215 To do a function test of the system. To do a function test of the system. To do a function test of the system. To do a function test of the system. To do a function test of the system. Revision 1 - Jan 16/2004 Page 3
CHANGE IN WEIGHT AND BALANCE KIT WEIGHT INCREASE RESULTANT MOMENT/100 MOMENT -0 +0.96 Pounds +97.53 Inch-Pounds +0.98 Inch-Pounds -1 +9.01 Pounds +614.35 Inch-Pounds +6.14 Inch-Pounds -2 +10.69 Pounds +762.55 Inch-Pounds +7.63 Inch-Pounds -3 +9.33 Pounds +809.10 Inch-Pounds +8.09 Inch-Pounds -4 +0.02 Pounds +0.88 Inch-Pounds +0.01 Inch-Pounds -5 +0.08 Pounds +3.90 Inch-Pounds +0.04 Inch-Pounds -6 +0.30 Pounds +29.01 Inch-Pounds +0.29 Inch-Pounds -7 +0.02 Pounds +1.19 Inch-Pounds +0.01 Inch-Pounds -8 +0.19 Pounds +48.69 Inch-Pounds +0.49 Inch-Pounds -9 +0.20 Pounds +53.19 Inch-Pounds +0.53 Inch-Pounds -10 +0.02 Pounds +1.16 Inch-Pounds +0.01 Inch-Pounds -11 +0.19 Pounds +48.69 Inch-Pounds +0.49 Inch-Pounds -12 +0.21 Pounds +57.82 Inch-Pounds +0.58 Inch-Pounds -13 +0.00 Pounds +0.00 Inch-Pounds +0.00 Inch-Pounds -14 +0.01 Pounds +0.51 Inch-Pounds +0.01 Inch-Pounds Delta Carpet Weight for the +0.00 Pounds +0.00 Inch-Pounds +0.00 Inch-Pounds -2 Delta Carpet Weight for the -3-1.31 Pounds -98.97 Inch-Pounds -0.99 Inch-Pounds REFERENCES Cessna Model 550 Bravo Maintenance Manual Cessna Model 550 Bravo Illustrated Parts Catalog Cessna Model 550 Bravo Wiring Diagram Manual Cessna Model 550 Bravo Airplane Flight Manual Airplanes installing the Mark VIII TAWS system must order the following engineering drawings. The latest revision and all applicable drawing change notices for each document must be used. MAIN MARK VIII TAWS INSTALLATION ENGINEERING DRAWING LIST DOCUMENT NUMBER TITLE 9690457 TEST PORT INSTL-MOD (EGPWS) 9690454 FEED THRU PLATE FOR EGPWS 9690452 EGPWS ANNUN. PANEL ASSY MOD 550 BRAVO 9690455 EGPWS EL PNL AND CB PNL MOD 550 BRAVO 9616208 CABLE ASSY FMS INTERFACE TO MARK VIII EGPWS Revision 1 - Jan 16/2004 Page 4
9616219 CABLE ASSY TCAS INTERFACE TO MARK VIII EGPWS 9616222 MARK VIII EGPWS SYSTEM PROGRAMMING In addition to the drawings listed in the main engineering drawing list, airplanes installing the EGPWS computer at location A must order the following engineering drawings. The latest revision and all applicable drawing change notices for each document must be used. MARK VIII TAWS INSTALLATION FOR LOCATION A DOCUMENT NUMBER 9616050 EGPWS INSTL. RH MOD TITLE 9616205 CABLE ASSY MARK VIII EGPWS In addition to the drawings listed in the main engineering drawing list, airplanes installing the EGPWS computer at location B must order the following engineering drawings. The latest revision and all applicable drawing change notices for each document must be used. MARK VIII TAWS INSTALLATION FOR LOCATION B DOCUMENT NUMBER TITLE 4890307 NOSE BAGGAGE CARPET INSTALLATION (MOD) 9616058 EGPWS INSTL. RH MOD 9616206 CABLE ASSY MARK VIII EGPWS 9656057 NOSE BAGGAGE COMPARTMENT INSTL (EXTENDED RH) In addition to the drawings listed in the main engineering drawing list, airplanes installing the EGPWS computer at location C must order the following engineering drawings. The latest revision and all applicable drawing change notices for each document must be used. MARK VIII TAWS INSTALLATION FOR LOCATION C DOCUMENT NUMBER PUBLICATIONS AFFECTED TITLE 4811983 NOSE BAGGAGE CARPET INSTALLATION 9616064 EGPWS MARK VIII INSTL. RH MOD 9616207 CABLE ASSY MARK VIII EGPWS 9656060 NOSE BAGGAGE COMPARTMENT INSTALLATION Cessna Model 550 Bravo Maintenance Manual Cessna Model 550 Bravo Illustrated Parts Catalog Cessna Model 550 Bravo Wiring Diagram Manual Cessna Model 550 Bravo Airplane Flight Manual Revision 1 - Jan 16/2004 Page 5
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" written on them. 2. Remove any previously installed TAWS system from the airplane. (Refer to the applicable chapters in the Maintenance Manual and the Wiring Diagram Manual as necessary.) 3. (Refer to Figure 1, Detail A.) Choose a location to install the 965-1206-004 EGPWS Computer. NOTE: In addition to the -0 Kit, order the -1 Kit for airplanes that will have the 965-1206-004 EGPWS Computer installed at location option A. NOTE: In addition to the -0 Kit, order the -2 Kit for airplanes that will have the 965-1206-004 EGPWS Computer installed at location option B. NOTE: In addition to the -0 Kit, order the -3 Kit for airplanes that will have the 965-1206-004 EGPWS Computer installed at location option C. 4. Use the following Cessna engineering drawings to install the system on the airplane. A. Install the wiring in the airplane. (1) Install the Mark VIII EGPWS Cable Assembly to the airplane. (a) (For airplanes that will install the 965-1206-004 EGPWS Computer at location option A.) Install the 9616205-1 Mark VIII EGPWS Cable Assembly. (Refer to Cessna Engineering Drawing 9616205.) NOTE: In addition to the -0 Kit, order the -1 subkit. (b) (For airplanes that will install the 965-1206-004 EGPWS Computer at location option B.) Install the 9616206-1 Mark VIII EGPWS Cable Assembly. (Refer to Cessna Engineering Drawing 9616206.) NOTE: In addition to the -0 Kit, order the -2 subkit. (c) (For airplanes that will install the 965-1206-004 EGPWS Computer at location option C.) Install the 9616207-1 Mark VIII EGPWS Cable Assembly. (Refer to Cessna Engineering Drawing 9616207.) NOTE: In addition to the -0 Kit, order the -3 subkit. (2) Install the correct Flight Management System (FMS) interface cable assembly to the airplane. (a) (For airplanes that have the UNS-1K FMS installed.) Install the 9616208-1 UNS-1K FMS Interface Cable Assembly. (Refer to Cessna Engineering Drawing 9616208.) NOTE: In addition to the -0 Kit, order the -4 subkit. (b) (For airplanes that have the GNS-XLS FMS installed.) Install the 9616208-2 GNS-XLS FMS Interface Cable Assembly. (Refer to Cessna Engineering Drawing 9616208.) NOTE: In addition to the -0 Kit, order the -5 subkit. (c) (For airplanes that have the UNS-1CSP FMS installed.) Install the 9616208-3 UNS-1CSP FMS Interface Cable Assembly. (Refer to Cessna Engineering Drawing 9616208.) NOTE: In addition to the -0 Kit, order the -6 subkit. Revision 1 - Jan 16/2004 Page 6
(3) Install the correct Traffic Alert and Collision Avoidance System (TCAS) interface cable assembly to the airplane. (a) (For airplanes that have the TCAS I system installed in the nose of the airplane.) Install the 9616219-3 TCAS I Interface Cable Assembly. (Refer to Cessna Engineering Drawing 9616219.) NOTE: In addition to the -0 Kit, order the -7 subkit. (b) (For airplanes that have the TCAS I system installed in the right hand side of the tailcone.) Install the 9616219-1 TCAS I Interface Cable Assembly. (Refer to Cessna Engineering Drawing 9616219.) NOTE: In addition to the -0 Kit, order the -8 subkit. (c) (For airplanes that have the TCAS I system installed in the left hand side of the tailcone.) Install the 9616219-2 TCAS I Interface Cable Assembly. (Refer to Cessna Engineering Drawing 9616219.) NOTE: In addition to the -0 Kit, order the -9 subkit. (d) (For airplanes that have the TCAS II system installed in the nose of the airplane.) Install the 9616219-6 TCAS II Interface Cable Assembly. (Refer to Cessna Engineering Drawing 9616219.) NOTE: In addition to the -0 Kit, order the -10 subkit. (e) (For airplanes that have the TCAS II system installed in the right hand side of the tailcone.) Install the 9616219-4 TCAS II Interface Cable Assembly. (Refer to Cessna Engineering Drawing 9616219.) NOTE: In addition to the -0 Kit, order the -11 subkit. (f) (For airplanes that have the TCAS II system installed in the left hand side of the tailcone.) Install the 9616219-5 TCAS II Interface Cable Assembly. (Refer to Cessna Engineering Drawing 9616219.) NOTE: In addition to the -0 Kit, order the -12 subkit. (g) (For airplanes that have the SKY-497 Skywatch system installed on the airplane.) Install the 9616219-7 Skywatch SKY-497 Interface Cable Assembly. (Refer to Cessna Engineering Drawing 9616219.) NOTE: In addition to the -0 Kit, order the -13 subkit. (h) (For airplanes that have the SKY-899 Skywatch system installed on the airplane.) Install the 9616219-8 Skywatch SKY-899 Interface Cable Assembly. (Refer to Cessna Engineering Drawing 9616219.) NOTE: In addition to the -0 Kit, order the -14 subkit. B. Use the applicable subkit and Cessna Engineering Drawing to locate and install the 965-1206-004 EGPWS Computer. (Refer to Cessna Engineering Drawing 9616050-5, 9616058-1 or 9616064-1.) (1) The 9616058-1 EGPWS Installation also requires the 9656057-1 Closeout and the 4890307-2 Carpet. (a) Order the correct color carpet from Citation Parts Distribution, Telephone number 1-800-835-4000 (Domestic) or 316-517-7542 (International) or Telefax 316-517-7711. Refer to the MATERIAL INFORMATION section of this service bulletin for the proper part number of the carpet based on your airplanes color scheme. Revision 1 - Jan 16/2004 Page 7
(2) The 9616064-1 EGPWS Installation also requires the 9656060-15 Closeout and the 4811983-37 Carpet. (a) Order the correct color carpet from Citation Parts Distribution, Telephone number 1-800-835-4000 (Domestic) or 316-517-7542 (International) or Telefax 316-517-7711. Refer to the MATERIAL INFORMATION section of this service bulletin for the proper part number of the carpet based on your airplanes color scheme. C. Use the applicable Cessna Engineering Drawing to locate and install the Test Port. (Refer to Cessna Engineering Drawing 9690457.) D. Install the 9690454-2 Feed Thru Plate Assembly on the airplane. (Refer to Cessna Engineering Drawing 9690454.) E. Install the annunciators to the instrument panel at the location of your choice. (Refer to Cessna Engineering Drawing 9690452.) (1) Cessna Engineering Drawing 9690452 gives three location recommendations to install the annunciators. F. Install the circuit breakers to the circuit breaker panel as shown. (Refer to Cessna Engineering Drawing 9690455.) G. Set the EGPWS configuration module to the settings shown. (Refer to Cessna Engineering Drawing 9616222.) 5. Remove maintenance warning tags and connect external electrical power to the airplane. 6. Do a functional test of the Mark VIII TAWS system. A. Make sure that all of the appropriate circuit breakers are engaged. B. Turn on the avionics power. C. Connect the personal computer (PC) to the GPWS RS-232 port and open Winviews software. D. Load the appropriate configuration file under the File pull down menu. E. Use F6 to select the display mode. F. Make sure that the FMS has been initialized before testing the Mark VIII EGPWS system. G. Do a power on check. (1) Make sure that the green COMPUTER OK light on the face of the EGPWS is on when the EGPWS computer is booted up. The amber EXTERNAL FAIL and red COMPUTER FAIL light should NOT come on. H. Do the cockpit audio check. (1) The Mark VIII EGPWS audio announcements can be activated by pressing the test switch. (2) Do not hold the switch for more than two seconds. NOTE: Not all of the announcements will be activated, and the test volume is 6dB lower than the normal operation volume. Speaker Annunciations PASS FAIL I. Do the cockpit annunciators check. (1) Set the rotary test switch to the annunciator test position. (2) Make sure that the following annunciators light up: Revision 1 - Jan 16/2004 Page 8
TERR NORM / TERR INHIB GPWS FLAP NORM / GPWS FLAP OVRD ANNUNCIATOR PASS FAIL (3) The EGPWS TEST and GPWS G/S portion of the GPWS G/S / CANCELLED annunciators are visible white and will only be on when the Day/Night switch is in the Night position. J. Do a Level 1 Self Test. (1) Start the GPWS Level 1 Test sequence. (2) Press the EGPWS TEST annunciator, holding for not more than two seconds. Make sure the following happens: (a) The GPWS INOP, TERR INOP, and TERR NOT AVAIL annunciators stay on throughout the test. (b) The GPWS G/S / CANCELLED light comes on, and you can hear the Glideslope aural warning. (c) The PULL UP annunciator on the PFD comes on, and you can hear the Pull up aural warning. (d) The GPWS FAIL, TERR NOT AVAIL, PULL UP annunciators/lights turn off after the test. Level 1 Self Test PASS FAIL K. Do a Level 2 Self Test. (1) Start the GPWS Level 1 Test sequence as above. (2) Once the self test audio starts, press the EGPWS TEST switch again for not more than two seconds. This will begin the Level 2 Test sequence. (3) Make sure that the following aural messages are annunciated: (a) Current faults. (b) If the airplane is in a location which allows the GPS receiver to receive enough satellites to become valid, the following messages will also be annunciated: 1 Terrain awareness - no valid latitude. 2 Terrain awareness - no valid longitude. 3 Terrain awareness clearance floor - position error. 4 Press to continue. Level 2 Self Test PASS FAIL L. Do a Level 3 Self Test. (1) Start the GPWS Level 1 Test sequence as above. (2) Once the self test audio starts, press the EGPWS TEST switch again for not more than two seconds. This will begin the Level 2 Test sequence. (3) Immediately after the Level 2 Self Test callout Press to continue message is annunciated, push the EGPWS TEST switch. (4) Make sure that the following aural messages are annunciated: Revision 1 - Jan 16/2004 Page 9
SYSTEM CONFIGURATION CHECKS EXPECTED VALUES ACTUAL VALUES PART NUMBER 965-1206-004 * MOD STATUS ONE * SERIAL NUMBER APPLICATIONS SOFTWARE VERSION ZERO ZERO FOUR TERRAIN DATABASE VERSION FOUR TWO NINE **** ENVELOPE MOD DATABASE VERSION B ZERO FOUR **** BOOT CODE VERSION B ONE ZERO ONE POINT THREE * AIRCRAFT TYPE TWO FIVE FIVE ** AIR DATA TYPE FIVE RADIO ALTITUDE TYPE ONE *** NAVIGATION INPUT TYPE ATTITUDE INPUT TYPE MAGNETIC HEADING TYPE POSITION INPUT TYPE CALLOUTS OPTION AUDIO MENU VOLUME SELECT TERRAIN DISPLAY TYPE I/O DESCRETE TYPE WINDSHEAR INPUT FLAP WOW REVERSAL SELECTED BANK ANGLE SELECTED SMART CALLOUTS SELECTED OBSTACLE AWARENESS ENABLED PEAKS MODE ENABLED MODE 6 LOW VOLUME SELECTED GPS ALTITUDE PREFERENCE WGS 84 SELECTED *subject to change by vendor **numerical callout for Bravo ***numeric callouts for ALT55 (ZERO=AA300) ****EXAMPLE- SUBJECT TO REGIONAL AREA *****OPTION DEPENDENT NO CALLOUT WITH 1L, 1ESP, GNSXLS. FOUR TWO ZERO ONE (iii) THREE (ii) ZERO ZERO TWO FOUR EIGHT ONE ZERO (i) ***** Revision 1 - Jan 16/2004 Page 10
(i) no audio callout (not selected) (ii) CUSTOMER DEPENDENT (THREE NORMALLY LOADED AT CESSNA) (iii) ONE = 1K AND CSP. ZERO = 1L, 1ESP, GNSXLS (5) The Level 3 test will continue, and the configuration of the airplane will be annunciated. Make sure that the following message is annunciated when the test is complete: (a) Press to continue. M. Do a Level 6 Self Test. (1) Immediately after the Level 3 Self Test callout Press to continue message is annunciated, push the EGPWS TEST switch. (2) Immediately after the Level 4 Self Test callout Press to continue message is annunciated, push the EGPWS TEST switch. (3) Immediately after the Level 5 Self Test callout Press to continue message is annunciated, push the EGPWS TEST switch. (a) The Discrete input test will be annunciated. (4) Do a radio altimeter validity test. (a) Disengage the RAD ALT circuit breaker. (b) The annunciation Radio altimeter one invalid should be heard through the audio system. CALLOUT PASS FAIL Radio Altimeter 1 Invalid (c) (d) Engage the RAD ALT circuit breaker. The annunciation Radio altimeter one valid should be heard through the audio system. CALLOUT PASS FAIL Radio Altimeter 1 Valid (5) Do a glideslope inhibit discrete input test. (a) Press the glideslope inhibit button. (b) The annunciation Glideslope inhibit should be heard through the audio system. Glideslope Inhibit (c) (d) CALLOUT PASS FAIL Press the glideslope inhibit button. The annunciation Glideslope not inhibit should be heard through the audio system. CALLOUT PASS FAIL Glideslope Not Inhibit (6) Do a terrain inhibit discrete input test. (a) Press the terrain inhibit button. Revision 1 - Jan 16/2004 Page 11
(b) The annunciation Terrain off should be heard through the audio system. Terrain Off CALLOUT PASS FAIL (c) (d) Press the terrain inhibit button. The annunciation Terrain on should be heard through the audio system. Terrain On CALLOUT PASS FAIL (7) Do a landing flaps discrete input test. (a) (b) Extend the flaps to the fully extended position. Once the flaps are fully extended the annunciation Landing flaps should be heard through the audio system. Landing Flaps CALLOUT PASS FAIL (c) (d) Put the flap control in the fully retract position. Once the flaps are fully retracted the annunciation Not landing flaps should be heard through the audio system. Not Landing Flaps CALLOUT PASS FAIL (8) Do a TCAS inhibit discrete output test. (a) (b) (c) Start the TCAS self test. Wait several seconds, then activate the GPWS test. Make sure that the TCAS system aural message is inhibited by the GPWS. TCAS Aural Warning Inhibit PASS FAIL (9) When finished with the Level 6 Discrete Input test, press the EGPWS TEST button to the self test. N. Do signal input tests. (1) Do a radio altitude test. (a) (b) Make sure that the NAV radio which is connected to the EFIS under test is not turned to a valid ILS frequency. Take note of the altitude with the airplane on the ground. Revision 1 - Jan 16/2004 Page 12
(c) Press the TEST button on the DC-550 PFD display controller and take note of the altitude. Honeywell AA300 Radio Altimeter EFIS TEST TEST VALUE EXPECTED VALUE PASS FAIL TEST Not Active AC on ground -15 to +3 feet TEST Active 100 feet 100 feet Collins ALT-55 Radio Altimeter EFIS TEST TEST VALUE EXPECTED VALUE PASS FAIL TEST Not Active AC on ground -15 to +3 feet. TEST Active 50 feet 50 feet (2) Do a test of the air data computer. (a) (b) Connect the air data test set to the airplane and set the altitude to 2000 feet and the airspeed to 100 knots. Set the pilot s altimeter to a pressure setting of 29.92 and monitor the following parameters: SIGNAL CVT ITEM TEST VALUE EXPECTED VALUE Uncorrected Baro Altitude Computed Airspeed RawBAlt1 2000 feet 2000 ft. +/- 300 RawCAS1 100 knots 100 +/- 10 knots Baro Alt Rate RawBaroRt1 0 fmp 0 +/- fmp Outside air temperature RawSAT1 OAT (C) OAT (C) +/- 5 PASS FAIL (c) Increase the pressure setting on the pilot s altimeter so that indicated altitude increases by 500 feet and monitor the following parameters: NOTE: Make sure that the adjustment did not alter the Uncorrected Baro altitude. SIGNAL CVT ITEM TEST VALUE EXPECTED VALUE Corrected Baro Altitude Uncorrected Baro Altitude RawBCAlt1 2500 feet 2000 feet +/- 300 RawBAlt1 2000 feet 2000 feet +/- 300 PASS FAIL (d) Bring the airplane back down to the ground on the air data test set and disconnect. (3) Do a test of the glideslope. (a) Tune the pilot s NAV control unit to a valid ILS frequency (108.10MHz) then deselect it and monitor the valid ILS parameters. Revision 1 - Jan 16/2004 Page 13
(b) Switch from display mode to command prompt in Winviews by pressing F6 and type ps for present status. Make sure that when ps is typed with a valid ILS frequency tuned, no faults are displayed. SIGNAL CVT ITEM TEST VALUE EXPECTED VALUE ILS Select ILSTuned1 Valid (tuned) 1 PASS FAIL (c) (d) Deselect the ILS frequency. Make sure that when the NAV radio is not tuned to a valid ILS frequency, the CVT item becomes valid. SIGNAL CVT ITEM TEST VALUE EXPECTED VALUE ILS Deselect ILSTuned1 Invalid (not tuned) 0 PASS FAIL (e) Using the VOR/Localizer test set, simulate a glideslope signal and make sure that the valid and deviation parameters are as follows: SIGNAL CVT ITEM TEST VALUE EXPECTED VALUE Glideslope Valid AGS1Val Valid (ILS tuned and GS valid) Glideslope Valid AGS1Val Invalid (ILS not tuned and GS not valid) Glideslope RawAACGS1 1 dot fly down +1 +/-.3 DOT Glideslope RawAACGS1 2 dots fly up -2 +/-.3 DOT 1 0 PASS FAIL (f) Check the Glideslope/Cancel discrete by changing status of the annunciator, and verify the following parameters: SIGNAL CVT ITEM TEST VALUE EXPECTED VALUE G/S Cancel GSCan Press and hold GS cancel switch G/S Cancel GSCan Release GS cancel switch 1 0 PASS FAIL (4) Do a test of the landing gear. (a) Using the squat switch/gear position simulators, switch gear from down to up and make sure: SIGNAL CVT ITEM TEST VALUE EXPECTED VALUE Landing Gear LandGrDsc Gear down 1 Landing Gear LandGrDsc Gear up 0 PASS FAIL Revision 1 - Jan 16/2004 Page 14
(5) Do a flap position test. (a) (b) Make sure that the flap override switch is in the normal (Override off) position while performing this test. Make sure to take all necessary precautions in moving flaps on the airplane and verify the following parameters for each of the given detents: SIGNAL CVT ITEM TEST VALUE EXPECTED VALUE 0 Flaps LandFlDsc 0 +/- 2 0 0 Flaps LandFlFAng 0 +/- 2 0 +/- 2 35 Flaps LandFlDsc 35 +/- 5 1 35 Flaps LandFIFAng 35 +/- 5 35 +/- 5 PASS FAIL (c) Put the flaps back in the normal position. (6) Do a terrain inhibit test. (a) The terrain inhibit function is checked by changing the status of the terrain inhibit switch. Make sure that the status of the switch changes per the following table: SIGNAL CVT ITEM TEST VALUE EXPECTED VALUE Terrain Inhibit TerrDis Select Terrain Inhibit Terrain Inhibit TerrDis De-Select Terrain Inhibit 1 0 PASS FAIL (7) Do an altitude (pitch and roll) test. (a) (b) (c) (d) (e) Disengage the VG2 circuit breaker. Look for the pitch/roll valid signal. Engage the VG2 circuit breaker. Look for the altitude valid signal. The wiring of the altitude system to the EGPWS can be verified by installing the AHRS/gyro(s) on a tilt table, then inputting altitude changes while observing that the EGPWS sees the changes. Verify the attitude input to the EGPWS per the following table: SIGNAL CVT ITEM TEST VALUE EXPECTED VALUE Pitch Angle RawPitch 1 0 0 +/- 1 Pitch Angle RawPitch 1 +10 10 +/- 1 Roll Angle RawRoll 1 0 0 +/- 1 Roll Angle RawRoll 1 +15 15 +/- 1 Roll Angle RawRoll 1-20 20 +/- 1 PASS FAIL Revision 1 - Jan 16/2004 Page 15
(8) Do a position source test. NOTE: Verifying the following data checks the FMS/GPS input to the Mark VIII EGPWS. Position inputs are provided in the form of W x y.z or N x y.z. The Mark VIII EGPWS stores position as +/- x.xxx. For reference, in the Mark VIII EGPWS CVT item, West and South = - and North and East = +. To convert the x y.z to x.xxx, divide the y.z by 60 and add it to the leading x. For example, W 119 36.6 is equivalent to the Mark VIII EGPWS value -119.610 (36.66/60 + 119). (a) Verify the FMS position per the following table: SIGNAL CVT ITEM TEST VALUE EXPECTED VALUE Latitude GPSLatitude1 Present position Longitude GPSLngude1 Present position Magnetic Heading RawAACMHd Present Heading (+/- from Zero North) Altitude RawGAlt1 Present altitude feet PP +/- 0.008 PP +/- 0.008 PH +/- 1 PH +/- 500 feet PASS FAIL 7. Remove external electrical power and connect the airplane battery. 8. Make sure that the Airplane Flight Manual Supplement 37, or any revisions are put in the airplane flight manual. NOTE: Look at the configuration codes listed in the applicable supplement and in Section 1 of the FAA Approved Flight Manual to make sure that all changed crew procedures or limitations are complied with. 9. 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. 10. 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 67277. MATERIAL INFORMATION NOTE: The parts included in this service bulletin cover installation for one airplane. -0 1 Kit, consisting of the following parts: D9/370000V30 8 Lock MS21042-04 8 Nut Revision 1 - Jan 16/2004 Page 16
MS35206-215 8 Screw M7928/1-22 1 Terminal M81044/12-20-9 40 Inches Wire (Marked EEJF909-2448) S2899L1.0 1 Circuit Breaker S2899L5.0 1 Circuit Breaker 6565136-48 1 Angle 9112004-1 4 Bus Terminator 9690454-2 1 Feed Thru Plate Assembly 1 Instructions NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes that will install the EGPWS computer at location option A. -1 1 Kit, consisting of the following parts: MS35206-228 4 Screw S1741-1 1 Anchor 9256010-1 2 Stud Assembly 9616050-6 1 Bracket Assembly 9616050-8 1 Silkscreen 9616205-1 1 Mark VIII EGPWS Cable Assembly 965-1206-004 1 EGPWS Computer NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes that will install the EGPWS computer at location option B. -2 1 Kit, consisting of the following parts: MS35206-231 4 Screw MS35206-243 8 Screw 9256010-1 2 Stud Assembly 9616038-2 1 Adapter Assembly 9616038-3 1 Adapter Assembly Revision 1 - Jan 16/2004 Page 17
9616206-1 1 Mark VIII EGPWS Cable Assembly 9656057-1 1 Closeout 965-1206-004 1 EGPWS Computer NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes that will install the EGPWS computer at location option C. -3 1 Kit, consisting of the following parts: MS21059-08 2 Nutplate MS21059-3 4 Nutplate MS24694-S5 4 Screw MS35206-245 2 Screw MS35206-263 4 Screw S1741-1 2 Anchor 9256010-1 1 Stud Assembly 9616064-2 2 Zee Assembly 9616064-4 1 Silkscreen 9616207-1 1 Mark VIII EGPWS Cable Assembly 9656060-15 1 Closeout 965-1206-004 1 EGPWS Computer NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes with the UNS-1K Flight Management System installed. -4 1 Kit, consisting of the following parts: 9616208-1 1 UNS-1K FMS Interface Cable Assembly NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes with the GNS-XLS Flight Management System installed. Revision 1 - Jan 16/2004 Page 18
-5 1 Kit, consisting of the following parts: 9616208-2 1 GNS-XLS FMS Interface Cable Assembly NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes with the UNS-1CSP Flight Management System installed. -6 1 Kit, consisting of the following parts: 9616208-3 1 UNS-1CSP FMS Interface Cable Assembly NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes with the TCAS I system installed in the nose of the airplane. -7 1 Kit, consisting of the following parts: 9616219-3 1 TCAS I Interface Cable Assembly NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes with the TCAS I system installed in the right hand side of the tailcone. -8 1 Kit, consisting of the following parts: 9616219-1 1 TCAS I Interface Cable Assembly NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes with the TCAS I system installed in the left hand side of the tailcone. Revision 1 - Jan 16/2004 Page 19
-9 1 Kit, consisting of the following parts: 9616219-2 1 TCAS I Interface Cable Assembly NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes with the TCAS II system installed in the nose of the airplane. -10 1 Kit, consisting of the following parts: 9616219-6 1 TCAS II Interface Cable Assembly NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes with the TCAS II system installed in the right hand side of the tailcone. -11 1 Kit, consisting of the following parts: 9616219-4 1 TCAS II Interface Cable Assembly NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes with the TCAS II system installed in the left hand side of the tailcone. -12 1 Kit, consisting of the following parts: 9616219-5 1 TCAS II Interface Cable Assembly NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes with the SKY-497 Skywatch System installed. Revision 1 - Jan 16/2004 Page 20
-13 1 Kit, consisting of the following parts: 9616219-7 1 Skywatch SKY-497 Interface Cable Assembly NOTE: In addition to -0 Kit, the following will be required to accomplish this service bulletin on airplanes with the SKY-899 Skywatch System installed. -14 1 Kit, consisting of the following parts: 9616219-8 1 Skywatch SKY-899 Interface Cable Assembly In addition to the -2 Kit, one of the following items must be ordered separately from Citation Parts Distribution. Please contact Citation Parts Distribution, telephone number 1-800-835-4000 (Domestic) or 1-316-517-7542 (International) or telefax 1-316-517-7711. Provide the airplane serial number when ordering so that the correct color scheme is ordered. 4890307-2-1 1 Carpet (Medium Grey) 4890307-2-2 1 Carpet (Charcoal) KEY WORD OLD P/N INSTRUC- TIONS/ DIS- POSITION APPLICABLE UNIT NUMBERS -0809, -0815, -0827, -0831, -0833, -0834, -0836, -0837, -0840, -0843, -0850, -0852, -0853, -0854, -0856, -0858, -0859, -0862, -0864, -0871, -0872, -0883, -0885, -0886, -0893, -0898, -0905, -0908, -0910, -0911, -0916, -0917, -0919, -0930, -0947, -0955, -0957, -0985, -0998, -1000, -1011-0807, -0812, -0899, -0901, -0904, -0915, -0920, -0923, -0935, -0949, -0965, -0968, -0982, -0988, -0989, -1002, -1005, -1007, -1009, -1013 Revision 1 - Jan 16/2004 Page 21
KEY WORD OLD P/N INSTRUC- TIONS/ DIS- POSITION APPLICABLE UNIT NUMBERS 4890307-2-3 1 Carpet (Sand) -0801, -0802, -0803, -0804, -0805, -0806, -0808, -0810, -0811, -0813, -0814, -0816, -0817, -0818, -0819, -0820, -0821, -0822, -0823, -0824, -0825, -0826, -0828, -0829, -0830, -0832, -0835, -0838, -0839, -0841, -0842, -0844, -0845, -0846, -0847, -0848, -0849, -0851, -0855, -0857, -0860, -0861, -0863, -0865, -0866, -0867, -0868, -0869, -0870, -0873, -0874, -0875, -0876, -0877, -0878, -0879, -0880, -0881, -0882, -0884, -0887, -0888, -0889, -0890, -0891, -0892, -0894, -0895, -0896, -0897, -0900, -0902, -0903, -0906, -0907, -0909, -0912, -0913, -0914, -0918, -0921, -0922, -0924, -0925, -0926, -0927, -0928, -0929, -0931, -0932, -0933, -0934, -0936, -0937, -0938, -0939, -0940, -0941, -0942, -0943, -0944, -0945, -0946, -0948, -0950, -0951, -0952, -0953, -0954, -0956, -0958, -0959, -0960, -0961, -0962, -0963, -0964, -0966, -0967, -0969, -0970, -0971, -0972, -0973, -0974, -0975, -0976, -0977, -0978, -0979, -0980, -0981, -0983, -0984, -0986, -0987, -0990, -0991, -0992, -0993, -0994, -0995, -0996, -0997, -0999, -1001, -1003, -1004, -1006, -1008, -1010, -1012, -1014, -1015, -1016 Revision 1 - Jan 16/2004 Page 22
In addition to the -3 Kit, one of the following items must be ordered separately from Citation Parts Distribution. Please contact Citation Parts Distribution, telephone number 1-800-835-4000 (Domestic) or 1-316-517-7542 (International) or telefax 1-316-517-7711. Provide the airplane serial number when ordering so that the correct color scheme is ordered. 4811983-37-1 1 Carpet (Medium Grey) 4811983-37-2 1 Carpet (Charcoal) KEY WORD OLD P/N INSTRUC- TIONS/ DIS- POSITION APPLICABLE UNIT NUMBERS -0809, -0815, -0827, -0831, -0833, -0834, -0836, -0837, -0840, -0843, -0850, -0852, -0853, -0854, -0856, -0858, -0859, -0862, -0864, -0871, -0872, -0883, -0885, -0886, -0893, -0898, -0905, -0908, -0910, -0911, -0916, -0917, -0919, -0930, -0947, -0955, -0957, -0985, -0998, -1000, -1011-0807, -0812, -0899, -0901, -0904, -0915, -0920, -0923, -0935, -0949, -0965, -0968, -0982, -0988, -0989, -1002, -1005, -1007, -1009, -1013 Revision 1 - Jan 16/2004 Page 23
KEY WORD OLD P/N INSTRUC- TIONS/ DIS- POSITION APPLICABLE UNIT NUMBERS 4811983-37-3 1 Carpet (Sand) -0801, -0802, -0803, -0804, -0805, -0806, -0808, -0810, -0811, -0813, -0814, -0816, -0817, -0818, -0819, -0820, -0821, -0822, -0823, -0824, -0825, -0826, -0828, -0829, -0830, -0832, -0835, -0838, -0839, -0841, -0842, -0844, -0845, -0846, -0847, -0848, -0849, -0851, -0855, -0857, -0860, -0861, -0863, -0865, -0866, -0867, -0868, -0869, -0870, -0873, -0874, -0875, -0876, -0877, -0878, -0879, -0880, -0881, -0882, -0884, -0887, -0888, -0889, -0890, -0891, -0892, -0894, -0895, -0896, -0897, -0900, -0902, -0903, -0906, -0907, -0909, -0912, -0913, -0914, -0918, -0921, -0922, -0924, -0925, -0926, -0927, -0928, -0929, -0931, -0932, -0933, -0934, -0936, -0937, -0938, -0939, -0940, -0941, -0942, -0943, -0944, -0945, -0946, -0948, -0950, -0951, -0952, -0953, -0954, -0956, -0958, -0959, -0960, -0961, -0962, -0963, -0964, -0966, -0967, -0969, -0970, -0971, -0972, -0973, -0974, -0975, -0976, -0977, -0978, -0979, -0980, -0981, -0983, -0984, -0986, -0987, -0990, -0991, -0992, -0993, -0994, -0995, -0996, -0997, -0999, -1001, -1003, -1004, -1006, -1008, -1010, -1012, -1014, -1015, -1016 Revision 1 - Jan 16/2004 Page 24
Figure 1. Location Options for the EGPWS Computer (Sheet 1) Revision 1 - Jan 16/2004 Page 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 the Airplane Flight Manual for a complete list of operational changes to the airplane as a result of accomplishing this service bulletin.
TITLE SUPPLEMENTAL DATA NAVIGATION - MARK VIII TERRAIN AWARENESS & WARNING SYSTEM (TAWS) INSTALLATION EFFECTIVITY MODEL UNIT NUMBERS 550-0801 thru -1016 NOTE: This service bulletin may only be accomplished at a Cessna owned or authorized Citation Service Center. NOTE: SB550-34-71, Navigation - Honeywell Primus 1000 Phase II Software Upgrade, should be accomplished prior to or in conjunction with this service bulletin. The equivalent of this service bulletin has been incorporated on production airplanes -1017 and On. MANPOWER WORK PHASE Modification MAN-HOURS As Required Page 1 of 2 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-6000, Fax 1-316-517-8500 COPYRIGHT 2003
SUPPLEMENTAL DATA MATERIAL - Cost and Availability PART NUMBER AVAILABILITY COST -0 * * -1 * * -2 * * -3 * * -4 * * -5 * * -6 * * -7 * * -8 * * -9 * * -10 * * -11 * * -12 * * -13 * * -14 * * * 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: citationparts@cessna.textron.com 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. Page 2