.&IF. PLAl%-S STRVTCES, COW. A12 PLA,'.IEFLI(;HT mi'4ual SUPPLEMEKT '+bellmgton.slrpc)rt C!80 SERI.AL I.;UMBEE.S. l8052490. If~ELLWGTOK,KS 07 15.2 1XflT3fiO! :hrou$q 115053293 STC 5 4~71343AT Reg. No. Ser. No. FAA APPROVED FOR CESSNA 180J,Serial Number 18052490 180K, Serial Number 18053007 through 18053203 This Airplane Flight Manual Supplement (AFM) applies to the airplane noted above when a Continental Model 10-520-D engine and one of the following propellers and associated spinner is installed on Cessna 180 aircraft in accordance with Supplemental Type Certificate (STC) No. SAOI 345AT. Hartzell PHC-C3YF-I RFiF8468A ( )-6R Harkell PHC-C3YF-1 RFIF7691 ( ) McCauley D3A34C40119ODFA-I0 The information herein supplements or supersedes the information presented in the flight manual and on placards in the airplane. For Limitations, Procedures and Performance information not contained in the AFM Supplement, consult the flight manual or placards in the airplane. FAA APPROVED: Ronald K. Rathgeber, Manager Wichita Aircraft Certification Office Federal Aviation Administration
FAA APPROVED FOR CESSNA 180J, Serial Number 18052490 180K, Serial Number 18053001 through 18053203 Reg. No. Ser. No. This Airplane Flight Manual Supplement (AFM) applies to the airplane noted above when a Continental Model IO-520-D engine and one of the following propellers and associated spinner is installed on Cessna 180 aircraft in accordance with Supplemental Type Certificate (STC) No. SA01345AT. Hartzell PHC-C3YF-1RF/F8468A ( )-6R Hartzell PHC-C3YF-1RF/F7691 ( ) McCauley D3A34C401/90DFA-10 The information herein supplements or supersedes the information presented in the flight manual and on placards in the airplane. For Limitations, Procedures and Performance information not contained in the AFM Supplement, consult the flight manual or placards in the airplane. FAA APPROVED: Ronald K. Rathgeber, Manager Wichita Aircraft Certification Office Federal Aviation Administration Dated: DOCUMENT NUMBER C180-520-APSFM6 Page 1 of 26
AIR PLAINSSERVICES, CORP 2diELLINGTON AIRPORT C180 SERIAL NUMBERS: 18052490, WELLINGTON, KS 672 52 18053001 through I8053203 LOG OF REVISIONS Table 0-1 Rev. No. Orig 1 Pages All 2,4,6,10,14, 22,24 Oescript~on - For the indicated C180 arcraft modified IAW A I~ Plains Services, Corp. Master Drawing List Document 1018DL-APS Added fuel shutoff valve. Added placard, Rev~sed footer for document number Date March 1, ' 2002 June 28, 2005 Approved* G. M. Baker p& *For Manager, Wichita Aircraft Certification Office DOCUMENT NUMBER C180-520-APSFM6 Page 2 of 26 Rev 1, Dated: June 28,2005
SUPPLEMENT INDEX Description Page SECTION 1. GENERAL...4 SECTION 2. LIMITATIONS...8 SECTION 3. EMERGENCY PROCEDURES...13 SECTION 4. NORMAL PROCEDURES...15 SECTION 5. PERFORMANCE...20 SECTION 6. WEIGHT & BALANCE/EQUIPMENT LIST...20 SECTION 7. AIRPLANE & SYSTEMS DESCRIPTIONS...21 SECTION 8. HANDLING, SERVICE & MAINTENANCE...26 SECTION 9. SUPPLEMENTS (Optional Systems Description & Operating Procedures)...26 DOCUMENT NUMBER C180-520-APSFM6 Page 3 of 26
SECTION 1. GENERAL GENERAL NOTES. Coordinate your Owner s Manual with this supplement. This supplement supersedes the information in your Owner s Manual where the text is discussing engine operation. Limitations -- This STC DOES NOT CHANGE ANY AIRSPEED OR WEIGHT LIMITS. Cooling -- With the higher horsepowered IO-520-D engine, additional care must be taken to ensure proper cooling After maintenance, ensure the proper reinstallation of all baffling and check to see that soft baffle seals tightly seal up gaps. During preflight walk arounds, check for obstructions at the cooling air intake locations and oil cooler face. Also check for bird nest debris or other obstructions inside the cowling. On hot days, minimize taxi and runup time. During climb, maintain 95-105 KIAS, 100-120 MPH after obstacle clearance. Mixture Management -- The mixture is set to specific fuel flows with the vernier or by EGT as described in the Amplified Check List. Throughout your Owner s Manual the following deletions and substitutions apply: Carburetor...Deleted (Engine has injection system) Carburetor Heat...Substitute -- Alternate Air Carburetor Air Filter...Substitute -- Induction Air Filter Engine Primer...Substitute -- Manual Primer (Optional) Mixture Control...Substitute -- Mixture Control (With Vernier Adjustment) Full Throttle, xxxx RPM...Substitute -- Full Throttle, 2850 RPM (5 Min) Oil Filter Screen...Engine is equipped with disposable spin-on filter or oil screen) Fuel Selector Off...Substitute - Fuel Shut off Control OFF (full out) Fuel Selector On...Substitute - Fuel Shut off Control On (full in) DOCUMENT NUMBER C180-520-APSFM6 Page 4 of 26 Rev 1, Dated: June 28 2005
SECTION 1. GENERAL, (Cont d.) ENGINE Number of Engines: 1 Engine Manufacturer: Teledyne Continental Engine Model Number: IO-520-D Engine Type: Normally-aspirated, direct-drive, air-cooled, horizontally opposed, fuel-injected, six-cylinder engine with 520 cu. in. displacement. Horsepower Rating and Engine Speed: Maximum Power (5 minutes - takeoff): 300 rated at 2850 RPM. Maximum Continuous Power: 285 rated BHP at 2700 RPM. PROPELLER Propeller Manufacturer: Hartzell Propeller Model Number: PHC-C3YF-1RF/F8468A ( )-6R Number of Blades: 3 Propeller Diameter: Maximum: 80 inches Minimum: 77 inches Propeller Type: Constant speed and hydraulically actuated with a low pitch setting of 10.4 + 0.2 and a high pitch setting of 30-32 (30 inch station). Propeller Manufacturer: Hartzell Propeller Model Number: PHC-C3YF-1RF/F7691 ( ) Number of Blades: 3 Propeller Diameter: Maximum: 78 inches Minimum: 77 inches Propeller Type: Constant speed and hydraulically actuated with a low pitch setting of 11.8 + 0.1 and a high pitch setting of 30-32 (30 inch station). Propeller Manufacturer: McCauley Propeller Model Number: D3A34C401/90DFA-10 Number of Blades: 3 Propeller Diameter: Maximum: 80 inches Minimum: 78 inches Propeller Type: Constant speed and hydraulically actuated with a low pitch setting of 10.4 + 0.2 and a high pitch setting of 28.5 +.5 (30 inch station). DOCUMENT NUMBER C180-520-APSFM6 Page 5 of 26
SECTION 1. GENERAL,, (Cont d) FUEL Approved Fuel Grades (and Colors): 100LL Grade Aviation Fuel (Blue). 100 (Formerly 100/130) Grade Aviation Fuel (Green). NOTE Isopropyl alcohol and ethylene glycol monomethyl ether may be added to the fuel supply. Additive concentrations shall not exceed 1% for isopropyl alcohol or.15% for ethylene glycol monomethyl ether. OIL To ensure maximum fuel capacity when refueling and minimize cross-feeding when parked on a sloping surface, place the fuel selector value in the LEFT or RIGHT position. Oil Specification: The engine was delivered from the factory with corrosion-preventive aircraft engine oil. This oil should be drained after the first 25 hours of operation. MIL-L-6082 Aviation Grade Straight Mineral Oil: Use to replenish supply during the first 25 hours. Continental Motors Specification MHS-24 Aviation Grade Ashless Dispersant Oil: Oil conforming to Continental Motors Specification MHS-24, and all revisions or supplements thereto, must be used after first 25 hours. Refer to Continental Aircraft Engine Service Bulletin M82-8, and any superseding bulletins, revisions, or supplements thereto, for further recommendations. DOCUMENT NUMBER C180-520-APSFM6 Page 6 of 26 Rev 1, Dated: June 28 2005
SECTION 1. GENERAL,, (Cont d) Recommended Viscosity for Temperature Range: All temperatures, use multi-viscosity oil or Above 4 o C (40 o F), use SAE 50. Below 4 o C (40 o F), use SAE 30. NOTE When operating temperatures overlap, use the lighter grade of oil. Multi-viscosity oil is recommended for improved starting in cold weather. Oil Capacity: Sump: 12 Quarts Total: 13 Quarts DOCUMENT NUMBER C180-520-APSFM6 Page 7 of 26
SECTION 2. LIMITATIONS ENGINE OPERATION LIMITATIONS ENGINE This 180 is powered by one Teledyne Continental Motors Corporation model IO-520-D, fuel-injected, direct drive, air-cooled, horizontally opposed, six-cylinder, 520 cubic inch displacement, engine rated at 300 horsepower. OPERATING LIMITATIONS Take-off and Maximum Maximum Power (5 Minutes, Take-off)....300 BHP Rating Maximum Continuous Power... 285 BHP Rating Cylinder Head Temperature Maximum... 460 F Oil Temperature Minimum (Take-off)... 100 F Maximum... 240 F Oil Pressure Minimum (Idle)... 10 PSI Maximum... 100 PSI Fuel Pressure (Flow) Maximum... 19.54 PSI...(25.2 GPH) POWER PLANT INSTRUMENT MARKINGS OIL TEMPERATURE GAUGE Operation Range (Green ARC)...100 to 240 F Maximum (Red Radial)... 240 F OIL PRESSURE GAUGE Minimum (Idle) (Red Radial)... 10 PSI Operating Range (Green ARC)... 30 to 60 PSI Maximum (Red Radial)... 100 PSI DOCUMENT NUMBER C180-520-APSFM6 Page 8 of 26
SECTION 2. LIMITATIONS, (Cont d.) TACHOMETER (Hartzell Propeller) (PHC-C3YF-1RF/8468A ( )-6R) Operating Range (Green ARC)... 2200 to 2550 RPM Caution Range (Yellow ARC)... 2700 to 2850 RPM Maximum (Red Radial)...2850 RPM TACHOMETER (Hartzell Propeller) (PHC-C3YF-1RF/F7691 ( )) Operating Range (Green ARC)... 2200 to 2550 RPM Caution Range (Yellow ARC)... 2700 to 2850 RPM Maximum (Red Radial)...2850 RPM TACHOMETER (McCauley Propeller) (D3A34C401/90DFA-10) Operating Range (Green ARC)... 2200 to 2550 RPM Caution Range (Yellow ARC)... 2700 to 2850 RPM Maximum (Red Radial)...2850 RPM CYLINDER HEAD TEMPERATURE Operating Range (Green ARC)...200 F to 460 F Maximum (Red Radial)... 460 F MANIFOLD PRESSURE Operating Range (Green ARC)... 15.0 to 25.0" HG FUEL FLOW Operating Range (Green ARC)... 7 to 17.0 GPH Maximum (Red Radial) 25.2 GPH...(19.5 PSI) No other powerplant limitation changes. AUX FUEL PUMP The PRIME position of the Auxiliary Fuel Pump Switch is not to be used during flight except when failure of the engine-driven fuel pump occurs. Use the ON position of the switch for fuel vaporization problems. DOCUMENT NUMBER C180-520-APSFM6 Page 9 of 26
SECTION 2. LIMITATIONS, (Cont d.) PROPELLER SPECIFICATIONS A constant speed, three-blade propeller is optional for the Cessna 180 with an IO-520-D engine with maximum/minimum diameters and propeller blade angles at 30 inch station as described in Section 1. MANEUVER LIMITS This is a normal category airplane, Spins are prohibited. No aerobatic maneuvers are approved except those listed under Approved Maneuvers. PLACARDS (Standard Tanks) (180K, S/N 18053001 & On) Service this airplane with 100LL/100 minimum grade gasoline. Capacity 30.5 gal. (Long Range Tanks) (180K, S/N 18053001 & On) Service this airplane with 100LL/100 minimum grade gasoline. Capacity 40.0 gal. On the instrument panel above the alternate air control. ALT. AIR Adjacent to the fuel shut off control FUEL SHUT OFF DOCUMENT NUMBER C180-520-APSFM6 Page 10 of 26 Rev 1, Dated: June 28 2005
SECTION 2. LIMITATIONS, (Cont d.) Near the fuel selector valve: Near Auxiliary Pump Switch: On the Instrument Panel near Fuel Flow gauge: MIN. FUEL FLOWS AT FULL THROTTLE RPM SL 4000 8000 12000 2700 23 GPH 21 GPH 19 GPH 17 GPH 2850 24 GPH 22 GPH 20 GPH 18 GPH DOCUMENT NUMBER C180-520-APSFM6 Page 11 of 26
SECTION 2. LIMITATIONS, (Cont d.) On oil filler cap (not required if appropriate markings are on cap as received): OIL CAPACITY 12 QTS. On the Instrument Panel near the Tachometer: (For Hartzell Prop -PHC-C3YF-1RF/F7691( ) Land or Amphib) Surrounding the Fuel Pump Switch: Fuel Pump Switch PRIME (above switch) - OFF (center of switch) - ON (below Switch) NOISE LEVEL The corrected noise level of this aircraft with this engine and propeller is equivalent to that of production Cessna 180 airplanes. No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into, or out of, any airport. The above statement not withstanding, the relative noise level of the modified aircraft has been verified by and approved by the Federal Aviation Administration by comparative means to Production Cessna 180 airplanes. DOCUMENT NUMBER C180-520-APSFM6 Page 12 of 26
SECTION 3. EMERGENCY PROCEDURES Make the following changes to the procedures in your Cessna Owner s Manual. Engine Failure During Flight Below the lead-in paragraph, replace the restart check list with the list below: 1. Airspeed -- 74 KIAS, 85 MPH. 2. Fuel Selector Valve -- BOTH. 3. Mixture -- RICH. 4. Throttle -- CRACKED 1 INCH. 5. Primer -- IN and LOCKED. 6. Auxiliary Fuel Pump -- ON to obtain 4-6 GPH, then OFF. 7. Ignition Switch -- BOTH (or START if propeller is stopped). Fires DURING START ON GROUND -- Add between Steps 1 and 2. Auxiliary Fuel Pump -- OFF. ENGINE FIRE IN FLIGHT Add: Auxiliary Fuel Pump - OFF AMPLIFIED PROCEDURES Rough Engine Operation or Loss of Power The fuel injection system on this engine is considered to be non-icing. In the event that icing conditions cause the intake air filter to become clogged or iced over, the alternate air source should be manually opened. Due to the lower intake pressure available through the alternate air valve, full throttle manifold pressure can decrease approximately 1.5 inches Hg. DOCUMENT NUMBER C180-520-APSFM6 Page 13 of 26
SECTION 3. EMERGENCY PROCEDURES, (Cont d) Engine-Driven Fuel Pump Failure Failure of the engine-driven fuel pump will be evidenced by a sudden reduction in the fuel flow indication prior to a loss of power, while operating from a fuel tank containing adequate fuel. In the event of an engine-driven fuel pump failure during takeoff, immediately hold the auxiliary fuel pump switch in the PRIME position until the airplane is well clear of obstacles. Upon reaching a safe altitude and reducing the power to a cruise setting, release the PRIME side of the switch. If indication of engine driven fuel pump failure is evident place the auxiliary fuel pump switch in the ON position and land at the nearest airport and repair before proceeding flight. If an engine-driven fuel pump failure occurs during cruising flight, apply full rich mixture and hold the auxiliary fuel pump switch in the PRIME position to re-establish fuel flow. If indication of engine driven fuel pump failure is evident place the auxiliary fuel pump switch in the ON position and land at the nearest airport and repair before proceeding flight. FIRE DURING STARTING OR DURING FLIGHT Improper starting procedures during a difficult or cold start may lead to a backfire which could ignite the fuel in the induction system. If an engine fire occurs during starting turn the electric fuel pump OFF and pull the fuel shut off control up to the OFF position (full out). Continue cranking until the fire is out. Secure the aircraft and inspect for damage prior to continuing. If a fire occurs during flight turn the electric fuel pump OFF. Pull the fuel shut off control up to the OFF position (full out), and execute an immediate forced landing. Engine Icing The fuel injection system used on this engine is considered to be non-icing. Watch for signs of induction air filter ice and use alternate air as required. An unexplained loss of manifold pressure could be caused by air intake filter ice. In the event that icing conditions cause the intake air filter to become clogged or iced over, the alternate air source should be manually opened. Lean the mixture if alternate air is used continuously. Due to the lower intake pressure available through the alternate air valve or a partially blocked filter, full throttle manifold pressure can decrease approximately 1.5 in. Hg. DOCUMENT NUMBER C180-520-APSFM6 Page 14 of 26 Rev 1, Dated: June 28 2005
SECTION 4. NORMAL PROCEDURES Make the following changes to the Check List in your Cessna Owner s Manual. Starting Engine - Replace with list below. 1. Set mixture control to FULL RICH (full in). 2. Set propeller control for HIGH RPM (full in). 3. Turn master switch ON. 4. Auxiliary Fuel Pump PRIME. 5. Throttle -- ADVANCE for 8-10 GPH; then immediately RETARD to IDLE. 6. Auxiliary Fuel Pump -- OFF as throttle is retarded. 7. Turn ignition switch to BOTH. 8. Clear the propeller. 9. Ignition Switch START (Hold until engine fires, but not longer than 30 seconds.. 10. Advance throttle slowly. Note The engine should start in two to three revolutions. If it does not continue running, start again at step 3 above. If the engine still does not start, leave auxiliary fuel pump switch off, set mixture to idle cut-off, open throttle, and crank until engine fires or for approximately 15 seconds. If still unsuccessful, start again using the normal starting procedure after allowing the starter motor to cool. 11. Throttle -- ADJUST for 1000 RPM or less. 12. Oil Pressure -- CHECK. (10 PSI min. within 30 seconds at moderate temperatures). 13. Starter -- CHECK DISENGAGED (if starter were to remain engaged, ammeter would indicate full scale charge with engine running at 1000 RPM). 14. Avionics -- ON. 15. Navigation Lights and Flashing Beacon -- ON as required. BEFORE TAKEOFF - Add before runup. Auxiliary Fuel Pump -- OFF. Alternate Air - CHECK for RPM drop TAKE-OFF: Normal Take-Off - Add Power-FULL THROTTLE and 2850 RPM Substitute Alternate Air for Carburetor Heat DOCUMENT NUMBER C180-520-APSFM6 Page 15 of 26
SECTION 4. NORMAL PROCEDURES, (Cont d.) Short Field Take-Off - Add Power-FULL THROTTLE and 2850 RPM Substitute Alternate Air for Carburetor Heat ENROUTE CLIMB: Normal Climb: 25, 2850 RPM Cruise climb. Maximum Performance Climb 25, 2850 RPM Cruise climb. CRUISE: Power 15 to 25 Hg, 2200 to 2550 RPM. DESCENT - Add Auxiliary Fuel Pump -- OFF. Substitute Alternate Air for Carburetor Heat BEFORE LANDING - Add Auxiliary Fuel Pump -- OFF. Substitute Alternate Air for Carburetor Heat LANDING Balked Landing (Go-Around) Power -- Full throttle and 2850 RPM Substitute Alternate Air for Carburetor Heat After Landing Substitute Alternate Air for Carburetor Heat DOCUMENT NUMBER C180-520-APSFM6 Page 16 of 26
SECTION 4. NORMAL PROCEDURES, (Cont d.) AMPLIFIED PROCEDURES Starting Engine Proper fuel management and throttle adjustments are the determining factors in securing an easy start from your continuous-flow fuel-injection engine. The procedure outlined in the checklist should be followed closely as it is effective under nearly all operating conditions, including hot and cold weather conditions. Slight variations from this procedure may be necessary at times to compensate for extreme conditions. Conventional full rich mixture and high RPM propeller settings are used for starting; the throttle, however, should be fully closed initially. When ready to start, advance the throttle half way, place the auxiliary fuel pump switch in the PRIME position until positive fuel flow is observed on the fuel flow indicator. Then promptly turn off the auxiliary fuel pump and return the throttle to the 1/2 inch open position. Rotate the ignition switch to the START position. Return the ignition switch to the both position when the engine starts and slowly retard the throttle to 1000 RPM or less. Engine starting in hot weather or with a hot engine is sometimes hampered by vapor formation in the fuel lines. To purge the vapor, move the mixture control to full rich, open the throttle 1 1/2 inches, and prime with the auxiliary fuel pump switch in the PRIME position until the fuel flow indicator reads 8-10 gal/hr. Then turn off the fuel pump switch and engage the starter. As the flooded mixture becomes progressively leaner, reaching a combustible mixture, the engine will start. If the engine tends to die, turn the auxiliary fuel pump switch momentarily to ON at appropriate intervals until the vapor is fully cleared and the engine runs smoothly. If prolonged cranking is necessary, allow the starter motor to cool at frequent intervals, since excessive heat may damage the armature. If oil pressure is not indicated within 30 seconds in normal temperatures and 60 seconds in cold temperatures, shut off engine and investigate the cause. Takeoff For maximum engine power, the mixture should be adjusted during the initial take off roll to the fuel flow corresponding to the field elevation. The power increase is significant above 3000 feet and this procedure always should be employed for field elevations greater than 5000 feet above sea level. DOCUMENT NUMBER C180-520-APSFM6 Page 17 of 26
SECTION 4. NORMAL PROCEDURES, (Cont d.) Maximum Performance Climb The mixture should be leaned as shown by the fuel flow placard, located on the instrument panel or leaned for maximum power and smooth operation before takeoff. Engine Roughness During Climb or Cruise If engine roughness, fuel flow fluctuations or low fuel occur, turn Auxiliary Fuel Pump on and manually lean to the following fuel flow schedule placard: MIN. FUEL FLOWS AT FULL THROTTLE RPM SL 4000 8000 12000 2700 23 GPH 21 GPH 19 GPH 17 GPH 2850 24 GPH 22 GPH 20 GPH 18 GPH Leaning With A Cessna Economy Mixture Indicator (EGT) Exhaust gas temperature (EGT) as shown on the optional Cessna Economy Mixture Indicator may be used as an aid for mixture leaning in cruising flight at 75% power or less. To adjust the mixture, using this indicator, lean to establish the peak EGT as a reference point and then enrichen the mixture by a desired increment based on data in the table below. MIXTURE DESCRIPTION BEST POWER (Maximum Speed) RECOMMENDED LEAN (75% Power or Less) BEST ECONOMY (65% Power or Less) EGT Table EXHAUST GAS TEMPERATURE 100 0 F Rich of Peak EGT 50 o F Rich of Peak EGT Peak EGT DOCUMENT NUMBER C180-520-APSFM6 Page 18 of 26
SECTION 4. NORMAL PROCEDURES, (Cont d.) Continuous operation at peak EGT is authorized only at 65% power or less. This best economy mixture setting results in approximately 6% greater range accompanied by approximately 3 knots decrease in speed. Note Operation on the lean side of peak EGT is not approved. When leaning the mixture, if a distinct peak is not obtained, use the corresponding maximum EGT as a reference point for enrichening the mixture to the desired cruise setting. Any change in altitude or power will require a recheck of the EGT indication. DOCUMENT NUMBER C180-520-APSFM6 Page 19 of 26
SECTION 5. PERFORMANCE Performance with the Teledyne Continental IO-520-D Engine and any of the listed propellers equals or exceeds the performance with the original engine and propeller. SECTION 6. WEIGHT & BALANCE/EQUIPMENT LIST Refer to current weight & balance/equipment list. DOCUMENT NUMBER C180-520-APSFM6 Page 20 of 26
SECTION 7. AIRPLANE & SYSTEMS DESCRIPTIONS Engine Controls Throttle and Propeller Controls -- No Change. The mixture control, located on the lower center portion of the instrument panel, is a red knob with raised points around the circumference and is equipped with a lock button in the end of the knob. The rich position is full forward, and full aft is the idle cut-off position. For small adjustments, the control may be moved forward by rotating the knob clockwise, and aft by rotating the knob counterclockwise. For rapid or large adjustments, the control may be moved forward or aft by depressing the lock button in the end of the control, and then positioning the control as desired. Engine Instruments In Addition To The Information Provided In The Owners Handbook The Following Information Is Applicable. The Manifold Pressure / Fuel Flow gage is a dual indicating instrument displaying manifold pressure on the left side and fuel flow on the right side. The manifold pressure side is direct reading and indicates induction air pressure in inches of mercury. It has a normal operating range (green arc) of 15 to 25 inches of mercury. The fuel flow side is fuel pressure gage calibrated to indicate the approximate gallons per hour of fuel being metered to the engine. The normal operating range (green arc) is from 7 to 17 gallons per hour, the minimum (red line) is 3.5 psi, and the maximum (red line) is 19.5 psi (25.2 gallons per hour). Engine operation is monitored by the following instruments: oil pressure gauge, oil temperature gauge, cylinder head temperature gauge, tachometer, and manifold pressure/fuel flow indicator. An economy mixture (EGT) indicator is also available. Air Induction System The engine air induction system receives ram air through an intake in the lower front portion of the engine cowling. The intake is covered by an air filter which removes dust and other foreign matter from the induction air. Airflow passing through the air filter enters an air box which has a cable controlled alternate air valve. If the induction air filter should become blocked, actuating the alternate air control will open the alternate air valve and draw unfiltered air from inside the cowl area. DOCUMENT NUMBER C180-520-APSFM6 Page 21 of 26
SECTION 7. AIRPLANE & SYSTEMS DESCRIPTIONS, (Cont d) Fuel Injection System The engine is equipped with a fuel injection system. The system is comprised of an engine-driven fuel pump, fuel/air control unit, fuel manifold, fuel flow indicator, and air bleed type injector nozzles. Fuel is delivered by the engine-driven fuel pump to the fuel/air control unit on the bottom of the engine. The fuel/air control unit correctly proportions the fuel flow to the induction air flow. After passing through the control unit, induction air is delivered to the cylinders through intake manifold tubes, and metered fuel is delivered to a fuel manifold. The fuel manifold, through spring tension on a diaphragm and valve, evenly distributes the fuel to an air-bleed type injector nozzle in the intake valve chamber of each cylinder. A pressure line is also attached to the fuel manifold, and is connected to a fuel flow indicator on the instrument panel. Optional Hand Pump Priming System -- No Change. FUEL SYSTEM IN ADDITION TO THE INFORMATION PROVIDED IN THE OWNERS HANDBOOK THE FOLLOWING INFORMATION IS APPLICABLE. Fuel flows by gravity from the wing tanks to a three-position selector valve, labeled LEFT, RIGHT and BOTH. With the fuel selector in the LEFT, RIGHT, or BOTH position fuel flows through a reservoir tank, the fuel shut off valve, through a bypass in the auxiliary fuel pump (when it is not in operation), the fuel strainer and to an engine driven fuel pump. The engine driven fuel pump delivers the fuel to the fuel control unit where it is metered and directed to a manifold which distributes it to each cylinder. Vapor and excess fuel from the engine driven fuel pump and fuel control unit are returned by way of a vapor return line to the wing tank vent line NOTE Wing heavy conditions may occur during cruising flight. Wing heavy conditions can be alleviated gradually by turning the fuel selector to the heavy wing until balance is achieved then returning the fuel selector to BOTH. An additional fuel sump drain is installed in the aircraft belly aft of the firewall. This drain allows water and or contaminates to be drained from the reservoir tank. An electric fuel pump is used for normal engine starting, minor vapor purging and continued engine operation in the event of an engine driven fuel pump failure. The fuel pump is controlled with a three position toggle switch located in the lower section of the instrument panel. The center position is OFF, up is the PRIME (emergency position,) and down is ON. With the fuel pump in the ON position the pump operates at one of DOCUMENT NUMBER C180-520-APSFM6 Page 22 of 26 Rev 1, Dated: June 28 2005
SECTION 7. AIRPLANE & SYSTEMS DESCRIPTIONS, (Cont d) two flow rates that are dependent upon the setting of the throttle. With the throttle open to a cruise setting the pump operates at a high enough capacity to supply sufficient fuel flow to maintain flight with an inoperative engine driven fuel pump. When the throttle is moved toward the closed position the flow rate is automatically reduced, preventing an excessive rich mixture during those periods of reduced engine speed. NOTE With the engine pump operating and the electric fuel pump placed in the ON position an excessively rich fuel mixture will be produced unless the mixture is leaned. The electric fuel pump switch should be OFF for takeoff. Operating the electric fuel pump with the engine OFF will result in flooding of the intake manifold. If a fuel tank is completely exhausted of fuel the electric fuel pump will be needed to assist in restarting the engine. Prior to running a fuel tank dry an operational check of the electric fuel pump should be accomplished by momentarily switching the pump ON and watching for a slight rise in fuel flow. Rough Engine Operation or Loss of Power The fuel injection system on this engine is considered to be non-icing. In the event that icing conditions cause the intake air filter to become clogged or iced over, the alternate air source should be manually opened. Due to the lower intake pressure available through the alternate air valve, full throttle manifold pressure can decrease approximately 1.5 inches Hg. Engine-Driven Fuel Pump Failure Failure of the engine-driven fuel pump will be evidenced by a sudden reduction in the fuel flow indication prior to a loss of power, while operating from a fuel tank containing adequate fuel. In the event of an engine-driven fuel pump failure during takeoff, immediately hold the auxiliary fuel pump switch in the PRIME position until the airplane is well clear of obstacles. Upon reaching a safe altitude and reducing the power to a cruise setting, release the PRIME side of the switch. If indication of engine driven fuel pump failure is evident place the auxiliary fuel pump switch in the ON position and land at the nearest airport and repair before proceeding flight. If an engine-driven fuel pump failure occurs during cruising flight, apply full rich mixture and hold the auxiliary fuel pump switch in the PRIME position to re-establish fuel flow. If indication of engine driven fuel pump failure is evident place the auxiliary fuel DOCUMENT NUMBER C180-520-APSFM6 Page 23 of 26
SECTION 7. AIRPLANE & SYSTEMS DESCRIPTIONS, (Cont d) pump switch in the ON position and land at the nearest airport and repair before proceeding flight. FIRE DURING STARTING OR DURING FLIGHT Improper starting procedures during a difficult or cold start may lead to a backfire which could ignite the fuel in the induction system. If an engine fire occurs during starting turn the electric fuel pump OFF, and pull the fuel shut off control up to the OFF position (full out). Continue cranking until the fire is out. Secure the aircraft and inspect for damage prior to continuing. If a fire occurs during flight turn the electric fuel pump OFF. Pull the fuel shut off control up to the OFF position (full out) and execute an immediate forced landing. DOCUMENT NUMBER C180-520-APSFM6 Page 24 of 26 Rev 1, Dated: June 28 2005
SECTION 7. AIRPLANE & SYSTEMS DESCRIPTIONS, (Cont d) FUEL SYSTEM LEFT WING TANK RIGHT WING TANK FUEL SELECTOR VALVE FUEL RESERVOIR TANK FUEL SHUT OFF VALVE ELECTRIC FUEL PUMP FUEL STRAINER ENGINE DRIVEN FUEL PUMP FUEL CONTROL UNIT FUEL MANIFOLD VALVE CODE FUEL SUPPLY RETURN FUEL FUEL NOZZLES CHECK VALVE FUEL RETURN FUEL FLOW GAGE VENT CESSNA 180 FUEL SYSTEM SCHEMATIC DOCUMENT NUMBER C180-520-APSFM6 Page 25 of 26 Rev 1, Dated: June 28 2005
SECTION 7. AIRPLANE & SYSTEMS DESCRIPTIONS, (Cont d) OIL DIPSTICK CALIBRATIONS The oil dipstick is calibrated for both landplane and floatplane/amphibian use. Oil level readings for the floatplane/amphibian will register below the calibrations for the landplane due to the difference in attitude of the airplane. When checking the oil level, take precautions to assure that you are using the correct calibrations for your airplane. The landplane side of the dipstick is marked with four lines representing six, eight, ten and twelve quarts. The bottom line is the six quart level; the top line is the twelve quart (full) level. The floatplane/amphibian side of the dipstick has two x marks. The lower mark indicates nine quarts and the upper mark indicates twelve quarts. SECTION 8. HANDLING, SERVICE & MAINTENANCE NO CHANGE. SECTION 9. SUPPLEMENTS (Optional Systems Description & Operating Procedures) NO CHANGE. DOCUMENT NUMBER C180-520-APSFM6 Page 26 of 26