SERVICE BULLETIN REVISION

Transcription

1 Revision 2 REVISION TRANSMITTAL SHEET This sheet transmits Revision 2 to, which: A. Removes JAA and replaces it with EASA. B. Adds the EASA Approval statement. NOTE: This revision replaces the original issue and Revision 1 of in its entirety. NOTE: Change bars and pointing hands are not used in this publication to denote revised material. This transmittal sheet provides a complete description of the changes made by this revision, except for editorial changes. REVISION COMPLIANCE NO EFFECT. Airplanes previously modified by this service bulletin are not effected by this revision. SUMMARY OF REVISIONS Original Issue Feb 2/2006 Revision 1 Oct 22/2009 Revision 2 Jun 2/2010

2

3 Revision 1 REVISION TRANSMITTAL SHEET This sheet transmits Revision 1 to, which: A. Changes the TITLE from NAVIGATION - HONEYWELL PRIMUS 2000 PHASE 6A WITH VERTICAL GLIDE PATH (VGP) to NAVIGATION - HONEYWELL PRIMUS 2000 PHASE 6A WITH FMS SOFTWARE NZ 6.0. B. Changes the EFFECTIVITY section to divide the serial numbers. C. Changes the entire document for the software upgrade from NZ 5.1 to NZ 6.0 and NZ 5.9 to NZ 6.0. 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 RECOMMEND. It is recommend that airplanes previously modified by this service bulletin do this revision. SUMMARY OF REVISIONS Original Issue Feb 2/2006 Revision 1 Oct 22/2009

4

5 TITLE NAVIGATION - HONEYWELL PRIMUS 2000 PHASE 6A WITH FMS SOFTWARE NZ 6.0 EFFECTIVITY MODEL SERIAL NUMBERS 750 (Citation X) thru -0159; thru not incorporating SB REASON To update the Phase 6A Primus 2000 Integrated Avionics Computers (IAC) software to incorporate design improvements to the flight management system (FMS). The new FMS software is designated as NZ 6.0. See the attached Flight Crew Operations Summary for a list of enhancements. DESCRIPTION This service bulletin provides parts and instructions to remove the existing IAC's, return them to Cessna for upgrade, and install the upgraded IAC's. COMPLIANCE RECOMMENDED. This service bulletin should be accomplished during a scheduled maintenance period. NOTE: This upgrade of the FMS function in the IAC involves changes that do not have an effect on the altitude-hold function of the autopilot. This service bulletin does not have an effect on the Reduced Vertical Separation Minimum (RVSM) qualification of the airplane. If your airplane is RVSM approved, please correct the IAC part number in the RVSM manual equipment list. Send a copy of the new list to local authorities. If the local authorities send an acknowledgement letter, it must be included in the RVSM manual. NOTE: If your airplane has Altitude/Heading Reference Units (AHRS) and SB has been installed, refer to SB Revision 5 or later for the final wiring modifications and Flight Crew Operations Summary. FLIGHT CREW OPERATIONS See the attached Flight Crew Operations Summary. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. EASA 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 and should be accomplished within the specified time requirement. Revision 2 - Jun 2/2010 Page 1 of 8 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A , Fax COPYRIGHT 2006

6 MANPOWER WORK PHASE MAN-HOURS Modification * MATERIAL - Cost and Availability PART NUMBER AVAILABILITY COST * * * * * Refer to the attached Service Bulletin Supplemental Data sheet for man-hours, material cost and availability, and warranty information. CHANGE IN WEIGHT AND BALANCE Negligible REFERENCES Cessna Model 750 Citation X Maintenance Manual Cessna Model 750 Citation X Wiring Diagram Manual PUBLICATIONS AFFECTED CessnaModel750CitationXIllustratedPartsCatalog Cessna Model 750 FAA Approved Airplane Flight Manual Honeywell FMZ Series Flight Management System Pilots Manual Honeywell FMZ Series Citation X TOLD Pilot Manual Cessna Model 750 Airplane Flight Manual Supplement 11, Honeywell FMZ Series P-2000 Flight Management System 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 batteries. (2) Disconnect external electrical power. C. Attach maintenance warning tags to the batteries and external power receptacle that have "Do not connect electrical power - maintenance in progress" on them. 2. Remove and return the IAC's for modification. A. Remove the IAC's. (1) Disengage circuit breakers IAC 1 and IAC 2 located on the right circuit breaker panel. (2) Open the nose compartment access doors to gain access to the IAC's. The pilot's IAC is in the left nose compartment and the copilot's IAC is in the right nose compartment. Revision 2 - Jun 2/2010 Page 2

7 (3) (Refer to Figure 1.) Remove the left and right IAC's. (Refer to the Model 750 Maintenance Manual, Chapter 34, Honeywell Primus 2000 Electronic Flight Instrument System (EFIS) - Maintenance Practices.) B. Send the IAC's for upgrade. NOTE: Contact Cessna Citation to schedule modification at or telefax or to: cpdavionicsteam@cessna.textron.com. This will require advance notification. Citation Repairs will schedule the units and arrange for their return. Allow five to seven days for modification. This service bulletin may not be signed off as completed unless the units are scheduled through Cessna Citation. 3. (Refer to Figure 1.) Install the upgraded IAC's. A. Remove the plugs from the connectors on the back of the IAC's as necessary. B. Install one (FAA) or one (EASA) IAC each on the left and right sides. (Refer to the Model 750 Maintenance Manual, Chapter 34, Honeywell Primus 2000 Electronic Flight Instrument System (EFIS) - Maintenance Practices.) CAUTION: Use care when you install the IAC's into its mounting rack. Improper seating of the units electrical connectors in the mounting rack could result in damage when the knob is rotated clockwise. C. Engage circuit breakers IAC 1 and IAC 2 located on the right circuit breaker panel. 4. Prepare the airplane for an operational check. A. Remove the maintenance warning tags B. Connect the airplane batteries C. Connect external electrical power. 5. Do an operational check. A. Apply avionics power and allow time for all systems to initialize. B. Upload the navigation data base, airplane data base version CX-L2 and the checklist. C. Enter the airplane serial number. NOTE: Use one of the two MFD's to enter the airplane serial number. (1) Push the < button until MAIN MENU 2/2 is displayed. (2) Push the LRU TEST. (3) Push MAINT. NOTE: This step will put the system on the IMT page. (4) Push PROGRAM. (5) Enter the airplane serial number. (6) Push SAVE. (7) Push the EXIT IMT. D. Make sure that the message CONFIG MISMATCH 1-2 is not present and there are no system failures within the Primus 2000 system annunciated on EICAS that cannot be accounted for. E. Using each FMS CDU, make sure that the IDENT page shows NZ 6.0 software. F. (Refer to Figure 2.) Make sure that the following configuration straps are cut on both the left and right configuration modules. Use either MFD to enter the Integrated Maintenance Test (IMT). Press <, LRU TEST, MAINT, LIST, SUBSYS, IAC 1-IOP, LRU TESTS, IAC CONFIG MODULE STATUS, Repeat for the right (copilot's) side by selecting IAC 2-IOP. Revision 2 - Jun 2/2010 Page 3

8 Strap 55 should already be cut on all airplanes. (Enables Category II display capability.) (FAA certified airplanes.) Strap 69 should already be cut. (Enables the Takeoff and Landing Database (TOLD) capability.) (EASA certified airplanes.) Cut Strap 69. (Enables the Takeoff and Landing Database (TOLD) capability.) NOTE: Use one of the two MFD's to access the configuration module status screen. (1) Push the < button until MAIN MENU 2/2 is displayed. (2) Push the LRU TEST. (3) Push MAINT. NOTE: This step will put the system on the IMT page. (4) Push LIST. (5) Push SUBSYS. (6) Push IAC 1-IOP. (7) Push LRU TEST. (8) Push IAC CONFIG MODULE STATUS. (9) Do steps 5F(1) thru 5F(8) for the right side by selecting IAC 2-IOP in Step 5F(6). (10) Push the EXIT IMT. 6. Make sure that the AIRSHOW/FMS ARINC 429 interface setup is "GENERIC 429". NOTE: You can use the VIP seat mouse or install a serial mouse for the AIRSHOW into port J7 on the face of the unit for this setup change. A. Press and hold the mouse buttons (L and R) during the system power-up. The AIRSHOW system will enter the Configuration Main Menu. B. Select I/O to get to the input/output setup page. C. Select NAV to get to the navigation page. D. Check box for "GENERIC 429" should be selected. (1) If the check box for "GENERIC 429" is not selected, select the check box for "GENERIC 429". E. Select RETURN for the Main Menu. F. Select EXIT and YES to Write New Configuration. 7. Make sure that Cessna Model 750 Airplane Flight Manual, Supplement 11, Honeywell FMZ Series P-2000 Flight Management System, Revision 14 or later, is inserted in the airplane flight manual. NOTE: You can contact Citation Technical Publications at for the Cessna Model 750 Airplane Flight Manual, Supplement 11, Honeywell FMZ Series P-2000 Flight Management System, Revision 14 or later. 8. Make sure that the manuals that follow are given to the flight crew to inform them of the operational changes resulting from incorporation of this service bulletin. Honeywell FMZ Series Flight Management System Pilots Manual - Software Version 5.9/6.0, Publication Number A Honeywell FMZ Series Citation X TOLD Pilot Manual, Publication Number A Revision 1orlater NOTE: You can contact Citation Technical Publications at for the Honeywell FMZ Series Flight Management System Pilots Manual - Software Version 5.9/6.0, Publication Number A and the Honeywell FMZ Series Citation X TOLD Pilot Manual, Publication Number A Revision 1 or later. Revision 2 - Jun 2/2010 Page 4

9 9. Make sure that the Flight Crew Operations Summary included with this service bulletin is given to the flight crew to inform them of the operational changes resulting from incorporation of this service bulletin. 10. Fill out Honeywell compliance forms that are included in the software kits and forward to Honeywell using the envelopes provided in the software kits. It is necessary to fill out one form for each IAC upgraded. 11. Record that you completed this service bulletin as follows: 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 NOTE: The parts that follow cover installation for one FAA certified airplane. NEW P/N QUAN- TITY IC-800 Computer (IAC) (FAA Certified Airplanes) KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION NOTE: The parts that follow cover installation for one EASA certified airplane. NEW P/N QUAN- TITY IC-800 Computer (IAC) (EASA Certified Airplanes) Return to Cessna for upgrade. KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION Return to Cessna for upgrade. NOTE: Contact Cessna Citation to schedule modification at or telefax or to: cpdavionicsteam@cessna.textron.com. This will require advance notification. Citation Repairs will schedule the units and arrange for their return. Allow five to seven days for modification. This service bulletin may not be signed off as completed unless the units are scheduled through Cessna Citation. NOTE: In addition to the IAC's that are to be modified, you will also need the publications that follow to complete this service bulletin. To order these publications, contact Citation Technical Publications at Cessna Model 750 Airplane Flight Manual, Supplement 11, Honeywell FMZ Series P-2000 Flight Management System, Revision 14 or later Honeywell FMZ Series Flight Management System Pilots Manual - Software Version 5.9/6.0, Publication Number A Honeywell FMZ Series Citation X TOLD Pilot Manual, Publication Number A Revision 1 or later. Revision 2 - Jun 2/2010 Page 5

10 Figure 1. Integrated Avionics Computer Installation (Sheet 1) Revision 2 - Jun 2/2010 Page 6

11 Figure 2. Strapping Card Modification (Sheet 1) Revision 2 - Jun 2/2010 Page 7

12 Figure 2. Strapping Card Modification (Sheet 2) Revision 2 - Jun 2/2010 Page 8

13 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 or EASA Approved Airplane Flight Manual. The FMS software upgrade from NZ 5.1 to NZ 6.0 and NZ 5.9 to NZ 6.0 includes multiple changes and new features. The list that follows is an Overview of Phase 6A NZ 6.0 FMS Enhancements. NOTE: The previous custom database is not transferable and will need to be reentered by the flight crew. System Operation Two NZ 6.0 Navigation Computers may be operated in Dual, Initiated Transfer, Independent, and Single modes in the same way as two NZ 5.1 Navigation Computers. Enhancements NZ 6.0 provides significant new enhancements, as listed below. The summary that follows is for airplanes that have upgraded from software NZ 5.1 to NZ 6.0. Adds vertical and lateral guidance enhancements which includes Vertical Glide Path Mode (VGP). Addition of runway displaced threshold to NDB. Display of data on WAYPOINT LIST page. Default of RADIO TUNE page to select previous frequency. Access to airport runway information when airport displayed on WPT LIST page. Airway entry consisting of start.airway.end where start and end are waypoints on the airway, e.g. OAK.J80.BGR. Entry of altitude constraints with temporary waypoints, e.g. P/B/D/ALTITUDE or P/B/P/B/ALTITUDE, into active flight plan. Units conversion pages, e.g. lb/kg, deg F/deg C, ft/m, gal/liters, kts / m/s, nm/m. Synchronization of FMS date/time to GPS date/time. (On NAV IDENT page, change GMT to UTC.). Capability to automatically display FLIGHT SUMMARY page following landing. Ability to store and assign the active flight plan a name following creation of the active flight plan. Enhancements to the EGPWS interface. The summary that follows is for airplanes that have upgraded from software NZ 5.9 to NZ 6.0. Ability to read waypoint wind/temp data from flight plans on diskettes or AFIS and insert data into active flight plan at each waypoint. Adds runway factors selection page. Displays corrected (factored) and actual (unfactored) landing distances on Landing Data page. Provides corrections to the Takeoff and Landing Database. Preview of a flight plan change to the active leg. A change to the active leg of the flight plan can be drawn on the CD-820 (if installed). The pilot can then accept or reject the change. Simple UNDO. If a Direct-To is performed and then the pilot wishes to amend the change and return to the original flight plan, the UNDO function can be selected. An UNDO message appears under the FN key on the CD-820 when UNDO is available. Simple BACK. This feature returns the pilot to the previous CDU page. If a graphics page is presently being displayed, the CDU returns to the last FMS page. If an FMS page is presently being displayed, the previous FMS page is displayed. Increased Custom Data Base storage. Up to 3000 custom flight plans may be stored in non-volatile memory.

14 ATTACHMENT Satellite Deselection. Provides the ability for the pilot to deselect satellites for GPS Predictive RAIM computations. Standby power down. With this feature enabled, the flight plan and performance initialization data are stored in non-volatile memory for one cycle of aircraft power. Autotuning of localizer frequencies. If 1) an ILS approach has been incorporated into the active flight plan, 2) the FMS tuning mode is autotune, and 3) the active flight plan leg has a procedure specified NAVAID from the Navigation Data Base, the FMS will autotune the procedure specified NAVAID (localizer). When SB is accomplished at the same time as this service bulletin, AHRS equipped airplanes will fully comply with the requirements of EASA MPA (x).

15 TITLE SUPPLEMENTAL DATA NAVIGATION - HONEYWELL PRIMUS 2000 PHASE 6A WITH FMS SOFTWARE NZ 6.0 EFFECTIVITY MODEL SERIAL NUMBERS 750 (Citation X) thru -0159; thru not incorporating SB MANPOWER WORK PHASE MAN-HOURS Modification 3.0 MATERIAL - Cost and Availability PART NUMBER AVAILABILITY COST * * * * * Please contact Cessna Service Parts & Programs for current cost and availability of parts listed in this service bulletin. Phone at (Domestic) or (International). Send to: citationparts@cessna.textron.com or telefax at Based on availability and lead times, parts may require advanced scheduling. In cases where the required part(s) are available as exchange, order the exchange part and, upon completion, expedite the return of the removed core to avoid return penalties. Contact the Cessna Service Parts & Programs Sales Desk for availability of exchange parts. Revision C - Dec 20/2011 Page 1 of 2 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A , Fax COPYRIGHT 2006

16 SUPPLEMENTAL DATA WARRANTY CREDIT PROGRAM This bulletin is recommended. Eligible airplanes may qualify for parts and labor coverage, as described below. Eligibility: Parts Coverage: Labor Coverage: Credit Application: All affected airplanes. Authorized Citation Service Facilities, operators, or other maintenance facilities may submit a Citation Credit Claim Form for the parts required to accomplish this bulletin. Authorized Citation Service Facilities may submit a Citation Credit Claim Form for the labor necessary to accomplish this service bulletin. Please note Manpower Requirements for coverage guidelines. If actual labor differs from coverage guidelines, claim actual labor and detail all discrepancies. All work must be completed and the Citation Credit Claim Form submitted before the date shown below. Send the Citation Credit Claim, along with any required parts (see Material Information), to the point of purchase. Parts to be returned to Citation Parts Distribution should be forwarded to: Citation Warranty Administration 7121 Southwest Boulevard Wichita, KS USA Expiration: Dec 18/2012 Revision C - Dec 20/2011 Page 2