SERVICE BULLETIN. To prevent the wing fuel boost pump wiring from chafing on the wing structure and/or fuel tube assemblies.

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1 TITLE FUEL - WING FUEL BOOST PUMP WIRE ROUTING IMPROVEMENT EFFECTIVITY MODEL SERIAL NUMBERS thru REASON To prevent the wing fuel boost pump wiring from chafing on the wing structure and/or fuel tube assemblies. DESCRIPTION This service bulletin provides parts and instructions to inspect and route the fuel boost pump wires and install clamps so the wires will not rub on the fuel tube assemblies or the wing structure. This service bulletin imposes a minimum fuel load for wing fuel boost pump operations and instructions to insert the applicable Temporary Changes in the Airplane Flight Manual until this service bulletin is completed. COMPLIANCE MANDATORY. This service bulletin must be accomplished as follows: Steps 1, 2 and 3 of the ACCOMPLISHMENT INSTRUCTIONS must be incorporated into daily operations immediately upon receipt of this service bulletin. The remaining steps of this service bulletin must be accomplished within the next 300 flight hours or at the next phase 2 inspection. 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. Page 1 of 12 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A , Fax COPYRIGHT 2004

2 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. This information shall be considered an amendment to the Cessna Manufacturer s Maintenance Manual or Instructions for Continued Airworthiness, and must be accomplished for ongoing airworthiness compliance as required per 14 CFR Part MANPOWER WORK PHASE MATERIAL - Cost and Availability MAN-HOURS Modification * PART NUMBER AVAILABILITY COST * * * Refer to the attached Service Bulletin Supplemental Data sheet for man-hours, material cost and availability, and warranty information. CONSUMABLE MATERIAL In addition to the above kit(s), the following materials, or equivalent, are required for the accomplishment of this service bulletin. NAME NUMBER MANUFACTURER USE Sealant Type 1, Class B-1/2 (CMNP021 CLASSB1/2) Cessna Citation Parts Distribution Wichita, KS To seal the fuel boost pump connector (if replaced) and to repair the wiring. Color Chemical Film Treatment Alodine 1201 Henkel (Parker Amchem) Stephenson Highway Madison Heights, MI To protect the fuel tube repair. CHANGE IN WEIGHT AND BALANCE Negligible REFERENCES Cessna Model 560 Maintenance Manual Cessna Model 500 Series Structural Repair Manual PUBLICATIONS AFFECTED Cessna Model 560 Maintenance Manual Cessna Model 560 Illustrated Parts Catalog Cessna Model 560 Citation V Approved Airplane Flight Manual Cessna Model 560 Citation Ultra Approved Airplane Flight Manual Page 2

3 ACCOMPLISHMENT INSTRUCTIONS 1. Make sure that the appropriate temporary changes or latest Airplane Flight Manual revision that are associated with this service bulletin are inserted into the Airplane Flight Manual. NOTE: The temporary changes are to remain effective until superseded by an Airplane Flight Manual revision, or until this service bulletin has been accomplished. 2. Do not use the wing fuel boost pumps to defuel or transfer fuel if the individual fuel load in each wing is less than 600 pounds. NOTE: The above restriction will remain effective until all of the inspection, repair and replacement requirements in this service bulletin have been accomplished. 3. Make a placard that states: MINIMUM FUEL 600 POUNDS PER WING. NOTE: Make the placard using the best standard shop practice. The placard should be as large as possible to fit into an open space that is close to the fuel quantity gage and be in clear view of the pilot. The lettering must have a high color contrast to the background color of the placard. A. Install the placard on the instrument panel close to the fuel quantity gage in clear view of the pilot. WARNING: THE AIRPLANE HAS A TENDENCY TO BE TAIL-HEAVY WHEN THE INTERIOR FURNISHINGS, FORWARD-MOUNTED EQUIPMENT AND/OR FUEL ARE REMOVED. ADDING AND PLACING WEIGHTS ON A SUITABLE PLYWOOD SURFACE IN THE FORWARD CABIN OR NOSE BAGGAGE AREA IS ADVISABLE TO PREVENT POSSIBLE DAMAGE TO THE AIRPLANE AND PERSONNEL. THE TAIL STAND SHOULD BE IN PLACE AT ALL TIMES, EXCEPT WHILE IN THE PROCESS OF RAISING AND LOWERING THE AIRPLANE ON JACKS. CAUTION: DO NOT OPERATE THE BOOST PUMPS WITH THE FUEL LEVEL BELOW 600 POUNDS IN THE INDIVIDUAL WING TANKS. 4. Defuel the airplane. (Refer to the Maintenance Manual, Chapter 12, Fuel - Servicing.) NOTE: It is permissible to defuel the airplane to 600 pounds per wing with the wing fuel boost pumps, then defuel the last 600 pounds in each wing with your best shop practice. 5. 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. 6. Drain all remaining fuel from wing fuel sumps. 7. Remove access panels 512AB, 512BB and 512AZ (left) and 612AB, 612BB and 612AZ (right). (Refer to the Maintenance Manual, Chapter 6, Access Plates and Panel Identification - Description and Operation and Chapter 57, Wing Skin/Access Plates - Description and Operation.) 8. Examine the full length of the wing fuel boost pump wiring, especially near the fuel lines and the wing structure that are close to the wing fuel boost pump wiring. NOTE: Remove the wing fuel boost pump, if necessary, to examine the full length of the wiring. (Refer to the Maintenance Manual, Chapter 28, Fuel Boost Pump - Removal/Installation.) A. Remove the tie strap that is wrapped around the wing fuel boost pump to hold the wires in place. B. (See the illustrations below.) The following conditions are acceptable: No chafing Chafing through the outer jacket Page 3

4 Chafing through the wire braid (shielding) Chafing into the wire insulation, if the wire conductor is not exposed. NOTE: It is acceptable to have chafing at more than one location if the wire conductor is not exposed at any of the chafing locations. C. Apply Type 1, Class B-1/2 Sealant to any damaged areas, that are acceptable, of the wing fuel boost pump wiring. D. Install P Spiral Wrap on the fuel boost pump wiring if an acceptable condition exists. NOTE: Wrap the entire length of the wing fuel boost pump wiring with P Spiral Wrap. The P Spiral Wrap must come within 0.5 inch of the connector and the point that the wiring enters the wing fuel boost pump housing. E. (See the illustration below.) If there is chafing through the outer jacket, the wire braid and the wire insulation with the wire conductor exposed, the wing fuel boost pump must be replaced. Page 4

5 9. Replace the wing fuel boost pump if required. (Refer to the Maintenance Manual, Chapter 28, Fuel Boost Pump - Removal/Installation.) A. Remove the tie strap that is installed on the wing fuel boost pump. B. Install P Spiral Wrap on the fuel boost pump wiring before the wing fuel boost pump is installed. NOTE: Wrap the entire length of the wing fuel boost pump wiring with P Spiral Wrap. The P Spiral Wrap must come within 0.5 inch of the connector and the point that the wiring enters the wing fuel boost pump housing. NOTE: If the wing fuel boost pump must be replaced, complete Steps 10 through 12 before the wing fuel boost pump is installed. 10. (Refer to Figure 1.) Examine the fuel tube that the fuel boost pump wiring may have been chafing on for damage. A. The damage limit for fuel tubes is 20% (0.007 inch) of the wall thickness. (Refer to the Maintenance Manual, Chapter 20, Tubing, Hose and Fluid Fittings - Maintenance Practices.) NOTE: The wall thickness of the fuel tubes that the wing fuel boost pump wiring may come into contact with is inch. B. If the damage to the fuel tube is 20% (0.007 inch) or less, burnish the damaged area with emery cloth or an equivalent, and protect the repaired area with Alodine (Refer to the Structural Repair Manual, Chapter 51, Protective Treatment of Metal.) C. If the damage is greater than 20% (0.007 inch) replace the fuel tube. 11. (Refer to Figure 1.) Examine the wing structure that the wing fuel boost pump wiring may have been chafing on for damage. A. Repair or replace any damage to the wing structure that is found. (Refer to the Structural Repair Manual, Chapter 51, Crack, Scratch, Gouge And Corrosion - Damage Classification.) B. Apply Alodine 1201 to any bare metal that is present. (Refer to the Structural Repair Manual, Chapter 51, Protective Treatment of Metal.) Page 5

6 12. (Refer to Figure 1.) Install one MS Tie Strap around the wing fuel boost pump, wing fuel boost pump wiring and spiral wrap. A. Route the wires from the wing fuel boost pump housing down to the base of the wing fuel boost pump and install a tie strap around the wing fuel boost pump housing and wiring approximately half way down the wing fuel boost pump housing. 13. Install the wing fuel boost pump, if removed. (Refer to the Maintenance Manual, Chapter 28, Fuel Boost Pump - Removal/Installation.) 14. Install the MS21919WDF Clamps to support the wing fuel boost pump wiring. NOTE: The clamp installations in the left and right wing fuel sumps are not the same. A. (Refer to Figure 1, Sheets 1 and 2.) Install the MS21919WDF Clamps in the left wing fuel sump. (1) Install one MS21919WDF12 Clamp on the Line Assembly approximately in the middle of the straight section of the line. (2) Install one MS21919WDF4 Clamp on the wing fuel boost pump wiring. (3) Attach the MS21919WDF12 Clamp to the MS21919WDF4 Clamp with one AN3C20A Bolt, one NAS42DD3-96FC Spacer and one MS Nut. (4) Install one MS21919WDF12 Clamp on the Line Assembly slightly below the mid-point of the straight section of the line. (5) Install one MS21919WDF4 Clamp on the wing fuel boost pump wiring. (6) Attach the MS21919WDF12 Clamp to the MS21919WDF4 Clamp with one AN3C16A Bolt, one NAS42DD3-80FC Spacer and one MS Nut. B. (Refer to Figure 1, Sheets 3 and 4.) Install the MS21919WDF Clamps in the right wing fuel sump. (1) Install one MS21919WDF12 Clamp on the Line Assembly approximately in the middle of the straight section of the line. (2) Install one MS21919WDF4 Clamp on the wing fuel boost pump wiring. (3) Attach the MS21919WDF12 Clamp to the MS21919WDF4 Clamp with one AN3C16A Bolt, one NAS42DD3-80FC Spacer and one MS Nut. (4) Install one MS21919WDF12 Clamp on the Line Assembly slightly below the mid-point of the straight section of the line. (5) Install one MS21919WDF4 Clamp on the wing fuel boost pump wiring. (6) Attach the MS21919WDF12 Clamp to the MS21919WDF4 Clamp with one AN3C16A Bolt, one NAS42DD3-80FC Spacer and one MS Nut. CAUTION: MAKE SURE THAT THE WING FUEL BOOST PUMP WIRING DOES NOT CONTACT THE WING STRUCTURE OR OTHER SYSTEMS COMPONENTS. FAILURE TO FOLLOW THIS STEP WILL CAUSE DAMAGE TO THE WING FUEL BOOST PUMP WIRING. 15. Make sure that the wing fuel boost pump wires will not contact any fuel lines or the airplane structure. A. Apply light hand pressure to the fuel boost pump wires between: The wing fuel boost pump and the first clamp location The first clamp location and the second clamp location The second clamp location and the fuel boost pump connector. Page 6

7 B. The wing fuel boost pump wiring should deflect approximately 0.5 inch. Make sure that the wiring does not touch the fuel system plumbing, wing structure or other systems components. (1) If the wing fuel boost pump wiring does not deflect approximately 0.5 inch adjust the wire routing so that some deflection is present. NOTE: It is acceptable to change the NAS43DD3-64FC Spacer and the AN3C14A Bolt. The spacer is not to exceed 1.5 inches in length and is not to be shorter than 0.75 inch in length. NOTE: It is acceptable to change the NAS43DD3-135FC Spacer and the AN3C25A Bolt. The spacer is not to exceed 2.5 inches in length and is not to be shorter than 1.75 inches in length. CAUTION: IF AN AN3C BOLT IS REPLACED WITH ANOTHER BOLT DO NOT USE A BOLT THAT IS CADMIUM PLATED. THE CADMIUM PLATING WHEN CONTINUOUSLY IN CONTACT WITH JET FUEL WILL DISPERSE CADMIUM FROM THE BOLT INTO THE FUEL SYSTEM WHICH WILL BE DETRIMENTAL TO THE ENGINES. 16. Install the access panels that were removed in Step 7. (Refer to the Maintenance Manual, Chapter 57, Wing Skin/Access Plates - Description and Operation.) 17. After all of the inspection, repair and replacement requirements in this service bulletin have been accomplished, remove the temporary changes from the Approved Airplane Flight Manual. A. Remove the minimum fuel placard that was installed on the instrument panel close to the fuel quantity gage. 18. Remove the warning tags and connect the airplane battery. 19. Record that this service bulletin has been completed. A. Complete a Maintenance Transaction Report. B. Put a copy of the completed Maintenance Transaction Report in the airplane logbook. C. Send a copy of the completed Maintenance Transaction Report to: CESCOM, PO Box 7706, Wichita, KS Page 7

8 MATERIAL INFORMATION NOTE: The parts included in this service bulletin cover installation for one airplane. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION 1 Kit, consisting of the following parts: AN3C16A 3 Bolt None AN3C20A 1 Bolt None MS Nut None MS21919WDF4 4 Clamp None MS21919WDF12 4 Clamp None MS Tie Strap MS NAS43DD3-80FC 3 Spacer None NAS43DD3-96FC 1 Spacer None P Feet Spiral Wrap None 1 Instructions NOTE: (British certified airplanes only.) Order the following part, if necessary, in addition to the above kit. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION EX 1 Fuel Boost Pump Return to Cessna NOTE: (All airplanes that are not British certified.) Order the following part, if necessary, in addition to the above kit. NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION EX 1 Fuel Boost Pump Return to Cessna Page 8

9 Figure 1. Wing Fuel Boost Pump Wiring Modification (Sheet 1) Page 9

10 Figure 1. Wing Fuel Boost Pump Wiring Modification (Sheet 2) Page 10

11 Figure 1. Wing Fuel Boost Pump Wiring Modification (Sheet 3) Page 11

12 Figure 1. Wing Fuel Boost Pump Wiring Modification (Sheet 4) Page 12

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 Approved Airplane Flight Manual. 1. (Prior to the incorporation of this service bulletin.) The airplane must be operated in accordance with the applicable Temporary Changes to the Approved Airplane Flight Manual until all of the inspection, repair and replacement requirements in this service bulletin have been accomplished. 2. (After the incorporation of this service bulletin.) The applicable Temporary Changes in the Model 560 Citation V Approved Airplane Flight Manual or the Model 560 Citation Ultra Approved Airplane Flight Manual must be removed from the flight manual after all of the inspection, repair and replacement requirements in this service bulletin have been accomplished.

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15 TITLE SUPPLEMENTAL DATA FUEL - WING FUEL BOOST PUMP WIRE ROUTING IMPROVEMENT EFFECTIVITY MODEL SERIAL NUMBERS thru MANPOWER MATERIAL - Cost and Availability WORK PHASE MAN-HOURS Modification 11.5 PART NUMBER AVAILABILITY COST * * * 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 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 1 of 2 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A , Fax COPYRIGHT 2004

16 SUPPLEMENTAL DATA WARRANTY CREDIT PROGRAM This bulletin is mandatory. Eligible airplanes may qualify for parts and labor coverage, as described below. Eligibility: Parts Coverage: Labor Coverage: Credit Application: Citations identified within the serial number effectivity of this service bulletin which are within the five year warranty period on the original issue date of this bulletin. 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: Apr 30/2006 Page 2