Revision 1 REVISION TRANSMITTAL SHEET This sheet transmits Revision 1 to. A. Adds Sheet 4 to Figure 1. B. Adds instructions to make the cutouts in the stiffener on the upper engine cowl larger. NOTE: This revision replaces the original issue of in its entirety. NOTE: Change bars and pointing hands are not used in this publication to denote revised material. This transmittal sheet provides a complete description of the changes made by this revision, except for editorial changes. REVISION COMPLIANCE NO EFFECT. Airplanes previously modified by this service bulletin are not affected by this revision. SUMMARY OF REVISIONS Original Issue Revision 1 Nov 24/2004
TITLE POWER PLANT - UPPER ENGINE COWL SUPPORT MODIFICATION EFFECTIVITY MODEL SERIAL NUMBERS 525A -0001 thru -0158 The equivalent of this service bulletin has been incorporated on production airplanes -0159 and On. NOTE: This Service Bulletin should be accomplished at a Cessna-owned or an authorized Citation Service Center, because of the unique tooling requirements. REASON To improve the fit between the engine pylon skin and upper engine cowl. DESCRIPTION This service bulletin provides parts and instructions to add a bracket assembly to the engine and a fastener to the upper engine cowl. COMPLIANCE OPTIONAL. This service bulletin may be accomplished at the discretion of the owner. A service bulletin published by Cessna Aircraft Company may be recorded as completed in an aircraft log only when the following requirements are satisfied: 1) The mechanic must complete all of the instructions in the service bulletin, including the intent therein. 2) The mechanic must correctly use and install all applicable parts supplied with the service bulletin kit. Only with written authorization from Cessna Aircraft Company can substitute parts or rebuilt parts be used to replace new parts. 3) The mechanic or airplane owner must use the technical data in the service bulletin only as approved and published. 4) The mechanic or airplane owner must apply the information in the service bulletin only to aircraft serial numbers identified in the Effectivity section of the bulletin. 5) The mechanic or airplane owner must use maintenance practices that are identified as acceptable standard practices in the aviation industry and governmental regulations. No individual or corporate organization other than Cessna Aircraft Company is authorized to make or apply any changes to a Cessna-issued service bulletin, service letter, or flight manual supplement without prior written consent from Cessna Aircraft Company. Cessna Aircraft Company is not responsible for the quality of maintenance performed to comply with this document, unless the maintenance is accomplished at a Cessna-owned Citation Service Center. FLIGHT CREW OPERATIONS No Change. Revision 1 - Nov 24/2004 Page 1 of 9 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-6000, Fax 1-316-517-8500 COPYRIGHT 2004
APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. This information shall be considered an amendment to the Cessna Manufacturer's Maintenance Manual. MANPOWER MATERIAL - Cost and Availability WORK PHASE MAN-HOURS Modification * PART NUMBER AVAILABILITY COST * * * 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 Color Chemical Film Treatment Corrosion-Resistant Primer Alodine 1201 Henkel (Parker Amchem) 32100 Stephenson Highway Madison Heights, MI 48071 513 x 419 PRC - Desoto International 5430 San Fernando Road Glendale, CA 91209 To protect the bare aluminum. To protect against corrosion and prepare surface for final finish. TOOLING NAME NUMBER MANUFACTURER USE Dimple Set 140 x 0.656 inch TR8228 and TR6145 Cessna Aircraft Company Department 166 PO Box 7706 Wichita, KS 67277 To dimple the upper engine cowl. CHANGE IN WEIGHT AND BALANCE MODEL WEIGHT INCREASE RESULTANT MOMENT MOMENT/100 525A 0.57 pounds 213.04 inch pounds 2.13 inch pounds REFERENCES Cessna Model 525A CJ2 Maintenance Manual Cessna Model 525A CJ2 Citation Structural Repair Manual Revision 1 - Nov 24/2004 Page 2
PUBLICATIONS AFFECTED Cessna Model 525A CJ2 Illustrated Parts Catalog ACCOMPLISHMENT INSTRUCTIONS 1. Prepare the airplane for maintenance. A. Make sure that all switches are in the OFF/NORM position. B. Disconnect electrical power from the airplane. (1) Disconnect the airplane battery. (2) Disconnect external electrical power. C. Attach maintenance warning tags to the battery and external power receptacle that have "DO NOT CONNECT ELECTRICAL POWER - MAINTENANCE IN PROGRESS" writtenonthem. 2. Remove the upper and lower engine cowl from the left engine. (Refer to the Maintenance Manual, Chapter 71, Engine Cowling - Maintenance Practices.) 3. (Refer to Figure 1, Sheet 4.) Cut the 6352700 Stiffener (if installed). A. Make the forward cutout larger. (1) Make the forward cutout 3.2 inches. (2) Make the cutout flushwiththeflanges of the stiffener. NOTE: The original cutouts will not be flush with the flanges of the stiffener. (3) Make the radii 0.16 inch. (4) Treat the bare material with color chemical film and corrosion resistant primer. B. Make the aft cutout larger. (1) Make the aft cutout 3.7 inches (2) Make the cutout flushwiththeflanges of the stiffener. NOTE: The original cutouts will not be flush with the flanges of the stiffener. (3) Make the radii 0.16 inch. (4) Treat the bare material with color chemical film and corrosion resistant primer. 4. Install the cowl bracket assemblies. A. (Refer to Figure 1, Sheet 2, View B-B.) Install the forward bracket assembly. (1) Install the 6352500-29 Engine Side Bracket on the inboard side of the engine and on the forward side of where the interstage housing and the fan case are bolted together. (a) Remove and keep two bolts, nuts and washers from the interstage housing and fan case flanges. (b) Install the 6352500-29 Engine Side Bracket with the kept hardware. (c) Lubricate the hardware from the engine with engine oil before installation. (d) Torque the hardware 25 to 28 inch-pounds. (2) Install one 6352500-30 Cowl Bracket Assembly with one AN3-3A Bolt, one NAS1149F0332P Washer and one MS21046C3 Nut through the 6352500-30 Cowl Bracket Assembly and the hole in the 6352500-29 Side Engine Bracket. NOTE: Tighten the hardware so the 6352500-30 Cowl Bracket Assembly can be moved by hand, but sufficiently tight to maintain a set position. Revision 1 - Nov 24/2004 Page 3
(3) Adjust the position of the 6352500-30 Cowl Bracket Assembly to make it approximately flush with the engine channel mount. B. (Refer to Figure 1, Sheet 3, View C-C.) Install the aft bracket assembly. (1) Install the 6352500-33 Left Aft Bracket on the inboard side of the engine and on the aft side of where the interstage housing and the diffuser case are bolted together. (a) Remove and keep two bolts, nuts and washers from the interstage housing and fan case flanges. (b) Install the 6352500-33 Left Aft Bracket with the kept hardware. (c) Lubricate the hardware from the engine with engine oil before installation. (d) Torque the hardware 25 to 28 inch-pounds. (2) Install one 6352500-30 Cowl Bracket Assembly with one AN3-3A Bolt, one NAS1149F0332P Washer and one MS21046C3 Nut through the 6352500-30 Cowl Bracket Assembly and the hole in the 6352500-33 Left Aft Bracket. NOTE: Tighten the hardware so the 6352500-30 Cowl Bracket Assembly can be moved by hand, but sufficiently tight to maintain a set position. (3) Adjust the position of the 6352500-30 Cowl Bracket Assembly to make it approximately flush with the engine channel mount. (4) Install the upper engine cowl. (Refer to the Maintenance Manual, Chapter 71, Engine Cowling - Maintenance Practices.) C. Adjust the position of the 6352500-30 Cowl Bracket Assemblies to hold the fire seal on the upper engine cowl is tight against the pylon. D. Apply a clamping device or identify the location of the hole in the 6352500-29 Engine Side Bracket on the 63525500-30 Cowl Bracket Assembly. E. Apply a clamping device or identify the location of the hole in the 6352500-33 Left Aft Bracket on the 6352500-30 Cowl Bracket Assembly. F. Remove the upper engine cowl. (Refer to the Maintenance Manual, Chapter 71, Engine Cowling - Maintenance Practices.) G. Drill one 13/64 (0.203)-inch diameter hole through the 6352500-30 Cowl Bracket Assembly to align with the slot in the 6352500-29 Side Engine Bracket. H. Drill one 13/64 (0.203)-inch diameter hole through the 6352500-30 Cowl Bracket Assembly to align with the slot in the 6352500-33 Left Aft Bracket Assembly. I. Deburr the edges of the drilled holes. J. Apply color chemical film treatment to any bare material. (Refer to the Structural Repair Manual, Chapter 51, Protective Treatment of Metal.) K. Install one AN3-3A Bolt, one NAS1149F0332P Washer and one MS21046C3 Nut through the 6352500-30 Cowl Bracket Assembly and the 6352500-29 Side Engine Bracket. L. Install one AN3-3A Bolt, one NAS1149F0332P Washer and one MS21046C3 Nut through the 6352500-30 Cowl Bracket Assembly and the 6352500-33 Left Aft Bracket. 5. (Refer to Figure 1, Sheet 1, View A-A.) Drill two holes in the upper engine cowl. A. Install the upper engine cowl. (Refer to the Maintenance Manual, Chapter 71, Engine Cowling - Maintenance Practices.) B. Identify the location of the holes to be drilled through the upper engine cowl. C. Remove the upper engine cowl. (Refer to the Maintenance Manual, Chapter 71, Engine Cowling - Maintenance Practices.) Revision 1 - Nov 24/2004 Page 4
D. Drill two 0.473-inch diameter holes in the upper engine cowl to match the 6352500-30 Cowl Bracket Assemblies. E. Deburr the drilled holes. F. Dimple the two drilled holes 140 x 0.656-inch diameter. NOTE: Use a squeeze that uses a linear motion (such as a C squeeze). Do not use a squeeze that uses an arch motion (such as an A squeeze). If an arch motion squeeze is used, it will damage the dimple dies. G. Apply color chemical film treatment to any bare aluminum. (Refer to the Structural Repair Manual, Chapter 51, Protective Treatment of Metal.) H. Apply corrosion-resistant primer to the area treated with color chemical film treatment. (Refer to the Structural Repair Manual, Chapter 51, Protective Treatment of Metal.) I. Install two S2319-63 Grommets with two CM2791-2 Snap Rings in the dimpled holes. J. Install one S3412-103 Fastener in each S2319-63 Grommet. 6. Install the upper and lower engine cowl on the left engine. (Refer to the Maintenance Manual, Chapter 71, Engine Cowling - Maintenance Practices.) 7. Do Steps 2 through 6 for the right engine and engine cowl. 8. 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 67277. 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: AN3-3A 8 Bolt None CM2791-2 4 Snap Ring None MS21046C3 8 Nut None NAS1149F0332P 8 Washer None S2319-63 4 Grommet None S3412-103 4 Fastener None 6352500-29 2 Side Engine Bracket (FWD) None 6352500-30 4 Cowl Bracket Assembly None 6352500-32 1 Aft Bracket (Right) None 6352500-33 1 Aft Bracket (Left) None 1 Instructions Revision 1 - Nov 24/2004 Page 5
Figure 1. Upper Engine Cowl Support (Sheet 1) Revision 1 - Nov 24/2004 Page 6
Figure 1. Upper Engine Cowl Support (Sheet 2) Revision 1 - Nov 24/2004 Page 7
Figure 1. Upper Engine Cowl Support (Sheet 3) Revision 1 - Nov 24/2004 Page 8
Figure 1. Upper Engine Cowl Support (Sheet 4) Revision 1 - Nov 24/2004 Page 9
TITLE SUPPLEMENTAL DATA POWER PLANT - UPPER ENGINE COWL SUPPORT MODIFICATION EFFECTIVITY MODEL SERIAL NUMBERS 525A -0001 thru -0158 The equivalent of this service bulletin has been incorporated on production airplanes -0159 and On. MANPOWER WORK PHASE Modification MAN-HOURS As Required MATERIAL - Cost and Availability PART NUMBER AVAILABILITY COST * * * Please contact Citation Parts Distribution for current cost and availability of parts listed in this service bulletin. Phone at 1-800-835-4000 (Domestic) or 1-316-517-7542 (International). Send Email to: citationparts@cessna.textron.com or telefax at 1-316-517-7711. Based on availability and lead times, parts may require advanced scheduling. In cases where the required part(s) are available as exchange, order the exchange part and, upon completion, expedite the return of the removed core to avoid return penalties. Contact the Citation Parts Distribution Sales Desk for availability of exchange parts. Page 1 of 1 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-6000, Fax 1-316-517-8500 COPYRIGHT 2004