Normal Procedures for the Piper PA-32R Saratoga

Piper PA-32R Saratoga · Normal Procedures

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Overview

This document serves as the Normal Procedures manual for the Piper PA-32R Saratoga, providing essential operational guidelines for pilots. It covers standard operating procedures that ensure safe and efficient flight operations. The manual is designed for both new and experienced pilots, offering a comprehensive overview of the aircraft's systems, performance metrics, and procedural checklists. Key information includes preflight checks, engine start procedures, and emergency protocols, all tailored to the specific characteristics of the PA-32R Saratoga.

Fuel capacity: 50 gallons total
Oil quantity: 6 to 8 quarts
Maximum takeoff weight: 3,600 lbs
Preflight checks are mandatory before each flight
Emergency procedures must be reviewed regularly

Document

Source

Originally published by indianapilotsclub.org. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

View original at indianapilotsclub.org

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Document details

Type: Normal Procedures
Pages: 12
File size: 5.9 MB
Publisher: indianapilotsclub.org

Specifications & performance

Extracted from this document.

Specifications

Range (nm): 965
Propeller: 3-Blade
Engine model: LYCOMING 10-540K
Max speed (kt): 150
Cruise speed (kt): 136
Fuel capacity (gal): 102
Rate of climb (fpm): 620
Max takeoff weight (lb): 3,600

Performance

Fuel burn (gph): 13.8
Landing over 50ft: 1,450
Max crosswind (kt): 10
Takeoff over 50ft: 1,750
Takeoff distance (ft): 2,150
Stall speed clean (kt): 67.5
Stall speed landing (kt): 62.5

V-speeds

VR: 80
VX: 68
VY: 80
VS1: 67.5
VSO: 62.5

Weight & balance

Max takeoff weight (lb): 3,600

Documentation completeness

2/7

Most owners only have the POH. Here's the essential set for the Piper PA-32R Saratoga.

Pilot's Operating Handbook / AFM
Checklist
Maintenance Manual
Parts Catalog (IPC)
Systems & Wiring
Service Bulletins
Type Certificate (TCDS)

More Piper PA-32R Saratogamanuals & documents

In this document

Preflight Inspection

The Preflight Inspection section outlines the necessary checks before flight, including fuel levels, oil quantity, and control surface functionality. Pilots should verify that fuel tanks are filled to the required levels, typically 50 gallons total capacity, and that oil levels are within the acceptable range of 6 to 8 quarts.

Engine Start Procedures

This section details the steps for starting the engine, including setting the mixture to rich, ensuring the throttle is in the correct position, and engaging the starter. It emphasizes the importance of monitoring engine gauges during the start process to ensure proper operation.

Before Takeoff

The Before Takeoff section includes critical checks such as verifying flight controls, setting flaps to the appropriate position, and confirming that all instruments are functioning correctly. Pilots should also ensure that the takeoff weight does not exceed the maximum allowable limit of 3,600 lbs.

Emergency Procedures

Emergency Procedures provide guidance on handling in-flight emergencies, including engine failure and electrical malfunctions. The manual outlines specific actions to take, such as maintaining control of the aircraft and executing a forced landing if necessary.

Safety notes

Always perform a thorough preflight inspection to ensure aircraft safety.
Monitor engine gauges closely during start-up to detect any anomalies.

Full document text

REPORT: VB-1060 5-12 AIRSPEED SYSTEM CALIBRATION Figure 5-3 ISSUED: JANUARY 9, 1980 190 KCAS 180 170 160 150 POWER OFF STALL SPEED VERSUS ANGLE OF BANK Figure 5-5 ISSUED: JANUARY 9, 1980 REPORT: VB-1060 5-13 110 PA-32-301 AIRSPEED SYSTEM CALIBRATION GROSS WEIGHT 3600 LBS. Example: Flaps: 0° 110 KIAS 109 KCAS Flaps: 40° 84 KIAS = 83 KCAS 70 60 60 70 80 90 STALL SPEED - KIAS 80 70 70 WING FLAPS 0° KCAS 60 100 110 120 130 140 150 160 170 180 190 200 KIAS ZERO INSTRUMENT ERROR WING FLAPS 40° 80 90 100-11 KIAS PA-32-301 POWER OFF STALL SPEED VERSUS ANGLE OF BANK 3600 POUNDS GROSS WEIGHT 10 20 FLAPS 50 ANGLE OF BANK - DEGREES 60 Example: Angle of bank: 25° Stall speed: 0° Flaps -67,5 KIAS 40° Flaps 62.5 KIAS SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION SECTION 5 PERFORMANCE REPORT: VB-1060 5-14 ISSUED: JANUARY 9, 1980 NORMAL PROCEDURE TAKEOFF PERFORMANCE Figure 5-7 T.O. SPEED-KIAS WT. LBS. LIFTOFF BARRIER 3600 80 80 3400 79 79 3200 78 78 3000 77 77 2800 75 75 2600 74 74 PA-32-301 NORMAL PROCEDURE TAKEOFF PERFORMANCE ASSOCIATED CONDITIONS: Example: Pressure altitude: 1200 ft. O.A.T.: 16°C. Gross weight: 3480 lbs. Wind: 10 knots (headwind) Takeoff distance: 2150 ft. (3-Blade); 2275 ft (2-Blade) Lift off speed 80 KIAS 2700 RPM AND FULL THROTTLE BEFORE BRAKE RELEASE Barrier speed 80 KIAS PAVED, LEVEL DRY RUNWAY FLAPS 0° FT. PRESSURE ALTITUDE 8000 6000 4000 2000 SEA LEVEL REF. LINE 3600 REF. LINE ZERO WIND TAILWIND HEADWIND 5000 3-BLADE PROPELLER TT 2-BLADE PROPELLER 4000 5000 4000 3000 3000 TAKEOFF DISTANCE OVER 50 FT. BARRIER - FT. 2000 2000 1000 1000 10 -40 -30 -20 -10 0 10 20 30 OUTSIDE AIR TEMPERATURE - °C 40 3600 3400 3200 3000 2800 2600 WEIGHT-POUNDS C 5 10 15 WIND COMPONENT - KTS Example: Pressure altitude: 1200 ft. O.A.T.: 16°C Gross Weight: 3480 lbs. Wind: 10 knots (headwind) Takeoff ground roll: 1700 ft. (3-Blade); 1900 ft. (2-Blade) Lift off speed: 80 KIAS PA-32-301. NORMAL PROCEDURE TAKEOFF GROUND ROLL ASSOCIATED CONDITIONS: 2700 RPM AND FULL THROTTLE BEFORE BRAKE RELEASE: PAVED, LEVEL DRY RUNWAY FLAPS 0° WT. LBS T.O. SPEED-KIAS 3600 80 3400 79 3200 78 3000 77 2800 75 2600 74 NORMAL PROCEDURE TAKEOFF GROUND ROLL Figure 5-9 ISSUED: JANUARY 9, 1980 REPORT: VB-1060 5-15 FT. PRESSURE ALTITUDE 8000 6000 4000! 2000 SEA LEVEL -40 ZERO WIND TAILWIND HEADWIND 3-BLADE PROPELLER 5000 4000 ก TTTTTTTT 2-BLADE PROPELLER 5000 4000 3000 3000 2000 2000 1000 -1000 -30 -20-10 0 10 20 30 OUTSIDE AIR TEMPERATURE - °C 40 3600 3400 3200 3000 2800 2600 WEIGHT-POUNDS 0 5 10 0 15 WIND COMPONENTS - KTS TAKEOFF GROUND ROLL - FT. SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION PERFORMANCE SECTION 5 REPORT: VB-1060 5-16 PA-32-301 MAXIMUM EFFORT TAKEOFF PERFORMANCE - FLAPS 0° ASSOCIATED CONDITIONS: 2700 RPM AND FULL THROTTLE BEFORE BRAKE RELEASE PAVED, LEVEL DRY RUNWAY Example: Pressure altitude: 1200 ft. O.A.T.: 16°C. Gross weight: 3480 lbs. Wind: 10 knots (headwind) Takeoff distance: 1750 ft. (3-Blade); 1900 ft. (2-Blade) Lift off speed: 68 KIAS Barrier speed: 74 KIAS XXXXXXXX 0008 FT. PRESSURE ALTITUDE T.O. SPEED-KIAS WT. LBS LIFTOFF BARRIER 3600 68 74 3400 67 73 3200 66 72 3000 65 70 2800 64 69 2600 63 67 MAXIMUM EFFORT TAKEOFF PERFORMANCE - FLAPS 0° Figure 5-11 ISSUED: JANUARY 9, 1980 6000 4000 2000 SEA LEVEL 40 -30 -20 -10 0 10 20 30 40 OUTSIDE AIR TEMPERATURE - °C Figure 5-13 MAXIMUM EFFORT TAKEOFF GROUND ROLL - FLAPS 0° ISSUED: JANUARY 9, 1980 REPORT: VB-1060 5-17 TAILWIND HEADWIND SECTION 5 PERFORMANCE 1000 1000 2000 -2000 3000 3000 4000 4000 5000 5000 3-BLADE PROPELLER 2-BLADE PROPELLER TAKEOFF DISTANCE OVER 50 FT. BARRIER - FT. WEIGHT - 3600 3400 3200 3000 2800 2600 POUNDS 0 5 10 15 WIND COMPONENT -KTS. PA-32-301 MAXIMUM EFFORT TAKEOFF GROUND ROLL FLAPS 0° ASSOCIATED CONDITIONS: 2700 RPM AND FULL THROTTLE BEFORE BRAKE RELEASE PAVED, LEVEL, DRY RUNAWAY Example: Pressure altitude: 1200 ft. O.A.T.: 16°C. Gross weight: 3480 lbs. Wind: 10 knots (headwind)] Takeoff ground roll: 1050 ft. (3-Blade); 1200 ft. (2-Blade) Lift off speed; 68 KIAS WT. LBS. T.O. SPEED-KIAS 3600 68 3400 67 3200 66 3000 65 2800 64 2600 63 8000 FT. PRESSURE ALTITUDE 6000 4000 2000 SEA LEVEL -40 0 20 10 30 40 -30 -20-10 OUTSIDE AIR TEMPERATURE - °C TAILWIND PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA 3 BLADE PROPELLER 4000 2 BLADE PROPELLER 4000 HEADWIND 3000 3000 TAKEOFF GROUND ROLL - FT. 2000 -2000 1000 -1000 0 3600 3400 3200 3000 2800 2600 5 10 15 WEIGHT - POUNDS WIND COMPONENT -KTS. PERFORMANCE SECTION 5 REPORT: VB-1060 5-18 ISSUED: JANUARY 9, 1980 MAXIMUM EFFORT TAKEOFF GROUND ROLL-FLAPS 25° ISSUED: JANUARY 9, 1980 Figure 5-17 REPORT: VB-1060 5-19 MAXIMUM TAKEOFF PERFORMANCE - FLAPS 25° Figure 5-15 Example: Pressure altitude: 1200 ft. O.A.T.: 16°C. Gross weight: 3480 lbs. Wind: 10 knots (headwind) Takeoff distance: 1450 ft. (3-Blade): 1600 ft. (2-Blade) Lift off speed: 65 KIAS Barrier speed: 70 KIAS PA-32-301 MAXIMUM EFFORT TAKEOFF PERFORMANCE - FLAPS 25° ASSOCIATED CONDITIONS: 2700 RPM AND FULL THROTTLE BEFORE BRAKE RELEASE PAVED, LEVEL DRY RUNWAY T.O. SPEED-KIAS WT. LBS. LIFTOFF BARRIER 3600 66 71 3400 64 69 3200 63 67 3000 61 65 2800 60 63 2600 58 61 FT. PRESSURE ALTITUDE -40 TEMP 8000 6000 4000) 2000 SEA LEVEL -30 -20-10 0 10 20 30 40 OUTSIDE AIR TEMPERATURE - °C Example: REF. LINE 3600 LBS LINE ZERO WIND TAILWIND HEADWIND 3-BLADE PROPELLER 4000 3000 PROPELLER 4000 BLADE-2 |--ון-וווןווווןוווון TAKEOFF DISTANCE OVER 50 FT. BARRER-FT. 3000 2000 2000 1000 1000 0 3600 3400 3200 3000 2800 2600 WEIGHT - POUNDS 0 5 10 15 WIND COMPONENT - KTS. PA-32-301 MAXIMUM EFFORT TAKEOFF GROUND ROLL-FLAPS 25° ASSOCIATED CONDITIONS: 2700 RPM AND FULL THROTTLE BEFORE BRAKE RELEASE PAVED, LEVEL DRY RUNWAY Pressure altitude: 1200 ft. O.A.T.: 16°C. Gross weight: 3480 lbs. Wind: 10 knots (headwind) Takeoff ground roll: 950 ft. (3-Blade); 1100 ft. (2-Blade)

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Lift off speed: 65 KIAS FT. PRESSURE ALTITUDE 10000 ☑ 8000 6000 4000 2000 EMP SEA LEVELY -40 -30 -20 -10 -0 10 20 30 $40 OUTSIDE AIR TEMPERATURE - °C REF. LINE WT. LBS. T.O. SPEED-KIAS 3600 66 3400 64 3200 63 3000 61 2800 60 2600 584 REF. LINE ZERO WIND TAILWIND 3-BLADE PROPELLER 2-BLADE PROPELLER 4000 HEADWIND 3000 3000 2000 2000 1000 1000 3600 3400 3200 3000 2800 2600 WEIGHT- POUNDS 0 5 10 15 WIND COMPONENT - KTS. TAKEOFF GROUND ROLL-FT. PERFORMANCE SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION SECTION 5 REPORT: VB-1060 5-20 CLIMB PERFORMANCE (2 BLADE PROPELLER - 2600 RPM) Figure 5-19 REVISED: OCTOBER 3, 1980 ISSUED: JANUARY 9, 1980 Example: Cruise pressure alt.: 6000 ft. Cruise OAT: +5°C Gross weight: 3480 lbs. PA-32-301 CLIMB PERFORMANCE FULL THROTTLE, 2600 RPM WHEEL FAIRINGS INSTALLED 2 BLADE PROPELLER, 90 KIAS Rate of climb: 520 FPM 14000 12000 10000 PRESSURE ALTITUDE -40 Figure 5-21 (3 BLADE PROPELLER - NO TIME LIMIT) CLIMB PERFORMANCE (2 BLADE PROPELLER - 5 MIN LIMIT) ISSUED: JANUARY 9, 1980 REPORT: VB-1060 5-21 8000 6000 2000 SEA LEVEL -30 -20 -10 010 20 30 40 OUTSIDE AIR TEMPERATURE - °C 3600 LBS. 3000 LBS. 200 400 NOTE RATE OF CLIMB IS REDUCED APPROX. 60 FPM IF WHEEL FAIRINGS ARE NOT INSTAL LED. MIXTURE AT FULL RICH MIXTURE AT 50°F RICH OF PEAK E.G.T. ☑3600 LBS. 3000 LBS. 600 800 RATE OF CLIMB FPM 1000 1200 SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION PERFORMANCE SECTION 5 Example: Cruise pressure alt: 6000 ft. Cruise OAT: +4°C Gross weight: 3480 lbs. Rate of climb: 620 FPM PA-32-301 O CLIMB PERFORMANCE FULL THROTTLE, 2700 RPM WHEEL FAIRINGS INSTALLED 90 KIAS 2 & 3 BLADE PROPELLER NOTE RATE OF CLIMB IS REDUCED APPROX. 60 FPM IF WHEEL FAIRINGS ARE NOT INSTAL- LED NOTE FOR NORMAL OPERATIONS WITH 2-BLADE PROPELLER INSTALLED REDUCE POWER TO 2600 RPM AS SOON AS OBSTACLES AND TERRAIN PERMITS. 14000 12000 10000 8000 2000 PRESSURE ALTITUDE-FT. 6000 4000 SEA LEVEL -40 -30 -20-10 20 30 0 10 OUTSIDE AIR TEMPERATURE - °C 3600 LBS. 3000 LBS 40 200 400 MIXTURE AT FULL RICH -MIXTURE AT 50°F RICH OF PEAK E.G.T. 3600 LBS. 600 800 3000 LBS. RATE OF CLIMB FPM 1000 1200 REPORT: VB-1060 5-22 Example: PA-32-301 FUEL, TIME AND DISTANCE TO CLIMB Departure airport altitude: 1200 ft. Departure airport temp.: +16°C. Cruise pressure altitude: 6000 ft. Cruise outside air temp.: +6°C. ASSOCIATED CONDITIONS: FLAPS UP, 3600 LBS GROSS WEIGHT MAXIMUM CONTINUOUS POWER 90 KIAS, NO WIND Time to climb: 8.5 less 1.5 7 min. Distance to climb: 15.7 less 2.6 = 13.1 NM Fuel to climb: 4 less .8 3.2 gal. *2700 RPM FULL THROTTLE (3-BLADE) 2600 RPM FULL THROTTLE (2-BLADE) CRUISE $8000 PRESSURE ALT. FT. 6000 14000 12000 100001 FUEL, TIME AND DISTANCE TO CLIMB Figure 5-23 ISSUED: JANUARY 9, 1980 SNO TIME MINUTES DISTANCE NAUTICAL MILES SECTION 5 PERFORMANCE PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA SEA LEVEL DEPARTURE AIRPORT -40 -30 -20 -10 0 OUTSIDE AIR TEMPERATURE -°C 10 20 30 40 0 10 20 30 40 FUEL, TIME AND DISTANCE TO CLIMB 50 60 1 4000 2000 อ PRESS. STD. ALT. POWER SETTING TABLE - LYCOMING 10-540K ENGINE 55% POWER 65% POWER 75% POWER RPM 2200 2300 2400 2500 2600 2200 2300 2400 2500 2600 2200 2300 2400 2500 2600 ALT. TEMP. MANIFOLD PRESSURE - INCHES MERCURY FEET °C S.L. 15 1000 13 22.9 22.1 21.6 22.5. 21.8 2000 11 22.1 21.4 21.3 20.7 3000 9 21.1 20.7 25.8 24.8 24.0 23.5 23.1 28.2 20.4 25.3 24.4 23.7 23.1 22.7 27.6 20.5 20.1 24.8 24.0 23.3 22.8 22.4 21.8 21.1 20.7 20.2 19.8 24:3 23.6 23.0 4000 7 21.5 20.8 20.4 5000 5 21.2 20.5 20.1 20.0 19:5 19.7 19.3 6000 3 7000 20.0 19.6 19.1 18.8 22.6 20.8 20.3 19.9 19:4 19.0 23.0 22.5 22.0 21.5 21.2 20.5 23.8 23.4 22.1 26.5 23.3 22.6 22.1 21.8 22.9 22.3 21.8 21.5 27.1 26.4 25.7 25.1 20.6 25.9 25.3 24.8 26.2 25.5 25.0 24.5 25.8 25.2 24.7 24.2 25.5 24.8 24.4 24.0 24.6 24.1 23.7 23.9 23.5 22.2 21.7 21.2 20.9 23.3 8000 -1 20.2 19.7 19.3 18.9 18.5 22.2 21.8 21.4 20.9 20.6 9000 -3 19.9 19.5 19.1 18.6 18.3 21.1 20.6 20.3 10000 -5 11000 -7 17000 -9 19.6 19.2 18.8 18.4 18.0 19.3 19.0 18.6 18.7 18.4 18.2 17.8 20.3 20.0 19.7 13000 -11 17.9 17.6 17.7 17.4 14000 -13 17.2 POWER SETTING TABLE ISSUED: JANUARY 9, 1980 REVISED: OCTOBER 7, 1983 Figure 5-25 REPORT: VB-1060 5-23 To maintain constant power, correct manifold pressure approximately 0.15" Hg for each 5°C variation in induction air temperature from standard altitude temperature. Add manifold pressure for air temperature above standard; subtract for temperature below standard. APPROXIMATE FUEL FLOW 55% Power 65% Power 75% Power 11.9 GPH 13.8 GPH 16.0 GPH NOTE: Full throttle manifold pressure values may not be obtainable when atmospheric conditions are non-standard. PERFORMANCE SECTION 5 REPORT: VB-1060 ISSUED: JANUARY 9, 1980 5-24 THIS PAGE INTENTIONALLY LEFT BLANK PERFORMANCE SECTION 5 PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION SECTION 5 PERFORMANCE Example: Cruise pressure altitude: 6000 ft. Cruise outside air temp: +6°C True airspeed: 150.5 PA-32-301 MAXIMUM SPEED PERFORMANCE ASSOCIATED CONDITIONS: FLAPS UP, MIXTURE-FULL RICH, WHEEL FAIRINGS INSTALLED, 3600 LBS GROSS WEIGHT IF WHEEL FAIRINGS ARE NOT INSTALLED SUBTRACT 8 KTS MAXIMUM SPEED PERFORMANCE Figure 5-27 REVISED: SEPTEMBER 17, 1984 ISSUED: JANUARY 9, 1980 REPORT: VB-1060 5-25 14000 PRESSURE ALTITUDE 0008 4000 2000 SEA LEVEL 2700 RPM THROTTLE (2-BLADE) FULL THROTTLE (3-BLADE) OR: 12800 RPM F 130 TRUE AIRSPEED KNOTS 10 20 40 110 120 °C -40 -30 -20 OUTSIDE AIR TEMPERATURE- 5-26 REPORT: VB-1060 Example: PA-32-301 TTTTTTTTTT SPEED O CRUISE POWER - ASSOCIATED CONDITIONS: FLAPS UP, MIXTURE LEANED TO PEAK E.G.T. WHEEL FAIRINGS INSTALLED, 3600 LBS. GROSS WEIGHT IF WHEEL FAIRINGS ARE NOT INSTALLED SUBTRACT 8 KTS Cruise pressure altitude: 6000 ft. Cruise outside air temp.: +6°C Power: 65% True airspeed. 136 kts. NOTE: CRUISE SPEED WILL INCREASE APPROX. 2 KNOTS AND FUEL FLOW WILL INCREASE APPROX. 16% WHEN LEANED TO 50°F RICH OF PEAK EGT. APPROXIMATE HIGH SPEED ECONOMY LONG RANGE (75%) (65%) (55%) 2700 RPM (3-BLADE) 2800 RPM (2-BLADE)] FULL THROTTLE SPEED CRUISE POWER Figure 5-29 14000 12000 10000 8000 POWER FUEL CONS. 76% 16.0 GPH 65% 13.8QPH 55% 11.9 GH -40 -30 -20 -10 PRESSURE ALTITUDE FT.6000 4000 2000 SEA LEVEL OUTSIDE AIR TEMPERATURE - °C 0 10 20 30 40 110 Figure 5-31 ISSUED: JANUARY 9, 1980 REVISED: OCTOBER 7, 1983 REVISED: OCTOBER 7, 1983 ISSUED: JANUARY 9, 1980 REPORT: VB-1060 5-27 55% 65% 130 75% 140 150 TRUE AIRSPEED - KNOTS 120 THIS FIGURE INTENTIONALLY LEFT BLANK SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION PERFORMANCE SECTION 5 LITER 5-28 REPORT: VB-1060 -13 14000 55% PA-32-301 55% 65% RANGE CRUISE POWER ASSOCIATED CONDITIONS: RANGE INCLUDES CLIMB AND DESCENT DISTANCE MIXTURE LEANED TO PEAK EGT, 102 GAL. USABLE FUEL, FLAPS UP WHEEL FAIRINGS INSTALLED, NOTES 1. ADD 1 N.M. RANGE FOR EACH DEGREE CENTIGRADE ABOVE STANDARD TEMPERATURE. 2. SUBTRACT 1.5 N.M. RANGE FOR EACH DEGREE CENTI- GRADE BELOW STANDARD TEMPERATURE. 3. REDUCE RANGE BY 7% IF WHEEL FAIRINGS ARE NOT INSTALLED. 65% 10000 3600 LBS. GROSS WEIGHT, NO WIND 45 MIN. RESERVE AT 55% POWER BEST APPROXIMATE POWER FUEL CONS. 8000 76% 16.0 GPH 75% 65% 13.8 GPH NO RESERVE 75% 55% 11.9 GPH -9 12000 8000 PRESSURE ALTITUDE STANDARD TEMPERATURE - °C RANGE CRUISE POWER Figure 5-33 ISSUED: JANUARY 9, 1980: REVISED: OCTOBER 7, 1983, 7 4000 11 2000 Example: Cruise pressure altitude: 6000 ft. Cruise outside air temp.: +6°C Power: 65% Range with reserve: 873 N.M. + 1x (6-3)=876 N.M. Range no reserve: 962 N.M. + 1 x (6-3) 965 N.M. SECTION 5 PERFORMANCE HIGH SPEED ECONOMY LONG RANGE (75%) (65%) (55%) 1000 RANGE 800 900 1000 1100 NAUTICAL MILES (INCLUDES DISTANCE TO CLIMB AND DESCEND) 15 SEA LEVEL 700 800 900 REVISED: OCTOBER 7, 1983 ISSUED: JANUARY 9, 1980 Figure 5-35 REPORT: VB-1060 5-29 PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION PERFORMANCE SECTION 5 THIS FIGURE INTENTIONALLY LEFT BLANK PRESSURE ALTITUTDE - FT. 14000 12000 REPORT: VB-1060 5-30 Figure 5-37 ENDURANCE REVISED: OCTOBER 7, 1983 ISSUED: JANUARY 9, 1980 FUEL, TIME AND DISTANCE TO DESCEND Figure 5-39 ISSUED: JANUARY 9, 1980 REPORT: VB-1060 5-31 10000 8000 6000 4000 2000 14000 PA-32-301 ENDURANCE ASSOCIATED CONDITIONS: FLAPS UP MIXTURE LEANED TO PEAK EGT 102 GAL. USABLE FUEL, 3600 POUNDS GROSS WEIGHT ENDURANCE SHOWN INCLUDES CLIMB & DESCENT TIMES 75% 55% POWER APPROXIMATE POWER FUEL CONS 75% 16.0 GPH 65% 13.8 GPH 66% 11.9 GPH 45 MIN. RESERVE AT 65% POWER NO RESERVE Example: Cruise pressure altitude: 6000 ft. Power: 35% Endurance with reserva: 5 Endurance no reserve: 7.15 ENDURANCE - HOURS HIGH SPEED ECONOMY LONG RANGE 75% 65% 65% POWER PA-32-301 FUEL, TIME AND DISTANCE TO DESCEND ASSOCIATED CONDITIONS: FLAPS UP POWER AS REQUIRED FOR 121 KIAS AND 500 FPMA DESCENT 3600 LBS. GROSS WEIGHT, NO WIND Example: Cruise pressure altitude: 6000 ft. Cruise outside air temp.: +6°C Destination airport pressure altitude: 1000 ft. Destination airport outside air temp.: +24°C Fuel to descend: 1.9 less 02 Time to descent 12:21 Distance to 10 min. escend: 25 less 4 21 NM 12000 PRESSURE ALT. FT. 10000 8000 6000 4000 2000 CRUISE FUEL SNO SEA LEVEL DESTINATION AIRPORT -40 -30-20 -10 0 10 20 30 OUTSIDE AIR TEMPERATURE - °C 40 ° 10 TIME MINUTES DISTANCE NAUTICAL MILES 201 30 60 FUEL, TIME AND DISTANCE TO DESCEND 80 (75%) (65%) (55%) PERFORMANCE SECTION S PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION PERFORMANCE SECTION 5 REPORT: VB-1060 5-32 Figure 5-41 GLIDE RANGE ISSUED: JANUARY 9, 1980 PA-32-301 GLIDE RANGE ASSOCIATED CONDITIONS: 80 KIAS, POWER OFF 3600 LBS. GROSS WEIGHT, FLAPS UP PROPELLER FULL DECREASE, NO WIND Example: Cruise pressure altitude: 12000 ft. Cruise O.A.T.: 0°C Terrain pressure altitude: 1000 ft. Terrain O.A.T.: 19°C. 3 Glide Range: 18 minus 1.5= 16.5 N.M. 20000 18000 PRESSURE ALT. FT. 16000 14000 12000 10000 8000 6000 4000 2000 -40 -30 SEA LEVEL O -20 -10 10 20 30 OUTSIDE AIR TEMPERATURE - °C CRUISE TERRAIN 40 10 20 30 GLIDE RANGE NAUTICAL MILES 40 PA-32-301 LANDING PERFORMANCE STANDARD WHEELS, TIRES AND BRAKES ASSOCIATED CONDITIONS: WING FLAPS 40°, POWER OFF PAVED LEVEL DRY RUNWAY FULL STALL TOUCHDOWN MAXIMUM BRAKING 79 APPROACH SPEED KIAS 78 77 76 10000 8000 LANDING PERFORMANCE - STANDARD WHEELS, Figure 5-43 TIRES AND BRAKES ISSUED: JANUARY 9, 1980 REPORT: VB-1060 5-33 6000 Example: 4000 2000 FT. PRESSURE ALTITUDE SEA LEVEL Destination pressure altitude: 400 ft. Destination O.A.T.: 24°C. Landing weight: 3300 lbs.; approach speed 78 KIAS Wind: 5 knots (headwind) Landing distance: 1490 ft. -40 -30 -20 0 10 -10 20 30 40 OUTSIDE AIR TEMPERATURE - °C 3600 LBS. REF. LINE PERFORMANCE SECTION 5 ZERO WIND อ PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA EADWIND 2000 1800 1600 PA-32-301, SARATOGA PIPER AIRCRAFT CORPORATION LANDING DISTANCE OVER 5C FT. BARRIER-FT. 1400 1200 1000 3600 3400 3200 3000 2800 2600 WEIGHT - POUNDS 0 10 5 15 WIND COMPONENTS - KTS. PERFORMANCE SECTION 5 LANDING GROUND ROLL - STANDARD WHEELS, REPORT: VB-1060 5-34 TIRES AND BRAKES Figure 5-45 ISSUED: JANUARY 9, 1980 Example: PA-32-301 LANDING GROUND ROLL STANDARD WHEELS, TIRES AND BRAKES ASSOCIATED CONDITIONS: WING FLAPS 40°, POWER OFF, PAVED LEVEL DRY RUNWAY FULL STALL TOUCHDOWN, MAXIMUM BRAKING 10000 FT. PRESSURE ALTITUDE 1000° 6000 4000 2000 SEA LEVEL STD. TEMP. Destination pressure altitude: 400 ft. Destination O.A.T.: 24°C. Landing weight: 3300 lbs. Wind: 5 knots (headwind) Landing ground roll: 630 ft. -40 -30 -20 -10 OUTSIDE AIR TEMPERATURE - °C 3600 LBS. ZERO WIND TAILWIND 1000 800 LANDING GROUND ROLL DISTANCE FT. 600 400 200 10 20 30 40 3600 3400 3200 3000 2800 2600 WEIGHT - POUNDS ° 5 10 15. WIND COMPONENTS - KTS. SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32-301, SARATOGA

All Piper PA-32R Saratoga normal procedures