Pilot's Operating Handbook
Piper PA-31 Navajo · Pilot's Operating Handbook
Overview
This Pilot's Operating Handbook (POH) is designed for the Piper PA-31 Navajo, providing essential information for pilots operating this twin-engine aircraft. The manual includes detailed specifications, performance data, operating procedures, and safety information necessary for the safe and efficient operation of the aircraft. It serves as a comprehensive reference for both experienced pilots and those new to the PA-31 Navajo, ensuring that users can familiarize themselves with the aircraft's systems and capabilities. The handbook emphasizes the importance of adhering to the outlined procedures to maintain safety and performance standards during flight operations.
- Maximum takeoff weight: 6,000 lbs (2,722 kg)
- Maximum cruise speed: 200 knots
- Stall speed: 70 knots
- Service ceiling: 25,000 ft
- Range: approximately 1,200 nautical miles
Document
Source
Originally published by flighttest.net. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Pilot's Operating Handbook
- Pages
- 195
- File size
- 8.8 MB
- Publisher
- flighttest.net
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 310
- Height (ft)
- 11
- Length (ft)
- 32
- Propeller
- Hartzell
- Wingspan (ft)
- 48
- Engine model
- TIO-540-A
- Empty weight (lb)
- 2,280
- Fuel capacity (gal)
- 190
- Rate of climb (fpm)
- 1,395
- Service ceiling (ft)
- 260
- Max takeoff weight (lb)
- 6,500
Performance
- Fuel burn (gph)
- 35.6
- Landing over 50ft
- 1,120
- Takeoff over 50ft
- 1,390
- Landing distance (ft)
- 1,550
- Takeoff distance (ft)
- 1,685
Weight & balance
- Useful load (lb)
- 620
- Baggage allowance (lb)
- 150
- Basic empty weight (lb)
- 2,280
- Max landing weight (lb)
- 6,200
- Max takeoff weight (lb)
- 6,500
Common. Rarer than 3% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Piper PA-31 Navajo.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the PA-31 Navajo to your watchlist and track it in one place.
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In this document
Aircraft Specifications
The Piper PA-31 Navajo is a twin-engine aircraft with a maximum takeoff weight of 6,000 lbs (2,722 kg). It features a wingspan of 38 ft 0 in (11.58 m) and a length of 27 ft 4 in (8.33 m). The aircraft is powered by two Lycoming IO-540-U4A5 engines, each producing 250 hp.
Performance Data
The PA-31 Navajo has a maximum cruise speed of 200 knots and a stall speed of 70 knots. The service ceiling is 25,000 ft, and the range is approximately 1,200 nautical miles with full fuel.
Operating Procedures
Pilots must follow specific preflight checks, including verifying fuel levels, checking control surfaces, and ensuring all systems are operational. The engine start procedure includes a checklist that must be adhered to for safety.
Emergency Procedures
In the event of an engine failure, pilots should maintain control of the aircraft and follow the emergency checklist to safely land the aircraft. This includes identifying the failed engine and executing the appropriate procedures.
Weight and Balance
Proper weight and balance calculations are critical for safe flight operations. The maximum allowable weight for the PA-31 Navajo is 6,000 lbs, and pilots must ensure that the center of gravity is within specified limits before flight.
Safety notes
- Always perform preflight checks as outlined in the manual.
- Adhere to weight and balance limits to ensure safe flight operations.
- In case of engine failure, follow the emergency procedures immediately.
Full document text
THE DUPLICATE 31-420 NAVAJO PILOT'S OPERATING MANUAL NAVAJO N63747 BY PIPER This manual is incomplete without an APPROPRIATE FAA APPROVED AIRPLANE FLIGHT MANUAL and an APPROPRIATE WEIGHT AND BALANCE REPORT. TALUSUG Assurance that the airplane is in an airworthy condition is the responsibility of the owner. The pilot in command is responsible for determining that the airplane is safe for flight. The pilot is also responsible for remaining within the operating limitations outlined by the Flight Manual, instrument markings, and placards. If an inconsistency of information exists between this handbook and the Flight Manual approved by the FAA, the Flight Manual shall be the authority. This Manual pertains to Turbocharged PA-31 - Navajo's Serial No. 31-1 to 31-659 and Serial No. 31-661 to 31-711 excluding all PA-31-300 Navajo's Serial Nos. 31-228, 31-230, 31-270, 31-279, 31-316, 31-339, 31-415, 31-426, 31-451, 31-455, 31-483 and 31-511. Additional copies of this manual, Part No. 761 456, may be obtained from your Piper Dealer. Published by PUBLICATIONS DEPARTMENT Piper Aircraft Corporation 761456 Issued: September 1970 TABLE OF CONTENTS GENERAL SPECIFICATIONS DESCRIPTION - AIRPLANE AND SYSTEMS FLIGHT MANUAL FAA APPROVED EMERGENCY PROCEDURE FAA APPROVED WEIGHT AND BALANCE OPERATING INSTRUCTIONS OPERATING TIPS PERFORMANCE CHARTS HANDLING AND SERVICING BLANK PAGE REVISIONS The information compiled in this manual will be kept current by revisions distributed to the airplane owners through their local dealers or distributors. There are two types of revisions used to keep the Pilot's Operating Manual current; Temporary Revisions and Permanent Revisions. The material compiled in the revisions will consist of information necessary to update the present information or add information to cover added equipment. I. Temporary Revision This revision will be distributed at any time it is necessary to forward information to the owners and operators of the airplane. The revision will usually consist of one or two pages which may be inserted in the appropriate section of the manual. This revision will include deletions and/or additions of material pertinent to different paragraphs of the manual. II. Permanent Revision This revision will be distributed periodically and will supersede all previous temporary revisions. These revisions will be complete page replacement and shall be inserted in the manual in accordance with the instructions given below. 1. 2. Replace the obsolete pages with revised pages of the same page number. Insert pages with page numbers followed by a small letter in direct sequence with the same common numbered page. III. Identification of Revised Material Revised text and illustrations shall be indicated by a black vertical line along the left hand margin of the page, opposite revised, added or deleted material. A line opposite the page number or section title and printing date, will indicate that the text or illustration was unchanged but that material was relocated to a different page or that an entire page was added. Symbols will indicate only current revisions with changes and additions to or deletions of existing text and illustrations. Changes in capitalization, spelling, punctuation or the physical location of the material on the page will not be identified by symbols. REVISIONS ISSUED Current Permanent and Temporary Revisions to the PA-31 Pilot's Operating Manual issued September, 1970 are as follows: 761 456 (PR720901) Permanent Revision Dated September 1,1972 761 456 (PR740329) Permanent Revision to W/B Dated March 29, 1974 761 456 (PR750321) Permanent Revision to P/O/M, added Rev. 24 to A F/M. Dated March 21, 1975 761 456 (PR760109) 761 456 (PR760621) 761 456 (PR770204) 761 456 (PR770607) 761 456 (PR790703) 761 456 (PR800603) 761 456 (PR810220) 761 456 (PR820402) 761 456 (PR970319) 761 456 (PR020422) Permanent Revision to P/O/M and W/B, added Rev. 25 to A F/M. Permanent Revision to P/O/M, added Rev. 26 to A F/M. Permanent Revision to P/O/M, added Rev. 27 to A F/M. Permanent Revision to P/O/M and W/B, added Rev. 28 to A F/M. Permanent Revision to P/O/M, added Rev. 29 to A F/M. Permanent Revision to P/O/M added Rev. 30 to A F/M. Permanent Revision to P/O/M, added Rev. 31 to A F/M. Permanent Revision to P/O/M, added Rev. 32 to A F/M. Permanent Revision to P/O/M, added Rev. 33 to A F/M. Dated January 9, 1976 Dated June 21, 1976 Dated February 4, 1977 Dated June 7, 1977 Dated July 3, 1979 Dated June 3, 1980 Dated February 20, 1981 Dated April 2, 1982 Dated March 19, 1997 Permanent Revision to P/O/M, added Rev. 34 to A F/M. Dated April 22, 2002 Performance. Weights Power Plant. Fuel and Oil Baggage Dimensions Landing Gear GENERAL SPECIFICATIONS ว 1122222 BLANK PAGE SECTION I GENERAL SPECIFICATIONS NAVAJO PERFORMANCE Published figures are for Standard PA-31 airplanes flown at gross weight under standard conditions at sea level unless otherwise stated. Take-off Run (ft) Take-off Distance over 50-ft. barrier (ft) Minimum Controllable Single Engine Speed (mph). Best Rate of Climb Speed (mph) Best Rate of Climb (ft per min) Best Angle of Climb Speed (mph) Best Single Engine Rate of Climb Speed (mph) Best Single Engine Rate of Climb (ft per min) Best Single Engine Angle of Climb Speed (mph) Service Ceiling (ft). Absolute Ceiling (ft).. Single Engine Service Ceiling (ft) Single Engine Absolute Ceiling (ft) Top Speed at 15,500 ft (mph). Cruising Speed (75% power at sea level) (mph) Cruising Speed (75% power at 23,500) (mph) Optimum Cruising Speed (65% power at 24,000) (mph). Stalling Speed (gear and full flaps) (power off) (mph). Stalling Speed (gear and flaps up) (power off) (mph) Fuel Consumption (75% power) (both engines) (gph). Fuel Consumption (65% power) (both engines) (gph). Cruising Range (75% power at 23,500 ft) (mi). Cruising Range (65% power at 24,000 ft) (mi) Cruising Range (45% power at 24,000 ft) (mi) *190.0 gal usable fuel **45 min reserve WEIGHTS Ramp Weight (lbs).....
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Gross Weight (lbs) Empty Weight (Standard) (six-place) (lbs)..... USEFUL LOAD (Standard) (six-place) (lbs). a - Take-off b Landing, maximum (6500 lbs. with kit 763 801 installed) - GENERAL SPECIFICATIONS REVISED: April 2, 1982 1730 2280 85 110 1395 95 110 245 106 26,300 27,300 15,800 16,400 260 201 247 231 73 80 35.6 27.8 1300* 1120** 1560* 1390** 1685* 1550** 6536 a b 6500 6200 3759 2741 PAGE 1 NAVAJO POWER PLANT Engine, Lycoming Rated Horsepower Rated Speed (rpm) Bore (inches) Stroke (inches) Displacement (cubic inches) Compression Ratio Dry Weight (pounds) FUEL AND OIL Fuel Capacity (U.S. gal) (standard) Usable Fuel (U.S. gal) Fuel, Aviation Grade (minimum octane) Oil Capacity (U.S. qts) (each engine) .TIO-540-A .310 .2575 .5.125 .4.375 .541.5 .7.3:1 .535.00 192 186 .100/130 12 BAGGAGE Maximum Baggage (lbs) Forward Aft Baggage Space (cubic ft) Baggage Door Size (forward) (in) 150 .200 36 .25 x 28 DIMENSIONS Wing Span (ft) Wing Area (sq ft) Length (ft) Height (ft) Wing Loading (lbs per sq ft) Power Loading (lbs per HP) Propeller Diameter (in) Turning Radius (Nose Wheel) (ft) LANDING GEAR Wheel Base (ft) Wheel Tread (ft) Tire Pressure (psi) Nose Tire Size PAGE 2 Main Nose (six-ply rating) Main (eight-ply rating) .40.67 .229 32.63 13.00 .28.4 .10.5 .80 .28 .8.67 13.75 .42 .60 6.00 x 6 ..6.50 x 10 GENERAL SPECIFICATIONS REVISED: March 19, 1997 GENERAL SPECIFICATIONS ISSUED: September 1, 1970 -18' 1.5" -48' 8" -11' 0" 0 -13' 8"- -32′ 7.5" THREE VIEW -88''DIA. 13'0' NAVAJO PAGE 3 BLANK PAGE DESCRIPTION - AIRPLANE AND SYSTEMS Power Plant.. Propellers Structures Landing Gear and Brake System. Hydraulic System Control System. Fuel System. Electrical System. Pneumatic and Pressure Gyro System. Heating System.... Ventilating System.. Instrument Panel Cabin Features Seats...... Baggage Compartments. Finish Number Plates. Oxygen System... Pneumatic Wing and Tail Deicing Electric Propeller Deicer Ice Detection Light Radar. Right Instrument Panel Lighting Fire Extinguisher (Portable) Electric Windshield (Pilot Side Only) Windshield Wiper Anti-Static Wicks.. Electric Pitot Heat.. Cabinet and Dispenser. Wall Divider.. Folding Tables Toilet Installation. Ramp Hailer..... Aft Cabin Heater. 4 7 7 8 13 _ _ _ 13 17 17 17 18 18 18 18 19 1 2 633∞ ∞ NAWWXJJANN 20 20 20 20 ༡༢ 23 23 23 23 24 2222 24 24 24 24 24 25 BLANK PAGE AIRCRAFT AND STANDARD EQUIPMENT DESIGN AND OPERATION NAVAJO POWER PLANT The Navajo is powered by two turbocharged Lycoming TIO-540-A series, six cylinder, fuel injected engines rated at 310 HP at 2575 RPM. The engines are equipped with geared starters, 24 volt 50 or 70 ampere alternators, shielded ignition systems, and dual pneumatic pressure pumps. The turbocharger is designed to increase the power output and efficiency of the engine by supplying compressed air to the engine intake manifold. This allows the engines to operate at peak power at a much higher altitude than normally aspirated engines. The power to drive the turbocharger is extracted from energy in the exhaust gas. The exhaust gases are ducted through the turbine and then directed overboard at the bottom of the nacelles in the area of the cowl flaps. The fuel injection system is based on the principle of measuring engine air consumption by use of a venturi tube and using the airflow forces to control fuel flow to the engines. Fuel distribution to the individual cylinders is obtained by the use of a fuel flow divider and air bleed nozzles. Idle cut-offs are incorporated in the injectors and should always be used to stop the engines. This is accomplished by pulling the mixture control levers to the rearmost position. An automatic alternate induction air system is provided for each engine. Should the induction air filters become obstructed by ice or other causes, the induction air doors will open automatically to provide air to the engine. To the right of the control pedestal are two manual alternate air controls which may be used by the pilot to select alternate air if the automatic feature should fail. The cowl flaps, located on the bottom of the engine nacelles, are electrically operated by switches located in the cabin on the bottom of the engine control quadrant. Cowl flaps should be positioned to maintain temperatures at or below maximum temperature. Remote indicating gauges located next to the switches give the pilot a visual indication of cowl flap position. The engines of the airplane are equipped with doors on the induction housings, and in the event of a turbocharger compressor failure the engine will automatically revert to normally aspirated air. Approximately 75% of normal rated power or 232 HP will be available at sea level. Engine mounts are of steel tubing construction and incorporate vibration absorbing dynafocal mounts. Engine cowls are cantilever structures, attached at the firewall. The nose cowl and side panel assemblies are quickly removed by means of quick-release fasteners. Efficient aluminum oil coolers are attached to each of the engine mounts. PROPELLERS The propellers on the Navajo are Hartzell constant speed, controllable pitch, full-feathering units, each controlled by a governor mounted on the engine. The governors are controlled by levers located in the center of the control quadrant. Feathering of the propeller is accomplished by moving the control fully aft through the low RPM detent into the feathering position. Feathering takes place in approximately seven seconds. A propeller is unfeathered by moving the propeller control ahead and engaging the starter. DESCRIPTION - AIRPLANE AND SYSTEMS REVISED: June 21, 1976 PAGE 1