IM199-110 INSTALLATION MANUAL WITH IPL FOR CONVERSION KIT PART NO. 199-110

wheel and brake assemblies. 3.0 PRODUCT REGISTRATION The product registration card is located at the front of this manual. The card is our way of tracking the conversion kits and your guarantee of receiving any future airworthiness information applicable to Conversion Kit No. 199-110. Please fill out the registration card completely and return promptly. Postage is prepaid. 4.0 KIT APPLICABILITY NOTE: Service bulletins, service letters and similar documentation issued by the airframe manufacturer or other STC installations can affect the installation of Conversion Kit No. 199-110. Contact the airframe manufacturer for documentation applicable to your model aircraft and review the maintenance log for any other STC’s installed for their compatibility before installing Conversion Kit No. 199-110. IM199-110 INSTALLATION MANUAL WITH IPL FOR CONVERSION KIT PART NO. 199-110 Page 2 June 18, 2010 The equipment supplied as Kit No. 199-110 is applicable to the following Beech model aircraft under the listed STC. NOTE: For those aircraft equipped with Beech brake deice system; use of 199-168 Hot Air Manifold Kit is required. Table 1 Kit Applicability MAKE STC MODELS Beech Aircraft with standard gear SA646GL 99, 99A, A99A, B99, C99, 100, A100, B100 SA650GL F90 SA890GL 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT, B200T, B200GT, B200CGT 4.1 KIT EQUIPMENT Refer to paragraph 14.0 for the kit parts list. NOTE: Review this installation manual and the installation drawing, number 50-79, completely before removal of existing original equipment and installation of 199-110 kit equipment. The following hardware is not included in the 199-110 Conversion Kit: - Axle nut, washer and cotter pin. 5.0 SAFETY Follow proper safety precautions when servicing aircraft braking systems. A “SAFETY WARNING” flagged by this symbol , calls attention to possible serious or life threatening situations if procedures are not followed. A “WARNING” calls attention to use of materials, processes, methods, procedures, or limits which must be followed precisely to avoid injury to persons. A “CAUTION” calls attention to methods and procedures that must be followed to avoid damage to equipment. A “NOTE” calls attention to an essential operating or maintenance procedure, condition, or statement, which must be highlighted. IM199-110 INSTALLATION MANUAL WITH IPL FOR CONVERSION KIT PART NO. 199-110 Page 3 August 10, 2004 6.0 ORDER INFORMATION To order spare parts, contact the nearest Parker Hannifin, Aircraft Wheel and Brake distributor in your area, or contact Aircraft Wheel and Brake at the following address or numbers: Parker Hannifin Corporation Website: www.parker.com/cleveland Aircraft Wheel & Brake Division E-mail: techhelp@parker.com 1160 Center Road Fax: (440) 937-5409 Avon, Ohio 44011 U.S.A. Tel: 1-800-BRAKING (1-800-272-5464) Attn: Technical Services/Hotline (440) 937-1315 7.0 EQUIPMENT DESCRIPTION 7.1 BRAKE ASSEMBLY For a complete parts breakdown of the brake assembly, refer to CM30-146 Maintenance Manual. The brake is a dual caliper, four piston external disc design, with sintered metallic lining. It is suitable for use with brake fluid conforming to MIL-H-5606. 7.2 WHEEL ASSEMBLY For a complete parts breakdown of the wheel assembly, refer to CM40-289, Maintenance Manual. The wheel is cast aluminum and conforms to all tire and rim association standards for an 18 x 5.5 divided type wheel, suitable for use with all 18 x 5.5, 10 ply tubeless tires. 8.0 GENERAL INFORMATION a. The brakes are shipped from the factory as a complete assembly. Relocate the bleeder components and the fitting assembly to the necessary ports for left hand or right hand installation. The brakes are equipped with 7/16-20 UNF–3B ports. b. The wheels are shipped from the factory as a complete assembly. The bearing cones are packed with grease and installed in the wheel halves. NOTE: Extended storage (longer than two years) of lubricated bearings will require re- lubrication. Refer to paragraph 8.1 for grease packing procedure. IM199-110 INSTALLATION MANUAL WITH IPL FOR CONVERSION KIT PART NO. 199-110 Page 4 August 10, 2004 8.1 BEARING CONE GREASE PACKING PROCEDURE The proper application of grease to the tapered roller bearing will reduce friction, dissipate heat and maintain a rust and corrosion proof coating on the operating surfaces of the roller bearings. CAUTION: USE GREASE CONFORMING TO MIL-PRF-81322 GRADE 2 OR DOD-G- 24508A; OR USE MOBILE AVIATION GREASE SHC 100. DO NOT MIX THE GREASES WITH EACH OTHER. MIXING THE GREASE CAN DECREASE GREASE PERFORMANCE AND CAUSE FAILURE OF THE BEARING. NOTE: To prevent foreign matter contamination, clean and pack bearing cones just before installing or clean and pack bearing cones and store cones in a protective container until ready to install. NOTE: Packing bearing cones with grease is best performed by mechanical means such as a bearing greaser. a. If necessary, clean the bearing cones in mineral spirits. Make sure the bearing cones are completely dry before packing them with grease. b. Refer to Figure 1 and pack the bearing cone with grease. c. Force the grease up between rollers, cone and cage, making sure that all voids inside the cone are filled (see Figure 1). Also, make sure that a generous amount of grease is applied to the roller surfaces on the outside of the cone. NOTE: Shaded area indicates the recommended amount of grease. Figure 1, Packing Bearing Cones IM199-110 INSTALLATION MANUAL WITH IPL FOR CONVERSION KIT PART NO. 199-110 Page 5 August 10, 2004 9.0 KIT INSTALLATION Read this installation manual and look at the installation drawing, 50-79, before removing and installing components. SAFETY WARNING: INSURE AIRCRAFT IS SECURE AND STABLE BEFORE BEGINNING ANY WORK. WORKING UNDER AN IMPROPERLY STABILIZED AIRCRAFT CAN CAUSE INJURY OR DEATH. SAFETY WARNING: COMPLETELY DEFLATE THE TIRE BEFORE REMOVING THE VALVE CORE. VALVE CORES UNDER PRESSURE CAN BE EJECTED LIKE A BULLET AND CAUSE INJURY OR DEATH. NOTE: If aircraft is equipped with brake de-ice, refer to 199-168 Hot Air Manifold Installation Kit for installation instructions. 9.1 REMOVE ORIGINAL EQUIPMENT CAUTION: ALWAYS CHECK THE CONDITION OF ORIGINAL EQUIPMENT HARDWARE THAT WILL BE RETAINED SUCH AS FITTINGS, AXLE NUTS, ETC. REPLACE THESE ITEMS AS NEEDED. a. Properly raise and support the aircraft off the ground following the airframe manufacturer’s instructions. b. Remove the cap from the tire inflation valve and slowly deflate the tire. c. Confirm that the tire is completely deflated. d. When all the tire pressure has been released, remove the valve core from the inside of the valve stem. NOTE: The cotter pin is not supplied as part of the 199-110 kit and must be obtained separately. Refer to the airframe parts catalog for the part number and the quantity. e. Remove and retain the axle nut and washer. Discard the cotter pin. f. Remove the original equipment main landing gear wheels from the axle. g. Disconnect, remove and cap the hydraulic lines from existing brakes. Next, remove the existing hose assembly and cap upper line at the AN837-4D elbow. h. Remove the original equipment brake assemblies from the axle. IM199-110 INSTALLATION MANUAL WITH IPL FOR CONVERSION KIT PART NO. 199-110 Page 6 August 10, 2004 9.2 INSTALL CLEVELAND EQUIPMENT Refer to installation drawing, 50-79, for item number identification. There are two wheel assemblies and two brake assemblies per gear leg. The following instructions are per assembly. 9.2.1 Mount Tubeless Tire a. Remove all six nuts, item 12, twelve washers, item 11, and six bolts, item 10, and separate the wheel halves. b. Keep the brake disc with the inner wheel half. c. Remove the snap ring, item 5, hubcap, item 7, grease seal ring, item 8, and bearing cone, item 9, from the outer wheel half. Place the removed items on a clean surface to avoid contamination. NOTE: Do not remove the inner wheel half snap ring, item 5 and grease seal, item 6. d. Make sure the inside of the tire is clean and dry. Inspect the bead seat area and wipe it clean with denatured alcohol, followed by soap and water, then dry thoroughly. e. Position the inner wheel half with brake disc on a flat surface with the register side of the wheel half facing up. CAUTION: THE O-RING (20) MUST BE INSTALLED UNIFORMLY. DO NOT STRETCH OR TWIST THE O-RING. f. Coat O-ring, item 20 with Dow Corning Molycoat 55M or equivalent and install in the wheel register groove of the inner wheel half. g. Place a serviceable tire over the inner wheel half and then place the outer wheel half in the tire, making sure to properly align the inner and outer wheel half registers. CAUTION: FAILURE TO PROPERLY TORQUE THE WHEEL ASSEMBLY BOLTS MAY RESULT IN PREMATURE FAILURE OF THE MATING COMPONENTS OR HARDWARE. NOTE: The nuts, item 12 should be located on the outer wheel half side of the wheel assembly opposite the brake disc, item 13. h. Slide the washers and bolts, items 11 and 10 through the bolt holes in the brake disc and then through the bolt holes in the wheel halves. Install the remaining washers and nuts, items 11 and 12 onto the bolts and torque the nuts to between 290-300 lb-in. IM199-110 INSTALLATION MANUAL WITH IPL FOR CONVERSION KIT PART NO. 199-110 Page 7 August 10, 2004 SAFETY WARNING: INFLATION OF THE TIRE CAN BE DANGEROUS. INFLATE THE TIRE IN AN INFLATION CAGE TO PREVENT INJURY TO PERSONNEL FROM POSSIBLE EXPLOSION. TIRES AND WHEEL ASSEMBLIES MUST BE SERVICED WITH INFLATION EQUIPMENT THAT HAS BEEN SPECIFICALLY DESIGNED FOR THIS OPERATION. DO NOT INFLATE THE TIRE TO THE OPERATING PRESSURE UNTIL THE WHEEL ASSEMBLY HAS BEEN MOUNTED ON THE AIRCRAFT. i. Inflate the tire to the tire manufacturer’s specifications to seat the beads on the wheel. j. Place the wheel assembly and tire on a clean surface. Position the wheel assembly with the outer wheel half side of the wheel assembly (inflation valve side) face down. 9.2.2 Attach the Brake Assembly to the Wheel NOTE: The bolts, item 14 and washers, item 15, can remain in the cylinder bolt holes. a. Loosen the eight bolts, item 14, on the brake assembly and remove the two backplate/lining segments, item 16, and the two insulator shims, item 17. Leave the pressure plate/lining segment, item 21 on the anchor bolts, item 19. b. Place the torque plate assembly, item 18 with attached brake assembly into the wheel assembly and tire unit (disc side up). c. Position the two insulator shims, item 17, over the eight bolts, item 14. Next, slip the two backplate/lining segments, item 16, between the brake disc, item 13, and the inner wheel half flange. Position to align holes and tighten the bolts. Torque the bolts to between 85 to 90 lb-in. d. For those aircraft equipped with brake de-ice; installation of 199-168 Hot Air Manifold kit is required at this point. Refer to the 199-168 Hot Air Manifold kit installation manual. 9.2.3 Mount the Wheel and Brake onto the Axle a. Pickup the whole assembly and slide it onto the axle, positioning the torque plate lugs over the torque pads on the gear leg. b. Apply a thin coat of bearing grease to the axle, axle threads and axle nut. NOTE: Use the same grease that was used to pack the bearing cones. c. Install the bearing cone, item 9, which was removed in section 9.2.1, onto the axle and in the outer wheel half. IM199-110 INSTALLATION MANUAL WITH IPL FOR CONVERSION KIT PART NO. 199-110 Page 8 August 10, 2004 d. Install the grease seal ring, item 8, wheel bearing washer and axle nut. e. Apply an initial torque of 60 to 100 lb-in to seat the bearings then back the torque off to 0 lb-in or a snug condition. f. While rotating the wheel, re-torque the axle nut to 30 lb-in. If the slots in the axle nut do not line up with the cotter pin hole in the axle, continue to tighten the axle nut until the first available alignment is reached, but do not advance the axle nut in excess of 30 . g. Install the cotter pin. h. Coat the rubber compound on the hubcap, item 7, with a light coat of silicone spray or bearing grease. Install the hubcap into the hub of the outer wheel half and secure the hubcap with the snap ring, item 5. NOTE: Use the same grease that was used to pack the bearing cones. i. Carefully inflate the tire to the necessary operating pressure. j. Connect the 111-05800 hydraulic line assembly, item 3, to each 104-03100 brake fitting assembly, item 22. k. Connect the 207-01901 hose assembly, item 4, to the remaining end of the 111- 05800 hydraulic line assembly, item 3. l. Connect the remaining end of the 207-01901 hose assembly, item 4, into the AN837-4D elbow. m. Check the reservoir fluid level and bleed the system. Check for system leakage. 9.3 SYSTEM CHECKS a. Depress and release toe pedals several times. Rotate the wheels by hand to check for excessive play. A slight amount of drag is acceptable, however a severely bound-up system should be investigated and corrected. Drag could be caused by cocked lining, or air in the hydraulic system. b. Check for possible interference applicable to the individual aircraft. Investigate and correct or contact Technical Support. See beginning of this manual. c. Properly remove the aircraft from the supports. 9.4 BRAKE LINING CONDITIONING When new linings are installed, it is important to condition them properly to obtain the service life designed into them. Condition linings per attached product reference memo PRM14A. IM199-110 INSTALLATION MANUAL WITH IPL FOR CONVERSION KIT PART NO. 199-110 Page 9 August 10, 2004 10.0 WEIGHT AND BALANCE COMPUTATIONS Weigh the original equipment wheels and brakes. Subtract from the new weights to derive weight increase created by the kit installation. Multiply the weight increase by the applicable aircraft moment and revise the weight and balance information in the log book. 10.1 WEIGHT AND BALANCE DATA New installed (per gear leg) Wheel assy........18.00 lbs. each x 2 = 36.00 lbs. per gear leg. Brake assy ....... 10.69 lbs. each x 2 = 21.38 lbs. per gear leg. Total ...........…...28.69 lbs. each x 2 = 57.38 lbs. per gear leg. Complete form 337 and make appropriate log book entries. 11.0 PILOT OPERATING MANUAL INSERTS Inserts are located in front with conversion kit documentation. Attach the label in the pilot operating manual as close as possible to the original section labeled Main Wheel Assembly. Enter the correct arm and moment in the blocks provided. Zero the items out for the original main wheel and brake assemblies that have been removed. Inserts are reprinted below for reference: x Two dual piston, single disc Brake Assemblies, Cleveland P/N 30-146 10.69 ea. x Two 18 x 5.5 Type III Wheel Assemblies, Cleveland P/N 40-289 18.00 ea. Cleveland Brake Assembly P/N 30-146 is a dual caliper, single fixed disc design, using two pistons per caliper which respond to fluid pressure from the master cylinders for brake application. IM199-110 INSTALLATION MANUAL WITH IPL FOR CONVERSION KIT PART NO. 199-110 Page 10 August 10, 2004 12.0 KIT PARTS LIST 199-110 KIT (1) ITEM NUMBER PART NUMBER DESCRIPTION QUANTITY (2) 1 40-289 Wheel Assembly 4 (3) 2 30-146 Brake Assembly 4 3 111-05800 Hydraulic Line Assembly 2 4 207-01901 Hose Assembly 2 IM199-110 Installation Manual for Conversion Kit 199-110 1 50-79 Installation Drawing 1 CM40-289 Component Maintenance Manual for 40-289 Wheel Assembly 1 CM30-146 Component Maintenance Manual for 30-146 Brake Assembly 1 SA646GL Supplemental Type Certificate 1 SA650GL Supplemental Type Certificate 1 SA890GL Supplemental Type Certificate 1 PRM14A Conditioning Procedure for 1 Metallic Brake Lining PRM51 Alternate Cylinder Connecting Line Installation for Brake Model 30-146 1 PRM78 Wheel Assemblies-Alternate Bearing Grease 1 ------- Pilot Operating Manual Inserts 1 ------- Product Registration Card 1 (1) Refer to 50-79 Installation Drawing. (2) For a complete parts breakdown, refer to Maintenance Manual CM40-289. (3) For a complete parts breakdown, refer to Maintenance Manual CM30-146. CLEVELAND WHEELS & BRAKES OVERHAUL MANUAL WITH ILLUSTRATED PARTS LIST FOR BRAKE ASSEMBLY PART NO. 30-146 Aerospace PARKER HANNIFIN CORPORATION AIRCRAFT WHEEL & BRAKE 1160 Center Road - Avon, Ohio 44011 Aerospace Revision D Highlights Page 1 of 1 January 19, 2011 OVERHAUL MANUAL WITH IPL BRAKE ASSEMBLY 30-146 REVISION D DATED JANUARY 19, 2011 Section / Page No. Description of Change Revision D Highlights Ref: DCN 0390-56 Page 1of 1 Added new Revision Highlights Dated January 19, 2011 Page for Rev. D Record of Revisions, Page 1 Added Revision D information List of Effective Pages, Page 1 Updated to reflect changed pages & deleted Page 2 Dissasembly, Page 101 E. Remove the pressure plate assembly, inlet fitting, bleeder fitting, hose assembly (P/N 207- 01600 or 207-07600) and fittings (P/N 104- 04900 or 104-04700). (See Exploded View). was: E. Remove the pressure plate assembly, inlet fitting, bleeder fitting, hose assembly (P/N 207- 01600 ) and fittings (P/N 104-04900). (See Exploded View). Assembly, Page 502 B Lubricate …..on P/N 104-04900 (207-01600 Hose Assembly used) or 104-04700 (if 207- 07600 Hose Assembly used) fittings and install fitting into brake housing. ….. was: B. Lubricate ….on P/N 104-04900 fittings and install fitting into brake housing. …. Assembly, Page 503 H. Fasten the P/N 207-01600 hose assembly to the two P/N 104-04900 fitting assemblies. If 207- 07600 hose assembly is used, fasten to the two P/N 104-04700 fitting assemblies. was: Fasten the P/N 207-01600 or 207-07600 hose assembly to the two 104-04700 fitting assemblies. Parts List, Page 1003 Fitting Assembly, Item 18 P/N 104-07600, Qty 2 was: P/N 104-04900, Qty 1 Hose Assembly, Item 25 P/N 207-07600 was: P/N 207-01600 Aerospace Revision D Highlights Page 1 of 1 January 29, 2016 OVERHAUL MANUAL WITH IPL BRAKE ASSEMBLY 30-146 REVISION E DATED JANUARY 29, 2016 Section / Page No. Description of Change Revision E Highlights Ref: ECO-0063275 Record of Revisions, Page 1 Added Revision E information List of Effective Pages, Page 1 Updated to reflect changed pages Parts List, Page 1003 Fitting Assembly, Item 18 (NOW) P/N 104-04700 (WAS) P/N 104-07600 Aerospace Record of Revisions Page 1 January 29, 2016 OVERHAUL MANUAL WITH IPL BRAKE ASSEMBLY 30-146 RECORD OF REVISIONS REV NO. ISSUE DATE DATE INSERTED BY REV NO. ISSUE DATE DATE INSERTED BY NC 11-24-1993 11-24-1993 PH A 06-15-2004 06-15-2004 PH B 08-10-2004 08-10-2004 PH C 05-15-2007 05-15-2007 PH D 01-19-2011 01-19-2011 PH E 01-29-2016 01-29-2016 PH Aerospace List of Effective Pages Page 1 January 29, 2016 OVERHAUL MANUAL WITH IPL BRAKE ASSEMBLY 30-146 LIST OF EFFECTIVE PAGES SUBJECT PAGE(S) DATE SUBJECT PAGE(S) DATE Record of Revisions 1 01-29-16 Cleaning 201 202 06-15-04 11-24-93 Record of Temporary Revisions 1 11-24-93 Check 301 302 303 304 305 11-24-93 11-24-93 11-24-93 11-24-93 11-24-93 Service Bulletin List 1 11-24-93 Repair 401 402 403 404 08-10-04 06-15-04 11-24-93 08-10-04 List of Effective Pages 1 01-29-16 Assembly 501 502 503 06-15-04 01-19-11 01-19-11 Table of Contents 1 2 11-24-93 06-15-04 Fits and Clearances 601 602 11-24-93 06-15-04 Introduction 1 2 06-15-04 11-24-93 Testing 701 06-15-04 Trouble Shooting 801 801 11-24-93 11-24-93 Description & Operation 1 2 11-24-93 06-15-04 Storage Instructions 901 11-24-93 Disassembly 101 01-19-11 Illustrated 1001 11-24-93 102 08-10-04 Parts List 1002 11-24-93 103 08-10-04 1003 01-29-16 1004 06-15-04 Aerospace Page 101 January 19, 2011 OVERHAUL MANUAL WITH IPL BRAKE ASSEMBLY 30-146 DISASSEMBLY 1. General It is NOT necessary to remove the wheel from the aircraft to disassemble and service the brake cylinder assembly. 1. Disassembly Procedures A. Remove and cap the hydraulic line. B. Remove the eight cylinder tie bolts and eight washers, and two back plate assemblies and insulator shims (see Figure 101). C. Slide the cylinder out of the torque plate. (The torque plate will remain mounted to the axle.) D. Place the assembly on a clean flat surface. E. Remove the pressure plate assembly, inlet fitting, bleeder fitting, hose assembly (P/N 207-01600 or 207-07600) and fittings (P/N 104-04900 or 104-04700). (See Exploded View). F. Drain the hydraulic fluid from the cylinder housing. G. If necessary, remove the piston insulators. H. Remove the pistons by applying a slight amount of air pressure to the inlet or outlet ports of the cylinder. I. Remove the O-Ring from each piston bore groove. Remove the four Parker P/N 103-10100 bolts and four Parker P/N 095-10200 washers from the four Parker P/N 069-02000 anchor bolts. J. If necessary, the anchor bolts may be removed by using a holding fixture and arbor press. If possible, place the anchor bolts into the holding fixture so that the anchor bolt is piloted while being removed. (See Figure 102). Thread an AN4- 15A (or equivalent) bolt into the anchor bolt. Press out the anchor bolt and unthread the AN4-15A bolt from the anchor bolt. See Figure 102. NOTE: The cylinder must be square with the arbor press so that the anchor bolts do not cock. Aerospace Page 502 January 19, 2011 OVERHAUL MANUAL WITH IPL BRAKE ASSEMBLY 30-146 A. If removed, press anchor bolts into brake housing and install P/N 095-10200 washers and P/N 103-10100 bolts. Dry torque the bolts to 60 – 90 in-lbs. B. Lubricate all P/N 101-24600 O-Rings with Dow Corning Molykote 55M (or equivalent) silicone grease. Install P/N 101-24600 O-Ring on bleeder seat, and then screw bleeder seat into cylinder housing. Dry torque to 65 - 70 in-lbs. Install bleeder screw into bleeder seat. Install P/N 101-24600 O-Rings on P/N 104-04900 (207-01600 Hose Assembly used) or 104-04700 (if 207-07600 Hose Assembly used) fittings and install fitting into brake housing. Dry torque to 65 - 70 in-lbs. CAUTION: DO NOT USE IMPACT OR POWER WRENCHES TO INSTALL OR TORQUE HYDRAULIC FITTINGS. C. Lubricate threads of P/N 104-03100 fitting assembly and new P/N 101-20400 O- Ring with Dow Corning Molykote 55M. Install new O-Ring (Parker P/N 101- 20400) onto fitting, and then screw fitting into port and dry torque to 65-70 in-lbs. D. Install the four P/N 082-02000 drag rings onto the four P/N 139-09300 piston guides. Slide one P/N 095-10800 washer followed by one P/N 095-02600 seal onto each of the four P/N 103-00100 bolts. Install each of the four P/N 103- 00100 bolts into the brake cylinders. Install each of the four P/N 139-09300 piston guides onto the P/N 103-00100 bolts, couterbore side first, and dry torque to 25 – 30 in-lbs. E. Lubricate the four piston O-Rings (Parker P/N 101-26500) with hydraulic fluid. Install O-Rings into the cylinder housing O-Ring grooves. Place each piston into a piston bore and rotate to seat the drag ring and to insure that the piston and seal are in proper alignment. Tap the piston with a wooden, plastic, or rubber mallet while alternately rotating. If considerable effort is required, remove the piston and inspect both the bore and the pilot bore for damage. If the bore is damaged, check the corresponding area of the piston for damage. Repair if necessary, and repeat the above procedure once the piston is seated. F. Install the piston insulators into the pistons (if removed). G. Install the pressure plate assembly, the lining side must not face the pistons) by aligning the anchor bolt holes with the anchor bolts and slide the pressure plate onto the cylinder. The pressure plate MUST float freely on the anchor bolts. Aerospace Page 503 January 19, 2011 OVERHAUL MANUAL WITH IPL BRAKE ASSEMBLY 30-146 H. Fasten the P/N 207-01600 hose assembly to the two P/N 104-04900 fitting assemblies. If 207-07600 hose assembly is used, fasten to the two P/N 104- 04700 fitting assemblies. I. Install each brake housing into the torque plate by aligning the anchor bolts with the torque plate holes and sliding the brake assembly onto the torque plate. It MUST slide freely. J. Place a countersunk washer on each of the eight brake tie bolts, and insert these bolts into the respective brake housing holes. NOTE: THE COUNTERSUNK SIDE OF THE WASHER MUST FACE THE BOLT HEAD OR BOLT FAILURE MAY RESULT. K. Install two new insulator shims onto the brake housings. L. Install the two backplate assemblies onto the brake housings, dry torque the brake tie bolts P/N 103-11800 to 85 – 90 in-lbs. NOTE: BE SURE THAT THE BRAKE DISC IS SANDWICHED BETWEEN THE BACKPLATE AND THE PRESSURE PLATE. (AS SHOWN IN FIGURE 101). M. Reconnect the hydraulic lines and bleed the system. Check the pedal for proper feel and travel. Aerospace Page 1003 January 29, 2016 OVERHAUL MANUAL WITH IPL BRAKE ASSEMBLY 30-146 2. Parts List FIGURE ITEM PART NUMBER NOMENCLATURE UNITS PER ASSY 1 30-146 BRAKE ASSEMBLY 1 2 091-14000 CYLINDER ASSEMBLY 2 3 061-10700 CYLINDER 1 4 101-26500 O-RING 2 5 092-05200 PISTON ASSEMBLY 2 6 062-05600 PISTON 1 7 082-02000 SPRING 1 8 088-00200 INSULATOR 1 9 139-09300 PISTON GUIDE 1 10 103-00100 BOLT (AN3-5A) 2 11 066-09100 PRESSURE PLATE 1 12 066-09200 BACKPLATE 1 13 068-04100 SHIM 1 14 103-11800 BOLT (ABP4-21AM) 4 15 081-00200 BLEEDER SEAT 1 16 079-00300 BLEEDER SCREW 1 17 101-24600 O-RING 2 18 104-04700 FITTING ASSEMBLY 2 19 095-10800 WASHER (AN960-10L) 2 20 095-02600 SEAL 4 21 069-02000 ANCHOR BOLT 4 22 095-10200 WASHER (AN960-416L) 12 23 103-10100 BOLT (AN4H5A) 4 24 104-03100 TUBE FITTING 1 25 207-07600 HOSE ASSEMBLY 1 26 * NAMEPLATE 1 REVISION C, 15 JANUARY 2016 JANUARY 15, 2016 OVERHAUL MANUAL WITH IPL WHEEL ASSEMBLY 40-289 Revision B Highlights Page 1 of 2 August 10, 2004 REVISION B DATED 10 AUGUST 2004 Section/Page No. Description of Change As Follows: Rev B. (DCN 0362-52) Record of Update page to reflect Rev. B Revisions, pg 1 Effective Update applicable page dates to reflect Rev. B Pages, pg 1 Introduction, pg 1 Update contact information Description para. 3, Leading Particulars updated: and Operation, pg 2 Correct wheel weight callout: (now) 18.0 (was) 19.3 Bolt torque: (now) 290-300 lb-in (was) 300 lb-in Bearing Lubricant: (now) Refer to the Assembly section (was) MIL-G-81322(Royco 22C or Aeroshell 22) Primer: (now) Refer to the Repair section. (was) Epoxy Polyamide per MIL-P-23377. Topcoat: (now) Refer to the Repair section. (was) White Polyurethane per MIL-C-83286. Cleaning, pg 301 (Remove) "Isopropyl Alcohol" from materials list (now) para. 2.D. "Clean rubber parts by wiping with a clean, soft cloth dampened in a mild dish soap and water solution." (was) para. 2.D. "Clean rubber parts in isopropyl alcohol and dry with a clean, soft cloth." Check, pg 401 (now) NOTE: "Penetrant inspection of wheel halves is recommended at the following intervals: First inspection after the fifth (5th) tire change, and then after the third (3rd) subsequent tire change for a total of twenty tire changes, and then at each and every tire change thereafter." (was) NOTE: "Penetrant inspection of wheel halves is recommended at the following intervals: First inspection after 3rd tire change, then at every tire change thereafter." pg 402 (add) to para. 3.B. "NOTE: THE PROTECTIVE TOPCOAT PAINT AND PRIMER MUST BE REMOVED FROM THE WHEEL HALVES TO CONDUCT AN ACCURATE DYE-PENETRANT INSPECTION." pg 404 (add) to para. I. "Examine the sealed hubcap also." OVERHAUL MANUAL WITH IPL WHEEL ASSEMBLY 40-289 Revision B Highlights Page 2 of 2 August 10, 2004 Repair, pg 501 For Repair Materials list: (add) Primer: P/N 18-017A (Gray) Columbia Paint Corp. Topcoat: P/N 11-358A 641 Jackson Ave. (524 Gloss White) Huntington, WV 25728 Primer: P/N P60G2 and R7K44 Sherwin Williams Co. Topcoat: P/N F63W13 (White) 101-T Prospect Ave. N.W. Cleveland, OH 44115 (add) "NOTE: BECAUSE OF EPA LOW VOC REQUIREMENTS, AIRCRAFT WHEEL & BRAKE USES THE COLUMBIA OR SHERWIN WILLIAMS PRIMERS AND TOPCOATS IN THE PRODUCTION OF THE WHEEL ASSEMBLY. THE USE OF MIL-P-23377 AND MIL-C-85285 IS PERMITTED AS AN ALTERNATE." pg 504 para. 4.C.: (now) "Apply the primer. Refer to table 501." (was) "Apply one coat of epoxy polyamide primer, specification MIL-P-23377 to reworked areas." para. 4.D.: (now) "Apply the topcoat. Refer to table 501." (was) "Apply one coat of White Polyurethane Topcoat, specification MIL-C-83286." pg 505 Figure 502: revise to follow Table 501 for primer/topcoat. pg 506 Figure 503: revise to follow Table 501 for primer/topcoat. pg 507 (add) Primer and Topcoat Table 501 Assembly, pg 601 Materials List: (remove) "Isopropyl Alcohol" (add) "Mobile Aviation Grease SHC 100 pg 602 para. E.: (now) "Clean wheel flange, bead seat,...with a cloth dampened with denatured alcohol followed by a soap and water solution. Dry thoroughly." (was) "Clean wheel flange, bead seat,...with a cloth dampened with isopropyl alcohol." pg 603 para. K.: (now) 290-300 lb-in (was) 300 inch-pounds. para. N.: (now) "Pack bearing cones with clean bearing grease listed in para. 1., Assembly Materials List and install in..." (was) "Pack bearing cones with clean bearing grease, specification MIL-G-81322 and install in..." Section/Page No. Description of Change 08-10-04 08-10-04 08-10-04 08-10-04 08-10-04 08-10-04 08-10-04 08-10-04 08-10-04 January 15, 2016 08-10-04 507 08-10-04 08-10-04 08-10-04 08-10-04 508 01-15-16 01-15-16 01-15-16 440-937-1315 Fax: 440-937-5409 Technical Support August 10, 2004 August 10, 2004 18.0 290-300 lb-in Lubtork. Refer to the Assembly section. Refer to the Repair section. Refer to the Repair section. by wiping with a clean, soft cloth August 10, 2004 dampened in a mild dish soap and water solution. First inspection after the fifth (5th) tire change, and then after and then at each and every tire change thereafter. the third (3rd) subsequent tire change for a total of twenty tire changes, August 10, 2004 NOTE: THE PROTECTIVE TOPCOAT PAINT AND PRIMER MUST BE REMOVED FROM THE WHEEL HALVES TO CONDUCT AN ACCURATE DYE-PENETRANT INSPECTION. August 10, 2004 August 10, 2004 Examine the sealed hubcap also. Page 501 August 10, 2004 1 NOTE: BECAUSE OF EPA LOW VOC REQUIREMENTS, AIRCRAFT WHEEL & BRAKE USES THE COLUMBIA OR SHERWIN WILLIAMS PRIMERS AND TOPCOATS IN THE PRODUCTION OF THE WHEEL ASSEMBLY. THE USE OF MIL-P-23377 AND MIL-C-85285 IS PERMITTED AS AN ALTERNATE. Primer: MIL-P-23377 Commercially Available Topcoat: MIL-C-85285 Primer: P/N 18-017A (Gray) Columbia Paint Corp. Topcoat: P/N 11-358A (524 Gloss White) 641 Jackson Ave. Huntington, WV 25728 Primer: P/N P60G2 and R7K44 Sherwin Williams Co. Topcoat: P/N F63W13 (White) 101-T Prospect Ave. N.W. Cleveland, OH 44115 1 1 August 10, 2004 the primer. Refer to table 501. the topcoat. Refer to table 501. OVERHAUL MANUAL WITH IPL WHEEL ASSEMBLY 40-289 FIGURE 503 Page 505 August 10, 2004 OVERHAUL MANUAL WITH IPL WHEEL ASSEMBLY 40-289 FIGURE 503 Page 506 August 10, 2004 Page 507 August 10, 2004 MANUFACTURER PRIMER TOPCOAT DRY FILM THICKNESS AND AIR DRY TIMES Refer to Manufacturer’s Data Sheet for forced dry schedule PRIMER AND TOPCOAT TABLE, TABLE 501 1 1 Commercially MIL-P-23377 MIL-C-85285 Refer to MIL Specifications Available Columbia Paint Corp. P/N 18-017A P/N 11-358A (524 Gloss White) Primer: .0002-.0005 in. Huntington, WV (water reducible) (water reducible) 15 minutes min. No mixing required No mixing required. (to touch or topcoat) 60 minutes (to handle) It is desirable to apply topcoat 4-24 hours (dry hard) without thinning, however, topcoat material may be thinned up to 10% Topcoat (including primer): by volume with either water (use .0008-.0014 in. distilled) or a mixture of 4 parts 15 minutes (to touch) water to 1 part butyl cellosolve. 30 minutes (to handle) 48 hours (dry hard) Sherwin Williams Co. 2 parts washcoat P/N F63W13 (White) Primer: .0002-.0004 in. Cleveland, OH (P/N P60G2) 6 parts base 3-10 minutes (to touch) 3 parts catalyst 1 part catalyst (P/N V66V27) 10-60 minutes (to topcoat) reducer (P/N R7K44) Topcoat (including primer): Thin using up to 20% polane .0008-.0014 in. reducer (P/N R7K84) 20 minutes (to touch) 60 minutes (to handle) 24 hours (dry hard) August 10, 2004 ExxonMobil Corp. Beaumont, TX 77704 Aeroshell Grease 22 MIL-PRF-81322, grade 2 and DOD-G-24508A Mobile Aviation Grease SHC 100 NOTE: EQUIVALENT SUBSTITUTES MAY BE USED FOR ITEMS LISTED BELOW. Shell Oil Company, Metairie, LA denatured alcohol followed by a mild dish soap and water solution. Dry thoroughly. August 10, 2004 290-300 lb-in. August 10, 2004 Assembly Materials list and install in wheel assembly. listed in para. 1., ClevelandWheels & Brakes Parker Hannifin Corporation Aircraft Wheel & Brake 1160 Center Road Avon, Ohio 44011 USA 1-800-BRAKING (272-5464) 216-937-1272 l FAX 216-937-5409 PRODUCT REFERENCE MEMO Initial Release December 12, 1983 Rev A July 1, 1995 PRM14A Page 1 of 1 METALLIC BRAKE LINING CONDITIONING PROCEDURE The brake lining material used in this brake assembly is an iron based metallic composition. This material must be properly conditioned (glazed) in order to provide optimum service life. Dynamometer tests have shown that at low braking energies, unglazed linings experience greater wear and the brake discs can become severely scored. Conditioning may be accomplished as follows: 1. Perform two (2) consecutive full stop braking applications from 30 to 35 kts. Do not allow the brake discs to cool substantially between stops. 2. On aircraft with tail wheels, exercise caution during stopping to prevent tail lifting. Due to the efficiency of these brakes, extremely hard braking could result in lifting the tail from the ground. This conditioning procedure will wear off high spots and generate sufficient heat to glaze the linings. Once the linings are glazed, the braking system will provide many hours of maintenance free service. Visual inspection of the brake disc will indicate the lining condition. A smooth surface, without grooves, indicates the linings are properly glazed. If the disc is rough (grooved), the linings must be reglazed. The conditioning procedure should be performed whenever the rough disc condition is evident. Light use, such as in taxiing, will cause the glaze to be worn rapidly. Use caution in performing this procedure, as higher speeds with successive stops could cause the brakes to overheat resulting in warped discs and/or pressure plates. ClevelandWheels & Brakes Parker Hannifin Corporation Aircraft Wheel & Brake 1160 Center Road, P.O. Box 158 Avon, Ohio 44011 USA 1-800-BRAKING (272-5464) 216-937-1272  FAX 216-937-5409 PRODUCT REFERENCE MEMO Initial Release June 20, 1989 Rev B January 19, 2011 PRM51 Page 1 of 2 ALTERNATE CYLINDER CONNECTING LINE INSTALLATION FOR BRAKE MODEL 30-146 APPLICABILITY: All aircraft converted to Cleveland Main Wheels and Brakes per Parker Hannifin, Aircraft Wheel & Brake Conversion Kit No.199-110, per STC’s SA646GL, SA650GL and SA890GL: Beech Models 99, 99A, A99A, B99, C99, 100, A100, B100, F90, 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT and B200T PURPOSE: Provides for fabrication and installation of an alternate cylinder connecting line. Use of alternate line gives added brake to ground clearance for operations on unimproved runways. NOTE: This is an OPTIONAL installation. PROCEDURE: At owner’s discretion: 1. Jack aircraft and remove wheels and brakes per Manual. 2. Remove existing hose assembly P/N 207-01600 and fittings P/N 104-04900 or P/N 207-07600 hose assembly and fittings P/N 104-04700 from each brake. 3. Install 90 fittings, P/N 104-03100 (Parker 4-C50X), one in each cylinder positioned, as in Figure 1. 4. Fabricate a brake line, bent as shown in Figure 1, cut and double flared to length needed for proper fit. Brake line to be made of 1/4” stainless steel brake line with AN819-4 sleeves and AN818-4 nuts. Fabrication to be per “Airframe and Powerplant Mechanics General Handbook”, FAA publication EA-AC65-9A, Chapter 5. 5. Install brake line, as shown in Figure 1, and tighten per above referenced handbook. 6. After line nuts and fittings are tightened, assure that both cylinders slide freely (as a unit) in the torque plate. If not, adjust tubing bend as needed for a free fit. 7. Repeat procedure for all four (4) brakes, then reinstall wheels and brakes per manual. 8. Bleed brake system and remove aircraft from jacks. 9. Make a log book entry referencing this activity and return the aircraft to service. PRODUCT REFERENCE MEMO PRM51 Page 2 of 2 Initial ReleaseJune 20, 1989 Rev B January 19, 2011 Figure 1 30-146 Brake Assembly - Connecting Hose Modification ClevelandWheels & Brakes Parker Hannifin Corporation Aircraft Wheel & Brake 1160 Center Road Avon, Ohio 44011 USA 1-800-BRAKING (272-5464) 440-937-1315 z FAX 440-937-5409 PRODUCT REFERENCE MEMO Initial Release October 22, 2002 Revision A January 29, 2007 PRM 78 Page 1 of 1 WHEEL ASSEMBLIES – PREFERRED BEARING GREASE (MOBIL AVIATION GREASE SHC 100) EFFECTIVITY: All Parker Hannifin (Cleveland Wheels & Brakes) wheel assemblies. APPLICABILITY: Any aircraft equipped with Parker Hannifin wheel assemblies. REASON: ExxonMobil “Mobil Aviation Grease SHC 100” is the preferred bearing grease for use in all Parker Hannifin (Cleveland Wheels & Brakes) wheel assemblies. DESCRIPTION: Mobil Aviation Grease SHC 100 is a high performance grease which combines a synthesized hydrocarbon base fluid with a lithium soap thickener. The thickener system provides a high dropping point, excellent resistance to water wash and a tenacious structural stability. The unique properties provide outstanding protection against wear, rust, corrosion and high temperature degradation. The grease is recommended for aviation applications which need a lubricant that can perform normal functions yet go far beyond in terms of high and low temperature and long- life performance. The grease has an operating temperature range of -65°F (-54°C) to + 350°F (+177°C). There is no Military specification for this product. CAUTION: Aviation bearing greases should not be intermixed with each other. Precautions should be taken to ensure that this grease is not intermixed with other wheel bearing greases and is being used in accordance with the manufacturer’s guidelines. For technical Data and MSDS sheets on Mobil Aviation Grease SHC 100, visit the manufactures Web Site at: www.mobil.com COMPLIANCE: Recommended APPROVAL: The engineering contents of this Product Reference Memo are FAA DER approved. WEIGHT & BALANCE: Not applicable PUBLICATIONS: The information contained in this Product Reference Memo (PRM78) is to be incorporated into the Product Catalog and Maintenance Manual at the next revision of each. INSTRUCTIONS: At next tire change or overhaul remove and discard the grease felts. Thoroughly clean wheel assembly and completely remove the contained grease from the bearings, bearing bore and hub per Component Maintenance Manual. Refer to AWBCMM0001, latest issue, for grease packing instructions. Pack bearings with Mobile SHC-100. Install new felt grease seals lubricated with Mobile SHC-100. 1 Parker Hannifin Corporation Aerospace/Aircraft Wheel & Brake 1160 Center Road Avon, OH 44011 Date: _ _/_ _/20_ _ Subject: Letter of Authorization for Installation of STC’d Conversion Kits To whom it may concern: Parker Hannifin Corporation, Aircraft Wheel & Brake Division, hereby states that the following item(s): KIT NUMBER: 199-___________ FAA APPROVAL: 1) STC # ________________________ NO OTHER APPROVALS NECESSARY AUTHORIZATION TO INSTALL: With the sale of this STC KIT, OWNER of the Supplemental Type Certificate agrees to permit the buyer or buyer’s agent or agency to use the certificate to alter the product under the terms and conditions of this STC. A/C MAKE: ______________________ A/C MODEL______________________ TAIL # __________________________ Regards, Technical Support Team Technical Hotline (800) 272-5464 Clevelandwbhelp@parker.com Web-site: www.clevelandwheelandbrake.com Manufacturer of Cleveland Wheels & Brakes