SERVICE BULLETIN REVISION

Transcription

1 Revision 7 REVISION TRANSMITTAL SHEET This sheet transmits Revision 7 to Service Bulletin. A. Replaces the AN960PD10L Washers with NAS1149D0316K Washers. B. Removes the optional Aviation Brake System antiskid statements from the -0 and -1 kits. C. Adds Manufacturer information for the Identification Tape in the CONSUMABLE MATERIAL section NOTE: This revision replaces the original issue of and previous revisions in their 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 Feb 2/1989 Revision 1 Mar 24/1998 Revision 2 Nov 14/1989 Revision 3 Sep 14/1990 Revision 4 Jul 1/1992 Revision 5 Jul7/1993 Revision 6 Feb7/1995 Revision 7 Feb 8/2006

2

3 TITLE LANDING GEAR - BFGOODRICH BRAKES AND WHEELS INSTALLATION EFFECTIVITY MODEL SERIAL NUMBERS 500/ thru except British Certified Airplanes and airplanes equipped with Aviation Brake Systems Limited, STC antiskid brake systems NOTE: This service bulletin is applicable to the following airplanes: 1. Airplanes thru without an optional antiskid brake system or optional skid warning system. 2. Airplanes thru with optional antiskid brake system (factory installed). 3. Airplanes thru with optional service bulletin SB Antiskid Brake System Installation. REASON To provide BFGoodrich brakes and wheels as a replacement for Goodyear or Cleveland (Parker-Hannifin) brakes and wheels. DESCRIPTION This service bulletin provides parts and instructions to install a BFGoodrich brake and wheel on each main landing gear and replace the hydraulic and pneumatic hoses to the brakes. NOTE: The BFGoodrich brakes have a larger total piston area than the Goodyear brakes and are therefore a more powerful brake. The increased braking power may be perceived as excessive and unacceptable sensitivity. NOTE: The BFGoodrich wheel bearings are provided prepacked with MIL-G-3545 grease. MIL-PRF or equivalent grease must be available to coat the axle, threads and axle nut during installation. NOTE: A BFGoodrich brake and wheel must be installed on both the left and right main landing gears during accomplishment of this service bulletin. Do not operate the airplane with one BFGoodrich brake and wheel on one side and one Goodyear or Cleveland (Parker-Hannifin) brake and wheel on the other side. COMPLIANCE OPTIONAL. This service bulletin may be accomplished at the discretion of the owner. FLIGHT CREW OPERATIONS No Change. Revision 7 - Feb 8/2006 Page 1 of 10 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A , Fax COPYRIGHT 1989

4 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 WORK PHASE MAN-HOURS Installation * MATERIAL - Cost and Availability PART NUMBER AVAILABILITY COST -0 * * -1 * * * 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 Identification Tape RH BRAKE Identification Tape LH BRAKE Identification Tape AUX BRAKE CM CM CM Cessna Aircraft Company, Citation Marketing Division Department 579 PO Box 7706 Wichita, KS Cessna Aircraft Company, Citation Marketing Division Department 579 PO Box 7706 Wichita, KS Cessna Aircraft Company, Citation Marketing Division Department 579 PO Box 7706 Wichita, KS To identify the right hand brake hose. To identify the left hand brake hose. To identify the auxiliary brake hose. TOOLING A 2 1/8 inch socket that is adaptable to a torque wrench will be required to install the axle nut. A socket such as a MAC Tools Incorporated Z682 Socket will be satisfactory. Revision 7 - Feb 8/2006 Page 2

5 CHANGE IN WEIGHT AND BALANCE MODEL 500/ /501 Airplanes thru not incorporating SB32-1 or SB32-12 Airplanes thru and airplanes thru incorporating SB32-1 or SB32-12 WEIGHT INCREASE No Change RESULTANT MOMENT 5054 Inch-Pounds MOMENT/ Inch-Pounds REFERENCES Cessna Model 500 Citation/Citation I Maintenance Manual Cessna Model 500 Series Structural Repair Manual BFGoodrich Aerospace and Defense Division Part Number JN45927/175 Component Maintenance Manual, dated 30 November 1988 or later revision. PUBLICATIONS AFFECTED Cessna Model 500 Citation/Citation I Maintenance Manual Cessna Model 500 Citation/Citation I 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. Raise the airplane on jacks until the tires are clear of the ground. (Refer to the Maintenance Manual, Chapter 7, Lifting - Maintenance Practices.) 3. (Airplanes equipped with an antiskid brake system.) Place the ANTI-SKID control switch in the OFF position and disengage the SKID CONTROL circuit breaker (located on the left circuit breaker panel). 4. Attach a warning tag to the emergency brake control handle and brake pedals stating: WARNING: DO NOT OPERATE, MAINTENANCE IN PROGRESS 5. Release the parking brake, if applied. 6. Remove the wheel and tire from the left main landing gear. (Refer to the Maintenance Manual, Chapter 32, Main Gear Wheels - Maintenance Practices.) Revision 7 - Feb 8/2006 Page 3

6 CAUTION: READ AND OBSERVE THE PHOSPHATE ESTER SAFETY PRECAUTIONS AND TECHNICAL PRECAUTIONS REGARDING HYDRAULIC FLUID. REFER TO THE MAINTENANCE MANUAL, CHAPTER 29, GENERAL - MAINTENANCE PRACTICES FOR THESE PRECAUTIONS. 7. (Refer to Figure 1.) Disconnect the hydraulic hose and the pneumatic hose from the fittings located on the main landing gear drag brace. Cap the fittings to prevent entry of foreign material. Cut all tie straps that secure the hydraulic and pneumatic hoses to the wire bundle and ground strap as they route to the brake assembly. Remove the screw that secures the ground strap to the brake assembly and discard the screw. Cut the safety wire connecting the strut service valve to the brake. 8. Remove the brake assembly from the main landing gear. Remove the clamp from the hydraulic and pneumatic hoses. Retain clamp for reinstallation. Discard the clamp hardware and the old hydraulic and pneumatic hoses. 9. Clean the main landing gear strut and axle to remove all dirt, grease and residue with Stoddard solvent or an equivalent. Apply a light coat of MIL-PRF or equivalent grease to the axle in the area where the brake assembly will contact the axle. 10. Select the brake assembly with the shuttle valve (hydraulic and pneumatic hose attachment) positioned so that it will be on the aft side when installed. Install the brake assembly onto the main landing gear axle. NOTE: Utilize the Brake Assembly (BFGoodrich part number ) on airplanes without an antiskid brake system. Utilize the Brake Assembly (BFGoodrich part number ) on airplanes with an antiskid brake system. 11. Remove the Union Fitting installed in the upper port (hydraulic) of the brake assembly and install a Union Fitting with new O-ring (provided with union fitting), lubricated with hydraulic fluid, in the port. A. (Airplanes without antiskid brakes) Connect the new AE E0150 or 124K001-4CL-0150 Hose Assembly (hydraulic) to the Union Fitting and the fitting (aft) mounted on the drag brace. B. (Airplanes with antiskid brakes) Connect the new AE E0150 or 124K001-4CL-0150 Hose Assembly (hydraulic) to the Union Fitting and the fitting (aft) mounted on the drag brace. C. Install CM RH BRAKE or CM LH BRAKE identification tape onto the hose assembly, as applicable. 12. Install the new AE E0154 or 124K001-4CL-0154 Hose Assembly (pneumatic) and connect from the union fitting installed in the brake lower port (pneumatic) to the fitting (forward) mounted on the drag brace. Install CM AUX BRAKE identification tape to the hose assembly. 13. Install the clamp on the hose assemblies at mid-span with a new MS Screw, AN960PD10L Washer and MS21044N3 Nut. 14. (Refer to Figure 1, Sheet 2.) Remove the paint from the area under the ground strap attach point. Apply chemical film treatment to the bare aluminum. (Refer to the Structural Repair Manual, Chapter 51 Protective Treatment of Metal.) Connect the ground strap to the brake assembly with a MS Screw at the location shown. Touch up any exposed unpainted areas and install safety wire from the screw to the strut service valve. 15. Route the wire bundle and ground strap along the hoses and secure at two-inch intervals with MS Tie Straps. 16. Mount the tire and assemble the Wheel (BFGoodrich part number ) in accordance with the procedures defined in Component Maintenance Manual (BFGoodrich Aerospace and Defense Division). NOTE: The existing tire may be used (if in serviceable condition), or a new 220K08-2 (Goodyear), as defined in the Illustrated Parts Catalog, or a Tire. 17. Install a or Placard on the wheel as defined in the table below. Clean an area on the wheel with isopropyl alcohol and install the placard as shown in Figure 2. Revision 7 - Feb 8/2006 Page 4

7 Placard Part Number Airplane Availability Inflation Pressure thru except airplanes incorporation SB thru and airplanes thru incorporating SB PSIG +3 or -1 PSIG at 70 F 100 PSIG ±5 PSIG at 70 F 18. (Refer to Figure 2.) The wheel bearings are provided prepacked with MIL-G-3545 grease and are installed in the wheel with seals and snap rings. Disassembly of these parts is not required prior to installation of the wheel. Install the Wheel (BFGoodrich part number ) with Tire installed onto the main landing gear axle as follows: A. Apply a thin coating of MIL-PRF or equivalent grease to the main landing gear axle and slide the spacer (provided with the brake assembly) onto the axle. NOTE: Do not allow grease to contact brake carriers and stators. B. Carefully align the drive tangs on the outside of the brake rotating discs with the wheel key slots and slide the wheel onto the axle. C. Tighten axle nut to 40 foot-pounds of torque while rotating the wheel. D. Back off the axle nut to zero inch-pounds of torque but with wheel and bearings still seated. E. Torque nut to 20 foot-pounds while rotating the wheel. F. If not at position to install locking screws, advance axle nut to nearest locking location and install screws engaging antiskid transducer (if installed). 19. Install Hubcap as follows: NOTE: Utilize the Hubcap Kit on airplanes without an antiskid brake system. Utilize the Hubcap Kit on airplanes with an antiskid brake system. A. Clean mating surfaces of wheel and hubcap with methyl ethyl ketone (MEK) and wipe dry. B. Apply a thin coating of RTV106 Adhesive Sealant to the hubcap mating surface on the wheel (except do not apply any sealant to the bolt lug portion of the hubcap mounting area to facilitate removal). Install the hubcap using the bolts and washers provided with the hubcap and tighten to 60 to 70 inch-pounds of torque. Install safety wire to secure the three bolts in place. NOTE: (Airplanes equipped with antiskid brake systems) Ensure the drive clip in hubcap engages and aligns properly with the antiskid transducer drive tang. 20. Repeat Steps 6 thru 19 for the right main landing gear wheel and brake. 21. Service the tires with nitrogen. (Refer to the Maintenance Manual, Chapter 12, Tires - Servicing.) 22. Remove all warning tags and connect the airplane to external electrical and hydraulic power. CAUTION: CYCLE THE LANDING GEAR VERY SLOWLY THE FIRST FEW TIMES TO CHECK FOR PROPER CLEARANCE OF LANDING GEAR COMPONENTS. BE PREPARED TO STOP LANDING GEAR MOVEMENT IF INTERFERENCE IS DISCOVERED. 23. Perform a landing gear operational test to ensure proper clearance exists for all landing gear components in the wheel well. A. Check for proper clearance of the brake hoses in the wheel well during retraction. If hoses contact the wheel well, reposition the hose clamp and hoses as necessary to achieve proper clearance. Revision 7 - Feb 8/2006 Page 5

8 WARNING: THE NEW BRAKES HAVE TWO (2) BLEEDER PORTS AND BOTH MUST BE USED IN THE BLEEDING PROCESS OR SENSITIVE OPERATION CHARACTERISTICS WILL RESULT. CAUTION: WHEN BLEEDING THE BRAKES, DO NOT USE THE METHOD WHERE HYDRAULIC FLUID IS PUMPED INTO THE SYSTEM AT THE BRAKE BLEEDER PORT. THIS METHOD MAY FLUSH CONTAMINANTS FROM THE BRAKE INTO THE HYDRAULIC SYSTEM. 24. Bleed the brakes. A. Airplanes without an antiskid brake system. (Refer to the Maintenance Manual, Chapter 32, Main Gear Wheel and Brake - Maintenance Practices.) B. Airplanes with an antiskid system. (Refer to the Maintenance Manual, Chapter 32, Power Brake Antiskid System - Maintenance Practices.) 25. Perform an emergency brake operational test by operating the emergency brake control handle and checking for braking action by attempting to manually rotate the tires on the left and right sides. 26. Service the pneumatic storage bottle. (Refer to the Maintenance Manual, Chapter 12, Gear and Brake Pneumatic System Servicing.) 27. Bleed the brakes again. A. Airplanes without an antiskid brake system. (Refer to the Maintenance Manual, Chapter 32, Main Gear Wheel and Brake - Maintenance Practices.) B. Airplanes with an antiskid system. (Refer to the Maintenance Manual, Chapter 32, Power Brake Antiskid System - Maintenance Practices.) 28. Lower the airplane from jacks. (Refer to the Maintenance Manual, Chapter 7, Lifting - Maintenance Practices for instructions for lowering the airplane. CAUTION: THE FOLLOWING PROCEDURE MUST ONLY BE ATTEMPTED BY A QUALIFIED PILOT WHO IS FAMILIAR WITH THE PROPER FIELD LENGTHS REQUIRED FOR VARIOUS ACCELERATION AND STOP DISTANCES. OPERATE THE AIRPLANE IN ACCORDANCE WITH THE FAA APPROVED AIRPLANE FLIGHT MANUAL. 29. Perform an operational test of the brakes. From a speed of approximately 80 knots, apply brakes firmly but not excessively and hold pedal force until the airplane decelerates to a safe taxi speed. NOTE: No other brake burn in, other than that defined above, is required for the brakes. 30. 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 MATERIAL INFORMATION NOTE: The parts included in this service bulletin cover installation for one airplane. For airplanes thru not incorporating: Optional antiskid brake system (factory installed on airplanes thru -0689), or optional service bulletin SB Antiskid Brake System Installation. Order the following kit. Revision 7 - Feb 8/2006 Page 6

9 NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION -0 1 Kit, consisting of the following AE E0150 (Alternate124K001-4CL0150) 2 parts: Hose Assembly (Hydraulic) AE E0154 Discard AE E0154 (Alternate124K001-4CL0154) 2 Hose Assembly (Pneumatic) AE E0157 Discard NAS1149D0316K 2 Washer MS21044N3 2 Nut MS Screw MS Tie Strap MS Screw Hubcap Kit Placard Placard Wheel Assembly , or , or , or Brake Assembly , or , or , or , or , or , or Instructions NOTE: The parts included in this service bulletin cover installation for one airplane. NEW P/N For airplanes thru incorporating: Optional antiskid brake system (factory installed on airplanes thru -0689), or optional service bulletin SB Antiskid Brake System Installation. Order the following kit. QUAN- TITY Return to Cessna fo credit Return to Cessna fo credit KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION -1 1 Kit, consisting of the following parts: AE E0150 (Alternate124K001-4CL0150) 2 Hose Assembly (Hydraulic) AE E0154 Discard AE E0154 (Alternate124K001-4CL0154) NAS1149D0316K 2 Washer MS21044N3 2 Nut MS Screw 2 Hose Assembly (Pneumatic) AE E0157 Discard Revision 7 - Feb 8/2006 Page 7

10 NEW P/N QUAN- TITY KEY WORD OLD P/N INSTRUCTIONS/ DISPOSITION MS Tie Strap MS Screw Union Fitting (Includes O-Ring) Hubcap Kit Hubcap Kit Placard Placard Wheel Assembly , or , or , or Brake Assembly , or , or , or , or , or , or Instructions Return to Cessna for credit Return to Cessna for credit Revision 7 - Feb 8/2006 Page 8

11 Figure 1. Brake Assembly Installation (Sheet 1) Revision 7 - Feb 8/2006 Page 9

12 Figure 2. Wheel Assembly Installation (Sheet 1) Revision 7 - Feb 8/2006 Page 10

13 TITLE SUPPLEMENTAL DATA LANDING GEAR - BFGOODRICH BRAKES AND WHEELS INSTALLATION EFFECTIVITY MODEL SERIAL NUMBERS 500/ thru except British Certified Airplanes and airplanes equipped with Aviation Brake Systems Limited, STC antiskid brake systems NOTE: This service bulletin is applicable to the following airplanes: 1. Airplanes thru without an optional antiskid brake system or optional skid warning system. 2. Airplanes thru with optional antiskid brake system (factory installed). 3. Airplanes thru with optional service bulletin SB Antiskid Brake System Installation. MANPOWER WORK PHASE Installation MAN-HOURS As Required MATERIAL - Cost and Availability PART NUMBER AVAILABILITY COST -0 * * -1 * * * 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. Oct 10/ Revision 6 - Feb 8/2006 Page 1 of 1 Cessna Aircraft Company, Citation Marketing Division, P.O. Box 7706, Wichita, KS 67277, U.S.A , Fax COPYRIGHT 1989

14