Supplemental Type Certificate for CESSNA 172E SKYHAWK

Installation Drawing 0441150. 50-25 SHEET 1 or 4 PREPARED BY JW 3-9-73 APPROVED BY C. Delardean Cleveland Wheels & Brakes INSTALLATION INSTRUCTIONS REVISION (A) 10-13-72 (B) 02-02-73 SUBJECT 50-25 SHEET OF 4 EFFECTIVE DATE 8-29-72 4. 5. 6. CONVERTING FROM GOODYEAR 6.00-6 WHEELS & BRAKES TO CLEVELAND WHEELS & BRAKES FOR CESSNA AIRCRAFT MODELS 120, 140, 140A, SERIAL NUMBER 13400 & UP ALSO MODELS 170 AND 170A (SEE NOTE BELOW) Place new brake assembly (30-63A) in torque plate assembly and install (2) washers (095-10200) and two (2) thru bolts (103-11600) to secure back plate assembly 074-01000. Torque bolts to 90 in./ lbs. When necessary, cut existing rigid hydraulic line and flare open end. Attach flexible high pressure hose between flared end and brake assembly. It may be necessary to add an additional support for the hose in order to prevent excessive line vibration. Bleed both brake assemblies. 7. Check reservoir for correct fluid level, and check to see that both brake pedals are solid. NOTE: Before modifying a model 170A, visually inspect the four bolts that attach the axle to the main landing gear spring. If these bolts are the same diameter, follow the procedure outlined below. If these bolts are not the same diameter, refer to Sheet 3 of 4, FIGURE 2. RETAIN THE (2) 145-10 BUSHINGS IN THE TORQUE PLATE WHEN RECEIVED (REF. 20-134) INSTALL (2) 145-10 BUSHINGS, 1/8 1.0. FIGURE 1 PREPARED BY JW 3-9-73 APPROVED BY C. Debardian EFFECTIVE DATE 8-29-72 SUBJECT Cleveland Wheels & Brakes INSTALLATION INSTRUCTIONS REVISION (A) 10-13-72 (B) 02-02-73 CONVERTING FROM GOODYEAR 6.00-6 WHEELS AND BRAKES TO CLEVELAND WHEELS & BRAKES FOR CESSNA AIRCRAFT MODELS 120, 140, 140A, SERIAL NUMBER 13400 & UP ALSO MODELS 170 AND 170A 10 FIGURE 2. USE BRAKE ASSEMBLY AS RECEIVED (NO MODIFICATION NECESSARY) (REF DWG NO. 20-134) 50-25 SHEET 3 OF 4 PREPARED BY JW 3-9-73 APPROVED BY C. Debardean EFFECTIVE DATE 8-29-72 SUBJECT Cleveland Wheels & Brakes INSTALLATION INSTRUCTIONS REVISION (A) 10-13-72 (B) 02-02-73 CONVERTING FROM GOODYEAR 6.00-6 WHEELS AND BRAKES TO CLEVELAND WHEELS & BRAKES FOR CESSNA AIRCRAFT MODELS 120, 140, 140A, SERIAL NUMBER 13400 & UP ALSO MODELS 170 AND 170A WHEN APPLICABLE THE FOLLOWING MODIFICATIONS MUST BE MADE: 1. Modify brake cutout contour on existing mounting plate assembly to fit over Cleveland (30-63A) brake assembly, or purchase new mounting plate assembly. Attain correct part number from Cessna Parts Catalog. 2. Modify existing brake disc cover plate to allow Cleveland brake assembly (30-63A to float freely when installed or purchase new disc cover plate. Attain correct part number from Cessna Parts Catalog. 3. Rework existing hubcap (dust shield) to dimensions shown. 2.252 2.237 DIA. (REF) 6.688 DIA. B.C. (REF.) 120° (TYP) 50-25 SHEET 4 OF 4 OPEN EXISTING HOLES TO FIT CLEVELAND WHEEL ASSEMBLY (40-974) 11 PREPARED BY JW 3-9-73 APPROVED BY C. Debardian Cleveland Wheels & Brakes INSTALLATION INSTRUCTIONS REVISION (A) 10-13-72 (B) 02-02-73 EFFECTIVE DATE 8-29-72 I. SUBJECT CONVERTING FROM GOODYEAR 6.00-6 WHEELS AND BRAKES TO CLEVELAND WHEELS AND BRAKES FOR CESSNA AIR- CRAFT MODELS 170B, 172, 172A THRU 172E, 175, 175A 175B, 175C, P172D, 180, 180A THRU 180F, 182, 182A, THRU 1826 Ригрове: This procedure will outline the steps for converting early Cessna Model Aircraft as noted above.* II. Removal: 1. Block brake pedals in retracted position to prevent movement during conversion. 2. Remove old wheel assembly from axle. 3. Remove hydraulic line from brake cylinder. III. 4. 5. Remove nuts, washers, and bolts which secure brake assembly to the mounting flange and remove brake assembly. When applicable, modify the brake disc cover plate, mounting plate assembly and hubcap per instructions on Page 3. Installation of Cleveland Wheel and Brake Assemblies per Drawing 20-134: 1. Modify torque plate assembly per Figure 1 and install on axle. Retighten the four axle attachment bolts per torque specifications in Cessna Service Manual. 2. 3. Remove two through bolts (103-11600) and washers (095-10200) to remove back plate assembly (074-01000) from brake cylinder. Place new wheel assembly (40-97A) on axle and start axle nut on threads. While rotating the wheel, hand tighten the axle nut to properly seat the wheel bearings. When the bearings are seated, hand tighten the nut until it stops, back off the nut to the nearest hole and install cotter pin. Restricted from usage on aircraft using optional Goodyear Crosswind Landing Gear. Reference Cessna Installation Drawing 0441150. 12 50-26 SHEET 1 OF 3 PREPARED BY JW 3-9-73 APPROVED BY C.Debardian EFFECTIVE DATE 8-29-72 SUBJECT Cleveland Wheels & Brakes INSTALLATION INSTRUCTIONS CONVERTING FROM GOODYEAR 6.00-6 WHEELS AND BRAKES TO CLEVELAND WHEELS AND BRAKES FOR CESSNA AIR- CRAFT MODELS 170B, 172, 172A THRU 172E, 175, 175A, 175B, 175C, P172D, 180, 180A THRU 180F, 182, 182A, THRU 182G REVISION (A) 10-13-72 (B) 02-02-73 4. Place new brake assembly (30-63A) in torque plate assembly and install two (2) washers (095-10200) and two (2) thru bolts (103-11600) to secure back plate assembly 074-01000. Torque bolts to 90 in./ lbs. 5. When necessary, cut existing rigid hydraulic line and flare open end. Attach flexible high pressure hose between flared end and brake assembly. It may be necessary to add an additional support for the hose in order to prevent excessive line vibration. 6. Bleed both brake assemblies. 7. Check reservoir for correct fluid level, and check to see that both brake pedals are solid. USE BRAKE ASSEMBLY AS RECEIVED (NO MODIFICATION NECESSARY) (REF. 20-134) FIGURE 1. 50-26 SHEET 2 OF 3 13 PREPARED BY 3-9-73 APPROVED BY C. Debardian EFFECTIVE DATE 8-29-72 SUBJECT Cleveland Wheels & Brakes INSTALLATION INSTRUCTIONS CONVERTING FROM GOODYEAR 6.00-6 WHEELS AND BRAKES TO CLEVELAND WHEELS AND BRAKES FOR CESSNA AIR- CRAFT MODELS 170B, 172, 172A THRU 172E, 175, 175A, 175B, 175C, P172D, 180, 180A THRU 180F, 182, 182A, THRU 182G REVISION (A) 10-13-72 (B) 02-02-73 WHEN APPLICABLE THE FOLLOWING MODIFICATIONS MUST BE MADE: 1. Modify brake cutout contour on existing mounting plate assembly to fit over Cleveland (30-63A) brake assembly, or purchase new mounting plate assembly. Attain correct part number from Cessna Parts Catalog. 2. Modify existing brake disc cover plate to allow Cleveland brake assembly (30-63A) to float freely when installed or purchase new disc cover plate. Attain correct part number from Cessna Parts Catalog. 3. Rework existing hubcap (dust shield) to dimensions shown. 14 ninj 237 DIA (REF) 6.688 CJA. B.C. (REF) 120° (TYP) 50-26 SHEET 3 OF 3 OPEN EXISTING HOLES TO FIT CLEVELAND WHEEL ASSEMBLY (40-STA) United States of America Department of Transportation-Federal Aviation Administration Supplemental Type Certificate Number SA13GL This certificate, issued to Aircraft Wheel and Brake Division Parker Hannifin Corporation 1160 Center Road Avon, Ohio 44011 certifies that the change in the type design for the following product with the limitations and conditions therefor as specified hereon meets the airworthiness requirements of Part 3 of the Civil Air Regulations as defined on individual model specification/type certification data sheet. Original Product-Type Certificate Number A-768, A-799, 3A12, 3A13, 3A17, 5A2, 5A6 Make Model Cessna Description of Type Design Change 120, 140 (S/N 8004 thru 13399), 120, 140, 140A, (S/N 13400 and up), 170, 170A, 170B, 172, 172A thru 172E, 175, 175A, 175B, 175C, P172D, 180, 180A thru 180F, 182, 182A thru 182G Install Cleveland Wheel #40-97A, Brake #30-63A in accordance with Cleveland Drawings 20-134, Revision A, dated October 12, 1972, and mounting instructions 50-24, Revision C, dated February 2, 1973, 50-25 Revision C, dated February 2, 1973, 50-26 Revision C, dated February 1973, as appropriate. Limitations and Conditions This approval should not be extended to other aircraft of these models on which other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect on the airworthiness of that aircraft. This approval is not extended to aircraft with Goodyear cross-wind (castering) landing gear. This certificate and the supporting data which is the basis for approval shall remain in effect until sur- rendered; suspended, revoked, or a termination date is otherwise established by the Administrator of the Federal Aviation Administration Date of application October 13, 1972 Date of issuance February 20, 1973 Date issued July 23, 1974, October 28, 1980 Date amended July 24, 1973, April 1, 1981 FEDERAL AVIATION Administrator TOHINISTRATION W. F. Horn, Jr. (Signat Chief, Engineering and Manufacturing Branch, Great Lakes Region AGL-210 (Title) Any alteration of this certificate is punishable by a fine of not exceeding $1,000, or imprisonment not exceeding 3 years, or both. FAA FORM 8110-2 (10-681 This certificate may be transferred in accordance with FAR 21 47 NOTES 8-32250 DP 3 PLACES C.C8B BC. (REF) 15005 1.5000 BRS DIA (REF) 1.646 1.625 (888) WHEEL ( 3.292 3.250 WHEEL RATING PER FAR-750-C E64 STATIC LOAD - 2500 LBS. LIMIT LOAD-8975 +5. 2. BRAKE KINETIC ENERGY CAPACITY 290,000 FT 85, 100 STOPS FROM 72M.PH Ar 10 FT/SEC/SEE DECELERATION WITHOUT DISC OR LINING CHANGE 3 BRAKE FLUID DISPLACEMENT 4 MAXIMUM NEW TO FULLY WORN 1.08 CU. IN. NORMAL CLEARANCE TO 700 PSI. 19 CU.IN. TREO VALVE SHOWN IN PHANTOM [] SATIC THRUST AT GROUND LINE IS (16,800 PSI UNE PRESSURE CAN SUBSTAIN PRESSURE THRUST LOAD AT THE GROUND LINE) 6.600-6 TIRE SHOWN MY PHANTOM 800 STATIC 220704x) ROTATING PARTS (F) 1.625(REF) GREASE SEAC DIA STATIC THRUST (LBS.) PER BRAKE 800 700 600 500 400 300 200 100 INDING GENE 40-97A WHEEL ASSY 6.00-6 TYPE II -14-5-10 BUSHING (REF.) AS SHIPPED REFERENCE ONLY - DO NOT USE FOR PRODUCTION -30-63 A BRAKE ASSY PRESSURES TO THSTAND STATIC THRUST AND TO PRODUCE 10 FT/R/SRC. DECELERATION AT VARIOUS WEIGHTS 17515 1560 VEVO 1115 590 6.70 950 225 0 200 400 600 ado 1000 PRESSURE RSI 600-6 LANDING WEIGHTS LBS PER BRAKE THIS DRAWING SHOWS THE BELE A536nely 80-584 AND THE TORQUE PLATE ASSEMBL 75-37 NA SHIPPED CONDITION. PLEASE REPER TO SWEET NO 30-28, 50-25, 00 40 26 FDC TORQUE PLATE MODIFICATION AND SPECCHATICANEDOFT INSTALLA7/04 HEIGHTS WHEEL OBSC BRAKE CUL TORQUE R- TOTAL- 3.78 Les -2.09.203. -1.50 480 776283 20-134 WORK TO DIMENSIONS Do NOT BALE ALL DIMENSICHER UNLERE OTHER SPECIFIED TOLERANCE POR XXX010 TOLERANCE FOR ULAN DIN 16° TOLERABLE FOR PRACY DONG 1/2" BREAK SILLAPSES-REMOVE ALL 78/28/72 CHACKED BY WT MATERIAL HEATTAY ASSEMBLY USED ON APPLICATION FULL NEXT ADVERBLY FINAL ASSEMBLY QUANTITY REQ'D SURFACE MEATMENT PATTERN, FORGING PLANK NO CLEVELAND AIRCRAFT PROD. AVON, OHIO HUGELY BRAKE ASSEMBLY 20-34 NAME DESCRIPTION OF CHANGE O OF RATE RYBY 52 020-13400