TITLE ICE AND RAIN PROTECTION - WING ANTI-ICE SYSTEM IMPROVEMENT EFFECTIVITY MODEL SERIAL NUMBERS 525B -0002 thru -0012 The equivalent of this service bulletin has been incorporated on production airplanes -0013 and On. NOTE: This service bulletin may only be accomplished at a Cessna owned or authorized Citation Service Center. REASON The 525B is not approved for flight into known icing conditions. NOTE: After the completion of this service bulletin the 525B will be approved for flight into known icing conditions. DESCRIPTION This service bulletin provides parts and instructions to replace the wing anti-ice printed circuit boards (PCB), add insulation to the wing anti-icing lines and replace the wing anti-ice piccolo tubes. 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 2005
COMPLIANCE RECOMMENDED. This service bulletin should be accomplished at a scheduled maintenance period or phase 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. FLIGHT CREW OPERATIONS Refer to the FAA Approved Airplane Flight Manual, Revision 2 or later. 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 and should be completed within the scheduled time period. 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. Page 2
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 RTV 106 General Electric Company Silicone Products Department Hudson River Road Waterford, NY 12301 Thermal Conductive Grease DC340 Dow Corning Corporation 3901 South Saginaw Road Midland, MI 48640-6030 Loctite 592 Loctite Corporation Newington, CT 06111 High temperature sealing. To coat transducer for contact with the wing skin. To seal the plug in the piccolo tube. TOOLING NAME NUMBER MANUFACTURER USE Brake Bleed Kit Locally Manufactured To remove air from the main landing gear brake hydraulic system. CHANGE IN WEIGHT AND BALANCE MODEL WEIGHT INCREASE RESULTANT MOMENT MOMENT/100 525B 0.34 pounds 107.66 inch pounds 1.08 inch pounds REFERENCES Cessna Model 525B (CJ3) Maintenance Manual All airplanes that will install this service bulletin must obtain the engineering drawings that follow. The latest revision and all applicable DCN's for each document must be used. DOCUMENT NUMBER TITLE 6398017 Wing A/I Insulation Instl Mod 6392380 Piccolo Tube Instl Mod 6318909 Power J-Box Instl 6327300 Hyd Instl -Fwd Wing Fairing PUBLICATIONS AFFECTED Cessna Model 525B (CJ3) Illustrated Parts Catalog Cessna Model 525B (CJ3) FAA Approved Airplane Flight Manual Page 3
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 access panels that follow: (Refer to the Maintenance Manual, Chapter 6, Access Plates And Panels Identification - Description And Operation.) 163AB 163B 163C 163D 165B 164B 164C 164D 166A 321A. 3. Replace the 6318342-25 Anti-Ice Printed Circuit Boards. A. Remove two 6318342-25 Anti-Ice PCBs. (Refer to the Maintenance Manual, Chapter 24, DC Electrical Load Distribution - Maintenance Practices and Cessna Engineering Drawing 6318909.) B. Install two 6318342-29 Anti-Ice PCBs. (Refer to the Maintenance Manual, Chapter 24, DC Electrical Load Distribution - Maintenance Practices and Cessna Engineering Drawing 6318909.) 4. Look for RTV sealant at the wing leading edge under temperature switch. NOTE: This procedure is the same for the left and right wings. A. Remove the wing tip. (Refer to the Maintenance Manual, Chapter 57, Wing Tips - Maintenance Practices.) B. Remove all of the RTV sealant that is around the 1050C Transducer. C. Remove the 1050C Transducer from the inner surface of the leading edge. D. Put the thermal conductive grease on the face of the 1050C Transducer and the area on the wing that the transducer will contact. E. Install the 1050C Transducer in the wing leading edge. F. Install the wing tip. (Refer to the Maintenance Manual, Chapter 57, Wing Tips - Maintenance Practices.) CAUTION: When a hydraulic line or component is disconnected, plug the line and/or fitting immediately. This will prevent the contamination of the system and will reduce the possibility of a system malfunction. 5. Remove the brake accumulator. (Refer to the Maintenance Manual, Chapter 32, Hydraulic Pack Assembly And Accumulator - Maintenance Practices.) NOTE: There is a permanent fitting on the pneumatic line for the hydraulic accumulator. The accumulator removal requires the permanent fitting to be held with a wrench and the accumulator spun off of the fitting. 6. Remove hydraulic lines that follow: (Refer Cessna Engineering Drawing 6327300.) 6327300-2 Tube Assembly Page 4
6327300-3 Tube Assembly 6327300-4 Tube Assembly 6327300-5 Tube Assembly 6327300-6 Tube Assembly 6327300-7 Tube Assembly 6327300-8 Tube Assembly 6327300-10 (airplane -0002) or 6327300-17(-0003 and On) Tube Assembly 6327300-11 Tube Assembly 6327300-16 Tube Assembly. 7. Replace the piccolo tubes. NOTE: The removal and installation procedures are the same for the left and right wings. A. Remove the wing ram air hose from the left and right wings. B. Remove the bleed air line from the piccolo tube. (Refer to the Maintenance Manual, Chapter 30, Airfoil Anti-Ice - Maintenance Practices.) C. Remove any RTV sealant that is around the piccolo tube. D. Remove and keep two MS27039-1-09 Screws from the inboard end of the piccolo tube. E. Gently pull the piccolo tube from the wing leading edge. NOTE: Look at the 6320380-11 (left) or 6320380-12 (right) Piccolo Tubes to determine if the end plug has been installed. If the 6320380-1 Plug has not been installed remove the plugs from the removed piccolo tubes and install the plugs in the 6320380-11 (left) or 6320380-12 (right) Piccolo Tubes with Loctite 592 Adhesive. F. Install the 6320380-11 (left) or 6320380-12 (right) Piccolo Tube in the leading edge. NOTE: There are seven Teflon spacers that hold the piccolo tube in position. Do not attempt to force the piccolo tube into the leading edge. The piccolo tube should route through the spacers when less than moderate force is applied. If a Teflon spacer is broken or damaged the leading edge will have to be removed from the airplane and disassembled to replace the Teflon spacer. G. Install two MS27039-1-09 Screws that were kept to hold the inboard end piccolo tube into position. H. Apply a fillet seal to the inboard end of the piccolo tube and MS27039-1-09 Screws with RTV 106 sealant. I. Install the bleed air line that was removed. (Refer to the Maintenance Manual, Chapter 30, Airfoil Anti-Ice - Maintenance Practices.) 8. Install the hydraulic lines that were removed. (Refer the Maintenance Manual, Chapter 20, Tubing, Hose And Fittings - Maintenance Practices and Cessna Engineering Drawing 6327300.) 9. Install the brake accumulator. (Refer to the Maintenance Manual, Chapter 32, Hydraulic Pack Assembly And Accumulator - Maintenance Practices.) 10. Install the F441659 Insulation on the wing anti-ice lines. (Refer to Cessna Engineering Drawing 6398017.) 11. Remove the warning tags and connect external power to the airplane. 12. Bleed the main landing gear brakes. CAUTION: Do not attempt to back flush or back bleed the brake hydraulic system. Microscopic contamination from the brakes may cause contamination or a malfunction of the anti-skid servo valve. A. Make sure that the BRAKE SYSTEM and SKID CONTROL circuit breakers are disengaged. B. Service the brake accumulator. (Refer to the Maintenance Manual, Chapter 12, Brake Accumulator - Servicing.) Page 5
C. Service the brake system hydraulic reservoir, if necessary. (Refer to the Maintenance Manual, Chapter 12, Brake Reservoir - Servicing.) D. Install the brake bleed lines on the left and right brake assemblies on the highest bleed port of each brake. E. Insert the return hose in to the brake system hydraulic reservoir. F. Release the parking brake, if engaged. G. Apply external power to the airplane. H. Make sure that the ANTI-SKID switch is in the OFF position. I. Engage the BRAKE SYSTEM circuit breaker. J. Look for hydraulic leaks on the lines that were removed. (1) Let the accumulator charge fully. (2) Press the toe of both rudder pedals to apply the left and right brakes and look for leaks around the removed hydraulic lines. (3) Repair any leaks that were found. K. Service the brake system hydraulic reservoir, if necessary. (Refer to the Maintenance Manual, Chapter 12, Brake Reservoir - Servicing.) NOTE: The brake reservoir must have the proper amount of hydraulic fluid at all times while completing the brake bleeding procedure. If the brake system reservoir hydraulic fluid becomes low, stop the brake bleeding procedure to service the reservoir and start the procedure again from Step 12L. L. Press the toe of the left rudder pedal fully and hold for two minutes (minimum). NOTE: If the toe of the rudder pedal is released for any reason the two minutes must be started over. M. Release the toe of the left rudder pedal. N. Press the toe of the right rudder pedal fully and hold for two minutes (minimum). NOTE: If the toe of the rudder pedal is released for any reason the two minutes must be started over. O. Release the toe of the right rudder pedal. P. Press the toe of both rudder pedals fully and hold for one minute (minimum). Q. Release the toe of the rudder pedals. R. Disengage the BRAKE SYSTEM circuit breaker. S. Bleed off the pressure that is in the brake system accumulator with the accumulator bleed lever located on the right forward pressure bulkhead. T. Remove the brake bleed lines. U. Service the brake system hydraulic reservoir, if necessary. (Refer to the Maintenance Manual, Chapter 12, Brake Reservoir - Servicing.) 13. Remove external power and make sure that the airplane battery is connected. 14. Make sure that the anti-ice PCBs work correctly and there are no bleed air leaks on the disturbed connectors. A. Start the engines and move the airplane to a location where the engines can be run at take-off power. B. Move the AIR SOURCE SELECT knob to BOTH. C. Move the TEMPERATURE SELECT knob into the AUTO range. D. Advance the throttles until 75% N 2 is reached. Page 6
E. Make sure that the engine anti-ice works correctly. (1) Record the ITT values. (2) Move the left and right ANTI-ICE/DE-ICE switch to the ENG ON position. NOTE: The engine inlet under temperature switch closes between 50 Fahrenheit (temperature falling) and 70 Fahrenheit (temperature rising). If the ambient air temperature is above 50 Fahrenheit the ENG ANTI-ICE and MASTER CAUTION annunicators may not come on. (3) Make sure that the ITT increases. (4) Make sure that the ENG ANTI-ICE L and ENG ANTI-ICE R annunicators come on and the MASTER CAUTION does not come on. (5) Make sure that the ENG ANTI-ICE L and ENG ANTI-ICE R annunicators goes out in less than one minute. (6) Move the left and right ANTI-ICE/DE-ICE switch to the OFF position. (7) Make sure that the ITT returns to the original value (approximately). F. Make sure that the wing anti-ice works correctly. (1) Record the ITT values. CAUTION: Do not leave the ANTI-ICE/DE-ICE switches on for more than one minute. The wing leading edge can be damaged from the high temperatures of the anti-ice system. The ANTI-ICE/DE-ICE switches can be turned on again for one minute after a five minute cooling period. CAUTION: Turn off the ANTI-ICE/DE-ICE switches immediately if the WING O'HEAT or AIR DUCT O'HEAT annunicators come on at anytime, and allow the components to cool off for five minutes before resuming the procedure. (2) Move the left and right ANTI-ICE/DE-ICE switch to the WING/ENG position. (3) Make sure that the WING ANTI-ICE L and WING ANTI-ICE R annunicators come on and the MASTER CAUTION does not come on. (4) Make sure that the ITT increases. (5) Make sure that hot air is exhausted from the louvers on the lower surface of the left and right wing tips. (6) Make sure that there are no bleed air leaks from the piccolo tubes or the bleed air lines that were removed. (7) Make sure that the pylon ram air scoop on the left and right pylons is warm to the touch. NOTE: The pylon ram air scoop anti-ice is linked to the wing anti-ice system and not to the engine anti-ice system. (8) Make sure that the WING ANTI-ICE L and WING ANTI-ICE R annunicators go out in less than one minute. (9) Move the left and right ANTI-ICE/DE-ICE switches to the OFF position. (10) Make sure that the ITT returns to the original values (approximately). (11) Return the engines to ground idle and allow the leading edges five minutes to cool off. (12) Advance the throttles until 75% N 2 is reached. (13) Move the AIR SOURCE SELECT knob to the L position. (14) Move the ANTI-ICE/DE-ICE cross flow switch to the WING XFLOW position. (15) Move the right ANTI-ICE/DE-ICE switch to the WING/ENG position. Page 7
(16) Make sure that the WING ANTI-ICE L and WING ANTI-ICE R annunicators come on and the MASTER CAUTION does not come on. (17) Make sure that the right engine ITT increases. (18) Make sure that hot air is exhausted from the louvers on the lower surface of the left and right wing tips. (19) Make sure that the WING ANTI-ICE L and WING ANTI-ICE R annunicators go out in less than one minute. (20) Move the right ANTI-ICE/DE-ICE switch to the OFF position. (21) Make sure that the right engine ITT returns to the original value (approximately). (22) Return the engines to ground idle and allow the leading edges five minutes to cool off. (23) Advance the throttles until 75% N 2 is reached. (24) Move the AIR SOURCE SELECT knob to the R position. (25) Move the ANTI-ICE/DE-ICE cross flow switch to the WING XFLOW position. (26) Move the left ANTI-ICE/DE-ICE switch to the WING/ENG position. (27) Make sure that the WING ANTI-ICE L and WING ANTI-ICE R annunicators come on and the MASTER CAUTION does not come on. (28) Make sure that the left engine ITT increases. (29) Make sure that hot air is exhausted from the louvers on the lower surface of the left and right wing tips. (30) Make sure that the WING ANTI-ICE L and WING ANTI-ICE R annunicators go out in less than one minute. (31) Move the left ANTI-ICE/DE-ICE switch to the OFF position. (32) Make sure that the left engine ITT returns to the original values (approximately). (33) Move the ANTI-ICE/DE-ICE cross flow switch to the OFF position. G. Movethethrottlestothegroundidleposition. H. Shutdown the engines. 15. Install the access panels that were removed. (Refer to the Maintenance Manual, Chapter 6, Access Plates And Panels Identification - Description And Operation.) 16. Make sure that Revision 2 or later of the FAA Approved Airplane Flight Manual is placed onboard of the airplane for use by the flight crew. 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, PO Box 7706, Wichita, KS 67277. Page 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: F441659 20 feet Insulation None F840021 1 roll Tape None 6320380-11 1 Piccolo Tube 6320380-9 Discard 6320380-12 1 Piccolo Tube 6320380-10 Discard 6318342-29 2 Anti-Ice PCB 6318342-25 Return to Cessna 1 Instructions Page 9
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. Refer to the FAA Approved Airplane Flight Manual, Revision 2 or later for operational changes resulting from the incorporation of this service bulletin.
TITLE SUPPLEMENTAL DATA ICE AND RAIN PROTECTION - WING ANTI-ICE SYSTEM IMPROVEMENT EFFECTIVITY MODEL SERIAL NUMBERS 525B -0002 thru -0012 The equivalent of this service bulletin has been incorporated on production airplanes -0013 and On. MANPOWER MATERIAL - Cost and Availability WORK PHASE MAN-HOURS Modification 40.0 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 2 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 2005
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: 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 67215 USA Expiration: Jan 31/2007 Page 2