Weight & Balance, Performance Calculation

Piper PA-32R Saratoga II HP · Weight And Balance

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Overview

This document serves as a Weight & Balance reference for the Piper PA-32R Saratoga II HP, detailing critical information regarding the aircraft's loading limits, fuel capacity, and performance calculations. It is intended for pilots and aviation enthusiasts who require precise data for safe operation. The manual outlines the maximum weight limits, fuel specifications, and loading recommendations to ensure compliance with safety regulations. It also includes emergency procedures and performance metrics essential for flight planning and execution.

Maximum ramp weight: 3,615 lbs
Maximum takeoff weight: 3,600 lbs
Total fuel capacity: 107 US gallons
Usable fuel: 102 US gallons
Emergency airspeed for power-off landing: 83 KIAS

Document

Source

Originally published by www.lausanne-aeroclub.ch. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Weight And Balance
Year: 2004
Pages: 62
File size: 59 MB
Publisher: www.lausanne-aeroclub.ch

Specifications & performance

Extracted from this document.

Specifications

Engine (hp): 300
Propeller: 3 blade
Engine model: Lycoming
Max speed (kt): 191
Fuel capacity (gal): 107
Max takeoff weight (lb): 3,600

Performance

Max crosswind (kt): 17

V-speeds

VA: 134
VX: 85
VY: 93
VFE: 110
VNE: 191
VNO: 160

Weight & balance

Max ramp weight (lb): 3,615
Baggage allowance (lb): 100
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 II HP.

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

More Piper PA-32R Saratoga II HPmanuals & documents

In this document

Limitations

This section outlines the operational limitations for the Piper PA-32R Saratoga II HP, including airspeed limits such as VNE (191 KIAS), VNO (160 KIAS), and maximum takeoff weight (3,600 lbs). It emphasizes the importance of adhering to these limitations to ensure safe flight operations.

Weight and Balance

The maximum ramp weight for the Piper PA-32R Saratoga II HP is 3,615 lbs, with a maximum takeoff weight of 3,600 lbs. Each baggage compartment can hold up to 100 lbs. Pilots are reminded to check weight and balance before flight to ensure compliance with safety standards.

Fuel Capacity

The aircraft has a total fuel capacity of 107 US gallons, with 102 US gallons usable. Each wing holds 51 US gallons, and there is an unusable fuel amount of 5 US gallons (2.5 US gallons per wing). This information is crucial for flight planning and weight calculations.

Emergency Procedures

The manual includes emergency procedures for engine power loss in flight, advising pilots to maintain a safe airspeed of 83 KIAS and prepare for a power-off landing if necessary. It emphasizes the importance of following these procedures to ensure passenger safety.

Performance Calculations

Performance calculations are essential for flight planning, including takeoff and landing distances, climb rates, and fuel consumption. The document provides guidelines for calculating these metrics based on the aircraft's weight and environmental conditions.

Safety notes

Check weight and balance before flight
Adhere to operational limitations to ensure safety
Monitor fuel levels and ensure compliance with usable fuel specifications

Full document text

07.06.16 PA-32-301 / pac 1 PA-32R-301 SARATOGA II HP HB-PJE S/N 3246223 2004 07.06.16 PA-32-301 / pac 2 TECHNICAL GROUND COURSE PROGRAM • AIRCRAFT GENERAL • Airplane Equipment • Airframe Structure • Fuselage - Wings • Limitations PA-32R-301 • POWERPLANT • Engine Description • Engine Fuel System • Oil System • Propeller System • Engine Controls • Indicating System • Limitations • Emergency Procedures 07.06.16 PA-32-301 / pac 3 TECHNICAL GROUND COURSE PROGRAM • SYSTEMS • Fuel System • Electrical System • Landing Gear • Environmental Systems • Flight Controls • Flight Instrumentation • Mass & Balance • General Loading Recommendations • Mass & Balance Record • Performances • Airspeed Calibration • Stall Speeds • Wind Components • Take-Off performances • Climb: Time, Consumption, Distance • Cruise Performances • Descent: Time, Consumption, Distance • Landings Performances PA-32R-301 07.06.16 PA-32-301 / pac 4 Airplane Equipment ü 3 blade propeller ü engine: - Lycoming 300Hp (AVGAS only) - Six cylinder, direct drive, horizontally opposed, air cooled, fuel injected ü retractable gear ü 6 seats (2 center seats aft facing) ü 2 doors: - RH for pilot & copilot - LH for passengers ü 2 separate baggage compartments PA-32R-301 07.06.16 PA-32-301 / pac 5 Airframe / Fuselage / Wing ü basic airframe: aluminum alloy exeption: - steel engine mount - landing gear - tips of wings, tail fin, stabilisator (plastic) ü wings: semi-tapered design main spar ≈ 40% of the chord each wing: 2 interconnected fuel tanks ü fuselage: semi-monocoque structure front door on the RH side rear door on the LH side cargo door aft of the rear passenger door PA-32R-301 07.06.16 PA-32-301 / pac 6 Airframe / Fuselage / Wing PA-32R-301 07.06.16 PA-32-301 / pac 7 Airframe / Fuselage / Wing PA-32R-301 07.06.16 PA-32-301 / pac 8 Limitations ü Airspeed: VNE: 191 KIAS (red radial) VNO: 160 KIAS (yellow arc limit) VA: 134 KIAS (3’600 Lbs) 105 KIAS (2’230 Lbs) VFE: 110 KIAS VLO: extention 132 KIAS retraction 110 KIAS VLE: 132 KIAS 1 LDG Gear Flaps PA-32R-301 07.06.16 PA-32-301 / pac 9 Limitations Green arc: 160 KIAS to 67 KIAS White arc: 110 KIAS to 63 KIAS 2 PA-32R-301 Yellow arc: 160 KIAS to 67 KIAS 07.06.16 PA-32-301 / pac 10 Limitations 2 PA-32R-301 Vy Vx gear down, flaps up not published gear up, flaps up gear down, flaps up 85 KIAS gear up, flaps up 93 KIAS not published 07.06.16 PA-32-301 / pac 11 Limitations 2 Max demo X-WIND: 17 Kts PA-32R-301 07.06.16 PA-32-301 / pac 12 Limitations ü Weight: Max Ramp W. : 3’615 Lbs 2 Max TOF W. : 3’600 Lbs Max Bag : 100 Lbs each comp. ! Check W & B ! ü Fuel: Total capacity: 107 USG Unusable: 5 USG (2.5 USG / wing) Usable: 102 USG (51 USG / wing) PA-32R-301 07.06.16 PA-32-301 / pac 13 ü Load factors: Max positive 0° flaps : 3.8 G Max positive full flaps : 2.0 G Max negative : no inverted maneuvers approved ! ü Types of operations: Day VFR / Night VFR Day IFR / Night IFR Non icing ! Limitations 3 PA-32R-301 07.06.16 PA-32-301 / pac 14 ü Lycoming: 300 Hp at 2’700 RPM Powerplant 1 geared starter 90 A alternator dual magnetos vacuum pump drive diaphragm-type fuel pump fuel injection PA-32R-301 07.06.16 PA-32-301 / pac 15 intake air box 2 Lycoming: Powerplant induction air through the filter (normal procedure) bypass the filter (heated air directly to the engine) (in case of blocked filter) Not be used for GND OP & TOF a manually operated two-way valve PA-32R-301 07.06.16 PA-32-301 / pac 16 fuel injection system 3 ü Lycoming: Powerplant servo regulator (meters fuel flow in proportion to airflow) fuel flow divider to the individual cylinder fuel nozzles PA-32R-301 07.06.16 PA-32-301 / pac 17 4 Powerplant ü Engine Monitoring System: PA-32R-301 07.06.16 PA-32-301 / pac 18 4 Powerplant Oil quantity: max 12 Qts min 6 Qts ü Lycoming: PA-32R-301 07.06.16 PA-32-301 / pac 19 5 constant speed propeller Powerplant ü Propeller: controlled by a governor hydraulically actuated PA-32R-301 07.06.16 PA-32-301 / pac 20 1 Engine controls PA-32R-301 Propeller control lever Throttle control lever Mixture control lever 07.06.16 PA-32-301 / pac 21 2 Engine controls Propeller (RPM) Throttle (MP) Mixture (GPH) PA-32R-301 07.06.16 PA-32-301 / pac 22 2 Engine limitations TOF power 2’700 RPM 3 blades prop: no limitation Max cont. power 2’600 RPM PA-32R-301 07.06.16 PA-32-301 / pac 23 1 PA-32R-301 Emergency Engine limitations .....................UP If sufficient altitude has been gained to attempt a restart: Maintain safe airspeed Fuel selector .................................................................................... switch to tank containing fuel Electric fuel pump .................................................................................. check ON Mixture ..............................................................................................check RICH Alternate air ................................................................................................ OPEN If power is not regained, proceed with power offlanding. ENGINE POWER LOSS IN FLIGHT If at low altitude: Airspeed .............................................................•...............MAINTAIN 83 KIAS Prepare for power off landing. REPORT: VB-1669 3-2 Minimum ISSUED: JUNE 30, 1997 PA-32R-301, SARATOGA II HP SECTION3 EMERGENCY PROCEDURES ENGINE POWER LOSS IN FLIGHT (continued) If permits: Fuel selector .................................................................................... switch to tank containing fuel Electric fuel pump ......................................................................................: .... ON Mixture ........................................................................................................ RICH Alternate air ................................................................................................ OPEN

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Engine gauges ....................................................................... check for indication of cause of power loss If no fuel flow is indicated, check tank selector position to be sure it is on a tank containing fuel. When power is restored: Alternate air ...........................................................................................CLOSED Electric fuel pump .......................................................................................... OFF Mixture ................................................................................... adjust as necessary If power is not restored prepare for power off landing. POWER OFF LANDING Trim for 83 KIAS Locate suitable field. Establish spiral pattern. 1000 ft. above field at downwind position for normal landing approach. When field can easily be reached extend full flaps for shortest landing. 07.06.16 PA-32-301 / pac 24 PA-32R-301 1 Fuel system Standard capacity 102 USG usable (51 USG each wing) (107 USG total) 07.06.16 PA-32-301 / pac 25 PA-32R-301 2 Fuel system 07.06.16 PA-32-301 / pac 26 PA-32R-301 3 Fuel system 3 drains 07.06.16 PA-32-301 / pac 27 PA-32R-301 3 Fuel system 3 drains 07.06.16 PA-32-301 / pac 28 PA-32R-301 3 Fuel system 2 gauges in the cockpit 51 usable USG 51 usable USG 07.06.16 PA-32-301 / pac 29 PA-32R-301 1 Electrical system: 24 volts system 24 volts battery (beneath the floor of aft baggage compartment) 90 A alternator External power relay (right side) 07.06.16 PA-32-301 / pac 30 PA-32R-301 1 Electrical system: Remember: starting with external source is in normal procedure !! 07.06.16 PA-32-301 / pac 31 PA-32R-301 2 Electrical system: switches Starter BAT ALT Fuel Pump Magnetos Magnetos 07.06.16 PA-32-301 / pac 32 PA-32R-301 3 Electrical system: switches 07.06.16 PA-32-301 / pac 33 PA-32R-301 4 Electrical system: breakers 07.06.16 PA-32-301 / pac 34 PA-32R-301 5 Electrical system: rheostat switches Must be to DAY position to check LDG Gear 3 green lights 07.06.16 PA-32-301 / pac 35 PA-32R-301 5 Electrical system: Anunciator panel 07.06.16 PA-32-301 / pac 36 PA-32R-301 6 Electrical system: avionic master switch 07.06.16 PA-32-301 / pac 37 PA-32R-301 7 Electrical system: avionic master switch bypass ? 07.06.16 PA-32-301 / pac 38 PA-32R-301 8 Electrical system: cabine lights Check OFF position when leaving 07.06.16 PA-32-301 / pac 39 PA-32R-301 2 Electrical system: 2 cabin courtesy lights !! Directly wired to the hot battery 07.06.16 PA-32-301 / pac 40 PA-32R-301 1 Landing gear: retractable tricycle hydraulic actuated by an electrically powered reversible pump 07.06.16 PA-32-301 / pac 41 PA-32R-301 2 Landing gear: selector switch LDG Gear is retracted or extended in about 7 seconds 07.06.16 PA-32-301 / pac 42 PA-32R-301 2 Landing gear: Gear Warning Light + Warning Horn q Gear Up + PWR < 14 inches (Manifold Pressure) q Gear Selector Switch UP + ACFT on Ground q Gear not down and locked + Flaps beyond Approach Position ( >10°) 07.06.16 PA-32-301 / pac 43 PA-32R-301 4 Landing gear: emergency procedure Ø distinguish between emergency and training (next page) !! 07.06.16 PA-32-301 / pac 44 PA-32R-301 5 Landing gear: emergency procedure / TRAINING In Normal Procedures (section 4) 07.06.16 PA-32-301 / pac 45 PA-32R-301 6 Landing gear: steering & towing 07.06.16 PA-32-301 / pac 46 PA-32R-301 1 Environmental system: heating & ventilating system 07.06.16 PA-32-301 / pac 47 PA-32R-301 2 Environmental system: heating & ventilating system 07.06.16 PA-32-301 / pac 48 PA-32R-301 1 Flight controls: dual flight controls 07.06.16 PA-32-301 / pac 49 PA-32R-301 2 Flight controls: trims 07.06.16 PA-32-301 / pac 50 PA-32R-301 4 Flight controls: rudder trims 07.06.16 PA-32-301 / pac 51 PA-32R-301 5 Flight controls: Flaps 07.06.16 PA-32-301 / pac 52 PA-32R-301 5 Flight controls: Flaps 0° & 10° 25° & 40° PA·32R-301, SARATOGA II HP • SECTION7 DESCRIPTION & OPERATION 07.06.16 PA-32-301 / pac 53 PA-32R-301 1 Flight instruments: pitot-static system Airspeed indicator Altimeters (2) Vertical speed indicator 07.06.16 PA-32-301 / pac 54 PA-32R-301 2 Flight instruments: pitot-static system 07.06.16 PA-32-301 / pac 55 PA-32R-301 3 Flight instruments: pitot-static system pitot heat 07.06.16 PA-32-301 / pac 56 PA-32R-301 5 Flight instruments: pitot-static system Alternate Static air Window & cabin vent: closed ! Cabin heater & defroster: ON ! 07.06.16 PA-32-301 / pac 57 PA-32R-301 6 Flight instruments: remember: to operate the air driven gyros vacuum system 07.06.16 PA-32-301 / pac 58 PA-32R-301 6 Flight instruments: vacuum system See Section 9 / Supp 2 PA-32R-301, SARATOGA ll HP SECTION 1 - GENERAL SECTION9 SUPPLEMENT 2 This supplement supplies information necessary for the operation of the airplane when the optional Piper Auxiliary Vacuum System is installed. The information contained within this supplement is to be used in conjunction with the complete handbook. SECTION 2- LIMITATIONS (a) The auxiliary vacuum system is limited to standby function only, do not take off with the engine driven dry air pump inoperative. (b) Discontinue flight in Instrument Meteorological Conditions (IMC) if vacuum pressure falls below 4.8 ln. Hg. (c) The auxiliary pump/motor assembly and elapsed time indicator must be removed from service after 500 hours accumulated operating time or 10 years whichever occurs first. SECTION 3- EMERGENCY PROCEDURES (a) VAC OFF or Vacuum lnop. Warning- Auxiliary Vacuum Switch AUXON. (b) Verify vacuum system suction is within the normal operating range. CAUTION Compass error may exceed 10° when auxiliary vacuum system is in operation. (c) Monitor electrical load - verify alternator capacity is not being exceeded as indicated by the ammeter. If required turn off non-essential electrical equipment. (d) Land at the earliest opportunity.to have primary system repaired. 07.06.16 PA-32-301 / pac 59 PA-32R-301 7 Flight instruments: Horizontal Situation Indicator 07.06.16 PA-32-301 / pac 60 PA-32R-301 8 Flight instruments: Autopilot 07.06.16 PA-32-301 / pac 61 PA-32R-301 8 Flight instruments: Autopilot S-TEC CORPORATION MINERAL WELLS, TEXAS 76067 FAA/DAS APPROVED • PILOT'S OPERATING HANDBOOK AND/OR AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR PIPER MODELS PA-32R-301 AND PA-32R-301 T Immediately regain control of the aircraft by ovexpowering the autopilot as necessary and then immediately disconnect the autopilot. Do not re- engage the autopilot nntil the problem has been identified and corrected. 1. The autopilot may be disconnected by: a. Depressing the "AP Disconnect" Switch on the left hom of the pilot's control wheel. b. Placing the "AP Master Switch" in the "OFF" position. c. Momentarily interrupting aircraft electrical power at the battery master switch. d. Pulling the autopilot circuit breaker. 2. Trim: a. In the event of a trim failure, manually control aircraft I and DEPRESS AND HOLD "Trim Interrupt/AP Disconnect Switch" on control wheel. b. Place trim master switch in "OFF" position, pull circuit breaker, release interrupt switch. c. Retrim aircraft. Leave trim system OFF until corrected. 3. Altitude loss during a malfunction and recovery: a. The following . altitude losses and bank angles were recorded after a malfunction with a 3 second recovery delay: Weight & Balance, Performance Calculation See separate presentation PA-32R-301

All Piper PA-32R Saratoga II HP weight and balance