Pilot´s Operating Handbook for the Piper PA-28-140 - Cherokee Cruiser, Piper PA-28-150/160/180 - Cherokee, Piper PA-28-151 - Cherokee Warrior, Piper PA-28-161 - Cadet, Warrior II & III Equipped with TAE 125 Installation

property damage, impairment to the aircraft's operating safety or damage to it as a result of improper functioning. UPDATE AND REVISION OF THE MANUAL
WARNING: Non-compliance with these safety rules could lead to injury or even death.
CAUTION: Non-compliance with these special notes and safety measures could cause damage to the engine or to the other components.  Note: Information added for a better understanding of an instruction.
WARNING: A safe operation is only assured with an up to date POH supplement. Information about actual POH supplement issues and revisions are published in the TAE Service Bulletin TM TAE 000-0004.  Note: The TAE-No. of this POH supplement is published on the cover sheet of this supplement. Supplement POH PA-28-140/150/151/160/161/180 Page 1-2 Issue 4 Revision 3, March 2012 ENGINE Engine manufacturer:............... Thielert Aircraft Engines GmbH Engine model: ........................... TAE 125-01 or TAE 125-02-99 The TAE 125-02-99 is the successor of the 125-01. Both engine variants have the same power output and the same propeller speeds but different displacement. While the TAE 125-01 has 1689 ccm, the TAE 125-02 has 1991 ccm. Both TAE 125 engine variants are liquid cooled in-line four-stroke 4-cylinder motor with DOHC (double overhead camshaft) and are direct Diesel injection engines with common-rail technology and turbocharging. Both engine variants are controlled by a FADEC system. The propeller is driven by a built-in gearbox with mechanical vibration damping and overload release. Both engines have an electrical self starter and an alternator. Due to this specific characteristic, all of the information from the flight manual recognized by EASA are no longer valid with reference to: • carburetor and carburetor pre-heating • ignition magnetos and spark plugs, and • mixture control and priming system
WARNING The engine requires an electrical power source for operation. If the main battery and alternator fail simultaneously, the engine will only operate on A-FADEC for maximum 30 minutes on FADEC backup battery power (if installed). Therefore, it is important to pay attention to indications of alternator failure. Supplement POH PA-28-140/150/151/160/161/180 Page 1-3 Issue 4 Revision 3, March 2012 PROPELLER Manufacturer:.........................MT Propeller Entwicklung GmbH Model: ........................................................... MTV-6-A/187-129 Number of blades:.................................................................... 3 Diameter: ..........................................................1.87 m (73.6 in) Type: ......................... Variable-pitch propeller (constant speed) LIQUIDS Fuel: ........................................................JET A-1 (ASTM 1655) Alternatives: ........................................... JET A (ASTM D 1655) ..........................................Fuel No.3 (GB 6537-2006) ............................ JP-8, JP-8+100 (MIL-DTL-83133E) ................................................... Diesel (DIN EN 590) Only TAE 125-02-99 (C2.0): .............................................. TS-1 (GOST 10227-86) ...........................TS-1 (GSTU 320.00149943.011-99) Engine oil: ......................................... AeroShell Oil Diesel Ultra ...................................... AeroShell Oil Diesel 10W-40 ...............................................Shell Helix Ultra 5W-40 ...............................................Shell Helix Ultra 5W-30 Gearbox oil:.............................. Shell Spirax S6 GXME 75W-80 .......................................... Shell Spirax S4 G 75W-90 ....................... Shell Getriebeöl EP 75W-90 API GL-4 ............................................. Shell Spirax EP 75W-90 ..................................Shell Spirax GSX 75W-80 GL-4
CAUTION: Use of unapproved fuels may result in damage to the engine and fuel system components, resulting in possible engine failure.
CAUTION: Use the approved oil with exact designation only. Supplement POH PA-28-140/150/151/160/161/180 Page 1-4 Issue 4 Revision 3, March 2012 Coolant:................Water/Radiator Protection at a ratio of 50:50 Radiator Protection: ............. BASF Glysantin Protect Plus/G48 ......................................... Mobil Antifreeze Extra/G48 ........................................ESSO Antifreeze Extra/G48 ............... Comma Xstream Green - Concentrate/G48 ................................................... Zerex Glysantin G48
WARNING: The engine must not be started under any circumstances if any fluid level is too low.
CAUTION: Normally it is not necessary to fill the cooling liquid or gearbox oil between maintenance intervals. If the level is too low, please notify the TAE service department immediately.  Note: The freezing point of the coolant is -36°C (-32.8°F). Supplement POH PA-28-140/150/151/160/161/180 Page 2-1 Issue 4 Revision 3, March 2012 SECTION 2 LIMITATIONS AIRSPEED LIMITATIONS No change AIRSPEED INDICATIOR MARKINGS No change ENGINE OPERATING LIMITS Engine manufacturer:............... Thielert Aircraft Engines GmbH Engine model: .......................... TAE 125-01 or TAE 125-02-99 Take-off and Max. continuous power:.............. 99 kW (135 HP) Take-off and Max. continuous RPM:...........................2300 rpm Propeller Manufacturer: .........MT Propeller Entwicklung GmbH Propeller Model:............................................ MTV-6-A/187-129 Number of blades:.................................................................... 3 Propeller Diameter: ...........................................1.87 m (73.6 in)
WARNING The engine requires an electrical power source for operation. If the main battery and alternator fail simultaneously, the engine will only operate on A-FADEC for maximum 30 minutes on FADEC backup battery power (if installed). Therefore, it is important to pay attention to indications of alternator failure.
WARNING It is not allowed to start up the engine using external power. If starting the engine is not possible using battery power, the condition of the battery must be verified before flight. Supplement POH PA-28-140/150/151/160/161/180 Page 2-2 Issue 4 Revision 3, March 2012 Engine operating limits for take-off and continuous operation: Oil temperature Minimum engine starting temperature: ................... -32°C (-25.6°F) Minimum operating limit temperature: ........................50°C (122°F) Maximum operating limit temperature: .....................140°C (284°F) Coolant temperature Minimum engine starting temperature: ................... -32°C (-25.6°F) Minimum operating limit temperature: ........................60°C (140°F) Maximum operating limit temperature: .....................105°C (221°F) Gearbox temperature Minimum operating limit temperature: ....................... -30°C (-22°F) Maximum operating limittemperature: ......................120°C (248°F)  Note: This change of the original aircraft is certified up to an altitude of 14,000 ft.  Note: In the absence of any other explicit statements, all of the information on RPM in this supplement to the Pilot’s Operating Handbook are propeller RPM.
WARNING: It is not allowed to start the engine outside of these temperature limits.  Note: The operating limit temperature is a temperature limit below which the engine may be started, but not operated at the Take-off RPM. The warm-up RPM to be selected can be found in Section 4 of this supplement. Supplement POH PA-28-140/150/151/160/161/180 Page 2-3 Issue 4 Revision 3, March 2012 Fuel temperature Min. fuel temperature limits in the fuel tank: Table 2-1 Minimum fuel temperature limits in the fuel tank Oil pressure Minimum oil pressure:......................................1.2 bar (14.5psi) Minimum oil pressure (at Take-off power): .....2.3 bar (33.4 psi) Minimum oil pressure (in flight): ......................2.3 bar (33.4 psi) Maximum oil pressure:.......................................6.0 bar (87 psi) Maximum oil pressure (cold start < 20 sec.):....6.5 bar (94.3 psi) Maximum oil consumption: ..........................0.1 l/h (0.1 quart/h) Fuel Minimum permissible fuel temperature in the fuel tank before take-off Minimum permissible fuel temperature in the fuel tank during the flight JET A-1, JET A, Fuel No.3, JP-8, JP-8+100, TS-1 (only C2.0) -30°C (-22°F) -35°C (-31°F) Diesel greater than 0° (32°F) -5° (23°F)
WARNING: The fuel temperature of the fuel tank not used should be monitored if its later use is intended.
WARNING: The following applies to Diesel and JET fuel mixtures in the tank: As soon as the proportion of Diesel in the tank is more than 10% Diesel, the fuel temperature limits for Diesel operation must be observed. If there is uncertainty about which fuel is in the tank, the assumption should be made that it is Diesel. Supplement POH PA-28-140/150/151/160/161/180 Page 2-4 Issue 4 Revision 3, March 2012 ENGINE INSTRUMENT MARKINGS The engine data of the TAE 125 installation to be monitored are integrated in the combined engine instrument CED-125. The ranges of the individual engine monitoring parameters are shown in the following table. Table 2-2 Markings of the engine instruments Figure 2-1a AED 125 Figure 2-1b CED 125 Instrument Red range Amber range Green range Amber range Red range Tachometer [RPM] -------- -------- 0-2300 -------- > 2300 Oil pressure [bar] 0-1.2 1.2-2.3 2.3-5.2 5.2-6.0 > 6.0 [psi] 0-17.4 17.4-33.4 33.4-75.4 75.4-87.0 > 87.0 Coolant temperatur [°C] < -32 -32...+60 60-101 101-105 > 105 [°F] < -25.6 -25.6+140 140-214 214-221 > 221 Oil temperatur [°C] < -32 -32...+50 50-125 125-140 > 140 [°F] < -25.6 -25.6+122 122+257 257-284 > 284 Gearbox temperatur [°C] -------- -------- < 115 115-120 > 120 [°F] -------- -------- < 239 239-248 > 248 Load [%] -------- -------- 0-100 -------- --------  Note: If an engine reading is in the amber or red range, the caution light is activated. It only extinguishes when the "CED/AED-Test/ Confirm" button is pressed. If this button is pressed longer than a second, a selftest of the instrument is initiated. • • 105 % RPM 1/ min bar 6 60 °C °C 105 50 °C 140 120 100 2300 OP OT LOAD GT CT 2.3 75 -30 75 -30 30 22 -5 -5 FUEL TEMP RIGHT °C FUEL TEMP LEFT °C V VOLT FUEL FLOW gal/h WATER LEVEL 60 A AMPERE Supplement POH PA-28-140/150/151/160/161/180 Page 2-5 Issue 4 Revision 3, March 2012 WEIGHT LIMITS PA 28-140 (Normal category): Serial no. 28-20001 to 28-20939: Maximum Ramp Weight: ..................... 886 kg (1952 lbs) Maximum Takeoff Weight: ................... 885 kg (1950 lbs) Maximum Landing Weight ................... 885 kg (1950 lbs) Serial no. 28-20001 to 28-20939, with Piper Kit 756962 in- stalled and, Serial no. 28-20940 and up: Maximum Ramp Weight: ..................... 977 kg (2152 lbs) Maximum Takeoff Weight: ................... 976 kg (2150 lbs) Maximum Landing Weight ................... 976 kg (2150 lbs) PA 28-140 (utility category): Maximum Ramp Weight: ..................... 886 kg (1953 lbs) Maximum Takeoff Weight: ................... 885 kg (1950 lbs) Maximum Landing Weight ................... 885 kg (1950 lbs) PA 28-150 (normal category): Maximum Ramp Weight: ..................... 977 kg (2152 lbs) Maximum Takeoff Weight: ................... 976 kg (2150 lbs) Maximum Landing Weight ................... 976 kg (2150 lbs) PA 28-151 (normal category): Maximum Ramp Weight: .................. 1,056 kg (2327 lbs) Maximum Takeoff Weight: ................ 1,055 kg (2325 lbs) Maximum Landing Weight ................ 1,055 kg (2325 lbs) PA 28-151 (utility category): Maximum Ramp Weight: ..................... 886 kg (1953 lbs) Maximum Takeoff Weight: ................... 885 kg (1950 lbs) Maximum Landing Weight ................... 885 kg (1950 lbs) Supplement POH PA-28-140/150/151/160/161/180 Page 2-6 Issue 4 Revision 3, March 2012 PA 28-160 (normal category, reduced weight): Maximum Ramp Weight: ..................... 977 kg (2152 lbs) Maximum Takeoff Weight: ................... 976 kg (2150 lbs) Maximum Landing Weight ................... 976 kg (2150 lbs) PA 28-161 (normal category, Warrior III reduced weight): Maximum Ramp Weight: .................. 1,056 kg (2327 lbs) Maximum Takeoff Weight: ................ 1,055 kg (2325 lbs) Maximum Landing Weight ................ 1,055 kg (2325 lbs) PA 28-161 (utility category): Maximum Ramp Weight: ..................... 917 kg (2022 lbs) Maximum Takeoff Weight: ................... 916 kg (2020 lbs) Maximum Landing Weight ................... 916 kg (2020 lbs) PA 28-180 (normal category, reduced weight): Maximum Ramp Weight: ..................... 977 kg (2152 lbs) Maximum Takeoff Weight: ................... 976 kg (2150 lbs) Maximum Landing Weight ................... 976 kg (2150 lbs) PA 28-180 (utility category): Maximum Ramp Weight: ..................... 886 kg (1953 lbs) Maximum Takeoff Weight: ................... 885 kg (1950 lbs) Maximum Landing Weight ................... 885 kg (1950 lbs) CENTER OF GRAVITY LIMITS No change, note the maximum weight Supplement POH PA-28-140/150/151/160/161/180 Page 2-7 Issue 4 Revision 3, March 2012 MANEUVER LIMITS Normal Category: No change Utility Category: Intentionally initiating spins is prohibited FLIGHT LOAD FACTORS No change KINDS OF OPERATION EQUIPMENT LIST No change
CAUTION: Intentionally initiating negative G maneuvers is prohibited!  Note: The load factor limits for the engine must also be observed. Refer to the Operation & Maintenance Manual for the engine.
CAUTION: Avoid extended negative g-loads duration. Extended negative g-loads can cause propeller control and engine problems. Supplement POH PA-28-140/150/151/160/161/180 Page 2-8 Issue 4 Revision 3, March 2012 PERMISSIBLE FUEL GRADES Fuel: .........................................................JET A-1(ASTM 1655) Alternative: ............................................. JET A (ASTM D 1655) ..........................................Fuel No.3 (GB 6537-2006) ..............................................JP-8 (MIL-DTL-83133E) ......................................JP-8+100 (MIL-DTL-83133E) ................................................... Diesel (DIN EN 590) Only TAE 125-02-99 (C2.0): .............................................. TS-1 (GOST 10227-86) ...........................TS-1 (GSTU 320.00149943.011-99) MAXIMUM FUEL QUANTITIES Due to the higher specific density of Kerosene and Diesel in comparison to Aviation Gasoline (AVGAS) with the TAE 125 installation the permissible tank capacity has been reduced 2 standard tanks: ....................................each 85.2 l (22.5 US gal) Total capacity: ..................................................170.4 l (45 US gal) Total usable fuel: ..............................................162.8 l (43 US gal) Total unusable fuel: ................................................7.6 l (2 US gal)
CAUTION: Using non-approved fuels and additives can lead to dangerous engine malfunctions.
CAUTION: To prevent air from penetrating into the fuel system avoid flying the tanks dry. As soon as the "Low Level" Warning Light illuminates, switch to a tank with sufficient fuel or land.  Note The tanks are equipped with a Low Fuel Warning. If the fuel level is below 10 l (2.6 US gal), the "Fuel L" or "Fuel R" Warning Light illuminates respectively. Supplement POH PA-28-140/150/151/160/161/180 Page 2-9 Issue 4 Revision 3, March 2012 PERMISSIBLE OIL TYPES Engine oil: ......................................... AeroShell Oil Diesel Ultra ...................................... AeroShell Oil Diesel 10W-40 ...............................................Shell Helix Ultra 5W-40 ...............................................Shell Helix Ultra 5W-30 Gearbox oil:.............................. Shell Spirax S6 GXME 75W-80 .......................................... Shell Spirax S4 G 75W-90 ....................... Shell Getriebeöl EP 75W-90 API GL-4 ............................................. Shell Spirax EP 75W-90 ..................................Shell Spirax GSX 75W-80 GL-4 PERMISSIBLE COOLING LIQUID Coolant:................Water/Radiator Protection at a ratio of 50:50 Radiator Protection: ............. BASF Glysantin Protect Plus/G48 ......................................... Mobil Antifreeze Extra/G48 ........................................ESSO Antifreeze Extra/G48 ............... Comma Xstream Green - Concentrate/G48 ................................................... Zerex Glysantin G48
CAUTION: Use the approved oil with exact designation only.
WARNING The engine must not be started under any circumstances if any fluid level is too low. Supplement POH PA-28-140/150/151/160/161/180 Page 2-10 Issue 4 Revision 3, March 2012 PLACARDS Near the fuel tank caps: JET A-1 / Diesel Fuel CAP. 81.0 LITER (21.5 U.S. GAL.) USABLE TO BOTTOM OF FILLER INDICATOR TAB On the oil funnel or at the flap of the engine cowling: "Oil, see POH supplement" If installed, at the flap of the engine cowling to the External Power Receptacle: „ATTENTION 12 V DC OBSERVE CORRECT POLARITY“ OR „ATTENTION 24 V DC OBSERVE CORRECT POLARITY“ Supplement POH PA-28-140/150/151/160/161/180 Page 3-1 Issue 4 Revision 3, June 2011 SECTION 3 EMERGENCY PROCEDURES INDEX OF CHECKLISTS GENERAL........................................................................................3-2 EMERGENCY PROCEDURES CHECK LIST .................................3-2 ENGINE FIRE WHEN STARTING ENGINE ON GROUND.............3-2 ENGINE MALFUNCTION DURING TAKE-OFF (ON GROUND) ..............................................3-2 ENGINE MALFUNCTION IMMEDIATELY AFTER TAKE-OFF...........................................................................3-3 LOSS OF ENGINE POWER DURING FLIGHT ...............................3-3 EMERGENCY LANDING WITH ENGINE OUT ...............................3-4 ENGINE FIRE IN FLIGHT................................................................3-4 ELECTRICAL FIRE IN FLIGHT .......................................................3-5 LOSS OF OIL PRESSURE ..............................................................3-6 LOSS OF FUEL PRESSURE...........................................................3-6 HIGH OIL TEMPERATURE .............................................................3-7 HIGH COOLANT TEMPERATURE..................................................3-7 “Water Level“ LIGHT ILLUMINATES ...............................................3-7 HIGH GEARBOX TEMPERATURE .................................................3-7 ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS.............................................................................3-8 ALTERNATOR WARNING LIGHT ILLUMINATES DURING NORMAL ENGINE OPERATION ................................................................... 3-10 AMMETER SHOWS BATTERY DISCHARGE DURING NORMAL ENGINE OPERATION FOR MORE THAN 5 MINUTES .................................................................................... 3-11 TOTAL ELECTRICAL FAILURE ....................................................3-12 FADEC WARNING LIGHTS ILLUMINATE .................................... 3-13 ABNORMAL ENGINE BEHAVIOR................................................. 3-15 SPIN RECOVERY..........................................................................3-15 OPEN DOOR ................................................................................. 3-15 ROUGH ENGINE OPERATION..................................................... 3-16 ENGINE MALFUNCTION DURING FLIGHT ............................ 3-16 PROPELLER RPM TOO HIGH ................................................ 3-16 FLUCTUATIONS IN PROPELLER RPM.................................. 3-17 ENGINE SHUT DOWN IN FLIGHT................................................ 3-17 RESTART ATER ENGINE FAILURE............................................. 3-18 CARBURETOR ICING ................................................................... 3-18 FLIGHT IN ICING CONDITIONS ................................................... 3-19 Supplement POH PA-28-140/150/151/160/161/180 Page 3-2 Issue 4 Revision 3, June 2011 GENERAL In addition to the original AFM/POH, the following applies: EMERGENCY PROCEDURES CHECK LIST ENGINE FIRE WHEN STARTING ENGINE ON GROUND (1) Engine Master - OFF (2) Fuel Selector - CLOSED (3) Electrical Fuel Pump - OFF (4) Switch “Battery“ - OFF (5) Extinguish the flames with a fire extinguisher, wool blankets or sand. (6) Examine the fire damages throughly and repair or replace the damaged parts before the next flight. ENGINE MALFUNCTION DURING TAKE-OFF (ON GROUND) (1) Thrust Lever - IDLE (2) Brakes - APPLY (3) Wing flaps (if extended) - RETRACT to increase the braking effect on the runway. (4) Engine Master - OFF (5) Circuit Breaker or Switch “Alternator“, Switches “Main Bus“ and “Battery“ - OFF
WARNING: Due to an engine shut-off or a FADEC diagnosed failure there might be a loss propeller valve currency which leads in a low pitch setting of the propeller. This might result in propeller overspeed. Airspeeds below 100 KIAS/ 115 mph are suitable to avoid propeller overspeed in failure case. If the propeller speed control fails, climb flights can be performed at 65 KIAS/ 75 mph and a powersetting of 100%. Supplement POH PA-28-140/150/151/160/161/180 Page 3-3 Issue 4 Revision 3, June 2011 ENGINE MALFUNCTION IMMEDIATELY AFTER TAKE-OFF - Take-off abort - If there is an engine malfunction after take-off, at first lower the nose to keep the airspeed and attain gliding attitude. In most cases, landing should be executed straight ahead with only small corrections in direction to avoid obstacles. (1) Airspeed.............................. 73 KIAS (wing flaps retracted) ............................65 KIAS (wing flaps extended) (2) Fuel Selector - CLOSED (3) Engine Master - OFF (4) Wing flaps - as required (40° is recommended) (5) Circuit Breaker or Switch "Alternator", Switches "Main Bus" and "Battery" - OFF LOSS OF ENGINE POWER DURING FLIGHT (1) Push Thrust Lever full forward (Take-off position). (2) Fuel Selector to tank with sufficient fuel quantity and temperature (3) Electrical Fuel Pump - ON (4) Establish Best Glide Speed (5) Check engine parameters (FADEC lights, oil pressure and temperature, fuel quantity) If normal engine performance is not achieved, the pilot should: i) Land as soon as possible. ii) Be prepared for an emergency landing iii) Expect an engine failure.
WARNING: Altitude and airspeed are seldom sufficient for a return to the airfield with a 180° turn while gliding.
WARNING: The high-pressure pump must be checked before the next flight. Supplement POH PA-28-140/150/151/160/161/180 Page 3-4 Issue 4 Revision 3, June 2011 EMERGENCY LANDING WITH ENGINE OUT If all attempts to restart the engine fail and an emergency landing is imminent, select suitable site and proceed as follows: (1) When field can easily be reached slow down to 63 KIAS for shortest landing. (2) Fuel Selector - CLOSED (3) Engine Master - OFF (4) Flaps - as required (40° is recommended) (5) Circuit Breaker or Switch “Alternator“, Switches “Main Bus“ and Battery“ - OFF (6) Seat belts and harnesses - TIGHT (7) Touch-down-slightly nose up attitude (8) Brake firmly ENGINE FIRE IN FLIGHT (1) Engine Master - OFF (2) Fuel Selector - CLOSED (3) Selector an appropriate airspeed to avoid engine overspeed (4) Electrical Fuel Pump - OFF (if in use) (5) Switch “Main Bus“ - OFF (6) Cabin heat and defroster - OFF (7) Perform emergency landing (as described in the procedure “Emergency Landing With Engine Out“)  Note: Gliding Distance. Refer to Figure “Glide range“ in Section 5 of this Supplement to the Pilot’s Operating Handbook. Supplement POH PA-28-140/150/151/160/161/180 Page 3-5 Issue 4 Revision 3, June 2011 ELECTRICAL FIRE IN FLIGHT The first signs of an electrical fire is usually the odour of burning or smouldering insulation. Proceed as follows: (1) Switch “Main Bus“ - OFF (2) Switch “Avionics“ - OFF (3) Vents - OPEN (4) Cabin Heat - OFF (5) Fire Extinguisher – Activate (if available) If there is evidence of continued electrical fire, consider turning off battery and alternator. (6) Check Circuit Breaker, do not reset if open (7) Switch “Main Bus“ - ON (8) Switch “Avionics“ - ON
WARNING: After the fire extinguisher has been used, make sure that the fire is extinguished before exterior air is used to remove smoke from the cabin.
WARNING: If the FADEC Backup battery is not installed this will shut down the engine and require an emergency landing. The engine has been demonstrated to continue operating for a maximum of 30 minutes when powered by the FADEC Backup battery only.
WARNING: Turn on only electrical equipment required to continue flight depending on the situation and land as soon as practical. Do only switch ON one at a time, with delay after each. Supplement POH PA-28-140/150/151/160/161/180 Page 3-6 Issue 4 Revision 3, June 2011 LOSS OF OIL PRESSURE (<2.3 bar IN CRUISE (amber range) OR <1.2 bar AT IDLE (red range)) (1) Reduce power as quickly as possible (2) Check oil temperature: If the oil temperature is high or near operating limits, i) Land as soon as possible. ii) Be prepared for an emergency landing. iii) Expect an engine failure. (1) Increase airspeed by decreasing the pitch angle (2) Reduce power, if the engine temperatures approach the red area LOSS OF FUEL PRESSURE Not applicable for TAE 125 installation  Note: During warm-weather operation or longer climbouts at low airspeed engine temperatures could rise into the amber range and trigger the caution light. This warning allows the pilot to avoid overheating of the engine as follows: Supplement POH PA-28-140/150/151/160/161/180 Page 3-7 Issue 4 Revision 3, June 2011 HIGH OIL TEMPERATURE (“OT“ in red range) (1) Increase airspeed and reduce power as quickly as possible (2) Check the oil pressure: if the oil pressure is lower than normal (<2.3 bar at cruise or <1.2 bar at idle), i) Land as soon as possible. ii) Be prepared for an emergency landing. iii) Expect an engine failure. (3) If the oil pressure is in normal range: i) Land as soon as practical. HIGH COOLANT TEMPERATURE (“CT“ in red range) (1) Increase airspeed and reduce power as quickly as possible (2) Cabin Heat and Shut Off Cabin Heat - COLD, resp. CLOSED (3) If this reduces the coolant temperature to within the normal operating range quickly, continue to fly normally and observe coolant temperature, Cabin Heat as required (4) As far as this does not cause the coolant temperature to drop i) Land as soon as practical. ii) Be prepared for an emergency landing. iii) Expect an engine failure. “Water Level“ LIGHT ILLUMINATES (1) Increase airspeed and reduce power as quickly as possible (2) Coolant temperature “CT“ - CHECK and OBSERVE (3) Oil temperature “OT“ - CHECK and OBSERVE (4) As far as coolant temperature and/or oil temperature are rising into amber or red range, i) Land as soon as practical. ii) Be prepared for an emergency landing. iii) Expect an engine failure. HIGH GEARBOX TEMPERATURE (“GT“ in red range) (1) Reduce power to 55% - 75% as quickly as possible (2) Land as soon as practical Supplement POH PA-28-140/150/151/160/161/180 Page 3-8 Issue 4 Revision 3, June 2011 ELECTRICAL POWER SUPPLY SYSTEM MALFUNCTIONS (continued next page)
CAUTION: The TAE 125 requires an electrical power source for its operation. If the alternator fails, continued engine operation time is dependant upon the remaining capacity of the main batter, the FADEC backup battery (if installed) and equipment powered. The engine has been demonstrated to continue operating for approximately 120 minutes based upon the following assumptions: Equipment Time switched on in [min] in [%] NAV/COM 1 receiving ON 120 100 NAV/COM 1 transmitting ON 12 10 NAV/COM 2 receiving OFF 0 0 NAV/COM 2 transmitting OFF 0 0 GPS ON 60 50 Transponder ON 120 100 Fuel Pump OFF 0 0 AED-125 ON 120 100 Battery Ignition Relay ON 120 100 CED-125 ON 120 100 Landing Light ON 12 10 Flood Light ON 1.2 1.0 Pilot Heat ON 24 20 Wing Flaps ON 1.2 1.0 Interior Lightning OFF 0 0 Navigation Lights OFF 0 0 Beacon Lights OFF 0 0 Strobe Lights OFF 0 0 ADF OFF 0 0 Intercom OFF 0 0 Turn Indicator OFF 0 0 Engine control system ON 120 100 Supplement POH PA-28-140/150/151/160/161/180 Page 3-9 Issue 4 Revision 3, June 2011
CAUTION: This table only gives a reference point. The pilot should turn off all nonessential items and supply power only to equipment which is absolutely necessary for continued flight depending upon the situation. If deviated from this recommendation, the remaining engine operating time may change.
WARNING: If the power supply from both alternator and main battery is interrupted, continued engine operation is dependant on the remaining capacity of the FADEC backup battery (if installed). The engine has been demonstrated to continue operating for 30 minutes when powered by the FADEC backup battery only. In this case, all electrical equipment will not operate: - land immidiately - do not switch the „FORCE-B“ switch, this will shut down the engine Supplement POH PA-28-140/150/151/160/161/180 Page 3-10 Issue 4 Revision 3, June 2011 ALTERNATOR WARNING LIGHT ILLUMINATES DURING NORMAL ENGINE OPERATION (1) Ammeter - CHECK (2) Circuit Breaker or Switch “Alternator“ CHECK - ON (3) Battery Switch CHECK - ON (4) Electrical load - REDUCE IMMEDIATELY depending upon operation as follows: i) NAV/ COM 2 – OFF ii) Fuel Pump – OFF iii) Landing Light – OFF (use as required for landing) iv) Taxi Light – OFF v) Strobe Light – OFF vi) Nav Lights – OFF vii) Beacon – OFF viii)Interior Lights – OFF ix) Intercom – OFF x) Pitot Heat – OFF (use as required) xi) Autopilot – OFF xii) Non-essential equipment – OFF (5) The pilot should i) Land as soon as practical. ii) Be prepared for an emergency landing. iii) Expect an engine failure.
CAUTION: If the FADEC was supplied by battery only until this point, the RPM can momentarily drop, when the alternator will be switched on. In any case: leave the alternator switched ON! Supplement POH PA-28-140/150/151/160/161/180 Page 3-11 Issue 4 Revision 3, June 2011 AMMETER SHOWS BATTERY DISCHARGE DURING NORMAL ENGINE OPERATION FOR MORE THAN 5 MINUTES (1) Circuit Breaker or Switch “Alternator“ CHECK - ON (2) Battery Switch CHECK - ON (3) Electrical load - REDUCE IMMEDIATELYdepending upon operation as follows: i) NAV/ COM 2 – OFF ii) Fuel Pump – OFF iii) Landing Light – OFF (use as required for landing) iv) Taxi Light – OFF v) Strobe Light – OFF vi) Nav Lights – OFF vii) Beacon – OFF viii)Interior Lights – OFF ix) Intercom – OFF x) Pitot Heat – OFF (use as required) xi) Autopilot – OFF xii) Non-essential equipment – OFF (4) The pilot should, i) Land as soon as practical. ii) Be prepared for an emergency landing. iii) Expect an engine failure.  Note: When the AED Ammeter indication is illuminated at the outer left side and the voltage indication is decreasing simultaneously, the battery is being discharged.
CAUTION: If the FADEC was supplied by battery only until this point, the RPM can momentarily drop, when the alternator will be switched on. In any case: leave the alternator switched ON! Supplement POH PA-28-140/150/151/160/161/180 Page 3-12 Issue 4 Revision 3, June 2011 TOTAL ELECTRICAL FAILURE (all equipment inoperative, except engine) (1) Circuit Breaker or Switch “Alternator” CHECK – ON (2) Battery Switch CHECK – ON (3) Land as soon as possible i) Be prepared for an emergency landing ii) Expect an engine failure
WARNING: If the power supply from both alternator and main battery is interrupted simultaneously, continued engine operation is dependant on the remaining capacity of the FADEC backup battery. The engine has been demonstrated to continue operating for 30 minutes when powered by the FADEC backup battery only. In this case, all other electrical equipment will not operate.
WARNING: If the aircraft was operated on battery power only until this point (alternator warning light illuminated), the remaining engine operating time may be less than 30 minutes.
WARNING: Do not active the FORCE-B switch, this will shut down the engine. Supplement POH PA-28-140/150/151/160/161/180 Page 3-13 Issue 4 Revision 3, June 2011 FADEC WARNING LIGHTS ILLUMINATE One FADEC Light is flashing (1) Press FADEC-Testknob at least 2 seconds (2) FADEC Light extinguished (LOW category warning): a) Continue flight normally b) Inform service center after landing (3) FADEC Light steady illuminated (HIGH category warning): a) Observe the other FADEC light b) Land as soon as practical c) Select an airspeed to avoid engine overspeed d) Inform service center after landing (continued next page)  Note: The FADEC consists of two components that are independent of each other: FADEC A and FADEC B. In case of malfunctions in the active FADEC, it automatically switches to the other. Supplement POH PA-28-140/150/151/160/161/180 Page 3-14 Issue 4 Revision 3, June 2011 Both FADEC Lights are flashing (1) Press FADEC-Testknob at least 2 seconds (2) FADEC Light extinguished (LOW category warning): a) Continue flight normally b) Inform service center after landing (3) FADEC Light steady illuminated (HIGH category warning): a) Check the available engine power b) Expect engine failure c) Flight can be continued, however the pilot should: i) Select an appropriate airspeed to avoid engine overspeed. ii) Land as soon as possible. iii) Be prepared for an emergency landing. d) Inform service center after landing. (4) In case a tank was flown dry, proceed at the first signs of insufficient fuel feed as follows: a) Immediately switch the Fuel Selector to tank with sufficient fuel quantity. b) Electrical Fuel Pump - ON c) Select an appropriate airspeed to avoid engine overspeed. d) Check the engine (engine parameters, airspeed / altitude change, whether the engine responds to changes in the Thrust Lever position). e) If the engine acts normally, continue the flight and land as soon as practical.  Note: The load display may not correspond to the actual value.
WARNING: The high-pressure pump must be checked before the next flight Supplement POH PA-28-140/150/151/160/161/180 Page 3-15 Issue 4 Revision 3, June 2011 ABNORMAL ENGINE BEHAVIOR If the engine acts abnormally during flight and the system does not automatically switch to the B-FADEC, it is possible to switch to the B-FADEC manually. (1) Select an appropriate airspeed to avoid engine overspeed (2) "Force B" switch - SELECT manually to B-FADEC (3) Flight may be continued, but the pilot should: i) Select an appropriate airspeed to avoid engine overspeed. ii) Land as soon as practical iii) Be prepared for an emergency landing SPIN RECOVERY No change for the TAE 125 installation OPEN DOOR No change for the TAE 125 installation
WARNING: It is only possible to switch from the automatic position to B-FADEC (A-FADEC is active in normal operation, B-FADEC is active in case of malfunction). This only becomes necessary when no automatic switching occurred in case of abnormal engine behavior.
WARNING: When opearting on FADEC backup battery only, the "Force B" switch must not be activated. This will shutdown the engine. Supplement POH PA-28-140/150/151/160/161/180 Page 3-16 Issue 4 Revision 3, June 2011 ROUGH ENGINE OPERATION ENGINE MALFUNCTION DURING FLIGHT In case that one tank was flown dry, at the first signs of insufficient fuel feed proceed as follows: (1) Immediately switch the Fuel Selector to tank with sufficient fuel quantity (2) Electrical Fuel Pump - ON (3) Check the engine (engine parameters, airspeed/altitude change, whether the engine responds to changes in the Thrust Lever position) (4) If the engine acts normally, continue the flight and land as soon as practical. PROPELLER RPM TOO HIGH with propeller RPM between 2,300 and 2,400 for more than 20 seconds or over 2,400: (1) Reduce power (2) Reduce airspeed below 100 KIAS or as appropriate to prevent propeller overspeed (3) Set power as required to maintain altitude and land as soon as practical.  Note: Flying a tank dry activates both FADEC lights flashing.
WARNING: The high-pressure pump must be checked before the next flight.  Note: If the propeller speed control fails, climb flights can be performed at 65 KIAS/ 75 mph and a power setting of 100%. In case of overspeed the FADEC will reduce the engine power at higher airspeeds to avoid propeller speeds above 2500 rpm Supplement POH PA-28-140/150/151/160/161/180 Page 3-17 Issue 4 Revision 3, June 2011 FLUCTUATIONS IN PROPELLER RPM If the propeller RPM fluctuates by more than +/- 100 RPM with a constant Thrust Lever position: (1) Change the power setting and attempt to find a setting where the propeller RPM no longer fluctuates (2) If this does not work, set the maximum power at an airspeed <100 KIAS until the propeller speed stabilizes (3) If the problem is resolved, continue the flight (4) If the problem continues, reduce power to 55% - 75& or select a power level where the propeller RPM fluctuations are minimum. Fly at an airspeed below 110 KIAS and land as soon as practical ENGINE SHUT DOWN IN FLIGHT If it is necessary to shut down the engine in flight (for instance, abnormal engine behavior does not allow continued flight or there is a fuel leak, etc.), proceed as follows: (1) Select an appropriate airspeed to avoid engine overspeed (2) Engine Master - OFF (3) Fuel Selector - CLOSED (4) Electrical Fuel Pump - OFF (if in use). (5) If the propeller also has to be stopped (for instance, due to excessive vibrations) i) Reduce airspeed to below 55 KIAS. ii) when the propeller is stopped, continue to glide at 73 KIAS. Supplement POH PA-28-140/150/151/160/161/180 Page 3-18 Issue 4 Revision 3, June 2011 RESTART AFTER ENGINE FAILURE Whilst gliding to a suitable landing strip, try to determine the reason for the engine malfunction. If time permits and a restart of the engine is possible, proceed as follows: (1) Airspeed between 65 and 85 KIAS (maximal 100 KIAS) (2) Glide below 13000 ft (3) Fuel Selector to tank with sufficient fuel quantity and temperature (4) Electrical Fuel Pump - ON (5) Thrust Lever - IDLE (6) Engine Master OFF, than ON (if the propeller does not turn, then additionally “Starter“ ON) (7) Check the engine power: Thrust Lever 100%, engine parameters, check altitude and airspeed CARBURETOR ICING Not applicable for the TAE installation.  Note: The propeller will normally continue to turn as long as the airspeed is above 65 KIAS. Should the propeller stop at an airspeed of 65 KIAS or more, the reason for this should be found out before attempting a restart. If it is obvious that the engine or propeller is jammed, do not use the starter  Note: If the Engine Master is in position OFF, the load display shows 0% even if the propeller is turning. Supplement POH PA-28-140/150/151/160/161/180 Page 3-19 Issue 4 Revision 3, June 2011 FLIGHT IN ICING CONDITIONS In case of inadvertent icing encounter proceed as follows: (1) Pitot Heat switch - ON (if installed) (2) Turn back or change the altitude to obtain an outside air temperature that is less conducive to icing. (3) Cabin heat control full and open defroster outlets to obtain maximum windshield defroster airflow. Adjust cabin air control to get maximum defroster heat and airflow. (4) Advance the Thrust Lever to increase the propeller speed and keep ice accumulation on the propeller blades as low as possible. (5) Watch for signs of air filter icing and pull the "Alternate Air Door" control if necessary. An unexplained loss in engine power could be caused by ice blocking the air intake filter. Opening the "Alternate Air Door" allows preheated air from the engine compartment to be aspirated. (6) Plan a landing at the nearest airfield. With an extremely rapid ice build up, select a suitable "off airfield" landing side. (7) With an ice accumulation of 0.5 cm or more on the wing leading edges, a significantly higher stall speed should be expected. (8) Leave wing flaps retracted. With a severe ice build up on the horizontal tail, the change in wing wake airflow direction caused by wing flap extension could result in a loss of elevator effectiveness. (9) Open left window, if practical, scrape ice from a portion of the windshield for visibility in the landing approach. (10) Perform a landing approach using a forward slip, if necessary, for improved visibility. (11) Approach at increased airspeed depending upon the amount of the accumulation. (12) Perform a landing in level attitude.
WARNING: Flight into known icing conditions is prohibited. Supplement POH PA-28-140/150/151/160/161/180 Page 3-20 Issue 4 Revision 3, June 2011 This page is intentionally left blank Supplement POH PA-28-140/150/151/160/161/180 Page 4-1 Issue 4 Revision 2, March 2012 SECTION 4 NORMAL PROCEDURES PREFLIGHT INSPECTION PREPARATION Airplane status ................................ airworthy, papers on board Logbook ....CHECK refuelling with allowed fuel (see section 2) Weather ........................................................................suitable Baggage ................................................. weighed, stowed, tied Weight and CG ........................................................within limits Navigation ..................................................................... planned Charts and navigation equipment ................................on board Performance and range .............................. computed and safe Supplement POH PA-28-140/150/151/160/161/180 Page 4-2 Issue 4 Revision 2, March 2012 COCKPIT Control wheel .........................................................release belts Avionics...............................................................................OFF Parking brake ..................................................................... SET Electric switches .................................................................OFF Engine Master switch..........................................................OFF Shut-off Cabin Heat .........................................................OPEN Switches "Battery" and "Main Bus“ .......................................ON Fuel quantity gauges..................................................... CHECK Fuel Temperature ......................................................... CHECK "Water level" Light on AED ........................... CHECK, that OFF Annunciator panel ......................................................... CHECK Switches "Battery" and "Main Bus“ .....................................OFF Flight Controls............................................................... CHECK Flaps ............................................................................. CHECK Trim.......................................................CHECK, set NEUTRAL Pitot drain..........................................................DRAIN, CLOSE Static drain ........................................................DRAIN, CLOSE Windows ......................................................... CHECK, CLEAN Tow bar ........................................................................... STOW Baggage...................................................................... SECURE Baggage door ...............................................CLOSE, SECURE
WARNING: When turning on the battery switch, using an external power source, or pulling the propeller through by hand, treat the propeller as if the Engine Master was ON. Supplement POH PA-28-140/150/151/160/161/180 Page 4-3 Issue 4 Revision 2, March 2012 RIGHT WING Wing........................................................free of ice, snow, frost Control surfaces................................... CHECK for interference ................................................................free of ice, snow, frost Hinges.................................................. CHECK for interference Static wicks ................................................................... CHECK Wing tip and lights......................................................... CHECK Fuel tank .............................................. CHECK supply visually, ........................fuel level not above bottom of filler indicator tab ................................................................................secure caps Fuel tank sump ................................. DRAIN, CHECK for water ...................................sediment and proper fuel (see section 2) Fuel vent ........................................................................ CLEAR Tie down and chock ................................................... REMOVE Main gear strut ............. Proper Inflation (114 ± 6 mm / 4.50 in.) Tire................................................................................ CHECK Brake block and discs ................................................... CHECK Fresh air inlet ................................................................. CLEAR NOSE Oil.......................................................................... CHECK level Oil dipstick................................................................... SECURE Fuel and oil .....................................................CHECK for leaks Cowling ....................................................................... SECURE Windshield .................................................................... CHECK Propeller and spinner.................................................... CHECK Air inlets ..........................................UNDAMAGED and CLEAR Landing light.................................................................. CHECK Gearbox oil............................................................ CHECK level Nose chock ................................................................ REMOVE Nose gear strut .............. Proper Inflation (83 ± 6 mm / 3.25 in.) Nose wheel tire ............................................................. CHECK Fuel strainer ....................................................................DRAIN ....... CHECK for watersediment and proper fuel (see section 2) Supplement POH PA-28-140/150/151/160/161/180 Page 4-4 Issue 4 Revision 2, March 2012 LEFT WING Wing........................................................free of ice, snow, frost Fresh air inlet ................................................................. CLEAR Main gear strut ............. Proper Inflation (114 ± 6 mm / 4.50 in.) Tire................................................................................ CHECK Brake block and discs ................................................... CHECK Fuel tank .............................................. CHECK supply visually, ........................fuel level not above bottom of filler indicator tab ................................................................................secure caps Fuel tank sump ................................ DRAIN, CHECK for water, ...................................sediment and proper fuel (see section 2) Fuel vent ........................................................................ CLEAR Tie down and chock ................................................... REMOVE Pitot heat..................................REMOVE cover - holes CLEAR Wing tip and lights......................................................... CHECK Control surfaces.................................. CHECK for interference- ................................................................free of ice, snow, frost Hinges.................................................. CHECK for interference Static wicks ................................................................... CHECK FUSELAGE Antennas....................................................................... CHECK Empennage.............................................free of ice, snow, frost Fresh air inlet ................................................................. CLEAR Stabilator and trim tab.......................... CHECK for interference Tie down .................................................................... REMOVE Battery switch........................................................................ON Check lighting ............................................................... CHECK Nav and strobe lights .................................................... CHECK Stall warning ................................................................. CHECK Pitot heat....................................................................... CHECK All switches .........................................................................OFF Passengers .......................................................................board Supplement POH PA-28-140/150/151/160/161/180 Page 4-5 Issue 4 Revision 2, March 2012 Cabin door ..............................................CLOSE and SECURE Seat belts and harnesses .......... FASTEN - CHECK inertia reel BEFORE STARTING ENGINE Brakes................................................................................. SET Fuel Selector.......................................................... desired tank Radios.................................................................................OFF Alternate Air Door ....................................................... CLOSED STARTING ENGINE Thrust Lever....................................................................... IDLE Circuit Breaker "Alternator“ .......................................CHECK IN or Switch "Alternator" ................................................................ON Switches "Battery" and "Main Bus" .......................................ON .......................................CHECK fuel quantity and temperature Strobe lights ..........................................................................ON Electrical fuel pump...............................................................ON Engine Master.......................................................................ON Glow Control Light .................................CHECK ON, then OFF (continued next page)
WARNING: It is not allowed to start up the engine using external power. If starting the engine is not possible using battery power, the condition of the battery must be verified before flight.
CAUTION: The electronic engine control needs an electrical power source for its operation. For normal operation battery, alternator and main bus have to be switched on. Separate switching is only allowed for tests and in the event of emergencies. Supplement POH PA-28-140/150/151/160/161/180 Page 4-6 Issue 4 Revision 2, March 2012 Starter ........................................... ENGAGE until engine starts Oil pressure................................................................... CHECK CED/AED Test Button............ PRESS (to delete Caution Light) Ammeter .......................... CHECK for positive charging current Voltmeter.......................................... CHECK for GREEN range FADEC Backup Battery Test (if installed) a) Alternator ............ OFF, engine must operate normally b) Battery ............................... OFF, for min. 10 seconds; engine must operate normally, the red FADEC lamps must not be illuminated c) Battery ....................................................................ON d) Alternator ................................................................ON Avionics.................................................................................ON Ammeter ............................ Check for positive charging current Voltmeter................................................ Check for green range STARTING ENGINE WHEN COLD.....................................N/A STARTING ENGINE WHEN HOT .......................................N/A STARTING ENGINE WHEN FLOODED .............................N/A GROUND CHECK ...............................................................N/A
CAUTION: Shut down the engine immediately if the minimum oil pressure of 1 bar is not indicated after 3 seconds!
WARNING It must be ensured that both battery and alternator are ON! If the guarded alternator switch is installed, the switch guard must be closed. Supplement POH PA-28-140/150/151/160/161/180 Page 4-7 Issue 4 Revision 2, March 2012 WARM UP Let the engine warm up for about 2 minutes at 890 RPM. Increase RPM to 1400 until Oil temperature 50°C, Coolant temperature 60°C. FADEC AND PROPELLER ADJUSTMENT FUNCTION CHECK a) Thrust Lever - IDLE, both FADEC lights should be OFF b) FADEC Test Button - PRESS and HOLD for entire test c) Both FADEC lights - ON, RPM increases d) The FADEC automatically switches to B-component (only FADEC B light is ON) e) The propeller control is excited; RPM decreases f) The FADEC automatically switches to A-component (only FADEC A light is ON), RPM increases g) The propeller control is excited; RPM decreases h) FADEC A light goes OFF, idle RPM is reached, the test is completed i) FADEC Test Button - RELEASE
WARNING: If the FADEC lights do not come on at this point, it means that the test procedure has failed and take-off should not be attempted.
WARNING: If there are prolonged engine misfires or the engine shuts down during the test, take off may not be attempted.
WARNING: The whole test procedure has to be performed without any failure. In case the engine shuts down or the FADEC lights are flashing, take-off is prohibited. This applies even if the engine seems to run without failure after the test. Supplement POH PA-28-140/150/151/160/161/180 Page 4-8 Issue 4 Revision 2, March 2012 Thrust Lever .................................................FULL FORWARD, ..................................load display min. 94%, RPM 2240 - 2300 Thrust Lever....................................................................... IDLE BEFORE TAKE-OFF Circuit Breaker or Switch "Alternator", Switches "Battery" and "Main Bus“............................................................... CHECK ON Flight instruments.......................................................... CHECK Alternator Warning Light ....................................................OFF Fuel Selector............................................................proper tank Fuel Temperature ......................................................... CHECK Electrical Fuel Pump ............................................................ON Engine Instruments ....................................................... CHECK Alternate Air Door ....................................................... CLOSED Seat backs .....................................................................ERECT Belts / harness ........................................ FASTENED / CHECK Empty seats. ............................... seat belts snugly FASTENED Flaps ................................................................................... SET Trim tab............................................................................... SET Controls............................................................................ FREE Door ............................................................................... LATCH  Note: If the Test Button is released before the self-test is over, the FADEC immediately switches over to normal operation.  Note: While switching from one FADEC to another, it is normal to hear and feel a momentary surge in the engine. Supplement POH PA-28-140/150/151/160/161/180 Page 4-9 Issue 4 Revision 2, March 2012 TAKE-OFF Normal take-off - PA 28-140/-150/-160/-180 Flaps ..................................................................10° (first notch) Trim..................................................................................... SET Accelerate to 57 KIAS Control wheel .............. back pressure to rotate to climb attitude Accelerate to and maintain 65 KIAS until obstacle clearance is achieved. Best rate climb speed (flaps 10°) ..................................70 KIAS Flaps .............................................................. RETRACT slowly Normal take-off - PA 28-151/161 Flaps ..................................................................10° (first notch) Trim..................................................................................... SET Accelerate to 50 KIAS Control wheel .............. back pressure to rotate to climb attitude Accelerate to and maintain 55 KIAS until obstacle clearance is achieved. Best rate climb speed (flaps 10°) ..................................65 KIAS Flaps .............................................................. RETRACT slowly  Note: For better engine cooling a climb speed of 79 KIAS is recommended.  Note: For better engine cooling a climb speed of 79 KIAS is recommended. Supplement POH PA-28-140/150/151/160/161/180 Page 4-10 Issue 4 Revision 2, March 2012 CLIMB Best rate climb speed (flaps up) PA 28-140/150/160/180 .........................................75 KIAS PA 28-151/161 .......................................................70 KIAS En route ........................................................................87 KIAS Electrical Fuel Pump ............................. OFF at desired altitude CRUISING Cruise Power ...................................................................... SET .............................. (max. 100%, 75% or less is recommended) CED 125, AED 125 and Caution Light...................... MONITOR ............. (oil pressure, water level as well as temperature of oil, .........................water, gearbox and fuel within operating limits) Fuel quantity ............................................................. MONITOR (Gauges and LOW LEVEL caution lights) Select the other fuel tank approximately every 30 minutes to empty and heat both tanks equally (observe Section 2 "Operating Limits" Chapter "Engine Operating Limits"). FADEC Warning Lights............................................. MONITOR DESCENT Normal Thrust Lever...................................................... AS REQUIRED Airspeed...................................................... NOT EXCEED VNO  Note: For better engine cooling a climb speed of 79 KIAS is recommended.
CAUTION: Do not use any fuel tank below the minimum permissible fuel temperature! Supplement POH PA-28-140/150/151/160/161/180 Page 4-11 Issue 4 Revision 2, March 2012 Power off Thrust Lever....................................................................... IDLE Airspeed............................................................ AS REQUIRED Power.......................verify with Thrust Lever every 30 seconds APPROACH AND LANDING Fuel Selector............................................................proper tank Seat backs .....................................................................ERECT Belts / harness ............................................. FASTEN / CHECK Electrical Fuel Pump .............................................................ON Flaps ..................................................SET - NOT EXCEED VFE Trim...........................................................................to 70 KIAS Final approach speed (flaps 40°) ..................................63 KIAS STOPPING ENGINE Flaps ......................................................................... RETRACT Electrical Fuel Pump ...........................................................OFF Radios.................................................................................OFF Thrust Lever....................................................................... IDLE Engine Master.....................................................................OFF Switches "Battery" and "Main Bus“ .....................................OFF Supplement POH PA-28-140/150/151/160/161/180 Page 4-12 Issue 4 Revision 2, March 2012 This page is intentionally left blank Supplement POH PA-28-140/150/151/160/161/180 Page 5-1 Issue 4 Revision 2, Juni 2011 SECTION 5 PERFORMANCE FLIGHT PLANNING EXAMPLE a) Airplane Loading The first step in planning a flight is to calculate the airplane weight and center of gravity by utilizing the information provided by Section 6 (Weight and Balance) of this supplement to the Pilot’s Operating Handbook. The Basic Empty Weight of the airplane, determined by the company who made the modification, has been entered in Figure 6-5a of this supplement. If any alterations to airplane have been made affecting weight and balance, reference to the aircraft logbook and Weight and Balance Record (Figure 6-7) should be made to determine the current Basic Empty Weight of the airplane. Make use of the Weight and Balance Loading Form (Figure 6- 11a) of this supplement and the C.G. Range and Weight graph of the EASA approved Pilot's Operating Handbook approved to determine the total weight of the airplane and the center of gravity position.  Note: The information contained in this Section is to be used for example purposes only. The maximum weights according to section 2 are to be observed for flight planning. This example is based on a PA 28-161 - Normal category; Max. Ramp Weight 1056 kg (2327 lbs), Max. Take-Off Weight 1055 kg (2325 lbs) Supplement POH PA-28-140/150/151/160/161/180 Page 5-2 Issue 4 Revision 2, Juni 2011 After proper utilization of the information provided, the following weights apply to the flight planning example: The landing weight cannot be determined until the weight of fuel to be used has been established (refer to item (g)(1)). (1) Basic Empty Weight ............................... 730 kg (1609 lbs) (2) Occupants (2 x 77 kg/ 170 lbs)................. 154 kg (340 lbs) (3) Baggage and cargo ...................................... 24 kg (51 lbs) (4) Fuel (0.84 kg/l x 170 l, 7 lb/gal x 45 US gal, JET A-1) .................................................................. 142 kg (315 lbs) (5) Take-off Weight ................................... 1,050 kg (2315 lbs) (6) Landing Weight (a) (5) minus (g) (1) (1050 kg minus 51.6 kg)............................... 998.4 kg (2317 lbs minus 113.4 lbs) .........................2201.6 lbs The take-off weight is below the maximum of 1055 kg (2325 lbs), and the weight and balance calculations have determined that the C.G. position is within the approved limits. (b) Take-off and landing Now that the aircraft loading has been determined, all aspects of the take-off and landing must be considered. All of the existing conditions at the departure and destination airport must be acquired, evaluated and maintained throughout the flight. Apply the departure airport conditions and take-off weight to the appropriate take-off performance figures (Figure 5-1) to determine the length of runway necessary for the take-off and/ or the barrier distance. The landing distance calculations are performed in the same manner using the existing conditions at the destination airport and, when established, the landing weight. Supplement POH PA-28-140/150/151/160/161/180 Page 5-3 Issue 4 Revision 2, Juni 2011 The conditions and calculations for the example flight are listed below. The take-off and landing distances required for the example flight have fallen well below the available runway lengths. Departure Airport Destination Airport (1) Pressure Altitude 1,500ft 2,500 ft (2) Temperature 27°C (ISA + 15°C) 24°C (ISA + 14°C) 81°F (ISA + 27°F) 75°F (ISA + 25°F) (3) Wind Component 0 knots 0 knots (4) Runway Length Available 1,463 m 2,316 m The takeoff distance chart, Figure 5-1 (Takeoff Distance), should be consulted, keeping in mind that distances shown are based on the short field technique. Conservative distances can be established by reading the chart at the next higher value of weight, temperature and altitude. For example, in this particular sample problem, the takeoff distance information presented for a weight of 1,055 kg, pressure altitude of 2000 ft and a temperature of ISA+20°C/ +36°F should be used and results in the following: Ground Roll 424 m (1391ft) Total Distance to clear a 15 m obstacle 714 m (2343ft) For calculation of landing distance refer to original POH  Note: The remainder or the performance charts used in this flight planning example assume no wind condition. The effect of winds aloft must be considered by the pilot when computing climb, cruise and descent performance. Supplement POH PA-28-140/150/151/160/161/180 Page 5-4 Issue 4 Revision 2, Juni 2011 (c) Climb The next step in the flight plan is to determine the necessary climb segment components. The desired cruise pressure altitude and corresponding cruise outside air temperature values are the first variables to be considered in determining the climb components from the table "Time, Fuel and Distance to Climb" (Tab. 5-3). After time, distance and quantity of fuel for the cruise pressure altitude and outside air temperature values have been established, apply the existing conditions at the departure field to Tab. 5-3. Now, subtract the values obtained from the table for the field of departure conditions from those for the cruise pressure altitude.The remaining values are the true fuel, time and distance components for the climb segment of the flight plan corrected for field pressure altitude and temperature. The following values were determined from the above instructions in the flight planning example: (1) Cruise Pressure Altitude.................................. 5,000 ft (2) Cruise OAT...... 16°C (ISA + 11°C)/ 61°F (ISA + 20°F) Due to the difference in temperature to the standard atmosphere, the following correction applies: (3) Time to Climb (8.4 min minus 1.6 min = 6.8) + 11%) ............. 7.5 min (4) Distance to Climb ((10.4 NM minus 1.9 NM = 8.5) + 11%)............9.4 NM (5) Fuel to Climb ((4.3 l minus 0.8 l Jet A-1 = 3.5 l) + 11%) ............. 3.9 l ((1.1 minus 0.2 US gal = 0.9 US gal) + 11%) 1 US gal (6) Fuel to start-up, taxi and take-off............1l/ 0.3 US gal (7) Fuel for start-up, taxi and take-off and climb (1 l plus 3.9 l) ........................................................ 4.9 l (0.3 US gal plus 1 US gal) .......................... 1.3 US gal 11°C 20°F ( ) 10°C 18°F ( ) --------------------------------x10% 11% Increase = Supplement POH PA-28-140/150/151/160/161/180 Page 5-5 Issue 4 Revision 2, Juni 2011 (d) Descent To determine the descent data for fuel, time and distance Table 5-4 "Cruise performance, range and endurance" can be used with sufficient accuracy. (e) Cruise Using the total distance to be traveled during the flight, subtract the previously calculated distance to climb to establish the total cruise distance. Calculate the cruise fuel consumption for the cruise power setting with Table 5-4. The cruise time is found by dividing the cruise distance by the cruise speed and the cruise fuel is found by multiplying the cruise fuel consumption by the cruise time. The cruise calculations established for the cruise segment of the flight planning example are as follows: (1) Total Distance................................................. 300 NM (2) Cruise Distance (e)(1) minus (c)(4) (300 NM - 9.4 NM) ....................................... 290.6 NM (3) Cruise Power ........................................................70% (4) Cruise Speed (98 KTAS + 2%)....................100 KTAS (5) Cruise Fuel Consumption ......... 19.4 l/h (5.1 US gal/h) (6) Cruise Time (e)(2) divided by (e)(4) (290.6 NM divided by 100 KTAS) .................... =2.91 h (7) Cruise Fuel (e)(5) multiplied by (e)(6) (19.4 l/h x 2.91 h).............................................. =56.5 l (5.1 US gal/h x 2.91 h)............................ =14.9 US gal Supplement POH PA-28-140/150/151/160/161/180 Page 5-6 Issue 4 Revision 2, Juni 2011 (f) Total Flight Time The total flight time is determined by adding the time to climb and the cruise time. The following flight time is required for the flight planning example: Total Flight Time (c)(3) plus (e)(6) (0.1 h + 2.91 h) ................................................ =3.01 h (g) Total Fuel Required Determine the total fuel required by adding the fuel to climb and the cruise fuel. When the total fuel (in US gal or liters) is determined, multiply this value by 0.84 kg/l (7 lb/US gal) for JET A-1 or for Diesel to determine the total fuel weight used for flight. The total fuel calculations for the example flight plan are shown below: (1) Total Fuel Required (c)(7) plus (e)( 7) (4.9 l plus 56.5 l of Jet A-1)................................. 61.4 l (1.3 US gal plus 14.9 US gal) ................... 16.2 US gal (61.4 l x 0.84 kg/l) ............................................ 51.6 kg (16.2 US gal x 7 lb/ US gal) ...........................113.4 lbs  Note: The time values taken from the climb table are in minutes and must be converted to hours before adding them to the cruise time. Supplement POH PA-28-140/150/151/160/161/180 Page 5-7 Issue 4 Revision 2, Juni 2011 TAKE-OFF DISTANCE for PA-28-151/-161 Conditions: Flaps 10° Full Power Prior to Brake Release Paved, level, dry runway Zero Wind Lift-off speed: 50 KIAS Speed at 15 m (50 ft): 55 KIAS Notes: (1) Decrease distances 10% for each 9 Knots headwind; Increase distances 10% for each 2 knots of tailwind up to 10 Knots. (2) For operation on dry, grass runway, increase distances by 15% of the "ground roll" figure. (3) Consider additionals for wet grass runway, softened ground or snow. Supplement POH PA-28-140/150/151/160/161/180 Page 5-8 Issue 4 Revision 2, Juni 2011 Takeoff Distance at 1,055 kg (2325 lbs) PA 28-151/-161 Figure 5-1a Takeoff Distance at take-off weight 1055 kg (2325 lbs) PRESS ALT DISTANCE TEMPERATURE - °C [ft] [m] ISA ISA+10°C ISA+20°C ISA+30°C 0 Gnd Roll 309 337 366 397 50 ft 512 560 611 665 1000 Gnd Roll 333 362 394 427 50 ft 553 605 661 719 2000 Gnd Roll 358 390 424 460 50 ft 598 654 714 777 3000 Gnd Roll 386 421 458 496 50 ft 647 708 773 841 4000 Gnd Roll 417 454 493 535 50 ft 701 766 837 910 5000 Gnd Roll 450 490 532 577 50 ft 759 830 906 986 6000 Gnd Roll 485 529 575 623 50 ft 822 900 982 1068 PRESS ALT DISTANCE TEMPERATURE - °F [ft] [m] ISA ISA+18°F ISA+36°F ISA+54°F 0 Gnd Roll 1014 1106 1201 1302 50 ft 1680 1837 2005 2182 1000 Gnd Roll 1093 1188 1293 1401 50 ft 1814 1985 2169 2359 2000 Gnd Roll 1175 1280 1391 1509 50 ft 1962 2146 2343 2549 3000 Gnd Roll 1266 1381 1503 1627 50 ft 2123 2323 2536 2759 4000 Gnd Roll 1368 1490 1617 1755 50 ft 2300 2513 2746 2986 5000 Gnd Roll 1476 1608 1745 1893 50 ft 2490 2723 2972 3235 6000 Gnd Roll 1591 1736 1886 2044 50 ft 2697 2953 3222 3504 Supplement POH PA-28-140/150/151/160/161/180 Page 5-9 Issue 4 Revision 2, Juni 2011 Takeoff Distance at 885 kg (1950 lbs) PA 28-151/-161 Figure 5-1b Takeoff Distance at take-off weight 885 kg (1950 lbs) PRESS ALT DISTANCE TEMPERATURE - °C [ft] [m] ISA ISA+10°C ISA+20°C ISA+30°C 0 Gnd Roll 196 213 232 251 50 ft 324 355 387 421 1000 Gnd Roll 211 229 249 270 50 ft 350 383 418 454 2000 Gnd Roll 227 247 269 291 50 ft 379 414 452 492 3000 Gnd Roll 245 267 290 314 50 ft 410 448 489 533 4000 Gnd Roll 264 287 312 339 50 ft 444 485 530 576 5000 Gnd Roll 285 310 337 365 50 ft 481 526 574 624 6000 Gnd Roll 307 335 364 395 50 ft 521 570 622 677 PRESS ALT DISTANCE TEMPERATURE - °F [ft] [m] ISA ISA+18°F ISA+36°F ISA+54°F 0 Gnd Roll 643 699 761 823 50 ft 1063 1165 1270 1381 1000 Gnd Roll 692 751 817 886 50 ft 1148 1257 1371 1490 2000 Gnd Roll 745 810 883 955 50 ft 1243 1358 1483 1614 3000 Gnd Roll 804 876 951 1030 50 ft 1345 1470 1604 1749 4000 Gnd Roll 866 942 1024 1112 50 ft 1457 1591 1739 1890 5000 Gnd Roll 935 1017 1106 1198 50 ft 1578 1726 1883 2047 6000 Gnd Roll 1007 1099 1194 1296 50 ft 1709 1870 2041 2221 Supplement POH PA-28-140/150/151/160/161/180 Page 5-10 Issue 4 Revision 2, Juni 2011 TAKE-OFF DISTANCE for PA-28-140/-150/-160/-180 Conditions: Flaps 10° Full Power Prior to Brake Release Paved, level, dry runway Zero Wind Lift-off speed: 57 KIAS Speed at 15 m (50 ft): 65 KIAS Notes: (1) Decrease distances 10% for each 9 Knots headwind; Increase distances 10% for each 2 Knots of tailwind up to 10 Knots. (2) For operation on dry, grass runway, increase distances by 15% of the "ground roll" figure. (3) Consider additionals for wet grass runway, softened ground or snow. Supplement POH PA-28-140/150/151/160/161/180 Page 5-11 Issue 4 Revision 2, Juni 2011 Takeoff Distance at 976 kg (2150 lbs) PA 28-140/-150/-160/-180 Figure 5-1c Takeoff Distance at take-off weight 976 kg (2150 lbs) PRESS ALT DISTANCE TEMPERATURE - °C [ft] [m] ISA ISA+10°C ISA+20°C ISA+30°C 0 Gnd Roll 297 323 352 381 50 ft 543 594 648 705 1000 Gnd Roll 320 348 379 410 50 ft 587 642 701 760 2000 Gnd Roll 345 345 408 442 50 ft 635 694 758 824 3000 Gnd Roll 371 405 440 477 50 ft 686 751 820 892 4000 Gnd Roll 401 436 474 514 50 ft 743 813 887 965 5000 Gnd Roll 432 471 512 555 50 ft 805 880 961 1046 6000 Gnd Roll 467 508 553 599 50 ft 872 954 1041 1133 PRESS ALT DISTANCE TEMPERATURE - °F [ft] [m] ISA ISA+18°F ISA+36°F ISA+54°F 0 Gnd Roll 974 1060 1155 1250 50 ft 1781 1949 2126 2313 1000 Gnd Roll 1050 1142 1243 1345 50 ft 1926 2106 2300 2493 2000 Gnd Roll 1132 1132 1339 1450 50 ft 2083 2277 2487 2703 3000 Gnd Roll 1217 1329 1444 1565 50 ft 2251 2464 2690 2927 4000 Gnd Roll 1316 1430 1555 1686 50 ft 2438 2667 2910 3166 5000 Gnd Roll 1417 1545 1680 1821 50 ft 2641 2887 3153 3432 6000 Gnd Roll 1532 1667 1814 1965 50 ft 2861 3130 3415 3717 Supplement POH PA-28-140/150/151/160/161/180 Page 5-12 Issue 4 Revision 2, Juni 2011 Takeoff Distance at 885 kg (1950 lbs) PA 28-140/-150/-160/-180 Figure 5-1d Takeoff Distance at take-off weight 885 kg (1950 lbs) PRESS ALT DISTANCE TEMPERATURE - °C [ft] [m] ISA ISA+10°C ISA+20°C ISA+30°C 0 Gnd Roll 231 251 273 296 50 ft 422 462 504 548 1000 Gnd Roll 249 271 294 319 50 ft 456 499 545 594 2000 Gnd Roll 268 292 317 344 50 ft 493 540 589 641 3000 Gnd Roll 289 314 342 370 50 ft 534 584 637 693 4000 Gnd Roll 311 339 396 400 50 ft 578 632 690 750 5000 Gnd Roll 336 366 398 431 50 ft 626 684 747 813 6000 Gnd Roll 363 395 430 465 50 ft 678 742 810 881 PRESS ALT DISTANCE TEMPERATURE - °F [ft] [m] ISA ISA+18°F ISA+36°F ISA+54°F 0 Gnd Roll 758 823 896 971 50 ft 1385 1516 1654 1798 1000 Gnd Roll 817 889 965 1047 50 ft 1496 1637 1788 1949 2000 Gnd Roll 879 958 1040 1129 50 ft 1617 1772 1932 2103 3000 Gnd Roll 948 1030 1122 1214 50 ft 1752 1916 2090 2274 4000 Gnd Roll 1020 1112 1299 1312 50 ft 1896 2073 2264 2461 5000 Gnd Roll 1102 1201 1306 1414 50 ft 2054 2244 2451 2667 6000 Gnd Roll 1191 1296 1411 1526 50 ft 2224 2434 2657 2890 Supplement POH PA-28-140/150/151/160/161/180 Page 5-13 Issue 4 Revision 2, Juni 2011 MAXIMUM CLIMBSPEED for PA-28-151/-161 Conditions: Take-off weight 1055 kg (2325 lbs) Climb speed Vy = 70 KIAS Flaps Up Full Power Figure 5-2a Climbspeed, PA-28-151/-161, 1055 kg (2325 lbs) Pressure altitude [FT] Climbspeed (ft/min) ISA ISA + 10°C (ISA + 18°F) ISA + 20°C (ISA + 36°F) ISA + 30°C (ISA + 54°F) 0 606 606 602 595 1000 606 602 595 584 2000 603 596 585 569 3000 597 586 571 549 4000 588 572 552 523 5000 574 554 528 495 6000 556 531 500 461 7000 533 503 468 422 8000 506 470 431 380 9000 474 433 390 335 10000 437 392 346 287 11000 396 348 299 237 12000 351 301 251 Supplement POH PA-28-140/150/151/160/161/180 Page 5-14 Issue 4 Revision 2, Juni 2011 MAXIMUM CLIMBSPEED for PA-28-151/-161 Conditions: Take-off weight 885 kg (1950 lbs) Climb speed Vy = 70 KIAS Flaps Up Full Power Figure 5-2b Climbspeed, PA-28-151/-161, 855 kg (1950 lbs) Pressure altitude [FT] Climbspeed (ft/min) ISA ISA + 10°C (ISA + 18°F) ISA + 20°C (ISA + 36°F) ISA + 30°C (ISA + 54°F) 0 759 759 757 752 1000 759 757 753 744 2000 758 753 745 730 3000 754 746 732 711 4000 747 734 714 685 5000 736 716 689 650 6000 719 692 656 606 7000 695 659 615 551 8000 663 618 563 485 9000 623 567 500 406 10000 572 504 425 313 11000 510 430 337 204 12000 436 341 235 Supplement POH PA-28-140/150/151/160/161/180 Page 5-15 Issue 4 Revision 2, Juni 2011 MAXIMUM CLIMBSPEED for PA-28-140/-150/-160/-180 Conditions: Take-off weight 976 kg (2150 lbs) Climb speed Vy = 75 KIAS Flaps Up Full Power Figure 5-2c Climbspeed, PA-28-140/-150/-160/-180, 976 kg (2150 lbs) Pressure altitude [FT] Climbspeed (ft/min) ISA ISA + 10°C (ISA + 18°F) ISA + 20°C (ISA + 36°F) ISA + 30°C (ISA + 54°F) 0 548 547 541 530 1000 547 542 531 513 2000 543 532 515 490 3000 534 517 493 460 4000 520 496 465 424 5000 499 468 430 381 6000 472 433 389 334 7000 437 393 343 281 8000 397 346 292 226 9000 351 296 239 171 10000 300 242 184 118 11000 246 187 131 70 12000 191 133 82 Supplement POH PA-28-140/150/151/160/161/180 Page 5-16 Issue 4 Revision 2, Juni 2011 MAXIMUM CLIMBSPEED for PA-28-140/-150/-160/-180 Conditions: Take-off weight 885 kg (1950 lbs) Climb speed Vy = 75 KIAS Flaps Up Full Power Figure 5-2d Climbspeed, PA-28-140/-150/-160/-180, 855 kg (1950 lbs) Pressure altitude [FT] Climbspeed (ft/min) ISA ISA + 10°C (ISA + 18°F) ISA + 20°C (ISA + 36°F) ISA + 30°C (ISA + 54°F) 0 657 653 643 627 1000 654 644 629 607 2000 646 631 610 583 3000 633 612 586 552 4000 615 589 557 517 5000 592 560 523 477 6000 564 526 484 431 7000 531 487 440 381 8000 492 444 391 325 9000 449 395 337 264 10000 400 431 279 198 11000 346 282 215 126 12000 287 218 146 Supplement POH PA-28-140/150/151/160/161/180 Page 5-17 Issue 4 Revision 2, Juni 2011 TIME, FUEL AND DISTANCE TO CLIMB for PA-28-151/-161 Notes : (1) Add 1 l (0.3 US gal) of fuel for engine start, taxi and takeoff allowance. (2) Increase time and distance by 10% for 10°C/ 18°F above standard temperature. (3) Distances shown are based on zero wind. (4) Time, distance and fuel required are only valid from the point where the airplane climbs at vy = 70 KIAS. Conditions: Takeoff weight 1055 kg (2325 lbs); Climb speed vy = 70 KIAS Flaps Up; Full Power; Zero wind, Standard Temperature Figure 5-3a Time, Fuel and Distance to Climb at 1055 kg (2325 lbs) PA-28-151/-161 From Sea Level Press. Alt. Temp. (ISA) Rate of Climb Time Distance to climb Fuel used [ft] [°C] [°F] [ft/min] [MIN] [NM] [US gal] [l] 0 15 59 606 0.0 0.0 0.0 0.0 1000 13 55 606 1.6 1.9 0.2 0.8 2000 11 52 603 3.3 3.9 0.4 1.6 3000 9 48 597 5.0 6.0 0.7 2.5 4000 7 45 588 6.7 8.1 0.9 3.4 5000 5 41 574 8.4 10.4 1.1 4.3 6000 3 38 556 10.1 12.8 1.4 5.3 7000 1 34 533 12.0 15.3 1.7 6.3 8000 -1 30 506 13.9 18.0 2.0 7.4 9000 -3 27 474 15.9 21.0 2.2 8.5 10000 -5 23 437 18.1 24.3 2.6 9.7 11000 -7 20 396 20.5 27.9 2.9 11.0 12000 -9 16 351 23.2 32.1 3.2 12.3 Supplement POH PA-28-140/150/151/160/161/180 Page 5-18 Issue 4 Revision 2, Juni 2011 Conditions: Takeoff weight 885 kg (1950 lbs); Climb speed vy = 70 KIAS Flaps Up; Full Power; Zero wind, Standard Temperature Figure 5-3b Time, Fuel and Distance to Climb at 885 kg (1950 lbs) PA-28-151/-161 From Sea Level Press. Alt. Temp. (ISA) Rate of Climb Time Distance to climb Fuel used [ft] [°C] [°F] [ft/min] [MIN] [NM] [US gal] [l] 0 15 59 759 0.0 0.0 0.0 0.0 1000 13 55 759 1.3 1.5 0.2 0.6 2000 11 52 758 2.6 3.1 0.3 1.3 3000 9 48 754 4.0 4.8 0.5 2.0 4000 7 45 747 5.3 6.5 0.7 2.7 5000 5 41 736 6.6 8.2 0.9 3.5 6000 3 38 719 8.0 10.1 1.1 4.3 7000 1 34 695 9.4 12.0 1.4 5.2 8000 -1 30 663 10.9 14.1 1.6 6.0 9000 -3 27 623 12.5 16.4 1.8 7.0 10000 -5 23 572 14.1 18.9 2.1 7.9 11000 -7 20 510 16.0 21.7 2.4 9.0 12000 -9 16 436 18.1 25.0 2.7 10.1 Supplement POH PA-28-140/150/151/160/161/180 Page 5-19 Issue 4 Revision 2, Juni 2011 TIME, FUEL AND DISTANCE TO CLIMB for PA-28-140/-150/-160/-180 Notes : (1) Add 1 l (0.3 US gal) of fuel for engine start, taxi and takeoff . (2) Increase time and distance by 10% for 10°C/ 18°F above standard temperature. (3) Distances shown are based on zero wind. (4) Time, distance and fuel required are only valid from the point where the airplane climbs at vy = 75 KIAS. Conditions: Takeoff weight 976 kg (2150 lbs); Climb speed vy = 75 KIAS Flaps Up; Full Power; Zero wind, Standard Temperature Figure 5-3c Time, Fuel and Distance to Climb at 976 kg (2150 lbs) PA-28-140/-150/-160/-180 From Sea Level Press. Alt. Temp. (ISA) Rate of Climb Time Distance to climb Fuel used [ft] [°C] [°F] [ft/min] [MIN] [NM] [US gal] [l] 0 15 59 548 0.0 0.0 0.0 0.0 1000 13 55 547 1.8 2.2 0.2 0.9 2000 11 52 543 3.7 4.4 0.5 1.8 3000 9 48 534 5.5 6.8 0.7 2.7 4000 7 45 520 7.4 9.2 1.0 3.7 5000 5 41 499 9.4 11.9 1.2 4.7 6000 3 38 472 11.4 14.7 1.6 5.9 7000 1 34 437 13.6 17.8 1.9 7.1 8000 -1 30 397 16.0 21.3 2.2 8.4 9000 -3 27 351 18.7 25.2 2.6 9.8 10000 -5 23 300 21.8 29.8 3.0 11.3 11000 -7 20 246 25.4 35.3 3.4 13.0 12000 -9 16 191 30.0 42.4 4.0 15.1 Supplement POH PA-28-140/150/151/160/161/180 Page 5-20 Issue 4 Revision 2, Juni 2011 Conditions: Takeoff weight 885 kg (1950 lbs); Climb speed vy = 75 KIAS Flaps Up; Full Power; Zero wind, Standard Temperature Figure 5-3d Time, Fuel and Distance to Climb at 885 kg (1950 lbs) PA-28-140/-150/-160/-180 From Sea Level Press. Alt. Temp. (ISA) Rate of Climb Time Distance to climb Fuel used [ft] [°C] [°F] [ft/min] [MIN] [NM] [US gal] [l] 0 15 59 657 0.0 0.0 0.0 0.0 1000 13 55 654 1.5 1.8 0.2 0.7 2000 11 52 646 3.1 3.7 0.4 1.5 3000 9 48 633 4.6 5.7 0.6 2.3 4000 7 45 615 6.2 7.8 0.8 3.2 5000 5 41 592 7.9 10.0 1.1 4.1 6000 3 38 564 9.6 12.4 1.3 5.0 7000 1 34 531 11.4 14.9 1.6 6.1 8000 -1 30 492 13.4 17.8 1.9 7.2 9000 -3 27 449 15.5 20.9 2.2 8.3 10000 -5 23 400 17.9 24.4 2.5 9.6 11000 -7 20 346 20.6 28.6 2.9 10.9 12000 -9 16 287 23.7 33.5 3.3 12.5 Supplement POH PA-28-140/150/151/160/161/180 Page 5-21 Issue 4 Revision 2, Juni 2011 CRUISE PERFORMANCE, RANGE AND ENDURANCE for PA-28-151/-161 Conditions: Flaps Up Zero wind Notes: (1) Endurance information are based on fuel tanks with a ca- pacity of 162.8 l (43 US gal) usable fuel and include a re- serve of 45 min at 55% power (11.1 l / 2.9 US gal). (2) Increase true airspeed and range by 2% per 10°C (18°F) above ISA temperature. Decrease true airspeed and range by 2% per 10°C (18°F) below ISA temperature. Supplement POH PA-28-140/150/151/160/161/180 Page 5-22 Issue 4 Revision 2, Juni 2011 Cruise Performance, Range and Endurance for PA-28-151/-161 at 1055 kg (2325 lbs) Figure 5-4a Cruise Performance, Range and Endurance at 1055 kg (2325 lbs) Press.Alt. [ft] Load [%] KTAS FF[l/h] FF [US gal/h] NM Hrs 2000 60 88 17.4 4.6 819 9.3 2000 70 95 19.4 5.1 793 8.4 2000 80 101 22.1 5.8 740 7.3 2000 90 106 25.6 6.8 671 6.3 4000 60 90 17.4 4.6 838 9.3 4000 70 97 19.4 5.1 810 8.4 4000 80 102 22.1 5.8 748 7.3 4000 90 107 25.6 6.8 677 6.3 6000 60 91 17.4 4.6 847 9.3 6000 70 98 19.4 5.1 818 8.4 6000 80 104 22.1 5.8 762 7.3 6000 90 109 25.6 6.8 690 6.3 8000 60 93 17.4 4.6 866 9.3 8000 70 100 19.4 5.1 835 8.4 8000 80 106 22.1 5.8 777 7.3 8000 90 111 25.6 6.8 702 6.3 10000 60 94 17.4 4.6 875 9.3 10000 70 101 19.4 5.1 843 8.4 10000 80 108 22.1 5.8 792 7.3 12000 60 96 17.4 4.6 894 9.3 12000 70 103 19.4 5.1 860 8.4 12000 80 110 22.1 5.8 806 7.3 Supplement POH PA-28-140/150/151/160/161/180 Page 5-23 Issue 4 Revision 2, Juni 2011 Cruise Performance, Range and Endurance for PA-28-151/-161 at 885 kg (1950 lbs) Figure 5-4b Cruise Performance, Range and Endurance at 885 kg (1950 lbs) Press.Alt. [ft] Load [%] KTAS FF[l/h] FF [US gal/h] NM Hrs 2000 60 100 17.4 4.6 931 9.3 2000 70 106 19.4 5.1 885 8.4 2000 80 112 22.1 5.8 821 7.3 2000 90 117 25.6 6.8 740 6.3 4000 60 101 17.4 4.6 940 9.3 4000 70 108 19.4 5.1 902 8.4 4000 80 114 22.1 5.8 836 7.3 4000 90 119 25.6 6.8 753 6.3 6000 60 103 17.4 4.6 959 9.3 6000 70 110 19.4 5.1 919 8.4 6000 80 116 22.1 5.8 850 7.3 6000 90 121 25.6 6.8 766 6.3 8000 60 105 17.4 4.6 978 9.3 8000 70 112 19.4 5.1 935 8.4 8000 80 118 22.1 5.8 865 7.3 8000 90 123 25.6 6.8 778 6.3 10000 60 107 17.4 4.6 996 9.3 10000 70 114 19.4 5.1 952 8.4 10000 80 120 22.1 5.8 880 7.3 12000 60 109 17.4 4.6 1015 9.3 12000 70 116 19.4 5.1 969 8.4 12000 80 123 22.1 5.8 902 7.3 Supplement POH PA-28-140/150/151/160/161/180 Page 5-24 Issue 4 Revision 2, Juni 2011 CRUISE PERFORMANCE, RANGE AND ENDURANCE for PA-28-140/-150/-160/-180 Conditions: Flaps Up Zero wind Notes: (1) Endurance information are based on fuel tanks with a ca- pacity of 162.8 l (43 US gal) usable fuel and include a re- serve of 45 min at 55% power (11.1 l / 2.9 US gal). (2) Increase true airspeed and range by 2% per 10°C (18°F) above ISA temperature. Decrease true airspeed and range by 2% per 10°C/ (18°F) below ISA temperature. Supplement POH PA-28-140/150/151/160/161/180 Page 5-25 Issue 4 Revision 2, Juni 2011 Cruise Performance, Range and Endurance for PA-28-140/-150/-160/-180 at 976 kg (2150 lbs) Figure 5-4c Cruise Performance, Range and Endurance at 976 kg (2150 lbs) Press.Alt. [ft] Load [%] KTAS FF[l/h] FF [US gal/h] NM Hrs 2000 60 85 17.4 4.6 791 9.3 2000 70 94 19.4 5.1 785 8.4 2000 80 102 22.1 5.8 748 7.3 2000 90 109 25.6 6.8 690 6.3 4000 60 85 17.4 4.6 791 9.3 4000 70 95 19.4 5.1 793 8.4 4000 80 103 22.1 5.8 755 7.3 4000 90 110 25.6 6.8 696 6.3 6000 60 86 17.4 4.6 801 9.3 6000 70 96 19.4 5.1 802 8.4 6000 80 104 22.1 5.8 762 7.3 6000 90 112 25.6 6.8 709 6.3 8000 60 87 17.4 4.6 810 9.3 8000 70 97 19.4 5.1 810 8.4 8000 80 105 22.1 5.8 770 7.3 8000 90 113 25.6 6.8 715 6.3 10000 60 87 17.4 4.6 810 9.3 10000 70 98 19.4 5.1 818 8.4 10000 80 107 22.1 5.8 784 7.3 12000 60 88 17.4 4.6 819 9.3 12000 70 99 19.4 5.1 827 8.4 12000 80 108 22.1 5.8 792 7.3 Supplement POH PA-28-140/150/151/160/161/180 Page 5-26 Issue 4 Revision 2, Juni 2011 Cruise Performance, Range and Endurance for PA-28-151/-161 at 885 kg (1950 lbs) Figure 5-4d Cruise Performance, Range and Endurance at 885 kg (1950 lbs) Press.Alt. [ft] Load [%] KTAS FF[l/h] FF [US gal/h] NM Hrs 2000 60 93 17.4 4.6 866 9.3 2000 70 102 19.4 5.1 852 8.4 2000 80 110 22.1 5.8 806 7.3 2000 90 118 25.6 6.8 747 6.3 4000 60 94 17.4 4.6 875 9.3 4000 70 104 19.4 5.1 868 8.4 4000 80 112 22.1 5.8 821 7.3 4000 90 119 25.6 6.8 753 6.3 6000 60 95 17.4 4.6 884 9.3 6000 70 105 19.4 5.1 877 8.4 6000 80 113 22.1 5.8 828 7.3 6000 90 121 25.6 6.8 766 6.3 8000 60 96 17.4 4.6 894 9.3 8000 70 106 19.4 5.1 885 8.4 8000 80 115 22.1 5.8 843 7.3 8000 90 123 25.6 6.8 778 6.3 10000 60 97 17.4 4.6 903 9.3 10000 70 108 19.4 5.1 902 8.4 10000 80 117 22.1 5.8 858 7.3 12000 60 98 17.4 4.6 912 9.3 12000 70 109 19.4 5.1 910 8.4 12000 80 118 22.1 5.8 865 7.3 Supplement POH PA-28-140/150/151/160/161/180 Page 5-27 Issue 4 Revision 2, Juni 2011 GLIDE RANGE PA 28-151/-161 Conditions: Take-off weight 1055 kg (2325 lbs) Propeller windmilling Flaps 0°, Zero wind, 73 KIAS Figure 5-5a Glide Range PA 28-151/-161 Glide Distance Propeller Windmilling 0 2000 4000 6000 8000 10000 12000 14000 0 5 10 15 20 Glide Range [Nm] Pressure Altitude [ft] Supplement POH PA-28-140/150/151/160/161/180 Page 5-28 Issue 4 Revision 2, Juni 2011 GLIDE RANGE PA 28-140/-150/-160/-180 Conditions: Take-off weight 976 kg (2150 lbs) Propeller windmilling Flaps 0°, Zero wind, 78 KIAS Figure 5-5b Glide Range PA 28-140/-150/-160/-180 Glide Distance, Propeller Windmilling 0 2000 4000 6000 8000 10000 12000 14000 0 5 10 15 20 Glide Range [Nm] Pressure Altitude [ft] Supplement POH PA-28-140/150/151/160/161/180 Page 5-29 Issue 4 Revision 2, Juni 2011 Figure 5-6a Engine Power Diagram Supplement POH PA-28-140/150/151/160/161/180 Page 5-30 Issue 4 Revision 2, Juni 2011 This page is intentionally left blank Supplement POH PA-28-140/150/151/160/161/180 Page 6-1 Issue 4 Revision -, Feb. 2010 SECTION 6 WEIGHT & BALANCE MODEL PA-28-151/-161 with TAE-125 AIRPLANE BASIC EMPTY WEIGHT * The standard empty weight includes full engine oil capacity, full gearbox oil capacity, full coolant capacity and 8 l (2 US gal) unusable fuel. AIRPLANE USEFUL LOAD (Ramp Weight) - (Basic Empty Weight) = Useful Load (Normal category: 1056 kg) - (.............kg) = kg (2327 lb) - (..............lb) = lb (PA 28-161 Utility cat.: 917 kg) - (.............kg) = kg (2022 lb) - (..............lb) = lb (PA 28-151 Utility cat.: 886 kg) - (.............kg) = kg (1952 lb) - (..............lb) = lb THIS BASIC EMPTY WEIGHT, C.G. AND USEFUL LOAD ARE FOR THE AIRPLANE AS INSPECTED AFTER MODIFICATION. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. WEIGHT & BALANCE DATA FORM Figure 6-5a Airplane Serial Number: Registration Number: Date: Item Weight x C.G. Arm = Moment (kg/ lb) (m/ in Aft (kgm/ lbs in) of Datum) Standard Empty Weight Actual: Computed: Optional Equipment Basic Empty Weight Supplement POH PA-28-140/150/151/160/161/180 Page 6-2 Issue 4 Revision -, Feb. 2010 MODEL PA-28-140 with TAE-125 AIRPLANE BASIC EMPTY WEIGHT * The standard empty weight includes full engine oil capacity, full gearbox oil capacity, full coolant capacity and 8 l (2 US gal) unusable fuel. AIRPLANE USEFUL LOAD (Ramp Weight) - (Basic Empty Weight) = Useful Load (Normal category: 977 kg*) - (.............kg) = kg (2152 lb*) - (..............lb) = lb (Normal category: 886 kg*) - (.............kg) = kg (1952 lb*) - (..............lb) = lb (Utility category: 886 kg) - (.............kg) = kg (1952 lb) - (..............lb) = lb THIS BASIC EMPTY WEIGHT, C.G. AND USEFUL LOAD ARE FOR THE AIRPLANE AS INSPECTED AFTER MODIFICATION. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. WEIGHT & BALANCE DATA FORM Figure 6-5b *Serial no. 28-20001 to 28-20939: 886 kg, if Piper Kit 756962 installed 997 kg, Serial no. 28-20940 and up: 977 kg. Refer to original POH. Airplane Serial Number: Registration Number: Date: Item Weight x C.G. Arm = Moment (kg/ lb) (m/ in Aft (kgm/ lbs in) of Datum) Standard Empty Weight Actual: Computed: Optional Equipment Basic Empty Weight Supplement POH PA-28-140/150/151/160/161/180 Page 6-3 Issue 4 Revision -, Feb. 2010 MODEL PA-28-150/-160/-180 with TAE-125 AIRPLANE BASIC EMPTY WEIGHT * The standard empty weight includes full engine oil capacity, full gearbox oil capacity, full coolant capacity and 8 l (2 US gal) unusable fuel. AIRPLANE USEFUL LOAD (Ramp Weight) - (Basic Empty Weight) = Useful Load (Normal category: 977 kg) - (.............kg) = kg (2152 lb) - (.............lb ) = lb (PA 28-180 Utility cat.: 886 kg) - (.............kg) = kg (1952 lb) - (..............lb) = lb THIS BASIC EMPTY WEIGHT, C.G. AND USEFUL LOAD ARE FOR THE AIRPLANE AS INSPECTED AFTER MODIFICATION. REFER TO APPROPRIATE AIRCRAFT RECORD WHEN ALTERATIONS HAVE BEEN MADE. WEIGHT & BALANCE DATA FORM Figure 6-5b Airplane Serial Number: Registration Number: Date: Item Weight x C.G. Arm = Moment (kg/ lb) (m/ in Aft (kgm/ lbs in) of Datum) Standard Empty Weight Actual: Computed: Optional Equipment Basic Empty Weight Supplement POH PA-28-140/150/151/160/161/180 Page 6-4 Issue 4 Revision -, Feb. 2010 WEIGHT & BALANCE DETERMINATION FOR FLIGHT (a) Add the weight of all items to be loaded to the basic empty weight. (b) Use the Loading Graph (Figure 6-13) to determine the mo- ment of all items to be carried in the airplane. (c) Add the moment of all items to be loaded to the basic empty weight moment. (d) Divide the total moment by the total weight to determine the C.G. location. (e) By using the figures of item (a) and (d) (above), locate a point on the C.G. range and weight graph (Figure 6-15). If the point falls within the C.G. envelope, the loading meets the weight and balance requirements. Supplement POH PA-28-140/150/151/160/161/180 Page 6-5 Issue 4 Revision -, Feb. 2010 WEIGHT & BALANCE LOADING FORM PA 28-151/-161 * Utility Category Operation - No baggage or aft passengers allowed. Maximum baggage as per original POH Totals must be within approved weight and C.G. limits. It is the responsibility of the airplane owner and the pilot to insure that the airplane is loaded properly. The Basic Empty Weight C.G. is noted on the Weight & Balance Data Form (Figure 6-5a). If the airplane has been altered, refer to the Weight and Balance Record for this information. Figure 6-11a Weight (kg) Arm Aft Datum (m) Moment (kgm) - Basic Empty Weight - Pilot and Front Passenger 2.04 - Passengers (Rear Seats)* 3.00 - Fuel (max. 162.8 l usable) 2.41 - Baggage* (max. 90 kg, PA 28-161 Cadet max. 23 kg) 3.63 - Ramp Weight PA 28-151 (1056 kg Normal aircraft, 886 kg Utility, Maximum) PA 28-161 (1056 kg Normal aircraft, 917 kg Utility Maximum) - Fuel Allowance for Engine Start, Taxi and Run up -1 2.41 -2.41 - Take-off Weight PA 28-151 (1055 kg Normal aircraft, 885 kg Utility, Maximum) PA 28-161 (1055 kg Normal, 916 kg Utility, Maximum) Supplement POH PA-28-140/150/151/160/161/180 Page 6-6 Issue 4 Revision -, Feb. 2010 WEIGHT & BALANCE LOADING FORM PA 28-151/-161 * Utility Category Operation - No baggage or aft passengers allowed. Maximum baggage as per original POH Totals must be within approved weight and C.G. limits. It is the respon