BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL

hinge strap for parallelism within .03 inch. Check the valve P-195) for an opening of 35 ± 10 degrees. (Figure 203) Aircraft that have or will have the existing inboard leading NOTE edge fuel cells replaced with spare fuel cells P/N 58-380030-¯/, 58-380030-8, 58-380030-9, and if the fuel cell is to be stored for a period of 10 58-380030-10 should install Kit 60-9002-3 S in the fuel cell days or longer, coat the inside of the cell with liner top, bottom, root rib, and spar as described below and light engine oil to prevent cracking or in Service instructions No.0585-281. If only one fuel cell is deterioration- to be replaced, use Kit 60-9002-1 S for left hand installation and Kit 60-9002-2 S for right hand installation. Serials P-196 and after are delivered from the factory with INBOA RD L EA DING ED GE FUEL - CELL the equivalent of Kit 60-9002-3 S installed. INSTALLATION - ' a. Remove the fuel cell as described in INBOARD LEADING EDGE FUEL CELL REMOVAL. CAUTION Exercise caution when ·installing baffled fuel NOTE cells to prevent damage to the flapper valve. Aircraft that have had any of the above fuel a. Carefully insert the fuel cell through the fuel cell cells installed do not require complete removal access hole (2) and snap the cell in place. of the fuel cell. Access .covers and inboard b. Install the fuel cell outlet plate with screws and fittings should be removed and the inboard end 28-10-00 Page 202 Nov 2/73 BEECHCRAFT DUKE60 SERIES MA1NTENANCEMANUAL of the fuel cell pulled back far enough to allow kit are unnecessary when new fuel cells are installation of the velcro tape. installed. h. Make the appropriate log book entry. i. After installation of baffled fuel cells, change the DO NOT ADO VELCRo Usable fuel placards on the filler caps and fuel selector valve scHAMFERED VELCROTAPE BS instructed in Service Instructions No.0559-281. INBOARD LEADING EDGE BAFFLED FUEL CELL - FLAPPER VALVE INSPECTION On aircraft that are equipped with baffled fuel cells, the 'EN OEAFU C tNG Ílapper ValVOS should be inspected periodicalily (Beech Aircraft recommends that the inspection be accomplished at each annual inspection) for freedom of operation and proper seating. The inspection may be accomplished as follows: / TRIM P1LE a. Remove the fuel boost pump (refer to 28-20-00). b. Open the zipper in the fuel cell baffle. Installation of Velcro Tape c. Locate the flapper valve in the lower aft portion of Figure 203 the baffle and determine whether the valve element is metal or phenolic. d. If the flapper valve element is metal, it should be b. Lightly sand the surface that the veicro tape will be inspected and repaired, if necessary, as described below; bonded to as shown in Figure 203 and thoroughly clean the sanded surface with toluol (22, Chart 207,91-004)O). 1. Move the flapper valve element through its full c. Apply a coat of cement (39, Chart 207, 91-00-00) travel. There should be no binding and the element should to the cleaned surface. seat flush against the valve plate. d. Activate the velcro tape by dipping into a bath of 2. If the flapper valve element binds and/or does M I L-M-13999 methyl ethyl ketone (21, Chart 207, not seat properly, the element arm could be bent. The arm 91-00-00) and press the backing of the velcro tape to the can be straightened by placing a screwdriver between the cemented surfaces. Allow 15 minutes (minimum) for drying arm and element and pressing the element toward the to ensure a good bond. closed position. e. Position the fuel cell in place and press the velcro 3. If after straightening the arm, the element still hook and pile together by pressing outward in the area of binds and/or does not seat property, the element should be the vetero tape. removed and replaced with a new element. The element f. Inspect the flapper valve for freedom of movement may be replaced by removing the two bolts from the upper under its own weight. If the flapper valve binds, refer to part of the flapper valve assembly. The same attaching parts INBOARD LEADING EDGE FUEL CELL FLAPPER should be used to install the new element. The new flapper VALVE INSPECTION. element should be inspected after installation, to determine that it was not damaged during installation which could cause it to bind and/or not seat properly. NOTE e. If the flapper valve element is phenolic, it should Before closing the zipper, inspect the cavity be inspected and reworked, if necessary, as described inboard of the baffle for foreign material, below: g. Gosethe zipper and refer to INBOARD LEADING 1. Move the flapper valve element through its full EDGE FUEL CE LL I N STA LL ATION for further travel. There should be no binding and the element should instructions on installing the fuel cell. seat flush against the valve plate. 2. If the flapper valve element binds and/or does not seat properly, the upper rear side of the element may NOTE be binding against the valve plate. 3. The flapper valve element may be relieved installation of Kit 60-9002-3 S is required on a from binding by filing a small radius on the upper rear side first time basis only. Repeat installations of the of the element. 28-10-00 Page 203 Nov 2/73 BEECHCHAFT DUKE60 SERIES MAINTENANCE MANUAL NOTE A shop towel saturated with light oil may be placed directly below the flapper valve to 1 absorb the phenolic dust during rework. 4. After determining that the flapper valve is functioning properly, thoroughly wipe the area in the vicinity of the flapper valve with an oil saturated shop - - - - towel. f. Close the zipper in the main fuel cell baffle. TOP VIEW g. Clean the gasket contact areas on the fuel cell and the fuel boost pump. h. Install the fuel boost pump (refer to 28-20-00). BOX SECTION FUEL CELL REMOVAL (Figure 204) 3 a. Drain and purge the fuel cell. b. Remove the access plate (1). c. Remove the inboard (2) and outboard (3) access plates on the underside of the wing. r d. Remove the fuel cell plates and remove the internal - - - fuel cell interconnect clamps. 60-12-4 NOTE 2 BOTTOM VIEW On later Duke A60's, beaded interconnects are incorporated in the fuel system so that fuel 1. Access Plate œ\ls aft of the main spar can be attached 2. Box Section Cell Inboard Access without opening the leading edge cavities. 3. Box Section Cell Outboard Access e. Disconnect the drain and vent plumbing. f. Unsnap the fuel cell and remove it from the wing Box Section Fuel Cell Access Openings cavity through the outboard access hole (3). Figure 204 NOTE plates on the underside of the wing. Torque access plates to 45 to 55 inch-pounds. If the fuel cell is to be stored for a period of 10 e. Install access plate (1). days or longer, coat the inside of the cell with light engine oil to prevent cracking or deterioration. OUTBOARD LEADING EDGE FUEL CELL REMOVAL (Figure 205) BOX SECTION FUEL CELL INSTALLATION a. Carefully insert the fuel cell into the wing cavity a. Drain and purge the fuel cell. through the outboard access hole (3), and snap in place. b. Remove the screws securing the filter neck (3) to b. Connect all fuel and vent plumbing. Torque the the wing skin, rubber fuel fitting nipples to 25± 5 inch-pounds. c. Remove the access plates (2) and the fuel and vent c. Install the internal fuel cell interconnect clamps. plumbing access plate (1) on the underside of the wing. Torque clamps to 25 ± 5 inch-pounds. d. Disconnect the fuel and vent plumbing. d. Install the inboard (2) and outboard (3) access e. Remove the internal fuel cell interconnect clamps. 28-10-00 Page 204 Nov 2/73 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL g. Install and secure access plates. clean water and wipe dry with clean cloths. h. Pressurize the fuel system using 0.50 + 0.25 - i. Install wet wing tip on airplane. 0.00 psig. There should be no pressure loss in 15 minutes. i. Fuel and restore electrical power tothe airplane as LEAKAGE CHECKS AND REPAIRS (WET WING T/P) required. (Figure 208) LEAK TEST To classify the degree of leakage in a wet wing tip fuel cell, (Figure 207) measure the size of the wet area around the leak. A more accurate measurement may be obtained by wiping the leak- a. Ensure that all repairs to the wet wing tip are com- age clean and applyingtalcum powder in the area of the leak. pleted and sealed. After 30 minutes, recheck the area to determine if the leak b. Connect pressure source to the wet wing tip as classifies as a stain, seep, heavy seep or running teak as shown in Figure 207. Indicated in Figure 208. Fuel leaks must also be classified as to whether they occur in an open area or in an enclosed area to differentiate between those that require immediate repair CAUTION and those not considered potential flight hazards. Ensure that the filler cap and access plate are secure. This test should be done when the wet WARNING wing tip is removed from the fuel system of the airplane. Any leakage in an enclosed area, such as the wheel well, or in an area where the fuel will blow into the fuselage, requires grounding until repair c. Apply 3.73 ± 0.25 psig to the wet wing tip for 5 is made. - minutes. d. Apply leak detector compound MIL-L-25567 (14, Chart 207, 91-00-00) to the outside of the wet wing tip. a. Repair of heavy seeps or smaller leaks in an open e. Mark all leaks as indicated by bubbles. area may be delayed until the airplane is down for other f. Depressurize the wet wing tip, locate and repair maintenance. feaks (see Figure 206).. b. Any leakage in an enclosed area requires im- g. Repeat the pressurization test procedure and re- mediate grounding and repair. pair leaks until there is no leakage. c. Remove any sealant around the leak with a sharp, h. Rinse leak detector compound offwet wing tipwith nonmetallic tool, such as a toolof chisel-shaped Formica. OPEN END R EUSLSAU RO M A AO ETER WET WING TIP CLEAN COMPRESSED AND/OR FILTERED AIR I PRESSURE SOURCE PLUGS OF 5.6 ±.25 PSIG Leak Test Set-up Figure 207 28-10-00 Page 207 Oct 19/77 BEECHCRAFT DUKE60 SERIES MAINTENANCEMANUAL Scarf the ends of the existing fillefso that a new sealant can opening or fitting, retorque the attaching hardware. If the form a continuous and smooth tie-in. PR-890B-1/2 (19, leak persists, replace the gasket. Chart 205, 91-00-00) or EC-1675B-1/2 (20, Chart 205, 91-00-00) is recommended for the sealing process. Thoroughly clean the area to be repaired with methyl ethyl FUEL CEL LL EA KA GE CHECK ketone or naphtha prior to sealing. The following repairs are permissible: Although the chemical test is more sensitive, either of the following test procedures may be used to detect leaks in the 1. If the leakage is around a rivet, restrike the bladder cells. rivet. This can only be done once. If the leak persists, replace the rivet. a. Soapsuds Test. 2. If the leakage is around a bolt with a gasket type seal, retorque the bolt. If the leak persists, replace the 1. Attach test plates to all fittings. seal or the bolt. 2. Inflate the cell with air to a pressure of 1/4 psi 3. If the leakage is at the gasket around an access maximum. RUNNING LEAK 3/4' DIA. O 4" -5" DIA. STAIN 1 1/2" DIA. O SEEP 6"MAX. 3 1/2"-4" DIA- O AREA WHERE FUEL APPEARS TO FLOW OR RUN, FOLLOWING CONTOUR OF SKIN WHEN THIS AREA IS WIPED DRY. FUEL WILL USUALLY BEGIN TO DRIP HEAVY SEEP AFTER REACHING THIS POINT. A100-281-23 Leakage of Wet Wing Tip Fuel Cell Figure 208 28-10-00 Page 208 Oct 27/75 BEECHCRAFT DUKE60SERIES MAINTENANCEMANUAL 3. Apply a soap and water solution to all repaired c. Abraided holes. areas and any areas suspected of leakage. Bubbles will d. Loose hangers and glove snaps (hot repair only). appear at any point where leakage occurs. 4. After test, remove all plates and wipe soap Repair the fuel cell as follows: residue from the exterior of the cell. a. Thoroughly clean the damaged area, (at least one b. Chemical Test square foot surrounding the injury) with methyl ethyl ketone solvent. Three washings are recanmended to assure 1. Attach test plates to all fitting openings except cleanliness. one. b. Cut a patch from repair material fumished in repair 2. Pour ammonia on the absorbent cloth in the Kit No. 2F1-2-31853, large enough to extend beyond ratio of 3 cc per cubic foot of cell capacity. Place the damaged area by 2 inches in all directions. 'The patch saturated cloth inside the cell and install the remaining test should be thinned toward the edges. plate. c. Place the dull or gum stock side of thie patch next 3. Make up a phenolphthalein solution as to the cell. Wash the patch thoroughly in methyl ethyl follows: add 40 grams phenolphthalein crystals to 1/2 ketone. gallon of ethyl alcohol, mix, then add 1/2 gallon of water. 4. Inflate the cell with air to a pressure of 1/4 psi NOTE maximum. 5. Soak a large white ci oth in the No patch is required for loose hanger or glove phenolphthalein solution, then wring it out thoroughly and snap repair, but heat must be used for curing. spread it smoothly on the outer surface of the cell. Press the cloth down to insure detection of minute leaks. d. Mix the cement in the following proportions and 6. Check the cloth for red spots which will sequence. Use one quart can containing 272 grams of indicate a leak. Mark any leaks found and move the cloth to 2342C, heat if necessary to liquify. To this, add one can of a new location. Repeat this procedure until the entire 2233C (185cc) and stir until smooth (a minimum of 5 exterior surface of the cell has been covered. If red spots minutes is required). appear on the cloth, they may be removed by resoaking the e. Apply two evenly brushed coats of cement to the cloth in the solution. cell and patch surface. Allow 30 minutes drying time 7. The solution and test cloth are satisfactory between the second coat and the application of patch (do only as long as they remain clean. Indicator solution that is not use cement after it has been mixed more than two not in immediate use should be stored in a closed container hours). to prevent evaporation and deterioration. f. Center repair patch over repair area and roll down firmly using the 1 inch stitcher. Start rolling from center of After the test, remove all plates and test equipment. Allow patch to the outside edge. This will remove any trapped air. the cell to air out. Hanger or glove snap repairs use the same cementing and drying time as regular repair but will require heat for curing. g. Place cellophane over repair and on inside of cell NOTE under repair. It is very important that the cellophane on the inside of the cell be placed under the repair area, thus In conducting the tests outlined above, the cell preventing the two inside surfaces of the cell from being need not be confined by a cage or jig, providing cemented together. Over the outside cellophane place the the 1/4 psi pressure is not exceeded. 1/4 inch cloth-backed foam rubber, cloth side up. Over the foam rubber place a 1/4 x 6 x 6 aluminum plate and place a "C" clamp (8 inch min. clamp) over the metal plate and FUEL _CELL REPAIR underneath the work bench top. With patch and plate centered over repair area, tighten the "C" clamp until GOODYEAR FUEL CELLS cement is forced out under edges of the repair (let cure for 72 hours). The following items for field repairable injuries (inside or outside) are permissible. Damaged cells, not covered by NOTE these items should be returned to the Goodyear Tire And Rubber Company, Rockmart, Georgia, for repair. Air cured repairs are to be made at room temperature of approximately 75°F. Add 25% a. Punctures. to the cure time for each 10° drop in b. Slits - to maximum 3 inch length. temperature. 28-10410 Page 209 Oct 27/75 BEECHCRAFT DUKE 60 SERIES MAINTENANCE MANUAL If heat is used for curing, insert element from No. b. Heat Cure: (Kit No. 2F1-2-31234). Kit consists of 2F1-3-25721 cure iron (contained in Kit 2F1-2-31234) all the above items listed in the air cure repair kit, plus the between "C" clamp and metal plate, then tighten "C" following items: clamp until cement is forced out from edges of the patch. Cure for 2 hours at 240°F. Allow iron to cool for 15 to 20 QUANT/TY NOMENCLA TURE GOODYEAR minutes before removing. Remove iron, metal plate, foam PART NO. rubber and cellophane. Dampen cellophane with water, using a sponge, and remove by peeling off. Loose edges of 1 1" Paint Brush oatch up to 1/4 inch maximum may be trimmed off and 1 1" Stitcher buffed smooth. Protect area of tank around buffed area- 1 Cure Iron (240°F) 2F1-3-25721 with masking tape. Loose edges exceeding 1/4 inch may be 2 1/4" x 6" x 6" recemented using the same cure procedure as previously Aluminum Plate used. Storage and Handlirig: Prior to storage, clean the cell with UNIRO YAL FUEL CEL LS warm water and soap. Dry and wrap in as small a package as possible and place in a cardboard box. Store in a cool dry For repairs of Uniroyal fuel cells, refer to Uniroyal room away from any electric motor that might be in Handbook , Recommended Handling and Storage operation. Procedures for Bladder Type Fuel and Oil Cells P/N FC 1473-73. Materials and Equipment needed for repair: a. Air Cure: (Kit 2F1-2-31853) QUANT/TY NOMENCLATURE GOODYEAR PART NO. 2Qts. Cement 2342C 2-1/2 Pts. Mixture 2333C 2 Bottles Mixture . 2315C 2 (1 Pts.) Methyl Ethyl Ketone 1 Sheet 12" x 12" Patch BTC39 1 Sheet 12" x 24" Cellophane 1 Sheet 1/4 x Foam Rubber 12" x 12" Cloth Back "END" 28-10-00 Page 210 Oct 27/75 BEECHCRAFT DUKE 60 SERIES MAINTENANCEMANUAL DISTRIBUTION - MAINTENANCE PRACTICES c. Install the fuel pump heat shield. d. Close the right cowl door. FUEL BOOST PUMP REMOVAL ENGINE DRIVEN FUEL PUMP ADJUS7MENT a. Drain and purge the fuel system for the a. The fuel pump is located at the rear, onthe lower appropriate wing. right side of the engine. Access is the right cowl door on b. Make sure the electrical power to the boost pump each nacelle. is off. b. Install a fuel pressure gage (0-30 psi range) and a c. Remove the pump access cover on the underside of "T" fitting on the pressure side of the pump. the wing. c. Break the safety wire and loosen the lock nut of d. Disconnect the electrical leads to the pump. the adjusting screw. e. Cut the safety wire from around the retaining bolts d. Disconnect and plug the air reference line from the and remove the bolts. enginè pump. f. Pull the pump down far enough to gain access to the pump outlet line. NOTE g. Disconnect the outlet line and remove the pump. Allow the air reference line fitting on the fuel FUEL BOOSTPUMPINSTALLATION pump to remain open while adjusting; the pressure on the pump. a. Clean the gasket contact areas on the fuel cell and the fuel pump. e. Operate the engine at 2900 rpm and set the engine b. Connect the fuel outlet line to the fuel boost pump to 23 psi with the boost pump off. pump. f. Reinstall the air reference line to the pump. c. Install the boost pump with new gaskets. Torque g. Tighten the lock nut and safety wire. the bolts to 45 to 55 inch-pounds and safety wire. d. Connect electrical leads to the pump. FUEL SELECTOR VAL VE REMOVAL e. Install the pump access plate on the underside of the wing. a. Drain the fuel system. b. Place the aircraft on jacks and partially retract the ENGINE DR/VEN FUEL PUMP REMOVAL gear until the inboard main gear door is fully extended. c. Remove the selector control cable. (Refer to FUEL a. Access to the engine-driven fuel pump is gained SELECTOR VALVE CONTROL CABLE REMOVAL). through the right cowl door on each nacelle. d. Remove the fuel selector valve plumbing. b. The fuel pump is located at the rear, on the lower e. Remove the bolts securing the selector valve to the right side of the engine. mounting bracket. c. Disconnect the fuel inlet, outlet and drain plumbing from the pump. Remove the fuel pump heat FUEL SELECTOR VALVE INSTALLATION shield. a. Position selector valve on the mounting bracket and install attaching bolts. NOTE b. Lubricate threaded fittings with VV-P-236 petrolatum (Chart 208, 91-00-00). The 60-910031-3 elbow in the inlet port of the c. Connect the fuel selector plumbing. fuel pump is not a reusable part. Anytime the d. Install the selector control cable. (Refer to FUEL elbow is loosened or removed, it should be SELECTOR V A LVE CONTROL C A BLE replaced with a new part. INSTALLATION.) e. Rig the selector control cable. (Refer to FUEL SELECTOR VALVE CONTROL CABLE RIGGING.) d. Remove the pump retaining nuts and remove the pump. FUEL SELECTOR VALVE CONTROL CABLE REMOVAL ENGINE DR/VEN FUEL PUMP INSTALLATION (Figure201) a. Install the fuel pump, on the lower rear right side of the engine, with a new gasket. a. Remove the cover plate (not shown), stop screw b. Connect fuel inlet, outlet and drain plumbing on (1) and overtravel tube (2) from the valve gearbox (3) the pump. located in the wheel well. 28-20-00 Page 201 Nov 2/73 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL CROSSFEED O O I - - TO + FUEL --- 1 in. SELECTOR 5 3 PANEL -- -- - -- ON- 1/8 in. DIAM. 1/4 in. LONG APPROX. 1/8 in. OFF 60-17-3 Fuel Selector Valve (LH Shown, Cover Plate Removed) Rigging Tool Figure 202 L Stop Screw 6. Slider 2. Over Travel Tube 7. Cable Housing 3. Selector Valve Gearbox 8. Cross Feed Port port and rotate the cable (LH thread) to engage two threads 4. Selector Gear 9. Over Travel Port in the selector valve gear. 5. Control Cable e. Rotate the selector gear 6-3/4 revolutions to feed the control cable through its housing up to the fuel selector Fuel Selector Valve panel gearbox in the pilot's compartment. Figure 201 f. Screw the cable in (LH ihread) until the cable end is 4.3 inches minimum to 4.5 inches maximum from the face b. The cable may be removed through the overtravel of the overtravel port. It will be necessary to have someone port by rotating the selector gear. hold the selector handle pointer in position until the control cable is engaged with the gears in the fuel selector FUEL SELECTOR VALVE CONTROL CABLE panel. INSTALLATION g. Move the fuel selector handle pointer to the CROSSFEED position. The arrow on the selector gear Refer to FUEL SELECTOR VALVE CONTROL CABLE should now be at the 12 o'clock position. The cable ena RIGGING for installation procedures. should measure 2.7 inches minirnum to 3.3 inches maximum from the overtravel port. FUEL SELECTOR VALVE CONTROL CABLE h. Install the stop screw and install and safety the R/GGING overtravel tube. Place the selector handle in all positions to (Figure 201 and 202) insure proper selection and operation. i. Install and safety the cover plate. No lubricant is used To aid in the rigging procedure, a locally manufactured on the fuel selector valve. "rigging tool" (see Figure 202) may be constructed for turning the selector gear. Tubing of 1/4 to 3/8 inch VENTFLOATVALVEREMOVAL diameter is used for the handle and 1/8 inch steel pins are used for the protrusions which,contact the selector gear. a. Remove the two access plates on the lower side of the wing tip. a. Remove Tie c4ver plate (not shown), stop screw b. Loosen the clamps and disconnect the three vent lines (1) and overtravel tube (2) from the fuel selector valve from the float valve. gearbox (3) located in the wheel well. (See Figure 201). c. Loosen the clamp securing the float valve in position. b. Using the rigging tool, set the selector gear (4) in the CROSSFEED position. Thè arrow on the selector gear NOTE should be positioned at 12 o'clock. c. Set the selector handle pointer on the fuel selector Mark the position of the float valve in the panel 180° from the ON position and hold firmly in this clamp. The float valve must be reinstalled in the position. same position to enable the float to function d. Insert the control cable (5) through the overtravel properly. 28-20-00 Page 202 Nov 2/73 BEECHCRAFT DUKE 60 SERIES MAINTENANCEMANUAL TAPERED LUBRICATE LUBRICATE LUBRICATE PIPE THREADS DO NOT LUBRICATE STRAIGHT THREADS FEMALE THREADS NEVER ALLOW LUBRICANT TO CONTACT THIS SURFACE 0-604-5 Lubrication of Flared Fittings Figure 203 d. Remove the float valve from the clamp. 45 degree angle facing forward to ensure a positive vent pressure, for any other configuration would create a negative pressure that would pull the air, or air and fuel VENT FLOAT VALVE INSTALLATION from the fuel cell. a. Position the float valve in the clamp in the same position as noted during removal. Torque the clamp to 25± 5 inch- pounds. b. Connect the three vent lines to the float valve and torque the hose clamps to 25 ± 5 inch-pounds. c. Install the two access plates on the lower side of the gE F/TTINGS 2 2 (Figue 203) 45° When installing flared fittings and hoses, make sure the threads are properly lubricated with VV-P-236 petrolatum (Chart 208, 91-00-00). When previously installed fittings - - are removed, they should be wiped clean and relubricated - before they are reinstalled. Torque all fittings in accordance with (Chart 204, 91-00-00). EXTERNAL FUEL CELL VENT LINE 10 6°"°, (Figure 204) The end of the fuel vent lines should extend 10 degrees forward from vertical for a distance of 2.2 inches below the Fuel Vent Line lower surface of the wing. The end of the line is scarfed at a Figure 204 "END" 28-20-00 Page 203 Nov 2/73 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL INDICATING - MAINTENANCE PRACTICES 1. Connect the resistor to wire E13A20 (at in- board leading edge transmitter) and to E11B20 (at nacelle FUEL QUANTITY INDICATORS transmitter) for the right wing system. Fuel quantity is measured by float type transmitter units 2. Connect the resistor to wire E17A20 (at in- which transmit the common level indication to a single indi- board leading edge transmitter) and to E15820 (at nacelle cator for each respective wing. Two transmitters are located transmitter case) for the left wing system. in each inboard leading edge wing cell, one outboard and one inboard. One transmitter is located in each nacelle fuel Actual fuel level for this test is irrevalent. cell. FUEL TRANSMITTER REMOVAL NOTE a. Remove fuel cell access plate. (See Figure 201 or A potentiometer, located on the printed circuit 202, 28-10-00.) board behind each fuel quantity gage, naay be b. Disconnect electrical wire at the transmitter. adjusted to obtain a full reading on the gage. c. Remove the bolts attaching the fuel transmitter to the fuel cell. d. Cover the open fuel cell port to prevent entry of c. The empty reading on the fuel gage may be foreign materials. checked by jumping a 20 gage wire between the inboard leading edge transmitter and the nacelle transmitter.Connect FUEL TRANSMITTER INSTALLATION wire E13A20 to E11B20 (right wing) anä! E17A20 to E15B20 (left wing). Fuel level for this test is irrelevant. a. Remove the cover from the fuel cell port. Clean the - d. To check the transmitters for the proper resistance surfaces of the fuel cell and transmitter. in the empty position, it is necessary to defuel the airplane. If b. Install the fuel transmitter with a new gasket. Tor- the fuel gages do not read empty, measure the resistance of que the attaching bolts to 25 ± 5 inch-pounds and safety the transmitters in series. wire. c. Connect the electrical wire to the transmitter. 1. Connect the lead of an ohmeter to the number d. Install the fuel cell access plate. 2 terminal of the inboard leading edge transmitter and the other lead to the number one terminal on the nacelle trans- mitter (right wing). NOTE 2. Connect the lead of an ohmeter to the number 2 terminal of the inboard leading edge transmitter and the On airplanes serials prior to P-186, when AC other lead to the case terminal of the nacelle transmitter (left transmitters are removed for replacement, install wing). Rochester transmitters. When this is done, the remaining transmitters in the applicable wing and The total resistance for each side should be 0 to 0.5 ohms. If the printed circuit board must be replaced. the total resistance is excessive, check each transmitter and/or associated wiring for the cause of high resistance. ADJUSTING AND TESTING FUEL GAGING SYSTEM e. To check the transmitters for theproper resistance in the full position, visually check to determine all tanks are An external power unit regulated at.28.25 VDC should be full. If the fuel gage does not give a full indication, check the connected to the airplane when checking and adjusting the resistance total for each wing as in the preceding step. fuel gages for proper indication in the full and empty posi- f. With AC transmitters installed, the total resistance tions should be 90 ohms per wing; individual transmitters should register 30 ± 2 ohms. With Rochester transmitters installed, a. Remove the access plates covering the fuel quan- the total resistance should be 270 ohms per wing; individual tity transmitters. transmitters should register 90 ± 2 ohms. b. To check the fuel gage for full readings it is neces- g, Replace the access covers. sary tosubstitutea resistor for the three transmitters on each Iside. On airplanes equipped with AC transmitters, a 90 ohm resistor is required; on airplanes equipped with Rochester FUEL FLOW INDICATOR transmitters, a 270 ohm resistor is required. The resistor maý be connected as follows: For fuel flow indicator refer to Chapter 73. 28-40-00 Page 201 Oct 19/77 BEECHCAAFT DUKE60 SERIES MAINTENANCE MANUAL FUEL SIGHT GA GE (P-402 and after) b. Remove the screws around the sight gage and remove the gage. For conveniance during fueling operations there is a fuel sight gage installed in each wing. The gage is installed in the FUEL SIGHT GAGE INSTALLATION (P-402 and after) upper leading edge just outboard of each nacelle. The gage is of the mechanical float type and the indicated fuel quantity is a. Position the gasket and gage in place (the gage in U.S. gallons. will fit only one way). b. Install the attachment screws and torque to 25 FUEL SIGHT GAGE REMOVAL (P402 and after) inch-pounds. c. Safety wire the attachment screws. a. Remove the screws in the access plate and re- d. Install the access cover plate and secure with move the plate. screws. "END" 28-40-00 Page 202 Oct 19/T7 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL CHAPTER 30 LIST OF PAGE EFFECTIVITY CHAPTER SECTION SUBJECT PAGE DATE 30-EFFECTIVITY 1 Jun 21/82 30-CONTENTS 1 Jun 21/82 2 Jun 21/82 30-00-00 1 Nov 2/73 30-10-00 1 May 30/75 2 May 30/75 101 Nov 2/73 102 Oct 19 77 201 Oct19J7 202 Oct 19/77 203 Oct 19/77 30-20-00 1 Oct 19/77 30-30-00 1 Nov 2/73 30-40-00 1 May 12/78 101 Nov 2/73 201 May 12/78 202 Nov 2/73 30-60-00 1 Jun 21/82 101 Jun 21/82 102 Jun 21/82 103 Jun 21/82 104 Jun 21/82 105 Jun 21/82 106 Jun 21/82 201 Jun 21/82 202 Jun 21/82 203 Jun 21/82 204 Jun 21/82 205 Jun 21/82 206 Jun 21/82 207 Jun 21/82 208 Jun .21/82 "END" 30-EFFECTIVITY Page 1 A13 Jun 21/82 BEECHCRAFT - DUKE60 SERIES MAINTENANCE MANUAL CHAPTER 30 - ICE AND RAIN PROTECTION TABLE OF CONTENTS CHAPTER SECTION SUBJECT SUBJECT PAGE GENERAL 30-00-00 Description and Operation 1 AIRFOlL 30-10-00 Description and Operation i Troubleshooting 101 Maintenance Practices 201 Servicing 201 Surface Deicer Boot Removal 201 Surface Deicer Boot Installation 201 Preparation of Metal Surfaces 201 Preparation of Rubber Surfaces 201 Spray Coat Method 201 Brush Coat Method 201 Installation of the Boot 201 Sealing Edges 202 Stall Strip Installation 202 Resurfacing Deicer Boots 202 Adjustment 203 Component Location 203 Time Delay Relay 203 Control Relay 203 Distributor Valve 203 Component Replacement 203 AIR INTAKES 30-20-00 Description and Operation 1 PITOT AND STATIC 30-30-00 Description and Operation 1 WINDOWS AND WINDSHIELD 30-40-00 Description and Operation 1 Troubleshooting 101 Maintenance Practices 201 Electrically Heated Windshield Resistance Check 201 Sensing Element Resistance Check 201 J¯\eçtgcally.Heated Windshield Voltage Check 201 Electrically Heated Windshield Functional Test 201 PROPELLERS 30-60-00 Description and Operation 1 Electric Propeller Deicing (Prior to P-579) 1 Electric Propeller Deicing (P-579 and After) 1 Troubleshooting Troubleshooting Propeller Deicing System (Prior to P-579) 101 3|D-CONTENTS Page 1 A13 June 21/82 BEECHCRAFT DUKE 60 SERIES MAINTENANCEMANUAL CHAPTER 30 - ICE AND RAIN PROTECTION TABLE OF CONTENTS (Cont'd) CHAPTER SECTION SUBJECT SUBJECT PAGE Troubleshooting Electrothermal Propeller Deice (Cont d) 30-60-00 System (P-579 and After) 105 Maintenance Practices 201 Propeller Deicer Boot Removal 201 Propeller Deicer Boot Installation 201 Deicer Timer Check (Prior to P-579) 203 Deicer Timer Check (P-579 and After) 203 Heat Test (Prior to P-579) 203 Heat Test (P-579 and After) 204 Continuity Test (Prior to P-579) 204 Continuity Test (P-579 and After) 204 Brush to Slip Ring Resistance Test 204 Brush Block Resistance Check (Prior to P-579) 204 Brush Block Resistance Check (P-579 and After) 205 Brush Replacement (Prior to P-579) 205 Brush Replacement (P-579 and After) 207 Slip Ring Machining 207 "END" 30-CONTENTS Page 2 June 21/82 A13 BEECHCRAFT DUKE 60 SERIES MAINTENANCEMANUAL GENERAL - DESCRIPTION AND OPERATION pneumatically operated surface deice boots and electrically heated propellers, heated windshield and heated ventilation The Duke 60 series aircraft utilizes heated pitot, heated ram air inlet scoop. In addition, an alternate static air stall warning, and heated fuel vents for standard ice source backs up the fuselage mounted static air source protection equipment. Optional icing equipment includes: buttons. "END" 30-00-00 Page 1 Nov 2/73 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL AIRFOIL - DESCRIPTION AND OPERATION operation of the system is available with one engine (Figure 1) inoperative. On airplane serials P-3 through P-307, when the surface deice system is operated with the cabin pressure switch in the DUMP position, cabin pressure oscillations will occur. This is caused by a momentary loss of vacuum to the Deice boots on the wing and empennage leading edges are outflow valve while the boots are pressurizinq. This vacuum inflated by the two engine-driven pressure pumps. A loss allows the outflow valve to close and create a small venturi, operated from the pressure pumps, supplies residual cabin pressure. After a small increase, this pressure vacuum for boot hold down at all times except during the is then dumped by the safety valve. inflation mode. Through an electric timer, solenoid-operated control valves cause all the boots to be The cabin pressurization shut off controls should be pulled inflated simultaneously. The timer is controlled by a during this mode to divert cabin pressurizing air overboard three-position switch: SURFACE ONE CYCLE, and and prevent excessive cabin pressure osciliations. Cabin MANUAL with OFF position centered. This switch is ventilation may be obtained by pulling out the cabin air located on the left subpanel. ONE CYCLE and MANUAL control. In this mode pressure oscillations will be small. switch positions are momentary. A gage is provided to indicate system pressure. Momentary engagement of the On airplane serials P-308 and after, the vacuum used by the ONE CYCLE position will cause the boots to inflate for cabin pressurization system is developed in an ejector five to eight seconds, then deflate to the vacuum hold-down installed in the supply line for the deice distribution valve. condition. The MANUAL position will inflate the boots Thus, operation of the deice system does not cause only as long as the switch is held in engagernent;when the fluctuations of cabin pressurization. switch is released, the boots deflate. Leave the deicing system off until 1/2 to 1 inch of ice is accumulated. During For night operation, a wing ice light is provided on the inflation, the deice system pressure gage should register outboard side of the left nacelle. The switch, placarded approximately 15 to 18 psi. Sufficient pressure for proper WING ICE, is on the left subpanel. 30-10-00 Page 1 May 30/75 BEECHCRAFT DUKE60 SERIES MAINTENANCEMANUAL VERTICAL STABILI2ER RH STABILIZER LH STABILIZER VENTURI DISTRIBUTOR VALVE REGULATOR AND Ë EJECTOR (P-308 and after) TO AUTOPILOT - RH WING LH WING MANIFOLD TO AIR PUMP TO AIR PUMP (PRESSURE) (PRESSURE) 60-603-17A Airfoil Deice System Schematic Figure 1 30-10-00 "END" Page 2 May 30/75 BEECHCRAFT DUKE60 SERIES MAINTENANCEMANUAL TROUBLESHOOTING AIRFOlL DElCER SYSTEM The following troubleshooting procedures are based on the assumption that the engine-driven dry air pumps are operational. TROUBLE PROBABLE CAUSE REMARKS 1. Deicer boots do not inflate a. Open circuit breaker. a. Push deicer circuit breaker to (either or both engines reset. operating at a minimum cruise RPM for a period of b. Loose electrical connection b. Tighten or repair as required. eight seconds). or broken wire. c. Time delay relay not c. Replace time delay relay. functioning. d. Control relay not functioning d. Replace control relay. e. Deicer boot punctured. e. Repair as described in this chapter or replace, f. Distributor valve not f. See steps 4 and 5. functioning. g. Piping lines kinked, blocked, g. Inspect and repair or replace or not connected. as required. h. Leak in system. h. Locate and repair. 2. Deicer boots inflate too a. Piping lines kinked, partially a. Inspect and repair or replace slowly (either or both blocked, or not securely as required. engine operating at mini- connected. mum cruise RPM for a period of eight seconds) b. Leak in system. b. Locate and repair. c. Deicer boot punctured. c. Repair as described in this chapter or replace. d. Distributor valve not d. See steps 4 and 5. functioning. 3. Deicer boots deflate too a. Piping lines kinked, partially a. Inspect and repair or replace slowly. blocked, or not securely as required. connected. b. Overboard line from dis- b. Inspect and repair or replace tributor valve partially as required. blocked. c. Distributor valve not c. Overhaul or replace. operating properly. d. Electrical circuit mal- d. See Wiring Diagram Manual, functioning. P/N 60-590001-29. e. Vacuum ejector on distributor e. Remove obstruction or replace. valve plugged. 30-10-00 Page 101 Nov 2/73 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING AIRFOIL DEICER SYSTEM (Cont'd) TROUBLE PROBABLE CAUSE REMARKS NOTE The following items might aid in ascertaining whether or not the distributor valve is function- ing properly, 4. One or more boots do not in- a. Defective wiring in external a. See Wiring Diagram Manual PIN 60- flate -- with pressure gage at circuitor other units. 590001-29 and disconnect plug at dis- normal reading with switch tributor valve. Voltage should be approxi- held in MANUAL or momen- mately 28 VDC between A-C and B-C. tarily placed in SINGLE Make sure C is well grounded. On air- position. plane P-390 and after, voltage should cy- cie at approximately28 VDC between the blue-white wires. Make sure the white wire is well grounded b. Faulty solenoids in distributor b. Measure resistance of solenoids. Reading valve. should be 17.5 ohms + 5% through the receptacle pins A-C and B-C. Ori airplanes P-390 and after reading should be 127 ohms ± 5% between the blue-white wires. Replace the distributor valve if readings do not check. c. Mechanical failure in dis- c. Disconnect lines at the outlet ports of the tributor valve. distributor valve and check valve operation with a gage. If trouble is not foundin the distributor valve, inspect boots and lines for leaks or blockage. d. Piping lines kinked, blocked, d. Inspect and repair or replace as required. or not connected. 5. One or more boots inflate but a. Defective boots. a. Repair as described in this chapter or do not deflate readily -- with replace. pressure gage at normal reading. b. Obstruction of lines. b. Disconnect line from exhaust port of dis- tributor valve and see if line is clear to low pressure area. c. Mechanical failure in dis- c. With line disconnected, see if exhaust port tributor valve. is discharging, if not replace distributor valve. "END" 30-10·00 Page 102 Oct 19/77 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL AIRFOIL DEICER - MAINTENANCE PRACTICES After the acid cleaner has had one minute's contact, wipe dry with a clean cloth. Allow a minimum of one hour dry-time SERVIC/NG before applying cement. At the end of the dry-time, wipe the surface with a clean cloth and inspect the cloth for dirt. If dirt Since the deicer boots and related components operate on is present, reclean with methyl ethyl ketone; if not, cover the clean air supplied from the pressure manifold, little is re- clean sudace with. paper until the cementing operations are quired in the form of servicing the system. The boots should begun. be checked for engine oil after servicing and at the end of each flight, and any oil found should be removed. This can be PREPARATION OF RUBBER SURFACES accomplished by the use of a neutral soap and water solu- tion.Care should be exercised to avoid scrubbing the surface If the deicer boot has a smooth back finish, roughen itslightly of the boot as this will tend to remove the special conductive with sandpaper before beginning the cleaning operation. Wet sudacing. a clean cloth with toluol (22, Chart 207, 91-00-00) and care- fully clean the rough back surface of the boot. Change cloths NOTE frequently to avoid contamination of the cleaned areas. Clean the boot a minimum of two times;if the area stillseems Because the deicer boots are made of soft flex- dirty, reclean the surface in the same manner. ible stock, care must be exercised against drag- ging gasoline hoses over them or resting ladders Application of Adhesive: The drying of the cement is a func- or platforms against the surface of the boots. tion of time and temperature, and the table below should be used as a shop guide when applying the cernent: SURFA CE DE/CER BOOT REMOVAL Temperature - °F Minutes of Dry Time Above 80 30 To loosen or remove an installed deicer boot, use toluol(22, - 60-80 45 Chart 207, 91-00-00) to soften the "adhesion" line where the Below 60 60 boot is joined to the metal surface. The solvent should be applied sparingly with a brush or trigger type oil can with a Do not apply cement under dusty conditions or in high humid- spout. Slowly peel the boot back, allowing the solvent timeto ity (80% relative humidity or above). Prior to cementing, undercut the boot. Exercise care not to injure the boot during mask off the boot area on the metal surfaces, allowing 1/2 to removaL 3/4 inch margin. SURFACE DE/CER BOOT INSTALLATION SPRAY COAT METHOD: PREPARATION OF METAL SURFACES If the EC-1300L adhesive (12, Chart 205, 91-00-00) is applied by spray, the first coat on the back surface of the boot Solvent Cleaning: The metal surface should be completely and on the metal surface should dry a minimum of 30 min- clean to prevent adhesion failure. Using a grease-free cloth utes. The second cross coat on each surface should be dampened in MIL-M-13999 methyl ethyl ketone, (21, Chart allowed to dry a minimum of 30 minutes, preferably one hour. 207, 91-00-00) go over the area to be covered by the boot. Change the cloths frequently, to avoid contaminating a prev¡- BRUSH COAT METHOD: ously cleaned area. Do not contaminate the clean supply of methyl ethyl ketone, by dipping a used cloth into it. Repeat Apply an even brush coat of EC-1300L adhesive (12, Chart the process. Using a clean, damp cloth and a clean dry cloth, 205, 91-00-00) to the back surface of the boot and the metal go over the area again; use the dry cloth (following the damp surface of theairplane.Allow a minimum of 30 minutes to dry. cloth) to wipe the surface dry, rather than letting it air dry. Apply a second coat to each surface in a smooth, even layer. Brushing in one area too long tends to soften the first coat Chemical Gleaning:Follow the solvent cleaning, with a and "rolling" and "balling up" will result. Allow the coating to grease-free cloth wetted with an acid cleaner (41, Chart 207, thoroughlydry a minimumof 30 minutes, preferably one hour 91-00-00). Vigorously scrub surface. before installation. Excess drying time (not to exceed 7 days) is not critical as long as the surfaces are not contaminated. CAUTION INSTALLATION OF THE BOOT Although the acid cleaner is a mild acid solution, Using a chalk line, snap a line centrally located on the leading protective rubber gloves should be worn and edge of the surface. Snap a line, centrally located cordwise, contact with the skin should be avoided. on the cemented side of the boot. 30-10-00 Page 201 Oct 19/77 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL Securely attach hoses to the deicer connection, being careful c. Bostic 1008, a two part cement, (18, Chart 205, to handle the boot section without getting linger marks on the 91-00-00) is used to jointhe stall strip to the deicer boot. Mix adhesive. Using a lint-free cloth, heavily moistened (not drip. the Bostic 1008 in the following manner:30 parts (by weight) ping) with toluol, (22, Chart 207, 91-00-00) reactivate the of the base material (in the "A" package) with 1 part (by surface of the leading edge and boot about 3 inches on either weight) of the accelerator (in the "B" package). side of the chalk line. Position the boot chalk line directly on d. Apply a coat to both the stall strip and the area to the leading edge chalk line and hand roll the boot surface which it will be bonded. Allow to dry 10 to 15 rninutes, then onto the leading edge. Moving along the center line .of the install the strip as shown in the illustration. The cement will leading edge, continue reactivating the adhesive in strips 6 set in about 6 hours. inches wide by 24 inches long. Avoid excessive rubbing of e. When dry, coat the area with AS6B cement (1, the adhesive surface as some of the adhesive may be re- Chart 205, 91-00-00) to replace the conductivity of the boot. moved. Hand roll the joined surfaces to ensure complete contact of the adhesive and elimination of air pockets. If the boot does not follow the chalk line on the leading edge, pull it up immediately with a quick motion and reposition properly. Now complete the installation by activating the adhesive W. S. W. S. surfaces and rolling on the top and lower half of the boot in 122. 93 123. 06 sequence. Finally roll the entire boot (applying pressure) moving in a direction parallel with the inflatable tubes. Use a narrow stitch rotter between tubes to eliminate air entrap- ment. If an air pocket or blister is noted immediately after W. S. W. S. boot installation, the air may be removed by inserting a 130. 55 133. 56 hypodermic needte into the blister and allowing the air to escape. The surfaces may then be pressed down, permitting the surfaces to adhere. NOTE A When removing entrapped air from the boot by use of a needle, be extremely careful not to puncture one of the inflatable tubes. SEALING EDGES Faîr in all around cut edges and trailingedges of the boot with EC-80t sealer (11, Chart 205, 91-00-00) and cover all ex- es24. posed adhesive. Never try to remove excess adhesive closer than 1/4 inch from the boot edge. After all adhesives and Right Wing Left Wing sealing compounds have dried and cured, remove masking tape and clean adjacent areas with solvent. Dimension "A" is 15. 69 Dimension "A" is 15. 69 at Wing Station 122.93 at Wing Station 123.06 STALL STRIP INSTALLATION (RUBBER) and and (Figure 201) 15. 06 at Wing Station 15. 00 at Wing Station 130.55. 133.56. a. The stall strips are 7.62 inches long for the right wing and 10.50.inches longfor the left. The right stallstrip is. installed with its inbo rd end at Wing Station 122.93 and the Stall Strip installation left stall strip is installed with its inboard end at Wing Station Figure 201 123.06. b. Clean boot surface thoroughly; removing all old RESURFAC/NG DE/CER BOOTS cement. Mask off the area where the new strip is to be installed and wipe with MIL-M-13999 methyl ethyl ketone (21, Static electric charges, if allowed to accumulate, would even- Chart 207, 91-00-00). tuallydischarge through the boot to the metal skin beneath, 30-1(M)0 Page 202 Oct 19/77 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL causing static interference with radio equipment and possibly ADJUSTMENT puncturing the rubber. Also, such static changes are a tem- porary fire hazard after each flight.To dissipate static electric charges, a thin coating of conductive cement is applied over Adjustment of the pneumatic pressure system is performed the neoprene of the boot. From timeto time it may be neces- by adjusting the various regulators in a specified sequence. A sary to restore the conductivity to efficiently dissipate such PRESSURIZATION SYSTEM ADJUSTMENT CHART cor- charges. When resurfacing seems advisable, the principal responding to applicable illustrations and a general adjust- factors involved are: ment procedure for each individual regulator are provided in Chapter 36-00-00. a. If the surfacing material has abraded. b. If the surfacing has developed cracks. c. If the conductivity is low. COMPONENT LOCAT/ON The following procedures should be accomplished when re- TIME DELAY RELAY surfacing deicer boots. The time delay relay is located forward of the instrument a. Clean the deicer boots thoroughlywith toluol (22, panel in the upper LH corner of the forward pressure bul- Chart 207, 91-00-00). khead, b. Roughen the entire surface of the boot with fine sandpaper. CONTROL RELAY c. Clean the surface again with a clean lint-free cloth moistened with toluol. The control relay is located forward ofthe instrument panel in d. Apply masking tape beyond the upper and lower the upper LH corner of the forward pressure bulkhead. trailing edges, leaving a 1/4 inch gap of bare metal. e. Brush one coat of Goodrich A568 cement (1, Chart DISTRIBUTOR VALVE 205, 91-00-00) on the boot and allow it to dry at least one hour. Then apply a second coat and allow it to dry at least The distributor valve is located just forward of the access four hours before operating the deicers. The airplane may be opening on the RH side of the aft fuselage. The distributor flown as soon as the cement is dry. valve is accessible, for removal and installation, through the access openings on the lower aft fuselage and the RH side of the aft fuselage. The valve may be removed by disconnecting NOTE the hoses and removing the attaching screws. If A56B cement has aged three months or more, COMPONENT REPLACEMENT it may be necessary to dilute it with toluol to obtain the proper brushing consistency. Mix No maintenance on these components is recommended. thoroughly, approximately five parts cement to Repair or replacement of parts should be made through the one part toluol. Beech Aircraft Corporation overhaul, and exchange program. "END" 30-10-00 Page 203 Oct 19/TT BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL AIR INTAKES - DESCRIPTION AND OPERATION induction system will operate on alternate air. When operat- ing on alternate air above the critical altitude, approximately 8 The possibility of induction system icing is reduced by the to 10 inches of manifold pressure will be lost. non-icing characteristics of fuel injection engines and is backed up by an automatic alternate air source. Should the On airplanes P-3 thru P-266, an optional equiprnent ram air ram air scoop or filter become clogged with ice, a spring- inlet electrothermal lip boot is utilized. The boot is activated loaded door on the firewall will open automatically, and the by a separate switch placarded RAM AIR INLET-OFF. "END" 30-2040 Page 1 Oct 19/77 BEECHCRAFT DUKE 80 SERIES MAINTENANCEMANUAL PITOT AND STATIC - DESCRIPTION AND opening from becoming clogged with ice. The heating OPERATION element is connected into the aircraft electrical system through a 5-ampere circuit breaker. A heating element in the pitot mast prevents the pitot "END" 30-30-00 Page 1 Nov 2/73 BEECHCRAFT. DUKE60 SERIES MAINTENANCE MANUAL WINDOWS AND WINDSHIELD - DESCRIPTION AND position. This opens a relay to direct the current from the OPERATION windshield heat inverter to the avionics provided the L WSHLD switch is on. Power for the operation of both sys- tems cannot be supplied by thÏsinverter at the same time. The pilot's and copilot's windshields are electrically heated to protect against icing. An inverter, also used as a standby for On airplane serials P-459 and after and prior airplane serials the avionics inverter, is installed for the operation of the with Kit No. 60-3008-15 installed, a windshield voltage indi- pilot's windshield heat and is activated by a switch on the cator is provided on the instrument panel which enables the pilot's subpanel marked L WSHLD -OFF. The copilot's wind- operator and/or maintenance to monitor the voltage from the shield is activated by a switch on the pilot's subpanet marked inverter to the windshield heater, R WSHLD - OFF - L WSHLD. Each switch is protected by a 3/4-ampere circuit breaker located on the right subpanel. The In operation a sensing element installed in the windshield 45-ampere circuit breaker that protects the other compo- sends a signal to the temperature control box located on the nents of the system is located between the two LH bus aft side of the forward pressure bulkhead at the base of the isolation circuit breakers in the LH nacelle electrical equip- pilot's windshield, closing a relay permitting current to flow ment compartment. For equipment requiring AC current, a through the heating elements. The control box is factory three position switch marked MN INV- OFF -STBY INV must adjusted between 90°F and 110°F to maintain the desired be placed in the MN INV position. Should a failure occur in mean temperature. The control box operates in an ambient the main inverter, the switch can be placed in the STBY INV temperature range of -65°F to 160°F. "END" 3040410 Page 1 May 12/18 BEECHCRAFT DUKE 60SERIES MAINTENANCEMANUAL TROUBLESHOOTING WINDOWSAND WINDSHIELD DEICER SYSTEM TROUBLE PROBABLE CAUSE REMARKS 1. Windshield fails to heat. a. Circuit breaker on RH a. If circuit breaker persists in subpanel tripped. tripping, check for short and correct. b. Sovitch faulty. b. If no voltage at switch output with correct voltage at switch input, replace switch. c. No input or output voltage c. Check for short and correct. to inverter circuit breaker. d. Sensing element faulty. d. Check for circuit continuity and replace windshield. e. No AC output voltage e. Check control relay, sensing from control relaY. element and control box and replace as required. f. Damaged heater circuit. f. Replace windshield. "END" 30-40-00 Page 101 Nov 2/73 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL WINDOWS AND WINDSHIELD - MAINTENANCE ELECTR/CALLY HEATED WINDSH/ELD VOLTAGE PRACTICES CHECK CAUTION ELECTRICALLY HEA TED WINDSHIELD RES/ST- Ground use of windshield heat is limited to 10 ANCE CHECK minutes. a. Connect a precision voltmeter between the wind- To check for incorrect resistance or the presence of a short or shield heater control switch and the windshield heater. open circuit in the heating elements of the windshield, the b. Start the engines in accordance with the applicable following procedure may be used: Pilot's Operating Manual. c. Set propeller speed at 1200 to 1500 rpm. a. With the windshield deicing system turned OFF, d. Turn the LH windshield switch ON. Note the in- disconnect the leads to the heating element at the lower end crease on the voltmeter (minimum reading of 220 vac). A of each bus. voltmeter reading of less than 220 vac indicates a malfunc- b. Using an ohmmeter, determine the resistance of tion of windshield heat. the heating element by placing the leads of the ohmmeter e. Repeat steps "a" through "d" with the RH wind- across the heating element leads. The resistance should shield heat switch ON. measure 97.0 ± 9.7 ohms. f. Shut-down airplane engines in accordance with c. Reconnect the leads of the heating element. the applicable Pilot's Operating Manual. g. Remove voltmeter from the airplane and restore wiring to the windshield heater circuit. SENSING ELEMENT RES/STANCE CHECK (Figure ELECTRICALLY HEATED WINDSHIELOFUNCTION- 201) AL.TES T After completing the preceeding resistance checks, deter- The resistance of the sensing elementof the windshield minethattheambienttemperatureis90°oriessandperform varies with temperature changes. Figure 201 provides the the following functional check: acceptable range of resistance values at various ambient temperatures. The resistance of the sensing element may be CAUTION checked as follows: Ground use of windshield heat is limited to 10 a. With the windshield deicing system tumed OFF, minutes to prevent damage to the inverter. disconnect the wire connected to one of the terminals of the sensing element. a. Place the windshield DEICE control switch in the L b. Use an ohmmeter to determine the resistance of WSHLD position. the sensing element. b. Determine that the windshield should immediately c. Determine the temperature of the windshield. begin to heat. Presence of heat may be determined by hold- d. Determine if the resistance measured falls within ing the hand against the heated portion of the windshield. the tolerance shown in Figure 201. c. Place the windshield DEICE control switch in the e. Reconnect the windshield sensing element wire. OFF position. 3tMO40 Page 201 May 12/78 BEECHCRAFT DUKE 60 SERIES MAINTENANCEMANUAL 360 340 MAXIMUM LtMIT CU 320 I 300 MINIMUM LIMIT CURVE o w 0280 I 260 240 220 onn 40 0 40 80 120 160 TEMPERATURE ( F) Asoeol-as Sensing Element Resistance Graph Figure 201 3040-00 Page 202 Nov 2/73 "END" BEECHCAAFT · DUKE60 SERIES MAINTENANCE MANUAL PROPELLERS - DESCRIPTION AND OPERATION ELECTRIC PROPELLER DE/CING ELECTRIC PROPELLER DE/C/NG (P-579 and after} (Prior to P-579, F/GURE 1) On airplanes P-579 and after, the electrothermal deice The electric propeller deicer system includes an electrically boots mounted on the propeller blades are electrically heated boot for each propeller blade, brush assemblies, slip heated. Direct current for deice boot heating is supplied rings, an ammeter, a control switch and a circuit breaker. through a system of controls by two brushes which ride on When the switch is turned on, the ammeter registers the dual slip rings mounted on the propeller assembly. amount of current (14 to 18 amps) passing through the system. If a short develops in the system the circuit breaker The brushes used on this installation are of the modular will cut off the power to the timer.The current flows from the block type. The dual slip rings are supplied as an assembly. timer to the brush assembly mounted on the front of the Maintenance of the modular brush blocks and slip ring engine case and is conducted by the brush assembly to the assemblies are covered elsewhere in this chapter under slip rings installed on the starter ring gear. The slip rings respective headings. distribute current to the deicer boots on the propeller blades. Heat from the boots reduces the grip of the ice, which is Current for operation of the deice timingcontrol and the deice then removed by the centrifugal effect of propeller rotation boots is supplied through a switch, located on the pilot's LH and the blast of the airstream. Power to the two heating subpanel, and a 20-ampere circuit breaker. When the switch elements on each blade is cycled by the timer to the is placed in the ON position, the deice timer begiins to run, outboard and inboard heating elements in the following initiating automatic cycling of electrical power to the deice sequence: RH outboard, RH inboard, LH outboard, LH boots. At intervals of approximately90 seconds in duration, inboard. Since each of these phases is 30 seconds in the timer alternately cycles power to the LH then RH duration, the timer makes a complete cycle every two propeller deice boots. Current for operation of the deice minutes. Whenever the timer switches to the next phase of system is indicated by an ammeter located on the RH operation, the ammeter will register a momentary deflection. instrument panel. RH FIREWALL CIRCUIT LH FIREWALL GENERATOR/STARTER -BREAKER GENERATOR/STARTER CONNECTOR SWITCH CONNECTOR AMMETER TIMER ' AMMETER SHUNT DEICER BOOT - i DEICER BOOT so-soa-is Propeller Deicer System Figure 1 "END" 30-60-00 Page 1 A13 Jom 21/82 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL PROPELLERS - TRQUBLESHOOTING of the circuits is open between the slip ring and deicer heater. If the ammeter registers excess current, the power lead is shorted to ground. It may be possible that the excess The ammeter of the deicer system can be used to indicate current has welded the timer contacts in one phase. Under the general nature of most electrical problems. these circumstances, the timer will either feed current to the Consequently, it is recommended that troubleshooting be welded contacts continuously or will not cycle. Ifthe former preceded by the ammeter test as outlined under ELECTRIC is true, the heat test will show two phases heating PROPELLER DEICER in Chapter 5-20-00 of this simultaneously throughout three of the four phases. Unless manual, and the HEAT TEST described in this chapter to the grounded power lead is located and corrected, any new determine which circuits are involved. A reading of two- timer that is installed may suffer the same internal damage thirds the normal amount of current is an indication that one during the first use of the system. TROUBLESHOOTING PROPELLER DEICING SYSTEM (PRIOR TO P-579) TROUBLE PROBABLE CAUSE REMARKS 1. Ammeter shows zero current. a. Circuit breaker tripped. a. Locate and correct short before resetting I (All 4 phases of the 2-minute circuit breaker. 16-second cycle.) b. Switch faulty. b. If no voltage at switch output with voltage at switch input, replace the switch. If voltage is OK at switch output, go to step "d". c. No power from aircraft. c. If no voltage into switch, locate and correct open circuit. d. Ammeter faulty. (If some or all d. Test for voltage up to and out of ammeter. deicers heat with ammeter at If low or zero output but proper input, zero, replace the ammeter.) replace ammeter. If no voltage to ammeter, locate and fix open between switch and ammeter. e. Open c i rcu i t between e. Disconnect harness at timer and check ammeter and timer. voltage pin B (of harness) to ground. If none, locate and correct open circuit. 2. Ammeter shows normal a. Open in wiring between timer a. Refer to HEAT TEST in this chapter to current part of cycle, zero and firewall connector. find deicers not heating and test for current rest of cycle. voltage on that pin of firewall connector. If zero over 2 minutes, locate and fix open in wiring from timer to firewall. b. Open between firewall and b. If voltage to firewall plug, try voltage at deicer lead straps. junctionof deicer lead and slip ring lead. If no voltage, find and correct open in wiring to brush block, open within brush block, or no contact brush to slip rinig. c. No ground circuit, one engine. c. If voltage at deicer leads, locate and fix open from deicer to ground. 3. Ammeter shows normal a. Inner and outer deicers a. Locate and repair incorrect connections. current part of cycle, Iow heating same phase. current rest of cycle. 30-6040 Page 101 A13 Jun 21/82 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING PROPELLER DEICING SYSTEM (Cont'd) (PRIOR TO P-579) TROUBLE PROBABLE CAUSE REMARKS b. Open in deicer or slip ring b. Disconnect deicer straps to check heate assembly. resistance. If resistance is within specifiet limits, locate and fix open in slip rin leads. If not, replace deicer with oper circuit, c. High resistance in circuit with c. If oot in contact of brush to slip rinc low current. (including ground brush), trace wiring tc deicer and to timer to fix partially broker wire, loose or corroded connection. 4. Ammeter shows low current a. Aircraft voltage low. a. Check voltage into switch. over entire cycle. b. Ammeter faulty. b. Refer to step "1d". c. High resistance up to timer. c. Check for partially broken wire, loose o corroded connection in wiring fom aircra1 supply to timer input. 5. Ammeter shows excess a. Ammeter faulty. a. Refer to step "1d". current over entire cycle. b. Ground between ammeter b. Disconnect harness at timer and, witl and timer. ohmmeter, check from pin B (of hamess to ground. If ground is indicated, locati and correct. 6. Ammeter shows normal a. Ground between timer and a. Disconnect leads at brush block ani current part of cycle, excess brush block. check from power leads to ground v. ti current rest of cycle. ohmmeter. If ground is indicated, locati and correct. b. Ground between brush block b. . If no short exists at brush-slip ring and deicers. (Excluding contact, check for ground from slip ring ground brush circuit.) lead to bare prop while flexing slip rini and deicer leads. If a ground is indicatec locate and correct. c. Short between two adjacent c. Check for shorts or low resistanct circuits. between circuits, if any, locate ani correct. d. Timer faulty. d. Test timer as indicated in DEICER TIMEF CHECK in this chapter. 7. Ammeter does not "flick" a. Timer ground open. a. Disconnect harness at timer check witi each 34 seconds. ohmmeter from pin G (of hamess) ti ground. If no circuit, refer to Wirini Diagram Manual (P/N 60-590001-29) ti fix open circuit. 30-60-00 Page 102 Jun 21/82 A1 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING PROPELLER DEICING SYSTEM (Cont'd) (PRIOR TO P-579) TROUBLE PROBABLE CAUSE REMARKS b. Timer contacts are welded b. Test timer as in DEICER TIMER CHECK (caused by shod circuit in in this chapter. If timerdoes not cycle with system). voltage at pin B, replace timer but be sure short causing original problem has been located and corrected. 8. Ammeter flicks between 34 a. Loose connection between a. If trouble occurs over entire cycle, trace second phase periods. aircraft power supply and wiring from power source to timer input to timer input. locate and tighten loose connection. b. Loose or poor connection b. If trouble occurs in part of cycle, find timer to deicers. which deicers are affected and check for rough to dirty slip rings causing brush to "skip". If not this, trace circuits to locate and fix loose or poor connection. (If all deicers on one prop are affected, check the ground circuit.) c. Timer cycles erratically. c. Test timer as indicated in DElCER TIMER CHECK in this chapter. 9. Radio noise or interference a. Brushes "arcing". a. Check brush alignment as outlined under with deicers on, ELECTRICAL PROPELLER DEICER in Chapter 5-20-00 of this manual. Look for rough or dirty slip rings. If this is the cause, clean, machine or replace slip ring assembly. Check for slip ring alignment. b. Loose connection. b. Refer to step 8 above. c. Switch faulty. c. Try jumper wire across switch if radio noise disappears, replace the switch. d. Wiring located less than 8 d, Replace at least 8 inches from input inches from radio equipment wiring to radio equipment. wiring. 10. Cycling sequence not correct. a. Crossed connections. a. Check Wiring Diagram Manual (P/N 60- 590001-29) for improper connections. 11. Rapid brush wear or frequent a. Brush block out of alignment. a. Check brush alignment as outlined under breakage ELECTRIC PROPELLER DEICER in |Chapter 5-20-00 Of this manual. E b. Slip ring wobbles. b. Check slip ring alignment with dial indicator. "END" 30-60-00 Page 103 A13 Jun 21/82 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL TROU B LES HOOTING ELE CTROTHERMAL multimeter be used known to be accurate with ±1% (digital PROPELLER DEICE SYSTEM (P-579 and After) being preferred). Propeller deice ammeter reading outside the shaded area of The test unit (Figure 101) was designed to be used in the meter (14-18 amperes) is an indication that a fault may conjunction with these troubleshooting procedures and can exist in the deice system. It should be noted, however, that be built with standard parts normally found in the shop. Current readings above or below the shaded areas of the Operation and use of the test unit as outlined in the deice ammeter may indicate an output voltage outside the troubleshooting procedure makes it possible to positively normal operating range (28.25 ± .25 vdc) rather than a check the timer in the airplane during system operation. defect in the deice system itself. Excessively high operating voltage could conceivably damage the deice system and The troubleshooting chart which follows allows for an create a multiple fault condition, therefore, operation should orderly flow of checks in a sequence consistent with the not be instituted until the fault or faults have been corrected rñost convenient order of activity for the technician. The Use of battery power alone, during operation of the deice numbers in parenthesis, preceding some steps of the system, should be avoided because the battery output troubleshoot sequence, refer to notes found at the voltage will be lower than normal operating voltage and may bottom of th hart. An electrothermal propeller deice produce ammeter readings below the shaded area of the control scheñ (Figure 102) should be used for reference meter. during system troubleshooting. All resistance and continuity checks .are made with the engines off, battery off and the timer disconnected. CAUTION Resistance values specified in the troubleshooting chart may not be exact, as small variances may occur from one Propeller deice system must not be ground installation to another and will be subject to the accuracy of operated for extended periods of time as the particular resistance measuring instrument being used. damage to the deice boots and pitting of the slip For this reason it is recommended that a sensitive rings may occur. NORMAL RESISTANCE AT PIN LOCATIONS G = 0 OHM (CONTINUITY) F = 1.56 - 2.04 OHMS A/P D = 1.56 - 2.04 OHMS HARNESS B = x (NO CONÏ\NUITY) TO TIMER ,- R1 P1 m --, L1 AND L2 327 LAMP AND PANEL I DUtI -MOUNT LAMP HOLDER G - G D1 TYPICAL CURRENT BLOCKING DIODE I SW1 SINGLE POLE 5 F -- F I POSITION ROTARY I SWITCH OFF I SW1 I SW2 4 POLE DOUBLE I THROW TOGGLE SWITCH D i P1 ANS AMPHENOL I PLUG D1 I R1 ANS AMPHENOL LEFT I RECEPTICAL OFF I J1 AND J2 TO BE COMPATIBLE WITH - J1 J2 RIGHT -- A METER LEADS BEING USED MULTIMETER • e "D L2 SW2 JACKS ALIGATOR CLIP GROUND TO STRUCTURE C99-25018 Electrothermal Propeller Deice Test Unit Figure 101 30-60-00 Page 104 Jun 21/82 gig BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL LH DEICE BOOT RH DEICE BOOl MODULAR MODULAR BRUSH BLOCK BRUSH BLOCK -- SLIP RING SLIP RING - ABC D EFG, AMMETER AMMETER DEICE SWITCH DEICE CB SHUNT 20 AMP 60-251 Propeller Deice Control Schematic Figure 102 30-60-00 Page 105 A13 Jun 21/82 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL TROUBLESHOOTING ELECTROTHERMAL PROPELLER DEICE (P-579 and after) PROPELLER DEICE NOT OPERATING PROPERLY \(1) 2ero resistance at pin *G" (continuity). Poor ground or open Resistance at Pin "F" is circuit from pin "G" to 1¾ to 204 ohms. (tert ground connection. deice) I Resistance at Pin "D" is F No- Resistance is more than - Ya 1.56 to 2.04 ohms. (right 2.04 ohms. deice) I incate and conect short yes circuit between thner and No- IndnNe msistance at pin "B" No (2) 28.25 ± 25 vde at "8. Locate and correct shon I tersninal of brush block. drcuit between tkner and switch and circuit relay and brush IN • ND - 28.25 2 25 vde at pin (4) Rasistance Straugh (6) Locale and correct No- brush blocka not more open between timer and than 0.013 ahms. circuit breaker. Defecdte brush block Yes No- (3) Does lamp L2 iHuminate. Correct alignment of No b brush contacurig sMp 7)!ner brush blockand sNp ring. " ring surfam through 360' Yes or scannon. I Repeat for pin "P (lamp No--" L1). No- Is contact surface of sMp I fing ciaan and ernaath Defecdve tIrner Yes Recondition slip ring assembly Yes Do lamps L1 ätid L2 Is ground connection No-HIuminatafor90s-conds No.. from "C" terminei of each through one 180 brush block cimen and Defective dmer aecond cycle. Canect fmdt. secure. . Yes Yes | Ai! checks are M fauN (5) Defective dolce boat. Is in ammatar and shunt circult. (1) AII resistance and continuity checks are made with the battery switch OFF and (4) Resistance is measumd from face of brush block to terminal and must not exceed the timer disconnected (if using lest una in Figure 101, placing SW 2 in the OFF 0.013 ohms. position will disconnect dmer) (2) VoRage measŒ made with the propeller deice switch ON, circuit (5) Resistance measured through indiviclual deiced boots should not exceed 5.9 breaker in, ared an auxniary power una connected or at least one generatar on the ohm. line. Deice ammeter readings WIIIvary dhoctly with voltage. (3) Reconnect timer (If using test una Figure 101, place SW 2 in run posidan) (6) Check switch and circut breaker for continuity through swach in on poshion. advance tknar by turning automatic propeiter deice switch off then on again tHi lamp L2 illuminates. At no time during this check should both lamps (L1 and L2) be illuminated. "END" 30-60-00 Page 106 Jun 21/82 A13 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL- PROPELLER - MAINTENANCE PRACTICES the blade leading edge. Be sure the lead strap is in the proper position to be clamped to the blade retaining clamp. PROPELLER DE/CER BOOT REMOVAL b. Mask off an area approximately 1/2 inch from the end and each side of the boot, a. Remove the propeller spinner. c. Remove the deice boot and strip any paint in the b. On airplanes P-3 thru P-309, disconnect the masked area from the retaining clamp outboard. On deicer boot leads from the spinner bulkhead. Remove the propeller blades coated with urethane, sand lightly, using clip securing the strap to the spinner bulkhead and the 320 grit sandpaper, to remove all glaze from the urethane clamp securing it to the propeller hub. coating. Clean the area thoroughlywith MIL-M-13999 methyl c. On airplanes P-310 and after, disconnect the ethyl ketone (21, Chart 207, 91-00-00). For final cleaning, deicer boot leads from the clamp on the propeller hub. wipe the solvent off quickly with a clean, dry, lint-free cloth d. Use MIL-M-13999 methyl ethyl ketone (21, Chart to avoid leaving a film. 207, 91-00-00) or toluol(22, Chart 207, 91-00-00) to soften the adhesion line between the boot and the blade, loosen one corner of the boot sufficiently to grasp it with vise grip CAUT/ON pliers or a similar tool. The metal and rubber parts must be thoroughly clean to assure maximum adhesion. CAUT/ON Unless the boot being removed is to be d Moisten a clean cloth with methyl ethyl ketone or scrapped, cushion the jaws of any pulling tool to toluoi and clean the unglazed surface of the deicer boot, prevent damaging the boot surface. changing the cloth frequently to avoid contarnination of the clean area. e. Apply a slow, steady pull on the boot to pull it off the propeller surface while continuing to use the solvent to NOTE soften the adhesive. f. Remove the remaining adhesive from the boot To prevent the edges of the deicer boots from and propeller blade with toluol or methyl ethyl ketone. curling while applying the cement, place masking tape around the edges of the glazed side of the boot. Remove the masking tape PROPELLER DE/CER BOOT /NSTALLAT/ON before installing the boot. (Figure 201) a. Position the deicer boot on the propeller blade so e. Apply one .even brush coat of EC-1300L cement that its center line at the inboard end is adjacent to the split (12, Chart 205, 91-00-00) to the propeller blade. Allow the in the propeller blade clamp and 2 ± 1/16 inch outboard of cement to dry for at least one hour at 40°F or above when the clamp, and the center line at the outboard end falls on the relative humidity is less than 75%, or two hours if the DEICER BOOT 1/2" 2 ± 1/16" 0 1/2" MASKING TAPE 60-251-7 Deicer Boot Installation Figure 201 30-60-00 Page 201 A13 Jun 21/82 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL CAUT/ON I Never use a metal or wooden roller for this purpose, for they would damage the heating elements in the deicer boot. h. Gradually tilting the roller, work the boot carefully --- --- - over each side of the blade contour. Avoid trapping air pockets under the boot. (See Figure 203.) i. Roll outwardly from the center line to the edges of the boot. (See Figure 204.) If excess material at the edges tends to form puckers, work them out smoothly and carefully with the fingers. j. Roll the tapered edges of the boot with a narrow steel stitcher roller. k. Clean the blade with a clean cloth moistened with 60-251-8 toluol or methyl ethyl ketone. Be careful not to let solvent run into the edge of the boot. Center Rolling, l. Apply one even brush coat or EC-801 sealer (11, Figure 202 Chart 205, 91-00-00) behind the lead strap where the boot and the blade meet. humidity is between 75% and 90%. Do not apply the cement if the relative humidity is higher than 90%. f. After allowing sufficient drying time, apply a second brush coat of cement to the propeller and one coat of cement to the unglazed surface of the deicer boot. Do not " apply cement to more than 1/2 inch of the deicer lead strap. Allow the cement to dry. g. Position the deicer boot on the propeller, starting 2 ± 1/16 inch from the blade retaining clamp, making sure the lead strap is in position to clamp to the blade retaining clamp. Moisten the cement lightly with methyl ethyl ketone so.22,_,o or toluol and tack the boot center line to the blade leading edge. If the center line of the boot deviates from the blade Edge Rolling leading edge, pull up with a quick motion and replace Figure 204 properly. Roll firmly along the center line with a rubber roller. (See Figure 202.) NOTE The EC-801 sealer is a two part sealer and must be thoroughly mixed. Mix the EC-801A and EC-801B combination as directed on the containers. m. Apply one even brush coat of EC-801 sealer around the edges of the boot, allowing 1/16 to 1/8 inch overlap on the boot but extended to the masking tape. Remove the masking tape immediately after applying the sealer to obtain a neat border. n. Allow sufficient time for the EC-801 to dry (from 24 to 72 hours, depending on conditions). so-2s" o. Apply satin finish black urethane paint to an area around the boot so that it covers all of the sealer and Side Rolling overlaps the edge of the boot and the blade by a minimum Figure 203 of 1/8 inch. 30-60-00 Page 202 Jun 21/82 A13 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL NOTE NOTE To prevent propeller blade bearing grease from The timer does not reposition itself to start at pin causing the boot to peel back or deteriorate, the C when the system is turned off, but will begin urethane paint should be applied in a uniform its cycling at the same position in which it was coat so that grease cannot get to the boot when last turned off. Cycling will then proceed cement or sealer. in the order of C, D. E, and F as before. p. Allow the urethane paint to dry as specified by the After a voltage reading of 24 volts DC is obtained, hold the manufacturer. voltmeter probe on the pin until the voltage drops to zero q. On airplanes P-3 thru P-309, install the clamp before moving the probe on to the next pin in the sequence securing the lead strap to the propeller blade retaining noted above. After the correctness of the cycling sequence clamps. Connect the lead terminals and install the clip on has been established, turn the deicing system switch OFF the spinner bulkhead. There must be no stack between the at the beginning of one of the "on-time' periods and record terminal and the clip to assure enough slack between the the letter of the pin at which the voltage supply is present to clip and the clamp on the blade to allow propeller feathering. facilitate performance of the following test. r. On airplanes P-310 and after, connect the lead terminals to the ciamp at the propeller hub. DE/CER TIMER CHECK (P-579 AND AF7ER) DE/CER TIMER CHECK (PRIOR TO P-579) Experience in the tield has indicated that often the timer is considered inoperable when the source of the trouble is Experience in the field has indicated that often the timer is elsewhere. For this reason, the following test should be considered defective when the source of the trouble lies performed before the timer is judged to be inoperable. elsewhere. For this reason, the following test should be performed before the timer is removed as defective- a. With the timer harness plug disconnected and the deicer switch in the ON position, check for voltage from pin a. With the wiring harness disconnected at the timer B of the plug to ground. If no voltage is present, the timeris and the deicer switch in the ON position, check the voltage not defective; check the circuit breaker switch or the power from pin B of the harness plug to ground. If no voltage is supply. However, if system voltage is present at pin B, present, the timer is NOT at fault; however, if system check the circuit from the harness to ground with an voltage is present at pin B, check the circuit from hamess ohmmeter. If there is no continuity,the fault is in the ground plug pin G to ground with an ohmmeter. If no circuit is circuit rather than the timer. If the ground circuit is open, the indicated, the fault is in the ground lead rather than the timer will not cycle. timer. Ifground connection is open, the timer step switch will b. After the ground and power circuits have been not change position. Checked, connect a jumper wire between pin B of the timer b. After the ground and power circuits have been receptacle and terminal B of the connector plug, and from checked, connect a jumper wire between pin B of the timer pin G on the timer receptacle to ground. With the deicing receptacle and terminal B of the connector plug and from system switch ON, check the voltage to ground from pin B pin G of the timer receptacle to ground. With the deicing of the timer. The voltmeter should indicate approximately 24 system switch ON, check the voltage to ground from pin B volts dc when the airplane battery supply is being used. of the timer. The voltmeter should indicate approximately24 Next, check the voltage to ground from pins D and F, the volts when the airplane battery supply is being used. Next, points at which the system voltage is impressed in check the DC voltage to ground from pins C, D, E, and F, sequence to cycle power to the LH and RH propeller the points at which the system voltage is impressed in deicers. The presence of 24 vde system voltage should sequence to cycle power to the propeller deicers. Each of alternate at pins D and F for 90 seconds in duration as the the plugs•should read 24 volts in the following sequence. timer cycles. Timing Time Sequence ON Areas of Prop Deicers Heated HEA T TEST (PRIOR TO P-579) Pin C 30 sec. Right engine prop, Outb'd. halves Before this test can be performed, the jumperwire installed Pin D 30 sec. Right engine prop, Inb'd. halves - for the timer test must be removed so that the connector Pin E 30 sec. Left engine prop, Outb d. halves plug can be replaced in the timer receptacle. Two men are Pin F 30 sec. Left engine prop, inb'd. halves required to perform this test, one in the pilot's compartment 30-60-00 Page 203 A13 Jun 21/82 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL to monitor the ammeter while the other checks the deicer a. Pin C of the plug to the outboard terminal of one boots. The man in the pilot's compartment turns the deicer prop boot on the right engine. system switch ON while the man outside feels the deicer b. Pin D of the plug to the inboard terminal of one boots to see if they are heating properly. The man in the prop boot on the right engine, pilot's compartment observes the ammeter for the proper c. Pin E of the plug to the outboard terminal of one readings (14 to 18 amperes) throughoutthe timingsequence. prop boot on the left engine. The ammeter needle should deflect every 30 seconds in d. Pin F of the plug to the inboard terminal of one response to the switching action of the timer. Each time this prop boot on the left engine. occurs, the man in the pilot's compartment must notify the e. Pin G of the plug to ground. man inspecting the propeller deicer boots so that the latter f. Ground terminal of one prop boot on the right can change the position of his hands to check the proper engine to ground. heating sequence of the propeller deicer areas. If any g. Ground terminal of one prop boot on the left irregularities are detected, a continuity check should be engine to ground. performed on the wiring from the timer to the brush block holders and the propeller deicer terminal conriections. CONTINUITY TEST (P-579 AND AFTER) After removing the plug from the timer, use an ohmmeter to check continuityfrom: HEAT TEST (P-579 AND AFTER) a. Pin D of the plug to the terminai of the propeller Remove the jumper wires that were installed for the timer deice boot on the right engine. test and reconnect the timer receptacle. To perform this b. Pin F of the plug to the terminal of the propeller test, two people are required - one person in the flight deice boot on the left engine. compartment to operate the propeller deice switch and c. Pin G of the plug to ground. observe the propeller deice ammeter, the other on the d. Ground terminal of the propetter boot on the right ground checking the deice boots for proper heating. While engine to ground. the person in the flight compartment observes the ammeter e. Ground terminal of the propeller boot on the left for a reading of 14 to 18 amps, the person on the ground engine to ground. Checks for a rise in heat on each propeller deice boot for approximately 90 seconds on each side. If either boot fails to heat, check the circuit between the timer and the BRUSH TO SL/P RING RES/STANCE TEST propeller deice boot for continuity. To check for incorrect resistance or the presence of a short or open circuit at the brush-to-slip ring contact, disconnec1 CAUTION the harness at the timer and check the resistance from each deicer circuit lead (pins C, D, E, and F of the harness plug) While following the instructions of the above to ground with a low range ohmmeter. If the resultan1 "Heat Test" section, rotate the propeller back readings are not 1.55 to 1.78 ohms, disconnect the deicer and forth to prevent arcing between the brushes lead straps to measure heater resistance individually. and slip ring. Individual boot resistance should measure between 4.56 and 5.26 ohms. If the readings in the first check are noi within the accepted limits but those in the second check are the trouble is probably in the brush-to-slip ring area. If the WARNING readings in the second check are also off, the deicel concerned is damaged and must be replaced. Before moving the propeller, ensure that the ignition switc if OFF and that the engine has BRUSH BLOCK RES/STANCE CHECK (PRIOR TC completely cooled, as there is always the P-579) danger of a cylinder firing when the propeller is moved. To check for an open circuit, a short, or high resistance ir the brush block, measure the resistance from the face of the brush to its terminal studs with a low range ohmmeter. If this resistance measures over 0.013 ohms, locate and repair the CONT/NUITY TEST (PRIOR TO P-579) cause of excessive resistance. If the resistance is infinite locate and correct the open circuit or ground, or else replace After removing the plug from the timer, use an ohmmeter to the brush. Check the resistance between the three termina check continuity from: studs. This resistance should not be less than 5 megohms. 30-60-00 Page 204 Jun 21/82 A12 BEECHCRAFT DUKE60 SERÌES MAINTENANCE MANUAL- BRUSH BLOCK RES/STANCE CHECK (P-579 AND AFTER) To determine if an open or short circuit or high resistance is RUBBER present in the brush block, measure the resistance from the . BANDS face of the brush to its terminal stud or receptacle pin with a TO HOLD low-range ohmmeter. The resistance reading should not BRUSH BRUSHES BLOCK IN PLACE exceed 0,013 ohms. If this ohm value is exceeded, locate and repair the problem area. If the resistance reading is - MOUNTING infinite, locate and repair the open circuit or replace the BRACKET brush. Check the resistance between the receptacle pins and the terminal studs. (The resistance reading should be less than 0.5 megohms). PAINT THIS AREA WITH BLACK PAINT a 60-151-2 1-7/16 Marking Location of Brush Block ' INCH Figure 206 - MAX. • a. Loosen both ends of the brush block mounting bracket and remove the complete assembly. b. Tag the lead wires attached to the terminals on the brush block and disconnect them. c. Clean the brush block and mounting bracket. Paint the side of the brush block and the edge of the so-2si.i mounting bracket as shown in Figure 206 with black paint. d. Remove the brush block from the mounting Determining Deicer Brush Wear bracket. Figure 205 5 BRUSH REPLACEMENT (PRIOR TO P-579) 3 2 The propeller deicer brushes should be replaced when a minimum of 1/4 inch of brush material remains. It is good practice, however, to replace the brushes when 3/8 inch of ' the brush material still remains. Brush length may be determined by inserting a piece of safety wire into the holes at the back of the brush block assembly (Figure 205). When 11- 16s ch dirnesnsiomna en leashre eree is eapbprroximsateas NOTE The brush block and mounting bracket should be removed intact so the brush block's exact 1 a. location with respect to the mounting bracket can be marked. This will facilitate alignment of Deicer Brush Block Assembly the brush block during reinstallation. Figure 207 30-60-00 Page 205 A13 Jun 21/82 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL - BRUSH BLOCK SLIP RING ASSEMBLY BRUSH BLOCK WHITE PAINT M2e ASSEMBLY .170 TO .180 INCH ' ROTATIOND ococ . 210 INCH 1/32 MIN. 3/32 MAX. 2° . 210 INCH MOUNTING SCREWS BRUSH GUIDE 6 ·251-5 Deicer Brush Block Installation.170 TO .180 INCH so.2si.4 Figure 209 Deicer Brush Alignment Strip k. Check the amount of brush protrusion from the Figure 208 block. If the brushes protrude less than 9/16 inch, the brush leads should be untwisted to give more length. If this distance is more than 5/8 inch, the lead should be twisted to shorten the effective length until the brushes protrude from e. Disassemble the brush block (Figure 207) by 9/16 to 5/8 inch. The brushes should then be checked for removing the screws attaching the terminal plate to the free sliding action. brush block, then separate the brush block by pulling the 1. Reinstall the brush block assembly on the guide block approximately 1/4 inch toward the terminals to mounting bracket, using the black paint (see step "c") as a disengage the guide pins. guide for correct alignment. f. Mask off and paint a white stripe .170 to .180 inch m. Carefully push the brushes back into the brush wide on the brush block and brush guide. Locate as shown block and secure them in place with a rubber band. (See in Figure 208. The white stripes should be in line with the Figure 206). outer brush and will be used to align the brushes with the n. Using care not to bend or distort the mounting slip ring during reinstallation. brackets. reinstall the brush block and bracket assembly as g. Remove the terminal plate, brushes and springs originally removed from the engine in step "a". Cut the from the brush block. rubber band and rotate the propeller to remove the broken h. Disconnect the wires from the brushes being pieces of rubber band. replaced, noting which terminal they correspond to. i. Solder the wires from the new brushes to the appropriate terminals, holding the "wicking" to 1/8 inch NOTE maximum. j. Install each brush in its correct groove in the The white stripes on the top and bottom of the guide block. Insert new springs into the guide block behind brush block should align with the outer slip ring. the brushes. Taking care not to apply a side load on the if the white stripes do not align with the outer brushes or damage or pinch the brush leads, bring the slip ring it may be necessary to add or remove, support block into position. Install the opposite end of the all or part of the Iaminated shim. Removing springs into their corresponding holes in the support block. shim material will move the brush block out. , Press the two blocks- together until the guide pins in the Each laminate in the shim is approximately .003 support block slip into the holes in the guide block. Install inch. the screws which hold the terminal plate to both blocks. o. Check for proper clearance between the slip rings NOTE and the brush block (see Figure 209). The clearance should be 1/16 ± 1/32 inch with an angle of approximately two When replacing brushes or brush retainer degrees from perpendicular, as measured toward the assemblies, always install new brush springs. direction of slip ring rotation. If not correct, loosen the brush 30-60410 Page 206 Jun 21182 A13 BEECHCRAFT DUKE60 SERIES MAINTENANCE MANUAL block mounting screws and move in the elongated holes to between the star washer and the modular housing and correct the brush block position. install the retaining nut. Ensure that the assembly is square p. To preclude arcing caused by the rough surfaces before tightening the assembly screws. of the new brushes, the engine should be operated for at g. Place the modular brush assembly on th