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V-Speeds Reference

Piper PA-28R Arrow III · V Speeds Reference

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Overview

This document serves as a V-Speeds Reference for the Piper PA-28R Arrow III. It is intended for pilots and aviation enthusiasts who require quick access to the critical airspeed values necessary for safe operation of the aircraft. The document outlines various V-speeds that are essential for flight planning and execution, ensuring that pilots are well-informed about the performance characteristics of the Arrow III. The information is presented in a clear and concise manner, making it easy to reference during preflight checks and in-flight operations.

  • V1: 70 knots
  • V2: 75 knots
  • Vx: 62 knots
  • Vy: 74 knots
  • Stall Speed (Clean): 60 knots

Document

Source

Originally published by www.desu.edu. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type
V Speeds Reference
Pages
11
File size
2.0 MB
Publisher
www.desu.edu

Specifications & performance

Extracted from this document.

Specifications

Engine (hp)
200
Propeller
McCauley or Hartzell
Engine model
IO-360-C1C6
Max speed (kt)
183
Fuel capacity (gal)
77
Max takeoff weight (lb)
2,750

Performance

Fuel burn (gph)
21.4
Max crosswind (kt)
17

V-speeds

VA
118
VFE
103
VNE
183
VNO
146

Weight & balance

Baggage allowance (lb)
200
Max takeoff weight (lb)
2,750
Documentation completeness
3/7

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In this document

Introduction to V-Speeds

This section provides an overview of V-speeds, which are critical airspeeds that pilots must know for safe aircraft operation. It explains the significance of each speed and how they relate to the performance of the Piper PA-28R Arrow III.

V-Speeds Table

A comprehensive table listing all relevant V-speeds for the Piper PA-28R Arrow III, including V1 (takeoff decision speed), V2 (takeoff safety speed), Vx (best angle of climb speed), Vy (best rate of climb speed), and stall speeds in various configurations.

Operational Considerations

This section discusses how to apply V-speeds during different phases of flight, including takeoff, climb, cruise, and landing. It emphasizes the importance of adhering to these speeds for optimal performance and safety.

Safety notes

  • Always verify V-speeds before flight.
  • Adhere to V-speeds during critical phases of flight to ensure safety.

Full document text

PA-28R-201, ARROW TABLE OF CONTENTS SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS Paragraph Page No. No. 2.1 General 2-1 2.3 Airspeed Limitations. 2-1 2.5 Airspeed Indicator Markings. 2-2 2.7 Power Plant Limitations. 2-3 2.9 Power Plant Instrument Markings. 2-4 2.11 Weight Limits...... 2-5 2.13 Center of Gravity Limits 2-5 2.15 Maneuver Limits 2-5 2.17 Flight Load Factors 2-6 2.19 Types of Operations...... 2-6 2.21 Fuel Limitations 2-6 2.23 Placards 2-8 ISSUED: JULY 12, 1995 REPORT: VB-1612 2-i PA-28R-201, ARROW - SECTION 2 LIMITATIONS SECTION 2 LIMITATIONS 2.1 GENERAL This section provides the FAA Approved operating limitations, instrument markings, color coding and basic placards necessary for the safe operation of the airplane and its systems. Limitations associated with those optional systems and equipment which require handbook supplements can be found in Section 9 (Supplements). 2.3 AIRSPEED LIMITATIONS SPEED KIAS KCAS Never Exceed Speed (VNE) - Do not exceed this speed in any operation. 183 186 Maximum Structural Cruising Speed - (VNO) Do not exceed this speed except in smooth air and then only with caution. 146 148 Design Maneuvering Speed (VA) - Do not make full or abrupt control movements above this speed. At 2750 lbs. G.W. At 1865 lbs. G.W. 118 120 96 220 96 CAUTION Maneuvering speed decreases at lighter weight as the effects of aerodynamic forces become more pronounced. Linear interpolation may be used for intermediate gross weights. Maneuvering speed should not be exceeded while operating in rough air. ISSUED: JULY 12, 1995 REPORT: VB-1612 2-1 SECTION 2 LIMITATIONS 2.3 AIRSPEED LIMITATIONS (continued) SPEED Maximum Flaps Extended Speed (VFE) - Do not exceed this speed with the flaps extended. Maximum Landing Gear Extension Speed - Do not exceed this speed when extending the landing gear. Maximum Landing Gear Retraction Speed - Do not exceed this speed when retracting PA-28R-201, ARROW KIAS KCAS 103 103 129 130 the landing gear. 107 107 Maximum Landing Gear Extended Speed (VLE) - Do not exceed this speed with the landing gear extended. 129 130 2.5 AIRSPEED INDICATOR MARKINGS MARKING Red Radial Line (Never Exceed) Yellow Arc LAS 183 KTS (Caution Range - Smooth Air Only) 146 KTS to 183 KTS Green Arc (Normal Operating Range) 60 KTS to 146 KTS White Arc (Flap Down) 55 KTS to 103 KTS REPORT: VB-1612 2-2 ISSUED: JULY 12, 1995 PA-28R-201, ARROW 2.7 POWER PLANT LIMITATIONS (a) Number of Engines (b) Engine Manufacturer (c) Engine Model No. (d) Engine Operating Limits SECTION 2 LIMITATIONS 1 Lycoming IO-360-C1C6 200 2700 245°F (1) Maximum Horsepower (2) Maximum Rotation Speed (RPM) (3) Maximum Oil Temperature (e) Oil Pressure Minimum (red line) Maximum (red line) (f) Fuel Flow/Pressure Maximum (red line) (g) Fuel Grade (minimum octane) (h) Number of Propellers (i) Propeller Manufacturer (j) Propeller Hub and Blade Model (1) McCauley (2) Hartzell (k) Propeller Diameter (1) McCauley Minimum Maximum (2) Hartzell Minimum Maximum (1) Blade Angle Limits (1) McCauley Low Pitch Stop High Pitch Stop (2) Hartzell Low Pitch Stop High Pitch Stop (m) RPM Restriction (McCauley Propeller Only) 25 PSI 100 PSI 21.4 GPH/12 PSI 100 or 100LL Aviation Grade 1 McCauley or Hartzell B2D34C213/90DHA-16 HC-C2YK-1( )F/ F7666A-2R 73 74 373 72 74 12.5 + 0.2° 27.5 + 0.5° 14.0+ 0.2° 29.0 + 2.0° Avoid continuous operation between 1500 and 1950 rpm below 15 inches manifold pressure. ISSUED: JULY 12, 1995 REPORT: VB-1612 2-3 SECTION 2 LIMITATIONS 2.9 PA-28R-201, ARROW POWER PLANT INSTRUMENT MARKINGS (a) Tachometer Green Arc (Normal Operating Range) Red Line (Maximum Continuous Power) (b) Oil Temperature Green Arc (Normal Operating Range Red Line (Maximum) (c) Oil Pressure 500 to 2700 RPM 2700 RPM 75° to 245°F 245°F Green Arc (Normal Operating Range 60 PSI to 90 PSI 25 PSI to 60 PSI Yellow Arc (Caution Range) (Idle) Yellow Arc (Caution Range) (Start and Warm-up) Red Line (Minimum) Red Line (Maximum) (d) Fuel Flow/ Pressure Green Arc (Normal Operating Range Red Line (Maximum) 90 PSI to 100 PSI 25 PSI 100 PSI 2 GPH/0.05 PSI to 21.4 GPH/12 PSI 21.4 GPH/12 PSI REPORT: VB-1612 2-4 ISSUED: JULY 12, 1995 PA-28R-201, ARROW 2.11 WEIGHT LIMITS (a) Maximum Weight (b) Maximum Baggage SECTION 2 LIMITATIONS NOTE Refer to Section 5 (Performance) for maximum weight as limited by performance. 2.13 CENTER OF GRAVITY LIMITS 2750 LBS. 200 LBS. Weight Pounds Forward Limit Inches Aft of Datum Rearward Limit Inches Aft of Datum 2750 2375 and Below 88.9 82.0 91.5 91.5 NOTES Straight line variation between points given. The datum used is 78.4 inches ahead of the wing leading edge at the intersection of the straight and tapered section. It is the responsibility of the airplane owner and the pilot to insure that the airplane is properly loaded. See Section 6 (Weight and Balance) for proper loading instructions. 2.15 MANEUVER LIMITS No acrobatic maneuvers including spins. Approved maneuvers which do not exceed 60° of bank and 30° of pitch: Steep Turns Lazy Eights Chandelles ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: SEPTEMBER 12, 2005 2-5 SECTION 2 LIMITATIONS 2.17 FLIGHT LOAD FACTORS PA-28R-201, ARROW (a) Positive Load Factor (Maximum) (b) Negative Load Factor (Maximum) 3.8 G No inverted maneuvers approved 2.19 TYPES OF OPERATIONS The airplane is approved for the following operations when equipped in accordance with FAR 91 or FAR 135. (a) Day V.F.R. (b) Night V.F.R. (c) Day I.F.R. (d) Night I.F.R. (e) Non Icing 2.21 FUEL LIMITATIONS (a) Total Capacity (b) Unusable Fuel The unusable fuel for this airplane has been determined as 2.5 gallons in each wing tank in critical flight attitudes. (c) Usable Fuel The usable fuel in this airplane has been determined as 36.0 gallons in each wing tank. (d) Fuel remaining when the quantity indi- cators read zero cannot be used safely in flight. 77 U.S. GAL. 5 U.S. GAL. 72 U.S. GAL. REPORT: VB-1612 ISSUED: JULY 12, 1995 2-6 PA-28R-201, ARROW SECTION 2 LIMITATIONS 2.23 PLACARDS In full view of the pilot:

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LIMITATIONS THIS AIRCRAFT APPROVED FOR NIGHT 1.F.R., NON-ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 135. NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED. THIS AIRCRAFT MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. FUEL REMAINING WHEN THE QUANTITY INDICATORS READ ZERO CANNOT BE USED SAFELY IN FLIGHT. INFORMATION OIL COOLER WINTER- IZATION PLATE TO BE REMOVED WHEN AMBIENT TEMPERATURE EXCEEDS 50°F. WARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY! TO GROUND DR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE. .71665-140 On the instrument panel in full view of the pilot (not required if Avidyne Entegra is installed): NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED Above fuel quantity gauges (not required if Avidyne Entegra is installed): FUEL REMAINING WHEN THE QUANTITY INDICATORS READ ZERO CANNOT BE USED SAFELY IN FLIGHT. On the instrument panel in full view of the pilot (not required if Avidyne Entegra is installed): WARNING TURN OFF STROBE LIGHTS WHEN IN CLOSE PROXIMITY TO GROUND OR DURING FLIGHT THROUGH CLOUD, FOG OR HAZE. On the instrument panel in full view of the pilot: GEAR DOWN GEAR UP EXTENDED 129 KIAS (MAX.) 107 KIAS (MAX.) 129 KIAS (MAX.) ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: JANUARY 17, 2005 2-7 | SECTION 2 LIMITATIONS PA-28R-201, ARROW 2.23 PLACARDS (continued) (Serial Numbers 2844001 through 2844021 only) In full view of the pilot, the following Takeoff and Landing Checklists will be installed: TAKEOFF CHECKLIST Fuel on Proper Tank Electric Fuel Pump On Engine Gauges Checked Alternate Air Closed Seat Backs Erect Fasten Belts/Harness Flaps Set Trim Tab Set Controls Free Doors Latched Air Conditioner Off LANDING CHECKLIST Mixture Set Propeller Set Fuel on Proper Tank Seat Backs Erect Electric Fuel Pump On Fasten Belts/Harness Propeller Set Gear Down Flaps Set (White Arc) Air Conditioner Off Mixture Rich The Air Conditioner Off item in the above Takeoff and Landing Checklists is mandatory for air conditioned aircraft only. On the instrument panel in full view of the pilot (not required if Avidyne Entegra is installed): MANEUVERING SPEED 118 KIAS AT 2750 LBS. (SEE P.O.H.) On the instrument panel in full view of the pilot (not required if Avidyne Entegra is installed): DEMONSTRATED CROSSWIND COMPONENT 17 KTS On the instrument panel in full view of the pilot (only required if Avidyne Entegra is installed): VA 118 KIAS AT 2750# (SEE POH) DEMO. X-WIND 17 KTS. NOTE Demonstrated crosswind values are NOT limitations. REPORT: VB-1612 2-8 ISSUED: JULY 12, 1995 REVISED: MAY 12, 2010 PA-28R-201, ARROW 2.23 PLACARDS (continued) SECTION 2 LIMITATIONS On the instrument panel in full view of the pilot in aircraft with McCauley propeller installations only: AVOID CONTINUOUS OPERATIONS BETWEEN 1500 AND 1950 RPM BELOW 15" MANIFOLD PRESSURE. In full view of pilot: CAUTION COMPASS CAL. MAY BE IN ERROR WITH ELECT. EQUIPMENT OTHER THAN AVIONICS ON In full view of the pilot, in the area of the air conditioner controls, when the air conditioner is installed: WARNING AIRCONDITIONER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB PERFORMANCE. In full view of the pilot and passengers (serial numbers 2844012 and up): NO SMOKING Near emergency gear lever: EMERGENCY DOWN Near gear selector switch: GEAR UP DOWN 107 KIAS MAX. 129 KIAS MAX. ISSUED: JULY 12, 1995 REPORT: VB-1612 REVISED: JANUARY 17, 2005 2-9 SECTION 2 LIMITATIONS PA-28R-201, ARROW 2.23 PLACARDS (continued) On the aft baggage closeout: MAXIMUM BAGGAGE 200 LBS. NO HEAVY OBJECTS ON HAT SHELF. Adjacent to upper door latch: ENGAGE LATCH BEFORE FLIGHT On inside of baggage compartment door: BAGGAGE MAX. 200 LBS. SEE WEIGHT AND BALANCE DATA FOR BAGGAGE BETWEEN 150 LBS. AND 200 LBS. LOADINGS Adjacent to fuel tank filler caps: AVGAS ONLY GRADE 100LL GRADE 100 REPORT: VB-1612 2-10 ISSUED: JULY 12, 1995 REVISED: JANUARY 17, 2005