SID97-3F - JP Instruments
Contents
1. 105 CT EA ee E L HF H Recommended Setup tor TI r Cirrus SR20 Installation _ l J Fuel 100 100LL 2700 rpm WOT Full Rich 2700 RPM na E Fuel Temo 72 F H EEEE EE OKY tt jete LT T 555 FT Z sel T l TH t Z H PE KJ f I ni A 2 a0 m Backs a FT 3 S R 3 9 BE o 78 I a oo et i mi HH tT 70 IJS K H i i HH i I 65 HE NS MR I i J 60 Sl 1 2 3 4 5 6 7 8 9 10 11 12 B 14 15 16 17 Pressure Altitude X 1000 ft Figure 3 IO 360ES 6B Altitude Leaning Schedule 2700 RPM with Full Rich Mixture Wide Open Throttle ll issvep REVISED _ PAGE NO REVISION YYYY MM DD YYYY MM DD a 19 of 28 1997 03 24 2013 05 10 Continental Motors Inc siD97 3 P O Box 90 Mobile Alabama e 251 436 8299 Table 7 IO 550 D E F amp L ENGINE ALTITUDE FUEL SCHEDULE FULL OPEN THROTTLE FULL RICH MIXTURE 300 BHP 2700 RPM Pressure Altitude Fuel Flow Fuel Flow Metered Fuel Set Altimeter at lbs hr gals hr Pressure PSID 29 92 in Hg Min Max Min Max Min Max 160 150 140 130 Fuel Flow 120 5 6 7 8 9 10 14 12 13 14 Pressure Altitude X 1000 ft Figure 4 IO 550 D E F L Altitude Leaning Schedule Full Rich 2700 RPM 0 1 2 3 4 issueo REVISED ES PAG2. _ PAGE NO REVISION YYYY MM DD YYYY MM DD N y 6 of 28 Continental Motors Inc P O Box 90 Mobile Alabama e 251 436 8299 SID97 3 20 21 22 c Recheck IDLE RPM unmetered pump pressure If pressure is not within limits repeat Steps 18 19 19a 19b and 19c before proceeding 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 Figure 5 through Figure 7 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 regulator the full power metered fuel pressure and fuel flow must be adjusted to five 5 percent higher than the maximum specified limit a Loosen the aneroid adjustment screw jam nut See Figure 8 through Figure 9 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 jam nut to 25 30 inch pounds DO NOT EXCEED JAM NUT TORQUE LIMITS Exceeding the jam nut torque specification will result in damage to the aneroid housing threads and subsequent maladjustment For engines equipped with a fuel pressure regulator perform a final adjustment to the full power metered fuel p
3. 1 calibrated 0 30 PSI gauge graduated in 2 PSI maximum increments to be used for metered pressure measurements and verification of aircraft fuel flow indications on normally aspirated engines only 3 One 1 calibrated differential gauge 0 30 PSID maximum graduated in 2 PSI maximum increments to 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 calibrated in accordance with the manufacturer s instructions Calibrated pressure gauges may be purchased from various suppliers such as issvep REvisep YYYY MM DD YYYY MM DD l Davis Instruments 4701 Mount Hope Drive Baltimore MD 21215 Phone 1 410 358 3900 or 1 800 368 2516 Two 2 P N MS51523 B4 swivel tee These fittings will be used to tee into fuel lines for unmetered and metered pressure reference Hoses of appropriate diameters and sufficient lengths to allow personnel and equipment to be located away from propeller arc and blast area 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 sockets universal swivel extension and a 5 32 hex key Allen wrench common screw driver a calibrated torque wrench an oil can mirror and flashlight Safety equipment including hearing and eye protection must b
4. 28 0 32 0 13 6 15 3 125 135 21 3 23 0 36 0 2600 35 0 45 0 NOTE 8 140 150 23 3 25 5 38 0 TSIO 360 SB 700 6 25 6 75 s 2600 31 36 15 1 17 8 131 151 22 3 25 7 39 0 2600 23 8 25 3 14 7 16 9 122 129 20 8 22 0 2600 24 7 27 7 14 8 17 3 123 130 21 0 22 1 L M N S U 2625 25 0 28 0 15 0 17 5 124 131 21 1 22 3 2600 24 7 27 7 14 8 17 3 123 130 21 0 22 1 2625 28 3 29 8 17 8 18 8 123 5 131 21 0 22 3 me Y a mam mau 2625 28 8 31 0 17 8 18 8 132 137 5 22 5 23 4 eg Pe 2400 26 0 28 0 15 5 16 5 145 155 24 7 26 4 TSIO 470 B C D 600 32 60 2600 28 0 30 0 15 0 17 0 145 155 24 7 26 4 35 0 2700 29 0 32 0 15 9 18 2 136 146 23 2 24 9 C CB 2700 28 0 31 0 14 9 17 2 136 146 23 2 24 9 ll issueo reviseo _ PAGE NO REVISION YYYY MM DD YYYY MM DD Ma PS 13 of 28 1997 03 24 EN Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 Table 3 Fuel System Adjustment Values IDLE AND FULL POWER FUEL PRESSURES AND FLOWS Fuel gal hr ENGINE SEE NOTE 1 Prop RPM amp Unmetered Pump PSI NOTE 2 Metered Nozzle PSI NOTE 3 Fuel Ibs hr NOTE 4 NOTE 4 2850 30 0 33 0 17 0 19 4 143 153 24 4 26 1 2850 209 0 32 0 16 1 18 3 143 153 24 4 26 1 IO 520 M MB 600 6 0 7 0 2700 29 0 32 0 16 7 19 3 136 146 23 2 24 9 IO 520
5. 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 500x20 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 NOTE Reference Service Information Letter SIL95 5 for information specific to hose and tubing installation issvep REVISED _ YYYY MM DD YYYY MM DD l ST _ PaGE NO REVISION Continental Motors Inc P O Box 90 Mobile Alabama e 251 436 8299 10 of 28 SID97 3 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 I0 520 BB Maximum Rated RPM 2700 Metered Fuel Pressure Limits lt 14 9 17 2 If maximum static engine RPM 2640 60
6. THROTTLE FULL RICH MIXTURE 210 BHP 2800 RPM Set Altimeter at Ibs hr gals hr Pressure PSID 29 92 in Hg Min Max Min Max Min Max 21 182 Gasoline 5 87 Ibs per gallon 70 F 110 a 105 N i i i i i Fuel 100 100LL 100 a Rich 2800 PRM a T T uel Temp 72 F 95 4 NK H L z 85 t S S EP Ree gt 80 HE TT mnie ME EEE 65 f 60 I I SA 1 2 3 4 5 6 T JB 9 10 11 12 13 14 15 16 17 Pressure Altitude X 1000 ft Figure 2 IO 360 ES Altitude Leaning Schedule 2800 RPM with Full Rich Mixture Wide Open Throttle issvep REVISED PAGE NO REVISION YYYY MM DD YYYY MM DD CAS A 18 of 28 1997 03 24 2013 05 10 Continental Motors Inc siD97 3 P O Box 90 Mobile Alabama e 251 436 8299 Table 6 IO 360 ES ENGINE ALTITUDE FUEL SCHEDULE WIDE OPEN THROTTLE FULL RICH MIXTURE 200 BHP 2700 RPM SEE NOTE 7 Pressure Altitude 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 Ibs per gallon 70 F
7. 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 With engine operating 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 the IDLE fuel air mixture A rise of 25 to 50 RPM should be obtained An IDLE RPM rise greater than 50 indicates the mixture is too rich and a rise of less than 25 RPM indicates the mixture is too lean Adjust mixture conditions that are too rich or too lean as follows a Identify the type of mixture control assembly that is to be adjusted See Figure 10 Figure 12 and Figure 13 b If the IDLE 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 fuel air mixture check Make the necessary adjustment Repeat this procedure until the specified IDLE RPM rise is achieved issueo REVISED Fi
8. as turbo normalizing systems turbocharging systems intercoolers after coolers fuel nozzles etc whether by STC or field approval must use the instructions provided by the STC holder or installer CMI will not accept responsibility or liability for any modified engine set up according to the instructions contained in this Service Information Directive NOTE 2 FULL POWER unmetered fuel pump pressure limits are provided for reference only Use metered fuel pressure specifications for adjustments at full power NOTE 3 Use for full power maximum RPM adjustment only All other parameters for reference only NOTE 2 applies NOTE 4 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 5 Engine equipped with Altitude Compensating fuel pump NOTE 6 applies NOTE 6 Flight test required to verify fuel flow vs pressure altitude values are within the limits specified See applicable Table 4 through Table 7 and Figure through Figure 4 for applicable values by engine model NOTE 7 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 plate reflects original TC and PC data of 210 HP at 2800 RPM Refer to Cirrus SR20 Maintenance Manual and Pilots Operating Hand
9. instructions A flight test is required whenever an adjustment is made that may affect engine operational characteristics or performance If FULL POWER RPM was not obtained during fuel injection system setup and adjustment a flight test is required to ensure 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 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 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 4 and Auto Leaning Chart Figure 1 provide fuel flow vs pressure altitude specifications for the IO 360 DB engine with altitude compensating fuel pump Table 5 and Table 6 and Auto Leaning Charts Figure 2 and Figure 3 provide fuel flow vs pressure altitude issuep REvisep YYYY MM DD YYYY MM DD i R specifications for the IO 360 ES engine with altitude compensating fuel pump Table 7 and Auto Leaning Chart Figure 4 provide fuel flow vs pressure altitude specifications for the IO 550 Sandca
10. so could cause Hydraulic Lock and subseguent engine failure 11 Install the engine cowling or cooling shroud during ground operation issvep REVISED YYYY MM DD YYYY MM DD l 12 Refer to Table 3 beginning on page 12 for specific data applicable to your engine Record the applicable IDLE and FULL POWER adjustment points RPM fuel pressure fuel flow manifold pressure and IDLE RPM rise provided in this document and the Aircraft Maintenance Manual on the operational check form included on the last page of this service bulletin The Operational Check Form may be reproduced for use in recording adjustments and test indications NOTE To ensure optimum cooling during FULL POWER operations the FULL POWER fuel flow should be set to the maximum specification limit WARNING Ensure the aircraft brakes are set and wheel chocks are properly placed forward and aft of the main landing gear tires before engine start 13 SS Continental Motors Inc 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 at this power setting until the engine temperatures and pressures have stabilized in the operational range With the mixture control in the FULL RICH position reduce the throttle to the specified IDLE RPM Record the unmetered pressure indicated on
11. 24 4 26 4 10 550 G SEE Maintenance Manual M 16 IO 550 N SEE Maintenance Manual M 16 issueo REVISED A _ PAGE NO REVISION YYYY MM DD YYYY MM DD N W 15 of 28 1997 03 24 Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 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 SEE NOTE 1 Pump PSI Nozzle PSI NOTE 2 NOTE 3 NOTE 4 NOTE 4 IO 550 P SEE Maintenance Manual M 16 IO 550 R SEE Maintenance Manual M 16 GIO 550 A 600 25 Minimum 2267 45 55 NOTE 8 175 185 29 8 31 5 TSIO 550 B C E SEE Maintenance Manual M 18 G K N TSIO 550 G 7 0 9 0 MOONEY 20 0 23 0 10 4 11 6 177 180 30 0 30 7 NOTE 9 TSIOL 550 A 600 5 5 6 5 2600 32 5 35 5 17 0 19 0 170 180 29 0 30 7 35 0 TSIOL 550 B 600 6 0 8 0 2700 36 0 40 0 20 0 22 5 175 185 29 8 31 5 35 0 TSIOL 550 C 600 6 0 8 0 2600 37 0 40 0 15 0 16 5 204 216 34 8 36 8 39 5 6 285 TIARA See latest revision of Continental Motors Service Bulletin M79 4 NOTE 1 The setup procedures contained in this bulletin are only for use on engines that have not been modified from their original configuration as shipped from the factory by Continental Motors Engines which have been modified by the installation of aftermarket components such
12. A AB 600 6 5 7 5 s a 2800 272 312 15 8 16 7 119 124 20 1 21 0 32 0 TSIO 360 B BB 600 6 5 7 5 2800 272 312 15 8 16 7 115 124 20 1 21 0 32 0 TSIO 360 C CB 600 6 5 7 5 2800 34 0 37 0 16 7 19 3 135 145 23 0 24 7 37 0 TSIO 360 D DB 600 6 5 7 5 E E 2800 34 0 37 0 16 7 19 3 135 145 23 0 24 7 36 0 TSIO 360 E EB 700 6 25 6 75 a p LTSIO 360 E EB 2575 43 0 46 0 15 8 18 3 130 140 22 1 23 8 40 0 TSIO 360 F FB 700 6 25 6 75 lt E lt 2575 40 0 43 0 15 8 18 3 130 140 22 1 23 8 41 0 TSIO 360 G GB 700 6 25 6 75 2700 45 0 49 0 16 7 19 3 135 145 23 0 24 7 40 0 issueD Revisep ATAR _ PAGE NO REVISION YYYY MM DD YYYY MM DD MID sO 120f28 ES 1997 03 24 Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 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 SEE NOTE 1 Pump PSI Nozzle PSI NOTE 2 NOTE 3 NOTE 4 NOTE 4 TSIO 360 H HB 600 6 5 7 5 2800 29 0 33 0 14 9 17 3 125 135 21 3 23 0 34 5 2800 34 5 37 5 16 7 19 3 134 145 22 8 24 7 37 0 TSIO 360 KB 700 6 5 7 5 S L TSIO 360 KB 2800 36 0 39 0 17 7 21 2 140 155 23 8 26 4 40 0 TSIO 360 LB 700 6 25 6 75 2700 34 0 38 0 14 7 16 7 135 145 23 0 24 7 40 0 TSIO 360 MB 700 6 25 6 75 2700
13. E NO REVISION YYYY MM DD YYYY MM DD A Wt 2 120 of 28 1997 03 24 EN Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 VAPOR RETURN ADJUSTABLE ORIFICE FUEL INLET INLET LOW LOW PRESSURE PRESSURE 1 0 RELIEF O RELIEF a VALVE a CW INCREASE INCREASE 4 FUEL OUTLET i k 7 UNMETERED FUEL OUTLET DRAIN PRESSURE UNMETERED PRESSURE Figure 5 Fuel Pump Naturally Aspirated Engine VAPOR RETURN LOCATED ON OPPOSITE SIDE ON MOST FUEL PUMPS ADJUSTABLE ORIFICE CW INCREASE FUEL INLE FUEL INLET LOW LOW PRESSURE A PRESSURE RELIEF VALVE ne VALVE CW z INCREASE INCREASE FUEL OUTLET y E s EH IDLE CUTOFF FULL RICH PRESSURE Figure 6 Fuel Pump with Mixture Control Naturally Aspirated Engine issueo REVISED _ PAGE NO REVISION YYYY MM DD YYYY MM DD AND 01 of 28 1997 03 24 2013 05 10 Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 ADJUSTABLE ORIFICE INCREASE LOW PRESSURE RELIEF VALVE CW INCREASE lt 4 ANEROID AMBIENT ADJUSTMENT PRESSURE FACTORY SET REFERENCE FUEL OUTLET ADJUSTMENT NOT UNMETERED NORMALLY REGUIRED PRESSURE Figure 7 Altitude Compensating Fuel Pump Naturally Aspirated Engine RETURN FUEL RETURN TURBOCHARGE DISCHARGE PRESSURE REFERENCE ANEROID USTMENT LOW PRESSURE RELIEF VALVE CW INCREASE FUEL OUTLET DRAIN lt l
14. I CONTINENTAL MOTORS AIRCRAFT ENGINE SERVICE INFORMATION DIRECTIVE COMPLIANCE WILL ENHANCE SAFETY MAINTENANCE OR ECONOMY OF OPERATION SUBJECT CONTINENTAL MOTORS INC CMI CONTINUOUS CATEGORY 4 SID97 3F SUPERSEDES SID97 3E and SID07 3A Technical Portions FAA APPROVED FLOW FUEL INJECTION SYSTEMS ADJUSTMENT SPECIFICATIONS AND INSTRUCTIONS PURPOSE COMPLIANCE At Engine Installation Provide specifications and instructions for adjustment of CMI fuel injection systems 100 hour Annual Inspection fuel system component replacement or as required if operation is not within specifications MODELS AFFECTED All CMI 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 instructions and values provided in the document apply to CMI fuel injected engines that conform to the original type design Refer to the Supplemental Type Certificate STC holder s instructions for aircraft that have been modified from the original type design GENERAL INFORMATION Fuel injection system components manufactured by CMI are adjusted and calibrated to meet engineering specifications Fuel injection system components installed on factory new and rebuilt engines are adjusted to meet design specifications during operation in the production engine test facility These tests and adjustments are carried out in an environment of c
15. P 600 6 0 7 0 LIO 520 P 2500 26 2 26 9 14 3 16 2 130 140 22 1 23 9 TSIO 520 AE 600 7 5 8 5 S LTSIO 520 AE 2400 34 5 38 0 15 2 16 5 160 165 27 3 28 1 32 5 TSIO 520 AF 600 5 5 6 5 2700 35 0 39 0 18 4 19 9 180 186 30 7 31 7 35 5 TSIO 520 B BB 600 5 5 7 0 32 0 TSIO 520 BE 600 3 3 7 0 2600 25 0 28 0 12 7 14 1 214 224 36 5 38 2 38 0 TSIO 520 C H 600 5 5 7 0 2700 29 0 32 0 15 3 172 160 170 27 3 29 0 32 5 TSIO 520 CE 600 5 5 6 5 S gt S 2700 33 0 36 0 16 2 18 0 215 225 36 6 38 3 87 0 TSIO 520 D DB 600 5 5 7 0 lt E lt 2700 29 0 32 0 13 3 15 1 160 170 27 3 29 0 32 5 TSIO 520 E EB 600 5 5 6 5 S E 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 TSIO 520 K KB 600 5 5 7 0 2700 29 0 32 0 15 1 17 4 163 175 27 8 29 8 33 0 TSIO 520 L LB 600 25 Minimum 2700 45 0 55 0 NOTE 8 180 190 30 7 32 4 38 0 IssurD_ REVISED y _ PAGE no REVISION YYYY MM DD YYYY MM DD S7 14 of 28 SID97 3 1997 03 24 Continental Motors Inc P O Box 90 Mobile Alabama e 251 436 8299 Table 3 Fuel System Adjustment Values IDLE AND FULL POWER FUEL PRESSURES AND FLOWS ENGINE
16. PPER DECK PRESSURE UNMETERED FUEL PRESSURE SS VAPOR RETURN FE METERED FUEL PRESSURE A Figure 18 Typical Turbo Charged Engine Fuel System Schematic Fuel Pump w Integral Mixture Control issueo REVISED PAGE NO REVISION YYYY MM DD YYYY MM DD M V 97 of 08 ES 1997 03 24 EN Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 me jo 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 l gt 5 ea ow Te Pressure Altitude Set Fuel Flow UL altimeter to 29 92 Hg Remarks Idle fuel air mixture RPM rise magneto drop etc Signature
17. Prop RPM amp Unmetered Metered Fuel Ibs hr Fuel gal hr SEE NOTE 1 Pump PSI Nozzle PSI NOTE 2 NOTE 3 NOTE 4 NOTE 4 TSIO 520 M R 600 5 5 6 5 2700 33 0 37 0 16 9 19 9 170 186 29 0 31 7 36 5 TSIO 520 N NB 600 5 5 6 5 2700 32 0 35 0 16 9 19 9 170 186 28 9 31 7 38 0 TSIO 520 P 600 5 5 6 5 2700 33 0 37 0 18 4 19 9 180 186 30 7 31 7 36 5 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 TSIO 520 UB 600 5 5 6 5 2700 33 0 37 0 14 4 16 0 195 205 33 2 34 9 36 0 2700 36 0 39 5 16 9 18 7 200 210 34 1 35 8 40 5 TSIO 520 WB 600 25 Minimum 2700 45 0 55 0 NOTE 8 190 200 32 4 34 1 39 5 GTSIO 520 C 525 4 0 7 0 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 NOTE 8 2267 38 0 41 0 17 4 18 8 300 310 51 1 52 8 44 5 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 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 NOTE 8 2234 29 5 35 0 16 4 17 9 255 265 43 4 45 1 39 0 IO 550 A B C SEE Maintenance Manual M 16 IO 550 D E F L 600 8 0 10 0 NOTES 5 amp 6 2700 32 0 36 0 17 2 20 0 143 155
18. RES WARNING Failure to properly support and stabilize component fittings can result in fitting and or component damage and loss of system pressure Reference the latest revision of 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 the fuel pump outlet fitting the fuel control unit inlet fitting or the throttle body metering unit inlet tee whichever is most issvep revisen YYYY MM DD YYYY MM DD l SS Continental Motors Inc P O Box 90 Mobile Alabama e 251 436 8299 accessible Some engine models have a fuel pressure connection fitting in the fuel control inlet screen that may be utilized for unmetered pressure gauge attachment For engine models with integral throttle body metering units REF Figure 10 remove and set aside the 639494 cap fitting from the inlet tee This cap will be reinstalled after setup is complete Install the MS51523 B4 swivel tee directly to the fuel pump outlet fitting or to the fuel control inlet fitting REF Figure 5 through Figure 11 as applicable torque the tee fitting to the value specified in Table 1 NOTE Some installations may require combinations of different fittings and hoses to facilitate installation of unmetered and metered test equip
19. RPM use Correction Factor 973 Metered Fuel Pressure Limits x Correction Factor lt 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 o fo fo fo le a la fo he e A R jo S issueo REVISED s _ PAGE NO REVISION YYYY MM DD YYYY MM DD AO 1 of 28 ES 1997 03 24 Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 I Adjustment Specifications 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 SEE NOTE 1 Pump PSI Nozzle PSI NOTE 2 NOTE 3 NOTE 4 NOTE 4 IO 240 A B SEE Maintenance Manual M 6 10 346 A B 7 0 7 5 a l 19 0 21 0 12 5 14 0 78 85 133 14 5 IO 360 A AB C 7 0 9 0 X B CB D 24 0 27 0 15 8 18 2 100 106 17 0 18 1 DB NOTE 5 G ee bete Meso GB H HB J JB 10 360 ES 600 7 0 90 14 3 16 5 100 107 17 0 18 1 NOTES 5 amp 6 2800 23 0 26 0 600 i IO 360 ES 70 90 i CIRRUS E i H NOTES 5 6 amp 7 2700 21 0 24 0 13 8 15 5 96 102 16 4 17 4 Sea Level NS 600 7 0 9 0 NOTES 5 6 amp 7 2700 19 0 22 0 13 3 14 6 94 98 16 0 16 7 1 500ft Press Alt IO 360 K KB 600 7 0 9 0 2600 7 1 21 0 24 0 14 3 16 3 93 5 97 5 15 9 16 6 TSIO 360
20. SIO520 D F H K L M amp N ll issueo_ REVISED S _ PAGE NO REVISION YYYY MM DD YYYY MM DD gt gt ww J on ot 28 1997 03 24 2013 05 10 Continental Motors Inc siD97 3 P O Box 90 Mobile Alabama e 251 436 8299 INLET SCREEN THROTTLE BODY FUEL sauna IDLE MIXTURE IDLE SPEED STOP ADJUSTMENT SCREW CCW zENRICH CW lt INCREASE Figure 13 Throttle and Control Assembly Side View All GTSIO 520 except GTSIO 520 C F amp K FUEL PRESSURE ME ADJUSTMENT CW INCREASE TURBOCHARGER DISCHARGE PRESSURE REFERENCE C CENTER PORT UNMETERED J OUTLET CY O ll issvep REVISED S __ PAGE No REVISION YYYY MM DD YYYY MM DD AND 25 of 28 1997 03 24 2013 05 10 Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 METERED FUEL PRESSURE INLET FUEL FROM AIRCRAFT J VAPOR RETURN UNMETERED FUEL PRESSURE ES RETURN FUEL FROM CONTROL UNIT Es METERED FUEL PRESSURE PSI FUEL VAPOR a AE F TES AN RETURN TO TANK FUEL INLET eedd eer SSS FROM TANK Er FUEL CONTROL r ea h FUEL PUMP ASSEMBLY AAA RETURN FROM FUEL N CONTROL UNIT b MANIFOLD VALVE ASSEMBLY a Lc E FUEL INJECTOR Ml N 7 IDLE MIXTURE ADJUSTMENT d DRAIN UNMETERED IDLE RPM ADJUSTMENT FUEL PRESSURE THROTTLEBODY Figure 15 Typical Naturally Aspirated Fuel System Schematic with Fuel Contr
21. STMENT NOTE On IO 550 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 Section C of this document for reguired test eguipment setup 1 If not previously accomplished adjust the engine fuel injection system according to instructions in Section C of this document using the appropriate table for the engine and aircraft 2 Adjustments to the engine driven fuel pump aneroid adjustment screw will result in a change to the auto leaning schedule One complete revolution of the aneroid adjustment screw will increase or decrease the auto leaning schedule approximately 1000 feet 3 Refer to Figure 1 through Figure 4 Adjustment of the aneroid adjustment screw 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 The adjustable orifice REF Figure 7 will correct fuel pump output vertically 4 Adjustments to the aneroid will affect the FULL POWER unmetered fuel pressure metered pressure and fuel flow It is important to maintain the balance between these adjustments in order to achieve the specified fuel system parameters Readjustment of the adjustable orifice unmetered pressure may be necessary CAUTION Exercise caution when adjustments to the ane
22. book NOTE 8 Refer to the aircraft manufacturer s instructions for adjustment procedures NOTE 9 TSIO 550 G installed in Mooney aircraft has been rated to a power level that is less than the approved Type Certificate Data Sheet Refer to the Mooney Aircraft maintenance manual for setup instructions issvep REVSED ENI _ PAGE NO REVISION YYYY MM DD YYYY MM DD OD gt 46 of 28 1997 03 24 Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 Table 4 IO 360 DB engine WIDE OPEN THROTTLE FULL RICH MIXTURE 210 BHP 2800 RPM Set Altimeter at Ibs hr gals hr Pressure PSID 29 92 in Hg in Max Min Max Min Max Gasoline 5 87 Ibs per gallon 70 F IO 360 DB Installed in T 41 ACFT Refer to Cessna SL81 2 date 28 July 1981 for amplified instructions EFE S S S e PEE EFS S E E HFH E Fuel Flow pph 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Altitude ft 1000 Curve No 00 002 Figure 1 IO 360 DB34B Altitude Leaning Schedule issueo REvisep _ PAGE NO REVISION YYYY MM DD YYYY MM DD NED 170f28 1997 03 24 2013 05 10 Continental Motors Inc siD97 3 P O Box 90 Mobile Alabama e 251 436 8299 Table 5 IO 360 ES ENGINE ALTITUDE FUEL SCHEDULE WIDE OPEN
23. e used Tachometer verification instrument various types are available Verify aircraft tachometer accuracy prior to fuel system adjustment PRE SETUP PROCEDURES WARNING Do not smoke or expose the work area to ignition sources while performing this procedure Work with clean hands tools and shop towels Mm Remove the engine cowling according to the aircraft manufacturer s instructions Purge the fuel system according to the following instructions during engine installation or when any fuel system component is replaced a Utilizing the airframe boost pump flush a minimum of one gallon of fuel from the fuel pump inlet hose into a clean dry container Inspect the flushed fuel If free from contamination connect to the engine driven fuel pump using the appropriate maintenance instructions If contamination exists correct before proceeding _ PAGE NO REVISION O gt 20f 28 1997 03 24 Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 b Using the airframe boost pump flush a minimum of one guart of fuel through the engine driven fuel pump into a clean dry repaired or replaced before adjusting the fuel system container while working the mixture 4 Ensure all fuel system components are of the control through its full range of operation correct part number and are installed properly Inspect the flushed fuel If free from Correct any discrepancies noted contaminati
24. gs to the value specified in Table 1 Verify Cap Assembly Part No 639494 REF Figure 10 is correctly installed on the inlet tee fitting on throttle body metering units Torque the cap 135 190 inch pounds according to TABLE 1 DO NOT install any cap other than Part No 639494 on the tee fitting under any circumstance Perform a complete fuel system leak check according to the aircraft manufacturer s instructions If the aircraft manufacturer does not provide specific instructions the instructions below may be used Correct any discrepancies noted e Turn aircraft master switch to ON position e Adjust mixture control to full rich e Adjust throttle control to 1 4 inch open e Activate the aircraft boost pump ON e Inspect entire fuel system for fuel leakage e Return mixture and throttle to idle closed position _ PAGE NO REVISION 7 of 28 ST SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 FLIGHT TEST e Turn aircraft boost pump OFF e Turn the aircraft master switch OFF 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 All naturally aspirated engines except those with altitude compensating fuel pump Refer to the AFM POH supplied by the aircraft manufacturer or Supplemental Type Certificate STC holder for aircraft operating
25. ment connections Attach the unmetered fuel supply hose to the straight end of the tee connector and torque to the value specified in Table 1 Connect the Unmetered test hose from the Porta Test Unit to the tee fitting and torque If using the alternative procedure connect the 0 to 60 PSI gauge to the swivel tee using a length of hose which will provide proper clearance from the engine cowling and propeller arc Torque connections to the value specified in Table 1 REF Figure 15 through Figure 18 Loosen and remove the metered fuel supply hose from the manifold valve inlet fitting Install and torque the second MS51523 B4 swivel tee directly to the fuel manifold valve inlet fitting Attach the metered fuel supply hose to the straight end of the tee connector and torque to the value specified in Table 1 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 to 30 PSI gauge to the swivel tee using a hose long enough to provide proper clearance from the engine cowling and een I _ PAGE NO REVISION 4 of 28 LU SID97 3 10 propeller arc Torgue all connections to the value specified in Table 1 REF Figure 15 and Figure 16 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 alter
26. native procedure connect the 0 to 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 REF Figure 17 and Figure 18 Torgue connections to the value specified in Table 1 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 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 eguipment Verify that all fuel lines hoses and fittings are secured and torgued and that no fuel leaks exist before proceeding Ensure test hoses have been routed clear of the exhaust system and are supported their entire length to avoid inaccurate gauge readings WARNING Verify all fuel has drained from the induction system prior to attempting engine start Failure to do
27. ngine operation The adjustment procedures provided in this document also apply to engine fuel systems equipped with CMI Position Tuned Fuel Nozzles Refer to Publication Number FI 2 Position Tuned Fuel Injector Nozzle Installation and Maintenance NES E _ PAGE NO REVISION P O Box 90 Mobile Alabama e 251 436 8299 1997 2013 CONTINENTAL MOTORS INC 1 of 28 SID97 3 Manual for more detailed information and installation instructions CAUTION Refer to the torque specifications Table 1 page 10 for specified values when applying torque to hose end fittings A TOOLS AND EQUIPMENT REQUIRED A complete set of tools and test equipment is essential for correct setup of CMI 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 CMI recommends the Model 20 ATM C Porta Test Unit P N 630045 20 ATM C or equivalent to ensure the fuel injection system meets all pressure and flow specifications The Model 20 ATM C Porta Test Unit is available from the manufacturer APPROVED AIRCRAFT ACCESSORIES 29300 Goddard Road Romulus Michigan 48174 734 946 9000 Calibrated gauges may be used as an alternative to the Porta Test Unit 1 One 1 calibrated 0 60 PSI gauge graduated in 1 PSI increments This gauge will be used for unmetered pressure measurement 2 One
28. ol Unit UNMETERED PRESSURE THROTTLE amp CONTROL ASSEMBLY INLET FUEL FROM AIRCRAFT UNMETERED FUEL PRESSURE E METERED FUEL PRESSURE NYJ VAPOR RETURN VAPOR RETURN RS SEEN N ES E METERED AIRCRAFT 7 PRESSURE j FUEL INLET yM Y IA AAA K FUEL PUMP V FUEL MANIFOLD VALVE ASSEMBLY di y Figure 16 Typical Naturally Aspirated Engine Fuel System Schematic ISSUED REVISED corran PAGE NO REVISION YYYY MM DD YYYY MM DD N y gt 96 of 28 SID97 3 Fuel Pump w Integral Mixture Control 1997 03 24 P O Box 90 Mobile Alabama e 251 436 8299 FUEL MANIFOLD VALVE FROM rrr TU S nma THROTTLEAND CONTROLASSEMBLY F FUEL PRESSURE s eu SE REGULATOR C b FUEL NI KI INJECTOR iM a NOZZLES G I I METERED FUEL PRESSURE FUEL PUMP INLET FUEL FROM AIRCRAFT VAPOR RETURN UNMETERED FUEL PRESSURE ES RETURN FUEL FROM CONTROL UNIT METERED FUEL PRESSURE ES UPPER DECK PRESSURE UNMETERED FUEL PRESSUR Figure 17 Typical Turbo Charged Fuel System Schematic with Fuel Control Unit and Fuel Regulator UPPER DECK PRESSURE FROM TURBOCHARGER UNMETERED PRESSURE FUEL INJECTOR a sl NOZZLES AIRCRAFT FUEL INLET METERED PRESSURE ES INLET FUEL FROM AIRCRAFT S U
29. on connect to the throttle and 5 Remove inspect clean and reinstall the control unit using the appropriate E E 7 ee aircraft and engine fuel screens according to maintenance instructions If contamination 13 the aircraft manufacturer s instructions is found correct the issue before proceeding further 6 Inspect the aircraft induction air filter and c Using the airframe boost pump flush a alternate air system for condition operation minimum of one guart of fuel through the and cleanliness Repair or replace any throttle and control unit into a clean dry component that is not airworthy according to container while working the throttle the aircraft manufacturer s instructions control through its full range of operation Inspect the flushed fuel If free from 7 Inspect the aircraft vapor return system for contamination connect to the manifold proper operation according to the aircraft valve using the appropriate maintenance manufacturer s instructions Correct any instructions If contamination is found discrepancies noted correct the issue before proceeding further s E P 8 8 Ensure the fuel manifold valve vent and fuel d Using the airframe boost pump flush a a k E pump drain lines are properly installed open minimum of one quart of fuel through the and free of obstruction Correct any fuel transducer hose into a clean dry di ted container Inspect the flushed fuel If free i from contamination install the f
30. ontrolled 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 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 issueo mevseD YYYY MM DD YYYY MM DD 1997 03 24 Continental Motors Inc Supplemental Type Certificate Holder s FAA approved instructions Fuel System Operational Check is required after any of the following circumstances 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 ADJUSTMENT PROCEDURES The following adjustment procedures are presented in a sequential format that must be followed to ensure proper fuel system adjustment Reference the applicable Aircraft Maintenance Manual for detailed fuel system adjustment and maintenance procedures Any fuel system that cannot be adjusted to meet the specified values will require repair or replacement of the affected components prior to further e
31. recorded values are within specifications proceed to step 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 ensure adequate part throttle fuel flow 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 driven fuel pump output pressures vary with engine RPM During ground operation full power RPM may not be obtained Use the Compensation Table for Static Ground Setup in Table 2 to correct the specified metered pressures if full power RPM cannot be achieved On turbocharged engines ensure manifold pressure is adjusted according to 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 positions 18 To adjust the IDLE RPM unmetered pump 19 pressure loosen the jam nut on the low pressure relief valve See Figure 5 through Figure 9 Turning the adjustment clockwise CW will increase pressure
32. ressure and fuel flow as follows Refer to Figure 14 Reconnect the regulator and torque connections to the value specified in Table 1 Loosen the jam nut on the regulator adjustment set screw Turn the regulator adjustment screw clockwise to increase metered fuel pressure and fuel flow turn the set screw counterclockwise to decrease metered fuel pressure and fuel flow After final adjustment is completed torque the jam nut to 21 25 inch pounds issvep revisen YYYY MM DD YYYY MM DD l 23 24 Mm Continental Motors Inc When full power metered fuel pressure has been adjusted to the specified values recheck a IDLE RPM b unmetered fuel pressure c IDLE fuel air 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 RPM stop screw Figure 10 through Figure 13 clockwise to increase RPM or counterclockwise to decrease RPM POST SETUP PROCEDURES Ensure the master switch ignition switch and fuel selector are in the OFF positions Remove the engine cowling or cooling shroud in accordance with the aircraft manufacturer s instructions a remove all test gauges fittings and hoses that were installed for fuel system setup b reconnect all fuel hoses and cap fittings to their original locations c torque all fittin
33. roid are accomplished The aneroid stem has an extra fine thread exceeding the jam nut torgue will damage either the aneroid stem or housing threads Jam nut torgue value is 25 30 inch pounds NOTE It will be necessary to cut and remove the safety wire and manufacturer s seal from the aneroid adjustment screw Cut the safety wire as close to the termination point as mssum mevseD YYYY MM DD YYYY MM DD l 1997 03 24 Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 10 rc Mi _ PAGE NO REVISION Mm possible twist the loose wire ends together and bend to form a pigtail It is not necessary to re safety the aneroid adjustment screw after adjustment has been completed and the jam nut has been properly torgued 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 As an example looking at Figure 4 IO 550 D engine at a pressure altitude of 4000 feet the recorded fuel flow was 138 PPH Point A The fuel flow specified for this pressure altitude is 139 PPH to 151 PPH The recorded fuel flow of 138 PPH would be correct if we were between 5000 feet and 7000 feet To achieve the specified fuel flow versus pressure altitude we must adjust the aneroid adjustment screw counterclockwise Adjustment of the aneroid adjustment screw two complete revolutions will adjust
34. ssure gauge and fuel flow gauge Any gauge found to be inaccurate must be REVISED l ISSUED PAGE no REVISION YYYY MM DD YYYY MM DD 3 of 28 SID97 3 1997 03 24 Continental Motors Inc P O Box 90 Mobile Alabama e 251 436 8299 WARNING Failure to correctly install and maintain engine controls can result in loss of system control and subseguent loss of engine power 13 Locate the IDLE speed RPM stop screw on the throttle body and turn it counter clockwise two complete turns REF Figure 10 through Figure 13 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 REF Figure 14 To deactivate the fuel pressure regulator loosen and remove the fuel line or hose from the center port fitting at the pressure regulator Install a cap on the center port fitting Install a plug in the removed line Torgue the cap and plug to the value specified in Table 1 Perform a pressurized leak test on the connections prior to proceeding with fuel system adjustments C SETUP PROCEDU
35. st series engine with altitude compensating fuel pumps Ensure 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 on the last page of this document record all pressure altitudes and corresponding minimum and maximum fuel flows recorded Perform a complete preflight inspection engine start and ground run up according to the aircraft manufacturer s instructions Set the aircraft altimeter to 29 92 inches Hg In accordance with the aircraft manufacturer s instructions conduct a normal take off Climb must be accomplished using full throttle FULL RICH mixture and maximum rated full power RPM Using the aircraft fuel flow gauge and altimeter record fuel flows at all pressure altitudes specified Compare the recorded fuel flows with the specified fuel flows for all pressure altitudes If fuel flow is within the minimum and maximum limits at all altitudes no adjustments are required If the fuel flow is not within specified limits at all pressure altitudes the fuel injection system auto leaning schedule requires adjustment PAGE NO REVISION Ne gt 8 of 28 Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 G FUEL PUMP AUTOLEAN SCHEDULE ADJU
36. t UNMETERED PRESSURE Figure 8 Aneroid Equipped Fuel Pump Turbocharged Engine issueo reviseo _ PAGE NO REVISION YYYY MM DD YYYY MM DD AS S P 22 of 28 1997 03 24 2013 05 10 Continental Motors Inc siD97 3 P O Box 90 Mobile Alabama e 251 436 8299 VAPOR RETURN FUEL RETURN seja FUEL INLET TURBOCHARGER DECK PRESSURE REFERENCE 1 of 2LOCATIONS LOW PRESSURE RELIEF VALVE CW INCREASE ANEROID ADJUSTMENT CCW INCREASE CUTOFF RICH FUEL OUTLET Figure 9 Aneroid and Mixture Control Equipped Fuel Pump Turbocharged Engine IDLE MIXTURE ADJUSTMENT Currently CW LEAN 39494 CCW ENRICH IDLE SPEED STOP SCREW CW INCREASE CCW DECREASE FUEL OUTLET FUEL INLET METERED PRESSURE UNMETERED PRESSURE Figure 10 Throttle and Metering Assembly issueo reviseo _ PAGE No REVISION YYYY MM DD YYYY MM DD AS A s 23 of 28 1997 03 24 2013 05 10 Continental Motors Inc SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 INLET SCREEN FUEL INLET FITTING UNMETERED PRESSURE THROTTLE LEVER MIXTURE LEVER FUEL OUTLET METERED FUEL RETURN PRESSURE TO FUEL PUMP Figure 11 Throttle and Control Assembly Front View except GTSIO520 D F H K LM amp N IDLE SPEED STOP SCREW CW INCREASE IDLE MIXTURE ADJUSTMENT CW ENRICH Figure 12 Throttle and Control Assembly Side View except GT
37. the gauge Check the IDLE fuel air mixture by slowly moving the mixture control toward the IDLE CUT OFF position and record the IDLE RPM rise Return the mixture control to FULL RICH 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 control for 800 to 1000 RPM NOTE Test gauge readings must be taken with the gauges held at the same height above the 5 of 28 LU SID97 3 P O Box 90 Mobile Alabama e 251 436 8299 ground as the fuel system component it is attached to NOTE For L TSIO 360 and TSIO 520 engine models equipped with a fixed ground adjustable exhaust bypass verify that the wastegate is adjusted according to 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 17 Compare the recorded IDLE fuel pressure IDLE RPM 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
38. the pressure altitude two thousand feet to the right to 6000 feet Point B After completing the aneroid screw adjustments torque the jam nut to 25 30 inch pounds Perform a complete ground run up and verify 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 according to Section C instructions to achieve the specified values Once the adjustments are complete remove the test equipment in accordance with Section D POST SETUP PROCEDURES Perform a flight test according to instructions in Section F FLIGHT TEST Naturally Aspirated engines with altitude compensating fuel pumps AUTO LEAN 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 A 9 of 28 ST 11 Repeat these procedures until the engine s fuel injection system meets specifications all published Table 1 Torgue Specifications for Hose End and Cap Fittings BRASS or ALUMINUM END FITTINGS CAPS STEEL HOSE END FITTINGS CAPS Hose Size Fitting Material Torque inch lbs Hose Size Fitting Material Torque inch lbs 2 Hose end fitting 50 80 2 Steel End Fitting 75 120 31x24 Brass Aluminum 31x24 3
39. uel 9 Inspect all engine control rod ends for wear transducer according to the aircraft freedom of movement proper installation and maintenance instructions If contamination security according to the aircraft is found correct the issue before manufacturer s instructions Correct any proceeding further discrepancies noted e Using the airframe boost pump flush each fuel injector line into an appropriate clean 10 Inspect the throttle and control assembly link dry container one per fuel line If the rods where used for correct installation flushed fuel is free from contamination security and wear at the attach points Correct connect to the fuel injectors using the any discrepancies noted appropriate maintenance instructions If contamination is found correct the issue 11 Ensure all engine controls operate freely before proceeding further throughout their full range of travel and are properly adjusted according to the aircraft WARNING manufacturer s instructions Use of inaccurate gauges will result in incorrect 12 Lubricate all control rod ends and fuel system adjustment of the engine fuel system possible cylinder wear due to lean operation pre ignition detonation loss of power and severe components according to the latest revision of CMI Service Bulletin SB95 2 and the Aircraft Maintenance Manual engine damage 3 Before making any checks or adjustments verify the accuracy of the aircraft tachometer manifold pre
Download Pdf Manuals
Related Search