PARTS LIST 199-164 CONVERSION KIT

temperatures; installation per PRM 56.” 1006 Add new page with supplemental Figure 1001 1007 was Page Number 1005 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Revision Highlights Page 5 Sept 01/02 Revision D, dated September 01, 2002 DCN Number 0352-68 Highlights Revision D contains all pages of the manual. Pages which have been added or revised are outlined below with a description of change. Please retain all Highlights pages, inserting them into the manual for future reference. Page No. Description of Change Record of Revisions Update to show latest revision List Of Effective Pages Update to show latest page revisions Introduction Page 1 Contact information updated. Description & Operation Reformatted section per addition and deletion of material. Page 2 Para. 4. Brake lining wear check (now) “…brake assembly 30-189A requires overhaul per paragraph 5. (was) “…brake assembly 30-189A requires heat stack replacement per Section 5.B.” Figure 1 Brake Lining Wear Check (delete) “Note: When retract stud is flush with friction sleeve (three places) remove brake assembly for overhaul.” Page 3 Para. 5. Maintenance (add) Table 1 Overhaul Intervals (delete) paragraph A and B Heat Stack Replacement including identification procedure. Page 4 (now) Blank CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Revision Highlights Page 6 Sept 01/02 Revision D Highlights (Cont’d) Page No. Description of Change Check Reformatted section per addition and deletion of material. Page 302 Para. 3.A.1) (now) “NOTE: THE PROTECTIVE TOP COAT PAINT AND PRIMER MUST BE REMOVED FROM THE CYLINDER HOUSING TO CONDUCT AN ACCURATE DYE- PENETRANT INSPECTION. REFER TO CLEANING SECTION FOR PAINT REMOVAL INSTRUCTIONS.” (WAS) “NOTE: THE PROTECTIVE TOP COAT PAINT AND PRIMER SHOULD BE STRIPPED FROM THE CYLINDER HOUSING PRIOR TO INSPECTION BY PENETRANT METHODS (SEE PAINT REMOVAL PROCEDURES IN CLEANING). FALSE CRACK INDICATIONS COULD RESULT IF HOUSING IS NOT CLEAN OF PROTECTIVE PAINT FINISH. Para. 3.A. (now) “4) See Figure 300 and check bushing (58) for wear. Install new bushing in accordance with REPAIR if bushing is worn beyond limits shown and specified in Figure 601, FITS AND CLEARANCES.” (was) “4) Check bushing (58) for wear. Install new bushing in accordance with REPAIR if inside diameter reaches 1.815 inches or more. Page 303 (add) “Figure 300, Bushing Limits” Page 304 Para. 3.E. (now) “1) Check torque plate (5) for cracks either visually or using magnetic particle or dye penetrant inspection techniques…” (was) “1) Check torque plate (5) for cracks either visually or with magnetic particle inspection techniques…” (now) “3) < DELETED >” (was) “3) Check torque plate for distortion. Replace torque plate if it is more than 0.020 inch out-of-flat.” CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Revision Highlights Page 7 Sept 01/02 Revision D Highlights (Cont’d) Page No. Description of Change Check Page 304 Para. 3.E. (now) “4) Replace all wear pads (7), regardless of condition, in accordance with REPAIR.” (was) “4) Check wear pads (7) for wear. Replace all wear pads if four or more are worn to 1.375 inches or less in width on the horizontal centerline between rivets (Ref. Fig. 301), if any pad is cracked or loose or if any rivets are sheared. Replace all wear pads if one or more wear pads measure 0.086 inch or less in thickness. This measurement shall be taken on the flat area between wear pad rivet heads. Replace wear pads in accordance with REPAIR.” (add) “5) Check torque plate lug outer surfaces for damage due to disk shrinkage. Blend out damaged areas in accordance with REPAIR.” Page 305 (now) Para. “3.F. Discs (8)” (was) Para. “3.H. Discs (8)” Para. 3.F. (now) “5) …, or if any tang is 0.457 inch or less in width.” (was) “5) …, or if any tang is 0.442 inch or less in width.” (now) Para. “3.G. Center Stator Subassembly (9)” (was) Para. “3.I. Center Stator Subassembly (9)” Para. 3.G. (now) “1) Check center stator (10) for cracks using magnetic particle or dye-penetrant inspection techniques.” (was) “1) Check center stator (10) for cracks.” Page 305 Para. 3.G. (now) “2) Replace all wear pads (12), regardless of condition, in accordance with REPAIR. (was) “2) Check wear pads (12) for wear. Replace all wear pads if four or more per side are worn to 1.375 inches or less in width on the horizontal centerline between rivets (Ref. Fig. 301), if any pad is cracked or loose, or if any rivets are sheared. Replace wear pads in accordance with REPAIR.” CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Revision Highlights Page 8 Sept 01/02 Revision D Highlights (Cont’d) Page No. Description of Change Check Page 305 Para. 3.G. (now) “3) < DELETED >” (was) “3) Check center stator subassembly (9). The minimum allowable overall thickness of the center stator subassembly is 0.412 inch. If one or more wear pads per side of the center stator measure 0.086 inch or less, all of the pads on that side of the center stator shall be replaced. Measurements shall be taken on the flat area between wear pad rivet heads. Replace wear pads in accordance with REPAIR.” (now) “4) < DELETED >” (was) “4) Check subassembly for dishing or distortion. Replace center stator subassembly if dished or warped 0.020 inch or more out-of-flat.” (now) “6) …if keyslots are less than 0.770 inch wide or greater than 0.790 inch wide.” (was) “6) …if keyslots are less than 0.745 inch wide or greater than 0.795 inch wide.” Page 306 (now) Para. “3.H. Pressure Plate Subassembly (27)” (was) Para. “3.J. Pressure Plate Subassembly (27)” Para. 3.H. (now) “1) Check pressure plate (28) for cracks using magnetic particle or dye-penetrant inspection techniques.” (was) “1) Check pressure plate (28) for cracks.” (now) “2) Replace all wear pads (30), regardless of condition, in accordance with REPAIR.” (was) “2) Check wear pads (30) for wear. Replace all wear pads if four or more are worn to 1.375 inches or less in width on the horizontal centerline between rivets (Ref. Fig. 301), if any pad is cracked or loose, or if any rivets are sheared. Replace wear pads in accordance with REPAIR.” (now) “3) < DELETED >” (was) “3) Check pressure plate subassembly (27). Replace all wear pads if total thickness of plate and pads is 0.274 inch or less. The measurement shall be taken on the flat area between wear pad rivet heads. Replace wear pads in accordance with REPAIR.” CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Revision Highlights Page 9 Sept 01/02 Revision D Highlights (Cont’d) Page No. Description of Change Check Page 306 Para. 3.H. (now) “4) …if keyslots are less than 0.770 inch wide or greater than 0.790 inch wide.” (was) “4) …if keyslots are less than 0.745 inch wide or greater than 0.795 inch wide.” (now) “5) < DELETED >” (was) “5) Check subassembly for distortion. Replace pressure plate subassembly if it is dished 0.020 inch or more out-of-flat.” (now) Para. “3.I. Retract Assemblies (13)” (was) Para. “3.K. Retract Assemblies (13)” (now) Para. “3.J. Inserts (56)” (was) Para. “3.L. Inserts (56)” Para. 3.J. (now) “1) …Replace inserts having any of the above defects…” (was) “1) …Repair inserts having any of the above defects…” Page 307 (add) Para. “4. Procedure For Overheated Brakes” (add) “Figure 302, Heat Damage Hardness Test – Brake Housing” Page 308 (now) Blank Repair Reformatted section per addition of material. Page 403 Figure 401, Limits for Newly Re-padded…Subassemblies (add) graphics and limits for torque plate subassembly Page 404 Para. 4. (add) “B) Repair torque plate lug outer surfaces damaged by disk shrinkage to limits shown in Figure 406. No damage or rework is permitted in the radius indicated.” Para. 5.B. (now) “…The axle bore diameter after rework should be no more than ∅ 2.528 inch.” (was) “…The axle bore diameter after rework should be no less than 2.498 inch.” Para. 5.C. (add) “…Maintain a surface finish of 32 microinches rms.” CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Revision Highlights Page 10 Sept 01/02 Revision D Highlights (Cont’d) Page No. Description of Change Repair Page 405 Figure 403 (add) “rework not permissible in indicated areas.” Page 406 Para. 6.A. (add) “…Maintain a surface finish of 16 microinches rms.” Page 408 (add) “Figure 406, Torque Plate Lug Repair Limits” Fits and Clearances Figure 601, Wear and Distortion Tolerances Page 601 For torque plate subassembly (4): (add) “lug height 0.407 (minimum)” For disc (8): (now) total thickness “0.250 (minimum)” (was) total thickness “0.025 (minimum)” (now) tang width “0.457 (minimum)” (was) tang width “0.442 (minimum)” For center stator subassembly (9): (now) “total thickness (including pads) 0.407 (minimum)” (was) “total thickness 0.412 (minimum)” (add) “total thickness (stator only) 0.235 (minimum)” (now) keyslot widths “0.770 (minimum)” and “0.790 (maximum)” (was) keyslot widths “0.745 (minimum)” and “0.795 (maximum)” For pressure plate subassembly (27): (now) “total thickness (including pads) 0.269 (minimum)” (was) “total thickness 0.274 (minimum)” (add) “total thickness (plate only) 0.183 (minimum)” (add) “pad thickness 0.086 (minimum)” (now) keyslot widths “0.770 (minimum)” and “0.790 (maximum)” (was) keyslot widths “0.745 (minimum)” and “0.795 (maximum)” For bushing (58): (add) “(Dim. ∅A)” as identification for inside diameter (add) “overall length (Dim. B) 0.998 (minimum)” (add) “bushing (58A)”: “inside diameter (Dim. ∅A)” 1.815 (maximum)” “overall length (Dim. B) 1.014 (minimum)” CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Revision Highlights Page 11 Sept 01/02 Revision D Highlights (Cont’d) Page No. Description of Change Illustrated Parts List IPL parts list Page 1007 (add) for item 58, P/N, 145-10200, Bushing: “Repld by item 58A” (add) item “58A, P/N, 145-15400, Bushing, Repls Item 58, qty 1” (add) footnotes: “Replaced by REPLD BY The part in the part number column is replaced by and interchangeable with the item number shown in the notation.” “Replaces REPLS The part in the part number column replaces and is interchangeable with the item number shown in the notation.” CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Revision Highlights Page 1 April 20/04 Revision E, dated April 20, 2004 DCN Number 0361-20 Highlights Revision E contains all pages of the manual. Pages which have been added or revised are outlined below with a description of change. Please retain all Highlights pages, inserting them into the manual for future reference. Page No. Description of Change Record of Revisions Update to show latest revision List Of Effective Pages Update to show latest page revisions Check Page 304 Para. 3.E. (now) “1) Check torque plate (5) for cracks using magnetic particle or dye penetrant inspection techniques…” (was) “1) Check torque plate (5) for cracks either visually or using magnetic particle or dye-penetrant inspection techniques…” Repair (revise) para. 5.E.) Page 405 (now) “Rework procedure to eliminate potential strut to cylinder interference and to repair damage caused by interference.” “1) Refer to rework dimensions in Figure 402.” (was) “Rework procedure to repair damage caused by strut to cylinder interference.” “1) Machine a 45° chamfer at area indicated and to dimensional limits as shown in Figure 402.” (revise) Figure 402 (add) rework dimensions: 2X R 0.060; 2X 0.225 ± 0.025; 2X 0.0129 ± 0.025 X 45° ± 3° Chamfer CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Record of Revision Page RR-1 April 20/04 RECORD OF REVISIONS REV NO. ISSUE DATE DATE INSERTED BY REV NO. ISSUE DATE DATE INSERTED BY NC 07-18-89 07-18-89 AWB A 06-03-91 06-03-91 AWB B 10-27-92 10-27-92 AWB C 02-20-96 02-20-96 AWB D 09-01-02 09-01-02 AWB E 04-20-04 04-20-04 AWB CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Service Bulletin List Page SB-1 Feb 20/96 SERVICE BULLETIN LIST Note: Parker Hannifin Service Bulletins are issued in order to provide general information on product line concerns. The bulletin listings contained herein identify subject matter directly related to the support and function of the Brake Assembly and Components. SERVICE BULLETIN NO. REV NO. DATE INCORPORATED SERVICE BULLETIN NO REV NO. DATE INCORPORATED SB7028 A 11-10-92 SB7046 NC 10-01-95 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace List of Effective Pages Page LEP-1 April 20/04 LIST OF EFFECTIVE PAGES SUBJECT PAGE(S) DATE SUBJECT PAGE(S) DATE Title Page Check 308 Sept. 01/02 Repair 401 Feb 20/96 402 Feb 20/96 403 Sept. 01/02 Record of 1 Sept. 01/02 404 Sept. 01/02 Revision 405 April 20/04 406 Sept. 01/02 Service 1 Feb 20/96 407 Sept. 01/02 Bulletin List 408 Sept. 01/02 List of 1 Sept. 01/02 Effective Pages Assembly 501 Feb 20/96 Table of 1 Feb 20/96 502 Feb 20/96 Contents 2 Feb 20/96 503 Feb 20/96 504 Feb 20/96 Introduction 1 Sept. 01/02 2 Feb 20/96 Fits and 601 Sept. 01/02 Clearances 602 Feb 20/96 Description and 1 Feb 20/96 Operation 2 Sept. 01/02 Testing 701 Feb 20/96 3 Sept. 01/02 702 Feb 20/96 4 Sept. 01/02 Trouble 801 Feb 20/96 Disassembly 101 Feb 20/96 Shooting 802 Feb 20/96 102 Feb 20/96 Storage 901 Feb 20/96 Cleaning 201 Feb 20/96 Instructions 902 Feb 20/96 202 Feb 20/96 Illustrated 1001 Feb 20/96 Check 301 Feb 20/96 Parts List 1002 Feb 20/96 302 Sept. 01/02 1003 Feb 20/96 303 Sept. 01/02 1004 Feb 20/96 304 April 20/04 1005 Feb 20/96 305 Sept. 01/02 1006 Feb 20/96 306 Sept. 01/02 1007 Sept. 01/02 307 Sept. 01/02 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Table of Contents Page T/C-1 Feb 20/96 TABLE OF CONTENTS Subject Page INTRODUCTION 1 DESCRIPTION AND OPERATION 1 1. Description 1 2. Operation 2 3. Leading Particulars 2 4. Brake Lining Wear Check 2 5. Maintenance 3 DISASSEMBLY 101 1. General 101 2. Disassembly Procedures 101 CLEANING 201 1. Cleaning Materials 201 2. Cleaning Metallic Parts 201 3. Cleaning Nonmetallic Parts 202 4. Paint Removal Procedures 202 CHECK 301 1. Check Materials 301 2. General 302 3. Detailed Check 302 REPAIR 401 1. Repair Materials 401 2. General Repair Procedures 401 3. Repair of Pressure Plate Subassembly 402 and Torque Plate Subassembly 4. Repair of Torque Plate 404 5. Repair of Cylinder Housing 404 6. Repair of Pistons 406 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Table of Contents Page T/C-2 Feb 20/96 TABLE OF CONTENTS Subject Page REPAIR (Cont’d) 7. Repair of Defective Inserts 406 8. Retreating and Repainting Cylinder Housing Subassembly 406 9. Resetting Adjuster Assembly 406 ASSEMBLY 501 1. Assembly Materials 501 2. General Assembly Procedures 501 FITS AND CLEARANCES 601 TESTING 701 1. General 701 2. Testing Procedure 701 TROUBLE SHOOTING 801 STORAGE INSTRUCTIONS 901 1. Brake Assembly 901 ILLUSTRATED PARTS LIST 1001 1. Introduction 1001 2. Parts List 1003 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Introduction Page INTRO-1 Sept 01/02 INTRODUCTION This manual is published for the guidance of personnel responsible for the overhaul and/or maintenance of the Parker Hannifin 30-189A Brake Assembly covered in this publication. The procedures outlined in this manual may be altered if better and/or more economical methods can be employed by the individual facilities. However, alternative procedures must not reduce the efficiency of operation of the assembly. NOTE: All torque values and specified limits or values set by Parker Hannifin Engineering and contained herein must be strictly observed and not deviated from. While Parker Hannifin Corporation represents that the information contained in this manual was current at the time of publication, it is recommended that the user inquire as to the latest revision level in existence before proceeding with overhaul or maintenance operations. This can be accomplished by contacting the Product Support Department of the Aircraft Wheel & Brake Division at the following address or numbers: Parker Hannifin Corporation Phone: 1-800-272-5464 Aircraft Wheel & Brake Division Fax: (440) 937-5409 1160 Center Road Website: www.parker.com/cleveland Avon, Ohio 44011 U.S.A. Attn.: Technical Services/Hotline CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Introduction Page INTRO-2 Feb 20/96 TSO NOTICE This assembly carries a “TSO” marking for commercial transport usage, which identifies it as having been fully tested in the laboratory and qualified to applicable FAA (Federal Aviation Administration) requirements and specifications. As a commercial transport category assembly, it is also tested and qualified to the requirements of Cessna Aircraft Company. After final certification, substitutions of critical parts or changes of processes or materials are not permitted without requalification of the assembly and resubmittal of the test data to the FAA for approval. FAA regulations subject both Parker Hannifin, Aircraft Wheel & Brake Division and the user to constant surveillance to assure that uncompromising quality assurance material and processing controls are maintained in order to provide replacement parts that are the same as the parts originally certified in the assembly. DATA RIGHTS The unit charge for this manual covers reproduction and handling costs only and does not constitute purchase of the data or design contained herein, nor does it convey to the purchaser any rights, patent or otherwise, to reproduce or manufacture from said data. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 1 Feb 20/96 DESCRIPTION AND OPERATION 1. Description A. The brake assembly is a piston actuated, hydraulically operated multiple disc unit designed for use with phosphate ester (SAE AS 1241 Type IV, Class 2, Grade A) hydraulic fluid. The right and left brake assemblies are directly interchangeable by simply switching the fittings on the top of the housing to the opposite respective ports. B. Each brake assembly is composed of a pressure plate assembly, two rotating discs, a stationary center stator assembly, a torque plate assembly and a forged aluminum cylinder housing assembly containing six pistons. Five bolts hold the housing assembly and torque plate assembly together as a unit. The inner perimeters of the pressure plate assembly and center stator assembly have six keyslots that engage the keys on the torque tube and prevent them from rotating. Drive tangs on the outer perimeter of the rotating discs engage drive slots in the inner wheel half flange, transmitting a braking force to the main wheel during a braking application. C. O-rings and wiper rings installed in grooves in the housing cylinder walls prevent leakage past the pistons. An insulator in the end of each piston reduces the amount of brake heat transmitted into the pistons and housing. D. In the event of hydraulic line failure, pneumatic pressure is applied into the pneumatic inlet fitting located directly below the hydraulic inlet. Upon actuation of pneumatic pressure, a spool valve in the shuttle valve assembly is actuated in the opposite direction sealing off inlet flow of fluid and allowing controlled pneumatic pressure to be applied directly to the pistons from the cockpit of the aircraft. E. The brake assembly utilizes three self-adjusting retract assemblies installed in the cylinder housing. When brake pressure is released, the pressure plate assembly is pulled back toward the cylinder housing by the retracts thus maintaining a constant running clearance in the brake stack at all times. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 2 Sept 01/02 DESCRIPTION AND OPERATION 2. Operation Braking action begins to occur when hydraulic pressure applied to the brake, via the pilots and co-pilots master cylinders, moves the pistons out of the cylinder housing. As this pressure overcomes the spring force in the retract assemblies, the pistons will contact the pressure plate assembly and force the discs and center stator into the torque plate generating torque. This braking action is then transmitted to the wheel by the drive tangs on the discs. 3. Leading Particulars Hydraulic fluid.................................SAE AS 1241, Type IV, Class 2, Grade A. Normal Operating Pressures..........350-600 psi Running Clearance of Stack.......... .060 (nom.) Weight of Assembly....................... 35.8 lbs. Cylinder Housing Material............. 2014 Forged Aluminum 4. Brake Lining Wear Check The Parker Hannifin 30-189A brake assembly utilizes the retract stud in each of three retract mechanisms as a lining wear indicator. When the broached end of any of the three retract studs become flush with the brass friction sleeve (Ref. Fig. 1 below), brake assembly 30-189A requires overhaul per paragraph 5. Brake Lining Wear Check Figure 1 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 3 Sept 01/02 DESCRIPTION AND OPERATION 5. Maintenance Refer to IPL Figure 1001 for identification of brake assembly components. Table 1 Overhaul Intervals SCHEDULED INTERVAL ITEM MAINTENANCE TASK (procedures per CHECK section) All components a. General inspection per para. 2. b. Detailed inspection per para 3. as applicable O-Rings (34, 36, 39, 40, 42, 46, 50) Replace Wiper Ring (49) Replace Wear Pads (7, 12, 30) and Rivets (6, 11, 29) Replace Brake Cylinder (54) a. Detailed inspection per para. 3.A. b. Penetrant inspect. Torque Tube (5) a. Detailed inspection per para. 3.E. b. Magnetic particle or penetrant inspect. Center Stator (10) a. Detailed inspection per para. 3.I. b. Magnetic particle or penetrant inspect. When brake lining check indicates worn condition. See paragraph 4. Brake Lining Wear Check Pressure Plate (28) a. Detailed inspection per para. 3.J. b. Magnetic particle or penetrant inspect. UNSCHEDULED INTERVAL ITEM MAINTENANCE TASK All components a. General inspection per para. 2. b. Detailed inspection per para. 3. as applicable Brake Cylinder (54) Hardness test per para. 4. O-Rings (34, 36, 39, 40, 42, 46, 50) Replace 1. Rejected Take-Off 2. Overheating such that at least one of the three fusible plugs release in the mating main wheel assembly. Additionally, the brake may show evidence of overheating, such as brake housing paint discoloration or melted seals. Wiper Ring (49) Replace CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 4 Sept 01/02 THIS PAGE INTENTIONALLY LEFT BLANK CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 101 Feb 20/96 DISASSEMBLY 1. General Disassemble the brake assembly in accordance with the following instructions after removal from aircraft (Ref. IPL Fig. 1001). 2. Disassembly Procedures A. Place brake assembly on a clean, flat work surface. B. Remove five bolts (2) and washers (3). C CA AU UT TIIO ON N:: D DO O N NO OT T U US SE E IIM MP PA AC CT T O OR R P PO OW WE ER R W WR RE EN NC CH HE ES S T TO O R RE EM MO OV VE E B BR RA AK KE E B BO OL LT TS S.. C. Remove torque plate subassembly (4), discs (8) and center stator subassembly (9). D. Remove three adjuster subassemblies (14) from retract base subassemblies (19) with a 1/8 inch allen wrench. Remove and retain retract base subassemblies that engage pressure plate subassembly (27). E. Remove pressure plate subassembly (27). F. Remove three retract housing subassemblies (22) from cylinder subassembly (53). Remove snap rings (24), washers (25) and springs (26) from retract housings (23). G. Remove bleeder cap (31) and bleeder screw (32) and drain hydraulic fluid from cylinder housing. H. Remove bleeder seat (33), O-ring (34), plug (35) and O-ring (36). I. Remove expander fitting (37) if applicable, shuttle valve assembly (38), and O-rings (39 and 40). Remove fitting (45) and O-ring (46). CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 102 Feb 20/96 DISASSEMBLY J. Remove insulators (47) and then remove pistons (48) by threading an AN-4 bolt into the threaded portion of the piston and pulling outward slowly, making sure not to cock the pistons. K. Remove wiper rings (49) and O-rings (50) from piston bore grooves. L. Remove screws (51) and torque liners (52) from cylinder subassembly (53). C CA AU UT TIIO ON N:: B BU US SH HIIN NG G ((5588)) IIS S S SH HR RIIN NK K F FIIT TT TE ED D IIN NT TO O C CY YL LIIN ND DE ER R H HO OU US SIIN NG G ((5544)) A AN ND D S SH HO OU UL LD D N NO OT T B BE E R RE EM MO OV VE ED D U UN NL LE ES SS S R RE EP PL LA AC CE EM ME EN NT T IIS S N NE EC CE ES SS SA AR RY Y.. R RE EF FE ER R T TO O ""C CH HE EC CK K"" F FO OR R L LIIM MIIT TS S.. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 201 Feb 20/96 CLEANING 1. Cleaning Materials NOTE: EQUIVALENT SUBSTITUTES MAY BE USED FOR ITEMS LISTED BELOW. Dry Cleaning Solution Specification P-D-680 Stoddard Solvent Commercially Available Isopropyl Alcohol Commercially Available Soft Bristle Brush Commercially Available Clean Wiping Cloth Commercially Available 2. Cleaning Metallic Parts (Ref. IPL Fig. 1001) A. Clean all metal parts of brake assembly, except discs (8), in dry-cleaning solution, Specification P-D-680 (Stoddard Solvent) or isopropyl alcohol and dry with filtered compressed air. A soft bristle brush may be used where necessary. W WA AR RN NIIN NG G:: C CL LE EA AN NIIN NG G S SO OL LU UT TIIO ON NS S S SH HO OU UL LD D B BE E U US SE ED D IIN N A A W WE EL LL L V VE EN NT TIIL LA AT TE ED D A AR RE EA A.. A AV VO OIID D P PR RO OL LO ON NG GE ED D IIN NH HA AL LA AT TIIO ON N O OF F F FU UM ME ES S.. B. Dry discs (8) with compressed air and a bristle brush. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 202 Feb 20/96 CLEANING 3. Cleaning Nonmetallic Parts (Ref. IPL Fig. 1001) O-rings (34, 36, 39, 40, 46, and 50) and wiper rings (49) should be replaced at each overhaul. If necessary to reuse, clean them in isopropyl alcohol and dry with a clean cloth. 4. Paint Removal Procedures A. Remove paint from the cylinder housing (54) using chemical paint removal solvents or plastic media stripping in accordance with the following instructions. W WA AR RN NIIN NG G::D DU UE E T TO O T TH HE E T TO OX XIIC CIIT TY Y O OF F C CH HE EM MIIC CA AL L P PA AIIN NT T R RE EM MO OV VA AL L S SO OL LV VE EN NT TS S,, IIT T IIS S H HIIG GH HL LY Y R RE EC CO OM MM ME EN ND DE ED D T TH HA AT T P PA AIIN NT T R RE EM MO OV VA AL L B BY Y T TH HIIS S M ME ET TH HO OD D B BE E A AC CC CO OM MP PL LIIS SH HE ED D B BY Y A A C CO OM MM ME ER RC CIIA AL L F FA AC CIIL LIIT TY Y W WIIT TH H T TH HE E P PR RO OP PE ER R E EQ QU UIIP PM ME EN NT T A AN ND D C CH HE EM MIIC CA AL L D DIIS SP PO OS SA AL L C CA AP PA AB BIIL LIIT TIIE ES S.. C CA AU UT TIIO ON N:: R RE EF FE ER R T TO O T TH HE E A AP PP PL LIIC CA AB BL LE E M MA AN NU UF FA AC CT TU UR RE ER R’’S S IIN NS ST TR RU UC CT TIIO ON NS S W WH HE EN N U UT TIIL LIIZ ZIIN NG G C CH HE EM MIIC CA AL L P PA AIIN NT T R RE EM MO OV VA AL L S SO OL LV VE EN NT TS S O OR R P PL LA AS ST TIIC C M ME ED DIIA A S ST TR RIIP PP PIIN NG G E EQ QU UIIP PM ME EN NT T.. B. Completely disassemble the brake prior to paint removal. N NO OT TE E:: R RE EF FE ER R T TO O ""R RE EP PA AIIR R"" F FO OR R R RE ET TR RE EA AT TIIN NG G A AN ND D R RE EP PA AIIN NT TIIN NG G T TH HE E C CY YL LIIN ND DE ER R H HO OU US SIIN NG G.. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 301 Feb 20/96 CHECK 1. Check Materials NOTE: EQUIVALENT SUBSTITUTES MAY BE USED FOR ITEMS LISTED BELOW: Type Penetrant Developer Supplier Fluorescent Zyglo ZL-16 Zyglo ZP-13 (wet) optional Penetrex ZL-2A with emulsifier ZE-4 Penetrex ZP-4 (dry) or ZP-13 optional Magnaflux Corp. 7310 West Lawrence Ave. Chicago, IL. 60656 Red Dye Spot Check Spot Check Dy-Chek Dy-Chek Turco Products Division of Purex Corp. P.O. Box 6200 Carson, CA 90749 Met-L-Chek Met-L-Chek Met-L-Chek Company 1639 Euclid Street Santa Monica, CA 90404 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 302 Sept 01/02 CHECK 2. General (Ref. IPL Fig. 1001) A. Check all parts for cracks, wear, structural damage, corrosion, and damaged threads. Replace all parts that show evidence of cracks, excessive wear, and structural and thread damage. Repair minor scratches and corrosion. Check specific parts in accordance with the following instructions (Ref. IPL Fig. 1001). 3. Detailed Check (Ref. IPL Fig. 1001) A. Cylinder Subassembly (53) 1) Check cylinder housing (54) for cracks using a dye-penetrant method. Replace cylinder if cracks are present. NOTE: THE PROTECTIVE TOP COAT PAINT AND PRIMER MUST BE REMOVED FROM THE CYLINDER HOUSING TO CONDUCT AN ACCURATE DYE-PENETRANT INSPECTION. REFER TO CLEANING SECTION FOR PAINT REMOVAL INSTRUCTIONS. 2) Check cylinder subassembly for condition of threads in inlet and bleeder ports. Replace all housings that have badly damaged threads in ports. 3) Check piston bores for wear. Replace housing if any piston bore exceeds 1.378 inches in diameter. 4) See Figure 300 and check bushing (58) for wear. Install new bushing in accordance with R RE EP PA AIIR R if bushing is worn beyond limits shown and specified in Figure 601, FITS AND CLEARANCES. 5) Check cylinder housing for nicks, scratches and corrosion. Blend out damage in accordance with R RE EP PA AIIR R. Check cylinder housing axle bore for damage or corrosion. See R RE EP PA AIIR R for damage limits and refurbishment. B. Pistons (48) 1) Check pistons for wear. Measure diameter of pistons at three places around circumference. Replace pistons if diameter measures 1.370 inches or less at any point. 2) Check pistons for burrs, scratches, or nicks. Replace any pistons that are damaged more than 0.003 inch deep on seal contacting surfaces. Repair pistons that are damaged less than 0.003 inch deep as described in R RE EP PA AIIR R. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 303 Sept 01/02 CHECK Bushing Limits Figure 300 C. Insulators (47) 1) Check insulators for cracks. Replace cracked insulators. D. Bolts (2) 1) Carefully check brake bolts for thread damage, and check for cracks in the radius under the bolt head and in threads adjacent to the bolt shank using magnetic particle inspection technique. Replace bent, cracked, or thread damaged bolts. No reworking or refinishing of bolts is permissible. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 304 April 20/04 CHECK E. Torque Plate Subassembly (4) 1) Check torque plate (5) for cracks using magnetic particle or dye-penetrant inspection techniques. Any evidence of cracks necessitates replacement. 2) Check width of torque plate lug. Replace torque plate if lug width is 0.695 inch or less at any point along length of any lug. 3) <DELETED> 4) Replace all wear pads (7), regardless of condition, in accordance with R RE EP PA AIIR R. 5) Check torque plate lug outer surfaces for damage due to disc shrinkage. Blend out damaged areas in accordance with R RE EP PA AIIR R.. Wear Pad Limits Figure 301 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 305 Sept 01/02 CHECK F. Discs (8) 1) Check discs for cracks. Pay close attention to relief slot terminal holes and drive tang radii. Replace any cracked discs. 2) Check discs for wear. Replace disc when minimum thickness across the mix reaches .250 inch or less, or if mix is worn to .015 inch thick or less at any point on either face of disc. 3) Check discs for distortion. Replace discs that are dished in excess of 0.020 inch. 4) Check condition of mix. Pitting is acceptable if area of pitting does not exceed 0.250 inch in diameter. Crumbling of mix along all edges of disc is acceptable, if loss from any edge does not exceed 0.125 inch. 5) Check disc drive tangs for wear and battering. Replace discs if one or more tangs are bent, or if any tang is 0.457 inch or less in width. 6) Check relief slot terminal holes for cracks, rust, and corrosion. Replace cracked discs. Repair rusted or corroded terminal holes in accordance with R RE EP PA AIIR R. G. Center Stator Subassembly (9) 1) Check center stator (10) for cracks using magnetic particle or dye-penetrant inspection techniques. Pay close attention to the relief slot terminal holes, rivet holes, and corners of keyslots. Replace cracked center stator. 2) Replace all wear pads (12), regardless of condition, in accordance with R RE EP PA AIIR R. 3) <DELETED> 4) <DELETED> 5) Check relief slot terminal holes for rust and corrosion. Repair rusted or corroded terminal holes in accordance with R RE EP PA AIIR R. 6) Check keyslots for wear. Replace center stator subassembly if keyslots are less than 0.770 inch wide or greater than 0.790 inch wide. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 306 Sept 01/02 CHECK H. Pressure Plate Subassembly (27) 1) Check pressure plate (28) for cracks using magnetic particle or dye-penetrant inspection techniques. Pay close attention to the relief slot terminal holes, rivet holes, retract slots and corners of keyslots. Replace cracked pressure plate. 2) Replace all wear pads (30), regardless of condition in accordance with R RE EP PA AIIR R. 3) <DELETED> 4) Check keyslots for wear. Replace pressure plate subassembly if keyslots are less than 0.770 inch wide or greater than 0.790 inch wide. 5) <DELETED> I. Retract Assemblies (13) 1) Check all adjuster subassemblies (14). Replace damaged and worn subassemblies. Replace subassembly if stud (15) has damaged threads or elevated nicks on the shaft surface. 2) Reset usable adjuster subassemblies in accordance with R RE EP PA AIIR R. 3) Check all retract base subassemblies (19). Replace damaged and worn subassemblies. Check threaded inserts (21) for worn, stripped or crossed threads. Replace retract base subassembly if this condition exists. Check self- locking feature. Replace retract base subassembly if stud (15) can be run down into the retract base subassembly (19) with the fingers. 4) Inspect all retract housing subassemblies (22). Replace damaged and worn subassemblies. Replace snap ring (24) if it becomes bent or twisted during removal. Inspect springs (26) for load at installed height of 0.537 - 0.570. Replace any spring with pre-load less than 21 pounds at the installed height. J. Inserts (56) 1) Check inserts (56) for worn, stripped, or damaged threads. Also, check to insure that the locking feature is imbedded in the parent material. (Insert does not rotate when screws (51) are installed or removed). Replace inserts having any of the above defects according to procedures in REPAIR. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 307 Sept 01/02 CHECK 4. Procedure For Overheated Brakes Refer to IPL Figure 1001 for identification of brake assembly components. A. In the event of overheating (see para. 2. Maintenance Schedule) a hardness test must be performed on the brake housing (54) per the following procedure. Refer to Figure 302 and acceptance values. ITEM BRINELL TEST BALL DIAMETER 10 mm TEST LOAD 500 kg. NUMBER OF READINGS (EQUALLY SPACED) 3 ACCEPTABLE MINIMUM AVERAGE HARDNESS 125 Heat Damage HardnessTest – Brake Housing Figure 302 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 308 Sept 01/02 THIS PAGE INTENTIONALLY LEFT BLANK CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 401 Feb 20/96 REPAIR 1. Repair Materials Equipment/Material Description NOTE: EQUIVALENT SUBSTITUTES MAY BE USED FOR ITEMS LISTED BELOW. Aluminum Oxide Cloth (400 Grit Wet or Dry) Commercially Available Dry Cleaning Solvent Specification P-D-680 Commercially Available Cold Galvanizing Compound Specification MIL-P-26915A Type 1, Class A ZRC Products Quincy, MA Epoxy-Polyamide Primer Specification MIL-P-23377 Commercially Available Epoxy-Polyamide Topcoat Specification MIL-C-83286 Gloss Grey FED-STD-595 Color No. 16440 Commercially Available Slimsert Repair Kit K4SRW192-192L Rosan Inc. 2091 W. Coast Highway Newport Beach, California 92663 2. General Repair Procedures Repair of the brake is limited to the replacement of damaged parts and to the specific repairs listed in this section. ( Ref. IPL Fig. 1001) CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 402 Feb 20/96 REPAIR 3. Repair of Pressure Plate Subassembly (27) Center Stator Subassembly (9) and Torque Plate Subassembly (4). A. Removing Wear Pads 1) Using a 7/32 (.219) inch drill, drill out shop head of rivets and punch rivets from wear pads. C CA AU UT TIIO ON N:: E EX XE ER RC CIIS SE E C CA AR RE E T TO O A AV VO OIID D D DR RIIL LL LIIN NG G IIN NT TO O A AN ND D D DA AM MA AG GIIN NG G O OR R E EN NL LA AR RG GIIN NG G R RIIV VE ET T H HO OL LE ES S IIN N P PR RE ES SS SU UR RE E P PL LA AT TE E ((2288)),, C CE EN NT TE ER R S ST TA AT TO OR R ((1100)) A AN ND D T TO OR RQ QU UE E P PL LA AT TE E ((55)).. 2) After removing wear pads, dry blast pressure plate (28), center stator (10) and torque plate (5). Use sand or glass blasting medium. B. Re-padding Procedure 1) Check pressure plate, center stator and torque plate for cracks, using magnetic particle inspection methods. Replace pressure plate, center stator and/or torque plate if cracked. Replace pressure plate, center stator and/or torque plate if dished .020 or more. 2) Remove rust pits, corrosion pits, tool marks, and nicks up to .015 inch deep from relief slot terminal holes in center stator (10) and pressure plate (28). Terminal holes may be enlarged to a maximum diameter of .477 inch for center stator and 1.030 inch for pressure plate. After enlarging relief slot terminal holes, break sharp edges on both sides of hole. Maintain a surface finish of 50 microinches rms. Replace if pits or nicks remain in any hole after machining to maximum diameter. 3) Blend out and polish corrosion pits, tool marks, and nicks if present in outer diameter of lightning holes. 4) Clean torque plate (5), center stator (10) and pressure plate (28) in dry-cleaning solvent, specification P-D-680. 5) Repaint torque plate (except mounting bolt holes), center stator and pressure plate with Cold Galvanizing Compound. Apply a uniform coat over entire piece. Refer to manufacturers instructions for drying time. 6) Clean new wear pads in Dry-cleaning solvent, specification P-D-680, to remove protective coating, grease, and dirt. 7) Remove any burrs or raised metal around nicks on bottom of wear pads. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 403 Sept 01/02 REPAIR 8) Rivet wear pads to pressure plate, center stator, and torque plate in accordance with the following instructions: a) Install rivets so that shop head of rivet is formed in base plate counter bore (Ref. Fig. 401). C CA AU UT TIIO ON N:: T TW WO O C CR RA AC CK KS S A AR RE E P PE ER RM MIIT TT TE ED D IIN N T TH HE E S SH HO OP P H HE EA AD D O OF F T TH HE E R RIIV VE ET T,, P PR RO OV VIID DE ED D T TH HE E C CR RA AC CK KS S D DO O N NO OT T E EX XT TE EN ND D IIN NT TO O T TH HE E R RIIV VE ET T S SH HA AN NK K.. C CA AU UT TIIO ON N:: C CA AR RE E M MU US ST T B BE E E EX XE ER RC CIIS SE ED D T TO O P PR RO OD DU UC CE E T TH HE E P PR RO OP PE ER R R RIIV VE ET T S SQ QU UE EE EZ ZE E W WH HE EN N A AD DJJU US ST TIIN NG G R RIIV VE ET TIIN NG G M MA AC CH HIIN NE ES S.. E EX XC CE ES SS SIIV VE E S SQ QU UE EE EZ ZE E P PR RE ES SS SU UR RE E W WIIL LL L R RE ES SU UL LT T IIN N W WE EA AR R P PA AD D C CO OR RN NE ER R L LIIF FT T--U UP P,, W WH HIIL LE E IIN NS SU UF FF FIIC CIIE EN NT T S SQ QU UE EE EZ ZE E P PR RE ES SS SU UR RE E W WIIL LL L R RE ES SU UL LT T IIN N L LO OO OS SE E P PA AD DS S A AN ND D IIM MP PR RO OP PE ER RL LY Y F FO OR RM ME ED D H HE EA AD DS S.. b) Subassemblies must be flat within .010 inch. Thickness of newly padded subassemblies shall be as shown in Figure 401. Limits for Newly Re-padded Pressure Plate, Center Stator and Torque Plate Subassemblies Figure 401 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 404 Sept 01/02 REPAIR 4. Repair of Torque Plate (5) A. Repair torque plate lugs that have not worn to .695 or less by blending out indentations along sides of lugs. B. Repair torque plate lug outer surfaces damaged by disk shrinkage to limits shown in Figure 406. No damage or rework is permitted in the radius indicated. 5. Repair of Cylinder Housing (54) A. Blend out burrs, nicks and scratches less than .030 inch. deep on outside of housing with 400 grit, aluminum oxide paper. B. Blend corroded or damaged areas of cylinder housing axle bore (Ref. Fig. 403) with 400 grit aluminum oxide cloth. Corrosion pits or damage shall not exceed 0.12 inch diameter by 0.020 inch deep, and if pits are concentrated in an area greater than 30% of the indicated axle bore area, replace cylinder housing. The axle bore diameter after rework should be no more than ∅ 2.528 inch. C. Blend out and polish scratches not exceeding .003 inch deep in piston cavities and O-ring packing grooves with fine (400 grit) aluminum oxide paper. Maintain a surface finish of 32 microinches rms. Remove rough edges or burrs from edges of O-ring packing grooves. Break edges of O-ring packing grooves to a .005 to .010 inch radius. D. Remove and install damaged cylinder housing bushing (58) as follows: 1) Heat housing area surrounding bushing in 180o F. (82o C.) water for 30 minutes and press bushing out of housing. 2) Clean bushing seat in housing of all oil, primer residue, dirt and grease. 3) Heat bushing seat area of housing to 180o F. (82o C.) for 30 minutes and dry thoroughly with clean compressed air or a lint-free cloth. 4) Coat housing contacting surface of bushing (58) with a generous but not dripping application of MIL-P-23377 Epoxy-Polyamide Primer. Install bushing (58) immediately into heated housing while primer is still wet. C CA AU UT TIIO ON N:: S SU UP PP PO OR RT T H HO OU US SIIN NG G IIN N A AR RE EA A IIM MM ME ED DIIA AT TE EL LY Y A AR RO OU UN ND D B BU US SH HIIN NG G D DU UR RIIN NG G P PR RE ES SS S--O OU UT T A AN ND D P PR RE ES SS S--IIN N O OP PE ER RA AT TIIO ON N.. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 405 April 20/04 REPAIR E. Rework procedure to eliminate potential strut to cylinder interference and to repair damage caused by interference. 1) Refer to rework dimensions in Figure 402. Figure 402 Cylinder Rework Area and Dimensional Limits Figure 403 Axle Bore Repair Areas CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 406 Sept 01/02 REPAIR 6. Repair of Pistons (48) A. Blend out and polish scratches, nicks and burrs on seal contacting surfaces of piston to .003 inch deep. Blend repair areas into surrounding surfaces to avoid local indentation. Maintain a surface finish of 16 microinches rms. Replace pistons that are damaged deeper than .003 inch. 7. Repair of Defective Inserts (56) A. Using Rosan slimsert repair kit K4SRW192-192L replace defective slimsert(s) per manufacturers instructions. B. Install new repair insert (57). 8. Retreating and Repainting Cylinder Housing Subassembly (53) A. Rinse reworked areas with dry-cleaning solution, specification P-D-680 and dry thoroughly with filtered compressed air. W WA AR RN NIIN NG G:: C CL LE EA AN NIIN NG G S SO OL LU UT TIIO ON NS S S SH HO OU UL LD D B BE E U US SE ED D IIN N A A W WE EL LL L V VE EN NT TIIL LA AT TE ED D A AR RE EA A.. A AV VO OIID D P PR RO OL LO ON NG GE ED D IIN NH HA AL LA AT TIIO ON N O OF F F FU UM ME ES S.. B. Treat reworked areas with chromate conversion coating, specification MIL-C-5541, Class 1A. C. Apply one coat of epoxy-polyamide primer, specification MIL-P-23377 to reworked areas. C CA AU UT TIIO ON N:: D DO O N NO OT T G GE ET T P PA AIIN NT T O OR R P PR RIIM ME ER R IIN N C CY YL LIIN ND DE ER R B BO OR RE ES S,, IIN NL LE ET T O OR R B BL LE EE ED DE ER R P PO OR RT TS S,, O OR R O ON N IIN NS SIID DE E O OR R E EN ND D S SU UR RF FA AC CE ES S O OF F C CY YL LIIN ND DE ER R H HO OU US SIIN NG G B BU US SH HIIN NG G ((5566)).. D. Apply two coats of epoxy-polyamide topcoat, specification MIL-C-83286, gloss grey, FED- STD-595 color no. 16440 to reworked areas. N NO OT TE E:: R RE EF FE ER RE EN NC CE E F FIIG GU UR RE E 440044 F FO OR R L LO OC CA AT TIIO ON NA AL L P PA AIIN NT T R RE EQ QU UIIR RE EM ME EN NT TS S.. 9. Resetting Adjuster Assembly (14) A. Press retract stud (15) through friction sleeve (16) to dimension shown in Figure 405. Replace any adjuster subassembly (14) that requires less than the force specified in FITS AND CLEARANCES (Ref. Fig. 603) to move the stud (15) through the friction sleeve (16). CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 407 Sept 01/02 REPAIR Paint Requirements Figure 404 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 408 Sept 01/02 REPAIR Adjuster Reset Dimension Figure 405 Torque Plate Lug Repair Limits Figure 406 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 501 Feb 20/96 ASSEMBLY 1. Assembly Materials NOTE: EQUIVALENT SUBSTITUTES MAY BE USED FOR ITEMS LISTED BELOW. Hydraulic Fluid SAE AS1241 Type IV, Class 2, Grade A Monsanto Chemical Corp. St. Louis, MO or Standard Oil of CA San Francisco, CA Antiseize Thread Compound Specification MIL-T-5544 W.J. Ruscoe & Co. 479 Kenmore Blvd. Akron, OH 44301 Silicone Grease Dow Corning 55 O-Ring Lubricant Dow Corning Corp. Box 1767 Midland, Michigan 48640 2. General Assembly Procedures Assemble the brake assembly in accordance with the following procedures (Ref. IPL Fig. 1001): C CA AU UT TIIO ON N:: A AS SS SE EM MB BL LE E T TH HE E B BR RA AK KE E O ON N A A C CL LE EA AN N,, F FL LA AT T S SU UR RF FA AC CE E.. A AV VO OIID D D DA AM MA AG GIIN NG G B BR RA AK KE E P PA AR RT TS S.. N NO OT TE E:: IIT T IIS S R RE EC CO OM MM ME EN ND DE ED D T TH HA AT T A AL LL L O O--R RIIN NG GS S A AN ND D W WIIP PE ER R R RIIN NG GS S R RE EM MO OV VE ED D A AT T D DIIS SA AS SS SE EM MB BL LY Y B BE E R RE EP PL LA AC CE ED D W WIIT TH H N NE EW W O O--R RIIN NG GS S A AN ND D W WIIP PE ER R R RIIN NG GS S A AT T A AS SS SE EM MB BL LY Y.. A. Lubricate threads of bleeder seat (33) and O-ring (34) with Dow Corning 55 O-ring Lubricant. Install O-ring on bleeder seat, and then screw bleeder seat into cylinder housing (54). Torque to 200 pound-inches. Screw bleeder screw (32) into bleeder seat. C CA AU UT TIIO ON N:: D DO O N NO OT T U US SE E IIM MP PA AC CT T O OR R P PO OW WE ER R W WR RE EN NC CH HE ES S T TO O IIN NS ST TA AL LL L O OR R T TO OR RQ QU UE E H HY YD DR RA AU UL LIIC C F FIIT TT TIIN NG GS S.. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 502 Feb 20/96 ASSEMBLY B. Lubricate threads of plug (35) and O-ring (36) with Dow Corning 55 O-ring Lubricant. Install O-ring (36) on plug (35), and then screw plug into port below the bleeder seat (33). Torque to 150 pound-inches. C. Lubricate O-rings (39 & 40) and threads of shuttle valve body (41) with Dow Corning 55 O- ring Lubricant. Install O-ring (40) in groove on the bottom end of shuttle valve body (41). Install O-ring (39) on shuttle valve body in radius between the hex head and top of the body threads. Screw shuttle valve into top port in cylinder housing (54) and torque to 200 pound-inches. D. Lubricate threads of fitting (45) and O-ring (46) with Dow Corning 55 O-ring Lubricant. Install O-ring on fitting, and then screw fitting in inlet port below the shuttle valve subassembly (38). Torque to 150 pound-inches. E. Install torque liners (52) onto cylinder housing (54) and secure with screws (51). Make sure edge of torque liner mates flat with edge of torque slot in cylinder housing to insure adequate clearance between cylinder and strut of aircraft. After screws have been tightened, lockwire as required. F. Lubricate O-ring packings (50) with a coat of the same fluid used in the brake assembly then install the O-rings in the inner groove of the piston bore. G. Install wiper rings (49) into outer groove of piston bore (groove nearest machined face.) H. Lubricate the inside edge of the wiper rings and the piston bore with a liberal amount of brake fluid. Place the piston (48) into the bore and work in by hand alternately rotating until piston seats in the bottom of the bore. Insulators (47), may then be placed in the pistons (chamfered end first). I. Prior to installing retract housing subassembly (22) into cylinder housing (54), pre-install spring (26), washer (25) and snap ring (24) into retract housing (23). Retract housings may now be inserted into the cylinder housing. N NO OT TE E:: L LIIP P O ON N R RE ET TR RA AC CT T H HO OU US SIIN NG G S SH HO OU UL LD D M MA AT TE E W WIIT TH H S SU UR RF FA AC CE E O OF F C CO OU UN NT TE ER RB BO OR RE E W WH HE EN N C CO OR RR RE EC CT TL LY Y IIN NS ST TA AL LL LE ED D.. J. Install pressure plate subassembly (27). Place three retract base subassemblies (19) into slots in pressure plate. Thread adjuster subassemblies (14) into their respective retract base subassemblies. Torque 30 - 35 pound-inches. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 503 Feb 20/96 ASSEMBLY K. Install disc (8), Center Stator subassembly (9), disc (8) onto torque plate subassembly (4). L. Install Cylinder Subassembly (53) with Pressure Plate Subassembly (27) attached onto the torque plate subassembly (4), aligning holes with the tapped holes on the lugs of the torque plate (5). M. Coat threads of bolts (2) and bearing surfaces of bolt heads and washers (3) with antiseize compound, specification MIL-T-5544. N. Install countersunk washer (3) onto bolt (2) and slide five bolts through cylinder housing and thread into torque plate (5). N NO OT TE E:: W WH HE EN N IIN NS ST TA AL LL LIIN NG G W WA AS SH HE ER R ((33)) O ON NT TO O B BO OL LT T ((22)) T TH HE E C CO OU UN NT TE ER RS SIIN NK K O ON N T TH HE E W WA AS SH HE ER R M MU US ST T F FA AC CE E B BO OL LT T H HE EA AD D O OR R B BO OL LT T F FA AIIL LU UR RE E M MA AY Y R RE ES SU UL LT T.. Lubtork bolts to 150 pound-inches, and safety wire with MS20995C32 per MS33540. C CA AU UT TIIO ON N:: D DO O N NO OT T U US SE E IIM MP PA AC CT T O OR R P PO OW WE ER R W WR RE EN NC CH HE ES S T TO O IIN NS ST TA AL LL L O OR R T TIIG GH HT TE EN N B BR RA AK KE E B BO OL LT TS S.. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 504 Feb 20/96 THIS PAGE INTENTIONALLY LEFT BLANK CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 601 Sept 01/02 FITS AND CLEARANCES ITEM NO. (REF. IPL) (FIG. 1001) NOMENCLATURE REPLACEMENT DIMENSION (IN INCHES) 4 TORQUE PLATE SUBASSEMBLY PAD THICKNESS OUT-OF-FLAT LUG WIDTH LUG HEIGHT 0.086 (MINIMUM) 0.020 (MAXIMUM) 0.695 (MINIMUM) 0.407 (MINIMUM) 8 DISC TOTAL THICKNESS MIX THICKNESS PER SIDE OUT-OF-FLAT TANG WIDTH 0.250 (MINIMUM) 0.015 (MINIMUM) 0.020 (MAXIMUM) 0.457 (MINIMUM) 9 CENTER STATOR SUBASSEMBLY PAD THICKNESS PER SIDE TOTAL THICKNESS (including pads) TOTAL THICKNESS (stator only) OUT-OF-FLAT KEYSLOT WIDTH KEYSLOT WIDTH 0.086 (MINIMUM) 0.407 (MINIMUM) 0.235 (MINIMUM) 0.020 (MAXIMUM) 0.770 (MINIMUM) 0.790 (MAXIMUM) 27 PRESSURE PLATE SUBASSEMBLY PAD THICKNESS TOTAL THICKNESS (including pads) TOTAL THICKNESS (plate only) OUT-OF-FLAT KEYSLOT WIDTH KEYSLOT WIDTH 0.086 (MINIMUM) 0.269 (MINIMUM) 0.183 (MINIMUM) 0.020 (MAXIMUM) 0.770 (MINIMUM) 0.790 (MAXIMUM) 7, 12 AND 30 WEAR PAD WIDTH (MEASURED ON HORIZONTAL CENTERLINE) 1.375 (MINIMUM) 48 PISTON OUTSIDE DIAMETER 1.370 (MINIMUM) 53 CYLINDER SUBASSEMBLY PISTON BORE DIAMETER 1.378 (MAXIMUM) 58 BUSHING INSIDE DIAMETER (DIM. ∅A) OVERALL LENGTH (DIM. B) 1.815 (MAXIMUM) 0.998 (MINIMUM) 58A BUSHING (ref Figure 300) INSIDE DIAMETER (DIM. ∅A) OVERALL LENGTH (DIM. B) 1.815 (MAXIMUM) 1.014 (MINIMUM) Wear and Distortion Tolerances Figure 601 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 602 Feb 20/96 FITS AND CLEARANCES ITEM NO. (REF. IPL) (FIG. 1001) NOMENCLATURE TORQUE VALUE 2 BRAKE BOLTS 150 POUND-INCHES (LUBTORK) 14 ADJUSTER SUBASSEMBLY 30 TO 35 POUND-INCHES 33 BLEEDER SEAT 200 POUND-INCHES 35 PLUG 150 POUND-INCHES 38 SHUTTLE VALVE 200 POUND-INCHES 45 FITTING 150 POUND-INCHES Torque Value Table Figure 602 ITEM NO. (REF. IPL) (FIG. 1001) NOMENCLATURE PULL THROUGH FORCE MINIMUM MAXIMUM 14 ADJUSTER SUBASSEMBLY 50 LBS. 150 LBS. Adjuster Subassembly Pull Through Force Data Figure 603 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 701 Feb 20/96 TESTING 1. General Test the brake assembly in accordance with the following procedure. (Ref. IPL Fig. 1001) 2. Testing Procedure A. Test brake assembly with a hydraulic test stand capable of applying 820 psi hydraulic pressure to brake. Attach inlet line from test stand to shuttle valve (38) and tighten. C CA AU UT TIIO ON N:: H HY YD DR RA AU UL LIIC C T TE ES ST T S ST TA AN ND D M MU US ST T C CO ON NT TA AIIN N S SA AE E A AS S11224411 T Tyyp pee IIV V,, C Cllaassss 22,, G Grraad dee A A H HY YD DR RA AU UL LIIC C F FL LU UIID D.. B. Apply pressure and bleed brake. Fitting (45) should be open to the atmosphere. C. Apply and release brake pressure (820 psi) several times and check for proper brake release. Discs (8) should be free to rotate when brake is released. D. Apply 820 psi for 15 to 30 seconds; check for leaks. Check carefully for leaks through the emergency pneumatic inlet fitting (45). No leaks are permitted. E. Disconnect inlet line from shuttle valve (38) and connect to emergency pneumatic inlet fitting (45). Shuttle valve should be open to atmosphere. F. Apply 820 psi for 15 to 30 seconds. Check carefully for leaks through the shuttle valve. No leakage through shuttle valve is permissible. G. If any leakage is observed through fitting (45) or shuttle valve (38), replace shuttle valve and retest. H. Drain excess hydraulic fluid from brake after completion of test and install suitable protective caps over shuttle valve and emergency pneumatic inlet fitting. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 702 Feb 20/96 THIS PAGE INTENTIONALLY LEFT BLANK CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 801 Feb 20/96 TROUBLE SHOOTING Trouble Cause Correction Hydraulic fluid leaking from brake assembly Defective hydraulic Connection Tighten connection or replace fitting Defective O-ring Replace O-ring Piston or cylinder housing worn or damaged Replace piston and/or cylinder housing Brake not engaging correctly Air in brake Bleed brake Obstruction in hydraulic line or fluid passage Remove obstruction Pistons sticking Replace piston O-ring and wiper rings Pistons damaged Replace pistons Cylinder housing damaged Replace cylinder housing Torque plate damaged Replace torque plate Pressure plate, rotating disk or center stator not moving freely on torque plate Repair or replace defective plate or disk Brake not releasing correctly. Obstruction in hydraulic line or fluid passage Remove obstruction Pistons sticking Replace piston O-Ring and wiper rings Trouble Shooting Chart (Sheet 1 of 2) Figure 801 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 802 Feb 20/96 TROUBLE SHOOTING Trouble Cause Correction Brake not releasing correctly (cont’d.) Pistons damaged Replace pistons Cylinder housing damaged Replace cylinder housing Torque plate damaged Replace torque plate Pressure plate, rotating disc or center stator not moving freely on torque plate Repair or replace defective plate or disc Disc or center stator excessively dished Replace disc or center stator Trouble Shooting Chart (Sheet 2 of 2) Figure 801 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 901 Feb 20/96 STORAGE INSTRUCTIONS 1. Brake Assembly A. Brake hydraulic and pneumatic inlet fittings should be protected during shelf storage by suitable caps or other means. B. The brake assembly should be stored in moisture-barrier material and a sealed corrugated cardboard container, or equivalent. C. The brake assembly should be stored in a clean, dry storeroom. The desirable storeroom temperature range is from 50o to 70o F. (10o to 21o C.). If this temperature range cannot be maintained, temperatures as high as +125o F. (+52o C.) and as low as -20o F. (-29o C.) can be tolerated for short periods. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 902 Feb 20/96 THIS PAGE INTENTIONALLY LEFT BLANK CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 1001 Feb 20/96 ILLUSTRATED PARTS LIST 1. Introduction A. The Illustrated Parts List (IPL) section lists and illustrates the procurable parts of the Parker Hannifin assembly covered in this publication. The components are listed in the order of disassembly. B. The Figure Item column provides the cross reference between the parts list and IPL Figure 1001. C. The Part Number column gives the part number of the item, which is stamped on the part when practical. This number should be used when ordering parts. D. The Nomenclature column gives the basic noun name of each part, together with any specifications required to identify the part listed. The descriptions are indented under the column heading to show the relationship of the parts to their subassemblies and to the assembly. E. The Units Per Assembly column gives the number of parts required for each assembly or subassembly. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 1002 Feb 20/96 ILLUSTRATED PARTS LIST Illustrated Parts List (IPL) for 30-189A Brake Assembly Figure 1001 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 1003 Feb 20/96 ILLUSTRATED PARTS LIST 2. Parts List FIGURE ITEM PART NUMBER NOMENCLATURE UNITS PER ASSY 1 30-189A BRAKE ASSEMBLY 1 2 103-85300 BOLT (MS21250H05022) 5 3 095-02800 WASHER (MS20002C5) 5 4 075-17600 TORQUE PLATE SUBASSEMBLY 1 5 * TORQUE PLATE 1 6 105-01300 RIVET 24 7 109-00100 WEAR PAD 12 8 159-03500 DISC 2 9 242-00700 CENTER STATOR SUBASSEMBLY 1 10 * CENTER STATOR 1 11 105-01200 RIVET 32 12 109-00100 WEAR PAD 32 13 111-07900 RETRACT ASSEMBLY 3 14 111-08200 ADJUSTER SUBASSEMBLY 3 15 * STUD 3 16 * FRICTION SLEEVE 3 17 * SLEEVE RETAINER 3 18 * SPACER 3 19 111-08300 RETRACT BASE SUBASSEMBLY 3 20 * RETRACT BASE 3 21 * INSERT 3 * PART NOT PROCURABLE CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 1004 Feb 20/96 ILLUSTRATED PARTS LIST Illustrated Parts List (IPL) for 30-189A Brake Assembly Figure 1001 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 1005 Feb 20/96 ILLUSTRATED PARTS LIST FIGURE ITEM PART NUMBER NOMENCLATURE UNITS PER ASSY 22 111-08400 RETRACT HOUSING SUBASSEMBLY 3 23 071-00200 RETRACT HOUSING 3 24 155-07800 SNAP RING(WALDES N5000-62MD) 3 25 095-13600 WASHER (MS20002-5) 3 26 082-10400 SPRING (LEE LC-072H-2) 3 27 073-08200 PRESSURE PLATE SUBASSEMBLY 1 28 * PRESSURE PLATE 1 29 105-01100 RIVET 24 30 109-00100 WEAR PAD 12 31 183-00100 BLEEDER CAP 1 32 079-00300 BLEEDER SCREW 1 33 081-00600 BLEEDER SEAT 1 34 101-28000 O-RING (PARKER 3-907) 1 35 104-05400 PLUG (AN814-4LK) 1 36 101-28200 O-RING (NAS1612-4) 1 37 104-06500 EXPANDER FITTING 1 38 111-09801 ‡ SHUTTLE VALVE ASSEMBLY 1 39 101-28000 O-RING (PARKER 3-907) 1 40 101-28100 O-RING (NAS 1611-013) 1 41 * SHUTTLE VALVE BODY 1 42 * O-RING 1 (DELETED) 44 * SPOOL VALVE 1 * PART NOT PROCURABLE ‡ Shuttle Valve 111-09801 has superseded both P/N 111-07800 and 111-09800. Refer to Sevice Bulletin SB7046. Note - SB7046 replaces PRM56, which allowed an optional field replacement of 111-07800 with 111-09800. CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 1006 Feb 20/96 ILLUSTRATED PARTS LIST Illustrated Parts List (IPL) for 30-189A Brake Assembly Figure 1001 CM30-189A COMPONENT MAINTENANCE MANUAL FOR BRAKE ASSEMBLY 30-189A Aerospace Page 1007 Sept 01/02 ILLUSTRATED PARTS LIST FIGURE ITEM PART NUMBER NOMENCLATURE UNITS PER ASSY 45 104-05200 FITTING (AN815-4K) 1 46 101-28200 O-RING (NAS1612-4) 1 47 088-01900 INSULATOR 6 48 062-06300 PISTON 6 49 107-00500 WIPER RING 6 50 101-27900 O-RING (NAS1611-220) 6 51 102-07100 SCREW (AN501A10-6) 4 52 205-00900 TORQUE LINERS 2 53 091-17800 CYLINDER SUBASSEMBLY 1 54 * CYLINDER HOUSING 1 55 * * * PLUG 5 56 * INSERT (ROSAN SR192L) 6 57 * * * INSERT (ROSAN SRW192L) (REPAIR ONLY) 6 58 145-10200 BUSHING, REPLD BY ITEM 58A 1 58A 145-15400 BUSHING, REPLS ITEM 58 1 * * * 235-01100 HEAT STACK-FACTORY REBUILT 1 DISC (NEW) 2 PRESSURE PLATE SUBASSEMBLY (REBUILT) 1 CENTER STATOR SUBASSEMBLY (REBUILT) 1 TORQUE PLATE SUBASSEMBLY (REBUILT) 1 * PART NOT PROCURABLE * * PART NOT ILLUSTRATED * * * OPTIONAL REPLACEMENT EQUIPMENT Replaced by REPLD BY The part in the part number column is replaced by and interchangeable with the item number shown in the notation. Replaces REPLS The part in the part number column replaces and is interchangeable with the item number shown in the notation. Manufacturer: Parker Hannifin Corporation Aircraft Wheel and Brake Division 1160 Center Road Avon, Ohio 44011 U.S.A. Page T-1 October 22, 2010 Cessna Citation Model 500 & 501 Series Aircraft Citation Model 550 & 551 Series Aircraft Component Maintenance Publication Main Wheel Assembly Parker Hannifin Part No. 40-239 CM40-239 Revision E This document contains information that is confidential and proprietary to Parker Hannifin Corporation (“Parker”). This document is furnished on the understanding that the document and the information it contains will not be copied or disclosed to others except with the written consent of Parker, will not be used for any purpose other than conducting business with Parker, and will be returned and all further use discontinued upon request by Parker. Copyright Parker. Year of copyright is first year indicated on this document. All rights reserved. U.S. EXPORT CONTROLLED – Dissemination is restricted by the Export Administration Act of 1979 (50 U.S.C. App. 2401, et seq) and the Export Administration Regulations. Publication No.: CM40-239, Revision E CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Revision Highlights Proprietary Information – Page INTRO-1 Page 1 May 26/88 Revision A, dated May 26, 1988 Pages which have been revised are listed below, together with the highlights of the revision. Please delete the affected pages and insert Revision A, dated May 26, 1988. Enter Revision A, dated May 26, 1988 and insertion date on the Record of Revisions Sheet. HIGHLIGHTS Page No. Description of Change List Of Effective Pages Revised to reflect latest revision. (Deleted Introduction Pages 3 - 7) Introduction, Page 2 Added “DISTRIBUTORS” paragraph 301 Added CAUTION about spinning bearings with compressed air. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Revision Highlights Page 2 Proprietary Information – Page INTRO-1 April 01/91 Revision B, dated April 1, 1991 Please delete the affected pages and insert Revision B, dated April 1, 1991. Enter Revision B, dated April 1, 1991 and insertion date on the Record of Revisions Sheet. HIGHLIGHTS Page No. Description of Change Introduction, Page 1 Removed old 1-800 telephone number. Description & Operation, Paragraph 1.F - . . . stainless steel heat shield clips . . . was . . . Page 1 stainless steel tire heat shield . . . 201 Paragraph 2.G - . . . heat shield clips (25) . . . was . . . heat shields (25) . . . 302 Paragraph 3.B - . . . heat shield clips (25) . . . was . . . heat shields . . . 506 Paragraph 6.D - . . . heat shield clips (25) . . . was . . . heat shield segments (25) . . . 507 Paragraph 6.G - . . . Align the heat shield clips (25) . . . was . . . Align the 3 segment heat shield (25) . . . Paragraph 6.G - . . . Deleted sentence – Secure the heat shield to key drives . . . Deleted Note . . . When aligning heat shield segments . . . Paragraph 6.H - . . . Deleted sentence . . . Rivets should be installed starting from the center . . . 508 Completely revised graphics to show new heat shield clip and drive key configuration. 1002 Revised graphics to show new heat shield clip and drive key configuration. 1004 Item 25 – 157-01600 Heat Shield Clip, qty. 9 was 157-01300 Heat Shield, qty. 3. Item 26 – 205-00801 Drive Key, qty. 9 was 205- 00800 Drive Key, qty. 9. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Revision Highlights Proprietary Information – Page INTRO-1 Page 3 Jan 03/94 Revision C, dated January 3, 1994 Pages which have been revised are listed below, together with the highlights of the revision. Please delete the affected pages and insert Revision C, dated January 3, 1994. Enter Revision C, dated January 3, 1994 and insertion date on the Record of Revisions Sheet. HIGHLIGHTS Page No. Description of Change Introduction, Page 1 FAX: (216) 937-6416 -was- Telex: #21257 PHAVUR Description & Operation, Flange of inner wheel half has nine slots that engage the drive Page 1 tangs of the rotating brake discs. Steel key drives are riveted to the wheel flange to provide a hard wearing surface for the disc tangs and to prevent damage to the softer metal of the wheel. Stainless steel heat shields and heat shield clips are held in place on the outer surface of the inner wheel half flange by the same rivets used to attach the key drives to the wheel. -was- Flange of inner wheel half has nine slots that engage the drive tangs of the rotating brake discs. Steel key drives are riveted to the wheel flange to provide a hard wearing surface for the disc tangs and to prevent damage to the softer metal of the wheel. A stainless steel heat shield is held in place on the outer surface of the inner wheel half flange by the same rivets used to attach the key drives to the wheel. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Revision Highlights Page 4 Proprietary Information – Page INTRO-1 Jan 03/94 Revision C Highlights (Cont’d) Page No. Description of Change 201 Fuse plugs (22), bearing cups (16 and 27), key drives (26), heat shields (28), and heat shield clips (25) should not be removed from the wheel halves unless replacement is required. -was- Fuse plugs (22), bearing cups (16 and 27), key drives (26), and heat shield clips (25) should not be removed from the wheel halves unless replacement is required. Note: Inflation valve, fuse plugs, bearing cups, key drives, heat shields, and heat shield clips must be removed if paint is to be stripped from wheel halves. -was- Note: Inflation valve, fuse plugs, bearing cups, key drives, and heat shields, must be removed if paint is to be stripped from wheel halves. Added Note: Paint removal procedures are required only for complete overhaul which shall occur every 500 landings. If 500 landings have not been accumulated at the time of a tire change, do not remove paint. All other component overhaul procedures required every tire change. 302 Completely disassemble the wheel prior to paint removal. Remove fuse plugs (22), inflation valve (15), heat shields (28), heat shield clips (25), key drives (26) and bearing cups (16 and 17). -was- Completely disassemble the wheel prior to paint removal. Remove fuse plugs (22), inflation valve (15), heat shield clips (25), key drives (26) and bearing cups (16 and 17). CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Revision Highlights Proprietary Information – Page INTRO-1 Page 5 Jan 03/94 Revision C Highlights (Cont’d) HIGHLIGHTS Page No. Description of Change 402 Added Noottee:: ddyyee ppeenneettrraanntt pprroocceedduurree ffoorr w whheeeellss aarree rreeqquuiirreedd oonnllyy ffoorr ccoom mpplleettee oovveerrhhaauull w whhiicchh sshhaallll ooccccuurr eevveerryy 550000 llaannddiinnggss.. IIff 550000 llaannddiinnggss hhaavvee nnoott bbeeeenn aaccccuum muullaatteedd aatt tthhee ttiim mee ooff ttiirree cchhaannggee,, ddoo nnoott ddyyee ppeenneettrraanntt iinnssppeecctt w whheeeellss.. A Allll ootthheerr ccoom mppoonneenntt oovveerrhhaauull procedures required every tire change. 403 Paragraph 3.I.: Added the following: If any wheel bolt exhibits cracks, replace all nine (9) bolts. 506 Replacing Defective Key Drives (26), Heat Shields (28), and Heat Shield Clips (25) From Inner Wheel Half (21) -was- Replacing Defective Key Drives (26), and Heat Shield Clips (25) From Inner Wheel Half (21) Remove and discard key drives (26), heat shields (28), and heat shield clips (25). -was- Remove and discard key drives (26), and heat shield segments (25). CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Revision Highlights Page 6 Proprietary Information – Page INTRO-1 Jan 03/94 Revision C Highlights (Cont’d) HIGHLIGHTS Page No. Description of Change 507 Using one .125 dia. Cleco, fasten one 157-01900 heat shield, one 220055--0044440000 ddrriivvee kkeeyy,, aanndd oonnee 115577--0011660000 hheeaatt sshhiieelldd cclliipp ttoo tthhee iinnnneerr w whheeeell hhaallff aass sshhoow wnn iinn F Fiigguurree 550033.. Install one 105-09900 rivet through c’sunk side of the wheel, through tthhee hhoollee aaddjjaacceenntt ttoo tthhee C Clleeccoo.. S Sqquueeeezzee tthhee rriivveett aanndd iinnssppeecctt ttoo IInnssuurree tthhaatt tthhee ..118877 m miinn.. cclliinncchh ddiiaa.. R Reeqquuiirreem meenntt iiss oobbttaaiinneedd.. R Reeppeeaatt tthhiiss pprroocceedduurree ttoo iinnssttaallll aallll eeiigghhtteeeenn 220055--0044440000 ddrriivvee kkeeyyss,, nniinnee 115577--0011990000 hheeaatt sshhiieellddss,, nniinnee 115577--0011660000 hheeaatt sshhiieelldd cclliippss,, aanndd eeiigghhtteeeenn 110055--0099990000 rriivveettss.. -was- Install new key drives (26) so that holes in key drives align with holes oonn w whheeeell ffllaannggee.. A A ffllaatt sstteeeell bbaarr ccaann bbee uusseedd ttoo ddiissttrriibbuuttee tthhee llooaadd eevveennllyy aaccrroossss tthhee kkeeyy ddrriivvee w whhiillee ttaappppiinngg tthhee kkeeyy ddrriivvee iinnttoo ppoossiittiioonn.. Align the heat shield clips (25) over the key drives so that the tabs on tthhee hheeaatt sshhiieelldd eennggaaggee iinnttoo tthhee sslloottss oonn tthhee w whheeeell ffllaannggee.. Install rivets (24) one at a time and squeeze to the clinch diameter shown in Figure 503. 508 Figure 503 was altered to show the new key drive (205-04400) and the new heat shield (157-01900) geometry. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Revision Highlights Proprietary Information – Page INTRO-1 Page 7 Jan 03/94 Revision C Highlights (Cont’d) HIGHLIGHTS Page No. Description of Change 601 If removed, install the bearing cups (16 and 27), key drives (26), hheeaatt sshhiieellddss ((2288)),, aanndd hheeaatt sshhiieelldd cclliippss ((2255)) iinn aaccccoorrddaannccee w wiitthh R RE EP PA AIIR R.. -was- If removed, install the bearing cups (16 and 27), key drives (26) aanndd hheeaatt sshhiieellddss ((2255)) iinn aaccccoorrddaannccee w wiitthh R RE EP PA AIIR R.. 1002 The Illustrated Parts List was revised to show the new key drive ((220055--00444400))00 aanndd tthhee nneew w hheeaatt sshhiieelldd ((115577--0011990000)) ggeeoom meettrryy.. 1003 Figure Units Item Part Number Nomenclature Per Assy 7 154-06200 Grease Seal 2 -was- 7 154-05400 Grease Seal 2 24 105-09900 Rivet (MS20426-AD4-9) 36 -was- 24 105-01700 Rivet (MS20426-AD4-8) 36 25 157-01600 Heat Shield Clip 9 -was- 25 157-01300 Heat Shield 3 26 205-04400 Key Drive 18 -was- 26 205-00801 Key Drive 9 -added- 28 157-01900 Heat Shield 9 CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Revision Highlights Page 8 Proprietary Information – Page INTRO-1 Nov 01/02 Revision D, dated November 01, 2002 DCN Number 0353-44 Highlights Revision D contains all pages of the manual. Pages which have been added or revised are outlined below with a description of change. Please retain all Highlights pages, inserting them into the manual for future reference. Page No. Description of Change All Pages Retyped into electronic format. Record of Revisions Update to show latest revision. List Of Effective Pages Update to show latest page revisions. Introduction Page 1 Contact information updated. Disassembly (ADD) instruction to disassembly procedure, para. 2.: Page 201 “A. Jack aircraft per aircraft maintenance manual until tire is clear of ground and fully deflate tire. Remove any lockwire securing screws (2) on hubcap subassembly (3).” “B. Remove screws (2) and hubcap subassembly (3) from outer wheel half subassembly (13).: “C. Remove and retain two screws securing axle nut and anti-skid transducer, then remove and retain axle nut and tanged washer.” (NOW) Para. “D. Remove wheel assembly from axle and place on a clean flat surface.” (WAS) Para. “A. place wheel assembly on a clean flat surface.” Re-identify remaining steps. Page 202 (ADD) page. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Revision Highlights Proprietary Information – Page INTRO-1 Page 9 Jan 03/94 Revision D (cont;d) Page No. Description of Change Check Page 406 (ADD) blank page for document formatting purposes. Assembly Para. 2.D. Page 601 (NOW) “…Torque to 50 to 60 in-lb.” (WAS) “…Torque to 35 in-lb.” Page 603 Para. 2.P. (ADD) “Torque screws 25 to 30 in-lb.” Para. 2.O. (NOW) “Pack bearing cones (8) with clean bearing grease, specification MIL-G-81322 and install in wheel assembly. Para. 2.O. (WAS) “Pack bearing cones (8) with clean bearing grease, specification MIL-G-81322 and bag separately until wheel is installed on aircraft. Para. 2.P. (NOW) “Install grease seals (7). Para. 2.P. (WAS) “Bag grease seals (7) separately and Install hubcap subassembly (3) with screws (2) on outer wheel half subassembly (13) until wheel is installed on aircraft. Para. 2.Q. (NOW) “Install hubcap subassembly (3) with screws (2) on outer wheel half subassembly (13). Torque screws 25 to 30 in-lb. Para. 2.Q. (WAS) “Bag grease seals (7) separately and Install hubcap subassembly (3) with screws (2) on outer wheel half subassembly (13) until wheel is installed on aircraft. Para. 2.R. (NOW) identified as “2.R.” (WAS) identified as “2.Q.” Page 604 (ADD) blank page for document formatting purposes. Storage Instructions Page 701 (ADD) to paragraph 3: “Plug or cover bearing hub area during storage to prevent contamination.” Page 702 (ADD) blank page for document formatting purposes. Fits and Clearances Table 801, Torque Values Page 801 (NOW) for item 15, “50 to 60 in-lb. (WAS) “35 in-lb.” Page 802 (ADD) blank page for document formatting purposes. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Revision Highlights Proprietary Information – Page INTRO-1 Page 1 of 1 October 22, 2010 TO: HOLDERS OF CM40-239 COMPONENT MAINTENANCE MANUAL WITH ILLUSTRATED PARTS LIST FOR MAIN WHEEL ASSEMBLY PART NO. 40-239. Attached to this transmittal letter is Revision E of CM40-239 (dated October 22, 2010) Revision E, Dated October 22, 2010 REVISION E CONTAINS ALL PAGES OF THE MANUAL. Pages that have been added or revised are outlined below together with the highlights of the revision. Please retain all REVISION HIGHLIGHTS pages, inserting them into the manual for future reference. REVISION HIGHLIGHTS Section/Page No. Description Of Change As Follows: DCN 0391-57 Cover Page (DELETE) cover page to comply with current standard practice. T-1 Update title page to comply with current standard practice. RR-1 Update to reflect current revision. LEP-1 Update to reflect current revision. INTRO-1 (NOW) 40-239 (WAS) 040-23901 Update Parker contact information. Update Data Rights statement and move to page INTRO-1. (ADD) Export compliance statement. INTRO-2 (NOW) 40-239 (WAS) 040-23901 Description & Operation Leading Particulars Pg 2 (NOW) Mobile Aviation Grease SHC 100 (WAS) MIL-G-81322 Cleaning Paragraph 2.C. Pg 301 (NOW) Mobile Aviation Grease SHC 100 (WAS) MIL-G-81322 Assembly Assembly Materials Pg 601 (NOW) Mobile Aviation Grease SHC 100 (WAS) MIL-G-81322 Paragraph 2.O. Pg 603 (NOW) Mobile Aviation Grease SHC 100 (WAS) MIL-G-81322 Storage Instructions Paragraph 3. Pg 701 (NOW) Mobile Aviation Grease SHC 100 (WAS) MIL-G-81322 CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Record of Revision Proprietary Information – Page INTRO-1 Page RR-1 October 22, 2010 RECORD OF REVISIONS REV NO. ISSUE DATE DATE INSERTED BY REV NO. ISSUE DATE DATE INSERTED BY A 05-26-88 05-26-88 JW B 04-01-91 04-01-91 JW C 01-03-94 01-03-94 BB D 11-01-02 11-01-02 AWB E 10-22-2010 10-22-2010 PH CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Service Bulletin List Proprietary Information – Page INTRO-1 Page SB-1 April 08/88 SERVICE BULLETIN LIST Note: Parker Hannifin Service Bulletins are issued in order to provide general information on product line concerns. The bulletin listings contained herein identify subject matter directly related to the support and function of the Wheel Assembly and Components. SERVICE BULLETIN NO. REV NO. DATE INCORPORATED SERVICE BULLETIN NO REV NO. DATE INCORPORATED CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 List of Effective Pages Proprietary Information – Page INTRO-1 Page LEP-1 October 22, 2010 LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE SUBJECT PAGE DATE Title Page Oct 22, 2010 Repair 501 April 08/88 502 April 08/88 Record of 1 Oct 22, 2010 503 April 08/88 Revision 504 April 08/88 505 April 08/88 Service 1 April 08/88 506 Jan 03/94 Bulletin List 507 Jan 03/94 508 Jan 03/94 List of 1 Oct 22, 2010 Effective Pages Assembly 601 Oct 22, 2010 602 April 08/88 Table of 1 April 08/88 603 Oct 22, 2010 Contents 2 April 08/88 604 Blank Introduction 1 Oct 22, 2010 Storage 701 Oct 22, 2010 2 Oct 22, 2010 Instructions 702 Blank Description and 1 Jan 03/94 Fits and 801 Nov 01/02 Operation 2 Oct 22, 2010 Clearances 802 Blank Testing 101 April 08/88 Illustrated 1001 April 08/88 102 April 08/88 Parts List 1002 Jan 03/94 1003 Jan 03/94 Disassembly 201 Nov 01/02 1004 Jan 03/94 202 Nov 01/02 Cleaning 301 Oct 22, 2010 302 Jan 03/94 Check 401 April 08/88 402 April 08/88 403 Jan 03/94 404 April 08/88 405 April 08/88 406 Blank CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Table of Contents Proprietary Information – Page INTRO-1 Page T/C-1 April 08/88 TABLE OF CONTENTS Subject Page INTRODUCTION 1 DESCRIPTION AND OPERATION 1 1. Description and Operation 1 2. Handling Procedures 1 3. Leading Particulars 2 TESTING 101 1. General 101 2. Testing Procedures 101 DISASSEMBLY 201 1. General 201 2. Disassembly Procedures 201 CLEANING 301 1. Cleaning Materials 301 2. Cleaning Procedures 301 3. Paint Removal Procedures 302 CHECK 401 1. Check Materials 401 2. General 401 3. Detailed Check 401 CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Table of Contents Page T/C-2 Proprietary Information – Page INTRO-1 April 08/88 TABLE OF CONTENTS Subject Page REPAIR 501 1. Repair Materials 501 2. General 501 3. Repair of Wheel Halves 502 4. Repainting 504 5. Replacing Defective Bearing Cups 504 6. Replacing Defective Key Drives and Heat Shields 506 7. Replacing Fuse Plugs 507 8. Replacing Defective Inserts 507 ASSEMBLY 601 1. Assembly Materials 601 2. Assembly Procedures 601 STORAGE INSTRUCTIONS 701 FITS AND CLEARANCES 801 ILLUSTRATED PARTS LIST 1001 1. Introduction 1001 2. Parts List 1003 CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Introduction Proprietary Information – Page INTRO-1 Page INTRO-1 October 22, 2010 INTRODUCTION This manual is published for the guidance of personnel responsible for the overhaul and/or maintenance of the Parker Hannifin 40-239 Wheel Assembly covered in this publication. The procedures outlined in this manual may be altered if better and/or more economical methods can be employed by the individual facilities. However, alternative procedures must not reduce the efficiency of operation of the assembly. NOTE: All torque values and specified limits or values set by Parker Hannifin Engineering and contained herein must be strictly observed and not deviated from. While Parker Hannifin Corporation represents that the information contained in this manual was current at the time of publication, it is recommended that the user inquire as to the latest revision level in existence before proceeding with overhaul or maintenance operations. This can be accomplished by contacting the Product Support Department of the Aircraft Wheel & Brake Division at the following address or numbers: Parker Hannifin Corporation Website: www.parker.com Aircraft Wheel & Brake Division E-mail: clevelandwbhelp@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 Data Rights This document contains information that is confidential and proprietary to Parker Hannifin Corporation (“Parker”). This document is furnished on the understanding that the document and the information it contains will not be copied or disclosed to others except with the written consent of Parker, will not be used for any purpose other than conducting business with Parker, and will be returned and all further use discontinued upon request by Parker. Copyright Parker. Year of copyright is first year indicated on this document. All rights reserved. Export Statement U.S. EXPORT CONTROLLED – Dissemination is restricted by the Export Administration Act of 1979 (50 U.S.C. App. 2401, et seq) and the Export Administration Regulations. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Introduction Page INTRO-2 Proprietary Information – Page INTRO-1 October 22, 2010 INTRODUCTION TSO NOTICE This assembly carries a “TSO” marking for commercial transport usage, which identifies it as having been fully tested in the laboratory and qualified to applicable FAA (Federal Aviation Administration) requirements and specifications. As a commercial transport category assembly, it is also tested and qualified to the requirements of Cessna Aircraft Company. After final certification, substitutions of critical parts or changes of processes or materials are not permitted without requalification of the assembly and resubmittal of the test data to the FAA for approval. FAA regulations subject both Parker Hannifin, Aircraft Wheel & Brake Division and the user to constant surveillance to assure that uncompromising quality assurance material and processing controls are maintained in order to provide replacement parts that are the same as the parts originally certified in the assembly. DISTRIBUTORS To obtain information as to the availability of the 40-239 wheel assembly on component parts for overhaul, contact your local Cleveland Wheels & Brakes distributor. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Proprietary Information – Page INTRO-1 Page 1 Jan 03/94 DESCRIPTION AND OPERATION 1. Description and Operation A. Main wheel assembly is designed for a 22 x 8.0-10, 10 ply tubeless tire. B. Divided type main wheel to facilitate tire installation and removal. C. Two wheel halves (inner and outer wheel half assemblies) fastened together with high strength bolts, washers and self-locking nuts. Wheel halves machined from aluminum alloy forgings. D. O-ring installed on outer wheel half to provide an air seal at the juncture of the wheel halves. An inflation valve assembly is installed in the outer wheel half to inflate and deflate the tire. E. Wheel assembly rotates on two tapered roller bearings. Bearings are protected by a molded type lip seal in each hub and an integrally forged spacer on the inside of the wheel prevents grease from entering the cavity between the wheel halves. Bearing cups are shrink-fitted into the hubs of the wheel. F. Flange of inner wheel half has nine slots that engage the drive tangs of the rotating brake discs. Steel key drives are riveted to the wheel flange to provide a hard wearing surface for the disc tangs and to prevent damage to the softer metal of the wheel. Stainless steel heat shields and heat shield clips are held in place on the outer surfaces of the inner wheel half flange by the same rivets used to attach the key drives to the wheel. G. Three equally spaced fuse plugs installed in the inner wheel half will melt and Release tire pressure in the event the wheel becomes overheated. 2. Handling Procedures A. Strictly observe the deflation and inflation procedures, and the torque and lubtork values specified in this manual. Do not overtighten any bolt, nut, or fitting. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Page 2 Proprietary Information – Page INTRO-1 October 22, 2010 DESCRIPTION AND OPERATION B. Handle the wheel bearing cones with extreme care. Many bearing failures can be Traced to dropping or mishandling the cones during maintenance. C. Handle and maintain the wheel halves properly to protect the paint and surface finishes. Exposed aluminum is susceptible to corrosion. 3. Leading Particulars Wheel Tire Size and Type...........… 22.0 x 8.00-10, 10 Ply Tubeless Material......…………………………. Aluminum Forging Wheel Weight (Approx.).................. 18.9 lbs. Wheel Bolt Nut Torque...........……. 300 Pound-Inches Lubtork Bearing Lubricant..........…………... Mobile Aviation Grease SHC100 CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Proprietary Information – Page INTRO-1 Page 101 April 08/88 TESTING 1. General Test the wheel assembly in accordance with the following procedure. (Ref. IPL Fig. 1). 2. Testing Procedures A. Clean bearing cones (8) in dry cleaning solution, specification P-D-680, and visually check roller contacting surfaces for nicks, scratches, rust, corrosion, spalling, flat spots, pitting, heat discoloration and wear. Check bearing cage for dents or distortion and for wear of sides, corners and at ends of roller pockets. Replace bearing cones having any defects. B. Wipe bearing cups (16) and (27) free of grease and visually check cup face for scratches, pitting, brinelling, spalling, heat discoloration, rust, corrosion and wear. Remove defective cups and install new cups per REPAIR. C. Visually check grease seals (7) for cuts and wear on rubber sealing lip and bent or distorted reinforcing washer. Replace damaged grease seals. D. Cover hub openings of wheel halves to prevent contamination of bearing lubricant. Check Check wheel hardness in accordance with CHECK section. E. Place wheel/tire assembly in an inflation cage and inflate to recommended operating pressure. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Page 102 Proprietary Information – Page INTRO-1 April 08/88 TESTING F. Coat juncture around inflation valve (15), fuse plugs (22), and tire beads with soap solution. Check carefully for air leaks in the form of soap bubbles. If air leaks occur aarroouunndd ttiirree bbeeaadd sseeaatt,, ccoom mpplleetteellyy ddeeffllaattee ttiirree aanndd rreem moovvee aasssseem mbbllyy ffrroom m iinnffllaattiioonn cage. Remove tire from wheel and examine wheel bead seat and tire for damage. If wheel bead seat is scratched, nicked or pitted, repair in accordance with REPAIR. G. Place wheel/tire assembly in an inflation cage and inflate to recommended operating pressure. Check pressure after 24 hours. If reduction in pressure exceeds five percent of inflation pressure, replace wheel O-ring (19) and retest wheel/tire assembly in accordance with step F. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Proprietary Information – Page INTRO-1 Page 201 Nov 01/02 DISASSEMBLY 1. General Disassemble the main wheel assembly in accordance with the following instructions (Ref. IPL Fig. 1). W WA AR RN NIIN NG G:: D DO O N NO OT T A AT TT TE EM MP PT T T TO O D DIIS SA AS SS SE EM MB BL LE E W WH HE EE EL L U UN NT TIIL L T TIIR RE E H HA AS S B BE EE EN N C CO OM MP PL LE ET TE EL LY Y D DE EF FL LA AT TE ED D;; O OT TH HE ER RW WIIS SE E,, S SE ER RIIO OU US S IIN NJJU UR RY Y T TO O P PE ER RS SO ON NN NE EL L O OR R D DA AM MA AG GE E T TO O E EQ QU UIIP PM ME EN NT T C CA AN N R RE ES SU UL LT T.. C CA AU UT TIIO ON N:: B BE EA AR RIIN NG G S SE EA AL LS S A AN ND D B BE EA AR RIIN NG G C CO ON NE ES S W WIIL LL L B BE E R RE EL LE EA AS SE ED D W WH HE EN N W WH HE EE EL L A AS SS SE EM MB BL LY Y IIS S R RE EM MO OV VE ED D F FR RO OM M A AIIR RC CR RA AF FT T A AX XL LE E.. C CA AR RE E S SH HO OU UL LD D B BE E T TA AK KE EN N T TO O P PR RE EV VE EN NT T D DR RO OP PP PIIN NG G A AN ND D D DA AM MA AG GIIN NG G T TH HE ES SE E P PA AR RT TS S.. 2. Disassembly Procedure A. Jack aircraft per aircraft maintenance manual until tire is clear of ground and fully deflate tire. Remove any lockwire securing screws (2) on hubcap subassembly (3). B. Remove screws (2) and hubcap subassembly (3) from outer wheel half subassembly (13). C. Remove and retain two screws securing axle nut and anti-skid transducer, then remove and retain axle nut and tanged washer. D. Remove wheel assembly from axle and place on a clean flat surface. E. Remove grease seals (7) and bearing cones (8). F. Break tire beads away from both wheel flanges by applying pressure in even increments around entire sidewall as close to tire beads as possible. C CA AU UT TIIO ON N:: D DO O N NO OT T U US SE E IIM MP PA AC CT T O OR R P PO OW WE ER R W WR RE EN NC CH HE ES S T TO O R RE EM MO OV VE E W WH HE EE EL L N NU UT TS S A AN ND D B BO OL LT TS S.. G. Remove nuts (9), washers (10), bolts (11) and countersunk washers (12). H. Separate the wheel halves and remove tire. I. Remove O-ring (19) from wheel register groove of outer wheel half (14). N NO OT TE E:: IIT T IIS S R RE EC CO OM MM ME EN ND DE ED D T TH HA AT T A A N NE EW W O O--R RIIN NG G B BE E IIN NS ST TA AL LL LE ED D A AT T E EA AC CH H O OV VE ER RH HA AU UL L.. CM40-239 COMPONENT MAINTENANCE MANUAL WITH IPL FOR MAIN WHEEL ASSEMBLY PART NO. 40-239 Page 202 Proprietary Information – Page INTRO-1 Nov 01/02 DISASSEMBLY J. Fuse plugs (22), bearing cups (16 and 27), key drives (26), heat shields (28), and heat shield clips (25) should not be removed from wheel halves unless replacement is required. Refer to REPAIR for removal and installation procedures. N NO OT TE E:: IIN NF FL LA AT TIIO ON N V VA AL LV VE E,, F FU US SE E P PL LU UG GS S,, B BE EA AR RIIN NG G C CU UP PS S,, K KE EY Y D DR RIIV VE ES S,, A AN ND D HEAT SHIELD CLIPS