Page 1 HANDBOOK THIS ELECTRONIC VERSION OF THE POH IS NOT APPROVED TO REPLACE ANY OPERATING INFORMATION REQUIRED BY THE REGULATIONS. PIPER CHEROKEE WARRIOR II APPROVED NORMAL UTILITY PA-28-161 CATEGORIES BASED ON CAR 3 AND FAR PART 21, REPORT: VB-880 SUBPART J. THIS HANDBOOK INCLUDES THE...
Page 2 SUBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE IDENTIFIED ON THE FACE OF THE TITLE PAGE WHEN OFFICIALLY APPROVED. SUBSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT CORPORATION MUST BE PROPERLY INSERTED. MODEL PA-28-161, CHEROKEE WARRIOR II PILOT’S OPERATING HANDBOOK, REPORT: VB-880 REVISION _________________________________...
Page 3 APPLICABILITY Application of this handbook is limited to the specific Piper PA-28-161 model airplane designated by serial number and registration number on the face of the title page of this handbook. This handbook cannot be used for operational purposes unless kept in a current status.
Page 4 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS Current Revisions to the PA-28-161 Cherokee Warrior II Pilot’s Operating Handbook, REPORT:-VB-880 issued December 16, 1976. Revision FAA Approval Revised Number and Description of Revision Signature and Pages Code Date Rev. 1 - 761 649 Corrected to “Meteorological.”...
Page 5 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Revised Number and Description of Revision Signature and Pages Code Date Rev. 2 - 761 649 5-19 Relocated Best Econ. Cruise Perf. to 5-23; (PR770711) added chart relocated from 5-16. (cont) 5-20 Relocated Best Power Mix.
Page 6 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Revised Number and Description of Revision Signature and Pages Code Date Rev. 2 - 761 649 Added STC No. to Section 1 - General; in (PR770711) Section 2 revised (a); in Section 3 revised (cont) (a), deleted (c) and renumbered accordingly, revised (c) and (d);...
Page 7 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Revised Number and Description of Revision Signature and Pages Code Date Rev. 3-761649 6-45 Added info. from pg. 6-44; revised item 201; re- (PR780630) located info. to pg. 6-46. (cont.) 6-46 Added info.
Page 8 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Revised Number and Description of Revision Signature and Pages Code Date Rev. 6 - 761 649 Revised Before Starting Engine. (PR790703) Added Descent; relocated Approach and (cont.) Landing to pg. 4-6. Added Approach and Landing from pg.
Page 9 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Revised Number and Description of Revision Signature and Pages Code Date Rev. 7 - 761 649 Revised para 1.7. (PR800530) Revised para. 1.11. Revised para. 2.7 Revised para. 2.13. Added page; added to para. 2.25. Revised para.
Page 10 Revised para. 7.25. Added supplement 6 and pages. 9-15 thru Retyped supplement 5 Century 21 auto pilot; 9-18 changed pg. nos. 9-19 thru Added supplement 6 Piper Control Wheel Clock 9-20 Installation. Ward Evans Dec. 18, 1980 REPORT: VB-880 iv-f...
Page 11 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Revised Number and Description of Revision Signature and Pages Code Date Rev. 10 - 761 649 Revised Warning. (PR810629) Revised para. 1.13. Added warning. Revised Figure 6-5. 6-19 Revised item 11 . 6-27 Revised items 33, 35 and 39.
Page 12 PILOT’S OPERATING HANDBOOK LOG OF REVISIONS (cont) Revision FAA Approval Revised Number and Description of Revision Signature and Pages Code Date Rev. 11 - 761 649 6-47 Relocated items 229 and 231 from pg. 6-46; (PR811120) moved item 247 to pg. 6-48. (cont) 6-48 Relocated item 247 from pg.
Page 13 TABLE OF CONTENTS SECTION 1 GENERAL SECTION 2 LIMITATIONS SECTION 3 EMERGENCY PROCEDURES SECTION 4 NORMAL PROCEDURES SECTION 5 PERFORMANCE SECTION 6 WEIGHT AND BALANCE SECTION 7 DESCRIPTION AND OPERATION OF THE AIRPLANE AND ITS SYSTEMS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE SECTION 9 SUPPLEMENTS...
Page 14: Table Of Contents
TABLE OF CONTENTS SECTION 1 GENERAL Paragraph Page Introduction............................Engines.............................. Propellers ............................Fuel ..............................Oil ..............................1.11 Maximum Weights..........................1.13 Standard Airplane Weights ....................... 1.15 Baggage Space..........................1.17 Specific Loadings ..........................1.19 Symbols, Abbreviations and Terminology ..................1.21 Conversion Factors ........................... 1-11 REPORT: VB-880...
Page 15: Introduction
PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-161, CHEROKEE WARRIOR II GENERAL SECTION 1 GENERAL 1.1 INTRODUCTION This Pilot’s Operating Handbook is designed for maximum utilization as an operating guide for the pilot. It includes the material required to be furnished to the pilot by C.A.R. 3 and FAR Part 21, Subpart J.
Page 16 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-161, CHEROKEE WARRIOR II THREE VIEW Figure 1-1 REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 17: Engines
PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-161, CHEROKEE WARRIOR II GENERAL 1.3 ENGINES (a) Number of Engines (b) Engine Manufacturer Lycoming (c) Engine Model Number 0-320-D2A or 0-320-D3G (d) Rated Horsepower (e) Rated Speed (rpm) 2700 Bore (inches) 5.125 (g) Stroke (inches) 3.875...
Page 18: Maximum Weights
SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-161, CHEROKEE WARRIOR II 1.11 MAXIMUM WEIGHTS NORMAL UTILITY (a) Maximum Takeoff Weight (lbs) 2325 2020 (b) Maximum Landing Weight (lbs) 2325 2020 (c) Maximum Weights in Baggage Compartment 1.13 STANDARD AIRPLANE WEIGHTS Refer to Figure 6-5 for the Standard Empty Weight and the Useful Load.
Page 19: Symbols, Abbreviations And Terminology
PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-161, CHEROKEE WARRIOR II GENERAL 1.19 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY The following definitions are of symbols, abbreviations and terminology used throughout the handbook and those which may be of added operational significance to the pilot.
Page 20 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-161, CHEROKEE WARRIOR II (b) Meteorological Terminology International Standard Atmosphere in which: The air is a dry perfect gas; The temperature at sea level is 15° Celsius (59° Fahrenheit); The pressure at sea level is 29.92 inches hg. (1013 mb);...
Page 21 PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-161, CHEROKEE WARRIOR II GENERAL (c) Power Terminology Takeoff Power Maximum power permissible for takeoff. Maximum Continuous Maximum power permissible continuously during flight. Power Maximum Climb Power Maximum power permissible during climb. Maximum Cruise Power Maximum power permissible during cruise.
Page 22 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-161, CHEROKEE WARRIOR II Weight and Balance Terminology Reference Datum An imaginary vertical plane from which all horizontal distances are measured for balance purposes. Station A location along the airplane fuselage usually given in terms of distance from the reference datum.
Page 23 PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-161, CHEROKEE WARRIOR II GENERAL THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: DECEMBER 16, 1976 REPORT: VB-880...
Page 24 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976 1-10...
Page 25: Conversion Factors
PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-161, CHEROKEE WARRIOR II GENERAL 1.21 CONVERSION FACTORS MULTIPLY TO OBTAIN MULTIPLY TO OBTAIN acres 0.4047 cubic inches (cu. in.) 16.39 43560 sq. ft. 1.639 x 10 0.0015625 sq. mi. 5.787 x 10 cu. ft.
Page 26 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-161, CHEROKEE WARRIOR II MULTIPLY TO OBTAIN MULTIPLY TO OBTAIN feet per second 0.6818 hectares (ha) 2.471 acres (ft./sec.) 1.097 km/hr. 107639 sq. ft. 30.48 cm/sec. 10000 0.5921 kts. horsepower (hp) 33000 ft.-lb./min. foot-pounds (ft.-lb.) 0.138255...
Page 27 PIPER AIRCRAFT CORPORATION SECTION 1 PA-28-161, CHEROKEE WARRIOR II GENERAL MULTIPLY TO OBTAIN MULTIPLY TO OBTAIN kilograms per square 2.896 x 10 in. Hg meters per minute 0.06 km/hr. meter (kg/m 1.422 x 10 lb./sq. in. (m/min.) 0.2048 lb./sq. ft.
Page 28 SECTION 1 PIPER AIRCRAFT CORPORATION GENERAL PA-28-161, CHEROKEE WARRIOR II MULTIPLY TO OBTAIN MULTIPLY TO OBTAIN ounces, fluid per 0.073 l/ha 16.5 acre (fl. oz./ acre) 5.029 pounds (lb.) 0.453592 slug 32.174 453.6 3.108 x 10 slug square centimeters 0.1550 sq.
Page 29 TABLE OF CONTENTS SECTION 2 LIMITATIONS Paragraph Page General.............................. Airspeed Limitations......................... Airspeed Indicator Markings ......................Power Plant Limitations........................Power Plant Instrument Markings ....................2.11 Weight Limits............................ 2.13 Center of Gravity Limits........................2.15 Maneuver Limits..........................2.17 Flight Load Factors ........................... 2.19 Types of Operations ..........................
Page 30 PIPER AIRCRAFT CORPORATION SECTION 2 PA-28-161, CHEROKEE WARRIOR II LIMITATIONS SECTION 2 LIMITATIONS 2.1 GENERAL This section provides the “FAA Approved” operating limitations, instrument markings, color coding and basic placards necessary for operation of the airplane and its systems. This airplane must be operated as a normal or utility category airplane in compliance with the operating limitations stated in the form of placards and markings and those given in this section and handbook.
Page 31: Airspeed Indicator Markings
SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-28-161, CHEROKEE WARRIOR II 2.5 AIRSPEED INDICATOR MARKINGS MARKING Red Radial Line (Never Exceed) 160 KTS Yellow Arc (Caution Range - Smooth Air Only) 126 KTS to 160 KTS Green Arc (Normal Operating Range)
Page 32: Power Plant Instrument Markings
PIPER AIRCRAFT CORPORATION SECTION 2 PA-28-161, CHEROKEE WARRIOR II LIMITATIONS 2.9 POWER PLANT INSTRUMENT MARKINGS (a) Tachometer Green Arc (Normal Operating Range) 500 to 2700 RPM Red Line (Maximum Continuous Power) 2700 RPM (b) Oil Temperature Green Arc (Normal Operating Range) 75°...
Page 33: Center Of Gravity Limits
SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-28-161, CHEROKEE WARRIOR II 2.13 CENTER OF GRAVITY LIMITS (a) Normal Category Weight Forward Limit Rearward Limit Pounds Inches Aft of Datum Inches Aft of Datum 2325 87.0 93.0 1950 (and less) 83.0 93.0...
Page 34: Types Of Operations
PIPER AIRCRAFT CORPORATION SECTION 2 PA-28-161, CHEROKEE WARRIOR II LIMITATIONS 2.19 TYPES OF OPERATION 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.
Page 35 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 36: Placards
PIPER AIRCRAFT CORPORATION SECTION 2 PA-28-161, CHEROKEE WARRIOR II LIMITATIONS 2.25 PLACARDS In full view of the pilot: “THIS AIRPLANE MUST BE OPERATED AS A NORMAL OR UTILITY CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS.
Page 37 SECTION 2 PIPER AIRCRAFT CORPORATION LIMITATIONS PA-28-161, CHEROKEE WARRIOR II In full view of the pilot, in the area of the air conditioner control panel when the air conditioner is installed: “WARNING—AIR CONDITIONER MUST BE OFF TO INSURE NORMAL TAKEOFF CLIMB PERFORMANCE.”...
Page 38 PIPER AIRCRAFT CORPORATION SECTION 2 PA-28-161, CHEROKEE WARRIOR II LIMITATIONS Adjacent to fuel filler caps: FUEL - 100 OR 100LL AVIATION GRADE FUEL - 100 AVIATION GRADE MIN. USABLE CAPACITY 24 GAL. USABLE CAPACITY TO BOTTOM OF FILLER NECK INDICATOR 17 GAL.
Page 39 TABLE OF CONTENTS SECTION 3 EMERGENCY PROCEDURES Paragraph Page General ..............................Emergency Procedures Check List ...................... Engine Fire During Start ......................Engine Power Loss During Takeoff ................... Engine Power Loss On Flight ....................Power Off Landing ........................Fire In Flight..........................Loss of Oil Pressure ........................
Page 40: General
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-161, CHEROKEE WARRIOR II EMERGENCY PROCEDURES SECTION 3 EMERGENCY PROCEDURES 3.1 GENERAL This section provides the recommended procedures for coping with various emergency or critical situations. All of the emergency procedures required by the FAA as well as those necessary for operation of the airplane, as determined by the operating and design features of the airplane, are presented.
Page 41 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 42: Emergency Procedures Check List
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-161, CHEROKEE WARRIOR II EMERGENCY PROCEDURES 3.3 EMERGENCY PROCEDURES CHECK LIST ENGINE FIRE DURING START If power is not restored prepare for power off landing. Starter ............crank engine Trim for 73 KIAS Mixture ............idle cut-off Throttle ..............open...
Page 43: Loss Of Fuel Pressure
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-161, CHEROKEE WARRIOR II LOSS OF FUEL PRESSURE ELECTRICAL OVERLOAD (Alternator over 20 amps above known electrical load) Electric fuel pump ..........ON Fuel selector ........check on full tank FOR AIRPLANES WITH SEPARATE BAT...
Page 44: Open Door
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-161, CHEROKEE WARRIOR II EMERGENCY PROCEDURES OPEN DOOR If both upper and lower latches are open, the door will trail slightly open and airspeeds will be reduced slightly. To close the door in flight: Slow airplane to 89 KIAS Cabin vents ............close...
Page 45 SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 46: Amplified Emergency Procedures (General)
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-161, CHEROKEE WARRIOR II EMERGENCY PROCEDURES 3.5 AMPLIFIED EMERGENCY PROCEDURES (GENERAL) The following paragraphs are presented to supply additional information for the purpose of providing the pilot with a more complete understanding of the recommended course of action and probable cause of an emergency situation.
Page 47: Engine Power Loss In Flight
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-161, CHEROKEE WARRIOR II 3.11 ENGINE POWER LOSS IN FLIGHT Complete engine power loss is usually caused by fuel flow interruption and power will be restored shortly after fuel flow is restored. If power loss occurs at a low altitude, the first step is to prepare for an emergency landing (refer to paragraph 3.13).
Page 48: Fire In Flight
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-161, CHEROKEE WARRIOR II EMERGENCY PROCEDURES 3.15 FIRE IN FLIGHT The presence of fire is noted through smoke, smell and heat in the cabin. It is essential that the source of the fire be promptly identified through instrument readings, character of the smoke, or other indications since the action to be taken differs somewhat in each case.
Page 49: Loss Of Fuel Pressure
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-161, CHEROKEE WARRIOR II 3.19 LOSS OF FUEL PRESSURE If loss of fuel pressure occurs, turn “ON” the electric fuel pump and check that the fuel selector is on a full tank. If the problem is not an empty tank, land as soon as practical and have the engine-driven fuel pump and fuel system checked.
Page 50: Spin Recovery
PIPER AIRCRAFT CORPORATION SECTION 3 PA-28-161, CHEROKEE WARRIOR II EMERGENCY PROCEDURES For airplanes with separate BATT and ALT switch operations, turn the BATT switch OFF and the ammeter should decrease. Turn the BATT switch ON and continue to monitor the ammeter. If the alternator output does not decrease within 5 minutes, turn the BATT switch OFF and land as soon as practical.
Page 51: Open Door
SECTION 3 PIPER AIRCRAFT CORPORATION EMERGENCY PROCEDURES PA-28-161, CHEROKEE WARRIOR II 3.27 OPEN DOOR The cabin door on the Cherokee is double latched, so the chances of its springing open in flight at both the top and side are remote. However, should you forget the upper latch, or not fully engage the side latch, the door may spring partially open.
Page 52 TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES Paragraph Page General ..............................Airspeed for Safe Operation ........................ Normal Procedures Check List ......................Preflight Check........................... Before Starting Engine ....................... Starting Engine When Cold......................Starting Engine When Hot ......................Starting Engine When Flooded ....................Starting With Extemal Power Source..................
Page 53 TABLE OF CONTENTS SECTION 4 NORMAL PROCEDURES (Continued) Paragraph Page 4.31 Stopping Engine ........................... 4-15 4.33 Parking ..............................4-15 4.35 Stalls ..............................4-16 4.37 Turbulent Air Operation........................4-16 4.39 Weight and Balance..........................4-16 REPORT: VB-880 4-ii...
Page 54: General
This section describes the recommended procedures for the conduct of normal operations for the Cherokee Warrior II. All of the required (FAA regulations) procedures and those necessary for operation of the airplane as determined by the operating and design features of the airplane are presented.
Page 55 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 56: Normal Procedures Check List
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-161, CHEROKEE WARRIOR II NORMAL PROCEDURES WALK-AROUND Figure 4-1 4.5 NORMAL PROCEDURES CHECK LIST Pitot head..........remove cover - holes clear PREFLIGHT CHECK Windshield ............clean Control wheel ...........release belts Propeller and spinner ..........check Avionics ..............OFF Fuel and oil ..........check for leaks Master switch ............ON...
Page 57: Before Starting Engine
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-161, CHEROKEE WARRIOR II BEFORE STARTING ENGINE STARTING WITH EXTERNAL POWER SOURCE Brakes ..............set Master switch............OFF Carburetor heat..........full OFF All electrical equipment........OFF Fuel selector..........desired tank Terminals ............connect Radios ..............OFF External power plug ........insert in...
Page 58: Before Takeoff
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-161, CHEROKEE WARRIOR II NORMAL PROCEDURES BEFORE TAKEOFF Master switch ............ON SOFT FIELD, OBSTACLE CLEARANCE Flight instruments ..........check Fuel selector..........proper tank Flaps..........25° (second notch) Electric fuel pump ..........ON Accelerate and lift off nose gear as soon as possible.
Page 59: Approach And Landing
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-161, CHEROKEE WARRIOR II DESCENT POWER OFF Carburetor heat ........ON if required Throttle...............closed Airspeed............as required Mixture ............as required Power ....verify with throttle every 30 seconds APPROACH AND LANDING Fuel selector..........proper tank Seat backs .............erect Belts/harness ..........fasten/adjust...
Page 60: Preflight Check
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-161, CHEROKEE WARRIOR II NORMAL PROCEDURES 4.7 AMPLIFED NORMAL PROCEDURES (GENERAL) The following paragraphs are provided to supply detailed information and explanations of the normal procedures necessary for the safe operation of the airplane. 4.9 PREFLIGHT CHECK The airplane should be given a thorough preflight and walk-around check.
Page 61: Before Starting Engine
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-161, CHEROKEE WARRIOR II Check all of the fuel tank vents to make sure they are open. Next, a complete check of the landing gear. Check the main gear shock struts for proper inflation.
Page 62: Startingengine
(d) Starting Engine With External Power Source An optional feature called the Piper External Power (PEP) allows the operator to use an external battery to crank the engine without having to gain access to the airplane’s battery.
Page 63 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-161, CHEROKEE WARRIOR II CAUTION Care should be exercised because if the ship’s battery has been depleted, the external power supply can be reduced to the level of the ship’s battery. This can be tested by turning the master switch ON momentarily while the starter is engaged.
Page 64: Warm-Up
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-161, CHEROKEE WARRIOR II NORMAL PROCEDURES 4.15 WARM-UP Warm-up the engine at 800 to 1200 RPM for not more than two minutes in warm weather and four minutes in cold. Avoid prolonged idling at low RPM, as this practice may result in fouled spark plugs.
Page 65: Before Takeoff
SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-161, CHEROKEE WARRIOR II 4.21 BEFORE TAKEOFF All aspects of each particular takeoff should be considered prior to executing the takeoff procedure. Turn “ON” the master switch and check and set all of the flight instruments as required. Check the fuel selector to make sure it is on the proper tank (fullest).
Page 66: Climb
PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-161, CHEROKEE WARRIOR II NORMAL PROCEDURES obstacle clearance is attained. After the obstacle has been cleared, accelerate to 79 KIAS and then slowly retract the flaps. A short field takeoff with no obstacle is accomplished with no flaps and applying full power before brake release, lift off at 50 KIAS and accelerate to best rate of climb speed, 79 KIAS.
Page 67: Descent
PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-161, CHEROKEE WARRIOR II will have approximately one and one half hours of fuel remaining if the tanks were full at takeoff. The second tank will contain approximately one half hour of fuel. Do not run tanks completely dry in flight.
Page 68 PIPER AIRCRAFT CORPORATION SECTION 4 PA-28-161, CHEROKEE WARRIOR II NORMAL PROCEDURES The mixture control should be kept in full “RICH” position to insure maximum acceleration if it should be necessary to open the throttle again. Carburetor heat should not be applied unless there is an indication of carburetor icing, since the use of carburetor heat causes a reduction in power which may be critical in case of a go-around.
Page 69 SECTION 4 PIPER AIRCRAFT CORPORATION NORMAL PROCEDURES PA-28-161, CHEROKEE WARRIOR II 4.35 STALLS The stall characteristics are conventional. An approaching stall is indicated by a stall warning horn which is activated between five and ten KTS above stall speed. Mild airframe buffeting and gentle pitching may also precede the stall.
Page 70 TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph Page General ..............................Introduction to Performance and Flight Planning................Flight Planning Example........................Performance Graphs..........................List of Figures ..........................REPORT: VB-880...
Page 71 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE SECTION 5 PERFORMANCE 5.1 GENERAL All of the required (FAA regulations) and complementary performance information applicable to this aircraft is provided by this section. Performance information associated with those optional systems and equipment which require handbook supplements is provided by Section 9 (Supplements).
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Page 73 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (a) Aircraft Loading The first step in planning our flight is to calculate the airplane weight and center of gravity by utilizing the information provided by Section 6 (Weight and Balance) of this handbook.
Page 74 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II The conditions and calculations for our example flight are listed below. The takeoff and landing distances required for our example flight have fallen well below the available runway lengths. Departure...
Page 75 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE (d) Descent The descent data will be determined prior to the cruise data to provide the descent distance for establishing the total cruise distance. Utilizing the cruise pressure altitude and OAT we determine the basic time, distance and fuel for descent (Figure 5-25).
Page 76 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Total Flight Time The total flight time is determined by adding the time to climb, the time to descend and the cruise time. Remember! The time values taken from the climb and descent graphs are in minutes and must be converted to hours before adding them to the cruise time.
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Page 78 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 79 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE 5.7 PERFORMANCE GRAPHS LIST OF FIGURES Figure Page Airspeed System Calibration ....................... 5-11 Stall Speed............................5-12 Normal Short Field Ground Roll Distance - No Obstacle ..............5-13 Normal Short Field Takeoff Distance - No Obstacle ................
Page 80 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976 5-10...
Page 81 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE AIRSPEED SYSTEM CALIBRATION Figure 5-1 ISSUED: DECEMBER 16, 1976 REPORT: VB-880 5-11...
Page 82 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Example: Gross weight: 2170 lbs. Angle of bank: 20° Flap position: 40° Stall speed, indicated: 44 KTS STALL SPEED Figure 5-3 REPORT: VB-880 ISSUED: DECEMBER 16, 1976 5-12...
Page 83 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE Example: Departure airport pressure altitude: 1500 ft. Departure airport temperature: 80°F Weight: 2325 lbs. Wind: 15 KTS headwind Ground roll: 1150 ft. Lift-off speed: 50 KIAS NORMAL SHORT FIELD GROUND ROLL DISTANCE - NO OBSTACLE...
Page 84 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Example: Departure airport pressure altitude: 1500 ft. Departure airport temperature: 80°F Weight: 2325 lbs. Wind: 15 KTS headwind Distance over 50 ft. barrier: 2100 ft. Lift-off speed: 50 KIAS Barrier speed: 55 KIAS...
Page 85 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE Example: Departure airport pressure altitude: 1500 ft. Departure airport temperature: 80°F Weight: 2175 lbs. Wind: 15 KTS headwind Ground roll: 975 ft. Lift-off speed: 48 KIAS OBSTACLE CLEARANCE SHORT FIELD GROUND ROLL DISTANCE...
Page 86 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Example: Departure airport pressure altitude: 1500 ft. Departure airport temperature: 80°F Weight: 2175 lbs. Wind: 15 KTS headwind Distance over 50 ft. barrier: 1600 ft. Lift-off speed: 48 KIAS Barrier speed: 53 KIAS...
Page 87 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 60°F Cruise power: 75% Engine RPM: 2645 ENGINE PERFORMANCE (SERIAL NOS. 28-7716001 THROUGH 7716323) Figure 5-9 ISSUED: DECEMBER 16, 1976 REPORT: VB-880...
Page 88 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 60°F Cruise power: 75% Engine RPM: 2620 ENGINE PERFORMANCE (SERIAL NOS. 28-7816001 AND UP) Figure 5-10 REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 89 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE Example: Climb pressure altitude: 5000 ft. Climb OAT: 60°F Rate of climb: 420 ft/min. CLIMB PERFORMANCE Figure 5-11 ISSUED: DECEMBER 16, 1976 REPORT: VB-880 REVISED: JUNE 30, 1978 5-19...
Page 90 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Example: Departure airport pressure altitude: 1500 ft. Departure airport temperature: 80°F (27°C) Cruise pressure altitude: 5000 ft. Cruise OAT: 60°F (16°C) Time to climb (10 min. minus 2.5 min.): 7.5 min.
Page 91 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 60°F Cruise power: 75% best power mixture Cruise speed: 116.5 KTS TAS BEST POWER CRUISE PERFORMANCE (SERIAL NOS. 28-7716001 THROUGH 7716323) Figure 5-15...
Page 92 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 60°F Cruise power: 75% best power mixture Cruise speed: 122.5 KTS TAS BEST POWER CRUISE PERFORMANCE (SERIAL NOS. 28-7816001 AND UP) Figure 5-16...
Page 93 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 60°F Cruise power: 75% best economy mixture Cruise speed: 112.5 KTS TAS BEST ECONOMY CRUISE PERFORMANCE (SERIAL NOS. 28-7716001 THROUGH 7716323) Figure 5-17...
Page 94 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 60°F Cruise power: 75% best power mixture Cruise speed: 118 KTS TAS BEST ECONOMY CRUISE PERFORMANCE (SERIAL NOS. 28-7816001 AND UP) Figure 5-18...
Page 95 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 16°C (11°C above standard) Cruise power: 75% best power mixture Range w/45 min. reserve @ 55% power: 476 + (.6 x 11) = 482.6 nautical miles Range w/no reserve: 533 + (.6 x 11) = 539.6 nautical miles...
Page 96 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 16°C (11°C above standard) Cruise power: 75% best power mixture Range w/45 min. reserve @ 55% power: 501 + (.6 x 11) = 507.6 nautical miles Range w/no reserve: 561 + (.6 x 11) = 567.6 nautical miles.
Page 97 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 16°C (11°C above standard) Cruise power: 75% best economy mixture Range w/45 min. reserve @ 55% power: 540 + (.7 x 11) = 547.7 nautical miles Range w/no reserve: 602 + (.7 x 11) = 609.7 nautical miles...
Page 98 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 16°C (11°C above standard) Cruise power: 75% best economy mixture Range w/ 45 min. reserve @ 55% power: 567 + (.7 x 11) = 574.7 nautical miles Range w/no reserve: 635 + (.7 x 11) = 642.7 nautical miles...
Page 99 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE Example: Cruise pressure altitude: 5000 ft. Cruise power: 75% best economy mixture Endurance w/45 min. reserve @ 55% power: 4.85 hrs. Endurance w/no reserve: 5.45 hrs. ENDURANCE Figure 5-23 ISSUED: JULY 11, 1977...
Page 100 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Example: Destination airport pressure altitude: 2500 ft. Destination airport temperature: 75°F (24°C) Cruise pressure altitude: 5000 ft. Cruise OAT: 60°F (16°C) Time to descend (6.5 min. minus 3.5 min.): 3 min.
Page 101 PIPER AIRCRAFT CORPORATION SECTION 5 PA-28-161, CHEROKEE WARRIOR II PERFORMANCE Example: Cruise pressure altitude: 5000 ft. Terrain pressure altitude: 2000 ft. Glide distance (9.5 miles minus 3.8 miles): 5.7 nautical miles GLIDE PERFORMANCE Figure 5-27 ISSUED: JULY 11, 1977 REPORT: VB-880...
Page 102 SECTION 5 PIPER AIRCRAFT CORPORATION PERFORMANCE PA-28-161, CHEROKEE WARRIOR II Example: Destination airport pressure altitude: 2500 ft. Destination airport temperature: 75°F Destination airport wind: 0 KTS Ground roll: 660 ft. Distance over 50 ft. barrier: 1190 ft. LANDING PERFORMANCE Figure 5-29...
Page 103 TABLE OF CONTENTS SECTION 6 WEIGHT AND BALANCE Paragraph Page General ..............................Airplane Weighing Procedure ......................Weight and Balance Data and Record....................Weight and Balance Determination for Flight ..................6-11 Equipment List ............................. 6-17 Propeller and Propeller Accessories................... 6-17 Engine and Engine Accessories ....................6-19 Landing Gear and Brakes ......................
Page 104: General
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE SECTION 6 WEIGHT AND BALANCE 6.1 GENERAL In order to achieve the performance and flying characteristics which are designed into the airplane, it must be flown with the weight and center of gravity (C.G.) position within the approved operating range (envelope).
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Page 106: Airplane Weighing Procedure
WEIGHT AND BALANCE 6.3 AIRPLANE WEIGHING PROCEDURE At the time of delivery, Piper Aircraft Corporation provides each airplane with the basic empty weight and center of gravity location. This data is supplied by Figure 6-5. The removal or addition of equipment or airplane modifications can affect the basic empty weight and center of gravity.
Page 107 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II (c) Weighing - Airplane Basic Empty Weight (1) With the airplane level and brakes released, record the weight shown on each scale. Deduct the tare, if any, from each reading.
Page 108 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (2) The basic empty weight center of gravity (as weighed including optional equipment, full oil and unusable fuel) can be determined by the following formula: C.G. Arm = N (A) + (R+ L) (B) inches...
Page 109: Weight And Balance Data And Record
SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II 6.5 WEIGHT AND BALANCE DATA AND RECORD The Basic Empty Weight, Center of Gravity Location and Useful Load listed in Figure 6-5 are for the airplane as delivered from the factory. These figures apply only to the specific airplane serial number and registration number shown.
Page 110 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE MODEL PA-28-161 CHEROKEE WARRIOR II 28-7916159 Airplane Serial Number ________________________ N3067D Registration Number __________________________ 11/10/78 Date _______________________________________ AIRPLANE BASIC EMPTY WEIGHT C.G. Arm Weight (Inches Aft Moment Item...
Page 111 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 112 10-19-80 1465.9 ELT install and collins SB# 1 236.2 126995 10-22-81 IFR avionics package installation 1878.9 128874.5 1487.5 21.6 87.0 Piper SB# 631B kit installation 113.6 1489.5 2-21-82 129101.5 KN64 DME installation 6-6-86 58.3 1492.8 129294.5 Nose fairing removal 129139.5 -5.0...
Page 113 PA-28-161 Serial Number Registration Number Page Number Item No. Weight Change Running Basic Added (+) Removed (-) Empty Weight Date Description of Article or Modification In Out Wt. Arm Moment Wt. Arm Moment Wt. Moment (Lb.) (In.) /100 (Lb.) (In.) /100 (Lb.) /100...
Page 114: Weight And Balance Determination For Flight
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE 6.7 WEIGHT AND 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 moment of all items to be carried in the airplane.
Page 115 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II Arm Aft Weight Datum Moment (Lbs) (Inches) (In-Lbs) Basic Empty Weight Pilot and Front Passenger 80.5 Passenger (Rear Seats)* 118.1 Fuel (48 Gallon Maximum) 95.0 Baggage* (200 Lbs. Maximum) 142.8...
Page 116 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE LOADING GRAPH Figure 6-13 ISSUED: DECEMBER 16, 1976 REPORT: VB-880 6-13...
Page 117 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II C. G. RANGE AND WEIGHT Figure 6-15 REPORT: VB-880 ISSUED: DECEMBER 16, 1976 6-14 REVISED: MAY 30, 1980...
Page 118 (b) Decide how to change his load if his first loading is not within the allowable envelope. Heat can warp or ruin the plotter if it is left in the sunlight. Replacement plotters may be purchased from Piper dealers and distributors.
Page 119 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II SAMPLE PROBLEM REPORT: VB-880 ISSUED: DECEMBER 16, 1976 6-16 REVISED: MAY 30, 1980...
Page 120 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE SAMPLE PROBLEM A sample problem will demonstrate the use of the weight and balance plotter. Assume a basic weight and C.G. location of 1300 pounds at 85.00 inches respectively. We wish to carry a pilot and 3 passengers.
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Page 122: Equipment List
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE 6.9 EQUIPMENT LIST The following is a list of equipment which may be installed in the PA-28-161. It consists of those items used for defining the configuration of an airplane when the basic empty weight is established at the time of licensing.
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Page 124: (B) Engine And Engine Accessories
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (b) Engine and Engine Accessories Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Engine a. Lycoming Model 0-320-D2A ______ 272.0 21.3 5794 b. Lycoming Model 0-320-D3G ______ 268.0...
Page 125 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976 6-20...
Page 126: (C) Landing Gear And Brakes
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (c) Landing Gear and Brakes Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) 16 A Two Main Wheel Assemblies a. Cleveland Aircraft Products ______ 32.3...
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Page 128: (D) Electrical Equipment
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (d) Electrical Equipment Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) 20 A Voltage Regulator Piper Dwg. 68804-3 51.9 21 B Battery Piper Dwg. 35544...
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Page 130: (E) Instruments
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (e) Instruments Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) 26 B Altimeter Piper PS50008-2 or -3 Cert. Basis - TSO C10b ______ 60.9...
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Page 132: (F) Miscellaneous
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE Miscellaneous Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) 33 A Front Seat Belts (2) Piper PS50039-4-2A American Safety Eqpt. Corp. 500576 Davis Acft. Prod. Inc.
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Page 134: (G) Engine And Engine Accessories (Optional Equipment)
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (g) Engine and Engine Accessories (Optional Equipment) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Primer System Piper Dwg. 35327-0 ______ 50.0 Carburetor Ice Detector Piper Dwg.
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Page 136: (H) Propeller And Propeller Accessories (Optional Equipment)
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (h) Propeller and Propeller Accessories (Optional Equipment) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) ISSUED: DECEMBER 16, 1976 REPORT: VB-880 6-31...
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Page 138: (I) Landing Gear And Brakes (Optional Equipment)
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE Landing Gear and Brakes (Optional Equipment) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Nose Wheel Fairing Piper Dwg. 35513 ______ 29.8 Main Wheel Fairings Piper Dwg.
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Page 140: (J) Electrical Equipment (Optional Equipment)
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE Electrical Equipment (Optional Equipment) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Instrument Panel Lights Piper Dwg. 35544 ______ 62.8 Instrument Light (2), Grimes...
Page 141 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II Electrical Equipment (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Anti-Collision Lights (Wing tips only) Cert. Basis - STC SA800 EA ______ 157.9...
Page 142: (K) Instruments (Optional Equipment)
60.3 Altitude Digitizer (United Instruments P/N 5125-P3) Cert. Basis - TSO C88 ______ 51.5 Vertical Speed Piper Dwg. 99010-2, -4 or -5 Cert. Basis - TSO C8b ______ 60.9 Alternate Static Source Piper Dwg. 35493 ______ 61.0 Turn and Slip Indicator Piper PS50030-2 or -3 Cert.
Page 143 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II (k) Instruments (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Engine Hour Meter Piper Dwg. 69889-0 ______ 61.2 Clock ______ 62.4...
Page 144: Autopilots (Optional Equipment)
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE Autopilots (Optional Equipment) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) AutoFlite II Piper Dwg. 99447 Cert. Basis - STC SA3066SW-D ______ 91.8...
Page 145: (M) Radio Equipment (Optional Equipment)
SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II (m) Radio Equipment (Optional Equipment) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Bendix AS-2015A-7 or -9 Audio Panel ______ 66.4 Bendix CN2013-1 Com/Nav Cert.
Page 146 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (m) Radio Equipment (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Collins VHF-250 or VHF-251 Comm Transceiver a. Single ______ 56.9...
Page 147 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II Radio Equipment (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Collins AMR-350 Audio/Marker Panel Cert. Basis - TSO C35d, C50b ______ *3.3...
Page 148 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (m) Radio Equipment (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) King KX 175 ( ) VHF a. Transceiver ______ 56.6...
Page 149 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II (m) Radio Equipment (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) King KI 206 VOR/LOC Indicator Cert. Basis - TSO C40a, C36c ________ 60.9...
Page 150 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (m) Radio Equipment (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) King KR 86 ADF with KA 42B Loop and Sense Antenna a.
Page 151 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II (m) Radio Equipment (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Narco Comm 111 VHF Transceiver a. Single ______ 57.4 b.
Page 152 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (m) Radio Equipment (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Narco Nav 121 VHF Receiver a. Single ______ 58.4 b.
Page 153 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II (m) Radio Equipment (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Narco CP135 Audio Selector Panel Cert. Basis - TSO C50b ______ 55.0...
Page 154 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (m) Radio Equipment (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Antenna and Cable a. Nav Receiving VRP-37 or AV12-PPR ______ 171.3...
Page 155 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II (m) Radio Equipment (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Boom Microphone, Headset Piper Dwg. 37921-2 ______ 80.5 Cabin Speaker Piper Dwg.
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Page 157 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976 6-52...
Page 158: (N) Miscellaneous (Optional Equipment)
PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (n) Miscellaneous (Optional Equipment) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Zinc Chromate Finish Piper Dwg. 79700 ______ 158.0 Stainless Steel Control Cables Piper Dwg.
Page 159 SECTION 6 PIPER AIRCRAFT CORPORATION WEIGHT AND BALANCE PA-28-161, CHEROKEE WARRIOR II (n) Miscellaneous (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Inertia Safety Belts (Rear) (2) 0.8 lbs. each, Piper PS50039-4-14 Pacific Scientific 1107319-01 American Safety Eqpt.
Page 160 PIPER AIRCRAFT CORPORATION SECTION 6 PA-28-161, CHEROKEE WARRIOR II WEIGHT AND BALANCE (n) Miscellaneous (Optional Equipment) (cont) Item Mark if Weight Arm (In.) Moment Item Instl. (Pounds) Aft Datum (Lb-In.) Locking Gas Cap Piper Dwg. 39830-2 ______ *0.1 94.1 *Weight and moment difference between standard and optional equipment.
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Page 162 7.25 Cabin Features............................7-21 7.27 Baggage Area ............................7-22 7.29 Stall Warning............................7-22 7.31 Finish..............................7-22 7.33 Piper External Power..........................7-23 7.35 Emergency Locator Transmitter......................7-23 7.37 Air Conditioning ..........................7-25 7.39 Carburetor Ice Dectection System ....................... 7-26 REPORT: VB-880...
Page 163 OF THE AIRPLANE AND ITS SYSTEMS 7.1 THE AIRPLANE The Cherokee Warrior II is a single-engine, fixed gear monoplane of all metal construction with low semi-tapered wings. It has four place seating and a two hundred pound baggage capacity. 7.3 AIRFRAME The primary structure, with the exception of the steel tube engine mount, steel landing gear struts and isolated areas, is of aluminum alloy construction.
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Page 165 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-161, CHEROKEE WARRIOR II DESCRIPTION AND OPERATION 7.5 ENGINE AND PROPELLER The PA-28- 161 is powered by a four cylinder, direct drive, horizontally opposed engine rated at 160 H P at 2700 RPM. It is equipped with a starter, a 60 amp 14 volt alternator, a shielded ignition, two magnetos, vacuum pump drive, a fuel pump, a wetted polyurethane foam induction air filter.
Page 166 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-28-161, CHEROKEE WARRIOR II MAIN WHEEL ASSEMBLY Figure 7-1 REPORT: VB-880 ISSUED: DECEMBER 16 1976...
Page 167 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-161, CHEROKEE WARRIOR II DESCRIPTION AND OPERATION 7.7 LANDING GEAR The fixed gear PA-28-161 is equipped with a Cleveland 5.00 x 5 wheel on the nose gear and a Cleveland 6.00 x 6 wheel on each main gear (Figure 7-1). Cleveland single disc hydraulic brake assemblies are provided on the main gear.
Page 168 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 169 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-161, CHEROKEE WARRIOR II DESCRIPTION AND OPERATION FLIGHT CONTROL CONSOLE Figure 7-3 7.9 FLIGHT CONTROLS Dual flight controls are provided as standard equipment. The flight controls actuate the control surfaces through a cable system. The horizontal surface (stabilator) is of the flying tail design with a trim tab mounted on the trailing edge.
Page 170 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-28-161, CHEROKEE WARRIOR II Manually controlled flaps are provided on the PA-28-161. The flaps are balanced and spring loaded to return to the retracted (up) position. A control handle, which is located between the two front seats on the control console (Figure 7-3), extends the flaps by the use of a control cable.
Page 171 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-161, CHEROKEE WARRIOR II DESCRIPTION AND OPERATION CONTROL QUADRANT AND CONSOLE Figure 7-5 ISSUED: DECEMBER 16, 1976 REPORT: VB-880...
Page 172 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-28-161, CHEROKEE WARRIOR II FUEL SELECTOR Figure 7-7 7.13 FUEL SYSTEM Fuel is stored in two twenty-five gallon (24 gallons usable) fuel tanks, giving the airplane a total capacity of fifty U.S. gallons (48 gallons usable). Each tank is equipped with a filler neck indicator tab to aid in deter- mining fuel remaining when the tanks are not full.
Page 173 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-161, CHEROKEE WARRIOR II DESCRIPTION AND OPERATION FUEL SYSTEM SCHEMATIC Figure 7-9 ISSUED: DECEMBER 16, 1976 REPORT: VB-880 7-11...
Page 174 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-28-161, CHEROKEE WARRIOR II Fuel quantity and fuel pressure gauges are mounted in a gauge cluster located on the left side of the instrument panel to the right of the control wheel (refer to Figure 7-15).
Page 175 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-161, CHEROKEE WARRIOR II DESCRIPTION AND OPERATION Unlike previous generator systems, the ammeter as installed does not show battery discharge; rather, it indicates the electrical load on the alternator in amperes. With all the electrical equipment off and the master switch on, the ammeter will indicate the charging rate of the battery.
Page 176 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-28-161, CHEROKEE WARRIOR II ALTERNATOR AND STARTER SCHEMATIC Figure 7-11 REPORT: VB-880 ISSUED: DECEMBER 16, 1976 7-14 REVISED: DECEMBER 18, 1980...
Page 177 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-161, CHEROKEE WARRIOR II DESCRIPTION AND OPERATION CIRCUIT BREAKER PANEL Figure 7-13 7.17 VACUUM SYSTEM* The vacuum system is designed to operate the air driven gyro instruments. This includes the directional and attitude gyros when installed. The system consists of an engine driven vacuum pump, a vacuum regulator, a filter and the necessary plumbing.
Page 178 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-28-161, CHEROKEE WARRIOR II 7.19 INSTRUMENT PANEL The instrument panel (Figure 7-15) is designed to accommodate instruments and avionics equipment for VFR and IFR flights. The radios and the circuit breakers are located on the upper and lower right panel respectively, and have circuits provided for the addition of optional radio equipment.
Page 180 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-28-161, CHEROKEE WARRIOR II 7.21 PITOT-STATIC SYSTEM The system supplies both pitot and static pressure for the airspeed indicator, altimeter, and the optional vertical speed indicator (Figure 7-17) Pitot and static pressure are picked up by a pitot head installed on the bottom of the left wing and carried through pitot and static lines within the wing and fuselage to the gauges on the instrument panel.
Page 181 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-161, CHEROKEE WARRIOR II DESCRIPTION AND OPERATION PITOT-STATIC SYSTEM Figure 7-17 ISSUED: DECEMBER 16, 1976 REPORT: VB-880 7-19...
Page 182 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-28-161, CHEROKEE WARRIOR II HEATING AND VENTILATING SYSTEM Figure 7-19 REPORT: VB-880 ISSUED: DECEMBER 16, 1976 7-20 REVISED: JULY 3, 1979...
Page 183 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-161, CHEROKEE WARRIOR II DESCRIPTION AND OPERATION 7.23 HEATING AND VENTILATING SYSTEM Heat for the cabin interior and the defroster system is provided by a shroud attached to the muffler (Figure 7-19). The amount of heat can be regulated with the controls located on the far right side of the instrument panel.
Page 184 7.31 FINISH All exterior surfaces are primed with etching primer and finished with acrylic lacquer. To keep the finish attractive, economy size spray cans of touch-up paint are available from Piper Dealers. An optional polyurethane finish is available. REPORT: VB-880...
Page 185 DESCRIPTION AND OPERATION 7.33 PIPER EXTERNAL POWER* An optional starting installation known as Piper External Power (PEP) is accessible through a receptacle located on the right side of the fuselage aft of the baggage door. An external battery can be connected to the socket, thus allowing the operator to crank the engine without having to gain access to the airplane’s battery.
Page 186 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-28-161, CHEROKEE WARRIOR II The ELT should be checked to make certain the unit has not been activated during the ground check. Check by selecting 121.50 MHz on an operating receiver. If there is an oscillating chirping sound, the ELT may have been activated and should be turned off immediately.
Page 187 PIPER AIRCRAFT CORPORATION SECTION 7 PA-28-161, CHEROKEE WARRIOR II DESCRIPTION AND OPERATION 7.37 AIR CONDITIONING* The air conditioning system is a recirculating air system. The major items include: evaporator, condenser, compressor, blower, switches and temperature controls. The evaporator is located behind the left rear side of the baggage compartment. This cools the air that is used for air conditioning.
Page 188 SECTION 7 PIPER AIRCRAFT CORPORATION DESCRIPTION AND OPERATION PA-28-161, CHEROKEE WARRIOR II 7.39 CARBURETOR ICE DETECTION SYSTEM* A carburetor ice detection system is available as optional equipment. The system consists of a control box mounted on instrument panel, a probe sensor mounted in the carburetor and a red warning light to indicate the presence of ice in the carburetor.
Page 189 TABLE OF CONTENTS SECTION 8 AIRPLANE HANDLING, SERVICING AND MAINTENANCE Paragraph Page General ..............................Airplane Inspection Periods ......................... Preventive Maintenance ........................Airplane Alterations ..........................Ground Handling..........................8.11 Engine Air Filter ..........................8.13 Brake Service ............................8.15 Landing Gear Service........................... 8-10 8.17 Propeller Service ..........................
Page 190 AIRPLANE HANDLING, SERVICING AND MAINTENANCE GENERAL This section provides general guidelines relating to the handling, servicing and maintenance of the Cherokee Warrior II. For complete maintenance instructions, refer to the PA-28 Service Manual. WARNING Inspection, maintenance and parts requirements for all non-PIPER approved STC installations are not included in this handbook.
Page 191 Service Letters deal with product improvements and servicing techniques pertaining to the airplane. They are sent to Piper Service Centers and, if necessary, to the latest FAA-registered owners in the U.S. Owners should give careful attention to Service Letter information.
Page 192 Piper Authorized Service Center or a reputable repair shop. Piper cannot accept responsibility for the continued airworthiness of any aircraft not maintained to these standards, and/or not brought into compliance with applicable Service Bulletins issued by Piper, instructions issued by the engine, propeller, or accessory manufacturers, or Airworthiness Directives issued by the FAA.
Page 193 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERVICING AND MAINTENANCE PA-28-161, CHEROKEE WARRIOR II 8.5 PREVENTIVE MAINTENANCE The holder of a pilot certificate issued under Federal Aviation Regulations (FAR) Part 61 may perform certain preventive maintenance as defined in the FARs. This maintenance may be performed only on an aircraft which the pilot owns and operates, and which is not used in air carrier or air taxi/commercial operations service.
Page 194 PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-161, CHEROKEE WARRIOR II HANDLING, SERVICING AND MAINTENANCE 8.7 AIRPLANE ALTERATIONS If the owner desires to have his aircraft modified, he must obtain FAA approval for the alteration. Major alterations accomplished in accordance with Advisory Circular 43.13-2, when performed by an A & P mechanic, may be approved by the local FAA office.
Page 195 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERVICING AND MAINTENANCE PA-28-161, CHEROKEE WARRIOR II 8.9 GROUND HANDLING (a) Towing The airplane may be moved on the ground by the use of the nose wheel steering bar that is stowed below the forward ledge of the baggage compartment or by power equipment that will not damage or excessively strain the nose gear steering assembly.
Page 196 PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-161, CHEROKEE WARRIOR II HANDLING, SERVICING AND MAINTENANCE (c) Parking When parking the airplane, be sure that it is sufficiently protected from adverse weather conditions and that it presents no danger to other aircraft. When parking the airplane for any length of time or overnight, it is suggested that it be moored securely.
Page 197 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERVICING AND MAINTENANCE PA-28-161, CHEROKEE WARRIOR II 8.11 ENGINE AIR FILTER The wet-type polyurethane foam air filter must be inspected at least once every fifty hours. Under extremely adverse operating conditions, it may be necessary to inspect the filter more frequently. The filter is disposable and inexpensive and a spare should be kept on hand for a rapid replacement.
Page 198 PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-161, CHEROKEE WARRIOR II HANDLING, SERVICING AND MAINTENANCE BRAKE SYSTEM Figure 8-1 ISSUED: DECEMBER 16, 1976 REPORT: VB-880...
Page 199 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERVICING AND MAINTENANCE PA-28-161, CHEROKEE WARRIOR II 8.15 LANDING GEAR SERVICE The main landing gears use 6.00 x 6 wheels and the nose gear carries a 5.00 x 5 wheel. All three tires are four-ply rating, type III tires with tubes. (Refer to paragraph 8.23).
Page 200 PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-161, CHEROKEE WARRIOR II HANDLING, SERVICING AND MAINTENANCE 8.17 PROPELLER SERVICE The spinner and backing plate should be cleaned and inspected for cracks. Before each flight the propeller should be inspected for nicks, scratches, and corrosion. If found, they should be repaired as soon as possible by a rated mechanic, since a nick or scratch causes an area of increased stress which can lead to serious cracks or the loss of a propeller tip.
Page 201 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERVICING AND MAINTENANCE PA-28-161, CHEROKEE WARRIOR II A summary of the current grades as well as the previous fuel designations is shown in the following chart: FUEL GRADE COMPARISON CHART Current Military Previous Commercial...
Page 202 PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-161, CHEROKEE WARRIOR II HANDLING, SERVICING AND MAINTENANCE FUEL DRAIN Figure 8-3 Filling Fuel Tanks Observe all required precautions for handling gasoline. Fuel is stored in two twenty-five gallon (24 usable) tanks. (d) Draining Fuel Strainer, Sumps and Lines The fuel system sumps and strainer should be drained daily prior to the first flight and after refueling to avoid the accumulation of contaminants such as water or sediment.
Page 203 SECTION 8 PIPER AIRCRAFT CORPORATION HANDLING, SERVICING AND MAINTENANCE PA-28-161, CHEROKEE WARRIOR II (e) Draining Fuel System The bulk of the fuel may be drained from the system by opening valve at the inboard end of each fuel tank. Push up on the arms of the drain valve and turn counterclockwise to hold the drain open.
Page 204 PIPER AIRCRAFT CORPORATION SECTION 8 PA-28-161, CHEROKEE WARRIOR II HANDLING, SERVICING AND MAINTENANCE CAUTION Do not operate the engine until excess solvent has evaporated or otherwise been removed. (4) Remove the protective tape from the magnetos. (5) Lubricate the controls, bearing surfaces, etc., in accordance with the Lubrication Chart.
Page 205 50°F. It is recommended that an optional Engine Breather Tube Winterization Kit be installed for cold weather operation. This kit is available through your Piper Dealer/Distributor. REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 206 AutoFlite II Autopilot Installation ....................... AutoControl IIIB Autopilot Installation ....................Piper Electric Pitch Trim........................Air Conditioning Installation ....................... 9-11 Century 21 Autopilot ........................... 9-15 Piper Control Wheel Clock Installation ....................9-19 Avidyne IFD540 GPS/NAV/COM..................L3 LYNX NGT-9000 ADS-B transponder................REPORT: VB-880...
Page 207 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-161, CHEROKEE WARRIOR II SUPPLEMENTS SECTION 9 SUPPLEMENTS 9.1 GENERAL This section provides information in the form of Supplements which are necessary for efficient operation of the airplane when equipped with one or more of the various optional systems and equipment not provided with the standard airplane.
Page 208 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 209 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-161, CHEROKEE WARRIOR II SUPPLEMENTS SUPPLEMENT 1 AUTOFLITE II AUTOPILOT INSTALLATION SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional AutoFlite II Autopilot is installed. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 210 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-161, CHEROKEE WARRIOR II AUTOFLITE II IN-FLIGHT PROCEDURE (a) Engagement (1) Check turn command knob in center detent position. (2) AutoFlite II master switch - ON. (b) Disengagement (1) AutoFlite II master switch - OFF.
Page 211 This supplement has been FAA Approved as a permanent part of this handbook based on EDO-AIRE Mitchell STC SA3065SW-D and must remain in this handbook at all times when the optional Piper AutoControl IIIB Autopilot is installed.
Page 212 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-161, CHEROKEE WARRIOR II (3) With card disabled: VOR and Glide Slope displays are still functional; use card set to rotate card to aircraft heading for correct picture. Localizer - left-right information still usable. Flag information is disabled - compare needle with No.
Page 213 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-161, CHEROKEE WARRIOR II SUPPLEMENTS (c) Roll Section: (1) To engage, center roll knob, push A/P “ON-OFF” switch to “ON” position. To turn, rotate console roll knob in desired direction. (Maximum angle of bank should not exceed 30°.) (2) For heading mode, set directional gyro with magnetic compass.
Page 214 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-161, CHEROKEE WARRIOR II SECTION 5 - PERFORMANCE No changes to the basic performance provided by Section 5 of the Pilot’s Operating Handbook are necessary for this supplement. REPORT: VB-880 ISSUED: DECEMBER 16, 1976...
Page 215 PIPER ELECTRIC PITCH TRIM SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Piper Electric Pitch Trim is installed. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 216 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: DECEMBER 16, 1976 9-10...
Page 217 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-161, CHEROKEE WARRIOR II SUPPLEMENTS SUPPLEMENT 4 AIR CONDITIONING INSTALLATION SECTION 1 - GENERAL This supplement supplies information necessary for the efficient operation of the airplane when the optional air conditioning system is installed. The information contained within this supplement is to be used “as described”...
Page 218 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-161, CHEROKEE WARRIOR II SECTION 4 - NORMAL PROCEDURES Prior to takeoff, the air conditioner should be checked for proper operation as follows: (a) Check aircraft master switch “ON.” (b) Turn the air conditioner control switch to “ON” and the fan switch to one of the operating positions - the “AIR COND DOOR OPEN”...
Page 219 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-161, CHEROKEE WARRIOR II SUPPLEMENTS The climb performance is not compromised measurably with the air conditioner operating since the compressor is declutched and the condenser door is retracted, both automatically, when a full throttle position is selected. When the full throttle position is not used or in the event of a malfunction which would cause the compressor to operate and the condenser door to be extended, a decrease in rate of climb of as much as 100 fpm can be expected.
Page 220 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: JULY 11, 1977 9-14...
Page 221 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-161, CHEROKEE WARRIOR II SUPPLEMENTS SUPPLEMENT 5 CENTURY 21 AUTOPILOT INSTALLATION SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the opitonal Century 21 Auotpilot is installed in accordance with STC SA3352SW. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 222 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-161, CHEROKEE WARRIOR II To disable heading card - pull circuit breaker and use magnetic compass for directional data. NOTE If heading card is not operational, autopilot should not be used. With card disabled VOR/Localizer and Glide Slope displays are still functional: use card set to rotate card to aircraft heading for correct picture.
Page 223 PIPER AIRCRAFT CORPORATION SECTION 9 PA-28-161, CHEROKEE WARRIOR II SUPPLEMENTS (4) With HDG bug centered select NAV or APPR mode and note control wheel movement toward VOR needle offset. (5) Select REV mode and note control wheel movement opposite VOR needle offset.
Page 224 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-161, CHEROKEE WARRIOR II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 ISSUED: AUGUST 14, 1980 9-18 REVISED: DECEMBER 18, 1980...
Page 225 PIPER CONTROL WHEEL CLOCK INSTALLATION SECTION 1 - GENERAL This supplement supplies information necessary for the operation of the airplane when the optional Piper control wheel clock is installed. The information contained within this supplement is to be used in conjunction with the complete handbook.
Page 226 SECTION 9 PIPER AIRCRAFT CORPORATION SUPPLEMENTS PA-28-161, CHEROKEE WARRIOR II (c) TIME SETTING The RST button must now be pressed two times to cause the hours digits to flash. The correct hour can be set in as described above. Pressing the RST button once again will now cause the minutes digits to flash. The minutes should be set to the next minute to come up at the zero seconds time mark.
Page 227 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 FAA Approved Airplane Flight Manual Supplement Piper Warrior PA28-161 _________________________________ Make and Model Airplane with Avidyne Integrated Flight Displays p/n 700-00182-XXX and 700- 00179-XXX N3067D Registration No. _________ 28-7916159 Serial No.
Page 228 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 LOG OF REVISIONS Revision Revised Pages Description of Revisions FAA Approval Date Number Initial Release Robert Mann Jul 24 2014 Pages 1,2, 3, 4, 5, Add IFD440 and Software 6, 7, 8, 9, 11, 15, Release 10.1.0.0 16, 17, 18, 21...
Page 229 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Section 1 – General This airplane is equipped with an Avidyne p/n 700-00182-XXX IFD5XX Integrated Flight Display (IFD) and /or Avidyne p/n 700- 00179-XXX IFD4XX Integrated Flight Display. Both part numbers may be referred to in this document as simply IFD.
Page 230 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 official sources, in a format compatible with the intended function of the unit. Avidyne requests that any observed database discrepancies are reported. These discrepancies may be in the form of an incorrect procedure, incorrectly identified terrain, obstacles, navigation fixes, or any other displayed item used for navigation or communication in the air or on the ground.
Page 231 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 is installed, this installation will not be able to receive TIS-B client status, and will not receive ADS-R or TIS-B broadcasts from ATC unless the aircraft is in the same area as a valid TIS-B client broadcasting that it has ADS-B In capability.
Page 232 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Figure 2. Avidyne IFD440 700-00179-XXX Integrated Flight Display (IFD). Volume / Power / CDI Nav Source Knob Squelch Knob Ambient Frequency Swap Light Sensor Line Select Dedicated Keys (LSKs) Function Keys...
Page 233 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Figure 3. Avidyne IFD550 700-00182-XXX Integrated Flight Display Ego-centric SVS. FAA APPROVED Page 7 of 26 P/N 600-00298-000 Date: Rev 08...
Page 234 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Section 2 – Limitations 1. The appropriate IFD4XX and IFD5XX Integrated Flight Display Pilot Guides must be available to the pilot during all flight operations: P/N 600-00300-001 for the IFD5XX Series P/N 600-00304-000 for the IFD4XX Series P/N 89000039-010 Bendix King AeroNav 900 and 910 P/N 89000041-008 Bendix King AeroNav 800...
Page 235 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 LNAV/VNAV minima; LPV minima; and LP minima. Note: The U.S. titles RNP instrument approach procedures “RNAV (GPS) Rwy XX”. Other States may use similar titling or may title these procedures “RNAV (GNSS) Rwy XX”.
Page 236 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 7. In areas where SBAS coverage is not available, the pilot must check RAIM availability. 8. The Avidyne moving map display provides visual depiction of the aircraft’s own-ship, GPS position on a moving map for situational awareness (SA) purposes only.
Page 237 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 13. The IFD545 and IFD550 may not be used for primary attitude information or standby attitude information (If required by type design). The IFD545 and/or IFD550 may only be used as a secondary (non-required) source for attitude information.
Page 238 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 CAUTION In IFD545 and IFD550 units the inertial reference accelerometers may be irreparably damaged by exposure to temperatures below -40°C. The units are capable of operating at -40°C, but exposure to temperatures below this, even when powered off, can stress the parts internally causing a detectable and annunciated failure of the sensors.
Page 239 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Section 3 – Emergency Procedures Loss of GPS In the event of the loss of the IFD440 or IFD540 GPS receiver, the FMS will enter dead reckoning mode for 5 minutes, after that all FMS functions are lost and the ownship is removed from map depictions.
Page 240 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 To Disable WiFi/Bluetooth Connectivity on IFD4XX/IFD5XX: 1. Press and hold the IFD4xx/IFD5XX power button/knob for 1 second (upper left bezel) -------------------------------------- 2. ALLOW/IGNORE WiFi Bluetooth dropdown is presented. Press IGNORE--------------------------- Dropdown is removed 3.
Page 241 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Caution Messages The Caution and Warning panel is not altered as part of this modification and remains the primary means of providing Caution and Warning messages. Caution and Warning messages are provided in the following table: EXCEEDANCES | WARNINGS Short Text...
Page 242 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 EXCEEDANCES | CAUTIONS YELLOW Short Text Text Comments Long Caution Terrain* Caution Terrain The FLTA algorithm is predicting a likely ground collision within approximately 60 seconds – initiate a proper recovery maneuver.
Page 243 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Short Text Text Comments Long GPS Fault No No position available The navigation solution cannot Position compute a position, typically after dead reckoning has expired. Execute a missed approach if this occurs while performing a GPS based approach.
Page 244 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Short Text Text Comments Long Check Altitude Too Aircraft is below the glide Correct aircraft altitude as slope altitude at FAF required to safely conduct the approach or initiate a climb to a published safe altitude and abort the approach.
Page 245 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Short Text Text Comments Long Traffic <Bearing in Traffic <bearing in clock Traffic advisories with no clock direction> direction> <distance in relative altitude information – <distance in NM>* NM>...
Page 246 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Short Text Text Comments Long No Comm with VHF No communication with Transition to a backup VHF the VHF radio com radio (if available) or initiate lost communication procedures.
Page 247 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Short Text Text Comments Long No ADS-B Position AXP322 Lost GPS ADS-B position data had Position Data previously been valid and then transitions to invalid. Check the ADS-B position source device.
Page 248 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Short Text Text Comments Long TIS traffic communications TIS Removed TIS Traffic Removed have ceased for >12 seconds No TIS ground station is TIS Unavailable TIS Traffic Unavailable available or communications have ceased for >60 seconds TAWS PDA algorithm has...
Page 249 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Section 4 – Normal Procedures To Activate the IFD4XX/IFD5XX : 1. Verify IFD circuit breakers (2) ------------------------------ IN 2. Verify Battery Master Switch --------------------------------ON 3. Avionics or Radio Master (if equipped) ------------------ ON To Deactivate the IFD4XX/IFD5XX : 4.
Page 250 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Section 5 – Performance No change from basic Handbook. FAA APPROVED Page 24 of 26 P/N 600-00298-000 Date: Rev 08...
Page 251 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Section 6 – Weight and Balance No change from basic Handbook. See AFM/POH for current weight and balance for this aircraft. FAA APPROVED Page 25 of 26 P/N 600-00298-000 Date: Rev 08...
Page 252 Avidyne Corporation 4 Middlesex Green - Suite 221 561 Virginia Road Concord MA 01742 Section 7 – Systems Description See Avidyne IFD4XX and IFD5XX FMS/GPS/Nav/Com Pilot Guides P/N 600-00300-001 for the IFD5XX Series P/N 600-00304-000 for the IFD4XX Series P/N 89000039-010 Bendix King AeroNav 900 and 910 P/N 89000041-008 Bendix King AeroNav 800 FAA APPROVED Page 26 of 26...
Page 253 Piper PA-28-161 28-7916159 N3067D...
Page 254 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT SUPPLEMENTAL FLIGHT MANUAL For The L3 Aviation Products Lynx Multilink Surveillance System Models NGT-9000 L3 Part Number 9029000-20000 RECORD OF REVISIONS Revision Date of Revision Description Original 3/31/2015...
Page 255 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 This page intentionally left blank Revision 4 Issue: 9/19/17 Page 3 of 27 Document Number L3-76AK-AFMS1 FAA Approved...
Page 256 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 TABLE OF CONTENTS SECTION 1. GENERAL ......................6 Functional Description ....................6 NGT-9000 ADS-B Traffic Advisory System (ATAS) [Optional] ........7 NGT-9000 Terrain Awareness and Warning System (TAWS) [Optional] ...... 7 NGT-9000+ Traffic Awareness Overview [Optional] ............
Page 257 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 TABLE OF FIGURES Figure 1-1: Lynx NGT-9000 ......................6 Figure 1-2: Typical NGT-9000 Traffic Screen ................10 Figure 1-3: NGT-9000 Connections and Functions ..............12 Figure 1-4: Installation Configuration Data ................13 TABLE OF TABLES Table 1-1: Typical Target Symbology ..................
Page 258: General
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 SECTION 1. GENERAL Functional Description The Lynx MultiLink Surveillance System (also referred to in this manual as the Lynx NGT-9000) is a Mode S Level 2 dens Class 1 Transponder with an integrated GPS receiver providing Automatic Dependent Surveillance-Broadcast (ADS-B) output using a 1090ES (Extended Squitter).
Page 259: Ngt-9000 Ads-B Traffic Advisory System (Atas) [Optional]
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 NGT-9000 ADS-B Traffic Advisory System (ATAS) [Optional] The ADS-B Traffic Advisory System (ATAS) is a passive system that monitors ADS-B, ADS-R and TIS-B ADS-B IN data and alerts the flight crew via on-screen alerts aural traffic calls and an optional Traffic Alert lamp to nearby aircraft and assists the pilot in the visual acquisition of aircraft that may represent a danger.
Page 260: Ngt-9000+ Traffic Awareness Overview [Optional]
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 There are four TAWS configurations available with the NGT-9000: • Disabled • TAWS B – Default Aural Phrases • TAWS B – Alternate Aural Phrases • Display Only – No Alerts When a TAWS configuration is enabled with audio, an Audio Acknowledge button will cancel the current aural announcement.
Page 261: L-Band Uat Antenna
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 L-Band UAT Antenna The L-Band antenna is used by the Lynx NGT-9000 to transmit and receive 1090 MHz ADS-B and receive 978MHz ADS-B (UAT). At least one L-band antenna must be located on the bottom of the aircraft.
Page 262: Traffic Displays
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 1.13 Traffic Displays The NGT-9000 will provide, at a minimum, UAT, TIS-B and ADS-R traffic on the unit’s built-in display and can repeat this traffic information on any approved ARINC-429 or RS-422 display. The NGT-9000+ can also display active Traffic Awareness System (TAS/TCAS) targets on the unit’s built-in display and can repeat this traffic information on any approved ARINC-429 or RS- 422 display.
Page 263: Table 1-1: Typical Target Symbology
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 Table 1-1: Typical Target Symbology * To promote cockpit commonality, installation configuration options are available to set the airborne PA & OT traffic color to either cyan or white. Revision 4 Issue: 9/19/17 Page 11 of 27 Document Number L3-76AK-AFMS1...
Page 264: Interaction Of Major Components
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 1.14 Interaction of Major Components Figure 1-3 shows how the major components of the NGT-9000 connect to other aircraft systems. Figure 1-3: NGT-9000 Connections and Functions Revision 4 Issue: 9/19/17 Page 12 of 27 Document Number L3-76AK-AFMS1 FAA Approved...
Page 265: Installation Configuration For This Aircraft
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 1.15 Installation Configuration for This Aircraft Figure 1-4 should be completed by a licensed installer. Model NGT-9000: P/N 9029000-20000 Model NGT-9000+: P/N 9029000-20000 Model NGT-9000D: P/N 9029000-20000 Model NGT-9000D+: P/N 9029000-20000 Aircraft Specific Tail Number: Mode S Identifier (Octal):...
Page 266: Limitations
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 SECTION 2. LIMITATIONS Minimum Documentation The L3 Pilot’s Guide for the NGT-9000 Part Number 0040-17000-01 (Rev K, or later revision) must be carried on board the aircraft at all times. Minimum Equipment The NGT-9000 must have the following system interfaces in Table 2-1 fully functional in order to be compliant with the requirements for 14 CFR 91.225 and 91.227 ADS-B OUT operations:...
Page 267: Terrain Awareness
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 Terrain Awareness a. Navigation must not be predicated on the use of TAWS; b. To avoid giving unwanted alerts, the TAWS must be inhibited when landing at an airport that is not included in the airport database;...
Page 268: Emergency Procedures
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 SECTION 3. EMERGENCY PROCEDURES Emergency Procedures 3.1.1 Terrain Warning Alert (Display Alert, Audio Alert, or Terrain Warning (Red) Lamp TAWS Display PULL UP, Audio Alert of “Terrain, Terrain; Pull Up, Pull UP” or “Obstacle, Obstacle;...
Page 269: Abnormal Procedures
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 3.1.4 Loss of GPS/SBAS Position Data Loss of GPS/SBAS indicated by a GPS failure message on the NGT-9000/CP-2500 and a PULL NGT CIRCUIT BREAKER. SLOW blinking ADS-B FAIL light (if installed) ..WAIT 5 SECONDS AND RESET.
Page 270 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 Table 3-1: Troubleshooting for the Panel Mount NGT-9000 Symptom Screen Cause/Corrective Actions Message page contains The following internal tests do not create a fail message messages that do not in the system status page.
Page 271 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 Table 3-1: Troubleshooting for the Panel Mount NGT-9000 Symptom Screen Cause/Corrective Actions • Display indicator ADS Traffic A traffic mode indicator that is shown when TAS/TCAS is ONLY (Models with failed (or not available) and ADS-B is operating.
Page 272 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 Table 3-1: Troubleshooting for the Panel Mount NGT-9000 Symptom Screen Cause/Corrective Actions Display indicator TRAFFIC Traffic ADS-B is operational but heading and track are invalid or UNAVAILABLE (Amber text) GPS is failed.
Page 273 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 Table 3-1: Troubleshooting for the Panel Mount NGT-9000 Symptom Screen Cause/Corrective Actions The traffic symbols on the Traffic Non-directional traffic symbols on the traffic display is traffic display are non- due to one of the following reasons: directional (diamond shape).
Page 274 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 Table 3-1: Troubleshooting for the Panel Mount NGT-9000 Symptom Screen Cause/Corrective Actions No TIS-B Coverage Traffic The No Coverage Indicator is shown on the traffic Indicator display for the following reasons: 1.
Page 275 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 Table 3-1: Troubleshooting for the Panel Mount NGT-9000 Symptom Screen Cause/Corrective Actions No FIS-B Coverage Weather The No Coverage Indicator is shown on the weather Indicator display for the following reasons: 1.
Page 276 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 Table 3-1: Troubleshooting for the Panel Mount NGT-9000 Symptom Screen Cause/Corrective Actions • ADS-B Out Fail lamp Weather GPS is Acquiring (In Air – no previous position fix). flashes (1 second 1.
Page 277 Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 Table 3-1: Troubleshooting for the Panel Mount NGT-9000 Symptom Screen Cause/Corrective Actions • Display indicator TAWS Displayed when an alert fault causing loss of terrain TERRAIN DISPLAY display. Alerting is still operational. FAILED (Amber text) 1.
Page 278: Normal Procedures
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 SECTION 4. NORMAL PROCEDURES The procedures described below are specific only to the NGT-9000. Reference the Pilot's Operating Handbooks and AFM Supplements for operating instructions specific to any installed displays or peripheral devices.
Page 279: Lightning Detection Sources [Optional]
Airplane Flight Manual Supplement or Supplemental Flight Manual for the NGT-9000 Lightning Detection Sources [Optional] The WX-500 Stormscope is required for installation configured for lightning detection. The WX- 500 detects electrical discharges from thunderstorms within a 200 nmi radius of the aircraft. This information plots the location of the thunderstorms and is shown on the right application screen of the NGT-9000.
Page 280 TABLE OF CONTENTS SECTION 10 SAFETY TIPS Paragraph Page 10.1 General ..............................10-1 10.3 Safety Tips ............................10-1 REPORT: VB-880 10-i...
Page 281 SAFETY TIPS 10.1 GENERAL This section provides safety tips of particular value in the operation of the Cherokee Warrior II. 10.3 SAFETY TIPS (a) Learn to trim for takeoff so that only a very light back pressure on the control wheel is required to lift the airplane off the ground.
Page 282 SECTION 10 PIPER AIRCRAFT CORPORATION SAFETY TIPS PA-28-161, CHEROKEE WARRIOR II Hand starting of the engine is not recommended, however, should hand starting of the engine be required, only experienced personnel should attempt this procedure. The magneto selector should be placed to “LEFT” during the starting procedures to reduce the probability of “kick back.” Place the ignition switch to “BOTH”...

Piper CHEROKEE WARRIOR II Pilot Operating Handbook

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