SID97-3C ADJUSTMENT OF Continental Fuel Injection Handout Page
Contents
1. BRASS or ALUMINUM END FITTINGS STEEL HOSE END FITTINGS Hose Size Fitting Material Torque inch Ibs Hose Size Fitting Material Torque inch Ibs 2 31x24 Hose end fitting 50 80 2 31x24 Steel End Fitting 75 120 Brass Aluminum 3 Hose end fitting 70 105 3 Steel End Fitting 95 140 38x24 Brass Aluminum 38x24 4 Hose end fitting 100 140 4 Steel End Fitting 135 190 4375x20 Brass Aluminum 4375x20 5 Hose end fitting 130 180 5 Steel End Fitting 170 240 500 20 Brass Aluminum 500x20 6 Hose end fitting 150 195 6 Steel End Fitting 215 280 5625x18 Brass Aluminum 5625x18 8 Hose end fitting 270 350 8 Steel End Fitting 470 550 750x16 Brass Aluminum 750x16 10 Hose end fitting 360 430 10 Steel End Fitting 620 745 875x14 Brass Aluminum 875x14 12 Hose end fitting 460 550 12 Steel End Fitting 855 1055 1 063x12 Brass Aluminum 1 063x12 Table 2 Compensation Table For Static Ground Setup Metered Pressure vs RPM 70 F Fuel Temperature Corrected Metered Pressure Static Engine RPM Correction Factor Metered Pressure x Correction Factor Rated RPM 946 NOTE All values are approximate Variations may occur due to engine and installation specific influences Example 1O 520 BB Maximum Rated RPM 2700 Metered Fuel Pressure Limits 14 9 17 2 If maximum static engine RPM 2640 60 RPM use Correction Fact2. 734 946 7777 An alternative procedure would be to use calibrated gauges 1 One 1 calibrated 0 60 PSI gauge graduated 1 PSI increments This gauge will be used for unmetered pressure measurement 2 One 1 calibrated 0 30 PSI gauge graduated in 2 PSI maximum increments This gauge will be used for metered pressure measurements and verification of aircraft fuel flow gauge indications on normally aspirated engines only 3 One 1 calibrated differential gauge 0 30 PSID maximum graduated in 2 PSI maximum increments This gauge will be used for metered pressure measurements and verification of aircraft fuel flow gauge on turbocharged engines only NOTE Pressure gauges must be accurate within 1 Pressure gauges must be checked for accuracy and if necessary calibrated at least once each calendar year Calibrated pressure gauges may be purchased from various suppliers such as Davis Instruments 4701 Mount Hope Drive Baltimore MD 21215 Phone 410 358 3900 or 1 800 368 2516 4 Two 2 P N MS51523 B4 swivel tee These fittings will be used to tee into fuel lines for unmetered and metered pressure reference 5 Hoses of appropriate diameters and sufficient lengths to allow personnel and equipment to be located away from propeller arc and blast area 6 Common hand tools including 7 8 11 16 9 16 1 2 3 8 7 16 11 32 and 5 16 wrenches A 1 4 drive ratchet and soc
3. metered pressures and fuel flows It is important to maintain the balance between these adjustments in order to achieve the specified fuel system parameters CAUTION Exercise caution when adjustments to the aneroid are accomplished The aneroid stem has an extra fine thread and over torqueing the lock nut will damage either the stem or housing threads NOTE It will be necessary to cut and remove the safety wire and manufacturer s seal from the variable orifice adjustment Cut the safety wire as close to the variable orifice stem as possible This will provide a pigtail for the fuel pump through bolts It is not necessary to resafety the aneroid after adjustments have been completed 5 By reviewing the data recorded on the operational test flight form we can determine if the auto leaning schedule is above or below the specified limits at the various pressure altitudes 6 Adjustment of the variable orifice aneroid clockwise will decrease the altitude move horizontally to the left on the chart while counterclockwise adjustments will increase the altitude move horizontally to the right on the chart at a given pressure altitude 7 As example looking at chart number 5 IO 550 B engine at a pressure altitude of 4000 feet the recorded fuel flow was 140 PPH point A The fuel flow specified for this pressure altitude is 142 PPH to 152 PPH The recorded fuel flow of 140 PPH would be correct if we were between 50
4. ISSUED REVISED PAGE REVISION vf best SID97 3 C P O Box 90 Mobile Alabama e 251 438 3411 TABLE 3 Fuel System Adjustment Values cont d IDLE AND FULL POWER FUEL PRESSURES AND FLOWS ENGINE Prop RPM amp Unmetered Metered Fuel Ibs hr Fuel gal hr MAP Pump PSI Nozzle PSI NOTE 3 NOTE 4 NOTE 5 NOTE 6 TSIO 520 D DB 6001 5 5 7 0 2700 29 0 32 0 13 3 15 1 160 170 27 3 29 0 32 5 600 TSIO 520 E 5 5 6 5 s 2700 31 0 34 0 15 6 17 7 175 185 29 8 31 5 34 5 TSIO 520 G 600 5 5 6 5 2700 31 0 34 0 15 8 17 6 181 191 30 8 32 5 35 0 TSIO 520 J JB 600 5 5 6 5 2700 31 0 34 0 16 9 18 7 170 178 29 0 30 3 36 0 600 5 5 7 0 2700 29 0 32 0 15 1 17 4 163 175 27 8 29 8 33 0 600 25 Minimum TSIO 520 K KB TSIO 520 L LB SEE NOTE 1 2700 45 0 55 0 180 190 30 7 32 4 TSIO 520 M R 5 5 6 5 33 0 37 0 169 199 170 186 29 0 31 7 TSIO 520 N NB 5 5 6 5 1 32 0 35 0 169 19 9 170 186 28 9 31 7 TSIO 520 P 5 5 6 5 33 0 37 0 18 4 19 9 180 186 30 7 31 7 YEAR YEAR 0 15 of 40 97 Teledyne Continental Motors Inc siosrs Box 90 Mobile Alabama e 251 438 3411 TABLE 3 Fuel System Adjustment Values cont d IDLE AND FULL POWER FUEL PRESSURES AND FLOWS ENGINE Prop RPM amp Unmetered Metered Fuel Ibs hr Fuel gal hr MAP Pump
5. M N REVISED PAGE NO REVISION IMG DAY ean Mo 36 of 40 97 SID97 3 Box 90 Mobile Alabama 251 438 3411 INLET THROTTLE REEN xix BODY FUEL SNO IDLE MIXTURE IDLE SPEED STOP ADJUSTMENT SCREW CCW ENRICH CW INCREASE FIGURE 9 THROTTLE amp CONTROL ASSEMBLY ALL GTSIO 520 EXCEPT GTSIO 520 C F amp K LOCK NUT FUEL PRESSURE ADJUSTMENT CW INCREASE TURBOCHARGER DISCHARGE PRESSURE REFERENCE CENTER PORT UNMETERED 4 OUTLET PRESSURE FIGURE 10 FUEL PRESSURE REGULATOR FOR TURBOCHARGED ENGINES px vean wor pA AB om 37 of 40 97 SID97 3 G P O Box 90 Mobile Alabama 251 438 3411 PRESSURE VAPOR VENT pun FUEL TANK E rel 5 FUEL INLET ri Vu NI 2 FROM FUEL TV 7 FUEL RETURN FROM TANK m FUEL CONTROL 2 za FUEL PUMP ASSEMBLY gt 1 cx II E FUEL CONTROL 2 MANIFOLD 7 VALVE ASSEMBLY HIE s Dp US I FUEL SCREEN m SS 7 p d E THROTTLEBODY S N IDLE MIXTURE O BYPASS Y ADJUST I 2 IDLE SPEED STOP SCREW li UNMETERED PRESSURE e FIGURE 11 Typical Naturally Aspirated Fuel System Schematic En FROM TURBOCHARGER SV METERED FU
6. REVISION ae 30 of 40 97 Teledyne Continental Motors Inc SID97 3 gt Box 90 Mobile Alabama 251 438 3411 TABLE 11 ALTITUDE FUEL SCHEDULE 550 ENGINE FULL OPEN THROTTLE FULL RICH MIXTURE Pressure Altitude Fuel Flow Metered Fuel Set Altimeter at Pressure PSID 29 92 in Hg 152 160 25 9 27 2 18 2 1000 151 159 25 7 27 1 18 0 2 000 148 156 25 2 26 6 17 5 1 59 j 167 159 53 147 13 129 23 Gasoline 5 87 165 per gallon 70 Altitude Leaning Schedule 550 Full Rich 2700 RPM eo e e Fuel Flow pph N e e e e 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Pressure Altitude X 1000 ft CHART 8 ISSUED REVISED REVISION DAY YEAR WO YEAR x of 0 Box 90 Mobile Alabama e 251 438 3411 TABLE 12 ALTITUDE FUEL SCHEDULE 10 550 D E F L ENGINE FULL OPEN THROTTLE FULL RICH MIXTURE 300 BHP 2700 RPM Pressure Altitude Fuel Flow Fuel Flow Metered Fuel Set Altimeter at Ibs hr gals hr Pressure PSID 29 92 in Hg Mi Max 20 0 Min Max Min Max n 13 s 24d 264 142 5 154 5 24 3 26 3 142 154 24 2 26 2 153 is 14 4 1 4 71 Gasoline 5 87 lbs per gallon 70 F Altitude Leaning Schedule IO 550 D E F L Full Rich 2700 RPM 160 150 140 130 F
7. control to 800 to 1000 RPM NOTE L TSIO 360 and TSIO 520 model engines with a fixed ground adjustable exhaust bypass verify that the wastegate 1s adjusted in accordance with the aircraft manufacturer s instructions Failure to do so can result in an improperly adjusted fuel system and possible engine damage CAUTION After FULL POWER operation turbocharged engines must be operated at 800 to 1000 RPM for a minimum of five 5 minutes to allow engine temperatures to stabilize prior to engine shutdown 16 Compare the recorded IDLE fuel pressure IDLE RPM fuel air mixture rise and full power RPM manifold pressure as applicable unmetered fuel pressure metered fuel pressure and fuel flow indications with the specified values If all recorded values are within specifications proceed to paragraph 24 NOTE Turbocharged engines equipped with fuel pressure regulators should indicate a full power metered pressure and fuel flow five 5 percent higher than specified This is required to insure adequate part throttle fuel flow PAGE NO REVISION Teledyne Continental Motors Inc SID97 3 C Box 90 Mobile Alabama 251 438 3411 17 If any of the recorded readings are not within specifications the fuel system must be completely adjusted ALL READINGS MUST BE TAKEN WITH MIXTURE CONTROL IN THE FULL RICH POSITION Install the engine cowling or cooling shroud during all ground operation NOTE Engine
8. from the engine cowling and propeller arc Torque all connections 5 Loosen and remove the metered fuel supply hose from the manifold valve inlet fitting 6 Install and torque the second MS51523 B4 swivel tee directly to the fuel manifold valve inlet fitting 7 Attach the metered fuel supply hose to the straight end of the tee connector and torque 8 Connect the metered pressure test hose from the Porta Test Unit to this second tee connector and torque If using the alternative procedure connect the 0 30 PSI gauge to the swivel tee using a hose long enough to provide proper clearance from the engine cowling and propeller arc Torque all connections 9 On turbocharged engines connect the Porta Test Manifold Pressure and Upper Deck Pressure hose to the engine following the instructions provided with the Porta Test Unit If using the alternative procedure connect the 0 30 PSId differential gauge pressure fitting to the metered pressure swivel tee using a hose of sufficient length to provide clearance from the aircraft and propeller arc Connect an equal length of hose to the suction side of the gauge and connect the other end to a location to reference turbocharger compressor discharge upper deck pressure See Figure 12 Torque all connections 10 Position the throttle control in the FULL OPEN position and the mixture control to FULL RICH Operate the aircraft boost pump in accordance with the aircraft manufacturer s
9. instructions Following the instructions provided with the Porta Test Unit bleed all air from the test unit and hoses If using the alternative calibrated test gauges loosen the test connections at each gauge to bleed the lines of any air Hold the gauge at or slightly above the height of the fuel system component during the bleeding operation Operate the boost pump only long enough to allow purging of air from the installed test equipment Verify that all fuel lines hoses and fittings are secured and torqued and that no fuel leaks exist before ge WZ a 4 of 40 Teledyne Continental Motors Inc SID97 3 Box 90 Mobile Alabama 251 438 3411 proceeding Insure test hoses have been routed clear of the exhaust system and are supported their entire length to avoid inaccurate gauge readings WARNING MAKE CERTAIN ALL FUEL HAS DRAINED FROM THE INDUCTION SYSTEM PRIOR TO ATTEMPTING ENGINE START FAILURE TO DO SO COULD CAUSE HYDRAULIC LOCK AND SUBSEQUENT ENGINE FAILURE 11 Install the engine cowling or cooling shroud during ground operation 12 Refer to TABLE 3 beginning on page 11 for specific data applicable to your engine Record the applicable IDLE and FULL POWER adjustment points RPM fuel pressure fuel flows manifold pressure and fuel air mixture rise provided in this Service Bulletin and Aircraft Maintenance Manual the operational test form included at the end of this service bulletin The Oper
10. 25 of 40 97 Teledyne Continental Motors Inc SID97 3 Teledyne Technologies Company P O Box 90 Mobile Alabama 251 438 3411 TABLE 6 ALTITUDE FUEL SCHEDULE 10 360 DB ENGINE FULL OPEN THROTTLE FULL RICH MIXTURE BHP 2800 RPM Set Altimeter at Ibs hr gals hr Pressure PSID 29 92 in Hg Min Max Min Max Min Max Gasoline 5 87 Ibs per gallon 70 F IO 360 DB Installed in T 41 ACFT Refer to Cessna SL 81 2 date 28 July 1981 for amplified instructions Altitude Leaning Schedule IO 360 DB 34 120 115 110 105 95 90 85 Fuel Flow 80 75 70 65 60 55 SL 1 2 3 4 5 6 7 8 9 0 H 1 1 14 15 16 Pressure Altitude X 1000 ft CHART 3 YEAR YEAR 26 of 40 97 Teledyne Continental Motors Inc SID97 3 Teledyne Technologies Company P O Box 90 Mobile Alabama 251 438 3411 TABLE 7 ALTITUDE FUEL SCHEDULE 10 360 ES ENGINE FULL OPEN THROTTLE FULL RICH MIXTURE BHP 2800 RPM Pressure Altitude Fuel Flow Fuel Flow Metered Fuel Set Altimeter at Ibs hr gals hr Pressure PSID 29 92 in Hg Min Max Min Max Min Max Gasoline 5 87 lbs per gallon 70 F ALTITUDE LEANING SCHEDULE IO 360 ES 2800 R P M and FULL RICH MIXTURE FULL OPEN THROTTLE Fuel 100 100LL Full Rich 2800 PRM Fuel Temp 72 F Fuel Flow pph 1114 ELE SL 1 2
11. PSI NOTE 3 NOTE 4 NOTE 5 NOTE 6 TSIO 550 E 600 7 0 9 0 2700 32 0 36 0 15 3 16 9 245 255 41 7 43 4 38 5 TSIOL 550 A 600 5 5 6 5 2700 32 5 35 5 17 0 19 0 170 180 29 0 30 7 38 0 TSIOL 550 B 600 60 80 2700 360 400 20 0 22 5 175 185 29 8 31 5 35 0 TSIOL 550 C 600 60 80 2600 37 0 40 0 15 0 16 5 204 216 34 8 36 8 39 5 6 285 TIARA See latest revision of Teledyne Continental Motors Service Bulletin M79 4 NOTE 1 Refer to the aircraft manufacturer s instructions for adjustment procedures NOTE 2 Flight test required to verify fuel flow vs pressure altitude values are within the limits specified See applicable Tables 5 through 12 and Charts 2 through 9 for specified values by engine model NOTE 3 FULL POWER unmetered fuel pump pressure limits are provided for reference only Use metered fuel pressure specifications for adjustments at full power NOTE 4 Use for full power maximum RPM adjustment only other parameters for reference only see note above NOTE 5 May be determined using a calibrated in line flow measuring device Otherwise use metered fuel pressure specifications Refer to Aircraft Manufacturer s Maintenance Manual for method of verifying accuracy of fuel flow indicator NOTE 6 This engine installed in Cirrus SR20 aircraft IO 360 ES 6 B engine has been de rated by Cirrus from original 210 HP at 2800 RPM to 200 HP at 2700 RPM Engine data plat
12. compensating fuel pump Tables 9 through 12 and Auto Leaning Charts 6 through 9 provide fuel flow vs pressure altitude specifications for the IO 550 series engine with altitude compensating fuel pumps Insure the accuracy of aircraft fuel flow gauge and tachometer has been verified These gauges must be accurate or the data recorded during flight test will not be valid Locate the correct table and auto leaning chart for the aircraft and engine On the operational test form provided in this Service Information Directive record all pressure altitudes and corresponding minimum and maximum fuel flows as specified In accordance with the aircraft manufacturer s instructions perform a complete preflight inspection engine start and ground runup Set the aircraft altimeter to 29 92 inches Hg In accordance with the aircraft manufacturer s instructions conduct a normal take off 8 Climb must be accomplished using full throttle FULL RICH mixture and maximum rated full power RPM 9 Using the aircraft fuel flow gauge and altimeter record fuel flows at all pressure altitudes specified 10 Compare the recorded fuel flows with the specified fuel flows for all pressure altitudes If fuel flows are within the minimum and maximum limits at all altitudes no adjustments are required 11 If the fuel flows are not within specified limits at all pressure altitudes the fuel injection system auto leaning schedule requires adjustme
13. driven fuel pump output pressures vary with engine RPM During ground operation FULL POWER RPM may not be obtained Use the Fuel Flow Compensation Table 2 on page 10 to correct the specified metered pressures if FULL POWER RPM cannot be achieved turbocharged engines insure that the manifold pressure is adjusted in accordance with the aircraft manufacturer s instructions Engine driven fuel pumps installed on turbocharged engines are referenced to turbocharger compressor discharge pressure upper deck pressure to achieve FULL POWER engine driven fuel pump pressure WARNING MAKE ALL ADJUSTMENTS WITH THE ENGINE STOPPED AND THE IGNITION AND MASTER SWITCHES IN THE OFF POSITION 18 To adjust the IDLE RPM unmetered pump pressure loosen the lock nut on the low pressure relief valve See Figures 1 through 5 Turning the adjustment clockwise CW will increase pressure and counterclockwise CCW will decrease pressure Operate the engine at 1500 1800 RPM for 15 seconds after each adjustment then retard the throttle to the specified IDLE RPM Repeat this step until pressure is within specified limits NOTE Maximum part throttle full rich fuel flow will be achieved by setting the idle rpm low unmetered fuel pump pressure to the minimum value specified With the idle rpm fuel air mixture properly adjusted step 19 the fuel control metering plate orifices are indexed to the maximum open position 19 With engine operati
14. proceeding with the fuel system adjustments SETUP PROCEDURES WARNING DURING REMOVAL AND INSTALLATION OF FUEL LINES AND HOSES FAILURE TO PROPERLY SUPPORT COMPONENT FITTINGS CAN RESULT IN FITTING AND OR COMPONENT DAMAGE AND LOSS OF SYSTEM PRESSURE REFERENCE THE LATEST REVISION OF TCM SERVICE BULLETIN SIL95 5 NOTE Adjustments to any component of the fuel injection system can affect other system settings Always verify the performance of the entire fuel injection system whenever any fuel injection system component is adjusted 1 Loosen and remove the unmetered fuel supply hose from either the fuel pump outlet fitting or the fuel control unit inlet fitting whichever is most accessible Some engine models have an unmetered fuel pressure connection you can access at the fuel control screen 2 Install and torque the MS51523 B4 swivel tee directly to the fuel pump outlet fitting or to the fuel control inlet fitting as applicable NOTE Some installations may require combinations of different fittings and hoses to facilitate installation of unmetered and metered test equipment connections 3 Attach the unmetered fuel supply hose to the straight end of the tee connector and torque 4 Connect the Unmetered test hose from the Porta Test Unit to the tee fitting and torque If using the alternative procedure connect the 0 60 PSI gauge to the swivel tee using a length of hose which will provide proper clearance
15. with Altitude Compensating fuel pumps See Note 2 page 18 of 38 10 550 600 8 0 10 0 3 SEE NOTE 2 2700 29 2 362 16 5 18 4 146 156 24 9 26 6 Engines with Altitude Compensating fuel pumps See Note 2 page 18 of 38 IO 550 C 600 8 0 10 0 SEE NOTE 2 2700 31 6 37 8 17 6 19 6 152 160 25 9 27 3 Engines with Altitude Compensating fuel pumps See Note 2 page 18 of 38 10 550 D E F 600 80 10 0 L SEE NOTE 2 2700 32 0 360 172 20 0 143 155 24 4 26 4 0 Engines with Altitude eee fuel pumps See Note 2 page 18 of 38 IO 550 G 8 0 10 0 2500 22 0 26 0 14 7 16 0 125 130 21 3 22 1 550 8 10 2700 28 32 19 21 3 150 160 25 6 27 3 10 550 P 600 8 10 i 2700 28 32 19 21 3 150 160 25 6 27 3 10 550 R 600 8 10 2700 28 32 19 21 3 150 160 25 6 27 3 GIO 550 A 600 25 Minimum 1 2267 45 55 175 185 29 8 31 5 TSIO 550 B 600 7 0 9 0 2700 32 0 36 0 15 3 16 9 245 255 41 7 43 4 cs o TSIO 550 C 7 0 9 0 2600 26 0 29 0 127 139 214 224 36 5 38 2 35 5 DAY YEAR DAY YEAR iror Teledyne Conti nental Motors Inc SID97 3 97 Teledyne Technologie any P O Box 90 Mobile Alabama 251 438 3411 TABLE 3 Fuel System Adjustment Values cont d IDLE AND FULL POWER FUEL PRESSURES AND FLOWS ENGINE Prop RPM amp Unmetered Metered Fuel Ibs hr Fuel gal hr MAP Pump PSI Nozzle
16. 0 49 0 6 5 7 5 29 0 33 0 6 5 7 5 34 5 37 5 6 5 7 5 36 0 39 0 6 25 6 75 34 0 38 0 6 25 6 75 28 0 32 0 Metered Nozzle PSI NOTE 4 0 Teledyne Continental Motors Inc P O Box 90 Mobile Alabama 251 438 3411 Fuel Ibs hr NOTE 5 16 7 19 3 135 145 15 8 18 3 15 8 18 3 16 7 19 3 14 9 17 3 130 140 130 140 135 145 125 135 134 145 140 155 135 145 125 135 Fuel gal hr NOTE 6 23 0 24 7 22 1 23 8 22 1 23 8 23 0 24 7 21 3 23 0 22 8 24 7 23 8 26 4 23 0 24 7 21 3 23 0 PAGE NO REVISION 12 of 40 SID97 3 G TABLE 3 Fuel System Adjustment Values cont d IDLE AND FULL POWER FUEL PRESSURES AND FLOWS ENGINE Prop RPM amp Unmetered Metered Fuel Ibs hr Fuel gal hr MAP Pump PSI Nozzle PSI NOTE 3 NOTE 4 NOTE 5 NOTE 6 L TSIO 360 RB 700 25 Minimum SEE NOTE 1 35 0 45 0 140 150 23 3 25 5 TSIO 360 SB 700 6 25 6 75 2600 31 36 15 1 17 8 131 151 22 3 25 7 39 0 O 470 GCI 600 9 0 11 0 2600 23 8 25 3 14 7 16 9 122 129 20 8 22 0 IO 470 C G P R 600 9 0 11 0 2600 24 7 27 7 14 8 17 3 123 130 21 0 22 1 IO 470 D E F H 600 9 0 11 0 L M N S U 2625 25 0 28 0 15 0 17 5 124 131 21 1 22 3 IO 470 J K 600 5 5 7 0 2600 24 7 27 7 14 8 17 3 123 130 21 0 22 1 10 470 V 600 6 5 7 5 10 470 VO
17. 00 feet and 7000 feet To REVISED achieve the specified fuel flow versus pressure altitude we must adjust the variable orifice out Adjustment of the variable orifice aneroid two complete revolutions will move point two thousand feet to the right to 6000 feet 8 After making any adjustment to the variable orifice torque the lock nut to 25 30 inch pounds 9 Perform a complete ground run up and verify that unmetered and metered pressures and fuel flows are within the limits specified in the appropriate table for the pressure altitude If these parameters are not within the limits specified make adjustments in accordance with PART C to achieve the specified values NOTE The adjustable orifice tapered needle may be damaged if forced against its seat The adjustment should move freely Do not continue adjustments if rotational resistance increases suddenly 10 Once the adjustments are completed remove the test equipment in accordance with part D Post Setup Procedures 11 Perform a flight test in accordance with part F Flight Test Naturally Aspirated engines with Auto Lean 12 Repeat these procedures until the engine s fuel injection system meets all published specifications PAGE NO REVISION ff CONTINENTAL CONTINENT Q 5 9 of 40 Teledyne Continental Motors Inc 5097 3 C P O Box 90 Mobile Alabama e 251 438 3411 TABLE 1 Torque Specifications for Hose End Fittings
18. 3 4 5 6 7 8 9 10 1 12 13 14 15 16 17 Pressure Altitude 1000 ft CHART 4 iSSUED __ REVISED __ PAGE NO REVISION_ DAY YEAR DAY YEAR 29 Teledyne Continental Motors Inc SID97 3 gt 97 Teledyne Technologies Company P O Box 90 Mobile Alabama 251 438 3411 105 TABLE 8 ALTITUDE FUEL SCHEDULE 10 360 ES ENGINE FULL OPEN THROTTLE FULL RICH MIXTURE BHP 2700 RPM Set Altimeter at Ibs hr gals hr Pressure PSID 29 92 in Hg Min Max Min Max Min Max Gasoline 5 87 Ibs per gallon 70 F ALTITUDE LEANING SCHEDULE 10 360 ES 6 AT 2700 RPM FULL RICH MIXTURE amp FULL OPEN THROTTLE 100 95 90 85 80 Fuel Flow PPH 75 70 65 60 S L Recommended Setup for Cirrus SR20 Installation Fuel 100 100LL 2700 rpm WOT Full Rich 2700 RPM Fuel Temp 72 F ES er re 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Pressure Altitude 1000 ft amsn YEAR NO AY YEAR 5 PAGE REVISION QU 28 of 40 T lechine continenter Motors Ine Sens Box 90 Mob
19. 600 6 5 7 5 GIO 470 A 450 9 0 11 0 TSIO 470 B C D 5 5 6 0 2600 28 0 30 0 15 0 17 0 145 155 24 7 26 4 35 0 10 520 A J 600 9 0 11 0 D 10 520 B 600 90 11 0 YEAR YEAR D u7 13 of 40 97 Teledyne Continental Motore Ines pen C P O Box 90 Mobile Alabama 251 438 3411 TABLE 3 Fuel System Adjustment Values cont d IDLE AND FULL POWER FUEL PRESSURES AND FLOWS ENGINE Prop RPM amp Unmetered Metered Fuel Ibs hr Fuel gal hr MAP Pump PSI Nozzle PSI NOTE 3 NOTE 4 NOTE 5 NOTE 6 10 520 D F K L 600 9 0 11 0 2850 30 0 33 0 17 0 19 4 143 153 24 4 26 1 520 600 9 0 11 0 2850 29 0 32 0 16 1 18 3 143 153 24 4 26 1 10 520 M MB 600 6 0 7 0 2700 290 320 167 193 1362146 232 249 10 520 P 600 6 0 7 0 LIO 520 P 2500 262 269 143 162 130 140 22422 0 16 160 165 273 281 TSIO 520 AE 600 7 5 8 5 L TSIO 520 AE 2400 34 5 38 0 15 2 16 5 32 5 TSIO 520 AF 600 5 5 6 5 2700 35 0 39 0 184 19 9 180 186 30 7 31 7 35 5 TSIO 520 B 600 5 5 7 0 2700 29 0 32 0 16 0 17 9 165 175 28 1 29 8 32 0 TSIO 520 BE 600 5 5 7 0 2600 25 0 28 0 12 7 14 1 214 224 36 5 382 38 0 0 TSIO 520 C H 600 55 70 2700 290 320 153 172 160 170 27 3 29 0 32 5 TSIO 520 CE 600 5 5 6 5 2700 33 0 360 162 180 215 225 36 6 38 3 37 0
20. AND SEVERE ENGINE DAMAGE 3 Remove the engine cowling in accordance with the aircraft manufacturer s instructions 4 Insure that all fuel system components are of the correct part number and are installed properly Correct any discrepancies noted 5 Remove inspect clean and reinstall the aircraft and engine fuel screens in accordance with the aircraft manufacturer s instructions 6 Inspect the aircraft induction air filter and alternate air system for condition operation and cleanliness Repair or replace component that is not airworthy in accordance with the aircraft manufacturer s instructions 7 Inspect the aircraft vapor return system for proper operation in accordance with the aircraft manufacturer s instructions Correct any discrepancies noted 8 Insure the fuel manifold valve vent and fuel pump drain lines are properly installed open and free of obstruction Correct any discrepancies noted 9 Inspect all engine control rod ends for wear freedom of movement proper installation and security in accordance with the aircraft manufacturer s instructions discrepancies noted Correct any 10 Inspect the throttle and control assembly link rods where used for correct installation security and wear at the attach points Correct any discrepancies noted 11 Insure all engine controls operate freely throughout their full range of travel and are properly adjusted in accordance with the aircraft manufa
21. EL PRESSURE THROTTLE UPPER DECK PRESSUR AND CONTROL UPPER DEGK PRESSURE FUEL PRESSURE REGULATOR FUEL MANIFOLD VALVE ASSEMBLY INLET FUEL FROM ACFT UPPER DECK PRESSURE FUEL INJECTOR VAPOR RETURN TURBOCHARGER DISCHARGE UPPER DECK PRESSURE METERED FUEL PRESSURE FUEL PUMP NOZZLE PRESSURE UNMETERED FUEL PRESSURE FIGURE 12 Typical Turbo Charged Fuel System Schematic With Regulator ISSUED __ REVISED lt gt PAGE NO REVISION_ SID97 3 YEAR Wo 97 Teledyne Continental Motors Inc Teledyne Technologies Company Kab m Box 90 Mobile Alabama e 251 438 3411 METERED FUEL FROM TURBOCHARGER PRESSURE GAUGE UPPER DECK PRESSURE METERED FUEL PRESSURE FUEL NOZZLE P gt UNMETERED FUEL PRESSURE UNMETERED FUEL PRESSURE GAUGE UNMETERED FUEL PRESSURE FIGURE 13 TURBOCHARGED ENGINE FUEL SYSTEMS WITH FUEL PUMP HAVING INTEGRAL MIXTURE CONTROL METERED FUEL PRESSURE GAUGE METERED FUEL PRESSURE iL FUEL NOZZLE P gt FROM AIRCRAFT FUEL SUPPLY UNMETERED FUEL PRESSURE GAUGE UNMETERED FUEL PRESSURE FIGURE 14 Naturally Aspirated Engine Fuel System With Fuel Pump Having Integral Mixture Control sue J YEAR WO DAY YEAR Dag ora 97 Teledyne Continental Motors Inc SID97 3 Teledyne Technologies Company PRESSURE REFERENCE ANEROID ADJ
22. PSI Nozzle PSI NOTE 3 NOTE 4 NOTE 5 NOTE 6 TSIO 520 T 600 5 5 6 5 2700 33 0 37 0 16 3 18 1 185 195 31 5 33 2 39 5 600 TSIO 520 UB 5 5 6 5 2700 33 0 37 0 144 16 0 195 205 33 2 34 9 36 0 TSIO 520 VB 600 5 6 6 5 2700 36 0 39 5 16 9 18 7 200 210 34 1 35 8 40 5 TSIO 520 WB 600 25 Minimum SEE NOTE 1 2700 45 0 55 0 190 200 324 34 1 39 5 GTSIO 520 C 525 40 70 2400 30 0 33 0 16 5 17 5 215 225 36 6 38 3 34 5 GTSIO 520 D H 467 4 0 7 0 2267 30 5 35 0 15 7 17 3 250 260 42 6 44 3 39 5 GTSIO 520 F K 600 6 75 7 25 SEE NOTE 1 2267 38 0 41 0 174 18 8 300 310 51 1 52 8 44 5 GTSIO 520 L 467 40 70 2234 29 5 35 0 16 4 17 9 255 265 43 4 45 1 39 0 GTSIO 520 M 467 4 0 7 0 2 2234 29 5 35 0 16 4 17 9 255 265 43 4 45 1 40 0 GTSIO 520 N 467 4 0 7 0 SEE NOTE 1 2234 29 5 35 0 16 4 17 9 255 265 43 4 45 1 39 0 DAY YEAR DAY YEAR YEAR MO AR NO WAP 16 of 40 97 Teledyne Continental Motors Inc sips7 3 P O Box 90 Mobile Alabama e 251 438 3411 TABLE 3 Fuel System Adjustment Values cont d IDLE AND FULL POWER FUEL PRESSURES AND FLOWS ENGINE Prop RPM amp Unmetered Metered Fuel Ibs hr Fuel gal hr MAP Pump PSI Nozzle PSI NOTE 3 NOTE 4 NOTE 5 NOTE 6 10 550 A 8 0 10 0 2700 32 0 36 0 17 7 20 0 142 150 24 2 25 6 Engines
23. RGE DISCHARGE PRESSURE REFERENCE LOW PRESSURE RELIEF VALVE CW INCREASE J FUEL OUTLET DRAIN UNMETERED PRESSURE FIGURE 4 ANEROID EQUIPPED FUEL PUMP TURBOCHARGED ENGINE DAY YEAR DAY YEAR EX C 97 Teledyne Continental SID97 3 Box 90 Mobile Alabama 251 438 3411 VAPOR VAPOR Ip RETURN FUEL INLET TURBOCHARGE DISCHARGE PRESSURE nama REFERENCE ANEROID ADJUSTMENT LOW zm CCW INCREASE PRESSURE J FULL RELIEF VALVE FUEL OUTLET IDLE CUTOFF RICH CW UNMETERED PRESSURE FIGURE 5 ANEROID amp MIXTURE CONTROL EQUIPPED FUEL PUMP TURBOCHARGED ENGINE IDLE MIXTURE ADJUSTMENT CW LEAN CCW ENRICH IDLE SPEED STOP SCREW CW INCREASE CCW DECREASE FUEL OUTLET FUEL INLET METERED PRESSURE UNMETERED PRESSURE FIGURE 6 THROTTLE amp METERING ASSEMBLY DAY A om 35 of 40 97 SID97 3 Box 90 Mobile Alabama 251 438 3411 INLET SCREEN FUEL INLET FITTING UNMETERED PRESSURE THROTTLE LEVER o 9 Cr LEVER FUEL OUTLET METERED FUEL RETURN PRESSURE TO FUEL PUMP FIGURE 7 THROTTLE amp CONTROL ASSEMBLY FRONT VIEW EXCEPT GTSIO 520 D F H K L M N IDLE SPEED STOP SCREW CW INCREASE IDLE MIXTURE ADJUSTMENT CW ENRICH FIGURE 8 THROTTLE amp CONTROL ASSEMBLY SIDE VIEW EXCEPT GTSIO 520 D F H K L
24. TELEDYNE CONTINENTAL AIRCRAFT ENGINE SERVICE INFORMATION DIRECTIVE Compliance Will Enhance Safety Maintenance or Economy Of Operation SID97 3C Technical Portions FAA APPROVED SUPERSEDES 73 22 M89 10 M92 17 SID98 10A SID97 3 SID97 3A and SID97 3B SUBJECT PROCEDURES AND SPECIFICATIONS FOR ADJUSTMENT OF TELEDYNE CONTINENTAL MOTORS TCM CONTINUOUS FLOW FUEL INJECTION SYSTEMS PURPOSE Provide procedures and specifications for the adjustment of Teledyne Continental Motors fuel injection systems COMPLIANCE At Engine Installation 100 hour Annual Inspection fuel system component replacement or as required if operation is not within specifications MODELS AFFECTED All TCM continuous flow fuel injected engine models except L TSIO 360 RB TSIO 520 L LB WB GTSIO 520 F K N and GIO 550 A engine models WARNING THE PROCEDURES AND VALUES PROVIDED IN THIS SERVICE BULLETIN APPLY TO TCM FUEL INJECTED ENGINES THAT HAVE NOT BEEN MODIFIED FROM THEIR ORIGINAL TYPE DESIGN REFER TO SUPPLEMENTAL TYPE CERTIFICATE STC HOLDER INFORMATION AND INSTRUCTIONS FOR AIRCRAFT AND ENGINES THAT HAVE BEEN MODIFIED FROM THEIR ORIGINAL TYPE DESIGN GENERAL INFORMATION Fuel injection system components manufactured by TCM are adjusted and calibrated to meet engineering specifications This insures operation within those specifications throughout the full range of operation Fuel injection system components installed on factory new an
25. USTMENT LOW CCW INCREASE PEESSUBE IDLE CUTOFF FULL RELIEF VALVE FUEL OUTLET RICH CW INCREASE UNMETERED PRESSURE FIGURE 15 ANEROID amp MIXTURE CONTROL EQUIPPED FUEL PUMP YEAR mo AY YEAR D IEEE TREE 40 of 40 97 Teledyne continente Motore Ine pens C Box 90 Mobile Alabama 251 438 3411 Date 0000 Location Elevation Field Hg Aircraft Make amp Model Aircraft Registration Engine Model Engine Position Right Front Engine Serial Number Engine Total Time New Overhaul Fuel System Adjustment Record engine specifications and actual gauge indications seve acta ncn nes 5 E E T Pressure Altitude Set altimeter to 29 92 Hg Remarks Idle RPM mixture rise magneto drop etc Signature
26. a Level 10 360 8 6 7 0 9 0 SEE NOTE 2 amp 6 19 0 22 0 13 3 14 6 gt 16 0 16 6 1 500 Press Alt Q Engines with Altitude Compensating fuel pumps See Note 2 page 18 of 38 10 360 K KB 600 70 90 2600 21 0 24 0 14 3 16 3 93 5 97 5 15 9 16 6 TSIO 360 A AB 6 5 7 5 27 2 312 15 8 16 7 119 124 20 1 21 0 TSIO 360 B BB 6 5 7 5 2800 272 312 15 8 16 7 115 124 20 1 21 0 32 2 TSIO 360 C 6 5 7 5 i i 2800 34 0 37 0 16 7 19 3 135 145 23 0 24 7 37 0 ISSUED REVISED CN PAGE REVISION pay YEAR WO DAY YEAR XP Teledyne Continental Motors Inc SID97 3 G 97 Teledyne Technologies Company P O Box 90 Mobile Alabama 251 438 3411 TABLE 3 Fuel System Adjustment Values cont d IDLE AND FULL POWER FUEL PRESSURES AND FLOWS ENGINE TSIO 360 D DB 600 2800 36 0 TSIO 360 E EB 700 L TSIO 360 E 2575 EB 40 0 TSIO 360 F FB 700 2575 41 0 TSIO 360 G GB 700 2700 40 0 TSIO 360 H HB 600 2800 34 5 TSIO 360 JB 600 2800 37 0 700 2800 40 0 TSIO 360 LB 700 2700 40 0 TSIO 360 MB 700 ISSUED REVISED DAY YEAR DAY YEAR YEAR Y TSIO 360 KB L TSIO 360 KB 2700 36 0 Prop RPM amp Unmetered MAP Pump PSI NOTE 3 6 5 7 5 34 0 37 0 6 25 6 75 43 0 46 0 6 25 6 75 40 0 43 0 6 25 6 75 45
27. ational Test Form may be reproduced for use in recording adjustments and test indications NOTE To insure optimum cooling during FULL POWER operations the FULL POWER fuel flow should be set to the maximum specification limit WARNING BEFORE STARTING THE ENGINE INSURE THAT THE AIRCRAFT WHEELS ARE CHOCKED AND BRAKES ARE SET 13 Prepare the aircraft for ground run and start the engine in accordance with the aircraft manufacturer s instructions Advance the throttle to 1500 to 1800 RPM While monitoring all engine gauges operate the engine this speed until the engine temperatures and pressures have stabilized in the operational range Use the operational test form to record the gauge indications NOTE Test gauge readings must be taken with the gauges held at the same height above the ground as the fuel system component it is attached to 14 With the mixture control in the FULL RICH position reduce the throttle to the specified IDLE RPM Record the unmetered pressure indicated on the gauge Slowly move the mixture control toward the IDLE CUT OFF position and record the maximum RPM rise Return the mixture control to FULL RICH 15 Monitoring all engine gauges slowly advance the throttle control to full rated power for the engine and allow the engine to stabilize for 15 seconds Record all engine and test gauge indications DO NOT ALLOW ENGINE TEMPERATURES TO EXCEED 420 F CHT AND 210 F OIL TEMP Retard throttle
28. cturer s instructions 12 Lubricate all control rod ends and fuel system components in accordance with the latest revision of TCM Service Bulletin SB95 2 and the Aircraft Maintenance Manual WARNING FAILURE TO CORRECTLY INSTALL AND MAINTAIN ENGINE CONTROLS CAN RESULT IN LOSS OF SYSTEM CONTROL AND SUBSEQUENT LOSS OF ENGINE POWER 13 Locate the IDLE speed stop screw on the throttlebody and turn it counter clockwise two complete turns See Figures 6 through 9 During fuel system adjustment IDLE RPM will be controlled manually using the cockpit throttle control 14 Inspect the exhaust and induction systems for proper installation security and leaks Correct any discrepancies noted 15 Inspect all lines hoses and wire bundles for chafing loose connections leaks and stains Correct any discrepancies noted Turbocharged engine models incorporating a fuel pressure regulator must have the regulator deactivated during initial fuel system adjustment To deactivate the fuel pressure regulator loosen and remove the fuel line or hose from the center port fitting at the pressure regulator Refer to Figure 10 Install and torque to the specified value a cap on the center port fitting Install and PAGE NO REVISION Teledyne Continental Motors Inc SID97 3 C Box 90 Mobile Alabama 251 438 3411 torque to the value specified a plug onto the removed line Pressure test these areas for fuel leaks prior to
29. d rebuilt engines are further adjusted to meet design specifications during operation in the production engine test facility These tests and adjustments are carried out in an environment of controlled fuel supply pressures and calibrated test equipment When engines are installed in aircraft they are subjected to a different induction system fuel supply system and operating environment These sue YEAR YEAR differences require checking and adjusting the fuel injection system to meet operational specifications before flight Aircraft and engines that have been modified from their original type design must have the fuel injection system maintained in accordance with the Supplemental Type Certificate Holder s FAA approved instructions Operational verification of the engine fuel system is required any time one of the following circumstances occurs 1 at engine installation 2 during 100 hour and annual inspections 3 whenever a fuel system component is replaced or adjusted 4 when changes occur in the operating environment CAUTION Engine performance service life and reliability will be compromised if the engine s fuel injection system is neglected The following adjustment procedures are presented in a sequential format that must be followed to insure proper fuel system adjustment Reference the applicable Aircraft Maintenance Manual for detailed fuel system adj
30. de IO240B Idle Unmetered Pressure Altitude Plot 1000 RPM 8 2 o O 74 2 2 7 2 6 rs ey a O 500 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 8500 9000 9500 10000 Pressure Altitude ft Adjust idle mixture screw to set RPM rise during mixture check at 1000 rpm to 20 50 rpm DAY YEAR DAY YEAR 20 20 of 40 Teledyne Continental Motors Inc 97 Teledyne Technologies Company Box 90 Mobile Alabama 251 438 3411 CHART 1 Con t Full Throttle Step 2 Adjust the aneroid rod to obtain the metered nozzle pressure 0 3 psi at pressure altitude and RPM per the chart above Turn clockwise to decrease pressure and counter clockwise to increase pressure After adjustment recheck idle unmetered pressure setting using the instructions in step 1 of this chart Reference Figure 15 Full throttle ground fuel pump set up Full Rich mixture setting 13 5 EIE 2450 9 5 2350 rpm 2250 Metered Nozzle Pressure psi 9 0 2150 rpm 8 5 2050 rpm 1950 rpm 8 0 7 5 7 0 1000 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 Pressure Altitude ft NOTE At conclusion of setup
31. de Compensating Pump and Fuel Scavenge Manifold Valve This test is for reference only actual RPM may vary due to the fixed pitch prop NOTE Pressure altitude must be used for the table and chart below when determining fuel system set up values To determine pressure altitude prior to take off set your altimeter to 29 92 in hg and the altimeter will indicate your pressure altitude 10 240 B Engine with Aneroid Fuel Pump and Fuel Scavenge Manifold Valve Full Throttle Full Rich Mixture at 2450 RPM Pressure Altitude Set Altimeter at Metered Fuel Pressure 29 92 in Hg Fuel Flow Ibs hr Fuel Flow gals hr PSID Minimum 263 287 7 9 7 525 60 1 000 N Maximum 96 90 95 Z 797 80 159 69 66 64 63 28 24 19 eet Maximum N 6000 369 434 13 5 33 9 405 64 ILI 63 pop x 2 o a wo CHART 2A Typical 10240 with Bypass Fuel System fuel flow leaning curve during flight test IO240B Altitude Leaning Schedule 2450 RPM full rich mixture O Oo a O Fuel Flow O C2 eo N 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 12000 13000 14000 15000 Pressure Altitude ft MO DAYS vee QV
32. e reflects original TC and PC data of 210 HP at 2800 RPM Refer to Cirrus SR20 Maintenance Manual and Pilots Operating Handbook YEAR NO YEAR D 0 18 of 40 97 Teledyne Continental Motors Ine s73 P O Box 90 Mobile Alabama 251 438 3411 TABLE 4 240 Without Altitude Compensating Aneroid Equipped Pump FULL THROTTLE STATIC RPM METERED FUEL PRESSURE SPECIFICATIONS FULL THROTTLE NOMINAL ALLOWED STATIC METERED VARIATION ENGINE RPM FUEL PRESSURE 1800 RPM 1850 RPM 1900 RPM 1950 RPM 2000 RPM 2050 RPM 2100 RPM 2150 RPM 2200 RPM 2250 RPM 2300 RPM 2350 RPM 2400 RPM REVISED O ffESNTNENTADA _ PAGE REVISION lt TERR DAY YEAR Mo CAN 19 of 40 97 Teledyne Continental Motors s093 P O Box 90 Mobile Alabama 251 438 3411 CHART 1 10 240 B with Altitude Compensating Aneroid Equipped Fuel Pump and Standard Fuel Manifold Valve Idle Step 1 Set Unmetered pump pressure and RPM rise at 1000 25 rpm to 9 6 0 2 psi sea level standard day If pressure altitude is different from sea level determine required unmetered pressure setting from the plot below Reference Figure 15 NOTE Pressure altitude must be used for the figures below when determining fuel system set up values To determine pressure altitude set your altimeter to 29 92 in hg and the altimeter will indicate your pressure altitu
33. egulator the full power metered fuel pressure and fuel flow must be adjusted to five 5 percent higher than the maximum specified limit WAS Pd en 6 of 40 Teledyne Continental Motors Inc SID97 3 Box 90 Mobile Alabama 251 438 3411 22 23 24 a Loosen the aneroid adjustment screw lock nut See Figures 4 and 5 b Turn the aneroid adjustment screw counterclockwise to increase metered fuel pressure and clockwise to decrease metered fuel pressure c After final adjustment is accomplished torque lock nut to 25 30 inch pounds DO NOT EXCEED LOCK NUT TORQUE LIMITS OVER TORQUING OF LOCK NUT WILL RESULT IN DAMAGE TO ANEROID HOUSING THREADS AND SUBSEQUENT LOSS OF ADJUSTMENT For engines equipped with a fuel pressure regulator the full power metered fuel pressure and fuel flow flow must now be set to the specified limit by adjustment of the regulator as follows See Figure 10 Reconnect the regulator and torque all connections to the specified value Loosen the lock nut on the regulator adjustment Turn the regulator adjusting screw clockwise to increase metered fuel pressure fuel flow counterclockwise to decrease metered fuel pressure and fuel flow After final adjustment is completed torque the lock nut to the specified value When full power metered fuel pressure has been adjusted to the specified values recheck a IDLE RPM b unmetered fuel pressure c fuel a
34. ile Alabama 251 438 3411 TABLE 9 ALTITUDE FUEL SCHEDULE 550 A ENGINE IO m x D m rs an x E 5 x an Z m Qu D gt x ae ea e 5 en Metered Fuel Fuel Flow Fuel Flow Pressure Altitude Set Altimeter at Pressure PSID gals hr 29 92 in Hg 142 150 242 25 6 16 5 Gasoline 5 87 Ibs per gallon 70 F Altitude Leaning Schedule Full Rich 2700 RPM 11771 II III M RP mmm en N MO 4 Jeng 90 8 9 10 11 12 13 14 7 6 Pressure Altitude X 1000 ft 5 CHART 6 PAGE NO REVISION REVISED 9 8 2 5 c 9 5 c 0 9 9 F Teledyne Technologies Company P O Box 90 Mobile Alabama 251 438 3411 TABLE 10 ALTITUDE FUEL SCHEDULE 550 ENGINE FULL OPEN THROTTLE FULL RICH MIXTURE Pressure Altitude Fuel Flow Fuel Flow Metered Fuel Set Altimeter at Ibs hr gals hr Pressure PSID 29 92 in Hg 1 Gasoline 5 87 Ibs per gallon 70 F Altitude Leaning Schedule IO 550 B Full Rich 2700 RPM 160 150 140 130 Fuel Flow pph 120 110 100 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Pressure Altitude X 1000 ft CHART 7 ISSUED REVISED ES PAGE NO
35. ir mixture If any values are not within specified limits repeat the adjustment procedures With the fuel system set to the specified metered fuel pressure set the IDLE RPM to the aircraft manufacturer s specified value by turning the Idle Speed Stop screw clockwise to increase RPM or counterclockwise to decrease RPM See Figures 6 8 and 9 POST SETUP PROCEDURES Insure that the master switch ignition switch and fuel selector are in the OFF position Remove the engine cowling or cooling shroud in accordance with the aircraft manufacturer s instructions remove all test gauges fitings and hoses that were installed for fuel system setup b reconnect all fuel hoses to their original locations c support and torque all fittings to the specified value see TABLE l Perform a complete fuel system leak check in accordance with the aircraft manufacturer s instructions Correct any discrepancies noted Install engine cowling in accordance with the aircraft manufacturer s instructions Perform a complete operational ground run up and verify that all fuel system performance specifications are achieved FLIGHT TEST Except naturally aspirated engines with altitude compensating fuel pump Refer to the aircraft manufacturer s or Supplemental Type Certificate STC holder s POH AFM for specific operational information A flight test is required whenever an adjustment is made that may affect engine operational characteri
36. kets universal swivel extension and a 5 32 allen wrench common screw driver a calibrated torque wrench an oil can mirror and flashlight Safety equipment including hearing and eye protection must be used 7 Tachometer verification instrument various types are available Verify aircraft tachometer accuracy prior to fuel system adjustment B PRE SETUP PROCEDURES 1 During engine installation or if any fuel system component has been replaced flush the aircraft fuel system by first removing the engine driven fuel pump inlet hose and terminating the end into a large clean container Operate the aircraft boost pump and allow a minimum of one gallon of fuel to flow through the system Take necessary precautions to prevent a fire hazard If CONTINENT PAGE NO REVISION S 2 of 40 Teledyne Continental Motors Inc SID97 3 C A Teledyne Technologies Company P O Box 90 Mobile Alabama e 251 438 3411 contamination is present locate and correct the source and repeat this step before proceeding 2 Before making any checks or adjustments verify the accuracy of the aircraft tachometer manifold pressure gauge and fuel flow gauge Any gauge found to be inaccurate must be repaired or replaced before adjusting the fuel system WARNING USE OF INACCURATE GAUGES WILL RESULT IN INCORRECT ADJUSTMENT OF THE ENGINE FUEL SYSTEM POSSIBLE CYLINDER WEAR DUE TO LEAN OPERATION PRE IGNITION DETONATION LOSS OF POWER
37. ng at the specified IDLE RPM and unmetered fuel pressure slowly move the mixture control from the FULL RICH position toward IDLE CUT OFF to check fuel air mixture A rise of 25 to 50 RPM should be obtained An RPM change greater than 50 indicates the mixture is too rich and a change that is less than 25 indicates the mixture is too lean Adjust mixture conditions that are too rich or too lean as follows a Identify the type of throttle and control assembly that is to be adjusted See Figures 6 8 and 9 b Perform an IDLE fuel air mixture check and observe RPM rise If the RPM rise is not within specifications advance the throttle control to 1500 1800 RPM for 15 seconds after each adjustment to clear the engine Retard the throttle control to IDLE RPM and repeat mixture check Make the necessary adjustment Repeat this procedure until the specified RPM rise is achieved c Recheck IDLE RPM unmetered pump pressure If pressure in not within limits repeat Steps 18 19 19 a and 19 b before continuing 20 On all naturally aspirated engines adjust the FULL POWER metered fuel pressure to the specified value by turning the adjustable orifice screw clockwise to increase fuel pressure and counterclockwise to decrease fuel pressure See Figures 1 2 and 3 2 On turbocharged engines adjust the full power metered fuel pressure to the specified value as follows NOTE On turbocharged engines equipped with a fuel pressure r
38. nt G ADJUSTMENT PROCEDURES Fuel Pump Auto Leaning Schedule NOTE On 550 and model engines do not attempt to adjust the auto leaning schedule if the aircraft is at a field with a pressure altitude greater than 1000 feet On IO 550 B D E F and L model engines do not attempt to adjust the auto leaning schedule if the aircraft is at a field with a pressure altitude greater than 3000 feet Refer to Part C of this Service Information Directive for installation of the required test equipment 1 If not previously accomplished adjust the engine fuel injection system in accordance with Part C of this Service Information Directive using the appropriate table for the engine and aircraft 2 Adjustments to the engine driven fuel pump variable orifice aneroid will result in a change to the auto leaning schedule One complete revolution of the aneroid adjustment will increase or decrease the auto leaning schedule approximately 1000 feet 3 Refer to the charts on pages 19 to 25 The variable orifice aneroid adjustment will move PAGE REVISION lt gt U 8 of 40 Teledyne Continental Motors Inc SID97 3 A Teledyne Technologies Company P O Box 90 Mobile Alabama 251 438 3411 you horizontally across the chart The adjustable orifice will move you vertically 4 Adjustments to the variable orifice aneroid will affect the FULL POWER unmetered fuel pressures adjustable orifice
39. or 973 Metered Fuel Pressure Limits x Correction Factor Corrected Metered Pressure Limits 14 9 x 973 14 5 Minimum Metered Pressure Limit 2640 RPM 17 2 x 973 16 7 Maximum Metered Pressure Limit 2640 RPM oo N fo ie A 6 rn r A PAGE REVISION 4 10 of 40 A Teledyne Technologies Company SID97 3 C Box 90 Mobile Alabama 251 438 3411 TABLE 3 Fuel System Adjustment Values IDLE AND FULL POWER FUEL PRESSURES AND FLOWS ENGINE Prop RPM amp Unmetered Metered Fuel Ibs hr Fuel gal hr MAP Pump PSI Nozzle PSI NOTE 3 NOTE 4 NOTE 5 NOTE6 0 240 A B 6 LOWE MMC 10 240 A BO Full Throttle See and See and For IO 240 A B with standard fuel pump installed Q For IO 240 B series with optional Altitude Compensating Pump and Standard Fuel Manifold Valve see Chart 1 and Table 5 for instructions See Note 2 page 18 of 38 For IO 240 B series with the optional Altitude Compensating Pump and Fuel Scavenge Manifold Valve see Chart 1A and Table 5A for instructions See Note 2 page 18 of 38 IO 346 A B 7 0 7 5 2700 19 0 21 0 12 5 14 0 78 85 13 3 14 5 10 360 A AB C 7 0 9 0 CB D DB G 2800 240 27 0 15 8 18 2 100 106 17 0 18 1 GB H HB J JB IO 360 ES 7 0 9 0 i SEE NOTE 2 2800 23 0 26 0 14 3 16 5 100 107 17 0 18 1 10 360 8 6 9 7 0 9 0 SEE NOTE 2 amp 6 21 0 24 0 13 8 15 5 16 4 17 4 Se
40. pm to 20 50 rpm YEAR MO DAYS QV 22 of 40 97 Teledyne Continental Motors Inc SID97 3 Teledyne Technologies Company P O Box 90 Mobile Alabama 251 438 3411 CHART 1A Con t FULL THROTTLE Step 2 Adjust the aneroid rod to obtain the metered nozzle pressure 0 3 psi at pressure altitude and RPM per the chart above Turn clockwise to decrease pressure and counter clockwise to increase pressure After adjustment recheck idle unmetered pressure setting using the instructions in step 1 of this chart Reference Figure 15 10240B WOT Fuel Pump Setup Full Rich Mixture Setting 10B Nozzles Metered Nozzle Fuel Pressure psig 2050 rpm 500 1500 2500 3500 4500 5500 6500 7500 8500 9500 Pressure Altitude ft NOTE At conclusion of setup reset the idle speed to 850 RPM 25 RPM and verify idle cutoff mixture rise acceleration deceleration without excessive idle speed dip and idle stability YEAR mo AY YEAR lt 23 40 97 Teledyne Continental Motore Inex P O Box 90 Mobile Alabama 251 438 3411 Table 5 Flight Test Verification 240 equipped with Altitude Compensating Pump and Standard Fuel Manifold Valve This test is fo
41. r reference only actual RPM may vary due to the fixed pitch prop NOTE Pressure altitude must be used for the table and chart below when determining fuel system set up values To determine pressure altitude prior to take off set your altimeter to 29 92 in hg and the altimeter will indicate your pressure altitude 240 Engine with Aneroid Fuel Pump Full Throttle Full Rich Mixtu 2450 RPM Pressure Altitude Set Altimeter at Metered Fuel Pressure 29 92 in a Fuel Flow Ibs hr Fuel Flow gals hr PSID 54 75 66 61 ns 400 408 69 80 76 108 6000 369 454 63 74 ss 96 800 340 405 56 69 65 91 10009 321 386 55 66 63 s7 CHART 2 Typical IO240B with altitude compensating fuel pump fuel flow leaning curve during flight test 10240B Altitude Leaning Schedule 2450 RPM full rich mixture O Fuel Flow ow Q Q O 0a O O O Q O 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000 12000 13000 14000 15000 Pressure Altitude ft ISSUED REVISED e ONTINENTAL __ PAGE REVISION DAY YEAR DAY YEAR zo Continental Motors Inc SID97 3 gt 97 Teledyne Technologies Company P O Box 90 Mobile Alabama 251 438 3411 Table 5 Flight Test Verification 240 equipped with Altitu
42. reset the idle speed to 850 RPM 25 RPM and verify idle cutoff mixture rise acceleration deceleration without excessive idle speed dip and idle stability DAY YEAR NO AY YEAR WP 21 97 Teledyne Technologies Company SID97 3 P O Box 90 Mobile Alabama 251 438 3411 CHART 1A IO240B Equipped With Altitude Compensating Pump and Fuel Scavenge Manifold Valve Idle Step 1 Set Unmetered pump pressure and RPM rise at 1000 25 rpm to 11 6 0 2 psi sea level standard day If pressure altitude is different from sea level determine required unmetered pressure setting from the plot below Reference Figure 15 NOTE Pressure altitude must be used for the figures below when determining fuel system set up values To determine pressure altitude prior set your altimeter to 29 92 in hg and the altimeter will indicate your pressure altitude 10240B w Bypass Fuel System Unmetered Fuel Pressure at 1000RPM Unmetered Fuel Pressure psig 24 T2 12 4 11 6 4 11 2 1 08 06 04 0 2 10 9g 9 6 9 4 9 2 9 8 8 8 6 84 8 2 8 500 1000 00 2000 2500 3000 3500 4000 4500 5000 5500 6000 6500 7000 7500 8000 8500 9000 9500 10000 Pressure Altitude ft a Adjust idle mixture screw to set RPM rise during mixture check at 1000 r
43. stics or performance If FULL POWER RPM was not obtained during fuel injection system setup and adjustment a flight test is required to insure that the fuel injection system is performing within specified limits for the engine and aircraft Repeat the setup and adjustments as required until the fuel injection system is performing within the published specification for the aircraft and engine PAGE REVISION S 7 of 40 Teledyne Continental Motors Inc SID97 3 C A Teledyne Technologies Company P O Box 90 Mobile Alabama e 251 438 3411 FLIGHT TEST Naturally Aspirated engines with altitude compensating fuel pumps AUTO LEAN All naturally aspirated engines utilizing an altitude compensating fuel pump require a flight test at a Initial installation b Every 12 months Scheduled to coincide with annual or 100 HR inspection c each time adjustments are made due to a fuel system component replacement and d at any indication of improper auto leaning feature operation Table 5 and Chart 1 provide fuel flow vs pressure altitude specifications for the IO 240 B senes engine with altitude compensating fuel pumps Table 6 and Auto Leaning Chart 3 provide fuel flow vs pressure altitude specifications for the IO 360 DB engine with altitude compensating fuel pump Tables 7 amp 8 and Auto Leaning Charts 4 amp 5 provide fuel flow vs pressure altitude specifications for the IO 360 ES engine with altitude
44. uel Flow 120 110 100 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Pressure Altitude X 1000 ft CHART 9 pav YEAR wo Day em NAP Teledyne Continental Motors Inc SID97 3 gt 97 Teledyne Technologies Company P O Box 90 Mobile Alabama 251 438 3411 VAPOR RETURN ADJUSTABLE ORIFICE FUEL INLET INLET LOW PRESSURE H RELIEF RELIEF VALVE VALVE CW CW INCREASE INCREASE FUEL OUTLET 9 UNMETERED FUEL OUTLET DRAIN PRESSURE UNMETERED PRESSURE FIGURE 1 NATURALLY ASPIRATED ENGINE FUEL PUMP VAPOR RETURN LOCATED ON OPPOSITE SIDE ON MOST FUEL PUMPS ADJUSTABLE ORIFICE CW INCREASE FUEL INLE FUEL INLET LOW LOW PRESSURE ERU RELIEF VALVE RELIEF VALVE R CW INCREASE INCREASE FUEL OUTLET e UNMETERED PRESSURE IDLE CUTOFF FULL RICH FIGURE 2 NATURALLY ASPIRATED ENGINE MIXTURE CONTROL EQUIPPED FUEL PUMP ISSUED REVISED BEES PAGE REVISION DAY YEAR DAY YEAR D Teledyne Motors Inc SID97 3 gt 97 Teledyne Technologies Company P O Box 90 Mobile Alabama 251 438 3411 ADJUSTABLE ORIFICE LOW PRESSURE RELIEF VALVE CW INCREASE ANEROID AMBIENT ADJUSTMENT PRESSURE FACTORY SET REFERENCE FUEL OUTLET ADJUSTMENT NOT UNMETERED NORMALLY REQUIRED PRESSURE FIGURE 3 ALTITUDE COMPENSATING FUEL PUMP ANEROID ADJUSTMENT Sy RETURN INCREASE TURBOCHA
45. ustment and maintenance procedures gt Teledyne Technologies Company ep 1 of 40 97 Teledyne Continental Motors Inc 51097 3 C P O Box 90 Mobile Alabama e 251 438 3411 2005 TELEDYNE TECHNOLOGIES INC Any fuel system that cannot be adjusted to meet the specified values will require repair or replacement of the affected components prior to further engine operation The adjustment procedures provided in this SID also apply to engine fuel systems equipped with TCM Position Tuned Fuel Nozzles Refer to Form X306474 Position Tuned Fuel Nozzle Installation and Maintenance Manual for more detailed information and installation instructions CAUTION Refer to the torque specifications Table 1 page 10 for specified values when torquing hose end fittings A ADJUSTMENT TOOLS AND EQUIPMENT REQUIRED A complete set of tools and test equipment is essential for correct setup of TCM fuel injection systems Various combinations of these tools and equipment will be used depending on the engine model A proper inventory of tools and equipment for fuel system adjustment will include the following 1 recommends the Model 20 Porta Test Unit P N 630045 20 ATM C or equivalent to insure the fuel injection system meets all pressure and flow specifications You may acquire a Model 20 ATM C Porta Test Unit by contacting the following company AERO TEST Inc 29300 Goddard Road Romulus Michigan 48174
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