SERVICE BULLETIN REVISION

Transcription

1 Revision 2 REVISION TRANSMITTAL SHEET This sheet transmits Revision 2 to. A. Revised Figure 2, View B-B to show the dimensions to locate the cutout for the Mark V EGPWS test switch. B. Removed the note that states that this service bulletin is not applicable to airplanes that are equipped with Mark V EGPWS. C. Added instructions for airplanes thru equipped with Mark V EGPWS to do a modification of the TAWS system D. Added a functional test for airplanes thru that are equipped with Mark V EGPWS. E. Added the requirement to Step 5 that airplanes equipped with Mark V or Mark VIII EGPWS must install the correct Airplane Flight Manual Supplement into the airplane flight manual. NOTE: This revision replaces the original issue and previous revisions of in their 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 OPTIONAL. Airplanes that are equipped with Mark V or Mark VIII EGPWS should do the applicable Steps 1 through 4 of this bulletin before installing steep approach. SUMMARY OF REVISIONS Original Issue Aug 5/2003 Revision 1 Feb 10/2004 Revision 2 Mar 18/2005

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3 Revision 1 REVISION TRANSMITTAL SHEET This sheet transmits Revision 1 to. A. Added a note to the SERIAL EFFECTIVITY that states that this service bulletin is not applicable to airplanes that are equipped with Mark V TAWS and will be applicable only when Mark V EGPWS is certified. B. Added Step 1 to upgrade the EGPWS computer for airplanes thru that are equipped with Mark VIII EGPWS. C. Added Step 2 to do a functional test for airplanes thru that are equipped with Mark VIII EGPWS. D. Added Step 3 to make sure that the correct flight manual supplement is put in the airplane flight manual for Mark VIII EGPWS. E. Added the -2 subkit to the MATERIAL INFORMATION list for airplanes thru that are equipped with Mark VIII EGPWS. 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 OPTIONAL. Airplanes that are equipped with Mark VIII EGPWS should do Steps 1, 2 and 3 of this bulletin before installing steep approach. SUMMARY OF REVISIONS Original Issue Aug 5/2003 Revision 1 Feb 10/2004

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5 TITLE FLIGHT CONTROLS - STEEP APPROACH CERTIFICATION - SPEED BRAKE SWITCH ADJUSTMENT EFFECTIVITY MODEL SERIAL NUMBERS and On REASON To allow speed brake deployment at a higher engine power setting to be in conformity with steep approach certification. DESCRIPTION This service bulletin provides parts and instructions to adjust the 85% N2 position switch, located at the power lever control quadrant, to 90% N2. COMPLIANCE OPTIONAL. This service bulletin may be performed at the discretion of the owner. NOTE: Airplanes that are equipped with Mark VIII EGPWS must upgrade the existing EGPWS computer to a EGPWS Computer configuration. NOTE: It is permissible to load the software necessary to upgrade the EGPWS computer on site with the assistance of a Honeywell Field Service Representative. 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 No Change. Revision 2 - Mar 18/2005 Page 1 of 24 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A , Fax COPYRIGHT 2003

6 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 -0 * 14,900 USD -1 * 14,900 USD -2 * * -3 * * NOTE: Owner/Operators must order the applicable airplane flight manual supplement listed in the Material Information List to complete incorporation of the steep approach certification. Please contact Citation Publications at for current availability of the documents listed in this service bulletin. * Refer to the attached Service Bulletin Supplemental Data sheet for man-hours, material cost and availability, and warranty information. TOOLING NAME NUMBER MANUFACTURER USE Laptop Personal Computer RS232 Diagnostic Connector Commercially available Commercially available To do the functional test of the MKVEGPWSinstallation. To connect the personal computer to the GPWS RS-232 port connection. CHANGE IN WEIGHT AND BALANCE Negligible REFERENCES Cessna Model 525 Maintenance Manual Cessna Model 525 UK Approved Airplane Flight Manual Serial and On Cessna Model 525 CJ1 FAA Approved Airplane Flight Manual Serial and On Cessna Engineering Drawing (attached) Revision 2 - Mar 18/2005 Page 2

7 PUBLICATIONS AFFECTED Cessna Model 525 Maintenance Manual Cessna Model 525 UK Approved Airplane Flight Manual Serial and On Cessna Model 525 CJ1 FAA Approved Airplane Flight Manual Serial and On ACCOMPLISHMENT INSTRUCTIONS NOTE: Airplanes that are equipped with Mark V or Mark VIII EGPWS should do the applicable Steps 1 through 5 of this bulletin before installing steep approach. 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 thru equipped with Mark V EGPWS) Do a modification of the TAWS system. A. Do a modification of the pilot's instrument panel. (1) Remove the pilot's instrument panel. (Refer to the Maintenance Manual, Chapter 31, Instrument Panels - Maintenance Practices Airplanes and On.) (2) (Refer to Figure 2, View B-B.) Make one S Cutout in the left instrument panel. (3) Deburr the edges of the cutout. (4) Remove the GPWS test switchlight and install it in the new S Cutout. (5) (Refer to Figure 2, View B-B.) Install the GPWS STP APR ACTIVE switchlight in the location where the GPWS test switchlight was removed with one each S Cap, LED Switch Body and Connector. B. (Refer to Figure 2, Sheet 3.) Do a modification of the wiring as shown. C. Install the pilot's instrument panel. (Refer to the Maintenance Manual, Chapter 31, Instrument Panels - Maintenance Practices.) 3. (Airplanes thru that are equipped with Mark V EGPWS) Do a functional test of the Mark VEGPWSinstallation. A. Prepare for the functional test. (1) Connect a ground power unit to the external jack and turn on the ground power unit (adjusted to VDC, or VDC). (2) Engage both avionics and electrical circuit breakers as necessary and set all necessary avionics power switches to ON. (3) Set the BATTERY switch to BATT, the BATT DISC switch to NORM and the AVIONICS MASTER POWER switch to OFF. (4) Make sure that all applicable circuit breakers are engaged. (5) Set the AVIONICS POWER switch to ON. Revision 2 - Mar 18/2005 Page 3

8 B. Do the functional test. (1) Doapowerontest. (a) Make sure that the COMPUTER OK lamp on the face of the EGPWS comes on when the EGPWS computer is booted up. NOTE: TheamberEXTERNALFAULTandtheredCOMPUTERFAILlampshouldnot be ON. (2) Do a Self Test Level 3 Test. (a) Press and hold the GPWS TEST annunciator for not more than two seconds. 1 The Level 1 self test will begin. 2 Once the self test starts it will state current faults. (b) Press and hold the GPWS TEST annunciator for not more than two seconds. 1 The Level 2 self test will begin 2 Once the Level 2 self test audio starts, an aural declaration states "COMPUTER OKAY, PRESS TO CONTINUE". (c) Press and hold the GPWS TEST switch again for not more than two seconds. 1 The Level 3 self test will begin NOTE: The Level 3 EGPWS configuration indicates the current configuration by listing the EGPWS hardware, software, databases and program pin inputs detected by the EGPWS. (d) After "SYSTEM CONFIGURATION" has finished, the Level 3 test will continue with the strapping configuration of the airplane. 1 Listen for the annunciation STEEP APPROACH ENABLED. 2 Let the test finish and do not press the EGPWS TEST again when it states PRESS TO CONTINUE. (e) After the test has timed out, re-test, re-test the Level 3 EGPWS TEST with the STP APR switch activated. C. Go to Step 5. 1 The self test annunciator should say "SELF TEST INHIBITED, STEEP APPROACH ACTIVATED, if correctly strapped. NOTE: EGPWS self test is inhibited in ground and air mode, if the steep approach switch is activated. 4. (Airplanes thru equipped with Mark VIII EGPWS) Update the TAWS System. A. (Refer to Figure 2, View A-A.) Remove the existing EGPWS Computer. (Refer to the Maintenance Manual, Chapter 34, AlliedSignal Enhanced Ground Proximity Warning System (EGPWS) - Removal/Installation.) Revision 2 - Mar 18/2005 Page 4

9 B. Send the removed EGPWS computer to Citation Parts Distribution, 7121 Southwest Boulevard, Wichita, Kansas 67215, for upgrade to a EGPWS Computer configuration. NOTE: It is permissible to load the software necessary to upgrade the EGPWS computer on site with the assistance of a Honeywell Field Service Representative. NOTE: International Owner/Operators: The existing EGPWS computer may be returned to Cessna Aircraft Company, Citation Parts Distribution, 7121 Southwest Boulevard, Wichita, KS 67215, USA, and exchanged for upgraded units. Due to the limited availability, please expedite the return of the removed part. NOTE: Domestic Owner/Operators: The existing EGPWS computer is to be returned to Cessna Aircraft Company, Citation Parts Distribution, 7121 Southwest Boulevard, Wichita, KS 67215, USA, upgraded to the current modification level and returned to the owner/operator for installation. This option will require advance scheduling with Citation Parts Distribution, telephone number (Domestic) or (International) or telefax and an estimated turnaround time of approximately seven to ten days. C. Install one EGPWS Computer. (Refer to the Maintenance Manual, Chapter 34, AlliedSignal Enhanced Proximity Warning System (EGPWS) - Removal/Installation.) D. Modify the pilot's instrument panel. (1) Remove the pilot's instrument panel. (Refer to the Maintenance Manual, Chapter 31, Instrument Panels - Maintenance Practices Airplanes and On.) (2) (Refer to Figure 2, View B-B.) Make one S Cutout in the left instrument panel. (3) Deburr the edges of the cutout. (4) Remove the GPWS test switchlight and install it in the new S Cutout. (5) (Refer to Figure 2, View B-B.) Install the GPWS STP APR ACTIVE switchlight in the location where the GPWS test switchlight was removed with one each S Cap, LED Switch Body and Connector. E. (Refer to Figure 2, Sheet 4.) Modify the wiring as shown. F. Install the pilot's instrument panel. (Refer to the Maintenance Manual, Chapter 31, Instrument Panels - Maintenance Practices.) G. Configure the Mark VIII GPWS Computer as outlined in the attached Cessna Engineering Drawing H. Put the Cessna Engineering Drawing in the avionics fly away book. 5. (Airplanes thru that are equipped with Mark VIII EGPWS) Do a functional test of the Mark VIII EGPWS Installation. A. Prepare for the functional test. (1) Connect a ground power unit to the external jack and turn on the ground power unit (adjusted to VDC, or VDC). (2) Engage both avionics and electrical circuit breakers as necessary and set all necessary avionics power switches to ON. (3) Set the BATTERY switch to BATT, the BATT DISC switch to NORM and the AVIONICS MASTER POWER switch to OFF. (4) Make sure that all applicable circuit breakers are engaged. (5) Set the AVIONICS POWER switch to ON. (6) Connect a PC to the GPWS RS232 diagnostic connector on the RS232 test port aft of the pedestal in the cockpit. Revision 2 - Mar 18/2005 Page 5

10 (7) Operate windows on the PC and find the WinViews icon. NOTE: If WinViews is not installed in the PC laptop computer, install the WinViews diskette and create a WinViews directory, then copy all the fixes to the PC. Open the ReadMe file for the latest details. Run the SETUP.EXE file to install WinViews on the PC and follow the on screen instructions. (a) The Winviews CMD file MK8CJ1.cmd should be used when doing the checkout procedure. (8) Double click on the WIN Views icon to start the program. (9) Load the applicable configuration file under the File Pull Down menu. (10) Use F6 to select the display mode. (11) Make sure that FMS has been initialized before testing the Mark VIII EGPWS. B. Do the functional test. (1) Doapowerontest. (a) Make sure that the COMPUTER OK lamp on the face of the EGPWS comes on when the EGPWS computer is booted up. NOTE: TheamberEXTERNALFAULTandtheredCOMPUTERFAILlampshouldnot be ON. (2) Do a cockpit audio test. (a) Press the Mark VIII EGPWS test switch. The switch must not be held for more than two seconds. NOTE: Not all of the announcements will be activated and the test volume is 6dB lower than normal operation. (b) Record the results of the test in the table below. Speaker annunciations Pass Fail (3) Do a cockpit annunciators test. (a) (b) (c) Set the rotary test switch to the test position. Make sure that the annunciators that follow come on. Record the results of the test in the table below. Annunciator Pass Fail TERR/NORM/TERR INHIB GPWS FLAP NORM/GPWS FLAP OVRD (4) Do a Self Test Level 1 Test. (a) Press and hold the EGPWS TEST annunciator for no more than two seconds. Revision 2 - Mar 18/2005 Page 6

11 (b) Make sure that the annunciators operate in the sequence that follows. 1 The GPWS INOP, TERR INOP, & TERR NOT AVAIL annunciators will remain on throughout the test. 2 The GPWS G/S CANCELLED light will come on. The GLIDESLOPE aural warning will be heard. 3 The PULL UP annunciation on the PFD will come on. The PULL UP aural warning will be heard. 4 The GPWS light will come on. The TERRAIN PULL UP aural warning will be heard. 5 The GPWS FAIL, TERR NOT AVAIL and PULL UP annunciator(s)/light(s) will go off after the test. 6 Record the results of the test in the table below. Self Test Level 1 Pass Fail (5) Do a Self Test Level 2 Test. (a) (b) (c) Press and hold the EGPWS TEST annunciator for no more than two seconds. Start a level 2 test sequence. 1 Press and hold the EGPWS TEST switch again for not more than two seconds when the self test audio starts. Make sure that the aural messages that follow come on. CURRENT FAULTS. 1 Iftheairplaneisnotinalocationthatallows the GPS receiver to receive enough satellites to become valid, the messages that follow will come on. Terrain Awareness - No Valid Latitude Terrain Awareness - No Valid Longitude Terrain Awareness Clearance Floor - Position Error Press To Continue 2 Record the results of the test in the table below. Self Test Level 2 Pass Fail (6) Do a Self Test Level 3 Test. (a) (b) (c) Press and hold the EGPWS TEST annunciator for not more than two seconds. Start a level 3 test sequence. 1 Press and hold the EGPWS TEST switch again for not more than two seconds when the self test audio starts. Push the EGPWS TEST switch immediately after the self test level 3 callout and the Press To Continue message will come on. Revision 2 - Mar 18/2005 Page 7

12 (d) Make sure the messages that follow come on. SYSTEM CONFIGURATION PART NUMBER SERIAL NUMBER APPLICATION SOFTWARE VERSION TERRAIN DATABASE VERSION ENVELOPE MOD DATABASE VERSION BOOT CODE VERSION AIRCRAFT DATA TYPE AIR DATA TYPE RADIO ALTITUDE TYPE NAVIGATION INPUT TYPE ATTITUDE INPUT TYPE MAGNETIC HEADING TYPE POSITION INPUT TYPE CALLOUTS OPTION AUDIO MENU VOLUME SELECT TERRAIN DISPLAY TYPE IO DISCRETE TYPE WINDSHEAR INPUT TYPE FLAP WOW REVERSAL SELECTED BANK ANGLE SELECTED SMART CALLOUT SELECTED OBSTACLE AWARENESS ENABLED PEAKS MODE ENABLED GPS ALTITUDE REFERENCE WGS 84 SELECTED (e) The level 3 test will continue and the configuration of the airplane will come on. (f) Make sure that the Press To Continue message comes on when the test is complete. (7) Do a Self Test Level 6 Test. (a) Press the EGPWS TEST switch immediately after the self test level 3 callout Press To Continue comes on. (b) Press the EGPWS TEST switch immediately after the self test level 4 callout Press To Continue comes on. (c) Press the EGPWS TEST switch immediately after the self test level 5 callout Press To Continue comes on. 1 The Discrete Input Test will come on. (8) Do a radio altimeter validity test. (a) Disengage the RAD ALT circuit breaker. 1 Radio Altimeter 1 Invalid should be come through the audio system. 2 Record the results of the test in the table below. Callout Pass Fail Radio Altimeter 1 Invalid (b) Engage the RAD ALT circuit breaker. Radio Altimeter 1 Valid should come on throughout the system. Revision 2 - Mar 18/2005 Page 8

13 (c) Record the results of the test in the table below. Callout Pass Fail Radio Altimeter 1 Invalid (9) Do a glideslope inhibit discrete input test. (a) Press the Glipeslope Inhibit button. 1 Glideslope Inhibit should come on through the audio system. 2 Record the results of the test in the table below. Callout Pass Fail Radio Altimeter 1 Invalid (10) Do a terrain inhibit discrete input test. (a) Press the Terrain Inhibit button. 1 Terrain Off should come on throughout the audio system. 2 Record the results of the test in the table below. Callout Pass Fail Terrain Off (b) Press the Terrain Inhibit button. 1 Terrain On should come on through the audio system. 2 Record the results of the test in the table below. Callout Pass Fail Terrain On (11) Do a landing flaps discrete input test. (a) Connect an external hydraulic pressure source to the airplane. NOTE: The flaps extended discrete equals approximately greater than 10. (b) Extend the flaps to the fully extended position. Landing Flaps 1 Landing Flaps should come on through the audio system. 2 Record the results of the test in the table below. Callout Pass Fail Revision 2 - Mar 18/2005 Page 9

14 (c) Put the flap control in the fully retracted position. 1 Not Landing Flaps should come on when the flaps are no longer in the fully retracted position. 2 Record the results of the test in the table below. Not Landing Flaps Callout Pass Fail NOTE: After cycling the flaps, the external hydraulic pressure source is no longer necessary for testing and should be turned off. (12) (Airplanes that are equipped with TCAS) Do a TCAS inhibit discrete output test. (a) Start the TCAS self test. (b) Activate the GPWS test after several seconds. 1 Make sure that the aural message is inhibited by the GPWS. 2 Record the results of the test in the table below. Callout Pass Fail TCAS Aural Warning Inhibit (13) (Airplanes that have installed the steep approach option) Do a steep approach discrete input test. NOTE: This test will test the steep approach switch logic but will not turn the steep approach light on. The steep approach light will be tested during the long test of the EGPWS. (a) Press the steep approach momentary switch. You must wait five seconds between each pressing of the switch to do the test. (b) Make sure that the steep approach discrete input is correct using the values shown in the table that follows. NOTE: This step is required for category 13 ID 6 and 7 using the momentary switch. Signal CVT Item Test Value Expected Value Observed Value Pass Fail Steep Approach MomSASel Steep Approach not selected 0 Steep Approach MomSASel Steep Approach selected (press and hold) 1 (14) Press the EGPWS TEST button to end the self test when the level six discrete input tests are complete. (15) Set up a PC laptop computer to operate WinViews. (a) Disengage the EGPWS circuit breaker and attach a nine pin test extender harness to the RS232 diagnostic connector on the RS232 test port aft of the pedestal in the cockpit and to the nine pin connector on the PC laptop computer. NOTE: The test port connector is not hard mounted and is bagged and stowed in the aft pedestal area. Revision 2 - Mar 18/2005 Page 10

15 (b) Initialize Windows version 3.1 or higher on the PC. (c) Start the WinViews.EXE program. (d) Select the Load Command File from the FILE Menu and load the applicable command file (*.cmd). (e) Press F6 to select the display mode. 1 Each CVT item listedinthecommandfile will be continuously updated. 2 The values shown on the screen for the CVT items found in the tables will be the test values. (16) Do an air data computer test. (a) Connect the air data test set to the airplane. (b) Setthealtitudeto2000feetandtheairspeedto100knots. (c) Set the pilot's altimeter to a pressure setting of hg and monitor the parameters that follow. (d) Record the results of the test in the applicable tables below. SIGNAL CVT ITEM TEST Uncorrected Baro Altitude Computed Airspeed Baro Alt Rate Outside Air Temp EXPECTED RawBAlt feet 2000 feet, +300 or -300 feet RawCAS1 100 knots 100 Knots, +10 of -10 knots RawBaroRt1 0 fmp 0 fpm, +0 or -0 FPM RawSAT1 OAT (C) OAT (C), +5 or -5 PASS FAIL (e) (f) Increase the pressure setting on the pilot's altimeter so that the indicated altitude increases by 500 feet and monitor the parameters that follow. Make sure that the adjustment did not alter the uncorrected Baro altitude. Record the results of the test in the applicable tables below. SIGNAL CVT ITEM TEST Corrected Baro Altitude Uncorrected Baro Altitude EXPECTED RawBCAlt feet 2000 feet, +300 or -300 feet RawBAlt feet 2000 feet, +300 or -300 feet PASS FAIL (g) Return the airplane back down to the ground on the air data test set. (h) Disconnect the air data test set. (17) Do a glideslope test. (a) Tune the pilot's NAV control unit to a vaild frequency ( MHz) then deselect it and monitor the valid ILD parameters. Revision 2 - Mar 18/2005 Page 11

16 (b) (c) (d) SwitchfromthedisplaymodetothecommandpromptinWinViewsbypressingF6and type ps for present status. Make sure that when ps is typed with a valid ILS frequency tuned, no faults are shown. Record the results of the test in the applicable tables below. SIGNAL CVT ITEM TEST EXPECTED ILS select ILSTuned1 Valid (tuned) 1 PASS FAIL (e) (f) (g) Deselect the ILS frequency. Make sure that CVT becomes invalid when the NAV radio is not tuned to a valid ILS frequency. Record the results of the test in the applicable tables below. SIGNAL CVT ITEM TEST EXPECTED ILS select ILSTuned1 Valid (tuned) 0 PASS FAIL (h) (i) Simulate a glideslope signal using the VOR/Localizer test set and make sure that the valid and deviation parameters are correct. Record the results of the test in the applicable tables below. SIGNAL CVT ITEM TEST Glideslope Valid Glideslope Valid Glideslope AGS1Val AGS1Val Valid (ILS tuned & GS valid) Invalid (ILS not tuned, no GS valid) RawAACGS1 1dotfly down EXPECTED , +0.3 DOT or -0.3 DOT Glideslope RawAACGS1 2 dots fly up -2 DOT, +0.3 DOT or -.3 DOT PASS FAIL (j) (k) Make sure the Glideslope/Cancel discrete is correct by changing the status of the annunciator. Make sure that the parameters in the table that follows are shown. Revision 2 - Mar 18/2005 Page 12

17 (l) Record the results of the test in the table below. SIGNAL CVT ITEM TEST EXPECTED PASS FAIL G/S Cancel GSCan Press and hold GS cancel switch 1 G/S Cancel GSCan Release GS switch 0 (18) Do a landing gear test. (a) (b) Switch the landing gear from down to up. Make sure that the parameters that follow are shown. Record the results of the test in the table below. SIGNAL CVT ITEM TEST Landing Gear Landing Gear EXPECTED LandGrDsc Gear down 1 LandGrDsc Gear Up 0 PASS FAIL (19) Do a flap position test. (a) (b) (c) (d) Make sure that the flap override switch is in the normal (override off) position. Make sure to take all the necessary precautions when moving the flaps on the airplane. Make sure that the parameters that are in the table below are shown for each of the given detents. Record the results of the test in the table below. SIGNAL CVT ITEM TEST EXPECTED 0 Flaps LandFlDsc 0, +2 or Flaps LandFiFAng 0, +2 or -2 0, +2 or Flaps LandFlDsc 35, +5 or Flaps LandFiFAng 35, +5 or , +5 or -5 PASS FAIL (e) Set the lamps to the normal position. (20) Do a terrain inhibit test. (a) (b) Change the status of the terrain inhibit switch. Make sure that the status of the switch changes as shown in the table that follows. Revision 2 - Mar 18/2005 Page 13

18 (c) Record the results of the test in the table below. SIGNAL CVT ITEM TEST EXPECTED PASS FAIL Terrain Inhibit TerrDis Select Terrain Inhibit 1 Terrain Inhibit TerrDis Deselect Terrain Inhibit 0 (21) Do an attitude (pitch and roll) test. (a) Make sure that the wiring from the attitude system to the EGPWS is operating correctly by installing the EGPWS/gyro(s) on a tilt table. (b) Input attitude changes and monitor the EGPWS to make sure that it sees the changes. (c) Make sure that the attitude input to the EGPWS is as shown in the table that follows. (d) Record the results of the test in the table below. SIGNAL CVT ITEM TEST EXPECTED Pitch Angle RawPitch1 0 0, +1 or -1 Pitch Angle RawPitch , +1 or -1 Roll Angle RawRoll1 0 0, +1 or -1 Roll Angle RawRoll , +1 or -1 Roll Angle RawRoll , +1 or -1 PASS FAIL (22) Do a position source test. (a) Make sure that the data in the table that follows verifies that the FMS/GPS input to the MK VIII EGPWS is correct. NOTE: Position inputs are provided in the form of W x y.z' or Nx y.z'. The MK VIII EGPWS stores position as +x.xxx or -x.xxx. For reference, in the MK 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 ' is equivalent to the MK VIII EGPWS value (36.66/ ). (b) Make sure that the FMS position is correct as shown in the table that follows. Revision 2 - Mar 18/2005 Page 14

19 (c) Record the results of the test in the table below. SIGNAL CVT ITEM TEST EXPECTED PASS FAIL Latitude GPSLatude1 Present position x PP, or Longitude GPSLngude1 Present position x PP, or Magnetic Heading RasAACMHd Present Heading ( +or-from zero north) PH, +1 or -1 Altitude RawGAlt1 Present altitude x ft PA, +500 feet or -500 feet (23) Remove the ground power unit from the airplane. (24) Remove the computer from the RS232 test port. 6. Make sure that the correct airplane flight manual supplement is in the airplane flight manual. A. (Airplanes thru that are equipped with Mark V EGPWS) Make sure that Airplane Flight Manual Supplement 32, Revision 1 or later is in the airplane flight manual. B. (Airplanes thru that are equipped with Mark VIII EGPWS) Make sure that Airplane Flight Manual Supplement 35, Revision 1 or later is in the airplane flight manual. C. Go to Step Put the airplane in a correct engine run-up area. NOTE: Proper throttle cable rigging must be verified prior to adjusting the 85% N2 position switches. (Refer to the Maintenance Manual, Chapter 76, Engine Power Controls - Adjustment/Test.) NOTE: Adjustment of left and right throttle switches is typical. Adjustment must be done to both the SI085 N2 Position Switch (left) and the SI084 N2 Position Switch (right). 8. Do a normal engine start. (Refer to the applicable Approved Airplane Flight Manual.) 9. Operate the engine at 90% N Put marks on the control quadrant cover plate using tape or an erasable marker to show the throttle lever position. 11. Shut down the engines. (Refer to the applicable Approved Airplane Flight Manual.) NOTE: The airplane may be returned to the hangar after putting marks on the control quadrant cover plate to show the 90% N2 throttle lever position. 12. Get access to the 85% N2 position switches by removing the pedestal equipment aft of the control quadrant. (Refer to applicable chapters and sections of the Maintenance Manual.) Revision 2 - Mar 18/2005 Page 15

20 13. (Refer to Figure 1.) Adjust the SI085 85% N2 Position Switch (left) and the SI084 85% N2 Position Switch (right) to actuate at 90%, +0% or -3% N2 throttle position using the 85% N2 position adjustment screw. NOTE: The 85% N2 position switch actuation can be sensed by listening for a click from the switch, by monitoring resistance across the common and normally open contacts of the switch, or by actuation of the speed brakes with electrical and hydraulic ground power connected. NOTE: The 85% N2 position switch adjustment screw will adjust both the SI085 N2 Position Switch (left) and the SI084 N2 Position Switch (right) at the same time. If there is an existing split in switch rigging, individual switch adjustments must be made. A. If both switches are within specification, go to Step 15. B. If both switches cannot be brought within specification using the 85% N2 position switch adjustment screw, adjust the switch settings individually as given in Step (Refer to Figure 1.) Adjust each 85% N2 position switch. A. Loosentheattachingscrewsonthe85%N2positionswitchtobeadjusted. B. Adjust the 85% N2 position switch to actuate when throttle lever is moved forward into the position that agrees with the 90%, +0% or -3% N2 throttle position as marked on the control quadrant cover plate in Step 4. (1) The 85% N2 position switch adjustment must be set at the 90%, +0% or -3% N2 throttle position. C. Tighten the screws attaching the SI085 N2 Position Switch (left) or SI084 N2 Position Switch (right) to the switch mount. 15. Install the pedestal equipment that was removed. (Refer to the applicable chapters and sections of the Maintenance Manual.) 16. Put the applicable supplement in the airplane flight manual. NOTE: Look at the configuration codes listed in the applicable supplement and/or in Section 1 of the FAA Approved Flight Manual to make sure all changed crew procedures or limitations are complied with. A. (Airplanes that are certified to be operated with the CJ1 FAA airplane flight manual) Make sure that Cessna Model 525 CJ1 FAA Approved Airplane Flight Manual Supplement Serial and On, 45, Revision 1 or later, or the applicable foreign airplane flight manual steep approach supplement inserted in the airplane flight manual. B. (Airplanes that are certified to be operated with the CJ1 UK airplane flight manual) Make sure that Cessna Model 525 UK Approved Airplane Flight Manual Supplement 11, Revision 1 or later, or the applicable foreign airplane flight manual steep approach supplement is inserted in the airplane flight manual. 17. 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 United States registered and foreign registered airplanes that use the US AFM 525FMA01 must order the following kit. Revision 2 - Mar 18/2005 Page 16

21 NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION -0 1 Kit, consisting of the following parts: 525FMA-S Supplement 45 None 1 Instructions CAA registered airplanes certified to be operated with the UK airplane flight manual 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: 525UKA-S Supplement 11 None 1 Instructions NOTE: Please contact Citation Publications at for part numbers and pricing of the applicable foreign airplane flight manual steep approach supplement. In addition to the above applicable kit, airplanes thru that are equipped with Mark VIII EGPWS that need to upgrade their EGPWS computer to a EGPWS Computer configuration 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: CM Nameplate (Marked SI837) None LED Switch Body None M39029/ Contact None M39029/ Contact None M39029/ Contact None M81044/ inches Electrical Wire (Marked None GSI837-GSI835) M81044/ inches Electrical Wire (Marked None CSI837-DDCDC10) M81044/ inches Electrical Wire (Marked None ASI837-41JB813) M81044/ inches Electrical Wire (Marked None 42PB813-31PN842) M81044/ inches Electrical Wire (Marked None 41PB813-25PN900) M81044/ inches Electrical Wire (Marked None 5PN900-52PN841) M81044/ inches Electrical Wire (Marked A4SI837-BSI837) None Revision 2 - Mar 18/2005 Page 17

22 NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION M81044/ inches Electrical Wire (Marked None ASI837-42JB813) S Contact None S Cap None Connector None In addition to the above applicable kit, airplanes thru that are equipped with Mark V EGPWS that need to upgrade EGPWS computer to a EGPWS Computer configuration must order the following kit. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION -3 1 Kit, consisting of the following parts: CM Nameplate (Marked SI838) None LED Switch Body None M39029/ Contact None M81044/ inches Electrical Wire (Marked None A4SI838-BSI838) M81044/ inches Electrical Wire (Marked None A4SI838-B1SI838) M81044/ inches Electrical Wire (Marked None B4SI838-DSI838) M81044/ inches Electrical Wire (Marked None CSI838-DDCDC10) M81044/ inches Electrical Wire (Marked None 56PN900-43PN337) M81044/ inches Electrical Wire (Marked None 57PN837-41PI813) M81044/ inches Electrical Wire (Marked None 41JB813-ASI838) M81044/ inches Electrical Wire (Marked None GSI819-GSI838) M81044/ inches Electrical Wire (Marked None 14APN834-42PI813) M81044/ inches Electrical Wire (Marked None 42JB813-A1SI838) M81044/ inches Electrical Wire (Marked None 1APN834-MNCS11) M39029/ Socket Contact None M39029/ Contact Pin None M81824/1-1 1 Splice None Revision 2 - Mar 18/2005 Page 18

23 NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION S Cap None Connector None In addition to the above applicable kits, airplanes thru that are equipped with Mark VIII EGPWS that choose to install an upgraded EGPWS processor must order the following part. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION EGPWS Computer S or S Return to Cessna for upgrade. NOTE: International Owner/Operators: The existing EGPWS computer may be returned to Cessna Aircraft Company, Citation Parts Distribution, 7121 Southwest Boulevard, Wichita, KS 67215, USA, and exchanged for upgraded units. Due to the limited availability, please expedite the return of the removed part. NOTE: Domestic Owner/Operators: The existing EGPWS computer is to be returned to Cessna Aircraft Company, Citation Parts Distribution, 7121 Southwest Boulevard, Wichita, KS 67215, USA, upgraded to the current modification level and returned to the owner/operator for installation. This option will require advance scheduling with Citation Parts Distribution, telephone number (Domestic) or (International) or telefax and an estimated turnaround time of approximately seven to ten days. Revision 2 - Mar 18/2005 Page 19

24 Figure 1. Throttle Switch Adjustment (Sheet 1) Revision 2 - Mar 18/2005 Page 20

25 Figure 2. Mark VIII EGPWS Upgrade (Sheet 1) Revision 2 - Mar 18/2005 Page 21

26 Figure 2. Mark VIII EGPWS Upgrade (Sheet 2) Revision 2 - Mar 18/2005 Page 22

27 Figure 2. Mark VIII EGPWS Upgrade (Sheet 3) Revision 2 - Mar 18/2005 Page 23

28 Figure 2. Mark VIII EGPWS Upgrade (Sheet 4) Revision 2 - Mar 18/2005 Page 24

29 TITLE SUPPLEMENTAL DATA FLIGHT CONTROLS - STEEP APPROACH CERTIFICATION - SPEED BRAKE SWITCH ADJUSTMENT EFFECTIVITY MODEL SERIAL NUMBERS and On MANPOWER WORK PHASE Modification MAN-HOURS As Required MATERIAL - Cost and Availability PART NUMBER AVAILABILITY COST -0 * 14,900 USD -1 * 14,900 USD -2 ** ** -3 ** ** * Please contact Citation Publications for current cost and availability of manuals listed in this service bulletin. Phone at ** 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 Page 1 of 1 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A , Fax COPYRIGHT 2003

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