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1. B Kind of Agency e No i US Certificated Mechanic RENS gt 3 00287 1A _ Foreign Certificated Mechanic _ Certificated Repaw Station _ Manufacturer certify that the repair and or alteration made to the unit s identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U 5 Federal Aviation Regulations and that the information furnished herein is true and correct to the best of idis sus Date o Signature of vu Individual MEE UO T Approval for ern To Service Pursuant to the authority given persons specified below the unit identified in item 4 was in in the manner prescribed by the Administrator of the Federal Aviaton Administration and is APPROVED REJECTED FAA Fit Standards F Other Specify 1 Inspector X Inspection Authonzation 1 Person Approved by Transport Canada Ainworthiness Group Date of Approval or Rejechon Certificate or Signature of Authonzed individual Manufacturer j AA x m FAA Designee Repair Staton Designation No e 0 os 26160057 IA FAA Form 337 12 88 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness require2. Idenfifted herein complies with applicable airworthiness requiremeria s gg The data 4 Type 5 Unit Identification AIRFRAME As described in Item 1 above APPLIANCE Manufacturer 6 Conformity Statement B Kind of Agency A Agency s Name and Address Name D_Buiss U S Certificated Mechanic Manufacturer address Hl 32 Ai Oe T RORI Foreign Certificated Mechanic C Certificate No ow 6560 6 FIED sue 127 CerifcstedRepairsiien ay lt 3172 USA oranan 3456074 D certify that the repair and or alteration made to the unit s identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U S Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge 7 of Authorized Individual Extended range fuel per 14 CFR Part 43 x Lex M A 011 7 Approval for Return to Service Pursuant to the authority given persons specified below the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is L Approved L Rejected FAA Fit Standards A TET Persons Approved by Canadian BY u Other Specify FAA Designee Repair Station x Inspection Authorization Certificate or Signature Date of Autho
3. R China 111003 TEST REPORT FRY STEEL CO CERTIFIES THAT THIS IS Customer FRY STEEL A TRUE COPY OF THE ORIGINAL MILL TEST REPORT NOW ON FILE Customer POH 44952 RECEIVED AND INSPECTED Item Code FRY 000187 MIL 1200 NA Die Number 7 APR 10 2008 Alloy amp Temper 6061 T6511 Production Description 1 7 8 ROUND BAR 12 Adel Heat Number ZW08020319 BY Lot Number 20080224551 0 2 Date 72 Applicable Specifications ASTM B221 02 AMS QQ A 200 8 QQ A 200 8F AMS 4173 E CHEMICAL ANALYSIS Yield Strength ksi Elongation LN 2 We hereby certify that the item listed have been checked and tested in accordance with the specifications noted and have been found to meet all the applicable requirements Certifications are kept on file for 36 months from the date of purchase and are available for review upon request This test report applies to bundle mark 011070 0J1071 011039 55 011050 033051 0111054 011059 011 061 0111072 01108 Li Yansong Quality Manager id v7 1 1 2 Golden State Metal Finishing b E RTI F CATION 2737 Via Orange Way Date Suite 104 103 Spring Valley CA 91978 1750 11 23 2010 Bill To GROVE AIRCRAFT LGS INC ACCTS PAYABLE 1800 JOE CROSSON DRIVE SUITE A EL CAJON CA 92020 GROVE AIRCRAFT LGS INC 1800 JOE CROSSON DRIVE SUITE A 10327366 11 23 2010 WILLCALL Quantity Item Code Description 4 010 016 ANODIZE CLEAR P
4. limitation changes shall be entered in the appropriate aircraft record An alteration mustbe compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements 8 Description of Work Accomplished If more space is required attach additional sheets Identily with aircraft nationality and registration mark and date work completed Tui su eqs A WSL Ne aus E en m 260 Sit Reade uiuders ANEW ack 2N Qesdumd Gad Kid XA AL 3 Dem ler awd Bers pa Te Nu See DA l l N BG NU Wes eds V ET wend era Uwa and Breed de Taare Cu Meus rende aen e ween BW Necesse ce Te A AN NES Ale l Qae Be LO oder win ERA Mopeds eets Are Attached U S GPO 1994 568 012 00019 NOTICE Weg ard balance a operating iru on changes shall be entered ut The anpropriate anera recor An musfbe Carpe ech a erro aVergivans fo azrone COOL DT WEP IE ae ADAN JE Description of Wok amp ccomplihen ee Degree acum O ona sheets Idec wort accra naar AT RESTON Pra Ge eek come 1 Installed Cleveland wheels and brakes 2 Adapted wheels to tapered axle by using 13 0D 058 4130 tubing and 15 8 OD 058 4130 tubing for bearing st
5. 97 371598 gt 1 Description of Goods Round bars Requirements on the Products Grade of Product Dimensions inch mm Material conforms lo quality of alloy 6061 T6511 Mi d2 75 144 Product conforms to all requirements of gt 0 5 13658 AMS 4173 ASTM B221 08 AMS QQ A 200 8 QQ A 200 8F This product conforms to European Union m RoHS Directive 2002 95 EC Ty ke Mechanical Properties in The Lot Number 1 Cast Number Number T Number of Yield Strength Condition Tests Strength 0 2 offset of Tested Standards Required Sa 65537 17 2991 51 8 48 4 13 5 14 0 Chemical Composition Mn un 9 dia EE LTE Im aps s gw Tin Simao iz NM Ten Le aso ee AAA EE i Contents H2 of metals ductivity cm3 100gr Mercury Free Russia is country of melt and manufacture i 2 i x Y STEEL CO CERTIFIES On behai MATL GNE WE KUMW JSC A TRUE E COPY OF THE ORIGINAL MLE TEST REPORT Now W ON RECEIV Shipping Date 14 04 2009 ED AND INSPECTED L V Belousova UN 01 2009 N V Alekhina BY Inspector f Inspection 000806 BRIE BANBOVAL 8 17 e e Preso bil LiaoNing ZhongWang Group Co Ltd Tl 1 Tel 0086 419 4150985 4153521 Fax 0086 419 4150985 4150491 MET 299 Wensheng Road Liaoyang city Liaoning Province P
6. AJON CA 92020 Aircraft Landing Gear Systems inc Wheel amp Brake Assy DWG NO 61 138 scale 6 SHEET 1 of 1 TOLERANCE DECIMAL XX 030 DECIMAL XXX 010 DECIMAL XXXX 005 DRAWN BY ANGLE 0 25 DEGREES R P Grove FINAL ASSY o 91609 020 074 TORQUE PLATE ASSY 0 19 83 1 CALIPER ASSY 90490 8 EQL SPC WHEEL SIZE 600X6 TYPE Ill STATIC LOAD RATING 1250 LBS TORQUE WHEEL NUTS TO 150 IN LBS TORQUE BACK PLATE BOLTS TO 90 IN LBS MAX OPERATING PRESSURE 800 PSI KINETIC ENERGY RATING 168 934 FT LB BRAKING TORQUE 600 PSI 5 683 IN LBS LIMIT LOAD RATING 4000 LBS FOR USE ON TAYLOR CRAFT Grove Aircraft Company Page of Light Weight 600x6 Wheel amp SUME Brake Set aee e Fits standard 600x6 1 1 2 s axle Brake Calipers utilize standard brake pads and O ring seals e Brake Discs are machined from one piece forging e Discs are heat treated for longer life e Static Load Rating 1250 pounds per wheel e Kinetic Eneregy 163 366 ft Ib 4 Model 61 1 Price 749 00 http w groveaircraft com 61 1 html 11 04 Grove Aircraft Company Page of 2 BRAKE PEDAL GEOMETRY Brake pedal geometry plays an important role in the performance of a brake system The brake cylinder must deliver the proper pressure and fluid volume to the caliper for optimum braking All Grove Aircraft brake systems are designed
7. December 4 2010 To Nashville FSDO From Charles V Avon Re Taylorcraft wheel and brake modification To whom it may concern To improve the safety of N26658 a 1940 Taylorcraft BL 65 I have inspected the original shinn wheel and mechanical brakes assemblies and determined that they are unsuitable for use on an airworthy aircraft This leaves me with a couple of options either try to find serviceable shinn wheel and brake assemblies which I have tried and haven t found anything satisfactory or convert the airplane to hydraulic disk brakes I cannot find any STC from Cleveland or any other company that would include the Taylorcraft BL65 In addition the STC s I have seen through Cleveland for similar light airplanes have included larger brake calipers which is way too much braking action for a light tailwheel aircraft in my opinion I therefore have researched other options and discovered Grove Aircraft Landing Gear Systems Inc They are the FAA supplier of wheel and brake assemblies for some new models of American Champion Maule Air and Diamond Aircraft In studying the pictures of their various packages I have determined that I would like to use the light weight model 61 1 wheel and brake assemblies with Scott master cylinders My reasoning for preferring this versus a Cleveland counterpart is that the wheel bearings are farther apart in the wheel hubs and therefore closer to the original shinn bearing spacing They will still requi
8. ER MIL A 8625F TYPE IIB CLASS 1 SEAL CAP 415045 ANODIZE CLEAR PER MIL A 8625F TYPE IIB CLASS 1 TAYLOR CRAFT AXLE SLEEVE 215725 ANODIZE CLEAR PER MIL A 8625F TYPE IIB CLASS 1 TAYLOR CRAFT RESS CAP WE CERTIFY THAT THE PARTS LISTED HAVE BEEN PROCESSED IN ACCORDANCE WITH SPECIFICATIONS NOTED 619 670 0135 619 670 0490 Installation Aircraft Landing Gear Systems Inc Instructions Wheels e Tire amp Tube Installation When installing the tire and tube be sure to 1 sprinkle talc powder inside the tire to allow the tube to move to its seated position easily 2 install the red dot on the tire if so marked adjacent to the valve stem 3 lubricate the valve stem with a small amount of grease prior to pushing it through the grommet on the wheel and 4 take care not to pinch the tube when assembling the wheel halves Lubricate Wheel Bearings Grove Aircraft wheels are shipped with only a light protective coating of Aeroshell 22 grease on the bearings Prior to use on the aircraft you must remove and lubricate both tapered roller bearings on each wheel using Aeroshell 22 grease or equivalent Torque Wheel Bolts amp Nuts For 500x5 wheels 90 inch pounds for 600x6 wheels 150 inch pounds Pre Load Wheel Bearings It is important that the axle nut be tightened properly With the aircraft jacked up rotate the wheel and tire while tightening the axle nut until it is so tight that you are una
9. ble to turn the wheel and tire Care must be taken not to damage the valve stem during this process Loosen the axle nut just enough so that the wheel and tire are on the edge of rotating freely Install a safety cotter pin through the axle nut and axle Check to see that the installed cotter pin does not interfere with the valve stem or any other part of the wheel and tire assembly Brakes Use the Proper Brake Fluid Improper brake fluid will ruin the seals in the brake system Use only standard aircraft Mil H 5606 red hydraulic fluid Never use automotive brake fluid Bleed the Brakes The best method to fill and bleed aircraft brakes is from the bottom up Loosely connect a 1 8 ID clear hose to the brake caliper bleeder screw from your brake fluid source An oil can used exclusively for this purpose works well Pump the oil can until the hose is full of fluid with no air bubbles Tightly secure the hose to the bleeder valve while opening it a quarter turn Pump fluid into the system until it fills the brake cylinder reservoir The reservoir filler or vent cap must be open during this process Tighten the bleeder valve screw remove the hose and reseal the reservoir Check your work by insuring that the reservoir is full and that you have a hard pedal If you have a soft pedal pump the brakes several times Many times that will fix the problem If the problem persists drain the fluid and repeat the above proc
10. concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave SW Washington DC 20591 Attn Information Collection Clearance Officer AES 200 P N 5045 Taylorcraft Axle Sleeve P N 5725 Taylorcraft Press Cap Lot 10327572 CIN 1282 Lot 9201448 C N 1214 Grove Aircraft LGS Inc El Cajon CA 92020 Grove Aircraft LGS Inc El Cajon CA 92020 ph 619 562 1268 fx 619 562 3274 ph 619 562 1268 fx 619 562 3274 www groveaircraft com www groveaircraft com KEY TO PHOTOS 1 Parts for installation 2 3 Taylorcraft axle and gear for mach up 4 Grove axle sleeve Torq plates and AN3H 4A bolts 5 6 Axle sleeve in place against flange bolt will be torqued and safety wired 7 8 9 Shows the wheel on angle 10 11 Shows Grove press cap on axle 12 Taylorcraft axle washers and castle nut 13 Axle nut with cotter pin installed 14 18 Shows caliper installation v INSPECTION CERTIFICATE Ne 09 8292 1 A S A A a EN 10204 3 Y SGS am SGS NT STOCK COMPANY 5 Zavodskaya Str Kamensk Uralsky Sverdiovsk Region 623405 Russia T 439 39 52 22 Fax 3439 39 50 68 Fry Steel Company Contract number N11193 S Specification Ne N11193 45569 Lot Ne 1 x lt Article number 83105 Package Ne 371595 371 596 3715
11. ess Tighten and Safety Wire the Brake Calipers Torque the brake caliper bolts to 90 inch pounds and then safety wire Seat the Brake Pads These non asbestos organic composition brake pads require a thin layer of glazed material at the lining friction surface in order to provide maximum braking performance This glazed layer is produced by the heat generated during normal braking operations and is maintained during the life of the lining Since new brake pads do not have this layer it must be created by the following process 1 Heat the pads by dragging the brakes while taxiing at a slow speed with moderate power Do not use maximum braking pressure 2 Allow the brakes to cool for 5 10 minutes 3 Test the results at full static run up If the brakes hold break in is complete If they fail to hold repeat steps 1 and 2 until they do Replacement Brake Pad Part Number 066 105 Use on 36 Series Brake Calipers Brake Pad Part Number 066 106 Use on 30 35 amp 39 Series Brake Calipers Brake P ads Brake Pad Part Number 066 111 Use on 31 32 amp 33 Series Brake Calipers Customer Service Line 619 562 1268 www groveaircraft com SONS 61 1 WHEEL ASSY N Z i S 7 7 822 3 7 BEARING SPACING TEA SSS IS yl Gi 0 ve 1800 JOE CROSSON DRIVE ELC
12. ion 2 Hydraulic Systems Aircraft weighed prior to flight and weight and balance recorded Instructions for Continued Airworthiness Original size tire and tube 6 00 x 6 to be used with new wheel assemblies Tire pressure to be maintained in accordance with original service manual New wheel bearings service inspection intervals will follow original equipment intervals as outlined in the service manual The hydraulic system is to be serviced with MIL H 5606 Hydraulic fluid Brake pads to be replaced when worn as indicated by wear markers Inspect installation at applicable intervals annual or 100 hr using FAR 43 App D and applicable paragraphs of AC 43 13 1B Chapter 9 Section 2 Hydraulic Systems Additional Sheets Are Attached FAA Form 337 10 06 Paperwork Reduction Act Statement The reason for collecting this information is to track major maintenance performed on aircraft The collected information is used as part of the aircraft s historical file The public reporting burden for this collection of information is estimated to average 30 minutes per response Responses are mandated by 14 CFR Part 43 Collected information becomes part of the public record and no confidentiality is required An agency may not conduct or sponsor and a person is not required to respond to a collection of information unless it displays a currently valid OMB control number The OMB control number associated with this collection is 2120 0020 Comments
13. le paragraphs of AC 43 13 1B Chapter 9 Section 2 Hydraulic Systems Additional Sheets Are Attached USGPO 1990 761 753
14. ments ip st 670 3 for each heel brake pedal The new brake caliper mounts are bolted to the original axle bracket assemblies and axle spacers fabricated and installed as necessary to facilitate wheel to caliper alignment Support brackets were fabricated and installed to connect the individual master cylinders between the fuselage structure and their respective brake pedals The master cylinders were connected to a common reservoir mounted on the inside of the firewall by a combination of solid and flexible hydraulic lines The calipers are connected to the master cylinders by a combination of flexible hydraulic lines where movement will be required and solid hydraulic lines All hydraulic line installation performed in accordance with applicable paragraphs of AC 43 13 1B Chapter 9 Section 2 Hydraulic Systems Aircraft weighed prior to flight and weight and balance recorded Instructions for Continued Airworthiness Original size tire and tube 6 00 x 6 to be used with new wheel assemblies Tire pressure to be maintained in accordance with original service manual New wheel bearing service inspection intervals will follow original equipment intervals as outlined in the service manual The hydraulic system is to be serviced with MIL H 5606 hydraulic fluid Brake pads to be replaced when worn as indicated by wear markers Inspect installation at applicable intervals annua or 100 hr using FAR 43 App D and appicab
15. o report can result in a civil penalty not to exceed 1 000 for each such violation Section 901 Federal Aviation Act of 1958 1 269 MR No Nationality and Registration Mark O a SSM Name As shown on registration certificate Address As shown on registration certificate SAY Woed Adno Type A Agency s Name and Address B Kind of Agency C Certificate No Ves Neuss X U S Certificated Mechanic _ Foreign Certificated Mechanic WB Mak ime Bo uf imma APPLIANCE 6 Conformity Statement wb Certificated Repair Station aas D Icertify thatthe repair and or alteration made to the unit s identified in item 4 above and described onthereverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U S Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge Signature of Authorized Individual Sex as b 7 Approval for Return To Service Pursuant to the authority given persons specified below the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration andis A APPROVED D REJECTED Other Specif x Person Approved by Transport FAA Designee Canada Airworthiness Group Date of Approval or Rejection Certificate or Designation No awaato NOTICE Weight and balance or operating
16. ops Used factory nut and large washer with machined bushing inside of 14 axle see drawing rdware used in accordance with AC43 13 1A Chapter 5 craft Hardware 31 aac 4 Weight and balance computed and equipment list updated ANT Bolt 3 Wet STOPS obo 058 30 Feb ig Form Approved e OMB No 2120 0020 e MAJOR REPAIR AND ALTERATION _ For FAA Use O of Trareponaton Airframe Powerplant Propeller or Appliance nnd miy Federal Aviation Administration INSTRUCTIONS Print or type all entnes See FAR 43 9 FAR 43 Appendix 8 and 6 43 9 1 or subsequent revision thereof for instructions and disposition of this form This report is required by law 49 U S C 1421 Failure to report can result in civil penalty not to exceed 1 000 for each such violation Section 901 Federal Aviation Act of 1958 Make Model Luscombe 82 Senal No Nationality and Registration Mark 1383 N28554 Name As shown on registration certificate Address As shown on registration certificate Lindsey Robert J 982 Prine Rd Giroux Luke D Baldwinsville NY 13027 9627 1 Aircraft 3 For PAA Use Only THE ALTERATION OR REPAIR IDENTIFIED 7 REQUIREMENTS AND IS APPROVED FOR USE NC Y ON THE ABOVE DESCRIBED AIRC TO CONFORMITY INSPECTION BY A PERSON IN 14 CFR PART 43 7 7 y APPROVING INSPECTOR lt 4 Unit Identification Alteration As described in ttem 1 above 6 Conformity Statement
17. re spacers between the bearing and axle nuts but the wider bearing spacing would spread the load out more similar to the original design In studying the tech articles and flight reviews of this particular aircraft design it appears that the landing gear design has given the airplane a reputation for spirited ground handling and I want to improve the ground handling while providing safe and dependable brakes The Modification I am proposing will serve to make the airplane safer and more reliable Thank you for your consideration and help E Cheka wave Form 6 Electronic Tracking Number OMB No 2120 0020 2 28 2011 For FAA Use Only INSTRUCTIONS Print or type all entries See Title 14 CFR 43 9 Part 43 Appendix 8 and AC 43 9 1 or subsequent revision thereof for instructions and disposition of this form This report is required by law 49 U S C 44701 Failure to report can result in a civil penalty for each such violation 49 U S C 46301 a e MAJOR REPAIR AND ALTERATION le Airframe Powerplant Propeller or Appliance Federal Aviation Administration Nationality and Registration Mark Serial No N26658 2000 Taylorcraft BL Name As shown on registration certificate Address As shown on registration certificate Address 4149 W Main St ciy Hohenwald 1 1 0 1 1 56181 Zip 38462 County USA 3 For FAA Use Charles Victor Avon
18. rized Individual Designation No 2 3 6414 1A A 24 Form 337 10 06 NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements 8 Description of Work Accomplished If more space is required attach additional sheets Identify with aircraft nationality and registration mark and date work completed IN26658 4 20 Nationality and Registration Mark Date Removed original shinn and mechanical brakes Installed Grove Aircraft Landing Gear Systems Inc Taylorcraft axel sleeve P N 5045 over original axle also installed Grove torch plates over axle sleeve and bolted them to the original axle flange with 8 AN3 4 bolts and safety wired them with 032 wire Next installed 600 6 wheels model number 61 1 with Grove Taylorcraft press cap P N 5725 and original Taylorcraft axle washer and castle nut and safety with cotter pin Next install Scott master cylinders model number P N 1248H and 1260H using 4 AN3 11 bolts and 4 AN365 1032A nuts and 4 AN970 3 washers Next run hydraulic lines from master cylinders to calipers using aeroquip hose model 666 flexible hose and reusable 37 degree fittings All hydraulic line installation performed in accordance with applicable paragraphs of AC 43 13 1B Chapter 9 Sect
19. to work well together and with other high pressure systems from other manufacturers A general rule of thumb is to design the brake pedal geometry to have a 2 to 1 ratio of pedal travel to brake cylinder travel Thus 1 of pedal travel will result in 1 2 of cylinder travel A pedal force of about 75 pounds will result in an adequate 500 psi force to the brake caliper BRAKE SYSTEM PLUMBING The drawing to the right represents a typical brake plumbing installation Note The most upstream componet must be a reservoir You pa can use either the 675 series master cylinder with integral resevoir or a separate remote reservoir KINETIC ENERGY One of the functions of the brake system is to absorb the heat energy deve during braking The majority of this heat is absorbed by the brake disc 1 the mass of the disc the more heat energy it is able to absorb A well desi system will provide adequate disc mass without excessive weight As you from the formula on the left kinetic energy is a function of the mass weig aircraft and its landing speed http www groveaircraft com brakedesign html 11 1 04 MAJOR REPAIR AND ALTERATION OMB No 2120 0020 Air rame Powerplant Propeller or Appliance Office tificati INSTRUCTIONS Print or type all entries See FAR 43 9 FAR 43 Appendix B and AC 43 9 1 or subsequent revision thereof for instructions and disposition of this form This report is required by law 49 U S C 1421 Failure t
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