ENGINEERING ORDER. E.O. No: E Revision: A Page 2 of 17 RECORD OF REVISIONS. Approvals. Pages. Description Of Revision

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2 Page 2 of 17 Rev Date Pages Affected RECORD OF REVISIONS Description Of Revision Approvals IR 6/10/04 All Initial release Prepared: E. Weaver Checked: Gary Fischer Approved: B. Culberson A See front sheet 8 Added note to Section 12.7 for Pitot / Static heat. Prepared: See front sheet Checked: See front sheet Approved: See front sheet

3 6.0 REFERENCES 6.1 Generating Documents None ENGINEERING ORDER Page 3 of Source Documents ISS Interface Control Document Air Data Display Unit, 1G ISS Interface Control Document Analog Interface Unit, 1G Cessna/Citation Publication S55CD1-04 Dated May Cross References Star Aviation Documents Referenc e Title Document Number 1 Certification Plan R-34-Y Weight and Balance Report R-34-Y System Safety Assessment R-34-Y Continued Airworthiness Report R Structural Substantiation Report R-53-Y AFM Supplement R Operational Test R Master Data List R-34-Y Approved Model List R-34-Y Skin Mapping Procedure R Superceded Documents None. 6.5 Drawings Star Aviation Drawings The following Star Aviation drawings are required to accomplish this EO. Drawing Number Title D-34-Y Pitot and Static System Modification D-25-Y RVSM Equipment Installation D-34-Y Ships Wiring Routing and Clipping D RVSM Air Data System For Dual FD Aircraft OEM Drawings Cessna Citation Wire Diagram Manual.

4 Page 4 of Attachments None. 7.0 PUBLICATIONS AFFECTED 7.1 Maintenance Manual See Star Aviation ref Illustrated Parts Catalog See Star Aviation ref Wiring Diagram Manual Operator to incorporate Star Aviation Drawing D , RVSM Air Data System For Dual FD Aircraft; into the Aircraft Wiring Diagram Manual. 7.4 Airplane Flight Manual See Star Aviation ref 6.

5 8.0 WEIGHT AND BALANCE ENGINEERING ORDER Page 5 of 17 See Star Aviation Weight and Balance Report R-34-Y , Ref ELECTRICAL LOAD ANALYSIS See Star Aviation System Safety Assessment R-34-Y Ref SCHEDULED MAINTENANCE PROGRAM IMPACT See Star Aviation Continued Airworthiness Report R , Ref DEPARTMENTAL INSTRUCTIONS 11.1 Planning Mod-Center to schedule planning sequence Avionics All avionics installations must be performed in accordance the following documents: 1) AC B CHG 1 Dated 9/27/01, Acceptable Methods, Techniques, and Practices Aircraft Inspection and Repair, Chapter 11 Aircraft Electrical Systems. 2) SAE AS50881, Wiring Aerospace Vehicle Rev A Dated ) Manufacturers Chapter 20 Standard Wiring Practices Structures All structural installations must be performed in accordance with Cessna Citation Structural Repair Manual, Chapter 51 standard practices.

6 Page 6 of WORK INSTRUCTIONS 12.1 PREPARATION Ensure all power is removed from the aircraft GAIN ACCESS Remove the radome to gain access to the avionics rack Open the pilots side baggage compartments and remove access panels to gain access in these areas Remove panels as needed to gain access to work areas in the cockpit EQUIPMENT REMOVALS Remove the existing Air Data Computer, equipment tray and retaining hardware and return to stores for disposition Remove the old air data computer connector, P322, pull back, cap and stow old ADC wiring in accordance with standard practices Remove the Pilots altimeter and return to stores for disposition Pull back, coil, bag and stow the pilot s old altimeter connector, P337 in accordance with standard practices Remove the Copilots altimeter and retain for reinstallation as a standby altimeter If installed remove the XPDR ALT PRI/SEC Switch and bag and stow its connector. NOTE: This location can be used as the location for the New Altitude Select Switch ADC1/ADC2 instead of cutting a new hole on the copilots panel Depending on the location of the standby altimeter, remove all instruments from the pilots or copilot s instrument panel and retain for reinstallation. Salvage hardware for reinstallation Depending on the location of the standby altimeter, remove the pilots or copilots Instrument panel and route to the shop for disposition. Salvage hardware for reinstallation SHOP Rework existing pilots or co-pilots instrument panel to a 1 or -2 configuration per Star Aviation Drawing D-25-Y Note that the 1 Installation modifies the copilots side instrument panel for installation of the standby altimeter and the 2 Installation modifies the pilots side instrument panel. OR Request new instrument panel configuration from Star Aviation ( ).

7 Page 7 of Part mark the existing instrument panel D-25-Y or D-25-Y using indelible black ink or other suitable permanent marking per MIL-STD-130,.125 inch high letters minimum If required, reinstall any equipment removed during panel modification and route the D-25-Y or -2 instrument panel to the aircraft for installation PITOT AND STATIC SYSTEMS MODIFICATIONS Remove existing static system components in accordance with Star Aviation Drawing D-34-Y Install new static system components in accordance with Star Aviation Drawing D-34-Y , using the 101 Instl when the standby altimeter is relocated on the copilots instrument panel or the 103 Instl if relocating standby altimeter on the Pilots instrument panel Remove existing pitot system components in accordance with Star Aviation Drawing D-34-Y Install new pitot system components in accordance with Star Aviation Drawing D-34-Y , using the 101 installation when the standby altimeter is relocated on the co-pilots instrument panel or the 103 instl if relocating standby altimeter on the pilots instrument panel. NOTE: Steps thru must be conducted at an ambient temperature of 50 to 95 F. The aircraft does not need to be jacked or leveled to perform these steps Visually inspect to verify the absence of skin waviness, scratches or damage in the RVSM critical region defined in Figure Verify entire inspection area meets all criteria found in the Cessna Model S550 Structural Repair Manual, Chapter , Aerodynamic Surfaces-Description. Repair any discrepancies found using standard procedures found in the SRM Accomplish the static port refinishing process specified in Appendix B of Star Aviation Report No. R , Reduced Vertical Separation Minimum (RVSM) Skin Waviness Inspection Procedures for the Cessna Model 560 and S550 Citation Aircraft Map the skin of the aircraft in the RVSM Critical Region as specified in Star Aviation Report No. R , Reduced Vertical Separation Minimum (RVSM) Skin Waviness Inspection Procedures for the Cessna Model 560 and S550 Citation Aircraft Compare the results of the skin mapping procedure from step above to the tolerances shown in Table 3-1 of Section 3.4 of Star Aviation Report No. R , Instructions for Continued Airworthiness for the Cessna Model S550 Citation S/II Aircraft Equipped with an RVSM Air Data System and Dual Flight Directors and Qualified for Operations in RVSM Airspace. If the aircraft exceeds the allowances in Table 3-1 contact Star Aviation at (251) Place small permanent markings at the corners of the RVSM Critical Region defined by Figure 1. These markings may be any shape or color; with the only requirement that they are visible to an individual conducting an inspection.

8 Page 8 of Install placard P/N D-11-Y or -37 in the location shown in Figure Verify that all placards or stencils are located outside of the RVSM Critical Area defined in Figure Purge the pitot and static systems in accordance with AMM AVIONICS RACK EQUIPMENT PROVISIONS INSTALLATION Install the D-25-Y Angle in accordance with Star Aviation Drawing D-25-Y , installation Install two ground blocks P/N RBGB20-1 onto the D-25-Y angle in accordance with Star Aviation Drawing D-25-Y , Installation Install two ground studs onto the D-25-Y angle in accordance with Star Aviation Drawing D-25-Y , Installation Install D-25-Y Bracket Assembly in accordance with Star Aviation Drawing D-25-Y , Installation WIRING MODIFICATIONS NOTE: FOR A/C THAT CURRENTLY HAVE A REQUIREMENT FOR ONLY THE PILOT S PITOT / STATIC HEAT TO BE ON THE EMERGENCY BUS, REWIRE SO THAT ONLY THE CO-PILOT S PITOT / STATIC HEAT IS ON THE EMERGENCY BUS On the unpressurized side of the FWD Pressure Bulkhead Disc. locate and disconnect connector P350, pull back, bag and stow On the pressurized side of the FWD Pressure Bulkhead Disc. remove connector J350 from the bulkhead; pull back, bag and stow Install and route the Dual S550 AIU Harness Assy, P/N D-34-Y in accordance with Star Aviation Drawing D-34-Y (-1007) Terminate the following wires at ground block GN9000 using M39029/1-101 contacts supplied with the D-34-Y harness assy. Reference Star Aviation Drawing D P9500SH1-GN9000 7P9500-GN P9500-GN P9500-GN P9500-GN P9500-GN P9500-GN9000 X2P9507-GN P9501-GN9000 2P9501-GN9000 7P9501-GN9000 8P9501-GN P9501-GN P9501-GN P9501-GN P9501-GN9000

9 Page 9 of Terminate the following wires at ground block GN9001 using M39029/1-101 contacts supplied with the D-34-Y or 5 harness assy. Reference Star Aviation Drawing D-34-Y or D-34-Y P9505SH1-GN9001 7P9505-GN P9505-GN P9505-GN P9505-GN P9505-GN P9505-GN9001 X2P9509-GN P9506-GN9001 2P9506-GN9001 7P9506-GN9001 8P9506-GN P9506-GN P9506-GN P9506-GN P9506-GN Terminate the following wires at ground stud GN9002 using MS ring terminals supplied with the D-34-Y harness assy. Reference Star Aviation Drawing D P9501-GN9002 4P9506-GN Terminate wire P9509SH1-GN9003 at GN9003 using a MS ring terminal. Reference Star Aviation Drawing D Cap and stow the following wires at connector P310 (Bottom Plug) on the Pilots Flight Director Computer. Reference Star Aviation Drawing D P310-31P322 82P310-34P322 84P310-35P322 36P310-32P322 37P310-33P322 44P310-65P Terminate the following wires from the D-34-Y harness assy into connector P310 on the Pilots Flight Director Computer using contacts P/N Reference Star Aviation Drawing D for shield terminations. 81P310-33P P310-31P P310-32P P310-39P9501 (R) 37P310-40P9501 (B) 44P310-23P Cap and stow the following wires at connector P308 (Top Plug) on the Pilots Flight Director Computer. Reference Star Aviation Drawing D P308-/64P322 /42P308-/12P322 44P308-63P322 NOTE: See Star Aviation drawing D for final wiring configuration at pin Terminate the following wires into connector P308 on the Pilots Flight Director Computer using contacts P/N Reference Star Aviation Drawing D for shield terminations. 44P308-8P P308-/21P9501 /42P308-/19P9501

10 Page 10 of Cap and stow the following wires at connector P311 (Bottom Plug) on the Copilots Flight Director Computer. Reference Star Aviation Drawing D P311-40P322 82P311-43P322 84P311-44P322 36P311-41P322 37P311-42P322 44P311-/65P Terminate the following wires into connector P311 (Bottom Plug) on the Copilots Flight Director Computer using contacts P/N Reference Star Aviation Drawing D for shield terminations. 81P311-33P P311-31P P311-32P P311-39P P311-40P P311-23P9506 NOTE: Re-identify wire number 44P311-23P9506 as 45P311-23P9506 in accordance with standard practices for A/C which require this connection to pin 45 of connector P311. Reference Star Aviation Drawing D and A/C WDM Cap and stow the following wires at connector P309 (Top Plug) on the Copilots Flight Director Computer. Reference Star Aviation Drawing D P309-/63P322 43P309-/64P322 /42P309-/12P Terminate the following wires into connector P309 (Top Plug) on the Copilots Flight Director Computer using contacts P/N Reference Star Aviation Drawing D for shield terminations. 44P309-8P P309-/21P9506 /42P309-/19P Cap and stow wire 44P313-/12P322 at Connector P313 on the Auto Pilot Computer Terminate wire 44P313-B2P9509 from the D-34-Y harness assembly into connector P313 on the Autopilot Computer using contacts P/N Reference Star Aviation Drawing D NOTE: Cap and Stow this wire for A/C with autopilot computers P/N or Cap and stow the following wires at connector P312 on the Auto Pilot Computer: 21P312-/52P322 39P312-/64P Terminate the following wires from the D-34-Y harness assembly into connector P312 on the Autopilot Computer using contacts P/N Reference Star Aviation Drawing D /F2P P312 39P312-A2P9509 NOTE: For A/C with autopilot computers P/N or 920 cap and stow wire /F2P P312.

11 Page 11 of Install and route the Dual ADDU Harness Assy, P/N D-34-Y in accordance with Star Aviation Drawing D-34-Y (-1007) Install and identify the following ground studs in accordance with Star Aviation Drawing D-34-Y : GI9000, GI9001, GI9002, GI9003, GI9004, and GI Terminate the following wires from the Pilot s ADDU connector P9502 at the grounds indicated below using MS ring terminals supplied with the D-34-Y harness. (Reference Star Aviation Drawing D ) WIRE NUMBER BP9502-GI9000 MP9502-GI9000 *XP9502-GI9000 BBP9502-GI9001 FFP9502-GI9001 *WP9502-GI9000 GROUND GI9000 GI9000 GI9000 GI9001 GI9001 GI At the Transponder Control panel connector PD86 splice the following wires into existing Control Panel wiring as shown on D using splice P/N supplied with the D-34-Y harness assembly. WIRE NUMBER *GP9503- /FPD86 *FP9503- /HPD86 *AP9503- /*DPD86 YP9503- /*CPD86 *EP9503-/JPD86 ZP9503- /*EPD86 *DP9503- /*FPD86 *HP9503- /*PPD86 *BP9503- /*IPD86 *CP9503-/*HPD86 WIRE NUMBER *GP9502- /FPD86 *FP9502- /HPD86 *AP9502- /*DPD86 YP9502- /*CPD86 *EP9502-/JPD86 ZP9502- /*EPD86 *DP9502- /*FPD86 *HP9502- /*PPD86 *BP9502- /*IPD86 *CP9502-/*HPD86 NOTE: When existing wires at connector PD86 are cut to allow splicing of new wires cap and stow existing wire such that final wiring configuration shown on D is achieved Re-identify wire 12P9508-*GPD86, Part of Loose Wire Kit P/N D-34-Y as 15P *GPD86 and route from the ADC System Select Switch to the Transponder Control Panel Terminate wire 15P9508-*GPD86 at pin *G on PD86 using contact P/N M39029/ supplied with the D-34-Y harness assembly Cap and stow wire AP337-1P920 (W) at connector P920 and wire BP337-YP923 (B) at connector P923. Reference Star Aviation Drawing D Terminate wires CP9502-1P920 (R) and DP9502-YP923 (B) at connectors P920 pin 1 and P923 pin Y respectively. Reference Star Aviation Drawing D

12 Page 12 of Terminate wires HI9000-AP9502 and HI9000-6J9504 at the Air Data Sys 1 28V DC Circuit Breaker, (HI9000) on the RVSM Aux Circuit Breaker Panel using MS ring terminals supplied with the D-34-Y harness assy. Reference Star Aviation Drawing D Terminate wire HI9001-1J9504 at the Air Data Sys1 26V AC Circuit Breaker, (HI9001) on the RVSM Aux Circuit Breaker Panel using a MS ring terminal supplied with the D-34-Y harness assy. Reference Star Aviation Drawing D Terminate the following wires from the Copilot s ADDU connector P9503 at the grounds indicated below using MS ring terminals supplied with the D-34-Y Reference Star Aviation Drawing D WIRE NUMBER BP9503-GI9002 MP9503-GI9002 *XP9503-GI9003 BBP9503-GI9003 FFP9503-GI9003 *WP9503-GI9005 GROUND GI9002 GI9002 GI9003 GI9003 GI9003 GI Reroute the copilot s altimeter connector, P849 and associated wiring from its existing location to the new location for the copilot s altimeter. Reference Star Aviation Drawing D-25-Y for new location of altimeter Terminate wires CP P922 (R) and DP9503-YP925 (B) at connectors P922 pin 18 and P925 pin Y respectively. Reference Star Aviation Drawing D and Citation WDM Terminate wire HI9002-AP9503 at the Air Data Sys 2 28V DC Circuit Breaker, (HI9002) on the RVSM Aux Circuit Breaker Panel using an MS ring terminal. Reference Star Aviation Drawing D Terminate wire HI9003-2J9504 at the Air Data Sys 2 26 VAC Circuit Breaker, (HI9003) on the RVSM Aux Circuit Breaker Panel using an MS ring terminal. Reference Star Aviation Drawing D Terminate ADC System Select Switch, P9508, wiring in accordance with Star Aviation Drawing D-34-Y sheet Terminate Dimming Relay, P9510, wiring in accordance with Star Aviation Drawing D-34-Y sheet 18.

13 Page 13 of Cap and stow the following wires at connector P335 on the VNAV control. Reference Star Aviation Drawing D NOTE: See Star Aviation Drawing D for final wiring configuration at P335 pins 36, 39, and J350-40P335 (W) 21J350-41P335 (R) 22J350-/42P335 (B) /11J350-/36P335 *GP337-18P335 /FP337-/39P335 23J350-37P335 (W) 24J350-14P335 (R) 25J350-15P335 (B) /EP337-38P335 (W) *AP337-/36P Terminate the following wires into connector P335 on the VNAV Control using M contacts supplied with the D-34-Y harness assy. Reference Star Aviation Drawing D NOTE: See Star Aviation Drawing D for final wiring configuration at P335 pins 36 and J P335 (Y) 47J P335 (R) 48J9504-/42P335 (B) /8J9504-/36P335 35J P335 (Y) 36J P335 (R) 34J P335 (B) Install and terminate the following wires /39P335-GI9004 and /15P335-GI9002 from the D-34-Y loose wire kit. Reference Star Aviation Drawing D Cap and stow wire *FP337-/1J318 near connector J318. See Star Aviation Drawing D for final wiring configuration Install and identify diodes DI9002 and DI9003 P/N 1N4006. Heat shrink sleeving or other protective material must be installed over the diodes to insulate the leads. Reference Star Aviation Drawing D Note: Wire /1J318-EP9502 and /1J319-EP9503 are part of the D-34-Y harness assy Terminate the following wires from the D-34-Y harness assy as follows. Reference Star Aviation Drawing D WIRE NUMBER TERMINATION HP9502-/18P335 SPLICE P335 (18) /DDP9502-/17P1A SPLICE P1A (17) HP9503-/18P335 SPLICE P335 (18) Cap and Stow wire /11J350-1SPKR8 at SPKR8. Reference Star Aviation Drawing D Terminate wire /8J9504-1SPKR8 at SPKR8 terminal 1. Reference Star Aviation Drawing D

14 Page 14 of Terminate wire HI P335 from the D-34-Y Loose Wire Kit using an M contact and MS ring terminal. Reference Star Aviation Drawing D Install supply side circuit breaker wiring for circuit breakers HI9000, HI9001, HI9002, and HI9003 in accordance with Star Aviation Drawing D-34-Y sheet On the RH CB Panel remove Air Data Circuit Breaker CB462 and wire DP901-1CB462 and relocate wire EEP901-2CB462 from the supply side of CB462 to the supply side of the adjacent circuit breaker on the 115 VAC Bus Install a button plug in the location of the Removed Air Data Circuit Breaker. Paint to match as needed Checks Using Star Aviation Drawing D perform a continuity check of all installed and modified wiring Using Star Aviation Drawing D check for grounds on appropriate pins of connectors P9500, P9501, P9502, P9503, P9505, P9506, P9507, P9508, P9509 and P Using Star Aviation Drawing D check for correct voltage on appropriate pins of connectors P9500, P9501, P9502, P9503, P9505, P9506, P9507, P9508, P9509 and P AVIONICS RACK EQUIPMENT INSTALLATION Install relay base P9507 and P9509, part of the D-34-Y harness assembly, in accordance with Star Aviation Drawing D-34-Y , Installation Install relay P/N MS25329-D1 into relay base P9507 and P9509 in accordance with Star Aviation Drawing D-25-Y , Installation Install two AIUs P/N 9B in accordance with Star Aviation Drawing D-25-Y , Installation FLIGHT DECK EQUIPMENT INSTALLATION Install the D-25-Y relay bracket on the rear of the copilot s instrument panel in accordance with Star Aviation Drawing D-34-Y , Instl Install Relay Socket P/N SO and relay P/N XD4N into the D-25-Y relay bracket in accordance with Star Aviation Drawing D-25-Y , Instl Install instrument panel, P/N D-25-Y , -2 or Design Deviation panel in accordance with Star Aviation Drawing D-25-Y using salvaged hardware Install and connect the standby altimeter removed and retained in step into the location defined in Star Aviation Drawing D-25-Y Install and connect all remaining instruments removed and retained in step into their original locations on the pilot s or copilot s instrument panel.

15 Page 15 of Install and connect ADDU P/N 9D into the copilot s instrument panel in accordance with Star Aviation Drawing D-25-Y , Instl. Note: Ensure Config Module P/N 9B is connected to the ADDU and it s lanyard is attached to the backshell of the ADDU harness connector prior to installation of ADDU Install the ADC System Select Switch P/N FK into the copilot s instrument panel in accordance with Star Aviation Drawing D-25-Y , Instl. NOTE: If the A/C was equipped with an XPDR ALT PRI / SEC Switch the ADC System Select Switch may be installed in the location from which the XPDR ALT PRI / SEC switch was removed Install the ADC System Select Switch Placard P/N D-11-Y in accordance with Star Aviation Drawing D-25-Y , Instl Install and connect ADDU P/N 9D into the pilot s instrument panel in accordance with Star Aviation Drawing D-25-Y , Instl. Note: Ensure Config Module P/N 9B is connected to the ADDU and it s lanyard is attached to the backshell of the ADDU harness connector prior to installation of ADDU Install RVSM Circuit Breaker Panel P/N D-25-Y in accordance with Star Aviation Drawing D-25-Y , Instl TESTING Perform a pitot - static system leak check as described in the Cessna Citation Maintenance Manual, except for the static leak check, set the air data test unit at 30,000 feet and an indicated airspeed of 200 knots. Leak rate no to exceed 300 feet/min Accomplish RVSM Operational Test per R Accomplish Section 3.5 Air Data System Accuracy check of Star Aviation Report No. R , Instructions for Continued Airworthiness for the Cessna Model S550 Citation S/II Aircraft Equipped with an RVSM Air Data System and Dual Flight Directors and Qualified for Operations in RVSM Airspace. Note: This can be done in conjunction with step above and must be done at an ambient temperature between 50 and 95 F CLOSE UP Close all panels and doors opened to perform the installation of the RVSM Air Data System. END

16 Page 16 of 17 RVSM CRITICAL REGION FIGURE 1

17 13.0 BILL OF MATERIALS 13.1 Basis: Per aircraft. ENGINEERING ORDER Page 17 of Modified or Repaired Assemblies None New Materials Item No. Part Number Nomenclature Vendor Remarks Qty 1 K-34-Y Citation RVSM Wiring Kit Star Aviation 1 2 K-34-Y Citation RVSM LRU Kit Star Aviation 1 3 K-34-Y Citation RVSM Misc. Parts Kit Star Aviation 1 4 K-34-Y Citation RVSM Pitot and Static Kit Star Aviation 1 5 K-34-Y Citation RVSM Equip Mounting Kit Star Aviation Old Materials Item No. Part Number Nomenclature Vendor Remarks Qty Air Data Computer Altimeter Pilots /8S-1-DPXB-0 Equipment Tray Special Tooling Item No. Part Number Nomenclature Vendor Remark s Qty 1 KSR TOL 723 Skin Map Reference Bar With Base KSR Dial Indicator Depth Gauge Mitutoyo 1 3 Various 24 inch flexible steel ruler Various 1