SERVICE BULLETIN SB7106
BEECHCRAFT F33A · Service Bulletins
Overview
This service bulletin provides inspection guidelines for the wheel halves of specific Beechcraft aircraft models to ensure safety and performance. It outlines the necessary steps for inspecting wear limits and the required actions if those limits are exceeded.
- Applicable to Beechcraft models G33, F33A, F33C, and others.
- Mandatory initial inspection at next scheduled overhaul or flight.
- Subsequent inspections required every tire change, annual inspection, and overhaul.
- Inspection involves checking bolt holes and lateral movement of wheel halves.
- Standard inspection tools include dial indicators and Vernier calipers.
- Replacement of parts may be necessary based on inspection results.
- Weight and balance are not affected by this service bulletin.
- This bulletin is approved for FAA-TSO-C26 product support.
Document
Source
Originally published by clevelandwheelandbrake.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Service Bulletins
- Year ·
- 2015
- File size ·
- 10 MB
- Publisher ·
- clevelandwheelandbrake.com
- Language ·
- en
What is the SERVICE BULLETIN SB7106?
The SERVICE BULLETIN SB7106 is a service bulletins for the BEECHCRAFT F33A, dated 2015.
Where does the SERVICE BULLETIN SB7106 come from?
This copy of the SERVICE BULLETIN SB7106 was originally published by clevelandwheelandbrake.com and is hosted on Sprinkle as a free, searchable reference copy.
What year was the SERVICE BULLETIN SB7106 published?
The SERVICE BULLETIN SB7106 — the BEECHCRAFT F33A service bulletins on file — is dated 2015.
Most owners only have the POH. Here's the essential set for the BEECHCRAFT F33A.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
More BEECHCRAFT F33Amanuals & documents
In this document
Planning Information
Details the applicability of the service bulletin to specific Beechcraft models and outlines the reasons for the inspection.
Accomplishment Instructions
Provides step-by-step instructions for removing the wheel assembly, disassembling the wheel, and inspecting for wear limits.
Inspection Wear Limit Results
Describes the actions to take based on the results of the wear limit inspections, including replacement of wheel halves if necessary.
Safety Warnings
Includes critical safety warnings regarding aircraft stability and tire deflation before performing inspections.
Tooling
Lists the standard inspection equipment required for the inspection process.
Compliance
Outlines the mandatory compliance requirements for inspections and intervals.
Safety notes
- Ensure the aircraft is secure and stable before beginning any work.
- Fully deflate the tire before removing the valve core to prevent injury.
- Do not disassemble the wheel until the tire is completely deflated.
- Avoid C-clamp induced damage to the bead seat during inspections.
Full document text
Parker Hannifin Corporation Aircraft Wheel & Brake 1160 Center Road Avon, Ohio 44011 USA 1-800-BRAKING (272-5464) 440-937-1213 FAX 440-937-5409 SERVICE BULLETIN Initial Release 08-14-2015 Rev. B, 01-25-2016 SB7106 Page 1 of 17 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS 1. PLANNING INFORMATION A. APPLICABILITY Refer to Table 1. This service bulletin is applicable to the Beechcraft models listed using the designated Parker Hannifin Corporation, Aircraft Wheel & Brake Division main wheel assembly part numbers: Table 1 Applicability Parker Hannifin Part No. Beechcraft Model Serial Number 40-83 G33, F33A, F33C, V35BTC, 36, 76 CD-1272 thru 1304; CE-301 thru 634; CJ-31 thru 124; D-9193 thru 9861; E- 1 thru 824; D-9862 and on. 40-83A F33A, F33C, A36, A36TC, F33A, F33C CE-635 thru 1071; CJ-125 thru 155; E-825 thru 1802; EA-1 thru 186; CE- 1072 and on; CJ-156 and on. 40-83B A36, A36TC, B36TC E-1803 thru 2254; EA-187 thru 442; E-2255 and on; EA-443 and on. B. REASON To establish product life wear limits and prevent stress to assembly hardware (bolts) from excessive wheel half wear resulting in possible lateral shift between wheel halves. C. DESCRIPTION This service bulletin will provide instruction to the level required for inspection and the return of product to service. Replacement of parts may be required dependent on results of wear limit inspection per this document. Refer to paragraph 3. Material Information. D. COMPLIANCE Mandatory – Initial inspection at time of next scheduled overhaul or next scheduled flight of the aircraft; whichever occurs first. Maintain subsequent inspection intervals as follows: Every tire change Every annual inspection Every overhaul. SERVICE BULLETIN SB7106 Page 2 of 17 Initial Release 08-14-2015 Rev. B, 01-25-2016 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS E. APPROVAL This service bulletin is approved for support of an FAA-TSO-C26 product. F. MANPOWER Estimate. 2 to 3 hours per aircraft. G. TOOLING Standard inspection equipment: Inspection surface plate CMM machine, if facility is so equipped; otherwise, the following inspection equipment can be used for measurements: o Dial indicator o Vernier dial calipers o Gage pins: Ø 0.321 to Ø 0.329 H. WEIGHT AND BALANCE Not affected. I. REFERENCES Use the latest issue in effect. AWBPC0001 ................. Product Catalog. (Contains illustrated parts list of wheel and brake assemblies). AWBCMM0001 ............. Component Maintenance Manual – External Design Wheels & Brakes (General maintenance support data for external design wheels & brakes) AWBTSG0001............... Technician’s Service Guide (Condensed data from AWBCMM0001) J. OTHER PUBLICATIONS AFFECTED Not applicable. K. PREVIOUS MODIFICATIONS None. SERVICE BULLETIN Initial Release 08-14-2015 Rev. B, 01-25-2016 SB7106 Page 3 of 17 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS 2. ACCOMPLISHMENT INSTRUCTIONS Instructions are per landing gear. All instruction related to aircraft support and non-related Parker Hannifin, Aircraft Wheel & Brake equipment shall be in accordance with the airframe manufacturer’s instructions. A. REMOVE THE WHEEL ASSEMBLY SAFETY WARNING: MAKE SURE THE AIRCRAFT IS SECURE AND STABLE BEFORE BEGINNING ANY WORK. WORKING AROUND AN AIRCRAFT THAT IS NOT SECURE AND STABLE CAN CAUSE INJURY OR DEATH. SAFETY WARNING: FULLY DEFLATE THE TIRE BEFORE REMOVING THE VALVE CORE. THE AIR IN A TIRE PUTS PRESSURE ON THE VALVE CORE. THE VALVE CORE CAN EJECT WITH GREAT FORCE AND CAN CAUSE INJURY OR DEATH. (1) Refer to the airframe manufacturer’s instructions to lift and support the aircraft. (2) Fully deflate the tire by depressing the valve stem plunger in the tube valve stem until air can no longer be heard escaping from the tube. (3) When all the tire pressure is released, then carefully remove the valve core from the tube valve stem. NOTE: The brake disc on the wheel assembly is sandwiched between components of the brake assembly (back plate and pressure plate assemblies). The back plate assemblies must first be removed before the wheel assembly can be removed from the axle. (4) Refer to Figure 1. Remove the four attachment bolts and washers from the cylinder assembly and remove the back plate assemblies. (5) Remove the axle mounting hardware and slide the wheel assembly off the axle. NOTE: It may be necessary to rock the wheel/tire slightly to unseat the outboard bearing. B. DISASSEMBLE THE WHEEL SAFETY WARNING: DO NOT DISASSEMBLE THE WHEEL UNTIL THE TIRE IS COMPLETELY DEFLATED. SERIOUS INJURY TO PERSONS, OR DAMAGE TO EQUIPMENT CAN RESULT. CAUTION: REFER TO FIGURE 1. REPLACE BOLTS, WASHERS, AND NUTS AFTER THREE TORQUING APPLICATIONS. THE FACTORY ASSEMBLY TORQUE COUNTS AS ONE TORQUE APPLICATION. THE PRELOAD CONDITION WILL DIMINISH AFTER THREE TORQUING APPLICATIONS AND HARDWARE MAY SELF-LOOSEN FROM VIBRATION. NOTES: Refer to AWBCMM0001 and inspect all removed components prior to re-installing. Refer to AWBPC0001 for component part numbers for the 40-83, 40-83A, and 40-83B wheel assemblies. SERVICE BULLETIN SB7106 Page 4 of 17 Initial Release 08-14-2015 Rev. B, 01-25-2016 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS (1) Confirm that the tire is completely deflated. (2) Separate tire beads from the wheel halves using a bead breaker. (3) Remove the three nuts, washers, and bolts holding the wheel halves together. (4) Remove the brake disc from the inner wheel half. (5) Remove the following to prevent accidental damage during the inspection procedure: (a) For the 40-83 and 40-83A: snap rings, grease seal felts and rings, bearing cones. (b) For the 40-83B: snap rings, molded grease seals, bearing cones. (6) Separate the inner wheel half and outer wheel half assemblies and remove the tire. Figure 1 Remove the back plate assemblies SERVICE BULLETIN Initial Release 08-14-2015 Rev. B, 01-25-2016 SB7106 Page 5 of 17
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40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS C. WHEEL HALVES – INSPECT BOLT HOLES Inspect features of the bolt holes as shown in Figure 2. Figure 2 Wheel half bolt hole features (1) Refer to Figure 3. Use gage pin diameters from Ø 0.321 inch to Ø 0.328 inch and measure all the bolt holes of the inboard and outboard wheel halves. The gage pins should fit into each of the bolt holes. (2) Use a gage pin diameter of Ø 0.329 inches. If the gage pin can fit into one of the bolt holes, then the bolt hole is too large and the wheel half is considered scrap. Refer to E. Inspection Wear Limit Results. SERVICE BULLETIN SB7106 Page 6 of 17 Initial Release 08-14-2015 Rev. B, 01-25-2016 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS Figure 3 Measure bolt hole diameter SERVICE BULLETIN Initial Release 08-14-2015 Rev. B, 01-25-2016 SB7106 Page 7 of 17 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS NOTE: With the outboard wheel halves, be sure that the register face is laying on the flat surface and not the register lip. Refer to Figure 4. Figure 4 Setup for bolt hole length measurement SERVICE BULLETIN SB7106 Page 8 of 17 Initial Release 08-14-2015 Rev. B, 01-25-2016 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS (3) Refer to Figure 5. With the wheel register side of each wheel half laying on a flat surface, measure the bolt hole length using the depth gage on a Vernier caliper. Refer to Table 2 for acceptable limits. (4) Check the base material for noticeable compression from the washer. This is a result of applying a torque greater than the maximum torque allowed for the wheel nuts. If there is notable compression of the base material, then the wheel half is considered scrap. Refer to E. Inspection Wear Limit Results. Figure 5 Measure bolt hole length Table 2 Bolt hole length limits Wheel Half Subassy Part No. Wheel Assembly Part No. Measurement Action 162-02700 (outboard) 40-83, 40-83A Less than 1.538 inch Replace wheel half 161-03000 (inboard) Less than 1.588 inch Replace wheel half 162-02711 (outboard) 40-83B Less than 1.588 inch Replace wheel half 161-03011 (inboard) Less than 1.588 inch Replace wheel half SERVICE BULLETIN Initial Release 08-14-2015 Rev. B, 01-25-2016 SB7106 Page 9 of 17 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS D. WHEEL HALVES – INSPECT LATERAL MOVEMENT ALONG WHEEL REGISTERS Inspect lateral movement limits of wheel halves. CAUTION: AVOID C-CLAMP INDUCED DAMAGE TO THE BEAD SEAT. (1) Refer to Figure 6. Bring both wheel halves together so that one is stacked on top of the other (outboard or inboard). Clamp the bottom wheel half to a flat surface. Figure 6 Setup for dial indicator inspection SERVICE BULLETIN SB7106 Page 10 of 17 Initial Release 08-14-2015 Rev. B, 01-25-2016 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS (2) Refer to Figure 7. Set the dial indicator so that it is touching the register lip of the bottom wheel half. (a) Zero out the dial indicator. Figure 7 Setup the first position of the dial indicator SERVICE BULLETIN Initial Release 08-14-2015 Rev. B, 01-25-2016 SB7106 Page 11 of 17 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS (3) Refer to Figure 8. Carefully move the dial indicator to the register lip of the top wheel half without disturbing the reading on the dial indicator. Figure 8 Setup the second position of the dial indicator SERVICE BULLETIN SB7106 Page 12 of 17 Initial Release 08-14-2015 Rev. B, 01-25-2016 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS (4) Lightly pull the top wheel half (without tilting it) toward you and slowly rotate the top wheel half. (a) Mark at least 3 of the biggest deviations that are found. (5) Once rotated a full 360 degree of rotation, lightly push the top wheel half (without tilting it) away from you until it cannot go any further, then slowly rotate the top wheel half. (a) Mark at least 3 of the biggest deviations that are found. (6) Once rotated another full 360 degree of rotation, shift the top wheel half back and forth at the highest marked deviations to determine the total register clearance at each point. (a) Add the total reading, “A” going clockwise (push or pull depending on the setup) from the zero indicator and total reading, “B” going counterclockwise (push or pull depending on the setup) from the zero indicator. This is the total clearance between the wheel half registers. (7) Refer to Figure 9. If the total register clearance is more than 0.007 inch, then both wheel halves are considered scrap. Refer to E. Inspection Wear Limit Results. Figure 9 Dial indicator reading, example SERVICE BULLETIN Initial Release 08-14-2015 Rev. B, 01-25-2016 SB7106 Page 13 of 17 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS E. INSPECTION WEAR LIMIT RESULTS (1) If both wheel halves satisfy the wear limit requirements in accordance with this service bulletin., then complete the service bulletin accomplishment instructions starting with paragraph F. Assemble the Wheel. NOTES: Wheel halves are not procurable at the 151- or 152- part level and must be obtained at the 161- or 162- wheel half subassembly level which includes the installed bearing cup. Replace bearing cups and cones as a matched set. A new wheel half subassembly includes a new installed bearing cup. If replacing a wheel half subassembly, replace the mating bearing cone. (2) If either of the wheel halves do not satisfy the wear limit requirements per section 2.C., then replace the applicable wheel half subassembly and complete the service bulletin accomplishment instructions starting with paragraph F. Assemble the Wheel. (3) If the total register clearance per section 2.D. is more than 0.007 inches, then replace both wheel half subassemblies and complete the service bulletin accomplishment instructions starting with paragraph F. Assemble the Wheel. SERVICE BULLETIN SB7106 Page 14 of 17 Initial Release 08-14-2015 Rev. B, 01-25-2016 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS F. ASSEMBLE THE WHEEL (1) Wheel and tire pre-assembly preparation (a) Examine the bead seat area of the wheel halves. If necessary, remove all lubricant, grease or foreign material with a clean cloth moistened with a mild soap and water solution or with denatured alcohol. (b) The mating surfaces of the wheel halves should not have nicks, burrs, small dents, or other damage. Damaged mating surfaces can prevent the wheel halves from mating or sealing. (c) Make sure that the tire is clean inside. If it is not clean, then wipe the bead base with a clean cloth moistened with a mild dishwashing soap and water solution or a suitable rubber cleaner. (2) Tire mounting and assembly of wheel Refer to Figure 10. SAFETY WARNING: WEAR THE APPROPRIATE PROTECTIVE CLOTHING AND ALWAYS FOLLOW PROPER TIRE INFLATION SAFETY PRACTICES. SERVICE THE TIRE WITH INFLATION SAFETY EQUIPMENT DESIGNED FOR THIS OPERATION. NOTE: Refer to AWBPC0001 for component part numbers for the 40-83, 40-83A, and 40-83B wheel assemblies. (a) After the inside of the tire has been cleaned, lubricate lightly with tire talc. (b) Inflate the tube with dry nitrogen to slightly round, and insert in the tire. The tube heavy spot is indicated by a painted yellow stripe about ½ inch wide by 2 inches long. Align the stripe on the tube with the tire red balance dot. If the tube has no balance mark, align the tube valve with the tire red balance dot. (c) Position the tire on the outer wheel half subassembly (2), inserting the valve stem through the valve hole in the wheel. (d) Place the inner wheel half subassembly (1) inside the tire, aligning the bolt holes. (e) Install the brake disc (3) in the inner wheel half aligning the bolt holes. (f) Install the three bolts (8) through the brake disc. NOTE: The washers (9) and nuts (10) must be located on the outer wheel half. (g) Compress the wheel halves and install a washer and nut on each of the three bolts. Run the nuts down by hand as far as possible. CAUTION: DO NOT USE IMPACT OR POWER WRENCHES TO TORQUE THE WHEEL NUTS AND BOLTS. THE USE OF IMPACT OR POWER WRENCHES CAN CAUSE OVER TIGHTENING. NOTE: The fasteners must be tightened by applying the torque to the nut while holding the bolt head. (h) Final torque the nuts to 150 lb-in (16.9 N-m). SERVICE BULLETIN Initial Release 08-14-2015 Rev. B, 01-25-2016 SB7106 Page 15 of 17 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS (i) Install the following in each wheel half subassembly: For the 40-83 and 40-83A: bearing cone (4), grease seal felt (5A) and rings (6), snap ring (7). For the 40-83B: bearing cone (4), molded grease seal (5), snap ring (7). NOTE: Install the end of the snap ring into the groove in the hub of the wheel half and wind or spiral the ring into the groove. Figure 10 Wheel assembly components SERVICE BULLETIN SB7106 Page 16 of 17 Initial Release 08-14-2015 Rev. B, 01-25-2016 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS G. INSTALL THE WHEEL ASSEMBLY ON THE AXLE (1) Install the wheel/tire unit on the axle making certain that the bearing cones are seated. (2) Install the axle hardware in accordance with the airframe manufacturer’s manual. (3) Inflate the tire to the required service pressure. H. RE-ATTACH THE BACK PLATE ASSEMBLIES Refer to Figure 11. (1) Install four bolts and washers into the cylinder assembly. (2) Slide the two back plate assemblies between the brake disc and the wheel flange. (3) Thread two bolts into each back plate assembly and tighten the bolts to the torque listed on the brake assembly nameplate: Figure 11 Re-attach the back plate assemblies SERVICE BULLETIN Initial Release 08-14-2015 Rev. B, 01-25-2016 SB7106 Page 17 of 17 40-83, 40-83A, 40-83B – WHEEL HALVES – INSPECT WEAR LIMITS 3. MATERIAL INFORMATION A. MATERIAL-REQUIREMENTS Contact Parker Hannifin for replacement parts availability. Parker Hannifin Corporation Aircraft Wheel & Brake Division Technical Service Hotline: 1-800-BRAKING Customer Support Fax: 440-937-5409 E-mail: clevelandwbhelp@parker.com B. LIST OF COMPONENTS Not applicable. C. INTERCHANGEABILITY None. D. PARTS DISPOSITION Not applicable.