SERUICE ilIAI{UAt - Univair Aircraft Corporation
Contents
1. INTRODUCTION This manual contains routine inspection maintenance overhaul and minor repair procedures which can be accomplished by propeller servicing facilities These instructions are intended to supplement the criteria set forth in Civil Air Regulations Part 18 and Civil Aeronautics Manual 18 In no case are they to be construed or interpreted as overriding or contradictory to the material in the regulations or manual The use of this manual by any propeller servicing facility shall not under any circumstances be interpreted or construed as an approval of the facility by Universal Aircraft Industries NOTE This manual has been approved by the Federal Aviation Agency Revised July 10 1962 SECTION I SPECIFICATIONS AND DESCRIPTION A General Specifications Type Number of Blades Blade Material Hub Material Engine Shaft Total Pitch Range Low Pitch High Pitch weight B Installations Aircraft Engine Beech Debonair Continental 35 33 A33 ITO U470 J 35 B33 10 470 K Beech Bonanza Continental H 35 0 470 G J35 K35 M35 TO 470 C N35 P35 10 470 N C Governors Hydraulically Operated Constant Speed Two Aluminum Alloy Steel l Flanged Shaft 4 inch Diameter Bolt Circle 1 2 inch Bolts and Dowel Pins 20 Degrees Adjustable at Pitch Control Arms Fixed High Pitch Stop on Piston Rod 68 lbs Rating Propeller Blade Propeller Assy Assy Diameter Max Min 225 HP FIZA 4 5 8400 0 84 822. ke Install 31 bearing balls 7 16 diam and pack with grease such as Sinclair AF No 2EP 5 Install both blades being especially careful not to allow any of the bearing balls to fall out NOTE At this stage the faces of the blade retainer flanges and the shelf or seat in the hub on which they rest should not be lubricated 6 Install pitch control arm 2 2 set screws 1 2 bolts nuts and washers 3 and balance screws plates and weights 10 on each blade The stud 5 must be at the leading edge of the blade and point toward the hub The arm must enclose the ridge which runs around the blade retainer approximately 3 4 inch outboard of the retention nut and must be pushed outboard until it rests against ite Set the center line of the arm at 16 1 2 to the 33R blade reference station on each blade see Figure 7 Snug up the clamp bolts 3 but not the set screws 1 LI ain Etor _ Q i LI VIEW WITH BLADE TIP NEAREST OBSERVER Figure 7 Pitch Control Arm Setting Revised July 10 1962 20 Te 9 13 14 150 16 LTe FE A Te Balance the propeller as outlined in paragraph E Remove both blades and liberally apply grease such as Sinclair AF No 2EP to the face of the blade retainer flanges and to the shelves or seats in the hub on which they rest Re install blades Tighten the retention nut until all play other than rotation disappears from the tip Loose
3. 2600 RPM 225 HP F12A 4 5 8400 0 84 82 2600 RPM 240 HP F12A 5 8400 0 84 83 2600 RPM 250 HP F12A 3 8400 2 82 814 2600 RPM 260 HP F12A 3 8400 2 82 82 2625 RPM The Flottorp governor Model 1F 1 is the Garwin Model 34 825 and is used on the Beech Debonair series aircraft For service in structions refer to Garwin Handbook of Overhaul Instructions and Parts List No 825 The Woodward governor 210 series is used on the Beech Bonanza series aircraft For service instructions refer to the appropriate Woodward service manuals Revised July 10 1962 De Description The hub of the Model F12 propeller is machined from welded and furnace brazed steel tubing and is attached to the engine crankshaft flange with 6 bolts and 2 dowelse The hub encloses the hydraulic piston and piston rode Forward of the hub body the piston rod is attached to a bar that links it with the two blades through ball joint links which entirely eliminate all binding in the control system A permanent lubricant is used in the ball joints to eliminate the necessity for periodic lubrication for the life of the propeller The blades are retained in the hub by a retention nut The retention nut and the bearing races are a part of the permanent blade assembly However the bearing races are designed so that if it becomes necessary to replace them they can be broken and new races which have previously been broken can be installed The aluminum alloy spinner str
4. AN l Align the two guide pins in the propeller hub with the corresponding holes in the engine crankshaft flange placing the No l blade on the Revised July 10 1962 aa a side of the TC mark on the engine flange and install the propeller 2 Install the 6 retaining bolts and washers Torque them to 600 to 700 inch pounds e 3 Secure the bolts with safety wire 4 Position spinner dome on propeller according to marks made on removal and install 12 retaining screws D Checking Propeller Track in the Shop l With the propeller in low pitch mount it on a protractor bench mandrel 2 Place a stationary object at the tip of one of the blades and make a mark on the object where the center of the blade touches it 3 Rotate the propeller 180 degrees and repeat the above operation with this blade 4 Measure the distance between the centerlines of the two marks The allowable difference is 1 8 inch 2e If the distance is greater than 1 8 inch the propeller should be sent to a FAA certificated propeller repair station for further inspection and repair E Checking Propeller Track on the Aircraft The following procedure should not be attempted unless it is known that the engine shaft is not out of line When checking the track the airplane must be in a hangar where air currents will not rock it Use the following procedure l Place a stationary object at the tip of one of the blades and make a mark on the object wh
5. If the trouble disappears the governor was at fault if the trouble persists the propeller may be at fault The governor is mounted on the engine pad with four studs and self locking nuts Removal is accomplished as follows l Disconnect the control bracket at the governor control lever 2 Remove the four mounting nuts and pull the governor from the studs 3 Install a shipping cover on the governor base to protect it 4 Cover the engine pad with a dummy base or accessory pad cover Revised July 10 1962 10 Installation of the governor is accomplished as follows l Ze 36 Use a clean dry cloth and wipe the engine pad clean CAUTION When installing the governor make certain the male splines on the governor drive mesh with the female splines on the engine drive before placing the governor on the mounting pad and tightening the nuts Place the mounting gasket over the engine pad studs with the raised surface of the gasket screen facing away from the engine Do not use sealing compounds of any kind Place the governor in position on the mounting studs and rotate the propeller sufficiently to mesh the governor and engine drive splines When the splines are meshed the governor will easily fit into place on the engine pad CAUTION Do not force the governor onto the engine pad To do so will force apart the beveled gears in the engine Install four plain washers and self locking nuts on the studs and tigh
6. fe Assy No Req Per Assy 8400 0 2 31 8400 0 2 1 FKP LE ZP 135 2 135 2 135 2 135 2 135 2 FS200 amp FS200 1 12 248 amp 248 1 12 248 amp 248 1 24 136 2 Uni VERSAL AIRCRAF T INous TRIES PROPELLER DIVISION Sky Ranch Airport Post Office Box 5306 Denver Colorado 80217 November 1 1962 SERVICE BULLETIN NO 1 Approved by FAA Applies to F12A 4 Propellers In some instances where excessibe clearance exists between the bore of the spinner bulkhead and the hub flange some of the AN3 bolts which attach the bulkhead to the flange have failed Where broken bolts have been found the following rework is recommended immediately Where no broken bolts have been found the following rework is recommended at the next overhaul The sequence of installation is important In all cases use new bolts which have been mag netically inspected 1 Tap the 2 holes marked A with 4 20UNC 3B threads using an H3 tap 2 Slide the bulkhead onto the hub 3 Re install both blade retention nut locks 237 AN4H7A bolts and AN960 416L washers 4 Re install 4 AN3H7A bolts and AN960 10 washers Note If 10 washers are not available use 2 10L washers under each bolt head 5 Torque the AN4H7A bolts to 70 to 90 in lbs 6 Install 2 M 20UNC 3A socket head cone point or cup point set screws inch long into the e two tapped holes Tighten securely by hand with a hex key 7 Torque the AN3H7A bolts to 30 to 35 i
7. assembly all O Rings and the surfaces on which they ride should be coated with a lubricating oil to facilitate installation and prevent tearing or shearing the O Ring Revised July 10 1962 SECTION IV MAINTENANCE With proper care the Model Fle propeller can give many hours of efficient operation Inspect the blades and hub at the recommended intervals and perform only the maintenance described in the following paragraphs maintenance and repairs which require more involved procedures or disassembly of the propeller must be performed by a FAA certificated propeller repair station If an out of balance condition is suspected remove the propeller and send it to a FAA certificated propeller repair station Line maintenance personnel should not attempt to balance the propeller since balance procedures are intricate and require special tools and equipment A Be Ce Propeller Removal The propeller should be in the full low pitch high rpm position before beginning removal Normally the propeller will stop in this position and the piston will be in its extreme aft position leaving a minimum amount of oil within the cylinder A rag should be kept handy to catch the oil that is freed during the removal operation Remove the propeller as follows l Remove the 12 spinner dome retaining screws and remove the dome taking care that the propeller blades are not damaged Mark the dome and mating bulkhead for identical re
8. i in lbs 3 AN310 5 Pitch Control Arm Clamp Nut 120 to 140 5 AN310 5 Pitch Control Arm Stud Nut 100 to 120 AN4H7A Retention Nut Lock Screw 70 to 90 11 AN364 1018C Piston Rod Nut 450 to 500 28 AN3H7A Spinner Rear Bulkhead Screw to 40 28 AN4H7A Spinner Rear Bulkhead Screw to 90 ANSH10A Hub Flange Attaching Bolts to 700 Figure 6 Wrench Torque for Bolts and Nuts Since it is necessary to pass the spindle of the balancer through the hub cylinder only the blades and the spinner rear bulkhead assy should be installed prior to balancing the propeller l Install spinner rear bulkhead assy 29 and 6 bolts and washers 28 onto the engine mounting flange of the hub The bulkhead should be parallel to the hub flange within O40 TIR when measured near the outer flange CAUTION Propeller F12A 4 has hub 212 S N 1 thru 206 and FS200 spinner assy No S N or S N thru 213 which uses bulkhead a if 248 These parts are drilled and tapped for AN3 attaching bolts Propellers F12A 3 and F12A 5 have hub 212 1 S N 207 and after and FS200 1 spinner assy S N 214 and after which uses bulkhead 248 1 These parts are drilled and tapped for 4 AN4 attaching bolts Take care not to interchange parts a Revised July 10 1962 19 2 Install the O Ring in the retention nut on the blade 3 Assure proper seating of the outer bearing race in the retention nut and of the inner bearing race on the blade retainer
9. 74 PARTO L 36 Plastic amp Rubber Products Co PRP568 333 2597 AMS 7274 Parker Appliance Co 2 333 N180 7 25 AN123888 O Ring 1 8 and AN123891 O Ring 2 26 35 AN3H7A Bolt F12A 4 Propeller 6 35 AN4H7A Bolt F12A 3 5 Propellers 6 15 AN4H7A Bolt 2 36 ANSH10A Bolt 6 46 AN310 5 Nut 2 23 and AN364 1018C Nut 2 53 E 49 AN501A 416 12 Screw as req 52 AN960 10L Washer F12A 4 Propeller 6 52 AN960 416L Washer F12A 3 5 Propellers 6 14 AN960 416L Washer 2 47 AN960 616 Washer 2 37 AN960 816 Washer 6 L5 AN381 2 12 Cotter 2 6 Snap Ring Waldes Kohinoor Inc 1 N5000 287 MS20995 C32 Lock Wire as req 38 5002 Dia X 1 00 long Hardened Steel Dowel 2 Revised July 10 1962 27 TABLE D i Purchased Parts Which Are Included In F12 Sub i Assemblies But Which May Be Ordered Separately Item Part No No 27 7 16 diam 29 44 AN5 31 40 AN310 5 41 AN960 D516 39 AN381 2 12 43 1 28UNF x 7 16 2 AN525 10R10 34 AN362F1032 33 MS20426AD3 8 55 3 8 diam x li Revised July 10 1962 Nomenclature Bearing Balls Chrome Steel Grade 1 O Ring Plastic amp Rubber Products Co PRP6227 47 7163 Silastic Compound O Ring Precision Rubber Products Corp 344 11306 Compound equivalent to Dow Corning 7 163 Silastic Bolt Nut Washer Cotter Hex Socket Cup Point Set Screw Screw Plate Nut Rivet 100 c sk head long Grooved Pin Groov Pin Corp Type l 28
10. a dust free atmosphere Revised July 10 1962 aite de Apply the first topcoat so that it covers the primary coat completely The topcoat shall be camouflage flat black lacquer thinned with cellulose nitrate thinner They shall be throughly mixed before applying e Allow the first topcoat to dry thoroughly at least 15 minutes and then apply the second topcoat in a similar manner Allow the final topcoat to dry for at least two hours at a normal room temperature The blades shall not be considered ready for service until they have dried for a period of 48 hours fe Apply one coat of zinc chromate primer and two coats of camouflage flat yellow lacquer to both sides of the outer four inches of the blade Also apply a stripe of yellow lacquer at the 33 in reference station on the flat face of the blade This stripe shall be 1 8 in wide by 2 in in length starting l 7 8 inches from the leading edge of the blade g Install the bearing ball information decal on the flat face side of the blade shank l 1 4 inches from the steel retainer After it has dried apply clear lacquer over its surface D Assembly L When assembling the propeller always remember before inserting O Rings apply a coating of clean engine oil to the O Rings and to all surfaces onto which they are assembled apply the proper torque to all screws bolts and nuts see Fig 6 safety all bolts nuts screws etc where necessary Item Part Number Part Torque
11. air far enough to use a smooth wrench on the flats on the front end Revised July 10 1962 21 fe _ 18 Inspect for and remove burrs on piston rod at the flats 19 Place a AN960 616 washer on stud 5 in arm 2 and slide end of link 4 onto stud on top of washer install nut Repeat for other blade 20 Loosen the clamp bolts 3 in each pitch arm Set the blade low pitch angle of 11 7 at the 33R blade reference station Tighten the clamp bolts Recheck pitch and reset if necessary Torque the nuts and install cotters CAUTION When adjusting the blade pitch or when changing pitch manually observe the cautions noted in Section IV F3 of this manual 2l Tighten the set screws 1 and stake with a center punch E Balance Following any appreciable blade repair propeller overhaul or major part replacement the propeller assy must be balanced The suspension type balancer is recommended because of the direct indication of the direction in which the propeller is out of balance no delicately adjusted balance ways are necessary and because of its ease of interpretation Vertical balance of each blade and final balance of the propeller assye is accomplished by attaching lead segments topped by steel plates with cap screws to the outboard face of the pitch control arm 2 The lead segments can be cut and trimmed to any size as long as at least one full screw hole remains in each segment The lead segmen
12. ak is even and clean with no chips in evidence as this will cause a Brinelling action to bearingse Races must also be kept in matched pairs When installing the inboard and outboard races should be positioned so that the breaks are 90 degrees apart The inboard and outboard races are not alike they are identified by the 2 and li stamp on them The race fits into blade retention nut having a larger chamfer around inner circumference for seal clearance If they are placed in blade opposite to this the blade will bind when tightened Painting Blade Repair Carefully touch up blades having minor paint damage due to repair operations or wear Blades requiring complete repainting shall first be stripped of their remaining paint and then painted according to the following instructions a All surfaces to be painted shall be thoroughly cleaned immediately before the application of the primary coat Use one of the following solvents benzol carbon tetrachloride or some other suitable organic solvent Use same care when applying second topcoat that preceding topcoat has not become soiled be The flat face of the blade will receive a three coat application one primary coat and two topcoats Mask off the camber face of the blade using any suitable method ce The primer shall be zinc chromate thinned with toluol Apply it evenly over the surface of blade avoiding a heavy coat Allow to dry for at least 30 minutes at room temperature in
13. ange linkage in this propeller has been purposely designed with ball joints to eliminate all binding in the system during operation The links 4 will always be in tension thus seeking to remain in a plane passing through the piston rod This will cause the front cross bar piston rod and piston to rotate amp small amount during travel between the extremes of pitch However if the natural forces are reversed 1 e pitch is increased manually by twisting the blade or pitch is decreased manually by pushing back on the front cross bar the links will then be in compression and will seek to align themselves perpendicular to a plane passing through the piston rod This action will cause rotation of the front bar until the ends of the link jam against the bar 23 or against the pitch arm 2 which places an undue strain on the ball joints tending to pry them apart If no resistance other than normal friction of the system is encountered the joints will not be harmed However in any case it is strongly re commended that when adjusting or changing the pitch increase the pitch by pulling on the front cross bar Revised July 10 1962 9 at the center and decrease the pitch by twisting both blades This not only will protect the ball Joints against damage but will also eliminate errors in setting the pitch k Tighten the clamp bolts 3 to proper torque See Fig 6 CAUTION It is extremely important to apply the correct
14. chine honed to remove roughness or scoring using a very fine stone Although the piston bore may be honed to a maximum I D of 2 881 inches for use with a standard sized piston only the minimum amount of material necessary to clean up any scoring should be removed Care must be exercised to maintain straight cylinder walls throughout the area traveled by the piston Spinner Repair Inspect the spinner for cracks tears and other damage Small cracks may be stopedrilled No patches or doublers are recommended because of the critical balance condition to be maintained Should it become necessary in an emergency to add a patch or a doubler be sure to add one of equal weight to the opposite side Polish out minor nicks and scratches with emery paper Blade minor and major Repair Repairs only within the limitations of CAM 18 are permissible Blade Bearing Races All blades have thrust bearing races with grooves ground 180 degrees apart in the aft side This groove assists in breaking the race for replacement and was designed for thet purpose Races cannot be repaired they must be replaced when they become brinelled or chipped If races in stock are not broken devise a tool to break the races see Figure 5 Set race in pr sg and place tool above the race Bringing press into action exert an even pressure over the grooves cut in races pve Revised July 10 1962 17 6 Figure 5 Breaking Blade Races NOTE Be sure bre
15. d of the piston rod use only an adjustable or open end wrench with smooth jaws on the flate 22 at the front end of the piston rod so as not to raise burrs on the rod Burrs will damage the piston rod bearing materiale If this surface does become burred use a fine file to dress the rod down to its original diameter be Remove nut 24 pitch bar and link assembly 4 23 31 piston rod guide 18 O Ring 19 O Ring 20 from the front end of the piston rod Bearing 21 is a press fit into guide 18 and need be removed and replaced only for damage and excessive weare CAUTION Do not disassemble pitch bar and link assembly 4 23 31 unless looseness or damage has occurred to link 4 or bar 23 If necessary to disassemble always push on the ungrooved end of the pin 31 Always replace with a new pin and insert it so that the grooves will not line up with the grooves in bar 23 Do not attempt to disassemble the pitch links 4 Although they appear to be turnbuckles they are not but are permanently pinned together Any attempt to rotate the sleeve of this link will damage it so that replacement of the entire link will be necessary Figure 2 Pitch Control Assembly Revised July 10 1962 oe k Ye 5e 6 Te 8 Je Remove hub pilot ring 25 O Ring 26 and O Ring 27 from rear of hub See Figure 3 Remove 2 screws washers retention nut locks 8 Remove 6 bolts and washers 28 from the
16. each propeller overhaul inspect the hub by magnetic particle inspection or FAA approved equivalent method Give particular attention to the weld where the aft side of the barrel is joined to the hydraulic cylinder c Replace cracked parts with new parts prior to further flight Note Repairs are not permissible d This bulletin applies only to hubs with serial numbers lower than 400 Uni VERSAL AIRCRAF T INous TRIES PROPELLER DIVISION Sky Ranch Airport Post Office Box 5306 Denver Colorado 80217 July 18 1963 SERVICE BULLETIN NO 4 Approved by FAA Applies to F12A 3 F12A 4 and F12A 5 Propellers installed on various Beech Model 33 Debonair and Model 35 Bonanza Aircraft It has been found in many cases impossible to align the slot in the AN310 5 nut with the cotter pin hole in the pitch control arm stud item 5 in Figure 1 of Flottorp Model F12 Service Manual within the specified torque range Figure 6 in the Manual Advancing the nut results in shearing the locking pin in the arm Backing the nut off may eliminate the torque entirely We recommend that at next overhaul the AN310 5 nuts and AN381 2 12 cotters on these two studs be discarded Replace with MS20365 524C all metal nuts Torque to 70 to 80 inch pounds SECTION I SECTION II SECTION III SECTION IV SECTION V SECTION VI TABLE OF CONTENTS Specifications and Description A General Specifications B Installations C Gove
17. eamlines the propeller installation and contributes to engine cooling The spinner dome is attached firmly to the rear bulkhead Drain holes in the rear bulkhead flange prevent accumulation of moisture which could cause an outeof balance condition All functional parts of the actuating mechanism are made from materials specifically selected to require no lubrication The retention assembly is prepacked with grease not requiring replenishment during the overhaul periode All grease and oil seals are synthetic rubber O rings operating at low pressure to assure long life All parts subject to corrosion are anodized or protected by suitable plating Ee Principles of Operation The Model Fl2 constant speed propeller is a single acting unit using hydraulic pressure for increasing the blade angle decreasing RPM and the natural centrifugal twisting moment of the blades for decreasing the blade angle increasing RPM The hydraulic source for operation is oil from the engine lubricating system boosted in pressure by the governor gear pump and supplied to the propeller through the propeller shaft flange A conventional governing system centrifugal flyweights balanced by a speeder spring operating a pilot valve meters oil to and fram the propeller increasing or decreasing the blade angle to maintain a pre selected RPM In case of failure of the oil supply to the propeller the blades will go to low pitche Under this condition flight may be ma
18. ere the center of the blade touches it 2e Rotate the propeller 180 degrees and repeat the above operation with this blade 3 Measure the distance between the centerlines of the two marks The allowable difference is 1 8 inch 4 If the distance is greater than 1 8 inch the propeller should be sent to a FAA certificated propeller repair station for further inspection and repair F Low Pitch Adjustment Low pitch settings for the F12 propellers are measured at the 33R blade station Revised July 10 1962 8 Aircraft Propeller Blade Pitch Assy Assy Angle Beech Debonair FI2A 4 5 8400 0 11 72 35 33 A33 B33 Beech Bonanza H35 F12A 5 8400 0 13 0 Beech Bonanza J35 K35 M35 N35 P35 F12A 3 8400 2 1355 l 2e 36 If the pitch angle is not correct refer to Figure l and use the following procedure With a hexagon wrench loosen 2 set screws 1 in each pitch control arm 2 one in each half This will require same effort to back them out against the safety staking Remove cotters and loosen the 2 clamp bolts 3 on each blade Adjust the blade pitch to the desired angle CAUTION Do not attempt to adjust the propeller blade angle with the pitch control links 4 Although they appear to be turnbuckles they are not but are permanently pinned together Any attempt to rotate the sleeve of this link will damage it so that replacement of the entire link will be necessary CAUTION The pitch ch
19. ernor Controls Propeller Blades Propeller Governor Controls Propeller Hub and Blades the blade Obvious Damage and Security of Mounting Leaks and Security of Mounting Connections Mechanically Secure and Safetied Corrosion Cracks Nicks or Dents Beyond Permissible Limits Travel and Wear Blade Retention and Propeller Track WARNING Postflight Postflight Postflight Postflight nearest 30 hours Postflight nearest 30 hours Postflight nearest 120 hours During postflight inspection if the 10 470 fuel injection engine is warm and it is necessary to move the propeller stand clear of the area of rotation and move the propeller against the normal direction of rotation magneto switch is off Make certain the While the engine is wern residual fuel in the intake ports and injectors may ignite Revised July 10 1962 and cause the engine to kick Component Nature of Inspection Propeller Hub and Visual Blades Propeller Assembly Overhaul Governor Assembly Overhaul B Lubrication Inspection Time Overspeed up to 3150 rpm If the propeller rer iad 3150 rpm replace ite At Engine Overhaul but not to exceed 1000 hrs At Engine Overhaul No external lubrication of any parts of this propeller is necessary At overhaul after cleaning and inspection of the blade bearing races and balls they should be repacked with clean grease such as Sinclair AF No 2EP Prior to
20. ght as a bright fluorescent line Other Aluminum Alloy Parts The following parts are structural parts of the pitch control system and should be inspected for fatigue cracks by penetrant inspections or anodize a Pitch control arm 2 Inspect adjacent to all tapped holes be Piston rod 17 Inspect each end at the shoulder fillet and adjacent to the threads Ce Pitch control bar 23 Inspect adjacent to all holes Magnetic Inspection Carefully inspect the hub pitch links blade races retention nut and all steel bolts and nuts by magnetic inspection preferably the fluorescent type in accordance with the best recommended practices When checking the blade races place a copper braided cable between the races and the blade Then placing the bar between the electrode plates fashion the cable between plate and bar thus inducing magnetic contact Magnetize the races in five or more equally spaced positions to insure complete coverage No insulation is necessary between cable and racese De magnetize all parts prior to returning to service Visual Inspection Carefully inspect all parts for wear galling metal pickup cracks nicks burrs and other damage Examine all O Rings for damage deformation and deterioration Check blade races for chipping at break points This causes a brinelling action to the bearings Races showing chipping effect at break points will be replaced Check all threads for rough edges irregularities meta
21. h long into the two tapped holes Tighten securely by hand with a hex key 6 Re install the remaining four AN4H bolts and AN960 416 L washers 7 Torque these four bolts to 70 to 90 in lbs 8 Re check the torque on the first two AN4H A bolts 9 Re check tightness of set screws Safety stake each with a center punch in 2 places 10 Safety all the bolt heads with one continuous piece of MS20995 C32 wire 5 16 18UNC 3A socket head cone point or cup point Screen 248 1 Bulkhead FS200 1 Spinner 237 Lock l Lol AN4H7A Bolt e AN A H AN4H7A Bolt AN960 416 L Washer E AN960 416 L Washer SOG a Rear View ee ree pr a Uni VERSAL AIRCRAF T INous TRIES PROPELLER DIVISION Sky Ranch Airport Post Office Box 5306 Denver Colorado 80217 July 18 1963 SERVICE BULLETIN NO 3 Approved by FAA Applies to F12A 3 F12A 4 and F12A 5 Propellers installed on various Beech Model 33 Debonair and Model 35 Bonanza Aircraft A small crack has been found in the welded joint where the aft side of the hub barrel is joined to the hydraulic cylinder Such cracks could lead to serious oil loss a Within the next 25 hours of time in service after the effective date of this bulletin and thereafter within each 100 hours time in service remove the propeller spinner and visually inspect for cracks and oil leaks in the weld area where the aft side of the hub barrel is joined to the hydraulic cylinder b At
22. installation if the original marking has been obliterated 2 Remove the six propeller retafning bolts and washers at the crankshaft flange and remove the propeller assembly Minor Repair Cleaning and Inspection No repairs are authorized on the propeller hub and the only acceptable methods of repairing cuts nicks cracks etc in blades are those by which the damaged portion is removed from the blades to leave a smooth well faired surface Methods which attempt to relocate metal by cold working to cover or conceal the defect rather than remove the damage are not permissible acceptable blade repairs are described in CAM 13 For cleaning use warm fresh water and soap unleaded gasoline or kerosene and suitable brushes or cloths After the blades have been cleaned all cleaning substances must be immediately removed Soap in any form should be removed by thoroughly rinsing with fresh water after which all steel surfaces should be dried and coated with clean engine oil Scrapers power buffers steel brushes and any other tools or substances that will scratch or otherwise mar the surface must not be used on blades In special cases where a high polish is desired a good metal aircraft polish may be used however upon completion of the polishing all traces of polish should be immediately removed In no instance shall the blades be polished with a power buffer Propeller Installation To install the propeller use the following procedure
23. intained at reduced throttle to prevent engine overspeeding where sufficient power is available to climb or cruise at various flight configurations at lower forward airspeeds Revised July 10 1962 A SECTION II SERVICE TOOLS amp EQUIPMENT Only one special tool is necessary for maintenance and overhaul of the Fl2 propeller Blade Retention Nut Wrench Part No EB19000 Standard tools and equipment necessary for maintenance and overhaul of the F12 propeller Propeller Assy Table Pliers for Internal Snap Ring Waldes Truarc No 5 or No 25 90 tips Suspension Type Propeller Balancer Revised July 10 1962 k SECTION III PERIODIC INSPECTION AND LUBRICATION A Periodic Inspecti Component Propeller Hub Propeller Blades on Nature of Inspection Security of Mounting and Mounting Bolts Safetied Minor Nicks Scratches and Cracks CAUTION Inspection Time Postflight Postflight Due to the high stresses to which the propeller blades are subjected their careful maintenance is vitally important particularly on the leading edge of each blade from the tip inboard for approximately 8 inches All nicks and scratches must be repaired before the flown Nicks and scratches set up concen trations of stress which can exceed the strength of the blade material the result will be a crack and premature airplane is failure of Propeller Spinner Propeller Governor Propeller Gov
24. l pickup and galling Thoroughly examine all plated and painted parts for damage exposing bare metal It should be noted at this point that the blade is anodized giving it a dull gray finish Plated parts with exposed base metal must be stripped and replated Painted parts may be touched up using approved methods Revised July 10 1962 16 fe NOTE All steel parts that have been re cadmium plated must be embrittlement relieved Inspect moving parts for freedom of movement Check shrink fits such as the blade retainer for tightness Examine internal passages for cleanliness and freedom from loose particles of metal or other substances C Repair and Overhaul le Ze 3e Le De Hub Minor Repair Minor galling and scoring of the mounting flange may be removed by polishing with emery paper If the threads in the mounting flange are damaged ream out and install a heli coil Minor scoring and scratches to the dowel pins in the mounting flange may be removed with emery paper More serious damages to the dowel pins will require replacement Corrosion sometimes develops in the rear portion of the cylinder due to gases from the engine This corrosion and or minor scoring may be removed by polishing with crocus cloth Do not use emery paper and always remove a minimum amount of metal Scrap the hub if threads in the hub for the blade retention nut are damaged beyond repair Hub Major Repair i The cylinder may be ma
25. n lbs 8 Re check the torque on the AN4H7A bolts 9 Re check tightness of set screws Safety stake each with a center punch in 2 places 10 Safety all the bolt heads with one continuous piece of MS20995 C32 wire 20UNC 3A socket head cone point or cup point 248 Bulkhead set screw FS200 Spinner 237 Lock AN4H7A Bolt AN3H7A Bolt AN960 416 L Washer AN960 10 Washer Rear View A Universar AlRcRAFr INDUSTRIES PROPELLER DIVISION Sky Ranch Airport Post Office Box 5306 Denver Colorado 80217 July 15 1963 SERVICE BULLETIN NO 2 Approved by FAA Applies to F12A 3 and F12A 5 Propellers In some cases where excessive clearance exists between the bore of the spinner bulkhead and the hub flange some of the bolts which attach the bulkhead to the flange have failed Where broken bolts have been found the following rework is recommended immediately Where no broken bolts have been found the following rework is recommended at the next overhaul The sequence of installation is important In all cases use new bolts which have been magnetically inspected l Tap the 2 holes marked A with 5 16 18UNC 3B threads using an H3 tap 2 Slide the bulkhead onto the hub AD by me J 3 Re install both blade retention nut locks 237 and their sane attaching bolts and AN960 416 L washers 4 Torque these two bolts to 70 to 90 in lbs 5 Install two 5 16 18UNC 3A socket head cone point or cup point set screws inc
26. n the nut l to l 1 2 notches until a small amount of play can be felt between the nut and retainer Over tightening will damage the blade bearing and impair operation of the propeller Install 2 screws washers retention nut locks 8 an the rear of the hub insert hub pilot 25 and O Rings 26 and 27 Stand the hub with the engine mounting flange down on a smooth surface that will prevent the hub pilot 25 from slipping out Assemble the piston rod 17 high pitch stop 15 piston 12 O Rings 13 and 14 and nut ll Insert this assy through the front of the cylinder taking care to prevent shearing the O Rings and to prevent the piston from binding Pour 1 1 2 to 3 oze of clean engine oil on top of the piston NOTE The purpose of this oil is to prevent corrosion of the exposed surface of the cylinder between overhaul periods Sa io rod guide 18 O Rings 19 and 20 and snap ring 7 NOTE This assye may not stay in its position until installation of the snap ring because the air trapped between it and the piston will be compressed and will tend to force sia the guide assy out of the hub However this compressed air will be useful later to help keep the piston to the rear of the cylinder while setting the low pitch Install pitch bar and link assy 4 23 31 and nut 24 NOTE It will be necessary to use a little effort to pull the piston rod out of the cylinder against the compressed
27. ntion nut If the outboard race does not fall wrap tape around the blade shank and lift the retention nut above the steel retainer Hold the nut in this position slip a flat curved blunt end tool between the blade and retention nut and tap lightly rotating the nut while tapping figure 4 e With the race free from the retention nut remove the blade O Ring Figure 4 Removing Blade Race B Inspection l Blades In addition to the methods discussed in CAM 18 another satisfactory method for detecting cracks in blades is as follows a Clean the blade carefully with carbon tetrachloride and dry the blade thoroughly using a clean air blast if necessary Revised July 10 1962 15 f Ze 3e l b Prepare a solution of 50 non toxic non corrosive oil which has fluorescent quality and 50 kerosene Ce Completely immerse the blade in the solution including the blade retaining nut and allow it to remain for a minimum of thirty minutes After this period remove the blade from the bath and allow the excess fluid to drain Spray the blade with carbon tetrachloride to completely remove the remaining solution Allow the blade to stand for fifteen minutes so that the solution will bleed out of any cracks present de Carefully inspect the entire blade under a near ultraviolet Light source The inspection must be conducted in a darkened booth or room Solution bleeding from a surface crack will show up under the li
28. periphery of engine mounting flange on the hub and remove spinner rear bulkhead assy 29 CAUTION While removing and replacing this bulkhead when it is not necessary to remove the propeller blades take care not to rotate the blades or in any way disturb the retention nut settings Since the retention nut locks have been removed the nuts are free to rotate Using wrench EB 19000 remove both blade assemblies Pull them straight out so as not to damage the threads on the retention nut 30 and on the inside of the hub A rag tied around the blade shank between the retention nut and the pitch control arm 2 will hold the nut in place to prevent the loose bearing balls from falling out of the races Blade disassembly Figure 3 a With a hexagon wrench loosen 2 set screws l in each pitch control arm 2 one in each half This will require some effort to back them out against the safety staking Revised July 10 1962 4 b Remove cotters nuts washers and bolts 3 and arm 2 CAUTION When it is necessary to remove the balance screws plates and weights 10 carefully note their exact location and identify them by blade Replacement as they were originally will greatly simplify balancing the propeller ce Lift the blade retention nut 30 and remove the 31 balls from the thrust bearing race de Shake the blade retention nut up and down to drop the outboard thrust bearing race from within the blade rete
29. rnors D Description E Principles of Operation Service Tools and Equipment Periodic Inspection and Lubrication A Periodic Inspection Be Lubrication Maintenance A Propeller Removal Be Minor Repair Cleaning and Inspection C Propeller Installation D Checking Propeller Track in Shop E Checking Propeller Track on Aircraft F Low Pitch Adjustment Ge Governor Maintenance Inspection Repair and Overhaul A Disassembly B Inspection C Repair and Overhaul D Assembly E Balance Parts Lists Revised July 10 1962 Page Eoo J Aw un T WWhN ND M f
30. ston Rod 113 Piston 128 High Pitch Stop Obsolete Replace with part 231 129 High Pitch Stop Washer Used only with part 128 136 Pitch Control Bar amp Link Assy 156 Balance Plate 157 Balance Plate 158 Balance Weight 171 Hub Pilot 212 Hub F12A 4 Propeller 212 1 Hub F12A 3 5 Propellers 231 High Pitch Stop 237 Retention Nut Lock 238 Balance Plate 241 Piston Rod Guide Assy TABLE B Manufactured Parts Which Are Included in F12 Sub Assys But Which May Be Ordered Separately Part Nomenclature No 131 Pitch Control Bar 133 Pitch Link Assy 135 Pitch Control Arm Assy 191 Bearing Races Pair 194 Bearing Placard 217 Spinner Dome 220 Blade Placard 239 Piston Rod Bearing 248 Spinner Aft Bulkhead Assy 248 1 Spinner Aft Bulkhead Assy 277 Spinner Placard 277 Spinner Placard Revised July 10 1962 Assy 136 136 8400 0 2 8400 0 2 8400 0 2 FS200 amp FS200 1 8400 0 2 241 FS200 FS200 1 FS200 FS200 1 No Per Propeller as as as as No Req e oe pe pe pk ped pe ge NON Bon 0 AA req m H NEH Req Per Assy eem pe pe pen pe pe pa pa NO UOuDIILUAP SHD Popojdx3 6 n y 9 o tan z s 26 Revised July 10 1962 4 TABLE C F12 Purchased Parts Item Part Nomenclature No Req No No Per Propeller 20 AN123867 O Ring 1 10 AN123874 O Ring 1 22 O Ring Precision Rubber Products Cor 333 8187 AMS72
31. t indicates a considerable change secondary balancing was incorrectly accomplished If only a slight change has occured correct it It will then not be necessary to re check secondary balance BALANCER CABLE DISC INDICATES HEAVY ON THIS SIDE THIS DISTANCE TO BE THE SAME ON BOTH aa C G ADDED WT TO CORRECT UNBALANCE C G ADDED WT TO CORRECT UNBALANCE Figure 8 Secondary Balance Correction Revised July 10 1962 23 fe For those who have conventional balancing arbors adapter cones and parallel knife edges the procedure is identical to the preceeding instructions However instead of unbalance being indicated by a disc indicator it is indicated by a tendency of the propeller to rotate toward the heavy side It should be noted that the knife edges arbors and adapters must be free from all foreign matter and must be smooth and true The ways should be checked for parallelism prior to balancing the propeller Revised July 10 1962 yan Item No 32 32 24 17 21 19 18 50 48 51 24 11 11 19 48 Item No 56 54 42 28 30 31 16 16 SECTION VI L PARTS LISTS TABLE A F12 Manufactured Parts and Sub assys Part Nomenclature No 8400 0 Blade Assy F12A 4 5 Propellers 8400 2 Blade Assy F12A 3 propeller FS200 Spinner Assy F12A 4 Propeller FS200 1 Spinner Assy F12A 3 5 Propellers 106 Hub Pilot Obsolete Replace with part 171 112 Pi
32. ten evely Recommended torque is 20 foot pounds 240 inch pounds 4 Attach the control rod to the governor control lever being sure that the lever can be operated against both high and low speed stops through the linkage from the cockpit propeller control Check for excessive binding or lost motion in the linkage Revised July 10 1962 11 SECTION V INSPECTION REPAIR AND OVERHAUL In general all instructions and procedures outlined in CAM 18 for all inspection repair and overhaul of parts of this propeller should be adhered to The following instructions supplement those in CAM 18 with details peculiar to this propeller A Disassembly Refer to Figures 1 2 3 and 4 le Remove cotter and nut from the blade end of each pitch link 4 slide end of link from stud 5 in arm 2 and remove washer 2 Remove snap ring 7 3 Carefully remove through the front of the hub the entire pitch control assembly taking care not to tilt the piston to cause it to bind in the cylinder Also have rags or container handy to catch oil from in front of piston This complete assembly is shown in Figure 2 Figure 1 L Disassemble the pitch control mechanism as follows see Fig 2 a Remove nut 11 piston 12 O Ring 13 O Ring 14 and high pitch stop 15 from rear end of piston rod 17 Revised July 10 1962 12 A CAUTION When removing and replacing the nuts at each en
33. torque to these nutg The clamping action of these bolts plus the biting of the set screw into the retainer must resist the centrifugal twisting moment of the blade under vibratory conditions If either or both blades slip from their set position the propeller will become extremely rough from aerodynamic exci tation A forced landing may result 2e Re check the pitch angle If incorrect repeat steps 2 3 and 4 6 Install cotters If cotter hole does not line up always advance nut to next slot as long as torque does not exceed 140 in lbs Te Tighten the set screws l 8 Stake the set screws with a center punch Ge Governor Maintenance Governor maintenance that can be performed by operating personnel is limited by the availability of special facilities required for extensive repairs Governor repair and overhaul should be accomplished only by facilities having adequate servicing and test equipment and either Garwin Manual No 825 or the appropriate Woodward service publications Since governor action is directly related to the propeller pitch changing mechanism there are very few governor troubles that can be isolated with the governor installed and operating Failure of the propeller to change pitch correctly might be caused either by the governor or the propeller Except for locating obvious troubles it is best to replace the governor with one known to be in good condition when trouble occurs in the propeller pitch changing system
34. ts should always be topped by a steel plate Do not alter the steel plates in any way 1 For the primary balance operation set each blade angle at the value specified in Section IV F and tighten each blade retain ing nut sufficiently to prevent blade angle change during the balancing operation 2 Check the track of each blade as prescribed in Section IV D 3 Mount the propeller in the balancer using the proper adapter cones le Add or remove lead as indicated until balance in all directions is obtained 5 Remove the propeller from the balancer and for the secondary balance operation reset the blade angle 90 above low pitch position 6 Mount the propeller in the balancer Te Because longitudinal balance was obtained during the primary operation any unbalance that occurs in the secondary position should be to either side only If longitudinal unbalance is indicated recheck the primary balance the accuracy of the balancer or both Revised July 10 1962 22 fe 8 To correct sideways unbalance in the secondary position in a manner that will not affect the primary balance add an equal amount of lead in 4 places on the same side of the hub 2 on each blade as shown in Figure 8 Where only a small correction is required l screws without any lead or plates may be used It would also be permissible to use several AN960 416 washers on each screw the same quantity on each 9 Re check the primary balance If i
Download Pdf Manuals
Related Search